FN Thomson Reuters Web of Science™ VR 1.0 PT S AU Helbert, J Wendler, D Walter, I Widemann, T Marcq, E Guignan, G Ferrari, S Maturilli, A Mueller, N Kappel, D Jaenchen, J D'Amore, M Boerner, A Dyar, D Arnold, GE Smrekar, S AF Helbert, Joern Wendler, Dennis Walter, Ingo Widemann, Thomas Marcq, Emmanuel Guignan, Gabriel Ferrari, Sabrina Maturilli, Alessandro Mueller, Nils Kappel, David Jaenchen, Judit D'Amore, Mario Boerner, Anko Dyar, Darby Arnold, Gabriele E. Smrekar, Suzanne BE Strojnik, M TI The Venus Emissivity Mapper Concept SO INFRARED REMOTE SENSING AND INSTRUMENTATION XXIV SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Infrared Remote Sensing and Instrumentation XXIV CY AUG 29-30, 2016 CL San Diego, CA SP SPIE DE Venus; near infrared; spectroscopy AB Based on experience gained from using the VIRTIS instrument on Venus Express to observe the surface of Venus and the new high temperature laboratory experiments, we have developed the multi spectral Venus Emissivity Mapper (VEM) to study the surface of Venus. VEM imposes minimal requirements on the spacecraft and mission design and can therefore be added to any future Venus mission. Ideally, the VEM instrument will be combined with a high-resolution radar mapper to provide accurate topographic information, as it will be the case for the NASA Discovery VERITAS mission or the ESA EnVision M5 proposal. C1 [Helbert, Joern; Wendler, Dennis; Walter, Ingo; Maturilli, Alessandro; Kappel, David; Jaenchen, Judit; D'Amore, Mario; Boerner, Anko; Arnold, Gabriele E.] Deutsch Zentrum Luft & Raumfahrt eV, Cologne, Germany. [Widemann, Thomas] Lab Etud Spatiales & Instrumentat & Astrophys, Paris, France. [Marcq, Emmanuel; Guignan, Gabriel] LATMOS, Guyancourt, France. [Ferrari, Sabrina] Univ Pavia, I-27100 Pavia, Italy. [Mueller, Nils; Smrekar, Suzanne] CALTECH, Pasadena, CA 91125 USA. [Mueller, Nils; Smrekar, Suzanne] Jet Prop Lab, Pasadena, CA USA. [Dyar, Darby] Mt Holyoke Coll, S Hadley, MA USA. RP Helbert, J (reprint author), Deutsch Zentrum Luft & Raumfahrt eV, Cologne, Germany. EM joern.helbert@dlr.de NR 14 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0337-0; 978-1-5106-0338-7 J9 PROC SPIE PY 2016 VL 9973 AR UNSP 99730R DI 10.1117/12.2237568 PG 13 WC Instruments & Instrumentation; Remote Sensing SC Instruments & Instrumentation; Remote Sensing GA BG6GD UT WOS:000390265000022 ER PT S AU Leppik, K AF Leppik, K. BE Strojnik, M TI SOFIA Flight Planning and Execution SO INFRARED REMOTE SENSING AND INSTRUMENTATION XXIV SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Infrared Remote Sensing and Instrumentation XXIV CY AUG 29-30, 2016 CL San Diego, CA SP SPIE AB The Stratospheric Observatory For Infrared Astronomy (SOFIA) is a 2.5-m telescope mounted inside of a Boeing 747SP. Planning and executing astronomical observations from an aircraft moving at 500 miles per hour has its own unique challenges and advantages. Scheduling and optimizing an entire year of science observations is a balancing act with target availability, instrument availability, and operational constraints. A SOFIA flight is well choreographed, and successfully executing observations on SOFIA requires many systems and people to work together- from the telescope assembly compensating for the continual vibration and movement of the plane in order to accurately point the telescope, the expertise of the telescope operators to prepare the telescope for use by the instrument operators, aircraft operations ensuring that the aircraft is ready for flight, and the mission systems control computers keeping track of all the data. In this paper we will discuss what it takes to plan a SOFIA flight, and what we do once we're in the air. We will share a typical science flight, as well as more challenging and unique observations that require SOFIA being in the right place at the right time. C1 [Leppik, K.] NASA, SOFIA Operat Ctr, Univ Space Res Assoc, Armstrong Bldg 703,2825 E Ave P MS-S241, Palmdale, CA 93550 USA. RP Leppik, K (reprint author), NASA, SOFIA Operat Ctr, Univ Space Res Assoc, Armstrong Bldg 703,2825 E Ave P MS-S241, Palmdale, CA 93550 USA. NR 1 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0337-0; 978-1-5106-0338-7 J9 PROC SPIE PY 2016 VL 9973 AR UNSP 99730N DI 10.1117/12.2237933 PG 12 WC Instruments & Instrumentation; Remote Sensing SC Instruments & Instrumentation; Remote Sensing GA BG6GD UT WOS:000390265000019 ER PT S AU Reinacher, A Lammen, Y Graf, F Jakob, H AF Reinacher, Andreas Lammen, Yannick Graf, Friederike Jakob, Holger BE Strojnik, M TI SOFIA Pointing and Chopping: Performance and Prospect SO INFRARED REMOTE SENSING AND INSTRUMENTATION XXIV SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Infrared Remote Sensing and Instrumentation XXIV CY AUG 29-30, 2016 CL San Diego, CA SP SPIE DE SOFIA; chopper; secondary mirror; control; performance AB The Stratospheric Observatory for Infrared Astronomy (SOFIA) is a 2.5m infrared telescope built into a Boeing 747 SP. In 2014 SOFIA reached its Full Operational Capability milestone and nowadays takes off about three times a week to observe the infrared sky from altitudes above most of the atmosphere's water vapor content. Despite reaching this major milestone the work to improve the observatory's performance is continuing in many areas. This paper focuses on the telescope's current pointing and chopping performance and gives an overview over the ongoing and foreseen work to further improve in those two areas. Pointing performance as measured with the fast focal plane camera in flight is presented and based on that data it is elaborated how and in which frequency bands a further reduction of image jitter might be achieved. One contributor to the remaining jitter as well as the major actuator to reduce jitter with frequencies greater than 5 Hz is SOFIA's Secondary Mirror Assembly (SMA) or Chopper. As-is SMA jitter and chopping performance data as measured in flight is presented as well as recent improvements to the position sensor cabling and calibration and their effect on the SMA's pointing accuracy. Furthermore a brief description of a laboratory mockup of the SMA is given and the intended use of this mockup to test major hardware changes for further performance improvement is explained. C1 [Reinacher, Andreas; Lammen, Yannick; Graf, Friederike; Jakob, Holger] Univ Stuttgart, Deutsch SOFIA Inst, Pfaffenwaldring 29, D-70569 Stuttgart, Germany. [Reinacher, Andreas; Lammen, Yannick; Jakob, Holger] NASA, Armstrong Flight Res Ctr, SOFIA Airborne Syst Operat Ctr, Mail Stop AFRC Bldg 703,S241,POB 273, Edwards AFB, CA 93523 USA. [Graf, Friederike] NASA, Ames Res Ctr, SOFIA Sci Ctr, Mail Stop N-211-1, Moffett Field, CA 94035 USA. RP Reinacher, A (reprint author), Univ Stuttgart, Deutsch SOFIA Inst, Pfaffenwaldring 29, D-70569 Stuttgart, Germany.; Reinacher, A (reprint author), NASA, Armstrong Flight Res Ctr, SOFIA Airborne Syst Operat Ctr, Mail Stop AFRC Bldg 703,S241,POB 273, Edwards AFB, CA 93523 USA. EM reinacher@dsi.uni-stuttgart.de NR 12 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0337-0; 978-1-5106-0338-7 J9 PROC SPIE PY 2016 VL 9973 AR UNSP 99730L DI 10.1117/12.2237789 PG 12 WC Instruments & Instrumentation; Remote Sensing SC Instruments & Instrumentation; Remote Sensing GA BG6GD UT WOS:000390265000017 ER PT S AU Taylor, CR Gross, MAK AF Taylor, Charles R. Gross, Michael A. K. BE Strojnik, M TI SOFIA tracking image simulation SO INFRARED REMOTE SENSING AND INSTRUMENTATION XXIV SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Infrared Remote Sensing and Instrumentation XXIV CY AUG 29-30, 2016 CL San Diego, CA SP SPIE DE SOFIA; astronomy; telescope; tracking; camera; image simulation AB The Stratospheric Observatory for Infrared Astronomy (SOFIA) tracking camera simulator is a component of the Telescope Assembly Simulator (TASim). TASim is a software simulation of the telescope optics, mounting, and control software. Currently in its fifth major version, TASim is relied upon for telescope operator training, mission planning and rehearsal, and mission control and science instrument software development and testing. TASim has recently been extended for hardware-in-the-loop operation in support of telescope and camera hardware development and control and tracking software improvements. All three SOFIA optical tracking cameras are simulated, including the Focal Plane Imager (FPI), which has recently been upgraded to the status of a science instrument that can be used on its own or in parallel with one of the seven infrared science instruments. The simulation includes tracking camera image simulation of starfields based on the UCAC4 catalog at real-time rates of 4-20 frames per second. For its role in training and planning, it is important for the tracker image simulation to provide images with a realistic appearance and response to changes in operating parameters. For its role in tracker software improvements, it is vital to have realistic signal and noise levels and precise star positions. The design of the software simulation for precise subpixel starfield rendering (including radial distortion), realistic point-spread function as a function of focus, tilt, and collimation, and streaking due to telescope motion will be described. The calibration of the simulation for light sensitivity, dark and bias signal, and noise will also be presented. C1 [Taylor, Charles R.; Gross, Michael A. K.] NASA, Univ Space Res Assoc, Ames Res Ctr, Bldg N232,M-S 232-12, Moffett Field, CA 94035 USA. RP Taylor, CR (reprint author), NASA, Univ Space Res Assoc, Ames Res Ctr, Bldg N232,M-S 232-12, Moffett Field, CA 94035 USA. EM ctaylor@sofia.usra.edu NR 11 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0337-0; 978-1-5106-0338-7 J9 PROC SPIE PY 2016 VL 9973 AR UNSP 99730K DI 10.1117/12.2236431 PG 14 WC Instruments & Instrumentation; Remote Sensing SC Instruments & Instrumentation; Remote Sensing GA BG6GD UT WOS:000390265000016 ER PT S AU te Plate, M Birkmann, S Sirianni, M Rumler, P Jensen, P Ehrenwinkler, R Mosner, P Karl, H Rapp, R Wright, R Wu, R AF te Plate, Maurice Birkmann, Stephan Sirianni, Marco Rumler, Peter Jensen, Peter Ehrenwinkler, Ralf Mosner, Peter Karl, Hermann Rapp, Robert Wright, Ray Wu, Rai BE Strojnik, M TI JWST's Near Infrared Spectrograph Status and Performance Overview SO INFRARED REMOTE SENSING AND INSTRUMENTATION XXIV SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Infrared Remote Sensing and Instrumentation XXIV CY AUG 29-30, 2016 CL San Diego, CA SP SPIE DE James Webb Space Telescope; NIRSpec; Multi-object spectrograph; Infrared; Micro Shutter Assrmbly; MEMS AB The James Webb Space Telescope (JWST) Observatory is the follow-on mission to the Hubble Space Telescope (HST). JWST will be the biggest space telescope ever built and it will lead to astounding scientific breakthroughs. The mission will be launched in October 2018 from Kourou, French Guyana by an ESA provided Ariane 5 rocket. NIRSpec, one of the four instruments on board of the mission, recently underwent a major upgrade. New infrared detectors were installed and the Micro Shutter Assembly (MSA) was replaced as well. The rework was necessary because both systems were found to be degrading beyond a level that could be accepted. Now in its final flight configuration, NIRSpec underwent a final cryogenic performance test at NASA's Goddard Space Flight Center (GSFC) as part of the Integrated Science Instrument Module (ISIM). This paper will present a status overview and results of the recent test campaigns. C1 [te Plate, Maurice; Birkmann, Stephan; Sirianni, Marco] European Space Agcy, STScI, 3700 San Martin Dr, Baltimore, MD 21218 USA. [Rumler, Peter; Jensen, Peter] European Space Agcy, Keplerlaan 1,POB 299, NL-2200 AG Noordwijk, Netherlands. [Ehrenwinkler, Ralf; Mosner, Peter; Karl, Hermann] AIRBUS Def & Space, D-81663 Munich, Germany. [Rapp, Robert; Wright, Ray; Wu, Rai] NASA, Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. RP te Plate, M (reprint author), European Space Agcy, STScI, 3700 San Martin Dr, Baltimore, MD 21218 USA. NR 7 TC 0 Z9 0 U1 1 U2 1 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0337-0; 978-1-5106-0338-7 J9 PROC SPIE PY 2016 VL 9973 AR UNSP 99730E DI 10.1117/12.2238125 PG 13 WC Instruments & Instrumentation; Remote Sensing SC Instruments & Instrumentation; Remote Sensing GA BG6GD UT WOS:000390265000011 ER PT S AU Ting, DZ Soibel, A Khoshakhlagh, A Keo, SA Hill, CJ Fisher, AM Luong, EM Liu, JK Mumolo, JM Rafol, SB Pepper, BJ Gunapala, SD AF Ting, David Z. Soibel, Alexander Khoshakhlagh, Arezou Keo, Sam A. Hill, Cory J. Fisher, Anita M. Luong, Edward M. Liu, John K. Mumolo, Jason M. Rafol, Sir B. Pepper, Brian J. Gunapala, Sarath D. BE Strojnik, M TI Carrier transport in nBn infrared detectors SO INFRARED REMOTE SENSING AND INSTRUMENTATION XXIV SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Infrared Remote Sensing and Instrumentation XXIV CY AUG 29-30, 2016 CL San Diego, CA SP SPIE DE infrared detector; nBn; unipolar barrier; type-II superlattice; conductivity effective mass ID PHOTODETECTORS; SUPERLATTICES; HGCDTE AB The nBn photodetector architecture proposed and demonstrated by Maimon and Wicks provides an effective means for lowering generation-recombination dark current by suppressing Shockley-Read-Hall processes, and for reducing surface leakage dark current. This has been especially beneficial for III-V semiconductor based infrared photodiodes, which traditionally tend to suffer from excess depletion dark current and lack of good surface passivation. We examine how contact (n), barrier (B), and absorber (n) properties can affect carrier transport in nBn infrared detector. In an nBn detector the unipolar electron barrier should block only the electrons while allowing the un-impeded flow of holes, but improper barrier doping or barrier-absorber band offset could also block hole transport and result in higher turn-on bias. Contact doping has also been observed to result in higher turn-on bias at higher temperatures. In the case when the absorber is made from n-doped type-II superlattice (T2SL), although it is often assumed that the exceedingly large growth-direction band-edge curvature hole effective mass in n-type long-wavelength infrared (LWIR) T2SL would lead to low hole mobility and therefore low detector collection quantum efficiency, in practice mid-wavelength infrared (MWIR) and LWIR nBn infrared detectors have demonstrated good optical response. We explore how hole mobility can be affected by band structure effects such as band mixing and subband splitting to gain better understanding of hole transport in T2SL. C1 [Ting, David Z.; Soibel, Alexander; Khoshakhlagh, Arezou; Keo, Sam A.; Hill, Cory J.; Fisher, Anita M.; Luong, Edward M.; Liu, John K.; Mumolo, Jason M.; Rafol, Sir B.; Pepper, Brian J.; Gunapala, Sarath D.] CALTECH, Jet Prop Lab, Ctr Infrared Photodetectors, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Ting, DZ (reprint author), CALTECH, Jet Prop Lab, Ctr Infrared Photodetectors, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 39 TC 1 Z9 1 U1 1 U2 1 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0337-0; 978-1-5106-0338-7 J9 PROC SPIE PY 2016 VL 9973 AR UNSP 997304 DI 10.1117/12.2238853 PG 11 WC Instruments & Instrumentation; Remote Sensing SC Instruments & Instrumentation; Remote Sensing GA BG6GD UT WOS:000390265000003 ER PT S AU Wolf, J Colditz, S Lachenmann, M Pfuller, E Schindler, K Wiedemann, M Zinnecker, H Krabbe, A AF Wolf, Juergen Colditz, Sebastian Lachenmann, Michael Pfueller, Enrico Schindler, Karsten Wiedemann, Manuel Zinnecker, Hans Krabbe, Alfred BE Strojnik, M TI Deutsches SOFIA Institut (DSI) at the SOFIA Science Center: Engineering and scientific contributions to the airborne observatory SO INFRARED REMOTE SENSING AND INSTRUMENTATION XXIV SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Infrared Remote Sensing and Instrumentation XXIV CY AUG 29-30, 2016 CL San Diego, CA SP SPIE DE Stratospheric Observatory for Infrared Astronomy; SOFIA; astronomy; CCD; infrared detectors; instrumentation; telescope pointing ID IMAGES AB The Stratospheric Observatory for Infrared Astronomy (SOFIA) is a 2.5 meter infrared telescope built into a Boeing 747SP. In 2014 SOFIA reached its "Full Operational Capability" milestone and nowadays takes off about three times a week to observe the infrared sky from altitudes above most of the atmosphere's water vapor content. Despite reaching this major milestone, efforts to improve the observatory's performance are continuing in many areas. The team of the Deutsches SOFIA Institut, DSI (German SOFIA Institute) at the SOFIA Science Center in Moffett Field, CA works in several engineering areas to improve the observatory's performance and its efficiency. DSI supports the allocation process of SOFIA's observation time for guest observers, provides and supports two facility science instruments and conducts an observing program of stellar occultations by small objects of the solar system. This paper summarizes results and ongoing work on a spare secondary mirror made of aluminum, the new and improved Focal Plane Imager (FPI+) that has become a facility science instrument, the Field-Imaging Far-Infrared Line Spectrometer (FIFI-LS), new cameras and optics for the Fine Field and Wide Field Imagers (FFI+ and WFI+), real-time astrometric solution of star field images, ground support equipment and astronomical observations. C1 [Wolf, Juergen; Colditz, Sebastian; Lachenmann, Michael; Pfueller, Enrico; Schindler, Karsten; Wiedemann, Manuel; Zinnecker, Hans; Krabbe, Alfred] Univ Stuttgart, Deutsch SOFIA Inst, Pfaffenwaldring 29, D-70569 Stuttgart, Germany. [Wolf, Juergen; Colditz, Sebastian; Lachenmann, Michael; Pfueller, Enrico; Schindler, Karsten; Wiedemann, Manuel; Zinnecker, Hans] NASA, Ames Res Ctr, SOFIA Sci Ctr, Mail Stop 211-1, Moffett Field, CA 94035 USA. RP Wolf, J (reprint author), Univ Stuttgart, Deutsch SOFIA Inst, Pfaffenwaldring 29, D-70569 Stuttgart, Germany.; Wolf, J (reprint author), NASA, Ames Res Ctr, SOFIA Sci Ctr, Mail Stop 211-1, Moffett Field, CA 94035 USA. EM wolf@dsi.uni-stuttgart.de NR 18 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0337-0; 978-1-5106-0338-7 J9 PROC SPIE PY 2016 VL 9973 AR UNSP 99730J DI 10.1117/12.2237207 PG 14 WC Instruments & Instrumentation; Remote Sensing SC Instruments & Instrumentation; Remote Sensing GA BG6GD UT WOS:000390265000015 ER PT S AU Bottone, M Primiero, G Raimondi, F Rungta, N AF Bottone, Michele Primiero, Giuseppe Raimondi, Franco Rungta, Neha BE Novais, P Konomi, S TI From Raw Data to Agent Perceptions for Simulation, Verification, and Monitoring SO INTELLIGENT ENVIRONMENTS 2016 SE Ambient Intelligence and Smart Environments LA English DT Proceedings Paper CT 12th International Conference on Intelligent Environments (IE) CY SEP 12-16, 2016 CL London, ENGLAND SP IEEE Comp Soc, Middlesex Univ London, Kingston Univ, Queen Mary Univ London, IEEE Syst Man & Cybernet Soc, AAAI, BCS, IOS Press DE Intelligent environments; multiagent systems; modelling; MQTT; publish-subscribe ID INTERNET; THINGS AB In this paper we present a practical solution to the problem of connecting "real world" data exchanged between sensors and actuators with the higher level of abstraction used in frameworks for multiagent systems. In particular, we show how to connect an industry-standard publish-subscribe communication protocol for embedded systems called MQTT with two Belief-Desire-Intention agent modelling and programming languages: Jason/AgentSpeak and Brahms. In the paper we describe the details of our Java implementation and we release all the code open source. C1 [Bottone, Michele; Primiero, Giuseppe; Raimondi, Franco] Middlesex Univ, Dept Comp Sci, London, England. [Rungta, Neha] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Raimondi, F (reprint author), Middlesex Univ, Dept Comp Sci, London, England. EM f.raimondi@mdx.ac.uk NR 25 TC 0 Z9 0 U1 0 U2 0 PU IOS PRESS PI AMSTERDAM PA NIEUWE HEMWEG 6B, 1013 BG AMSTERDAM, NETHERLANDS SN 1875-4163 BN 978-1-61499-690-3; 978-1-61499-689-7 J9 AMB INTELL SMART ENV PY 2016 VL 21 BP 66 EP 75 DI 10.3233/978-1-61499-690-3-66 PG 10 WC Computer Science, Cybernetics; Computer Science, Interdisciplinary Applications SC Computer Science GA BG6IS UT WOS:000390309400010 ER PT J AU Crucian, B Babiak-Vazquez, A Johnston, S Pierson, DL Ott, CM Sams, C AF Crucian, Brian Babiak-Vazquez, Adriana Johnston, Smith Pierson, Duane L. Ott, C. Mark Sams, Clarence TI Incidence of clinical symptoms during long-duration orbital spaceflight SO INTERNATIONAL JOURNAL OF GENERAL MEDICINE LA English DT Article DE spaceflight; immunity; clinical incidence; astronauts; gravity; clinical risk; disease ID IMMUNE-SYSTEM DYSREGULATION; EPSTEIN-BARR-VIRUS; SPACE-FLIGHT; CYTOKINE PRODUCTION; ASTRONAUTS; REACTIVATION; RESPONSES; LYMPHOCYTES; EXPRESSION; MISSIONS AB Background: The environment of spaceflight may elevate an astronaut's clinical risk for specific diseases. The purpose of this study was to derive, as accurately as currently possible, an assessment of in-flight clinical "incidence" data, based on observed clinical symptoms in astronauts on board the International Space Station (ISS). Methods: Electronic medical records were examined from 46 long-duration ISS crew members, each serving approximately a 6-month mission on board the ISS, constituting 20.57 total flight years. Incidence for immunological-related adverse health events or relevant clinical symptoms was tabulated in a non-identifiable fashion. Event categories included infectious diseases, allergies, and rashes/hypersensitivities. A subsequent re-evaluation of more notable events, either of prolonged duration or unresponsive to treatment, was performed. Results: For the disease/symptom categories used in this evaluation, the ISS incidence rate was 3.40 events per flight year. Skin rashes were the most reported event (1.12/flight year) followed by upper respiratory symptoms (0.97/flight year) and various other (non-respiratory) infectious processes. During flight, 46% of crew members reported an event deemed "notable". Among the notable events, 40% were classified as rashes/hypersensitivities. Characterization of on-orbit rashes manifested as redness with irritation, and could present on a variety of body locations. Conclusion: Based on reported symptoms, astronauts experience adverse medical events of varying severity during long-duration spaceflights. The data suggests caution, from both a vehicle design and biomedical countermeasures perspective, as space agencies plan for prolonged deep space exploration missions. C1 [Crucian, Brian; Johnston, Smith; Pierson, Duane L.; Ott, C. Mark; Sams, Clarence] NASA, Johnson Space Ctr, Biomed Res & Environm Sci Div, Houston, TX USA. [Babiak-Vazquez, Adriana] KBR Wyle, Epidemiol Lifetime Surveillance Astronaut Hlth, Houston, TX USA. RP Crucian, B (reprint author), NASA, Johnson Space Ctr, 2101 NASA Pkwy, Houston, TX USA. EM brian.crucian-1@nasa.gov NR 42 TC 0 Z9 0 U1 2 U2 2 PU DOVE MEDICAL PRESS LTD PI ALBANY PA PO BOX 300-008, ALBANY, AUCKLAND 0752, NEW ZEALAND SN 1178-7074 J9 INT J GEN MED JI Int. J. Gen. Med. PY 2016 VL 9 BP 383 EP 391 DI 10.2147/IJGM.S114188 PG 9 WC Medicine, General & Internal SC General & Internal Medicine GA EF4AC UT WOS:000390265700001 PM 27843335 ER PT S AU Broy, M Havelund, K Kumar, R Steffen, B AF Broy, Manfred Havelund, Klaus Kumar, Rahul Steffen, Bernhard BE Margaria, T Steffen, B TI Towards a Unified View of Modeling and Programming (Track Summary) SO LEVERAGING APPLICATIONS OF FORMAL METHODS, VERIFICATION AND VALIDATION: DISCUSSION, DISSEMINATION, APPLICATIONS, ISOLA 2016, PT II SE Lecture Notes in Computer Science LA English DT Proceedings Paper CT 7th International Symposium on Leveraging Applications of Formal Methods, Verification and Validation (ISoLA) CY OCT 10-14, 2016 CL Corfu, GREECE C1 [Broy, Manfred] Tech Univ Munich, Munich, Germany. [Havelund, Klaus] CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. [Kumar, Rahul] Microsoft Res, Redmond, WA USA. [Steffen, Bernhard] TU Dortmund Univ, Dortmund, Germany. RP Havelund, K (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. EM klaus.havelund@jpl.nasa.gov NR 16 TC 0 Z9 0 U1 0 U2 0 PU SPRINGER INT PUBLISHING AG PI CHAM PA GEWERBESTRASSE 11, CHAM, CH-6330, SWITZERLAND SN 0302-9743 BN 978-3-319-47169-3; 978-3-319-47168-6 J9 LECT NOTES COMPUT SC PY 2016 VL 9953 BP 3 EP 10 DI 10.1007/978-3-319-47169-3_1 PG 8 WC Computer Science, Software Engineering; Computer Science, Theory & Methods SC Computer Science GA BG6CH UT WOS:000389942800001 ER PT S AU Rouquette, NF AF Rouquette, Nicolas F. BE Margaria, T Steffen, B TI Simplifying OMG MOF-Based Metamodeling SO LEVERAGING APPLICATIONS OF FORMAL METHODS, VERIFICATION AND VALIDATION: DISCUSSION, DISSEMINATION, APPLICATIONS, ISOLA 2016, PT II SE Lecture Notes in Computer Science LA English DT Proceedings Paper CT 7th International Symposium on Leveraging Applications of Formal Methods, Verification and Validation (ISoLA) CY OCT 10-14, 2016 CL Corfu, GREECE AB This paper advocates for a unification of modeling & programming from the perspective of normalized, implementation-neutral database schemas: representing programs and models in terms of irreducible and independent tables. This idea departs from the mainstream of modeling & programming, which typically revolves around Application Program Interface (API) ecosystems for operational needs and external serialization for interchange needs. Instead, this idea emphasizes an information-centric architecture to separate the structural aspects of language syntax via normalized schema tables from the operational aspects of language syntax and semantics via programs operating on normalized tables or derived table views. Such tables constitute the basis of a functional information architecture unifying modeling and programming as a radical departure from standardizing APIs in a programming fashion or standardizing serialization interchange in a modeling fashion. This paper focuses on the current API-less serialization-centric modeling paradigm because it is the farthest from a unified functional information architecture compared to functional programming languages where thinking about programs as pure functions and models as pure data is closest to this kind of unification. This paper first deconstructs the multi-level, reflective architecture for modeling languages defined at the Object Management Group (OMG) based on the Meta-Object Facility (MOF) and the Unified Modeling Language (UML) and subsequently reconstructs several normalized schema accounting for the information content and organization of different kinds of resources involved in modeling: libraries of datatypes, metamodels like UML, profiles like the Systems Modeling Language (SysML) that extend metamodels and models that conform to metamodels optionally extended with applied profiles. C1 [Rouquette, Nicolas F.] CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. RP Rouquette, NF (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. EM nicolas.f.rouqette@jp.nasa.gov NR 15 TC 0 Z9 0 U1 0 U2 0 PU SPRINGER INT PUBLISHING AG PI CHAM PA GEWERBESTRASSE 11, CHAM, CH-6330, SWITZERLAND SN 0302-9743 BN 978-3-319-47169-3; 978-3-319-47168-6 J9 LECT NOTES COMPUT SC PY 2016 VL 9953 BP 97 EP 118 DI 10.1007/978-3-319-47169-3_8 PG 22 WC Computer Science, Software Engineering; Computer Science, Theory & Methods SC Computer Science GA BG6CH UT WOS:000389942800008 ER PT S AU Broy, M Havelund, K Kumar, R AF Broy, Manfred Havelund, Klaus Kumar, Rahul BE Margaria, T Steffen, B TI Towards a Unified View of Modeling and Programming SO LEVERAGING APPLICATIONS OF FORMAL METHODS, VERIFICATION AND VALIDATION: DISCUSSION, DISSEMINATION, APPLICATIONS, ISOLA 2016, PT II SE Lecture Notes in Computer Science LA English DT Proceedings Paper CT 7th International Symposium on Leveraging Applications of Formal Methods, Verification and Validation (ISoLA) CY OCT 10-14, 2016 CL Corfu, GREECE AB In this paper we argue that there is a value in providing a unified view of modeling and programming. Models are meant to describe a system at a high level of abstraction for the purpose of human understanding and analysis. Programs, on the other hand, are meant for execution. However, programming languages are becoming increasingly higher-level, with convenient notation for concepts that in the past would only be reserved formal specification languages. This leads to the observation, that programming languages could be used for modeling, if only appropriate modifications were made to these languages. At the same time, model-based engineering formalisms such as UML and SysML are highly popular in engineering communities due to their graphical nature. However, these communities are, due to the complex nature of these formalisms, struggling to find grounds in textual formalisms with proper semantics. A unified view of modeling and programming may provide a common ground. The paper illustrates these points with selected examples comparing models and programs. C1 [Broy, Manfred] Tech Univ Munich, Munich, Germany. [Havelund, Klaus] CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. [Kumar, Rahul] Microsoft Res, Redmond, WA USA. RP Havelund, K (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. EM klaus.havelund@jpl.nasa.gov NR 27 TC 0 Z9 0 U1 0 U2 0 PU SPRINGER INT PUBLISHING AG PI CHAM PA GEWERBESTRASSE 11, CHAM, CH-6330, SWITZERLAND SN 0302-9743 BN 978-3-319-47169-3; 978-3-319-47168-6 J9 LECT NOTES COMPUT SC PY 2016 VL 9953 BP 238 EP 257 DI 10.1007/978-3-319-47169-3_17 PG 20 WC Computer Science, Software Engineering; Computer Science, Theory & Methods SC Computer Science GA BG6CH UT WOS:000389942800017 ER PT S AU Reger, G Havelund, K AF Reger, Giles Havelund, klaus BE Margaria, T Steffen, B TI What Is a Trace? A Runtime Verification Perspective SO LEVERAGING APPLICATIONS OF FORMAL METHODS, VERIFICATION AND VALIDATION: DISCUSSION, DISSEMINATION, APPLICATIONS, ISOLA 2016, PT II SE Lecture Notes in Computer Science LA English DT Proceedings Paper CT 7th International Symposium on Leveraging Applications of Formal Methods, Verification and Validation (ISoLA) CY OCT 10-14, 2016 CL Corfu, GREECE ID METRIC TEMPORAL LOGIC; EMBEDDED SYSTEMS; AUTOMATA; PROGRAMS AB Runtime Monitoring or Verification deals with traces. In its most simple form a monitoring system takes a trace produced by a system and a specification of correct behaviour and checks if the trace conforms to the specification. More complex applications may introduce notions of feedback and reaction. The notion that unifies the field is that we can abstract the runtime behaviour of a system by an execution trace and check this for conformance. However, there is little uniform understanding of what a trace is. This is most keenly seen when comparing theoretical and practical work. This paper surveys the different notions of trace and reflects on the related issues. C1 [Reger, Giles] Univ Manchester, Manchester, Lancs, England. [Havelund, klaus] CALTECH, Jet Prop Lab, Pasadena, CA USA. RP Reger, G (reprint author), Univ Manchester, Manchester, Lancs, England. EM giles.reger@manchester.ac.uk NR 67 TC 0 Z9 0 U1 0 U2 0 PU SPRINGER INT PUBLISHING AG PI CHAM PA GEWERBESTRASSE 11, CHAM, CH-6330, SWITZERLAND SN 0302-9743 BN 978-3-319-47169-3; 978-3-319-47168-6 J9 LECT NOTES COMPUT SC PY 2016 VL 9953 BP 339 EP 355 DI 10.1007/978-3-319-47169-3_25 PG 17 WC Computer Science, Software Engineering; Computer Science, Theory & Methods SC Computer Science GA BG6CH UT WOS:000389942800025 ER PT S AU Kauffman, S Joshi, R Havelund, K AF Kauffman, Sean Joshi, Rajeev Havelund, Klaus BE Margaria, T Steffen, B TI Towards a Logic for Inferring Properties of Event Streams SO LEVERAGING APPLICATIONS OF FORMAL METHODS, VERIFICATION AND VALIDATION: DISCUSSION, DISSEMINATION, APPLICATIONS, ISOLA 2016, PT II SE Lecture Notes in Computer Science LA English DT Proceedings Paper CT 7th International Symposium on Leveraging Applications of Formal Methods, Verification and Validation (ISoLA) CY OCT 10-14, 2016 CL Corfu, GREECE AB We outline the background, motivation, and requirements of an approach to create abstractions of event streams, which are time-tagged sequences of events generated by an executing software system. Our work is motivated by the need to process event streams with millions of events that are generated by a spacecraft, that must be processed quickly after they are received on the ground. Our approach involves building a tool that adds hierarchical labels to a received event stream. The labels add contextual information to the event stream, and thus make it easier to build tools for visualizing and analyzing telemetry. We describe a notation for writing hierarchical labeling rules; the notation is based on a modification of Allen Temporal Logic, augmented with rule-definitions and features for referring to data in data parameterized events. We illustrate our notation and its use with an example. C1 [Kauffman, Sean] Univ Waterloo, Waterloo, ON, Canada. [Joshi, Rajeev; Havelund, Klaus] CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. RP Havelund, K (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. EM klaus.havelund@jpl.nasa.gov NR 6 TC 0 Z9 0 U1 0 U2 0 PU SPRINGER INT PUBLISHING AG PI CHAM PA GEWERBESTRASSE 11, CHAM, CH-6330, SWITZERLAND SN 0302-9743 BN 978-3-319-47169-3; 978-3-319-47168-6 J9 LECT NOTES COMPUT SC PY 2016 VL 9953 BP 394 EP 399 DI 10.1007/978-3-319-47169-3_31 PG 6 WC Computer Science, Software Engineering; Computer Science, Theory & Methods SC Computer Science GA BG6CH UT WOS:000389942800031 ER PT S AU Gurov, D Havelund, K Huisman, M Monahan, R AF Gurov, Dilian Havelund, Klaus Huisman, Marieke Monahan, Rosemary BE Margaria, T Steffen, B TI Static and Runtime Verification, Competitors or Friends? (Track Summary) SO LEVERAGING APPLICATIONS OF FORMAL METHODS, VERIFICATION AND VALIDATION: FOUNDATIONAL TECHNIQUES, PT I SE Lecture Notes in Computer Science LA English DT Proceedings Paper CT 7th International Symposium on Leveraging Applications of Formal Methods, Verification and Validation (ISoLA) CY OCT 10-14, 2016 CL Corfu, GREECE C1 [Gurov, Dilian] KTH Royal Inst Technol, Stockholm, Sweden. [Havelund, Klaus] Jet Prop Lab, Pasadena, CA 91109 USA. [Huisman, Marieke] Univ Twente, Enschede, Netherlands. [Monahan, Rosemary] Maynooth Univ, Maynooth, Kildare, Ireland. RP Havelund, K (reprint author), Jet Prop Lab, Pasadena, CA 91109 USA. EM dilian@kth.se; klaus.havelund@jpl.nasa.gov; m.huisman@utwente.nl; Rosemary.Monahan@nuim.ie NR 9 TC 0 Z9 0 U1 0 U2 0 PU SPRINGER INT PUBLISHING AG PI CHAM PA GEWERBESTRASSE 11, CHAM, CH-6330, SWITZERLAND SN 0302-9743 BN 978-3-319-47166-2; 978-3-319-47165-5 J9 LECT NOTES COMPUT SC PY 2016 VL 9952 BP 397 EP 401 DI 10.1007/978-3-319-47166-2_27 PG 5 WC Computer Science, Software Engineering SC Computer Science GA BG6CE UT WOS:000389939100027 ER PT S AU Goodloe, A AF Goodloe, Alwyn BE Margaria, T Steffen, B TI Challenges in High-Assurance Runtime Verification SO LEVERAGING APPLICATIONS OF FORMAL METHODS, VERIFICATION AND VALIDATION: FOUNDATIONAL TECHNIQUES, PT I SE Lecture Notes in Computer Science LA English DT Proceedings Paper CT 7th International Symposium on Leveraging Applications of Formal Methods, Verification and Validation (ISoLA) CY OCT 10-14, 2016 CL Corfu, GREECE ID PROGRAMS; JAVA AB Safety-critical systems are growing more complex and becoming increasingly autonomous. Runtime Verification (RV) has the potential to provide protections when a system cannot be assured by conventional means, but only if the RV itself can be trusted. In this paper, we present a number of challenges to realizing high-assurance RV and illustrate how we have addressed them in our research. We argue that high-assurance RV provides a rich target for automated verification tools in hope of fostering closer collaboration among the communities. C1 [Goodloe, Alwyn] NASA, Langley Res Ctr, Hampton, VA 23665 USA. RP Goodloe, A (reprint author), NASA, Langley Res Ctr, Hampton, VA 23665 USA. EM a.goodloe@nasa.gov NR 30 TC 0 Z9 0 U1 0 U2 0 PU SPRINGER INT PUBLISHING AG PI CHAM PA GEWERBESTRASSE 11, CHAM, CH-6330, SWITZERLAND SN 0302-9743 BN 978-3-319-47166-2; 978-3-319-47165-5 J9 LECT NOTES COMPUT SC PY 2016 VL 9952 BP 446 EP 460 DI 10.1007/978-3-319-47166-2_31 PG 15 WC Computer Science, Software Engineering SC Computer Science GA BG6CE UT WOS:000389939100031 ER PT S AU Cansizoglu, H Gao, Y Kaya, A Ghandiparsi, S Polat, KG Wang, YC Zhang, RZ Reggad, H Mayet, A Devine, EP Islam, MS AF Cansizoglu, Hilal Gao, Yang Kaya, Ahmet Ghandiparsi, Soroush Polat, Kazim G. Wang, Yichuan Zhang, Runzhou Reggad, Hind Mayet, Ahmed Devine, Ekaterina Ponizovskaya Islam, M. Saif BE Kobayashi, NP Talin, AA Islam, MS Davydov, AV TI Efficient Si photovoltaic devices with integrated micro/nano holes SO LOW-DIMENSIONAL MATERIALS AND DEVICES 2016 SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Low-Dimensional Materials and Devices CY AUG 30-31, 2016 CL San Diego, CA SP SPIE DE nanoscale holes; crystalline Si; thin solar cell; light trapping structures ID SILICON SOLAR-CELLS; THIN-FILM; PIN DIODES; ABSORPTION; LIMIT; DARK AB Efficient light harvesting in a thin layer of crystalline Si can be realized by implementing nanoscale pillars and holes to the device structure. The major drawback of the pillars and holes based photovoltaic devices is high surface to volume ratio, contributing to an increase in surface recombination rate of the photo-generated carriers. The common techniques used in pillars/holes fabrication such as dry etching make the surface even worse by bombarding it with high energy ions. Therefore, such damaged surfaces of high aspect ratio structures need to be effectively passivated. In this study, we demonstrate a hole based thin crystalline Si photovoltaic device with enhanced open circuit voltage and short circuit current after a successful surface passivation process through a wet oxidation. In addition, the effect of passivation layer fabricated by rapid thermal oxide growth on photo response is investigated. A successful fabrication of thin crystalline Si solar cells can lead to the applications of ultra-thin, highly efficient, flexible and wearable energy sources. C1 [Cansizoglu, Hilal; Gao, Yang; Kaya, Ahmet; Ghandiparsi, Soroush; Polat, Kazim G.; Wang, Yichuan; Zhang, Runzhou; Reggad, Hind; Mayet, Ahmed; Islam, M. Saif] Univ Calif Davis, Dept Elect & Comp Engn, Davis, CA 95618 USA. [Devine, Ekaterina Ponizovskaya] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Cansizoglu, H (reprint author), Univ Calif Davis, Dept Elect & Comp Engn, Davis, CA 95618 USA. OI Ponizovskaya-Devine, Ekaterina/0000-0003-0768-5981 NR 20 TC 0 Z9 0 U1 1 U2 1 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0239-7; 978-1-5106-0240-3 J9 PROC SPIE PY 2016 VL 9924 AR 99240V DI 10.1117/12.2241794 PG 6 WC Engineering, Electrical & Electronic; Optics; Physics, Condensed Matter SC Engineering; Optics; Physics GA BG6DG UT WOS:000390027500012 ER PT S AU Fryauf, DM Phillips, AC Kobayashi, NP AF Fryauf, David M. Phillips, Andrew C. Kobayashi, Nobuhiko P. BE Kobayashi, NP Talin, AA Islam, MS Davydov, AV TI Corrosion protection of silver-based telescope mirrors using evaporated anti-oxidation overlayers and aluminum oxide films by atomic layer deposition SO LOW-DIMENSIONAL MATERIALS AND DEVICES 2016 SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Low-Dimensional Materials and Devices CY AUG 30-31, 2016 CL San Diego, CA SP SPIE DE silver; mirror; ALD; aluminum oxide; corrosion barrier; protected silver; reflective coatings AB An urgent demand remains in astronomy for high-reflectivity silver mirrors that can withstand years of exposure in observatory environments. The University of California Observatories Astronomical Coatings Lab has undertaken development of protected silver coatings suitable for telescope mirrors that maintain high reflectivity at wavelengths from 340 nm through the mid-infrared spectrum. We present results on superior protective layers of transparent dielectrics produced by evaporation and atomic layer deposition. Several novel coating recipes have been developed with ion-assisted electron beam deposition (IAEBD) of various fluorides, oxides, and nitrides in combination with conformal layers of aluminum oxide (AlOx) deposited by ALD using trimethylaluminum as a metal precursor and water vapor as a reactant. Extending on our previous results demonstrating the superior durability of ALD-based AlOx top barrier layers over conventionally-deposited AlOx, this work investigates the effects on mirror barrier durability comparing different anti-oxidation materials on Ag with an identical AlOx top barrier layer deposited by ALD. Samples of coating recipes with different anti-oxidation layers undergo aggressive environmental testing, including high temperature/high humidity (HTHH), in which samples are exposed to an environment of 80% humidity at 80 degrees C for ten days in a simple test set-up. While most samples show fairly successful endurance after HTHH testing, visible results suggest that MgAl2O4, Al2O3, and AlN anti-oxidation layers offer enhanced robust protection against chemical corrosion and moisture in an accelerated aging environment, which is attributed to superior adhesion and intermolecular bonding between the Al-based anti-oxidation layers and the AlOx top barrier layer. Mirror samples are further characterized by reflectivity/absorption before and after deposition of oxide coatings. We also show that the performance of the ALD-AlOx barrier layer depends in part on the temperature of that process. C1 [Fryauf, David M.; Kobayashi, Nobuhiko P.] Univ Calif Santa Cruz, Baskin Sch Engn, Santa Cruz, CA 95064 USA. [Fryauf, David M.; Kobayashi, Nobuhiko P.] Univ Calif Santa Cruz, NASA, Ames Res Ctr, Adv Studies Labs,Nanostruct Energy Convers Techno, Moffett Field, CA USA. [Phillips, Andrew C.] Univ Calif Santa Cruz, Univ Calif Observ, Santa Cruz, CA 95064 USA. RP Fryauf, DM (reprint author), Univ Calif Santa Cruz, Baskin Sch Engn, Santa Cruz, CA 95064 USA.; Fryauf, DM (reprint author), Univ Calif Santa Cruz, NASA, Ames Res Ctr, Adv Studies Labs,Nanostruct Energy Convers Techno, Moffett Field, CA USA. NR 13 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0239-7; 978-1-5106-0240-3 J9 PROC SPIE PY 2016 VL 9924 AR 99240S DI 10.1117/12.2238749 PG 8 WC Engineering, Electrical & Electronic; Optics; Physics, Condensed Matter SC Engineering; Optics; Physics GA BG6DG UT WOS:000390027500010 ER PT S AU Fryauf, DM Leon, JJD Phillips, AC Kobayashi, NP AF Fryauf, David M. Leon, Juan J. Diaz Phillips, Andrew C. Kobayashi, Nobuhiko P. BE Kobayashi, NP Talin, AA Islam, MS Davydov, AV TI Effects of ion bombardment on silver/dielectric interfaces with ion assisted e-beam evaporation SO LOW-DIMENSIONAL MATERIALS AND DEVICES 2016 SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Low-Dimensional Materials and Devices CY AUG 30-31, 2016 CL San Diego, CA SP SPIE DE silver; e-beam evaporation; ion bombardment; ripening; surface plasmon resonance AB Silver thin films were deposited by electron beam evaporation for application as telescope mirrors using a custom PVD chamber from the University of California Observatories Astronomical Coatings Lab. The silver (Ag) surface has been bombarded with different ion conditions prior to and during deposition of subsequent dielectric protective barrier layers by ion assisted electron beam evaporation. Ion source gases including nitrogen and argon are used, and dielectric barrier stacks utilizing silicon nitride and titanium dioxide are deposited onto Ag. We report the effects on mirror stack reflectivity spectra caused by ion bombardment parameters with different gases and different holding-time in vacuum prior to ion bombardment. We suggest that evolving Ag surface morphology and surface plasmon resonance coupling contribute to the changing optical properties of the mirror stack. C1 [Fryauf, David M.; Leon, Juan J. Diaz; Kobayashi, Nobuhiko P.] Univ Calif Santa Cruz, Baskin Sch Engn, Santa Cruz, CA 95064 USA. [Fryauf, David M.; Leon, Juan J. Diaz; Kobayashi, Nobuhiko P.] Univ Calif Santa Cruz, NASA, Ames Res Ctr, Nanostruct Energy Convers Technol & Res,Adv Studi, Moffett Field, CA 94035 USA. [Phillips, Andrew C.] Univ Calif Santa Cruz, Univ Calif Observ, Santa Cruz, CA 95064 USA. RP Fryauf, DM (reprint author), Univ Calif Santa Cruz, Baskin Sch Engn, Santa Cruz, CA 95064 USA.; Fryauf, DM (reprint author), Univ Calif Santa Cruz, NASA, Ames Res Ctr, Nanostruct Energy Convers Technol & Res,Adv Studi, Moffett Field, CA 94035 USA. NR 10 TC 0 Z9 0 U1 1 U2 1 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0239-7; 978-1-5106-0240-3 J9 PROC SPIE PY 2016 VL 9924 AR 99240M DI 10.1117/12.2238741 PG 7 WC Engineering, Electrical & Electronic; Optics; Physics, Condensed Matter SC Engineering; Optics; Physics GA BG6DG UT WOS:000390027500008 ER PT S AU Leon, JJD Norris, KJ Sevic, JF Kobayashi, NP AF Leon, Juan J. Diaz Norris, Kate J. Sevic, John F. Kobayashi, Nobuhiko P. BE Kobayashi, NP Talin, AA Islam, MS Davydov, AV TI Integration of a niobium oxide selector on a tantalum oxide memristor by local oxidation using Joule heating SO LOW-DIMENSIONAL MATERIALS AND DEVICES 2016 SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Low-Dimensional Materials and Devices CY AUG 30-31, 2016 CL San Diego, CA SP SPIE DE selector; memristor; self-assembly; electroforming AB Memristive devices are two-terminal electrical switches with electrical resistance that depends on a state variable equivalent to electrical charge. In practice, multiple memristive devices are arranged into a crossbar array to form such components as memory and logic. For reliable operation of the crossbar array, electrical current sneak paths need to be eliminated by combining a highly nonlinear component, known as selector, with a memristive device. This ensures the explicit selection of an intended memristive device without disturbing the states of surrounding devices. However, integrating a selector onto a memristive device at the circuit level is not an appealing option for large scale integration. In this paper, a monolithic structure that contains a memristive device and a self-aligned selector is presented. A niobium oxide (NbO2) selector is built directly on a tantalum oxide (TaOx) memristive device by fist depositing an Nb layer on a TaOx memristive device and then forming NbO2 at the Nb/TaOx interface. Discussion will focus on an experimental and theoretical assessment on the electrothermal behavior of the Nb/TaOx structure that results in NbO2/TaOx selector/memristive devices. C1 [Leon, Juan J. Diaz; Norris, Kate J.; Sevic, John F.; Kobayashi, Nobuhiko P.] Univ Calif Santa Cruz, Baskin Sch Engn, Santa Cruz, CA 95064 USA. [Leon, Juan J. Diaz; Norris, Kate J.; Sevic, John F.; Kobayashi, Nobuhiko P.] Univ Calif Santa Cruz, NASA, Ames Res Ctr, Adv Studies Labs,Nanostruct Energy Convers Techno, Moffett Field, CA USA. RP Leon, JJD (reprint author), Univ Calif Santa Cruz, Baskin Sch Engn, Santa Cruz, CA 95064 USA.; Leon, JJD (reprint author), Univ Calif Santa Cruz, NASA, Ames Res Ctr, Adv Studies Labs,Nanostruct Energy Convers Techno, Moffett Field, CA USA. NR 16 TC 1 Z9 1 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0239-7; 978-1-5106-0240-3 J9 PROC SPIE PY 2016 VL 9924 AR 99240I DI 10.1117/12.2239609 PG 5 WC Engineering, Electrical & Electronic; Optics; Physics, Condensed Matter SC Engineering; Optics; Physics GA BG6DG UT WOS:000390027500006 ER PT S AU Leon, JJD Fryauf, DM Cormia, RD Kobayashi, NP AF Leon, Juan J. Diaz Fryauf, David M. Cormia, Robert D. Kobayashi, Nobuhiko P. BE Kobayashi, NP Talin, AA Islam, MS Davydov, AV TI Study of the formation of native oxide on copper at room temperature SO LOW-DIMENSIONAL MATERIALS AND DEVICES 2016 SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Low-Dimensional Materials and Devices CY AUG 30-31, 2016 CL San Diego, CA SP SPIE DE Copper oxide; ellipsometry; phase composition ID THIN-FILMS; OXIDATION; SURFACES AB Native oxide grown on copper has been a nuisance in electrical devices due to extra electrical resistance added to copper electrodes. However, copper oxide, known to have two primary stable phases, cuprous oxide (Cu2O) and cupric oxide (CuO), is a material worth investigating for electronic applications. These two phases exhibiting distinctive electrical characteristics, would make copper oxide a prospective material for resistive switches. Cu2O and CuO often form concurrently within the native oxide. Because of their similar refractive index and extinction coefficient, optically differentiating these two phases is a challenge, yet it is critical for designing devices. In this study, thin copper films were deposited using electron-beam evaporation and sputtering. A native oxide was grown on the prepared copper films over 250 days in air and periodically evaluated with reflectometry-ellipsometry. X-ray photoelectron spectroscopy was also performed on the samples aged for 7 months to obtain their chemical characteristics. A comprehensive analysis on the progressive formation of native oxide on copper is discussed. C1 [Leon, Juan J. Diaz; Fryauf, David M.; Kobayashi, Nobuhiko P.] Univ Calif Santa Cruz, Baskin Sch Engn, Santa Cruz, CA 95064 USA. [Leon, Juan J. Diaz; Fryauf, David M.; Kobayashi, Nobuhiko P.] Univ Calif Santa Cruz, Adv Studies Labs, Nanostruct Energy Convers Technol & Res, Moffett Field, CA USA. [Leon, Juan J. Diaz; Fryauf, David M.; Kobayashi, Nobuhiko P.] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Cormia, Robert D.] Foothill Coll, Los Altos Hills, CA 94022 USA. RP Leon, JJD (reprint author), Univ Calif Santa Cruz, Baskin Sch Engn, Santa Cruz, CA 95064 USA.; Leon, JJD (reprint author), Univ Calif Santa Cruz, Adv Studies Labs, Nanostruct Energy Convers Technol & Res, Moffett Field, CA USA.; Leon, JJD (reprint author), NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. NR 17 TC 0 Z9 0 U1 1 U2 1 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0239-7; 978-1-5106-0240-3 J9 PROC SPIE PY 2016 VL 9924 AR 99240O DI 10.1117/12.2238745 PG 7 WC Engineering, Electrical & Electronic; Optics; Physics, Condensed Matter SC Engineering; Optics; Physics GA BG6DG UT WOS:000390027500009 ER PT S AU Danchi, W Bailey, V Bryden, G Defrere, D Ertel, S Haniff, C Hinz, P Kennedy, G Mennesson, B Millan-Gabet, R Rieke, G Roberge, A Serabyn, E Skemer, A Stapelfeldt, K Weinberger, A Wyatt, M Vaz, A AF Danchi, W. Bailey, V. Bryden, G. Defrere, D. Ertel, S. Haniff, C. Hinz, P. Kennedy, G. Mennesson, B. Millan-Gabet, R. Rieke, G. Roberge, A. Serabyn, E. Skemer, A. Stapelfeldt, K. Weinberger, A. Wyatt, M. Vaz, A. BE Malbet, F CreechEakman, MJ Tuthill, PG TI Enabling the Direct Detection of Earth-sized Exoplanets with the LBTI HOSTS Project: A Progress Report SO OPTICAL AND INFRARED INTERFEROMETRY AND IMAGING V SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Optical and Infrared Interferometry and Imaging V CY JUN 27-JUL 01, 2016 CL Edinburgh, SCOTLAND SP SPIE DE debris disks; exozodiacal dust; stellar interferometry; nulling interferometry; exoplanet detection; infrared astronomy ID KECK INTERFEROMETER NULLER; SOLAR-TYPE STARS; BINOCULAR TELESCOPE INTERFEROMETER; MAIN-SEQUENCE STARS; DEBRIS DISKS; TARGET SELECTION; SPITZER MIPS; DUST; CHARA/FLUOR; SCIENCE AB NASA has funded a project called the Hunt for Observable Signatures of Terrestrial Systems (HOSTS) to survey nearby solar type stars to determine the amount of warm zodiacal dust in their habitable zones. The goal is not only to determine the luminosity distribution function but also to know which individual stars have the least amount of zodiacal dust. It is important to have this information for future missions that directly image exoplanets as this dust is the main source of astrophysical noise for them. The HOSTS project utilizes the Large Binocular Telescope Interferometer (LBTI), which consists of two 8.4-m apertures separated by a 14.4-m baseline on Mt. Graham, Arizona. The LBTI operates in a nulling mode in the mid-infrared spectral window (8-13 mu m), in which light from the two telescopes is coherently combined with a 180 degree phase shift between them, producing a dark fringe at the location of the target star. In doing so the starlight is greatly reduced, increasing the contrast, analogous to a coronagraph operating at shorter wavelengths. The LBTI is a unique instrument, having only three warm reflections before the starlight reaches cold mirrors, giving it the best photometric sensitivity of any interferometer operating in the mid-infrared. It also has a superb Adaptive Optics (AO) system giving it Strehl ratios greater than 98% at 10 mu m. In 2014 into early 2015 LBTI was undergoing commissioning. The HOSTS project team passed its Operational Readiness Review (ORR) in April 2015. The team recently published papers on the target sample, modeling of the nulled disk images, and initial results such as the detection of warm dust around eta Corvi. Recently a paper was published on the data pipeline and on-sky performance. An additional paper is in preparation on beta Leo. We will discuss the scientific and programmatic context for the LBTI project, and we will report recent progress, new results, and plans for the science verification phase that started in February 2016, and for the survey. C1 [Danchi, W.; Roberge, A.; Stapelfeldt, K.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Bailey, V.; Defrere, D.; Ertel, S.; Hinz, P.; Rieke, G.; Skemer, A.; Vaz, A.] Univ Arizona, Tucson, AZ USA. [Bryden, G.; Mennesson, B.; Serabyn, E.] Jet Prop Lab, Pasadena, CA USA. [Haniff, C.; Kennedy, G.] Univ Cambridge, Cambridge, England. [Millan-Gabet, R.] CALTECH, Pasadena, CA USA. [Weinberger, A.] Carnegie Inst, Washington, DC USA. RP Danchi, W (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. EM william.c.danchi@nasa.gov OI Kennedy, Grant/0000-0001-6831-7547; Bailey, Vanessa/0000-0002-5407-2806 NR 39 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0193-2 J9 PROC SPIE PY 2016 VL 9907 AR 990713 DI 10.1117/12.2233397 PG 13 WC Engineering, Aerospace; Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Engineering; Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BG6DE UT WOS:000390024400029 ER PT S AU Darre, P Grossard, L Delage, L Reynaud, F Scott, NJ Sturmann, J ten Brummelaar, TA AF Darre, P. Grossard, L. Delage, L. Reynaud, F. Scott, N. J. Sturmann, J. ten Brummelaar, T. A. BE Malbet, F CreechEakman, MJ Tuthill, PG TI ALOHA/CHARA at 1.55 mu m: Sensitivity improvement and on-sky ability to detect astronomical sources in H band SO OPTICAL AND INFRARED INTERFEROMETRY AND IMAGING V SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Optical and Infrared Interferometry and Imaging V CY JUN 27-JUL 01, 2016 CL Edinburgh, SCOTLAND SP SPIE DE Interferometry; High angular resolution; Near-infrared; Sum frequency generation AB The interferometric concept named ALOHA (Astronomical Light Optical Hybrid Analysis) offers an alternative for high resolution imaging in the mid-infrared domain by shifting the astronomical light to shorter wavelength where optical guided components from telecommunications are available and efficient. A prototype with two arms converting a signal from 1.55 mu m to 630 nm is used to validate the concept in laboratory and on-sky. Thanks to collaboration with the CHARA team, photometric tests were achieved with a single arm of the interferometer and have allowed to predict instrument performance in its interferometric configuration in order to obtain first fringes in H band. C1 [Darre, P.; Grossard, L.; Delage, L.; Reynaud, F.] XLIM, Ave Albert Thomas, Limoges, France. [Scott, N. J.; Sturmann, J.; ten Brummelaar, T. A.] Mt Wilson Observ, CHARA Array, Los Angeles, CA USA. [Scott, N. J.] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Darre, P (reprint author), XLIM, Ave Albert Thomas, Limoges, France. NR 16 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0193-2 J9 PROC SPIE PY 2016 VL 9907 AR 990724 DI 10.1117/12.2232315 PG 8 WC Engineering, Aerospace; Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Engineering; Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BG6DE UT WOS:000390024400059 ER PT S AU Defrere, D Hinz, P Downey, E Bohm, M Danchi, WC Durney, O Ertel, S Hill, JM Hoffmann, WF Mennesson, B Milian-Gabet, R Montoya, M Pott, JU Skemer, A Spalding, E Stone, J Vaz, A AF Defrere, D. Hinz, P. Downey, E. Bohm, M. Danchi, W. C. Durney, O. Ertel, S. Hill, J. M. Hoffmann, W. F. Mennesson, B. Milian-Gabet, R. Montoya, M. Pott, J. -U. Skemer, A. Spalding, E. Stone, J. Vaz, A. BE Malbet, F CreechEakman, MJ Tuthill, PG TI Simultaneous Water Vapor and Dry Air Optical Path Length Measurements and Compensation with the Large Binocular Telescope Interferometer SO OPTICAL AND INFRARED INTERFEROMETRY AND IMAGING V SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Optical and Infrared Interferometry and Imaging V CY JUN 27-JUL 01, 2016 CL Edinburgh, SCOTLAND SP SPIE DE Infrared interferometry; Nulling interferometry; Fringe tracking; Water vapor; LBT; ELT ID PERFORMANCE; MIDI AB The Large Binocular Telescope Interferometer uses a near-infrared camera to measure the optical path length variations between the two AO-corrected apertures and provide high-angular resolution observations for all its science channels (1.5-13 microns). There is however a wavelength dependent component to the atmospheric turbulence, which can introduce optical path length errors when observing at a wavelength different from that of the fringe sensing camera. Water vapor in particular is highly dispersive and its effect must be taken into account for high-precision infrared interferometric observations as described previously for VLTI/MIDI or the Keck Interferometer Nuller. In this paper, we describe the new sensing approach that has been developed at the LBT to measure and monitor the optical path length fluctuations due to dry air and water vapor separately. After reviewing the current performance of the system for dry air seeing compensation, we present simultaneous H-, K-, and N-band observations that illustrate the feasibility of our feedforward approach to stabilize the path length fluctuations seen by the LBTI nuller. C1 [Defrere, D.; Hinz, P.; Downey, E.; Durney, O.; Ertel, S.; Hoffmann, W. F.; Montoya, M.; Spalding, E.; Stone, J.; Vaz, A.] Univ Arizona, Steward Observ, 933 N Cherry Ave, Tucson, AZ 85721 USA. [Defrere, D.] Univ Liege, STAR Inst, 17 Allee Six Aout, B-4000 Sart Tilman Par Liege, Belgium. [Bohm, M.] Univ Stuttgart, ISYS, Pfaffenwaldring 9, D-70569 Stuttgart, Germany. [Danchi, W. C.] NASA, Goddard Space Flight Ctr, Exoplanets & Stellar Astrophys Lab, Code 685, Greenbelt, MD 20771 USA. [Hill, J. M.] Univ Arizona, Large Binocular Telescope Observ, 933 N Cherry Ave, Tucson, AZ 85721 USA. [Mennesson, B.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Milian-Gabet, R.] CALTECH, NASA Exoplanet Sci Ctr NExSci, 770 South Wilson Ave, Pasadena, CA 91125 USA. [Pott, J. -U.] Max Planck Inst Astron, Konigstuhl 17, D-69117 Heidelberg, Germany. [Skemer, A.] Univ Calif Santa Cruz, Dept Astron & Astrophys, 1156 High St, Santa Cruz, CA 95064 USA. RP Defrere, D (reprint author), Univ Arizona, Steward Observ, 933 N Cherry Ave, Tucson, AZ 85721 USA.; Defrere, D (reprint author), Univ Liege, STAR Inst, 17 Allee Six Aout, B-4000 Sart Tilman Par Liege, Belgium. EM denis@lbti.org NR 16 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0193-2 J9 PROC SPIE PY 2016 VL 9907 AR 99071G DI 10.1117/12.2233884 PG 7 WC Engineering, Aerospace; Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Engineering; Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BG6DE UT WOS:000390024400042 ER PT S AU Dhabal, A Rinehart, SA Rizzo, MJ Mundy, L Fixsen, D Sampler, H Mentzell, E Veach, T Silverberg, RF Furst, S Dow, T Ade, P Tucker, C AF Dhabal, Arnab Rinehart, Stephen A. Rizzo, Maxime J. Mundy, Lee Fixsen, Dale Sampler, Henry Mentzell, Eric Veach, Todd Silverberg, Robert F. Furst, Stephen Dow, Thomas Ade, Peter Tucker, Carole BE Malbet, F CreechEakman, MJ Tuthill, PG TI Optics of Balloon Experimental Twin Telescope for Infrared Interferometry (BETTII): delay lines and alignment SO OPTICAL AND INFRARED INTERFEROMETRY AND IMAGING V SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Optical and Infrared Interferometry and Imaging V CY JUN 27-JUL 01, 2016 CL Edinburgh, SCOTLAND SP SPIE DE spatio-spectral interferometry; far infra-red; delay line; capacitive sensor; interferometric simulation; metrology; alignment ID RESOLUTION AB We present the optics of Balloon Experimental Twin Telescope for Infrared Interferometry (BETTII) as it gets ready for launch. BETTII is an 8-meter baseline far-infrared (30-90 mu m) interferometer mission with capabilities of spatially resolved spectroscopy aimed at studying star formation and galaxy evolution. The instrument collects light from its two arms, makes them interfere, divides them into two science channels (30-50 mu m and 60-90 mu m), and focuses them onto the detectors. It also separates out the NIR light (1-2.5 mu m) and uses it for tip-tilt corrections of the telescope pointing. Currently, all the optical elements have been fabricated, heat treated, coated appropriately and are mounted on their respective assemblies. We are presenting the optical design challenges for such a balloon borne spatio-spectral interferometer, and discuss how they have been mitigated. The warm and cold delay lines are an important part of this optics train. The warm delay line corrects for path length differences between the left and the right arm due to balloon pendulation, while the cold delay line is aimed at introducing a systematic path length difference, thereby generating our interferograms from where we can derive information about the spectra. The details of their design and the results of the testing of these opto-mechanical parts are also discussed. The sensitivities of different optical elements on the interferograms produced have been determined with the help of simulations using FRED software package. Accordingly, an alignment plan is drawn up which makes use of a laser tracker, a CMM, theodolites and a LUPI interferometer. C1 [Dhabal, Arnab; Rinehart, Stephen A.; Rizzo, Maxime J.; Fixsen, Dale; Sampler, Henry; Mentzell, Eric; Veach, Todd; Silverberg, Robert F.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20770 USA. [Dhabal, Arnab; Rizzo, Maxime J.; Mundy, Lee] Univ Maryland, Dept Astron, College Pk, MD 20741 USA. [Furst, Stephen; Dow, Thomas] North Carolina State Univ, Precis Engn Ctr, 1001 Capabil Dr, Raleigh, NC 27606 USA. [Ade, Peter; Tucker, Carole] Cardiff Univ, Sch Phys & Astron, Cardiff CF24 3AA, S Glam, Wales. RP Dhabal, A (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20770 USA.; Dhabal, A (reprint author), Univ Maryland, Dept Astron, College Pk, MD 20741 USA. EM adhabal@astro.umd.edu NR 12 TC 0 Z9 0 U1 3 U2 3 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0193-2 J9 PROC SPIE PY 2016 VL 9907 AR 99070T DI 10.1117/12.2230218 PG 12 WC Engineering, Aerospace; Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Engineering; Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BG6DE UT WOS:000390024400021 ER PT S AU Hicks, BA Lyon, RG Bolcar, MR Clampin, M Petrone, P Helmbrecht, MA Howard, JM Miller, IJ AF Hicks, Brian A. Lyon, Richard G. Bolcar, Matthew R. Clampin, Mark Petrone, Peter, III Helmbrecht, Michael A. Howard, Joseph M. Miller, Ian J. BE Malbet, F CreechEakman, MJ Tuthill, PG TI Recent developments with the Visible Nulling Coronagraph SO OPTICAL AND INFRARED INTERFEROMETRY AND IMAGING V SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Optical and Infrared Interferometry and Imaging V CY JUN 27-JUL 01, 2016 CL Edinburgh, SCOTLAND SP SPIE DE Exoplanets; high-contrast imaging; nulling coronagraphy; laboratory demonstrations; space telescopes AB A wide array of general astrophysics studies including detecting and characterizing habitable exoplanets could be enabled by a future large segmented telescope with sensitivity in the UV, optical, and infrared bands. When paired with a starshade or coronagraph, such an observatory could enable direct imaging and detailed spectroscopic observations of nearby Earth-like habitable zone planets. Over the past several years, a laboratory-based Visible Nulling Coronagraph (VNC) has evolved to reach requisite contrasts over a similar to 1 nm bandwidth at narrow source angle separation using a segmented deformable mirror in one arm of a Mach-Zehnder layout. More recent efforts targeted broadband performance following the addition of two sets of half-wave Fresnel rhomb achromatic phase shifters (APS) with the goal of reaching 10(-9) contrast, at a separation of 2 lambda/D, using a 40 nm (6%) bandwdith single mode fiber source. Here we present updates on the VNC broadband nulling effort, including approaches to addressing system contrast limitations. C1 [Hicks, Brian A.] Univ Maryland, CRESST, College Pk, MD 20742 USA. [Hicks, Brian A.; Lyon, Richard G.; Bolcar, Matthew R.; Clampin, Mark; Howard, Joseph M.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Petrone, Peter, III] Sigma Space Corp, Lanham, MD USA. [Helmbrecht, Michael A.] Iris AO Inc, Berkeley, CA USA. [Miller, Ian J.] LightMachinery Inc, Ottawa, ON, Canada. RP Hicks, BA (reprint author), Univ Maryland, CRESST, College Pk, MD 20742 USA.; Hicks, BA (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. EM bahicksmail@gmail.com NR 14 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0193-2 J9 PROC SPIE PY 2016 VL 9907 AR 99072O DI 10.1117/12.2234315 PG 9 WC Engineering, Aerospace; Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Engineering; Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BG6DE UT WOS:000390024400072 ER PT S AU Hinz, PM Defrere, D Skemer, A Bailey, V Stone, J Spalding, E Vaz, A Pinna, E Puglisi, A Esposito, S Montoya, M Downey, E Leisenring, J Durney, O Hoffmann, W Hill, J Millan-Gabet, R Mennesson, B Danchi, W Morzinski, K Grenz, P Skrutskie, M Ertel, S AF Hinz, P. M. Defrere, D. Skemer, A. Bailey, V. Stone, J. Spalding, E. Vaz, A. Pinna, E. Puglisi, A. Esposito, S. Montoya, M. Downey, E. Leisenring, J. Durney, O. Hoffmann, W. Hill, J. Millan-Gabet, R. Mennesson, B. Danchi, W. Morzinski, K. Grenz, P. Skrutskie, M. Ertel, S. BE Malbet, F CreechEakman, MJ Tuthill, PG TI Overview of LBTI: a multipurpose facility for high spatial resolution observations SO OPTICAL AND INFRARED INTERFEROMETRY AND IMAGING V SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Optical and Infrared Interferometry and Imaging V CY JUN 27-JUL 01, 2016 CL Edinburgh, SCOTLAND SP SPIE DE LBT; interferometry; infrared instruments; adaptive optics; imaging AB The Large Binocular Telescope Interferometer (LBTI) is a high spatial resolution instrument developed for coherent imaging and nulling interferometry using the 14.4 m baseline of the 2x8.4 m LBT. The unique telescope design, comprising of the dual apertures on a common elevation-azimuth mount, enables a broad use of observing modes. The full system is comprised of dual adaptive optics systems, a near-infrared phasing camera, a 1-5 mu m camera (called LMIRCam), and an 8-13 mu m camera (called NOMIC). The key program for LBTI is the Hunt for Observable Signatures of Terrestrial planetary Systems (HOSTS), a survey using nulling interferometry to constrain the typical brightness from exozodiacal dust around nearby stars. Additional observations focus on the detection and characterization of giant planets in the thermal infrared, high spatial resolution imaging of complex scenes such as Jupiter's moon, Io, planets forming in transition disks, and the structure of active Galactic Nuclei (AGN). Several instrumental upgrades are currently underway to improve and expand the capabilities of LBTI. These include: Improving the performance and limiting magnitude of the parallel adaptive optics systems; quadrupling the field of view of LMIRcam (increasing to 20"x20"); adding an integral field spectrometry mode; and implementing a new algorithm for path length correction that accounts for dispersion due to atmospheric water vapor. We present the current architecture and performance of LBTI, as well as an overview of the upgrades. C1 [Hinz, P. M.; Defrere, D.; Skemer, A.; Bailey, V.; Stone, J.; Spalding, E.; Vaz, A.; Montoya, M.; Downey, E.; Leisenring, J.; Durney, O.; Hoffmann, W.; Hill, J.; Morzinski, K.; Grenz, P.; Ertel, S.] Univ Arizona, Steward Observ, 933 North Cherry Ave, Tucson, AZ 85721 USA. [Defrere, D.] Univ Liege, STAR Inst, 17 Allee Six Aout, B-4000 Sart Tilman Par Liege, Belgium. [Skemer, A.] Univ Calif Santa Cruz, Dept Astron & Astrophys, 1156 High St, Santa Cruz, CA 95064 USA. [Bailey, V.] Stanford Univ, Dept Phys, Kavli Inst Particle Astrophys & Cosmol, Stanford, CA 94305 USA. [Pinna, E.; Puglisi, A.; Esposito, S.] INAF Osservatorio Astrofis Arcetri, Largo E Fermi 5, I-50125 Florence, Italy. [Millan-Gabet, R.] CALTECH, NASA Exoplanet Sci Ctr NExSci, 770 South Wilson Ave, Pasadena, CA 91125 USA. [Mennesson, B.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Danchi, W.] NASA, Goddard Space Flight Ctr, Exoplanets & Stellar Astrophys Lab, Code 667, Greenbelt, MD 20771 USA. [Skrutskie, M.] Univ Virginia, 530 McCormick Rd, Charlottesville, VA 22904 USA. RP Hinz, PM (reprint author), Univ Arizona, Steward Observ, 933 North Cherry Ave, Tucson, AZ 85721 USA. EM phinz@as.arizona.edu OI Stone, Jordan/0000-0003-0454-3718; Bailey, Vanessa/0000-0002-5407-2806 NR 18 TC 0 Z9 0 U1 1 U2 1 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0193-2 J9 PROC SPIE PY 2016 VL 9907 AR 990704 DI 10.1117/12.2233795 PG 14 WC Engineering, Aerospace; Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Engineering; Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BG6DE UT WOS:000390024400004 ER PT S AU Hosseini, S Harris, W AF Hosseini, Sona Harris, Walter BE Malbet, F CreechEakman, MJ Tuthill, PG TI Khayyam; progress and prospects of coupling a Spatial Heterodyne Spectrometer (SHS) to a Cassegrain Telescope for Optical interferometry SO OPTICAL AND INFRARED INTERFEROMETRY AND IMAGING V SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Optical and Infrared Interferometry and Imaging V CY JUN 27-JUL 01, 2016 CL Edinburgh, SCOTLAND SP SPIE DE Tunable Spatial Heterodyne Spectrometer; SHS; extended targets; interferometry; spectrometry AB In the temporal study of faint, extended sources at high resolving power, Spatial Heterodyne Spectrometer (SHS) can offer significant advantages about conventional dispersive grating spectrometers. We describe here a four-year continuous progress in Mt. Hamilton, Lick Observatory, toward development of a prototype reflective Spacial Heterodyne Spectrometer, Khayyam, instrument-telescope configuration to combine all of the capabilities necessary to obtain high resolving power visible band spectra of diffuse targets from small aperture on-axis telescopes where significant observing time can be obtained. We will discuss the design considerations going into this new system, installation, testing of the interferometer-telescope combination, the technical challenges and procedures moving forward. C1 [Hosseini, Sona] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. [Harris, Walter] Univ Arizona, Lunar & Planetary Lab, Tucson, AZ 85721 USA. RP Hosseini, S (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. NR 11 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0193-2 J9 PROC SPIE PY 2016 VL 9907 AR 99072I DI 10.1117/12.2233120 PG 14 WC Engineering, Aerospace; Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Engineering; Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BG6DE UT WOS:000390024400069 ER PT S AU Iacchetta, AS Fienup, JR Leisawitz, DT AF Iacchetta, Alexander S. Fienup, James R. Leisawitz, David T. BE Malbet, F CreechEakman, MJ Tuthill, PG TI Rotation and Translation Registration of Bandlimited Interferometric Images using a Chirp Z-Transform SO OPTICAL AND INFRARED INTERFEROMETRY AND IMAGING V SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Optical and Infrared Interferometry and Imaging V CY JUN 27-JUL 01, 2016 CL Edinburgh, SCOTLAND SP SPIE DE Image registration; resampling; chirp z-transform; nonlinear optimization; double-Fourier interferometry; spatio-spectral interferometry; WIIT ID PHASE RETRIEVAL; TESTBED II; ALGORITHMS AB Image reconstruction algorithms for wide-field spatio-spectral interferometry require knowledge of registration parameters associated with low-resolution image measurements at various baseline orientations, such that the images can be registered to within the fine resolution of the final desired image. We have developed an image registration procedure that combines a nonlinear optimization algorithm with the sub-pixel precision of chirp z-transform resampling, particularly for rotation and translation, of bandlimited images with non-radially symmetric aberrations. We show the accuracy of this image registration technique on simulated images that have a complexity comparable to scenes observed experimentally with NASA's wide-field imaging interferometry testbed. Registration to within a tenth of a pixel for translation and within three arcminutes for rotation is demonstrated at the largest simulated noise levels. C1 [Iacchetta, Alexander S.; Fienup, James R.] Univ Rochester, Inst Opt, 275 Hutchison Rd, Rochester, NY 14627 USA. [Leisawitz, David T.] NASA, Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. RP Iacchetta, AS (reprint author), Univ Rochester, Inst Opt, 275 Hutchison Rd, Rochester, NY 14627 USA. NR 26 TC 0 Z9 0 U1 1 U2 1 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0193-2 J9 PROC SPIE PY 2016 VL 9907 AR 99073G DI 10.1117/12.2232178 PG 10 WC Engineering, Aerospace; Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Engineering; Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BG6DE UT WOS:000390024400089 ER PT S AU Ireland, MJ Monnier, JD Kraus, S Isella, A Minardi, S Petrov, R ten Brummelaar, T Young, J Vasisht, G Mozurkewich, D Rinehart, S Michael, EA van Belle, G Woillez, J AF Ireland, Michael J. Monnier, John D. Kraus, Stefan Isella, Andrea Minardi, Stefano Petrov, Romain ten Brummelaar, Theo Young, John Vasisht, Gautum Mozurkewich, David Rinehart, Stephen Michael, Ernest A. van Belle, Gerard Woillez, Julien BE Malbet, F CreechEakman, MJ Tuthill, PG TI Status of the Planet Formation Imager (PFI) concept SO OPTICAL AND INFRARED INTERFEROMETRY AND IMAGING V SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Optical and Infrared Interferometry and Imaging V CY JUN 27-JUL 01, 2016 CL Edinburgh, SCOTLAND SP SPIE DE interferometry; mid-infrared; exoplanets; planet formation; astronomy; facilities; imaging; infrared ID CALIBRATION; OPTICS AB The Planet Formation Imager (PFI) project aims to image the period of planet assembly directly, resolving structures as small as a giant planet's Hill sphere. These images will be required in order to determine the key mechanisms for planet formation at the time when processes of grain growth, protoplanet assembly, magnetic fields, disk/planet dynamical interactions and complex radiative transfer all interact - making some planetary systems habitable and others inhospitable. We will present the overall vision for the PFI concept, focusing on the key technologies and requirements that are needed to achieve the science goals. Based on these key requirements, we will define a cost envelope range for the design and highlight where the largest uncertainties lie at this conceptual stage. C1 [Ireland, Michael J.] Australian Natl Univ, Res Sch Astron & Astrophys, Canberra, ACT 2611, Australia. [Monnier, John D.] Univ Michigan, Dept Astron, Ann Arbor, MI 48109 USA. [Kraus, Stefan] Univ Exeter, Sch Phys, Exeter EX4 4QL, Devon, England. [Isella, Andrea] Rice Univ, Dept Phys & Astron, Houston, TX 77251 USA. [Minardi, Stefano] Leibniz Inst Astrophys Potsdam AIP, Potsdam, Germany. [Petrov, Romain] Univ Cote Azur, OCA, CNRS, Parc Valrose, F-06108 Nice, France. [ten Brummelaar, Theo] Georgia State Univ, CHARA Array, Atlanta, GA 30303 USA. [Young, John] Univ Cambridge, Cavendish Lab, JJ Thompson Ave, Cambridge CB3 0HE, England. [Vasisht, Gautum] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Mozurkewich, David] Seabrook Engn, 9310 Dubarry Ave, Seabrook, MD 20706 USA. [Rinehart, Stephen] NASA, Goddard Space Flight Ctr, Mail Code 665, Greenbelt, MD 20771 USA. [Michael, Ernest A.] Univ Chile, FCFM, Dept Elect Engn, Av Tupper 2007, Santiago, Chile. [van Belle, Gerard] Lowell Observ, 1400 W Mars Hill Rd, Flagstaff, AZ 86001 USA. [Woillez, Julien] ESO, Karl Schwarzschild Str 2, D-85748 Garching, Germany. RP Ireland, MJ (reprint author), Australian Natl Univ, Res Sch Astron & Astrophys, Canberra, ACT 2611, Australia. EM michael.ireland@anu.edu.au NR 14 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0193-2 J9 PROC SPIE PY 2016 VL 9907 AR 99071L DI 10.1117/12.2233926 PG 14 WC Engineering, Aerospace; Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Engineering; Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BG6DE UT WOS:000390024400046 ER PT S AU Juanola-Parramon, R Leisawitz, DT Bolcar, MR Maher, SF Rinehart, SA Iacchetta, A Savini, G AF Juanola-Parramon, Roser Leisawitz, David T. Bolcar, Matthew R. Maher, Stephen F. Rinehart, Stephen A. Iacchetta, Alex Savini, Giorgio BE Malbet, F CreechEakman, MJ Tuthill, PG TI The Wide-field Imaging Interferometry Testbed (WIIT): recent progress in the simulation and synthesis of WIIT data SO OPTICAL AND INFRARED INTERFEROMETRY AND IMAGING V SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Optical and Infrared Interferometry and Imaging V CY JUN 27-JUL 01, 2016 CL Edinburgh, SCOTLAND SP SPIE DE double Fourier; spectroscopy; interferometry; space instrumentation AB The Wide-field Imaging Interferometry Testbed (WIIT) is a double Fourier (DF) interferometer operating at optical wavelengths, and provides data that are highly representative of those from a space-based far-infrared interferometer like SPIRIT. This testbed has been used to measure both a geometrically simple test scene and an astronomically representative test scene. Here we present the simulation of recent WIIT measurements using FIInS (the Far-infrared Interferometer Instrument Simulator), the main goal of which is to simulate both the input and the output of a DFM system. FIInS has been modified to perform calculations at optical wavelengths and to include an extended field of view due to the presence of a detector array. C1 [Rinehart, Stephen A.] NASA, Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. [Iacchetta, Alex] Univ Rochester, Inst Opt, 275 Hutchison Rd, Rochester, NY 14627 USA. [Savini, Giorgio] UCL, Gower St, London, England. RP Rinehart, SA (reprint author), NASA, Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. EM roser.juanola@nasa.gov OI Savini, Giorgio/0000-0003-4449-9416 NR 7 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0193-2 J9 PROC SPIE PY 2016 VL 9907 AR 990740 DI 10.1117/12.2232090 PG 8 WC Engineering, Aerospace; Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Engineering; Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BG6DE UT WOS:000390024400102 ER PT S AU Kraus, S Monnier, JD Ireland, MJ Duchene, G Espaillat, C Honig, S Juhasz, A Mordasini, C Olofsson, J Paladini, C Stassun, K Turner, N Vasisht, G Harries, TJ Bate, MR Gonzalez, JF Matter, A Zhu, ZH Panic, O Regaly, Z Morbidelli, A Meru, F Wolf, S Ilee, J Berger, JP Zhao, M Kral, Q Morlok, A Bonsor, A Ciardi, D Kane, SR Kratter, K Laughlin, G Pepper, J Raymond, S Labadie, L Nelson, RP Weigelt, G ten Brummelaar, T Pierens, A Oudmaijer, R Kley, W Pope, B Jensen, ELN Bayo, A Smith, M Boyajian, T Quiroga-Nunez, LH Millan-Gabet, R Chiavassa, A Gallenne, A Reynolds, M de Wit, WJ Wittkowski, M Millour, F Gandhi, P Almeida, CR Herrero, AA Packham, C Kishimoto, M Tristram, KRW Pott, JU Surdej, J Buscher, D Haniff, C Lacour, S Petrov, R Ridgway, S Tuthill, P van Belle, G Armitage, P Baruteau, C Benisty, M Bitsch, B Paardekooper, SJ Pinte, C Masset, F Rosotti, GP AF Kraus, Stefan Monnier, John D. Ireland, Michael J. Duchene, Gaspard Espaillat, Catherine Honig, Sebastian Juhasz, Attila Mordasini, Chris Olofsson, Johan Paladini, Claudia Stassun, Keivan Turner, Neal Vasisht, Gautam Harries, Tim J. Bate, Matthew R. Gonzalez, Jean-Francois Matter, Alexis Zhu, Zhaohuan Panic, Olja Regaly, Zsolt Morbidelli, Alessandro Meru, Farzana Wolf, Sebastian Ilee, John Berger, Jean-Philippe Zhao, Ming Kral, Quentin Morlok, Andreas Bonsor, Amy Ciardi, David Kane, Stephen R. Kratter, Kaitlin Laughlin, Greg Pepper, Joshua Raymond, Sean Labadie, Lucas Nelson, Richard P. Weigelt, Gerd ten Brummelaar, Theo Pierens, Arnaud Oudmaijer, Rene Kley, Wilhelm Pope, Benjamin Jensen, Eric L. N. Bayo, Amelia Smith, Michael Boyajian, Tabetha Quiroga-Nunez, Luis Henry Millan-Gabet, Rafael Chiavassa, Andrea Gallenne, Alexandre Reynolds, Mark de Wit, Willem-Jan Wittkowski, Markus Millour, Florentin Gandhi, Poshak Ramos Almeida, Cristina Alonso Herrero, Almudena Packham, Chris Kishimoto, Makoto Tristram, Konrad R. W. Pott, Joerg-Uwe Surdej, Jean Buscher, David Haniff, Chris Lacour, Sylvestre Petrov, Romain Ridgway, Steve Tuthill, Peter van Belle, Gerard Armitage, Phil Baruteau, Clement Benisty, Myriam Bitsch, Bertram Paardekooper, Sijme-Jan Pinte, Christophe Masset, Frederic Rosotti, Giovanni P. BE Malbet, F CreechEakman, MJ Tuthill, PG TI Planet Formation Imager (PFI): science vision and key requirements SO OPTICAL AND INFRARED INTERFEROMETRY AND IMAGING V SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Optical and Infrared Interferometry and Imaging V CY JUN 27-JUL 01, 2016 CL Edinburgh, SCOTLAND SP SPIE DE planet formation; protoplanetary disks; extrasolar planets; high angular resolution imaging; interferometry ID GIANT PLANET; PROTOPLANETARY DISKS; ACCRETION; EVOLUTION; MODELS; STARS; LINES; GAS; INSTABILITY; RADIATION AB The Planet Formation Imager (PFI) project aims to provide a strong scientific vision for ground-based optical astronomy beyond the upcoming generation of Extremely Large Telescopes. We make the case that a breakthrough in angular resolution imaging capabilities is required in order to unravel the processes involved in planet formation. PFI will be optimised to provide a complete census of the protoplanet population at all stellocentric radii and over the age range from 0.1 to similar to 100 Myr. Within this age period, planetary systems undergo dramatic changes and the final architecture of planetary systems is determined. Our goal is to study the planetary birth on the natural spatial scale where the material is assembled, which is the "Hill Sphere" of the forming planet, and to characterise the protoplanetary cores by measuring their masses and physical properties. Our science working group has investigated the observational characteristics of these young protoplanets as well as the migration mechanisms that might alter the system architecture. We simulated the imprints that the planets leave in the disk and study how PFI could revolutionise areas ranging from exoplanet to extragalactic science. In this contribution we outline the key science drivers of PFI and discuss the requirements that will guide the technology choices, the site selection, and potential science/technology tradeoffs. C1 [Kraus, Stefan; Harries, Tim J.; Bate, Matthew R.] Univ Exeter, Sch Phys, Stocker Rd, Exeter, Devon, England. [Monnier, John D.; Reynolds, Mark] Univ Michigan, Dept Astron, 500 Church St, Ann Arbor, MI 48109 USA. [Ireland, Michael J.] Australian Natl Univ, Res Sch Astron & Astrophys, Canberra, ACT, Australia. [Duchene, Gaspard] Univ Calif Berkeley, Berkeley, CA 94720 USA. [Duchene, Gaspard] Grenoble Univ Alpes, CNRS, Inst Planetol & Astrophys Grenoble, Grenoble, France. [Espaillat, Catherine] Boston Univ, Boston, MA 02215 USA. [Honig, Sebastian; Gandhi, Poshak] Univ Southampton, Southampton, Hants, England. [Juhasz, Attila; Meru, Farzana; Ilee, John; Kral, Quentin; Bonsor, Amy; Buscher, David; Haniff, Chris; Rosotti, Giovanni P.] Inst Astron, Madingley Rd, Cambridge, England. [Mordasini, Chris; Bayo, Amelia] Univ Bern, Bern, Switzerland. [Olofsson, Johan] Inst Fis & Astron, Valparaiso, Chile. [Paladini, Claudia] Univ Libre Bruxelles, Brussels, Belgium. [Stassun, Keivan] Vanderbilt Univ, 221 Kirkland Hall, Nashville, TN 37235 USA. [Turner, Neal; Vasisht, Gautam] CALTECH, Jet Prop Lab, Pasadena, CA USA. [Gonzalez, Jean-Francois] Univ Lyon 1, Ens Lyon, CNRS, Ctr Rech Astrophys Lyon UMR5574,Univ Lyon, F-69230 St Genis Laval, France. [Matter, Alexis; Morbidelli, Alessandro; Chiavassa, Andrea; Millour, Florentin; Petrov, Romain] Univ Nice Sophia Antipolis, Observ Cote Azur, Nice, France. [Zhu, Zhaohuan] Princeton Univ, Dept Astrophys Sci, Princeton, NJ 08544 USA. [Regaly, Zsolt] Konkoly Observ Budapest, Res Ctr Astron & Earth Sci, Budapest, Hungary. [Wolf, Sebastian] Univ Kiel, Inst Theoret Phys & Astrophys, Kiel, Germany. [Berger, Jean-Philippe] European Southern Observ, Karl Schwarzschild Str 2, Garching, Germany. [Zhao, Ming] Penn State Univ, Dept Astron & Astrophys, 525 Davey Lab, University Pk, PA 16802 USA. [Morlok, Andreas] Inst Planetol Munster, Munster, Germany. [Ciardi, David; Millan-Gabet, Rafael] NASA Exoplanet Sci Inst, Pasadena, CA USA. [Kane, Stephen R.] San Francisco State Univ, San Francisco, CA 94132 USA. [Kratter, Kaitlin] Univ Arizona, Tucson, AZ 85721 USA. [Laughlin, Greg; Boyajian, Tabetha] Yale Univ, New Haven, CT USA. [Pepper, Joshua] Lehigh Univ, Bethlehem, PA 18015 USA. [Raymond, Sean; Pierens, Arnaud] Lab Astrophys Bordeaux, Bordeaux, France. [Labadie, Lucas] Univ Cologne, Cologne, Germany. [Nelson, Richard P.; Paardekooper, Sijme-Jan] Queen Mary Univ London, London, England. [Weigelt, Gerd] Max Planck Inst Radioastron, Bonn, Germany. [ten Brummelaar, Theo] Georgia State Univ, Atlanta, GA 30303 USA. [Oudmaijer, Rene] Univ Leeds, Leeds, W Yorkshire, England. [Kley, Wilhelm] Univ Tubingen, Tubingen, Germany. [Pope, Benjamin] Univ Oxford, Oxford, England. [Jensen, Eric L. N.] Swarthmore Coll, Swarthmore, PA 19081 USA. [Smith, Michael] Univ Kent, Canterbury CT2 7NZ, Kent, England. [Quiroga-Nunez, Luis Henry] Leiden Univ, Sterrewacht Leiden, Leiden, Netherlands. [Quiroga-Nunez, Luis Henry] Joint Inst VLBI ERIC JIVE, Dwingeloo, Netherlands. [Gallenne, Alexandre; de Wit, Willem-Jan; Tristram, Konrad R. W.] European Southern Observ, Santiago, Chile. [Ramos Almeida, Cristina] Inst Astrofis Canarias, San Cristobal la Laguna, Spain. [Alonso Herrero, Almudena] Univ Madrid, Univ Santander, Madrid, Spain. [Packham, Chris] Univ Texas San Antonio, San Antonio, TX USA. [Kishimoto, Makoto] Kyoto Sangyo Univ, Kyoto, Japan. [Pott, Joerg-Uwe] MPIA, Heidelberg, Germany. [Surdej, Jean] Univ Liege, Liege, Belgium. [Lacour, Sylvestre] Observ Paris, Paris, France. [Ridgway, Steve] Natl Opt Astron Observ, Tucson, AZ 85726 USA. [Tuthill, Peter] Univ Sydney, Sydney, NSW, Australia. [van Belle, Gerard] Lowell Observ, 1400 W Mars Hill Rd, Flagstaff, AZ 86001 USA. [Armitage, Phil] Univ Colorado, Boulder, CO 80309 USA. [Armitage, Phil] NIST, Boulder, CO USA. [Baruteau, Clement] CNRS, Inst Rech Astrophys & Planetol, Toulouse, France. [Baruteau, Clement] Univ Toulouse, Toulouse, France. [Bitsch, Bertram] Lund Observ, Lund, Sweden. [Masset, Frederic] Univ Nacl Autonoma Mexico, Mexico City 04510, DF, Mexico. RP Kraus, S (reprint author), Univ Exeter, Sch Phys, Stocker Rd, Exeter, Devon, England. EM skraus@astro.ex.ac.uk RI Alonso-Herrero, Almudena/H-1426-2015; OI Alonso-Herrero, Almudena/0000-0001-6794-2519; Paladini, Claudia/0000-0003-4974-7239; Ciardi, David/0000-0002-5741-3047; Pepper, Joshua/0000-0002-3827-8417 NR 40 TC 0 Z9 0 U1 1 U2 1 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0193-2 J9 PROC SPIE PY 2016 VL 9907 AR 99071K DI 10.1117/12.2231067 PG 12 WC Engineering, Aerospace; Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Engineering; Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BG6DE UT WOS:000390024400045 ER PT S AU Leisawitz, DT Juanola-Parramon, R Bolcar, M Fienup, JR Iacchetta, AS Maher, SF Rinehart, SA AF Leisawitz, David T. Juanola-Parramon, Roser Bolcar, Matthew Fienup, James R. Iacchetta, Alexander S. Maher, Stephen F. Rinehart, Stephen A. BE Malbet, F CreechEakman, MJ Tuthill, PG TI Recent experiments conducted with the Wide-field Imaging Interferometry Testbed (WIIT) SO OPTICAL AND INFRARED INTERFEROMETRY AND IMAGING V SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Optical and Infrared Interferometry and Imaging V CY JUN 27-JUL 01, 2016 CL Edinburgh, SCOTLAND SP SPIE DE Interferometry; WIIT; Spatio-spectral interferometry; Double Fourier interferometry AB The Wide-field Imaging Interferometry Testbed (WIIT) was developed at NASA's Goddard Space Flight Center to demonstrate and explore the practical limitations inherent in wide field-of-view "double Fourier" (spatio-spectral) interferometry. The testbed delivers high-quality interferometric data and is capable of observing spatially and spectrally complex hyperspectral test scenes. Although WIIT operates at visible wavelengths, by design the data are representative of those from a space-based far-infrared observatory. We used WIIT to observe a calibrated, independently characterized test scene of modest spatial and spectral complexity, and an astronomically realistic test scene of much greater spatial and spectral complexity. This paper describes the experimental setup, summarizes the performance of the testbed, and presents representative data. C1 [Leisawitz, David T.; Juanola-Parramon, Roser; Bolcar, Matthew; Maher, Stephen F.; Rinehart, Stephen A.] NASA, Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. [Fienup, James R.; Iacchetta, Alexander S.] Univ Rochester, Inst Opt, 275 Hutchison Rd, Rochester, NY 14627 USA. [Maher, Stephen F.] SSAI Inc, Signal Hill, CA USA. RP Leisawitz, DT (reprint author), NASA, Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. NR 4 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0193-2 J9 PROC SPIE PY 2016 VL 9907 AR 99070U DI 10.1117/12.2231789 PG 5 WC Engineering, Aerospace; Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Engineering; Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BG6DE UT WOS:000390024400022 ER PT S AU Matter, A Lopez, B Antonelli, P Lehmitz, M Bettonvil, F Beckmann, U Lagarde, S Jaffe, W Petrov, RG Betio, P Millour, F Robbe-Dubois, S Glindemann, A Bristow, P Schoeller, M Lanz, T Henning, F Weigelt, G Heininger, M Morel, S Cruzalebes, P 'Meisenheimer, K Hafferbert, R Wolf, S Bresson, Y Agocs, T Allouche, F Augereau, JC Avila, G Ballet, C Behrend, J Van Belle, G Berger, JP van Bockel, R Bourget, P Brast, R Clausse, JM Connot, C Conzelmann, R Csepany, G Danchi, WC Delbo, M Dominik, C van Duin, A Elswijk, E Fantei, Y Finger, G Gabasch, A Gonte, F Graser, U Gunton, F Guniat, S De Haan, M Haguonauer, P Hanenburg, H Hofmann, KH Hogerheijde, M ter Horst, R Hron, O Hummel, C Isderd, J Ives, D Jakob, G Jasko, A Jolley, P Kiraly, S Kragt, J Kroener, T Kroes, G Kuindersma, S Labadie, L Laun, W Leinert, C Lizon, JL Lucuix, C Marcotto, A Martinache, F Martinot-Lagarde, G Mauclert, N Mehrgan, L Meilland, A Mellein, M Menardi, S Merand, A Neumann, U Nussbaum, E Ottogalli, S Palsa, R Panduro, J Pantin, F Percheron, I Duc, TP Pott, JU Pozna, F Roelfsema, R Rupprecht, G Schertl, D Schmidt, C Schuil, M Spang, A Stegmeier, J Tromp, N Vakili, F Vannier, M Wagner, K Venema, L Woillez, J AF Matter, A. Lopez, B. Antonelli, P. Lehmitz, M. Bettonvil, F. Beckmann, U. Lagarde, S. Jaffe, W. Petrov, R. G. Betio, P. Millour, F. Robbe-Dubois, S. Glindemann, A. Bristow, P. Schoeller, M. Lanz, T. Henning, F. Weigelt, G. Heininger, M. Morel, S. Cruzalebes, P. 'Meisenheimer, K. Hafferbert, R. Wolf, S. Bresson, Y. Agocs, T. Allouche, F. Augereau, J. -C. Avila, G. Ballet, C. Behrend, J. Van Belle, G. Berger, J. -P. van Bockel, R. Bourget, P. Brast, R. Clausse, J. -M. Connot, C. Conzelmann, R. Csepany, G. Danchi, W. C. Delbo, M. Dominik, C. van Duin, A. Elswijk, E. Fantei, Y. Finger, G. Gabasch, A. Gonte, F. Graser, U. Gunton, F. Guniat, S. De Haan, M. Haguonauer, P. Hanenburg, H. Hofmann, K. -H. Hogerheijde, M. ter Horst, R. Hron, O. Hummel, C. Isderd, J. Ives, D. Jakob, G. Jasko, A. Jolley, P. Kiraly, S. Kragt, J. Kroener, T. Kroes, G. Kuindersma, S. Labadie, L. Laun, W. Leinert, C. Lizon, J. -L. Lucuix, C. Marcotto, A. Martinache, F. Martinot-Lagarde, G. Mauclert, N. Mehrgan, L. Meilland, A. Mellein, M. Menardi, S. Merand, A. Neumann, U. Nussbaum, E. Ottogalli, S. Palsa, R. Panduro, J. Pantin, F. Percheron, I. Duc, T. Phan Pott, J. -U. Pozna, F. Roelfsema, R. Rupprecht, G. Schertl, D. Schmidt, C. Schuil, M. Spang, A. Stegmeier, J. Tromp, N. Vakili, F. Vannier, M. Wagner, K. Venema, L. Woillez, J. BE Malbet, F CreechEakman, MJ Tuthill, PG TI An overview of the mid-infrared spectro-interferometer MATISSE: science, concept, and current status SO OPTICAL AND INFRARED INTERFEROMETRY AND IMAGING V SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Optical and Infrared Interferometry and Imaging V CY JUN 27-JUL 01, 2016 CL Edinburgh, SCOTLAND SP SPIE DE Astrophysics; Long-baseline interferometry; Infrared; Very Large Telescope Interferometer; MATISSE ID VLTI; INSTRUMENT; DISKS; STARS; MIDI AB MATISSE is the second-generation mid-infrared spectrograph and imager for the Very Large Telescope Interferometer (VLTI) at Paranal. This new interferometric instrument will allow significant advances by opening new avenues in various fundamental research fields: studying the planet-forming region of disks around young stellar objects, understanding the surface structures and mass loss phenomena affecting evolved stars, and probing the environments of black holes in active galactic nuclei. As a first breakthrough, MATISSE will enlarge the spectral domain of current optical interferometers by offering the L and M bands in addition to the N band. This will open a wide wavelength domain, ranging from 2.8 to 13 mu m, exploring angular scales as small as 3 mas (L band) / 10 mas (N band). As a second breakthrough, MATISSE will allow mid-infrared imaging - closure-phase aperture-synthesis imaging - with up to four Unit Telescopes (UT) or Auxiliary Telescopes (AT) of the VLTI. Moreover, MATISSE will offer a spectral resolution range from R similar to 30 to R similar to 5000. Here, we present one of the main science objectives, the study of protoplanetary disks, that has driven the instrument design and motivated several VLTI upgrades (GRA4MAT and NAOMI). We introduce the physical concept of MATISSE including a description of the signal on the detectors and an evaluation of the expected performances. We also discuss the current status of the MATISSE instrument, which is entering its testing phase, and the foreseen schedule for the next two years that will lead to the first light at Paranal. C1 [Matter, A.; Lopez, B.; Antonelli, P.; Lagarde, S.; Petrov, R. G.; Betio, P.; Millour, F.; Robbe-Dubois, S.; Lanz, T.; Morel, S.; Cruzalebes, P.; Bresson, Y.; Allouche, F.; Ballet, C.; Clausse, J. -M.; Delbo, M.; Fantei, Y.; Gunton, F.; Marcotto, A.; Martinache, F.; Martinot-Lagarde, G.; Mauclert, N.; Meilland, A.; Ottogalli, S.; Spang, A.; Vakili, F.; Vannier, M.] Univ Cote Azur, Observ Cote Azur, CNRS, Lab Lagrange, Blvd Observ,CS 34229, F-06304 Nice, France. [Lehmitz, M.; Henning, F.; 'Meisenheimer, K.; Hafferbert, R.; van Bockel, R.; Graser, U.; Kroener, T.; Laun, W.; Leinert, C.; Mellein, M.; Neumann, U.; Panduro, J.; Pott, J. -U.; Wagner, K.] Max Planck Inst Astron, Heidelberg, Germany. [Bettonvil, F.; Agocs, T.; van Duin, A.; Elswijk, E.; De Haan, M.; ter Horst, R.; Isderd, J.; Kroes, G.; Kuindersma, S.; Roelfsema, R.; Schuil, M.; Tromp, N.; Venema, L.] NOVA ASTRON, Dwingeloo, Netherlands. [Beckmann, U.; Weigelt, G.; Heininger, M.; Behrend, J.; Connot, C.; Hofmann, K. -H.; Kragt, J.; Nussbaum, E.; Schertl, D.] Max Planck Inst Radioastron, Bonn, Germany. [Jaffe, W.; Hogerheijde, M.; Venema, L.] Leiden Univ, Leiden Observ, NL-2300 RA Leiden, Netherlands. [Glindemann, A.; Bristow, P.; Schoeller, M.; Avila, G.; Bourget, P.; Brast, R.; Conzelmann, R.; Finger, G.; Gabasch, A.; Gonte, F.; Guniat, S.; Haguonauer, P.; Hanenburg, H.; Hummel, C.; Ives, D.; Jakob, G.; Jolley, P.; Lizon, J. -L.; Lucuix, C.; Mehrgan, L.; Menardi, S.; Merand, A.; Palsa, R.; Percheron, I.; Duc, T. Phan; Pozna, F.; Rupprecht, G.; Schmidt, C.; Stegmeier, J.; Woillez, J.] European Southern Observ, Garching, Germany. [Wolf, S.] Univ Kiel, Inst Theoret Phys & Astrophys, Kiel, Germany. [Augereau, J. -C.; Berger, J. -P.] Unive Grenoble Alpes, CNRS, IPAG, Grenoble, France. [Van Belle, G.; Jasko, A.; Kiraly, S.] Lowell Observ, 1400 W Mars Hill Rd, Flagstaff, AZ 86001 USA. [Csepany, G.] Konkoly Thege Miklos Astron Inst, MTA Res Ctr Astron & Earth Sci, Budapest, Hungary. [Danchi, W. C.] NASA, Goddard Space Flight Ctr, Greenbelt, MD USA. [Dominik, C.] Univ Amsterdam, Sterrenkundig Inst Anton Pannekoek, NL-1012 WX Amsterdam, Netherlands. [Hron, O.] Univ Vienna, Inst Astrophys, A-1010 Vienna, Austria. [Labadie, L.] Univ Cologne, Inst Phys, Cologne, Germany. [Pantin, F.] Univ Paris Diderot, Lab AIM, CEA, IRFU,Serv Astrophys,CEA Saclay,DSM,CNRS, Gif Sur Yvette, France. RP Matter, A (reprint author), Univ Cote Azur, Observ Cote Azur, CNRS, Lab Lagrange, Blvd Observ,CS 34229, F-06304 Nice, France. EM Alexis.Matter@oca.eu NR 13 TC 0 Z9 0 U1 1 U2 1 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0193-2 J9 PROC SPIE PY 2016 VL 9907 AR UNSP 99070A DI 10.1117/12.2233052 PG 11 WC Engineering, Aerospace; Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Engineering; Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BG6DE UT WOS:000390024400007 ER PT S AU Mennesson, B Defrere, D Nowak, M Hinz, P Millan-Gabet, R Absil, O Bailey, V Bryden, G Danchi, W Kennedy, GM Marion, L Roberge, A Serabyn, E Skemer, AJ Stapelfeldt, K Weinberger, AJ Wyatt, M AF Mennesson, Bertrand Defrere, Denis Nowak, Matthias Hinz, Philip Millan-Gabet, Rafael Absil, Olivier Bailey, Vanessa Bryden, Geoffrey Danchi, William Kennedy, Grant M. Marion, Lindsay Roberge, Aki Serabyn, Eugene Skemer, Andy J. Stapelfeldt, Karl Weinberger, Alycia J. Wyatt, Mark BE Malbet, F CreechEakman, MJ Tuthill, PG TI Making high accuracy null depth measurements for the LBTI Exozodi survey SO OPTICAL AND INFRARED INTERFEROMETRY AND IMAGING V SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Optical and Infrared Interferometry and Imaging V CY JUN 27-JUL 01, 2016 CL Edinburgh, SCOTLAND SP SPIE DE Exozodiacal light; nulling; mid-infrared; high contrast; interferometry; direct imaging; exoplanets ID EXO-EARTHS; TELESCOPE AB The characterization of exozodiacal light emission is both important for the understanding of planetary systems evolution and for the preparation of future space missions aiming to characterize low mass planets in the habitable zone of nearby main sequence stars. The Large Binocular Telescope Interferometer (LBTI) exozodi survey aims at providing a ten-fold improvement over current state of the art, measuring dust emission levels down to a typical accuracy of similar to 12 zodis per star, for a representative ensemble of similar to 30+ high priority targets. Such measurements promise to yield a final accuracy of about 2 zodis on the median exozodi level of the targets sample. Reaching a 1. measurement uncertainty of 12 zodis per star corresponds to measuring interferometric cancellation ("null") levels, i.e visibilities at the few 100 ppm uncertainty level. We discuss here the challenges posed by making such high accuracy mid-infrared visibility measurements from the ground and present the methodology we developed for achieving current best levels of 500 ppm or so. We also discuss current limitations and plans for enhanced exozodi observations over the next few years at LBTI. C1 [Mennesson, Bertrand; Bryden, Geoffrey; Serabyn, Eugene; Stapelfeldt, Karl] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Defrere, Denis; Absil, Olivier] Univ Liege, Inst Astrophys & Geophys, 19c Allee Six Aout, B-4000 Sart Tilman Par Liege, Belgium. [Nowak, Matthias] Univ Paris Diderot, UPMC, CNRS, LESIA,Observ Paris, 5 Pl Jules Janssen, F-92195 Meudon, France. [Hinz, Philip; Bailey, Vanessa; Skemer, Andy J.] Univ Arizona, Dept Astron, Steward Observ, 933 N Cherry Ave, Tucson, AZ 85721 USA. [Millan-Gabet, Rafael] CALTECH, NASA, Exoplanet Sci Inst, 770 South Wilson Ave, Pasadena, CA 91125 USA. [Danchi, William; Roberge, Aki] NASA, Goddard Space Flight Ctr, Exoplanets & Stellar Astrophys Lab, Code 667, Greenbelt, MD 20771 USA. [Kennedy, Grant M.; Wyatt, Mark] Univ Cambridge, Inst Astron, Madingley Rd, Cambridge CB3 0HA, England. [Weinberger, Alycia J.] Carnegie Inst Sci, Dept Terr Magnetism, 5241 Broad Branch Rd NW, Washington, DC 20015 USA. RP Mennesson, B (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Bertrand.Mennesson@jpl.nasa.gov OI Kennedy, Grant/0000-0001-6831-7547; Bailey, Vanessa/0000-0002-5407-2806 NR 15 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0193-2 J9 PROC SPIE PY 2016 VL 9907 AR 99070X DI 10.1117/12.2231839 PG 12 WC Engineering, Aerospace; Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Engineering; Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BG6DE UT WOS:000390024400024 ER PT S AU Monnier, JD Ireland, MJ Kraus, S Baron, F Creech-Eakman, M Dong, RB Isella, A Merand, A Michael, E Minardi, S Mozurkewich, D Petrov, R Rinehard, S ten Brummelaar, T Vasisht, G Wishnow, E Young, J Zhu, ZH AF Monnier, John D. Ireland, Michael J. Kraus, Stefan Baron, Fabien Creech-Eakman, Michelle Dong, Ruobing Isella, Andrea Merand, Antoine Michael, Ernest Minardi, Stefano Mozurkewich, David Petrov, Romain Rinehard, Stephen ten Brummelaar, Theo Vasisht, Gautum Wishnow, Ed Young, John Zhu, Zhaohuan BE Malbet, F CreechEakman, MJ Tuthill, PG TI Architecture design study and technology road map for the Planet Formation Imager (PFI) SO OPTICAL AND INFRARED INTERFEROMETRY AND IMAGING V SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Optical and Infrared Interferometry and Imaging V CY JUN 27-JUL 01, 2016 CL Edinburgh, SCOTLAND SP SPIE DE interferometry; mid-infrared; exoplanets; planet formation; astronomy; facilities; imaging; infrared ID OBSERVATIONAL SIGNATURES; DISKS; INTERFEROMETER; RADIATION AB The Planet Formation Imager (PFI) Project has formed a Technical Working Group (TWG) to explore possible facility architectures to meet the primary PFI science goal of imaging planet formation in situ in nearby star-forming regions. The goals of being sensitive to dust emission on solar system scales and resolving the Hill-sphere around forming giant planets can best be accomplished through sub-milliarcsecond imaging in the thermal infrared. Exploiting the 8-13 micron atmospheric window, a ground-based long-baseline interferometer with approximately 20 apertures including 10km baselines will have the necessary resolution to image structure down 0.1 milliarcseconds (0.014 AU) for T Tauri disks in Taurus. Even with large telescopes, this array will not have the sensitivity to directly track fringes in the mid-infrared for our prime targets and a fringe tracking system will be necessary in the near-infrared. While a heterodyne architecture using modern mid-IR laser comb technology remains a competitive option (especially for the intriguing 24 and 40 mu m atmospheric windows), the prioritization of 3-5 mu m observations of CO/H2O vibrotational levels by the PFI-Science Working Group (SWG) pushes the TWG to require vacuum pipe beam transport with potentially cooled optics. We present here a preliminary study of simulated L- and N-band PFI observations of a realistic 4-planet disk simulation, finding 21x2.5m PFI can easily detect the accreting protoplanets in both L and N-band but can see non-accreting planets only in L band. We also find that even an ambitious PFI will lack sufficient surface brightness sensitivity to image details of the fainter emission from dust structures beyond similar to 5 AU, unless directly illuminated or heated by local energy sources. That said, the utility of PFI at N-band is highly dependent on the stage of planet formation in the disk and we require additional systematic studies in conjunction with the PFI-SWG to better understand the science capabilities of PFI, including the potential to resolve protoplanetary disks in emission lines to measure planet masses using position-velocity diagrams. We advocate for a specific technology road map in order to reduce the current cost driver (telescopes) and to validate high accuracy fringe tracking and high dynamic range imaging at L, M band. In conclusion, no technology show-stoppers have been identified for PFI to date, however there is high potential for breakthroughs in medium-aperture (4-m class) telescopes architecture that could reduce the cost of PFI by a factor of 2 or more. C1 [Monnier, John D.] Univ Michigan, Ann Arbor, MI 48109 USA. [Ireland, Michael J.] Australian Natl Univ, Res Sch Astron & Astrophys, Canberra, ACT 2611, Australia. [Kraus, Stefan] Univ Exeter, Exeter EX4 4QJ, Devon, England. [Baron, Fabien] Georgia State Univ, Atlanta, GA 30303 USA. [Creech-Eakman, Michelle] New Mexico Inst Min & Technol, Socorro, NM USA. [Dong, Ruobing] Univ Calif Berkeley, Berkeley, CA 94720 USA. [Isella, Andrea] Rice Univ, Houston, TX 77251 USA. [Merand, Antoine] European Southern Observ, Santiago, Chile. [Michael, Ernest] Univ Chile, Santiago, Region Metropol, Chile. [Minardi, Stefano] Univ Jena, D-07745 Jena, Germany. [Mozurkewich, David] Seabrook Engn, Seabrook, MD USA. [Petrov, Romain] Univ Nice, F-06108 Nice 2, France. [Rinehard, Stephen] NASA GSFC, Greenbelt, MD USA. [ten Brummelaar, Theo] Georgia State Univ, CHARA Array, Atlanta, GA 30303 USA. [Vasisht, Gautum] Jet Prop Lab, Pasadena, CA USA. [Wishnow, Ed] Univ Calif Berkeley, Berkeley, CA 94720 USA. [Young, John] Univ Cambridge, Cambridge CB2 1TN, England. [Zhu, Zhaohuan] Princeton Univ, Princeton, NJ 08544 USA. RP Monnier, JD (reprint author), Univ Michigan, Ann Arbor, MI 48109 USA. EM monnier@umich.edu NR 14 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0193-2 J9 PROC SPIE PY 2016 VL 9907 AR 99071O DI 10.1117/12.2233311 PG 12 WC Engineering, Aerospace; Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Engineering; Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BG6DE UT WOS:000390024400048 ER PT S AU Rinehart, SA Savini, G Holland, W Absil, O Defrere, D Spencer, L Leisawitz, D Rizzo, M Juanola-Paramon, R Mozurkewich, D AF Rinehart, S. A. Savini, G. Holland, W. Absil, O. Defrere, D. Spencer, L. Leisawitz, D. Rizzo, M. Juanola-Paramon, R. Mozurkewich, D. BE Malbet, F CreechEakman, MJ Tuthill, PG TI The Path to Interferometry in Space SO OPTICAL AND INFRARED INTERFEROMETRY AND IMAGING V SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Optical and Infrared Interferometry and Imaging V CY JUN 27-JUL 01, 2016 CL Edinburgh, SCOTLAND SP SPIE DE Interferometry; Infrared; Nulling ID INFRARED INTERFEROMETER; ANGULAR RESOLUTION; PLANETS; TELESCOPE; FOMALHAUT; PROJECT; SEARCH; IMAGER; STARS; LIFE AB For over two decades, astronomers have considered the possibilities for interferometry in space. The first of these missions was the Space Interferometry Mission (SIM), but that was followed by missions for studying exoplanets (e.g Terrestrial Planet Finder, Darwin), and then far-infrared interferometers (e.g. the Space Infrared Interferometric Telescope, the Far-Infrared Interferometer). Unfortunately, following the cancellation of SIM, the future for space-based interferometry has been in doubt, and the interferometric community needs to reevaluate the path forward. While interferometers have strong potential for scientific discovery, there are technological developments still needed, and continued maturation of techniques is important for advocacy to the broader astronomical community. We review the status of several concepts for space-based interferometry, and look for possible synergies between missions oriented towards different science goals. C1 [Rinehart, S. A.; Leisawitz, D.; Juanola-Paramon, R.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Savini, G.] UCL, London WC1E 6BT, England. [Holland, W.] Univ Edinburgh, Edinburgh EH8 9YL, Midlothian, Scotland. [Absil, O.] Univ Liege, B-4000 Liege, Belgium. [Defrere, D.] Univ Liege, STAR Inst, B-4000 Liege, Belgium. [Spencer, L.] Univ Lethbridge, Lethbridge, AB T1K 3M4, Canada. [Rizzo, M.] Univ Maryland, College Pk, MD USA. [Mozurkewich, D.] Seabrook Engn, Seabrook, MD USA. RP Rinehart, SA (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. EM Stephen.A.Rinehart@nasa.gov OI Savini, Giorgio/0000-0003-4449-9416 NR 45 TC 0 Z9 0 U1 2 U2 2 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0193-2 J9 PROC SPIE PY 2016 VL 9907 AR 99070S DI 10.1117/12.2231754 PG 15 WC Engineering, Aerospace; Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Engineering; Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BG6DE UT WOS:000390024400020 ER PT S AU Scott, NJ Howell, SB Horch, EP AF Scott, Nicholas J. Howell, Steve B. Horch, Elliott P. BE Malbet, F CreechEakman, MJ Tuthill, PG TI Differential speckle and wide-field imaging for the Gemini-North and WIYN telescopes SO OPTICAL AND INFRARED INTERFEROMETRY AND IMAGING V SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Optical and Infrared Interferometry and Imaging V CY JUN 27-JUL 01, 2016 CL Edinburgh, SCOTLAND SP SPIE DE Instrumentation; Speckle interferometry; High resolution imaging ID BINARY STARS; KEPLER AB Two new instruments are currently being built for the Gemini-North and WIYN telescopes. They are based on the existing DSSI (Differential Speckle Survey Instrument), but the new dual-channel instruments will have both speckle and "wide-field" imaging capabilities. Nearly identical copies of the instrument will be installed as a public access permanent loan at the Gemini-N and WIYN telescopes. Many exoplanet targets will come from the NASA K2 and TESS missions. The faint limiting magnitude, for speckle observations, will remain around 16 to 17th magnitude depending on observing conditions, while wide-field, high speed imaging should be able to go to 21+. For Gemini, the instrument will be remotely operable from either the mid-level facility at Hale Pohaku or the remote operations base in Hilo. C1 [Scott, Nicholas J.; Howell, Steve B.] NASA, Ames Res Ctr, Mountain View, CA 94035 USA. [Horch, Elliott P.] Southern Connecticut State Univ, Dept Phys, 501 Crescent St, New Haven, CT USA. RP Scott, NJ (reprint author), NASA, Ames Res Ctr, Mountain View, CA 94035 USA. EM n.j.scott@nasa.gov; steve.b.howell@nasa.gov; horche2@southernct.edu NR 6 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0193-2 J9 PROC SPIE PY 2016 VL 9907 AR 99072R DI 10.1117/12.2231365 PG 8 WC Engineering, Aerospace; Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Engineering; Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BG6DE UT WOS:000390024400073 ER PT S AU ten Brummelaar, TA Gies, DG McAlister, HA Ridgway, ST Sturmann, J Sturmann, L Schaefer, GH Turner, NH Farrington, CD Scott, NJ Monnier, JD Ireland, MJ AF ten Brummelaar, T. A. Gies, D. G. McAlister, H. A. Ridgway, S. T. Sturmann, J. Sturmann, L. Schaefer, G. H. Turner, N. H. Farrington, C. D. Scott, N. J. Monnier, J. D. Ireland, M. J. BE Malbet, F CreechEakman, MJ Tuthill, PG TI An Update on the CHARA Array SO OPTICAL AND INFRARED INTERFEROMETRY AND IMAGING V SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Optical and Infrared Interferometry and Imaging V CY JUN 27-JUL 01, 2016 CL Edinburgh, SCOTLAND SP SPIE DE Optical ground based interferometry; Center for High Angular Resolution Astronomy AB The CHARA Array, operated by Georgia State University, is located at Mount Wilson Observatory just north of Los Angeles in California. The CHARA consortium includes many groups, including LIESA in Paris, Observatoire de la Cote d'Azur, the University of Michigan, Sydney University, the Australian National University, the NASA Exoplanet Science Institute, and most recently the University of Exeter. The CHARA Array is a six-element optical/NIR interferometer, and for the time being at least, has the largest operational baselines in the world. In this paper we will give a brief introduction to the array infrastructure with a focus on our Adaptive Optics program, and then discuss current funding as well as opportunities of funding in the near future. C1 [ten Brummelaar, T. A.; Sturmann, J.; Sturmann, L.; Schaefer, G. H.; Turner, N. H.; Farrington, C. D.] Georgia State Univ, CHARA Array, Mt Wilson, CA 91012 USA. [Gies, D. G.; McAlister, H. A.] Georgia State Univ, Ctr High Angular Resolut Astron, POB 4106, Atlanta, GA 30302 USA. [Ridgway, S. T.; Scott, N. J.] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Monnier, J. D.] Univ Michigan, Dept Astron, Ann Arbor, MI 48109 USA. [Ireland, M. J.] Australian Natl Univ, Res Sch Astron & Astrophys, Mt Stromlo Observ, Weston, ACT 2611, Australia. RP ten Brummelaar, TA (reprint author), Georgia State Univ, CHARA Array, Mt Wilson, CA 91012 USA. EM theo@chara-array.org NR 22 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0193-2 J9 PROC SPIE PY 2016 VL 9907 AR 990703 DI 10.1117/12.2232125 PG 7 WC Engineering, Aerospace; Astronomy & Astrophysics; Instruments & Instrumentation; Optics SC Engineering; Astronomy & Astrophysics; Instruments & Instrumentation; Optics GA BG6DE UT WOS:000390024400003 ER PT S AU Doll, P Douville, H Guntner, A Schmied, HM Wada, Y AF Doell, Petra Douville, Herve Guentner, Andreas Schmied, Hannes Mueller Wada, Yoshihide BE Cazenave, A Champollion, N Benveniste, J Chen, J TI Modelling Freshwater Resources at the Global Scale: Challenges and Prospects SO REMOTE SENSING AND WATER RESOURCES SE Space Science Series of ISSI LA English DT Proceedings Paper CT Workshop on Remote Sensing and Water Resources held as part of the International-Space-Science-Institute (ISSI) Earth Observation Programme CY OCT, 2014 CL Bern, SWITZERLAND SP Int Space Sci Inst DE Global hydrological model; Climate data; Water abstraction; Model uncertainty; Calibration; Remote sensing data ID CLIMATE-CHANGE IMPACT; HYDROLOGICAL MODEL; LAND-SURFACE; SOIL-MOISTURE; PARAMETER-ESTIMATION; DATA ASSIMILATION; RIVER RUNOFF; GRACE DATA; GROUNDWATER; CYCLE AB Quantification of spatially and temporally resolved water flows and water storage variations for all land areas of the globe is required to assess water resources, water scarcity and flood hazards, and to understand the Earth system. This quantification is done with the help of global hydrological models (GHMs). What are the challenges and prospects in the development and application of GHMs? Seven important challenges are presented. (1) Data scarcity makes quantification of human water use difficult even though significant progress has been achieved in the last decade. (2) Uncertainty of meteorological input data strongly affects model outputs. (3) The reaction of vegetation to changing climate and CO2 concentrations is uncertain and not taken into account in most GHMs that serve to estimate climate change impacts. (4) Reasons for discrepant responses of GHMs to changing climate have yet to be identified. (5) More accurate estimates of monthly time series of water availability and use are needed to provide good indicators of water scarcity. (6) Integration of gradient-based groundwater modelling into GHMs is necessary for a better simulation of groundwater-surface water interactions and capillary rise. (7) Detection and attribution of human interference with freshwater systems by using GHMs are constrained by data of insufficient quality but also GHM uncertainty itself. Regarding prospects for progress, we propose to decrease the uncertainty of GHM output by making better use of in situ and remotely sensed observations of output variables such as river discharge or total water storage variations by multi-criteria validation, calibration or data assimilation. Finally, we present an initiative that works towards the vision of hyperresolution global hydrological modelling where GHM outputs would be provided at a 1-km resolution with reasonable accuracy. C1 [Doell, Petra; Schmied, Hannes Mueller] Goethe Univ Frankfurt, Inst Phys Geog, D-60629 Frankfurt, Germany. [Douville, Herve] Meteo France, Ctr Natl Recherches Meteorol, 42 Av Coriolis, F-31057 Toulouse, France. [Guentner, Andreas] German Res Ctr Geosci, Helmholtz Ctr Potsdam, D-14473 Potsdam, Germany. [Wada, Yoshihide] Columbia Univ, Ctr Climate Syst Res, 2880 Broadway, New York, NY 10025 USA. [Wada, Yoshihide] NASA, Goddard Inst Space Studies, 2880 Broadway, New York, NY 10025 USA. [Wada, Yoshihide] Univ Utrecht, Fac Geosci, Dept Phys Geog, Heidelberglaan 2, NL-3584 CS Utrecht, Netherlands. RP Doll, P (reprint author), Goethe Univ Frankfurt, Inst Phys Geog, D-60629 Frankfurt, Germany. EM p.doell@em.uni-frankfurt.de; herve.douville@meteo.fr; guentner@gfz-potsdam.de; y.wada@uu.nl OI Muller Schmied, Hannes/0000-0001-5330-9923 NR 115 TC 0 Z9 0 U1 2 U2 2 PU SPRINGER PI DORDRECHT PA PO BOX 17, 3300 AA DORDRECHT, NETHERLANDS SN 1385-7525 BN 978-3-319-32449-4; 978-3-319-32448-7 J9 SPACE SCI SER ISSI PY 2016 VL 55 BP 5 EP 31 DI 10.1007/978-3-319-32449-4_2 PG 27 WC Remote Sensing; Water Resources SC Remote Sensing; Water Resources GA BG6KK UT WOS:000390418000002 ER PT S AU Chen, JL Famigliett, JS Scanlon, BR Rodell, M AF Chen, Jianli Famigliett, James S. Scanlon, Bridget R. Rodell, Matthew BE Cazenave, A Champollion, N Benveniste, J Chen, J TI Groundwater Storage Changes: Present Status from GRACE Observations SO REMOTE SENSING AND WATER RESOURCES SE Space Science Series of ISSI LA English DT Proceedings Paper CT Workshop on Remote Sensing and Water Resources held as part of the International-Space-Science-Institute (ISSI) Earth Observation Programme CY OCT, 2014 CL Bern, SWITZERLAND SP Int Space Sci Inst DE Groundwater; GRACE; Satellite gravity; Groundwater depletion; Land surface model; Well data ID CLIMATE EXPERIMENT GRACE; SATELLITE GRAVITY MEASUREMENTS; HIGH-PLAINS AQUIFER; SEA-LEVEL RISE; MIDDLE-EAST; ICE-SHEET; DEPLETION; WATER; RECOVERY; SUSTAINABILITY AB Satellite gravity measurements from the Gravity Recovery and Climate Experiment (GRACE) provide quantitative measurement of terrestrial water storage (TWS) changes with unprecedented accuracy. Combining GRACE-observed TWS changes and independent estimates of water change in soil and snow and surface reservoirs offers a means for estimating groundwater storage change. Since its launch in March 2002, GRACE time-variable gravity data have been successfully used to quantify long-term groundwater storage changes in different regions over the world, including northwest India, the High Plains Aquifer and the Central Valley in the USA, the North China Plain, Middle East, and southern Murray-Darling Basin in Australia, where groundwater storage has been significantly depleted in recent years (or decades). It is difficult to rely on in situ groundwater measurements for accurate quantification of large, regional-scale groundwater storage changes, especially at long timescales due to inadequate spatial and temporal coverage of in situ data and uncertainties in storage coefficients. The now nearly 13 years of GRACE gravity data provide a successful and unique complementary tool for monitoring and measuring groundwater changes on a global and regional basis. Despite the successful applications of GRACE in studying global groundwater storage change, there are still some major challenges limiting the application and interpretation of GRACE data. In this paper, we present an overview of GRACE applications in groundwater studies and discuss if and how the main challenges to using GRACE data can be addressed. C1 [Chen, Jianli] Univ Texas Austin, Ctr Space Res, Austin, TX 78759 USA. [Famigliett, James S.] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. [Famigliett, James S.] Univ Calif Irvine, Dept Earth Syst Sci, Irvine, CA 92697 USA. [Scanlon, Bridget R.] Univ Texas Austin, Jackson Sch Geosci, Bur Econ Geol, Austin, TX 78759 USA. [Rodell, Matthew] NASA, Goddard Space Flight Ctr, Hydrol Sci Lab, Greenbelt, MD 20771 USA. RP Chen, JL (reprint author), Univ Texas Austin, Ctr Space Res, Austin, TX 78759 USA. EM chen@csr.utexas.edu RI Scanlon, Bridget/A-3105-2009 OI Scanlon, Bridget/0000-0002-1234-4199 NR 70 TC 1 Z9 1 U1 0 U2 0 PU SPRINGER PI DORDRECHT PA PO BOX 17, 3300 AA DORDRECHT, NETHERLANDS SN 1385-7525 BN 978-3-319-32449-4; 978-3-319-32448-7 J9 SPACE SCI SER ISSI PY 2016 VL 55 BP 207 EP 227 DI 10.1007/978-3-319-32449-4_9 PG 21 WC Remote Sensing; Water Resources SC Remote Sensing; Water Resources GA BG6KK UT WOS:000390418000009 ER PT S AU Wada, Y AF Wada, Yoshihide BE Cazenave, A Champollion, N Benveniste, J Chen, J TI Modeling Groundwater Depletion at Regional and Global Scales: Present State and Future Prospects SO REMOTE SENSING AND WATER RESOURCES SE Space Science Series of ISSI LA English DT Proceedings Paper CT Workshop on Remote Sensing and Water Resources held as part of the International-Space-Science-Institute (ISSI) Earth Observation Programme CY OCT, 2014 CL Bern, SWITZERLAND SP Int Space Sci Inst DE Groundwater depletion (GWD); Climate variability; Socioeconomic development; Water scarcity; Sustainability; Projections ID WORLD WATER-RESOURCES; SEA-LEVEL RISE; SHARED SOCIOECONOMIC PATHWAYS; NORTH-AMERICAN DROUGHT; LAND-SURFACE MODEL; US HIGH-PLAINS; CLIMATE-CHANGE; FRESH-WATER; MULTIMODEL ENSEMBLE; HUMAN APPROPRIATION AB Except for frozen water in ice and glaciers, groundwater is the world's largest distributed store of freshwater and has strategic importance to global food and water security. In this paper, the most recent advances quantifying groundwater depletion (GWD) are comprehensively reviewed. This paper critically evaluates the recently advanced modeling approaches estimating GWD at regional and global scales, and the evidence of feedbacks to the Earth system including sea-level rise associated with GWD. Finally, critical challenges and opportunities in the use of groundwater are identified for the adaption to growing food demand and uncertain climate. C1 [Wada, Yoshihide] NASA, Goddard Inst Space Studies, 2880 Broadway, New York, NY 10025 USA. [Wada, Yoshihide] Columbia Univ, Ctr Climate Syst Res, 2880 Broadway, New York, NY 10025 USA. [Wada, Yoshihide] Univ Utrecht, Dept Phys Geog, NL-3584 CS Utrecht, Netherlands. RP Wada, Y (reprint author), NASA, Goddard Inst Space Studies, 2880 Broadway, New York, NY 10025 USA.; Wada, Y (reprint author), Columbia Univ, Ctr Climate Syst Res, 2880 Broadway, New York, NY 10025 USA.; Wada, Y (reprint author), Univ Utrecht, Dept Phys Geog, NL-3584 CS Utrecht, Netherlands. EM y.wada@uu.nl NR 195 TC 0 Z9 0 U1 0 U2 0 PU SPRINGER PI DORDRECHT PA PO BOX 17, 3300 AA DORDRECHT, NETHERLANDS SN 1385-7525 BN 978-3-319-32449-4; 978-3-319-32448-7 J9 SPACE SCI SER ISSI PY 2016 VL 55 BP 229 EP 261 DI 10.1007/978-3-319-32449-4_10 PG 33 WC Remote Sensing; Water Resources SC Remote Sensing; Water Resources GA BG6KK UT WOS:000390418000010 ER PT S AU Puschell, JJ Lock, R AF Puschell, Jeffery J. Lock, Robert BE Ardanuy, PE Puschell, JJ TI Areosynchronous Weather Imager SO REMOTE SENSING SYSTEM ENGINEERING VI SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Remote Sensing System Engineering VI as a part of the SPIE Optics+Photonics Symposium on Remote Sensing Track of Optical Engineering+Applications CY AUG 31-SEP 01, 2016 CL San Diego, CA SP SPIE DE remote sensing; environmental satellite system; Mars; areosynchronous Mars orbit AB Mars is characterized by rapidly changing, poorly understood weather that is a concern for future human missions. Future Areosynchronous Mars Orbit (AMO) communication satellites offer possible platforms for Mars weather imagers similar to the geosynchronous Earth orbit (GEO) weather imagers that have been observing Earth since 1966. This paper describes an AReosynchronous Environmental Suite (ARES) that includes two imagers: one with two emissive infrared bands (10.8 mu m and 12.0 mu m) at 4 km resolution and the other with three VNIR bands (500 nm, 700 nm, 900 nm) at 1 km resolution. ARES stares at Mars and provides full disk coverage as fast as every 40 sec in the VNIR bands and every 2 min in the emissive bands with good sensitivity (SNR similar to 200 in the VNIR for typical radiances and NEDT similar to 0.2K at 180 K scene temperature in the emissive infrared). ARES size, mass, power and data rate characteristics are compatible with expectations for hosted payloads onboard future AMO communication satellites. Nevertheless, more work is needed to optimize ARES for future missions, especially in terms of trades between data rate, full disk coverage rate, sensitivity, number of spectral bands and spatial resolution and in study of approaches for maintaining accurate line of sight knowledge during data collection. C1 [Puschell, Jeffery J.] Raytheon Space & Airborne Syst, 2000 East El Segundo Blvd,EO-E01-C150, El Segundo, CA 90245 USA. [Lock, Robert] Jet Prop Lab, Pasadena, CA USA. RP Puschell, JJ (reprint author), Raytheon Space & Airborne Syst, 2000 East El Segundo Blvd,EO-E01-C150, El Segundo, CA 90245 USA. EM jjpuschell@raytheon.com NR 12 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0345-5; 978-1-5106-0346-2 J9 PROC SPIE PY 2016 VL 9977 AR UNSP 99770E DI 10.1117/12.2242301 PG 13 WC Remote Sensing SC Remote Sensing GA BG6GG UT WOS:000390271100009 ER PT J AU Cha, E Mataric, M Fong, T AF Cha, Elizabeth Mataric, Maja Fong, Terrence GP ACM TI Nonverbal Signaling for Non-Humanoid Robots During Human-Robot Collaboration SO ELEVENTH ACM/IEEE INTERNATIONAL CONFERENCE ON HUMAN ROBOT INTERATION (HRI'16) LA English DT Proceedings Paper CT 11th ACM/IEEE International Conference on Human-Robot Interaction (HRI) CY MAR 07-10, 2016 CL Christchurch, NEW ZEALAND SP ACM, IEEE, ACM SIGCHI, ACM SIGAI, IEEE Robot & Automat Soc, HFES, AAAI, ACM SIGART AB Non-humanoid robots are becoming increasingly utilized for collaborative tasks across many domains, including industrial and service settings. Collaborative tasks between the human and robot rely on each collaborator's ability to effectively convey their mental state while accurately estimating and interpreting their partner's knowledge, intent, and actions. My research focuses on nonverbal communication signals that a non-humanoid robot can utilize during human-robot collaboration. We focus on motion, light and sound as they are commonly used communication channels across many domains and are available on most robot platforms. As a first step towards this goal, I present a completed study exploring how to use a simple multimodal light and sound signal to request help during a collaborative task. We then discuss future work to generate and utilize more complex signals to convey a variety of statuses to improve collaboration. C1 [Cha, Elizabeth; Mataric, Maja] Univ Southern Calif, Dept Comp Sci, Los Angeles, CA 90089 USA. [Fong, Terrence] NASA, Ames Res Ctr, Intelligent Robot Grp, Moffett Field, CA 94035 USA. RP Cha, E (reprint author), Univ Southern Calif, Dept Comp Sci, Los Angeles, CA 90089 USA. EM echa@usc.edu; mataric@usc.edu; terry.fong@nasa.gov NR 8 TC 0 Z9 0 U1 0 U2 0 PU ASSOC COMPUTING MACHINERY PI NEW YORK PA 1515 BROADWAY, NEW YORK, NY 10036-9998 USA BN 978-1-4673-8369-1 PY 2016 BP 601 EP 602 PG 2 WC Computer Science, Cybernetics; Robotics SC Computer Science; Robotics GA BG5YW UT WOS:000389809100151 ER PT S AU Back, TC Fairchild, SB Soukiassian, P Berger, MH Martinotti, D Douillard, L Kordesch, M Gruen, G Murray, PT Schmid, AK Chen, G Sayir, A AF Back, Tyson C. Fairchild, Steven B. Soukiassian, Patrick Berger, Marie-Helene Martinotti, Dominique Douillard, Ludovic Kordesch, Martin Gruen, Gregg Murray, P. Terrence Schmid, Andreas K. Chen, Gong Sayir, Ali GP IEEE TI Low Energy Electron Microscopy Study of Directionally Solidified LaB6 -( Zr, V)B-2 Eutectics SO 2016 29TH INTERNATIONAL VACUUM NANOELECTRONICS CONFERENCE (IVNC) SE International Vacuum Nanoelectronics Conference LA English DT Proceedings Paper CT 29th International Vacuum Nanoelectronics Conference (IVNC) CY JUL 11-15, 2016 CL Vancouver, CANADA SP IEEE, IEEE Electron Devices Soc, ZEISS, Modern Electron, Amer Vacuum Soci, Paul Scherrer Inst, Elect & Comp Engn, Univ British Columbia, Peter Wall Inst Adv Studies, Dept Elect & Comp Engn DE Low Energy Electron Microscopy; Eutectic; Lanthanum Hexaboride AB LaB6 eutectic materials show promise as a replacement for common thermionic cathode materials. This eutectic system belongs to a class of materials referred to as directionally solidified eutectics (DSEs). LaB6 DSEs consist of a LaB6 matrix with a second phase, a metal di-boride, forming cylindrical rods in the matrix. Previous investigations on this material were focused on its use as a high temperature structural material. Use as a thermionic emitter remains largely unexplored. C1 [Back, Tyson C.; Gruen, Gregg; Murray, P. Terrence] Univ Dayton Res Inst, 300 Coll Pk, Dayton, OH 45469 USA. [Back, Tyson C.; Fairchild, Steven B.; Gruen, Gregg; Murray, P. Terrence] US Air Force, Res Lab, Mat & Mfg Directorate, 3005 Hobson Way, Wright Patterson AFB, OH 45433 USA. [Soukiassian, Patrick; Martinotti, Dominique; Douillard, Ludovic] Univ Paris Sud Orsay, DSM DRECAM SPCSI, Lab Surfaces & Interfaces Mat Avances Assoc, Commissariat Energie Atom, Batiment 462, F-91191 Gif Sur Yvette, France. [Berger, Marie-Helene] Ecole Mines Paris, Ctr Mat, Evry, France. [Kordesch, Martin] Ohio Univ, Dept Phys & Astron, Athens, OH 45701 USA. [Schmid, Andreas K.; Chen, Gong] Lawrence Berkeley Natl Lab, NCEM Mol Foundry, Berkeley, CA 94720 USA. [Sayir, Ali] NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Back, TC (reprint author), Univ Dayton Res Inst, 300 Coll Pk, Dayton, OH 45469 USA.; Back, TC (reprint author), US Air Force, Res Lab, Mat & Mfg Directorate, 3005 Hobson Way, Wright Patterson AFB, OH 45433 USA. NR 6 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2164-2370 BN 978-1-5090-2419-3 J9 INT VACUUM NANOELECT PY 2016 PG 2 WC Engineering, Electrical & Electronic; Nanoscience & Nanotechnology SC Engineering; Science & Technology - Other Topics GA BG5ML UT WOS:000389543500027 ER PT J AU Liston, DB Simpson, S Wone, LR Rich, M Stone, LS AF Liston, Dorion B. Simpson, Sol Wone, Lily R. Rich, Mark Stone, Leland S. BE Spencer, SN TI Design and validation of a simple eye-tracking system SO 2016 ACM SYMPOSIUM ON EYE TRACKING RESEARCH & APPLICATIONS (ETRA 2016) LA English DT Proceedings Paper CT 9th Biennial ACM Symposium on Eye Tracking Research and Applications (ETRA) CY MAR 14-17, 2016 CL Charleston, SC SP ACM, ACM SIGGRAPH, ACM SIGCHI DE oculometric; eye position; tracking precision ID MOVEMENTS; PERCEPTION AB To address the need for portable systems to collect high-quality eye movement data for field studies, this paper shows how one might design, test, and validate the spatiotemporal fidelity of a home-brewed eye-tracking system. To assess spatial and temporal precision, we describe three validation tests that quantify the spatial resolution and temporal synchronization of data acquisition. First, because measurement of pursuit eye movements requires a visual motion display, we measured the timing of luminance transitions of several candidate LCD monitors so as to ensure sufficient stimulus fidelity. Second, we measured eye position as human observers (n=20) ran a nine-point calibration in a clinical-grade chin rest, delivering eye-position noise of 0.22 deg (range: 0.09-0.29 deg) and accuracy of 0.97 deg (range: 0.54-1.89 deg). Third, we measured the overall processing delay in the system to be 5.6 ms, accounted for by the response dynamics of our monitor and the duration of one camera frame. The validation methods presented can be used: 1) to ensure that eye-position accuracy and precision are sufficient to support scientific and clinical studies and are not limited by the hardware or software, and 2) the eyetracker, display, and experiment-control software are effectively synchronized. C1 [Liston, Dorion B.; Wone, Lily R.; Stone, Leland S.] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Liston, Dorion B.; Wone, Lily R.] San Jose State Univ, San Jose, CA USA. [Simpson, Sol] ISolverSolutions, Seattle, WA USA. [Rich, Mark] New York Univ, New York, NY USA. RP Liston, DB (reprint author), NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. EM dliston@arc.nasa.gov NR 21 TC 0 Z9 0 U1 0 U2 0 PU ASSOC COMPUTING MACHINERY PI NEW YORK PA 1515 BROADWAY, NEW YORK, NY 10036-9998 USA BN 978-1-4503-4125-7 PY 2016 BP 221 EP 224 DI 10.1145/2857491.2857534 PG 4 WC Computer Science, Artificial Intelligence; Computer Science, Cybernetics SC Computer Science GA BG5ZC UT WOS:000389809700033 ER PT J AU Gilbert, A Mesmer, B Watson, M AF Gilbert, Andrew Mesmer, Bryan Watson, Michael GP IEEE TI Exergy Based Optimization of Rocket System Staging Times SO 2016 ANNUAL IEEE SYSTEMS CONFERENCE (SYSCON) LA English DT Proceedings Paper CT 10th Annual IEEE International Systems Conference (SysCon) CY APR 18-21, 2016 CL Orlando, FL SP IEEE, IEEE Syst Council DE exergy; exergy analysis; system efficiency; optimization; rocket systems; rocket staging ID POWER-PLANTS AB Exergy is defined as the useful work available to a system. Exergy efficiency is an overall system metric that integrates across disciplines where exergy is used as a "common currency." The use of exergy efficiency gives an overall performance metric which accounts for interactions and couplings between systems. As a holistic metric designers can focus on modifying design variables to improve exergy efficiency. The process of modifying design variables is the focus of Multidisciplinary Design Optimization (MDO), which combines multidisciplinary analysis and optimization methods to form useful design frameworks for large, complex systems. The proposed paper will explore the utilization of MDO with exergy-based analysis in order to optimize the staging times of a rocket system. C1 [Gilbert, Andrew; Mesmer, Bryan] Univ Alabama, Ind & Syst Engn & Engn Management, Huntsville, AL 35899 USA. [Watson, Michael] NASA, Syst Engn Management Off, Marshall Space Flight Ctr, Huntsville, AL USA. RP Gilbert, A (reprint author), Univ Alabama, Ind & Syst Engn & Engn Management, Huntsville, AL 35899 USA. NR 22 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4673-9519-9 PY 2016 BP 646 EP 652 PG 7 WC Computer Science, Information Systems; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BG5PW UT WOS:000389647000099 ER PT S AU Cooper, KB Durden, S Choukroun, M Lebsock, M Siles, J Monje, R Lee, C AF Cooper, Ken B. Durden, Steve Choukroun, Mathieu Lebsock, Matt Siles, Jose Monje, Raquel Lee, Choonsup GP IEEE TI FMCW Radars at 95 and 183 GHz for Planetary and Earth Science Remote Sensing SO 2016 GLOBAL SYMPOSIUM ON MILLIMETER WAVES (GSMM) & ESA WORKSHOP ON MILLIMETRE-WAVE TECHNOLOGY AND APPLICATIONS SE Global Symposium on Milllimeter Waves LA English DT Proceedings Paper CT Global Symposium on Millimeter Waves (GSMM) / ESA Workshop on Millimetre-Wave Technology and Applications CY JUN 06-08, 2016 CL Espoo, FINLAND DE millimeter-wave radar; FMCW AB We are developing two prototype millimeter-wave radars at 95 and 183 GHz with a frequency-modulated continuous-wave (FMCW) architecture. The 95 GHz radar is intended to measure distributions and velocities of small particles in space, such as those ejected in cometary jets. The 183 GHz radar is to operate across the atmospheric water absorption line to perform humidity sounding inside clouds. Here we discuss the choice of frequency and critical components for the two radars and show some early performance results. C1 [Cooper, Ken B.; Durden, Steve; Choukroun, Mathieu; Lebsock, Matt; Siles, Jose; Monje, Raquel; Lee, Choonsup] CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. RP Cooper, KB (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. NR 6 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2380-9515 BN 978-1-5090-1348-7 J9 GLOB SYM MILLIM WAVE PY 2016 BP 168 EP 170 PG 3 WC Engineering, Electrical & Electronic SC Engineering GA BG5ZM UT WOS:000389825200047 ER PT J AU Kumar, S Erdogmus, H Falcao, JD Griss, M Iannucci, B AF Kumar, Sumeet Erdogmus, Hakan Falcao, Joao Diogo Griss, Martin Iannucci, Bob GP IEEE TI Location-Aware Wireless Emergency Alerts SO 2016 IEEE SYMPOSIUM ON TECHNOLOGIES FOR HOMELAND SECURITY (HST) LA English DT Proceedings Paper CT IEEE Symposium on Technologies for Homeland Security (HST) CY MAY 10-11, 2016 CL Waltham, MA SP IEEE AB The Wireless Emergency Alert (WEA) service allows short text messages to be broadcast to all capable mobile devices in a specified geographic area. Although it enjoys nationwide reach, the current WEA service has limitations that impede its public acceptance. These limitations include imprecise geographical targeting of alerts, which reduces the alerts' relevance to many recipients, increasing the likelihood of these recipients to opt out of receiving alerts or stop paying attention. The growing capabilities of smart phones, such as improved location awareness and increased computing power, provide opportunities to alleviate the limitations by personalizing targeted alerts and allowing optimized alert delivery decisions. Motivated by these opportunities, we designed and developed a prototypical, enhanced end-to-end WEA service that includes an alert creation subsystem, a message delivery subsystem, and a smart phone application for capturing, processing, and presenting simulated alerts to recipients. We conducted two public trials with over 225 subjects to evaluate several WEA enhancements using this service. The evaluated enhancements included (1) augmenting WEA messages with high-information maps, (2) precise geographical targeting of alerts, and (3) use of the recipient's location history to influence the alert delivery decision. Our results suggest significant added value for all three enhancements, making them worthy of consideration for future WEA implementations. C1 [Kumar, Sumeet; Erdogmus, Hakan; Falcao, Joao Diogo; Griss, Martin; Iannucci, Bob] Carnegie Mellon Univ, NASA, Ames Res Pk, Dept Elect & Comp Engn, Bldg 23,MS 23-11, Moffett Field, CA 94035 USA. RP Kumar, S (reprint author), Carnegie Mellon Univ, NASA, Ames Res Pk, Dept Elect & Comp Engn, Bldg 23,MS 23-11, Moffett Field, CA 94035 USA. EM sumeet.kumar@sv.cmu.edu; hakan.erdogmus@sv.cmu.edu; joao.diogo.de.menezes.falcao@sv.cmu.edu; martin.griss@sv.cmu.edu; bob@sv.cmu.edu NR 10 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-5090-0770-7 PY 2016 PG 6 WC Computer Science, Information Systems; Computer Science, Interdisciplinary Applications; Computer Science, Theory & Methods SC Computer Science GA BG5NO UT WOS:000389584500027 ER PT J AU Shaw, HC AF Shaw, Harry C. GP IEEE TI Network Security via biometric recognition of patterns of gene expression SO 2016 IEEE SYMPOSIUM ON TECHNOLOGIES FOR HOMELAND SECURITY (HST) LA English DT Proceedings Paper CT IEEE Symposium on Technologies for Homeland Security (HST) CY MAY 10-11, 2016 CL Waltham, MA SP IEEE DE network security; gene expression; transcription factors; translation AB Molecular biology provides the ability to implement forms of information and network security completely outside the bounds of legacy security protocols and algorithms. This paper addresses an approach which instantiates the power of gene expression for security. Molecular biology provides a rich source of gene expression and regulation mechanisms, which can be adopted to use in the information and electronic communication domains. Conventional security protocols are becoming increasingly vulnerable due to more intensive, highly capable attacks on the underlying mathematics of cryptography. Security protocols are being undermined by social engineering and substandard implementations by IT organizations. Molecular biology can provide countermeasures to these weak points with the current security approaches. Future advances in instruments for analyzing assays will also enable this protocol to advance from one of cryptographic algorithms to an integrated system of cryptographic algorithms and real-time expression and assay of gene expression products. C1 [Shaw, Harry C.] NASA Goddard Space Flight Ctr, Telecommunicat Networks & Technol Branch, Greenbelt, MD USA. RP Shaw, HC (reprint author), NASA Goddard Space Flight Ctr, Telecommunicat Networks & Technol Branch, Greenbelt, MD USA. EM Harry.c.shaw@nasa.gov NR 5 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-5090-0770-7 PY 2016 PG 6 WC Computer Science, Information Systems; Computer Science, Interdisciplinary Applications; Computer Science, Theory & Methods SC Computer Science GA BG5NO UT WOS:000389584500058 ER PT S AU Borner, A Swaminathan-Gopalan, K Stephani, KA Mansour, NN AF Borner, Arnaud Swaminathan-Gopalan, Krishnan Stephani, Kelly A. Mansour, Nagi N. BE Ketsdever, A Struchtrup, H TI Detailed DSMC Surface Chemistry Modeling of the Oxidation of Carbon-Based Ablators SO 30TH INTERNATIONAL SYMPOSIUM ON RAREFIED GAS DYNAMICS (RGD 30) SE AIP Conference Proceedings LA English DT Proceedings Paper CT 30th International Symposium on Rarefied Gas Dynamics (RGD) CY JUL 10-15, 2016 CL Univ Victoria, Victoria, CANADA HO Univ Victoria ID SIMULATION; ABLATION AB This work employs a recently developed gas-surface interaction model (referred to herein as PSMM) constructed from molecular beam experimental data for use with the direct simulation Monte Carlo (DSMC) method. While recent models have been proposed to produce macroscopic rates consistent with the experimental measurements for use in CFD solvers, this work aims to reproduce the microscopic details (including angular distributions and time-of-flight distributions) obtained from the experimental data for modeling gas-surface interactions in DSMC. The different mechanisms considered for the PSMM model include adsorption, desorption, surface participating and direct impact mechanisms. The microscopic data of probabilities and characteristic frequencies for each type of reaction are obtained from the macroscopic parameters of reaction rate constants and sticking coefficients. Numerical simulations closely resembling a recent set of molecular beam experiments were performed using this model within DSMC, and the performance of the Zhluktov-Abe and Alba models is also assessed. The molecular beam experiments involved the bombardment of a relatively smooth vitreous carbon surface using a hyperthermal O/O-2 beam to understand the product formation and the detailed reaction mechanisms and scattering at the surface. A comparison of the numerical flux distributions from the Zhluktov-Abe and Alba models with experimental flux distributions of the scattered products at different temperatures showed significant discrepancies. The PSMM model was found to reproduce the scattered product mole fractions as a function of temperature, as well as the reactively scattered CO time-of-flight data. Future work will aim to improve the DSMC predicted time-of-flight data for inelastically and elastically scattered O atoms based on the experimental data. C1 [Borner, Arnaud; Swaminathan-Gopalan, Krishnan; Stephani, Kelly A.] Univ Illinois, Dept Mech Sci & Engn, Urbana, IL 61801 USA. [Mansour, Nagi N.] NASA, Ames Res Ctr, Adv Supercomp Div, Computat Phys Branch, Moffett Field, CA 94035 USA. RP Borner, A (reprint author), Univ Illinois, Dept Mech Sci & Engn, Urbana, IL 61801 USA. EM arnaud.p.borner@nasa.gov NR 16 TC 0 Z9 0 U1 1 U2 1 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 978-0-7354-1448-8 J9 AIP CONF PROC PY 2016 VL 1786 AR UNSP 100001 DI 10.1063/1.4967612 PG 8 WC Physics, Applied SC Physics GA BG5JS UT WOS:000389513200076 ER PT S AU Liechty, DS Burt, JM AF Liechty, Derek S. Burt, Jonathan M. BE Ketsdever, A Struchtrup, H TI Extension of the Viscous Collision Limiting Direct Simulation Monte Carlo Technique to Multiple Species SO 30TH INTERNATIONAL SYMPOSIUM ON RAREFIED GAS DYNAMICS (RGD 30) SE AIP Conference Proceedings LA English DT Proceedings Paper CT 30th International Symposium on Rarefied Gas Dynamics (RGD) CY JUL 10-15, 2016 CL Univ Victoria, Victoria, CANADA HO Univ Victoria ID CONTINUUM AB There are many flows fields that span a wide range of length scales where regions of both rarefied and continuum flow exist and neither direct simulation Monte Carlo (DSMC) nor computational fluid dynamics (CFD) provide the appropriate solution everywhere. Recently, a new viscous collision limited (VCL) DSMC technique was proposed to incorporate effects of physical diffusion into collision limiter calculations to make the low Knudsen number regime normally limited to CFD more tractable for an all-particle technique. This original work had been derived for a single-species gas. The current work extends the VCL-DSMC technique to gases with multiple species. Similar derivations were performed to equate numerical and physical transport coefficients. However, a more rigorous treatment of determining the mixture viscosity is applied. In the original work, consideration was given to internal energy non-equilibrium, and this is also extended in the current work to chemical non-equilibrium. C1 [Liechty, Derek S.] NASA Langley Res Ctr, Aerothermodynam Branch, MS 408A, Hampton, VA 23681 USA. [Burt, Jonathan M.] US Air Force, Res Lab, Wright Patterson AFB, OH 45433 USA. RP Liechty, DS (reprint author), NASA Langley Res Ctr, Aerothermodynam Branch, MS 408A, Hampton, VA 23681 USA. EM Derek.S.Liechty@nasa.gov; Jonathan.M.Burt@nasa.gov NR 14 TC 0 Z9 0 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 978-0-7354-1448-8 J9 AIP CONF PROC PY 2016 VL 1786 AR UNSP 050008 DI 10.1063/1.4967558 PG 8 WC Physics, Applied SC Physics GA BG5JS UT WOS:000389513200022 ER PT S AU Gaudel, Q Ribot, P Chanthery, E Daigle, MJ AF Gaudel, Quentin Ribot, Pauline Chanthery, Elodie Daigle, Matthew J. BE Kordon, F Moldt, D TI Health Monitoring of a Planetary Rover Using Hybrid Particle Petri Nets SO APPLICATION AND THEORY OF PETRI NETS AND CONCURRENCY, PETRI NETS 2016 SE Lecture Notes in Computer Science LA English DT Proceedings Paper CT 37th International Conference on Application and Theory of Petri Nets and Concurrency (Petri Nets) CY JUN 19-24, 2016 CL Torun, POLAND SP Nicolaus Copernicus Univ, Fac Math & Comp Sci DE Diagnosis; Hybrid systems; Model-based monitoring; Health management; Uncertainty; Petri Nets; Particle filter ID DISCRETE-EVENT SYSTEMS; DIAGNOSABILITY; DIAGNOSIS AB This paper focuses on the application of a Petri Net-based diagnosis method on a planetary rover prototype. The diagnosis is performed by using a model-based method in the context of health management of hybrid systems. In system health management, the diagnosis task aims at determining the current health state of a system and the fault occurrences that lead to this state. The Hybrid Particle Petri Nets (HPPN) formalism is used to model hybrid systems behavior and degradation, and to define the generation of diagnosers to monitor the health states of such systems under uncertainty. At any time, the HPPN-based diagnoser provides the current diagnosis represented by a distribution of beliefs over the health states. The health monitoring methodology is demonstrated on the K11 rover. A hybrid model of the K11 is proposed and experimental results show that the approach is robust to real system data and constraints. C1 [Gaudel, Quentin; Ribot, Pauline; Chanthery, Elodie] Univ Toulouse, UPS, CNRS, INSA,LAAS, Toulouse, France. [Daigle, Matthew J.] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Chanthery, E (reprint author), Univ Toulouse, UPS, CNRS, INSA,LAAS, Toulouse, France. EM quentin.gaudel@laas.fr; pauline.ribot@laas.fr; elodie.chanthery@laas.fr; matthew.j.daigle@nasa.gov NR 24 TC 0 Z9 0 U1 0 U2 0 PU SPRINGER INT PUBLISHING AG PI CHAM PA GEWERBESTRASSE 11, CHAM, CH-6330, SWITZERLAND SN 0302-9743 BN 978-3-319-39085-7; 978-3-319-39086-4 J9 LECT NOTES COMPUT SC PY 2016 VL 9698 BP 196 EP 215 DI 10.1007/978-3-319-39086-4_13 PG 20 WC Computer Science, Software Engineering; Computer Science, Theory & Methods SC Computer Science GA BG5WS UT WOS:000389799200013 ER PT S AU Maschhoff, KR Polizotti, JJ Aumann, HH Susskind, J AF Maschhoff, K. R. Polizotti, J. J. Aumann, H. H. Susskind, J. BE Pagano, TS TI MISTiC WINDS, A MICRO-SATELLITE CONSTELLATION APPROACH TO HIGH RESOLUTION OBSERVATIONS OF THE ATMOSPHERE USING INFRARED SOUNDING AND 3D WINDS MEASUREMENTS SO CUBESATS AND NANOSATS FOR REMOTE SENSING SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on CubeSats and NanoSats for Remote Sensing CY AUG 31, 2016 CL San Diego, CA SP SPIE DE Atmospheric Motion-Vector Winds; Vertical Wind Profile; Infrared Temperature and Moisture Sounding ID AIRS AB MISTiC TM Winds is an approach to improve short-term weather forecasting based on a miniature high resolution, wide field, thermal emission spectrometry instrument that will provide global tropospheric vertical profiles of atmospheric temperature and humidity at high (3-4 km) horizontal and vertical (1 km) spatial resolution. MISTiC's extraordinarily small size, payload mass of less than 15 kg, and minimal cooling requirements can be accommodated aboard a 27U-class CubeSat or an ESPA-Class micro-satellite. Low fabrication and launch costs enable a LEO sun-synchronous sounding constellation that would collectively provide frequent IR vertical profiles and vertically resolved atmospheric motion vector wind observations in the troposphere. These observations are highly complementary to present and emerging environmental observing systems, and would provide a combination of high vertical and horizontal resolution not provided by any other environmental observing system currently in operation. The spectral measurements that would be provided by MISTiC Winds are similar to those of NASA's AIRS that was built by BAE Systems and operates aboard the AQUA satellite. These new observations, when assimilated into high resolution numerical weather models, would revolutionize short-term and severe weather forecasting, save lives, and support key economic decisions in the energy, air transport, and agriculture arenas-at much lower cost than providing these observations from geostationary orbit. In addition, this observation capability would be a critical tool for the study of transport processes for water vapor, clouds, pollution, and aerosols. Key remaining technical risks are being reduced through laboratory and airborne testing under NASA's Instrument Incubator Program. C1 [Maschhoff, K. R.] BAE Syst, Pob 868, Nashua, NH 03061 USA. [Maschhoff, K. R.; Polizotti, J. J.] JPL, Pasadena, CA 91109 USA. [Susskind, J.] NASA GSFC, Greenbelt, MD 20771 USA. RP Maschhoff, KR (reprint author), BAE Syst, Pob 868, Nashua, NH 03061 USA. NR 10 TC 0 Z9 0 U1 2 U2 2 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0347-9; 978-1-5106-0348-6 J9 PROC SPIE PY 2016 VL 9978 AR UNSP 997804 DI 10.1117/12.2239272 PG 14 WC Engineering, Aerospace; Remote Sensing SC Engineering; Remote Sensing GA BG5QP UT WOS:000389680800001 ER PT S AU Pagano, TS Rider, D Rud, M Ting, D Yee, K AF Pagano, Thomas S. Rider, David Rud, Mayer Ting, David Yee, Karl BE Pagano, TS TI Measurement approach and design of the CubeSat Infrared Atmospheric Sounder (CIRAS) SO CUBESATS AND NANOSATS FOR REMOTE SENSING SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on CubeSats and NanoSats for Remote Sensing CY AUG 31, 2016 CL San Diego, CA SP SPIE DE Infrared; Sounding; CubeSat; Grating; Spectrometer AB The CubeSat Infrared Atmospheric Sounder (CIRAS) will measure upwelling infrared radiation of the Earth in the MWIR region of the spectrum from space on a CubeSat. The observed radiances have information of potential value to weather forecasting agencies and can be used to retrieve lower tropospheric temperature and water vapor globally for weather and climate science investigations. Multiple units can be flown to improve temporal coverage or in formation to provide new data products including 3D atmospheric motion vector winds. CIRAS incorporates key new instrument technologies including a 2D array of High Operating Temperature Barrier Infrared Detector (HOT-BIRD) material, selected for its high uniformity, low cost, low noise and higher operating temperatures than traditional materials. The detectors are hybridized to a commercial ROIC and commercial camera electronics. The second key technology is an MWIR Grating Spectrometer (MGS) designed to provide imaging spectroscopy for atmospheric sounding in a CubeSat volume. The MGS has no moving parts and includes an immersion grating to reduce the volume and reduce distortion. The third key technology is an infrared blackbody fabricated with black silicon to have very high emissivity in a flat plate construction. JPL will also develop the mechanical, electronic and thermal subsystems for CIRAS, while the spacecraft will be a commercially available CubeSat. The integrated system will be a complete 6U CubeSat capable of measuring temperature and water vapor profiles with good lower tropospheric sensitivity. The CIRAS is the first step towards the development of an Earth Observation Nanosatellite Infrared (EON-IR) capable of operational readiness to mitigate a potential loss of CrIS on JPSS or complement the current observing system with different orbit crossing times. C1 [Pagano, Thomas S.; Rider, David; Rud, Mayer; Ting, David; Yee, Karl] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Pagano, TS (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 12 TC 0 Z9 0 U1 2 U2 2 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0347-9; 978-1-5106-0348-6 J9 PROC SPIE PY 2016 VL 9978 AR UNSP 997806 DI 10.1117/12.2235986 PG 7 WC Engineering, Aerospace; Remote Sensing SC Engineering; Remote Sensing GA BG5QP UT WOS:000389680800003 ER PT S AU Barnard, HS MacDowell, AA Parkinson, DY Venkatakrishnan, SV Panerai, F Mansour, NN AF Barnard, Harold S. MacDowell, A. A. Parkinson, D. Y. Venkatakrishnan, S. V. Panerai, F. Mansour, N. N. BE Stock, SR Muller, B Wang, G TI Developments in synchrotron X-ray micro-tomography for in-situ materials analysis at the Advanced Light Source SO DEVELOPMENTS IN X-RAY TOMOGRAPHY X SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Developments in X-Ray Tomography X CY AUG 29-31, 2016 CL San Diego, CA SP SPIE DE X-ray micro-Tomography; X-ray; micro-tomography; synchrotron AB The Advanced Light Source (ALS) is a third-generation synchrotron X-ray source that operates as a user facility with more than 40 beamlines hosting over 2000 users per year. Synchrotron sources like the ALS provide high quality X-ray beams, with flux that is several orders of magnitude higher than lab-based sources. This is particularly advantageous for dynamic applications because it allows for high-speed, high-resolution imaging and microscale tomography. The hard X-ray beamline 8.3.2 at the Advanced Light Source enables imaging of samples at high temperatures and pressures, with mechanical loading and other realistic conditions using environmental test cells. These test cells enable experimental observation of samples undergoing dynamic microstructural changes in-situ. We present recent instrumentation developments that allow for continuous tomography with scan rates approaching 1 Hz per 3D image. In addition, our use of iterative reconstruction techniques allows for improved image quality despite fewer images and low exposure times used during fast tomography compared to traditional Fourier reconstruction methods. C1 [Barnard, Harold S.; MacDowell, A. A.; Parkinson, D. Y.; Venkatakrishnan, S. V.] Lawrence Berkeley Natl Lab, Adv Light Source, Berkeley, CA 94720 USA. [Panerai, F.; Mansour, N. N.] NASA, Ames Res Ctr, Moffett Field, CA USA. RP Barnard, HS (reprint author), Lawrence Berkeley Natl Lab, Adv Light Source, Berkeley, CA 94720 USA. NR 18 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0325-7; 978-1-5106-0326-4 J9 PROC SPIE PY 2016 VL 9967 AR UNSP 99671H DI 10.1117/12.2238305 PG 13 WC Optics; Physics, Applied; Statistics & Probability SC Optics; Physics; Mathematics GA BG5IN UT WOS:000389506300042 ER PT S AU Akitaya, HA Cheung, KC Demaine, ED Horiyama, T Hull, TC Ku, JS Tachi, T Uehara, R AF Akitaya, Hugo A. Cheung, Kenneth C. Demaine, Erik D. Horiyama, Takashi Hull, Thomas C. Ku, Jason S. Tachi, Tomohiro Uehara, Ryuhei BE Akiyama, J Ito, H Sakai, T TI Box Pleating is Hard SO DISCRETE AND COMPUTATIONAL GEOMETRY AND GRAPHS, JCDCGG 2015 SE Lecture Notes in Computer Science LA English DT Proceedings Paper CT 18th Japan Conference on Discrete and Computational Geometry and Graphs (JCDCG2) CY SEP 14-16, 2015 CL Kyoto Univ, Kyoto, JAPAN HO Kyoto Univ AB Flat foldability of general crease patterns was first claimed to be hard for over twenty years. In this paper we prove that deciding flat foldability remains NP-complete even for box pleating, where creases form a subset of a square grid with diagonals. In addition, we provide new terminology to implicitly represent the global layer order of a flat folding, and present a new planar reduction framework for grid-aligned gadgets. C1 [Akitaya, Hugo A.] Tufts Univ, Medford, MA USA. [Cheung, Kenneth C.] NASA, Washington, DC USA. [Demaine, Erik D.; Ku, Jason S.] MIT, Cambridge, MA 02139 USA. [Horiyama, Takashi] Saitama Univ, Saitama, Japan. [Hull, Thomas C.] Western New England Univ, Springfield, MA USA. [Tachi, Tomohiro] Univ Tokyo, Tokyo, Japan. [Uehara, Ryuhei] JAIST, Nomi, Japan. RP Akitaya, HA (reprint author), Tufts Univ, Medford, MA USA. EM hugo.alves_akitaya@tufts.edu; kenneth.c.cheung@nasa.gov; edemaine@mit.edu; horiyama@al.ics.saitama-u.ac.jp; thull@wne.edu; jasonku@mit.edu; tachi@idea.c.u-tokyo.ac.jp; uehara@jaist.ac.jp NR 7 TC 0 Z9 0 U1 0 U2 0 PU SPRINGER INT PUBLISHING AG PI CHAM PA GEWERBESTRASSE 11, CHAM, CH-6330, SWITZERLAND SN 0302-9743 BN 978-3-319-48532-4; 978-3-319-48531-7 J9 LECT NOTES COMPUT SC PY 2016 VL 9943 BP 167 EP 179 DI 10.1007/978-3-319-48532-4_15 PG 13 WC Computer Science, Theory & Methods; Mathematics, Applied SC Computer Science; Mathematics GA BG5WH UT WOS:000389794000015 ER PT S AU Lupisella, M AF Lupisella, Mark BE Schwartz, JSJ Milligan, T TI Cosmological Theories of Value: Relationalism and Connectedness as Foundations for Cosmic Creativity SO ETHICS OF SPACE EXPLORATION SE Space and Society LA English DT Article; Book Chapter C1 [Lupisella, Mark] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Lupisella, M (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. EM mark.l.lupisella@nasa.gov NR 59 TC 0 Z9 0 U1 0 U2 0 PU SPRINGER INT PUBLISHING AG PI CHAM PA GEWERBESTRASSE 11, CHAM, CH-6330, SWITZERLAND SN 2199-3882 BN 978-3-319-39827-3; 978-3-319-39825-9 J9 SPACE SOCIETY PY 2016 BP 75 EP 91 DI 10.1007/978-3-319-39827-3_6 D2 10.1007/978-3-319-39827-3 PG 17 WC Ethics; Law SC Social Sciences - Other Topics; Government & Law GA BG4ZD UT WOS:000389274800006 ER PT S AU Giannakopoulou, D Guck, D Schumann, J AF Giannakopoulou, Dimitra Guck, Dennis Schumann, Johann BE Fitzgerald, J Heitmeyer, C Gnesi, S Philippou, A TI Exploring Model Quality for ACAS X SO FM 2016: FORMAL METHODS SE Lecture Notes in Computer Science LA English DT Proceedings Paper CT 21st International Symposium on Formal Methods (FM) CY NOV 09-11, 2016 CL Limassol, CYPRUS ID FORMAL VERIFICATION; CONFLICT-RESOLUTION; SYSTEMS AB The next generation airborne collision avoidance system, ACAS X, aims to provide robustness through a probabilistic model that represents sources of uncertainty. From this model, dynamic programming produces a look-up table that is used to give advisories to the pilot in real time. The model is not present in the final system and is therefore not included in the standard certification processes. Rather, the model is checked indirectly, by ensuring that ACAS X performs as well as, or better than, the state-of-the-art, TCAS. We claim that to build confidence in such systems, it is important to target model quality directly. We investigate this issue of model quality as part of our research on informing certification standards for autonomy. Using ACAS X as our driving example, we study the relationship between the probabilistic model and the real world, in an attempt to characterize the quality of the model for the purpose of building ACAS X. This paper presents model conformance metrics, their application to ACAS X, and the results that we obtained from our study. C1 [Giannakopoulou, Dimitra; Schumann, Johann] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Guck, Dennis] Univ Twente, Formal Methods & Tools, Enschede, Netherlands. RP Guck, D (reprint author), Univ Twente, Formal Methods & Tools, Enschede, Netherlands. EM d.guck@utwente.nl NR 16 TC 0 Z9 0 U1 0 U2 0 PU SPRINGER INT PUBLISHING AG PI CHAM PA GEWERBESTRASSE 11, CHAM, CH-6330, SWITZERLAND SN 0302-9743 BN 978-3-319-48989-6; 978-3-319-48988-9 J9 LECT NOTES COMPUT SC PY 2016 VL 9995 BP 274 EP 290 DI 10.1007/978-3-319-48989-6_17 PG 17 WC Computer Science, Software Engineering; Computer Science, Theory & Methods SC Computer Science GA BG5WG UT WOS:000389793300017 ER PT S AU Chanan, G Troy, M Raouf, N AF Chanan, Gary Troy, Mitchell Raouf, Nasrat BE Hall, HJ Gilmozzi, R Marshall, HK TI Phasing the Segments of the Keck and Thirty Meter Telescopes via the Narrowband Phasing Algorithm: Chromatic Effects SO GROUND-BASED AND AIRBORNE TELESCOPES VI SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Ground-Based and Airborne Telescopes VI CY JUN 26-JUL 01, 2016 CL Edinburgh, SCOTLAND SP SPIE DE segmented mirrors; wavefront control; phasing ID MIRROR SEGMENTS AB The narrowband phasing algorithm that was originally developed at Keck has largely been replaced by a broadband algorithm that, although it is slower and less accurate than the former, has proved to be much more robust. A systematic investigation into the lack of robustness of the narrowband algorithm has shown that it results from systematic errors (of order 20 nm) that are wavelength-dependent. These errors are not well-understood at present, but they do not appear to arise from instrumental effects in the Keck phasing cameras, or from the segment coatings. This leaves high spatial frequency aberrations or scattering within 60 mm of the segment edges as the most likely origin of the effect. C1 [Chanan, Gary] Univ Calif Irvine, Irvine, CA 92697 USA. [Troy, Mitchell; Raouf, Nasrat] Jet Prop Lab, Pasadena, CA 91124 USA. RP Chanan, G (reprint author), Univ Calif Irvine, Irvine, CA 92697 USA. EM gachanan@gmail.com NR 4 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0191-8; 978-1-5106-0192-5 J9 PROC SPIE PY 2016 VL 9906 AR UNSP 99066F DI 10.1117/12.2230748 PN 1 PG 12 WC Instruments & Instrumentation; Optics SC Instruments & Instrumentation; Optics GA BG2WM UT WOS:000387731100197 ER PT S AU Cortes-Medellin, G O'Dougherty, S Walker, C Goldsmith, PF Groppi, C Smith, S Bernasconi, P AF Cortes-Medellin, German O'Dougherty, Stefan Walker, Christopher Goldsmith, Paul F. Groppi, Chris Smith, Steve Bernasconi, Pietro BE Hall, HJ Gilmozzi, R Marshall, HK TI Optical Design for the Large Balloon Reflector SO GROUND-BASED AND AIRBORNE TELESCOPES VI SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Ground-Based and Airborne Telescopes VI CY JUN 26-JUL 01, 2016 CL Edinburgh, SCOTLAND SP SPIE DE Sub-mm; Stratospheric Balloon Telescope; THz Optical Design AB We present the details of the optical design, corrector system, mechanical layout, tolerances, pointing requirements, and overall performance of the sub-millimeter wavelength Large Balloon Reflector telescope (LBR). C1 [Cortes-Medellin, German] Univ Antioquia, Elect & Telecom Enginering Dept, Medellin, Colombia. [Cortes-Medellin, German] Cornell Univ, CCAPS Space Sci Bldg, Ithaca, NY 14853 USA. [O'Dougherty, Stefan; Walker, Christopher] Univ Arizona, Dept Astron, Tucson, AZ 85719 USA. [Goldsmith, Paul F.] Jet Prop Lab, Pasadena, CA 91109 USA. [Groppi, Chris] Arizona State Univ, Sch Earth & Space Explorat, Tempe, AZ 85287 USA. [Smith, Steve] Southwest Res Inst, San Antonio, TX 78238 USA. [Bernasconi, Pietro] APL Johns Hopkings Univ, Laurel, MD 20723 USA. RP Cortes-Medellin, G (reprint author), Univ Antioquia, Elect & Telecom Enginering Dept, Medellin, Colombia.; Cortes-Medellin, G (reprint author), Cornell Univ, CCAPS Space Sci Bldg, Ithaca, NY 14853 USA. NR 6 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0191-8; 978-1-5106-0192-5 J9 PROC SPIE PY 2016 VL 9906 AR UNSP 99061Y DI 10.1117/12.2233861 PN 1 PG 9 WC Instruments & Instrumentation; Optics SC Instruments & Instrumentation; Optics GA BG2WM UT WOS:000387731100058 ER PT S AU Graf, F Reinacher, A Jakob, H Lampater, U Pfueller, E Wiedemann, M Wolf, J Fasoulas, S AF Graf, Friederike Reinacher, Andreas Jakob, Holger Lampater, Ulrich Pfueller, Enrico Wiedemann, Manuel Wolf, Juergen Fasoulas, Stefanos BE Hall, HJ Gilmozzi, R Marshall, HK TI Pointing and Control System Performance and Improvement Strategies for the SOFIA Airborne Telescope SO GROUND-BASED AND AIRBORNE TELESCOPES VI SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Ground-Based and Airborne Telescopes VI CY JUN 26-JUL 01, 2016 CL Edinburgh, SCOTLAND SP SPIE DE Airborne Astronomy; SOFIA; Control Engineering; Pointing Stability; Flexible Structures; Image Motion Compensation AB The Stratospheric Observatory for Infrared Astronomy (SOFIA) has already successfully conducted over 300 flights. In its early science phase, SOFIA's pointing requirements and especially the image jitter requirements of less than 1 arcsec rms have driven the design of the control system. Since the first observation flights, the image jitter has been gradually reduced by various control mechanisms. During smooth flight conditions, the current pointing and control system allows us to achieve the standards set for early science on SOFIA. However, the increasing demands on the image size require an image jitter of less than 0.4 arcsec rms during light turbulence to reach SOFIA's scientific goals. The major portion of the remaining image motion is caused by deformation and excitation of the telescope structure in a wide range of frequencies due to aircraft motion and aerodynamic and aeroacoustic effects. Therefore the so-called Flexible Body Compensation system (FBC) is used, a set of fixed-gain filters to counteract the structural bending and deformation. Thorough testing of the current system under various flight conditions has revealed a variety of opportunities for further improvements. The currently applied filters have solely been developed based on a FEM analysis. By implementing the inflight measurements in a simulation and optimization, an improved fixed-gain compensation method was identified. This paper will discuss promising results from various jitter measurements recorded with sampling frequencies of up to 400 Hz using the fast imaging tracking camera. C1 [Graf, Friederike; Reinacher, Andreas; Jakob, Holger; Pfueller, Enrico; Wiedemann, Manuel; Wolf, Juergen] Univ Stuttgart, Deutsch SOFIA Inst, Pfaffenwaldring 29, D-70569 Stuttgart, Germany. [Graf, Friederike; Pfueller, Enrico; Wiedemann, Manuel; Wolf, Juergen] NASA, SOFIA Sci Ctr, Ames Res Ctr, Mail Stop N-211-1, Moffett Field, CA 94035 USA. [Reinacher, Andreas; Jakob, Holger] NASA, SOFIA Airborne Syst Operat Ctr, Armstrong Flight Res Ctr, MS DAOF 5231, Edwards AFB, CA 93523 USA. [Fasoulas, Stefanos] Univ Stuttgart, Deutsch SOFIA Inst, D-70569 Stuttgart, Germany. [Fasoulas, Stefanos] Univ Stuttgart, Inst Space Syst, Pfaffenwaldring 29, D-70569 Stuttgart, Germany. RP Graf, F (reprint author), Univ Stuttgart, Deutsch SOFIA Inst, Pfaffenwaldring 29, D-70569 Stuttgart, Germany.; Graf, F (reprint author), NASA, SOFIA Sci Ctr, Ames Res Ctr, Mail Stop N-211-1, Moffett Field, CA 94035 USA. EM graf@dsi.uni-stuttgart.de NR 14 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0191-8; 978-1-5106-0192-5 J9 PROC SPIE PY 2016 VL 9906 AR UNSP 99061T DI 10.1117/12.2231803 PN 1 PG 16 WC Instruments & Instrumentation; Optics SC Instruments & Instrumentation; Optics GA BG2WM UT WOS:000387731100053 ER PT S AU Karcher, HJ Erickson, EF Krabbe, A Wagner, J AF Kaercher, Hans J. Erickson, Edwin F. Krabbe, Alfred Wagner, Joerg BE Hall, HJ Gilmozzi, R Marshall, HK TI SOFIA Design History SO GROUND-BASED AND AIRBORNE TELESCOPES VI SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Ground-Based and Airborne Telescopes VI CY JUN 26-JUL 01, 2016 CL Edinburgh, SCOTLAND SP SPIE DE Telescope; infrared; air-borne; astronomy; SOFIA; design; optics; structure; mechanics ID GREAT AB SOFIA has reached in the last two years its full operational capabilities and is producing now great science on typically three observing flights per week. The telescope is the backbone of the observatory and is working nearly perfectly. This may be the right time to have a look on the design history of the telescope and some of the major subsystems, which ensure the functionality under the harsh aero-acoustic environment inside the aircraft cavity. A comparison with SOFIA's predecessor KAO gives insight in to the challenges of airborne telescope design. The paper describes the development of the optical subsystem, the telescopes structure, the telescope mount and the interface to the aircraft from the conceptual design up to the finally as-built telescope, and comments on their influence on the overall observatory performance. C1 [Kaercher, Hans J.] MT Mechatron, Weberstr 21, D-55130 Mainz, Germany. [Erickson, Edwin F.] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Krabbe, Alfred; Wagner, Joerg] Univ Stuttgart, Inst Raumfahrtsyst, DSI, Pfaffenwaldring 29, D-70569 Stuttgart, Germany. RP Karcher, HJ (reprint author), MT Mechatron, Weberstr 21, D-55130 Mainz, Germany. EM hans.kaecrcherr@mt-mechatronics.de RI Wagner, Joerg/B-7913-2015 OI Wagner, Joerg/0000-0002-8536-4668 NR 22 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0191-8; 978-1-5106-0192-5 J9 PROC SPIE PY 2016 VL 9906 AR UNSP 99061V DI 10.1117/12.2232715 PN 1 PG 13 WC Instruments & Instrumentation; Optics SC Instruments & Instrumentation; Optics GA BG2WM UT WOS:000387731100055 ER PT S AU Lammen, Y Reinacher, A Brewster, R Greiner, B Graf, F Krabbe, A AF Lammen, Yannick Reinacher, Andreas Brewster, Rick Greiner, Benjamin Graf, Friederike Krabbe, Alfred BE Hall, HJ Gilmozzi, R Marshall, HK TI A new test environment for the SOFIA Secondary Mirror Assembly to reduce the required time for in-flight testing SO GROUND-BASED AND AIRBORNE TELESCOPES VI SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Ground-Based and Airborne Telescopes VI CY JUN 26-JUL 01, 2016 CL Edinburgh, SCOTLAND SP SPIE DE secondary mirror; SOFIA; test environment; compliant mechanism; flexure; fast steering; telescope ID TELESCOPE AB The Stratospheric Observatory For Infrared Astronomy (SOFIA) reached its full operational capability in 2014 and takes off from the NASA Armstrong Flight Research Center to explore the universe about three times a week. Maximizing the program's scientific output naturally leaves very little flight time for implementation and test of improved soft- and hardware. Consequently, it is very important to have a comparable test environment and infrastructure to perform troubleshooting, verifications and improvements on ground without interfering with science missions. SOFIA's Secondary Mirror Mechanism is one of the most complex systems of the observatory. In 2012 a first simple laboratory mockup of the mechanism was built to perform basic controller tests in the lower frequency band of up to 50Hz. This was a first step to relocate required engineering tests from the active observatory into the laboratory. However, to test and include accurate filters and damping methods as well as to evaluate hardware modifications a more precise mockup is required that represents the system characteristics over a much larger frequency range. Therefore the mockup has been improved in several steps to a full test environment representing the system dynamics with high accuracy. This new ground equipment allows moving almost the entire secondary mirror test activities away from the observatory. As fast actuator in the optical path, the SMM also plays a major role in SOFIA's pointing stabilization concept. To increase the steering bandwidth, hardware changes are required that ultimately need to be evaluated using the telescope optics. One interesting concept presented in this contribution is the installation of piezo stack actuators between the mirror and the chopping mechanism. First successful baseline tests are presented. An outlook is given about upcoming performance tests of the actively controlled piezo stage with local metrology and optical feedback. To minimize the impact on science time, the laboratory test setup will be expanded with an optical measurement system so that it can be used for the vast majority of testing. C1 [Lammen, Yannick; Reinacher, Andreas; Greiner, Benjamin; Graf, Friederike; Krabbe, Alfred] Univ Stuttgart, Deutches SOFIA Inst, Pfaffenwaldring 29, D-70569 Stuttgart, Germany. [Lammen, Yannick; Reinacher, Andreas] NASA, Armstrong Flight Res Ctr, SOFIA Airborne Syst Operat Ctr, 2825 E Ave P,Bldg 703, Palmdale, CA 93550 USA. [Brewster, Rick; Graf, Friederike] NASA, Ames Res Ctr, SOFIA Sci Ctr, Moffett Field, CA 94035 USA. RP Lammen, Y (reprint author), Univ Stuttgart, Deutches SOFIA Inst, Pfaffenwaldring 29, D-70569 Stuttgart, Germany.; Lammen, Y (reprint author), NASA, Armstrong Flight Res Ctr, SOFIA Airborne Syst Operat Ctr, 2825 E Ave P,Bldg 703, Palmdale, CA 93550 USA. EM lammen@dsi.uni-stuttgart.de NR 10 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0191-8; 978-1-5106-0192-5 J9 PROC SPIE PY 2016 VL 9906 AR UNSP 99064T DI 10.1117/12.2232152 PN 1 PG 12 WC Instruments & Instrumentation; Optics SC Instruments & Instrumentation; Optics GA BG2WM UT WOS:000387731100143 ER PT S AU Lammen, Y Reinacher, A Kjelberg, I Droz, S Jakob, H Graf, F Lachenmann, M Krabbe, A AF Lammen, Yannick Reinacher, Andreas Kjelberg, Ivar Droz, Serge Jakob, Holger Graf, Friederike Lachenmann, Michael Krabbe, Alfred BE Hall, HJ Gilmozzi, R Marshall, HK TI SOFIA Secondary Mirror Mechanism Heavy Maintenance and Improvements SO GROUND-BASED AND AIRBORNE TELESCOPES VI SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Ground-Based and Airborne Telescopes VI CY JUN 26-JUL 01, 2016 CL Edinburgh, SCOTLAND SP SPIE DE secondary mirror; SOFIA; flexure; compliant mechanism; low temperature calibration; infrared; airborne telescope; autocollimator AB The Stratospheric Observatory For Infrared Astronomy (SOFIA) reached its full operational capability in 2014 and completed hundreds of observation flights. Since its installation in 2002, the Secondary Mirror Mechanism was subject to thousands of operating hours equivalent to millions of load cycles. During the aircraft heavy maintenance in fall 2014, a four month time window enabled the removal of the mechanism from the telescope structure for service and improvements. Next to visual corrosion- and crack-inspection of the flexures, critical electronic components (in particular the set of three eddy current position sensors that determine the mirror tilt) were replaced. Moreover, a detailed temperature dependent position calibration of the system was performed in a cold chamber to improve the pointing accuracy. Until then, a simple temperature independent linear gain was used to translate the sensor output voltage into a position. For accurate positioning across the whole temperature range, a temperature dependent correction function had to be developed. This calibration would have cost hours of observing time when performed in flight which made it an essential goal for completion during the maintenance period. An autocollimator was used as optical reference camera to measure the tip-tilt position of the secondary mirror in the cold chamber. Using this calibration setup, a pattern of many mirror positions in the tip-tilt domain was approached at several temperature points to provide a high resolution data set for the new multidimensional calibration function. Follow-up in-flight verification measurements confirmed a large improvement in pointing accuracy as soon as the temperature measurements were included into the position correction. Improvements of up to a factor of 10 were especially noticed in the lower temperature range. This contribution provides an insight into the work performed during the SOFIA - Secondary Mirror Mechanism maintenance with the focus on the temperature dependent position calibration. C1 [Lammen, Yannick; Reinacher, Andreas; Jakob, Holger; Graf, Friederike; Lachenmann, Michael; Krabbe, Alfred] Univ Stuttgart, Deutsch SOFIA Inst, Pfaffenwaldring 29, D-70569 Stuttgart, Germany. [Lammen, Yannick; Reinacher, Andreas; Jakob, Holger] NASA, SOFIA Airborne Syst Operat Ctr, Armstrong Flight Res Ctr, 2825 Ave P,Bldg 703, Palmdale, CA 93550 USA. [Kjelberg, Ivar; Droz, Serge] CSEM SA, Rue Jaquez Droz 1, CH-2002 Neuchatel, Switzerland. [Graf, Friederike; Lachenmann, Michael] NASA, SOFIA Sci Ctr, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Lammen, Y (reprint author), Univ Stuttgart, Deutsch SOFIA Inst, Pfaffenwaldring 29, D-70569 Stuttgart, Germany.; Lammen, Y (reprint author), NASA, SOFIA Airborne Syst Operat Ctr, Armstrong Flight Res Ctr, 2825 Ave P,Bldg 703, Palmdale, CA 93550 USA. NR 4 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0191-8; 978-1-5106-0192-5 J9 PROC SPIE PY 2016 VL 9906 AR UNSP 99061R DI 10.1117/12.2231352 PN 1 PG 11 WC Instruments & Instrumentation; Optics SC Instruments & Instrumentation; Optics GA BG2WM UT WOS:000387731100052 ER PT S AU Moore, AM Kasliwal, MM Gelino, CR Jencson, JE Jones, MI Kirkpatrick, JD Lau, RM Ofek, E Petrunin, Y Smith, R Terebizh, V Steinbring, E Yan, L AF Moore, Anna M. Kasliwal, Mansi M. Gelino, Christopher R. Jencson, Jacob E. Jones, Mike I. Kirkpatrick, J. Davy Lau, Ryan M. Ofek, Eran Petrunin, Yuri Smith, Roger Terebizh, Valery Steinbring, Eric Yan, Lin BE Hall, HJ Gilmozzi, R Marshall, HK TI Unveiling the Dynamic Infrared Sky with Gattini-IR SO GROUND-BASED AND AIRBORNE TELESCOPES VI SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Ground-Based and Airborne Telescopes VI CY JUN 26-JUL 01, 2016 CL Edinburgh, SCOTLAND SP SPIE DE Wide field infrared transient imaging in the Arctic and Antarctic AB While optical and radio transient surveys have enjoyed a renaissance over the past decade, the dynamic infrared sky remains virtually unexplored. The infrared is a powerful tool for probing transient events in dusty regions that have high optical extinction, and for detecting the coolest of stars that are bright only at these wavelengths. The fundamental roadblocks in studying the infrared time-domain have been the overwhelmingly bright sky background (250 times brighter than optical) and the narrow field-of-view of infrared cameras (largest is 0.6 sq deg). To begin to address these challenges and open a new observational window in the infrared, we present Palomar Gattini-IR: a 25 sq degree, 300mm aperture, infrared telescope at Palomar Observatory that surveys the entire accessible sky (20,000 sq deg) to a depth of 16.4 AB mag (J band, 1.25 um) every night. Palomar Gattini-IR is wider in area than every existing infrared camera by more than a factor of 40 and is able to survey large areas of sky multiple times. We anticipate the potential for otherwise infeasible discoveries, including, for example, the elusive electromagnetic counterparts to gravitational wave detections. With dedicated hardware in hand, and a F/1.44 telescope available commercially and cost-effectively, Palomar Gattini-IR will be on-sky in early 2017 and will survey the entire accessible sky every night for two years. We present an overview of the pathfinder Palomar Gattini-IR project, including the ambitious goal of sub-pixel imaging and ramifications of this goal on the opto-mechanical design and data reduction software. Palomar Gattini-IR will pave the way for a dual hemisphere, infrared-optimized, ultra-wide field high cadence machine called Turbo Gattini-IR. To take advantage of the low sky background at 2.5 um, two identical systems will be located at the polar sites of the South Pole, Antarctica and near Eureka on Ellesmere Island, Canada. Turbo Gattini-IR will survey 15,000 sq. degrees to a depth of 20 AB, the same depth of the VISTA VHS survey, every 2 hours with a survey efficiency of 97%. C1 [Moore, Anna M.; Smith, Roger] CALTECH, Opt Observ, 1200 E Calif Blvd,Mail Code 11-17, Pasadena, CA 91125 USA. [Kasliwal, Mansi M.; Jencson, Jacob E.] CALTECH, Div Phys Math & Astron, 1200 E Calif Blvd,Mail Code 249-17, Pasadena, CA 91125 USA. [Gelino, Christopher R.; Kirkpatrick, J. Davy; Yan, Lin] CALTECH, Infrared Proc & Anal Ctr, 770 S Wilson Ave,MS 100-22, Pasadena, CA 91125 USA. [Jones, Mike I.] Precis Opt Azle LLC, 816 Wayne Trail, Azle, TX 76020 USA. [Lau, Ryan M.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Ofek, Eran] Weizmann Inst Sci, IL-76100 Rehovot, Israel. [Petrunin, Yuri] Telescope Engn Co, 15730 W 6-th Ave, Golden, CO 80401 USA. [Terebizh, Valery] Crimean Astrophys Observ, Nauchnyi, Crimea, Ukraine. [Steinbring, Eric] Natl Res Council Canada, Herzberg Astron & Astrophys, 5071 West Saanich Rd, Victoria, BC V9E 2E7, Canada. RP Moore, AM (reprint author), CALTECH, Opt Observ, 1200 E Calif Blvd,Mail Code 11-17, Pasadena, CA 91125 USA. EM amoore@astro.caltech.edu NR 7 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0191-8; 978-1-5106-0192-5 J9 PROC SPIE PY 2016 VL 9906 AR UNSP 99062C DI 10.1117/12.2233694 PN 1 PG 12 WC Instruments & Instrumentation; Optics SC Instruments & Instrumentation; Optics GA BG2WM UT WOS:000387731100069 ER PT S AU Moretto, G Kuhn, JR Berdyugina, SV Langlois, M Tallon, M Thiebaut, E Halliday, D AF Moretto, Gil Kuhn, Jeff R. Berdyugina, Svetlana V. Langlois, Maud Tallon, Michel Thiebaut, Eric Halliday, David BE Hall, HJ Gilmozzi, R Marshall, HK TI Partially filled aperture interferometric telescopes: achieving large aperture and coronagraphic performance SO GROUND-BASED AND AIRBORNE TELESCOPES VI SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Ground-Based and Airborne Telescopes VI CY JUN 26-JUL 01, 2016 CL Edinburgh, SCOTLAND SP SPIE DE large telescopes; thin mirrors; redundant-baseline interferometry; phased array telescope; exoplanets AB The exponential growth in exoplanet studies and science cases requiring high contrast observations is a powerful reason for developing very large optical systems optimized for narrow-field science. Concepts which cross the boundary between fixed aperture telescopes and interferometers, combined with technologies that decrease the system moving mass, can violate the cost and mass scaling laws that make conventional large-aperture telescopes relatively expensive. Here we describe concepts of large, filled-aperture (Colossus) and partially filled aperture (ParFAIT) interferometric optical/IR telescope systems which break this scaling relation. These systems are dedicated to high dynamic range science such as detecting life and even civilizations on Earth-like planets. C1 [Moretto, Gil; Langlois, Maud; Tallon, Michel; Thiebaut, Eric] Ecole Normale Super Lyon, CNRS, CRAL, F-69561 St Genis Laval, France. [Kuhn, Jeff R.] Univ Hawaii, Inst Astron, 34 Ohia Ku, Maui, HI 96790 USA. [Berdyugina, Svetlana V.] Kiepenheuer Inst Sonnenphys, D-79104 Freiburg, Germany. [Berdyugina, Svetlana V.] Univ Hawaii, NASA Astrobiol Inst, 2680 Woodlawn Dr, Honolulu, HI 2680 USA. [Halliday, David] Dynam Struct Ltd, Port Coquitlam, BC, Canada. RP Moretto, G (reprint author), Ecole Normale Super Lyon, CNRS, CRAL, F-69561 St Genis Laval, France.; Kuhn, JR (reprint author), Univ Hawaii, Inst Astron, 34 Ohia Ku, Maui, HI 96790 USA. EM Gil.Moretto@ipn.in2p3.fr NR 10 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0191-8; 978-1-5106-0192-5 J9 PROC SPIE PY 2016 VL 9906 AR UNSP 99062B DI 10.1117/12.2233451 PN 1 PG 12 WC Instruments & Instrumentation; Optics SC Instruments & Instrumentation; Optics GA BG2WM UT WOS:000387731100068 ER PT S AU Troy, M Chanan, G Michaels, S Dekens, F Hein, R Herzig, S Karban, R Nissly, C Roberts, J Rud, M Seo, BJ AF Troy, Mitchell Chanan, Gary Michaels, Scott Dekens, Frank Hein, Randy Herzig, Sebastian Karban, Robert Nissly, Carl Roberts, Jennifer Rud, Michael Seo, Byoung-Joon BE Hall, HJ Gilmozzi, R Marshall, HK TI The Alignment and Phasing System for the Thirty Meter Telescope: Risk Mitigation and Status Update SO GROUND-BASED AND AIRBORNE TELESCOPES VI SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Ground-Based and Airborne Telescopes VI CY JUN 26-JUL 01, 2016 CL Edinburgh, SCOTLAND SP SPIE DE Telescopes; Segmented Mirrors; Optical Alignment; Phasing ID MIRROR SEGMENTS; KECK TELESCOPES; ALGORITHM AB Alignment and Phasing System (APS) is responsible for the optical alignment via starlight of the approximately 12,000 degrees of freedom of the primary, secondary and tertiary mirrors of Thirty Meter Telescope (TMT). APS is based on the successful Phasing Camera System (PCS) used to align the Keck Telescopes. Since the successful APS conceptual design in 2007, work has concentrated on risk mitigation, use case generation, and alignment algorithm development and improvement. Much of the risk mitigation effort has centered around development and testing of prototype APS software which will replace the current PCS software used at Keck. We present an updated APS design, example use cases and discuss, in detail, the risk mitigation efforts. C1 [Troy, Mitchell; Dekens, Frank; Hein, Randy; Herzig, Sebastian; Karban, Robert; Nissly, Carl; Roberts, Jennifer; Rud, Michael; Seo, Byoung-Joon] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Chanan, Gary] Univ Calif Irvine, Dept Phys & Astron, Irvine, CA 92697 USA. [Michaels, Scott] Thirty Meter Telescope, Pasadena, CA 91124 USA. RP Troy, M (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM mtroy@jpl.nasa.gov NR 13 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0191-8; 978-1-5106-0192-5 J9 PROC SPIE PY 2016 VL 9906 AR UNSP 99066A DI 10.1117/12.2231913 PN 1 PG 14 WC Instruments & Instrumentation; Optics SC Instruments & Instrumentation; Optics GA BG2WM UT WOS:000387731100192 ER PT S AU Wiedemann, M Wolf, J McGrotty, P Edwards, C Krabbe, A AF Wiedemann, Manuel Wolf, Juergen McGrotty, Paul Edwards, Chris Krabbe, Alfred BE Hall, HJ Gilmozzi, R Marshall, HK TI A high-sensitivity EM-CCD camera for the open port telescope cavity of SOFIA SO GROUND-BASED AND AIRBORNE TELESCOPES VI SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Ground-Based and Airborne Telescopes VI CY JUN 26-JUL 01, 2016 CL Edinburgh, SCOTLAND SP SPIE DE Stratospheric Observatory for Infrared Astronomy; SOFIA; CCD; Tracking Cameras; Environmental Testing AB The Stratospheric Observatory for Infrared Astronomy (SOFIA) has three target acquisition and tracking cameras. All three imagers originally used the same cameras, which did not meet the sensitivity requirements, due to low quantum efficiency and high dark current. The Focal Plane Imager (FPI) suffered the most from high dark current, since it operated in the aircraft cabin at room temperatures without active cooling. In early 2013 the FPI was upgraded with an iXon3 888 from Andor Techonolgy. Compared to the original cameras, the iXon3 has a factor five higher QE, thanks to its back-illuminated sensor, and orders of magnitude lower dark current, due to a thermo-electric cooler and "inverted mode operation." This leads to an increase in sensitivity of about five stellar magnitudes. The Wide Field Imager (WFI) and Fine Field Imager (FFI) shall now be upgraded with equally sensitive cameras. However, they are exposed to stratospheric conditions in flight (typical conditions: T approximate to -40 degrees C, p approximate to 0:1 atm) and there are no off-the-shelf CCD cameras with the performance of an iXon3, suited for these conditions. Therefore, Andor Technology and the Deutsches SOFIA Institut (DSI) are jointly developing and qualifying a camera for these conditions, based on the iXon3 888. These changes include replacement of electrical components with MIL-SPEC or industrial grade components and various system optimizations, a new data interface that allows the image data transmission over similar to 30m of cable from the camera to the controller, a new power converter in the camera to generate all necessary operating voltages of the camera locally and a new housing that fulfills airworthiness requirements. A prototype of this camera has been built and tested in an environmental test chamber at temperatures down to T = -62 degrees C and pressure equivalent to 50 000 ft altitude. In this paper, we will report about the development of the camera and present results from the environmental testing. C1 [Wiedemann, Manuel; Wolf, Juergen; Krabbe, Alfred] Univ Stuttgart, Deutsch SOFIA Inst, Pfaffenwaldring 29, D-70569 Stuttgart, Germany. [Wiedemann, Manuel; Wolf, Juergen] NASA, SOFIA Sci Ctr, Ames Res Ctr, Mail Stop 211-1, Moffett Field, CA 94035 USA. [McGrotty, Paul; Edwards, Chris] Andor Technol, 7 Millennium Way,Springvale Business Pk, Belfast BT12 7AL, Antrim, North Ireland. RP Wiedemann, M (reprint author), Univ Stuttgart, Deutsch SOFIA Inst, Pfaffenwaldring 29, D-70569 Stuttgart, Germany.; Wiedemann, M (reprint author), NASA, SOFIA Sci Ctr, Ames Res Ctr, Mail Stop 211-1, Moffett Field, CA 94035 USA. EM wiedemann@dsi.uni-stuttgart.de NR 7 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0191-8; 978-1-5106-0192-5 J9 PROC SPIE PY 2016 VL 9906 AR UNSP 99061U DI 10.1117/12.2231809 PN 1 PG 16 WC Instruments & Instrumentation; Optics SC Instruments & Instrumentation; Optics GA BG2WM UT WOS:000387731100054 ER PT J AU Radhakrishnan, R Edmonson, WW Afghah, F Rodriguez-Osorio, RM Pinto, F Burleigh, SC AF Radhakrishnan, Radhika Edmonson, William W. Afghah, Fatemeh Rodriguez-Osorio, Ramon Martinez Pinto, Frank, Jr. Burleigh, Scott C. TI Survey of Inter-Satellite Communication for Small Satellite Systems: Physical Layer to Network Layer View SO IEEE COMMUNICATIONS SURVEYS AND TUTORIALS LA English DT Article DE Artificial satellites; satellite communication; software defined networking; satellite antennas; access protocols; routing protocols ID INTERPLANETARY INTERNET; DELAY-TOLERANT; IP NETWORKS; MISSION AB Small satellite systems enable a whole new class of missions for navigation, communications, remote sensing, and scientific research for both civilian and military purposes. As individual spacecraft are limited by the size, mass, and power constraints, mass-produced small satellites in large constellations or clusters could be useful in many science missions such as gravity mapping, tracking of forest fires, finding water resources, etc. The proliferation of small satellites will enable a better understanding of the near-Earth environment and provide an efficient and economical means to access the space through the use of multi-satellite solution. Constellation of satellites provide improved spatial and temporal resolution of the target. Small satellite constellations contribute innovative applications by replacing a single asset with several very capable spacecraft, which opens the door to new applications. Future space missions are envisioned to become more complex and operate farther from Earth, and will need to support autonomous operations with minimal human intervention. With increasing levels of autonomy, there will be a need for remote communication networks to enable communication between spacecraft. These space-based networks will need to configure and maintain dynamic routes, manage intermediate nodes, and reconfigure themselves to achieve mission objectives. Hence, inter-satellite communication is a key aspect when satellites fly in formation. In this survey, we present the various research being conducted in the small satellite community for implementing inter-satellite communications based on the open system interconnection (OSI) model. This survey also reviews the various design parameters applicable to the first three layers of the OSI model, i.e., physical, data link, and network layer. Based on the survey, we also present a comprehensive list of design parameters useful for achieving inter-satellite communications for multiple small satellite missions. Specific topics include proposed solutions for some of the challenges faced by small satellite systems, enabling operations using a network of small satellites, and some examples of small satellite missions involving formation flying aspects. C1 [Radhakrishnan, Radhika; Edmonson, William W.; Pinto, Frank, Jr.] North Carolina A&T State Univ, Dept Elect & Comp Engn, Greensboro, NC 27411 USA. [Afghah, Fatemeh] No Arizona Univ, Dept Elect Engn & Comp Sci, Flagstaff, AZ 86001 USA. [Rodriguez-Osorio, Ramon Martinez] Univ Politecn Madrid, Madrid 28040, Spain. [Burleigh, Scott C.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Radhakrishnan, R (reprint author), North Carolina A&T State Univ, Dept Elect & Comp Engn, Greensboro, NC 27411 USA. EM rradhakr@ncat.edu; wwedmons@ncat.edu; fatemeh.afghah@nau.edu; ramon@gr.ssr.upm.es; fmpinto@ncat.edu; scott.c.burleigh@jpl.nasa.gov FU Langley Professor Program from the National Institute of Aerospace; North Carolina Space Grant [NNX10A168H]; Jet Propulsion Laboratory, California Institute of Technology; National Aeronautics and Space Administration FX This work was supported in part by the Langley Professor Program from the National Institute of Aerospace, in part by the North Carolina Space Grant under New Investigator Award NNX10A168H, and in part by the Jet Propulsion Laboratory, California Institute of Technology, under a contract with the National Aeronautics and Space Administration. NR 82 TC 0 Z9 0 U1 5 U2 5 PU IEEE-INST ELECTRICAL ELECTRONICS ENGINEERS INC PI PISCATAWAY PA 445 HOES LANE, PISCATAWAY, NJ 08855-4141 USA SN 1553-877X J9 IEEE COMMUN SURV TUT JI IEEE Commun. Surv. Tutor. PY 2016 VL 18 IS 4 BP 2442 EP 2473 DI 10.1109/COMST.2016.2564990 PG 32 WC Computer Science, Information Systems; Telecommunications SC Computer Science; Telecommunications GA ED9OS UT WOS:000389202500006 ER PT S AU Miller, CE Frankenberg, C Kuhnert, AC Spiers, GD Eldering, A Rud, M Pagano, TS Wilson, DW Brooks, C Jaffe, DT AF Miller, Charles E. Frankenberg, Christian Kuhnert, Andreas C. Spiers, Gary D. Eldering, Annmarie Rud, Mayer Pagano, Thomas S. Wilson, Daniel W. Brooks, Cynthia Jaffe, Daniel T. BE Silny, JF Ientilucci, EJ TI Capturing Complete Spatial Context in Satellite Observations of Greenhouse Gases SO IMAGING SPECTROMETRY XXI SE Proceedings of SPIE LA English DT Proceedings Paper CT SPIE's 21st Imaging Spectrometry Conference CY AUG 29-30, 2016 CL San Diego, CA SP SPIE DE Carbon Dioxide (CO2); Methane (CH4); Carbon Monoxide (CO); satellite; remote sensing; wide-field; Low Earth Orbit (LEO); mapping ID SCIAMACHY ONBOARD ENVISAT; SENTINEL-5 PRECURSOR; ATMOSPHERIC CO2; RETRIEVAL; METHANE; FLUORESCENCE; EMISSIONS; CH4; PATTERNS; CLIMATE AB Scientific consensus from a 2015 pre-Decadal Survey workshop highlighted the essential need for a wide-swath (mapping) low earth orbit (LEO) instrument delivering carbon dioxide (CO2), methane (CH4), and carbon monoxide (CO) measurements with global coverage. OCO-2 pioneered space-based CO2 remote sensing, but lacks the CH4, CO and mapping capabilities required for an improved understanding of the global carbon cycle. The Carbon Balance Observatory (CARBO) advances key technologies to enable high-performance, cost-effective solutions for a space-based carbon-climate observing system. CARBO is a compact, modular, 15-30 degrees field of view spectrometer that delivers high-precision CO2, CH4, CO and solar induced chlorophyll fluorescence (SIF) data with weekly global coverage from LEO. CARBO employs innovative immersion grating technologies to achieve diffraction-limited performance with OCO-like spatial (2x2 km(2)) and spectral (lambda/Delta lambda approximate to 20,000) resolution in a package that is >50% smaller, lighter and more cost-effective. CARBO delivers a 25- to 50-fold increase in spatial coverage compared to OCO-2 with no loss of detection sensitivity. Individual CARBO modules weigh < 20 kg, opening diverse new space-based platform opportunities. C1 [Miller, Charles E.; Frankenberg, Christian; Kuhnert, Andreas C.; Spiers, Gary D.; Eldering, Annmarie; Rud, Mayer; Pagano, Thomas S.; Wilson, Daniel W.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Frankenberg, Christian] CALTECH, Div Geol & Planetary Sci, 1200 Calif Blvd, Pasadena, CA 91125 USA. [Brooks, Cynthia; Jaffe, Daniel T.] Univ Texas, Dept Astron, Austin, TX 78712 USA. RP Miller, CE (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RI Frankenberg, Christian/A-2944-2013 OI Frankenberg, Christian/0000-0002-0546-5857 NR 43 TC 0 Z9 0 U1 2 U2 2 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0343-1; 978-1-5106-0344-8 J9 PROC SPIE PY 2016 VL 9976 AR UNSP 997609 DI 10.1117/12.2238766 PG 13 WC Instruments & Instrumentation; Spectroscopy SC Instruments & Instrumentation; Spectroscopy GA BG5QQ UT WOS:000389680900006 ER PT S AU Van Gorp, B Mouroulis, P Wilson, DW Green, RO Rodriguez, JI Liggett, E Thompson, DR AF Van Gorp, B. Mouroulis, P. Wilson, D. W. Green, R. O. Rodriguez, J. I. Liggett, E. Thompson, D. R. BE Silny, JF Ientilucci, EJ TI Compact Wide Swath Imaging Spectrometer (CWIS): Alignment and laboratory calibration SO IMAGING SPECTROMETRY XXI SE Proceedings of SPIE LA English DT Proceedings Paper CT SPIE's 21st Imaging Spectrometry Conference CY AUG 29-30, 2016 CL San Diego, CA SP SPIE DE Imaging Spectrometer; Imaging spectroscopy; Dyson spectrometer AB The Compact Wide Swath Imaging Spectrometer (CWIS) is a pushbroom imaging spectrometer for the solar reflected spectrum (380-2510 nm) with wide swath (1600/1280 elements), fast optical speed (F/1.8), and high uniformity (>= 95%). CWIS is currently being tested at the Jet Propulsion Laboratory and is intended to address the need for high signal-to-noise ratio (SNR) compact imaging spectrometer systems for the visible to short wave infrared wavelength (VSWIR) range. We give an overview of the instrument functionality, describe the spectrometer alignment and system integration and report laboratory data that include spatial, spectral and radiometric calibration. C1 [Van Gorp, B.; Mouroulis, P.; Wilson, D. W.; Green, R. O.; Rodriguez, J. I.; Liggett, E.; Thompson, D. R.] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Van Gorp, B (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. EM byron.e.van.gorp@jpl.nasa.gov NR 5 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0343-1; 978-1-5106-0344-8 J9 PROC SPIE PY 2016 VL 9976 AR UNSP 997605 DI 10.1117/12.2239080 PG 8 WC Instruments & Instrumentation; Spectroscopy SC Instruments & Instrumentation; Spectroscopy GA BG5QQ UT WOS:000389680900003 ER PT S AU Roberts, LC Burruss, R Fregoso, S Herzog, H MazzoIa, S Roberts, JE Spiers, GD Truong, TN AF Roberts, Lewis C., Jr. Burruss, Rick Fregoso, Santos Herzog, Harrison MazzoIa, Sabina Roberts, Jennifer E. Spiers, Gary D. Truong, Tuan N. BE VanEijk, AMJ Davis, CC Hammel, SM TI The Adaptive Optics and Transmit System for NASA's Laser Communications Relay Demonstration Project SO LASER COMMUNICATION AND PROPAGATION THROUGH THE ATMOSPHERE AND OCEANS V SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Laser Communication and Propagation through the Atmosphere and Oceans V CY AUG 30-31, 2016 CL San Diego, CA SP SPIE DE Laser Communication; Adaptive Optics ID TELESCOPE AB The Laser Communication Relay Demonstration is NASA's multi-year demonstration of laser communication to a geosynchronous satellite. We are currently assembling the optical system for the first of the two baseline ground stations. The optical system consists of an adaptive optics system, the transmit system and a camera for target acquisition. The adaptive optics system is responsible for compensating the downlink beam for atmospheric turbulence and coupling it into the modem's single mode fiber. The adaptive optics system is a woofer/tweeter design, with one deformable mirror correcting for low spatial frequencies with large amplitude and a second deformable mirror correcting for high spatial frequencies with small amplitude. The system uses a Shack-Hartmann wavefront sensor. The transmit system relays four beacon beams and one communication laser to the telescope for propagation to the space terminal. Both the uplink and downlink beams are centered at 1.55 microns. We present an overview of the design of the system as well as performance predictions including time series of coupling efficiency and expected uplink beam quality. C1 [Roberts, Lewis C., Jr.; Burruss, Rick; Fregoso, Santos; Herzog, Harrison; MazzoIa, Sabina; Roberts, Jennifer E.; Spiers, Gary D.; Truong, Tuan N.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Roberts, LC (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM lewis.c.roberts@jpl.nasa.gov NR 16 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0349-3; 978-1-5106-0350-9 J9 PROC SPIE PY 2016 VL 9979 AR UNSP 99790I DI 10.1117/12.2238589 PG 10 WC Optics; Telecommunications SC Optics; Telecommunications GA BG5QN UT WOS:000389680600015 ER PT S AU Refaat, TF Petros, M Antill, CW Singh, UN Yu, JR AF Refaat, Tamer F. Petros, Mulugeta Antill, Charles W. Singh, Upendra N. Yu, Jirong BE Singh, UN Sugimoto, N Jayaraman, A Seshasai, MVR TI Wavelength locking to CO2 absorption line-center for 2-mu m pulsed IPDA lidar application SO LIDAR REMOTE SENSING FOR ENVIRONMENTAL MONITORING XV SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Lidar Remote Sensing for Environmental Monitoring XV CY APR 04-07, 2016 CL Indian Soc Remote Sensing, New Delhi, INDIA SP SPIE, Indian Space Res Org, Natl Aeronaut & Space Adm, Minist Earth Sci HO Indian Soc Remote Sensing DE Active remote sensing; carbon dioxide; IPDA lidar; triple-pulse laser; wavelength locking; mid IR laser ID MU-M AB An airborne 2-mu m triple-pulse integrated path differential absorption (IPDA) lidar is currently under development at NASA Langley Research Center (LaRC). This IPDA lidar system targets both atmospheric carbon dioxide (CO2) and water vapor (H2O) column measurements. Independent wavelength control of each of the transmitted laser pulses is a key feature for the success of this instrument. The wavelength control unit provides switching, tuning and locking for each pulse in reference to a 2-mu m CW laser source locked to CO2 line-center. Targeting the CO2 R30 line center, at 2050.967 nm, a wavelength locking unit has been integrated using semiconductor laser diode. The CO2 center-line locking unit includes a laser diode current driver, temperature controller, center-line locking controller and CO2 absorption cell. This paper presents the CO2 center-line locking unit architecture, characterization procedure and results. Assessment of wavelength jitter on the IPDA measurement error will also be addressed by comparison to the system design. C1 [Refaat, Tamer F.; Petros, Mulugeta; Antill, Charles W.; Singh, Upendra N.; Yu, Jirong] NASA, Langley Res Ctr, 5N Dryden St,MS 468, Hampton, VA 23681 USA. RP Refaat, TF (reprint author), NASA, Langley Res Ctr, 5N Dryden St,MS 468, Hampton, VA 23681 USA. NR 6 TC 1 Z9 1 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0120-8 J9 PROC SPIE PY 2016 VL 9879 AR UNSP 987904 DI 10.1117/12.2224950 PG 8 WC Remote Sensing; Optics SC Remote Sensing; Optics GA BG5QW UT WOS:000389681400003 ER PT S AU Singh, UN Petros, M Refaat, TF Yu, JR AF Singh, Upendra N. Petros, Mulugeta Refaat, Tamer F. Yu, Jirong BE Singh, UN Sugimoto, N Jayaraman, A Seshasai, MVR TI 2-micron triple-pulse integrated path differential absorption lidar development for simultaneous airborne column measurements of carbon dioxide and water vapor in the atmosphere SO LIDAR REMOTE SENSING FOR ENVIRONMENTAL MONITORING XV SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Lidar Remote Sensing for Environmental Monitoring XV CY APR 04-07, 2016 CL Indian Soc Remote Sensing, New Delhi, INDIA SP SPIE, Indian Space Res Org, Natl Aeronaut & Space Adm, Minist Earth Sci HO Indian Soc Remote Sensing DE Active remote sensing; carbon dioxide; water vapor; DIAL; IPDA lidar; triple-pulse laser ID LASER; CO2 AB For more than 15 years, NASA Langley Research Center (LaRC) has contributed in developing several 2-micron carbon dioxide active remote sensors using the DIAL technique. Currently, an airborne 2-micron triple-pulse integrated path differential absorption (IPDA) lidar is under development at NASA LaRC. This paper focuses on the advancement of the 2-micron triple-pulse IPDA lidar development. Updates on the state-of-the-art triple-pulse laser transmitter will be presented including the status of wavelength control, packaging and lidar integration. In addition, receiver development updates will also be presented, including telescope integration, detection systems and data acquisition electronics. Future plan for IPDA lidar system for ground integration, testing and flight validation will be presented. C1 [Singh, Upendra N.] NASA, Langley Res Ctr, Engn & Safety Ctr, Hampton, VA 23665 USA. [Petros, Mulugeta; Refaat, Tamer F.; Yu, Jirong] NASA, Langley Res Ctr, Remote Sensing Branch, Hampton, VA 23665 USA. RP Singh, UN (reprint author), NASA, Langley Res Ctr, Engn & Safety Ctr, Hampton, VA 23665 USA. NR 13 TC 1 Z9 1 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0120-8 J9 PROC SPIE PY 2016 VL 9879 AR UNSP 987902 DI 10.1117/12.2223681 PG 10 WC Remote Sensing; Optics SC Remote Sensing; Optics GA BG5QW UT WOS:000389681400001 ER PT S AU Zhou, DK Larar, AM Liu, X Tian, JL Smith, WL Kizer, SH Goldberg, MD AF Zhou, Daniel K. Larar, Allen M. Liu, Xu Tian, Jialin Smith, William L. Kizer, Susan H. Goldberg, Mitch D. BE Larar, AM Chauhan, P Suzuki, M Wang, J TI Second SNPP Cal/Val campaign: environmental data retrieval analysis SO MULTISPECTRAL, HYPERSPECTRAL, AND ULTRASPECTRAL REMOTE SENSING TECHNOLOGY, TECHNIQUES AND APPLICATIONS VI SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Multispectral, Hyperspectral, and Ultraspectral Remote Sensing Technology, Techniques and Applications VI CY APR 04-07, 2016 CL Indian Soc Remote Sensing, New Delhi, INDIA SP SPIE, Indian Space Res Org, Minist Earth Sci, Natl Aeronaut & Space Adm HO Indian Soc Remote Sensing DE Remote sensing; hyperspectral; ultraspectral; inversion; temperature; moisture; validation ID VALIDATION; EAQUATE AB Satellite ultraspectral infrared sensors provide key data records essential for weather forecasting and climate change science. The Suomi National Polar-orbiting Partnership (Soumi NPP) satellite Environmental Data Records (EDRs) are retrieved from calibrated ultraspectral radiance or Sensor Data Records (SDRs). Understanding the accuracy of retrieved EDRs is critical. The second Suomi NPP Calibration/Validation field campaign was conducted during March 2015 with flights over Greenland. The NASA high-altitude ER-2 aircraft carrying ultraspectral interferometer sounders such as the National Airborne Sounder Testbed-Interferometer (NAST-I) flew under the Suomi NPP satellite that carries the Cross-track Infrared Sounder (CrIS) and the Advanced Technology Microwave Sounder (ATMS). Herein we inter-compare the EDRs produced from different retrieval algorithms employed on these satellite and aircraft campaign data. The available radiosonde measurements together with the European Centre for Medium-Range Weather Forecasts (ECMWF) analyses are used to assess atmospheric temperature and moisture retrievals from the aircraft and satellite platforms. Preliminary results of this experiment under a winter, Arctic environment are presented. C1 [Zhou, Daniel K.; Larar, Allen M.; Liu, Xu; Tian, Jialin] NASA Langley Res Ctr, Sci Directorate, Hampton, VA 23666 USA. [Smith, William L.; Kizer, Susan H.] Sci Syst & Applications Inc, Hampton, VA USA. [Goldberg, Mitch D.] NOAA NESDIS, College Pk, MD USA. RP Zhou, DK (reprint author), NASA Langley Res Ctr, Sci Directorate, Hampton, VA 23666 USA. EM daniel.k.zhou@nasa.gov NR 17 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0121-5 J9 PROC SPIE PY 2016 VL 9880 AR 988008 DI 10.1117/12.2223074 PG 6 WC Remote Sensing; Optics SC Remote Sensing; Optics GA BG5UZ UT WOS:000389776100004 ER PT S AU Day, J Yoon, H Kim, J Choi, SH Song, KD AF Day, John Yoon, Hargsoon Kim, Jaehwan Choi, Sang H. Song, Kyo D. BE Varadan, VK TI Simulation Study of a High Power Density Rectenna Array for Biomedical Implantable Devices SO NANOSENSORS, BIOSENSORS, AND INFO-TECH SENSORS AND SYSTEMS 2016 SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Nanosensors, Biosensors, and Info-Tech Sensors and Systems CY MAR 21-24, 2016 CL Las Vegas, NV SP SPIE, Polytec Inc, OZ Opt Ltd, APS Dynam Inc, TA Electroforce Corp, ElectroForce Syst Grp, Inst Phys, Amer Elements AB The integration of wireless power transmission devices using microwaves into the biomedical field is close to a practical reality. Implanted biomedical devices need a long lasting power source or continuous power supply. Recent development of high efficiency rectenna technology enables continuous power supply to these implanted devices. Due to the size limit of most of medical devices, it is imperative to minimize the rectenna as well. The research reported in this paper reviews the effects of close packing the rectenna elements which show the potential of directly empowering the implanted devices, especially within a confined area. The rectenna array is tested in the X band frequency range. C1 [Day, John; Yoon, Hargsoon; Song, Kyo D.] Norfolk State Univ, Dept Engn, Norfolk, VA 23504 USA. [Kim, Jaehwan] Inha Univ, Dept Mech Engn, Inchon, South Korea. [Choi, Sang H.] NASA, Langley Res Ctr, Hampton, VA 23665 USA. RP Song, KD (reprint author), Norfolk State Univ, Dept Engn, Norfolk, VA 23504 USA. EM ksong@nsu.edu NR 19 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0043-0 J9 PROC SPIE PY 2016 VL 9802 AR UNSP 980217 DI 10.1117/12.2222603 PG 15 WC Engineering, Multidisciplinary; Instruments & Instrumentation SC Engineering; Instruments & Instrumentation GA BG5RB UT WOS:000389682000028 ER PT S AU Duzik, AJ Choi, SH AF Duzik, Adam J. Choi, Sang H. BE Varadan, VK TI Low Temperature Rhombohedral Single Crystal SiGe Epitaxy on c-plane Sapphire SO NANOSENSORS, BIOSENSORS, AND INFO-TECH SENSORS AND SYSTEMS 2016 SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Nanosensors, Biosensors, and Info-Tech Sensors and Systems CY MAR 21-24, 2016 CL Las Vegas, NV SP SPIE, Polytec Inc, OZ Opt Ltd, APS Dynam Inc, TA Electroforce Corp, ElectroForce Syst Grp, Inst Phys, Amer Elements DE Magnetron Sputtering Deposition; Semiconductor Devices; Group IV Semiconductor Materials; Bandgap Engineering; X-ray Diffraction ID GERMANIUM; SILICON; CDTE AB Current best practice in epitaxial growth of rhombohedral SiGe onto (0001) sapphire (Al2O3) substrate surfaces requires extreme conditions to grow a single crystal SiGe film. Previous models described the sapphire surface reconstruction as the overriding factor in rhombohedral epitaxy, requiring a high temperature Al-terminated surface for high quality films. Temperatures in the 850-1100 degrees C range were thought to be necessary to get SiGe to form coherent atomic matching between the (111) SiGe plane and the (0001) sapphire surface. Such fabrication conditions are difficult and uneconomical, hindering widespread application. This work proposes an alternative model that considers the bulk sapphire structure and determines how the SiGe film nucleates and grows. Accounting for thermal expansion effects, calculations using this new model show that both pure Ge and SiGe can form single crystal films in the 450-550 degrees C temperature range. Experimental results confirm these predictions, where x-ray diffraction and atomic force microscopy show the films fabricated at low temperature rival the high temperature films in crystallographic and surface quality. Finally, an explanation is provided for why films of comparable high quality can be produced in either temperature range. C1 [Duzik, Adam J.] Natl Inst Aerosp, 100 Explorat Way, Hampton, VA 23666 USA. [Choi, Sang H.] NASA, Langley Res Ctr, 8 West Taylor St, Hampton, VA 23681 USA. RP Duzik, AJ (reprint author), Natl Inst Aerosp, 100 Explorat Way, Hampton, VA 23666 USA. EM adam.j.duzik@nasa.gov NR 6 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0043-0 J9 PROC SPIE PY 2016 VL 9802 AR UNSP 98020D DI 10.1117/12.2218646 PG 11 WC Engineering, Multidisciplinary; Instruments & Instrumentation SC Engineering; Instruments & Instrumentation GA BG5RB UT WOS:000389682000007 ER PT S AU Duzik, AJ Choi, SH AF Duzik, Adam J. Choi, Sang H. BE Varadan, VK TI Investigation of Miniaturized Radioisotope Thermionic Power Generation for General Use SO NANOSENSORS, BIOSENSORS, AND INFO-TECH SENSORS AND SYSTEMS 2016 SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Nanosensors, Biosensors, and Info-Tech Sensors and Systems CY MAR 21-24, 2016 CL Las Vegas, NV SP SPIE, Polytec Inc, OZ Opt Ltd, APS Dynam Inc, TA Electroforce Corp, ElectroForce Syst Grp, Inst Phys, Amer Elements DE Radioisotope thermoelectric generators; thermionic generator; thermionic emission ID EMISSION; HEXABORIDES; DIAMOND; RTG AB Radioisotope thermoelectric generators (RTGs) running off the radioisotope Pu-238 are the current standard in deep space probe power supplies. While reliable, these generators are very inefficient, operating at only similar to 7% efficiency. As an alternative, more efficient radioisotope thermionic emission generators (RTIGs) are being explored. Like RTGs, current RTIGs concepts use exotic materials for the emitter, limiting applicability to space and other niche applications. The high demand for long-lasting mobile power sources would be satisfied if RTIGs could be produced inexpensively. This work focuses on exposing several common materials, such as Al, stainless steel, W, Si, and Cu, to elevated temperatures under vacuum to determine the efficiency of each material as inexpensive replacements for thermoelectric materials. C1 [Duzik, Adam J.] Natl Inst Aerosp, 100 Explorat Way, Hampton, VA 23666 USA. [Choi, Sang H.] NASA, Langley Res Ctr, 8 West Taylor St, Hampton, VA 23681 USA. RP Duzik, AJ (reprint author), Natl Inst Aerosp, 100 Explorat Way, Hampton, VA 23666 USA. EM adam.j.duzik@nasa.gov NR 17 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0043-0 J9 PROC SPIE PY 2016 VL 9802 AR UNSP 98020C DI 10.1117/12.2222039 PG 8 WC Engineering, Multidisciplinary; Instruments & Instrumentation SC Engineering; Instruments & Instrumentation GA BG5RB UT WOS:000389682000006 ER PT S AU Martin, B Boucarut, R Gore, R Penn, J AF Martin, Bryan Boucarut, Ray Gore, Richard Penn, Jonathan BE Davis, AJ Hahlweg, CF Mulley, JR TI Design, Construction and Testing of Lateral Transfer Retroreflectors for Space-Based Applications SO NOVEL OPTICAL SYSTEMS DESIGN AND OPTIMIZATION XIX SE Proceedings of SPIE LA English DT Proceedings Paper CT 19th Annual Conference on Novel Optical Systems Design and Optimization CY AUG 29-30, 2016 CL San Diego, CA SP SPIE DE Optics; Lateral Transfer Retroreflector; LTR; Hollow Retroreflector; LTHR; ICESat-2 AB The function of a Lateral Transfer Retroreflector is to accurately shift a beam of light laterally, while changing its direction 180 degrees. It uses three optically-flat, reflective surfaces located in mutually perpendicular planes to return an output beam parallel, but laterally separated from the input beam. The device maintains parallelism of the two beams regardless of its own orientation. From mid-2011 to late 2015, two types of LTR were designed, developed, produced and tested at Goddard Space Flight Center in Greenbelt Maryland. Information about the development process, along with performance results is given. C1 [Martin, Bryan; Boucarut, Ray; Gore, Richard; Penn, Jonathan] Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Martin, B (reprint author), Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. NR 2 TC 0 Z9 0 U1 1 U2 1 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0287-8; 978-1-5106-0288-5 J9 PROC SPIE PY 2016 VL 9948 AR UNSP 99480I DI 10.1117/12.2242471 PG 17 WC Optics SC Optics GA BG5US UT WOS:000389774400015 ER PT S AU Scola, S Stavely, R Jackson, T Boyer, C Osmundsen, J Turczynski, C Stimson, C AF Scola, Salvatore Stavely, Rebecca Jackson, Trevor Boyer, Charlie Osmundsen, Jim Turczynski, Craig Stimson, Chad BE Kahan, MA LevineWest, MB TI Development and Implementation of a Generic Analysis Template for Structural-Thermal-Optical-Performance Modeling SO OPTICAL MODELING AND PERFORMANCE PREDICTIONS VIII SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Optical Modeling and Performance Predictions VIII CY AUG 31-SEP 01, 2016 CL San Diego, CA SP SPIE DE structural thermal optical performance analysis; STOP analysis; analysis template; optomechanical modeling; knowledge capture AB Performance-related effects of system level temperature changes can be a key consideration in the design of many types of optical instruments. This is especially true for space-based imagers, which may require complex thermal control systems to maintain alignment of the optical components. Structural-Thermal-Optical-Performance (STOP) analysis is a multi-disciplinary process that can be used to assess the performance of these optical systems when subjected to the expected design environment. This type of analysis can be very time consuming, which makes it difficult to use as a trade study tool early in the project life cycle. In many cases, only one or two iterations can be performed over the course of a project. This limits the design space to best practices since it may be too difficult, or take too long, to test new concepts analytically. In order to overcome this challenge, automation, and a standard procedure for performing these studies is essential. A methodology was developed within the framework of the Comet software tool that captures the basic inputs, outputs, and processes used in most STOP analyses. This resulted in a generic, reusable analysis template that can be used for design trades for a variety of optical systems. The template captures much of the upfront setup such as meshing, boundary conditions, data transfer, naming conventions, and post-processing, and therefore saves time for each subsequent project. A description of the methodology and the analysis template is presented, and results are described for a simple telescope optical system. C1 [Scola, Salvatore; Stavely, Rebecca; Jackson, Trevor; Boyer, Charlie; Osmundsen, Jim; Turczynski, Craig; Stimson, Chad] NASA, Langley Res Ctr, 1 Langley Blvd, Hampton, VA 23681 USA. RP Scola, S (reprint author), NASA, Langley Res Ctr, 1 Langley Blvd, Hampton, VA 23681 USA. NR 3 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0297-7; 978-1-5106-0298-4 J9 PROC SPIE PY 2016 VL 9953 AR UNSP 99530A DI 10.1117/12.2236427 PG 21 WC Optics SC Optics GA BG5UU UT WOS:000389775100009 ER PT S AU Sellar, RG Deen, RG Huffman, WC Willson, RG AF Sellar, R. Glenn Deen, Robert G. Huffman, William C. Willson, Reginald G. BE Kahan, MA LevineWest, MB TI Modeling the effects of distortion, contrast, and signal-to-noise ratio on stereophotogrammetric range mapping SO OPTICAL MODELING AND PERFORMANCE PREDICTIONS VIII SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Optical Modeling and Performance Predictions VIII CY AUG 31-SEP 01, 2016 CL San Diego, CA SP SPIE DE Stereophotogrammetry; stereo imaging; 3D imaging AB Stereophotogrammetry typically employs a pair of cameras, or a single moving camera, to acquire pairs of images from different camera positions, in order to create a three dimensional 'range map' of the area being observed. Applications of this technique for building three-dimensional shape models include aerial surveying, remote sensing, machine vision, and robotics. Factors that would be expected to affect the quality of the range maps include the projection function (distortion) of the lenses and the contrast (modulation) and signal-to-noise ratio (SNR) of the acquired image pairs. Basic models of the precision with which the range can be measured assume a pinhole-camera model of the geometry, i.e. that the lenses provide perspective projection with zero distortion. Very-wide-angle or 'fisheye' lenses, however (for e.g. those used by robotic vehicles) typically exhibit projection functions that differ significantly from this assumption. To predict the stereophotogrammetric range precision for such applications, we extend the model to the case of an equidistant lens projection function suitable for a very-wide-angle lens. To predict the effects of contrast and SNR on range precision, we perform numerical simulations using stereo image pairs acquired by a stereo camera pair on NASA's Mars rover Curiosity. Contrast is degraded and noise is added to these data in a controlled fashion and the effects on the quality of the resulting range maps are assessed. C1 [Sellar, R. Glenn; Deen, Robert G.; Huffman, William C.; Willson, Reginald G.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Sellar, RG (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Glenn.Sellar@jpl.nasa.gov NR 3 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0297-7; 978-1-5106-0298-4 J9 PROC SPIE PY 2016 VL 9953 AR UNSP 995304 DI 10.1117/12.2236366 PG 9 WC Optics SC Optics GA BG5UU UT WOS:000389775100004 ER PT J AU Rosu-Finsen, A Marchione, D Salter, TL Stubbing, JW Brown, WA McCoustra, MRS AF Rosu-Finsen, Alexander Marchione, Demian Salter, Tara L. Stubbing, James W. Brown, Wendy A. McCoustra, Martin R. S. TI Peeling the astronomical onion SO PHYSICAL CHEMISTRY CHEMICAL PHYSICS LA English DT Article ID AMORPHOUS SOLID WATER; THERMAL-DESORPTION; INTERSTELLAR GRAINS; ICE SURFACES; IRRADIATION; EVAPORATION; SIMULATION; MORPHOLOGY; GRAPHITE; CLUSTERS AB Water ice is the most abundant solid in the Universe. Understanding the formation, structure and multiplicity of physicochemical roles for water ice in the cold, dense interstellar environments in which it is predominantly observed is a crucial quest for astrochemistry as these are regions active in star and planet formation. Intuitively, we would expect the mobility of water molecules deposited or synthesised on dust grain surfaces at temperatures below 50 K to be very limited. This work delves into the thermally-activated mobility of H2O molecules on model interstellar grain surfaces. The energy required to initiate this process is studied by reflection-absorption infrared spectroscopy of small quantities of water on amorphous silica and highly oriented pyrolytic graphite surfaces as the surface is annealed. Strongly non-Arrhenius behaviour is observed with an activation energy of 2 kJ mol(-1) on the silica surface below 25 K and 0 kJ mol(-1) on both surfaces between 25 and 100 K. The astrophysical implication of these results is that on timescales shorter than that estimated for the formation of a complete monolayer of water ice on a grain, aggregation of water ice will result in a non-uniform coating of water, hence leaving bare grain surface exposed. Other molecules can thus be formed or adsorbed on this bare surface. C1 [Rosu-Finsen, Alexander; Marchione, Demian; McCoustra, Martin R. S.] Heriot Watt Univ, Inst Chem Sci, Edinburgh EH14 4AS, Midlothian, Scotland. [Salter, Tara L.; Stubbing, James W.; Brown, Wendy A.] Univ Sussex, Div Chem, Brighton BN1 9QJ, E Sussex, England. [Marchione, Demian] CALTECH, Jet Prop Lab, Div Sci, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Rosu-Finsen, A; McCoustra, MRS (reprint author), Heriot Watt Univ, Inst Chem Sci, Edinburgh EH14 4AS, Midlothian, Scotland. EM ar163@hw.ac.uk; m.r.s.mccoustra@hw.ac.uk RI Brown, Wendy/B-9434-2008; OI Brown, Wendy/0000-0001-5934-1270; McCoustra, Martin/0000-0002-5716-110X FU UK Science and Technology Facilities Council (STFC) [ST/M001075/1]; UK Engineering and Physical Science Research Council (EPSRC) [EP/D506158/1]; European Community [238258]; HWU; UoS FX The authors acknowledge the support of the UK Science and Technology Facilities Council (STFC, ST/M001075/1), the UK Engineering and Physical Science Research Council (EPSRC, EP/D506158/1) and the European Community FP7-ITN Marie-Curie Programme (LASSIE project, grant agreement #238258). ARF thanks HWU for a James Watt Scholarship and JWS thanks UoS for a studentship. DM clarifies that his contribution to this work has been done as a private venture and not in the author's capacity as an affiliate of the Jet Propulsion Laboratory, California Institute of Technology. NR 55 TC 0 Z9 0 U1 6 U2 6 PU ROYAL SOC CHEMISTRY PI CAMBRIDGE PA THOMAS GRAHAM HOUSE, SCIENCE PARK, MILTON RD, CAMBRIDGE CB4 0WF, CAMBS, ENGLAND SN 1463-9076 EI 1463-9084 J9 PHYS CHEM CHEM PHYS JI Phys. Chem. Chem. Phys. PY 2016 VL 18 IS 46 BP 31930 EP 31935 DI 10.1039/c6cp05751a PG 6 WC Chemistry, Physical; Physics, Atomic, Molecular & Chemical SC Chemistry; Physics GA EE1IE UT WOS:000389333700060 PM 27844080 ER PT S AU Wilson, JD Chaffee, DW Wilson, NC Lekki, JD Tokars, RP Pouch, JJ Roberts, TD Battle, P Floyd, BM Lind, AJ Cavin, JD Helmick, SR AF Wilson, Jeffrey D. Chaffee, Dalton W. Wilson, Nathaniel C. Lekki, John D. Tokars, Roger P. Pouch, John J. Roberts, Tony D. Battle, Philip Floyd, Bertram M. Lind, Alexander J. Cavin, John D. Helmick, Spencer R. BE Meyers, RE Shih, Y Deacon, KS TI Free-space quantum key distribution with a high generation rate potassium titanyl phosphate waveguide photon-pair source SO QUANTUM COMMUNICATIONS AND QUANTUM IMAGING XIV SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Quantum Communications and Quantum Imaging XIV CY AUG 28-29, 2016 CL San Diego, CA SP SPIE DE photon-pair source; entangled photons; quantum key distribution; quantum communications; B92 ID PARAMETRIC FLUORESCENCE AB A high generation rate photon-pair source using a dual element periodically-poled potassium titanyl phosphate (PP KTP) waveguide is described. The fully integrated photon-pair source consists of a 1064-nm pump diode laser, fiber-coupled to a dual element waveguide within which a pair of 1064-nm photons are up-converted to a single 532-nm photon in the first stage. In the second stage, the 532-nm photon is down-converted to an entangled photon-pair at 800 nm and 1600 nm which are fiber-coupled at the waveguide output. The photon-pair source features a high pair generation rate, a compact power-efficient package, and continuous wave (CW) or pulsed operation. This is a significant step towards the long term goal of developing sources for high-rate Quantum Key Distribution (QKD) to enable Earth-space secure communications. Characterization and test results are presented. Details and preliminary results of a laboratory freespace QKD experiment with the B92 protocol are also presented. C1 [Wilson, Jeffrey D.; Chaffee, Dalton W.; Wilson, Nathaniel C.; Lekki, John D.; Tokars, Roger P.; Pouch, John J.; Lind, Alexander J.; Cavin, John D.; Helmick, Spencer R.] NASA Glenn Res Ctr, 21000 Brookpark Rd, Cleveland, OH 44135 USA. [Roberts, Tony D.; Battle, Philip] AdvR Inc, 2310 Univ Way,Bldg 1-1, Bozeman, MT 59715 USA. [Floyd, Bertram M.] Sierra Lobo Inc, 102 Pinnacle Dr, Fremont, OH 43420 USA. RP Wilson, JD (reprint author), NASA Glenn Res Ctr, 21000 Brookpark Rd, Cleveland, OH 44135 USA. EM Jeffrey.D.Wilson@nasa.gov NR 14 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0351-6; 978-1-5106-0352-3 J9 PROC SPIE PY 2016 VL 9980 AR 99800U DI 10.1117/12.2237742 PG 16 WC Physics, Applied; Physics, Particles & Fields SC Physics GA BG6DH UT WOS:000390027600017 ER PT S AU Soibel, A Rafol, B Khoshakhlagh, A Nguyen, J Hoglund, L Fisher, A Keo, SA Ting, DZY Gunapala, SD AF Soibel, Alexander Rafol, B. Khoshakhlagh, Arezou Nguyen, Jean Hoglund, Linda Fisher, Anita Keo, Sam. A. Ting, David Z. -Y. Gunapala, Sarath D. BE Razeghi, M Brown, GJ Lewis, JS TI Radiation tolerance studies of long wavelength infrared InAs/GaSb detectors SO QUANTUM SENSING AND NANO ELECTRONICS AND PHOTONICS XIII SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Quantum Sensing and Nano Electronics and Photonics XIII CY FEB 14-18, 2016 CL San Francisco, CA SP SPIE DE Keywords: infrared detectors; long wavelength infrared (LWIR); InAs/GaSb photodiodes; complementary barrier infrared detector (CBIRD) ID SUPERLATTICE; PERFORMANCE AB In this work we investigated the effect of proton irradiation on the performance of long wavelength infrared (LWIR) InAs/GaSb photodiodes (lambda(c) = 10.2 mu m) based on the complementary barrier infrared detector (CBIRD) design. We found that irradiation with 68MeV protons up to the total ionizing dose TID = 200 kRad results in only small (about 15%) decrease of the Quantum Efficiency and does not increase the operational bias of the photodiodes. However, the irradiation causes a significant increase of the dark current from j(d) = 5x10(-5) A/cm(2) at V-b = 0.1V and T = 80K to jd = 6x10(-3) A/cm(2) at TID = 200 kRad. This change in the dark current mechanism can be attributed to the onset of surface leakage current, generated by the trap assisted tunneling processes in the proton displacement damage areas near the device sidewalls. C1 [Soibel, Alexander; Rafol, B.; Khoshakhlagh, Arezou; Nguyen, Jean; Hoglund, Linda; Fisher, Anita; Keo, Sam. A.; Ting, David Z. -Y.; Gunapala, Sarath D.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Soibel, A (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Alexander.Soibel@jpl.nasa.gov NR 23 TC 0 Z9 0 U1 2 U2 2 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-62841-990-0 J9 PROC SPIE PY 2016 VL 9755 AR 975511 DI 10.1117/12.2209187 PG 8 WC Engineering, Electrical & Electronic; Optics; Physics, Applied SC Engineering; Optics; Physics GA BG4AA UT WOS:000388442500015 ER PT J AU Chundawat, SPS Paavola, CD Raman, B Nouailler, M Chan, SL Mielenz, JR Receveur-Brechot, V Trent, JD Dale, BE AF Chundawat, Shishir P. S. Paavola, Chad D. Raman, Babu Nouailler, Matthieu Chan, Suzanne L. Mielenz, Jonathan R. Receveur-Brechot, Veronique Trent, Jonathan D. Dale, Bruce E. TI Saccharification of thermochemically pretreated cellulosic biomass using native and engineered cellulosomal enzyme systems SO REACTION CHEMISTRY & ENGINEERING LA English DT Article ID X-RAY-SCATTERING; CLOSTRIDIUM-THERMOCELLUM CELLULOSOME; CARBOHYDRATE-BINDING MODULES; COHESIN-DOCKERIN COMPLEX; CRYSTALLINE CELLULOSE; LIGNOCELLULOSIC BIOMASS; DESIGNER CELLULOSOMES; BIOLOGICAL MACROMOLECULES; TRICHODERMA-REESEI; FUNGAL CELLULASES AB Consolidated bioprocessing (CBP) of pretreated lignocellulosic biomass using microbes like Clostridium thermocellum allows simultaneous polysaccharide saccharification and sugar fermentation to produce fuels or chemicals using a one-pot process. C. thermocellum is a thermophilic bacterium that deconstructs biomass using large multi-enzyme complexes called cellulosomes. Characterization of cellulosomal enzymes tethered to native or engineered scaffoldin proteins has revealed that enzyme complexation is critical to the bacterium's cellulolytic ability. However, we have a limited understanding of the impact of enzyme complexation on the saccharification efficiency of various forms of industrially relevant pretreated biomass substrates. Here, we compared the hydrolytic activity of the most abundant cellulosomal enzymes from C. thermocellum and investigate the importance of enzyme complexation using a model engineered protein scaffold (called 'rosettasome'). The hydrolytic performance of non-complexed enzymes, enzyme-rosettasome (or rosettazyme) complexes, and cellulosomes was tested on distinct cellulose allomorphs formed during biomass pretreatment. The scaffold-immobilized enzymes always gave higher activity than free enzymes. However, cellulosomes exhibited higher activity than rosettazyme complexes. This was likely due to the greater flexibility of the native versus engineered scaffold, as deciphered using small angle X-ray scattering. Surprisingly, scaffold-tethered enzymes also gave comparable activity on all the cellulose allomorphs tested, which is unlike the preferential activity of non-complexed cellulases seen for certain allomorph forms. Tethered enzyme complexes also gave lower saccharification yields on industrially relevant lignin-rich switchgrass than cellulose alone. In summary, we find that the type of pretreatment can significantly impact the saccharification efficiency of cellulosomal enzymes for various CBP scenarios. C1 [Chundawat, Shishir P. S.] State Univ New Jersey, Dept Chem & Biochem Engn, 98 Brett Rd,Engn Wing C-150A, Piscataway, NJ 08854 USA. [Chundawat, Shishir P. S.; Dale, Bruce E.] Michigan State Univ, DOE Great Lakes Bioenergy Res Ctr GLBRC, E Lansing, MI 48824 USA. [Chundawat, Shishir P. S.; Dale, Bruce E.] Michigan State Univ, Chem Engn & Mat Sci, 3815 Technol Blvd,Suite 1045, Lansing, MI 48910 USA. [Paavola, Chad D.; Trent, Jonathan D.] NASA Ames, Bioengn Branch, Moffett Field, CA USA. [Raman, Babu; Mielenz, Jonathan R.] Oak Ridge Natl Lab, Biosci Div, Oak Ridge, TN USA. [Raman, Babu; Mielenz, Jonathan R.] Oak Ridge Natl Lab, BioEnergy Sci Ctr, Oak Ridge, TN USA. [Nouailler, Matthieu] CNRS, LISM UMR Inst Microbiol Mediterranee 7255, 31 Chemin Joseph Aiguier, F-13402 Marseille 20, France. [Nouailler, Matthieu] Aix Marseille Univ, 31 Chemin Joseph Aiguier, F-13402 Marseille 20, France. [Chan, Suzanne L.] SETI Inst, Mountain View, CA USA. [Receveur-Brechot, Veronique] Aix Marseille Univ, CNRS, INSERM, Inst Paoli Calmettes,CRCM, Marseille, France. [Trent, Jonathan D.] Univ Calif Santa Cruz, Dept Biomol Engn, Santa Cruz, CA 95064 USA. [Paavola, Chad D.] Eli Lilly & Co, Lilly Corp Ctr, Drop Code 0403, Indianapolis, IN 46285 USA. [Raman, Babu] Dow AgroSci, 9330 Zionsville Rd, Indianapolis, IN 46268 USA. RP Chundawat, SPS (reprint author), State Univ New Jersey, Dept Chem & Biochem Engn, 98 Brett Rd,Engn Wing C-150A, Piscataway, NJ 08854 USA.; Chundawat, SPS (reprint author), Michigan State Univ, DOE Great Lakes Bioenergy Res Ctr GLBRC, E Lansing, MI 48824 USA.; Chundawat, SPS (reprint author), Michigan State Univ, Chem Engn & Mat Sci, 3815 Technol Blvd,Suite 1045, Lansing, MI 48910 USA. EM shishir.chundawat@rutgers.edu; cdpaavola@gmail.com; BRaman@dow.com; Matthieu.Nouailler@imm.cnrs.fr; slchansf@yahoo.com; biofuels4me@gmail.com; veronique.brechot@inserm.fr; jonathan.d.trent@nasa.gov; bdale@egr.msu.edu NR 79 TC 0 Z9 0 U1 0 U2 0 PU ROYAL SOC CHEMISTRY PI CAMBRIDGE PA THOMAS GRAHAM HOUSE, SCIENCE PARK, MILTON RD, CAMBRIDGE CB4 0WF, CAMBS, ENGLAND SN 2058-9883 J9 REACT CHEM ENG JI REACT. CHEM. ENG. PY 2016 VL 1 IS 6 BP 616 EP 628 DI 10.1039/c6re00172f PG 13 WC Chemistry, Multidisciplinary SC Chemistry GA EE1DW UT WOS:000389322200004 ER PT S AU Elliott, J de Souza, RS Krone-Martins, A Cameron, E Ishida, EEO Hilbe, J AF Elliott, J. de Souza, R. S. Krone-Martins, A. Cameron, E. Ishida, E. E. O. Hilbe, J. BE Napolitano, NR Longo, G Marconi, M Paolillo, M Iodice, E TI Using Gamma Regression for Photometric Redshifts of Survey Galaxies SO UNIVERSE OF DIGITAL SKY SURVEYS: A MEETING TO HONOUR THE 70TH BIRTHDAY OF MASSIMO CAPACCIOLI SE Astrophysics and Space Science Proceedings LA English DT Proceedings Paper CT Meeting on Universe of Digital Sky Surveys CY NOV 25-28, 2014 CL Naples, ITALY ID GENERALIZED LINEAR-MODELS AB Machine learning techniques offer a plethora of opportunities in tackling big data within the astronomical community. We present the set of Generalized Linear Models as a fast alternative for determining photometric redshifts of galaxies, a set of tools not commonly applied within astronomy, despite being widely used in other professions. With this technique, we achieve catastrophic outlier rates of the order of similar to 1%, that can be achieved in a matter of seconds on large datasets of size similar to 1; 000;000. To make these techniques easily accessible to the astronomical community, we developed a set of libraries and tools that are publicly available. C1 [Elliott, J.] Harvard Smithsonian Ctr Astrophys, 60 Garden St, Cambridge, MA 02138 USA. [Elliott, J.] Max Planck Inst Extraterr Phys, Giessenbachstrabe 1, D-85748 Garching, Germany. [de Souza, R. S.] MTA Eotvos Univ, EIRSA Lendulet Astrophys Res Grp, H-1117 Budapest, Hungary. [Krone-Martins, A.] Univ Lisbon, Fac Ciencias, SIM, Ed C8,Campo Grande, P-1749016 Lisbon, Portugal. [Cameron, E.] Univ Oxford, Dept Zool, Tinbergen Bldg,South Parks Rd, Oxford OX1 3PS, England. [Ishida, E. E. O.] Max Planck Inst Astrophys, Karl Schwarzschild Str 1, D-85748 Garching, Germany. [Hilbe, J.] Arizona State Univ, Tempe, AZ 85287 USA. [Hilbe, J.] Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Elliott, J (reprint author), Harvard Smithsonian Ctr Astrophys, 60 Garden St, Cambridge, MA 02138 USA. EM jonathan.elliott@cfa.harvard.edu; rafael.2706@gmail.com; algol@sim.ul.pt; dr.ewan.cameron@gmail.com; emille@mpa-garching.mpg.de; j.m.hilbe@gmail.com OI Krone-Martins, Alberto/0000-0002-2308-6623 NR 14 TC 0 Z9 0 U1 0 U2 0 PU SPRINGER PI DORDRECHT PA PO BOX 17, 3300 AA DORDRECHT, NETHERLANDS SN 1570-6591 BN 978-3-319-19330-4; 978-3-319-19329-8 J9 ASTROPHYSICS SPACE PY 2016 VL 42 BP 91 EP 96 DI 10.1007/978-3-319-19330-4_13 PG 6 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BG5XG UT WOS:000389802600014 ER PT S AU Ambeau, BL Gerace, AD Montanaro, M McCorkel, J AF Ambeau, Brittany L. Gerace, Aaron D. Montanaro, Matthew McCorkel, Joel BE Butler, JJ Xiong, X Gu, X TI The characterization of a DIRSIG simulation environment to support the inter-calibration of spaceborne sensors SO Earth Observing Systems XXI SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Earth Observing Systems XXI CY AUG 30-SEP 01, 2016 CL San Diego, CA SP SPIE DE Calibration; Cross-calibration; Earth Observing (EO) System; Digital Image and Remote Sensing Image Generation (DIRSIG); Inter-calibration AB Climate change studies require long-term, continuous records that extend beyond the lifetime, and the temporal resolution, of a single remote sensing satellite sensor. The inter-calibration of spaceborne sensors is therefore desired to provide spatially, spectrally, and temporally homogeneous datasets. The Digital Imaging and Remote Sensing Image Generation (DIRSIG) tool is a first principle-based synthetic image generation model that has the potential to characterize the parameters that impact the accuracy of the inter-calibration of spaceborne sensors. To demonstrate the potential utility of the model, we compare the radiance observed in real image data to the radiance observed in simulated image from DIRSIG. In the present work, a synthetic landscape of the Algodones Sand Dunes System is created. The terrain is facetized using a 2-meter digital elevation model generated from NASA Goddard's LiDAR, Hyperspectral, and Thermal (G-LiHT) imager. The material spectra are assigned using hyperspectral measurements of sand collected from the Algodones Sand Dunes System. Lastly, the bidirectional reflectance distribution function (BRDF) properties are assigned to the modeled terrain using the Moderate Resolution Imaging Spectroradiometer (MODIS) BRDF product in conjunction with DIRSIG's Ross-Li capability. The results of this work indicate that DIRSIG is in good agreement with real image data. The potential sources of residual error are identified and the possibilities for future work are discussed. C1 [Ambeau, Brittany L.; Gerace, Aaron D.; Montanaro, Matthew] Rochester Inst Technol, 54 Lomb Mem Dr, Rochester, NY 14623 USA. [McCorkel, Joel] NASA, Goddard Space Flight Ctr, 8800 Greenbelt Rd Code 618, Greenbelt, MD 20771 USA. RP Ambeau, BL (reprint author), Rochester Inst Technol, 54 Lomb Mem Dr, Rochester, NY 14623 USA. EM bla2447@rit.edu NR 7 TC 0 Z9 0 U1 1 U2 1 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0335-6; 978-1-5106-0336-3 J9 PROC SPIE PY 2016 VL 9972 AR UNSP 99720M DI 10.1117/12.2238317 PG 9 WC Instruments & Instrumentation; Remote Sensing; Optics; Imaging Science & Photographic Technology SC Instruments & Instrumentation; Remote Sensing; Optics; Imaging Science & Photographic Technology GA BG5CW UT WOS:000389369500017 ER PT S AU Angal, A McCorkel, J Thome, K AF Angal, Amit McCorkel, Joel Thome, Kurt BE Butler, JJ Xiong, X Gu, X TI Evaluation of GLAMR-based calibration for SI-traceable field reflectance retrievals SO Earth Observing Systems XXI SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Earth Observing Systems XXI CY AUG 30-SEP 01, 2016 CL San Diego, CA SP SPIE ID RADIOMETRIC CALIBRATION; IMAGER AB The reflected solar instrument that is part of the Climate Absolute Radiance and Refractivity Observatory (CLARREO) mission is being formulated with a goal of providing SI-traceable measurement of radiance that is an order of magnitude more accurate than the current imaging sensors. The Goddard Laser for Absolute Measurement of Radiance (GLAMR) is a key element to reaching such accuracy along with transferring the laboratory calibration to on-orbit measurements. Results from field reflectance retrievals using three separate instruments all of which have been calibrated using GLAMR are shown. The instruments include a commercial field spectrometer and a portable version of CLARREO's calibration demonstration system. The third instrument is NASA Goddard's Lidar, Hyperspectral and Thermal Imager (G-LiHT) which is an airborne system. All three were operated during a March 2013 measurement campaign at Red Lake Playa, Arizona as part of the on-orbit commissioning phase of Landsat 8. Reflectance is derived from near-coincident measurements by the three sensors for a small area of the playa. The retrieved results are SI-traceable and demonstrate the ability to transfer the GLAMR calibration to the field. Use of the G-LiHT data in the calibration of Landsat-7 and -8 sensors permits them both to be placed on the GLAMR-scale as well. C1 [Angal, Amit] Sci Syst & Applications Inc, 10210 Greenbelt Rd, Lanham, MD 20706 USA. [McCorkel, Joel; Thome, Kurt] NASA, Goddard Space Flight Ctr, Washington, DC USA. RP Angal, A (reprint author), Sci Syst & Applications Inc, 10210 Greenbelt Rd, Lanham, MD 20706 USA. NR 10 TC 0 Z9 0 U1 2 U2 2 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0335-6; 978-1-5106-0336-3 J9 PROC SPIE PY 2016 VL 9972 AR UNSP 99721U DI 10.1117/12.2238630 PG 6 WC Instruments & Instrumentation; Remote Sensing; Optics; Imaging Science & Photographic Technology SC Instruments & Instrumentation; Remote Sensing; Optics; Imaging Science & Photographic Technology GA BG5CW UT WOS:000389369500054 ER PT S AU Angal, A McCorkel, J Thome, K AF Angal, Amit McCorkel, Joel Thome, Kurt BE Butler, JJ Xiong, X Gu, X TI Results from source-based and detector-based calibrations of a CLARREO Calibration Demonstration System SO Earth Observing Systems XXI SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Earth Observing Systems XXI CY AUG 30-SEP 01, 2016 CL San Diego, CA SP SPIE AB The Climate Absolute Radiance and Refractivity Observatory (CLARREO) mission is formulated to determine long-term climate trends using SI-traceable measurements. The CLARREO mission will include instruments operating in the reflected solar (RS) wavelength region from 320 nm to 2300 nm. The Solar, Lunar for Absolute Reflectance Imaging Spectroradiometer (SOLARIS) is the calibration demonstration system (CDS) for the reflected solar portion of CLARREO and facilitates testing and evaluation of calibration approaches. The basis of CLARREO and SOLARIS calibration is the Goddard Laser for Absolute Measurement of Response (GLAMR) that provides a radiance-based calibration at reflective solar wavelengths using continuously tunable lasers. SI-traceability is achieved via detector-based standards that, in GLAMR's case, are a set of NIST-calibrated transfer radiometers. A portable version of the SOLARIS, Suitcase SOLARIS is used to evaluate GLAMR's calibration accuracies. The calibration of Suitcase SOLARIS using GLAMR agrees with that obtained from source-based results of the Remote Sensing Group (RSG) at the University of Arizona to better than 5% (k= 2) in the 720-860 nm spectral range. The differences are within the uncertainties of the NIST-calibrated FEL lamp-based approach of RSG and give confidence that GLAMR is operating at < 5% (k= 2) absolute uncertainties. Limitations of the Suitcase SOLARIS instrument also discussed and the next edition of the SOLARIS instrument (Suitcase SOLARIS2) is expected to provide an improved mechanism to further assess GLAMR and CLARREO calibration approaches. C1 [Angal, Amit] Sci Syst & Applicat Inc, 10210 Greenbelt Rd, Lanham, MD 20706 USA. [McCorkel, Joel; Thome, Kurt] NASA, Goddard Space Flight Ctr, Lanham, MD USA. RP Angal, A (reprint author), Sci Syst & Applicat Inc, 10210 Greenbelt Rd, Lanham, MD 20706 USA. NR 8 TC 0 Z9 0 U1 2 U2 2 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0335-6; 978-1-5106-0336-3 J9 PROC SPIE PY 2016 VL 9972 AR UNSP 997206 DI 10.1117/12.2238634 PG 7 WC Instruments & Instrumentation; Remote Sensing; Optics; Imaging Science & Photographic Technology SC Instruments & Instrumentation; Remote Sensing; Optics; Imaging Science & Photographic Technology GA BG5CW UT WOS:000389369500005 ER PT S AU Aumann, HH Elliott, D Manning, E AF Aumann, H. H. Elliott, Denis Manning, Evan BE Butler, JJ Xiong, X Gu, X TI Comparison of the AIRS, IASI, and CrIS 900 cm(-1) channel for Dome Concordia SO Earth Observing Systems XXI SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Earth Observing Systems XXI CY AUG 30-SEP 01, 2016 CL San Diego, CA SP SPIE AB We compare AIRS, IASI-A and CrIS under the cold conditions encountered in the daily overpasses of Dome Concordia, located on a high plateau in Antarctica, between May 2012 and March 2016. The mean brightness temperature at DomeC for the 900 cm(-1) atmospheric window channel is 218K, but it varies seasonally from 185K to 255K. Averaged over all simultaneous overpass data AIRS is 26 +/- 13 mK warmer than IASI-A, AIRS is 116 +/- 7 mK colder than CrIS. This is excellent agreement and consistent with SNO analysis in the literature. However, we find that differences for both AIRS/IASI-A and AIRS/CrIS are temperature dependent. Scene temperature sensitivity of this magnitude have also been reported by other investigators. Scene temperature dependence biases can create sampling biases which need to be taken into account when comparing data from current instruments, and even more so when analyzing data from vintage instruments with respect to climate change. C1 [Aumann, H. H.; Elliott, Denis; Manning, Evan] CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. RP Aumann, HH (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. NR 8 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0335-6; 978-1-5106-0336-3 J9 PROC SPIE PY 2016 VL 9972 AR UNSP 997209 DI 10.1117/12.2235945 PG 6 WC Instruments & Instrumentation; Remote Sensing; Optics; Imaging Science & Photographic Technology SC Instruments & Instrumentation; Remote Sensing; Optics; Imaging Science & Photographic Technology GA BG5CW UT WOS:000389369500008 ER PT S AU Barsi, JA Markham, BL Czapla-Myers, JS Helder, DL Hook, SJ Schott, JR Haque, MO AF Barsi, Julia A. Markham, Brian L. Czapla-Myers, Jeffrey S. Helder, Dennis L. Hook, Simon J. Schott, John R. Haque, Md. Obaidul BE Butler, JJ Xiong, X Gu, X TI Landsat-7 ETM+ Radiometric Calibration Status SO Earth Observing Systems XXI SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Earth Observing Systems XXI CY AUG 30-SEP 01, 2016 CL San Diego, CA SP SPIE DE Landsat; ETM; radiometry; calibration; reflective; thermal ID DESERT SITES AB Now in its 17th year of operation, the Enhanced Thematic Mapper + (ETM+), on board the Landsat-7 satellite, continues to systematically acquire imagery of the Earth to add to the 40+ year archive of Landsat data. Characterization of the ETM+ on-orbit radiometric performance has been on-going since its launch in 1999. The radiometric calibration of the reflective bands is still monitored using on-board calibration devices, though the Pseudo-Invariant Calibration Sites (PICS) method has proven to be an effective tool as well. The calibration gains were updated in April 2013 based primarily on PICS results, which corrected for a change of as much as -0.2%/year degradation in the worst case bands. A new comparison with the SADE database of PICS results indicates no additional degradation in the updated calibration. PICS data are still being tracked though the recent trends are not well understood. The thermal band calibration was updated last in October 2013 based on a continued calibration effort by NASA/Jet Propulsion Lab and Rochester Institute of Technology. The update accounted for a 0.036 W/m(2) sr mu m or 0.26K at 300K bias error. The updated lifetime trend is now stable to within +/-0.4K. C1 [Barsi, Julia A.] NASA GSFC, SSAI, Greenbelt, MD 20771 USA. [Markham, Brian L.] NASA GSFC, Greenbelt, MD 20771 USA. [Czapla-Myers, Jeffrey S.; Hook, Simon J.] South Dakota State Univ, Brookings, SD 57007 USA. [Hook, Simon J.] NASA JPL, Pasadena, CA 91109 USA. [Schott, John R.] Rochester Inst Technol, Rochester, NY 14623 USA. [Haque, Md. Obaidul] Stinger Ghaffarian Technol Inc, Earth Resources Observat & Sci Ctr, US Geol Survey, Sioux Falls, SD 57198 USA. RP Barsi, JA (reprint author), NASA GSFC, SSAI, Greenbelt, MD 20771 USA. EM julia.barsi@nasa.gov NR 13 TC 0 Z9 0 U1 1 U2 1 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0335-6; 978-1-5106-0336-3 J9 PROC SPIE PY 2016 VL 9972 AR UNSP 99720C DI 10.1117/12.2238625 PG 12 WC Instruments & Instrumentation; Remote Sensing; Optics; Imaging Science & Photographic Technology SC Instruments & Instrumentation; Remote Sensing; Optics; Imaging Science & Photographic Technology GA BG5CW UT WOS:000389369500010 ER PT S AU Georgiev, GT Butler, JJ Thome, K Cooksey, C Ding, L AF Georgiev, Georgi T. Butler, James J. Thome, Kurt Cooksey, Catherine Ding, Leibo BE Butler, JJ Xiong, X Gu, X TI PRELIMINARY RESULTS OF BTDF CALIBRATION OF TRANSMISSIVE SOLAR DIFFUSERS FOR REMOTE SENSING SO Earth Observing Systems XXI SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Earth Observing Systems XXI CY AUG 30-SEP 01, 2016 CL San Diego, CA SP SPIE DE BRF; BRDF; Calibration; Spectralon; Reflectance; Remote Sensing AB Satellite instruments operating in the reflected solar wavelength region require accurate and precise determination of the optical properties of their diffusers used in pre-flight and post-flight calibrations. The majority of recent and current space instruments use reflective diffusers. As a result, numerous Bidirectional Reflectance Distribution Function (BRDF) calibration comparisons have been conducted between the National Institute of Standards and Technology (NIST) and other industry and university-based metrology laboratories. However, based on literature searches and communications with NIST and other laboratories, no Bidirectional Transmittance Distribution Function (BTDF) measurement comparisons have been conducted between National Measurement Laboratories (NMLs) and other metrology laboratories. On the other hand, there is a growing interest in the use of transmissive diffusers in the calibration of satellite, air-borne, and ground-based remote sensing instruments. Current remote sensing instruments employing transmissive diffusers include the Ozone Mapping and Profiler Suite instrument (OMPS) Limb instrument on the Suomi-National Polar-orbiting Partnership (S-NPP) platform,, the Geostationary Ocean Color Imager (GOCI) on the Korea Aerospace Research Institute's (KARI) Communication, Ocean, and Meteorological Satellite (COMS), the Ozone Monitoring Instrument (OMI) on NASA's Earth Observing System (EOS) Aura platform, the Tropospheric Emissions: Monitoring of Pollution (TEMPO) instrument and the Geostationary Environmental Monitoring Spectrometer (GEMS).. This ensemble of instruments requires validated BTDF measurements of their onboard transmissive diffusers from the ultraviolet through the near infrared. This paper presents the preliminary results of a BTDF comparison between the NASA Diffuser Calibration Laboratory (DCL) and NIST on quartz and thin Spectralon samples. C1 [Georgiev, Georgi T.; Ding, Leibo] Sci Syst & Applicat Inc, Lanham, MD 20706 USA. [Butler, James J.; Thome, Kurt] NASA, Goddard Space Flight Ctr, Biospher Sci Branch, Greenbelt, MD 20771 USA. [Cooksey, Catherine] Natl Inst Stand & Technol, Gaithersburg, MD 20899 USA. RP Georgiev, GT (reprint author), Sci Syst & Applicat Inc, Lanham, MD 20706 USA. EM georgi.t.georgiev@nasa.gov NR 8 TC 0 Z9 0 U1 1 U2 1 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0335-6; 978-1-5106-0336-3 J9 PROC SPIE PY 2016 VL 9972 AR UNSP 997205 DI 10.1117/12.2235802 PG 12 WC Instruments & Instrumentation; Remote Sensing; Optics; Imaging Science & Photographic Technology SC Instruments & Instrumentation; Remote Sensing; Optics; Imaging Science & Photographic Technology GA BG5CW UT WOS:000389369500004 ER PT S AU Grycewicz, TJ Tan, B Isaacson, PJ De Luccia, FJ Dellomo, J AF Grycewicz, Thomas J. Tan, Bin Isaacson, Peter J. De Luccia, Frank J. Dellomo, John BE Butler, JJ Xiong, X Gu, X TI Avoiding stair-step artifacts in image registration for GOES-R navigation and registration assessment SO Earth Observing Systems XXI SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Earth Observing Systems XXI CY AUG 30-SEP 01, 2016 CL San Diego, CA SP SPIE DE GOES-R; image registration; systematic error; stair-step artifact AB In developing software for independent verification and validation (IV&V) of the Image Navigation and Registration (INR) capability for the Geostationary Operational Environmental Satellite - R Series (GOES-R) Advanced Baseline Imager (ABI), we have encountered an image registration artifact which limits the accuracy of image offset estimation at the subpixel scale using image correlation. Where the two images to be registered have the same pixel size, subpixel image registration preferentially selects registration values where the image pixel boundaries are close to lined up. Because of the shape of a curve plotting input displacement to estimated offset, we call this a stair-step artifact. When one image is at a higher resolution than the other, the stair-step artifact is minimized by correlating at the higher resolution. For validating ABI image navigation, GOES-R images are correlated with Landsat-based ground truth maps. To create the ground truth map, the Landsat image is first transformed to the perspective seen from the GOES-R satellite, and then is scaled to an appropriate pixel size. Minimizing processing time motivates choosing the map pixels to be the same size as the GOES-R pixels. At this pixel size image processing of the shift estimate is efficient, but the stair-step artifact is present. If the map pixel is very small, stair-step is not a problem, but image correlation is computation-intensive. This paper describes simulation-based selection of the scale for truth maps for registering GOES-R ABI images. C1 [Grycewicz, Thomas J.; Isaacson, Peter J.; De Luccia, Frank J.] Aerosp Corp, 2310 E El Segundo Bl, El Segundo, CA 90245 USA. [Tan, Bin] SSAI, 10210 Greenbelt Rd,Suite 600, Lanham, MD 20706 USA. [Dellomo, John] GST, 7855 Walker Dr Suite 200, Greenbelt, MD 20770 USA. [Tan, Bin; Dellomo, John] NASA, GSFC Terr Informat Syst Lab, 8800 Greenbelt RD, Greenbelt, MD 20771 USA. RP Grycewicz, TJ (reprint author), Aerosp Corp, 2310 E El Segundo Bl, El Segundo, CA 90245 USA. EM Thomas.J.Grycewicz@aero.org NR 6 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0335-6; 978-1-5106-0336-3 J9 PROC SPIE PY 2016 VL 9972 AR UNSP 99720T DI 10.1117/12.2238640 PG 12 WC Instruments & Instrumentation; Remote Sensing; Optics; Imaging Science & Photographic Technology SC Instruments & Instrumentation; Remote Sensing; Optics; Imaging Science & Photographic Technology GA BG5CW UT WOS:000389369500024 ER PT S AU Hagopian, J Bolcar, M Chambers, J Crane, A Eegholm, B Evans, T Hetherington, S Mentzell, E Thompson, P Ramos-Izquierdo, L Vaughnn, D AF Hagopian, John Bolcar, Matthew Chambers, John Crane, Allen Eegholm, Bente Evans, Tyler Hetherington, Samuel Mentzell, Eric Thompson, Patrick Ramos-Izquierdo, Luis Vaughnn, David BE Butler, JJ Xiong, X Gu, X TI Advanced Topographic Laser Altimeter System (ATLAS) Receiver Telescope Assembly (RTA) and Transmitter Alignment and Test SO Earth Observing Systems XXI SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Earth Observing Systems XXI CY AUG 30-SEP 01, 2016 CL San Diego, CA SP SPIE DE ATLAS; Receiver Telescope Assembly; LIDAR; ICESat-2; Interferometry; Encircled Energy; Optical Test AB The sole instrument on NASA's ICESat-2 spacecraft shown in Figure 1 will be the Advanced Topographic Laser Altimeter System (ATLAS) 1. The ATLAS is a Light Detection and Ranging (LIDAR) instrument; it measures the time of flight of the six transmitted laser beams to the Earth and back to determine altitude for geospatial mapping of global ice. The ATLAS laser beam is split into 6 main beams by a Diffractive Optical Element (DOE) that are reflected off of the earth and imaged by an 800 mm diameter Receiver Telescope Assembly (RTA). The RTA is composed of a 2-mirror telescope and Aft Optics Assembly (AOA) that collects and focuses the light from the 6 probe beams into 6 science fibers. Each fiber optic has a field of view on the earth that subtends 83 micro Radians. The light collected by each fiber is detected by a photomultiplier and timing related to a master clock to determine time of flight and therefore distance. The collection of the light from the 6 laser spots projected to the ground allows for dense cross track sampling to provide for slope measurements of ice fields. NASA LIDAR instruments typically utilize telescopes that are not diffraction limited since they function as a light collector rather than imaging function. The more challenging requirements of the ATLAS instrument require better performance of the telescope at 1/4 wave level to provide for improved sampling and signal to noise. NASA Goddard Space Flight Center (GSFC) contracted the build of the telescope to General Dynamics (GD). GD fabricated and tested the flight and flight spare telescope and then integrated the government supplied AOA for testing of the RTA before and after vibration qualification. The RTA was then delivered to GSFC for independent verification and testing over expected thermal vacuum conditions. The testing at GSFC included a measurement of the RTA wavefront error and encircled energy in several orientations to determine the expected zero gravity figure, encircled energy, back focal length and plate scale. In addition, the science fibers had to be aligned to within 10 micro Radians of the projected laser spots to provide adequate margin for operations on-orbit. This paper summarizes the independent testing and alignment of the fibers performed at the GSFC. C1 [Hagopian, John; Bolcar, Matthew; Chambers, John; Crane, Allen; Eegholm, Bente; Evans, Tyler; Hetherington, Samuel; Mentzell, Eric; Thompson, Patrick; Ramos-Izquierdo, Luis; Vaughnn, David] Natl Aeronaut & Space Adm, Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20776 USA. RP Hagopian, J (reprint author), Natl Aeronaut & Space Adm, Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20776 USA. NR 2 TC 0 Z9 0 U1 2 U2 2 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0335-6; 978-1-5106-0336-3 J9 PROC SPIE PY 2016 VL 9972 AR UNSP 997207 DI 10.1117/12.2240241 PG 13 WC Instruments & Instrumentation; Remote Sensing; Optics; Imaging Science & Photographic Technology SC Instruments & Instrumentation; Remote Sensing; Optics; Imaging Science & Photographic Technology GA BG5CW UT WOS:000389369500006 ER PT S AU Haney, C Doelling, D Minnis, P Bhatt, R Scarino, B Gopalan, A AF Haney, Conor Doelling, David Minnis, Patrick Bhatt, Rajendra Scarino, Benjamin Gopalan, Arun BE Butler, JJ Xiong, X Gu, X TI The calibration of the DSCOVR EPIC multiple visible channel instrument using MODIS and VIIRS as a reference SO Earth Observing Systems XXI SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Earth Observing Systems XXI CY AUG 30-SEP 01, 2016 CL San Diego, CA SP SPIE DE DSCOVR; EPIC; Aqua; MODIS; Suomi-NPP; VIIRS; Radiometric Calibration; Deep Convective Clouds (DCC) ID DEEP CONVECTIVE CLOUDS; STABILITY; DESERT AB The Deep Space Climate Observatory (DSCOVR), launched on 11 February 2015, is a satellite positioned near the Lagrange-1 (L1) point, carrying several instruments that monitor space weather, and Earth-view sensors designed for climate studies. The Earth Polychromatic Imaging Camera (EPIC) onboard DSCOVR continuously views the sun-illuminated portion of the Earth with spectral coverage in the UV, VIS, and NIR bands. Although the EPIC instrument does not have any onboard calibration abilities, its constant view of the sunlit Earth disk provides a unique opportunity for simultaneous viewing with several other satellite instruments. This arrangement allows the EPIC sensor to be inter-calibrated using other well-characterized satellite instrument reference standards. Two such instruments with onboard calibration are MODIS, flown on Aqua and Terra, and VIIRS, onboard Suomi-NPP. The MODIS and VIIRS reference calibrations will be transferred to the EPIC instrument using both all-sky ocean and deep convective clouds (DCC) ray-matched EPIC and MODIS/VIIRS radiance pairs. An automated navigation correction routine was developed to more accurately align the EPIC and MODIS/VIIRS granules. The automated navigation correction routine dramatically reduced the uncertainty of the resulting calibration gain based on the EPIC and MODIS/VIIRS radiance pairs. The SCIAMACHY-based spectral band adjustment factors (SBAF) applied to the MODIS/VIIRS radiances were found to successfully adjust the reference radiances to the spectral response of the specific EPIC channel for over-lapping spectral channels. The SBAF was also found to be effective for the non-overlapping EPIC channel 10. Lastly, both ray-matching techniques found no discernable trends for EPIC channel 7 over the year of publically released EPIC data. C1 [Haney, Conor; Bhatt, Rajendra; Scarino, Benjamin; Gopalan, Arun] SSAI, 1 Enterprise Pkwy,Ste 200, Hampton, VA 23666 USA. [Doelling, David; Minnis, Patrick] NASA Langley Res Ctr, 1 Nasa Dr, Hampton, VA 23666 USA. RP Haney, C (reprint author), SSAI, 1 Enterprise Pkwy,Ste 200, Hampton, VA 23666 USA. EM conor.o.haney@nasa.gov NR 12 TC 0 Z9 0 U1 2 U2 2 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0335-6; 978-1-5106-0336-3 J9 PROC SPIE PY 2016 VL 9972 AR UNSP 99720P DI 10.1117/12.2238010 PG 13 WC Instruments & Instrumentation; Remote Sensing; Optics; Imaging Science & Photographic Technology SC Instruments & Instrumentation; Remote Sensing; Optics; Imaging Science & Photographic Technology GA BG5CW UT WOS:000389369500020 ER PT S AU Lei, N Xiong, XX AF Lei, Ning Xiong, Xiaoxiong BE Butler, JJ Xiong, X Gu, X TI Product of the SNPP VIIRS SD screen transmittance and the SD BRDF (RSB) from both yaw maneuver and regular on-orbit data SO Earth Observing Systems XXI SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Earth Observing Systems XXI CY AUG 30-SEP 01, 2016 CL San Diego, CA SP SPIE DE SNPP VIIRS; radiometric calibration; RSB; solar diffuser; BRDF degradation; solar diffuser screen transmittance; yaw maneuver ID REFLECTIVE SOLAR BANDS; PERFORMANCE; CALIBRATION; STABILITY AB To assure data quality, the Earth-observing Visible Infrared Imaging Radiometer Suite (VIIRS) regularly performs on-orbit radiometric calibrations of its 22 spectral bands. The primary calibration radiance source for the reflective solar bands (RSBs) is a sunlit solar diffuser (SD). During the calibration process, sunlight goes through a perforated plate (the SD screen) and then strikes the SD. The SD scattered sunlight is used for the calibration, with the spectral radiance proportional to the product of the SD screen transmittance and the SD bidirectional reflectance distribution function (BRDF). The BRDF is decomposed to the product of its value at launch and a numerical factor quantifying its change since launch. Therefore, the RSB calibration requires accurate knowledge of the product of the SD screen transmittance and the BRDF (RSB; launch time). Previously, we calculated the product with yaw maneuver data and found that the product had improved accuracy over the prelaunch one. With both yaw maneuver and regular on orbit data, we were able to improve the accuracy of the SDSM screen transmittance and the product for the solar diffuser stability monitor SD view. In this study, we use both yaw maneuver and a small portion of regular on-orbit data to determine the product for the RSB SD view. C1 [Lei, Ning] Sci Syst & Applicat Inc, 10210 Greenbelt Rd,Suite 600, Lanham, MD 20706 USA. [Xiong, Xiaoxiong] NASA, Goddard Space Flight Ctr, Sci & Explorat Directorate, Greenbelt, MD 20771 USA. RP Lei, N (reprint author), Sci Syst & Applicat Inc, 10210 Greenbelt Rd,Suite 600, Lanham, MD 20706 USA. EM ning.lei@ssaihq.com; xiaoxiong.xiong-1@nasa.gov NR 18 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0335-6; 978-1-5106-0336-3 J9 PROC SPIE PY 2016 VL 9972 AR UNSP 99721D DI 10.1117/12.2236943 PG 11 WC Instruments & Instrumentation; Remote Sensing; Optics; Imaging Science & Photographic Technology SC Instruments & Instrumentation; Remote Sensing; Optics; Imaging Science & Photographic Technology GA BG5CW UT WOS:000389369500041 ER PT S AU Lei, N Xiong, XX AF Lei, Ning Xiong, Xiaoxiong BE Butler, JJ Xiong, X Gu, X TI Functional form of the radiometric equation for the SNPP VIIRS reflective solar bands: an initial study SO Earth Observing Systems XXI SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Earth Observing Systems XXI CY AUG 30-SEP 01, 2016 CL San Diego, CA SP SPIE DE SNPP VIIRS; radiometric calibration; solar diffuser; BRDF degradation; reflective solar bands; functional form ID CALIBRATION AB The Visible Infrared Imaging Radiometer Suite (VIIRS) aboard the Suomi National Polar-orbiting Partnership (SNPP) satellite is a passive scanning radiometer and an imager, observing radiative energy from the Earth in 22 spectral bands from 0.41 to 12 mu m which include 14 reflective solar bands (RSBs). Extending the formula used by the Moderate Resolution Imaging Spectroradiometer instruments, currently the VIIRS determines the sensor aperture spectral radiance through a quadratic polynomial of its detector digital count. It has been known that for the RSBs the quadratic polynomial is not adequate in the design specified spectral radiance region and using a quadratic polynomial could drastically increase the errors in the polynomial coefficients, leading to possible large errors in the determined aperture spectral radiance. In addition, it is very desirable to be able to extend the radiance calculation formula to correctly retrieve the aperture spectral radiance with the level beyond the design specified range. In order to more accurately determine the aperture spectral radiance from the observed digital count, we examine a few polynomials of the detector digital count to calculate the sensor aperture spectral radiance. C1 [Lei, Ning] Sci Syst & Applicat Inc, 10210 Greenbelt Rd,Suite 600, Lanham, MD 20706 USA. [Xiong, Xiaoxiong] NASA, Goddard Space Flight Ctr, Sci & Explorat Directorate, Greenbelt, MD 20771 USA. RP Lei, N (reprint author), Sci Syst & Applicat Inc, 10210 Greenbelt Rd,Suite 600, Lanham, MD 20706 USA. EM ning.lei@ssaihq.com; xiaoxiong.xiong-1@nasa.gov NR 7 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0335-6; 978-1-5106-0336-3 J9 PROC SPIE PY 2016 VL 9972 AR UNSP 997219 DI 10.1117/12.2236950 PG 12 WC Instruments & Instrumentation; Remote Sensing; Optics; Imaging Science & Photographic Technology SC Instruments & Instrumentation; Remote Sensing; Optics; Imaging Science & Photographic Technology GA BG5CW UT WOS:000389369500038 ER PT S AU Li, YH Angal, A Wu, AS Geng, X Link, D Xiong, XX AF Li, Yonghong Angal, Amit Wu, Aisheng Geng, Xu Link, Daniel Xiong, Xiaoxiong BE Butler, JJ Xiong, X Gu, X TI Calibration Improvements in the Detector-to-Detector Differences for the MODIS Ocean Color Bands SO Earth Observing Systems XXI SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Earth Observing Systems XXI CY AUG 30-SEP 01, 2016 CL San Diego, CA SP SPIE DE Moderate Resolution Imaging Spectroradiometer (MODIS); calibration; ocean band; detector-to-detector difference ID REFLECTIVE SOLAR BANDS AB The Moderate Resolution Imaging Spectroradiometer (MODIS), a major instrument within NASA's Earth Observation System missions, has operated for over 16 and 14 years onboard the Terra and Aqua satellites, respectively. Its reflective solar bands (RSB) covering a spectral range from 0.4 to 2.1 mu m are primarily calibrated using the on-board solar diffuser (SD), with its on-orbit degradation monitored using the Solar Diffuser Stability Monitor. RSB calibrations are supplemented by near-monthly lunar measurements acquired from the instrument's space-view port. Nine bands (bands 8-16) in the visible to near infrared spectral range from 0.412 to 0.866 mu m are primarily used for ocean color observations. During a recent reprocessing of ocean color products, performed by the NASA's Ocean Biology Processing Group, detector-to-detector differences of up to 1.5% were observed in bands 13-16 of Terra MODIS. This paper provides an overview of the current approach to characterize the MODIS detector-to-detector differences. An alternative methodology was developed to mitigate the observed impacts for bands 13-16. The results indicated an improvement in the detector residuals and in turn are expected to improve the MODIS ocean color products. This paper also discusses the limitations, subsequent enhancements, and the improvements planned for future MODIS calibration collections. C1 [Li, Yonghong; Angal, Amit; Wu, Aisheng; Geng, Xu; Link, Daniel] Sci Syst & Applicat Inc, 10210 Greenbelt Rd, Lanham, MD 20706 USA. [Xiong, Xiaoxiong] NASA, Goddard Space Flight Ctr, Sci & Explorat Directorate, Greenbelt, MD 20771 USA. RP Li, YH (reprint author), Sci Syst & Applicat Inc, 10210 Greenbelt Rd, Lanham, MD 20706 USA. NR 7 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0335-6; 978-1-5106-0336-3 J9 PROC SPIE PY 2016 VL 9972 AR UNSP 99721V DI 10.1117/12.2236920 PG 7 WC Instruments & Instrumentation; Remote Sensing; Optics; Imaging Science & Photographic Technology SC Instruments & Instrumentation; Remote Sensing; Optics; Imaging Science & Photographic Technology GA BG5CW UT WOS:000389369500055 ER PT S AU Li, YH Angal, A Chen, N Geng, X Link, D Wang, ZP Wu, AS Xiong, XX AF Li, Yonghong Angal, Amit Chen, Na Geng, Xu Link, Daniel Wang, Zhipeng Wu, Aisheng Xiong, Xiaoxiong BE Butler, JJ Xiong, X Gu, X TI Improvement in the Characterization of MODIS Subframe Difference SO Earth Observing Systems XXI SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Earth Observing Systems XXI CY AUG 30-SEP 01, 2016 CL San Diego, CA SP SPIE DE Moderate Resolution Imaging Spectroradiometer (MODIS); calibration; subframe difference; image striping AB MODIS is a key instrument of NASA's Earth Observing System. It has successfully operated for 16+ years on the Terra satellite and 14+ years on the Aqua satellite, respectively. MODIS has 36 spectral bands at three different nadir spatial resolutions, 250m (bands 1-2), 500m (bands 3-7), and 1km (bands 8-36). MODIS subframe measurement is designed for bands 1-7 to match their spatial resolution in the scan direction to that of the track direction. Within each 1 km frame, the MODIS 250 m resolution bands sample four subframes and the 500 m resolution bands sample two subframes. The detector gains are calibrated at a subframe level. Due to calibration differences between subframes, noticeable subframe striping is observed in the Level 1B (L1B) products, which exhibit a predominant radiance-level dependence. This paper presents results of subframe differences from various onboard and earth-view data sources (e.g. solar diffuser, electronic calibration, spectro-radiometric calibration assembly, Earth view, etc.). A subframe bias correction algorithm is proposed to minimize the subframe striping in MODIS L1B image. The algorithm has been tested using sample L1B images and the vertical striping at lower radiance value is mitigated after applying the corrections. The subframe bias correction approach will be considered for implementation in future versions of the calibration algorithm. C1 [Li, Yonghong; Angal, Amit; Chen, Na; Geng, Xu; Link, Daniel; Wang, Zhipeng; Wu, Aisheng] Sci Syst & Applicat Inc, 10210 Greenbelt Rd, Lanham, MD USA. [Xiong, Xiaoxiong] NASA, Goddard Space Flight Ctr, Sci & Explorat Directorate, Greenbelt, MD 20771 USA. RP Li, YH (reprint author), Sci Syst & Applicat Inc, 10210 Greenbelt Rd, Lanham, MD USA. NR 11 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0335-6; 978-1-5106-0336-3 J9 PROC SPIE PY 2016 VL 9972 AR UNSP 99720W DI 10.1117/12.2238636 PG 14 WC Instruments & Instrumentation; Remote Sensing; Optics; Imaging Science & Photographic Technology SC Instruments & Instrumentation; Remote Sensing; Optics; Imaging Science & Photographic Technology GA BG5CW UT WOS:000389369500027 ER PT S AU Lin, G Wolfe, RE AF Lin, Guoqing (Gary) Wolfe, Robert E. BE Butler, JJ Xiong, X Gu, X TI JPSS-1 VIIRS at-launch geometric performance SO Earth Observing Systems XXI SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Earth Observing Systems XXI CY AUG 30-SEP 01, 2016 CL San Diego, CA SP SPIE DE JPSS; VIIRS; FOV; MTF; BBR; pointing; geolocation AB Following the successful operations of the first Visible Infrared Imaging Radiometer Suite (VIIRS) instrument on-board the Suomi National Polar-orbiting Partnership (SNPP) spacecraft since launch in October 2011, a second VIIRS instrument to be on-board the first Joint Polar Satellite System (JPSS-1) satellite has been fabricated, tested and integrated onto the spacecraft, readying for launch in 2017. The ground testing, including geometric functional performance testing and characterization, at the sensor level was completed in December 2014. Testing at the spacecraft level is on-going. The instrument geometric performance includes sensor (detector) spatial response, band-to-band co-registration (BBR), scan plane and pointing stability. The parameters have been calibrated and characterized through ground testing under ambient and thermal vacuum conditions, and numerical modeling and analysis. VIIRS sensor spatial response is measured by line spread functions (LSFs) in the scan and track directions for every detector. We parameterize the LSFs by: 1) dynamic field of view (DFOV) in the scan direction and instantaneous FOV (IFOV) in the track direction; and 2) modulation transfer function (MTF) for the 17 moderate resolution bands (M-bands) and for the five imagery bands (I-bands). We define VIIRS BBR for M-bands and I-bands as the overlapped fractional area of angular pixel sizes from the corresponding detectors in a band pair, including nested I-bands within the M-bands. The ground tests result in static BBR matrices. VIIRS pointing measurements include scan plane tilt and instrument-to-spacecraft mounting coefficients. This paper summarizes the pre-launch test results along with anomaly investigations. The pre-launch performance parameters will be tracked or corrected for as needed in on-orbit operations. C1 [Lin, Guoqing (Gary)] Sci Syst & Applicat Inc, 10210 Greenbelt Rd, Lanham, MD 20706 USA. [Lin, Guoqing (Gary); Wolfe, Robert E.] NASA, Goddard Space Flight Ctr, Code 619 8800, Greenbelt, MD 20771 USA. RP Lin, G (reprint author), Sci Syst & Applicat Inc, 10210 Greenbelt Rd, Lanham, MD 20706 USA.; Lin, G (reprint author), NASA, Goddard Space Flight Ctr, Code 619 8800, Greenbelt, MD 20771 USA. EM Gary.Lin@nasa.gov NR 10 TC 0 Z9 0 U1 1 U2 1 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0335-6; 978-1-5106-0336-3 J9 PROC SPIE PY 2016 VL 9972 AR UNSP 99721L DI 10.1117/12.2238804 PG 10 WC Instruments & Instrumentation; Remote Sensing; Optics; Imaging Science & Photographic Technology SC Instruments & Instrumentation; Remote Sensing; Optics; Imaging Science & Photographic Technology GA BG5CW UT WOS:000389369500047 ER PT S AU Lin, GQ Wolfe, RE Tilton, JC AF Lin, Guoqing (Gary) Wolfe, Robert E. Tilton, James C. BE Butler, JJ Xiong, X Gu, X TI Trending of SNPP ephemeris and its implications on VIIRS geometric performance SO Earth Observing Systems XXI SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Earth Observing Systems XXI CY AUG 30-SEP 01, 2016 CL San Diego, CA SP SPIE DE Suomi NPP; VIIRS; trends; ephemeris; altitude; inclination angle; ground speed; scan-to-scan overlap AB This paper describes trends in the Suomi National Polar-orbiting Partnership (SNPP) spacecraft ephemeris data over the four and half years of on-orbit operations. It then discusses the implications of these trends on the geometric performance of the Visible Infrared Imaging Radiometer Suite (VIIRS), one of the instruments onboard SNPP. The SNPP ephemeris data includes time stamped spacecraft positions and velocities that are used to calculate the spacecraft altitude and sub-satellite locations. Through drag make-up maneuvers (DMUs) the orbital mean altitude (spacecraft altitude averaged over an orbit) has been maintained at 838.8 km to within +/- 0.2 km and the orbital period at 101.5 minutes to within +/- 0.2 seconds. The corresponding orbital mean velocity in the terrestrial frame of reference has been maintained at 7524 m/s to within +/- 0.5 m/s. Within an orbit, the altitude varies from 828 km near 15 degrees N to 856 km near the South Pole. Inclination adjust maneuvers (IAMs) have maintained the orbit inclination angle at 98.67 degrees to with +/- 0.07 degrees and the sun-synchronous local time at ascending node (LTAN) at 13: 28 to within +/- 5 minutes. Besides these trends, it is interesting to observe that the orbit's elliptic shape has its major axis linking the perigee and apogee shorter than the line linking the ascending node and the descending node. This effect is caused by the Earth's oblate spheroid shape and deviates from a Keplerian orbit theory in which the two orbiting bodies are point masses. VIIRS has 5 imagery resolution bands, 16 moderate resolution bands and a day-night band, with 32, 16 and 16 detectors, respectively, aligned in the spacecraft flight (aka. track) direction. For each band's sample within a scan, the detectors sample the Earth's surface simultaneously in the track direction in the Earth Centered Inertial frame of reference. The distance between the center of the area sensed by the trailing detectors of one scan and the leading detectors of the next includes a component caused by earth rotation. This earth rotation component is relatively small (similar to 70 m/s) for an orbit like SNPP, but must be taken into account in the design of low-Earth orbit scanning sensors similar to VIIRS to ensure contiguous coverage at nadir. C1 [Lin, Guoqing (Gary)] Sci Syst & Applicat Inc, 10210 Greenbelt Rd, Lanham, MD 20706 USA. [Wolfe, Robert E.; Tilton, James C.] NASA, Goddard Space Flight Ctr, Code 606 8800, Greenbelt, MD 20771 USA. RP Lin, G (reprint author), Sci Syst & Applicat Inc, 10210 Greenbelt Rd, Lanham, MD 20706 USA. EM gary.lin@nasa.gov NR 7 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0335-6; 978-1-5106-0336-3 J9 PROC SPIE PY 2016 VL 9972 AR UNSP 99721K DI 10.1117/12.2239043 PG 11 WC Instruments & Instrumentation; Remote Sensing; Optics; Imaging Science & Photographic Technology SC Instruments & Instrumentation; Remote Sensing; Optics; Imaging Science & Photographic Technology GA BG5CW UT WOS:000389369500046 ER PT S AU Manning, EM Aumann, HH AF Manning, Evan M. Aumann, Hartmut H. BE Butler, JJ Xiong, X Gu, X TI Tropical SNO comparisons of AIRS and CrIS calibration for windows SO Earth Observing Systems XXI SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Earth Observing Systems XXI CY AUG 30-SEP 01, 2016 CL San Diego, CA SP SPIE DE AIRS; CrIS; hyperspectral; infrared sounder AB AIRS on EOS-Aqua and CrIS on Suomi NPP are two hyperspectral infrared sounders with similar capabilities and orbits, so there is a great opportunity to compare their absolute calibration while they are both in orbit. This insures that long-term climate record can be created by concatenating the two instrument records. There are significant differences in instrument architecture which may lead to subtle differences and complicate attempts to combine the records. We use Tropical Simultaneous Nadir Observations (TSNOs), cases where both instruments are looking nearly at the same place at the same time, to explore the differences. Due to the presence of cold clouds and clear hot desert surface, the data cover a brightness temperature range from 190 K to 340 K. We concentrate on the differences between the mean of the two instruments using atmospheric window channels as function of brightness temperature in 20-K wide bins. With the currently available AIRS and CrIS official calibrated data, radiometric differences as large as 0.3 K are seen at the extreme temperatures. These differences may be reduced in future releases of the AIRS and CrIS calibration. C1 [Manning, Evan M.; Aumann, Hartmut H.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Manning, EM (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 6 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0335-6; 978-1-5106-0336-3 J9 PROC SPIE PY 2016 VL 9972 AR UNSP 99720A DI 10.1117/12.2236672 PG 13 WC Instruments & Instrumentation; Remote Sensing; Optics; Imaging Science & Photographic Technology SC Instruments & Instrumentation; Remote Sensing; Optics; Imaging Science & Photographic Technology GA BG5CW UT WOS:000389369500009 ER PT S AU Markham, BL Jenstrom, D Masek, JG Dabney, P Pedelty, JA Barsi, JA Montanaro, M AF Markham, Brian L. Jenstrom, Del Masek, Jeffrey G. Dabney, Phil Pedelty, Jeffrey A. Barsi, Julia A. Montanaro, Matthew BE Butler, JJ Xiong, X Gu, X TI Landsat 9: Status and Plans SO Earth Observing Systems XXI SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Earth Observing Systems XXI CY AUG 30-SEP 01, 2016 CL San Diego, CA SP SPIE DE Landsat; Operational Land Imager 2; Thermal Infrared Sensor 2 ID THERMAL INFRARED-SENSOR; DESIGN AB The Landsat 9 mission, currently under development and proceeding towards a targeted launch in late 2020, will be very similar to the Landsat 8 mission, launched in 2013. Like Landsat 8, Landsat 9 is a joint effort between NASA and USGS with two sensors, the Operational Land Imager 2 (OLI-2), essentially a copy of the OLI on Landsat 8 and the Thermal Infrared Sensor 2 (TIRS-2), very similar to the TIRS on Landsat 8. The OLI-2, like OLI, provides 14-bit image data, though for Landsat 9, all 14 bits will be retained and transmitted to the ground. The focal plane modules to be used for OLI-2 were flight spares for OLI and are currently being retested by Ball Aerospace. Results indicate radiometric performance comparable to OLI. The TIRS was a class C instrument, with a 3-year design lifetime, and therefore had limited redundancy. TIRS-2 will be a class B instrument, with a 5-year design lifetime, like OLI (and OLI-2), necessitating design changes to increase redundancy. The stray light and Scene Select Mechanism (SSM) encoder problems observed on orbit with TIRS have also instigated a few design changes to TIRS-2. Stray light analysis and testing have indicated that additional baffles in the TIRS-2 optical system will suppress the out-of-field response. The SSM encoder problems have not been definitively traced to a route cause, though conductive anodic filament growth in the circuit boards is suspected. Improved designs for the encoder are being considered for TIRS-2. The spare Focal Plane Array (FPA) from TIRS is planned for use in TIRS-2; FPA spectral and radiometric performance testing is scheduled for September of this year at NASA's Goddard Space Flight Center. C1 [Markham, Brian L.; Masek, Jeffrey G.; Dabney, Phil] NASA, Goddard Space Flight Ctr, Biospher Sci Lab, Code 618, Greenbelt, MD 20771 USA. [Jenstrom, Del; Pedelty, Jeffrey A.] NASA, Goddard Space Flight Ctr, Landsat Project Office 9, Code 429, Greenbelt, MD 20771 USA. [Barsi, Julia A.] Sci Syst & Applicat Inc, Goddard Space Flight Ctr, Code 618, Greenbelt, MD 20771 USA. [Montanaro, Matthew] Rochester Inst Technol, Ctr Imaging Sci, Rochester, NY 14623 USA. RP Markham, BL (reprint author), NASA, Goddard Space Flight Ctr, Biospher Sci Lab, Code 618, Greenbelt, MD 20771 USA. EM Brian.L.Markham@nasa.gov NR 4 TC 0 Z9 0 U1 2 U2 2 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0335-6; 978-1-5106-0336-3 J9 PROC SPIE PY 2016 VL 9972 AR UNSP 99720G DI 10.1117/12.2238658 PG 6 WC Instruments & Instrumentation; Remote Sensing; Optics; Imaging Science & Photographic Technology SC Instruments & Instrumentation; Remote Sensing; Optics; Imaging Science & Photographic Technology GA BG5CW UT WOS:000389369500013 ER PT S AU Mu, QZ Wu, AS Chang, TJ Angal, A Link, D Xiong, XX Doelling, DR Bhatt, R AF Mu, Qiaozhen Wu, Aisheng Chang, Tiejun Angal, Amit Link, Daniel Xiong, Xiaoxiong Doelling, David R. Bhatt, Rajendra BE Butler, JJ Xiong, X Gu, X TI Assessment of MODIS On-orbit Calibration using a Deep Convective Cloud Technique SO Earth Observing Systems XXI SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Earth Observing Systems XXI CY AUG 30-SEP 01, 2016 CL San Diego, CA SP SPIE ID REFLECTIVE SOLAR BANDS AB The MODerate Resolution Imaging Spectroradiometer (MODIS) sensors onboard Terra and Aqua satellites are calibrated on-orbit with a solar diffuser (SD) for the reflective solar bands (RSB). The MODIS sensors are operating beyond their designed lifetime and hence present a major challenge to maintain the calibration accuracy. The degradation of the onboard SD is tracked by a solar diffuser stability monitor (SDSM) over a wavelength range from 0.41 to 0.94 mu m. Therefore, any degradation of the SD beyond 0.94 mu m cannot be captured by the SDSM. The uncharacterized degradation at wavelengths beyond this limit could adversely affect the Level 1B (L1B) product. To reduce the calibration uncertainties caused by the SD degradation, invariant Earth-scene targets are used to monitor and calibrate the MODIS L1B product. The use of deep convective clouds (DCCs) is one such method and particularly significant for the short-wave infrared (SWIR) bands in assessing their long-term calibration stability. In this study, we use the DCC technique to assess the performance of the Terra and Aqua MODIS Collection-6 L1B for RSB 1 37, and 26, with spectral coverage from 0.47 to 2.13 mu m. Results show relatively stable trends in Terra and Aqua MODIS reflectance for most bands. Careful attention needs to be paid to Aqua band 1, Terra bands 3 and 26 as their trends are larger than 1% during the study time period. We check the feasibility of using the DCC technique to assess the stability in MODIS bands 17-19. The assessment test on response versus scan angle (RVS) calibration shows substantial trend difference for Aqua band 1between different angles of incidence (AOIs). The DCC technique can be used to improve the RVS calibration in the future. C1 [Mu, Qiaozhen; Wu, Aisheng; Chang, Tiejun; Angal, Amit; Link, Daniel] Sci Syst & Applicat Inc, Lanham, MD 20706 USA. [Xiong, Xiaoxiong] NASA, GSFC, Sci & Explorat Directorate, Greenbelt, MD 20771 USA. [Doelling, David R.] NASA, Langley Res Ctr, 21 Langley Blvd MS 420, Hampton, VA 23681 USA. [Bhatt, Rajendra] Sci Syst & Applicat Inc, 1 Enterprise Pkwy,Suite 200, Hampton, VA 23666 USA. RP Mu, QZ (reprint author), Sci Syst & Applicat Inc, Lanham, MD 20706 USA. NR 22 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0335-6; 978-1-5106-0336-3 J9 PROC SPIE PY 2016 VL 9972 AR UNSP 997210 DI 10.1117/12.2237047 PG 10 WC Instruments & Instrumentation; Remote Sensing; Optics; Imaging Science & Photographic Technology SC Instruments & Instrumentation; Remote Sensing; Optics; Imaging Science & Photographic Technology GA BG5CW UT WOS:000389369500031 ER PT S AU Pagano, TS Broberg, SE AF Pagano, Thomas S. Broberg, Steven E. BE Butler, JJ Xiong, X Gu, X TI Recent checks on the radiometric and spatial calibration of AIRS in-orbit SO Earth Observing Systems XXI SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Earth Observing Systems XXI CY AUG 30-SEP 01, 2016 CL San Diego, CA SP SPIE DE Atmosphere; Infrared; Sounder; AIRS; Calibration AB The Atmospheric Infrared Sounder (AIRS) on the EOS Aqua Spacecraft was launched on May 4, 2002 and is currently fully operational. AIRS acquires hyperspectral infrared radiances in 2378 channels ranging in wavelength from 3.7-15.4 um with spectral resolution of better than 1200, and spatial resolution of 13.5 km with global daily coverage. The AIRS was designed to measure temperature and water vapor profiles for improvement in weather forecast and improved parameterization of climate processes. Currently the AIRS Level 1B Radiance Products are assimilated by NWP centers worldwide and have shown considerable forecast improvement. Although the calibration of AIRS (< 200 mK 3 sigma) is sufficient for data assimilation into Numerical Weather Prediction (NWP) models, long term trends of Earth's climate require radiances with stability approaching 10 mK/year, and absolute accuracies better than 100 mK. This investigation uses views of space during roll maneuvers of the Aqua spacecraft to calibrate the mirror emission (one of the largest error sources for AIRS) and reduce the residual errors in cold scenes. We also present results of a secondary study that uses MODIS data to determine the alignment of the AIRS boresight. In this study we match AIRS and MODIS data and iterate on the assumed boresight to find the minimum difference in signal. In this way we are able to confirm the boresight projections determined shortly after launch. C1 [Pagano, Thomas S.; Broberg, Steven E.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Pagano, TS (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Thomas.S.Pagano@jpl.nasa.gov NR 8 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0335-6; 978-1-5106-0336-3 J9 PROC SPIE PY 2016 VL 9972 AR UNSP 997208 DI 10.1117/12.2238765 PG 9 WC Instruments & Instrumentation; Remote Sensing; Optics; Imaging Science & Photographic Technology SC Instruments & Instrumentation; Remote Sensing; Optics; Imaging Science & Photographic Technology GA BG5CW UT WOS:000389369500007 ER PT S AU Wu, AS Xiong, XX Cao, CY AF Wu, Aisheng Xiong, Xiaoxiong (Jack) Cao, Changyong BE Butler, JJ Xiong, X Gu, X TI Tracking on-orbit stability of the response versus scan angle for the S-NPP VIIRS reflective solar bands SO Earth Observing Systems XXI SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Earth Observing Systems XXI CY AUG 30-SEP 01, 2016 CL San Diego, CA SP SPIE DE VIIRS; Suomi NPP; calibration; on-orbit; reflective solar bands ID MODIS; PERFORMANCE AB The Visible Infrared Imaging Radiometer Suite (VIIRS) on the Suomi NPP (National Polar-orbiting Partnership) satellite (http://npp.gsfc.nasa.gov/viirs.html) has been in operation for nearly five years. The on-board calibration of the VIIRS reflective solar bands (RSB) relies on a solar diffuser (SD) located at a fixed scan angle and a solar diffuser stability monitor (SDSM). The VIIRS response versus scan angle (RVS) was characterized prelaunch in ambient conditions and is currently used to determine the on-orbit response for all scan angles relative to the SD scan angle. Since the RVS is vitally important to the quality of calibrated level 1B products, it is important to monitor its on-orbit stability. In this study, the RVS stability is examined based on reflectance trends collected from 16-day repeatable orbits over pre-selected pseudo-invariant desert sites in Northern Africa. These trends nearly cover the entire Earth view scan range so that any systematic drifts in the scan angle direction would indicate a change in RVS. This study also compares VIIRS RVS on-orbit stability results with those from both Aqua and Terra MODIS over the first four years of mission for a few selected bands, which provides further information on potential VIIRS RVS on-orbit changes. C1 [Wu, Aisheng] Sci Syst & Applicat Inc, 10210 Greenbelt Rd, Lanham, MD 20706 USA. [Xiong, Xiaoxiong (Jack)] NASA, GSFC, Sci & Explorat Directorate, Greenbelt, MD 20771 USA. [Cao, Changyong] NOAA, NESDIS, STAR, College Pk, MD 20740 USA. RP Wu, AS (reprint author), Sci Syst & Applicat Inc, 10210 Greenbelt Rd, Lanham, MD 20706 USA. RI Cao, Changyong/F-5578-2010 NR 16 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0335-6; 978-1-5106-0336-3 J9 PROC SPIE PY 2016 VL 9972 AR UNSP 99721C DI 10.1117/12.2238106 PG 10 WC Instruments & Instrumentation; Remote Sensing; Optics; Imaging Science & Photographic Technology SC Instruments & Instrumentation; Remote Sensing; Optics; Imaging Science & Photographic Technology GA BG5CW UT WOS:000389369500040 ER PT S AU Xiong, XX Chen, N Li, YH Wilson, T AF Xiong, Xiaoxiong Chen, Na Li, Yonghong Wilson, Truman BE Butler, JJ Xiong, X Gu, X TI Assessments and Applications of Terra and Aqua MODIS On-orbit Electronic Calibration SO Earth Observing Systems XXI SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Earth Observing Systems XXI CY AUG 30-SEP 01, 2016 CL San Diego, CA SP SPIE DE MODIS; On-board Calibrators; Electronic Calibration; Gains ID REFLECTIVE SOLAR BANDS; PERFORMANCE AB MODIS has 36 spectral bands located on four focal plane assemblies (FPAs), covering wavelengths from 0.41 to 14.4 mu m. MODIS bands 1-30 collect data using photovoltaic (PV) detectors and, therefore, are referred to as the PV bands. Similarly, bands 31-36 using photoconductive (PC) detectors are referred to as the PC bands. The MODIS instrument was built with a set of on-board calibrators (OBCs) in order to track on-orbit changes of its radiometric, spatial, and spectral characteristics. In addition, an electronic calibration (ECAL) function can be used to monitor on-orbit changes of its electronic responses (gains). This is accomplished via a series of stair step signals generated by the ECAL function. These signals, in place of the FPA detector signals, are amplified and digitized just like the detector signals. Over the entire mission of both Terra and Aqua MODIS, the ECAL has been performed for the PV bands and used to assess their on-orbit performance. This paper provides an overview of MODIS on-orbit calibration activities with a focus on the PV ECAL, including its calibration process and approaches used to monitor the electronic performance. It presents the results derived and lessons learned from Terra and Aqua MODIS on-orbit ECAL. Also discussed are some of the applications performed with the information provided by the ECAL data. C1 [Xiong, Xiaoxiong] NASA, Goddard Space Flight Ctr, Sci & Explorat Directorate, Greenbelt, MD 20771 USA. [Chen, Na; Li, Yonghong; Wilson, Truman] Sci Syst & Applicat Inc, 10210 Greenbelt Rd, Lanham, MD USA. RP Xiong, XX (reprint author), NASA, Goddard Space Flight Ctr, Sci & Explorat Directorate, Greenbelt, MD 20771 USA. NR 22 TC 1 Z9 1 U1 1 U2 1 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0335-6; 978-1-5106-0336-3 J9 PROC SPIE PY 2016 VL 9972 AR UNSP 99720X DI 10.1117/12.2238603 PG 10 WC Instruments & Instrumentation; Remote Sensing; Optics; Imaging Science & Photographic Technology SC Instruments & Instrumentation; Remote Sensing; Optics; Imaging Science & Photographic Technology GA BG5CW UT WOS:000389369500028 ER PT S AU Eleftheratos, K Myhre, G Minnis, P Kapsomenakis, I Zerefos, C AF Eleftheratos, Kostas Myhre, Gunnar Minnis, Patrick Kapsomenakis, Ioannis Zerefos, Christos BE Grammelis, P TI lManmade Changes in Cirrus Clouds from 1984 to 2007: A Preliminary Study SO Energy, Transportation and Global Warming SE Green Energy and Technology LA English DT Article; Book Chapter ID CONTRAILS; AVIATION; CLIMATE; IMPACT; COVER C1 [Eleftheratos, Kostas] Univ Athens, Lab Climatol & Atmospher Environm, Fac Geol & Geoenvironm, Athens 15784, Greece. [Eleftheratos, Kostas] Acad Athens, Biomed Res Fdn, Athens, Greece. [Myhre, Gunnar] Ctr Int Climate & Environm Res Cicero Oslo CICERO, Oslo, Norway. [Minnis, Patrick] NASA Langley Res Ctr, Atmospher Sci, Hampton, VA USA. [Kapsomenakis, Ioannis] Acad Athens, Res Ctr Atmospher Phys & Climatol, Athens, Greece. [Zerefos, Christos] NEO, Messinia, Greece. RP Eleftheratos, K (reprint author), Univ Athens, Lab Climatol & Atmospher Environm, Fac Geol & Geoenvironm, Athens 15784, Greece.; Eleftheratos, K (reprint author), Acad Athens, Biomed Res Fdn, Athens, Greece. EM kelef@geol.uoa.gr NR 22 TC 0 Z9 0 U1 0 U2 0 PU SPRINGER INT PUBLISHING AG PI CHAM PA GEWERBESTRASSE 11, CHAM, CH-6330, SWITZERLAND SN 1865-3529 BN 978-3-319-30127-3; 978-3-319-30126-6 J9 GREEN ENERGY TECHNOL PY 2016 BP 827 EP 836 DI 10.1007/978-3-319-30127-3_61 D2 10.1007/978-3-319-30127-3 PG 10 WC Energy & Fuels; Environmental Sciences SC Energy & Fuels; Environmental Sciences & Ecology GA BG4PR UT WOS:000389037200062 ER PT S AU Hill, JR Caldwell, BS Miller, MJ Lees, DS AF Hill, Jordan R. Caldwell, Barrett S. Miller, Michael J. Lees, David S. BE Yamamoto, S TI Data Integration and Knowledge Coordination for Planetary Exploration Traverses SO Human Interface and the Management of Information: Applications and Services, Pt II SE Lecture Notes in Computer Science LA English DT Proceedings Paper CT 18th International Conference on Human-Computer Interaction (HCI International) CY JUL 17-22, 2016 CL Toronto, CANADA DE Physiological monitoring; Extravehicular activity; Human performance; Extreme environments; Distributed task coordination AB In order to implement an ambulatory physiological monitor in a free-range environment, a number of human performance sensing, human-computer interaction, data visualization, and wireless transmission technologies must be effectively and unobtrusively integrated. The Zephyr BioHarness (TM) is being integrated into NASA's Biologic Analog Science Associated with Lava Terrains (BASALT) Mars simulation in order to monitor and transmit crewmember health and activity information during "extravehicular activity" (EVA) sample collection tasks. The structure of the simulation and the different types of data and knowledge coordination are described. The importance of physiological monitoring in extreme environments, the selection of the BioHarness (TM) for use in the project, the process of integrating the monitor into the simulation, and the anticipated results from the analysis of the gathered data are also discussed. C1 [Hill, Jordan R.; Caldwell, Barrett S.] Purdue Univ, Ind Engn, W Lafayette, IN 47907 USA. [Miller, Michael J.] NASA, Kennedy Space Ctr, Titusville, FL USA. [Lees, David S.] CMU NASA, Ames Res Ctr, Moffett Field, Mountain View, CA USA. RP Hill, JR (reprint author), Purdue Univ, Ind Engn, W Lafayette, IN 47907 USA. EM hill265@purdue.edu; bscaldwell@purdue.edu; michael.j.miller@nasa.gov; david.s.lees@nasa.gov NR 21 TC 0 Z9 0 U1 0 U2 0 PU SPRINGER INT PUBLISHING AG PI CHAM PA GEWERBESTRASSE 11, CHAM, CH-6330, SWITZERLAND SN 0302-9743 BN 978-3-319-40397-7; 978-3-319-40396-0 J9 LECT NOTES COMPUT SC PY 2016 VL 9735 BP 414 EP 422 DI 10.1007/978-3-319-40397-7_39 PG 9 WC Computer Science, Cybernetics; Computer Science, Information Systems; Computer Science, Interdisciplinary Applications; Computer Science, Theory & Methods SC Computer Science GA BG5FS UT WOS:000389467600039 ER PT J AU Barad, MF Brehm, C Kiris, CC Biswas, R AF Barad, Michael F. Brehm, Christoph Kiris, Cetin C. Biswas, Rupak TI Parallel adaptive high-order CFD simulations characterising SOFIA cavity acoustics SO INTERNATIONAL JOURNAL OF COMPUTATIONAL FLUID DYNAMICS LA English DT Article DE higher order; immersed boundary; parallel CFD applications AB This paper presents large-scale parallel computational fluid dynamics simulations for the Stratospheric Observatory for Infrared Astronomy (SOFIA). SOFIA is an airborne, 2.5-m infrared telescope mounted in an open cavity in the aft fuselage of a Boeing 747SP. These simulations focus on how the unsteady flow field inside and over the cavity interferes with the optical path and mounting structure of the telescope. A temporally fourth-order accurate Runge-Kutta, and a spatially fifth-order accurate WENO-5Z scheme were used to perform implicit large eddy simulations. An immersed boundary method provides automated gridding for complex geometries and natural coupling to a block-structured Cartesian adaptive mesh refinement framework. Strong scaling studies using NASA's Pleiades supercomputer with up to 32 k CPU cores and 4 billion computational cells show excellent scaling. Dynamic load balancing based on execution time on individual adaptive mesh refinement (AMR) blocks addresses irregular numerical cost associated with blocks containing boundaries. Limits to scaling beyond 32 k cores are identified, and targeted code optimisations are discussed. C1 [Barad, Michael F.; Brehm, Christoph; Kiris, Cetin C.; Biswas, Rupak] NASA Ames Res Ctr, Mountain View, CA 94043 USA. RP Barad, MF (reprint author), NASA Ames Res Ctr, Mountain View, CA 94043 USA. EM michael.f.barad@nasa.gov FU NASA [STC-NNA10DF26C] FX NASA: contract STC-NNA10DF26C. NR 3 TC 0 Z9 0 U1 0 U2 0 PU TAYLOR & FRANCIS LTD PI ABINGDON PA 2-4 PARK SQUARE, MILTON PARK, ABINGDON OR14 4RN, OXON, ENGLAND SN 1061-8562 EI 1029-0257 J9 INT J COMPUT FLUID D JI Int. J. Comput. Fluid Dyn. PY 2016 VL 30 IS 6 SI SI BP 437 EP 443 DI 10.1080/10618562.2016.1222073 PG 7 WC Mechanics; Physics, Fluids & Plasmas SC Mechanics; Physics GA ED2SF UT WOS:000388698300009 ER PT J AU Ceze, MA Murman, SM AF Ceze, Marco A. Murman, Scott M. TI Global convergence strategies for a spectral-element space-time discontinuous-Galerkin discretization of the Navier Stokes-equations SO INTERNATIONAL JOURNAL OF COMPUTATIONAL FLUID DYNAMICS LA English DT Article DE Newton continuation methods; space-time discretization ID PSEUDOTRANSIENT CONTINUATION AB This paper presents two global convergence strategies for a spectral-element, space-time discretisation of the Navier-Stokes equations. The first employs a hierarchical temporal mesh subdivision and polynomial order reduction to approximate the high-order solution. The second generalises Pseudo-Transient Continuation for steady problems to a space-time system. C1 [Ceze, Marco A.; Murman, Scott M.] Oak Ridge Associated Univ, NASA Ames Res Ctr, Moffett Field, CA 94035 USA. RP Ceze, MA (reprint author), Oak Ridge Associated Univ, NASA Ames Res Ctr, Moffett Field, CA 94035 USA. EM marco.a.ceze@nasa.gov FU Oak Ridge Associated Universities via NASA's Postdoctoral Program FX The first author acknowledges the support provided by the Oak Ridge Associated Universities via NASA's Postdoctoral Program. NR 6 TC 0 Z9 0 U1 0 U2 0 PU TAYLOR & FRANCIS LTD PI ABINGDON PA 2-4 PARK SQUARE, MILTON PARK, ABINGDON OR14 4RN, OXON, ENGLAND SN 1061-8562 EI 1029-0257 J9 INT J COMPUT FLUID D JI Int. J. Comput. Fluid Dyn. PY 2016 VL 30 IS 6 SI SI BP 444 EP 449 DI 10.1080/10618562.2016.1250348 PG 6 WC Mechanics; Physics, Fluids & Plasmas SC Mechanics; Physics GA ED2SF UT WOS:000388698300010 ER PT J AU Schroeder, DM Seroussi, H Chu, W Young, DA AF Schroeder, Dustin M. Seroussi, Helene Chu, Winnie Young, Duncan A. TI Adaptively constraining radar attenuation and temperature across the Thwaites Glacier catchment using bed echoes SO JOURNAL OF GLACIOLOGY LA English DT Article DE attenuation; ice penetrating radar; temperature; thwaites glacier ID ANTARCTIC ICE-SHEET; AMUNDSEN SEA EMBAYMENT; WEST ANTARCTICA; BASAL CONDITIONS; EAST ANTARCTICA; RADIOFREQUENCY ATTENUATION; THERMAL REGIME; SHEAR-MARGIN; PINE ISLAND; GREENLAND AB Englacial temperature is a major control on ice rheology and flow. However, it is difficult to measure at the glacier to ice-sheet scale. As a result, ice-sheet models must make assumptions about en glacial temperature and rheology, which affect sea level projections. This is problematic if fundamental processes are not captured by models due to a lack of observationally constrained ice temperature values. Although radar sounding data have been exploited to constrain the temperature structure of the Greenland ice sheet using englacial layers, this approach is limited to areas and depths where these layers exist intact. In order to extend empirical radar-based temperature estimation beyond this limitation, we present a new technique for estimating englacial attenuation rates for the entire ice column using adaptive fitting of unfocused radar bed echoes based on the correlation of ice thickness and corrected bed echo power. We apply this technique to an airborne survey of Thwaites Glacier in West Antarctica and compare the results with temperatures and attenuation rates from a numerical ice-sheet model. We find that the estimated attenuation rates reproduce modelled patterns and values across the catchment with the greatest differences near steeply sloping bed topography. C1 [Schroeder, Dustin M.] Stanford Univ, Dept Geophys, Stanford, CA 94305 USA. [Seroussi, Helene] CALTECH, Jet Prop Lab, Pasadena, CA USA. [Chu, Winnie] Columbia Univ, Lamont Doherty Earth Observ, Palisades, NY USA. [Young, Duncan A.] Univ Texas Austin, Inst Geophys, Austin, TX USA. RP Schroeder, DM (reprint author), Stanford Univ, Dept Geophys, Stanford, CA 94305 USA. EM dustin.m.schroeder@stanford.edu RI Young, Duncan/G-6256-2010; OI Young, Duncan/0000-0002-6866-8176; Chu, Winnie/0000-0002-8107-7450; Schroeder, Dustin/0000-0003-1916-3929 FU NASA Cryospheric Sciences Program; NASA Sea Level Rise Program; NASA Earth and Space Science Fellowship FX The authors would like to thank N. Holschuh and an anonymous reviewer for their thoughtful comments. D.M.S. was supported by a grant from the NASA Cryospheric Sciences Program. H.S. was supported by grants from the NASA Cryospheric Sciences and Sea Level Rise Programs. W.C. was supported by a NASA Earth and Space Science Fellowship. Part of this work was carried out by the Jet Propulsion Laboratory, California Institute of Technology, under a contract with the National Aeronautics and Space Administration. NR 55 TC 0 Z9 0 U1 2 U2 2 PU CAMBRIDGE UNIV PRESS PI CAMBRIDGE PA EDINBURGH BLDG, SHAFTESBURY RD, CB2 8RU CAMBRIDGE, ENGLAND SN 0022-1430 EI 1727-5652 J9 J GLACIOL JI J. Glaciol. PY 2016 VL 62 IS 236 BP 1075 EP 1082 DI 10.1017/jog.2016.100 PG 8 WC Geography, Physical; Geosciences, Multidisciplinary SC Physical Geography; Geology GA ED9ER UT WOS:000389173500008 ER PT J AU Aller, J Mason, R Walls, K Tatar, G Jacobson, N Gannon, P AF Aller, Josh Mason, Ryan Walls, Kelly Tatar, Greg Jacobson, Nathan Gannon, Paul TI High-Temperature (550-700 degrees C) Chlorosilane Interactions with Iron SO JOURNAL OF THE ELECTROCHEMICAL SOCIETY LA English DT Article ID CHEMICAL-VAPOR-DEPOSITION; FE-SI; SILICON TETRACHLORIDE; HYDROGEN-CHLORIDE; DIFFUSION COUPLES; SILICIDES; CORROSION; MIXTURES; SYSTEM; OXYGEN AB Chlorosilane species are commonly used at high temperatures in the manufacture and refinement of ultra-high purity silicon and silicon materials. The chlorosilane species are often highly corrosive in these processes, necessitating the use of expensive, corrosion resistant alloys for the construction of reactors, pipes, and vessels required to handle and produce them. In this study, iron, the primary alloying component of low cost metals, was exposed to a silicon tetrachloride-hydrogen vapor stream at industrially-relevant times (0-100 hours), temperatures (550-700 degrees C), and vapor stream compositions. Post exposure analyses including FE-SEM, EDS, XRD, and gravimetric analysis revealed formation and growth of stratified iron silicide surface layers, which vary as a function of time and temperature. The most common stratification after exposure was a thin FeSi layer on the surface followed by a thick stoichiometric Fe3Si layer, a silicon activity gradient in an iron lattice, and finally, unreacted iron. Speculated mechanisms to explain these observations were supported by thermodynamic equilibrium simulations of experimental conditions. This study furthers the understanding of metals in chlorosilane environments, which is critically important for manufacturing the high purity silicon required for silicon-based electronic and photovoltaic devices. (C) The Author(s) 2016. Published by ECS. All rights reserved. C1 [Aller, Josh; Walls, Kelly] Montana State Univ, Mech & Ind Engn, Bozeman, MT 59717 USA. [Mason, Ryan; Tatar, Greg; Gannon, Paul] Montana State Univ, Chem & Biol Engn, Bozeman, MT 59717 USA. [Jacobson, Nathan] NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Aller, J (reprint author), Montana State Univ, Mech & Ind Engn, Bozeman, MT 59717 USA. EM josh.aller@yahoo.com FU GT Advanced Technologies; Montana State University College of Engineering FX We would like to graciously acknowledge GT Advanced Technologies for providing funding and industrial guidance on this project. Additionally, Montana State University College of Engineering provided secondary funding of this project. Finally, we acknowledge Montana State University's Imaging and Chemical Analysis Laboratory (ICAL) for their assistance with surface analysis. NR 36 TC 1 Z9 1 U1 2 U2 2 PU ELECTROCHEMICAL SOC INC PI PENNINGTON PA 65 SOUTH MAIN STREET, PENNINGTON, NJ 08534 USA SN 0013-4651 EI 1945-7111 J9 J ELECTROCHEM SOC JI J. Electrochem. Soc. PY 2016 VL 163 IS 10 BP C666 EP C674 DI 10.1149/2.0681610jes PG 9 WC Electrochemistry; Materials Science, Coatings & Films SC Electrochemistry; Materials Science GA ED8WF UT WOS:000389150900064 ER PT S AU Coulter, P Ohl, RG Blake, PN Bos, BJ Chambers, VJ Eichhorn, WL Gum, JS Hadjimichael, TJ Hagopian, JG Hayden, JE Hetherington, SE Kubalak, DA Mclean, KF McMann, JC Redman, KW Sampler, HP Wenzel, GW Young, JL AF Coulter, Phillip Ohl, Raymond G. Blake, Peter N. Bos, Brent J. Chambers, Victor J. Eichhorn, William L. Gum, Jeffrey S. Hadjimichael, Theodore J. Hagopian, John G. Hayden, Joseph E. Hetherington, Samuel E. Kubalak, David A. Mclean, Kyle F. McMann, Joseph C. Redman, Kevin W. Sampler, Henry P. Wenzel, Greg W. Young, Jerrod L. BE Sasian, J Youngworth, RN TI A Toolbox of Metrology-based Techniques for Optical System Alignment SO Optical System Alignment, Tolerancing, and Verification X SE Proceedings of SPIE LA English DT Proceedings Paper CT 10th Conference on Optical System Alignment, Tolerancing, and Verification X CY AUG 28-29, 2016 CL San Diego, CA SP SPIE DE JWST; metrology; optical alignment; OVIRS; spacecraft alignment AB The NASA Goddard Space Flight Center (GSFC) and its partners have broad experience in the alignment of flight optical instruments and spacecraft structures. Over decades, GSFC developed alignment capabilities and techniques for a variety of optical and aerospace applications. In this paper, we provide an overview of a subset of the capabilities and techniques used on several recent projects in a "toolbox" format. We discuss a range of applications, from small-scale optical alignment of sensors to mirror and bench examples that make use of various large-volume metrology techniques. We also discuss instruments and analytical tools. C1 [Coulter, Phillip; Ohl, Raymond G.; Blake, Peter N.; Bos, Brent J.; Chambers, Victor J.; Gum, Jeffrey S.; Hadjimichael, Theodore J.; Hetherington, Samuel E.; Kubalak, David A.; Sampler, Henry P.; Young, Jerrod L.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Eichhorn, William L.] Genesis Engn Solut Inc, Seabrook, MD USA. [Hagopian, John G.] John Hagopian Engn LLC, Binghamton, NY USA. [Hayden, Joseph E.] Sigma Space Corp, Lanham, MD USA. [Mclean, Kyle F.] Pinnacle Engn & Management Solut LLC, Princess Anne, MD USA. [McMann, Joseph C.; Redman, Kevin W.; Wenzel, Greg W.] Sierra Lobo Inc, Fremont, OH USA. RP Coulter, P (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. NR 21 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0293-9; 978-1-5106-0294-6 J9 PROC SPIE PY 2016 VL 9951 AR UNSP 995108 DI 10.1117/12.2239070 PG 20 WC Optics SC Optics GA BG5IG UT WOS:000389504700007 ER PT S AU Hadjimichael, T Ohl, RG Antonille, S Aronstein, DL Bartoszyk, A Berrier, J Cofie, E Coulter, P Gracey, R Hayden, J Howard, J Hylan, J Kubalak, D McLean, K Miskey, C Redman, K Rohrbach, S Sabatke, D Telfer, R Wenzel, G Zielinski, T Sullivan, J Hartig, G Eichhorn, W AF Hadjimichael, Theo Ohl, Raymond G. Antonille, Scott Aronstein, David L. Bartoszyk, Andrew Berrier, Josh Cofie, Emmanuel Coulter, Phil Gracey, Renee Hayden, Joseph Howard, Joseph Hylan, Jason Kubalak, David McLean, Kyle Miskey, Cherie Redman, Kevin Rohrbach, Scott Sabatke, Derek Telfer, Randal Wenzel, Greg Zielinski, Thomas Sullivan, Joseph Hartig, George Eichhorn, William BE Sasian, J Youngworth, RN TI Alignment of the James Webb Space Telescope Integrated Science Instrument Module Element SO Optical System Alignment, Tolerancing, and Verification X SE Proceedings of SPIE LA English DT Proceedings Paper CT 10th Conference on Optical System Alignment, Tolerancing, and Verification X CY AUG 28-29, 2016 CL San Diego, CA SP SPIE AB NASA's James Webb Space Telescope (JWST) is a 6.6m diameter, segmented, deployable telescope for cryogenic IR space astronomy. The JWST Observatory architecture includes the Optical Telescope Element (OTE) and the Integrated Science Instrument Module (ISIM) element which contains four science instruments (SI), including a guider. The SIs and guider are mounted to a composite metering structure with outer envelope approximate measurements of 2.2x2.2x1.7m. These SI units are integrated to the ISIM structure and optically tested at NASA Goddard Space Flight Center as an instrument suite using an Optical telescope element SIMulator (OSIM). OSIM is a high-fidelity, cryogenic JWST simulator that features a similar to 1.5m diameter powered mirror. The SIs are aligned to the flight structure's coordinate system under ambient, clean room conditions using opto-mechanical metrology and customized interfaces. OSIM is aligned to the ISIM mechanical coordinate system at the cryogenic operating temperature via internal mechanisms and feedback from alignment sensors and metrology in six degrees of freedom. SI performance, including focus, pupil shear, pupil roll, boresight, wavefront error, and image quality, is evaluated at the operating temperature using OSIM. This work reports on the as-run ambient assembly and ambient alignment steps for the flight ISIM, including SI interface fixtures and customization and kinematic mount adjustment. The ISIM alignment plan consists of multiple steps to meet the "absolute" alignment requirements of the SIs and OSIM to the flight coordinate system. In this paper, we focus on key aspects of absolute, optical-mechanical alignment. We discuss various metrology and alignment techniques. In addition, we summarize our approach for dealing with and the results of ground-test factors, such as gravity. C1 [Hadjimichael, Theo; Ohl, Raymond G.; Antonille, Scott; Aronstein, David L.; Bartoszyk, Andrew; Coulter, Phil; Howard, Joseph; Hylan, Jason; Kubalak, David; Rohrbach, Scott; Zielinski, Thomas] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Hadjimichael, T (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. NR 18 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0293-9; 978-1-5106-0294-6 J9 PROC SPIE PY 2016 VL 9951 DI 10.1117/12.2238829 PG 21 WC Optics SC Optics GA BG5IG UT WOS:000389504700010 ER PT S AU Kubalak, D Sullivan, J Ohl, R Antonille, S Beaton, A Coulter, P Hartig, G Kelly, D Lee, D Maszkiewicz, M Schweigerh, P Telfer, R Plate, MT Wells, M AF Kubalak, Dave Sullivan, Joe Ohl, Ray Antonille, Scott Beaton, Alexander Coulter, Phillip Hartig, George Kelly, Doug Lee, David Maszkiewicz, Michael Schweigerh, Paul Telfer, Randal Plate, Maurice Te Wells, Martyn BE Sasian, J Youngworth, RN TI JWST science instrument pupil alignment measurements SO Optical System Alignment, Tolerancing, and Verification X SE Proceedings of SPIE LA English DT Proceedings Paper CT 10th Conference on Optical System Alignment, Tolerancing, and Verification X CY AUG 28-29, 2016 CL San Diego, CA SP SPIE DE JWST; ISIM; pupil alignment; pupil; pupil shear; testing; verification AB NASA's James Webb Space Telescope (JWST) is a 6.5m diameter, segmented, deployable telescope for cryogenic IR space astronomy (similar to 40K). The JWST Observatory architecture includes the Optical Telescope Element (OTE) and the Integrated Science Instrument Module (ISIM) element that contains four science instruments (SI), including a guider. OSIM is a full field, cryogenic, optical simulator of the JWST OTE. It is the "Master Tool" for verifying the cryogenic alignment and optical performance of ISIM by providing simulated point source/star images to each of the four Science Instruments in ISIM. Included in OSIM is a Pupil Imaging Module (PIM) - a large format CCD used for measuring pupil alignment. Located at a virtual stop location within OSIM, the PIM records superimposed shadow images of pupil alignment reference (PAR) targets located in the OSIM and SI pupils. The OSIM Pupil Imaging Module was described by Brent Bos, et al, at SPIE in 2011 prior to ISIM testing. We have recently completed the third and final ISIM cryogenic performance verification test before ISIM was integrated with the OTE. In this paper, we describe PIM implementation, performance, and measurement results. C1 [Kubalak, Dave; Ohl, Ray; Antonille, Scott; Coulter, Phillip] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Sullivan, Joe] Ball Aerosp & Technol Corp, 1600 Commerce St, Boulder, CO 80306 USA. [Beaton, Alexander] ComDev Int, 303 Terry Fox Dr Suite 100, Ottawa, ON K2K 3J1, Canada. [Hartig, George; Telfer, Randal] Space Telescope Sci Inst, 3700 San Martin Dr, Baltimore, MD 21218 USA. [Kelly, Doug] Univ Arizona, Tucson, AZ 85721 USA. [Lee, David; Wells, Martyn] Royal Observ Edinburgh, UK Astron Technol Ctr, Edinburgh, Midlothian, Scotland. [Maszkiewicz, Michael] Canadian Space Agcy, 6767 Route Aeroport, St Hubert, PQ J3Y 8Y9, Canada. [Schweigerh, Paul] Lockheed Martin Space Syst Co, Denver, CO USA. [Plate, Maurice Te] European Space Agcy, Keplerlaan 1,POB 299, NL-2200 AG Noordwijk, Netherlands. RP Kubalak, D (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. NR 3 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0293-9; 978-1-5106-0294-6 J9 PROC SPIE PY 2016 VL 9951 AR UNSP 99510D DI 10.1117/12.2238830 PG 13 WC Optics SC Optics GA BG5IG UT WOS:000389504700011 ER PT S AU Reichard, TA Bond, NA Greeley, BW Malumuth, EM Melendez, M Shiri, R de Oliveira, CA Antonille, SR Birkmann, S Davis, C Dixon, WV Martel, A Miskey, CL Ohl, RG Sabatke, D Sullivan, J AF Reichard, Timothy A. Bond, Nicholas A. Greeley, Bradford W. Malumuth, Eliot M. Melendez, Marcio Shiri, Ron de Oliveira, Catarina Alves Antonille, Scott R. Birkmann, Stephan Davis, Clinton Dixon, William V. Martel, Andre Miskey, Cherie L. Ohl, Raymond G. Sabatke, Derek Sullivan, Joseph BE Sasian, J Youngworth, RN TI Cryogenic optical test planning using the Optical Telescope Element Simulator with the James Webb Space Telescope Integrated Science Instrument Module SO Optical System Alignment, Tolerancing, and Verification X SE Proceedings of SPIE LA English DT Proceedings Paper CT 10th Conference on Optical System Alignment, Tolerancing, and Verification X CY AUG 28-29, 2016 CL San Diego, CA SP SPIE DE James Webb Space Telescope; Optical Telescope Element Simulator; cryogenic optical testing; infrared detectors; telescopes; optical source brightness calibration; system verification AB NASA's James Webb Space Telescope (JWST) is a 6.5 m diameter, segmented, deployable telescope for cryogenic infrared space astronomy (similar to 40 K). The JWST Observatory architecture includes the Optical Telescope Element (OTE) and the Integrated Science Instrument Module (ISIM) element that contains four science instruments (SIs), including a guider. The SI and guider units are integrated to the ISIM structure and optically tested at NASA Goddard Space Flight Center as an instrument suite using a telescope simulator (Optical Telescope Element SIMulator; OSIM). OSIM is a high-fidelity, cryogenic JWST telescope simulator that features a similar to 1.5m diameter powered mirror. The SIs are aligned to the flight structure's coordinate system under ambient, clean room conditions using optomechanical metrology and customized interfaces. OSIM is aligned to the ISIM mechanical coordinate system at the cryogenic operating temperature via internal mechanisms and feedback from alignment sensors and metrology in six degrees of freedom. SI performance, including focus, pupil shear, pupil roll, boresight, wavefront error, and image quality, is evaluated at the operating temperature using OSIM. The comprehensive optical test plans include drafting OSIM source configurations for thousands of exposures ahead of the start of a cryogenic test campaign. We describe how we predicted the performance of OSIM light sources illuminating the ISIM detectors to aide in drafting these optical tests before a test campaign began. We also discuss the actual challenges and successes of those exposure predictions encountered during a test campaign to fulfill the demands of the ISIM optical performance verification. C1 [Reichard, Timothy A.; Bond, Nicholas A.] ADNET Syst Inc, 6720B Rockledge Dr,Suite 504, Bethesda, MD 20817 USA. [Reichard, Timothy A.; Bond, Nicholas A.; Greeley, Bradford W.; Malumuth, Eliot M.; Melendez, Marcio; Shiri, Ron; Antonille, Scott R.; Davis, Clinton; Miskey, Cherie L.; Ohl, Raymond G.] NASA, Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. [Malumuth, Eliot M.; Melendez, Marcio] KBRwyle Sci Technol & Engn Grp, 1290 Hercules Ave, Houston, TX 77058 USA. [de Oliveira, Catarina Alves; Birkmann, Stephan] European Space Agcy STScI, 3700 San Martin Dr, Baltimore, MD 21218 USA. [Davis, Clinton] Genesis Engn Solut Inc, 4501 Boston Way, Lanham, MD 20706 USA. [Dixon, William V.; Martel, Andre] STScI, 3700 San Martin Dr, Baltimore, MD 21218 USA. [Martel, Andre] NRC Herzberg Astron & Astrophys, 5071 West Saanich Rd, Victoria, BC, Canada. [Miskey, Cherie L.] Stinger Ghaffarian Technol Inc, 7701 Greenbelt Rd,Suite 400, Greenbelt, MD 20770 USA. [Sabatke, Derek; Sullivan, Joseph] Ball Aerosp & Technol Corp, 1600 Commerce St, Boulder, CO 80301 USA. RP Reichard, TA (reprint author), ADNET Syst Inc, 6720B Rockledge Dr,Suite 504, Bethesda, MD 20817 USA.; Reichard, TA (reprint author), NASA, Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. NR 10 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0293-9; 978-1-5106-0294-6 J9 PROC SPIE PY 2016 VL 9951 AR UNSP 99510N DI 10.1117/12.2237006 PG 15 WC Optics SC Optics GA BG5IG UT WOS:000389504700021 ER PT S AU Rohrbach, SO Kubalak, DA Gracey, RM Sabatke, DS Howard, JM Telfer, RC Zielinski, TP AF Rohrbach, Scott O. Kubalak, David A. Gracey, Renee M. Sabatke, Derek S. Howard, Joseph M. Telfer, Randal C. Zielinski, Thomas P. BE Sasian, J Youngworth, RN TI Critical science instrument alignment of the James Webb Space Telescope (JWST) Integrated Science Instrument Module (ISIM) SO Optical System Alignment, Tolerancing, and Verification X SE Proceedings of SPIE LA English DT Proceedings Paper CT 10th Conference on Optical System Alignment, Tolerancing, and Verification X CY AUG 28-29, 2016 CL San Diego, CA SP SPIE DE JWST; ISIM; focus; pupil shear; boresight AB This paper describes the critical instrument alignment terms associated with the six-degree of freedom alignment of each the Science Instrument ( SI) in the James Webb Space Telescope (JWST), including focus, pupil shear, pupil clocking, and boresight. We present the test methods used during cryogenic-vacuum tests to directly measure the performance of each parameter, the requirements levied on each, and the impact of any violations of these requirements at the instrument and Observatory level. C1 [Rohrbach, Scott O.; Kubalak, David A.; Howard, Joseph M.; Zielinski, Thomas P.] NASA, Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. [Gracey, Renee M.; Sabatke, Derek S.] Ball Aerosp & Technol Corp, 1600 Commerce St, Boulder, CO 80301 USA. [Telfer, Randal C.] Space Telescope Sci Inst, 3700 San Martin Dr, Baltimore, MD 21218 USA. RP Rohrbach, SO (reprint author), NASA, Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. EM Scott.rohrbach@nasa.gov NR 12 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0293-9; 978-1-5106-0294-6 J9 PROC SPIE PY 2016 VL 9951 AR UNSP 995106 DI 10.1117/12.2238825 PG 18 WC Optics SC Optics GA BG5IG UT WOS:000389504700005 ER PT S AU Sullivan, JF Eichhorn, WL Sabatke, DS Davis, CR Chu, J Tournois, SC Kubalak, DA Greeley, BW Kimble, RA Telfer, RC Hartig, GF Ohl, RG Kirk, JR von Handorf, RJ Wolf, EM Chang, WS AF Sullivan, Joseph F. Eichhorn, William L. Sabatke, Derek S. Davis, Clinton R. Chu, Jenny Tournois, Severine C. Kubalak, David A. Greeley, Bradford W. Kimble, Randy A. Telfer, Randal C. Hartig, George F. Ohl, Raymond G. Kirk, Jeffrey R. von Handorf, Robert J. Wolf, Erin M. Chang, William S. BE Sasian, J Youngworth, RN TI JWST's optical telescope simulator for verification of the Integrated Science Instrument Module SO Optical System Alignment, Tolerancing, and Verification X SE Proceedings of SPIE LA English DT Proceedings Paper CT 10th Conference on Optical System Alignment, Tolerancing, and Verification X CY AUG 28-29, 2016 CL San Diego, CA SP SPIE DE JWST; Optical Simulator; OSIM; ISIM AB OSIM is a full field, cryogenic, optical simulator of the James Webb Space Telescope (JWST) Optical Telescope Element (OTE). It is the "Master Tool" for verifying the cryogenic alignment and optical performance of the JWST Integrated Science Instrument Module (ISIM) by providing simulated point source/star images individually or simultaneously to each of the four Science Instruments in ISIM. Additionally, each star image can be scanned in focus to support the evaluation of both image quality and best focus for each Science Instrument. OSIM has recently completed supporting the ISIM performance verification test campaign which spanned three separate cryogenic test campaigns over 3 years. In this paper, we describe the alignment to the JWST coordinate system at cryogenic temperatures, OSIM optical performance, repeatability, and its role in testing the cryogenic optical performance of the individual Science Instruments in addition to providing calibration data needed for flight operations. C1 [Sullivan, Joseph F.; Sabatke, Derek S.; von Handorf, Robert J.] Ball Aerosp & Technol Corp, 1600 Commerce St, Boulder, CO 80301 USA. [Eichhorn, William L.; Kubalak, David A.; Greeley, Bradford W.; Kimble, Randy A.; Ohl, Raymond G.] NASA, Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. [Chu, Jenny] Orbital Sci Corp TSD, 7500 Greenway Ctr Dr, Greenbelt, MD 20770 USA. [Tournois, Severine C.] Sigma Space Corp, 4801 Forbes Blvd, Lanham, MD 20706 USA. [Chang, William S.] Edge Space Syst Inc, POB 310, Glenelg, MD 21737 USA. [Davis, Clinton R.; Kirk, Jeffrey R.; Wolf, Erin M.] Genesis Engn Solut Inc, 4501 Boston Way, Lanham, MD 20706 USA. [Telfer, Randal C.; Hartig, George F.] Space Telescope Sci Inst, 3700 San Martin Dr, Baltimore, MD 21218 USA. RP Sullivan, JF (reprint author), Ball Aerosp & Technol Corp, 1600 Commerce St, Boulder, CO 80301 USA. NR 11 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0293-9; 978-1-5106-0294-6 J9 PROC SPIE PY 2016 VL 9951 AR UNSP 99510E DI 10.1117/12.2237834 PG 20 WC Optics SC Optics GA BG5IG UT WOS:000389504700012 ER PT S AU te Plate, M Rumler, P Jensen, P Eder, R Ehrenwinkler, R Merkle, F Roedel, A Speckmaier, M Johnson, TE Mott, B Snodgrass, S Gunn, C Ward, J AF te Plate, Maurice Rumler, Peter Jensen, Peter Eder, Robert Ehrenwinkler, Ralf Merkle, Frank Roedel, Andreas Speckmaier, Max Johnson, Thomas E. Mott, Brent Snodgrass, Stephen Gunn, Chris Ward, Justin BE Sasian, J Youngworth, RN TI How to align a new detector and micro shutter inside JWST's Near Infrared Spectrograph (NIRSpec) SO Optical System Alignment, Tolerancing, and Verification X SE Proceedings of SPIE LA English DT Proceedings Paper CT 10th Conference on Optical System Alignment, Tolerancing, and Verification X CY AUG 28-29, 2016 CL San Diego, CA SP SPIE DE James Webb Space Telescope; NIRSpec; Multi-object spectrograph; Infrared; Micro Shutter Array; MEMS; SiC AB JWST will be the biggest space telescope ever built and it will lead to astounding scientific breakthroughs. The mission will be launched in October 2018 from Kourou, French Guyana by an ESA provided Ariane 5 rocket. NIRSpec, one of the four instruments on board of the mission, recently underwent a major upgrade. New infrared detectors were installed and the Micro Shutter Assembly (MSA) was replaced as well. The rework was necessary because both systems were found to be degrading beyond a level that could be accepted. The installation and "in situ" alignment of these new systems required special techniques and alignment jigs that will be described in this paper. Some first results will be presented as well. C1 [te Plate, Maurice] European Space Agcy, STScI, 3700 San Martin Dr, Baltimore, MD 21218 USA. [Rumler, Peter; Jensen, Peter] European Space Agcy, Keplerlaan 1,POB 299, NL-2200 AG Noordwijk, Netherlands. [Eder, Robert; Ehrenwinkler, Ralf; Merkle, Frank; Roedel, Andreas; Speckmaier, Max] AIRBUS Def & Space, D-81663 Munich, Germany. [Johnson, Thomas E.; Mott, Brent; Snodgrass, Stephen; Gunn, Chris; Ward, Justin] NASA, Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. RP te Plate, M (reprint author), European Space Agcy, STScI, 3700 San Martin Dr, Baltimore, MD 21218 USA. NR 4 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0293-9; 978-1-5106-0294-6 J9 PROC SPIE PY 2016 VL 9951 AR UNSP 99510F DI 10.1117/12.2238386 PG 11 WC Optics SC Optics GA BG5IG UT WOS:000389504700013 ER PT S AU Ramapriyan, HK Goldstein, JC Hua, H Wolfe, RE AF Ramapriyan, Hampapuram K. Goldstein, Justin C. Hua, Hook Wolfe, Robert E. BE Mattoso, M Glavic, B TI Tracking and Establishing Provenance of Earth Science Datasets: A NASA-Based Example SO Provenance and Annotation of Data and Processes, IPAW 2016 SE Lecture Notes in Computer Science LA English DT Proceedings Paper CT 6th International Provenance and Annotation Workshop (IPAW) CY JUN 07-08, 2016 CL McLean, VA SP MITRE Corp DE Information systems; Data provenance; Information quality; HISA reports; Climate Assessment; Lessons learned AB Information quality is of paramount importance to science. Accurate, scientifically vetted and statistically meaningful and, ideally, reproducible information engenders scientific trust and research opportunities. Therefore, so-called Highly Influential Scientific Assessments (HISA) such as the U.S. Third National Climate Assessment (NCA3) undergo a very rigorous process to ensure transparency and credibility. As an activity to support the transparency of such reports, the U.S. Global Change Research Program has developed the Global Change Information System (GCIS). Specifically related to the transparency of NCA3, a recent activity was carried out to trace the provenance as completely as possible for all figures in the NCA3 report that predominantly used NASA data. This paper discusses lessons learned from this activity that traces the provenance of NASA figures in a major HISA-class pdf report. C1 [Ramapriyan, Hampapuram K.] Sci Syst & Applicat Inc, Lanham, MD 20706 USA. [Goldstein, Justin C.] ICF Int, Fairfax, VA USA. [Goldstein, Justin C.; Wolfe, Robert E.] US Global Change Res Program, Washington, DC USA. [Hua, Hook] CALTECH, Pasadena, CA 91125 USA. [Hua, Hook] NASA, Jet Prop Lab, Pasadena, CA USA. [Wolfe, Robert E.] NASA, Goddard Space Flight Ctr, Greenbelt, MD USA. RP Ramapriyan, HK (reprint author), Sci Syst & Applicat Inc, Lanham, MD 20706 USA. EM Hampapuram.Ramapriyan@ssaihq.com; jgoldstein@usgcrp.gov; hook.hua@jpl.nasa.gov; robert.e.wolfe@nasa.gov RI Goldstein, Justin/J-6880-2012 OI Goldstein, Justin/0000-0001-5414-9589 NR 6 TC 0 Z9 0 U1 0 U2 0 PU SPRINGER INT PUBLISHING AG PI CHAM PA GEWERBESTRASSE 11, CHAM, CH-6330, SWITZERLAND SN 0302-9743 BN 978-3-319-40593-3; 978-3-319-40592-6 J9 LECT NOTES COMPUT SC PY 2016 VL 9672 BP 226 EP 229 DI 10.1007/978-3-319-40593-3_27 PG 4 WC Computer Science, Information Systems; Computer Science, Software Engineering; Computer Science, Theory & Methods SC Computer Science GA BG5GX UT WOS:000389496000027 ER PT S AU Lemaillet, P Patrick, HJ Germer, TA Hanssen, L Johnson, BC Georgiev, GT AF Lemaillet, Paul Patrick, Heather J. Germer, Thomas A. Hanssen, Leonard Johnson, B. Carol Georgiev, Georgi T. BE Hanssen, LM TI Goniometric and hemispherical reflectance and transmittance measurements of fused silica SO Reflection, Scattering, and Diffraction from Surfaces V SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Reflection, Scattering, and Diffraction from Surfaces V CY AUG 28-29, 2016 CL San Diego, CA SP SPIE DE BRDF; BTDF; diffusers; fused silica; reflectance; scattering coefficients; transmittance ID OPTICAL-PROPERTIES AB Fused silica diffusers, made by forming scattering centers inside fused silica glass, can exhibit desirable optical properties, such as reflectance or transmittance independent of viewing angle, spectrally flat response into the ultraviolet wavelength range, and good spatial uniformity. The diffusers are of interest for terrestrial and space borne remote sensing instruments, which use light diffusers in reflective and transmissive applications. In this work, we report exploratory measurements of two samples of fused silica diffusers. We will present goniometric bidirectional scattering distribution function (BSDF) measurements under normal illumination provided by the National Institute of Standards and Technology (NIST)'s Goniometric Optical Scatter Instrument (GOSI), by NIST's Infrared reference integrating sphere ( IRIS) and by the National Aeronautics and Space Administration (NASA)'s Diffuser Calibration Laboratory. We also present hemispherical diffuse transmittance and reflectance measurements provided by NIST's Double integrating sphere Optical Scattering Instrument (DOSI). The data from the DOSI is analyzed by Prahl's inverse adding-doubling algorithm to obtain the absorption and reduced scattering coefficient of the samples. Implications of fused silica diffusers for remote sensing applications are discussed. C1 [Lemaillet, Paul; Patrick, Heather J.; Germer, Thomas A.; Hanssen, Leonard; Johnson, B. Carol] NIST, 100 Bur Dr, Gaithersburg, MD 20899 USA. [Georgiev, Georgi T.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Georgiev, Georgi T.] Sci Syst & Applicat Inc, Lanham, MD 20706 USA. RP Lemaillet, P (reprint author), NIST, 100 Bur Dr, Gaithersburg, MD 20899 USA. EM paul.lemaillet@nist.gov NR 19 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0313-4; 978-1-5106-0314-1 J9 PROC SPIE PY 2016 VL 9961 AR UNSP 996109 DI 10.1117/12.2237975 PG 12 WC Optics; Physics, Applied SC Optics; Physics GA BG5CZ UT WOS:000389379000007 ER PT J AU Spann, JF Davis, JM AF Spann, James F. Davis, Jacqueline M. TI Selected contributions to the 2015 NASA/MSFC Science and Technology Jamboree SO Results in Physics LA English DT Editorial Material C1 [Spann, James F.; Davis, Jacqueline M.] NASA, Marshall Space Flight Ctr, Sci & Technol Off, ZP01,320 Sparkman Dr, Huntsville, AL 35805 USA. RP Spann, JF (reprint author), NASA, Marshall Space Flight Ctr, Sci & Technol Off, ZP01,320 Sparkman Dr, Huntsville, AL 35805 USA. EM jim.spann@nasa.gov NR 0 TC 0 Z9 0 U1 1 U2 1 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS SN 2211-3797 J9 RESULTS PHYS JI Results Phys. PY 2016 VL 6 BP 1178 EP 1178 DI 10.1016/j.rinp.2016.11.048 PG 1 WC Materials Science, Multidisciplinary; Physics, Multidisciplinary SC Materials Science; Physics GA EE7BU UT WOS:000389770300207 ER PT J AU Weisskopf, MC Ramsey, B O'Dell, SL Tennant, A Elsner, R Soffita, P Bellazzini, R Costa, E Kolodziejczak, J Kaspi, V Mulieri, F Marshall, H Matt, G Romani, R AF Weisskopf, Martin C. Ramsey, Brian O'Dell, Stephen L. Tennant, Allyn Elsner, Ronald Soffita, Paolo Bellazzini, Ronaldo Costa, Enrico Kolodziejczak, Jeffery Kaspi, Victoria Mulieri, Fabio Marshall, Herman Matt, Giorgio Romani, Roger CA IXPE Team TI The Imaging X-ray Polarimetry Explorer (IXPE) SO Results in Physics LA English DT Article DE X-ray astronomy; X-ray polarimetry; X-ray imaging AB The Imaging X-ray Polarimetry Explorer (IXPE) expands observation space by simultaneously adding polarization to the array of X-ray source properties currently measured (energy, time, and location). IXPE will thus open new dimensions for understanding how X-ray emission is produced in astrophysical objects, especially in systems under extreme physical conditions. Published by Elsevier B.V. C1 [Weisskopf, Martin C.; Ramsey, Brian; O'Dell, Stephen L.; Tennant, Allyn; Elsner, Ronald; Kolodziejczak, Jeffery] NASA, Marshall Space Flight Ctr, ZP12, Huntsville, AL 35812 USA. [Soffita, Paolo; Costa, Enrico; Mulieri, Fabio] IAPS INAF, I-00133 Rome, Italy. [Bellazzini, Ronaldo] Ist Nazl Fis Nucl, I-56127 Pisa, Italy. [Kaspi, Victoria] McGill Univ, Montreal, PQ H3A 0G4, Canada. [Marshall, Herman] MIT, Cambridge, MA 02139 USA. [Matt, Giorgio] Univ Roma Tre, I-00154 Rome, Italy. [Romani, Roger] Stanford Univ, Stanford, CA 94305 USA. RP Weisskopf, MC (reprint author), NASA MSFC ZP12, 320 Sparkman Dr, Huntsville, AL 35805 USA. EM martin.c.weisskopf@nasa.gov NR 1 TC 0 Z9 0 U1 1 U2 1 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS SN 2211-3797 J9 RESULTS PHYS JI Results Phys. PY 2016 VL 6 BP 1179 EP 1180 DI 10.1016/j.rinp.2016.10.021 PG 2 WC Materials Science, Multidisciplinary; Physics, Multidisciplinary SC Materials Science; Physics GA EE7BU UT WOS:000389770300208 ER PT J AU Gallagher, D AF Gallagher, D. TI Is there a hole in the topside, equatorial ionosphere? SO Results in Physics LA English DT Article DE Ionosphere; Topside; Magnetic equator; Plasmasphere AB A paper in 2000 (Huba, 2000) found a depression in electron density in the topside ionosphere near the magnetic equator, based on the SAMI-2 physical ionospheric model. The model showed, for the first time, the formation of a hole in electron density in the altitude range 1500-2500 km at geomagnetic equatorial latitudes. The model produced the hole because of transhemispheric O+ flows that collisionally couple to H+, transporting it to lower altitudes, and thereby reducing the electron density at high altitudes. At that time and until now, no published observations have been reported to confirm or refute this numerical result. Recent, new analysis of Dynamics Explorer 1 Retarding Ion Mass Spectrometer measurements provides the first tentative experimental support for this model result. Published by Elsevier B.V. C1 [Gallagher, D.] NASA, Marshall Space Flight Ctr, Space Res Off, Mail Code ZP10, Huntsville, AL 35812 USA. RP Gallagher, D (reprint author), NASA, Marshall Space Flight Ctr, Space Res Off, Mail Code ZP10, Huntsville, AL 35812 USA. NR 4 TC 0 Z9 0 U1 1 U2 1 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS SN 2211-3797 J9 RESULTS PHYS JI Results Phys. PY 2016 VL 6 BP 1181 EP 1182 DI 10.1016/j.rinp.2016.11.001 PG 2 WC Materials Science, Multidisciplinary; Physics, Multidisciplinary SC Materials Science; Physics GA EE7BU UT WOS:000389770300209 ER PT J AU Case, JL AF Case, Jonathan L. TI From drought to flooding in less than a week over South Carolina SO Results in Physics LA English DT Article DE Extreme precipitation; Flooding; NASA; Land surface modeling; Soil moisture AB A deep tropical moisture connection to Hurricane Joaquin led to historic rainfall and flooding over South Carolina from 3 to 5 October 2015, erasing the prevailing moderate to severe meteorological and agricultural drought that had developed from May through September. NASA's Global Precipitation Mission constellation of satellites and a real-time implementation of the NASA Land Information System highlight the precipitation and land surface response of this event. (C) 2016 Elsevier B.V. C1 [Case, Jonathan L.] NASA, ENSCO Inc, Short Term Predict Res & Transit SPoRT Ctr, 320 Sparkman Dr, Huntsville, AL 35805 USA. RP Case, JL (reprint author), NASA, ENSCO Inc, Short Term Predict Res & Transit SPoRT Ctr, 320 Sparkman Dr, Huntsville, AL 35805 USA. EM Jonathan.Case-1@nasa.gov NR 3 TC 0 Z9 0 U1 3 U2 3 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS SN 2211-3797 J9 RESULTS PHYS JI Results Phys. PY 2016 VL 6 BP 1183 EP 1184 DI 10.1016/j.rinp.2016.11.012 PG 2 WC Materials Science, Multidisciplinary; Physics, Multidisciplinary SC Materials Science; Physics GA EE7BU UT WOS:000389770300210 ER PT J AU Rabenberg, E Brown, A Kaukler, WF Grugel, RN AF Rabenberg, Ellen Brown, Arthur Kaukler, William F. Grugel, Richard N. TI Evaluation of an ionic liquid-based epoxy after exposure on the MISSE-8 Carrier SO Results in Physics LA English DT Article DE MISSE; ISS; Ionic liquid; Epoxy AB An ionic liquid-based epoxy was evaluated after more than two years of continual nadir space exposure on the MISSE-8 sample rack outside of the International Space Station. In addition to space radiation, atomic oxygen and vacuum space exposure the samples also experienced approximately 12,500 thermal cycles between similar to-40 degrees C and +40 degrees C. The returned samples exhibited no cracking or de-bonding from the aluminum discs to which the epoxy was initially applied; there was a slight change in color, and a miniscule variance in before-and-after weight was measured. Microscopic examination revealed some slight deformities, dimpling, and deposits on the exposed surfaces. These are put into the context of an ongoing effort to develop viable carbon-fiber based composite tanks for, but not inclusively, cryogenic liquid containment. Published by Elsevier B.V. C1 [Rabenberg, Ellen; Brown, Arthur; Grugel, Richard N.] Marshall Space Flight Ctr, Mat & Proc Lab, Huntsville, AL 35812 USA. [Kaukler, William F.] Univ Alabama, Huntsville, AL 35812 USA. RP Grugel, RN (reprint author), Marshall Space Flight Ctr, Mat & Proc Lab, Huntsville, AL 35812 USA. EM richard.n.grugel@nasa.gov OI Kaukler, William/0000-0002-7758-269X NR 3 TC 0 Z9 0 U1 2 U2 2 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS SN 2211-3797 J9 RESULTS PHYS JI Results Phys. PY 2016 VL 6 BP 1185 EP 1187 DI 10.1016/j.rinp.2016.11.010 PG 3 WC Materials Science, Multidisciplinary; Physics, Multidisciplinary SC Materials Science; Physics GA EE7BU UT WOS:000389770300211 ER PT J AU Grugel, RN Hastings, WC Rabenberg, E Kaukler, WF Henry, C AF Grugel, R. N. Hastings, W. C. Rabenberg, E. Kaukler, W. F. Henry, C. TI Evaluation of carbon fiber composites fabricated using ionic liquid based epoxies for cryogenic fluid applications SO Results in Physics LA English DT Article DE Ionic liquid; Carbon fiber; Epoxy; COPV; Cryogenic fluids AB Utilizing tanks fabricated from fiber reinforced polymeric composites for storing cryogenic fluids such as liquid oxygen and liquid hydrogen is of great interest to NASA as considerable weight savings can be gained. Unfortunately such composites, especially at cryogenic temperatures, develop a mismatch that initiates detrimental delamination and crack growth, which promotes leaking. On-going work with ionic liquid-based epoxies appears promising in mitigating these detrimental effects. Some recent results are presented and discussed. Published by Elsevier B.V. C1 [Grugel, R. N.; Hastings, W. C.; Rabenberg, E.; Henry, C.] Marshall Space Flight Ctr, Mat & Proc Lab, Huntsville, AL 35812 USA. [Kaukler, W. F.] Univ Alabama, Huntsville, AL 35649 USA. RP Grugel, RN (reprint author), Marshall Space Flight Ctr, Mat & Proc Lab, Huntsville, AL 35812 USA. EM Richard.n.grugel@nasa.gov OI Kaukler, William/0000-0002-7758-269X NR 3 TC 0 Z9 0 U1 2 U2 2 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS SN 2211-3797 J9 RESULTS PHYS JI Results Phys. PY 2016 VL 6 BP 1188 EP 1189 DI 10.1016/j.rinp.2016.11.011 PG 2 WC Materials Science, Multidisciplinary; Physics, Multidisciplinary SC Materials Science; Physics GA EE7BU UT WOS:000389770300212 ER PT J AU Wang, TS Stewart, ET Canabal, F AF Wang, Ten-See Stewart, Eric T. Canabal, Francisco TI Concept study of a hydrogen containment process during nuclear thermal engine ground testing SO Results in Physics LA English DT Article DE Hydrogen decomposition reactions; Hydrogen recombination reactions; Hydrogen containment process; Nuclear thermal propulsion; Ground testing AB A new hydrogen containment process was proposed for ground testing of a nuclear thermal engine. It utilizes two thermophysical steps to contain the hydrogen exhaust. First, the decomposition of hydrogen through oxygen-rich combustion at higher temperature; second, the recombination of remaining hydrogen with radicals at low temperature. This is achieved with two unit operations: an oxygen-rich burner and a tubular heat exchanger. A computational fluid dynamics methodology was used to analyze the entire process on a three-dimensional domain. The computed flammability at the exit of the heat exchanger was less than the lower flammability limit, confirming the hydrogen containment capability of the proposed process. Published by Elsevier B.V. C1 [Wang, Ten-See; Stewart, Eric T.; Canabal, Francisco] NASA, Marshall Flight Ctr, Engn Directorate, Huntsville, AL 35812 USA. RP Wang, TS (reprint author), NASA, Marshall Flight Ctr, Engn Directorate, Huntsville, AL 35812 USA. EM ten-see.wang-1@nasa.gov NR 4 TC 0 Z9 0 U1 1 U2 1 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS SN 2211-3797 J9 RESULTS PHYS JI Results Phys. PY 2016 VL 6 BP 1190 EP 1191 DI 10.1016/j.rinp.2016.11.019 PG 2 WC Materials Science, Multidisciplinary; Physics, Multidisciplinary SC Materials Science; Physics GA EE7BU UT WOS:000389770300213 ER PT B AU Yoshida, K Wilcox, B Hirzinger, G Lampariello, R AF Yoshida, Kazuya Wilcox, Brian Hirzinger, Gerd Lampariello, Roberto BE Siciliano, B Khatib, O TI Space Robotics SO SPRINGER HANDBOOK OF ROBOTICS LA English DT Article; Book Chapter ID PLANETARY EXPLORATION ROVERS; MOUNTED MANIPULATOR SYSTEMS; RIGID WHEELS; SATELLITE; DYNAMICS; CAPTURE; STATION; MODEL; ORBIT; MARS AB In the space community, any unmanned spacecraft can be called a robotic spacecraft. However, Space Robots are considered to be more capable devices that can facilitate manipulation, assembling, or servicing functions in orbit as assistants to astronauts, or to extend the areas and abilities of exploration on remote planets as surrogates for human explorers. In this chapter, a concise digest of the historical overview and technical advances of two distinct types of space robotic systems, orbital robots and surface robots, is provided. In particular, Sect. 55.1 describes orbital robots, and Sect. 55.2 describes surface robots. In Sect. 55.3, the mathematical modeling of the dynamics and control using reference equations are discussed. Finally, advanced topics for future space exploration missions are addressed in Sect. 55.4. C1 [Yoshida, Kazuya] Tohoku Univ, Dept Aerosp Engn, Aoba 01, Sendai, Miyagi 9808579, Japan. [Wilcox, Brian] CALTECH, Jet Prop Lab, 4800 Oak Ridge Grove Dr, Pasadena, CA 91109 USA. [Hirzinger, Gerd] German Aerosp Ctr DLR, Inst Robot & Mechatron, Munchner Str 20, D-82230 Wessling, Germany. [Lampariello, Roberto] German Aerosp Ctr DLR, Inst Robot & Mechatron, Munchner Str 20, D-82234 Wessling, Germany. RP Yoshida, K (reprint author), Tohoku Univ, Dept Aerosp Engn, Aoba 01, Sendai, Miyagi 9808579, Japan. EM yoshida@astro.mech.tohoku.ac.jp; brian.h.wilcox@jpl.nasa.gov; gerd.hirzinger@dlr.de; roberto.lampariello@dlr.de NR 113 TC 0 Z9 0 U1 1 U2 1 PU SPRINGER-VERLAG BERLIN PI BERLIN PA HEIDELBERGER PLATZ 3, D-14197 BERLIN, GERMANY BN 978-3-319-32552-1; 978-3-319-32550-7 PY 2016 BP 1423 EP 1461 D2 10.1007/978-3-319-32552-1 PG 39 WC Automation & Control Systems; Computer Science, Artificial Intelligence; Robotics SC Automation & Control Systems; Computer Science; Robotics GA BG4HU UT WOS:000388837200067 ER PT S AU Adumitroaie, V Levin, SM Costa, DS Gulkis, S Janssen, MA AF Adumitroaie, Virgil Levin, Steven M. Costa, Daniel Santos Gulkis, Samuel Janssen, Michael A. GP IEEE TI Towards A Fast Background Radiation Subtraction Technique for the Juno Mission SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE ID SYNCHROTRON-RADIATION; JUPITER; BELTS; MAGNETOSPHERE; POLARIZATION; ELECTRONS; EMISSION AB The Juno spacecraft will go into polar orbit after it arrives at Jupiter in 2016. Scientific instruments on Juno will make in situ charged particles and magnetic fields measurements. Remote sensing instruments will measure thermal and non-thermal emissions from the atmosphere and magnetosphere. Gravitational field measurements will be derived using radio tracking signals. The Microwave Radiometer (MWR) Instrument, one of the nine instruments on Juno, has been designed to measure the brightness temperatures of Jupiter at six microwave frequencies, sounding the atmosphere from 0.5 atm to over 100 atm pressure. Synchrotron emission generated by ultra-relativistic electrons trapped in Jupiter's magnetosphere will be detected and measured by the MWR Radiometer over a range of wavelengths from 2 cm to 50 cm. Synchrotron data collected with the MWR Radiometer will be used for two purposes: a) to improve the atmospheric measurements, and b) to provide new constraints on the synchrotron emission itself. The ancillary MWR data analysis requires a fast synchrotron radiation model that can be used in conjunction with the atmospheric retrieval algorithm. This paper describes an extension of the Levin at al. (2001) multi-zonal, multi-parameter model to a spacecraft point of view, along with a few testing and validation cases. C1 [Adumitroaie, Virgil; Levin, Steven M.; Gulkis, Samuel; Janssen, Michael A.] Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Costa, Daniel Santos] Southwest Res Inst, 6220 Culebra Rd, San Antonio, TX 78238 USA. RP Adumitroaie, V (reprint author), Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Virgil.Adumitroaie@jpl.nasa.gov; Steven.M.Levin@jpl.nasa.gov; daniel.santoscosta@swri.org; Samuel.Gulkis@jpl.nasa.gov; Michael.A.Janssen@jpl.nasa.gov NR 31 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 11 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374903084 ER PT S AU Alena, R Collier, P Ahkter, M Wood, B Sinharoy, S Shankar, D AF Alena, Richard Collier, Patrick Ahkter, Mohammad Wood, Barry Sinharoy, Soumik Shankar, Deepak GP IEEE TI High Performance Space VPX Payload Computing Architecture Study SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB This paper describes a functional reference design for a high-performance payload processor that captures images and spectra from multiple high-resolution instruments, processes and integrates multiple real-time data streams to perform feature recognition and spatial transformations providing autonomous navigation and rendezvous capability for future spacecraft and is equally applicable to Unmanned Aerial Systems (UAS). The proposed design uses two new standards: VITA 78 (SpaceVPX) for multi-processor architecture, and RapidIO (RIO) as the interconnect fabric. The SpaceVPX standard specifies physical form factor, logical, and physical interconnect technologies and architectures that can lead to high-performance fault tolerant computing for high-performance payloads. An overview of SpaceVPX and its relationship to OpenVPX is provided as a guide to practical implementations. The proposed design features a general-purpose host processor with GPU and FPGA-based image processing hardware. RIO is used for the instrument and processor interconnects, providing multiple gigabits per second of data communication capability. An overview of RIO features and operation is presented to complement the SpaceVPX architecture. A notional Reference Architecture is proposed for analysis using multiple methods for estimating avionics performance. The study objectives are to characterize throughput, latency and sub-system utilization using conventional system analysis, hardware prototype measurements and modeling and simulation software. We conducted first-order performance studies to identify bottlenecks in memory speed, I/O capacity and processing power. Initial performance analysis was performed on memory throughput rates, producing first-order values used as a performance baseline. A model of the Reference Architecture using VisualSim Architect was created and simulations run, producing insight into the complex interactions occurring between subsystems. Furthermore, the results of a prototype hardware implementation focusing on RIO throughput are presented as additional metrics. The study predicts RIO throughput between key elements of the Reference Architecture and identify major bottlenecks, and improvements needed for meeting mission requirements. The objective of this paper is to provide guidance to avionics designers regarding the adoption of SpaceVPX today and its anticipated evolution in the next few years. C1 [Alena, Richard] NASA, Ames Res Ctr, MS269-4,Rm 195, Moffett Field, CA 94035 USA. [Collier, Patrick] Air Force Res Lab, Space Vehicles Directorate, Albuquerque, NM USA. [Ahkter, Mohammad] Integrated Device Technol Corp, Interface & Connect Div, Ottawa, ON, Canada. [Wood, Barry] Integrated Device Technol Corp, Ottawa, ON, Canada. [Sinharoy, Soumik] Orange Silicon Valley, San Francisco, CA USA. [Shankar, Deepak] Mirabilis Design, Sunnyvale, CA USA. RP Alena, R (reprint author), NASA, Ames Res Ctr, MS269-4,Rm 195, Moffett Field, CA 94035 USA. EM richard.l.alena@nasa.gov; Charles.collier10@us.af.mil; mohammad.akhter@idt.com; soumik.sinharoy@orange.com; Deepak.shankar@mirabilisdesign.com NR 6 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 18 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374901058 ER PT S AU Aronstein, DL Smith, JS AF Aronstein, David L. Smith, J. Scott GP IEEE TI Phase-Retrieval Uncertainty Estimation and Algorithm Comparison for the JWST-ISIM Test Campaign SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE ID DIFFRACTION PLANE PICTURES; IMAGE AB Phase retrieval, the process of determining the exit-pupil wavefront of an optical instrument from image-plane intensity measurements, is the baseline methodology for characterizing the wavefront for the suite of science instruments (SIs) in the Integrated Science Instrument Module (ISIM) for the James Webb Space Telescope (JWST). JWST is a large, infrared space telescope with a 6.5-meter diameter primary mirror. JWST is currently NASA's flagship mission and will be the premier space observatory of the next decade. ISIM contains four optical benches with nine unique instruments, including redundancies. ISIM was characterized at the Goddard Space Flight Center (GSFC) in Greenbelt, MD in a series of cryogenic vacuum tests using a telescope simulator. During these tests, phase-retrieval algorithms were used to characterize the instruments. The objective of this paper is to describe the Monte-Carlo simulations that were used to establish uncertainties (i.e., error bars) for the wavefronts of the various instruments in ISIM. Multiple retrieval algorithms were used in the analysis of ISIM phase-retrieval focus-sweep data, including an iterative-transform algorithm and a nonlinear optimization algorithm. These algorithms emphasize the recovery of numerous optical parameters, including low-order wavefront composition described by Zernike polynomial terms and high-order wavefront described by a point-by-point map, location of instrument best focus, focal ratio, exit-pupil amplitude, the morphology of any extended object, and optical jitter. The secondary objective of this paper is to report on the relative accuracies of these algorithms for the ISIM instrument tests, and a comparison of their computational complexity and their performance on central and graphical processing unit clusters. From a phase-retrieval perspective, the ISIM test campaign includes a variety of source illumination bandwidths, various image-plane sampling criteria above and below the Nyquist-Shannon critical sampling value, various extended object sizes, and several other impactful effects. C1 [Aronstein, David L.; Smith, J. Scott] NASA, Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. RP Aronstein, DL (reprint author), NASA, Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. EM David.L.Aronstein@nsa.gov; J.Scott.Smith@nasa.gov NR 25 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 10 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374903008 ER PT S AU Asmar, S Ao, C Edwards, C Kahan, D Pi, XQ Paik, M Mannucci, A AF Asmar, Sami Ao, Chi Edwards, Charles, Jr. Kahan, Daniel Pi, Xiaoqing Paik, Meegeyong Mannucci, Anthony GP IEEE TI Demonstration of Mars Crosslink Occultation Measurements for Future Small Spacecraft Constellations SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB Future planetary atmospheric profiling via radio occultations (RO) benefits significantly from increased received signal-to-noise ratio as well as geometrical coverage of links between two or more spacecraft in orbit around a target planet. These can be small spacecraft, possibly dedicated to quality radio-metrics with precision clock reference. Motivated by long-term research investigating the optimum SNR for the science performance, the optimum reference clock stability, the number and combination of wavelengths driving the number of transmitters and antennas, the optimum number and orbital spacecraft configuration, and design modifications to existing radio communication systems that would allow these new science objectives on future missions, three crosslink occultation experiments have been acquired between the Mars Odyssey and Mars Reconnaissance Orbiter spacecraft to probe the Martian atmosphere. While crosslink occultations between Earth orbiting satellites have long been used to profile the Earth's atmosphere, this represents the first demonstration of crosslink occultation measurements at another planet. These measurements leverage the proximity link telecommunication payloads on each orbiter, which were designed to provide relay communication and navigation services to Mars landers and rovers. Analysis of the observed Doppler shift on each crosslink measurement reveals a clear signature of the Martian atmosphere, primarily the ionosphere. Inversion of the observed Doppler data yields vertical profiles of the Martian refractivity and electron density. The electron density profiles show the presence of two layers with peak densities and peak heights that are consistent with empirical models. C1 [Asmar, Sami; Ao, Chi; Edwards, Charles, Jr.; Kahan, Daniel; Pi, Xiaoqing; Paik, Meegeyong; Mannucci, Anthony] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Asmar, S (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM sami.asmar@jpl.nasa.gov; chi.ao@jpl.nasa.gov; charles.edwards@jpl.nasa.gov; daniel.kahan@jpl.nasa.gov; xiaoqing.pi@jpl.nasa.gov; meegeyong.paik@jpl.nasa.gov; anthony.mannucci@jpl.nasa.gov NR 5 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 6 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374902045 ER PT S AU Babuscia, A Divsalar, D Cheung, KM Lee, C AF Babuscia, Alessandra Divsalar, Dariush Cheung, Kar-Ming Lee, Charles GP IEEE TI CDMA communication system performance for a constellation of CubeSats around the Moon SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB In this paper a communication system for CubeSats in formation that operate in the vicinity of the Moon is proposed. A CDMA system for the fleet of CubeSats in the vicinity of the moon to communicate with the Earth station is considered. This is an extension of our previous proposed CDMA system for a concept Constellation of CubeSats. In this paper the Doppler effects on CDMA communication system performance for a constellation of CubeSats around the Moon will be investigated. As an example we have estimated the maximum Doppler and Doppler rate profile of a SOLARA/SARA CubeSat scenario. We investigate the Effects of Doppler Shift/Rate on the CDMA system performance as a result of the CubeSat constellation orbiting in a halo orbit around Earth-Moon Lagrange Point L1. A detailed analysis and simulation of system in presence of Doppler frequency and unknown carrier phase will be performed. First we define the CDMA system for uplink and downlink between the vicinity of the Moon and Earth station. Link budgets will be provided both for uplink and downlink. Bandwidth limitations imposed by the spectral standards will be investigated for modulation formats. All system simulations are done using Simulink Matlab platform. For highly efficient nonlinear power amplifiers, we prefer to use a filtered offset QPSK with phase modulation, which is a CCSDS standard for constant envelope signaling. This allows us to use a nonlinear amplifier at CubeSat to operate at saturation point for the highest efficiency. Filtered offset QPSK with phase modulation is much more bandwidth efficient scheme. We demonstrate that this modulation format satisfies the two international spectral standards. For estimated and specified Doppler frequencies and Doppler rates we design frequency-tracking loops to track the Doppler frequency and Doppler rate in the presence of data with filtered offset QPSK with phase modulation. For carrier phase offsets a well-designed tracking loop is derived with specified loop bandwidth for the same modulation format. We use the CCSDS standard LDPC codes for space applications to meet the link budget margins. C1 [Babuscia, Alessandra; Divsalar, Dariush; Cheung, Kar-Ming; Lee, Charles] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Babuscia, A (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM alessandra.babuscia@jpl.nasa.gov; dariush.divsalar@jpl.nasa.gov; kar-ming.cheung@jpl.nasa.gov; charles.lee@jpl.nasa.gov NR 10 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 15 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374902026 ER PT S AU Babuscia, A Sauder, J Thangavelautham, J Choi, T Chandra, A AF Babuscia, Alessandra Sauder, Jonathan Thangavelautham, Jekan Choi, Thomas Chandra, Aman GP IEEE TI Inflatable Antenna for CubeSats: Development of the X-band Prototype SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB CubeSats1 and small satellites have potential to provide means to explore space and to perform science in a more affordable way. As the goals for these spacecraft become more ambitious in space exploration, moving from Low Earth Orbit (LEO) to Geostationary Earth Orbit (GEO) or further, the communication systems currently implemented will need to be improved to support those missions. One of the bottlenecks is the antennas' size, due to the close relation between antenna gain and dimensions. Hence, a possible solution is to develop inflatable antennas which can be packaged efficiently, occupying a small amount of space, and they can provide, once deployed, large dish dimension and correspondent gain. A prototype of a 1 m inflatable antenna for X-Band has been developed in a joint effort between JPL and ASU. This paper will detail the principle challenges in developing the antenna technology focusing on: design, EM analysis, fabrication and tests. C1 [Babuscia, Alessandra; Sauder, Jonathan] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Thangavelautham, Jekan; Chandra, Aman] Arizona State Univ, 781 E Terrace Mall, Tempe, AZ USA. [Choi, Thomas] Georgia Inst Technol, Atlanta, GA 30332 USA. RP Babuscia, A (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Alessandra.Babuscia@jpl.nasa.gov; Jonathan.Sauder@jpl.nasa.gov; jekan@aus.edu; choit@gatech.edu; achand33@asu.edu NR 19 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 10 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374901087 ER PT S AU Backes, P Moreland, S Manohara, H Green, J Grimes-York, J Badescu, M Vieira, P Toda, R Carey, E Peters, G AF Backes, Paul Moreland, Scott Manohara, Harish Green, Jacklyn Grimes-York, Jesse Badescu, Mircea Vieira, Peter Toda, Risaku Carey, Elizabeth Peters, Gregory GP IEEE TI Experimental Results with the BiBlade Sampling Chain for Comet Surface Sampling SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE ID STRENGTH AB The BiBlade sampling chain has been developed for use in a potential Comet Surface Sample Return mission in a touch-and-go mission architecture. This paper describes the BiBlade sampling chain, an implementation of the system and experimental results. The system includes a BiBlade sampling tool, a robotic arm, a sample measurement system, a sample transfer system, and simulants. C1 [Backes, Paul; Moreland, Scott; Manohara, Harish; Green, Jacklyn; Grimes-York, Jesse; Badescu, Mircea; Vieira, Peter; Toda, Risaku; Carey, Elizabeth; Peters, Gregory] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Backes, P (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Paul.G.Backes@jpl.nasa.gov NR 19 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 10 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374904011 ER PT S AU Bairstow, B Lee, Y Smythe, W Zakrajsek, J AF Bairstow, Brian Lee, Young Smythe, William Zakrajsek, June GP IEEE TI Science Instrument Sensitivities to Radioisotope Power System Environment SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB Radioisotope Power Systems (RPS) have been and will be enabling or significantly enhancing for many missions, including several concepts identified in the 2011 Planetary Science Decadal Survey. Some mission planners and science investigators might have concerns about possible impacts from RPS-induced conditions upon the scientific capabilities of their mission concepts. To alleviate these concerns, this paper looks at existing and potential future RPS designs, and examines their potential radiation, thermal, vibration, electromagnetic interference (EMI), and magnetic fields impacts on representative science instruments and science measurements. Radiation impacts from RPS on science instruments are of potential concern for instruments with optical detectors and instruments with high-voltage electronics. The two main areas of concern are noise effects on the instrument measurements, and long-term effects of instrument damage. While RPS by their nature will contribute to total radiation dose, their addition for most missions should be relatively small. For example, the gamma dose rate from one Multi-Mission Radioisotope Thermoelectric Generator (MMRTG) would be an order of magnitude lower than the environmental dose rate at Mars, and would have a correspondingly lower contribution to instrument noise and to any permanent damage to payload sensors. Increasing the number of General Purpose Heat Source (GPHS) modules used in an RPS would be expected to increase the generated radiation proportionally; however, the effect of more GPHS modules is mitigated from a strictly linear relationship by self-shielding effects. The radiation field of an RPS is anisotropic due to the deviation of the modules from a point-source-geometry. For particularly sensitive instruments, the total radiation dose could be mitigated with separation or application of spot shielding. Though a new, higher-power RPS could generate more heat per unit than current designs, thermal impact to the flight system could be mitigated with shading and pointing if required by the mission. Alternatively, excess heat could prove beneficial in providing needed heat to spacecraft components and instruments in some thermal environments. Vibration for a new higher-power Stirling Radioisotope Generator (SRG) would be expected to be similar to the recent Advanced Stirling Radioisotope Generator (ASRG) design. While vibration should be low, it must be considered and addressed during spacecraft and instrument design. EMI and magnetic fields for new RPS concepts are expected to be low as for the current RPS, but must be considered and addressed if the mission includes sensitive instruments such as magnetometers. The assessment conducted for this paper focused on orbiter instrument payloads for two representative mission concepts- Titan Saturn System Mission (TSSM) and a Uranus Orbiter and Probe (UOP)-since both of these Decadal Survey concepts would include many diverse instruments on board. This paper describes how the potential impacts of the RPS on science instruments and measurements were assessed and which impacts were addressed. Then, this paper suggests mitigation strategies against those impacts, and provides an overview of several topics that would benefit from further work. C1 [Bairstow, Brian; Lee, Young; Smythe, William] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Zakrajsek, June] Glenn Res Ctr, 21000 Brookpark Rd, Cleveland, OH 44135 USA. RP Bairstow, B (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM brian.k.bairstow@jpl.nasa.gov; young.h.lee@jpl.nasa.gov; william.d.smythe@jpl.nasa.gov; june.f.zakrajsek@nasa.gov NR 13 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 13 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374902042 ER PT S AU Baldwin, I Kenig, S Nicholas, A Parrish, J Anderson, R Nesnas, I AF Baldwin, Ian Kenig, Sivan Nicholas, Austin Parrish, Joe Anderson, Robert Nesnas, Issa GP IEEE TI Extreme science: Exploring the use of extreme-terrain rovers in Mars Sample Return SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB The NASA Mars Exploration Program is developing mission concepts for the capture and return of diverse geological and atmospheric samples from Mars to Earth. The first phase of a hypothetical multi-year sample-return campaign is the collection and caching of the samples; the second phase would center on the retrieval of the cached samples and launch of the cache into Mars' orbit, with the third phase being responsible for the capture of the orbiting sample(s) and their return to Earth. The second phase is known as the Sample Retrieval and Launch (SRL) concept, which would require a dedicated rover to retrieve the previously-cached samples for launch into Martian orbit, and subsequent return to Earth. Our contribution assesses the feasibility of conducting an extreme-terrain exploration mission in the extended-phase, following the launch of the cache into orbit. Our study leverages prior development of the MobileMAV concept, which uses Mars Science Laboratory (MSL)-based mobility to carry the Mars Ascent Vehicle (MAV)[1]. Our proposal is driven by the scientific value of exploring various challenging topographies such as recurring slope lineae (RSLs), craters, fissures, canyons, gullies, caves, and stratified terrain. These geologic features are expected to contain a wealth of scientific information that would greatly advance scientific understanding of dynamic processes in the Martian environment. The ability to operate on (and in) these challenging areas (and their environs) would also aid in the search for habitable environments, and significantly shorten the path to human-driven Martian exploration. The core contribution is an investigation of a trade space that would integrate a two-wheel, tethered rappelling rover (based on the Axel extreme-terrain rover [2]) into the mobileMAV concept, capturing the key benefits and risks to the overall mission. Although introducing new rover designs reduces our ability to leverage flight-tested heritage hardware, the possibility of dramatically extending the science capabilities-while simultaneously achieving the primary mission goal of delivering the MAV to the launch site-would be compelling. We present a conceptual design that is, to first-order, compatible with the existing MSL launch, cruise, and entry, descent and landing (EDL) baseline. We require minimal changes to the existing architecture to accommodate the rover and MAV payload. Although some challenges exist with respect to flown weight (greater than MSL) and available avionics payload (smaller than MSL), the required technological advances appear well within the projected arc of technology development, given the proposed mission concept timeline. C1 [Baldwin, Ian; Kenig, Sivan; Nicholas, Austin; Parrish, Joe; Anderson, Robert; Nesnas, Issa] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Baldwin, I (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Ian.Baldwin@jpl.nasa.gov; Sivan.J.Kenig@jpl.nasa.gov; Austin.K.Nicholas@jpl.nasa.gov; Joseph.C.Parrish@jpl.nasa.gov; Robert.C.Anderson@jpl.nasa.gov; Issa.A.Nesnas@jpl.nasa.gov NR 10 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 11 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374903058 ER PT S AU Bienstock, B Beauchamp, P Venkatapathy, E Munk, M AF Bienstock, Bernie Beauchamp, Patricia Venkatapathy, Ethiraj Munk, Michelle GP IEEE TI IPPW: A Yearly Forum for Presentation of Planetary Entry Missions SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB For the past 13 years, we have conducted the International Planetary Probe Workshop (IPPW) at venues in the United States and Europe. Our yearly meetings are attended by engineers, technologists, scientists, mission designers, space agency leaders, and students from around the world. We review the state-of-the-art in science, mission design, engineering implementation and technologies for the in situ robotic exploration of Solar System bodies. We feature discussions on innovative methodologies and techniques for upcoming probe and surface science missions. Student participation in our workshops is emphasized by the scholarships we offer to attract early career scientists and engineers to the field of entry, descent and flight in planetary atmospheres, as well as surface science exploration of other worlds. Through their interaction with professionals, we enable students to learn from experienced researchers and practitioners. During the weekend preceding the week-long workshop, we conduct a Short Course taught by community leaders, on topics pertinent to planetary probes. Examples of past courses include Extreme Environments Technologies, Probe Science Instrument Technologies, and Planetary Protection. Beginning with our 11th workshop in 2014, we have published a summary of the findings during the various sessions. The reports, as well as the materials from all workshops, are available on our public archive, and distributed to the world's national space agencies to serve as a basis for future international collaborations. Our presentation will review the history of the yearly IPPWs as well as the findings of IPPW-11 and IPPW-12, as documented in their Science and Technology Progress Reports on Planetary Probes. C1 [Bienstock, Bernie; Beauchamp, Patricia] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Venkatapathy, Ethiraj] NASA, Ames Res Ctr, Naval Air Stn, Mountain View, CA 94035 USA. [Munk, Michelle] NASA, Langley Res Ctr, 11 Langley Blvd, Hampton, VA 23681 USA. RP Bienstock, B (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Bernie.Bienstock@jpl.nasa.gov; Patricia.M.Beauchamp@jpl.nasa.gov; Ethiraj.Venkatapathy-1@nasa.gov; Michelle.M.Munk@nasa.gov NR 0 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 10 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374902075 ER PT S AU Boslough, M Chodas, P Ezzedine, S Jennings, B Fogleman, B AF Boslough, Mark Chodas, Paul Ezzedine, Souheil Jennings, Barbara Fogleman, Bill GP IEEE TI Physical and Infrastructure Modeling for the 2015 PDC Asteroid Threat Exercise SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE ID DIRECTIONAL TENSILE FAILURE; ELASTIC-VISCOPLASTIC MODEL; IMPACT AB The 2015 Planetary Defense Conference (2015 PDC) was held in Frascati, Italy on April 13-17 by the International Academy of Astronautics (IAA). In addition to customary technical sessions, we performed the first week-long threat exercise designed to simulate and examine the process of decision making that would accompany the discovery and response to an asteroid on a collision course with Earth. Our role in the exercise was to develop and present a plausible scenario that would be of interest to as many participants as possible while considering the broad diversity in technical expertise, approach, values, missions, and national affiliations of the conference attendees. Moreover, we strove to present a reasonable sequence of events spanning several years that would provide many opportunities for collective decision making under uncertainty by parties likely to have conflicting interests. In order to hold the attention of the participants throughout the week we tried to create a scenario that would be as dramatic as possible-including "cliffhangers" and unexpected turns of events-but without sacrificing realism. This allowed us to discuss a wide range of potential responses, including kinetic and nuclear deflection, and potential outcomes, including tsunami-forming ocean impacts, crater-forming land impacts, and airbursts by objects over a large size range. In addition to creating the scenario, members of our team served on an expert panel in a role-playing exercise that included participants acting as world leaders of nations, both directly and indirectly affected members of the public in atrisk areas, and the media. This paper summarizes the exercise, focusing on physical and infrastructure modeling. The exercise spanned the entire week, with daily "injects" (or updates) of new observed data about what was currently known on the imaginary date. We presented models of potential physical effects and resulting infrastructure damage, with emphasis on the uncertainties. Seven updates spanned most of the time between when the asteroid (dubbed "2015 PDC") was discovered on April 13, 2015, and its impact date of September 3, 2022. Information about the orbit and technical response options were presented as a set of faux press releases that were made available to participants prior to each briefing. The scenario was based on an actual calculated orbit to provide as much realism as possible. The physical effects at each stage were predicted by using simulations for airburst and tsunami generation, and a shallow water model for tsunami propagation. Maps were generated using tools developed for the National Infrastructure Simulation and Analysis Center (NISAC), and were presented by expert panelists as part of a mock press briefing at each inject. We present the contents of those press briefings and put them into context with the threat exercise. C1 [Boslough, Mark; Jennings, Barbara] Sandia Natl Labs, POB 5800, Albuquerque, NM 87185 USA. [Chodas, Paul] Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Ezzedine, Souheil] Lawrence Livermore Natl Lab, POB 808, Livermore, CA 94551 USA. [Fogleman, Bill] GRIT Inc, 8817 James Ave NE, Albuquerque, NM 87111 USA. RP Boslough, M (reprint author), Sandia Natl Labs, POB 5800, Albuquerque, NM 87185 USA. EM mbboslo@sandia.gov; paul.w.chodas@jpl.nasa.gov; ezzedine1@llnl.gov; bjjenni@sandia.gov; wefogle@grit.us NR 22 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 18 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374900035 ER PT S AU Brandeau, E Clark, I Ginn, J Tanner, C AF Brandeau, Erich Clark, Ian Ginn, Jason Tanner, Christopher GP IEEE TI Ballutes for Supersonic Deceleration at Mars SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB Mars landers are mass limited by the available entry, descent, and landing technology. The Mars Science Laboratory rover pushed the boundaries of EDL technology to land 900 kg of rover at an elevation of -4.5 km MOLA (Mars Orbiter Laser Altimeter) on Mars. A ballute, a portmanteau of parachute and balloon, is a ram-air pressurized isotensoid trailing aerodynamic drag device. Unlike a parachute, the ballute can be deployed and is stable at higher Mach numbers because of the closed quasi-rigid structure. The NASA Low Density Supersonic Decelerators project developed a 4.4 meter diameter isotensoid ballute and successfully deployed it at Mach 2.8 at the top of the Earth's stratosphere and used it as a pilot device for a main parachute. The design and performance of that ballute is discussed, as well as possible infusion into a future Mars landing mission. The advantages of a ballute as a parachute deployment device are discussed, as well as the capability of ballutes as primary supersonic aerodynamic decelerators. Potential Mars Sample Return-class mission concepts can realize mass savings by using a ballute, rather than an attached Supersonic Inflatable Aerodynamic Decelerator (SIAD), in combination with a parachute. Future entry vehicles with high ballistic coefficients can utilize ballutes as the sole supersonic aerodynamic decelerator to realize retropropellant savings. A ballute mass model was developed to assess the limit of scaling. A number of technology developments still remain for future users of ballutes for Mars missions. C1 [Brandeau, Erich; Clark, Ian; Ginn, Jason; Tanner, Christopher] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Brandeau, E (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM erich@jpl.nasa.gov; Ian.G.Clark@jpl.nasa.gov; Jason.M.Ginn@jpl.nasa.gov; Christopher.L.Tanner@jpl.nasa.gov NR 22 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 14 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374903012 ER PT S AU Brooks, S Godart, P Backes, P Chamberlain-Simon, B Smith, R Karumanchi, S AF Brooks, Sawyer Godart, Peter Backes, Paul Chamberlain-Simon, Brendan Smith, Russell Karumanchi, Sisir GP IEEE TI An Untethered Mobile Limb for Modular In-Space Assembly SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB In-space assembly can enable new types of spacecraft and structures which are too large or fragile to be carried on a rocket in an assembled form, and robotic systems can make in-space assembly feasible and cost-effective. Such systems should be able to assemble large and complex structures while imposing minimal launch mass and mission risk. We propose an autonomous robotic limb, henceforth referred to as "Limbi," which is self-mobile and symmetric. Two identical electromechanical docking mechanisms serve as end-effectors. With either end-effector anchored to a base structure, the other can grab modular elements and attach them to the growing structure. Power and computing are provided by the spacecraft through these docks, enabling Limbi to walk end-over-end across the structure without a battery or tether. We have constructed and tested a prototype system in a planar workspace that demonstrates the mobility and assembly capabilities of the proposed limb. We also introduce the concept of "Limboids," consisting of multiple Limbi robots temporarily attached to each other to form more complex kinematic chains. The resulting configurations are application-specific and can be tailored to the degrees of freedom, range of motion, and general dexterity required by a particular task. Because Limbi and Limboids can assemble large and complex structures with minimal robotic complexity, the development of this class of robots is a critical step forward in low-risk and lightweight assembly. C1 [Brooks, Sawyer; Godart, Peter; Backes, Paul; Chamberlain-Simon, Brendan; Smith, Russell; Karumanchi, Sisir] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Brooks, S (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Sawyer.Brooks@jpl.nasa.gov NR 5 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 9 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374903100 ER PT S AU Bussey, B Hoffman, SJ AF Bussey, Ben Hoffman, Stephen J. GP IEEE TI Human Mars Landing Site and Impacts on Mars Surface Operations SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB This paper describes NASA's initial steps for identifying and evaluating candidate Exploration Zones (EZs) and Regions of Interests (ROIs) for the first human crews that will explore the surface of Mars. NASA's current effort to define the exploration of this planet by human crews, known as the Evolvable Mars Campaign (EMC), provides the context in which these EZs and ROIs are being considered. The EMC spans all aspects of a human Mars mission including launch from Earth, transit to and from Mars, and operations on the surface of Mars. An EZ is a collection of ROIs located within approximately 100 kilometers of a centralized landing site. ROIs are areas relevant for scientific investigation and/or development/maturation of capabilities and resources necessary for a sustainable human presence. The EZ also contains one or more landing sites and a habitation site that will be used by multiple human crews during missions to explore and utilize the ROIs within the EZ. With the EMC as a conceptual basis, the EZ model has been refined to a point where specific site selection criteria for scientific exploration and in situ resource utilization can be defined. In 2015 these criteria were distributed to the planetary sciences community and the in situ resource utilization and civil engineering communities as part of a call for EZ proposals. The resulting "First Landing Site/Exploration Zone Workshop for Human Missions to the Surface of Mars" was held in October 2015 during which 47 proposals for EZs and ROIs were presented and discussed. Proposed locations spanned all longitudes and all allowable latitudes (+/- 50 degrees). Proposed justification for selecting one of these EZs also spanned a significant portion of the scientific and resource criteria provided to the community. Several important findings resulted from this Workshop including: (a) a strong consensus that, at a scale of 100 km (radius), multiple places on Mars exist that have both sufficient scientific interest to sustain multiple crews of exploring astronauts, AND potential resource deposits for ISRU indicating the current EZ definition is viable and should be retained for now, (b) new data types (needed for more definitive analysis of EZs) argued strongly for a new orbiter mission, and possibly one or more surface missions, to obtain these data, (c) a general consensus that this Workshop was an excellent start to identifying a place where future human missions to Mars can productively explore this planet and learn to live and work there for the long term. Building on these findings, HEOMD and SMD are: (a) refining the EZ selection criteria and overall selection process to improve on lessons learned from the first EZ workshop, (b) using these proposed locations to develop "reference EZs" for assessment purposes (primarily engineering assessments), (c) gathering data and conducting analyses to better understanding the different potential sources for water, including the ease of extraction and purification, and (d) assessing trends in additional data that are needed to better characterize EZs proposed at the workshop and how these data needs impact the design and operation of future robotic Mars missions. C1 [Bussey, Ben] NASA HQ, 7R76,300 E St SW, Washington, DC 20546 USA. [Hoffman, Stephen J.] Sci Applicat Int Corp, 2450 NASA Pkwy, Houston, TX 77058 USA. RP Bussey, B (reprint author), NASA HQ, 7R76,300 E St SW, Washington, DC 20546 USA. EM david.b.bussey@nasa.gov; stephen.j.hoffman@nasa.gov NR 8 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 21 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374902091 ER PT S AU Carr, GA Iannello, CJ Hunter, DJ Lauenstein, JM Ikpe, SA Ludwig, LL Stell, C Vo, T Del Castillo, L Weber, C Mojarradi, MM Orellana, S Chen, Y AF Carr, Gregory A. Iannello, Christopher J. Hunter, Don J. Lauenstein, Jean-Marie Ikpe, Stanley A. Ludwig, Lawrence L. Stell, Christopher Tuan Vo Del Castillo, Linda Weber, Carissa Mojarradi, Mohammad M. Orellana, Sonny Chen, Yuan GP IEEE TI High Temperature Boost (HTB) Anode Power Supply for a Modular and Scalable Power Processing Unit SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB A concept of a modular and scalable 10kW to 80kW High Temperature Boost (HTB) Power Processing Unit (PPU) capable of operating at temperatures beyond the standard military temperature range was proposed for solar electric in-space propulsion. Within the PPU, the Anode Power Supply (APS) module is a 10kW modular power stage and is the key to the HTB PPU. This paper is to present the design, development, fabrication, testing and thermal demonstration of the 10kW HTB APS. The system architecture and the paradigm shift of the HTB PPU is also to be described. In addition, the extreme environments electronic and packaging technologies are addressed as the fundamental technology path. The HTB PPU is intended for power processing in the area of space solar electric propulsion, where reduction of in-space mass and volume are desired, and sometimes even critical, to achieve the goals of future space flight missions. The concept of the HTB PPU can also be applied to other extreme environment applications, such as geothermal and petroleum deep-well drilling, where higher temperature operation is required. C1 [Carr, Gregory A.; Hunter, Don J.; Stell, Christopher; Tuan Vo; Del Castillo, Linda; Weber, Carissa; Mojarradi, Mohammad M.; Orellana, Sonny] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Iannello, Christopher J.; Ludwig, Lawrence L.] NASA, Kennedy Space Ctr, Cocoa Beach, FL 32899 USA. [Lauenstein, Jean-Marie] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Ikpe, Stanley A.; Chen, Yuan] NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Carr, GA (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 4 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 6 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374904008 ER PT S AU Cates, G Stromgren, C Mattfeld, B Cirillo, W Goodliff, K AF Cates, Grant Stromgren, Chel Mattfeld, Bryan Cirillo, William Goodliff, Kandyce GP IEEE TI The Exploration of Mars Launch & Assembly Simulation SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB Advancing human exploration of space beyond Low Earth Orbit, and ultimately to Mars, is of great interest to NASA, other organizations, and space exploration advocates. Various strategies for getting to Mars have been proposed. These include NASA's Design Reference Architecture 5.0, a near-term flyby of Mars advocated by the group Inspiration Mars, and potential options developed for NASA's Evolvable Mars Campaign. Regardless of which approach is used to get to Mars, they all share a need to visualize and analyze their proposed campaign and evaluate the feasibility of the launch and on-orbit assembly segment of the campaign. The launch and assembly segment starts with flight hardware manufacturing and ends with final departure of a Mars Transfer Vehicle (MTV), or set of MTVs, from an assembly orbit near Earth. This paper describes a discrete event simulation based strategic visualization and analysis tool that can be used to evaluate the launch campaign reliability of any proposed strategy for exploration beyond low Earth orbit. The input to the simulation can be any manifest of multiple launches and their associated transit operations between Earth and the exploration destinations, including Earth orbit, lunar orbit, asteroids, moons of Mars, and ultimately Mars. The simulation output includes expected launch dates and ascent outcomes i.e., success or failure. Running 1,000 replications of the simulation provides the capability to perform launch campaign reliability analysis to determine the probability that all launches occur in a timely manner to support departure opportunities and to deliver their payloads to the intended orbit. This allows for quantitative comparisons between alternative scenarios, as well as the capability to analyze options for improving launch campaign reliability. Results are presented for representative strategies. C1 [Cates, Grant] Aerosp Corp, 15835 Phillips Pkwy, Eastern Range, FL 32925 USA. [Stromgren, Chel; Mattfeld, Bryan] Binera Inc, 912 Thayer Ave,Suite 209, Silver Spring, MD 20910 USA. [Cirillo, William; Goodliff, Kandyce] NASA, Langley Res Ctr, 1 North Dryden St, Hampton, VA 23681 USA. RP Cates, G (reprint author), Aerosp Corp, 15835 Phillips Pkwy, Eastern Range, FL 32925 USA. EM grant.r.cates@aero.org; c.stromgren@binera.com; b.mattfeld@binera.com; william.m.cirillo@nasa.gov; kandyce.e.goodliff@nasa.gov NR 13 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 12 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374902082 ER PT S AU Chappell, SP Beaton, KH Miller, MJ Graff, TG Abercromby, AFJ Gernhardt, ML Halcon, C AF Chappell, Steven P. Beaton, Kara H. Miller, Matthew J. Graff, Trevor G. Abercromby, Andrew F. J. Gernhardt, Michael L. Halcon, Christopher GP IEEE TI NEEMO 18-20: Analog Testing for Mitigation of Communication Latency during Human Space Exploration SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB NASA Extreme Environment Mission Operations (NEEMO) is an underwater spaceflight analog that allows a true mission-like operational environment and uses buoyancy effects and added weight to simulate different gravity levels. Three missions were undertaken from 2014-2015, NEEMO 18-20. All missions were performed at the Florida International University's Aquarius Reef Base, an undersea research habitat. During each mission, the effects of communication latencies on operations concepts, timelines, and tasks were studied. METHODS: Twelve subjects (4 per mission) were weighed out to simulate near-zero or partial gravity extravehicular activity (EVA) and evaluated different operations concepts for integration and management of a simulated Earth-based science team (ST) to provide input and direction during exploration activities. Exploration traverses were preplanned based on precursor data. Subjects completed science-related tasks including presampling surveys, geologic-based sampling, and marine-based sampling as a portion of their tasks on saturation dives up to 4 hours in duration that were designed to simulate EVA on Mars or the moons of Mars. One-way communication latencies, 5 and 10 minutes between space and mission control, were simulated throughout the missions. Objective data included task completion times, total EVA times, crew idle time, translation time, ST assimilation time (defined as time available for ST to discuss data/imagery after data acquisition). Subjective data included acceptability, simulation quality, capability assessment ratings, and comments. RESULTS : Precursor data can be used effectively to plan and execute exploration traverse EVAs (plans included detailed location of science sites, high-fidelity imagery of the sites, and directions to landmarks of interest within a site). Operations concepts that allow for presampling surveys enable efficient traverse execution and meaningful Mission Control Center (MCC) interaction across communication latencies and can be done with minimal crew idle time. Imagery and contextual information from the EVA crew that is transmitted real-time to the intravehicular activity (IVA) crewmember(s) can be used to verify that exploration traverse plans are being executed correctly. That same data can be effectively used by MCC (across comm latency) to provide meaningful feedback and instruction to the crew regarding sampling priorities, additional tasks, and changes to the EVA timeline. Text / data capabilities are preferred over voice capabilities between MCC and IVA when executing exploration traverse plans over communication latency. C1 [Chappell, Steven P.; Beaton, Kara H.] Wyle Sci Technol & Engn Grp, Wyle HAC 37C,1290 Hercules Dr, Houston, TX 77058 USA. [Miller, Matthew J.] Georgia Inst Technol, 270 Ferst Dr,Room 416, Atlanta, GA 30332 USA. [Graff, Trevor G.] Jacobs Engn Grp, Dept Sci, 2224 Bay Area Blvd, Houston, TX 77058 USA. [Abercromby, Andrew F. J.; Gernhardt, Michael L.] NASA, 2101 NASA Pkwy, Houston, TX 77058 USA. [Halcon, Christopher] US Navy, Washington, DC USA. RP Chappell, SP (reprint author), Wyle Sci Technol & Engn Grp, Wyle HAC 37C,1290 Hercules Dr, Houston, TX 77058 USA. EM steven.p.chappell@nasa.gov; kara.h.beaton@nasa.gov; mmiller@gatech.edu; trevor.g.graff@nasa.gov; andrew.abercromby@nasa.gov; michael.l.gernhardt@nasa.gov; Chalcon08@gmail.com NR 16 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 12 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374902033 ER PT S AU Cheatwood, FM Swanson, GT Johnson, RK Hughes, S Calomino, A Gilles, B Anderson, P Bond, B AF Cheatwood, F. McNeil Swanson, Gregory T. Johnson, R. Keith Hughes, Stephen Calomino, Anthony Gilles, Brian Anderson, Paul Bond, Bruce GP IEEE TI Manufacturing Challenges and Benefits when Scaling the HIAD Stacked-Torus Aeroshell to a 15m-Class System SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB Over a decade of work has been conducted in the development of NASA's Hypersonic Inflatable Aerodynamic Decelerator (HIAD) deployable aeroshell technology. This effort has included multiple ground test campaigns and flight tests culminating in the HIAD project's second generation (Gen-2) aeroshell system. The HIAD project team has developed, fabricated, and tested stacked-torus inflatable structures (IS) with flexible thermal protection systems (F-TPS) ranging in diameters from 3-6m, with cone angles of 60 and 70 deg. To meet NASA and commercial near term objectives, the HIAD team must scale the current technology up to 12-15m in diameter. Therefore, the HIAD project's experience in scaling the technology has reached a critical juncture. Growing from a 6m to a 15m-class system will introduce many new structural and logistical challenges to an already complicated manufacturing process. Although the general architecture and key aspects of the HIAD design scale well to larger vehicles, details of the technology will need to be reevaluated and possibly redesigned for use in a 15m-class HIAD system. These include: layout and size of the structural webbing that transfers load throughout the IS, inflatable gas barrier design, torus diameter and braid construction, internal pressure and inflation line routing, adhesives used for coating and bonding, and F-TPS gore design and seam fabrication. The logistics of fabricating and testing the IS and the F-TPS also become more challenging with increased scale. Compared to the 6m aeroshell (the largest HIAD built to date), a 12m aeroshell has four times the cross-sectional area, and a 15m one has over six times the area. This means that fabrication and test procedures will need to be reexamined to account for the sheer size and weight of the aeroshell components. This will affect a variety of steps in the manufacturing process, such as: stacking the tori during assembly, stitching the structural webbing, initial inflation of tori, and stitching of F-TPS gores. Additionally, new approaches and hardware will be required for handling and ground testing of both individual tori and the fully assembled HIADs. There are also noteworthy benefits of scaling up the HIAD aeroshell to a 15m-class system. Two complications in working with handmade textile structures are the non-linearity of the material components and the role of human accuracy during fabrication. Larger, more capable, HIAD structures should see much larger operational loads, potentially bringing the structural response of the material components out of the non-linear regime and into the preferred linear response range. Also, making the reasonable assumption that the magnitude of fabrication accuracy remains constant as the structures grow, the relative effect of fabrication errors should decrease as a percentage of the textile component size. Combined, these two effects improve the predictive capability and the uniformity of the structural response for a 12-15m HIAD. In this paper, the challenges and associated mitigation plans related to scaling up the HIAD stacked-torus aeroshell to a 15m-class system will be discussed. In addition, the benefits of enlarging the structure will be further explored. C1 [Cheatwood, F. McNeil; Johnson, R. Keith; Hughes, Stephen; Calomino, Anthony] NASA, Langley Res Ctr, Hampton, VA 23681 USA. [Swanson, Gregory T.] NASA, AMA Inc, Ames Res Ctr, Moffett Field, CA 94035 USA. [Gilles, Brian; Anderson, Paul] Airborne Syst, Lake Elsinore, CA 92530 USA. [Bond, Bruce] Jackson Bond Enterprises, Dover, NH 03820 USA. RP Cheatwood, FM (reprint author), NASA, Langley Res Ctr, Hampton, VA 23681 USA. EM F.M.Cheatwood@nasa.gov; Gregory.T.Swanson@nasa.gov; R.K.Johnson@nasa.gov; Stephen.J.Hughes@nasa.gov; Anthony.M.Calomino@nasa.gov; Brian.Gilles@airborne-sys.com; Paul.Anderson@airborne-sys.com; Bruce.Bond@jacksonbondllc.com NR 6 TC 0 Z9 0 U1 2 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 12 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374902089 ER PT S AU Chen, N Lin, Y Jackson, D Chung, S AF Chen, Nicole Lin, Ying Jackson, David Chung, Shirley GP IEEE TI Particulate Removal Using a CO2 Composite Spray Cleaning System SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB The Planetary Protection surface cleanliness requirements for potential Mars Sample Return hardware that would come in contact with Martian samples may be stricter than previous missions. The Jet Propulsion Laboratory has developed a new technology that will enable the removal of sub-micron size particles from critical hardware surfaces. A hand-held CO2 composite cleaning system was tested to verify its cleaning capabilities. This convenient, portable device can be used in cleanrooms for cleaning after rework or during spacecraft integration and assembly. It is environmentally safe and easy to use. This cleaning concept has the potential to be further developed into a robotic cleaning device on a Mars Lander to be used to clean sample acquisition or sample handling devices in situ. Contaminants of known sizes and concentrations, such as fluorescent microspheres and spores were deposited on common spacecraft material surfaces. The cleaning efficiency results will be presented and discussed. C1 [Chen, Nicole; Lin, Ying; Chung, Shirley] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Jackson, David] Clean Imagineering LLC, 26074 Ave Hall Unit 6, Santa Clarita, CA 91355 USA. RP Chen, N (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Nicole.C.Chen@jpl.nasa.gov; Ying.Lin@jpl.nasa.gov; David.jackson@cleanlogix.com; Shirley.Y.Chung@jpl.nasa.gov NR 18 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 13 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374903049 ER PT S AU Chesley, SR Veres, P AF Chesley, Steven R. Veres, Peter GP IEEE TI The Large Synoptic Survey Telescope: Projected Near-Earth Object Discovery Performance SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE ID PROCESSING SYSTEM AB The Large Synoptic Survey Telescope (LSST) is a large-aperture, wide-field survey that has the potential to detect millions of asteroids. LSST is under construction with survey operations slated to begin in 2022. We describe an independent study to assess the performance of LSST for detecting and cataloging near-Earth objects (NEOs). A significant component of the study will be to assess the survey's ability to link observations of a single object from among the large numbers of false detections and detections of other objects. We also will explore the survey's basic performance in terms of fraction of NEOs discovered and cataloged, both for the planned baseline survey, but also for enhanced surveys that are more carefully tuned for NEO search, generally at the expense of other science drivers. Preliminary results indicate that with successful linkage under the current baseline survey LSST would discover similar to 60% of NEOs with absolute magnitude H < 22, which corresponds approximately to 140m diameter. C1 [Chesley, Steven R.; Veres, Peter] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Chesley, SR (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM steve.chesley@jpl.nasa.gov; peter.veres@jpl.nasa.gov NR 7 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 8 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374900043 ER PT S AU Cheung, KM Choi, T AF Cheung, Kar-Ming Choi, Thomas GP IEEE TI Statistical ARQ Link Analysis and Planning for Dynamic Links SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB In [1] and [2], we discussed automatic Repeatre-Quest (ARQ) link analysis and planning in terms of effective data rate, effective throughput, latency, and frame-error-rate (FER), under the standard assumption that the signal-to-noise ratio (SNR) remains the same throughout the ARQ communication session. In [3], we argued that the concept of constant SNR might not be valid when considering events over a long time horizon, as many link parameters are inherently statistical. This is particularly true for long-haul ARQ links because the channel SNR changes during subsequent retransmissions of un-received or non-decodable frames. As shown in [3], this inaccurate assumption of constant SNR might be non-consequential for static links such as S-band and X-band, but can lead to large discrepancies in the analysis and planning of the more dynamic communication links such as Ka-band and optical communication frequencies. In this paper, using similar techniques developed in [3], we incorporate the effect of changing SNR, or link uncertainty, into the analysis of ARQ links. SNR is no longer considered as a fixed value, but a random variable whose long-term statistics can be characterized with a probability distribution function. We consider two limiting cases: 1. "Fast-varying" SNR: when SNRs in subsequent retransmissions of a code-block can assume different values, and they are independent. One example is the deep space link when the ARQ acknowledgement time is much larger than the coherency time of the channel. For communications between Earth's ground stations and spacecraft at Mars, the round trip light time is 20-40 minutes, and this is much more than the typical atmospheric coherency time of Ka-band. 2. "Slow-varying" SNR: when SNR values in subsequent retransmissions of a code-block remain the same. One example is the proximity link between a low-Mars-orbit orbiter and a surface asset at Mars. In this case, the ARQ acknowledgement time is of the order of milliseconds and we can assume identical channel environment in subsequent re-transmissions. We expect the ARQ behavior of real-world dynamic channels would fall in between the "fast-varying" and "slow-varying" cases, thus providing interesting insights on the ARQ data return performance and latency performance. We illustrate the aforementioned analysis using the NASA (1024, 1/2) low-density-parity check (LDPC) code. C1 [Cheung, Kar-Ming; Choi, Thomas] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Cheung, KM (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Kar-Ming.Cheung@jpl.nasa.gov; thomaschoi92@gmail.com NR 13 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 8 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374900051 ER PT S AU Clare, L Miles, G AF Clare, Loren Miles, Gregory GP IEEE TI Deep Space Optical Link ARQ Performance Analysis SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB Substantial advancements have been made toward the use of optical communications for deep space exploration missions, promising a much higher volume of data to be communicated in comparison with present-day Radio Frequency (RF) based systems. One or more ground-based optical terminals are assumed to communicate with the spacecraft. Both short-term and long-term link outages will arise due to weather at the ground station(s), space platform pointing stability, and other effects. To mitigate these outages, an Automatic Repeat Query (ARQ) retransmission method is assumed, together with a reliable back channel for acknowledgement traffic. Specifically, the Licklider Transmission Protocol (LTP) is used, which is a component of the Disruption-Tolerant Networking (DTN) protocol suite that is well suited for high bandwidth-delay product links subject to disruptions. We provide an analysis of envisioned deep space mission scenarios and quantify buffering, latency and throughput performance, using a simulation in which long-term weather effects are modeled with a Gilbert-Elliot Markov chain, short-term outages occur as a Bernoulli process, and scheduled outages arising from geometric visibility or operational constraints are represented. We find that both short- and long-term effects impact throughput, but long-term weather effects dominate buffer sizing and overflow losses as well as latency performance. C1 [Clare, Loren; Miles, Gregory] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Clare, L (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Loren.P.Clare@jpl.nasa.gov; Gregory.J.Miles@jpl.nasa.gov NR 7 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 11 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374903096 ER PT S AU Clark, I Adler, M AF Clark, Ian Adler, Mark GP IEEE TI Summary of the Second High-Altitude, Supersonic Flight Dynamics Test for the LDSD Project SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB NASA's Low-Density Supersonic Decelerator Project is developing and testing the next generation of supersonic aerodynamic decelerators for planetary entry. A key element of that development is the testing of full-scale articles in conditions relevant to their intended use, primarily in the tenuous Mars atmosphere. To achieve this testing, the LDSD project developed a new test architecture for the qualification of their supersonic parachute. A large, helium filled scientific balloon is used to hoist a 4.7 m blunt body test vehicle to an altitude of approximately 32 kilometers. The test vehicle is released from the balloon, spun up for gyroscopic stability, and accelerated to over four times the speed of sound and an altitude of 50 kilometers using a large solid rocket motor. Once at those conditions, the vehicle is despun and the test period begins. The second flight of this architecture occurred on June 8th, 2015. This flight sought to build on the very successful shakeout test of 2014 by testing an updated design of a new 30.5 meter nominal diameter supersonic parachute that applied lessons learned from the first flight. Two other supersonic decelerators were also tested: a 6 m diameter Supersonic Inflatable Aerodynamic Decelerator (SIAD), and a 4.4 m diameter trailing ballute. This paper summarizes the results from that test. C1 [Clark, Ian; Adler, Mark] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Clark, I (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM ian.g.clark@jpl.nasa.gov; mark.adler@jpl.nasa.gov NR 7 TC 0 Z9 0 U1 2 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 24 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374901027 ER PT S AU Clark, JJ Meakin, P AF Clark, Jessica Juneau Meakin, Peter GP IEEE TI The Soil Moisture Active Passive Mission: Fault Protection Performance and Lessons Learned SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB Fault protection as a discipline involves a collection of flight software logic and operational processes for detecting unacceptable anomalous behavior, responding prior to reaching criticality, restricting the propagation of a failure beyond a fault containment region, and recovering the vehicle back to full or degraded functionality if possible. The System Fault Protection (SFP) design for the SMAP Earth orbiter was put to the test during its 90-day vehicle Commissioning activities. During this time, the SFP software autonomously protected the vehicle from multiple faults to critical hardware, and the operations team successfully returned the observatory to its science state. The SFP also performed well in the presence of anomalous behavior below true safety limits by not taking unnecessary response actions, instead allowing the operations team time to monitor the behavior. Certain aspects of the SFP design were modified during operations via both parameter updates and a full flight software update in order to better match the vehicle behavior in the flight environment. An evaluation of the SMAP SFP performance during vehicle Commissioning will be provided in this paper, as well as a set of lessons learned largely focused on visibility, SFP mutability in operations, responses to peripheral device faults, and Safe Mode recovery and design. By capturing some of the knowledge gained during SMAP Commissioning, it is intended that this paper provide guidance for making future System Fault Protection designs more robust and supportive of operations. C1 [Clark, Jessica Juneau; Meakin, Peter] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Clark, JJ (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Jessica.Juneau@jpl.nasa.gov; Peter.C.Meakin@jpl.nasa.gov NR 2 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 9 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374902021 ER PT S AU Cohen, B AF Cohen, Barbara GP IEEE TI The Potassium-Argon Laser Experiment (KArLE): In Situ Geochronology for Planetary Robotic Missions SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE ID INDUCED BREAKDOWN SPECTROSCOPY; K-AR; INSTRUMENT AB The Potassium (K) - Argon (Ar) Laser Experiment (KArLE) will make in situ noble-gas geochronology measurements aboard planetary robotic landers and rovers. Laser-Induced Breakdown Spectroscopy (LIBS) is used to measure the K abundance in a sample and to release its noble gases; the evolved Ar is measured by mass spectrometry (MS); and relative K content is related to absolute Ar abundance by sample mass, determined by optical measurement of the ablated volume. KArLE measures a whole-rock K-Ar age to 10% or better for rocks 2 billion years old (Ga) or older, sufficient to resolve the absolute age of many planetary samples. The LIBS-MS approach is attractive because the analytical components have been flight proven, do not require further technical development, and provide complementary measurements as well as in situ geochronology. C1 [Cohen, Barbara] NASA, Marshall Space Flight Ctr, MS ZP13, Huntsville, AL 35758 USA. RP Cohen, B (reprint author), NASA, Marshall Space Flight Ctr, MS ZP13, Huntsville, AL 35758 USA. EM Barbara.A.Cohen@nasa.gov NR 40 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 9 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374904066 ER PT S AU Cole, B Dinkel, K AF Cole, Bjorn Dinkel, Kevin GP IEEE TI Multidisciplinary Model Transformation through Simplified Intermediate Representations SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB There has long been a challenge of making engineering tools from multiple disciplines interoperate. This problem extends to system modeling practices. This challenge has been confronted with a wide variety of techniques. These techniques include attempting to interface tools together into combined suites, attempting to find underlying commonalities in mathematics, supporting connections through semantic encoding, various graph mappings and transformations, and code wrappers. All of these approaches have strength s and weaknesses. These are measured in multiple areas: relative freedom of action of individual domain engineers in developing their own tools, speed of execution, ease of creation, traceability, fidelity of information transfer, and degree of alignment between the concepts of different domains. This paper presents an approach to this interoperation problem currently being used in the World-Wide Web. The approach is to develop easy-to-parse formats that allow flexibility to both the file author and file interpreter. Many of the formats that are currently deployed sacrifice runtime performance for the ability of third parties to easily understand what to do with the data. XML became popular earlier as a de - facto standard format for many web applications, but is now being replaced by JSON to enhance human readability and provide a simpler data model. This is the basis for work in this paper. Our approach, which provides the key to interoperation, is a simplified "shrapnel" intermediate collection of objects and relationships that is the result of a breakdown of the system model into minimal pieces. It is then reassembled on the destination side, forming a two-step transformation. Previous efforts with single-step transformations have proven too difficult to create efficiently. In contrast, the use of this approach leads to an almost automatic procedure for transformation development. The Europa project is a large engineering project that must coordinate the efforts of many different teams with different specialties. The traditional form of exchanging engineering information has been documentation. The vision of model-based systems engineering is to make this information exchange much more digital. This paper presents the application of our simplified format to connecting two different engineering tools to the system model, with a focus on a dynamic mission simulation encoded in Modelica. C1 [Cole, Bjorn; Dinkel, Kevin] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Cole, B (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Bjorn.Cole@jpl.nasa.gov; Kevin.Dinkel@jpl.nasa.gov NR 7 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 11 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374901064 ER PT S AU Dathathri, S Livingston, SC Reder, LJ Murray, RM AF Dathathri, Sumanth Livingston, Scott C. Reder, Leonard J. Murray, Richard M. GP IEEE TI Interfacing TuLiP with the JPL Statechart Autocoder: Initial progress toward synthesis of flight software from formal specifications SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB This paper describes the implementation of an interface connecting the two tools : the JPL SCA (Statechart Autocoder) and TuLiP (Temporal Logic Planning Toolbox) to enable the automatic synthesis of low level implementation code directly from formal specifications. With system dynamics, bounds on uncertainty and formal specifications as inputs, TuLiP synthesizes Mealy machines that are correct-by-construction. An interface is built that automatically translates these Mealy machines into UML statecharts. The SCA accepts the UML statecharts (as XML files) to synthesize flight-certified(2) implementation code. The functionality of the interface is demonstrated through three example systems of varying complexity a) a simple thermostat b) a simple speed controller for an autonomous vehicle and c) a more complex speed controller for an autonomous vehicle with a map-element. In the thermostat controller, there is a specification regarding the desired temperature range that has to be met despite disturbance from the environment. Similarly, in the speed-controllers there are specifications about safe driving speeds depending on sensor health (sensors fail unpredictably) and the map-location. The significance of these demonstrations is the potential circumventing of some of the manual design of statecharts for flight software/controllers. As a result, we expect that less testing and validation will be necessary. In applications where the products of synthesis are used alongside manually designed components, extensive testing or new certificates of correctness of the composition may still be required. C1 [Dathathri, Sumanth; Livingston, Scott C.; Murray, Richard M.] CALTECH, Pasadena, CA 91125 USA. [Reder, Leonard J.] Jet Prop Lab, Pasadena, CA USA. RP Dathathri, S (reprint author), CALTECH, Pasadena, CA 91125 USA. EM sdathath@caltech.edu; slivingston@cds.caltech.edu; Leonard.J.Reder@jpl.nasa.gov; murray@cds.caltech.edu NR 13 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 10 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374900061 ER PT S AU Deininger, W Moler, V Osborne, R Wotruba, L Plaisted, S Goldman, M Wendland, R Riesco, M Sexton, A Simmons, G Jonaitis, J McLean, C Smith, T Cavender, D Smith, D AF Deininger, William Moler, Vickey Osborne, Rob Wotruba, Luke Plaisted, Susanne Goldman, Michelle Wendland, Ron Riesco, Maureen Sexton, Adam Simmons, George Jonaitis, John McLean, Christopher Smith, Tim Cavender, Daniel Smith, Daniel GP IEEE TI Green Propellant Infusion Mission (GPIM) Space Vehicle Integration and Test Status SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB The Green Propellant Infusion Mission (GPIM) Project is sponsored by the NASA Space Technology Mission Directorate as part of the work conducted by the Technology Demonstration Mission Program Office. The goal of GPIM is to advance the technology readiness level (TRL) of a green propulsion technology based on the monopropellant AF-M315E via flight demonstration. As the Project lead, Ball Aerospace & Technologies Corp. (Ball) is coordinating contributions from industry, NASA, and the U.S. Air Force to execute the GPIM project. The GPIM Project started in October 2012. The SV bus was integrated and ready for payloads on schedule 23 months after contract start (September 2014). Work on the bus went into a 'bathtub' period to accommodate delays in payload arrival. In May 2014, post PDR, the GPIM Project was authorized to integrate three Air Force SERB payloads onto the GPIM space vehicle: iMESA, SWATS and SOS. These payloads were successfully integrated in June 2015. The Green Propellant Propulsion System (GPPS) arrived at Ball for integration in August 2015. SV integration and environmental testing has been successfully completed. The SV is in storage in a 'bathtub' period while waiting shipment to the launch site. This paper summarizes the flexibility of the BCP-100 spacecraft and describes the work to integrate the payloads and go through SV environmental testing. C1 [Deininger, William; Moler, Vickey; Osborne, Rob; Wotruba, Luke; Plaisted, Susanne; Goldman, Michelle; Wendland, Ron; Riesco, Maureen; Sexton, Adam; Simmons, George; Jonaitis, John; McLean, Christopher] Ball Aerosp & Technol Corp, 1600 Commerce St, Boulder, CO 80301 USA. [Smith, Tim; Cavender, Daniel] NASA, Marshall Space Flight Ctr, Huntsville, AL 35812 USA. [Smith, Daniel] SMC ADSS Space Acquisit & Dev Branch, 3548 Aberdeen Ave SE, Kirtland AFB, NM 87117 USA. RP Deininger, W (reprint author), Ball Aerosp & Technol Corp, 1600 Commerce St, Boulder, CO 80301 USA. EM wdeining@ball.com; vmoler@ball.com; rosborne@ball.com; lwotruba@ball.com; splaiste@ball.com; mgoldman@ball.com; rwendlan@ball.com; meriesco@ball.com; asexton@ball.com; gsimmons@ball.com; jjonaiti@ball.com; cmclean@ball.com; tim.smith@nasa.gov; Daniel.p.cavender@nasa.go; daniel.smith.163@us.af.mil NR 25 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 15 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374900045 ER PT S AU Del Castillo, L Weber, CT Mojarradi, M Carr, G Hunter, D Vo, T Stell, C Orellana, S Suh, JO Nieraeth, D Ikpe, SA Ludwig, LL Lauenstein, JM Iannello, CJ Chen, Y AF Del Castillo, Linda Weber, Carissa Tudryn Mojarradi, Mohammad Carr, Greg Hunter, Don Vo, Tuan Stell, Christopher Orellana, Sonny Suh, Jong-ook Nieraeth, Don Ikpe, Stanley A. Ludwig, Lawrence L. Lauenstein, Jean-Marie Iannello, Christopher J. Chen, Yuan GP IEEE TI High Temperature Anode Power Supply Parts and Packaging Reliability and Survivability SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB The power processing unit (PPU) of a solar electrical propulsion system for in-space propulsion is developed as a high power, temperature, and efficiency, modular, high specific impulse, and non-isolated converter topology unit for future deep space and manned missions. Overall, the High Temperature Boost (HTB) PPU has 87% improvement in PPU specific power/mass and 38% improvement in-space solar electric system mass saving. The objectives of this Phase 1 study are to develop a High Temperature Anode Power Supply 10kW Prototype module with new extreme environment component and packaging technology and determine the component reliability and packaging survivability for at least 50 cycles in the temperature range of -55 degrees C to +160 degrees C. After cycling, the functionality is tested at room temperature and elevated temperature (base plate at 100 degrees C). Selection of high temperature components and advanced packaging techniques enables operation at a higher base plate temperature of 100 degrees C. SiC MOSFETS and diodes were chosen as well as high temperature capacitors designed to operate at 1kV and 2.2 mu F at 150 degrees C. C1 [Del Castillo, Linda; Weber, Carissa Tudryn; Mojarradi, Mohammad; Carr, Greg; Hunter, Don; Vo, Tuan; Stell, Christopher; Orellana, Sonny; Suh, Jong-ook; Nieraeth, Don] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Ikpe, Stanley A.; Chen, Yuan] NASA, Langley Res Ctr, 8 Lindbergh Way, Hampton, VA 23665 USA. [Ludwig, Lawrence L.; Iannello, Christopher J.] NASA, Kennedy Space Ctr, Cocoa Beach, FL 32899 USA. [Lauenstein, Jean-Marie] NASA, Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. RP Del Castillo, L (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 8 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 8 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374904070 ER PT S AU Dillon, RL Oberhettinger, DJ Rogers, EW Tinsley, CH AF Dillon, Robin L. Oberhettinger, David J. Rogers, Edward W. Tinsley, Catherine H. GP IEEE TI A Different Kind of Organizational Silence: When Individuals Fail to Recognize a Problem Exists SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB After major disasters, significant contributing factors are commonly identified but too often only with hindsight. For individuals to report potential problems before the disaster, three steps need to occur: 1) he or she needs to recognize an event as a risk, problem, or possible wrongdoing, 2) he or she needs to choose to either speak up, neglect the problem, or leave the organization based on an assessment of the benefits and costs of each alternative, and 3) he or she must take action if speaking up is the chosen response. The organizational silence literature focuses mostly on step 2, where the culture of the organization causes individuals to choose to not speak up even when a problem is recognized. In this paper, we focus on step 1: where characteristics of the organization or the particular problem cause individuals to fail to recognize a problem exists. We first examine the 1998 incident at Wallops Flight Facility where an aircraft crashed during an engine water ingestion test. We then describe a series of behavioral lab experiments conducted to demonstrate how different conditions in the situation can influence the participant's ability to recognize increasing risk in a task. C1 [Dillon, Robin L.; Tinsley, Catherine H.] Georgetown Univ, McDonough Sch Business, Washington, DC 20057 USA. [Oberhettinger, David J.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Rogers, Edward W.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Dillon, RL (reprint author), Georgetown Univ, McDonough Sch Business, Washington, DC 20057 USA. EM rld9@georgetown.edu; davido@nasa.gov; ed.rogers@nasa.gov; tinsleyc@georgetown.edu NR 11 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 9 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374900009 ER PT S AU Dissanayake, A Zarembowitch, A Hogie, K Yang, X Lubelczyk, J Safavi, H AF Dissanayake, Asoka Zarembowitch, Alain Hogie, Keith Yang, Xun Lubelczyk, Jeffry Safavi, Haleh GP IEEE TI TDRSS Narrow-band Simulator and Test System SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB Introducing new communication equipment or system to the Tracking and Data Relay Satellite System (TDRSS) ground segment is a complicated process that involves a lengthy development and test cycle. Complexity arises due to the presence of the variety of signaling formats, operation and user constraints, monitor and control parameters, and the requirement to ensure the new piece of ground equipment or system meets the functional and performance requirements for all different combinations of system configuration parameters and operational scenarios. The development cycle starts with extensive software simulations to establish the performance parameters of the new equipment or system followed by a prototyping stage. The prototype system undergoes a battery of tests in a laboratory environment to verify that it is capable of meeting the performance levels derived from the software simulations. Testing must be performed using simulated signals generated either using software or hardware. The current practice is to use a chain of test equipment, each piece in the chain dedicated to a single function. This requires manual setup between different test configurations and test reporting is also handled manually. This is costly both in terms of test hardware investment and the manpower involved. The options available to reduce the cost are to use either a software or hardware simulator that can combine multiple functions in a single unit. Software simulation involves generating signal files that can be played back repeatedly. Depending on the data rate being simulated, each test file can occupy several Terabytes (TBs); in addition, it requires a playback system which tends to be relatively expensive to acquire and maintain. On the other hand, with more advanced signal processing technology the hardware simulation can be achieved with low cost Field Programmable Gate Array (FPGA). A low cost hardware simulator that can support data rates up to 25 Mbps is selected for the simulation system. The simulator supports baseband digital data formats and different modulation and coding schemes used in the TDRSS. Channel impairments applicable for communicating with orbiting platforms and signal impairments generated by the TDRSS itself are also simulated by the system; these include stressing profiles of delay, Doppler, and multipath. Hardware distortions of customer platforms are simulated by a set of software defined distortion filters designed according to the user constraints specified in the Space Network user's guide. In order to reduce the time spent during the prototype testing phase, an automated test system is being developed. Simulator architecture and the test automation approach will be presented. C1 [Dissanayake, Asoka] Harris Corp, 7855 Walker Dr, Greenbelt, MD 20770 USA. [Zarembowitch, Alain] MSS Comblock, 845-N Quince Orchard Blvd, Gaithersburg, MD 20878 USA. [Hogie, Keith] Comp Sci Corp, 12401 Mt Pleasant Dr, Laurel, MD 20708 USA. [Yang, Xun] Harris Corp, NASA GSFC, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. [Lubelczyk, Jeffry; Safavi, Haleh] NASA GSFC, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. RP Dissanayake, A (reprint author), Harris Corp, 7855 Walker Dr, Greenbelt, MD 20770 USA. EM Asoka.Dissanayake@harris.com; az@mobile-sat.com; Keith.Hogie@nasa.gov; Xun.Yang@nasa.gov; Jeffrey.T.Lubelczyk@nasa.gov; Haleh.Safavi@nasa.gov NR 6 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 10 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374902068 ER PT S AU Divsalar, D Asmar, S Farr, W Dolinar, S Vilnrotter, V AF Divsalar, Dariush Asmar, Sami Farr, William Dolinar, Sam Vilnrotter, Victor GP IEEE TI An Optical Receiver for Science Measurements and Data Detection SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB In the era of optical communications, the currently available optical system does not provide the required observations to extract the proper measurements for optical science experiments. Science investigations should utilize the optical telecommunication links between spacecraft and Earth to examine changes in the phase, frequency, amplitude, and polarization of radio signals to investigate planetary atmospheres, planetary rings, planetary surfaces, planetary interiors, solar corona and wind, comet mass flux, and fundamental physics. The proposed system in this paper provides an architectural improvement to the present state of the art optical communication systems utilized by NASA. In this paper we develop an optical receiver to provide amplitude, phase, and Doppler frequency for optical Science measurements in addition to detecting Pulse Position Modulation (PPM) signals. Currently available direct detection PPM does not provide these features. First we propose how to construct an optical receiver with mirrors, splitters, and photon counting detectors that produce in-phase and quadrature components. We analyze the performance of proposed optical system for PPM. The paper provides derivations, and analysis of proposed optical receiver. The innovations are methods to extract phase, Doppler frequency from PPM intensity modulated optical signal. We demonstrate how the receiver can detect the PPM data and at the same time provide phase information for science measurements. Numerical results are provided for the proposed optical receiver. C1 [Divsalar, Dariush; Asmar, Sami; Farr, William; Dolinar, Sam; Vilnrotter, Victor] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Divsalar, D (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM dariush.divsalar@jpl.nasa.gov; sami.asmar@jpl.nasa.gov; william.farr@jpl.nasa.gov; sam.dolinar@jpl.nasa.gov; victor.vilnrotter@jpl.nasa.gov NR 6 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 9 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374902027 ER PT S AU Dubos, GF Coren, DP Chung, SH Castet, JF AF Dubos, Gregory F. Coren, David P. Chung, Seung H. Castet, Jean-Francois GP IEEE TI Modeling of the Flight System Design in the Early Formulation of the Europa Project SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB During the early formulation stage of a mission concept, the multiple and frequent changes made to the system design present various systems engineering challenges, including: ensuring the internal consistency of multiple engineering reports describing distinct aspects of the same flight system; capturing the interdependencies between subsystems to guide the design iteration process; minimizing the amount of rework needed when the design is modified; managing multiple architectural alternatives while leveraging commonality; and finally providing traceability of the design changes made over time. This paper describes how such challenges have been partly addressed by the Model-Based Systems Engineering Team (MSET) on the Europa Project at the Jet Propulsion Laboratory (JPL), through the application of Model-Based Systems Engineering (MBSE) techniques. The paper first discusses the principle of Single-Source-of-Truth (SSoT) and how it can be supported by the use of a wellstructured system model relying on a rich vocabulary (e. g., based on the SysML language). The application of modeling patterns to organize the Flight System design information and make it queryable is then examined, with specific examples used on the Europa project (such as launch dry mass, electrical power, thermal power, fields-of-view). The benefits of checking formal rules to verify the correctness of the model and ensure that changes were properly incorporated are also discussed. The paper then presents model organization strategies that maximize the reuse of information across multiple design architectures that are explored in early formulation, as well as various practices used to control the numerous changes made to the model as the design matures. Finally, the paper concludes with a summary of the lessons learned from using a system model on the Europa project in order to capture design information about the Flight System. This has proved to play a key role in delivering high-quality representations of the spacecraft design to a variety of stakeholders as well as demonstrating its viability. C1 [Dubos, Gregory F.; Coren, David P.; Chung, Seung H.; Castet, Jean-Francois] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Dubos, GF (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Gregory.F.Dubos@jpl.nasa.gov NR 11 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 14 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374901013 ER PT S AU Edwards, BL Lafon, RE Luzhansky, EY AF Edwards, Bernard L. Lafon, Robert E. Luzhansky, Edward Y. GP IEEE TI Operational Impacts of the US Federal Aviation Administration and the US Laser Clearinghouse on an Optical Communications Earth Relay SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB NASA is planning to launch the next generation of a space-based Earth relay satellite sometime in the middle of the next decade to join the current Space Network, consisting of Tracking and Data Relay Satellites in space and the corresponding infrastructure on Earth. While the requirements and architecture for that relay satellite are unknown at this time, NASA is investing in communications technologies that could be deployed to provide new communications services. One of those new technologies is optical communications. The Laser Communications Relay Demonstration (LCRD) project, scheduled for launch in 2019 as a hosted payload, is a critical pathfinder towards NASA providing optical communications services on the next generation space-based relay. This paper will describe the concept of operations and the impacts of the U.S. Federal Aviation Administration and the U.S. Laser Clearinghouse on the Laser Communications Relay Demonstration. It will provide a high level overview of the link budgets and discuss the analysis done on both space to ground links and geostationary (GEO) to low Earth orbit (LEO) links. The U.S. Laser Clearinghouse is a United States Air Force Strategic Command organization that provides predictive avoidance analysis and deconfliction with U.S. and allies satellites and operations. NASA's policy is to be in compliant with the U.S. Laser Clearinghouse. Having a valid concept of operations that is compliant with the U.S. Federal Aviation Administration and the U.S. Laser Clearinghouse is critical to making optical communications a reality on future NASA science and exploration missions. C1 [Edwards, Bernard L.] NASA GSFC, Code 560, Greenbelt, MD 20771 USA. [Lafon, Robert E.; Luzhansky, Edward Y.] NASA GSFC, Code 554, Greenbelt, MD 20771 USA. RP Edwards, BL (reprint author), NASA GSFC, Code 560, Greenbelt, MD 20771 USA. EM Bernard.L.Edwards@nasa.gov; Robert.Lafon@nasa.gov; Eduard.Y.Luzhanskiy@nasa.gov NR 6 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 7 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374900038 ER PT S AU Edwards, CD Bell, DJ Biswas, A Cheung, KM Lock, RE AF Edwards, Charles D., Jr. Bell, David J. Biswas, Abhijit Cheung, Kar-Ming Lock, Robert E. GP IEEE TI Proximity Link Design and Performance Options for a Mars Areostationary Relay Satellite SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE ID EXPLORATION AB Current and near-term Mars relay telecommunications services are provided by a set of NASA and ESA Mars science orbiters equipped with UHF relay communication payloads employing operationally simple low-gain antennas. These have been extremely successful in supporting a series of landed Mars mission, greatly increasing data return relative to direct-to-Earth lander links. Yet their relay services are fundamentally constrained by the short contact times available from the selected science orbits. Future Mars areostationary orbiters, flying in circular, equatorial, 1-sol orbits, offer the potential for continuous coverage of Mars landers and rovers, radically changing the relay support paradigm. Achieving high rates on the longer slant ranges to areostationary altitude will require steered, high-gain links. Both RF and optical options exist for achieving data rates in excess of 100 Mb/s. Several point designs offer a measure of potential user burden, in terms of mass, volume, power, and pointing requirements for user relay payloads, as a function of desired proximity link performance. C1 [Edwards, Charles D., Jr.; Bell, David J.; Biswas, Abhijit; Cheung, Kar-Ming; Lock, Robert E.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Edwards, CD (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Charles.D.Edwards@jpl.nasa.gov NR 16 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 10 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374901088 ER PT S AU Evans, JP AF Evans, Jordan P. GP IEEE TI Taking the Tiger by the Tail: Leading Effective Tiger Teams and Working Groups on Flight Projects SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB Space flight projects typically bring with them a demanding schedule, deep technical challenges, and diverse personalities. As issues arise, project management regularly employs working groups, or "tiger teams," to assess a problem that has arisen or to answer a specific question. Leading a working group or "tiger team" in this environment can be difficult and still, in the end, rewarding. This paper explores some methods used to effectively lead these teams while being responsive to the needs of the flight project. Experiences and examples are drawn from many tiger teams and working groups led by the author throughout the Mars Science Laboratory development and post-launch cruise to Mars. C1 [Evans, Jordan P.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Evans, JP (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Jordan.P.Evans@jpl.nasa.gov NR 3 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 5 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374903019 ER PT S AU Frerking, MA Beauchamp, PM AF Frerking, Margaret A. Beauchamp, Patricia M. GP IEEE TI JPL Technology Readiness Assessment Guideline SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB New capabilities in spaceflight missions are enabled by new technologies. Transitioning new technology to spaceflight elements is difficult and introduces risk, but finding the right balance between benefit and risk leads to scientific advancements and novel space missions. A clear understanding of the risks of new technology can create an environment where innovation is nurtured rather than avoided. The Technology Readiness Level (TRL) was developed as a metric for the maturity of new technology, but, in the past, assessing the TRL was often done informally and inconsistently. This frequently led to discrepancies between the TRL as perceived by the technologist and that perceived by a project. JPL has developed a guideline for their projects to provide a basis for a consistent Technology Readiness Assessment (TRA). Highlights of this guideline are presented here. It is anticipated that the implementation of this guideline will enable the hand-off from technologists to project engineers leading to greater acceptance of technologies by flight projects. On completion of a satisfactory TRA, an agreement can be made between the parties on the maturation plan required for successful infusion of the technology into a flight mission. C1 [Frerking, Margaret A.; Beauchamp, Patricia M.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Frerking, MA (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Margaret.A.Frerking@jpl.nasa.gov; Patricia.M.Beauchamp@jpl.nasa.gov NR 7 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 10 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374904045 ER PT S AU Gao, JL AF Gao, Jay L. GP IEEE TI A Study of Adaptive Coding and Modulation Over Free Space Optical Link Using OCTL Data SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB In this paper we utilized the downlink channel data captured at the Optical Communication Test Laboratory (OCTL) in support of the Lunar Laser Communications Demonstration (LLCD) to evaluate the potential performance gain of using adaptive coding and modulation (ACM) scheme to increase data volume while mitigating weather impairment. The study assumed that the estimated signal and noise photon counts statistics generated by concurrent processing of the downlink signal is available in real time to drive a closed-loop control of the code rate and the PPM order of the downlink. Downlink data from two representative passes were used. Pass no. 12, which occurred on October 29, 2013 and lasted 24 minutes and 15 second, recorded several link outages due to thin cloud and cloud interruption and is used to calibrate the symbol error constraint for the adaptive modulation algorithm. Pass no. 20, which was 19 minutes and 16 seconds long and occurred on November 18, 2013, operated over very clear sky and large sun-earth-probe (SEP) angle (approx. 170 degrees) and provided a representative sample of a clean optical channel. This study ignores constraints such as peak and average power limitations and processing overhead. Impacts of delay in the control loop are not addressed in this study, therefore any performance enhancement indicated by this study is only applicable to a short propagation delay environment. For deep space environment, further analysis will be required to determine the benefit of ACM. C1 [Gao, Jay L.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Gao, JL (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Jay.L.Gao@jpl.nasa.gov NR 5 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 7 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374904006 ER PT S AU Gao, JL AF Gao, Jay L. GP IEEE TI On the Performance of Adaptive Data Rate over Deep Space Ka-Band Link: Case Study Using Kepler Data SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB Future missions envisioned for both human and robotic exploration demand increasing communication capacity through the use of Ka-band communications. The Ka-band channel, being more sensitive to weather impairments, presents a unique trade-offs between data storage, latency, data volume and reliability. While there are many possible techniques for optimizing Ka-band operations such as adaptive modulation and coding and site-diversity, this study focus exclusively on the use of adaptive data rate (ADR) to achieve significant improvement in the data volume-availability tradeoff over a wide range of link distances for near Earth and Mars exploration. Four years of Kepler Ka-band downlink symbol signal-to-noise (SNR) data reported by the Deep Space Network were utilized to characterize the Ka-band channel statistics at each site and conduct various what-if performance analysis for different link distances. We model a notional closed-loop adaptive data rate system in which an algorithm predicts the channel condition two-way light time (TWLT) into the future using symbol SNR reported in near-real time by the ground receiver and determines the best data rate to use. Fixed and adaptive margins were used to mitigate errors in channel prediction. The performance of this closed-loop adaptive data rate approach is quantified in terms of data volume and availability and compared to the actual mission configuration and a hypothetical, optimized single rate configuration assuming full a priori channel knowledge. C1 [Gao, Jay L.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Gao, JL (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Jay.L.Gao@jpl.nasa.gov NR 8 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 7 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374903030 ER PT S AU Gatens, R AF Gatens, Robyn GP IEEE TI Commercializing Low-Earth Orbit and the Role of the International Space Station SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB With the extension of the International Space Station (ISS) operations until at least 2024, NASA and its partners have the opportunity to leverage the orbiting laboratory to conduct research and validate systems in microgravity that will better prepare humans and systems for future missions, farther into deep space. Beyond 2024, it is vitally important to ensure that the infrastructure and capabilities that have been developed over the past three decades in low Earth orbit (LEO) do not languish, and in fact are used to enable sustainable commercial activity in LEO beyond the ISS. This paper will explore the opportunities and challenges in developing the commercial market in LEO through the ISS program while at the same time continuing to use the ISS as a testbed to enable human missions into deep space.. System and technology capability gaps requiring demonstrations on the ISS will be discussed in detail. NASA's strategic plan for leveraging the ISS to enable commercial markets and stimulate commercial supply of LEO services will be summarized, along with initial steps and progress. The intersection between NASA's needs beyond LEO and commercial LEO platforms will be explored. Finally, the paper will discuss preliminary measures that will indicate when a transition from ISS to the Proving Ground is appropriate. C1 [Gatens, Robyn] NASA Headquarters, 300 E St SW, Washington, DC 20546 USA. RP Gatens, R (reprint author), NASA Headquarters, 300 E St SW, Washington, DC 20546 USA. EM robyn.gatens@nasa.gov NR 1 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 8 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374902079 ER PT S AU Gatti, M Lin, HS Long, E Sosnowski, J Jamnejad, V AF Gatti, Mark Lin, Hungsheng Long, Ezra Sosnowski, John Jamnejad, Vahraz GP IEEE TI A Test-bed Validation of Electromagnetic Surface Wave Propagation Along a Dielectric-Coated Metal Pipe SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB This paper provides a summary of the results of an attempt at experimental verification of the propagation of electromagnetic surface waves at microwaves frequencies, in and along the uniform dielectric coating of a circular cylindrical metal pipe, based on the previously stablished theoretical investigation. These experimental results are of value for the diagnostic of anomalies on the surface of tar-coated pipes used in protecting the underground power transmission cables (feeder pipes). A test-bed was designed and implemented using an aluminum tubes (10 '' diameter) with an acrylic tube coating (0.25 '' thickness). Two identical wave launcher/receiver arrays, each of 32 elements around the tube for relatively uniform radiation/reception, were designed and fabricated at the frequency of interest (similar to 6 GHz). This arrangement was put in a specially designed small anechoic chamber and attached to a network analyzer. A variety of tests were performed to stablish the launch efficiency, prove surface wave propagation along, and reflection from different types of anomalies on the coating. In the paper, a number of test results and supporting graphs will be provided and future work for improving the performance of the launch array and the test-bed arrangement for better results will be outlined. C1 [Gatti, Mark; Lin, Hungsheng; Long, Ezra; Sosnowski, John; Jamnejad, Vahraz] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Jamnejad, V (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Vahraz.Jamnejad@jpl.nasa.gov NR 3 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 13 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374904037 ER PT S AU Gernhardt, ML Bekdash, OS Li, ZQ Abercromby, AFJ Chappell, SP Beaton, KH Bielski, P Crues, EZ AF Gernhardt, Michael L. Bekdash, Omar S. Li, Zu Qun Abercromby, Andrew F. J. Chappell, Steven P. Beaton, Kara H. Bielski, Paul Crues, Edwin Z. GP IEEE TI Human Exploration Missions to Phobos Prior to Crewed Mars Surface Missions SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE ID DYNAMICS AB Phobos is a scientifically interesting destination which offers engineering, operational and public outreach activities that could enhance subsequent Mars surface missions. A Phobos mission would serve to facilitate the development of the human-based Mars transportation infrastructure, unmanned cargo delivery systems, as well as habitation and exploration assets that would be directly relevant to subsequent Mars surface missions. It would also potentially provide for low latency teleoperations (LLT) of Mars surface robots performing a range of tasks from landing site validation to infrastructure development to support future crewed Mars surface Missions. A human mission to Phobos would be preceded by a cargo predeploy of a Phobos surface habitat and a pressurized excursion vehicle (PEV) to Mars orbit. Once in Mars orbit, the habitat and PEV would spiral to Phobos using solar electric propulsion (SEP)-based systems. When a crewed mission is launched to Phobos, it would include the remaining systems to support the crew during the Earth-to-Mars orbit transit and to reach Phobos after insertion into a high Mars orbit (HMO). The crew would taxi from HMO to Phobos in a spacecraft that is based on a MAV to rendezvous with the predeployed systems. A predominantly static Phobos surface habitat was chosen as a baseline architecture. The habitat would have limited capability to relocate on the surface to shorten excursion distances required by the PEV during exploration and to provide rescue capability should the PEV become disabled. PEVs would contain closed-loop guidance and provide life support and consumables for two crewmembers for two weeks plus reserves. The PEV has a cabin that uses the exploration atmosphere of 8.2psi with 34% oxygen. This atmosphere enables EVA to occur with minimal oxygen prebreathe before crewmembers enter their EVA suits through suit ports, and provides dust control to occur by keeping the suits outside the pressurized volume. When equipped with outriggers, the PEV enables EVA tasks without the need to anchor. Tasks with higher force requirements can be performed with PEV propulsion providing the necessary thrust to counteract forces. This paper overviews the mission operational concepts, and timelines, along with analysis of the power, lighting, habitat stability, and EVA forces. Exploration of Phobos builds heavily on the development of the cis-lunar proving ground and significantly reduces Mars surface risk by facilitating the design, development and testing of habitats, MAVs, and pressurized rover cabins that are all investments in Mars surface assets. C1 [Gernhardt, Michael L.; Li, Zu Qun; Abercromby, Andrew F. J.; Bielski, Paul] NASA, Johnson Space Ctr, 2101 NASA Pkwy, Houston, TX 77058 USA. [Bekdash, Omar S.; Chappell, Steven P.; Beaton, Kara H.; Crues, Edwin Z.] Wyle Sci Technol & Engn Grp, 1290 Hercules Ave, Houston, TX 77058 USA. RP Gernhardt, ML (reprint author), NASA, Johnson Space Ctr, 2101 NASA Pkwy, Houston, TX 77058 USA. EM michael.l.gernhardt@nasa.gov; omar.s.bekdash@nasa.gov; zuqun.li@nasa.gov; andrew.f.abercromby@nasa.gov; steven.p.chappell@nasa.gov; kara.h.beaton@nasa.gov; paul.bielski@nasa.gov; edwin.z.crues@nasa.gov NR 39 TC 0 Z9 0 U1 2 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 20 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374902034 ER PT S AU Ghaffarian, R Evans, JW AF Ghaffarian, Reza Evans, John W. GP IEEE TI Risk Analysis for CGA and Advanced Electronics Packaging SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB This paper first presents packaging technology trends and accelerated reliability testing and life projection methods that are being practiced by industry. Specifically, it presents industry status on key advanced electronic packages, factors affecting accelerated solder joint reliability of area array packages and approaches for characterizations of assemblies under accelerated thermal loading. Examples on projecting cycles-to-failure (CTF) from one accelerated thermal cycle condition to another for column grid arrays (CGAs) also presented. It was shown, even for thermal cycling, the limitation of projection using mildly accelerated thermal CTFs to a more severe accelerated thermal CTFs, both for CGA assembled with eutectic tin-lead solder and ball grid array (BGA) Pb-free assemblies. Examples also given for projection life of complex spacecraft using accelerated testing and analysis; thereby, reducing risk. Quantitative assessments necessarily involve the mathematics of probability and statistics. In addition, accelerated tests need to be designed which consider the desired risk posture and schedule for particular project. Such assessments relieve risks without imposing additional costs and constraints that are not value added for a particular mission. C1 [Ghaffarian, Reza] Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Evans, John W.] NASA HQ Off Safety Mission Assurance, Washington, DC USA. RP Ghaffarian, R (reprint author), Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Reza.Ghaffarian@jpl.nasa.gov; John.W.Evans@NASA.gov NR 24 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 10 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374900005 ER PT S AU Giga, A Terrile, RJ Belz, AP Zapatero, F AF Giga, Aleksandar Terrile, Richard J. Belz, Andrea P. Zapatero, Fernando GP IEEE TI The Impact of NASA's Small Business Innovation Research Program on Invention and Innovation SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE ID RESEARCH-AND-DEVELOPMENT; REGRESSION DISCONTINUITY DESIGNS; PATENT CITATIONS; PROPENSITY AB We empirically determine the impact of the NASA Small Business innovation Research (SBIR) Program on invention and innovation. The NASA SBIR program selects a portfolio of technology proposals, submitted by small businesses to an annual solicitation. Funding may be awarded in two tranches, a 6-month phase I award and a subsequent, 2-year phase II award. Over the last decade, the total annual awarded funding was about $100-140M with Phase I awards growing from $100-125K and phase II awards from $500-750K. Typically, about 15-20% of submitted Phase I proposals are awarded and only these awards are eligible to submit a phase II proposal. The success rate at phase II is about 40%. We looked at NASA SBIR data between 1999 and 2006 to determine the impact of receiving a phase II award on invention and innovation by using patent activity as a proxy. Data from all NASA Mission Directorates and over a range of years were considered and combined into a statistically significant collection. We examined the phase II proposed technologies and the subsequent patent history of the submitting companies in the five years after the award cycle. We find that phase II awarded companies had a significantly greater number of awarded and cited patents, over this time frame, than companies not awarded an SBIR phase II. Specifically, we find an overall increase in awarded patents of 39% for SBIR awarded companies versus non-awarded companies. This difference is statistically significant at the 95% confidence level. We also examined subsets for these data to quantify the effects of company size and previous patent awards on these trends. C1 [Giga, Aleksandar] Univ Southern Calif, Dept Econ, 3620 S Vermont Ave,KAP 300, Los Angeles, CA 90089 USA. [Terrile, Richard J.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Belz, Andrea P.] Univ Southern Calif, Viterbi Sch Engn, Olin Hall Engn 200, Los Angeles, CA 90089 USA. [Zapatero, Fernando] Univ Southern Calif, Marshall Sch Business, 3670 Trousdale Pkwy, Los Angeles, CA 90089 USA. RP Giga, A (reprint author), Univ Southern Calif, Dept Econ, 3620 S Vermont Ave,KAP 300, Los Angeles, CA 90089 USA. EM aleks.giga@gmail.com; rich.terrile@jpl.nasa.gov; abelz@marshall.usc.edu; fzapatero@marshall.usc.edu NR 23 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 8 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374904048 ER PT S AU Greenhouse, M AF Greenhouse, Matthew GP IEEE TI The James Webb Space Telescope: Mission Overview and Status SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB The James Webb Space Telescope (JWST) is the scientific successor to the Hubble Space Telescope. It is a cryogenic infrared space observatory with a 25 m(2) aperture (6 m class) telescope that will achieve diffraction limited angular resolution at a wavelength of 2 um. The science instrument payload includes four passively cooled near-infrared instruments providing broad- and narrow-band imagery, coronography, as well as multi-object and integral-field spectroscopy over the 0.6 < lambda < 5.0 um spectrum. An actively cooled mid-infrared instrument provides broad-band imagery, coronography, and integral-field spectroscopy over the 5.0 < lambda< 29 um spectrum. The JWST is being developed by NASA, in partnership with the European and Canadian Space Agencies, as a general user facility with science observations proposed by the international astronomical community in a manner similar to the Hubble Space Telescope. Technology development and mission design are complete. Construction, integration and verification testing is underway in all areas of the program. The JWST is on schedule for launch during 2018. C1 [Greenhouse, Matthew] Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Greenhouse, M (reprint author), Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. EM matt.greenhouse@nasa.gov NR 33 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 11 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374904061 ER PT S AU Hafiychuk, V Foygel, M Watson, MD Brown, B Ponizovskaya-Devine, E AF Hafiychuk, Vasyl Foygel, Michael Watson, Michael D. Brown, Barbara Ponizovskaya-Devine, E. GP IEEE TI Moving-boundary Model of Cryogenic Operation for Fault Detection and Diagnostics SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE ID GENERAL CORRELATION; 2-PHASE FLOWS; HEAT PIPES; EVAPORATORS; FORMULATION; SIMULATION AB A moving-boundary model of two-phase (TP) flow in a cross-country cryogenic fuel supply line has been developed. It is based on time-dependent one-dimensional ordinary differential equations that describe mass and energy conservation of the flowing cryogen that exchanges heat with the tubes' walls. The momentum conservation is taken into consideration by relating the pressure drop across the boundaries of the control volumes (CVs) with the corresponding inlet and outlet mass flow rates through the boundaries of these volumes. With a relatively small computational effort compare to full-scale schemes, the model describes pressure and temperature variations together with kinetics of vapor void fraction and of the interphase boundary motion in the different parts of the spatially distributed system. In this part, special attention is given to detailed study of the transient and steady state two-phase cryogenic movement in a long horizontal pipe with different regimes of flow: with and without heat exchange between the tube walls and the cryogen and between the walls and the environment; in the presence of local mass and heat leaks, and of sudden obstructions, etc. The convergence of the computational procedure with respect to the number of the CVs is discussed. C1 [Hafiychuk, Vasyl; Foygel, Michael; Ponizovskaya-Devine, E.] SGT Inc, NASA ARC, Mountain View, CA 94035 USA. [Watson, Michael D.] NASA, Marshall Space Flight Ctr, Huntsville, AL 35805 USA. [Brown, Barbara] NASA KSC, Kennedy Space Ctr, FL 32899 USA. RP Hafiychuk, V (reprint author), SGT Inc, NASA ARC, Mountain View, CA 94035 USA. EM vasyl.hafiychuk@nasa.gov; Michael.Foygel@sdsmt.edu; michael.d.watson@nasa.gov; barbara.l.brown@nasa.gov; ekaterina.v.ponizovskayadevine@nasa.gov NR 25 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 10 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374903028 ER PT S AU Hafiychuk, V AF Hafiychuk, Vasyl GP IEEE TI Modeling of Microstructure for Uncertainty Assessment of Carbon Fiber Reinforced Polymer Composites SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB This presentation deals with the mathematical modeling of composite microstructures for uncertainty quantification of composite structural parameters. Multiple designs of unidirectional fiber reinforced composite materials with arbitrary ply orientations are investigated. We consider a homogenization approach from microscopic to macroscopic scales for the prediction of mechanical properties of the composites. An uncertainty assessment of the effective structural modulus of composite materials consisting of an elastic matrix reinforced with fibers as functions of the phase volume fractions and the structural properties of the constituents is conducted. We consider the global sensitivity analysis (GSA) methods based both on the Fourier Amplitude Sensitivity Test (FAST) and on the Sobol global sensitivity index (GSI). The proposed approach makes it possible to quantify the effective structural parameters of the material based on the variance in the constituents. Numerical results of the GSI and FAST computed for composite materials reveal significant dependence of the macroscopic composite on the probabilistic properties of the fiber volume fraction. The GSA is performed to quantify the influence of fiber volume fraction variation, lamina thickness variation, etc. A nonlinear stage for composite failure prediction based on the Tsai-Wu failure theory was considered. The GSI quantify the relative contribution of variances in material constituents to the total variance of the material under a critical load. C1 [Hafiychuk, Vasyl] SGT Inc, NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Hafiychuk, V (reprint author), SGT Inc, NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. EM vasyl.hafiychuk@nasa.gov NR 24 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 9 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374903029 ER PT S AU Hamley, JA McCallum, PW Sandifer, CE Sutliff, TJ Zakrajsek, JF AF Hamley, John A. McCallum, Peter W. Sandifer, Carl E., II Sutliff, Thomas J. Zakrajsek, June F. GP IEEE TI NASA's Radioisotope Power Systems Program Overview A Focus on RPS Users SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB The goal of NASA's Radioisotope Power Systems (RPS) Program is to make RPS ready and available to support the exploration of the solar system in environments where the use of conventional solar or chemical power generation is impractical or impossible to meet potential future mission needs. To meet this goal, the RPS Program manages investments in RPS technologies and RPS system development, working closely with the Department of Energy. This paper provides an overview of the RPS Program content and status, its collaborations with potential RPS users, and the approach employed to maintain the readiness of RPS to support future NASA mission concepts. C1 [Hamley, John A.; McCallum, Peter W.; Sandifer, Carl E., II; Sutliff, Thomas J.; Zakrajsek, June F.] NASA, Glenn Res Ctr, 21000 Brookpk Rd, Cleveland, OH 44135 USA. RP Hamley, JA (reprint author), NASA, Glenn Res Ctr, 21000 Brookpk Rd, Cleveland, OH 44135 USA. EM john.a.hamley@nasa.gov; peter.w.mccallum@nasa.gov; carl.e.sandifer@nasa.gov; tsutliff@nasa.gov; june.f.zakrajsek@nasa.gov NR 10 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 12 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374901055 ER PT S AU Hayhurst, MR Bitten, RE Shinn, SA Judnick, DC Hallgrimson, IE Youngs, MA AF Hayhurst, Marc R. Bitten, Robert E. Shinn, Stephen A. Judnick, Daniel C. Hallgrimson, Ingrid E. Youngs, Megan A. GP IEEE TI Historical Mass, Power, Schedule, and Cost Growth for NASA Spacecraft SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB Although spacecraft developers have been moving towards standardized product lines as the aerospace industry has matured, NASA's continual need to push the cutting edge of science to accomplish unique, challenging missions can still lead to spacecraft resource growth over time. This paper assesses historical mass, power, cost, and schedule growth for multiple NASA spacecraft from the last twenty years and compares to industry reserve guidelines to understand where the guidelines may fall short. Growth is assessed from project start to launch, from the time of the preliminary design review (PDR) to launch and from the time of the critical design review (CDR) to launch. Data is also assessed not just at the spacecraft bus level, but also at the subsystem level wherever possible, to help obtain further insight into possible drivers of growth. Potential recommendations to minimize spacecraft mass, power, cost, and schedule growth for future missions are also discussed. C1 [Hayhurst, Marc R.; Bitten, Robert E.; Judnick, Daniel C.; Hallgrimson, Ingrid E.; Youngs, Megan A.] Aerosp Corp, 2310 E El Segundo Blvd, El Segundo, CA 90245 USA. [Shinn, Stephen A.] Goddard Space Flight Ctr, 8800 Greenbelt Rd,Code 400, Greenbelt, MD 20771 USA. RP Hayhurst, MR (reprint author), Aerosp Corp, 2310 E El Segundo Blvd, El Segundo, CA 90245 USA. EM marc.r.hayhurst@aero.org; robert.e.bitten@aero.org; stephen.a.shinn@nasa.gov; daniel.c.judnick@aero.org; ingrid.e.hallgrimson@aero.org; megan.a.youngs@aero.org NR 11 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 17 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374900057 ER PT S AU Helmlinger, M Eastwood, M Green, R Thompson, DR AF Helmlinger, Mark Eastwood, Michael Green, Robert Thompson, David R. GP IEEE TI Solar-Similar Near-Infra-Red Suppressed "Blue" Calibration Source SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB Laboratory calibration and characterization methods using incandescent sources have notoriously been weak at short wavelengths. A homogeneous spectral radiance source better matching that of a bright terrestrial target has been developed. Standard industry practices and the issues encountered are discussed. How our solution addresses the problem and experimental details of our approach will be presented. This effort is part of an overall goal of developing cost-effective techniques for accommodating and determining the radiometric calibration of imaging spectrometers operating in the long ultraviolet to short wavelength infrared, 380 to 2510 nm, region of the electromagnetic spectrum. C1 [Helmlinger, Mark; Eastwood, Michael; Green, Robert; Thompson, David R.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Helmlinger, M (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Mark.C.Helmlinger@jpl.nasa.gov; Michael.L.Eastwood@jpl.nasa.gov; Robert.O.Green@jpl.nasa.gov; David.R.Thompson@jpl.nasa.gov NR 3 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 10 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374902030 ER PT S AU Hibbard, KE Mason, LS Ndu, O Smith, C Withrow, JP AF Hibbard, Kenneth E. Mason, Lee S. Ndu, Obi Smith, Clay Withrow, James P. GP IEEE TI Stirling to Flight Initiative SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB NASA has a consistent need for radioisotope power systems (RPS) to enable robotic scientific missions for planetary exploration that has been present for over four decades and will continue into the foreseeable future, as documented in the most recent Planetary Science Decadal Study Report. As RPS have evolved throughout the years, there has also grown a desire for more efficient power systems, allowing NASA to serve as good stewards of the limited plutonium-238 (Pu-238), while also supporting the ever-present need to minimize mass and potential impacts to the desired science measurements. In fact, the recent Nuclear Power Assessment Study (NPAS) released in April 2015 resulted in several key conclusion regarding RPS, including affirmation that RPS will be necessary well into the 2030s (at least) and that Pu-238 is indeed a precious resource requiring efficient utilization and preservation. Stirling Radioisotope Generators (SRGs) combine a Stirling cycle engine powered by a radioisotope heater unit into a single generator system. Stirling engine technology has been under development at NASA Glenn Research Center (GRC) in partnership with the Department of Energy (DOE) since the 1970's. The most recent design, the Pu-238-fueled Advanced Stirling Radioisotope Generator (ASRG), was offered as part of the NASA Discovery 2010 Announcement of Opportunity (AO). The Step-2 selections for this AO included two ASRG-enabled concepts, the Titan Mare Explorer (TiME) and the Comet Hopper (CHopper), although the only non-nuclear concept, InSight, was ultimately chosen. The DOE's ASRG contract was terminated in 2013. Given that SRGs utilize significantly less Pu-238 than traditional Radioisotope Thermoelectric Generators (RTGs)-approximately one quarter of the nuclear fuel, to produce similar electrical power output-they provide a technology worthy of consideration for meeting the aforementioned NASA objectives. NASA's RPS Program Office has recently investigated a new Stirling to Flight (S2F) initiative with the objective of developing a 100-500 We Stirling generator system. Additionally, a different approach is being devised for this initiative to avoid pitfalls of the past, and apply lessons learned from the recent ASRG experience. Two key aspects of this initiative are a Stirling System Technology Maturation Effort, and a Surrogate Mission Team (SMT) intended to provide clear mission pull and requirements context. The S2F project seeks to lead directly into a DOE flight system development of a new SRG. This paper will detail the proposed S2F initiative, and provide specifics on the key efforts designed to pave a forward path for bringing Stirling technology to flight. C1 [Hibbard, Kenneth E.; Ndu, Obi; Smith, Clay] Johns Hopkins Univ, Appl Phys Lab, 11100 Johns Hopkins Rd, Laurel, MD 20723 USA. [Mason, Lee S.; Withrow, James P.] Natl Aeronaut & Space Adm, Glenn Res Ctr, 21000 Brookpk Rd, Cleveland, OH 44135 USA. RP Hibbard, KE (reprint author), Johns Hopkins Univ, Appl Phys Lab, 11100 Johns Hopkins Rd, Laurel, MD 20723 USA. EM Kenneth.Hibbard@jhuapl.edu; Lee.S.Mason@nasa.gov; Obibobi.Ndu@jhuapl.edu; Clay.Smith@jhuapl.edu; James.P.Withrow@nasa.gov NR 12 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 11 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374903040 ER PT S AU Hihn, J Juster, L Johnson, J Menzies, T Michael, G AF Hihn, Jairus Juster, Leora Johnson, James Menzies, Tim Michael, George GP IEEE TI Improving and Expanding NASA Software Cost Estimation Methods SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB Estimators and analysts are increasingly being tasked to develop better models and reliable cost estimates in support of program planning and execution. While there has been extensive work on improving parametric methods for cost estimation, there is very little focus on the use of cost models based on analogy and clustering algorithms. In this paper we summarize the results of our research in developing an analogy method for estimating NASA spacecraft flight software using spectral clustering on system characteristics (symbolic non-numerical data) and evaluate its performance by comparing it to a number of the most commonly used estimation methods. The strengths and weaknesses of each method based on their performance are also discussed. The paper concludes with an overview of the analogy estimation tool (ASCoT) developed for use within NASA that implements the recommended analogy algorithm. C1 [Hihn, Jairus; Juster, Leora] CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. [Johnson, James] NASA, Washington, DC 20546 USA. [Menzies, Tim; Michael, George] North Carolina State Univ, Raleigh, NC USA. RP Hihn, J (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. NR 14 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 12 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374901063 ER PT S AU Hinkel, H Strube, M Zipay, JJ Cryan, S AF Hinkel, Heather Strube, Matthew Zipay, John J. Cryan, Scott GP IEEE TI Technology Development of Automated Rendezvous and Docking/Capture Sensors and Docking Mechanism for the Asteroid Redirect Crewed Mission SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB This paper will describe the technology development efforts NASA has underway for Automated Rendezvous and Docking/Capture (AR& D/C) sensors and a docking mechanism and the challenges involved. The paper will additionally address how these technologies will be extended to other missions requiring AR& D/C whether robotic or manned. NASA needs AR& D/C sensors for both the robotic and crewed segments of the Asteroid Redirect Mission (ARM). NASA recently conducted a commonality assessment of the concept of operations for the robotic Asteroid Redirect Vehicle (ARV) and the crewed mission segment using the Orion spacecraft. The commonality assessment also considered several future exploration and science missions requiring an AR& D/C capability. Missions considered were asteroid sample return, satellite servicing, and planetary entry, descent, and landing. This assessment determined that a common sensor suite consisting of one or more visible wavelength cameras, a three-dimensional LIDAR along with long-wavelength infrared cameras for robustness and situational awareness could be used on each mission to eliminate the cost of multiple sensor developments and qualifications. By choosing sensor parameters at build-time instead of at design-time and, without having to requalify flight hardware, a specific mission can design overlapping bearing, range, relative attitude, and position measurement availability to suit their mission requirements with minimal non-recurring engineering costs. The resulting common sensor specification provides the union of all performance requirements for each mission and represents an improvement over the current systems used for AR& D/C today. These sensor specifications are tightly coupled to the docking system capabilities and requirements for final docking conditions. The paper will describe NASA's efforts to develop a standard docking system for use across NASA human spaceflight missions to multiple destinations. It will describe the current design status and the considerations and technologies involved in developing this docking mechanism. C1 [Hinkel, Heather; Zipay, John J.; Cryan, Scott] NASA, Johnson Space Ctr, 2101 NASA Rd 1, Houston, TX 77058 USA. [Strube, Matthew] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Hinkel, H (reprint author), NASA, Johnson Space Ctr, 2101 NASA Rd 1, Houston, TX 77058 USA. EM heather.hinkel-1@nasa.gov; matthew.j.strube@nasa.gov; john.j.zipay@nasa.gov; scott.p.cryan@nasa.gov NR 5 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 8 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374901045 ER PT S AU Hoffman, J AF Hoffman, Jim GP IEEE TI Modular Ku/Ka-Band Actively Calibrated Antenna Tile SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB This work attempts to leverage the very successful development of a beamforming architecture into a scalable solution suitable for multiple types of instrument platforms. This paper details the ongoing development of a modular dual-band active antenna tile, with the primary intended use in airborne and small platform space applications for radar remote sensing. A secondary objective is to develop the modular tile, such that it will be used as the basis for a building block required for a future spaceborne instrument, reducing instrument cost and mission risk. The actual development of such a spaceborne mission is likely + 10 years out, so we are focusing current efforts on developing this technology to fill the science gap, while the community waits for the more global coverage of an orbiting instrument. An airborne instrument is an asset regardless of an orbital instrument, as evidenced by the success of UAVSAR. C1 [Hoffman, Jim] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Hoffman, J (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM James.P.Hoffman@jpl.nasa.gov NR 6 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 6 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374904035 ER PT S AU Hogie, K Flanders, B Paulson, D Zarembowitch, A Safavi, H Lubelczyk, J AF Hogie, Keith Flanders, Bruce Paulson, Daniel Zarembowitch, Alain Safavi, Haleh Lubelczyk, Jeffry GP IEEE TI Low-cost Receiver Development for TDRSS DAS Sustainment and CubeSat Applications SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB Tracking and Data Relay Satellite System (TDRSS) Demand Access System (DAS) sustainment is aimed at modernizing the existing DAS using low-cost hardware components as well as a more robust monitor and control architecture. A key part of the system is the DAS receiver, which supports the Pseudo Noise (PN) modulation waveforms of the TDRSS. The receiver in the current DAS system is a custom design that has been increasingly difficult to maintain, due to hardware obsolescence and a lack of sufficient inventory of spare units. In addition, the receivers suffer from performance issues, which tend to limit the customer base subscribing to the DAS service. The DAS sustainment effort attempts to rectify the performance shortfall of the current receiver and address hardware obsolescence by making software portability a key design goal. As part of the DAS sustainment effort, two low-cost receivers were developed: one of them based on a commercial spread-spectrum receiver implemented on a Field Programmable Gate Array (FPGA), and the other a Software Defined Radio (SDR) implemented on a server class computer. The two receiver prototypes underwent extensive testing in a laboratory environment as well as on-air testing with orbiting customers. Receiver design details and test results are presented. The potential usages of such TDRSS compatible, low cost and small footprint of receivers in CubeSat are discussed. C1 [Hogie, Keith] Comp Sci Corp, 12401 Mt Pleasant Dr, Laurel, MD 20708 USA. [Flanders, Bruce; Paulson, Daniel] Harris Corp, 7855 Walker Dr, Greenbelt, MD 20770 USA. [Zarembowitch, Alain] Mobile Satellite Serv, 845-N Quince Orchard Blvd, Gaithersburg, MD 20878 USA. [Safavi, Haleh; Lubelczyk, Jeffry] NASA GSFC, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. RP Hogie, K (reprint author), Comp Sci Corp, 12401 Mt Pleasant Dr, Laurel, MD 20708 USA. EM Keith.Hogie@nasa.gov; Bruce.Flanders@harris.com; Daniel.A.Paulson@nasa.gov; info@comblock.com; Haleh.Safavi@nasa.gov; Jeffrey.T.Lubelczyk@nasa.gov NR 0 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 7 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374902069 ER PT S AU Hook, LR Clark, M Sizoo, D Skoog, MA Brady, J AF Hook, Loyd R. Clark, Matthew Sizoo, David Skoog, Mark A. Brady, James GP IEEE TI Certification strategies using run-time safety assurance for part 23 autopilot systems SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB Part 23 aircraft operation, and in particular general aviation, is relatively unsafe when compared to other common forms of vehicle travel. Currently, there exists technologies that could increase safety statistics for these aircraft; however, the high burden and cost of performing the requisite safety critical certification processes for these systems limits their proliferation. For this reason, many entities, including the Federal Aviation Administration, NASA, and the US Air Force, are considering new options for certification for technologies which will improve aircraft safety. Of particular interest, are low cost autopilot systems for general aviation aircraft, as these systems have the potential to positively and significantly affect safety statistics. This paper proposes new systems and techniques, leveraging run-time verification, for the assurance of general aviation autopilot systems, which would be used to supplement the current certification process and provide a viable path for near-term low-cost implementation. In addition, discussions on preliminary experimentation and building the assurance case for a system, based on these principles, is provided. C1 [Hook, Loyd R.] Univ Tulsa, ECE Dept, 800 S Tucker Dr,Rayzor 1130, Tulsa, OK 74104 USA. [Clark, Matthew] Air Force Res Lab, 2210 Eighth St, Wright Patterson AFB, OH 45433 USA. [Sizoo, David; Brady, James] Small Airplane Directorate, FAA Aircraft Certificat Serv, 901 Locust St, Kansas City, MO 64106 USA. [Skoog, Mark A.] NASA, Armstrong Flight Res Ctr, POB 273,MS 4830E, Edwards AFB, CA 93523 USA. RP Hook, LR (reprint author), Univ Tulsa, ECE Dept, 800 S Tucker Dr,Rayzor 1130, Tulsa, OK 74104 USA. EM Loyd-hook@utulsa.edu; Matthew.clark.20@us.af.mil; David.sizoo@faa.gov; Mark.a.skoog@nasa.gov; James.brady@faa.gov NR 14 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 10 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374903039 ER PT S AU Horner, MD Eremenko, A AF Horner, Matthew D. Eremenko, Alexander GP IEEE TI Europa Spacecraft Configuration Optimization for the Solar Powered Vehicle SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB A mission to Europa has been on the minds of NASA and JPL for many years. After the Galileo mission to Jupiter in the 1990s there have been various proposals for missions to the Jovian moon. The most recent proposal, previously named the Europa Clipper, has gone through numerous iterations of spacecraft configurations on its road to becoming an official NASA project in June of 2015. Most of these configurations included options for either multi-mission radioisotope thermoelectric generators (MMRTGs) or solar power. In 2014, the decision was made to focus on solar arrays as the source for spacecraft power. The decision to move forward with a baseline design that utilized only solar arrays as its power system meant that some configuration choices had to be reevaluated. Initially, a configuration was adapted to keep as much of the previous spacecraft design the same while replacing MMRTGs with solar panels. This proved to be difficult as the arrays presented a slew of new challenges that the nuclear vehicle was not optimized for. The solar arrays needed to be large due to Jupiter's substantial distance from the Sun. This meant that many of the instrument and radiator FOVs would now be obstructed, or would receive reflected light and heat from the large panels. Also, the mass of the panels meant that mounting near the bottom of the spacecraft would be sub-optimal as the wings would cause major disturbance to the vehicle as they oscillated in their deployed state. Another major, and possibly the largest, concern was the fact that as the high gain antenna pointed to Earth for communication, the Ice Penetrating Radar (IPR) would cast a large shadow on the cell-side of the array. This resulted in an estimated 10% power loss to the vehicle. On top of all this, NASA announced the selection of the instruments that would fly on the Europa mission and replace the notional instrument suite that had been used to develop and submit the project proposal. The selected instruments, while not varying widely from the notional suite, did come with a new set of challenges including a size increase over the notional package, thus requiring more room for accommodation. They also introduced new features not previously addressed by the notional package, such as a two-axis gimbal on one of the imagers. Additionally, two new instruments, an ultraviolet plume-hunting spectrograph, and an atmospheric dust analyzer we added to the payload and presented new challenges not previously covered in the proposal. Finally, additional payloads were under consideration, such as a 250kg ejectable payload that would be released at Jupiter and would accomplish flybys of some of the other Jovian moons. All of this resulted in a drastically different "family" of configurations that were capable of addressing these issues, and staying flexible to the numerous potential changes that could come. This paper discusses the details of the various configurations considered to address these items, and the configuration concepts that were selected as the baseline for moving forward with the proposal. C1 [Horner, Matthew D.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,M-S 303-410, Pasadena, CA 91109 USA. [Eremenko, Alexander] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,M-S 303-422, Pasadena, CA 91109 USA. RP Horner, MD (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,M-S 303-410, Pasadena, CA 91109 USA. EM mhorner@jpl.nasa.gov; Alexander.E.Eremenko@jpl.nasa.gov NR 2 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 10 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374903032 ER PT S AU Howe, AS Wilcox, B AF Howe, A. Scott Wilcox, Brian GP IEEE TI Outpost Assembly using the ATHLETE Mobility System SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB A planetary surface outpost will likely consist of elements delivered on multiple manifests, that will need to be assembled from a scattering of landings. Using the All-Terrain Hex-Limbed Extra-Terrestrial Explorer (ATHLETE) limbed robotic mobility system, the outpost site can be prepared in advance through leveling, paving, and in-situ structures. ATHLETE will be able to carry pressurized and non-pressurized payloads overland from the lander descent stage to the outpost location, and perform precision docking and assembly of components. In addition, spent descent stages can be carried to assembly locations to form elevated decks for external work platforms above the planet surface. This paper discusses several concepts that have been studied for possible inclusion in the NASA Evolvable Mars Campaign human exploration mission scenarios. C1 [Howe, A. Scott; Wilcox, Brian] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Howe, AS (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM a.scott.howe@jpl.nasa.gov; brian.h.wilcox@jpl.nasa.gov NR 19 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 9 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374903016 ER PT S AU Ianson, EE Komar, GJ Murphy, K Yuhas, C AF Ianson, Eric E. Komar, George J. Murphy, Kevin Yuhas, Cheryl GP IEEE TI NASA's Earth Science Flight Program Meets the Challenges of Today and Tomorrow SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB The National Aeronautics and Space Administration (NASA) Earth science flight program is a dynamic undertaking that consists of a large fleet of operating satellites, an array of satellite and instrument projects in various stages of development, a robust airborne science program, and a massive data archiving and distribution system. Each element of the flight program is complex and presents unique challenges. NASA builds upon its successes and learns from its setbacks to manage this evolving portfolio to meet NASA's Earth science objectives. NASA fleet of 19 operating missions provides a wide range of scientific measurements obtained from dedicated Earth science satellites and from instruments mounted to the International Space Station (ISS). Projects in development are divided into two broad categories: systematic missions and pathfinders. The Earth Systematic Missions (ESM) program includes a range of multi-disciplinary Earth-observing research satellite missions aimed at understanding the Earth system and its response to natural and human-induced forces and changes. The Earth System Science Pathfinder (ESSP) program provides frequent, regular, competitively selected Earth science research opportunities that accommodate new and emerging scientific priorities and measurement capabilities. The Earth Science Airborne Science Program provides manned and unmanned aircraft systems that further science and advance the use of satellite data. NASA uses these assets worldwide in campaigns to investigate extreme weather events, observe Earth system processes, obtain data for Earth science modeling activities, test and refine new instrument technologies, and calibrate instruments flying aboard Earth science spacecraft. Through the Earth Observing System Data and Information System (EOSDIS) NASA's Earth Science Division acquires, preserves, and distributes observational data from operating spacecraft to support Earth Science research focus areas. In addition, the Earth science flight program benefits from investments by the Earth Science Technology Office (ESTO) to develop and demonstrate cutting-edge technologies that can be reliably applied to the diverse needs of future NASA Earth science measurements and mission. NASA's current Earth Science portfolio is responsive to national scientific priorities. As the program evolves into the future, it will leverage the lessons learned from the current missions in operations and development, and plan for adjustments to future objectives in response to the needs of the United States and the Earth science community. C1 [Ianson, Eric E.; Murphy, Kevin; Yuhas, Cheryl] NASA Headquarters, 300 E St SW, Washington, DC 20546 USA. [Komar, George J.] NASA, Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. RP Ianson, EE (reprint author), NASA Headquarters, 300 E St SW, Washington, DC 20546 USA. EM eianson@nasa.gov; george.komar@nasa.gov; kevin.j.murphy@nasa.gov; cheryl.l.yuhas@nasa.gov NR 6 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 12 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374902080 ER PT S AU Inoue, H Ono, M Tamaki, S Adachi, S AF Inoue, Hiroka Ono, Masahiro Tamaki, Sakurako Adachi, Shuichi GP IEEE TI Active Localization for Planetary Rovers SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB This paper presents a path planning algorithm to reduce localization error by intelligently choosing a path that will result in low expected sensor errors. For example, Mars rovers can enhance localization accuracy by selectively driving over feature-rich terrain where visual odometry can be used. In general, having an accurate localization is vital for autonomous mobile exploration platforms such as rovers and aerial vehicles. However, typical path planning methods tend to narrowly focus on minimizing path length. Our proposed path planning algorithm, namely Error Propagation A*(EPA*), intelligently balances path length and localization. EPA* is a graph search algorithm, where a linear error propagation law is derived before the search on each edge of the graph. Using the propagation law, EPA* can quickly find a path that minimizes a given objective function, which includes both path length and error covariance. We demonstrate the EPA* algorithm using the real data from Curiosity. The result demonstrates that the EPA* algorithm can find a path that balances the path length and the expected localization error, as expected. C1 [Inoue, Hiroka; Tamaki, Sakurako; Adachi, Shuichi] Keio Univ, Dept Appl Phys & Physicoinformat, Yokohama, Kanagawa, Japan. [Ono, Masahiro] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Inoue, H (reprint author), Keio Univ, Dept Appl Phys & Physicoinformat, Yokohama, Kanagawa, Japan. EM hiroka_inoue@keio.jp; Masahiro.Ono@jpl.nasa.gov; jennifer.m@keio.jp; adachi@appi.keio.ac.jp NR 9 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 7 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374901008 ER PT S AU Ismail, MAA Balaban, E Spangenberg, H AF Ismail, Mohamed A. A. Balaban, Edward Spangenberg, Holger GP IEEE TI Fault Detection and Classification for Flight Control Electromechanical Actuators SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB Future aircraft architectures will incorporate more energy-efficient electromechanical actuators (EMA) for flight controls actuation. Development of reliable health monitoring techniques for EMAs promises to maintain or even increase the overall availability and safety of these new aircraft designs. When it comes to EMAs and similar mechanisms, certain fault types clearly manifest themselves through loss of functionality. Other faults, referred to as latent, do not immediately result in a significantly compromised actuator performance, thus making them challenging to detect. This paper presents a new vibration-based hybrid technique for detecting latent EMA faults without needing an initial stage of fault feature learning. The two faults considered in the study are a high-criticality jam and a low-criticality spall (metal flaking) in the actuator ballscrew mechanism. The actuator position is used to resample variable-speed vibration measurements of a single accelerometer into constant-rate measurements. A set of health characterization signatures is derived theoretically based on the EMA ballscrew kinematics. These theoretical signatures are compared with the signatures extracted from vibration signals measured experimentally on the EMA test articles. The vibration signatures approach is also compared to the diagnostic approach based on EMA motor current measurements. The ability to detect and classify latent faults early as high-or low-critical can improve maintenance planning and increase aircraft dispatch reliability. The technique has been validated on fault-injected data sets collected on the NASA Ames Research Center Flyable Electro-Mechanical Actuator (FLEA) test stand. C1 [Ismail, Mohamed A. A.; Spangenberg, Holger] DLR German Aerosp Ctr, Inst Flight Syst, D-38108 Braunschweig, Germany. [Balaban, Edward] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Ismail, MAA (reprint author), DLR German Aerosp Ctr, Inst Flight Syst, D-38108 Braunschweig, Germany. EM Mohamed.Ismail@dlr.de; Edward.Balaban@nasa.gov; Holger.Spangenberg@dlr.de NR 16 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 10 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374903006 ER PT S AU Israel, DJ Heckler, GW Menrad, RJ AF Israel, David J. Heckler, Gregory W. Menrad, Robert J. GP IEEE TI Space Mobile Network: A Near Earth Communications and Navigation Architecture SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB This paper shares key findings of NASA's Earth Regime Network Evolution Study (ERNESt) team resulting from its 18-month effort to define a wholly new architecture-level paradigm for the exploitation of space by civil space and commercial sector organizations. Since the launch of Sputnik in October 1957 spaceflight missions have remained highly scripted activities from launch through disposal. The utilization of computer technology has enabled dramatic increases in mission complexity; but, the underlying premise that the diverse actions necessary to meet mission goals requires minute-by-minute scripting, defined weeks in advance of execution, for the life of the mission has remained. This archetype was appropriate for a "new frontier" but now risks overtly constraining the potential market-based opportunities for the innovation considered necessary to efficiently address the complexities associated with meeting communications and navigation requirements projected to be characteristics of the next era of space exploration: a growing number of missions in simultaneous execution, increased variance of mission types and growth in location/ orbital regime diversity. The resulting ERNESt architectural cornerstone - the Space Mobile Network (SMN) - was envisioned as critical to creating an environment essential to meeting these future challenges in political, programmatic, technological and budgetary terms. The SMN incorporates technologies such as: Disruption Tolerant Networking (DTN) and optical communications, as well as new operations concepts such as User Initiated Services (UIS) to provide user services analogous to today's terrestrial mobile network user. Results developed in collaboration with NASA's Space Communications and Navigation (SCaN) Division and field centers are reported on. Findings have been validated via briefings to external focus groups and initial ground-based demonstrations. The SMN opens new niches for exploitation by the marketplace of mission planners and service providers. C1 [Israel, David J.; Menrad, Robert J.] NASA, GSFC, Code 450, Greenbelt, MD 20771 USA. [Heckler, Gregory W.] NASA, GSFC, Code 566, Greenbelt, MD 20771 USA. RP Israel, DJ (reprint author), NASA, GSFC, Code 450, Greenbelt, MD 20771 USA. EM dave.israel@nasa.gov; gregory.w.heckler@nasa.gov; robert.j.menrad@nasa.gov NR 6 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 7 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374901077 ER PT S AU Jackson, M Wilkerson, M AF Jackson, Maddalena Wilkerson, Marcus GP IEEE TI MBSE-driven Visualization of Requirements Allocation and Traceability SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB In a Model Based Systems Engineering (MBSE) infusion effort, there is a usually a concerted effort to define the information architecture, ontologies, and patterns that drive the construction and architecture of MBSE models, but less attention is given to the logical follow-on of that effort: how to practically leverage the resulting semantic richness of a well-formed populated model to enable systems engineers to work more effectively, as MBSE promises. While ontologies and patterns are absolutely necessary, an MBSE effort must also design and provide practical demonstration of value (through human-understandable representations of model data that address stakeholder concerns) or it will not succeed. This paper will discuss opportunities that exist for visualization in making the richness of a well-formed model accessible to stakeholders, specifically stakeholders who rely on the model for their day-to-day work. This paper will discuss the value added by MBSE-driven visualizations in the context of a small case study of interactive visualizations created and used on NASA's proposed Europa Mission. The case study visualizations were created for the purpose of understanding and exploring targeted aspects of requirements flow, allocation, and comparing the structure of that flow-down to a conceptual project decomposition. The work presented in this paper is an example of a product that leverages the richness and formalisms of our knowledge representation while also responding to the quality attributes SEs care about. C1 [Jackson, Maddalena; Wilkerson, Marcus] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Jackson, M (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM mjackson@jpl.nasa.gov; Marcus.Wilkerson@jpl.nasa.gov NR 7 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 17 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374901002 ER PT S AU Jackson, M Wilkerson, M Castet, JF AF Jackson, Maddalena Wilkerson, Marcus Castet, Jean-Francois GP IEEE TI Exposing Hidden Parts of the SE Process: MBSE Patterns and Tools for Tracking and Traceability SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB An interesting benefit of applying Model-Based Systems Engineering (MBSE) is that the rigor and coordination intrinsic to MBSE forces us to apply Systems Engineering to our own traditional activities, processes, and products, which results in richer, more expressive models, more powerful reasoning, and a clearer and more effective Systems Engineering (SE) process. Our MBSE frameworks and languages contain semantic richness sufficient to describe our systems at any particular point in time, often with an emphasis on the description of the system at major milestones. This is unarguably a real asset. However, when we apply MBSE in service of missions that are in development, rapidly evolving, of a larger scale, and where interpersonal communication is a critical part of the design process, we discover that our frameworks and languages are still not quite rich enough to enable us to ask the kinds of questions and get the kinds of answers we want in order to address the concerns of day to day work. This paper will discuss some patterns and tools we have developed to help address some of the not-always-explicit SE concerns that we have identified through our MBSE work. Particularly, this paper will discuss flexible yet practical methods for defining and capturing maturity, workflow, and agreement traceability within our system models, extensible ways to perform and track model audits, and ways to report and interact with this knowledge in the context of MBSE applied to support NASA's Europa Project. C1 [Jackson, Maddalena; Wilkerson, Marcus; Castet, Jean-Francois] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Jackson, M (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM mjackson@jpl.nasa.gov; Marcus.Wilkerson@jpl.nasa.gov; castet@jpl.nasa.gov NR 5 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 12 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374901003 ER PT S AU Jansma, PA Grogan, K Harris, I AF Jansma, P. A. Trisha Grogan, Keith Harris, Ian GP IEEE TI Scientist-Engineering Interactions across the Project Lifecycle SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB The roles and responsibilities of a Principal Investigator (PI) and/or Project Scientist (PS) and the Project Systems Engineer (PSE) on a NASA mission change across the project lifecycle, as do the nature and focus of their interactions. There are also interactions between the Investigation Scientist (IS) and the Payload System Engineer (PLSE) and Flight System Systems Engineer (FSSE). In order to achieve the best results for the mission, the interactions between the science community and the engineering community need to be rich, focused and frequent. In this paper, the author describes the roles and responsibilities of the PI, PS, IS, PSE, PLSE and FSSE, and the nature of the interactions between them in each phase of the lifecycle. She also describes the primary focus of each role in each phase, and gives specific examples and anecdotes of how solid interactions addressed key issues in a timely, productive manner. The paper concludes with some insights and recommendations for scientist-engineering interactions. C1 [Jansma, P. A. Trisha; Grogan, Keith; Harris, Ian] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,M-S 301-490, Pasadena, CA 91109 USA. RP Jansma, PA (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,M-S 301-490, Pasadena, CA 91109 USA. EM Patti.A.Jansma@jpl.nasa.gov; Keith.Grogan@jpl.nasa.gov; Ian.L.Harris@jpl.nasa.gov NR 18 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 13 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374903004 ER PT S AU Jansma, PA AF Jansma, P. A. Trisha GP IEEE TI How's That Change Working for You? SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB Major change initiatives must address three aspects of change in order to be successful - people, process, and technology. In addition, any change initiative needs to be actively aided by three important support components: Organizational Change Management (OCM), Customer Relationship Management (CRM), and a repeatable Deployment Process. This paper describes the three key aspects of change, their support components and how to apply them. It also describes a four-part deployment process to employ once a new product or asset has been created. It describes how this approach has been used to successfully deploy several major change initiatives at JPL and NASA, and concludes with some lessons learned. C1 [Jansma, P. A. Trisha] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr MS 301-490, Pasadena, CA 91109 USA. RP Jansma, PA (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr MS 301-490, Pasadena, CA 91109 USA. EM Patti.A.Jansma@jpl.nasa.gov NR 32 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 13 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374900093 ER PT S AU Johnson, JE Spry, JA Race, MS Conley, CA Siegel, B AF Johnson, James E. Spry, J. Andy Race, Margaret S. Conley, Catherine A. Siegel, Bette GP IEEE TI NASA's Path to Planetary Protection Requirements for Human Exploration Missions: Update on Recent Progress SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB NASA's Office of Planetary Protection (OPP) and Human Exploration and Operations Directorate (HEOMD) have been working collaboratively for the past several years to develop planetary protection requirements for future human missions to Mars. While implementable planetary protection requirements are in place for robotic missions, there is presently insufficient scientific and technological knowledge to establish effective quantitative requirements for the development of crewed spacecraft and missions to Mars or other habitable locations. Such requirements are needed to ensure that future human missions are in compliance with both the Outer Space Treaty and current principles and guidelines set by the Committee on Space Research (COSPAR). In preparation for eventual future crewed missions, in 2014 NASA released the NASA Policy Instruction on Planetary Protection Requirements for Human Extraterrestrial Missions (NPI 8020.7) which outlines a stepwise process going forward, and also identifies the need to increase knowledge in a number of areas in order to develop an appropriate set of future requirements. Three particular thematic areas of importance are: Microbial & human health monitoring; Technology and operations for contamination control; and Natural transport of contamination on Mars. This paper provides an overview of recent progress on the path towards eventual development of NASA'S planetary protection requirements (to be released in one or more NASA Procedural Requirements documents (NPRs), focusing on both science research and technology needs for human missions. Under the NPI to date, a literature survey and analysis was undertaken to gather background information and provide input to the subsequent conduct of a special Workshop on Planetary Protection Knowledge Gaps for Human Extraterrestrial Missions, which was held at NASA Ames Research Center, March 24-26, 2015. Both the literature review and the workshop focused on the three aforementioned thematic areas related to planetary protection and the cross-cutting nature of planetary protection for future human missions, information about both the literature review and the workshop is summarized here so members of diverse technical and engineering communities may stay aware of recent updates in planetary protection information of relevance to their work, particularly in areas related to natural and technological approaches to controlling and mitigating contamination. C1 [Johnson, James E.] NASA, Johnson Space Ctr, 2101 NASA Pkwy, Houston, TX 77058 USA. [Spry, J. Andy; Race, Margaret S.] SETI Inst, 189 Bernardo Ave, Mountain View, CA 94043 USA. [Conley, Catherine A.] NASA Headquarters OPP, 300 E St SW, Washington, DC 20546 USA. [Siegel, Bette] NASA Headquarters HEOMD, 300 E St SW, Washington, DC 20546 USA. RP Johnson, JE (reprint author), NASA, Johnson Space Ctr, 2101 NASA Pkwy, Houston, TX 77058 USA. EM james.e.johnson@nasa.gov; aspry@seti.org; mrace@seti.org; cassie.conley@nasa.gov; bette.siegel@nasa.gov NR 14 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 8 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374903059 ER PT S AU Johnston, MD Zurek, RW AF Johnston, M. Daniel (Dan) Zurek, Richard W. GP IEEE TI The Mars Reconnaissance Orbiter Mission: 10 Years of Exploration from Mars Orbit SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE ID CLIMATE SOUNDER; ICE AB The Mars Reconnaissance Orbiter (MRO) entered Mars orbit on March 10, 2006. After five months of aerobraking, a series of propulsive maneuvers were used to establish the desired low-altitude science orbit. The spacecraft has been on station in its 255 x 320 km, sun-synchronous (similar to 3 am-pm), primary science orbit since September 2006 performing both scientific and Mars programmatic support functions. This paper will provide a summary of the major achievements of the mission to date and the major flight activities planned for the remainder of its third Extended Mission (EM3). Some of the major flight challenges the flight team has faced are also discussed. C1 [Johnston, M. Daniel (Dan); Zurek, Richard W.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Johnston, MD (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Martin.D.Johnston@jpl.nasa.gov; Richard.W.Zurek@jpl.nasa.gov NR 22 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 13 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374900053 ER PT S AU Jones, DL Folkner, WM Jacobson, RA Jacobs, CS Romney, JD Dhawan, V Fomalont, E AF Jones, Dayton L. Folkner, William M. Jacobson, Robert A. Jacobs, Christopher S. Romney, Jonathan D. Dhawan, Vivek Fomalont, Ed GP IEEE TI Radio Astrometry of the Cassini Spacecraft with the Very Long Baseline Array SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB The planetary ephemeris is a fundamental tool of astronomy that is essential for dynamical studies of the solar system, pulsar timing, tests of general relativity, occultation and eclipse predictions, and interplanetary spacecraft navigation. Since Jupiter and Saturn dominate the dynamics of our solar system, improved knowledge of their orbits will result in a global improvement in the accuracy of the ephemeris. The Cassini spacecraft has been orbiting Saturn for over a decade, a third of Saturn's orbital period. This has provided an unprecedented opportunity to improve all components of Saturn's orbit by combining periodic very long baseline inferterometry (VLBI) measurements of Cassini's sky position with respect to background radio sources, which in turn can be tied to the inertial International Celestial Reference Frame (ICRF). The orbit of Cassini about the center of mass of Saturn is determined from Doppler tracking by the Deep Space Network. Combining these observations, we obtain the barycenter position of the Saturn system in an inertial frame at multiple epochs, with typical uncertainties of 0.3 milli-arcseconds in right ascension and 0.4 milli-arcseconds in declination. These results are then provided to JPL's ephemeris group for inclusion in future ephemeris solutions. At most epochs the largest component of the error budget is uncertainty in the ICRF position of the phase reference radio source used. These source positions are being continuously improved through additional VLBI observations. These VLBA observations have improved our knowledge of Saturn's orbit by nearly an order of magnitude. This technique will be expanded to include astrometric observations of the Juno spacecraft as soon as it enters Jupiter orbit in mid-2016. Although the orbital phase of the Juno mission is expected to last only a bit over one year, it will still allow a significant improvement in Jupiter's orbit. Previous missions to Jupiter have been single-epoch flybys with the exception of Galileo, for which the accuracy of VLBI position measurements was severely limited by failure of the high gain antenna. The Juno mission is scheduled to end in February 2018, five months after the scheduled end of the Cassini mission. At the ends of their missions the Juno and Cassini spacecraft will be destroyed in the atmospheres of Jupiter and Saturn to eliminate the possibility of a future crash onto any of the liquid-containing moons of these planets that may be habitats of life. C1 [Jones, Dayton L.] Space Sci Inst, 4750 Walnut St,Suite 205, Boulder, CO 80301 USA. [Folkner, William M.; Jacobson, Robert A.; Jacobs, Christopher S.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Romney, Jonathan D.; Dhawan, Vivek] Natl Radio Astron Observ, POB 0, Socorro, NM 87801 USA. [Fomalont, Ed] Natl Radio Astron Observ, 520 Edgemont Rd, Charlottesville, VA 22903 USA. RP Jones, DL (reprint author), Space Sci Inst, 4750 Walnut St,Suite 205, Boulder, CO 80301 USA. EM djones@spacescience.org; william.m.folkner@jpl.nasa.gov; jromney@aoc.nrao.edu; vdhawan@aoc.nrao.edu; efomalon@nrao.edu NR 15 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 7 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374900023 ER PT S AU Karp, AC Redmond, M Nakazono, B Vaughan, D Shotwell, R Story, G Jackson, D Young, D AF Karp, Ashley C. Redmond, Matt Nakazono, Barry Vaughan, David Shotwell, Robert Story, George Jackson, Dale Young, David GP IEEE TI Technology Development and Design of a Hybrid Mars Ascent Vehicle Concept SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB Hybrid propulsion has been investigated as an enhancing technology for a Mars Ascent Vehicle (MAV) concept as part of potential Mars Sample Return (MSR) because of its high specific impulse, restartability, and the ability to operate and survive at extremely low temperatures. A new wax-based hybrid fuel formulation has been developed that could withstand the harsh and variable Mars environment protected solely by a minimal layer of passive insulation. This formulation could provide substantial energy savings for a notional lander and is critical for rover mobility. Preliminary thermal cycle testing has determined that the formulation can survive the expected temperature extremes and lifetime thermal testing is currently underway. A complete preliminary design using this new fuel formulation combined with a low temperature oxidizer such as Mixed Oxides of Nitrogen (MON30) is presented. Several key features associated with a complete hybrid MAV concept are investigated to determine their mission suitability (e.g. Thrust Vector Control and restartable ignition options). Potential challenges along a path towards developing such a system are outlined and future work is suggested as a means of technology maturation. The hybrid design presented here was the lowest Gross Lift Off Mass (GLOM) result of a 2015 Jet Propulsion Laboratory (JPL) led MAV concept study [1]. C1 [Karp, Ashley C.; Redmond, Matt; Nakazono, Barry; Vaughan, David; Shotwell, Robert] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Story, George; Jackson, Dale; Young, David] Marshall Space Flight Ctr, Huntsville, AL 35811 USA. RP Karp, AC (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Ashley.C.Karp@jpl.nasa.gov; Matthew.J.Redmond@jpl.nasa.gov; Barry.Nakazono@jpl.nasa.gov; David.A.Vaughan@jpl.nasa.gov; Robert.F.Shotwell@jpl.nasa.gov; Geroge.Story@nasa.gov; Dale.A.Jackson@nasa.gov; David.T.Young@nasa.gov NR 22 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 10 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374903057 ER PT S AU Kellogg, R Bitten, R Mahr, E Holloman, S Roeum, V AF Kellogg, Robert Bitten, Robert Mahr, Eric Holloman, Sherrica Roeum, Voleak GP IEEE TI An Independent Cost and Schedule Estimate Process for NASA Science Projects SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB As a result of policy changes in 2009, NASA Headquarters mandated that projects must be budgeted using probabilistic cost and schedule estimating. As a response to this requirement, NASA's Science Mission Directorate (SMD) asked The Aerospace Corporation to use their estimating methodology to assess missions at project milestones. This paper describes the cost and schedule estimate processes used by Aerospace at KDP-C, when the agency commitments are established. Key unique features will be described including the use of multiple cost estimates for all WBS elements and an emphasis on analogy-based estimates for both cost and schedule. A comparison of the estimates with the as-launched development costs and schedules for 14 projects with launch dates from 2007 to 2013 will also be presented. C1 [Kellogg, Robert; Bitten, Robert; Mahr, Eric] Aerosp Corp, 2310 E El Segundo Blvd, El Segundo, CA 90245 USA. [Holloman, Sherrica] Aerosp Corp, 2011 Crystal Dr,Suite 900, Arlington, VA 22202 USA. [Roeum, Voleak] NASA Headquarters, 300 E St SW, Washington, DC 20546 USA. RP Kellogg, R (reprint author), Aerosp Corp, 2310 E El Segundo Blvd, El Segundo, CA 90245 USA. EM robert.c.kellogg@aero.org; robert.e.bitten@aero.org; eric.m.mahr@aero.org; sherrica.s.holloman@aero.org; vroeum@nasa.gov NR 9 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 11 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374904025 ER PT S AU Kerczewski, RJ Wilson, JD Bishop, WD AF Kerczewski, Robert J. Wilson, Jeffrey D. Bishop, William D. GP IEEE TI UAS CNPC Satellite Link Performance - Sharing Spectrum with Terrestrial Systems SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB In order to provide for the safe integration of unmanned aircraft systems into the National Airspace System, the control and non-payload communications (CNPC) link connecting the ground-based pilot with the unmanned aircraft must be highly reliable. A specific requirement is that it must operate using aviation safety radiofrequency spectrum. The 2012 World Radiocommunication Conference (WRC-12) provided a potentially suitable allocation for radio line-of-sight (LOS), terrestrial based CNPC link at 5030-5091 MHz. For a beyond radio line-of-sight (BLOS), satellite-based CNPC link, aviation safety spectrum allocations are currently inadequate. Therefore, the 2015 WRC will consider the use of Fixed Satellite Service (FSS) bands to provide BLOS CNPC under Agenda Item 1.5. This agenda item requires studies to be conducted to allow for the consideration of how unmanned aircraft can employ FSS for BLOS CNPC while maintaining existing systems. Since there are terrestrial Fixed Service systems also using the same frequency bands under consideration in Agenda Item 1.5 one of the studies required considered spectrum sharing between earth stations on-board unmanned aircraft and Fixed Service station receivers. Studies carried out by NASA have concluded that such sharing is possible under parameters previously established by the International Telecommunications Union. As the preparation for WRC-15 has progressed, additional study parameters Agenda Item 1.5 have been proposed, and some studies using these parameters have been added. This paper examines the study results for the original parameters as well as results considering some of the more recently proposed parameters to provide insight into the complicated process of resolving WRC-15 Agenda Item 1.5 and achieving a solution for BLOS CNPC for unmanned aircraft. C1 [Kerczewski, Robert J.; Wilson, Jeffrey D.] NASA, Glenn Res Ctr, 21000 Brookpark Rd,MS 54-1, Cleveland, OH 44135 USA. [Bishop, William D.] Jacobs Engn, FNS, 21000 Brookpark Rd,MS 54-1, Cleveland, OH 44135 USA. RP Kerczewski, RJ (reprint author), NASA, Glenn Res Ctr, 21000 Brookpark Rd,MS 54-1, Cleveland, OH 44135 USA. EM rkerczewski@nasa.gov; jeffrey.d.wilson@nasa.gov; william.d.bishop@nasa.gov NR 7 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 9 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374902055 ER PT S AU Kilcoyne, DK Headley, WC Leffke, ZJ Rowe, SA Mortensen, DJ Reinhart, RC McGwier, RW AF Kilcoyne, Deirdre K. Headley, William C. Leffke, Zach J. Rowe, Sonya A. Mortensen, Dale J. Reinhart, Richard C. McGwier, Robert W. GP IEEE TI Link Adaptation for Mitigating Earth-to-Space Propagation Effects on the NASA SCaN Testbed SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE ID STRATEGIES; SYSTEMS AB In Earth-to-Space communications, well-known propagation effects such as path loss and atmospheric loss can lead to fluctuations in the strength of the communications link between a satellite and its ground station. Additionally, the typically unconsidered effect of shadowing due to the geometry of the satellite and its solar panels can also lead to link degradation. As a result of these anticipated channel impairments, NASA's communication links have been traditionally designed to handle the worst-case impact of these effects through high link margins and static, lower rate, modulation formats. The work presented in this paper aims to relax these constraints by providing an improved trade-off between data rate and link margin through utilizing link adaptation. More specifically, this work provides a simulation study on the propagation effects impacting NASA's SCaN Testbed flight software-defined radio (SDR) as well as proposes a link adaptation algorithm that varies the modulation format of a communications link as its signal-to-noise ratio fluctuates. Ultimately, the models developed in this work will be utilized to conduct real-time flight experiments on-board the NASA SCaN Testbed. C1 [Kilcoyne, Deirdre K.; Headley, William C.; Leffke, Zach J.; Rowe, Sonya A.; McGwier, Robert W.] Virginia Tech, Hume Ctr, 1991 Kraft Dr, Blacksburg, VA 24061 USA. [Mortensen, Dale J.; Reinhart, Richard C.] NASA, Glenn Res Ctr, 21000 Brookpk Rd, Cleveland, OH 44135 USA. RP Kilcoyne, DK (reprint author), Virginia Tech, Hume Ctr, 1991 Kraft Dr, Blacksburg, VA 24061 USA. EM dkilcoyne@vt.edu; cheadley@vt.edu; zleffke@vt.edu; sarowe@vt.edu; dale.mortensen@nasa.gov; richard.c.reinhart@nasa.gov; rwmcgwi@vt.edu NR 19 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 9 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374902022 ER PT S AU Kizhner, S Parsons, A Sohl, DW Reynolds, RM Smith, JS AF Kizhner, Semion Parsons, Ann Sohl, David W. Reynolds, Renee M. Smith, Jeffrey Scott GP IEEE TI On Spaceflight Instrument Adaptive Electrical and Electronics Subsystem Functional Framework SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB Near-earth heritage spaceflight missions and contemporary large observatories such as the NASA Hubble Space Telescope (HST), future James Web Space Telescope (JWST), or planetary fly-by (Cassini with its 12 instruments) and orbiting deep space observatories like the Mars Reconnaissance Orbiter (MRO) have carried large electronics subsystems. The Kepler cosmology observatory 95 mega pixels focal plane servicing electronics comprises some 50 electronic boards. The future cosmology mission Wide Field Infra-Red Survey Telescope (WFIRST with 2 instruments) envisions a focal plane with 18 large 4Kx4K sensors totaling 4.8318e+09 bits also serviced by a multitude of electronic boards. On the other hand, a new class of NASA Earth small satellite missions (SmallSat), the Department of Defense Operationally Responsive Space small satellites (ORS) and planetary surface mission instruments require smaller scale electrical and electronics subsystems. These are challenged with unique external space launch technology requirements for eversmaller mass and volume, constraints on power and communications bandwidth, in addition to the requirements of space extreme environment of temperature variations and cosmic radiation. Within this wide range of space exploration and earth remote-sensing missions there is a need to revisit these external and internal spaceflight instrument science requirements from the point of view of developing the future spaceflight instrument scalable and adaptive electrical and electronics subsystem (IAEES) conceptual framework. We consider these instrument requirements and conceptual functionality framework on the precedent of the two future Decadal missions - the flagship cosmology observatory WFIRST pre-cursor study and proposal DESTINY [1] and the proposed Mars-2020 mission instrument - the Pulsed Neutron Generator and Gamma Ray Spectrometer (PING). Both proposals are now history with the first materializing as the winning WFIRST [2] and the PING destined to fly on some other than Mars-2020 mission. The purpose of this paper is to delineate the IAEES framework in proposal phase broad enough to be scalable and adaptive for future implementation. Representative top-level requirements - each originating in science definition and the instrument's other subsystems and the spacecraft needs constitute the basis of such a framework. A representative IAEES conceptual framework is elaborated on the precedent of the two future mission instruments' proposals and is analyzed as a reference scalable adaptive IAEES and its simulators. C1 [Kizhner, Semion; Parsons, Ann; Sohl, David W.; Reynolds, Renee M.; Smith, Jeffrey Scott] NASA, Goddard Space Flight Ctr, Greenbelt Rd, Greenbelt, MD 20771 USA. RP Kizhner, S (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt Rd, Greenbelt, MD 20771 USA. EM Semion.Kizhner-1@nasa.gov NR 5 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 13 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374903056 ER PT S AU Kolcio, K Fesq, L AF Kolcio, Ksenia Fesq, Lorraine GP IEEE TI Model-Based Off-Nominal State Isolation and Detection System for Autonomous Fault Management SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB This paper presents a model-based fault management (FM) system designed to provide off-nominal state detection and isolation capabilities that are key components to assessing spacecraft state awareness. The ability to autonomously isolate spacecraft failures to component levels will enable faster and more targeted responses and recovery thereby reducing down time. The use of model-based systems and practices is being explored by the FM community as a viable approach to developing more capable, autonomous systems in order to meet mission objectives. Model-based systems can provide better fault identification than traditional methods of fault detection such as limit-checking. They also lend themselves to more straight-forward approaches to verification and validation. We have chosen a particular model-based technique called Constraint Suspension for autonomous fault detection and isolation that does not require explicit fault modeling. The system is composed of a diagnostic engine and nominal system models of the target application, for example sensors and actuators. Sensed data are propagated through models of nominal system behavior. Faults are diagnosed when inconsistencies arise between sensed and modeled data. Several benefits result from this choice. First, because knowledge of faulty behavior is not required, it is possible to detect unanticipated and unforeseen faults. In fact, anomalous, degraded, and failed states all can be detected. Second, the same models used for nominal analyses and operations can be re-used for fault management, saving development resources and time. Third, the core diagnostic engine algorithm is complete and requires no additions to accommodate a potentially growing number of faults over time resulting in a relatively compact software footprint. Related to the second and third points is that the core algorithm and, potentially, models can be reused from mission to mission. Finally, the system can be used early in the design phase as a tool for sensor placement analyses and model verification. Health information produced by the FM system can be used to make resource allocation and planning and scheduling decisions by ground operations or by other on-board autonomy agents. Autonomous fault detection, isolation, and recovery (FDIR) on board space vehicles will provide protection and increased mission availability and reliability. On the ground such systems enable lights-out monitoring as well as training and support for operators. This paper presents the development of fault detection and isolation algorithms and models. Application of the system to a spacecraft attitude control system is discussed. Finally we apply Model-Based Systems Engineering (MBSE) modeling patterns to the fault management system models as a way to facilitate the development of the models through the use of SysML. C1 [Kolcio, Ksenia] Okean Solut Inc, 1463 E Republican St 32A, Seattle, WA 98112 USA. [Fesq, Lorraine] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Kolcio, K (reprint author), Okean Solut Inc, 1463 E Republican St 32A, Seattle, WA 98112 USA. EM ksenia@okeansolutions.com; Lorraine.M.Fesq@jpl.nasa.gov NR 7 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 12 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374903015 ER PT S AU Levy, N Ryan, JP Liggett, EH AF Levy, Noah Ryan, J. P. Liggett, Elliott H. GP IEEE TI Live View: A new utility for Real-Time Calibration of Focal Plane Arrays using Commodity Hardware SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE DE Imaging Spectroscopy; Parallelization; GPU; OpenMP; Qt AB This paper presents a novel application of commodity Graphics Processing Units (GPU), the OpenMP CPU parallelization library, and the Qt4.8 framework for a real-time characterization and calibration utility created to meet the needs of the Imaging Spectroscopy community. Until now FPA calibration was performed offline in MATLAB or IDL due to the high throughput required to process incoming data - a staggering 1.1 Gbit/sec on a CPU. Techniques better suited to this sort of high-throughput processing are described, as well as pitfalls. The real-time analysis of data produced by these algorithms is used to identify sources of electronic noise and interference in the imaging spectrometer and to characterize the FPA. Additionally, the methods for optimizing the calculation routines used in the software, such as Fourier Transforms (FFT) and Dark Subtraction Filters (DSF), are described along with their applications. This software has been used to provide critical support for the testing of several imaging spectrometers, such as AVIRIS Next Generation(2), NEON-3(3), PRISM4 and CWIS5. C1 [Levy, Noah] Cornell Univ, Dept Elect & Comp Engn, Ithaca, NY 14853 USA. [Ryan, J. P.] NYU, Dept Elect & Comp Engn, Polytech Sch Engn, Brooklyn, NY 11201 USA. [Liggett, Elliott H.] Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Levy, N (reprint author), Cornell Univ, Dept Elect & Comp Engn, Ithaca, NY 14853 USA. EM nml45@cornell.edu; jpr369@nyu.edu; eliggett@jpl.nasa.gov NR 12 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 8 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374902006 ER PT S AU Lewis, K Klaasen, K Susca, S Oaida, B Larson, M Vanelli, T Murray, A Jones, L Thomas, V Frank, L AF Lewis, Kari Klaasen, Ken Susca, Sara Oaida, Bogdan Larson, Melora Vanelli, Tony Murray, Alex Jones, Laura Thomas, Valerie Frank, Larry GP IEEE TI Use of Model Payload for Europa Mission Development IEEE Aerospace Conference SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB During the long early development of the Europa Mission concept, the team used a hypothetical, straw-man payload, called the Model Payload, to assist in the development of a complete mission design. The Model Payload comprised a suite of science instruments, and was structured to meet the science objectives of the mission. The science objectives were defined in terms of a set of specific physical measurements that would need to be made, including quality attributes such as resolution, accuracy, coverage, etc. The Model Payload was designed to acquire these data with the required attributes. A set of notional instruments was chosen to be able to meet the full set of science objectives. Each notional instrument was based on current capabilities and technologies of actual, similar instruments, and modeled with enough detail to be able to estimate aspects of the instrument such as power usage, pointing stability needs, thermal accommodation needs, etc. This paper discusses the basis for the Model Payload and how it was used to develop the mission design, observation and data acquisition strategy, needed spacecraft capabilities, spacecraft-payload interface needs, mission system requirements, and operational scenarios. Then we present a comparison of the Model Payload to the actual payload, recently selected by NASA for the proposed Europa Mission. The focus is on how well this process enveloped and constrained the design space and guided the development and analysis of not only instrument requirements, but also those of the flight system and the mission operations system. Specifically, we discuss those areas in which the Selected Payload drove the mission design and which areas remained unchanged. Lastly, we present lessons learned from the use of a Model Payload. C1 [Lewis, Kari; Klaasen, Ken; Susca, Sara; Oaida, Bogdan; Larson, Melora; Vanelli, Tony; Murray, Alex; Jones, Laura; Thomas, Valerie] Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Frank, Larry] Johns Hopkins Univ, Appl Phys Lab, 11100 Johns Hopkins Rd, Laurel, MD 20723 USA. RP Lewis, K (reprint author), Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Kari.A.Lewis@jpl.nasa.gov; Kenneth.P.Klaasen@jpl.nasa.gov; Sara.Susca@jpl.nasa.gov; Bogdan.V.Oaida@jpl.nasa.gov; Melora.E.Larson@jpl.nasa.gov; Tony.Vanelli@jpl.nasa.gov; Alexander.T.Murray@jpl.nasa.gov; Laura.L.Jones@jpl.nasa.gov; Valerie.C.Thomas@jpl.nasa.gov; Larry.Frank@jhuapl.edu NR 1 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 13 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374902024 ER PT S AU Li, X Cornish, T Ecelberger, S Getty, SA Brinckerhoff, WB AF Li, Xiang Cornish, Timothy Ecelberger, Scott Getty, Stephanie A. Brinckerhoff, William B. GP IEEE TI Tandem Mass Spectrometry on a Miniaturized Laser Desorption Time-of-Flight Mass Spectrometer SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE DE laser desorption time-of-flight mass spectrometer (LD-TOF-MS); laser desorption mass spectrometry (LDMS); tandem mass spectrometry (MS/MS); post-source decay (PSD); laser-assisted collision induced dissociation (L-CID) AB Tandem mass spectrometry (MS/MS) is a powerful and widely-used technique for identifying the molecular structure of organic constituents of a complex sample. Application of MS/MS to the study of unknown planetary samples on a remote space mission would contribute to our understanding of the origin, evolution, and distribution of extraterrestrial organics in our solar system. Here we report on the realization of MS/MS on a miniaturized laser desorption time-of-flight mass spectrometer (LD-TOF-MS), which is one of the most promising instrument types for future planetary missions. This achievement relies on two critical components: a curved-field reflectron and a pulsed-pin ion gate. These enable use of the complementary post-source decay (PSD) and laser-assisted collision induced dissociation (L-CID) MS/MS methods on diverse measurement targets with only modest investment in instrument resources such as volume and weight. MS/MS spectra of selected molecular targets in various organic standards exhibit excellent agreement when compared with results from a commercial, laboratory-scale TOFinstrument, demonstrating the potential of this powerful technique in space and planetary environments. C1 [Li, Xiang] Univ Maryland, Baltimore, MD 21250 USA. [Cornish, Timothy; Ecelberger, Scott] C&E Res Inc, Catonsville, MD 21228 USA. [Getty, Stephanie A.; Brinckerhoff, William B.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Li, X (reprint author), Univ Maryland, Baltimore, MD 21250 USA. EM xiang.li@nasa.gov; tcornish@CEResearchInc.com; SAE@CEResearchInc.com; stephanie.a.getty@nasa.gov; william.b.brinckerhoff@nasa.gov RI Li, Xiang/F-4539-2012 NR 7 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 8 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374901024 ER PT S AU Li, ZQ de Carufel, G Crues, EZ Bielski, P AF Li, Zu Qun de Carufel, Guy Crues, Edwin Z. Bielski, Paul GP IEEE TI Lighting Condition Analysis for Mars' Moon Phobos SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB This study used high fidelity computer simulation to investigate the lighting conditions, specifically the solar radiation flux over the surface, on Phobos. Ephemeris data from the Jet Propulsion Laboratory (JPL) DE405 model was used to model the state of the Sun, Earth, Moon, and Mars. An occultation model was developed to simulate Phobos' self-shadowing and its solar eclipses by Mars. The propagated Phobos state was compared with data from JPL's Horizon system to ensure the accuracy of the result. Results for Phobos lighting conditions over one Martian year are presented, which include the duration of solar eclipses, average solar radiation intensity, surface exposure time, and radiant exposure for both sun tracking and fixed solar arrays. The results show that: Phobos' solar eclipse time varies throughout the Martian year, with longer eclipse durations during the Martian northern spring and fall seasons and no eclipses during the Martian northern summer and winter seasons; solar radiation intensity is close to minimum in late spring and close to maximum in late fall; exposure time per orbit is relatively constant over the surface during the spring and fall but varies with latitude during the summer and winter; and Sun tracking solar arrays generate more energy than a fixed solar array. A usage example of the result is also present in this paper to demonstrate the utility. C1 [Li, Zu Qun; Crues, Edwin Z.; Bielski, Paul] NASA, Johnson Space Ctr, 2101 NASA Rd 1, Houston, TX 77058 USA. [de Carufel, Guy] NASA, Odyssey Space Res Llc, Johnson Space Ctr, Houston, TX 77058 USA. RP Li, ZQ (reprint author), NASA, Johnson Space Ctr, 2101 NASA Rd 1, Houston, TX 77058 USA. EM zuqun.li@nasa.gov; guy.decarufel@nasa.gov; edwin.z.crues@nasa.gov; paul.bielski@nasa.gov NR 6 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 9 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374902088 ER PT S AU Lock, RE Edwards, CD Nicholas, AK Woolley, R Bell, DJ AF Lock, Robert E. Edwards, Charles D., Jr. Nicholas, Austin K. Woolley, Ryan Bell, David J. GP IEEE TI Small Areostationary Telecommunications Orbiter Concepts for Mars in the 2020s SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB Current Mars science orbiters carry UHF proximity payloads to provide limited access and data services to landers and rovers on Mars surface. In the era of human spaceflight to Mars, very high rate and reliable relay services will be needed to serve a large number of supporting vehicles, habitats, and orbiters, as well as astronaut EVAs. These will likely be provided by a robust network of orbiting assets in very high orbits, such as areostationary orbits. In the decade leading to that era, telecommunications orbiters can be operated at areostationary orbit that can support a significant population of robotic precursor missions and build the network capabilities needed for the human spaceflight era. Telecommunications orbiters of modest size and cost, delivered by Solar Electric Propulsion to areostationary orbit, can provide continuous access at very high data rates to users on the surface and in Mars orbit. C1 [Lock, Robert E.; Edwards, Charles D., Jr.; Nicholas, Austin K.; Woolley, Ryan; Bell, David J.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Lock, RE (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Robert.E.Lock@jpl.nasa.gov NR 10 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 11 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374904020 ER PT S AU Lugo, R Litton, D Qu, M Shidner, J Powell, R AF Lugo, Rafael Litton, Daniel Qu, Min Shidner, Jeremy Powell, Richard GP IEEE TI A Robust Method to Integrate End-to-End Mission Architecture Optimization Tools SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB End-to-end mission simulations include multiple phases of flight. For example, an end-to-end Mars mission simulation may include launch from Earth, interplanetary transit to Mars and entry, descent and landing. Each phase of flight is optimized to meet specified constraints and often depend on and impact subsequent phases. The design and optimization tools and methodologies used to combine different aspects of end-to-end framework and their impact on mission planning are presented. This work focuses on a robust implementation of a Multidisciplinary Design Analysis and Optimization (MDAO) method that offers the flexibility to quickly adapt to changing mission design requirements. Different simulations tailored to the liftoff, ascent, and atmospheric entry phases of a trajectory are integrated and optimized in the MDAO program Isight, which provides the user a graphical interface to link simulation inputs and outputs. This approach provides many advantages to mission planners, as it is easily adapted to different mission scenarios and can improve the understanding of the integrated system performance within a particular mission configuration. A Mars direct entry mission using the Space Launch System (SLS) is presented as a generic end-to-end case study. For the given launch period, the SLS launch performance is traded for improved orbit geometry alignment, resulting in an optimized a net payload that is comparable to that in the SLS Mission Planner's Guide. C1 [Lugo, Rafael; Qu, Min; Shidner, Jeremy; Powell, Richard] Analyt Mech Associates Inc, 21 Enterprise Pkwy Suite 300, Hampton, VA 23666 USA. [Litton, Daniel] NASA, Langley Res Ctr, Mail Stop 489, Hampton, VA 23681 USA. RP Lugo, R (reprint author), Analyt Mech Associates Inc, 21 Enterprise Pkwy Suite 300, Hampton, VA 23666 USA. EM rafael.a.lugo@nasa.gov; daniel.k.litton@nasa.gov; min.qu-1@nasa.gov; jeremy.d.shidner@nasa.gov; richard.w.powell@nasa.gov NR 10 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 8 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374901030 ER PT S AU Maddock, R Henning, A Samarah, J AF Maddock, Robert Henning, Allen Samarah, Jamshid GP IEEE TI Passive vs. Parachute System Architecture for Robotic Sample Return Vehicles SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB The Multi-Mission Earth Entry Vehicle (MMEEV) is a flexible vehicle concept based on the Mars Sample Return (MSR) EEV design which can be used in the preliminary sample return mission study phase to parametrically investigate any trade space of interest to determine the best entry vehicle design approach for that particular mission concept. In addition to the trade space dimensions often considered (e.g. entry conditions, payload size and mass, vehicle size, etc.), the MMEEV trade space considers whether it might be more beneficial for the vehicle to utilize a parachute system during descent/landing or to be fully passive (i.e. not use a parachute). In order to evaluate this trade space dimension, a simplified parachute system model has been developed based on inputs such as vehicle size/mass, payload size/mass and landing requirements. This model works in conjunction with analytical approximations of a mission trade space dataset provided by the MMEEV System Analysis for Planetary EDL (M-SAPE) tool to help quantify the differences between an active (with parachute) and a passive (no parachute) vehicle concept. Preliminary results over a range of EEV and mission constraints (including entry conditions, vehicle size, payload mass, and landing requirements) are provided. For most sample return missions, the landing requirement (velocity and/or load) is ultimately determined by science considerations (e.g. sample preservation or containment). Regions of the trade space are identified where a parachute system is clearly more beneficial than the passive approach, and vice versa. Where the choice between the two architectures is less clear, additional considerations must also be taken into account including factors such as overall system reliability; system risk and complexity; and development and testing costs. C1 [Maddock, Robert; Samarah, Jamshid] NASA, Langley Res Ctr, 1 N Dryden St,MS 489, Hampton, VA 23681 USA. [Henning, Allen] Virginia Tech, 103 K Stratford Dr, Williamsburg, VA 23188 USA. RP Maddock, R (reprint author), NASA, Langley Res Ctr, 1 N Dryden St,MS 489, Hampton, VA 23681 USA. EM robert.w.maddock@nasa.gov; allenhenning3@vt.edu; jamshid.a.samareh@nasa.gov NR 12 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 10 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374900049 ER PT S AU Mahadevan, N Schumann, J Lowry, M Karsai, G AF Mahadevan, Nagabhushan Schumann, Johann Lowry, Michael Karsai, Gabor GP IEEE TI DVER: A Tool Chain for Cross-Validation and Perfection of Discrete Model-Based Diagnostic Systems SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB The safe and reliable operation of complex aerospace vehicles requires rapid and accurate detection and identification of system faults. Discrete model-based fault diagnostic systems (FDS) are often used when rapid real-time fault detection is needed. Given a vector of current discretized sensor readings, such a diagnostic algorithm produces fault hypotheses as its output. In this paper, we present DVER (Diagnostic VERification), a tool set to support the automation of validation and improvement of the central FDS components-the discrete model and associated sensor data processing capabilities. We present the results of applying the DVER tool chain to a model-based FDS for the NASA Advanced Diagnostic and Prognostic Testbed (ADAPT) system, a testbed for a redundant electrical power distribution system. C1 [Mahadevan, Nagabhushan; Karsai, Gabor] Vanderbilt Univ, Nashville, TN 37212 USA. [Schumann, Johann] SGT Inc, NASA Ames, Moffett Field, CA 94035 USA. [Lowry, Michael] NASA ARC, Moffett Field, CA 94035 USA. RP Mahadevan, N (reprint author), Vanderbilt Univ, Nashville, TN 37212 USA. EM nag.mahadevan@vanderbilt.edu; Johann.M.Schumann@nasa.gov; Michael.R.Lowry@nasa.gov; gabor.karsai@vanderbilt.edu NR 23 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 15 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374904034 ER PT S AU Majerowicz, W Shinn, SA AF Majerowicz, Walt Shinn, Stephen A. GP IEEE TI Schedule Matters: Understanding the Relationship between Schedule Delays and Costs on Overruns SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB This paper examines the relationship between schedule delays and cost overruns on complex projects. It is generally accepted by many project practitioners that cost overruns are directly related to schedule delays. But what does "directly related to" actually mean? Some reasons or root causes for schedule delays and associated cost overruns are obvious, if only in hindsight. For example, unrealistic estimates, supply chain difficulties, insufficient schedule margin, technical problems, scope changes, or the occurrence of risk events can negatively impact schedule performance. Other factors driving schedule delays and cost overruns may be less obvious and more difficult to quantify. Examples of these less obvious factors include project complexity, flawed estimating assumptions, over-optimism, political factors, "black swan" events, or even poor leadership and communication. Indeed, is it even possible the schedule itself could be a source of delay and subsequent cost overrun? Through literature review, surveys of project practitioners, and the authors' own experience on NASA programs and projects, the authors will categorize and examine the various factors affecting the relationship between project schedule delays and cost growth. The authors will also propose some ideas for organizations to consider to help create an awareness of the factors which could cause or influence schedule delays and associated cost growth on complex projects. C1 [Majerowicz, Walt; Shinn, Stephen A.] NASA, Goddard Space Flight Ctr, 8800 Greenbelt Rd,Code 400, Greenbelt, MD 20771 USA. RP Majerowicz, W (reprint author), NASA, Goddard Space Flight Ctr, 8800 Greenbelt Rd,Code 400, Greenbelt, MD 20771 USA. EM walt.majerowicz@nasa.gov; stephen.a.shinn@nasa.gov NR 11 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 8 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374902038 ER PT S AU Majerowicz, W Bitten, R Emmons, D Shinn, SA AF Majerowicz, Walt Bitten, Robert Emmons, Debra Shinn, Stephen A. GP IEEE TI Contribution of Schedule Delays to Cost Growth: How to Make Peace with a Marching Army SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB Numerous research papers have shown that cost and schedule growth are interrelated for NASA space science missions. Although there has shown to be a strong correlation of cost growth with schedule growth, it is unclear what percentage of cost growth is caused by schedule growth and how schedule growth can be controlled. This paper attempts to quantify this percentage by looking at historical data and show detailed examples of how schedule growth influences cost growth. The paper also addresses a methodology to show an alternate approach for assessing and setting a robust baseline schedule and use schedule performance metrics to help assess if the project is performing to plan. Finally, recommendations are presented to help control schedule growth in order to minimize cost growth for NASA space science missions. C1 [Majerowicz, Walt; Shinn, Stephen A.] Goddard Space Flight Ctr, 8800 Greenbelt Rd,Code 400, Greenbelt, MD 20771 USA. [Bitten, Robert] Aerosp Corp, 2310 E El Segundo Blvd, El Segundo, CA 90245 USA. [Emmons, Debra] Aerosp Corp, 2011 Crystal Dr,Suite 900, Arlington, VA 22202 USA. RP Majerowicz, W (reprint author), Goddard Space Flight Ctr, 8800 Greenbelt Rd,Code 400, Greenbelt, MD 20771 USA. EM walt.majerowicz@nasa.gov; robert.e.bitten@aero.org; debra.l.emmons@aero.org; stephen.a.shinn@nasa.gov NR 7 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 8 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374900056 ER PT S AU Marquez, JJ Adelstein, BD Ellis, S Chang, ML Howard, R AF Marquez, Jessica J. Adelstein, Bernard D. Ellis, Stephen Chang, Mai Lee Howard, Robert GP IEEE TI Evaluation of Human and Automation/Robotics Integration Needs for Future Human Exploration Missions SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB NASA employs Design Reference Missions (DRMs) to define potential architectures for future human exploration missions to deep space, the Moon, and Mars. While DRMs to these destinations share some components, each mission has different needs. This paper focuses on the identified human and automation/robotic integration needs for these future missions. The outcomes of our assessment is a human and automation/robotic (HAR) high-level task list for each of the four DRMs that we reviewed (i. e., Deep Space Sortie, Lunar Visit/Habitation, Deep Space Habitation, and Planetary), as well as a list of common critical HAR factors that drive the design of HAR integration. C1 [Marquez, Jessica J.; Adelstein, Bernard D.; Ellis, Stephen] NASA, Ames Res Ctr, M-S 262-2,Bldg 262,Rm 132,POB 1, Moffett Field, CA 94035 USA. [Chang, Mai Lee; Howard, Robert] NASA, Johnson Space Ctr, 2101 NASA Rd 1, Houston, TX 77058 USA. RP Marquez, JJ (reprint author), NASA, Ames Res Ctr, M-S 262-2,Bldg 262,Rm 132,POB 1, Moffett Field, CA 94035 USA. EM Jessica.J.Marquez@nasa.gov NR 18 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 9 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374900084 ER PT S AU McGirl, NA Castellanos, LA Srikrishna, AP Heilbronn, L La Tessa, C Rusek, A Sivertz, M Blattnig, S Clowdsley, M Slaba, T Zeitlin, C AF McGirl, Natalie A. Castellanos, Luis A. Srikrishna, Ashwin P. Heilbronn, Lawrence La Tessa, Chiara Rusek, Adam Sivertz, Michael Blattnig, Steve Clowdsley, Martha Slaba, Tony Zeitlin, Cary GP IEEE TI Accelerator-Based Measurements Relevant for Shielding Design in Space SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE ID NEUTRON YIELDS AB Experimental work on light charged ion production from thick target shielding began this past May at the NASA Space Radiation Laboratory (NSRL) at Brookhaven National Laboratory (BNL). This paper presents the measured secondary light charged ion and neutron yields produced by 0.4- and 2.5-GeV protons and 0.4- and 1.0-AGeV iron ions striking a 30 g/cm(2) aluminum target. Neutron and light charged ion (protons, deuterons, and tritons) measurements were taken with liquid scintillators and sodium iodide (NaI) detectors positioned at seven locations between 10 and 135 degrees off the beam axis to best cover the angular distributions of secondary particles, as determined by MCNPX simulations. In the liquid scintillators, neutron-gamma separation was achieved with pulse shape discrimination, and particle species were identified and isolated by analyzing the total charge deposited in the detector versus particle time of flight (TOF). After isolation, the TOF technique was utilized to produce energy spectra for protons, deuterons, tritons, and neutrons at various locations. Additionally, the stopping powers of light charged ions were compared in NaI detector pairs to generate energy spectra for protons, deuterons, and tritons. Preliminary results demonstrated promising agreement with MCNPX Monte Carlo transport code simulations for protons, deuterons, tritons, and neutrons, despite the lack of a full background characterization and optimization of detector settings. Results are expected to improve over the next three years with an increase in beam time, inclusion of specific liquid scintillator detection efficiencies, and an investigation of the physics model parameters in MCNPX. Future experiments will include the use of both forward and back targets composed of high-density polyethylene or aluminum with thicknesses of 20, 40, and 60 g/cm(2). Furthermore, proton, helium, carbon, silicon, and iron projectiles will be utilized at energies of 0.4, 0.75, 1.5, and 2.5 AGeV. Ultimately, these measurements will be incorporated in the uncertainty analysis for the engineering codes that NASA uses to develop optimal shielding thicknesses for spacecraft and space habitat design. C1 [McGirl, Natalie A.; Castellanos, Luis A.; Srikrishna, Ashwin P.; Heilbronn, Lawrence] Univ Tennessee, Dept Nucl Engn, Knoxville, TN 37996 USA. [La Tessa, Chiara; Rusek, Adam; Sivertz, Michael] NASA, Space Radiat Lab, Brookhaven Natl Lab, Upton, NY 11973 USA. [Blattnig, Steve; Clowdsley, Martha; Slaba, Tony] NASA, Langley Res Ctr, Hampton, VA 23681 USA. [Zeitlin, Cary] Lockheed Martin, Informat Syst & Global Solut, Houston, TX 77258 USA. RP McGirl, NA (reprint author), Univ Tennessee, Dept Nucl Engn, Knoxville, TN 37996 USA. EM nmcgirl@vols.utk.edu NR 11 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 10 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374903080 ER PT S AU McGuire, ML Burke, LM Hack, KJ Strange, NJ McElrath, TP Landau, DF Lantoine, G Lopez, P McDonald, MA AF McGuire, Melissa L. Burke, Laura M. Hack, Kurt J. Strange, Nathan J. McElrath, Timothy P. Landau, Damon F. Lantoine, Gregory Lopez, Pedro McDonald, Mark A. GP IEEE TI Potential Cislunar and Interplanetary Proving Ground Excursion Trajectory Concepts SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB NASA has been investigating potential translunar excursion concepts to take place in the 2020s that would be used to test and demonstrate long duration life support and other systems needed for eventual Mars missions in the 2030s. These potential trajectory concepts could be conducted in the proving ground, a region of cislunar and near-Earth interplanetary space where international space agencies could cooperate to develop the technologies needed for interplanetary spaceflight. Enabled by high power Solar Electric Propulsion (SEP) technologies, the excursion trajectory concepts studied are grouped into three classes of increasing distance from the Earth and increaseing technical difficulty: the first class of excursion trajectory concepts would represent a 90-120 day round trip trajectory with abort to Earth options throughout the entire length, the second class would be a 180-210 day round trip trajectory with periods in which aborts would not be available, and the third would be a 300-400 day round trip trajectory without aborts for most of the length of the trip. This paper provides a top-level summary of the trajectory and mission design of representative example missions of these three classes of excursion trajectory concepts. C1 [McGuire, Melissa L.; Burke, Laura M.; Hack, Kurt J.] NASA, Glenn Res Ctr, 21000 Brookpark Road, Cleveland, OH 44135 USA. [Strange, Nathan J.; McElrath, Timothy P.; Landau, Damon F.; Lantoine, Gregory] Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Lopez, Pedro; McDonald, Mark A.] NASA, Johnson Space Ctr, 2101 NASA Rd 1, Houston, TX 77058 USA. RP McGuire, ML (reprint author), NASA, Glenn Res Ctr, 21000 Brookpark Road, Cleveland, OH 44135 USA. EM Melissa.L.McGuire@nasa.gov; Laura.M.Burke@nasa.gov; Kurt.J.Hack@nasa.gov; Nathan.J.Strange@jpl.nasa.gov; Timothy.P.McElrath@jpl.nasa.gov; Damon.Landau@jpl.nasa.gov; Gregory.Lantoine@jpl.nasa.gov; Pedro.Lopez-1@nasa.gov; Mark.A.McDonald-1@nasa.gov NR 8 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 10 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374901089 ER PT S AU Miller, MJ Lim, DSS Brady, AL Cardman, Z Bell, E Garry, WB Reid, D Chappell, S Abercromby, AFJ AF Miller, Matthew J. Lim, Darlene S. S. Brady, Allyson L. Cardman, Zena Bell, Ernest Garry, W. Brent Reid, Donnie Chappell, Steve Abercromby, Andrew F. J. GP IEEE TI PLRP-3: Operational Perspectives Conducting Science-Driven Extravehicular Activity with Communications Latency SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE ID FRESH-WATER MICROBIALITES; NEAR-EARTH ASTEROIDS; PAVILION LAKE; SURFACE OPERATIONS; ANTARCTIC SEARCH; EXPLORATION; MARS; METEORITES; ANALOG; LIFE AB The Pavilion Lake Research Project (PLRP) is a unique program where a combination of scientific research and human space exploration concepts are integrated in an underwater spaceflight analog environment. The 2015 PLRP field season took place at Pavilion Lake, British Columbia, Canada, where science-driven exploration techniques focused on microbialite characterization and acquisition. These techniques were evaluated within the context of crew and robotic deep-space extravehicular activity (EVA) operations. The primary objective of this analog study was to detail the capabilities, decision-making processes, and operational concepts required to meet non-simulated scientific objectives during 5-minute one-way communication latency utilizing crew and robotic assets. The relationship and interaction between ground and flight crew was found to be dependent on the specific scientific activities being addressed. Furthermore, the addition of a second intravehicular operator was found to be highly enabling when conducting science-driven EVAs. C1 [Miller, Matthew J.] Georgia Inst Technol, 270 Ferst Dr,Room 416, Atlanta, GA 30332 USA. [Lim, Darlene S. S.] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Brady, Allyson L.] McMaster Univ, Sch Geog & Earth Sci, 1280 Main St West, Hamilton, ON, Canada. [Cardman, Zena] Penn State Univ, 208 Deike Bldg, University Pk, PA 16802 USA. [Bell, Ernest] Univ Maryland, College Pk, MD 20742 USA. [Garry, W. Brent] NASA, Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. [Reid, Donnie] Nuytco Res Ltd, N Vancouver, BC, Canada. [Chappell, Steve] Wyle Sci Technol & Engn Grp, Wyle HAC 37C,2101 NASA Pkwy, Houston, TX 77058 USA. [Abercromby, Andrew F. J.] NASA JSC, 2101 NASA Pkwy, Houston, TX 77058 USA. RP Miller, MJ (reprint author), Georgia Inst Technol, 270 Ferst Dr,Room 416, Atlanta, GA 30332 USA. EM mmiller@gatech.edu; darlene.lim@nasa.gov; bradyal@mcmaster.ca; zena@psu.edu; ebell1@umd.edu; brent.garry@nasa.gov; donnie@nuytco.com; steven.p.chappell@nasa.gov; andrew.abercromby@nasa.gov NR 45 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 13 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374901051 ER PT S AU Morgan, PS AF Morgan, Paula S. GP IEEE TI Enhancing the Cassini Mission through FP Applications after Launch SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB Although rigorous pre-emptive measures are taken to preclude failures and anomalous conditions from occurring in JPL spacecraft missions prior to launch, unforeseeable problems can still surface after liftoff. In the case of the Cassini/Huygens Mission-to-Saturn spacecraft, several problems were observed post-launch: 1) immediately after takeoff, the collected engineering/science data stored on the Solid State Recorders (SSR) contained a significantly higher number of corrupted bits than was expected (considerably over spec) due to human error in the memory mapping of these devices, 2) numerous Solid State Power Switches (SSPS) sporadically tripped off throughout the mission due to cosmic ray bombardment from the unique space environment, and 3) false assumptions in the pressure regulator design in combination with missing heritage test data led to inaccurate design conclusions, causing the issuance of two waivers for the regulator to close properly (a potentially mission catastrophic single-point failure which occurred 24 days after launch) amongst other problems. For Cassini, some of these anomalies led to arduous work-arounds or required continuous monitoring of telemetry variables by the ground-based Spacecraft Operations Flight Support (SOFS) team in order to detect and fix fault occurrences as they happened. Fortunately, sufficient funding and schedule margin allowed several Fault Protection (FP) solutions to be implemented into post-launch Flight Software (FSW) uploads to help resolve these issues autonomously, reducing SOFS ground support efforts while improving anomaly recovery time in order to preserve maximum science capture. This paper details the FP applications used to resolve the above issues as well as to optimize solutions for several other problems experienced by the Cassini spacecraft during its flight, in order to enhance the spacecraft's overall mission success throughout the 18 years of its 20 year expedition to and within the Saturnian system. C1 [Morgan, Paula S.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Morgan, PS (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Paula.S.Morgan@jpl.nasa.gov NR 18 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 19 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374901028 ER PT S AU Mounce, G Lyke, J Horan, S Doyle, R Some, R Powell, W AF Mounce, Gabriel Lyke, Jim Horan, Stephen Doyle, Rich Some, Rafi Powell, Wes GP IEEE TI Chiplet Based Approach for Heterogeneous Processing and Packaging Architectures SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB Creating integrated systems on-chip (SoCs) for aerospace platforms is becoming increasingly intractable in advanced semiconductor nodes (< 90 nm) due to: (1) the expense of semiconductor processing and fabrication, (2) sheer complexity in terms of number of circuit elements for a large die, and (3) limited quantities of systems over which development costs can be amortized. To overcome some of these barriers, a modular " chiplet" motif is proposed around which a scalable and heterogeneous architecture multi-generational roadmap for microelectronics can be based that preserves many of the benefits of a SoC approach. A chiplet is defined as a small, high-performance nodal architecture that can be connected to other chiplets using a number of universal links for high-speed communications. The links can be either parallel or serial, each conveying the same information. Parallel links are used in multichip module / 2.5D packaging, in which a number of chiplets may be a packaged into a tightly coupled configuration (having in theory thousands of interconnects). Serial links are used in simpler forms of packaging to connect nodes across boards, backplanes, and boxes. The universality is important for two reasons. First, by establishing an equivalence between parallel and serial links, the same grouping of chips can be packaged in several different ways that result in functionally equivalent implementations (except that the inter-nodal latency will vary between parallel and serial connections). The performance of the links can be evolved over time to take advantage of the fastest available transport (including optical) or the widest parallel embodiments (for aggressive 3-D throughsilicon via connections). Second, since the links only pass information, it is conceivable that node designs can be substantially different, allowing heterogeneous mixtures of chiplets, to include not only different embodiments of the same processor, but also wholly different classes of node types, to include ultradense memory " servers" (capable of managing multiple high-speed streams through the same link mechanisms), field programmable gate array (FPGA) clusters, and even extended to include complex, configurable analog and radiofrequency functional blocks in the future. By establishing standard messaging protocols, node arrangements can selforganize as more copies of different node types are added, creating a natural approach for building systems flexibly based on the best of breed semiconductor and packaging technologies. This paper will introduce the basic form of the chiplet concept inspired from joint AFRL/NASA work on next-generation space processing and previous work on scaled reconfigurable processing architectures, and describe some of the features we believe necessary to support scalability and heterogeneity with semiconductor technologies, transport concepts, and advanced packaging approaches. C1 [Mounce, Gabriel; Lyke, Jim] Air Force Res Lab, Kirtland AFB, NM 87112 USA. [Horan, Stephen] NASA, Langley Res Ctr, Washington, DC 20546 USA. [Doyle, Rich; Some, Rafi] CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. [Powell, Wes] NASA, Goddard Space Flight Ctr, Washington, DC 20546 USA. RP Mounce, G (reprint author), Air Force Res Lab, Kirtland AFB, NM 87112 USA. EM gabriel.mounce.3@us.af.mil; james.lyke.2@us.af.mil; stephen.j.horan@nasa.gov; wesley.a.powell@nasa.gov; richard.j.doyle@jpl.nasa.gov; rafi.some@jpl.nasa.gov NR 7 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 11 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374903052 ER PT S AU Munoz, G Toon, T Toon, J Conner, AC Adams, TC Miranda, DJ AF Munoz, Gisela Toon, Troy Toon, Jamie Conner, Angelo C. Adams, Timothy C. Miranda, David J. GP IEEE TI Evolving Reliability & Maintainability Allocations for NASA Ground Systems SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB This paper describes the methodology and value of modifying allocations to reliability and maintainability requirements for the NASA Ground Systems Development and Operations (GSDO) Program's ground systems. As systems progressed through their design life cycle and hardware data became available, it became necessary to reexamine the previously derived allocations. This iterative process provided an opportunity for the reliability engineering teamto reevaluate allocations as systems moved beyond their conceptual and preliminary design phases. These new allocations are based on updated designs and maintainability characteristics of the components. It was found that trade-offs in reliability and maintainability were essential to ensuring the integrity of the reliability and maintainability analysis. This paper discusses the results of reliability and maintainability reallocations made for the GSDO subsystems as the program nears the end of its design phase. C1 [Munoz, Gisela] Red Canyon Software, Kennedy Space Ctr, FL 32899 USA. [Toon, Troy; Toon, Jamie; Conner, Angelo C.] Millennium Engn & Integrat, Kennedy Space Ctr, FL 32899 USA. [Adams, Timothy C.; Miranda, David J.] NASA, Kennedy Space Ctr, FL 32899 USA. RP Munoz, G (reprint author), Red Canyon Software, Kennedy Space Ctr, FL 32899 USA. EM Gisela.A.Munoz@nasa.gov; Troy.T.Toon@nasa.gov; Jamie.A.Toon@nasa.gov; Angelo.C.Conner@nasa.gov; Tim.Adams@nasa.gov; David.J.Miranda@nasa.gov NR 11 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 8 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374902016 ER PT S AU Murchie, SL Chabot, NL Buczkowski, DL Eng, DA Peplowski, PN Ernst, CM Seelos, FP Horanyi, M Castillo-Rogez, JC Chmielewski, AB Maki, JN Trebi-Ollenu, A Ehlmann, BL Klingelhoefer, G Arvidson, RE Spence, HE Christian, JA AF Murchie, Scott L. Chabot, Nancy L. Buczkowski, Debra L. Eng, Douglas A. Peplowski, Patrick N. Ernst, Carolyn M. Seelos, Frank P. Horanyi, Mihaly Castillo-Rogez, Julie C. Chmielewski, Artur B. Maki, Justin N. Trebi-Ollenu, Ashitey Ehlmann, Bethany L. Klingelhoefer, Goestar Arvidson, Raymond E. Spence, Harlan E. Christian, John A. GP IEEE TI Mars-Moons Exploration, Reconnaissance, and Landed Investigation (MERLIN) SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE ID TAGISH LAKE METEORITE; TELEVISION OBSERVATIONS; CARBONACEOUS CHONDRITE; SURFACE-COMPOSITION; MARTIAN SATELLITES; TROJAN ASTEROIDS; COMETARY NUCLEI; IMAGING-SYSTEM; IMPACT EJECTA; SOLAR-SYSTEM AB MERLIN, the Mars-Moons Exploration, Reconnaissance and Landed Investigation, is a concept for the first mission to land on the Martian moon Phobos and the first U.S. mission to conduct an in situ investigation of a D-type body typical of the outer solar system. Understanding Phobos and Deimos provides key information for understanding the history and evolution of our solar system and drives MERLIN's combined orbital and landed mission design. MERLIN would perform 9 months of orbital reconnaissance of Phobos and Deimos, characterizing their geology and a landing site on Phobos. Once landed, MERLIN would perform 90 days of complementary measurements of chemical and mineralogic composition. Phobos' size and mass provide a low-risk landing environment for a small-body lander. Controlled descent is so slow that the landing can be rehearsed and even repeated, yet gravity is high enough that surface operations do not require anchoring. Imaging of Phobos from past missions demonstrates the existence of regions suitable for landing and provides knowledge for planning the orbital and landed investigations. MERLIN's dual orbital and landed data would deliver seminal science directly traceable to NASA's Strategic Goals and Objectives, NASA's Science Plan, and Decadal Survey goals, while simultaneously closing strategic knowledge gaps (SKGs) to prepare for future human exploration. MERLIN's landed compositional measurements would unravel the origin of Mars' moons, addressing the goal to understand how solar system objects formed and evolved. MERLIN would determine the inventory of prebiotic materials on Phobos, addressing the goal focused on the distribution of volatiles and organics across the solar system, and the origin and requirements of life. MERLIN's high-resolution images during low flyovers would investigate processes that affect the local regolith and provide geologic context for landed measurements. MERLIN would characterize the geology, surface regolith, and internal structure of Mars' moons, addressing the goal to understand processes that shape planetary bodies, and how those processes operate and interact. MERLIN's combined remote and landed investigations would deliver pioneering data about Phobos, characterizing an object on the flexible path for human exploration. C1 [Murchie, Scott L.; Chabot, Nancy L.; Buczkowski, Debra L.; Eng, Douglas A.; Peplowski, Patrick N.; Ernst, Carolyn M.; Seelos, Frank P.] Johns Hopkins Univ, Appl Phys Lab, 11100 Johns Hopkins Rd, Laurel, MD 20723 USA. [Horanyi, Mihaly] Univ Colorado, Boulder, CO 80309 USA. [Castillo-Rogez, Julie C.; Chmielewski, Artur B.; Maki, Justin N.; Trebi-Ollenu, Ashitey] Jet Prop Lab, Pasadena, CA 91109 USA. [Ehlmann, Bethany L.] CALTECH, Pasadena, CA 91125 USA. [Klingelhoefer, Goestar] Johannes Gutenburg Univ, D-55099 Mainz, Germany. [Arvidson, Raymond E.] Washington Univ, St Louis, MO 63130 USA. [Spence, Harlan E.] Univ New Hampshire, Durham, NH 03824 USA. [Christian, John A.] West Virginia Univ, Morgantown, WV 26506 USA. RP Murchie, SL (reprint author), Johns Hopkins Univ, Appl Phys Lab, 11100 Johns Hopkins Rd, Laurel, MD 20723 USA. EM Scott.Murchie@jhuapl.edu; Nancy.Chabot@jhuapl.edu; Debra.Buczkowski@jhuapl.edu; Doug.Eng@jhuapl.edu; Patrick.Peplowski@jhuapl.edu; Carolyn.Ernst@jhuapl.edu; Frank.Seelos@jhuapl.edu; Mihaly.Horanyi@lasp.colorado.edu; Julie.C.Castillo@jpl.nasa.gov; Artur.B.Chmielewski@jpl.nasa.gov; Justin.N.Maki@jpl.nasa.gov; Ashitey.Trebi-Ollennu@jpl.nasa.gov; Ehlmann@caltech.edu; Klingel@mail.uni-mainz.de; Arvidson@wunder.wustl.edu; Harlan.Spence@unh.edu; John.Christian@mail.wvu.edu RI Murchie, Scott/E-8030-2015 OI Murchie, Scott/0000-0002-1616-8751 NR 109 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 18 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374902070 ER PT S AU Murry, ML Randolph, TM AF Murry, Michael L. Randolph, Thomas M. GP IEEE TI V&V on a NASA Technology Demonstration Project: Low Density Supersonic Decelerator SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB Given their smaller budgets, but higher allowed risk posture, technology demonstration missions face different Verification and Validation (V&V) challenges than typical NASA missions. Despite these challenges, the Low Density Supersonic Decelerator (LDSD) project, managed by NASA's Jet Propulsion Laboratory (JPL), has been extremely successful in testing new supersonic atmospheric decelerator technologies. A contribution to the project's success is the unique V&V program that emphasized efficiency and flexibility. This paper will provide an overview of LDSD test objectives, Supersonic Flight Dynamics Tests (SFDT) performed so far, unique requirements structure and V& V processes implemented. The paper will focus on the V& V of the SFDT test architecture. Furthermore, lessons learned will also be presented at the end of the paper to aid future technology demonstration projects. C1 [Murry, Michael L.; Randolph, Thomas M.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Murry, ML (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Michael.L.Murry@jpl.nasa.gov; Thomas.M.Randolph@jpl.nasa.gov NR 3 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 6 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374904014 ER PT S AU Nambiar, SP Hussein, A Silva-Martinez, J Reinert, J Gonzalez, F AF Nambiar, Shrrirup P. Hussein, Alaa Silva-Martinez, Jackelynne Reinert, Jessica Gonzalez, Fernando GP IEEE TI Architecture for Mitigating Short-Term Warning Cosmic Threats: READI Project SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE DE Planetary Defense; Earth Protection; Comets; Asteroids; NEO; PHO; Short-Term Warning; ISU; SSP15 AB Earth is being constantly bombarded by a large variety of celestial bodies and has been since its formation 4.5 billion years ago. Among those bodies, mainly asteroids and comets, there are those that have the potential to create large scale destruction upon impact. The only extinction-level impact recorded to date was 65 million years ago, during the era of dinosaurs. The probability of another extinction-level, or even city-killer, impact may be negligible, but the consequences can be severe for the biosphere and for our species. Therefore it is highly imperative for us to be prepared for such a devastating impact in the near future, especially since humanity is at the threshold of wielding technologies that allow us to do so. Majority of scientists, engineers, and policymakers have focused on long-term strategies and warning periods for Earth orbit crossing Near-Earth Objects (NEOs), and have suggested methods and policies to tackle such problems. However, less attention has been paid to short warning period NEO threats. Such NEOs test current technological and international cooperation capabilities in protecting ourselves, and can create unpredictable devastation ranging from local to global scale. The most recent example is the Chelyabinsk incident in Russia. This event has provided a wakeup call for space agencies and governments around the world towards establishing a Planetary Defense Program. The Roadmap for EArth Defense Initiative (READI) is a project by a team of international, intercultural, and interdisciplinary participants of the International Space University's Space Studies Program 2015 hosted by Ohio University, Athens, OH proposing a roadmap for space agencies, governments, and the general public to tackle NEOs with a short warning before impact. Taking READI as a baseline, this paper presents a technical description of methodologies proposed for detection and impact mitigation of a medium-sized comet (up to 800m across) with a short-warning period of two years on a collision course with Earth. The hypothetical comet is on a highly-inclined orbit having a high probability for Earth impact after its perihelion. For detection, we propose a space-based infrared detection system consisting of two satellites located at the Earth-Moon Lagrange points L1 and L2 coupled with space observatories, like the James Webb telescope and the Centennial telescope. These telescopes are supported by ground-based telescopes, like the Arecibo and Green Bank telescope, in the search for NEOs. Upon detection, the comet is tracked constantly using space-and ground-based telescopes. The deflection system is two-pronged,firstly involving the use of a high energy Directed Energy Laser Terminals (DELT) placed at Sun-Earth Lagrange points L4 and L5 so as to initiate and increase the ablation rate of the comet and deviate it from its collision trajectory, and secondly by the Hypervelocity Comet Intercept Vehicle (HCIV), a space-borne system combining a kinetic impactor with a thermonuclear device. The policy and international collaboration aspects to implement these methods are also outlined in the paper. The techniques mentioned could also be applied to mitigate medium-to-large sized asteroids (up to 2km across). C1 [Nambiar, Shrrirup P.] Int Space Univ, Pune, Maharashtra, India. [Hussein, Alaa] Univ Sussex, Int Space Univ, Brighton BN1 9RH, E Sussex, England. [Silva-Martinez, Jackelynne] Int Space Univ, Cambridge, MA USA. [Reinert, Jessica] NASA, Glenn Res Ctr, Cleveland, OH USA. [Gonzalez, Fernando] European Space Agcy, Madrid, Spain. [Gonzalez, Fernando] Int Space Univ, Madrid, Spain. [Gonzalez, Fernando] Embry Riddle, Madrid, Spain. [Gonzalez, Fernando] European Space Agcy, Frankfurt, Germany. [Gonzalez, Fernando] Int Space Univ, Frankfurt, Germany. [Gonzalez, Fernando] Embry Riddle, Frankfurt, Germany. RP Nambiar, SP (reprint author), Int Space Univ, Pune, Maharashtra, India. EM shrrirup.fet@mriu.edu.in; A.Hussein@sussex.ac.uk; j.silva-martinez@community.isunet.edu; jessica.m.reinert@nasa.gov; fernando.gonzalez@community.isunet.edu NR 30 TC 0 Z9 0 U1 3 U2 3 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 11 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374904046 ER PT S AU Nixon, CA Esper, J Kirchman, F Folta, D Mashiku, A AF Nixon, Conor A. Esper, Jaime Kirchman, Frank Folta, David Mashiku, Alinda GP IEEE TI Aerocapture Design Study for a Titan Polar Orbiter SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE ID CASSINI RADAR; ATMOSPHERE; MISSION AB In 2014 a team at NASA Goddard Space Flight Center (GSFC) studied the feasibility of using active aerocapture to reduce the chemical Delta V requirements for inserting a small scientific satellite into Titan polar orbit. The scientific goals of the mission would be multi-spectral imaging and active radar mapping of Titan's surface and subsurface. The study objectives were to: (i) identify and select from launch window opportunities and refine the trajectory to Titan; (ii) study the aerocapture flight path and refine the entry corridor; (iii) design a carrier spacecraft and systems architecture; (iv) develop a scientific and engineering plan for the orbital portion of the mission. Study results include: (i) a launch in October 2021 on an Atlas V vehicle, using gravity assists from Earth and Venus to arrive at Titan in January 2031; (ii) initial aerocapture via an 8-km wide entry corridor to reach an initial 350x6000 km orbit, followed by aerobraking to reach a 350x1500 km orbit, and a periapse raise maneuver to reach a final 1500 km circular orbit; (iii) a three-part spacecraft system consisting of a cruise stage, radiator module, and orbiter inside a heat shield; (iv) a 22-month mission including station keeping to prevent orbital decay due to Saturn perturbations, with 240 Gb of compressed data returned. High-level issues identified include: (i) downlink capability - realistic downlink rates preclude the desired multi-spectral, global coverage of Titan's surface; (ii) power - demise of the NASA ASRG (Advanced Stirling Radioisotope Generator) program, and limited availability at present of MMRTGs (Multi-Mission Radioisotope Generators) needed for competed outer planet missions; (iii) thermal - external radiators must be carried to remove 4 kW of waste heat from MMRTGs inside the aeroshell, requiring heat pipes that pass through the aeroshell lid, compromising shielding ability; (iv) optical navigation to reach the entry corridor; (v) the NASA requirement of continuous critical event coverage for the orbiter, especially during the peak heating of the aerocapture when the radio link will be broken. In conclusion, although Titan aerocapture allows for considerable savings in propellant mass, this comes at a cost of increased mission complexity. Further architecture study and refinement is required to reduce high-level mission risks and to elucidate the optimum architecture. C1 [Nixon, Conor A.] NASA, Goddard Space Flight Ctr, Planetary Syst Lab, Greenbelt, MD 20771 USA. [Esper, Jaime] NASA, Goddard Space Flight Ctr, Adv Concepts Branch, Greenbelt, MD 20771 USA. [Kirchman, Frank] NASA, Goddard Space Flight Ctr, Mission Syst Engn Branch, Greenbelt, MD 20771 USA. [Folta, David; Mashiku, Alinda] NASA, Goddard Space Flight Ctr, Nav & Mission Design Branch, Greenbelt, MD 20771 USA. RP Nixon, CA (reprint author), NASA, Goddard Space Flight Ctr, Planetary Syst Lab, Greenbelt, MD 20771 USA. EM conor.a.nixon@nasa.gov; jaime.esper-1@nasa.gov; frank.j.kirchman@nasa.gov NR 29 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 16 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374903047 ER PT S AU Ono, M Rothrock, B Almeida, E Ansar, A Otero, R Huertas, A Heverly, M AF Ono, Masahiro Rothrock, Brandon Almeida, Eduardo Ansar, Adnan Otero, Richard Huertas, Andres Heverly, Matthew GP IEEE TI Data-Driven Surface Traversability Analysis for Mars 2020 Landing Site Selection SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB The objective of this paper is three-fold: 1) to describe the engineering challenges in the surface mobility of the Mars 2020 Rover mission that are considered in the landing site selection processs, 2) to introduce new automated traversability analysis capabilities, and 3) to present the preliminary analysis results for top candidate landing sites. The analysis capabilities presented in this paper include automated terrain classification, automated rock detection, digital elevation model (DEM) generation, and multi-ROI (region of interest) route planning. These analysis capabilities enable to fully utilize the vast volume of high-resolution orbiter imagery, quantitatively evaluate surface mobility requirements for each candidate site, and reject subjectivity in the comparison between sites in terms of engineering considerations. The analysis results supported the discussion in the Second Landing Site Workshop held in August 2015, which resulted in selecting eight candidate sites that will be considered in the third workshop. C1 [Ono, Masahiro; Rothrock, Brandon; Almeida, Eduardo; Ansar, Adnan; Otero, Richard; Huertas, Andres; Heverly, Matthew] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Ono, M (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM ono@jpl.nasa.gov; brothroc@jpl.nasa.gov; ealmeida@jpl.nasa.gov; aiansar@jpl.nasa.gov; otero@jpl.nasa.gov; mheverly@jpl.nasa.gov NR 15 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 12 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374901006 ER PT S AU Pich, MDS Garrett, HB Evans, RW Jun, I Kim, W Paranicas, C AF Pich, Maria de Soria-Santacruz Garrett, Henry B. Evans, Robin W. Jun, Insoo Kim, Wousik Paranicas, Chris GP IEEE TI The GIRE2 Model and Its Application to the Europa Mission SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE ID FIELD AB We present an empirical model of Jupiter's electron radiation environment and its application to the design of the future NASA mission to Europa. The model is based on data from the Galileo spacecraft. Measurements of the high-energy, omni-directional electrons from the Energetic Particle Detector (EPD) and magnetic field from the Magnetometer (MAG) onboard Galileo are used for this purpose. Ten-minute averages of the EPD data are used to provide an omni-directional electron flux spectrum at 0.238, 0.416, 0.706, 1.5, 2.0, and 11.0 MeV. Additionally, data from the Geiger Tube Telescope onboard Pioneer 10 and 11 are used to calculate the flux of 31 MeV electrons. The Galileo Interim Radiation Electron model v.2 (GIRE2) combines these datasets with the original Divine model and synchrotron observations to estimate the trapped electron radiation environment. Unlike the original Divine model, which was based on flybys of the Voyager and Pioneer spacecraft, the new GIRE2 model covers about 7 years of data and more than 30 orbits around Jupiter from the Galileo spacecraft. The model represents a step forward in the study of the Jovian radiation environment and is a valuable tool to assist in the design of future missions to Jupiter. This paper gives an overview of GIRE2 and focuses on its application to the design of the future NASA mission to Europa. The spacecraft will orbit Jupiter and perform multiple flybys of the moon Europa, which is embedded in the middle of a very strong radiation environment. The radiation environment surrounding the moon as well as along the trajectory are described in the paper together with the implications of this environment on the design of a mission. C1 [Pich, Maria de Soria-Santacruz; Garrett, Henry B.; Evans, Robin W.; Jun, Insoo; Kim, Wousik] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Paranicas, Chris] Johns Hopkins Univ, Appl Phys Lab, Baltimore, MD 21218 USA. RP Pich, MDS (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Maria.De.Soria-Santacruz.Pich@jpl.nasa.gov; Henry.B.Garrett@jpl.nasa.gov; Robin.W.Evans@jpl.nasa.gov; Insoo.Jun@jpl.nasa.gov; Wousik.Kim@jpl.nasa.gov; Chris.Paranicas@jhuapl.edu NR 14 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 7 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374900020 ER PT S AU Polsgrove, T Chapman, J Sutherlin, S Taylor, B Fabisinski, L Collins, T Cianciolo, AD Samareh, J Robertson, E Studak, B Vitalpur, S Lee, AY Rakow, G AF Polsgrove, Tara Chapman, Jack Sutherlin, Steve Taylor, Brian Fabisinski, Leo Collins, Tim Cianciolo, Alicia Dwyer Samareh, Jamshid Robertson, Ed Studak, Bill Vitalpur, Sharada Lee, Allan Y. Rakow, Glenn GP IEEE TI Human Mars Lander Design for NASA's Evolvable Mars Campaign SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB Landing humans on Mars will require entry, descent, and landing capability beyond the current state of the art. Nearly twenty times more delivered payload and an order of magnitude improvement in precision landing capability will be necessary. To better assess entry, descent, and landing technology options and sensitivities to future human mission design variations, a series of design studies has been initiated. This paper describes the results of the first design study in the series of studies to be completed in 2016 and includes system and subsystem design details including mass and power estimates for a lander design using the Hypersonic Inflatable Aerodynamic Decelerator (HIAD) entry technology. Future design activities in this series will focus on other entry technology options. C1 [Polsgrove, Tara; Chapman, Jack; Sutherlin, Steve; Taylor, Brian] NASA, Marshall Space Flight Ctr, Huntsville, AL 35812 USA. [Fabisinski, Leo] ISSI Jacobs ESSSA Grp, Huntsville, AL 35812 USA. [Collins, Tim; Cianciolo, Alicia Dwyer; Samareh, Jamshid] NASA, Langley Res Ctr, Hampton, VA 23681 USA. [Robertson, Ed; Studak, Bill; Vitalpur, Sharada] NASA, Johnson Space Ctr, 2101 NASA Pkwy, Houston, TX 77058 USA. [Lee, Allan Y.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Rakow, Glenn] NASA, Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. RP Polsgrove, T (reprint author), NASA, Marshall Space Flight Ctr, Huntsville, AL 35812 USA. EM Tara.Polsgrove@.nasa.gov NR 7 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 14 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374902094 ER PT S AU Ponchak, DS Auld, E Church, G Henriksen, S AF Ponchak, Denise S. Auld, Elisabeth Church, Gary Henriksen, Stephen GP IEEE TI A Summary of Two Recent UAS Command and Control (C2) Communications Feasibility Studies SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB In Spring of 2015, the NextGen Institute conducted two UAS C2 Communications Feasibility Studies on behalf of the FAA UAS Integration Office to develop two limited UAS C2 operational examples, each involving low-altitude BLOS (Beyond Line of Sight) Line of Communication (LOC) UAS applications, as part of assessing the myriad practical UAS C2 deployment challenges associated with these approaches. The studies investigated the feasibility of "Point-to-Point" (PTP) and "Network" approaches to UAS C2 to better understand potential user needs and to explore evolutionary paths to establishing a nation-wide system for delivering UAS C2 communications. This paper will summarize the solicitation, approach and results of the two studies teams led by Aviation Management Associates, Inc. and Exelis Inc. C1 [Ponchak, Denise S.] NASA, Glenn Res Ctr, 21000 Brookpk Rd, Cleveland, OH 44135 USA. [Auld, Elisabeth] NextGen Inst, 55 M St SE, Washington, DC 20003 USA. [Church, Gary] Aviat Management Associates, 1101 King St,Suite 325, Alexandria, VA 22314 USA. [Henriksen, Stephen] Exelis Inc, 12975 Worldgate Dr, Herndon, VA 20170 USA. RP Ponchak, DS (reprint author), NASA, Glenn Res Ctr, 21000 Brookpk Rd, Cleveland, OH 44135 USA. EM Denise.S.Ponchak@nasa.gov; Elisabeth.CTR.Auld@faa.gov; gary.church@avmgt.com; Stephen.Henriksen@exelisinc.com NR 2 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 10 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374901074 ER PT S AU Ponchak, GE Jordan, JL Scardelletti, MC AF Ponchak, George E. Jordan, Jennifer L. Scardelletti, Maximilian C. GP IEEE TI Ring Resonator for Detection of Melting Brine under Shallow Subsurface of Mars SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE ID DIELECTRIC-PROPERTIES; COMPLEX PERMITTIVITY; FREQUENCY-RANGE; SOIL-MOISTURE; SEA ICE; TEMPERATURE; WATER; GHZ; CONSTANT; SEAWATER AB Laboratory experimental evidence using Raman spectroscopy has shown that liquid brine may form below the shallow subsurface of Mars. A simpler experimental method to verify the presence of liquid brine or liquid water below Mars surface is needed. In this paper, a ring resonator is used to detect the phase change from frozen water to liquid water below a sandy soil that simulates the Mars surface. Experimental data shows that the ring resonator can detect the melting of thin layers of frozen brine or water up to 15 mm below the surface. C1 [Ponchak, George E.; Jordan, Jennifer L.; Scardelletti, Maximilian C.] NASA, Glenn Res Ctr, 21000 Brookpk Rd,MS 77-1, Cleveland, OH 44135 USA. RP Ponchak, GE (reprint author), NASA, Glenn Res Ctr, 21000 Brookpk Rd,MS 77-1, Cleveland, OH 44135 USA. EM george.ponchak@grc.nasa.gov; jennifer.l.jordan@nasa.gov; maximilian.c.scardelletti@nasa.gov NR 37 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 12 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374901059 ER PT S AU Post, E Cole, B Dinkel, K Kim, H Lee, E Nairouz, B AF Post, Ethan Cole, Bjorn Dinkel, Kevin Kim, Hongman Lee, Erich Nairouz, Bassem GP IEEE TI Cloud-Based Orchestration of a Model-Based Power and Data Analysis Toolchain SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB The proposed Europa Mission concept contains many engineering and scientific instruments that consume varying amounts of power and produce varying amounts of data throughout the mission. System-level power and data usage must be well understood and analyzed to verify design requirements. Numerous cross-disciplinary tools and analysis models are used to simulate the system-level spacecraft power and data behavior. This paper addresses the problem of orchestrating a consistent set of models, tools, and data in a unified analysis toolchain when ownership is distributed among numerous domain experts. An analysis and simulation environment was developed as a way to manage the complexity of the power and data analysis toolchain and to reduce the simulation turnaround time. A system model data repository is used as the trusted store of high-level inputs and results while other remote servers are used for archival of larger data sets and for analysis tool execution. Simulation data passes through numerous domain-specific analysis tools and end-to-end simulation execution is enabled through a web-based tool. The use of a cloud-based service facilitates coordination among distributed developers and enables scalable computation and storage needs, and ensures a consistent execution environment. Configuration management is emphasized to maintain traceability between current and historical simulation runs and their corresponding versions of models, tools and data. C1 [Post, Ethan; Cole, Bjorn; Dinkel, Kevin; Kim, Hongman; Lee, Erich; Nairouz, Bassem] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Post, E (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Ethan.A.Post@jpl.nasa.gov; Bjorn.Cole@jpl.nasa.gov; Kevin.Dinkel@jpl.nasa.gov; Hongman.Kim@jpl.nasa.gov; Erich.R.Lee@jpl.nasa.gov; Bassem.Nairouz@jpl.nasa.gov NR 7 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 12 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374901056 ER PT S AU Pugel, DE Rummel, JR Conley, C AF Pugel, D. E. (Betsy) Rummel, J. R. Conley, Catharine GP IEEE TI Tiny Houses: Planetary Protection-Focused Materials Selection for Spaceflight Hardware Surfaces SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE ID SULFATE-REDUCING BACTERIA; ATOMIC-FORCE MICROSCOPY; STAINLESS-STEEL; METAL-SURFACES; CORROSION BEHAVIOR; BACILLUS-SUBTILIS; BIOFILM FORMATION; VEGETATIVE CELLS; MICROBIAL-CELLS; SURVIVAL AB When developing spaceflight hardware, an engineering team is faced with a broad range of materials selections for design trade studies. Typical trade studies hone in on materials selection with thermal or mechanical environmental requirements as design selection drivers. With the growing interest in spaceflight hardware development for life-detection and restricted sample return missions, materials selection processes during the design phase will need to factor in the impact that materials selection will have on the growth of terrestrial microbes in the pre-and post-launch environment. From a planetary protection point of view, during the design and pre-fabrication processes, materials choices (composition, termination, finish) can result in surfaces that have the potential to support, sustain, or senesce microbes. We evaluate known surface properties of common spaceflight materials choices in the context of planetary protection considerations for future sample return and life-detection missions. C1 [Pugel, D. E. (Betsy); Conley, Catharine] NASA Headquarters, 300 E St SW, Washington, DC 20024 USA. [Rummel, J. R.] SETI Inst, POB 2838, Champlain, NY 12919 USA. RP Pugel, DE (reprint author), NASA Headquarters, 300 E St SW, Washington, DC 20024 USA. EM Betsy.Pugel@nasa.gov; jrummel@seti.org; Cassie.Conley@nasa.gov NR 70 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 13 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374902043 ER PT S AU Quijada, MA Seide, L Pasquale, BA McMann, JC Hagopian, JG Dominguez, M Gong, Q Marx, CT AF Quijada, Manuel A. Seide, Laurie Pasquale, Bert A. McMann, Joseph C. Hagopian, John G. Dominguez, Margaret Gong, Qian Marx, Catherine T. GP IEEE TI Spectral and Wavefront Error Performance of WFIRST/AFTA Bandpass Filter Prototypes SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB The Cycle 5 design baseline for the Wide-Field Infrared Survey Telescope Astrophysics Focused Telescope Assets (WFIRST/AFTA) instrument includes a single wide-field channel (WFC) instrument for both imaging and spectroscopy. The only routinely moving part during scientific observations for this wide-field channel is the element wheel (EW) assembly. This filter-wheel assembly will have 8 positions that will be populated with 6 bandpass filters, a blank position, and a Grism assembly that will consist of a three-element assembly to disperse the central wavelength undeviated for galaxy redshift surveys. All elements in the EW assembly will be made out of fused silica substrates (110 mm diameter) that will have the appropriate bandpass coatings according to the filter designations (Z087, Y106, J129, H158, F184, W149 and Grism). This paper presents and discusses filter performance, including spectral transmission and reflected/transmitted wavefront errors measurements, for a subset of the bandpass filter complement of the WFC instrument. The filters that are tested in this effort are the Z087, W149, and Grism. These filter coatings have been procured from three different vendors to assess the most challenging aspects in terms of the in-band throughput, out of band rejection (including the cut-on and cut-off slopes), and the impact the wavefront error distortions of these filters will have on the imaging performance of the wide-field channel in the WFIRST/AFTA observatory. C1 [Quijada, Manuel A.; Pasquale, Bert A.] NASA, Goddard Space Flight Ctr, MS 551 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. [Seide, Laurie] SGT, Goddard Corp Pk,7515 Mission Dr,Suite 300, Seabrook, MD 20706 USA. [McMann, Joseph C.] Sierra Lobo Inc, 6301 Ivy Lane,Suite 620, Greenbelt, MD 20770 USA. [Hagopian, John G.] Sigma Space Corp, 4600 Forbes Blvd, Lanham, MD 20706 USA. [Dominguez, Margaret] NASA, Goddard Space Flight Ctr, MS 448 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. [Gong, Qian] NASA, Goddard Space Flight Ctr, MS 550 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. [Marx, Catherine T.] NASA, Goddard Space Flight Ctr, MS 551 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. RP Quijada, MA (reprint author), NASA, Goddard Space Flight Ctr, MS 551 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. EM manuel.a.quijada@nasa.gov NR 3 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 12 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374904069 ER PT S AU Reh, K Lunine, JI Cable, ML Spilker, L Waite, JH Postberg, F Clark, K AF Reh, Kim Lunine, Jonathan I. Cable, Morgan L. Spilker, Linda Waite, J. Hunter Postberg, Frank Clark, Karla GP IEEE TI Enceladus Life Finder: The Search for Life in a Habitable Moon SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE ID SOUTH-POLAR TERRAIN; BIOMARKERS; GRAVITY; WATER; PLUME AB Enceladus is one of the most intriguing bodies in the solar system. In addition to having one of the brightest and youngest surfaces, this small Saturnian moon was recently discovered to have a plume erupting from its south polar terrain and a global subsurface ocean. The Cassini Mission discovered organics and nitrogen-bearing molecules in the plume, as well as salts and silicates that strongly suggest ocean water in contact with a rocky core. However, Cassini's instruments lack sufficient resolution and mass range to determine if these organics are of biotic origin. The Enceladus Life Finder (ELF) is a Discovery-class mission that would use two state-of-the-art mass spectrometers to target the gas and grains of the plume and search for evidence of life in this alien ocean. C1 [Reh, Kim; Cable, Morgan L.; Spilker, Linda; Clark, Karla] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91125 USA. [Lunine, Jonathan I.] Cornell Univ, Ctr Radiophys & Space Res, 402 Space Sci, Ithaca, NY 14853 USA. [Waite, J. Hunter] Southwest Res Inst, 6220 Culebra Rd, San Antonio, TX 78228 USA. [Postberg, Frank] Heidelberg Univ, Inst Earth Sci, Neuenheimer Feld 236, D-69120 Heidelberg, Germany. RP Reh, K (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91125 USA. EM kim.r.reh@jpl.nasa.gov; jlunine@astro.cornell.edu; morgan.l.cable@jpl.nasa.gov; linda.j.spilker@jpl.nasa.gov; hwaite@swri.edu; frank.postberg@geow.uni-heidelberg.de; karla.b.clark@jpl.nasa.gov NR 16 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 8 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374903035 ER PT S AU Rich, TM AF Rich, Thomas M. GP IEEE TI Multi-Center Space Data System Prototype Based on CCSDS Standards SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB Deep space missions beyond earth orbit will require new methods of data communications in order to compensate for increasing Radio Frequency (RF) propagation delay. The Consultative Committee for Space Data Systems (CCSDS) standard protocols Spacecraft Monitor & Control (SM&C), Asynchronous Message Service (AMS), and Delay/Disruption Tolerant Networking (DTN) provide such a method. However, the maturity level of this protocol stack is insufficient for mission inclusion at this time. This Space Data System prototype is intended to provide experience which will raise the Technical Readiness Level (TRL) of this protocol set. In order to reduce costs, future missions can take advantage of these standard protocols, which will result in increased interoperability between control centers. This prototype demonstrates these capabilities by implementing a realistic space data system in which telemetry is published to control center applications at the Jet Propulsion Lab (JPL), the Marshall Space Flight Center (MSFC), and the Johnson Space Center (JSC). Reverse publishing paths for commanding from each control center are also implemented. The target vehicle consists of realistic flight computer hardware running Core Flight Software (CFS) in the integrated Power, Avionics, and Power (iPAS) Pathfinder Lab at JSC. This prototype demonstrates a potential upgrade path for future Deep Space Network (DSN) modification, in which the automatic error recovery and communication gap compensation capabilities of DTN would be exploited. In addition, SM&C provides architectural flexibility by allowing new service providers and consumers to be added efficiently anywhere in the network using the common interface provided by SM&C's Message Abstraction Layer (MAL). In FY 2015, this space data system was enhanced by adding telerobotic operations capability provided by the Robot API Delegate (RAPID) family of protocols developed at NASA. RAPID is one of several candidates for consideration and inclusion in a new international standard being developed by the CCSDS Telerobotic Operations Working Group. Software gateways for the purpose of interfacing RAPID messages with the existing SM&C based infrastructure were developed. Telerobotic monitor, control, and bridge applications were written in the RAPID framework, which were then tailored to the NAO telerobotic test article hardware, a product of Aldebaran Robotics. C1 [Rich, Thomas M.] Tietronix Software Inc, NASA, Johnson Space Ctr, 2101 NASA Pkwy, Houston, TX 77058 USA. RP Rich, TM (reprint author), Tietronix Software Inc, NASA, Johnson Space Ctr, 2101 NASA Pkwy, Houston, TX 77058 USA. EM Thomas.M.Rich-1@nasa.gov NR 4 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 6 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374903020 ER PT S AU Rivkin, AS Anderson, R Barnouin, O Chabot, N Ernst, C Klima, R Leary, J Mehr, L Seifert, H Cohen, BA Sternovsky, Z Helbert, J AF Rivkin, Andrew S. Anderson, Richard Barnouin, Oliver Chabot, Nancy Ernst, Carolyn Klima, Rachel Leary, James Mehr, Lauren Seifert, Helmut Cohen, Barbara A. Sternovsky, Zoltan Helbert, Joern GP IEEE TI The Main-belt Asteroid and NEO Tour with Imaging and Spectroscopy (MANTIS) SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE ID GENERATED DUST CLOUDS; SOURCE REGIONS; SURFACE; EARTH; ICE; ORGANICS; WATER AB The asteroids preserve information from the earliest times in solar system history, with compositions in the population reflecting the material in the solar nebula and experiencing a wide range of temperatures. Today they experience ongoing processes, some of which are shared with larger bodies but some of which are unique to their size regime. They are critical to humanity's future as potential threats, resource sites, and targets for human visitation. However, over twenty years since the first spacecraft encounters with asteroids, they remain poorly understood. The mission we propose here, the Main-belt Asteroid and NEO Tour with Imaging and Spectroscopy (MANTIS), explores the diversity of asteroids to understand our solar system's past history, its present processes, and future opportunities and hazards. MANTIS addresses many of NASA's highest priorities as laid out in its 2014 Science Plan and provides additional benefit to the Planetary Defense and Human Exploration communities via a low-risk, cost-effective tour of the near-Earth region and inner asteroid belt. MANTIS would visit the materials that witnessed solar system formation and its earliest history, addressing the NASA goal of exploring and observing the objects in the solar system to understand how they formed and evolve. MANTIS measures OH, water, and organic materials via several complementary techniques, visiting and sampling objects known to have hydrated minerals and addressing the NASA goal of improving our understanding of the origin and evolution of life on Earth. The trajectory designed for MANTIS in 2014 enabled study of the geology and geophysics of nine diverse asteroids, with compositions ranging from water-rich to metallic, representatives of both binary and nonbinary asteroids, and sizes covering over two orders of magnitude, providing unique information about the chemical and physical processes shaping the asteroids, addressing the NASA goal of advancing the understanding of how the chemical and physical processes in our solar system operate, interact, and evolve. Finally, the set of measurements carried out by MANTIS at near-Earth and mainbelt asteroids will by definition characterize objects in the solar system that pose threats to Earth or offer resources for human exploration, a final goal in the NASA Science Plan. MANTIS would revolutionize our understanding of asteroids through its state-of-the-art payload of complementary instruments: A powerful infrared imaging spectrometer and narrow angle camera, both with recent flight heritage, an innovative dust analyzer with the potential for paradigm-shifting discoveries during and between asteroid encounters, and a capable mid-IR imager, potentially the first ever brought to a small body. MANTIS obtains datasets at each target that can be readily intercompared with one another, effectively doubling the current sample of asteroids visited by spacecraft. The MANTIS team is composed of leading international experts in asteroid science, led by PI Andrew Rivkin of the Johns Hopkins University Applied Physics Laboratory (APL) and Deputy PI Barbara Cohen of the NASA Marshall Space Flight Center (MSFC). Spacecraft and payload construction and mission management are conducted at APL, with payload elements also constructed at the University of Colorado and contributed by the German Aerospace Center (DLR). C1 [Rivkin, Andrew S.; Anderson, Richard; Barnouin, Oliver; Chabot, Nancy; Ernst, Carolyn; Klima, Rachel; Leary, James; Mehr, Lauren; Seifert, Helmut] Johns Hopkins Univ, Appl Phys Lab, 11100 Johns Hopkins Rd, Laurel, MD 20723 USA. [Cohen, Barbara A.] NASA, Marshall Space Flight Ctr, Heliophys & Planetary Sci Off, ZP13, Huntsville, AL 35812 USA. [Sternovsky, Zoltan] Univ Colorado, Lab Atmospher & Space Phys, 1234 Innovat Dr, Boulder, CO 80303 USA. [Helbert, Joern] DLR, Inst Planetary Res, Rutherfordstr 2, D-12487 Berlin, Germany. RP Rivkin, AS (reprint author), Johns Hopkins Univ, Appl Phys Lab, 11100 Johns Hopkins Rd, Laurel, MD 20723 USA. EM Andy.Rivkin@jhuapl.edu; Richard.C.Anderson@jhuapl.edu; Olivier.Barnouin@jhuapl.edu; Nancy.Chabot@jhuapl.edu; Carolyn.Ernst@jhuapl.edu; Rachel.Klima@jhuapl.edu; James.Leary@jhuapl.edu; Lauren.Mehr@jhuapl.edu; Helmut.Seifurt@jhuapl.edu; Barbara.A.Cohen@nasa.gov; Zoltan.Sternovsky@colorado.edu; joern.helbert@dlr.de NR 42 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 13 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374902073 ER PT S AU Royle, AW Yam, LS Pages, RJ AF Royle, Andrew W. Yam, Lorinda S. Pages, Raymond J. GP IEEE TI Development of "Off-Ramp" Methodology for Maintaining Satellite Ground System Schedule SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB The development, integration, and test of satellite ground systems offers significant opportunities to trade cost, schedule, technical capabilities, quality, and risk. However, given that spacecraft missions often have fixed schedules to meet launch windows or maintain constellation health, schedule may become the driving imperative as a launch date approaches. This paper describes a framework for satellite ground system project offices to manage the trade-offs of technical risk and capabilities in order to maintain schedule. The approach established in this paper begins with a prioritization of technical requirements in order to determine launch and mission criticality. Once these priorities are established, candidates for "off-ramps" to eliminate, reduce, or defer technical capability, or to increase technical risk can be defined. Subsequently, as the development, integration, and test schedules progress, trades can be conducted to maintain schedule at the expense of lower-priority requirements, or by increasing the risk posture of the system. The results of these trades, along with the execution status of the off-ramps, can provide a project management team with additional metrics and insight into the health of the project and their ability to meet schedule milestones. The off-ramp framework helps ensure that ground capabilities remain decoupled from the overall system critical path and provides a format in which trades can be analyzed in a structured manner. Off-ramps used as a stand-alone tool or in conjunction with a project's ability to conduct post-launch updates can be a powerful management tool to maintain cost and schedule. C1 [Royle, Andrew W.] Integr Applicat Inc, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Yam, Lorinda S.] ECG Inc, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Pages, Raymond J.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Royle, AW (reprint author), Integr Applicat Inc, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. EM andrew.w.royle@nasa.gov; lorinda.s.yam@nasa.gov; raymond.j.pages@nasa.gov NR 4 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 7 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374901032 ER PT S AU Rucker, MA Jefferies, S Howe, AS Howard, R Mary, N Watson, J Lewis, R AF Rucker, Michelle A. Jefferies, Sharon Howe, A. Scott Howard, Robert Mary, Natalie Watson, Judith Lewis, Ruthan GP IEEE TI Mars Surface Tunnel Element Concept SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB When the first human visitors on Mars prepare to return to Earth, they will have to comply with stringent planetary protection requirements. Apollo Program experience warns that opening an EVA hatch directly to the surface will bring dust into the ascent vehicle. To prevent inadvertent return of potential Martian contaminants to Earth, careful consideration must be given to the way in which crew ingress their Mars Ascent Vehicle (MAV). For architectures involving more than one surface element-such as an ascent vehicle and a pressurized rover or surface habitat-a retractable tunnel that eliminates extravehicular activity (EVA) ingress is an attractive solution. Beyond addressing the immediate MAV access issue, a reusable tunnel may be useful for other surface applications, such as rover to habitat transfer, once its primary mission is complete. A National Aeronautics and Space Administration (NASA) team is studying the optimal balance between surface tunnel functionality, mass, and stowed volume as part of the Evolvable Mars Campaign (EMC). The study team began by identifying the minimum set of functional requirements needed for the tunnel to perform its primary mission, as this would presumably be the simplest design, with the lowest mass and volume. This Minimum Functional Tunnel then becomes a baseline against which various tunnel design concepts and potential alternatives can be traded, and aids in assessing the mass penalty of increased functionality. Preliminary analysis indicates that the mass of a single-mission tunnel is about 237 kg, not including mass growth allowance. C1 [Rucker, Michelle A.; Howard, Robert] NASA, Johnson Space Ctr, 2101 Nasa Pkwy, Houston, TX 77058 USA. [Jefferies, Sharon] NASA, Langley Res Ctr, 1 Langley Blvd, Hampton, VA 23681 USA. [Howe, A. Scott] NASA, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Mary, Natalie] Booz Allen & Hamilton Inc, 2101 Nasa Pkwy, Houston, TX 77058 USA. [Watson, Judith] NASA, Langley Res Ctr, 1 Langley Blvd, Hampton, VA 23666 USA. [Lewis, Ruthan] NASA, Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. RP Rucker, MA (reprint author), NASA, Johnson Space Ctr, 2101 Nasa Pkwy, Houston, TX 77058 USA. EM michelle.a.rucker@nasa.gov; Sharon.a.jefferies@nasa.gov; Scott.Howe@jpl.nasa.gov; robert.l.howard@nasa.gov; natalie.a.mary@nasa.gov; judith.j.watson@nasa.gov; ruthan.lewis@nasa.gov NR 10 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 12 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374903003 ER PT S AU Seery, BD Bambacus, M Leung, R Greenaugh, K Raccah, F Boslough, M Yang, CP AF Seery, Bernard D. Bambacus, Myra Leung, Ron Greenaugh, Kevin Raccah, Fabien Boslough, Mark Yang, Chaowei Phil GP IEEE TI Near Earth Object Mitigation Studies SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE ID CARBONACEOUS CHONDRITE; POROSITY AB Early detection of an object on a collision course with Earth, leading to well-considered and effective measures to mitigate its hazards, is not always possible due to a number of extenuating factors. NASA and the Department of Energy (DOE)'s National Nuclear Security Administration (NNSA) have partnered to develop a full systems framework for understanding very short warning time scenarios requiring high-energy impulsive solutions to neutralize Potentially Hazardous Objects (PHOs) found to be on Earth-impacting trajectories. While previous studies have identified and studied certain aspects of the end-to-end impactor mitigation problem in some detail, the preliminary results for year one of a 3-year research investigation we report on herein will discuss the development of an integrated framework extensible to future data and emergent near-Earth object (NEO) mitigation strategies. As we will discuss, recent increases in computational power and algorithm sophistication now allow new calculations of the response of even irregularly shaped/structured NEOs to various proposed mitigation schemes. Representative energy deposition results on the first of 3 Design Reference Asteroids (DRAs), Bennu, will be included, along with mitigation mission designs and plans for subsequent DRAs. C1 [Seery, Bernard D.; Bambacus, Myra; Leung, Ron] NASA, Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. [Greenaugh, Kevin] Natl Nucl Secur Adm, 1000 Independence Ave SW, Washington, DC 20585 USA. [Raccah, Fabien] SMART LLC, 2709 Quitman Street, Denver, CO 80212 USA. [Boslough, Mark] Sandia Natl Labs, POB 5800, Albuquerque, NM 87185 USA. [Yang, Chaowei Phil] George Mason Univ, 4400 Univ Dr, Fairfax, VA 22030 USA. RP Seery, BD (reprint author), NASA, Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. EM bernard.d.seery@nasa.gov; myra.j.bambacus@nasa.gov; ronald.y.leung@nasa.gov; Kevin.Greenaugh@nnsa.doe.gov; fabienraccah@earthlink.net; mbboslo@sandia.gov; cyang3@gmu.edu RI Yang, Chaowei/A-9881-2017 NR 18 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 12 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374900050 ER PT S AU Seidleck, M Reynolds, S Krygiel, J AF Seidleck, Mark Reynolds, Scott Krygiel, Joseph GP IEEE TI Developing Forward-Looking Metrics to Interpret SPI and CPI Performance Indices for GSFC Projects SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB This paper describes the issues encountered when Earned Value Management (EVM) principles are applied to a non-traditional EVM baseline and the analytical techniques developed by NASA Goddard Space Flight Center's (GSFC) ICEsat-2 project to forecast Cost Performance Index (CPI) and Schedule Performance Index (SPI) performance indices to help determine whether the project would complete within its cost and schedule baseline agreements. C1 [Seidleck, Mark] Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. [Reynolds, Scott; Krygiel, Joseph] InuTeq LLC, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. RP Seidleck, M (reprint author), Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. EM Mark.S.Seidleck@nasa.gov; Scott.F.Reynolds@nasa.gov; Joseph.M.Krygiel@nasa.gov NR 0 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 8 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374900017 ER PT S AU Selva, D Dingwall, B Altunc, S AF Selva, Daniel Dingwall, Brenda Altunc, Serhat GP IEEE TI A Concept for an Agile Mission Development Facility for CubeSat and Suborbital Missions SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE ID PRODUCT PLATFORM DESIGN; EARTH OBSERVATION; SENSOR WEB AB This paper introduces the Agile Mission Development Facility (AMDF), a concept for a new mission development platform at NASAWallops that will develop a specific kind of Earth observing missions based on networks of small assets (CubeSats, UAVs and balloons) in a timeframe of weeks to months. To achieve this reduced development time, the AMDF will use a new catalog-based and platform-based approach to mission design that emphasizes commonality at the subsystem or assembly level and the use of COTS components when possible. This will necessarily constrain the range of performance achievable by these missions, since only a few alternatives will be available for each subsystem. Only missions whose objectives can be achieved through a combination of the available modules will be considered. In addition to providing a high-level description of the AMDF architecture, this paper describes the process by which this platform consisting of a few standard modules will be optimally designed to maximize the range of attainable performance while keeping short development times. Particular emphasis is put on the communications module that will enable cross-links between nanosatellites, UAVs, balloons, and ground assets. Importantly, the AMDF focuses on a different customer segment than other similar NASA facilities such as the IDC at GSFC or Team X at JPL. AMDF Missions are not meant to compete with larger NASA missions in terms of performance, operational risk or mission assurance, but rather they intend to be complementary. In particular, the very short development time and multi-asset character of these systems will enable a completely new class of missions that can effectively respond to a rapidly changing phenomenon of opportunity, such as a hurricane, a volcano or a geopolitical event of interest for which a larger mission would be inappropriate. Additionally, they can be used to accelerate technology infusion for future larger missions, as long as the new technology satisfies a certain set of interface requirements. The AMDF will maximize reuse of existing design, integration and testing software and hardware infrastructure at NASA Wallops as well as other NASA centers. All potentially relevant stakeholders, such as NASA Goddard, Headquarters, JPL, Ames, the Aerospace Corp., Applied Physics Lab, and universities with nanosatellite programs will be involved and considered in the AMDF development process. This paper focuses on the description of the design aspects of the AMDF, as this is where most of the novelty lies. Integration, testing, launching and operations are only briefly discussed. A description of the system architecture of the AMDF is given using model-based systems engineering tools (SysML). An example application mission to measure ecological changes in the Jefferson and Washington National Forests is also discussed to illustrate the new kinds of missions that this facility could enable. C1 [Selva, Daniel] Cornell Univ, 212 Upson Hall, Ithaca, NY 14850 USA. [Dingwall, Brenda] Goddard Space Flight Ctr, Wallops Flight Facil, Wallops Isl, VA 23337 USA. [Altunc, Serhat] Goddard Space Flight Ctr, Greenbelt, MD USA. RP Selva, D (reprint author), Cornell Univ, 212 Upson Hall, Ithaca, NY 14850 USA. EM daniel.selva@cornell.edu; brenda.j.dingwall@nasa.gov; serhat.altunc@nasa.gov NR 47 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 17 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374900068 ER PT S AU Sheldon, C Adams, N Srinivasan, D Hunt, J Pham, T AF Sheldon, Colin Adams, Norman Srinivasan, Dipak Hunt, Jack Pham, Timothy GP IEEE TI In-Flight Pointing Calibration Model of Large Aperture Antennas for Deep Space Missions SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB Large aperture antennas and operations at Ka-band frequencies enable higher data rates for deep space missions but require accurate pointing to realize the desired performance gains due to their inherently narrow beamwidth. We describe an in-flight pointing calibration model to aid the design and analysis of large aperture spacecraft telecommunications systems and to inform requirements on the spacecraft attitude control system (ACS) and ground support equipment. Understanding the expected residual in-flight antenna pointing calibration error allows the determination of the potential need for alternative methods to aid spacecraft high gain antenna pointing. The physically based time domain model incorporates both ground station and spacecraft contributions to the residual in-flight pointing calibration error. Spacecraft contributions are dominated by antenna pointing deviations from the commanded pointing positions due to spacecraft ACS performance limitations. The treatment of residual calibration error within a spacecraft's high gain antenna pointing budget is analyzed. The interpretation of in-flight calibration results is discussed. NASA's Europa mission is used as an example to evaluate the utility of this model for future large aperture deep space missions. The mission proposes to fly a 3-m Ka-band high gain antenna for science data return to Earth. Using typical assumptions for ground and spacecraft performance a 3-s residual pointing calibration error of 0.20 mrad is obtained. C1 [Sheldon, Colin; Adams, Norman; Srinivasan, Dipak; Hunt, Jack] Appl Phys Lab, 11100 Johns Hopkins Rd, Laurel, MD 20723 USA. [Pham, Timothy] Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Sheldon, C (reprint author), Appl Phys Lab, 11100 Johns Hopkins Rd, Laurel, MD 20723 USA. EM colin.sheldon@jhuapl.edu; Timothy.Pham@jpl.nasa.gov NR 7 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 6 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374900087 ER PT S AU Sherman, S Waydo, P Eremenko, A AF Sherman, Sarah Waydo, Peter Eremenko, Alexander GP IEEE TI Launch Vehicle Selection and the Implementation of the Soil Moisture Active Passive Mission SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB Soil Moisture Active Passive (SMAP) is a NASA-developed Earth science satellite currently mapping the soil moisture content and freeze/thaw state of Earth's land mass from a 685km, near-polar, sun-synchronous orbit. It was launched on January 31, 2015 from Vandenberg AFB upon a Delta II 7320 launch vehicle. Due to external considerations, SMAP's launch vehicle selection remained an open item until Project Critical Design Review (CDR). Thus, certain key aspects of the spacecraft design had to accommodate a diverse range of candidate launch vehicle environments, performance envelopes, interfaces and operational scenarios. Engineering challenges stemmed from two distinct scenarios: decisions that had to be made prior to launch vehicle selection to accommodate all possible outcomes, and post-selection changes constrained by schedule and the existing spacecraft configuration. The effects of the timing of launch vehicle selection reached virtually every aspect of the Observatory's design and development. Physical environments, mass allocations, material selections, propulsion system performance, dynamic response, launch phase and mission planning, overall size and configuration, and of course all interfaces to the launch vehicle were heavily dependent on this outcome. This paper will discuss the resolution of these technical challenges. C1 [Sherman, Sarah; Waydo, Peter; Eremenko, Alexander] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Sherman, S (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Sarah.Sherman@jpl.nasa.gov; Peter.J.Waydo@jpl.nasa.gov; Alexander.E.Eremenko@jpl.nasa.gov NR 1 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 9 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374901037 ER PT S AU Shimmin, R Priscal, C Oyadomari, K Murbach, M Alena, R Stone, T Gilstrap, R AF Shimmin, Rogan Priscal, Cedric Oyadomari, Ken Murbach, Marcus Alena, Richard Stone, Thom Gilstrap, Ray GP IEEE TI The Successful PhoneSat Wifi Experiment on the Soarex-8 Flight SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB On the 7th July 2015 at 06: 15 AM EDT a Terrier/Black Brant sounding rocket left the Earth from the Mid-Atlantic Regional Spaceport on Wallops Island in Virginia. On its 10-minute sojourn across the sky and into the sea it carried the 8th Sub-Orbital Aerodynamic Reentry Experiment (Soarex-8) payload. A description of some of the experimental elements on this payload were presented in last year's paper. The elements described (the exobrake, ZigBee wireless sensor net, and Iridium short message communications) were all successful. Another Soarex-8 experiment is described herein: the successful demonstration of point-to-point IEEE 802.11 (wifi) communications from space. We believe this set a new distance record for wifi as well as being the highest wifi-to-ground link, transmitting from the edge of space. Soarex-8 reached an apogee of 334 km (206 mi). During the flight we sent low frame rate video to a ground station at NASA Wallops Flight Facility from payload ejection until loss-of-signal when Soarex-8 passed over the horizon. The Soarex-8 team did not intend to achieve records in this endeavor. We were attempting to establish a very low cost method to downlink high speed data from small spacecraft. We will repeat this experiment as part of a future small spacecraft launch from the International Space Station in the near future. We will then send low frame rate video from orbit. This paper presents the methodology, process and interfaces of the long haul wifi experiment. We discuss an innovative space camera designed at NASA Ames Research Center (ARC) and the camera/wifi interface. We describe the onboard system, power requirements, hardware specifications, interface to the rest of the Soarex-8 payload and hardware integration. Flight software was written to circumvent the handshaking requirement of wifi links and deal with the image stream from the camera. We describe the ground system including the software and how we were able to use existing antenna at Wallops to track and downlink the wifi signal. Finally we present our plans for future orbital and suborbital flights. C1 [Shimmin, Rogan; Priscal, Cedric; Oyadomari, Ken; Murbach, Marcus; Alena, Richard; Stone, Thom; Gilstrap, Ray] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Shimmin, R (reprint author), NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. EM rogan.shimmin@nasa.gov NR 23 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 9 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374903048 ER PT S AU Shinn, SA Bryson, J Klein, G McKeever, J Majerowicz, W Nair, P Ruark, V Wunderlick, L AF Shinn, Stephen A. Bryson, Jonathan Klein, Gerald McKeever, J. Majerowicz, Walt Nair, Param Ruark, Val Wunderlick, Linda GP IEEE TI The Business Change Initiative: A Novel Approach to Improved Cost and Schedule Management SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB Goddard Space Flight Center's Flight Projects Directorate employed a Business Change Initiative (BCI) to infuse a series of activities coordinated to drive improved cost and schedule performance across Goddard's missions. This sustaining change framework provides a platform to manage and implement cost and schedule control techniques throughout the project portfolio. The BCI concluded in December 2014, deploying over 100 cost and schedule management changes including best practices, tools, methods, training, and knowledge sharing. The new business approach has driven the portfolio to improved programmatic performance. The last eight launched GSFC missions have optimized cost, schedule, and technical performance on a sustained basis to deliver on time and within budget, returning funds in many cases. While not every future mission will boast such strong performance, improved cost and schedule tools, management practices, and ongoing comprehensive evaluations of program planning and control methods to refine and implement best practices will continue to provide a framework for sustained performance. This paper will describe the tools, techniques, and processes developed during the BCI and the utilization of collaborative content management tools to disseminate project planning and control techniques to ensure continuous collaboration and optimization of cost and schedule management in the future. C1 [Shinn, Stephen A.; Majerowicz, Walt; Wunderlick, Linda] Goddard Space Flight Ctr, 8800 Greenbelt Rd,Code 400, Greenbelt, MD 20771 USA. [Bryson, Jonathan] Goddard Space Flight Ctr, 8800 Greenbelt Rd,Code 153, Greenbelt, MD 20771 USA. [Klein, Gerald] Goddard Space Flight Ctr, 8800 Greenbelt Rd,Code 470, Greenbelt, MD 20771 USA. [McKeever, J.] Goddard Space Flight Ctr, 8800 Greenbelt Rd,Code 460, Greenbelt, MD 20771 USA. [Nair, Param] Goddard Space Flight Ctr, 8800 Greenbelt Rd,Code 405, Greenbelt, MD 20771 USA. [Ruark, Val] Goddard Space Flight Ctr, Wallops Flight Facil, Code 732, Wallops Isl, VA 23371 USA. RP Shinn, SA (reprint author), Goddard Space Flight Ctr, 8800 Greenbelt Rd,Code 400, Greenbelt, MD 20771 USA. EM stephen.a.shinn@nasa.gov; jonathan.g.bryson@nasa.gov; gerald.a.klein@nasa.gov; j.mckeever@nasa.gov; walt.majerowicz@nasa.gov; param.nair@nasa.gov; val.lunz@nasa.gov; linda.wunderlick@nasa.gov NR 4 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 20 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374902049 ER PT S AU Shotwell, R AF Shotwell, Robert GP IEEE TI History of Mars Ascent Vehicle Development Over the Last 20 Years SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB The Mars Ascent Vehicle concept has seen many studies and development efforts over the last 20 years, up to efforts currently underway by the Mars Program Office. A wide range of concepts have been explored, and many participants over time have been involved. This paper will give an overview of this colorful history, including the context for the individual efforts, the people and organizations involved, and some details of various MAV concepts that have been considered. C1 [Shotwell, Robert] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Shotwell, R (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Robert.Shotwell@jpl.nasa.gov NR 23 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 10 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374903045 ER PT S AU Shotwell, R Benito, J Karp, A Dankanich, J AF Shotwell, Robert Benito, Joel Karp, Ashley Dankanich, John GP IEEE TI Drivers, Developments and Options Under Consideration for a Mars Ascent Vehicle SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB The NASA Mars Exploration Program has invested technology funds over the last couple of years to advance design concepts for a Mars Ascent Vehicle (MAV) and technologies that may be enhancing or enabling for various architectures to be pursued. A Mars Ascent Vehicle would fly on a potential future Mars Lander mission to recover and return the samples to be acquired by the Mars 2020 rover, or another future mission, to a retrievable orbit. Resembling a terrestrial Surface to Air Missile (SAM), the propulsion options considered for the MAV concept span the range from two stage solid rocket motors to monoprops, biprops and hybrids. This paper will highlight the driving constraints and performance requirements and the subsequent trades that would ultimately drive the selection of a chosen approach. C1 [Shotwell, Robert; Benito, Joel; Karp, Ashley] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Dankanich, John] Marshall Spaceflight Ctr, ZP30, Msfc, AL 35812 USA. RP Shotwell, R (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Robert.Shotwell@jpl.nasa.gov; Joel.Benito.Manrique@jpl.nasa.gov; Ashley.C.Karp@jpl.nasa.gov; john.dankanich@nasa.gov NR 4 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 13 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374903044 ER PT S AU Shrestha, R Anagnostou, DE Horst, SJ Hoffman, JP AF Shrestha, Ramila Anagnostou, Dimitris E. Horst, Stephen J. Hoffman, James P. GP IEEE TI Dual-Frequency and Dual-Polarization Antenna Array for Satellite Deployment SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB The development of an aperture coupled microstrip dual-band and dual-polarization 6x6 antenna array system on RO4003C is presented. The antenna array has a multilayer structure that consists of square microstrip elements, placed on each substrate layer to provide dual frequency operation at 14 and 35 GHz. Dual polarization is achieved by using two right-angled microstrip lines and two perpendicular slots to feed the antennas. The microstrip feed line is placed orthogonally from the center of the slot on the ground plane between the substrates. The energy from the microstrip feed line is aperture coupled to each square antenna element through the slot. Two right-angled non-overlapping slots are used on each antenna to enable the two different polarization states. The antenna array has 14 GHz patches on the top substrate layer and 35 GHz patches on the lower substrate layer in order to maintain a similar percentage bandwidth. The microstrip feed lines are located at the bottom of the feed substrate. A symmetric feed structure is followed for the antenna array. The aperture coupling feeding network has the advantage of reduced spurious radiation compared to edge or probe feeds as it utilized highly linearly polarized feed lines and slots, and a large ground plane to prevent backside radiation. The designed antenna array has linear polarization at 45-degrees and 135-degrees at the Ku- and Ka- frequency bands. The array is designed using a hybrid simulation scheme in Keysight Advance Design System (ADS). The ADS Schematic is used for the feed network while the ADS Momentum is used for the antenna elements and the entire array structure simulations. In this way, all aspects of the design (microstrip antenna elements and feed lines) can be optimized independently. This array is suitable for airborne (small remotely piloted), and small-satellite NASA flight programs. C1 [Shrestha, Ramila; Anagnostou, Dimitris E.] South Dakota Sch Mines, ECE Dept, 501 E St Joseph St, Rapid City, SD 57701 USA. [Horst, Stephen J.; Hoffman, James P.] Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Shrestha, R (reprint author), South Dakota Sch Mines, ECE Dept, 501 E St Joseph St, Rapid City, SD 57701 USA. EM ramila.shrestha@mines.sdsmt.edu; danagn@sdsmt.edu; Stephen.J.Horst@jpl.nasa.gov; James.P.Hoffman@jpl.nasa.gov NR 6 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 6 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374903011 ER PT S AU Smith, B Yount, B Kruger, C Brivkalns, C Makino, A Cassell, A Zarchi, K McDaniel, R Ross, J Wercinski, P Venkatapathy, E Swanson, G Gold, N AF Smith, Brandon Yount, Bryan Kruger, Carl Brivkalns, Chad Makino, Alberto Cassell, Alan Zarchi, Kerry McDaniel, Ryan Ross, James Wercinski, Paul Venkatapathy, Ethiraj Swanson, Gregory Gold, Nili GP IEEE TI Nano-ADEPT Aeroloads Wind Tunnel Test SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB A wind tunnel test of the Adaptable Deployable Entry and Placement Technology (ADEPT) was conducted in April 2015 at the US Army's 7x10 Foot Wind Tunnel located at NASA Ames Research Center. Key geometric features of the fabric test article were a 0.7 m deployed base diameter, a 70 degrees half-angle forebody cone angle, eight ribs, and a nose-to-base radius ratio of 0.7. The primary objective of this wind tunnel test was to obtain static deflected shape and pressure distributions while varying pretension at dynamic pressures and angles of attack relevant to entry conditions at Earth, Mars, and Venus. Other objectives included obtaining aerodynamic force and moment data and determining the presence and magnitude of any dynamic aeroelastic behavior (buzz/flutter) in the fabric trailing edge. All instrumentation systems worked as planned and a rich data set was obtained. This paper describes the test articles, instrumentation systems, data products, and test results. Four notable conclusions are drawn. First, test data support adopting a pre-tension lower bound of 10 lbf/in for Nano-ADEPT mission applications. Second, test results indicate that the fabric conditioning process needs to be reevaluated. Third, no flutter/buzz of the fabric was observed for any test condition and should also not occur at hypersonic speeds. Fourth, translating one of the gores caused ADEPT to generate lift without the need for a center of gravity offset. At hypersonic speeds, the lift generated by actuating ADEPT gores could be used for vehicle control. C1 [Smith, Brandon; Yount, Bryan; Kruger, Carl; Brivkalns, Chad; Makino, Alberto; Cassell, Alan; Zarchi, Kerry; McDaniel, Ryan; Ross, James; Wercinski, Paul; Venkatapathy, Ethiraj] NASA, Ames Res Ctr, M-S 229-1, Moffett Field, CA 94035 USA. [Swanson, Gregory] AMA Inc, NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Gold, Nili] US Army AFDD, NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Smith, B (reprint author), NASA, Ames Res Ctr, M-S 229-1, Moffett Field, CA 94035 USA. EM Brandon.P.Smith@nasa.gov NR 4 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 20 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374902035 ER PT S AU Smith, RM Craig, DA Lopez, P AF Smith, R. Marshall Craig, Douglas A. Lopez, Pedro, Jr. GP IEEE TI Proving Ground Potential Flight Test Objectives and Near-Term Architectures SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB NASA is evolving a long-term strategy to pioneer space to expand human and robotic presence farther into the solar system, not just to explore and visit, but to stay. NASA's strategy is designed to meet technical and non-technical challenges, leverage current and near-term activities, and lead to a future where humans can work, learn, operate, and thrive safely in space for an extended, and eventually indefinite, period of time. An important aspect of this strategy is the implementation of proving ground activities needed to ensure confidence in both Mars systems and deep space operations prior to embarking on the journey to Mars. As part of the proving ground development, NASA is assessing potential mission concepts that could validate the required capabilities needed to expand human presence into the solar system. An initial step in the proving ground is to establish human presence in cislunar space to enable development and testing of systems and operations required to enable crewed Mars missions in the 2030s and safely explore other deep space destinations. These capabilities may also be leveraged to support potential commercial and international objectives for lunar surface missions. This paper will identify a series of potential proving ground missions and flight test objectives that support NASA on the journey to Mars and can be leveraged for commercial and international goals. The paper will discuss how early missions will begin to satisfy these objectives, including extensibility and applicability to Mars exploration systems and operations. The initial capability provided by NASA's Space Launch System will be described as well as planned upgrades required to support longer and more complex missions. Potential architectures and mission concepts will be examined as options to satisfy proving ground objectives. In addition, commercial and international participation opportunities will be assessed on their ability to enable the development of exploration capabilities and operations applicable to Mars vicinity and surface missions. C1 [Smith, R. Marshall] NASA Headquarters, Strateg Anal Human Explorat & Operat Mission Dire, 300 E ST SW, Washington, DC USA. [Craig, Douglas A.] NASA Headquarters, 300 E ST SW, Washington, DC USA. [Lopez, Pedro, Jr.] NASA, Johnson Space Ctr, 2101 NASA Pkwy, Houston, TX 77058 USA. RP Smith, RM (reprint author), NASA Headquarters, Strateg Anal Human Explorat & Operat Mission Dire, 300 E ST SW, Washington, DC USA. EM marshall.smith@nasa.gov; douglas.a.craig-1@nasa.gov; pedro.lopez-1@nasa.gov NR 7 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 10 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374901038 ER PT S AU Smith, R Newill-Smith, D Udomkesmalee, G Lee, B Eberly, E Ortega, S Roman, M AF Smith, Russell Newill-Smith, David Udomkesmalee, Gabriel Lee, Brian Eberly, Eric Ortega, Sam Roman, Monsi GP IEEE TI Space Rendezvous and Capture Testbed SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB This paper presents a testbed for autonomous rendezvous and capture of small, high-speed, passive objects. While there have been several successful autonomous rendezvous and docking flight systems, a compact and standardized solution for the retrieval of very small passive objects has yet to be demonstrated. Development of a notional standard, on-orbit sample capture/return architecture would not only enable NASA missions such as potential Mars Sample Return and lunar sample return, but it could also minimize the cost and risks associated with those future missions. The testbed presented in this paper was designed for the Space Rendezvous And Capture Competition (Space RACE), a candidate competition being developed for NASA Centennial Challenges. The competition, in which competitors would build mobile robotic platforms to autonomously chase and capture a mock Orbital Sample (OS), emulates major aspects of proposed on-orbit sample capture: locating and tracking a passive target using limited fiducials, developing an approach algorithm, grappling the target, and manipulating the target for insertion into a notional Sample Return Capsule. These elements would also be pertinent to orbital debris cleanup and terrestrial applications such as warehouse packaging and autonomous harvesting. A prototype was built and successfully used to test the Space RACE concept. The prototype consists of a flat, circular track 17m in diameter, four PulsON 410 Ultra Wideband ranging radios, and a four-wheeled robotic platform called the OS-Bot. An on-board autonomous controller uses the ranging radios in the prototype to calculate the position of the OS-Bot in real-time and follow a predefined, arbitrary path. This method of navigation avoids the use of track-fixed fiducials and allows the simulation of any orbital scenario. The system also supports mounting of additional radios on competitor platforms, allowing for minimally invasive monitoring of competitor position and velocity. These aspects both prevent competitors from merely "line-following" to the OS and allow the simulation of numerous mission scenarios which approximate orbital dynamics. Results are presented in this paper for the successful testing of this platform using low resolution sensors in an environment subject to frequent multi-path ranging errors. In addition, a filter is presented which could improve the response of the controller and deliver more robust operation. C1 [Smith, Russell; Newill-Smith, David; Udomkesmalee, Gabriel] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Lee, Brian] CALTECH, 961 E Calif Blvd 223, Pasadena, CA 91106 USA. [Eberly, Eric; Ortega, Sam; Roman, Monsi] NASA Centennial Challenges, Huntsville, AL USA. RP Smith, R (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Russell.G.Smith@jpl.nasa.gov; David.E.Newill-Smith@jpl.nasa.gov; Suraphol.Udomkesmalee@jpl.nasa.gov; Bllee@caltech.edu; Eric.A.Eberly@nasa.gov; Sam.Ortega@nasa.gov; Monsi.Roman@nasa.gov NR 3 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 10 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374904023 ER PT S AU Snyder, JS Manzella, D Lisman, D Lock, RE Nicholas, A Woolley, R AF Snyder, John Steven Manzella, David Lisman, Doug Lock, Robert E. Nicholas, Austin Woolley, Ryan GP IEEE TI Additional Mission Applications for NASA's 13.3-kW Ion Propulsion System SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB NASA's Space Technology Mission Directorate has been recently developing critical technologies for high-power solar electric propulsion (SEP), including large deployable solar array structures and high-power electric propulsion components. An ion propulsion system based on these developments has been considered for many SEP technology demonstration missions, including the Asteroid Redirect Robotic Mission (ARRM) concept. These studies and the high-power SEP technology developments have generated excitement within NASA about the use of the ARRM ion propulsion system design for other types of potential missions. One application of interest is for Mars missions, especially with the types of orbiters now under consideration for flights in the early 2020's to replace the aging Mars Reconnaissance Orbiter. High-power SEP can deliver large payloads to Mars with many additional capabilities, including large orbital plane changes and round-trip missions, compared to chemically-propelled spacecraft. Another application for high-power SEP is for exo-planet observation missions, where a large starshade spacecraft would need to be repositioned with respect to its companion telescope relatively frequently and rapidly. SEP is an enabling technology for the ambitious science goals of these types of missions. This paper will discuss the benefits of high-power SEP for these concepts based on the STMD technologies now under development. C1 [Snyder, John Steven; Lisman, Doug; Lock, Robert E.; Nicholas, Austin; Woolley, Ryan] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Manzella, David] NASA, Glenn Res Ctr, 21000 Brookpark Rd, Cleveland, OH 44135 USA. RP Snyder, JS (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Steve.Snyder@jpl.nasa.gov; David.Manzella@nasa.gov; P.D.Lisman@jpl.nasa.gov; Robert.E.Lock@jpl.nasa.gov; Austin.K.Nicholas@jpl.nasa.gov; Ryan.C.Woolley@jpl.nasa.gov NR 19 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 13 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374903094 ER PT S AU Spaulding, M Eremenko, A Comandur, S Brennan, C Berman, S AF Spaulding, Matthew Eremenko, Alexander Comandur, Subha Brennan, Carolyn Berman, Simmie GP IEEE TI Discussion of the Driving Aspects for the Design and Layout of the Europa Project Radiation Vault SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB This paper discusses the challenges faced in packaging of radiation-sensitive electronics for the Europa project. In order to minimize shielding mass, an efficient layout of electronics within the vault is necessary to keep shielding area to a minimum while providing protection from the severe radiation environment surrounding Jupiter. Tight placement of internal electronics can, however, result in integration difficulties due to access problems for mounting hardware, routing constraints for harness management and vault wall penetrations, as well as thermal requirements for the enclosed electronics. Each of these aspects play into the configurations and integration requirements of the baseline Europa project vault. In order to study the potential geometries for the vault, conceptual physical models have been constructed, as well as multiple CAD based geometries in order to study potential layout configurations. These configurations have leveraged prior mission experience from the Curiosity rover as well as the JUNO radiation vault. C1 [Spaulding, Matthew; Eremenko, Alexander; Comandur, Subha; Brennan, Carolyn] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Berman, Simmie] Johns Hopkins Univ, Appl Phys Lab, 111000 Johns Hopkins Rd, Laurel, MD 20723 USA. RP Spaulding, M (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Matthew.D.Spaulding@jpl.nasa.gov; Alexander.E.Eremenko@jpl.nasa.gov; Subha.Comandur@jpl.nasa.gov; Carolyn.Brennan@jpl.nasa.gov; Simmie.Berman@jhuapl.edu NR 2 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 7 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374900085 ER PT S AU Spry, JA Race, M Rummel, J Conley, C AF Spry, J. Andy Race, Margaret Rummel, John Conley, Catharine GP IEEE TI Unanswered Questions in the Development of Planetary Protection Policy and Implementation for the Human Exploration of Mars SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB Ahead of the arrival of humans on Mars, which would be the culmination of the evolvable Mars campaign and the horizon goal on which NASA has set its sights, a new body of knowledge needs to be generated to ensure that this activity can be done safely. Not only in the engineering sense, but also in the sense of protecting both the astronauts and Mars from harmful contamination between "biospheres" (should there be a biosphere at Mars). This presentation will discuss the precursor knowledge that is needed to protect the integrity of science data from putative Mars biota during human exploration activities, as well as the information needed to preserve the health of the crew without compromising their effectiveness in exploration, or their return to Earth without threatening the terrestrial biosphere on which we all depend. C1 [Spry, J. Andy; Race, Margaret; Rummel, John] SETI Inst, 189 Bernardo Ave, Mountain View, CA 94043 USA. [Conley, Catharine] NASA Headquarters, 300 E St SW, Washington, DC 20546 USA. RP Spry, JA (reprint author), SETI Inst, 189 Bernardo Ave, Mountain View, CA 94043 USA. EM aspry@seti.org; mrace@seti.org; jrummel@seti.org; cassie.conley@nasa.gov NR 15 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 8 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374903090 ER PT S AU Starek, JA Schmerling, E Maher, GD Barbee, BW Pavone, M AF Starek, Joseph A. Schmerling, Edward Maher, Gabriel D. Barbee, Brent W. Pavone, Marco GP IEEE TI Real-Time, Propellant-Optimized Spacecraft Motion Planning under Clohessy-Wiltshire-Hill Dynamics SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE ID PROXIMITY OPERATIONS; GUIDANCE AB This paper presents a sampling-based motion planning algorithm for real-time, propellant-optimized autonomous spacecraft trajectory generation in near-circular orbits. Specifically, this paper leverages recent algorithmic advances in the field of robot motion planning to the problem of impulsivelyactuated, propellant-optimized rendezvous and proximity operations under the Clohessy-Wiltshire-Hill (CWH) dynamics model. The approach calls upon a modified version of the Fast Marching Tree (FMT*) algorithm to grow a set of feasible and actively-safe trajectories over a deterministic, low-dispersion set of sample points covering the free state space. Key features of the proposed algorithm include: (i) theoretical guarantees of trajectory safety and performance, (ii) real-time implementability, and (iii) generality, in the sense that a large class of constraints can be handled directly. As a result, the proposed algorithm offers the potential for widespread application, ranging from on-orbit satellite servicing to orbital debris removal and autonomous inspection missions. C1 [Starek, Joseph A.; Pavone, Marco] Stanford Univ, Aeronaut & Astronaut, Stanford, CA 94305 USA. [Schmerling, Edward; Maher, Gabriel D.] Stanford Univ, Inst Computat & Math Engn, Stanford, CA USA. [Barbee, Brent W.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Starek, JA (reprint author), Stanford Univ, Aeronaut & Astronaut, Stanford, CA 94305 USA. EM jstarek@stanford.edu; schmrlng@stanford.edu; gdmaher@stanford.edu; brent.w.barbee@nasa.gov; pavone@stanford.edu NR 36 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 16 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374902020 ER PT S AU Sturm, EJ AF Sturm, Erick J., II GP IEEE TI Contingency Planning for Cassini's Final Mission Phase SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB During the eleven years that the Cassini spacecraft has spent in Saturn orbit, it has flown throughout the Saturnian System. One place it has never been, however, is between Saturn's rings and atmosphere, which is exactly where it is headed for its final months. Two environmental factors pose a risk to the spacecraft in this region: D Ring dust and thermosphere density. Dust particle impacts could potentially damage sensitive components of the spacecraft or instruments. High thermospheric densities could cause the spacecraft to lose attitude control and tumble. Fortunately, these factors are anticorrelated; dust particle counts increase with radial distance whereas atmospheric density decreases, leaving a corridor of reduced risk between the rings and atmosphere. While this corridor reduces risk to the spacecraft, it does not eliminate it. Additional risk reduction could be had by restricting the spacecraft to certain orientations while within the corridor; however, this would come at the expense of science, as the safest orientations do not point the instruments in preferred directions. As such, a compromise must be achieved between risk reduction and science satisfaction. The Cassini Project maintains environmental contingency plans to respond to the uncertainties in the proximal corridor: the dustiness of the D ring and the thickness of the thermosphere. The contingency plans allow the nominal flight plan to use science-friendly orientations while within the corridor, which could then be superseded by a safer orientation should a contingency need to be invoked. This paper describes the contingency plans for dealing with deviations from the predicted environment in the proximal corridor. Moreover, it details the predicted environments, methods for detecting deviations from the predictions, the nominal flight plan, and the method for implementing the contingency responses into the spacecraft activity sequence. C1 [Sturm, Erick J., II] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Sturm, EJ (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Erick.J.Sturm@jpl.nasa.gov NR 5 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 8 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374901016 ER PT S AU Suhir, E Ghaffarian, R Bechou, L Nicolics, J AF Suhir, E. Ghaffarian, R. Bechou, L. Nicolics, J. GP IEEE TI Column-Grid-Array (CGA) Technology Could Lead to a Highly Reliable Package Design SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE ID FATIGUE LIFE PREDICTION; SOLDER JOINTS; RELIABILITY; SNAGCU; MODELS AB An analytical stress model is developed for a short cylinder (beam) with clamped and offset ends. The offset is caused by an external lateral force that has to be determined from the known offset. It is envisioned that such a beam can adequately mimic the stresses and strains in a column of a column-grid-array (CGA) solder joint interconnection. Such an interconnection is characterized by an elevated stand-off height of the solder joints compared to the joints in a widely used today ball-grid-array (BGA) system. In a simplified and conservative analysis the ends offset in a CGA joint can be determined beforehand as a product of the known thermal mismatch strain between the IC package and the printed circuit board (PCB), and the position of the joint with respect to the package mid-cross-section. The objective of our analysis is to use the developed model to demonstrate that the application of CGA technology enables one not only to significantly relieve the thermally induced stresses in the solder material, but to do that to an extent that the induced stresses remain within the elastic range. The analysis is limited therefore to elastic deformations. It should be emphasized that while the classical Timoshenko short-beam theory seeks the beam's deflections caused by the combined bending and shear deformations for the given loading, an inverse problem is considered here: the lateral force and the induced stresses are sought for the given end offset. In short beams this force is larger than in long beams, since, in order to achieve the given displacement (offset), the applied force has to overcome both bending and shear resistance of the beam. The carried out analysis and the numerical data indicate that by employing beam-like CGA solder joints one could possibly manage to remain within the elastic range, i.e. to avoid inelastic strains and, hence, low cycle fatigue conditions. If this is achievable, the fatigue lifetime of the solder material will increase dramatically, because the low-cycle fatigue condition will be replaced by the linear accumulation of elastic damages. The numerical example indicates that the stand-off of the CGA joint should be rather large to make the shearing stress low compared to the normal bending stress. The height-to-diameter ratio of the CGA joint should be increased to the level of about 12-13. In such a situation the Bernoulli beam model, could be used instead of Timoshenko model for stress evaluations. The further increase in the stand-off height over this ratio, even if it is technologically achievable, is not advisable, since this will not lead to an appreciable further stress reduction. Future work will include, but might not be limited to, the finite-element-analysis (FEA) computations and experimental evaluations (such as, e.g., shear-off testing and/or temperature cycling) of the induced stresses in, and the fatigue lifetime of, typical BGA and novel CGA joints. We would like to point out that a solder joint in isolation is neither reliable nor unreliable, and that reliability has meaning only in the context of interconnections either within package or outside of package onto PCB. For this reason the future work should include also better understanding of how to translate the stress relief in a single joint into the improved reliability of an interconnection as a whole, thereby leading to a highly-reliable solder joint interconnections and, since these interconnections are the bottle-neck of the today's IC packaging technologies, to a highly reliable package design as a whole. Particularly, for BGA/CGA package assemblies, it is critical to determine the effective offset values for the peripheral joints. C1 [Suhir, E.] Portland State Univ, Portland, OR 97207 USA. [Suhir, E.] Vienna Univ Technol, Vienna, Austria. [Suhir, E.] Ariel Univ, Ariel, Israel. [Suhir, E.] ERS Co LLC, 727 Alvina Ct, Los Altos, CA 94024 USA. [Ghaffarian, R.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Bechou, L.] Univ Bordeaux 1, Lab IMS, UMR CNRS 5218, Bat A31,351 Cours Liberat, F-33405 Talence, France. [Nicolics, J.] Vienna Univ Technol, Dept Appl Elect Mat, AEM, Inst Sensor & Actuator Syst, Gusshausstr 27-29, A-1010 Vienna, Austria. RP Suhir, E (reprint author), Portland State Univ, Portland, OR 97207 USA.; Suhir, E (reprint author), Vienna Univ Technol, Vienna, Austria.; Suhir, E (reprint author), Ariel Univ, Ariel, Israel.; Suhir, E (reprint author), ERS Co LLC, 727 Alvina Ct, Los Altos, CA 94024 USA. EM suhire@aol.com; reza.ghaffarian@jpl.nasa.gov; laurent.bechou@ims-bordeaux.fr; johann.nicolics@tuwien.ac.at NR 30 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 7 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374900006 ER PT S AU Swan, C AF Swan, Christopher GP IEEE TI Automated Commanding of the SMAP Spacecraft Enables Efficient, Reliable, and Responsive Operations SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB The Soil Moisture Active Passive (SMAP) mission developed and deployed a system to autonomously handle most routine commanding of the observatory. This system of ground software is able to build commands, validate them, and radiate the commands to the spacecraft, all without human interaction. In the case of an off-nominal scenario, the system will abort gracefully and notify the mission operations team of the problem. The system was phased into operations during the first three months of the SMAP mission and handles over 90% of the weekly commanding of the vehicle. The gradual introduction of the automation in flight, along with an extensive test campaign, was instrumental in the success of the software. The automation has enabled substantial efficiencies in operations team staffing and has improved reliability by removing the potential for human error. The system also allows the SMAP project to be more responsive which has shown significant benefits in areas of data latency and science accuracy. C1 [Swan, Christopher] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Swan, C (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Christopher.A.Swan@jpl.nasa.gov NR 4 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 8 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374901044 ER PT S AU Tabiryan, N Xianyu, H Roberts, D Liao, Z Steeves, D Kimball, B Serabyn, E Mawet, D AF Tabiryan, N. Xianyu, H. Roberts, D. Liao, Z. Steeves, D. Kimball, B. Serabyn, E. Mawet, D. GP IEEE TI 4G Optics for Communications and Astronomy SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE ID PHOTON SIEVE; LENSES AB The fourth generation of optics uses modulation of optical axis orientation in anisotropic materials for achieving a wide variety of optical functions. 4G optical components blend the thinness of zero-order waveplates with the high efficiency one gets with Bragg volume holographic gratings and in a broad band of wavelengths typical of conventional glass lenses, prisms, etc. (the first generation of optics). We will discuss the technology for applications in communications and astronomy. Particularly, we will present challenges and opportunities for fabrication of vector vortex waveplates and cross-waveplates for coronagraphy, and waveplate lenses - Pancharatnam-Berry phase lenses - for optical communications and imaging. C1 [Tabiryan, N.; Xianyu, H.; Roberts, D.; Liao, Z.] BEAM Engn Adv Measurements Co, 1300 Lee Rd, Orlando, FL 32810 USA. [Steeves, D.; Kimball, B.] US Army Natick Soldier, Res Dev & Engn Ctr, 15 Gen Greene Ave, Natick, MA 01760 USA. [Serabyn, E.; Mawet, D.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Tabiryan, N (reprint author), BEAM Engn Adv Measurements Co, 1300 Lee Rd, Orlando, FL 32810 USA. EM nelson@beamco.com; haiqing@beamco.com; david.roberts@beamco.com; zliao@beamco.com; diane.m.steeves.civ@mail.mil; brian.r.kimball.civ@mail.mil; eserabyn@s383.jpl.nasa.gov; dmawet@astro.caltech.edu NR 20 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 8 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374904052 ER PT S AU Thorpe, AK Frankenberg, C Green, RO Thompson, DR Aubrey, AD Mouroulis, P Eastwood, ML Matheou, G AF Thorpe, Andrew K. Frankenberg, Christian Green, Robert O. Thompson, David R. Aubrey, Andrew D. Mouroulis, Pantazis Eastwood, Michael L. Matheou, Georgios GP IEEE TI The Airborne Methane Plume Spectrometer (AMPS): Quantitative Imaging of Methane Plumes in Real Time SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE ID CARBON-DIOXIDE OBSERVATIONS; COLUMN-AVERAGED METHANE; EMISSION RATES; RETRIEVAL; AVIRIS; QUANTIFICATION; MARSHES; SYSTEM; MAMAP; OIL AB The Airborne Methane Plume Spectrometer (AMPS) is a mature instrument concept that is ready for development at the Jet Propulsion Laboratory (JPL). At its core is a novel high-resolution imaging spectrometer that records solar reflected light between 1.99 and 2.42 mu m at 1 nm resolution, including strong methane (CH4) bands in the short-wave infrared. The push-broom spectrometer will leverage recent advancements in grating design and large-format 2D focal plane arrays to enable-for the first time-the high spectral resolution necessary for trace gas retrievals combined with high-performance imaging capabilities developed for surface remote sensing. AMPS features a 36 degrees field of view with 600 resolved spatial elements across track (1 mRad) and 431 pixels in the spectral dimension. All other aspects of the instrument, such as the telescope, cryo-cooler, image stabilizer, GPS, are identical to available airborne JPL spectrometers in operation. The AMPS design is based on the next generation Airborne Visible Infrared Imaging Spectrometer (AVIRIS-NG), which has been used for high resolution mapping of CH4 concentrations from a controlled release experiment [1] and over existing natural gas fields [2]. A real time CH4 plume detection capability originally developed for AVIRIS-NG and successfully demonstrated over oil fields [3] will also be implemented with AMPS. This will facilitate surveys over existing oil and gas fields to identify and attribute CH4 emissions to individual point source locations, permit adaptive surveys with repeat imaging of suspected sources, and allow real time communication to site operators or ground crews equipped with additional instruments to verify observed plumes. AMPS will enable quantitative imaging of CH4 plumes at unprecedented spatial resolution and precision. Using a slow moving platform such as a helicopter at 100 m flight altitude (60 m image swath) will permit imaging CH4 enhancements at 10 cm spatial resolution and an unprecedented accuracy of 0.05 g CH4/m(2). This will allow robust detection of CH4 emissions as low as 0.17 m(3)/h (6 standard cubic feet per hour), an order of magnitude smaller than what current airborne systems can detect. Using fixed-wing aircraft, AMPS can also be flown faster and higher (1 to 8 km flight altitude), thereby providing larger image swaths (0.6 to 4.8 km swaths respectively) and effective large scale surveys. Mapping CH4 emissions to individual point source locations could allow site operators to identify and mitigate these emissions, which reflect both a potential safety hazard and lost revenue. For the regulatory and scientific communities, understanding the distribution (spatial, temporal) and size of these emissions is of interest given the large uncertainties associated with anthropogenic emissions, including industrial point source emissions and fugitive CH4 from oil and gas infrastructure. C1 [Thorpe, Andrew K.; Frankenberg, Christian; Green, Robert O.; Thompson, David R.; Aubrey, Andrew D.; Mouroulis, Pantazis; Eastwood, Michael L.; Matheou, Georgios] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Thorpe, AK (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Andrew.K.Thorpe@jpl.nasa.gov RI Frankenberg, Christian/A-2944-2013 OI Frankenberg, Christian/0000-0002-0546-5857 NR 31 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 14 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374902072 ER PT S AU Tirona, J AF Tirona, Joseph GP IEEE TI On the Maneuvers Operational Response for NASA's Soil Moisture Active-Passive (SMAP) Mission SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB The Soil-Moisture Active-Passive (SMAP) spacecraft requires various kinds of in-orbit maneuvers over the course of its three-year mission. The types of maneuvers include pre-planned commissioning maneuvers to reach its science orbit, regularly executed orbit maintenance maneuvers to overcome drag and other nominally occurring phenomena, as well as (the possibility of) collision avoidance maneuvers. The architecture of the spacecraft - in terms of availability of commanding via ground assets, the inherited avionics' ability to sequence and execute commands, and the capability of available subsystems able to carry out maneuvers - was well defined early in the development of the spacecraft and mission, well before the operational plan for responding to maneuver requests was cemented. [2] The systems engineering challenge became: how to accommodate all three types of maneuvers in the confines of this well-defined architecture. This paper will describe how the operations team on SMAP successfully met this challenge. Specifically, it will dive into the three pronged approach that SMAP developed to handle each type of maneuver described above - to meet the timeliness requirements leveraged on the operations team to execute said maneuvers, while continuing to fit within the allotted staffing profile during nominal operations. Defining this paradigm to fit the mission's architecture meant re-defining the original paradigm, (planned maneuvers being thought of separately than collision avoidance maneuvers), and re-classifying all responses to maneuver requests as variations and permutations of a singular operational response to a maneuver request. This paper will also describe the tools that were created to simplify the human interface and automate as much of the response as was possible. Finally, this paper will describe, at a very high level, some of the problems encountered and lessons learned by the operations team when this process was executed the first four times during the first ninety days of operations. Though the architecture of the operations team's response to maneuver requests will never be repeated exactly, the flexibility that was inserted via redefining the scope of the problem and by redefining the human interfaces should influence future projects' architectures earlier in their development -in the hopes that said influence will save time and money in the future. C1 [Tirona, Joseph] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Tirona, J (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Joseph.F.Tirona@jpl.nasa.gov NR 2 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 6 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374900014 ER PT S AU Toda, R Bae, Y Grimes-York, J Badescu, M Vieira, P Moreland, S Backes, P Manohara, H AF Toda, Risaku Bae, Youngsam Grimes-York, Jesse Badescu, Mircea Vieira, Peter Moreland, Scott Backes, Paul Manohara, Harish GP IEEE TI FiSI: Fiberscope Sample Imaging System for Robotic Comet Surface Sample Return Missions SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB This paper discusses the Fiberscope Sample Imaging (FiSI) system currently being developed for a potential robotic comet surface sample return mission. In this mission concept, the spacecraft would perform touch-and-go maneuver at a small body to collect a comet surface sample. Immediately after the sample is captured the FiSI would perform in situ verification of the comet sample. Sample volume would be estimated and images of the collected sample acquired and evaluated. If the captured sample volume were deemed insufficient, the sample collection maneuver would be re-attempted, multiple times if necessary, until a baseline sample volume was positively confirmed. This repeatability would improve the potential science outcome of the sample return mission. Our proof-of-concept FiSI hardware consists of nine imaging fiberscopes integrated into a single bundle. The nine fiberscopes are designed to provide wide swath coverage of overlapping fields of view within a sample measurement station. The achieved image resolution is in excess of 4 linepair/mm at 20 mm working distance. Surface color and texture of a comet sample simulant would clearly be discernible at this fidelity. The distal end of these fiberscopes are designed to tolerate harsh temperature and radiation environments near a comet while sensitive electronics and optical components at the proximal end can be placed in a more benign electronics bay of the notional spacecraft. An early FiSI prototype was tested in a -50 degrees C chamber and showed no image degradation. To study the FiSI proof-of-concept system response in a microgravity-like environment, a preliminary experiment was attempted using a neutral buoyancy sample. The test result was consistent with Monte Carlo simulation. C1 [Toda, Risaku; Bae, Youngsam; Grimes-York, Jesse; Badescu, Mircea; Vieira, Peter; Moreland, Scott; Backes, Paul; Manohara, Harish] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Bae, Youngsam] Ellipse Technol, Aliso Viejo, CA USA. RP Toda, R (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Risaku.Toda@jpl.nasa.gov; Harish.Manohara@jpl.nasa.gov NR 9 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 10 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374902031 ER PT S AU Toups, L Hoffman, SJ Watts, K AF Toups, Larry Hoffman, Stephen J. Watts, Kevin GP IEEE TI Mars Surface Systems Common Capabilities and Challenges for Human Missions SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE ID MANGALA VALLES AB This paper describes the current status of common systems and operations as they are applied to actual locations on Mars that are representative of Exploration Zones (EZ) NASA's term for candidate locations where humans could land, live and work on the martian surface. Given NASA's current concepts for human missions to Mars, an EZ is a collection of Regions of Interest (ROIs) located within approximately 100 kilometers of a centralized landing site. ROIs are areas that are relevant for scientific investigation and/or development/maturation of capabilities and resources necessary for a sustainable human presence. An EZ also contains a habitation site that will be used by multiple human crews during missions to explore and utilize the ROIs within the EZ. The Evolvable Mars Campaign (EMC), a description of NASA's current approach to these human Mars missions, assumes that a single EZ will be identified within which NASA will establish a substantial and durable surface infrastructure that will be used by multiple human crews. With this assumption it becomes important to evaluate the current suite of surface systems and operations being evaluated for the EMC are likely to perform at a variety of proposed EZ locations. Four locations identified in MEPAG's Human Exploration of Mars Science Analysis Group (HEM-SAG) report are used in this paper as representative of candidate EZs that will emerge from the selection process that NASA has initiated. A field station site plan is developed for each of these four HEM-SAG sites. Several important findings have emerged from these preliminary assessments: (1) at each of the four HEM-SAG sites there was a 10 km x 10 km area at or near the proposed landing site within which it is reasonable to set up a landing site and habitation site consistent with the needs of a Mars surface field station, (2) at each of these 10 km x 10 km sites it is possible to set up a central location for a common power system and locate the landing and habitation zones in a radial configuration around this power system. However, additional analysis will be needed to look at alternative site layouts that could "better" utilize the natural features of a particular site, and (3) with the possible exception of a climb to the top of Arsia Mons, all of the proposed traverses appear to be feasible for the small pressurized rover currently envisioned for these surface missions. Based on these findings our recommendation is to continue (a) the selection process of EZs used in the recent workshop that will lead to one or more optimum surface locations, (b) continue to evaluate the minimum functionality required to establish a surface field station within the center of an EZ, and (c) identify those demonstrations that could be conducted at the Mars surface field station utilizing local resources to gradually establish the Earth independence necessary to sustain crews for long periods of time. C1 [Toups, Larry; Watts, Kevin] NASA, Johnson Space Ctr, 2101 NASA Pkwy, Houston, TX 77058 USA. [Hoffman, Stephen J.] Sci Applicat Int Corp, 2450 NASA Pkwy, Houston, TX 77058 USA. RP Toups, L (reprint author), NASA, Johnson Space Ctr, 2101 NASA Pkwy, Houston, TX 77058 USA. EM larry.toups-1@nasa.gov; stephen.j.hoffman@nasa.gov; kevin.d.watts@nasa.gov NR 20 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 18 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374902087 ER PT S AU Tung, RH AF Tung, Ramona H. GP IEEE TI Development of Effective and Efficient Operations for NASA's Soil Moisture Active Passive Mission SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB NASA's Soil Moisture Active Passive (SMAP) is an earth orbiting mission which launched 1/31/2015, successfully completed an aggressive Commissioning plan, and is currently collecting Science data. A 90-day, activity-rich Launch and Commissioning Phase required 7 days per week operations with heavy staffing. It was followed by a steep ramp down to a very small operations team performing mostly unattended ("lights out") operations. Completing Commissioning ahead of schedule despite major inflight anomalies was made possible by transitioning development experts into operations, preparing sequences for all baseline activities and selected contingency scenarios prior to Launch, and developing tools to streamline routine activities (sequence generation/validation, data management, telemetry query and reporting, long term trending). Powerful operations analysis tools coupled with development experience allowed the team to quickly troubleshoot, work around, and recover from a variety of significant anomalies (including several safemode entries) and still maintain schedule. To enable lights out operation, SMAP developed a reliable infrastructure relying heavily on automation. Orbit determination was successfully automated to simplify Navigation. Automatic command generation and radiation was implemented for benign routine commanding. This capability was phased in during Commissioning, and now accounts for 95-100% of SMAP commanding during the week. SMAP also developed reliable autonomous monitoring and notification systems for non-receipt of data, detection of anomalous data, and auto-commanding failures. Upon detection of problems, SMAP uses a role-based email/text notification tool to disposition anomalies. These capabilities allow the SMAP mission operations center to be largely unattended. System engineers are cross-trained to perform numerous tasks including command radiation, scheduling, and sequence integration and testing. Choosing simplification over optimization allows most tasks to be performed by a handful of people. These are some of the efficiencies that have enabled successful small team operations in the Science Phase. C1 [Tung, Ramona H.] Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Tung, RH (reprint author), Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Ramona.H.Tung@jpl.nasa.gov NR 2 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 11 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374900092 ER PT S AU Vaughan, D Nakazono, B Karp, A Shotwell, R London, A Mehra, A Mechentel, F AF Vaughan, David Nakazono, Barry Karp, Ashley Shotwell, Robert London, Adam Mehra, Amit Mechentel, Flora GP IEEE TI Technology Development and Design of Liquid Bi-Propellant Mars Ascent Vehicles SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB A notional Mars Ascent Vehicle (MAV), that could help with potential Mars Sample Return (MSR) is a very unique challenge and has been the focus of technology development and design efforts at JPL for the several years. Trajectory studies, for the current range of potential MAV payloads, evaluated performance using propulsion systems in the 2.5 kN to 4.5kN (600-1000 lbf) thrust range. The current study examined several propulsion system approaches, solid rocket, bi-propellant and hybrid propulsion systems and developed a ranking based on several key figures of merit. This paper details the trades conducted for the two bi-propellant propulsion systems considered for a potential MAV. Historically bi-propellant propulsion systems have been considered for this application, however the desire to minimize development risk resulted in solid rocket options being selected as the baseline configuration. This study takes a fresh look at both a conventional pressure fed bi-propellant propulsion system and a new technology development using a small electrically driven pump fed bi-propellant propulsion system. A detailed design and mass breakdown for both a pressure fed and a low- complexity electrically driven pump fed (EDPF) propulsion system for a potential MAV were generated. The results showed that the EDPF system although lower in technology readiness level (TRL) provided performance, mass and packaging benefits that ranked EPDF higher than a conventional pressure fed system. C1 [Vaughan, David; Nakazono, Barry; Karp, Ashley; Shotwell, Robert] Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [London, Adam; Mehra, Amit] 1142 Howard St, San Francisco, CA 94103 USA. [Mechentel, Flora] 450 Serra Mall, Stanford, CA 94305 USA. RP Vaughan, D (reprint author), Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM David.A.Vaughan@jpl.nasa.gov; Amit.mehra@ventions.com; Floram@stanford.edu NR 5 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 10 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374903055 ER PT S AU Venkatapathy, E Beck, R Ellerby, D Feldman, J Gage, P Munk, M Wercinski, P AF Venkatapathy, Ethiraj Beck, Robin Ellerby, Donald Feldman, Jay Gage, Peter Munk, Michelle Wercinski, Paul GP IEEE TI Development Challenges of Game-Changing Entry System Technologies From Concept to Mission Infusion SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB NASA's Space Technology Mission Directorate (STMD) and the Game Changing Development Program (GCDP) were created to develop new technologies. This paper describes four entry system technologies that are funded by the GCDP and summarizes the lessons learned during the development. The investments are already beginning to show success, mission infusion pathways after five years of existence. It is hoped that our experience and observations, drawn from projects supported by the GCD program/STMD, Orion and SMD can help current and future technology development projects. Observations on fostering a culture of success and on constraints that limit greater success are also provided. C1 [Venkatapathy, Ethiraj; Beck, Robin; Ellerby, Donald; Wercinski, Paul] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Feldman, Jay] AMA Inc, Moffett Field, CA 94035 USA. [Gage, Peter] Neerim Corp, Moffett Field, CA 94035 USA. [Munk, Michelle] NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Venkatapathy, E (reprint author), NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. EM ethiraj.venkatapathy-1@nasa.gov; robin.a.beck@nasa.gov; donald.t.ellerby@nasa.gov; jay.d.feldman@nasa.gov; pgage@neerimcorp.com; Michelle.m.munk@nasa.gov; paul.wercinski@nasa.gov NR 17 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 13 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374903002 ER PT S AU Ward, ED Mundo, D Frerking, MA de Weck, OL AF Ward, Eric D. Mundo, Diego Frerking, Margaret A. de Weck, Olivier L. GP IEEE TI Engineering Change Activity Analysis of Space Mission Projects SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB Engineering changes and their propagation through a system provide insight into the complexity of a system. In an effort to identify systematic trends, we have analyzed two very different JPL-led space mission projects to classify the change activity and assess change propagation. The projects selected are a Mars lander mission, Mars Science Laboratory (MSL), and an Earth-orbiting mission, Soil Moisture Active Passive (SMAP). Change in space system development is recorded with engineering change requests (ECRs). ECRs can be regarded as an indicator of the progression of work. We employ time analysis of ECR initiation throughout the lifecycle, correlate ECR generators with ECR absorbers, and consider the distribution of ECRs across subsystems. Further, we analyze ECR-document and ECR-ECR networks to assess project interaction. These analyses give us insight into the similarities and differences between these projects. For both SMAP and MSL, similar subsystems generate or absorb change. However, SMAP followed a progression in which change was damped over time, whereas MSL often saw acceleration of change. The two projects also differed with regard to change management, with SMAP using a hierarchical approach while MSL interactions were more widely distributed. C1 [Ward, Eric D.; Mundo, Diego; de Weck, Olivier L.] MIT, 77 Massachusetts Ave, Cambridge, MA 02139 USA. [Frerking, Margaret A.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Ward, ED (reprint author), MIT, 77 Massachusetts Ave, Cambridge, MA 02139 USA. EM ericward@mit.edu; dmundo@mit.edu; margaret.a.frerking@jpl.nasa.gov; deweck@mit.edu NR 7 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 11 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374902009 ER PT S AU Wargo, CA DiFelici, J Roy, A Glaneuski, J Kerczewski, R AF Wargo, Chris A. DiFelici, John Roy, Aloke Glaneuski, Jason Kerczewski, Robert GP IEEE TI Crowd Sourcing Approach for UAS Communication Resource Demand Forecasting SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB Congressional attention to Unmanned Aircraft Systems (UAS)(1) has caused the Federal Aviation Administration (FAA) to move the National Airspace System (NAS) Integration project forward, but using guidelines, practices and procedures that are yet to be fully integrated with the FAA Aviation Management System. The real drive for change in the NAS will to come from both UAS operators and the government jointly seeing an accurate forecast of UAS usage demand data. This solid forecast information would truly get the attention of planners. This requires not an aggregate demand, but rather a picture of how the demand is spread across small to large UAS, how it is spread across a wide range of missions, how it is expected over time and where, in terms of geospatial locations, will the demand appear. In 2012 the Volpe Center performed a study of the overall future demand for UAS. This was done by aggregate classes of aircraft types. However, the realistic expected demand will appear in clusters of aircraft activities grouped by similar missions on a smaller geographical footprint and then growing from those small cells. In general, there is not a demand forecast that is tightly coupled to the real purpose of the mission requirements (e.g. in terms of real locations and physical structures such as wind mills to inspect, farms to survey, pipelines to patrol, etc.). Being able to present a solid basis for the demand is crucial to getting the attention of investment, government and other fiscal planners. To this end, Mosaic ATM under NASA guidance is developing a crowd sourced, demand forecast engine that can draw forecast details from commercial and government users and vendors. These forecasts will be vetted by a governance panel and then provide for a sharable accurate set of projection data. Our paper describes the project and the technical approach we are using to design and create access for users to the forecast system. C1 [Wargo, Chris A.; DiFelici, John] Mosa ATM Inc, 540 Ft Evans Rd,NE Suite, Leesburg, VA 20176 USA. [Roy, Aloke] Honeywell Int, 7000 Columbia Gateway Dr, Columbia, MD 21046 USA. [Glaneuski, Jason] Volpe Natl Transportat Syst Ctr, 55 Broadway, Cambridge, MA 02142 USA. [Kerczewski, Robert] NASA, Glenn Res Ctr, Natl Aeronaut & Space Adm, 21000 Brookpk Rd MS 54-2, Cleveland, OH 44135 USA. RP Wargo, CA (reprint author), Mosa ATM Inc, 540 Ft Evans Rd,NE Suite, Leesburg, VA 20176 USA. EM cwargo@mosaicatm.com; jdifelici@mosaicatm.com; Aloke.Roy@Honeywell.com; Jason.Glaneuski@dot.gov; rkerczewski@nasa.gov NR 2 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 14 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374902012 ER PT S AU Warner, N Silverman, M Samuels, J DeFlores, L Sengstacken, A Maki, J Scodary, A Peters, S Litwin, T Metz, B AF Warner, Noah Silverman, Milo Samuels, Jessica DeFlores, Lauren Sengstacken, Aaron Maki, Justin Scodary, Anthony Peters, Stephen Litwin, Todd Metz, Brandon GP IEEE TI The Mars Science Laboratory Remote Sensing Mast SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB The Mars Science Laboratory Remote Sensing Mast (RSM) was built to deploy, point and protect science instruments and navigation cameras used by the Curiosity rover in her mission to explore Gale Crater on Mars. The mechanical design of the RSM and the payload accommodation details are described along with some of the more difficult challenges faced in the assembly, test and operations phases of the mission. Details of the flight software design that allowed the team to meet tight pointing requirements and protect the sun-sensitive ChemCam instrument from the hazard of direct sun exposure are presented. Basic operations and early results of the performance of the mast on Mars are reviewed. C1 [Warner, Noah; Silverman, Milo; Samuels, Jessica; DeFlores, Lauren; Sengstacken, Aaron; Maki, Justin; Scodary, Anthony; Peters, Stephen; Litwin, Todd; Metz, Brandon] Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Warner, N (reprint author), Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Noah.Z.Warner@jpl.nasa.gov NR 3 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 8 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374900058 ER PT S AU Wham, R Onuschak, B Sutliff, T AF Wham, Robert Onuschak, Becky Sutliff, Thomas GP IEEE TI Plutonium-238 Supply Project-Additional Processing Enabling Power for Future NASA Missions SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB For more than five decades, Radioisotope Power Systems (RPSs) have enabled space missions to operate in locations where the Sun's intensity is either too dim, obscured, or otherwise inadequate for solar power or other conventional power ff generation technologi. The natural decay of the radioisotope plutonium-238 (Pu-238) provides the heat source used by an RPS to generate electricity (as well as heat to keep key subsystems warm) for National Aeronautics and Space Administration (NASA) missions such as Voyagers 1 and 2, the Cassini mission to Saturn, the New Horizons flyby of Pluto, and the Mars Curiosity rover. The United States has not produced new 238Pu since the late 1980s. RPS ff powered missions have continued since then using existi Pu-238 inventory managed by the U. S. Department of Energy (DOE), including material purchased from Russia. NASA and DOE have determined that a new domestic supply is needed to ensure the continued availability of RPSs for future NASA missions. Using funding provided by NASA since 2011, DOE is currently executing a project to reestablish a Pu-238 supply capability using its existing facilities and reactors. The project, known as the Plutonium-238 Supply Project (PSP) is led by the DOE Oak Ridge National Laboratory (ORNL). This paper will provide an overview of the PSP approach, its progress to date, and the potential benefits to NASA of missions that could be enabled by the new production of Pu-238. C1 [Wham, Robert] Oak Ridge Natl Lab, POB 2008, Oak Ridge, TN 37831 USA. [Onuschak, Becky] US DOE, 19901 Germantown Rd, Germantown, MD 20874 USA. [Sutliff, Thomas] NASA, Radioisotope Power Syst Program Off, Glenn Res Ctr, 21000 Brookpk Rd M-S 142-5, Cleveland, OH 44135 USA. RP Wham, R (reprint author), Oak Ridge Natl Lab, POB 2008, Oak Ridge, TN 37831 USA. EM whamrm@ornl.gov; Rebecca.Onuschak@nuclear.energy.gov; tsutliff@nasa.gov NR 5 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 9 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374901020 ER PT S AU Whitley, R Martinez, R AF Whitley, Ryan Martinez, Roland GP IEEE TI Options for Staging Orbits in Cislunar Space SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB NASA has been studying options to conduct missions beyond Low Earth Orbit, but within the Earth-Moon system, in preparation for deep space exploration including human missions to Mars. Referred to as the Proving Ground, this arena of exploration activities will enable the development of human spaceflight systems and operations to satisfy future exploration objectives beyond the cislunar environment. One option being considered includes the deployment of a habitable element or elements, which could be used as a central location for aggregation of supplies and resources for human missions in cislunar space and beyond. Characterizing candidate orbit locations for this asset and the impacts on system design and mission operations is important in the overall assessment of the options being considered. The orbits assessed in this paper were previously identified in work conducted by NASA and others. In this paper orbits are assessed for their relative attractiveness based on various factors. First, a set of constraints related to the capability of the combined Orion and Space Launch System (SLS) system to deliver humans and cargo to and from the orbit are evaluated. Second, the ability to support potential lunar surface activities is considered. Finally, deployed assets intended to spend multiple years in the Proving Ground would ideally require minimal station keeping costs to reduce the mass budget allocated to this function. Additional mission design drivers include potential for uninterrupted communication with deployed assets, thermal, communications, and other operational implications. The results of the characterization and evaluation of the selected orbits indicate a Near Rectilinear Orbit (NRO) is an attractive candidate as an aggregation point or staging location for operations. In this paper, the NRO is further described in terms which balance a number of key attributes that favor a variety of mission classes to meet multiple, sometimes competing, constraints. C1 [Whitley, Ryan; Martinez, Roland] NASA, Johnson Space Ctr, 2101 NASA Pkwy, Houston, TX 77058 USA. RP Whitley, R (reprint author), NASA, Johnson Space Ctr, 2101 NASA Pkwy, Houston, TX 77058 USA. EM ryan.j.whitley@nasa.gov; roland.m.martinez@nasa.gov NR 33 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 9 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374901043 ER PT S AU Wilmot, J Fesq, L Dvorak, D AF Wilmot, Jonathan Fesq, Lorraine Dvorak, Dan GP IEEE TI Quality Attributes for Mission Flight Software: A Reference for Architects SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB In the international standards for architecture descriptions in systems and software engineering (ISO/IEC/IEEE 42010), "concern" is a primary concept that often manifests itself in relation to the quality attributes or "ilities" that a system is expected to exhibit - qualities such as reliability, security and modifiability. One of the main uses of an architecture description is to serve as a basis for analyzing how well the architecture achieves its quality attributes, and that requires architects to be as precise as possible about what they mean in claiming, for example, that an architecture supports "modifiability." This paper describes a table, generated by NASA's Software Architecture Review Board, which lists fourteen key quality attributes, identifies different important aspects of each quality attribute and considers each aspect in terms of requirements, rationale, evidence, and tactics to achieve the aspect. This quality attribute table is intended to serve as a guide to software architects, software developers, and software architecture reviewers in the domain of mission-criticalreal-time embedded systems, such as space mission flight software. C1 [Wilmot, Jonathan] NASA, Goddard Spaceflight Ctr, Greenbelt, MD 20771 USA. [Fesq, Lorraine; Dvorak, Dan] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Wilmot, J (reprint author), NASA, Goddard Spaceflight Ctr, Greenbelt, MD 20771 USA. EM Jonathan.J.Wilmot@NASA.gov; Lorraine.M.Fesq@jpl.nasa.gov; Daniel.L.Dvorak@jpl.nasa.gov NR 9 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 7 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374903072 ER PT S AU Winternitz, LMB Mitchell, JW Hassouneh, MA Valdez, JE Price, SR Semper, SR Yu, WH Ray, PS Wood, KS Arzoumanian, Z Gendreau, KC AF Winternitz, Luke M. B. Mitchell, Jason W. Hassouneh, Munther A. Valdez, Jennifer E. Price, Samuel R. Semper, Sean R. Yu, Wayne H. Ray, Paul S. Wood, Kent S. Arzoumanian, Zaven Gendreau, Keith C. GP IEEE TI SEXTANT X-ray Pulsar Navigation Demonstration: Flight System and Test Results SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB The Station Explorer for X-ray Timing and Navigation Technology (SEXTANT) is a technology demonstration enhancement to the Neutron-star Interior Composition Explorer (NICER) mission. NICER is a NASA Explorer Mission of Opportunity that will be hosted on the International Space Station (ISS). SEXTANT will, for the first time, demonstrate real-time, on-board X-ray Pulsar Navigation (XNAV), a significant milestone in the quest to establish a GPS-like navigation capability available throughout our Solar System and beyond. This paper gives an overview of the SEXTANT system architecture and describes progress prior to environmental testing of the NICER flight instrument. It provides descriptions and development status of the SEXTANT flight software and ground system, as well as detailed description and results from the flight software functional and performance testing within the highfidelity Goddard Space Flight Center (GSFC) X-ray Navigation Laboratory Testbed (GXLT) software and hardware simulation environment. Hardware-in-the-loop simulation results are presented, using the engineering model of the NICER timing electronics and the GXLT pulsar simulator-the GXLT precisely controls NASA GSFC's unique Modulated X-ray Source to produce X-rays that make the NICER detector electronics appear as if they were aboard the ISS viewing a sequence of millisecond pulsars. C1 [Winternitz, Luke M. B.; Mitchell, Jason W.; Hassouneh, Munther A.; Valdez, Jennifer E.; Price, Samuel R.; Semper, Sean R.; Yu, Wayne H.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Ray, Paul S.; Wood, Kent S.] Naval Res Lab, Washington, DC 20375 USA. [Arzoumanian, Zaven] NASA GSFC USRA, Greenbelt, MD 20771 USA. [Gendreau, Keith C.] NASA GSFC, Code 662, Greenbelt, MD 20771 USA. RP Winternitz, LMB (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. EM luke.b.winternitz@nasa.gov NR 15 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 12 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374903060 ER PT S AU Wood, P Gramling, C Reiter, J Smith, P Stone, J AF Wood, Paul Gramling, Cheryl Reiter, Jennifer Smith, Patrick Stone, John GP IEEE TI Commissioning MMS: Challenges and Lessons Learned SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB This paper discusses commissioning of NASA's Magnetospheric MultiScale (MMS) Mission. The mission includes four identical spacecraft with a large, complex set of instrumentation. The planning for and execution of commissioning for this mission is described. The paper concludes by discussing lessons learned. C1 [Wood, Paul; Stone, John] Southwest Res Inst, 6220 Culebra Rd, San Antonio, TX 78238 USA. [Gramling, Cheryl] NASA, Goddard Space Flight Ctr, Code 595,Greenbelt Rd, Greenbelt, MD 20771 USA. [Reiter, Jennifer; Smith, Patrick] Lab Atmospher & Space Phys, 1234 Innovat Dr, Boulder, CO 80303 USA. RP Wood, P (reprint author), Southwest Res Inst, 6220 Culebra Rd, San Antonio, TX 78238 USA. EM Paul.Wood@swri.org; cheryl.j.gramling@nasa.gov; jennifer.reiter@lasp.colorado.edu; pat.smith@lasp.colorado.edu; John.Stone@swri.org NR 5 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 15 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374901069 ER PT S AU Woollard, BA Braun, RD Bose, D AF Woollard, Bryce A. Braun, Robert D. Bose, Deepak GP IEEE TI Aerothermodynamic and Thermal Protection System Instrumentation Reference Guide SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE ID RECONSTRUCTION; DESCENT; ENTRY AB The hypersonic regime of planetary entry combines the most severe environments that an entry vehicle will encounter with the greatest amount of uncertainty as to the events unfolding during that time period. This combination generally leads to conservatism in the design of an entry vehicle, specifically that of the thermal protection system (TPS). Each planetary entry provides a valuable aerodynamic and aerothermal testing opportunity; the utilization of this opportunity is paramount in better understanding how a specific entry vehicle responds to the demands of the hypersonic entry environment. Previous efforts have been made to instrument entry vehicles in order to collect data during the entry period and reconstruct the corresponding vehicle response. The purpose of this paper is to cumulatively document past TPS instrumentation designs for applicable planetary missions, as well as to list pertinent results and any explainable shortcomings. C1 [Woollard, Bryce A.; Braun, Robert D.] Georgia Inst Technol, Space Syst Design Lab, 270 Ferst Dr, Atlanta, GA 30332 USA. [Bose, Deepak] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Woollard, BA (reprint author), Georgia Inst Technol, Space Syst Design Lab, 270 Ferst Dr, Atlanta, GA 30332 USA. EM bwoollard3@gatech.edu; robert.braun@ae.gatech.edu; deepak.bose@nasa.gov NR 32 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 22 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374900060 ER PT S AU Yang, GN Lu, W Krainak, M Sun, XL AF Yang, Guangning Lu, Wei Krainak, Michael Sun, Xiaoli GP IEEE TI High-Precision Ranging and Range-Rate Measurements over Free-Space-Laser Communication Link SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE DE Space Optical ranging; Doppler range rate; Doppler ranging; space optical navigation; space optical communication; formation fly AB We present a high-precision ranging and range-rate measurement system via an optical-ranging or combined ranging-communication link. A complete bench-top optical communication system was built. It included a ground terminal and a space terminal. Ranging and range rate tests were conducted in two configurations. In the communication configuration with 622 data rate, we achieved a two-way range-rate error of 2 m/s, or a modified Allan deviation of 9x10(-15) with 10 second averaging time. Ranging and range-rate as a function of Bit Error Rate of the communication link is reported. They are not sensitive to the link error rate. In the single-frequency amplitude modulation mode, we report a two-way range rate error of 0.8 m/s, or a modified Allan deviation of 2.6x10(-15) with 10 second averaging time. We identified the major noise sources in the current system as the transmitter modulation injected noise and receiver electronics generated noise. A new improved system will be constructed to further improve the system performance for both operating modes. C1 [Yang, Guangning] NASA, Goddard Space Flight Ctr, Code 661, Greenbelt, MD 20771 USA. [Lu, Wei] NASA, Goddard Space Flight Ctr, ASRC Fed Inc, Code 661, Greenbelt, MD 20771 USA. [Krainak, Michael] NASA, Goddard Space Flight Ctr, Laser & Elect Opt Branch, Code 661, Greenbelt, MD 20771 USA. [Sun, Xiaoli] NASA, Goddard Space Flight Ctr, Solar Syst Explorat Div, Code 661, Greenbelt, MD 20771 USA. RP Yang, GN (reprint author), NASA, Goddard Space Flight Ctr, Code 661, Greenbelt, MD 20771 USA. EM Guangning.yang-1@nasa.gov NR 15 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 13 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374901060 ER PT S AU Zacny, K Paulsen, G Yaggi, B Wang, A Mellerowicz, B Hyman, C Hedlund, M Quinn, J Smith, J AF Zacny, Kris Paulsen, Gale Yaggi, Bryan Wang, Alex Mellerowicz, Bolek Hyman, Cody Hedlund, Magnus Quinn, Jackie Smith, Jim GP IEEE TI Resource Prospector Drill Performance During The Integrated Payload Tests SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB The goal of the Lunar Resource Prospector (RP) is to capture and evaluate volatile species within the top meter of the lunar regolith. The RP drill has been designed to 1. Generate cuttings and place them on the surface for analysis by the Near InfraRed Volatiles Spectrometer Subsystem (NIRVSS), and 2. Capture cuttings and transfer them to the Oxygen and Volatile Extraction Node (OVEN) coupled with the Lunar Advanced Volatiles Analysis (LAVA) subsystem. The drill auger is designed to capture cuttings as opposed to cores. The lower auger section has deep and low pitch flutes for retaining of cuttings. The upper section has been designed to efficiently move the cuttings out of the hole. The drill uses a "bite" sampling approach where samples are captured in similar to 10 cm intervals. The drill has been integrated with the NASA JSC RP rover prototype and tested in the summer of 2015. This paper describes the drill and test results. C1 [Zacny, Kris; Paulsen, Gale; Yaggi, Bryan; Wang, Alex; Mellerowicz, Bolek; Hyman, Cody; Hedlund, Magnus] Honeybee Robot, 398 W Washington Blvd,Suite 200, Pasadena, CA 91103 USA. [Quinn, Jackie; Smith, Jim] NASA, Kennedy Space Ctr, FL 32899 USA. RP Zacny, K (reprint author), Honeybee Robot, 398 W Washington Blvd,Suite 200, Pasadena, CA 91103 USA. EM zacny@honeybeerobotics.com; paulsen@honeybeerobotics.com; yaggi@honeybeerobotics.com; wang@honeybeerobotics.com; mellerowicz@honeybeerobotics.com; hyman@honeybeerobotics.com; hedlund@honeybeerobotics.com; jacqueline.w.quinn@nasa.gov; james.t.smith@nasa.gov NR 7 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 7 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374900039 ER PT S AU Zakrajsek, JF Woerner, DF Cairns-Gallimore, D Johnson, SG Qualls, L AF Zakrajsek, June F. Woerner, Dave F. Cairns-Gallimore, Dirk Johnson, Stephen G. Qualls, Louis GP IEEE TI NASA's Radioisotope Power Systems Planning and Potential Future Systems Overview SO 2016 IEEE AEROSPACE CONFERENCE SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT IEEE Aerospace Conference CY MAR 05-12, 2016 CL Big Sky, MT SP IEEE AB The goal of NASA's Radioisotope Power Systems (RPS) Program is to make RPS ready and available to support the exploration of the solar system in environments where the use of conventional solar or chemical power generation is impractical or insufficient to meet the needs of the missions. To meet this goal, the RPS Program, working closely with the Department of Energy, performs mission and system studies (such as the recently released Nuclear Power Assessment Study), assesses the readiness of promising technologies to infuse in future generators, assesses the sustainment of key RPS capabilities and knowledge, forecasts and tracks the Program's budgetary needs, and disseminates current information about RPS to the community of potential users. This process has been refined and used to determine the current content of the RPS Program's portfolio. This portfolio currently includes an effort to mature advanced thermoelectric technology for possible integration into an enhanced Multi-Mission Radioisotope Generator (eMMRTG), sustainment and production of the currently deployed MMRTG, and technology investments that could lead to a future Stirling Radioisotope Generator (SRG). This paper describes the program planning processes that have been used, the currently available MMRTG, and one of the potential future systems, the eMMRTG. C1 [Zakrajsek, June F.] NASA, Glenn Res Ctr, 21000 Brookpk Rd, Cleveland, OH 44135 USA. [Woerner, Dave F.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91011 USA. [Cairns-Gallimore, Dirk] US DOE, 19901 Germantown Rd, Germantown, MD 20874 USA. [Johnson, Stephen G.] Idaho Natl Lab, 2525 Freemont Ave, Idaho Falls, ID 83415 USA. [Qualls, Louis] Oak Ridge Natl Lab, 1 Bethel Valley Rd, Oak Ridge, TN 37831 USA. RP Zakrajsek, JF (reprint author), NASA, Glenn Res Ctr, 21000 Brookpk Rd, Cleveland, OH 44135 USA. EM june.f.zakrajsek@nasa.gov; david.f.woerner@jpl.nasa.gov; dirk.cairns-gallimore@nuclear.energy.gov; stephen.johnson@inl.gov; quallsal@ornl.org NR 9 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4673-7676-1 J9 AEROSP CONF PROC PY 2016 PG 10 WC Engineering, Aerospace SC Engineering GA BG3XT UT WOS:000388374901054 ER PT S AU Luckow, KS Pasareanu, CS AF Luckow, Kasper S. Pasareanu, Corina S. GP IEEE TI Log2model: Inferring Behavioral Models from Log Data SO 2016 IEEE INTERNATIONAL HIGH LEVEL DESIGN VALIDATION AND TEST WORKSHOP (HLDVT) SE IEEE International High Level Design Validation and Test Workshop LA English DT Proceedings Paper CT 18th IEEE International High Level Design Validation and Test Workshop (HLDVT) CY OCT 07-08, 2016 CL Santa Cruz, CA SP IEEE, IEEE Comp Soc, IEEE Test Technol Techn Council ID BUSINESS PROCESSES AB We present LOG2MODEL, an approach, supported by a tool, that builds behavioral models from log data. The logged data consists of time series encoding the values of the states of a system observed at discrete time steps. The models generated are Discrete-Time Markov Chains with states and transitions representing the values recorded in the log. The models contain key information that can be visualized and analyzed with respect to safety, delays, throughput etc, using off-the-shelf model checkers such as PRISM. The analysis results can be further used by users or automated tools to monitor and alter the system behavior. We present the architecture of LOG2MODEL and its application in the context of autonomous operations in the airspace domain. C1 [Luckow, Kasper S.; Pasareanu, Corina S.] Carnegie Mellon Univ Silicon Valley, Mountain View, CA 94035 USA. [Pasareanu, Corina S.] NASA, Ames Res Ctr, Mountain View, CA USA. RP Luckow, KS (reprint author), Carnegie Mellon Univ Silicon Valley, Mountain View, CA 94035 USA. NR 19 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1552-6674 BN 978-1-5090-4270-8 J9 INT HIGH LEVEL DESIG PY 2016 BP 25 EP 29 PG 5 WC Computer Science, Interdisciplinary Applications; Computer Science, Software Engineering SC Computer Science GA BG4PK UT WOS:000389035600004 ER PT S AU Davies, AG Chien, S Tran, D Doubleday, J AF Davies, Ashley Gerard Chien, Steve Daniel Tran Doubleday, Joshua BE Harris, AJL DeGroeve, T Garel, F Carn, SA TI The NASA Volcano Sensor Web, advanced autonomy and the remote sensing of volcanic eruptions: a review SO DETECTING, MODELLING AND RESPONDING TO EFFUSIVE ERUPTIONS SE Geological Society Special Publication LA English DT Review; Book Chapter ID SCIENCECRAFT EXPERIMENT; SATELLITE DATA; EYJAFJALLAJOKULL; SPACE; EO-1; HYPERION; KILAUEA AB The Volcano Sensor Web (VSW) is a globe-spanning net of sensors and applications for detecting volcanic activity. Alerts from the VSW are used to trigger observations from space using the Earth Observing-1 (EO-1) spacecraft. Onboard EO-1 is the Autonomous Sciencecraft Experiment (ASE) advanced autonomy software. Using ASE has streamlined spacecraft operations and has enabled the rapid delivery of high-level products to end-users. The entire process, from initial alert to product delivery, is autonomous. This facility is of great value as a rapid response is vital during a volcanic crisis. ASE consists of three parts: (1) Science Data Classifiers, which process EO-1 Hyperion data to identify anomalous thermal signals; (2) a Spacecraft Command Language; and (3) the Continuous Activity Scheduling Planning Execution and Replanning (CASPER) software that plans and replans activities, including downlinks, based on available resources and operational constraints. For each eruption detected, thermal emission maps and estimates of eruption parameters are posted to a website at the Jet Propulsion Laboratory, California Institute of Technology, in Pasadena, CA. Selected products are emailed to end-users. The VSW uses software agents to detect volcanic activity alerts generated from a wide variety of sources on the ground and in space, and can also be easily triggered manually. C1 [Davies, Ashley Gerard; Chien, Steve; Daniel Tran; Doubleday, Joshua] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Davies, AG (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Ashley.Davies@jpl.nasa.gov NR 48 TC 0 Z9 0 U1 0 U2 0 PU GEOLOGICAL SOC PUBLISHING HOUSE PI BATH PA UNIT 7, BRASSMILL ENTERPRISE CTR, BRASSMILL LANE, BATH BA1 3JN, AVON, ENGLAND SN 0305-8719 BN 978-1-86239-736-1 J9 GEOL SOC SPEC PUBL JI Geol. Soc. Spec. Publ. PY 2016 VL 426 BP 137 EP 158 PG 22 WC Geochemistry & Geophysics; Geology; Remote Sensing SC Geochemistry & Geophysics; Geology; Remote Sensing GA BG3YB UT WOS:000388378700007 ER PT S AU Patrick, MR Kauahikaua, J Orr, T Davies, A Ramsey, M AF Patrick, M. R. Kauahikaua, J. Orr, T. Davies, A. Ramsey, M. BE Harris, AJL DeGroeve, T Garel, F Carn, SA TI Operational thermal remote sensing and lava flow monitoring at the Hawaiian Volcano Observatory SO DETECTING, MODELLING AND RESPONDING TO EFFUSIVE ERUPTIONS SE Geological Society Special Publication LA English DT Article; Book Chapter ID KILAUEA VOLCANO; SATELLITE DATA; FIELD OBSERVATIONS; OLDOINYO LENGAI; MAUNA-LOA; ERUPTION; ASTER; MODIS; RESOLUTION; EVENTS AB Hawaiian volcanoes are highly accessible and well monitored by ground instruments. Nevertheless, observational gaps remain and thermal satellite imagery has proven useful in Hawai`i for providing synoptic views of activity during intervals between field visits. Here we describe the beginning of a thermal remote sensing programme at the US Geological Survey Hawaiian Volcano Observatory (HVO). Whereas expensive receiving stations have been traditionally required to achieve rapid downloading of satellite data, we exploit free, low-latency data sources on the internet for timely access to GOES, MODIS, ASTER and EO-1 ALI imagery. Automated scripts at the observatory download these data and provide a basic display of the images. Satellite data have been extremely useful for monitoring the ongoing lava flow activity on Kilauea's East Rift Zone at Pu`u `O`o over the past few years. A recent lava flow, named Kahauale `a2, was upslope from residential subdivisions for over a year. Satellite data helped track the slow advance of the flow and contributed to hazard assessments. Ongoing improvement to thermal remote sensing at HVO incorporates automated hotspot detection, effusion rate estimation and lava flow forecasting, as has been done in Italy. These improvements should be useful for monitoring future activity on Mauna Loa. C1 [Patrick, M. R.; Kauahikaua, J.; Orr, T.] US Geol Survey, Hawaiian Volcano Observ, POB 51,Hawaii Natl Pk, Volcano, HI 96718 USA. [Davies, A.] NASA, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Ramsey, M.] Univ Pittsburgh, Dept Geol & Planetary Sci, 4107 OHara St, Pittsburgh, PA 15260 USA. RP Patrick, MR (reprint author), US Geol Survey, Hawaiian Volcano Observ, POB 51,Hawaii Natl Pk, Volcano, HI 96718 USA. EM mpatrick@usgs.gov NR 60 TC 0 Z9 0 U1 0 U2 0 PU GEOLOGICAL SOC PUBLISHING HOUSE PI BATH PA UNIT 7, BRASSMILL ENTERPRISE CTR, BRASSMILL LANE, BATH BA1 3JN, AVON, ENGLAND SN 0305-8719 BN 978-1-86239-736-1 J9 GEOL SOC SPEC PUBL JI Geol. Soc. Spec. Publ. PY 2016 VL 426 BP 489 EP 503 PG 15 WC Geochemistry & Geophysics; Geology; Remote Sensing SC Geochemistry & Geophysics; Geology; Remote Sensing GA BG3YB UT WOS:000388378700026 ER PT S AU Harris, AJL Carn, S Dehn, J Del Negro, C Gudmundsson, MT Cordonnier, B Barnie, T Chahi, E Calvari, S Catry, T De Groeve, T Coppola, D Davies, A Favalli, M Ferrucci, F Fujita, E Ganci, G Garel, F Huet, P Kauahikaua, J Kelfoun, K Lombardo, V Macedonio, G Pacheco, J Patrick, M Pergola, N Ramsey, M Rongo, R Sahy, F Smith, K Tarquini, S Thordarson, T Villeneuve, N Webley, P Wright, R Zaksek, K AF Harris, A. J. L. Carn, S. Dehn, J. Del Negro, C. Gudmundsson, M. T. Cordonnier, B. Barnie, T. Chahi, E. Calvari, S. Catry, T. De Groeve, T. Coppola, D. Davies, A. Favalli, M. Ferrucci, F. Fujita, E. Ganci, G. Garel, F. Huet, P. Kauahikaua, J. Kelfoun, K. Lombardo, V. Macedonio, G. Pacheco, J. Patrick, M. Pergola, N. Ramsey, M. Rongo, R. Sahy, F. Smith, K. Tarquini, S. Thordarson, T. Villeneuve, N. Webley, P. Wright, R. Zaksek, K. BE Harris, AJL DeGroeve, T Garel, F Carn, SA TI Conclusion: recommendations and findings of the RED SEED working group SO DETECTING, MODELLING AND RESPONDING TO EFFUSIVE ERUPTIONS SE Geological Society Special Publication LA English DT Editorial Material; Book Chapter ID ROBUST SATELLITE TECHNIQUES; LAVA FLOW HAZARD; CELLULAR-AUTOMATA MODEL; MOUNT-ETNA; KILAUEA VOLCANO; ACTIVE VOLCANOS; SPATIAL-RESOLUTION; FIELD OBSERVATIONS; TEMPERATURE-FIELD; STROMBOLI VOLCANO C1 [Harris, A. J. L.; Barnie, T.; Kelfoun, K.] Univ Blaise Pascal, Lab Magmas & Volcans, CNRS, IRD,OPGC, 5 Rue Kessler, F-63038 Clermont Ferrand, France. [Carn, S.] Michigan Technol Univ, Dept Geol & Min Engn & Sci, 1400 Townsend Dr, Houghton, MI 49931 USA. [Dehn, J.; Webley, P.] Univ Alaska Fairbanks, Inst Geophys, 903 Koyukuk Dr, Fairbanks, AK 99775 USA. [Del Negro, C.; Calvari, S.; Ganci, G.] Osservatorio Etneo INGV, Inst Nazl Geofis & Vulcanol, Sez Catania, Piazza Roma 2, I-95125 Catania, Italy. [Gudmundsson, M. T.; Thordarson, T.] Univ Iceland, Inst Earth Sci, Sturlugata 7, IS-101 Reykjavik, Iceland. [Chahi, E.; Sahy, F.] Game Developers, 5 Rue Martins Pecheurs, F-34000 Montpellier, France. [Catry, T.] SEAS OI, UMR Espace Dev 228, UAG, UM2,IRD,UR, 40 Ave Soweto,CS 70561, St Pierre 97447, Reunion. [De Groeve, T.] European Commiss, Joint Res Ctr, Inst Protect & Secur Citizen, Via E Fermi, I-21027 Ispra, VA, Italy. [Coppola, D.] Univ Turin, Dipartimento Sci Terra, Via Valperga Caluso 35, I-10125 Turin, Italy. [Davies, A.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Favalli, M.; Tarquini, S.] Ist Nazl Geofis & Vulcanolo, Sez Pisa, Via Faggiola 32, I-56126 Pisa, Italy. [Ferrucci, F.] Open Univ, Deptartment Environm Earth & Ecosyst, Milton Keynes MK7 6AA, Bucks, England. [Ferrucci, F.] Univ Calabria, Deptartment Environm & Chem Engn, Ponte Bucci 44A, I-87036 Arcavacata Di Rende, CS, Italy. [Fujita, E.] Natl Res Inst Earth Sci & Disaster Prevent, Tennodai 3-1, Tsukuba, Ibaraki 3050006, Japan. [Garel, F.] Univ Montpellier, Geosci Montpellier, Pl Eugene Bataillon, F-34095 Montpellier, France. [Huet, P.] La Cite Volcan, Bourg Murat RN3, Le Tampon, Reunion. [Kauahikaua, J.; Patrick, M.] US Geol Survey, Hawaiian Volcano Observ, POB 22,Hawaii Natl Pk, Volcano, HI 96718 USA. [Lombardo, V.] Ist Nazl Geofis & Vulcanol, Ctr Nazl Terremoti, Via Vigna Murata 605, I-00143 Rome, Italy. [Macedonio, G.] Osserv Vesuviano, Ist Nazl Geofis & Vulcanol, Via Diocleziano 328, I-80124 Naples, Italy. [Pacheco, J.] Univ Acores, Ctr Vulcanol & Avaliacao Riscos Geol, Edificio Complexo Cient,3 Piso, P-9501801 Ala Sul, Ponta Delgada, Portugal. [Pergola, N.] CNR, Ist Metodol Anal Abientale, I-85050 Tito, Pz, Italy. [Ramsey, M.] Univ Pittsburgh, Dept Geol & Planetary Sci, 4107 OHara St, Pittsburgh, PA 15260 USA. [Rongo, R.] Univ Calabria, Dept Biol Ecol & Earth Sci, I-87036 Arcavacata Di Rende, CS, Italy. British Geol Survey, Lyell Ctr, Res Ave South, Edinburgh EH14 4AP, Midlothian, Scotland. [Smith, K.] Lab GeoSci Reunion, 15 Ave Rene Cassin,BP 7151, St Denis Messagerie 97715 9, Reunion. [Wright, R.] Univ Hawaii Manoa, Hawaii Inst Geophys & Planetol, 1680 East West Rd, Honolulu, HI 96822 USA. [Villeneuve, N.; Zaksek, K.] Univ Hamburg, Inst Geophys, Bundesstr 55, D-20146 Hamburg, Germany. RP Harris, AJL (reprint author), Univ Blaise Pascal, Lab Magmas & Volcans, CNRS, IRD,OPGC, 5 Rue Kessler, F-63038 Clermont Ferrand, France. EM A.Harris@opgc.univ-bpclermont.fr OI Pergola, Nicola/0000-0001-7619-6685; Patrick, Matthew/0000-0002-8042-6639 NR 355 TC 0 Z9 0 U1 3 U2 3 PU GEOLOGICAL SOC PUBLISHING HOUSE PI BATH PA UNIT 7, BRASSMILL ENTERPRISE CTR, BRASSMILL LANE, BATH BA1 3JN, AVON, ENGLAND SN 0305-8719 BN 978-1-86239-736-1 J9 GEOL SOC SPEC PUBL JI Geol. Soc. Spec. Publ. PY 2016 VL 426 BP 567 EP 648 PG 82 WC Geochemistry & Geophysics; Geology; Remote Sensing SC Geochemistry & Geophysics; Geology; Remote Sensing GA BG3YB UT WOS:000388378700030 ER PT S AU Kamenetzky, J Rangwala, N Glenn, J Maloney, P Conley, A AF Kamenetzky, Julia Rangwala, Naseem Glenn, Jason Maloney, Philip Conley, Alex BE Jablonka, P Andre, P VanDerTak, F TI High-J CO Intensity Measurements for Galaxies Observed by the Herschel FTS SO FROM INTERSTELLAR CLOUDS TO STAR-FORMING GALAXIES: UNIVERSAL PROCESSES? SE IAU Symposium Proceedings Series LA English DT Proceedings Paper CT 315th Symposium of the International-Astronomical-Union CY AUG 03-07, 2015 CL Honolulu, HI SP Int Astronom Union, Ecole Polythechnique Federale Lausanne, Netherlands Inst Space Res, Commissariat Lenergie Atomique & Aux Energies Alternat DE galaxies: ISM; ISM: molecules; submillimeter ID SPECTROSCOPY AB Molecular gas is the raw material for star formation and is commonly traced by the carbon monoxide (CO) molecule. The atmosphere blocks all but the lowest-J transitions of CO for observatories on the ground, but the launch of the Herschel Space Observatory revealed the CO emission of nearby galaxies from J = 4-3 to J = 13-12. Herschel showed that mid-and high-J CO lines in nearby galaxies are emitted from warm gas, accounting for approximately 10% of the molecular mass, but the majority of the CO luminosity. The energy budget of this warm, highly-excited gas is a significant window into the feedback interactions among molecular gas, star formation, and galaxy evolution. Likely, mechanical heating is required to explain the excitation. Such gas has also been observed in star forming regions within our galaxy. We have examined all similar to 300 spectra of galaxies from the Herschel Fourier Transform Spectrometer and measured line fluxes or upper limits for the CO J = 4-3 to J = 13-12, [CI], and [NII] 205 micron lines in similar to 200 galaxies, taking systematic effects of the FTS into account. We will present our line fitting method, illustrate trends available so far in this large sample, and preview the full 2-component radiative transfer likelihood modeling of the CO emission using an illustrative sample of 20 galaxies, including comparisons to well-resolved galactic regions. This work is a comprehensive study of mid-and high-J CO emission among a variety of galaxy types, and can be used as a resource for future (sub) millimeter studies of galaxies with ground-based instruments. C1 [Kamenetzky, Julia] Univ Arizona, Steward Observ, Tucson, AZ 85721 USA. [Rangwala, Naseem] NASA, Ames Res Ctr, Mountain View, CA USA. [Glenn, Jason; Maloney, Philip; Conley, Alex] Univ Colorado, Ctr Astrophys & Space Astron, Campus Box 391, Boulder, CO 80309 USA. RP Kamenetzky, J (reprint author), Univ Arizona, Steward Observ, Tucson, AZ 85721 USA. EM jkamenetzky@as.arizona.edu NR 8 TC 0 Z9 0 U1 0 U2 0 PU CAMBRIDGE UNIV PRESS PI CAMBRIDGE PA THE PITT BUILDING, TRUMPINGTON ST, CAMBRIDGE CB2 1RP, CAMBS, ENGLAND SN 1743-9213 BN 978-1-107-13520-8 J9 IAU SYMP P SERIES JI IAU Symposium Proc. Series PY 2016 VL 315 BP 26 EP 29 DI 10.1017/S1743921316007201 PG 4 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BG2ZL UT WOS:000387795900090 ER PT S AU Aller, MC Kulkarni, VP York, DG Welty, DE Vladilo, G Som, D Lackey, K Dwek, E Beiranvand, N Morrison, S AF Aller, Monique C. Kulkarni, Varsha P. York, Donald G. Welty, Daniel E. Vladilo, Giovanni Som, Debopam Lackey, Kyle Dwek, Eli Beiranvand, Nassim Morrison, Sean BE Jablonka, P Andre, P VanDerTak, F TI Connecting the Interstellar Gas and Dust Properties in Distant Galaxies Using Quasar Absorption Systems SO FROM INTERSTELLAR CLOUDS TO STAR-FORMING GALAXIES: UNIVERSAL PROCESSES? SE IAU Symposium Proceedings Series LA English DT Proceedings Paper CT 315th Symposium of the International-Astronomical-Union CY AUG 03-07, 2015 CL Honolulu, HI SP Int Astronom Union, Ecole Polythechnique Federale Lausanne, Netherlands Inst Space Res, Commissariat Lenergie Atomique & Aux Energies Alternat DE (galaxies:) intergalactic medium; (galaxies:) quasars: absorption lines; galaxies: ISM; (ISM:) dust; extinction; ISM: abundances ID SILICATE DUST; EXTINCTION; ABSORBER AB Gas and dust grains are fundamental components of the interstellar medium and significantly impact many of the physical processes driving galaxy evolution, such as star-formation, and the heating, cooling, and ionization of the interstellar material. Quasar absorption systems (QASs), which trace intervening galaxies along the sightlines to luminous quasars, provide a valuable tool to directly study the properties of the interstellar gas and dust in distant, normal galaxies. We have established the presence of silicate dust grains in at least some gas-rich QASs, and find that they exist at higher optical depths than expected for diffuse gas in the Milky Way. Differences in the absorption feature shapes additionally suggest variations in the silicate dust grain properties, such as in the level of grain crystallinity, from system-to-system. We present results from a study of the gas and dust properties of QASs with adequate archival IR data to probe the silicate dust grain properties. We discuss our measurements of the strengths of the 10 and 18 mu m silicate dust absorption features in the QASs, and constraints on the grain properties (e.g., composition, shape, crystallinity) based on fitted silicate profile templates. We investigate correlations between silicate dust abundance, reddening, and gas metallicity, which will yield valuable insights into the history of star formation and chemical enrichment in galaxies. C1 [Aller, Monique C.] Georgia Southern Univ, Dept Phys, Statesboro, GA 30460 USA. [Aller, Monique C.; Kulkarni, Varsha P.; Som, Debopam; Lackey, Kyle; Beiranvand, Nassim; Morrison, Sean] Univ South Carolina, Dept Phys & Astron, Columbia, SC 29208 USA. [York, Donald G.; Welty, Daniel E.] Univ Chicago, Dept Astron & Astrophys, Chicago, IL 60637 USA. [Vladilo, Giovanni] Osserv Astron Trieste, Via Tiepolo 11, I-34143 Trieste, Italy. [Dwek, Eli] NASA, GSFC, Greenbelt, MD 20771 USA. RP Aller, MC (reprint author), Georgia Southern Univ, Dept Phys, Statesboro, GA 30460 USA.; Aller, MC (reprint author), Univ South Carolina, Dept Phys & Astron, Columbia, SC 29208 USA. EM maller@georgiasouthern.edu NR 7 TC 0 Z9 0 U1 0 U2 0 PU CAMBRIDGE UNIV PRESS PI CAMBRIDGE PA THE PITT BUILDING, TRUMPINGTON ST, CAMBRIDGE CB2 1RP, CAMBS, ENGLAND SN 1743-9213 BN 978-1-107-13520-8 J9 IAU SYMP P SERIES JI IAU Symposium Proc. Series PY 2016 VL 315 DI 10.1017/S174392131600764X PG 2 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BG2ZL UT WOS:000387795900003 ER PT S AU Fischer, WJ Padgett, DL Stapelfeldt, KR AF Fischer, W. J. Padgett, D. L. Stapelfeldt, K. R. BE Jablonka, P Andre, P VanDerTak, F TI The WISE Census of Young Stellar Objects and Clusters in Canis Major SO FROM INTERSTELLAR CLOUDS TO STAR-FORMING GALAXIES: UNIVERSAL PROCESSES? SE IAU Symposium Proceedings Series LA English DT Proceedings Paper CT 315th Symposium of the International-Astronomical-Union CY AUG 03-07, 2015 CL Honolulu, HI SP Int Astronom Union, Ecole Polythechnique Federale Lausanne, Netherlands Inst Space Res, Commissariat Lenergie Atomique & Aux Energies Alternat DE protoplanetary disks; stars: formation; stars: protostars ID (CO)-C-13 J=1-0 SURVEY AB The photometric data returned by WISE, the Wide-field Infrared Survey Explorer, can be used to search the sky for young stellar objects (YSOs) away from the molecular clouds studied in detail by Spitzer and Herschel. We present updated results for a 100 deg(2) region centered on Canis Major, including a look at the clustering properties of YSOs in the region. C1 [Fischer, W. J.; Padgett, D. L.; Stapelfeldt, K. R.] NASA, Goddard Space Flight Ctr, Washington, DC 20546 USA. RP Fischer, WJ (reprint author), NASA, Goddard Space Flight Ctr, Washington, DC 20546 USA. EM william.j.fischer@nasa.gov NR 8 TC 0 Z9 0 U1 0 U2 0 PU CAMBRIDGE UNIV PRESS PI CAMBRIDGE PA THE PITT BUILDING, TRUMPINGTON ST, CAMBRIDGE CB2 1RP, CAMBS, ENGLAND SN 1743-9213 BN 978-1-107-13520-8 J9 IAU SYMP P SERIES JI IAU Symposium Proc. Series PY 2016 VL 315 DI 10.1017/S174392131600781X PG 2 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BG2ZL UT WOS:000387795900020 ER PT S AU Gezari, D Varosi, F Dwek, E Danchi, W Tan, J Okumura, S AF Gezari, Daniel Varosi, Frank Dwek, Eli Danchi, William Tan, Jonathan Okumura, Shin-ichiro BE Jablonka, P Andre, P VanDerTak, F TI Mid-IR Imaging of Orion BN/KL: Modeling of Physical Conditions and Energy Balance SO FROM INTERSTELLAR CLOUDS TO STAR-FORMING GALAXIES: UNIVERSAL PROCESSES? SE IAU Symposium Proceedings Series LA English DT Proceedings Paper CT 315th Symposium of the International-Astronomical-Union CY AUG 03-07, 2015 CL Honolulu, HI SP Int Astronom Union, Ecole Polythechnique Federale Lausanne, Netherlands Inst Space Res, Commissariat Lenergie Atomique & Aux Energies Alternat AB We have modeled two mid-infrared imaging photometry data sets to determine the spatial distribution of physical conditions in the BN/KL infrared complex. We observed the BN/KL region using the 10-m Keck I telescope and the LWS in the direct imaging mode, over a 13''x19'' field (Figure 1, left). We also modeled images obtained with COMICS (Kataza et al.2000) at the 8.2-m SUBARU telescope, over a total field of view is 31'' x 41'' (Figure 1, right), in a total of nine bands: 7.8, 8.8, 9.7, 10.5, 11.7, 12.4, 18.5, 20.8 and 24.8 mu m with similar to 1 mu m bandwidth interference filters. C1 [Gezari, Daniel; Dwek, Eli; Danchi, William] NASA GSFC, Code 667, Greenbelt, MD 20771 USA. [Varosi, Frank; Tan, Jonathan] Univ Florida, Gainesville, FL USA. [Okumura, Shin-ichiro] Okayama Astro Observ, Okayama, Japan. RP Gezari, D (reprint author), NASA GSFC, Code 667, Greenbelt, MD 20771 USA. EM Daniel.Y.Gezari@nasa.gov NR 4 TC 0 Z9 0 U1 0 U2 0 PU CAMBRIDGE UNIV PRESS PI CAMBRIDGE PA THE PITT BUILDING, TRUMPINGTON ST, CAMBRIDGE CB2 1RP, CAMBS, ENGLAND SN 1743-9213 BN 978-1-107-13520-8 J9 IAU SYMP P SERIES JI IAU Symposium Proc. Series PY 2016 VL 315 DI 10.1017/S1743921316007870 PG 2 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BG2ZL UT WOS:000387795900026 ER PT S AU Lindberg, JE Charnley, SB Jorgensen, JK Watanabe, Y Bisschop, SE Sakai, N Yamamoto, S AF Lindberg, Johan E. Charnley, Steven B. Jorgensen, Jes K. Watanabe, Yoshimasa Bisschop, Suzanne E. Sakai, Nami Yamamoto, Satoshi BE Jablonka, P Andre, P VanDerTak, F TI Protostellar chemistry dominated by external irradiation SO FROM INTERSTELLAR CLOUDS TO STAR-FORMING GALAXIES: UNIVERSAL PROCESSES? SE IAU Symposium Proceedings Series LA English DT Proceedings Paper CT 315th Symposium of the International-Astronomical-Union CY AUG 03-07, 2015 CL Honolulu, HI SP Int Astronom Union, Ecole Polythechnique Federale Lausanne, Netherlands Inst Space Res, Commissariat Lenergie Atomique & Aux Energies Alternat DE stars: formation; ISM: molecules; astrochemistry; radiative transfer AB Submillimetre observations of externally irradiated low - mass protostellar envelopes show that the gas temperature in the envelopes is dominated by the external irradiation. Detailed studies of the protostar IRS7B in Corona Australis also show that the chemistry is strongly affected by the irradiation, depleting the abundances of complex organic molecules. C1 [Lindberg, Johan E.; Charnley, Steven B.] NASA, Goddard Space Flight Ctr, Astrochem Lab, Mail Code 691,8800 Greenbelt Rd, Greenbelt, MD 20771 USA. [Jorgensen, Jes K.; Bisschop, Suzanne E.] Niels Bohr Inst, Ctr Star & Planet Format, Oster Voldgade 5-7, DK-1350 Copenhagen K, Denmark. [Jorgensen, Jes K.; Bisschop, Suzanne E.] Univ Copenhagen, Nat Hist Museum Denmark, Oster Voldgade 5-7, DK-1350 Copenhagen K, Denmark. [Watanabe, Yoshimasa; Sakai, Nami; Yamamoto, Satoshi] Univ Tokyo, Dept Phys, Bunkyo Ku, 7-3-1 Hongo, Tokyo 1130033, Japan. [Sakai, Nami] RIKEN, 2-1 Hirosawa, Wako, Saitama 3510198, Japan. RP Lindberg, JE (reprint author), NASA, Goddard Space Flight Ctr, Astrochem Lab, Mail Code 691,8800 Greenbelt Rd, Greenbelt, MD 20771 USA. EM johan.lindberg@nasa.gov NR 7 TC 0 Z9 0 U1 0 U2 0 PU CAMBRIDGE UNIV PRESS PI CAMBRIDGE PA THE PITT BUILDING, TRUMPINGTON ST, CAMBRIDGE CB2 1RP, CAMBS, ENGLAND SN 1743-9213 BN 978-1-107-13520-8 J9 IAU SYMP P SERIES JI IAU Symposium Proc. Series PY 2016 VL 315 DI 10.1017/S1743921316008139 PG 2 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BG2ZL UT WOS:000387795900051 ER PT S AU Menendez-Delmestre, K Capak, P Sheth, K AF Menendez-Delmestre, Karin Capak, Peter Sheth, Kartik BE Jablonka, P Andre, P VanDerTak, F TI High-Redshift Protoclusters Traced by Submillimeter Galaxies Tracing Star Formation Activity out to z > 4 SO FROM INTERSTELLAR CLOUDS TO STAR-FORMING GALAXIES: UNIVERSAL PROCESSES? SE IAU Symposium Proceedings Series LA English DT Proceedings Paper CT 315th Symposium of the International-Astronomical-Union CY AUG 03-07, 2015 CL Honolulu, HI SP Int Astronom Union, Ecole Polythechnique Federale Lausanne, Netherlands Inst Space Res, Commissariat Lenergie Atomique & Aux Energies Alternat DE Keyword1; keyword2; keyword3; etc. AB Clustering analysis indicate that at z similar to 2 submm-selected galaxies (SMGs) reside in very massive halos (M-DM > 5 x 10(13)), suggesting that SMGs trace high-density environments that evolve into rich galaxy clusters. Conversely, recent work suggests that SMGs are tracers of a broader range of environments, including structures with more modest masses caught in highly active periods; since galaxies in these structures are likely caught during episodes of peak star bursts, SMGs may be tracers of a wider range of environments beyond the progenitors of todays very rich clusters, opening a window for a more complete exploration of the details underpinning the process of galaxy evolution in concert with the assembly of the large scale structure (LSS). We have undertaken a large observing program comprising deep narrow-band Ly-alpha imaging and multi-object spectroscopy using Palomar/Keck/Magellan/Gemini telescopes to probe for galaxy overdensities in SMG environments at z similar to 1-5. With similar to 200 spectroscopically-confirmed Ly-alpha emitters, we are in a position to gauge the level of galaxy overdensity in these regions. C1 [Menendez-Delmestre, Karin] Univ Fed Rio de Janeiro, Observ Valongo, Ladeira Pedro Antonio 43, BR-20080090 Rio De Janeiro, RJ, Brazil. [Capak, Peter] IPAC, 1200 East Calif Blvd, Pasadena, CA 91125 USA. [Sheth, Kartik] NAASC, NRAO, 520 Edgemont Rd, Charlottesville, VA 22903 USA. [Sheth, Kartik] NASA HQ, 300 E St SW, Washington, DC 20546 USA. RP Menendez-Delmestre, K (reprint author), Univ Fed Rio de Janeiro, Observ Valongo, Ladeira Pedro Antonio 43, BR-20080090 Rio De Janeiro, RJ, Brazil. EM kmd@astro.ufrj.br NR 6 TC 0 Z9 0 U1 1 U2 1 PU CAMBRIDGE UNIV PRESS PI CAMBRIDGE PA THE PITT BUILDING, TRUMPINGTON ST, CAMBRIDGE CB2 1RP, CAMBS, ENGLAND SN 1743-9213 BN 978-1-107-13520-8 J9 IAU SYMP P SERIES JI IAU Symposium Proc. Series PY 2016 VL 315 DI 10.1017/S1743921316008164 PG 2 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BG2ZL UT WOS:000387795900054 ER PT S AU Riguccini, L Temi, P Amblard, A Fanelli, M AF Riguccini, Laurie Temi, Pasquale Amblard, Alexandre Fanelli, Michael BE Jablonka, P Andre, P VanDerTak, F TI Mid-Infrared Enhanced Lenticulars caught in the dusty midst of transformation in the Coma Cluster SO FROM INTERSTELLAR CLOUDS TO STAR-FORMING GALAXIES: UNIVERSAL PROCESSES? SE IAU Symposium Proceedings Series LA English DT Proceedings Paper CT 315th Symposium of the International-Astronomical-Union CY AUG 03-07, 2015 CL Honolulu, HI SP Int Astronom Union, Ecole Polythechnique Federale Lausanne, Netherlands Inst Space Res, Commissariat Lenergie Atomique & Aux Energies Alternat DE galaxies: elliptical and lenticular, cD; galaxies: clusters: individual (Virgo, Coma) ID EARLY-TYPE GALAXIES; STAR-FORMATION AB We explore the properties of early-type galaxies (ETGs) in rich environments such as clusters of galaxies. The L-24/L-K distribution of ETGs in both Virgo and Coma clusters shows that some lenticulars (S0, 10 in Coma and 3 in Virgo) have a much larger L-24/L-K ratio (0.5 to similar to 2 dex) than the bulk of the ETG population. We call these sources Mid-Infrared Enhanced Galaxies (MIEGs). In Coma, they are mostly located in the South-West part of the cluster where a substructure is falling onto the main cluster. MIEGs present lower g-r color than the rest of the ETGs, because of a blue continuum. We interpret the excess L-24/L-K ratio as evidence for an enhanced star-formation induced as a consequence of their infall into the main cluster. C1 [Riguccini, Laurie] Univ Fed Rio de Janeiro, Observ Valongo, BR-20080090 Rio de Janeiro, RJ, Brazil. [Riguccini, Laurie] CAPES BJT, Rio De Janeiro, RJ, Brazil. [Temi, Pasquale; Amblard, Alexandre; Fanelli, Michael] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Riguccini, L (reprint author), Univ Fed Rio de Janeiro, Observ Valongo, Ladeira Pedro Antonio 43, BR-20080090 Rio de Janeiro, RJ, Brazil. EM riguccini@astro.ufrj.br NR 6 TC 0 Z9 0 U1 0 U2 0 PU CAMBRIDGE UNIV PRESS PI CAMBRIDGE PA THE PITT BUILDING, TRUMPINGTON ST, CAMBRIDGE CB2 1RP, CAMBS, ENGLAND SN 1743-9213 BN 978-1-107-13520-8 J9 IAU SYMP P SERIES JI IAU Symposium Proc. Series PY 2016 VL 315 DI 10.1017/S1743921316008310 PG 2 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BG2ZL UT WOS:000387795900069 ER PT S AU Varosi, F Gezari, D Dwek, E Telesco, C AF Varosi, F. Gezari, D. Dwek, E. Telesco, C. BE Jablonka, P Andre, P VanDerTak, F TI Dust Temperatures and Opacities in the Central Parsec of the Galactic Center Modeled from Analysis of Multi-wavelength Mid-infrared Images SO FROM INTERSTELLAR CLOUDS TO STAR-FORMING GALAXIES: UNIVERSAL PROCESSES? SE IAU Symposium Proceedings Series LA English DT Proceedings Paper CT 315th Symposium of the International-Astronomical-Union CY AUG 03-07, 2015 CL Honolulu, HI SP Int Astronom Union, Ecole Polythechnique Federale Lausanne, Netherlands Inst Space Res, Commissariat Lenergie Atomique & Aux Energies Alternat C1 [Varosi, F.; Telesco, C.] Univ Florida Gainesville, Gainesville, FL 32611 USA. [Gezari, D.; Dwek, E.] NASA GSFC, Greenbelt, MD USA. RP Varosi, F (reprint author), Univ Florida Gainesville, Gainesville, FL 32611 USA. EM varosi@astro.ufl.edu NR 2 TC 0 Z9 0 U1 0 U2 0 PU CAMBRIDGE UNIV PRESS PI CAMBRIDGE PA THE PITT BUILDING, TRUMPINGTON ST, CAMBRIDGE CB2 1RP, CAMBS, ENGLAND SN 1743-9213 BN 978-1-107-13520-8 J9 IAU SYMP P SERIES JI IAU Symposium Proc. Series PY 2016 VL 315 DI 10.1017/S1743921316008413 PG 2 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BG2ZL UT WOS:000387795900079 ER PT J AU Koike, M Sano, Y Takahata, N Ishida, A Sugiura, N Anand, M AF Koike, Mizuho Sano, Yuji Takahata, Naoto Ishida, Akizumi Sugiura, Naoji Anand, Mahesh TI Combined investigation of H isotopic compositions and U-Pb chronology of young Martian meteorite Larkman Nunatak 06319 SO GEOCHEMICAL JOURNAL LA English DT Article DE NanoSIMS; Martian meteorites; D/H ratio; U-Pb dating; phosphate ID NOMINALLY ANHYDROUS MINERALS; ALLAN HILLS 84001; SNC METEORITES; CLOSURE TEMPERATURE; PHOSPHATE MINERALS; HYDROGEN ISOTOPES; MERIDIANI-PLANUM; WATER ABUNDANCES; MELT INCLUSIONS; LOS-ANGELES AB We measured the hydrogen isotopic composition (D/H ratios) and U-Pb chronology of phosphate minerals in a young Martian meteorite: LAR 06319. D/H ratios of melt-inclusions in the meteorite were also investigated to evaluate the presence of water reservoirs on Mars in recent times. The total Pb/U dating of multiple grains of apatite and merrillite yield a concordant date of 167 +/- 57 Ma, interpreted as the crystallization age, suggesting that both apatite and merrillite in this meteorite have preserved their igneous histories. The D/H ratios of an apatite grain show good reproducibility yielding a delta D value of 4250 +/- 120%, whereas those of merrillite show larger D/H variations with the maximum delta D value of 5260 +/- 790%. However, mafic glass in melt-inclusions shows extremely large variation in delta D, ranging from ca. 1070% to 6830 +/- 460%. The different D/H signatures recorded in these phases reflect the contributions of different hydrous components with distinct D/H ratios, possibly incorporated at different times. It is inferred that several isotopically distinct water reservoirs exist in the present Martian surface/sub-surface system. C1 [Koike, Mizuho; Sano, Yuji; Takahata, Naoto] Univ Tokyo, Atmosphere & Ocean Res Inst, Kashiwa, Chiba 2778564, Japan. [Sano, Yuji] Natl Taiwan Univ, Dept Geosci, Taipei, Taiwan. [Sugiura, Naoji] Univ Tokyo, Dept Earth & Planetary Sci, Bunkyo Ku, Tokyo 1130033, Japan. [Anand, Mahesh] Open Univ, Dept Phys Sci, Milton Keynes MK7 6AA, Bucks, England. [Anand, Mahesh] Nat Hist Museum, Dept Earth Sci, London SW7 5BD, England. [Ishida, Akizumi] Univ Wisconsin, NASA Astrobiol Inst, Dept Geosci, Madison, WI 53706 USA. RP Koike, M (reprint author), Univ Tokyo, Atmosphere & Ocean Res Inst, Kashiwa, Chiba 2778564, Japan. EM mizuho_k@aori.u-tokyo.ac.jp FU UK Science and Technology Facilities Council (STFC) [ST/I001298/1, ST/L000776/1]; Ministry of Education, Culture, Sports, Science and Technology of Japan [24221002, 2605] FX We are most grateful to Dr. M. Ito and an anonymous referee for valuable comments, and to Dr. K. Terada for kindly handling this paper. Mr. Y. Ota has contributed to the development of the basic analytical protocols, which were improved and used for this study. We thank Mr. K. Ichimura for his assistance with FE-EPMA analyses conducted at The University of Tokyo. Constructive discussions with Dr. H. Hiyagon and Dr. T. Iizuka related to experiments and data interpretation are greatly appreciated. Computer software "Isoplot/Ex" was kindly provided by Dr. K. R. Ludwig. We thank the Meteorites Working Group for providing polished sections of the Martian meteorites used for this study. This work has been partially supported by a UK Science and Technology Facilities Council (STFC) research grant to MA (grant numbers ST/I001298/1 and ST/L000776/1), and by a Grant-in-Aid for Scientific Research Program No. 24221002 and No. 2605 from the Ministry of Education, Culture, Sports, Science and Technology of Japan. NR 47 TC 0 Z9 0 U1 6 U2 6 PU GEOCHEMICAL SOC JAPAN PI TOKYO PA 358-5 YAMABUKI-CHO, SHINJUKU-KU, TOKYO, 162-0801, JAPAN SN 0016-7002 EI 1880-5973 J9 GEOCHEM J JI Geochem. J. PY 2016 VL 50 IS 5 BP 363 EP 377 DI 10.2343/geochemj.2.0424 PG 15 WC Geochemistry & Geophysics SC Geochemistry & Geophysics GA ED4HW UT WOS:000388809700001 ER PT S AU Billman, D Fayollas, C Feary, M Martinie, C Palanque, P AF Billman, Dorrit Fayollas, Camille Feary, Michael Martinie, Celia Palanque, Philippe BE Bogdan, C Gulliksen, J Sauer, S Forbrig, P Winckler, M Johnson, C Palanque, P Bernhaupt, R Kis, F TI Complementary Tools and Techniques for Supporting Fitness-for-Purpose of Interactive Critical Systems SO HUMAN-CENTERED AND ERROR-RESILIENT SYSTEMS DEVELOPMENT, HCSE 2016, HESSD 2016 SE Lecture Notes in Computer Science LA English DT Proceedings Paper CT IFIP WG 13.2/13.5 Joint Working Conference on 6th International Conference on Human-Centered Software Engineering (HCSE) / 8th International Conference on Human Error, Safety, and System Development (HESSD) CY AUG 29-31, 2016 CL Stockholm, SWEDEN SP Int Federat Informat Proc Working Grp 13 2 Methodologies User Centered Syst Design, Int Federat Informat Proc Working Grp 13 5 Resilience, Reliabil, Safety, & Human Error Syst Dev, KTH Royal Inst Technol, Sch Comp Sci & Commun, OpenLab, Int Federat Informat Proc Tech Comm 13 Human Comp Interact DE Work analysis and representation; Interactive systems behavior; Complementary approaches; Safety-critical systems; Aviation AB Sound design of complex, interactive, safety critical systems is very important, yet difficult. A particular challenge in the design of safety-critical systems is a typical lack of access to large numbers of testers and an inability to test early designs with traditional usability assessment tools. This inability leads to reduced information available to guide design, a phenomenon referred to as the Collingridge dilemma. Our research proposes to address parts of this problem with the development of tools and techniques for generating useful information and assessing developing designs early, to minimize the need for late change. More generally, we describe a set of three tools and techniques to support the process of ensuring fitness-for-purpose of complex interactive systems, helping designers focus on interaction across different functions of an overall system. These different tools and techniques support different parts of the overall design and evaluation process, but are focused on improving the coverage and effectiveness of evaluating interaction. C1 [Billman, Dorrit] San Jose State Univ, San Jos, CA USA. [Fayollas, Camille; Martinie, Celia; Palanque, Philippe] Univ Toulouse, ICS IRIT, Toulouse, France. [Feary, Michael] NASA, Ames Res Ctr, Mountain View, CA USA. RP Martinie, C (reprint author), Univ Toulouse, ICS IRIT, Toulouse, France. EM dorrit.billman@nasa.gov; fayollas@irit.fr; martinie@irit.fr; michael.s.feary@nasa.gov; palanque@irit.fr NR 31 TC 0 Z9 0 U1 0 U2 0 PU SPRINGER INT PUBLISHING AG PI CHAM PA GEWERBESTRASSE 11, CHAM, CH-6330, SWITZERLAND SN 0302-9743 BN 978-3-319-44902-9; 978-3-319-44901-2 J9 LECT NOTES COMPUT SC PY 2016 VL 9856 BP 181 EP 202 DI 10.1007/978-3-319-44902-9_12 PG 22 WC Computer Science, Information Systems; Computer Science, Software Engineering; Computer Science, Theory & Methods SC Computer Science GA BG4SC UT WOS:000389062800012 ER PT S AU Asnani, VM Deng, ZX Scheidler, JJ Dapino, MJ AF Asnani, Vivake M. Deng, Zhangxian Scheidler, Justin J. Dapino, Marcelo J. BE Griffin, SF TI Experimental comparison of piezoelectric and magnetostrictive shunt dampers SO INDUSTRIAL AND COMMERCIAL APPLICATIONS OF SMART STRUCTURES TECHNOLOGIES 2016 SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Industrial and Commercial Applications of Smart Structures Technologies CY MAR 21-22, 2016 CL Las Vegas, NV SP SPIE, Polytec Inc, OZ Opt Ltd, APS Dynam Inc, TA Electroforce Corp, ElectroForce Syst Grp, Inst Phys, Amer Elements DE Shunt damping; driveline vibration; piezoelectric; magnetostrictive AB A novel mechanism called the vibration ring is being developed to enable energy conversion elements to be incorporated into the driveline of a helicopter or other rotating machines. Unwanted vibration is transduced into electrical energy, which provides a damping effect on the driveline. The generated electrical energy may also be used to power other devices (e.g., health monitoring sensors). PZT ('piezoceramic') and PMN-30% PT ('single crystal') stacks, as well as a Tb0.3Dy0.7Fe1.92 ('Terfenol-D') rod with a bias magnet array and a pickup coil, were tested as alternative energy conversion elements to use within the vibration ring. They were tuned for broadband damping using shunt resistors, and dynamic compression testing was conducted in a high-speed load frame. Energy conversion was experimentally optimized at 750Hz by tuning the applied bias stress and resistance values. Dynamic testing was conducted up to 1000Hz to determine the effective compressive modulus, shunt loss factor, internal loss factor, and total loss factor. Some of the trends of modulus and internal loss factor versus frequency were unexplained. The single crystal device exhibited the greatest shunt loss factor whereas the Terfenol-D device had the highest internal and total loss factors. Simulations revealed that internal losses in the Terfenol-D device were elevated by eddy current effects, and an improved magnetic circuit could enhance its shunt damping capabilities. Alternatively, the Terfenol-D device may be simplified to utilize only the eddy current dissipation mechanism (no pickup coil or shunt) to create broadband damping. C1 [Asnani, Vivake M.] NASA, Mat & Struct Div, Glenn Res Ctr, Cleveland, OH 44135 USA. [Deng, Zhangxian; Dapino, Marcelo J.] Ohio State Univ, Dept Mech & Aerosp Engn, NSF I UCRC Smart Vehicle Concepts, Columbus, OH 43210 USA. [Scheidler, Justin J.] NASA, Univ Space Res Assoc, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Asnani, VM (reprint author), NASA, Mat & Struct Div, Glenn Res Ctr, Cleveland, OH 44135 USA. EM vivake.m.asnani@nasa.gov NR 14 TC 0 Z9 0 U1 1 U2 1 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0042-3 J9 PROC SPIE PY 2016 VL 9801 AR UNSP 98010R DI 10.1117/12.2220302 PG 10 WC Optics SC Optics GA BG4OX UT WOS:000389022200018 ER PT S AU Badescu, M Sherrit, S Lewis, D Bao, XQ Bar-Cohen, Y Hall, JL AF Badescu, Mircea Sherrit, Stewart Lewis, Derek Bao, Xiaoqi Bar-Cohen, Yoseph Hall, Jeffery L. BE Griffin, SF TI Digital valve for high pressure high flow applications SO INDUSTRIAL AND COMMERCIAL APPLICATIONS OF SMART STRUCTURES TECHNOLOGIES 2016 SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Industrial and Commercial Applications of Smart Structures Technologies CY MAR 21-22, 2016 CL Las Vegas, NV SP SPIE, Polytec Inc, OZ Opt Ltd, APS Dynam Inc, TA Electroforce Corp, ElectroForce Syst Grp, Inst Phys, Amer Elements DE Flow control; digital valve AB To address the challenges, which are involved with the development of flow control valves that can meet high demand requirements such as high pressure, high flow rate, limited power and limited space, the authors have conceived a novel design configuration [1]. This design consists of a digitalized flow control valve with multipath and multistage pressure reduction structures. Specifically, the valve is configured as a set of parallel flow paths from the inlet to the outlet. A choke valve controls the total flow rate by digitally opening different paths or different combination of the paths. Each path is controlled by a poppet cap valve basically operated in on-off states. The number of flow states is 2(N) where N is the number of flow paths. To avoid erosion from sand in the fluid and high speed flow, the seal area of the poppet cap valve is located at a distance from the flow inlet away from the high speed flow and the speed is controlled to stay below a predefined erosion safe limit. The path is a multistage structure composed of a set of serial nozzles-expansion chambers that equally distribute the total pressure drop to each stage. The pressure drop of each stage and, therefore, the flow speed at the nozzles and expansion chambers is controlled by the number of stages. The paths have relatively small cross section and could be relatively long for large number of stages and still fit in a strict annular space limit. The paper will present the design configuration, analysis and preliminary test results. C1 [Badescu, Mircea; Sherrit, Stewart; Lewis, Derek; Bao, Xiaoqi; Bar-Cohen, Yoseph; Hall, Jeffery L.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Badescu, M (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Mircea.Badescu@jpl.nasa.gov NR 4 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0042-3 J9 PROC SPIE PY 2016 VL 9801 AR UNSP 98010B DI 10.1117/12.2219350 PG 10 WC Optics SC Optics GA BG4OX UT WOS:000389022200009 ER PT J AU Mikami, M Kikuchi, M Kan, YJ Seo, T Nomura, H Suganuma, Y Moriue, O Dietrich, DL AF Mikami, Masato Kikuchi, Masao Kan, Yuji Seo, Takehiko Nomura, Hiroshi Suganuma, Yusuke Moriue, Osamu Dietrich, Daniel L. TI Droplet Cloud Combustion Experiment "Group Combustion" in KIBO on ISS SO INTERNATIONAL JOURNAL OF MICROGRAVITY SCIENCE AND APPLICATION LA English DT Review DE Microgravity combustion experiment; Droplet cloud; Flame spread; Group combustion; KIBO/ISS ID FLAME-SPREAD; MICROGRAVITY EXPERIMENTS; ARRAY COMBUSTION AB Flame spread in fuel spray near the flame base and subsequent excitation of group combustion of the whole spray are necessary for stable combustion of continuous burning of liquid fuel such as in aero engines or gas turbines. In order to elucidate the flame spread mechanism, flame spread experiments of a fuel-droplet array in microgravity have been undertaken. Based on the past short-duration microgravity experiments and a percolation model to describe group combustion excitation of randomly distributed droplet clouds, the droplet cloud combustion experiment named "Group Combustion" is planned as the first combustion experiment in the Japanese Experiment Module "KIBO" on the International Space Station. The objective of this experiment is to verify the flame spread hypotheses regarding the effects of droplet interaction, droplet motion, and radiative heat loss from the flame. The Group Combustion Experiment Module (GCEM) has been developed as experiment-dedicated apparatus. This paper will provide an overview of the experiment. C1 [Mikami, Masato; Seo, Takehiko] Grad Sch Sci & Technol Innovat, 2-16-1 Tokiwadai, Ube, Yamaguchi 7558611, Japan. [Kikuchi, Masao; Kan, Yuji] Japan Aerosp Explorat Agcy, JEM Utilizat Ctr, 2-1-1 Sengen, Tsukuba, Ibaraki 3058605, Japan. [Nomura, Hiroshi; Suganuma, Yusuke] Nihon Univ, Coll Ind Technol, 1-2-1 Izumi Cho, Narashino, Chiba 2758575, Japan. [Moriue, Osamu] Kyushu Univ, Fac Engn, Nishi Ku, 744 Motooka, Fukuoka 8190395, Japan. [Dietrich, Daniel L.] NASA, Glenn Res Ctr, 21000 Brookpk Rd, Cleveland, OH 44135 USA. RP Mikami, M (reprint author), Grad Sch Sci & Technol Innovat, 2-16-1 Tokiwadai, Ube, Yamaguchi 7558611, Japan. EM mmikami@yamaguchi-u.ac.jp NR 19 TC 0 Z9 0 U1 0 U2 0 PU JAPAN SOC MICROGRAVITY APPLICATION PI TOKYP PA JAPAN SOC MICROGRAVITY APPLICATION, TOKYP, 00000, JAPAN SN 0915-3616 EI 2188-9783 J9 INT J MICROGRAVITY S JI Int. J. Microgravity Sci. Appl. PY 2016 VL 33 IS 2 AR 330208 DI 10.15011/jasma.33.330208 PG 7 WC Physics, Applied SC Physics GA DV3TD UT WOS:000382845500008 ER PT B AU Guertin, SM Clark, LT AF Guertin, Steven M. Clark, Lawrence T. BE Bagatin, M Gerardin, S TI Microprocessor Radiation Effects SO IONIZING RADIATION EFFECTS IN ELECTRONICS: FROM MEMORIES TO IMAGERS SE Devices Circuits and Systems LA English DT Article; Book Chapter ID SINGLE-EVENT UPSET; RATE PREDICTION; LATCHUP; MEMORY; UNIT; EXECUTION; SRAMS; CACHE C1 [Guertin, Steven M.] CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. [Clark, Lawrence T.] Arizona State Univ, Tempe, AZ USA. RP Guertin, SM (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. NR 58 TC 0 Z9 0 U1 0 U2 0 PU CRC PRESS-TAYLOR & FRANCIS GROUP PI BOCA RATON PA 6000 BROKEN SOUND PARKWAY NW, STE 300, BOCA RATON, FL 33487-2742 USA BN 978-1-4987-2263-6; 978-1-4987-2260-5 J9 DEVICE CIRC SYST PY 2016 VL 50 BP 115 EP 152 PG 38 WC Engineering, Electrical & Electronic SC Engineering GA BG2JC UT WOS:000387422900007 ER PT J AU Jenny, B Liem, J Savric, B Putman, WM AF Jenny, Bernhard Liem, Johannes Savric, Bojan Putman, William M. TI Interactive video maps: A year in the life of Earth's CO2 SO JOURNAL OF MAPS LA English DT Article DE Video map; georeferenced video; video layer; film-map; map projection; raster projection; WebGL ID PROJECTIONS AB This article introduces interactive video maps for the web. The main component of video maps is a video stream that is areally georeferenced to a spatial reference system in the same way rectified raster orthoimages are georeferenced. The areal georeference allows for interactivity that goes beyond the play, pause, and stop functionality of video player software. We highlight two types of functionality, allowing the user to (1) combine the video stream layer with other raster and vector map layers and (2) adjust the projection of the map in real time. We exemplify video maps by A Year in the Life of Earth's CO2, an interactive video map that visualizes the results of a high-resolution NASA computer model of global atmospheric carbon dioxide distribution. The map shows how carbon dioxide travels around the globe over the course of one year. We use a combination of WebGL, a programming interface to the hardware-accelerated graphics pipeline, and HTML5 video for adding an areally georeferenced video layer to other map layers, and for the on the fly projection of the video stream in the web browser. C1 [Jenny, Bernhard] RMIT Univ, Sch Sci, Melbourne, Vic, Australia. [Jenny, Bernhard; Liem, Johannes; Savric, Bojan] Oregon State Univ, Coll Earth Ocean & Atmospher Sci, Corvallis, OR 97331 USA. [Liem, Johannes] City Univ London, Dept Comp Sci, London, England. [Savric, Bojan] Esri Inc, Redlands, CA USA. [Putman, William M.] NASA, Goddard Space Flight Ctr, Global Modeling & Assimilat Off, Greenbelt, MD USA. RP Jenny, B (reprint author), RMIT Univ, Sch Sci, Melbourne, Vic, Australia.; Jenny, B (reprint author), Oregon State Univ, Coll Earth Ocean & Atmospher Sci, Corvallis, OR 97331 USA. EM bernhard.jenny@rmit.edu.au OI Savric, Bojan/0000-0003-4080-6378; Jenny, Bernhard/0000-0001-6101-6100 NR 35 TC 2 Z9 2 U1 4 U2 4 PU TAYLOR & FRANCIS LTD PI ABINGDON PA 2-4 PARK SQUARE, MILTON PARK, ABINGDON OR14 4RN, OXON, ENGLAND SN 1744-5647 J9 J MAPS JI J. Maps PY 2016 VL 12 SU 1 BP 36 EP 42 DI 10.1080/17445647.2016.1157323 PG 7 WC Geography; Geography, Physical SC Geography; Physical Geography GA ED4KP UT WOS:000388817100004 ER PT J AU Ren, CL Gan, Y Lee, M Yang, CY He, F Jiang, YM Dong, GH Green, RD Xue, XJ AF Ren, Chunlei Gan, Yun Lee, Myongjin Yang, Chunyang He, Fei Jiang, Yanmei Dong, Guohui Green, Robert D. Xue, Xingjian TI Fabrication and Characterization of High Performance Intermediate Temperature Micro-Tubular Solid Oxide Fuel Cells SO JOURNAL OF THE ELECTROCHEMICAL SOCIETY LA English DT Article ID HOLLOW-FIBER; ELECTROCHEMICAL PERFORMANCE; PHASE-INVERSION; ANODE SUPPORT; SOFCS; MICROSTRUCTURE; ELECTROLYTES; IMPEDANCE; CATHODES AB A phase inversion-based dual-layer co-extrusion approach was advanced to fabricate micro-channel array structured micro-tubular solid oxide fuel cells (MT-SOFCs). The inner graphite layer was used as a sacrificial layer to eliminate the middle sponge-like layer and inner surface dense skin layer, which were normally formed using the single layer extrusion method. As a result, themicro-channel array generated in the outer layer was a more open structure and facile fuel/gas diffusion was obtained. The fuel/gas permeability of such an anode substrate Ni-Ce0.8Sm0.2O1.9 (Ni-SDC) was similar to 9 times that of an anode substrate fabricated using the phase inversion-based single layer extrusion method. The open circuit voltages (OCVs) of the corresponding cell Ni-SDC/SDC/PrBaCo2O5+delta were 0.89 V-0.85 V at 500-600 degrees C, much higher than those of other SDC electrolyte based MT-SOFCs. The peak power density of the cell was similar to 1484 mW cm(-2) at 600 degrees C, approximately 1.5 times that of a similar cell with an anode substrate fabricated from the single layer extrusion method. This is also the highest performance among the SOFCs with the same material system in open literature. The fuel utilization rate was also significantly improved in different degrees depending on the supplied inlet fuel flow rates. (C) 2016 The Electrochemical Society. All rights reserved. C1 [Ren, Chunlei; Gan, Yun; Lee, Myongjin; Yang, Chunyang; He, Fei; Jiang, Yanmei; Dong, Guohui; Xue, Xingjian] Univ South Carolina, Dept Mech Engn, Columbia, SC 29208 USA. [Green, Robert D.] NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Xue, XJ (reprint author), Univ South Carolina, Dept Mech Engn, Columbia, SC 29208 USA. EM Xue@cec.sc.edu FU NASA [NNX14AB26G] FX This work was supported by Early Stage Innovations grant #NNX14AB26G from NASA's Space Technology Research Grants Program. NR 52 TC 0 Z9 0 U1 2 U2 2 PU ELECTROCHEMICAL SOC INC PI PENNINGTON PA 65 SOUTH MAIN STREET, PENNINGTON, NJ 08534 USA SN 0013-4651 EI 1945-7111 J9 J ELECTROCHEM SOC JI J. Electrochem. Soc. PY 2016 VL 163 IS 9 BP F1115 EP F1123 DI 10.1149/2.1271609jes PG 9 WC Electrochemistry; Materials Science, Coatings & Films SC Electrochemistry; Materials Science GA ED6TC UT WOS:000388988100098 ER PT S AU Tchebakova, NM Parfenova, EI Soja, AJ AF Tchebakova, Nadezhda M. Parfenova, Elena I. Soja, Amber J. BE Mueller, L Sheudshen, AK Eulenstein, F TI Significant Siberian Vegetation Change is Inevitably Brought on by the Changing Climate SO NOVEL METHODS FOR MONITORING AND MANAGING LAND AND WATER RESOURCES IN SIBERIA SE Springer Water LA English DT Article; Book Chapter DE Vegetation; Siberia; Climate change; Scenario ID CLASSIFICATION; DYNAMICS; MODEL AB The redistribution of terrestrial ecosystems and individual species is predicted to be profound under Global Climate Model simulations. We modeled the progression of potential vegetation and forest types in Siberia by the end of the twenty-first century by coupling large-scale bioclimatic models of vegetation zones and major conifer species with climatic variables and permafrost using the B1 and A2 Hadley Centre HadCM3 climate change scenarios. In the projected warmer and dryer climate, Siberian taiga forests are predicted to dramatically decrease and shift to the northeast, and forest-steppe, steppe, and novel temperate broadleaf forests are predicted to dominate most of Siberia by 2090. The permafrost should not retreat sufficiently to provide favorable habitats for dark (Pinus sibiric, Abies sibirica, and Picea obovata) taiga, and the permafrost-tolerant L. dahurica taiga should remain the dominant forest type in many current permafrost-lain areas. Water stress and fire-tolerant tree species (Pinus sylvestris and Larix spp.) should have an increased advantage over moisture-loving tree species (P. sibirica, A. sibirica, and P. obovata) in a new climate. Accumulated surface fuel loads due to increased tree mortality from drought, insects, and other factors, especially at the southern forest border and in the Siberian interior (Yakutia), together with an increase in severe fire weather, should also lead to increases in large, high-severity fires that are expected to facilitate vegetation progression toward a new equilibrium with the climate. Adaptation of the forest types and tree species to climate change in the south may be based on the genetic means of individual species and human willingness to aid migration, perhaps by seeding. Additionally, useful and viable crops could be established in agricultural lands instead of failing forests. C1 [Tchebakova, Nadezhda M.; Parfenova, Elena I.] Russian Acad Sci, VN Sukachev Inst Forest, Siberian Branch SIF SB RAS, Akademgorodok 50-28, Krasnoyarsk 660036, Russia. [Soja, Amber J.] NASA, Langley Res Ctr, 21 Langley Blvd,Mail Stop 420, Hampton, VA 23681 USA. RP Tchebakova, NM (reprint author), Russian Acad Sci, VN Sukachev Inst Forest, Siberian Branch SIF SB RAS, Akademgorodok 50-28, Krasnoyarsk 660036, Russia. EM ncheby@ksc.krasn.ru; lyeti@ksc.krasn.ru; Amber.J.Soja@nasa.gov NR 51 TC 0 Z9 0 U1 2 U2 2 PU SPRINGER INT PUBLISHING AG PI CHAM PA GEWERBESTRASSE 11, CHAM, CH-6330, SWITZERLAND SN 2364-6934 BN 978-3-319-24409-9; 978-3-319-24407-5 J9 SPRINGER WATER PY 2016 BP 269 EP 285 DI 10.1007/978-3-319-24409-9_10 D2 10.1007/978-3-319-24409-9 PG 17 WC Environmental Sciences; Soil Science; Water Resources SC Environmental Sciences & Ecology; Agriculture; Water Resources GA BF9BQ UT WOS:000385421600011 ER PT B AU Ganapathi, G Palisoc, A Buchroithner, A Nataraj, S Nesmith, B Kindler, A Greschik, G Gidanian, K AF Ganapathi, Gani Palisoc, Arthur Buchroithner, Armin Nataraj, Sai Nesmith, Bill Kindler, Andrew Greschik, Gyula Gidanian, Koorosh GP ASME TI DEVELOPMENT AND PROTOTYPE TESTING OF LOW-COST LIGHTWEIGHT THIN FILM SOLAR CONCENTRATOR SO PROCEEDINGS OF THE ASME 10TH INTERNATIONAL CONFERENCE ON ENERGY SUSTAINABILITY, 2016, VOL 1 LA English DT Proceedings Paper CT 10th ASME International Conference on Energy Sustainability CY JUN 26-30, 2016 CL Charlotte, NC SP ASME, Adv Energy Syst Div, ASME, Solar Energy Div AB A low-cost rigid foam-based concentrator technology development program was funded by the DOE SunShot Initiative to meet installed cost goals of $75/m(2) vs. current costs of similar to$200-250/m(2). Phase 1 of the project focused on design trades and cost analyses leading to a cost-optimized self powered autonomous tracking heliostat concept with a mirror surface area in the 100m(2) range. In Phase 2 30-year accelerated testing of the mirror modules based on ReflecTec film with 94% specular reflectivity bonded on composite foam substrate were initiated and completed in Phase 3. The tests with 15 coupons showed optical performance degradation of less than 5% in specular reflectance following 30-year equivalent UV testing and other abuse testing such as acid rain, bird dropping, thermal cycling, etc. A small scale prototype (3mx2m) heliostat design based on modular truss elements with removable mirror modules was developed in detail. In this phase components such as the dual-axis actuators were sized and selected based on wind load requirements and pointing accuracy demands were completed. Finite Element analyses for the mechanical structure with mirror modules were performed using three separate commercial codes - ANSYS, COMSOL and Solid Works to validate the optical errors induced by wind loads on the structure up to 35 mph. Results indicated that the RMS deflections contributed to less than 0.4 mrad pointing error. Dynamic response of the heliostat indicated that the first 5 eigenmodes were in the 17-20 Hz range. The individual structure elements such as the trusses and c-rails were fabricated locally and assembled with the mirror facets in the lab for initial fit check and testing. The nine mirror facet surface errors were characterized using photogrammetry and verified using Reverse Hartmann techniques and showed to be in the order of 1 mrad or less. A three-level controller (main, gateway and heliostat) was architected and built. Tracking of the sun is done using NREL's Sun Tracking Algorithm implemented in the gateway controller. Target-pointing vectors are calculated for each heliostat and conveyed wirelessly to the individual heliostat controllers for actuating the azimuth and elevation motors. The power subsystem consisting of solar panels and a battery provide 24V for the actuators and controller boards. The system was sized to provide adequate power for a period of Shrs of operation when power is not available. Initial calibration will be performed with on-site camera tracking the sun's image on a target located approximately 52m from the heliostat. Testing of the heliostat pointing under calm and windy conditions will be done to demonstrate overall performance that meet DOE targets of 4 mrad under 27mph winds. Commercialization efforts are underway to transition the design to the commercial sector. The project is well on its way to approaching overall cost targets and current estimates are approximately $90-110/m(2) and lower costs can be achieved with alternates to the film we have identified. C1 [Ganapathi, Gani; Nesmith, Bill; Kindler, Andrew] CALTECH, JPL, Pasadena, CA 91125 USA. [Palisoc, Arthur] LGarde Inc, Tustin, CA USA. [Buchroithner, Armin] Graz Univ Technol, Graz, Austria. [Nataraj, Sai] Calif State Univ Los Angeles, Los Angeles, CA 90032 USA. [Greschik, Gyula] TentGuild Engn, Boulder, CO USA. [Gidanian, Koorosh] KNF Corp, Laguna Beach, CA USA. RP Ganapathi, G (reprint author), CALTECH, JPL, Pasadena, CA 91125 USA. NR 7 TC 0 Z9 0 U1 1 U2 1 PU AMER SOC MECHANICAL ENGINEERS PI NEW YORK PA THREE PARK AVENUE, NEW YORK, NY 10016-5990 USA BN 978-0-7918-5022-0 PY 2016 AR UNSP V001T04A025 PG 8 WC GREEN & SUSTAINABLE SCIENCE & TECHNOLOGY; Energy & Fuels; Engineering, Mechanical SC Science & Technology - Other Topics; Energy & Fuels; Engineering GA BG4TT UT WOS:000389094800044 ER PT S AU Jenkins, JM Twicken, JD McCauliff, S Campbell, J Sanderfer, D Lung, D Mansouri-Samani, M Girouard, F Tenenbaum, P Klaus, T Smith, JC Caldwell, DA Chacon, AD Henze, C Heiges, C Latham, DW Morgan, E Swade, D Rinehart, S Vanderspek, R AF Jenkins, Jon M. Twicken, Joseph D. McCauliff, Sean Campbell, Jennifer Sanderfer, Dwight Lung, David Mansouri-Samani, Masoud Girouard, Forrest Tenenbaum, Peter Klaus, Todd Smith, Jeffrey C. Caldwell, Douglas A. Chacon, A. Dean Henze, Christopher Heiges, Cory Latham, David W. Morgan, Edward Swade, Daryl Rinehart, Stephen Vanderspek, Roland BE Chiozzi, G Guzman, JC TI The TESS Science Processing Operations Center SO SOFTWARE AND CYBERINFRASTRUCTURE FOR ASTRONOMY IV SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Software and Cyberinfrastructure for Astronomy IV CY JUN 26-30, 2016 CL Edinburgh, SCOTLAND SP SPIE DE transit photometry; science pipelines; TESS mission; exoplanets; high performance computing AB The Transiting Exoplanet Survey Satellite (TESS) will conduct a search for Earth's closest cousins starting in early 2018 and is expected to discover similar to 1,000 small planets with R-p < 4 R circle plus and measure the masses of at least 50 of these small worlds. The Science Processing Operations Center (SPOC) is being developed at NASA Ames Research Center based on the Kepler science pipeline and will generate calibrated pixels and light curves on the NASA Advanced Supercomputing Division's Pleiades supercomputer. The SPOC will also search for periodic transit events and generate validation products for the transit-like features in the light curves. All TESS SPOC data products will be archived to the Mikulski Archive for Space Telescopes (MAST). C1 [Jenkins, Jon M.; Sanderfer, Dwight; Henze, Christopher] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Twicken, Joseph D.; Tenenbaum, Peter; Smith, Jeffrey C.; Caldwell, Douglas A.] NASA, Ames Res Ctr, SETI Inst, Moffett Field, CA 94035 USA. [McCauliff, Sean; Campbell, Jennifer] NASA, Ames Res Ctr, Wyle Labs, Moffett Field, CA 94035 USA. [Lung, David; Chacon, A. Dean] NASA, Ames Res Ctr, Millenium Engn, Moffett Field, CA 94035 USA. [Mansouri-Samani, Masoud; Klaus, Todd] SGT Inc, NASA, Ames Res Ctr, Moffett Field, CA USA. [Girouard, Forrest] Logyx LLC, NASA, Ames Res Ctr, Moffett Field, CA USA. [Heiges, Cory] NASA, Goddard Space Flight Ctr, Gen Dynam, Greenbelt, MD USA. [Latham, David W.] Harvard Smithsonian Ctr Astrophys, 60 Garden St, Cambridge, MA 02138 USA. [Morgan, Edward; Vanderspek, Roland] MIT, 77 Massachusetts Ave, Cambridge, MA 02139 USA. [Swade, Daryl] Space Telescope Sci Inst, 3700 San Martin Dr, Baltimore, MD 21218 USA. [Rinehart, Stephen] NASA, Goddard Space Flight Ctr, Greenbelt, MD USA. RP Jenkins, JM (reprint author), NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. EM jon.m.jenkins@nasa.gov NR 7 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0205-2; 978-1-5106-0206-9 J9 PROC SPIE PY 2016 VL 9913 AR UNSP 99133E DI 10.1117/12.2233418 PG 20 WC Astronomy & Astrophysics; Engineering, Electrical & Electronic; Optics SC Astronomy & Astrophysics; Engineering; Optics GA BG4GJ UT WOS:000388804600111 ER PT S AU Schindler, K Lang, D Moore, L Hummer, M Wolf, J Krabbe, A AF Schindler, Karsten Lang, Dustin Moore, Liz Huemmer, Martin Wolf, Juergen Krabbe, Alfred BE Chiozzi, G Guzman, JC TI Computer-aided star pattern recognition with astrometry.net: In-flight support of telescope operations on SOFIA SO SOFTWARE AND CYBERINFRASTRUCTURE FOR ASTRONOMY IV SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Software and Cyberinfrastructure for Astronomy IV CY JUN 26-30, 2016 CL Edinburgh, SCOTLAND SP SPIE DE SOFIA; telescope pointing; astrometry; pattern recognition; plate solving; blind astrometric calibration; data reduction; operations ID SCIENCE AB SOFIA is an airborne observatory, operating a gyroscopically stabilized telescope with an effective aperture of 2.5 m on-board a modified Boeing 747SP. Its primary objective is to conduct observations at mid-to far-infrared wavelengths. When SOFIA opens its door to the night sky, the initial telescope pointing is estimated from the aircraft's position and heading as well as the telescope's attitude relative to the aircraft. This initial pointing estimate needs to be corrected using stars that are manually identified in tracking camera images; telescope pointing also needs to be verified and refined at the beginning of each flight leg. We report about the implementation of the astrometry. net package on the telescope operator workstations on-board SOFIA. This package provides a very robust, reliable and fast algorithm for blind astrometric image calibration. Using images from SOFIA's Wide Field Imager, we are able to display an almost instant, continuous feedback of calculated right ascension, declination and field rotation in the GUI for the telescope operator. The computer-aided recognition of star patterns will support telescope pointing calibrations in the future, further increasing the efficiency of the observatory. We also discuss other current and future use cases of the astrometry.net package in the SOFIA project and at the German SOFIA Institute (DSI). C1 [Schindler, Karsten; Moore, Liz; Huemmer, Martin; Wolf, Juergen; Krabbe, Alfred] NASA, Ames Res Ctr, SOFIA Sci Ctr, Mail Stop N211-1 N232-12, Moffett Field, CA 94035 USA. [Schindler, Karsten; Huemmer, Martin; Wolf, Juergen] Univ Stuttgart, Deutsch SOFIA Inst, Pfaffenwaldring 29, D-70569 Stuttgart, Germany. [Lang, Dustin] Univ Toronto, Dept Astron & Astrophys, 50 St George St, Toronto, ON M5S 3H4, Canada. [Lang, Dustin] Univ Toronto, Dunlap Inst, 50 St George St, Toronto, ON M5S 3H4, Canada. RP Schindler, K (reprint author), NASA, Ames Res Ctr, SOFIA Sci Ctr, Mail Stop N211-1 N232-12, Moffett Field, CA 94035 USA.; Schindler, K (reprint author), Univ Stuttgart, Deutsch SOFIA Inst, Pfaffenwaldring 29, D-70569 Stuttgart, Germany. EM schindler@dsi.uni-stuttgart.de RI Schindler, Karsten/D-9950-2016 OI Schindler, Karsten/0000-0001-7337-2452 NR 21 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0205-2; 978-1-5106-0206-9 J9 PROC SPIE PY 2016 VL 9913 AR UNSP 991307 DI 10.1117/12.2231531 PG 14 WC Astronomy & Astrophysics; Engineering, Electrical & Electronic; Optics SC Astronomy & Astrophysics; Engineering; Optics GA BG4GJ UT WOS:000388804600006 ER PT S AU Gange, G Navas, JA Schachte, P Sondergaard, H Stuckey, PJ AF Gange, Graeme Navas, Jorge A. Schachte, Peter Sondergaard, Harald Stuckey, Peter J. BE Rival, X TI Exploiting Sparsity in Difference-Bound Matrices SO STATIC ANALYSIS, (SAS 2016) SE Lecture Notes in Computer Science LA English DT Proceedings Paper CT 23rd International Symposium on Static Analysis (SAS) CY SEP 08-10, 2016 CL Univ Edinburgh, Edinburgh, SCOTLAND SP Facebook, Fondation lENS, Springer HO Univ Edinburgh ID ALGORITHMS AB Relational numeric abstract domains are very important in program analysis. Common domains, such as Zones and Octagons, are usually conceptualised with weighted digraphs and implemented using difference-bound matrices (DBMs). Unfortunately, though conceptually simple, direct implementations of graph-based domains tend to perform poorly in practice, and are impractical for analyzing large code-bases. We propose new DBM algorithms that exploit sparsity and closed operands. In particular, a new representation which we call split normal form reduces graph density on typical abstract states. We compare the resulting implementation with several existing DBM-based abstract domains, and show that we can substantially reduce the time to perform full DBM analysis, without sacrificing precision. C1 [Gange, Graeme; Schachte, Peter; Sondergaard, Harald; Stuckey, Peter J.] Univ Melbourne, Dept Comp & Informat Syst, Melbourne, Vic 3010, Australia. [Navas, Jorge A.] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Gange, G (reprint author), Univ Melbourne, Dept Comp & Informat Syst, Melbourne, Vic 3010, Australia. EM gkgange@unimelb.edu.au NR 21 TC 0 Z9 0 U1 0 U2 0 PU SPRINGER INT PUBLISHING AG PI CHAM PA GEWERBESTRASSE 11, CHAM, CH-6330, SWITZERLAND SN 0302-9743 BN 978-3-662-53413-7; 978-3-662-53412-0 J9 LECT NOTES COMPUT SC PY 2016 VL 9837 BP 189 EP 211 DI 10.1007/978-3-662-53413-7_10 PG 23 WC Computer Science, Software Engineering; Computer Science, Theory & Methods SC Computer Science GA BG4JU UT WOS:000388924600010 ER PT S AU de Melo, ACV Pasareanu, CS Hanazumi, S AF de Melo, Ana C. V. Pasareanu, Corina S. Hanazumi, Simone BE Sampaio, A Wang, F TI Towards MC/DC Coverage of Properties Specification Patterns SO THEORETICAL ASPECTS OF COMPUTING - ICTAC 2016 SE Lecture Notes in Computer Science LA English DT Proceedings Paper CT 13th International Colloquium on Theoretical Aspects of Computing (ICTAC) CY OCT 24-31, 2016 CL Natl Taiwan Univ, Taipei, TAIWAN SP Microsoft Res, Springer, EasyChair, Minist Sci & Technol, Minist Educ, Minist Econ Affairs, Taipei Municipal Govt HO Natl Taiwan Univ AB Model based testing is used to validate the actual system against its requirements described as formal specification, while formal verification proves that a requirement is not violated in the overall system. Verifying properties, in certain cases, becomes very expensive (or unpractical), mainly when the application of test techniques is enough for the users purposes. The Modified Condition/Decision Coverage (MC/DC), used in the avionics software industry, is recognised as a good technique to find out the possible mistakes on programs logics because it covers how each condition can affect the programs' decisions outcomes. It has also been adapted to provide the coverage of specifications in the requirements-based approach. This paper proposes a technique to decompose properties (specifications), defined as regular expressions, into subexpressions representing test cases to cover the MD/DC for specifications (Unique First Word Recognition). Then, instead of proving an entire property, we can use a model checker to observe and select program executions that cover all the test cases given as the subexpressions. To support this approach, we give a syntactic characterisation of the properties decomposition, inductively defined over the syntax of regular expressions, and show how to use the technique to decompose Specification Patterns (SPS) and monitor their satisfiability using the Java PathFinder (JPF). C1 [de Melo, Ana C. V.; Hanazumi, Simone] Univ Sao Paulo, Dept Comp Sci, Sao Paulo, Brazil. [Pasareanu, Corina S.] Carnegie Mellon, NASA, Ames Res Ctr, M-S 269-2, Moffett Field, CA 94035 USA. RP de Melo, ACV (reprint author), Univ Sao Paulo, Dept Comp Sci, Sao Paulo, Brazil. EM acvm@ime.usp.br; corina.s.pasareanu@nasa.gov; hanazumi@ime.usp.br NR 14 TC 0 Z9 0 U1 0 U2 0 PU SPRINGER INT PUBLISHING AG PI CHAM PA GEWERBESTRASSE 11, CHAM, CH-6330, SWITZERLAND SN 0302-9743 BN 978-3-319-46750-4; 978-3-319-46749-8 J9 LECT NOTES COMPUT SC PY 2016 VL 9965 BP 158 EP 175 DI 10.1007/978-3-319-46750-4_10 PG 18 WC Computer Science, Software Engineering; Computer Science, Theory & Methods SC Computer Science GA BG4JS UT WOS:000388923700010 ER PT S AU Acosta-Zamora, A de la Torre, M Love, N Choudhuri, A AF Acosta-Zamora, Arturo de la Torre, Martin Love, Noonan Choudhuri, Ahsan GP AMER INST AERONAUT & ASTRONAUT TI Investigation on Flow-Flame Front Characteristics in a Backward Facing Step Combustor Using Laser Diagnostics SO 14TH INTERNATIONAL ENERGY CONVERSION ENGINEERING CONFERENCE SE International Energy Conversion Engineering Conference LA English DT Proceedings Paper CT 14th International Energy Conversion Engineering Conference CY JUL 25-27, 2016 CL Salt Lake City, UT AB Turbulent combustion effects on the flow field of a backward facing step combustor are studied in the work hereby presented. Turbulence effects on the thickened flame regime are of interest to this study. An air-methane mix was selected as the basis for this study. A combustor with a backward-facing step flame stabilization method and optical accessibility features for flow diagnostics houses the combustion processes. A grid, or perforated plate is used to generate flow turbulence. Flow field characteristics and flame front location are analyzed through a high speed Particle Image Velocimetry (PIV) and Laser Induced Fluorescence laser systems respectively. C1 [Acosta-Zamora, Arturo; de la Torre, Martin; Love, Noonan; Choudhuri, Ahsan] Univ Texas El Paso, Dept Mech Engn, NASA, Ctr Space Explorat Technol Res, El Paso, TX 79968 USA. RP Acosta-Zamora, A (reprint author), Univ Texas El Paso, Dept Mech Engn, NASA, Ctr Space Explorat Technol Res, El Paso, TX 79968 USA. EM csetr@utep.edu NR 11 TC 0 Z9 0 U1 0 U2 0 PU AMER INST AERONAUTICS & ASTRONAUTICS PI RESTON PA 1801 ALEXANDER BELL DR, STE 500, RESTON, VA 20191-4344 USA SN 1947-7805 BN 978-1-62410-407-7 J9 INT ENERGY CONVERS PY 2016 PG 10 WC Engineering, Aerospace SC Engineering GA BG4CX UT WOS:000388660400018 ER PT S AU Aulisio, MV Pinero, LR White, BL Hickman, TA Bontempo, JJ Hertel, TA Birchenough, AG AF Aulisio, Michael V. Pinero, Luis R. White, Brandon L. Hickman, Tyler A. Bontempo, James J. Hertel, Thomas A. Birchenough, Arthur G. GP AMER INST AERONAUT & ASTRONAUT TI Status of the Development of Flight Power Processing Units for the NASA's Evolutionary Xenon Thruster - Commercial (NEXT-C) Project SO 14TH INTERNATIONAL ENERGY CONVERSION ENGINEERING CONFERENCE SE International Energy Conversion Engineering Conference LA English DT Proceedings Paper CT 14th International Energy Conversion Engineering Conference CY JUL 25-27, 2016 CL Salt Lake City, UT AB A pathfinder prototype unit and two flight power processing units (PPUs) are being developed by the Aerojet Rocketdyne Corporation in Redmond, Washington and ZIN Technologies in Cleveland, Ohio, in support of the NEXT-C Project. This project is being led by the NASA Glenn Research Center in Cleveland, Ohio, and will also yield two flight thrusters. This hardware is being considered to be provided as Government Furnished Equipment for the New Frontiers Program, and is applicable to a variety of planetary science missions and astrophysics science missions. The design of the NEXT-C PPU evolves from the hardware fabricated under the NEXT technology development project. The power processing unit operates from two sources: a wide input 80 to 160 V high-power bus and a nominal 28 V low-power bus. The unit includes six power supplies. Four power supplies (beam, accelerator, discharge, and neutralizer keeper) are needed for steady state operation, while two cathode heater power supplies (neutralizer and discharge) are utilized during thruster startup. The unit in total delivers up to 7 kW of regulated power to a single gridded-ion thruster. Significant modifications to the initial design include: high-power adaptive-delay control, upgrade of design to EEE-INST-002 compliance, telemetry accuracy improvements, incorporation of telemetry to detect plume-mode operation, and simplification of the design in select areas to improve manufacturability and commercialization potential. The project is presently in the prototype phase and preparing for qualification level environmental testing. C1 [Aulisio, Michael V.; White, Brandon L.] NASA, Glenn Res Ctr, Power Management & Distribut Branch, 21000 Brookpk Rd,301-5, Cleveland, OH 44135 USA. [Pinero, Luis R.; Hickman, Tyler A.] NASA, Elect Prop Syst Branch, 21000 Brookpk Rd,301-3, Cleveland, OH 44135 USA. [Bontempo, James J.] ZIN Technol Inc, 6745 Engle Rd, Cleveland, OH 44130 USA. [Hertel, Thomas A.] Aerojet Rocketdyne, 8900 De Soto Ave, Canoga Pk, CA 91309 USA. [Birchenough, Arthur G.] Vantage Partners LLC, 3000 Aerosp Pkwy, Cleveland, OH 44135 USA. RP Aulisio, MV (reprint author), NASA, Glenn Res Ctr, Power Management & Distribut Branch, 21000 Brookpk Rd,301-5, Cleveland, OH 44135 USA. NR 4 TC 0 Z9 0 U1 0 U2 0 PU AMER INST AERONAUTICS & ASTRONAUTICS PI RESTON PA 1801 ALEXANDER BELL DR, STE 500, RESTON, VA 20191-4344 USA SN 1947-7805 BN 978-1-62410-407-7 J9 INT ENERGY CONVERS PY 2016 PG 6 WC Engineering, Aerospace SC Engineering GA BG4CX UT WOS:000388660400003 ER PT S AU Barklay, C Tolson, B Bolotin, G Keyawa, N Woerner, D AF Barklay, Chadwick Tolson, Boyd Bolotin, Gary Keyawa, Nicholas Woerner, David GP AMER INST AERONAUT & ASTRONAUT TI Performance Testing of the EU/QU MMRTG SO 14TH INTERNATIONAL ENERGY CONVERSION ENGINEERING CONFERENCE SE International Energy Conversion Engineering Conference LA English DT Proceedings Paper CT 14th International Energy Conversion Engineering Conference CY JUL 25-27, 2016 CL Salt Lake City, UT AB The Multi-Mission Radioisotope Thermoelectric Generator (MMRTG) Lifecycle Testing Laboratory is operated by the University of Dayton Research Institute (UDRI), which is dedicated to conducting life-cycle testing of electrically heated versions of the MMRTG. Since there are only two MMRTG electrically-heated thermoelectric generators (ETG) available for testing, a Test Plan Development Working Group was established to determine and prioritize the performance testing that is being conducted with the Engineering Unit (EU) and Qualification Unit (QU) ETGs. This working group is comprised of subject matter experts from the U.S. Department of Energy ( DOE), the National Aeronautics and Space Administration (NASA) Glenn Research Center (GRC), NASA Jet Propulsion Laboratory (JPL), Idaho National Laboratory (INL), Oak Ridge National Laboratory (ORNL), UDRI, Aerojet Rocketdyne, and Teledyne Energy Systems. The highest priority testing was concluded by the working group to be: 1) To determine the impact of thermal cycling on thermoelectric components by characterizing the evolution of the thermoelectric/electrical properties of the EU as a result of thermal cycling the ETG through a Martian Sol repeatedly; 2) to characterize the effect of a simulated cruise-phase environment on the QU by evaluating the change in performance of the ETG before and after a cruise-phase simulation; and 3) characterize and clear any potential MMRTG internal shorts to chassis by integrating the JPL derived active short technique between the internal electrical power circuit and chassis frame of the MMRTG. The data and risk mitigation techniques derived from this testing can potentially be incorporated into future missions that would employ the MMRTG or successor thermoelectric radioisotope power systems. C1 [Barklay, Chadwick] Univ Dayton, Res Inst, Energy Technol & Mat, 300 Coll Pk, Dayton, OH 45469 USA. [Tolson, Boyd] UES Inc, Aerosp Power & Prop, 4401 Dayton Xenia Rd, Dayton, OH 45432 USA. [Bolotin, Gary] CALTECH, Jet Prop Lab, Power & Sensor Syst, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Keyawa, Nicholas] CALTECH, Jet Prop Lab, Thermal Energy Convers Applicat & Syst, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Woerner, David] CALTECH, Jet Prop Lab, Nucl Space Power Off, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Barklay, C (reprint author), Univ Dayton, Res Inst, Energy Technol & Mat, 300 Coll Pk, Dayton, OH 45469 USA. NR 5 TC 0 Z9 0 U1 0 U2 0 PU AMER INST AERONAUTICS & ASTRONAUTICS PI RESTON PA 1801 ALEXANDER BELL DR, STE 500, RESTON, VA 20191-4344 USA SN 1947-7805 BN 978-1-62410-407-7 J9 INT ENERGY CONVERS PY 2016 PG 7 WC Engineering, Aerospace SC Engineering GA BG4CX UT WOS:000388660400033 ER PT S AU Briggs, MH Prahl, J Loparo, K AF Briggs, Maxwell H. Prahl, Joseph Loparo, Kenneth GP AMER INST AERONAUT & ASTRONAUT TI Improving Power Density of Free-Piston Stirling Engines SO 14TH INTERNATIONAL ENERGY CONVERSION ENGINEERING CONFERENCE SE International Energy Conversion Engineering Conference LA English DT Proceedings Paper CT 14th International Energy Conversion Engineering Conference CY JUL 25-27, 2016 CL Salt Lake City, UT AB Analyses and experiments demonstrate the potential benefits of optimizing piston and displacer motion in a free-piston Stirling Engine. Isothermal analysis shows the theoretical limits of power density improvement due to ideal motion in ideal Stirling engines. More realistic models based on nodal analysis show that ideal piston and displacer waveforms are not optimal, often producing less power than engines that use sinusoidal piston and displacer motion. Constrained optimization using nodal analysis predicts that Stirling engine power density can be increased by as much as 58% using optimized higher harmonic piston and displacer motion. An experiment is conducted in which an engine designed for sinusoidal motion is forced to operate with both second and third harmonics, resulting in a piston power increase of as much as 14%. Analytical predictions are compared to experimental data and show close agreement with indirect thermodynamic power calculations, but poor agreement with direct electrical power measurements. C1 [Briggs, Maxwell H.] NASA, Glenn Res Ctr, Thermal Energy Convers Branch, 21000 Brookpk Rd MS 301-2, Cleveland, OH 44135 USA. [Prahl, Joseph] Case Western Reserve Univ, Mech Engn, 10900 Euclid Ave, Cleveland, OH 44106 USA. [Loparo, Kenneth] Case Western Reserve Univ, Elect Engn, 10900 Euclid Ave, Cleveland, OH 44106 USA. RP Briggs, MH (reprint author), NASA, Glenn Res Ctr, Thermal Energy Convers Branch, 21000 Brookpk Rd MS 301-2, Cleveland, OH 44135 USA. NR 25 TC 0 Z9 0 U1 1 U2 1 PU AMER INST AERONAUTICS & ASTRONAUTICS PI RESTON PA 1801 ALEXANDER BELL DR, STE 500, RESTON, VA 20191-4344 USA SN 1947-7805 BN 978-1-62410-407-7 J9 INT ENERGY CONVERS PY 2016 PG 10 WC Engineering, Aerospace SC Engineering GA BG4CX UT WOS:000388660400063 ER PT S AU Briggs, MH Gibson, MA Geng, S Sanzi, J AF Briggs, Maxwell H. Gibson, Marc A. Geng, Steven Sanzi, James GP AMER INST AERONAUT & ASTRONAUT TI Fission Surface Power Technology Demonstration Unit Test Results SO 14TH INTERNATIONAL ENERGY CONVERSION ENGINEERING CONFERENCE SE International Energy Conversion Engineering Conference LA English DT Proceedings Paper CT 14th International Energy Conversion Engineering Conference CY JUL 25-27, 2016 CL Salt Lake City, UT AB The Fission Surface Power (FSP) Technology Demonstration Unit (TDU) is a system-level demonstration of fission power technology intended for use on manned missions to Mars. The Baseline FSP systems consists of a 190 kWt UO2 fast-spectrum reactor cooled by a primary pumped liquid metal loop. This liquid metal loop transfers heat to two intermediate liquid metal loops designed to isolate fission products in the primary loop from the balance of plant. The intermediate liquid metal loops transfer heat to four Stirling Power Conversion Units (PCU), each of which produce 12 kWe (48 kW total) and reject waste heat to two pumped water loops, which transfer the waste heat to titanium-water heat pipe radiators. The FSP TDU simulates a single leg of the baseline FSP system using an electrically heater core simulator, a single liquid metal loop, a single PCU, and a pumped water loop which rejects the waste heat to a Facility Cooling System (FCS). When operated at the nominal operating conditions (modified for low liquid metal flow) during TDU testing the PCU produced 8.9 kW of power at an efficiency of 21.7% resulting in a net system power of 8.1 kW and a system level efficiency of 17.2%. The reduction in PCU power from levels seen during electrically heated testing is the result of insufficient heat transfer from the NaK heater head to the Stirling acceptor, which could not be tested at Sunpower prior to delivery to GRC. The maximum PCU power of 10.4 kW was achieved at the maximum liquid metal temperature of 875 K, minimum water temperature of 350 K, 1.1 kg/s liquid metal flow, 0.39 kg/s water flow, and 15.0 mm amplitude at an efficiency of 23.3%. This resulted in a system net power of 9.7 kW and a system efficiency of 18.7 %. C1 [Briggs, Maxwell H.; Gibson, Marc A.; Geng, Steven] NASA, Glenn Res Ctr, Thermal Energy Convers Branch, 21000 Brookpk Rd MS 301-2, Cleveland, OH 44135 USA. [Sanzi, James] Vantage Partners, Thermal Energy Convers Branch, 21000 Brookpk Rd MS 301-2, Cleveland, OH 44135 USA. RP Briggs, MH (reprint author), NASA, Glenn Res Ctr, Thermal Energy Convers Branch, 21000 Brookpk Rd MS 301-2, Cleveland, OH 44135 USA. NR 15 TC 0 Z9 0 U1 0 U2 0 PU AMER INST AERONAUTICS & ASTRONAUTICS PI RESTON PA 1801 ALEXANDER BELL DR, STE 500, RESTON, VA 20191-4344 USA SN 1947-7805 BN 978-1-62410-407-7 J9 INT ENERGY CONVERS PY 2016 PG 7 WC Engineering, Aerospace SC Engineering GA BG4CX UT WOS:000388660400059 ER PT S AU Choi, MK AF Choi, Michael K. GP AMER INST AERONAUT & ASTRONAUT TI Swift BAT Thermal Recovery After Loop Heat Pipe #0 Secondary Heater Controller Failure in October 2015 SO 14TH INTERNATIONAL ENERGY CONVERSION ENGINEERING CONFERENCE SE International Energy Conversion Engineering Conference LA English DT Proceedings Paper CT 14th International Energy Conversion Engineering Conference CY JUL 25-27, 2016 CL Salt Lake City, UT AB The Swift BAT LHP #0 primary heater controller failed on March 31, 2010. It has been disabled. On October 31, 2015, the secondary heater controller of this LHP failed. On November 1, 2015, the LHP #0 CC temperature increased to as 18.6 degrees C, despite that the secondary heater controller set point was 8.8 degrees C. It caused the average DM XA1 temperature to increase to 25.9 degrees C, which was 5 degrees C warmer than nominal. As a result, the detectors became noisy. To solve this problem, the LHP #1 secondary heater controller set point was decreased in 0.5 degrees C decrements to 2.2 degrees C. The set-point decrease restored the average DM XA1 temperature to a nominal value of 19.7 degrees C on November 21. C1 [Choi, Michael K.] NASA, Goddard Space Flight Ctr, Thermal Engn Branch, Code 545, Greenbelt, MD 20771 USA. RP Choi, MK (reprint author), NASA, Goddard Space Flight Ctr, Thermal Engn Branch, Code 545, Greenbelt, MD 20771 USA. NR 6 TC 0 Z9 0 U1 0 U2 0 PU AMER INST AERONAUTICS & ASTRONAUTICS PI RESTON PA 1801 ALEXANDER BELL DR, STE 500, RESTON, VA 20191-4344 USA SN 1947-7805 BN 978-1-62410-407-7 J9 INT ENERGY CONVERS PY 2016 PG 14 WC Engineering, Aerospace SC Engineering GA BG4CX UT WOS:000388660400022 ER PT S AU Choi, MK AF Choi, Michael K. GP AMER INST AERONAUT & ASTRONAUT TI Using Paraffin PCM to Make Optical Communication Type of Payloads Thermally Self-Sufficient for Operation in Orion Crew Module SO 14TH INTERNATIONAL ENERGY CONVERSION ENGINEERING CONFERENCE SE International Energy Conversion Engineering Conference LA English DT Proceedings Paper CT 14th International Energy Conversion Engineering Conference CY JUL 25-27, 2016 CL Salt Lake City, UT AB An innovative concept of using paraffin phase change material with a melting point of 28 degrees C to make Optical Communication type of payload thermally self-sufficient for operation in the Orion Crew Module is presented. It stores the waste heat of the payload and permits it to operate for about one hour by maintaining its temperature within the maximum operating limit. It overcomes the problem of relying on the availability of cold plate heat sink in the Orion Crew Module. C1 [Choi, Michael K.] NASA, Goddard Space Flight Ctr, Thermal Engn Branch, Code 545, Greenbelt, MD 20771 USA. RP Choi, MK (reprint author), NASA, Goddard Space Flight Ctr, Thermal Engn Branch, Code 545, Greenbelt, MD 20771 USA. NR 11 TC 0 Z9 0 U1 0 U2 0 PU AMER INST AERONAUTICS & ASTRONAUTICS PI RESTON PA 1801 ALEXANDER BELL DR, STE 500, RESTON, VA 20191-4344 USA SN 1947-7805 BN 978-1-62410-407-7 J9 INT ENERGY CONVERS PY 2016 PG 7 WC Engineering, Aerospace SC Engineering GA BG4CX UT WOS:000388660400011 ER PT S AU Geng, SM Reid, TV AF Geng, Steven M. Reid, Terry V. GP AMER INST AERONAUT & ASTRONAUT TI Two-Step Multi-Physics Analysis of an Annular Linear Induction Pump for Fission Power Systems SO 14TH INTERNATIONAL ENERGY CONVERSION ENGINEERING CONFERENCE SE International Energy Conversion Engineering Conference LA English DT Proceedings Paper CT 14th International Energy Conversion Engineering Conference CY JUL 25-27, 2016 CL Salt Lake City, UT AB One of the key technologies associated with fission power systems (FPS) is the annular linear induction pump (ALIP). ALIPs are used to circulate liquid-metal fluid for transporting thermal energy from the nuclear reactor to the power conversion device. ALIPs designed and built to date for FPS project applications have not performed up to expectations. A unique, two-step approach was taken toward the multi-physics examination of an ALIP using ANSYS Maxwell 3D and Fluent. This multi-physics approach was developed so that engineers could investigate design variations that might improve pump performance. Of interest was to determine if simple geometric modifications could be made to the ALIP components with the goal of increasing the Lorentz forces acting on the liquid-metal fluid, which in turn would increase pumping capacity. The multi-physics model first calculates the Lorentz forces acting on the liquid metal fluid in the ALIP annulus. These forces are then used in a computational fluid dynamics simulation as (a) internal boundary conditions and (b) source functions in the momentum equations within the Navier-Stokes equations. The end result of the two-step analysis is a predicted pump pressure rise that can be compared with experimental data. C1 [Geng, Steven M.; Reid, Terry V.] NASA, Glenn Res Ctr, Thermal Energy Convers Branch, 21000 Brookpk Rd,M-S 301-2, Cleveland, OH 44135 USA. RP Geng, SM (reprint author), NASA, Glenn Res Ctr, Thermal Energy Convers Branch, 21000 Brookpk Rd,M-S 301-2, Cleveland, OH 44135 USA. NR 6 TC 0 Z9 0 U1 0 U2 0 PU AMER INST AERONAUTICS & ASTRONAUTICS PI RESTON PA 1801 ALEXANDER BELL DR, STE 500, RESTON, VA 20191-4344 USA SN 1947-7805 BN 978-1-62410-407-7 J9 INT ENERGY CONVERS PY 2016 PG 12 WC Engineering, Aerospace SC Engineering GA BG4CX UT WOS:000388660400060 ER PT S AU Holgate, TC Song, Y Bennett, R Keyser, S Hammel, T Sievers, R Caillat, T Fleurial, JP AF Holgate, Tim C. Song, Ying Bennett, Russell Keyser, Steven Hammel, Thomas Sievers, Robert Caillat, Thierry Fleurial, Jean-Pierre GP AMER INST AERONAUT & ASTRONAUT TI Enhancement of the Multi-Mission Radioisotope Thermoelectric Generator with efficient Skutterudite Thermoelectric Couples: Current Status of the Skutterudite Technology Maturation Program SO 14TH INTERNATIONAL ENERGY CONVERSION ENGINEERING CONFERENCE SE International Energy Conversion Engineering Conference LA English DT Proceedings Paper CT 14th International Energy Conversion Engineering Conference CY JUL 25-27, 2016 CL Salt Lake City, UT AB The Multi-Mission Radioisotope Thermoelectric Generator (MMRTG) developed for NASA by Aerojet Rocketdyne and Teledyne Energy Systems, Inc. (TESI) has been providing reliable power to the Mars Curiosity Rover since its launch in 2011 (Mission on Mars began in August 2012). An improvement of the performance of the MMRTG is underway at TESI through a technology maturation program where higher efficiency skutterudite materials developed on the laboratory scale at NASA's Jet Propulsion Laboratory (JPL) are being further developed at the production level into "flight-ready" materials and components. The success of this project will result in an enhanced MMRTG (eMMRTG) with an anticipated improvement of 25-30% in the beginning-of-life power and even greater improvement by end-of-life due to improved thermoelectric life properties. The status of the program, including engineering challenges, successes and current production capabilities will be presented. C1 [Holgate, Tim C.; Song, Ying; Bennett, Russell; Keyser, Steven; Hammel, Thomas; Sievers, Robert] Teledyne Energy Syst Inc, Adv Power Grp, Hunt Valley, MD 21043 USA. [Caillat, Thierry; Fleurial, Jean-Pierre] CALTECH, Jet Prop Lab, Power & Sensor Syst Sect, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Holgate, TC (reprint author), Teledyne Energy Syst Inc, Adv Power Grp, Hunt Valley, MD 21043 USA. NR 7 TC 0 Z9 0 U1 0 U2 0 PU AMER INST AERONAUTICS & ASTRONAUTICS PI RESTON PA 1801 ALEXANDER BELL DR, STE 500, RESTON, VA 20191-4344 USA SN 1947-7805 BN 978-1-62410-407-7 J9 INT ENERGY CONVERS PY 2016 PG 7 WC Engineering, Aerospace SC Engineering GA BG4CX UT WOS:000388660400036 ER PT S AU Lewandowski, EJ Dobbs, MW Oriti, SM AF Lewandowski, Edward J. Dobbs, Michael W. Oriti, Salvatore M. GP AMER INST AERONAUT & ASTRONAUT TI Advanced Stirling Radioisotope Generator EU2 Anomaly Investigation SO 14TH INTERNATIONAL ENERGY CONVERSION ENGINEERING CONFERENCE SE International Energy Conversion Engineering Conference LA English DT Proceedings Paper CT 14th International Energy Conversion Engineering Conference CY JUL 25-27, 2016 CL Salt Lake City, UT AB The Advanced Stirling Radioisotope Generator (ASRG) Engineering Unit 2 (EU2) is the highest fidelity electrically-heated Stirling radioisotope generator built to date. NASA Glenn Research Center (GRC) completed the assembly of the ASRG EU2 in September, 2014 using hardware from the now cancelled ASRG flight development project. The ASRG EU2 integrated the first pair of Sunpower's ASC-E3 Stirling convertors (ASC-E3 #1 and #2) in an aluminum generator housing with Lockheed Martin's Engineering Development Unit (EDU) 4 controller. After just 179 hours of EU2 generator operation, the first power fluctuation occurred on ASC-E3 #1. The first power fluctuation occurred 175 hours later on ASC-E3 #2. Over time, the power fluctuations became more frequent on both convertors and larger in magnitude. Eventually the EU2 was shut down in January, 2015. An anomaly investigation was chartered to determine root cause of the power fluctuations and other anomalous observations. A team with members from GRC, Sunpower, and Lockheed Martin conducted a thorough investigation of the EU2 anomalies. Findings from the EU2 disassembly identified proximate causes of the anomalous observations. Discussion of the team's assessment of the primary possible failure theories, root cause, and conclusions is provided. Recommendations are made for future Stirling generator development to address the findings from the anomaly investigation. Additional findings from the investigation are also discussed. C1 [Lewandowski, Edward J.; Oriti, Salvatore M.] NASA, Glenn Res Ctr, Thermal Energy Convers Branch, 21000 Brookpark Rd, Cleveland, OH 44135 USA. [Dobbs, Michael W.] Vantage Partners LLC, 3000 Aerosp Pkwy, Brookpark, OH 44142 USA. RP Lewandowski, EJ (reprint author), NASA, Glenn Res Ctr, Thermal Energy Convers Branch, 21000 Brookpark Rd, Cleveland, OH 44135 USA. NR 7 TC 0 Z9 0 U1 0 U2 0 PU AMER INST AERONAUTICS & ASTRONAUTICS PI RESTON PA 1801 ALEXANDER BELL DR, STE 500, RESTON, VA 20191-4344 USA SN 1947-7805 BN 978-1-62410-407-7 J9 INT ENERGY CONVERS PY 2016 PG 16 WC Engineering, Aerospace SC Engineering GA BG4CX UT WOS:000388660400035 ER PT S AU Li, BCY Firdosy, S Ravi, VA Smith, KL Uhl, D Ni, J Star, K Sujittosakul, S Villalpando, O Aranda, M Bux, S Ma, J Chanakian, S Nakatsukasa, G Fleurial, JP AF Li, Billy Chun-Yip Firdosy, Samad Ravi, Vilpanur A. Smith, Kevin L. Uhl, David Ni, Jennifer Star, Kurt Sujittosakul, Sutine Villalpando, Obed Aranda, Michell Bux, Sabah Ma, James Chanakian, Sevan Nakatsukasa, George Fleurial, Jean-Pierre GP AMER INST AERONAUT & ASTRONAUT TI Development of High Temperature Thermoelectric Device Technologies to Validated Materials Performance and Reliability for Advanced ThermoElectric Couple (ATEC) Program SO 14TH INTERNATIONAL ENERGY CONVERSION ENGINEERING CONFERENCE SE International Energy Conversion Engineering Conference LA English DT Proceedings Paper CT 14th International Energy Conversion Engineering Conference CY JUL 25-27, 2016 CL Salt Lake City, UT AB NASA has successfully demonstrated using Thermoelectric Radioisotope Generators (RTGs) as a power source to support a number of deep space missions. They have consistently demonstrated their extraordinary reliability and longevity (38 years of continuous operation for MHW-RTG on Voyager), relying on materials and device technologies developed in the 1960's and 1970's. The NASA Radioisotope Power Systems Program's Thermoelectric Technology Development Project (TTDP) is pursuing the development of more efficient thermoelectric technologies that can increase performance (conversion efficiency and specific power) by a factor of 2 to 4X over heritage systems. The TTDP's Advanced ThermoElectric Couple (ATEC) task has been advancing a new set of high performance materials and segmented device technologies that would offer a factor of 2 increase in conversion efficiency over Si-Ge alloys used in the GPHS-RTG. These materials, p-type Yb14MnSb11 and n-type La3-XTe4 segmented with p- and n-type filled skutterudites, have demonstrated stable performance over two years of testing. Proof-of-principle segmented devices have achieved conversion efficiencies of up to 15% at beginning-of-life when tested in a vacuum environment at hot-junction temperature up to 1273K and a cold-junction temperature of 473K. ATEC is now focusing on developing high reliability, long life components and devices, including scale-up processing of materials with enhanced mechanical robustness, fabrication of metallized leg segments and chemically and mechanically stable hot side interfaces, as well as mechanically compliant segmented multicouple device configurations. Such devices could enable the development of more capable RTGs, including modular system architectures. C1 [Li, Billy Chun-Yip; Firdosy, Samad; Ravi, Vilpanur A.; Smith, Kevin L.; Uhl, David; Ni, Jennifer; Star, Kurt; Sujittosakul, Sutine; Villalpando, Obed; Aranda, Michell; Bux, Sabah; Ma, James; Chanakian, Sevan; Nakatsukasa, George] CALTECH, Jet Prop Lab, Thermal Energy Convers Res & Adv Grp, 4800 Oak Grove Dr,M-S 277-207, Pasadena, CA 91109 USA. [Fleurial, Jean-Pierre] Thermal Energy Convers Res & Adv Grp, Power & Sensor Syst Sect, Pasadena, CA 91109 USA. RP Li, BCY (reprint author), CALTECH, Jet Prop Lab, Thermal Energy Convers Res & Adv Grp, 4800 Oak Grove Dr,M-S 277-207, Pasadena, CA 91109 USA. NR 5 TC 0 Z9 0 U1 0 U2 0 PU AMER INST AERONAUTICS & ASTRONAUTICS PI RESTON PA 1801 ALEXANDER BELL DR, STE 500, RESTON, VA 20191-4344 USA SN 1947-7805 BN 978-1-62410-407-7 J9 INT ENERGY CONVERS PY 2016 PG 8 WC Engineering, Aerospace SC Engineering GA BG4CX UT WOS:000388660400025 ER PT S AU McNatt, JS Piszczor, MF AF McNatt, Jeremiah S. Piszczor, Michael F., Jr. GP AMER INST AERONAUT & ASTRONAUT TI Improving Solar Arrays for LILT and High Radiation Environments SO 14TH INTERNATIONAL ENERGY CONVERSION ENGINEERING CONFERENCE SE International Energy Conversion Engineering Conference LA English DT Proceedings Paper CT 14th International Energy Conversion Engineering Conference CY JUL 25-27, 2016 CL Salt Lake City, UT AB NASA has initiated the Extreme Environments Solar Power (EESP) project to improve performance of solar arrays in low temperature, low intensity and high radiation environemts. The ultimate goal for this work is to enable long duration solar powered missions to Jupiter and its moons. Four research efforts were recently awarded to investigate methods to meet the project goals. C1 [McNatt, Jeremiah S.; Piszczor, Michael F., Jr.] NASA, Glenn Res Ctr, Photovolta & Electrochem Syst, 21000 Brookpk Rd MS 302-1, Cleveland, OH 44135 USA. RP McNatt, JS (reprint author), NASA, Glenn Res Ctr, Photovolta & Electrochem Syst, 21000 Brookpk Rd MS 302-1, Cleveland, OH 44135 USA. NR 1 TC 0 Z9 0 U1 0 U2 0 PU AMER INST AERONAUTICS & ASTRONAUTICS PI RESTON PA 1801 ALEXANDER BELL DR, STE 500, RESTON, VA 20191-4344 USA SN 1947-7805 BN 978-1-62410-407-7 J9 INT ENERGY CONVERS PY 2016 PG 3 WC Engineering, Aerospace SC Engineering GA BG4CX UT WOS:000388660400049 ER PT S AU Metscher, J Geng, S AF Metscher, Jonathan Geng, Steven GP AMER INST AERONAUT & ASTRONAUT TI Performance Testing of a High Temperature Linear Alternator for Stirling Convertors SO 14TH INTERNATIONAL ENERGY CONVERSION ENGINEERING CONFERENCE SE International Energy Conversion Engineering Conference LA English DT Proceedings Paper CT 14th International Energy Conversion Engineering Conference CY JUL 25-27, 2016 CL Salt Lake City, UT AB The NASA Glenn Research Center has conducted performance testing of a high temperature linear alternator (HTLA) in support of Stirling power convertor development for potential future Radioisotope Power Systems (RPS). The high temperature linear alternator is a modified version of that used in Sunpower's Advanced Stirling Convertor (ASC), and is capable of operation at temperatures up to 200 degrees C. Increasing the temperature capability of the linear alternator could expand the mission set of future Stirling RPS designs. High temperature Neodymium-Iron-Boron (Nd-Fe-B) magnets were selected for the HTLA application, and were fully characterized and tested prior to use. Higher temperature epoxy for alternator assembly was also selected and tested for thermal stability and strength. A characterization test was performed on the HTLA to measure its performance at various amplitudes, loads, and temperatures. HTLA endurance testing at 200 degrees C is currently underway. C1 [Metscher, Jonathan; Geng, Steven] NASA, Glenn Res Ctr, Thermal Energy Convers Branch, 21000 Brookpk Rd, Cleveland, OH 44135 USA. RP Metscher, J (reprint author), NASA, Glenn Res Ctr, Thermal Energy Convers Branch, 21000 Brookpk Rd, Cleveland, OH 44135 USA. NR 7 TC 0 Z9 0 U1 0 U2 0 PU AMER INST AERONAUTICS & ASTRONAUTICS PI RESTON PA 1801 ALEXANDER BELL DR, STE 500, RESTON, VA 20191-4344 USA SN 1947-7805 BN 978-1-62410-407-7 J9 INT ENERGY CONVERS PY 2016 PG 9 WC Engineering, Aerospace SC Engineering GA BG4CX UT WOS:000388660400061 ER PT S AU Myers, MG Wolford, DS Prokop, NF Krasowski, MJ Piszczor, MF McNatt, JS AF Myers, Matthew G. Wolford, David S. Prokop, Norman F. Krasowski, Michael J. Piszczor, Michael F. McNatt, Jeremiah S. GP AMER INST AERONAUT & ASTRONAUT TI Further Analyses of the NASA Glenn Research Center Solar Cell and Photovoltaic Materials Experiment onboard the International Space Station SO 14TH INTERNATIONAL ENERGY CONVERSION ENGINEERING CONFERENCE SE International Energy Conversion Engineering Conference LA English DT Proceedings Paper CT 14th International Energy Conversion Engineering Conference CY JUL 25-27, 2016 CL Salt Lake City, UT AB The NASA Glenn Research Center (GRC) has flown a solar cell characterization experiment onboard the International Space Station (ISS). The experiment was integrated into NASA Goddard Space Flight Center's (GSFC) Robotic Refueling Mission's (RRM) Task Board 4 (TB4). During the experiment's eight month deployment on the exterior of the station, several advanced photovoltaic (PV) devices were measured by the onboard PV measurement system. The experiment, which provided its own power and internal data storage, included several new cell technologies including four-junction (4J) Inverted Metamorphic Multi-junction (IMM) cells. C1 [Myers, Matthew G.; Wolford, David S.; Piszczor, Michael F.; McNatt, Jeremiah S.] NASA, Glenn Res Ctr, PV Electrochem Syst, 21000 Brookpk MS 302-1, Cleveland, OH 44135 USA. [Prokop, Norman F.; Krasowski, Michael J.] NASA, Glenn Res Ctr, Instrumentat, 21000 Brookpk MS 77-1, Cleveland, OH 44135 USA. RP Myers, MG (reprint author), NASA, Glenn Res Ctr, PV Electrochem Syst, 21000 Brookpk MS 302-1, Cleveland, OH 44135 USA. NR 3 TC 0 Z9 0 U1 0 U2 0 PU AMER INST AERONAUTICS & ASTRONAUTICS PI RESTON PA 1801 ALEXANDER BELL DR, STE 500, RESTON, VA 20191-4344 USA SN 1947-7805 BN 978-1-62410-407-7 J9 INT ENERGY CONVERS PY 2016 PG 4 WC Engineering, Aerospace SC Engineering GA BG4CX UT WOS:000388660400050 ER PT S AU Sadey, DJ Taylor, LM Beach, RF AF Sadey, David J. Taylor, Linda M. Beach, Raymond F. GP AMER INST AERONAUT & ASTRONAUT TI Proposal and Development of a High Voltage Variable Frequency Alternating Current Power System for Hybrid Electric Aircraft SO 14TH INTERNATIONAL ENERGY CONVERSION ENGINEERING CONFERENCE SE International Energy Conversion Engineering Conference LA English DT Proceedings Paper CT 14th International Energy Conversion Engineering Conference CY JUL 25-27, 2016 CL Salt Lake City, UT AB The development of ultra-efficient commercial vehicles and the transition to low-carbon emission propulsion are seen as strategic thrust paths within NASA Aeronautics. A critical enabler to these paths comes in the form of hybrid electric propulsion systems. For megawatt-class systems, the best power system topology for these hybrid electric propulsion systems is debatable. Current proposals within NASA and the Aero community suggest using a combination of alternating current (AC) and direct current (DC) for power generation, transmission, and distribution. This paper proposes an alternative to the current thought model through the use of a primarily high voltage AC power system, supported by the Convergent Aeronautics Solutions (CAS) Project. This system relies heavily on the use of doubly-fed induction machines (DFIMs), which provide high power densities, minimal power conversion, and variable speed operation. The paper presents background on the activity along with the system architecture, development status, and preliminary results. C1 [Sadey, David J.; Taylor, Linda M.; Beach, Raymond F.] NASA, Glenn Res Ctr, Power Syst Div, 21000 Brookpk Rd 301-5, Cleveland, OH 44135 USA. RP Sadey, DJ (reprint author), NASA, Glenn Res Ctr, Power Syst Div, 21000 Brookpk Rd 301-5, Cleveland, OH 44135 USA. NR 7 TC 0 Z9 0 U1 1 U2 1 PU AMER INST AERONAUTICS & ASTRONAUTICS PI RESTON PA 1801 ALEXANDER BELL DR, STE 500, RESTON, VA 20191-4344 USA SN 1947-7805 BN 978-1-62410-407-7 J9 INT ENERGY CONVERS PY 2016 PG 10 WC Engineering, Aerospace SC Engineering GA BG4CX UT WOS:000388660400048 ER PT S AU Smith, KL Li, BCY Firdosy, S Sujittosakul, S Errico, M Nakatsukasa, G Fleurial, JP Ewell, R AF Smith, Kevin L. Li, Billy Chun-Yip Firdosy, Samad Sujittosakul, Sutine Errico, Michael Nakatsukasa, George Fleurial, Jean-Pierre Ewell, Richard GP AMER INST AERONAUT & ASTRONAUT TI Development of Filled-Skutterudite Based Thermopile for High Temperature Sensors for Space and Terrestrial Applications SO 14TH INTERNATIONAL ENERGY CONVERSION ENGINEERING CONFERENCE SE International Energy Conversion Engineering Conference LA English DT Proceedings Paper CT 14th International Energy Conversion Engineering Conference CY JUL 25-27, 2016 CL Salt Lake City, UT AB The Thermal Energy Conversion Technologies Group at the Jet Propulsion Laboratory has been pursuing the development of thermopiles capable of higher temperature operation in support of terrestrial and space sensing applications in extreme environments. The next generation sensor technology would rely on filled skutterudite (SKD) compounds, the same materials currently being considered for use in the enhanced Multi-Mission Radioisotope Thermoelectric Generator (eMMRTG). We report on the design, development and fabrication of SKD-based prototype thermopile devices. The beginning-of-life (BOL) experimental and predicted performance of the SKD-based prototype thermopile in terms of electrical resistance, output voltage, current, power output and efficiency in the 423 to 723 K operating temperature range is reported and discussed. C1 [Smith, Kevin L.; Li, Billy Chun-Yip; Firdosy, Samad; Sujittosakul, Sutine; Errico, Michael; Nakatsukasa, George; Fleurial, Jean-Pierre; Ewell, Richard] CALTECH, Jet Prop Lab, MS 277-207,4800 Oak Grove Dr, Pasadena, CA 91107 USA. RP Smith, KL (reprint author), CALTECH, Jet Prop Lab, MS 277-207,4800 Oak Grove Dr, Pasadena, CA 91107 USA. EM Kevin.L.Smith@jpl.nasa.gov NR 4 TC 0 Z9 0 U1 1 U2 1 PU AMER INST AERONAUTICS & ASTRONAUTICS PI RESTON PA 1801 ALEXANDER BELL DR, STE 500, RESTON, VA 20191-4344 USA SN 1947-7805 BN 978-1-62410-407-7 J9 INT ENERGY CONVERS PY 2016 PG 7 WC Engineering, Aerospace SC Engineering GA BG4CX UT WOS:000388660400024 ER PT S AU Wilson, SD Metscher, JF Schifer, NA AF Wilson, Scott D. Metscher, Jonathan F. Schifer, Nicholas A. GP AMER INST AERONAUT & ASTRONAUT TI Active Vibration Reduction of the Advanced Stirling Convertor SO 14TH INTERNATIONAL ENERGY CONVERSION ENGINEERING CONFERENCE SE International Energy Conversion Engineering Conference LA English DT Proceedings Paper CT 14th International Energy Conversion Engineering Conference CY JUL 25-27, 2016 CL Salt Lake City, UT AB Stirling Radioisotope Power Systems (RPS) are being developed as an option to provide power on future space science missions where robotic spacecraft will orbit, flyby, land or rove. A Stirling Radioisotope Generator (SRG) could offer space missions a more efficient power system that uses one fourth of the nuclear fuel and decreases the thermal footprint compared to the current state of the art. The Stirling Cycle Technology Development (SCTD) Project is funded by the RPS Program to developing Stirling-based subsystems, including convertors and controller maturation efforts that have resulted in high fidelity hardware like the Advanced Stirling Radioisotope Generator (ASRG), Advanced Stirling Convertor (ASC), and ASC Controller Unit (ACU). The SCTD Project also performs research to develop less mature technologies with a wide variety of objectives, including increasing temperature capability to enable new environments, improving system reliability or fault tolerance, reducing mass or size, and developing advanced concepts that are mission enabling. Active vibration reduction systems (AVRS), or "balancers", have historically been developed and characterized to provide fault tolerance for generator designs that incorporate dual-opposed Stirling convertors or enable single convertor, or small RPS, missions. Balancers reduce the dynamic disturbance forces created by the power piston and displacer internal moving components of a single operating convertor to meet spacecraft requirements for induced disturbance force. To improve fault tolerance for dual-opposed configurations and enable single convertor configurations, a breadboard AVRS was implemented on the Advanced Stirling Convertor (ASC). The AVRS included a linear motor, a motor mount, and a closed-loop controller able to balance out the transmitted peak dynamic disturbance using acceleration feedback. Test objectives included quantifying power and mass penalty and reduction in transmitted force over a range of ASC operating parameters and mounting conditions. All tests were performed at three different piston amplitudes, 3.0 mm, 3.75 mm, and 4.5 mm. Overall, the transmitted force was reduced to 2% of the total unbalanced force by actively balancing out only the first fundamental frequency, with balancer motor power remaining under one watt. The test results will be used to guide future balancer designs. C1 [Wilson, Scott D.; Metscher, Jonathan F.; Schifer, Nicholas A.] NASA, Glenn Res Ctr, Thermal Energy Convers Branch, 21000 Brookpk Rd,Mail Stop 301-2, Cleveland, OH 44135 USA. RP Wilson, SD (reprint author), NASA, Glenn Res Ctr, Thermal Energy Convers Branch, 21000 Brookpk Rd,Mail Stop 301-2, Cleveland, OH 44135 USA. NR 6 TC 0 Z9 0 U1 0 U2 0 PU AMER INST AERONAUTICS & ASTRONAUTICS PI RESTON PA 1801 ALEXANDER BELL DR, STE 500, RESTON, VA 20191-4344 USA SN 1947-7805 BN 978-1-62410-407-7 J9 INT ENERGY CONVERS PY 2016 PG 10 WC Engineering, Aerospace SC Engineering GA BG4CX UT WOS:000388660400062 ER PT S AU Wilson, SD Nowlin, BC Dobbs, MW Schmitz, P Huth, J AF Wilson, Scott D. Nowlin, Brentley C. Dobbs, Michael W. Schmitz, Paul Huth, James GP AMER INST AERONAUT & ASTRONAUT TI Maturing Technologies for Stirling Space Power Generation SO 14TH INTERNATIONAL ENERGY CONVERSION ENGINEERING CONFERENCE SE International Energy Conversion Engineering Conference LA English DT Proceedings Paper CT 14th International Energy Conversion Engineering Conference CY JUL 25-27, 2016 CL Salt Lake City, UT AB Stirling Radioisotope Power Systems (RPS) are being developed as an option to provide power on future space science missions where robotic spacecraft will orbit, flyby, land or rove. A Stirling Radioisotope Generator (SRG) could offer space missions a more efficient power system that uses one fourth of the nuclear fuel and decreases the thermal footprint of the current state of the art. The RPS Program Office, working in collaboration with the U.S. Department of Energy (DOE), manages projects to develop thermoelectric and dynamic power systems, including Stirling Radioisotope Generators (SRGs). The Stirling Cycle Technology Development (SCTD) Project, located at Glenn Research Center (GRC), is developing Stirling-based subsystems, including convertors and controllers. The SCTD Project also performs research that focuses on a wide variety of objectives, including increasing convertor temperature capability to enable new environments, improving system reliability or fault tolerance, reducing mass or size, and developing advanced concepts that are mission enabling. Research activity includes maturing subsystems, assemblies, and components to prepare them for infusion into future convertor and generator designs. The status of several technology development efforts are described here. As part of the maturation process, technologies are assessed for readiness in higher-level subsystems. To assess the readiness level of the Dual Convertor Controller (DCC), a Technology Readiness Assessment (TRA) was performed and the process and results are shown. Stirling technology research is being performed by the SCTD Project for NASA's RPS Program Office, where tasks focus on maturation of Stirling-based systems and subsystems for future space science missions. C1 [Wilson, Scott D.] NASA, Glenn Res Ctr, Thermal Energy Convers Branch, 21000 Brookpk Rd,Mail Stop 301-2, Cleveland, OH 44135 USA. [Nowlin, Brentley C.] NASA, Avion Branch, 21000 Brookpk Rd,Mail Stop 301-2, Cleveland, OH 44135 USA. [Dobbs, Michael W.] Vantage Partners LLC, 3000 Aerosp Pkwy, Brookpark, OH 44142 USA. [Schmitz, Paul] Power Comp Solut Inc, 468 Newport Ct, Avon Lake, OH 44012 USA. [Huth, James] Converter Source LLC, 16922 S Canaan Rd, Athens, OH 45701 USA. RP Wilson, SD (reprint author), NASA, Glenn Res Ctr, Thermal Energy Convers Branch, 21000 Brookpk Rd,Mail Stop 301-2, Cleveland, OH 44135 USA. NR 17 TC 0 Z9 0 U1 0 U2 0 PU AMER INST AERONAUTICS & ASTRONAUTICS PI RESTON PA 1801 ALEXANDER BELL DR, STE 500, RESTON, VA 20191-4344 USA SN 1947-7805 BN 978-1-62410-407-7 J9 INT ENERGY CONVERS PY 2016 PG 10 WC Engineering, Aerospace SC Engineering GA BG4CX UT WOS:000388660400064 ER PT B AU Gong, XB Lydon, J Cooper, K Chou, K AF Gong, Xibing Lydon, James Cooper, Kenneth Chou, Kevin BE Srivatsan, TS Sudarshan, TS TI Powder and Part Characterizations in Electron Beam Melting Additive Manufacturing SO ADDITIVE MANUFACTURING: INNOVATIONS, ADVANCES, AND APPLICATIONS LA English DT Article; Book Chapter ID MECHANICAL-PROPERTIES; MELTED TI-6AL-4V; TITANIUM-ALLOYS; MICROSTRUCTURE; COMPONENTS; TEXTURE; EVOLUTION; BEHAVIOR; TI6AL4V; SIZE AB Ti-6Al-4V powder and parts from the electron beam melting (EBM) additive manufacturing (AM) process have been characterized. In the EBM AM process, preheating is applied and serves to aggregate the precursor powder and may affect the subsequent melting stage. Specimens with preheated Ti-6Al-4V powder enclosed and solid parts were fabricated and prepared for microstructural and morphological examinations. In addition, micro-CT scan analysis was conducted to study the powder porosity and powder size distributions. Moreover, the process parameters in EBM AM were investigated in build part microstructures. The results can be summarized as follows. Preheating results in metallurgical bonds or even partial melting of the powder and neck formations are clearly evident. Micro-CT scans show a porosity of 50% for the preheated powder in EBM AM. The microstructure of the Ti-6Al-4V build parts is characterized by a columnar structure of prior beta phase along the build direction, and fine Widmanstatten structures and martensites are presented inside of the prior beta. Uneven microstructures are noted along the build height; the top layers show finer microstructure while the bottom layers display a high percentage of alpha'. Both the prior beta grain size and alpha-lath thickness decrease with an increase of the scanning speed. C1 [Gong, Xibing; Chou, Kevin] Univ Alabama, Dept Mech Engn, Tuscaloosa, AL 35487 USA. [Lydon, James; Cooper, Kenneth] Marshall Space Flight Ctr, Addit Mfg Lab, Huntsville, AL USA. RP Gong, XB (reprint author), Univ Alabama, Dept Mech Engn, Tuscaloosa, AL 35487 USA. NR 57 TC 0 Z9 0 U1 0 U2 0 PU CRC PRESS-TAYLOR & FRANCIS GROUP PI BOCA RATON PA 6000 BROKEN SOUND PARKWAY NW, STE 300, BOCA RATON, FL 33487-2742 USA BN 978-1-4987-1478-5; 978-1-4987-1477-8 PY 2016 BP 179 EP 197 PG 19 WC Engineering, Manufacturing SC Engineering GA BG0JA UT WOS:000386261100008 ER PT S AU Khazanov, GV Himwich, EW Glocer, A Sibeck, DG AF Khazanov, George V. Himwich, Elizabeth W. Glocer, Alex Sibeck, David G. BE Zhang, Y Paxton, LJ TI Role of Multiple Atmospheric Reflections in Formation of Electron Distribution Function in the Diffuse Aurora Region SO AURORAL DYNAMICS AND SPACE WEATHER SE Geophysical Monograph Book Series LA English DT Article; Book Chapter ID SUPERTHERMAL ELECTRONS; TRANSPORT-EQUATION; IONOSPHERE; EMISSIONS; MODEL; PRECIPITATION; MAGNETOSPHERE; PLASMASPHERE; DEGRADATION; IONIZATION AB The precipitation of high-energy magnetospheric electrons (E > 500-600eV) in the diffuse aurora contributes significant energy flux into Earth's ionosphere. In the diffuse aurora, precipitating electrons initially injected from the plasmasheet via wave-particle interaction processes degrade in the atmosphere toward lower energies and produce secondary electrons via impact ionization of the neutral atmosphere. These initially precipitating electrons of magnetospheric origin can be additionally reflected back into the magnetosphere by the two magnetically conjugated atmospheres, leading to a series of multiple reflections that can greatly influence the initially precipitating flux at the upper ionospheric boundary (700-800 km) and the resultant population of secondary electrons and electrons cascading toward lower energies. We present the solution of the Boltzmann-Landau kinetic equation that uniformly describes the entire electron distribution function in the diffuse aurora, including the affiliated production of secondary electrons ( E <= 600 eV) and their energy interplay in the magnetosphere and two conjugated ionospheres. This solution takes into account the role of multiple atmospheric reflections of the precipitated electrons that were initially moved into the loss cone via wave-particle interaction processes in Earth's plasmasheet. C1 [Khazanov, George V.; Glocer, Alex; Sibeck, David G.] NASA Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Himwich, Elizabeth W.] Yale Univ, New Haven, CT USA. RP Khazanov, GV (reprint author), NASA Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RI Paxton, Larry/D-1934-2015 OI Paxton, Larry/0000-0002-2597-347X NR 35 TC 0 Z9 0 U1 0 U2 0 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 0065-8448 BN 978-1-118-97873-3; 978-1-118-97870-2 J9 GEOPHYS MONOGR SER PY 2016 VL 215 BP 115 EP 130 PG 16 WC Geochemistry & Geophysics; Meteorology & Atmospheric Sciences SC Geochemistry & Geophysics; Meteorology & Atmospheric Sciences GA BF9GJ UT WOS:000385571200010 ER PT S AU Zheng, YH Rastaetter, L AF Zheng, Yihua Rastaetter, Lutz BE Zhang, Y Paxton, LJ TI Space Weather Products and Tools Used in Auroral Monitoring and Forecasting at CCMC/SWRC SO AURORAL DYNAMICS AND SPACE WEATHER SE Geophysical Monograph Book Series LA English DT Article; Book Chapter ID ELECTRON-PRECIPITATION; STATISTICAL-MODEL; ION PRECIPITATION; CONE MODEL; PROPAGATION; CMES AB Key points discussed in this chapter are (1) the importance of aurora research to scientific advances and space weather applications, (2) space weather products at CCMC that are relevant to aurora monitoring and forecasting, and (3) the need for more effort from the whole community to achieve a better and long-lead-time forecast of auroral activity. Aurora, as manifestations of solar wind-magnetosphere-ionosphere coupling that occurs in a region of space that is relatively easy to access for sounding rockets, satellites, and other types of observational platforms, serves as a natural laboratory for studying the underlying physics of the complex system. From a space weather application perspective, auroras can cause surface charging of technological assets passing through the region, result in scintillation effects affecting communication and navigation, and cause radar cluttering that hinders military and civilian applications. Indirectly, an aurora and its currents can induce geomagnetically induced currents (GIC) on the ground, which poses major concerns for the wellbeing and operation of power grids, particularly during periods of intense geomagnetic activity. In addition, accurate auroral forecasting is desired for auroral tourism. In this chapter, we first review some of the existing auroral models and discuss past validation efforts. Such efforts are crucial in transitioning a model(s) from research to operations and for further model improvement and development that also benefits scientific endeavors. Then we will focus on products and tools that are used for auroral monitoring and forecasting at the Space Weather Research Center (SWRC). As part of the CCMC (Community Coordinated Modeling Center), SWRC has been providing space weather services since 2010. C1 [Zheng, Yihua; Rastaetter, Lutz] NASA Goddard Space Flight Ctr, Space Weather Lab, Heliophys Sci Div, Greenbelt, MD 20771 USA. RP Zheng, YH (reprint author), NASA Goddard Space Flight Ctr, Space Weather Lab, Heliophys Sci Div, Greenbelt, MD 20771 USA. RI Paxton, Larry/D-1934-2015 OI Paxton, Larry/0000-0002-2597-347X NR 44 TC 0 Z9 0 U1 0 U2 0 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 0065-8448 BN 978-1-118-97873-3; 978-1-118-97870-2 J9 GEOPHYS MONOGR SER PY 2016 VL 215 BP 291 EP 301 PG 11 WC Geochemistry & Geophysics; Meteorology & Atmospheric Sciences SC Geochemistry & Geophysics; Meteorology & Atmospheric Sciences GA BF9GJ UT WOS:000385571200020 ER PT B AU Tucker, CJ AF Tucker, Compton J. BE Thenkabail, PS TI Foreword: Satellite Remote Sensing Beyond 2015 SO LAND RESOURCES MONITORING, MODELING, AND MAPPING WITH REMOTE SENSING SE Remote Sensing Handbook LA English DT Editorial Material; Book Chapter C1 [Tucker, Compton J.] NASA, Div Earth Sci, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Tucker, CJ (reprint author), NASA, Div Earth Sci, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. NR 7 TC 0 Z9 0 U1 1 U2 1 PU CRC PRESS-TAYLOR & FRANCIS GROUP PI BOCA RATON PA 6000 BROKEN SOUND PARKWAY NW, STE 300, BOCA RATON, FL 33487-2742 USA BN 978-1-4822-1798-8; 978-1-4822-1795-7 J9 REMOTE SENS HBK PY 2016 VL 2 BP XI EP XV PG 5 WC Geosciences, Multidisciplinary; Remote Sensing SC Geology; Remote Sensing GA BG0JP UT WOS:000386278600001 ER PT B AU Teluguntla, P Thenkabail, PS Xiong, J Gumma, MK Giri, C Milesi, C Ozdogan, M Congalton, RG Tilton, J Sankey, TT Massey, R Phalke, A Yadav, K AF Teluguntla, Pardhasaradhi Thenkabail, Prasad S. Xiong, Jun Gumma, Murali Krishna Giri, Chandra Milesi, Cristina Ozdogan, Mutlu Congalton, Russell G. Tilton, James Sankey, Temuulen Tsagaan Massey, Richard Phalke, Aparna Yadav, Kamini BE Thenkabail, PS TI Global Food Security Support Analysis Data at Nominal 1 km (GFSAD1km) Derived from Remote Sensing in Support of Food Security in the Twenty-First Century: Current Achievements and Future Possibilities SO LAND RESOURCES MONITORING, MODELING, AND MAPPING WITH REMOTE SENSING SE Remote Sensing Handbook LA English DT Article; Book Chapter ID CLASSIFICATION ALGORITHM ACCA; CENTRAL GREAT-PLAINS; USE/LAND-COVER LULC; LAND-USE CHANGE; TIME-SERIES; IRRIGATED AREAS; MODIS DATA; WATER-USE; CROPLANDS; US C1 [Teluguntla, Pardhasaradhi; Thenkabail, Prasad S.; Xiong, Jun] US Geol Survey, Flagstaff, AZ 86001 USA. [Teluguntla, Pardhasaradhi] Bay Area Environm Res Inst, Sonoma, CA 95476 USA. [Xiong, Jun; Sankey, Temuulen Tsagaan; Massey, Richard] No Arizona Univ, Sch Earth Sci & Environm Sustainabil, Flagstaff, AZ USA. [Gumma, Murali Krishna] Int Crops Res Inst Semi Arid Trop, Remote Sensing & GIS Div, Hyderabad, Andhra Pradesh, India. [Giri, Chandra] US Geol Survey, EROS Ctr, Sioux Falls, SD USA. [Milesi, Cristina] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Ozdogan, Mutlu; Phalke, Aparna] Univ Wisconsin, Dept Forest & Wildlife Ecol, Madison, WI USA. [Ozdogan, Mutlu; Phalke, Aparna] Univ Wisconsin, Nelson Inst Environm Studies, Madison, WI USA. [Congalton, Russell G.; Yadav, Kamini] Univ New Hampshire, Dept Geog, Durham, NH 03824 USA. [Tilton, James] NASA, Goddard Space Flight Ctr, Greenbelt, MD USA. RP Teluguntla, P (reprint author), US Geol Survey, Flagstaff, AZ 86001 USA.; Teluguntla, P (reprint author), Bay Area Environm Res Inst, Sonoma, CA 95476 USA. NR 76 TC 0 Z9 0 U1 0 U2 0 PU CRC PRESS-TAYLOR & FRANCIS GROUP PI BOCA RATON PA 6000 BROKEN SOUND PARKWAY NW, STE 300, BOCA RATON, FL 33487-2742 USA BN 978-1-4822-1798-8; 978-1-4822-1795-7 J9 REMOTE SENS HBK PY 2016 VL 2 BP 131 EP 159 PG 29 WC Geosciences, Multidisciplinary; Remote Sensing SC Geology; Remote Sensing GA BG0JP UT WOS:000386278600008 ER PT S AU Sharma, M Das, K Bilgic, M Matthews, B Nielsen, D Oza, N AF Sharma, Manali Das, Kamalika Bilgic, Mustafa Matthews, Bryan Nielsen, David Oza, Nikunj BE Berendt, B Bringmann, B Fromont, E Garriga, G Miettinen, P Tatti, N Tresp, V TI Active Learning with Rationales for Identifying Operationally Significant Anomalies in Aviation SO MACHINE LEARNING AND KNOWLEDGE DISCOVERY IN DATABASES, ECML PKDD 2016, PT III SE Lecture Notes in Artificial Intelligence LA English DT Proceedings Paper CT European Conference on Machine Learning and Principles and Practice of Knowledge Discovery in Databases (ECMLPKDD) CY SEP 19-23, 2016 CL Riva del Garda, ITALY SP Google, IBM, Deloitte, Siemens, Unicredit, Zalando, UNITN, UNIFI, ISTI CNR, ICAR CNR AB A major focus of the commercial aviation community is discovery of unknown safety events in flight operations data. Data-driven unsupervised anomaly detection methods are better at capturing unknown safety events compared to rule-based methods which only look for known violations. However, not all statistical anomalies that are discovered by these unsupervised anomaly detection methods are operationally significant (e.g., represent a safety concern). Subject Matter Experts (SMEs) have to spend significant time reviewing these statistical anomalies individually to identify a few operationally significant ones. In this paper we propose an active learning algorithm that incorporates SME feedback in the form of rationales to build a classifier that can distinguish between uninteresting and operationally significant anomalies. Experimental evaluation on real aviation data shows that our approach improves detection of operationally significant events by as much as 75% compared to the state-of-the-art. The learnt classifier also generalizes well to additional validation data sets. C1 [Sharma, Manali; Bilgic, Mustafa] IIT, Chicago, IL 60616 USA. [Das, Kamalika] UARC, NASA Ames, Moffett Field, CA USA. [Matthews, Bryan] SGT Inc, NASA Ames, Moffett Field, CA USA. [Nielsen, David] MORi Associates, NASA Ames, Moffett Field, CA USA. [Oza, Nikunj] NASA Ames, Moffett Field, CA USA. RP Sharma, M (reprint author), IIT, Chicago, IL 60616 USA. EM msharm11@hawk.iit.edu; kamalika.das@nasa.gov; mbilgic@iit.edu; bryan.l.matthews@nasa.gov; david.l.nielsen@nasa.gov; nikunj.c.oza@nasa.gov NR 18 TC 0 Z9 0 U1 0 U2 0 PU SPRINGER-VERLAG BERLIN PI BERLIN PA HEIDELBERGER PLATZ 3, D-14197 BERLIN, GERMANY SN 0302-9743 BN 978-3-319-46131-1; 978-3-319-46130-4 J9 LECT NOTES ARTIF INT PY 2016 VL 9853 BP 209 EP 225 DI 10.1007/978-3-319-46131-1_25 PG 17 WC Computer Science, Artificial Intelligence; Computer Science, Information Systems SC Computer Science GA BG3ZQ UT WOS:000388437000025 ER PT S AU Abdollahi, A Pattipati, KR Kodali, A Singh, S Zhang, SG Luh, PB AF Abdollahi, Ali Pattipati, Krishna R. Kodali, Anuradha Singh, Satnam Zhang, Shigang Luh, Peter B. BE Fiondella, L Puliafito, A TI Probabilistic Graphical Models for Fault Diagnosis in Complex Systems SO PRINCIPLES OF PERFORMANCE AND RELIABILITY MODELING AND EVALUATION: ESSAYS IN HONOR OF KISHOR TRIVEDI ON HIS 70TH BIRTHDAY SE Springer Series in Reliability Engineering LA English DT Article; Book Chapter ID SET-COVERING PROBLEMS; TEST SEQUENCING ALGORITHMS; DISCRETE-EVENT SYSTEMS; HIDDEN MARKOV-MODELS; FAILURE-DETECTION; DYNAMIC-SYSTEMS; QUALITATIVE SIMULATION; ANALYTICAL REDUNDANCY; TECHNICAL PROCESSES; QUANTITATIVE MODEL AB In this chapter, we discuss the problem of fault diagnosis for complex systems in two different contexts: static and dynamic probabilistic graphical models of systems. The fault diagnosis problem is represented using a tripartite probabilistic graphical model. The first layer of this tripartite graph is composed of components of the system, which are the potential sources of failures. The condition of each component is represented by a binary state variable which is zero if the component is healthy and one otherwise. The second layer is composed of tests with binary outcomes (pass or fail) and the third layer is the noisy observations associated with the test outcomes. The cause-effect relations between the states of components and the observed test outcomes can be compactly modeled in terms of detection and false alarm probabilities. For a failure source and an observed test outcome, the probability of fault detection is defined as the probability that the observed test outcome is a fail given that the component is faulty, and the probability of false alarm is defined as the probability that the observed test outcome is a fail given that the component is healthy. When the probability of fault detection is one and the probability of false alarm is zero, the test is termed perfect; otherwise, it is deemed imperfect. In static models, the diagnosis problem is formulated as one of maximizing the posterior probability of component states given the observed fail or pass outcomes of tests. Since the solution to this problem is known to be NP-hard, to find near-optimal diagnostic solutions, we use a Lagrangian (dual) relaxation technique, which has the desirable property of providing a measure of suboptimality in terms of the approximate duality gap. Indeed, the solution would be optimal if the approximate duality gap is zero. The static problem is discussed in detail and some interesting properties, such as the reduction of the problem to a set covering problem in the case of perfect tests, are discussed. We also visualize the dual function graphically and introduce some insights into the static fault diagnosis problem. In the context of dynamic probabilistic graphical models, it is assumed that the states of components evolve as independent Markov chains and that, at each time epoch, we have access to some of the observed test outcomes. Given the observed test outcomes at different time epochs, the goal is to determine the most likely evolution of the states of components over time. The application of dual relaxation techniques results in significant reduction in the computational burden as it transforms the original coupled problem into separable subproblems, one for each component, which are solved using a Viterbi decoding algorithm. The problems, as stated above, can be regarded as passive monitoring, which relies on synchronous or asynchronous availability of sensor results to infer the most likely state evolution of component states. When information is sequentially acquired to isolate the faults in minimum time, cost, or other economic factors, the problem of fault diagnosis can be viewed as active probing (also termed sequential testing or troubleshooting). We discuss the solution of active probing problems using the information heuristic and rollout strategies of dynamic programming. The practical applications of passive monitoring and active probing to fault diagnosis problems in automotive, aerospace, power, and medical systems are briefly mentioned. C1 [Abdollahi, Ali; Pattipati, Krishna R.; Singh, Satnam; Zhang, Shigang; Luh, Peter B.] Univ Connecticut, Dept Elect & Comp Engn, 371 Fairfield Way,U-4157, Storrs, CT 06269 USA. [Kodali, Anuradha] Univ Calif Santa Cruz, NASA Ames Res Ctr, Mail Stop 269-1, Moffett Field, CA 94035 USA. RP Abdollahi, A (reprint author), Univ Connecticut, Dept Elect & Comp Engn, 371 Fairfield Way,U-4157, Storrs, CT 06269 USA. EM ali.abdollahi@uconn.edu; krishna@engr.uconn.edu; anuradha.kodali@nasa.gov; satnam74@yahoo.com; shigang391@foxmail.com; peter.luh@uconn.edu NR 134 TC 1 Z9 1 U1 2 U2 2 PU SPRINGER PI NEW YORK PA 233 SPRING STREET, NEW YORK, NY 10013, UNITED STATES SN 1614-7839 BN 978-3-319-30599-8; 978-3-319-30597-4 J9 SPRINGER SER RELIAB PY 2016 BP 109 EP 139 DI 10.1007/978-3-319-30599-8_5 D2 10.1007/978-3-319-30599-8 PG 31 WC Engineering, Industrial; Operations Research & Management Science SC Engineering; Operations Research & Management Science GA BG1HP UT WOS:000386786000006 ER PT S AU Agarwal, N Sova, S Singh, NB Arnold, B Choa, FS Cullum, B Su, CH AF Agarwal, Neelesh Sova, Stacey Singh, N. B. Arnold, Brad Choa, Fow-Sen Cullum, Brian Su, Ching-Hua BE Cullum, BM Kiehl, D McLamore, ES TI Effect of pH on the morphology of kidney stones SO SMART BIOMEDICAL AND PHYSIOLOGICAL SENSOR TECHNOLOGY XIII SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Smart Biomedical and Physiological Sensor Technology XIII CY APR 18-19, 2016 CL Baltimore, MD SP SPIE DE Crystal; Growth; pH; Needles; Prism; Kidney; Stones; Crystallization; Coarsening ID CRYSTALS; GROWTH AB The process for the formation of kidney stone is very complex phenomena and has some similarity to the crystal growth from a solution. It is very much dependent on the acidity pH of the fluids. This pH variation affects the content and amount of filtering residue and its morphology. In this study we have performed experiments using carbonate, oxides and urea to simulate and understand the morphologies of the residue filtered and coarsened in different conditions. We observed that different of morphologies of kidney stones can be explained on the basis of acidity and hydration conditions. At lower pH fat prism crystals are observed and as pH increases, long fat needle crystals with large aspect ratio are observed. The coarsening experiments showed further growth of crystals. The remelting experiments showed that during dissolution of kidney stones the joining material breaks first leaving the large faceted crystals undissolved when attempts are made to dissolve into small crystallites. However, the morphology did not change. It was also observed that impurities such as magnesium oxide (MgO) affect the morphology significantly. C1 [Agarwal, Neelesh; Sova, Stacey; Singh, N. B.; Arnold, Brad; Choa, Fow-Sen; Cullum, Brian] Univ Maryland Baltimore Cty, 1000 Hilltop Circle, Baltimore, MD 21043 USA. [Su, Ching-Hua] NASA, EM31, Marshall Space Flight Ctr, Huntsville, AL 35812 USA. RP Singh, NB (reprint author), Univ Maryland Baltimore Cty, 1000 Hilltop Circle, Baltimore, MD 21043 USA. EM singna@umbc.edu NR 3 TC 0 Z9 0 U1 1 U2 1 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0104-8 J9 PROC SPIE PY 2016 VL 9863 AR UNSP 986303 DI 10.1117/12.2219939 PG 8 WC Engineering, Biomedical; Engineering, Electrical & Electronic; Optics SC Engineering; Optics GA BG2WU UT WOS:000387732700001 ER PT S AU Singh, NB Coriell, SR Su, CH Hopkins, RH Arnold, B Choa, FS Cullum, B AF Singh, N. B. Coriell, S. R. Su, Ching Hua Hopkins, R. H. Arnold, B. Choa, Fow-Sen Cullum, Brian BE Cullum, BM Kiehl, D McLamore, ES TI Growth mechanism of nanowires: Binary and ternary chalcogenides SO SMART BIOMEDICAL AND PHYSIOLOGICAL SENSOR TECHNOLOGY XIII SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Smart Biomedical and Physiological Sensor Technology XIII CY APR 18-19, 2016 CL Baltimore, MD SP SPIE DE Nanowire; melt; chalcogenides; growth; thallium arsenic selenide; lead selenide; morphology AB Semiconductor nanowires exhibit very exciting optical and electrical properties including high transparency and a several order of magnitude better photocurrent than thin film and bulk materials. We present here the mechanism of nanowire growth from the melt-liquid-vapor medium. We describe preliminary results of binary and ternary selenide materials in light of recent theories. Experiments were performed with lead selenide and thallium arsenic selenide systems which are multifunctional material and have been used for detectors, acousto-optical, nonlinear and radiation detection applications. We observed that small units of nanocubes and elongated nanoparticles arrange and rearrange at moderate melt undercooling to form the building block of a nanowire. Since we avoided the catalyst, we observed self-nucleation and uncontrolled growth of wires from different places. Growth of lead selenide nanowires was performed by physical vapor transport method and thallium arsenic selenide nanowire by vapor-liquid-solid (VLS) method. In some cases very long wires (> mm) are formed. To achieve this goal experiments were performed to create situation where nanowires grew on the surface of solid thallium arsenic selenide itself. C1 [Singh, N. B.; Coriell, S. R.; Arnold, B.; Choa, Fow-Sen; Cullum, Brian] Univ Maryland Baltimore Cty, 1000 Hilltop Circle, Baltimore, MD 21250 USA. [Su, Ching Hua] NASA, EM31, Marshall Space Flight Ctr, Huntsville, AL 35812 USA. [Hopkins, R. H.] Hopkins Inc, Export, PA 15632 USA. RP Singh, NB (reprint author), Univ Maryland Baltimore Cty, 1000 Hilltop Circle, Baltimore, MD 21250 USA. NR 7 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0104-8 J9 PROC SPIE PY 2016 VL 9863 AR UNSP 986304 DI 10.1117/12.2220154 PG 7 WC Engineering, Biomedical; Engineering, Electrical & Electronic; Optics SC Engineering; Optics GA BG2WU UT WOS:000387732700002 ER PT J AU Miller, BJ AF Miller, Brien J. BE Harrigan, P Kirschenbaum, MG TI THE APPLICATION OF STATISTICAL AND FORENSICS VALIDATION TO SIMULATION MODELING IN WARGAMES SO ZONES OF CONTROL: PERSPECTIVES ON WARGAMING SE Game Histories LA English DT Article; Book Chapter C1 [Miller, Brien J.] FAA, Real Time & Simulat Syst, Washington, DC 20591 USA. [Miller, Brien J.] NASA, Real Time & Simulat Syst, Washington, DC 20546 USA. [Miller, Brien J.] US Navy, Real Time & Simulat Syst, Washington, DC USA. RP Miller, BJ (reprint author), FAA, Real Time & Simulat Syst, Washington, DC 20591 USA.; Miller, BJ (reprint author), NASA, Real Time & Simulat Syst, Washington, DC 20546 USA.; Miller, BJ (reprint author), US Navy, Real Time & Simulat Syst, Washington, DC USA. NR 0 TC 0 Z9 0 U1 0 U2 0 PU MIT PRESS PI CAMBRIDGE PA FIVE CAMBRIDGE CENTER, CAMBRIDGE, MA 02142 USA BN 978-0-262-03399-2 J9 GAME HIST PY 2016 BP 183 EP 200 PG 18 WC Computer Science, Interdisciplinary Applications; Computer Science, Theory & Methods; Management; Operations Research & Management Science; Political Science SC Computer Science; Business & Economics; Operations Research & Management Science; Government & Law GA BG3RG UT WOS:000388166000019 ER PT S AU Osmanoglu, B Rincon, RF Lee, S Fatoyinbo, T Bollian, T AF Osmanoglu, Batuhan Rincon, Rafael F. Lee, SeungKuk Fatoyinbo, Temilola Bollian, Tobias GP VDE VERLAG GMBH TI Radio frequency interference detection and mitigation techniques using data from EcoSAR 2014 Flight Campaign SO 11TH EUROPEAN CONFERENCE ON SYNTHETIC APERTURE RADAR (EUSAR 2016) SE EUSAR Proceedings LA English DT Proceedings Paper CT 11th European Conference on Synthetic Aperture Radar (EUSAR) CY JUN 07-09, 2016 CL Hamburg, GERMANY SP ITG, VDE, AIRBUS, Fraunhofer, DLR, EUREL, URSI, DGON, IEEE GRSS, IEEE AESS, TIMES Microwave Syst, GLOBES Elektronik GMBH & CO KG AB Radio frequency interference (RFI) has strong influence on wide band airborne radar systems, especially operaing at L-band (1-2 GHz) or lower frequencies. EcoSAR is a P-band digital beamforming radar system, and RFI has to be removed from raw echoes to obtain science quality data. In this paper we describe the current methodology used to tackle RFI with EcoSAR, and provide an example on its performance. Finally, we discuss the advantages and disadvantages of the method and mention potential improvements. C1 [Osmanoglu, Batuhan; Rincon, Rafael F.; Fatoyinbo, Temilola] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Lee, SeungKuk; Bollian, Tobias] NASA, USRA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Osmanoglu, B (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. NR 11 TC 0 Z9 0 U1 0 U2 0 PU VDE VERLAG GMBH PI BERLIN PA BISMARCKSTRASSE 33, BERLIN, 10625, GERMANY SN 2197-4403 BN 978-3-8007-4228-8 J9 EUSAR PROC PY 2016 BP 148 EP 151 PG 4 WC Remote Sensing; Imaging Science & Photographic Technology SC Remote Sensing; Imaging Science & Photographic Technology GA BG3MH UT WOS:000388020600035 ER PT S AU Sainath, K Hensley, S AF Sainath, Kamalesh Hensley, Scott GP VDE VERLAG GMBH TI Analysis of Polarimetric-Dependent InSAR Coherence Modulation Arising from Deep Electromagnetic Ground Penetration SO 11TH EUROPEAN CONFERENCE ON SYNTHETIC APERTURE RADAR (EUSAR 2016) SE EUSAR Proceedings LA English DT Proceedings Paper CT 11th European Conference on Synthetic Aperture Radar (EUSAR) CY JUN 07-09, 2016 CL Hamburg, GERMANY SP ITG, VDE, AIRBUS, Fraunhofer, DLR, EUREL, URSI, DGON, IEEE GRSS, IEEE AESS, TIMES Microwave Syst, GLOBES Elektronik GMBH & CO KG ID INTERFEROMETRY; DECORRELATION AB We examine cross-pol InSAR "volumetric" coherence behavior due to multiple-scatter, and the induced multiplicity of "similar", reciprocal backscatter mechanisms. Our results are as follows. First, the cross-pol volumetric coherence's unwrapped phase grows identically to co-pol volumetric coherence unwrapped phase in the strong subsurface wave guidance regime. Second, unlike co-pol volumetric correlation's inverse proportionality to InSAR baseline in this regime, said multiplicity can cause cross-pol volumetric correlation to degrade faster (inverse quadratic) versus baseline. Summarizing, the cross-pol and co-pol volumetric coherences can exhibit very different sensitivities to subsurface scatter, encouraging their combined exploitation for remote sensing of layered, penetrable media. C1 [Sainath, Kamalesh] Ohio State Univ, ElectroSci Lab, Columbus, OH 43210 USA. [Hensley, Scott] NASA, Jet Prop Lab, Pasadena, CA USA. RP Sainath, K (reprint author), Ohio State Univ, ElectroSci Lab, Columbus, OH 43210 USA. EM sainath.1@osu.edu; scott.hensley@jpl.nasa.gov NR 17 TC 0 Z9 0 U1 0 U2 0 PU VDE VERLAG GMBH PI BERLIN PA BISMARCKSTRASSE 33, BERLIN, 10625, GERMANY SN 2197-4403 BN 978-3-8007-4228-8 J9 EUSAR PROC PY 2016 BP 230 EP 234 PG 5 WC Remote Sensing; Imaging Science & Photographic Technology SC Remote Sensing; Imaging Science & Photographic Technology GA BG3MH UT WOS:000388020600053 ER PT S AU Brigot, G Koeniguer, E Simard, M Dupuis, X AF Brigot, Guillaume Koeniguer, Elise Simard, Marc Dupuis, Xavier GP VDE VERLAG GMBH TI Fusion of LIDAR and POLINSAR images for forest vertical structure retrieval SO 11TH EUROPEAN CONFERENCE ON SYNTHETIC APERTURE RADAR (EUSAR 2016) SE EUSAR Proceedings LA English DT Proceedings Paper CT 11th European Conference on Synthetic Aperture Radar (EUSAR) CY JUN 07-09, 2016 CL Hamburg, GERMANY SP ITG, VDE, AIRBUS, Fraunhofer, DLR, EUREL, URSI, DGON, IEEE GRSS, IEEE AESS, TIMES Microwave Syst, GLOBES Elektronik GMBH & CO KG AB This paper presents the overall strategy of fusion of LIDAR images and P-band PolInSAR images of forests in order to exploit their synergistic information. The images considered are from the 2010 BioSAR campaign on Remningstorp forest in Sweden. As a first step, we propose a pixel to pixel coregistration method of the images, and we assess the accuracy of this coregistration. Then, we propose descriptors for a given pixel, for each type of images. The primary challenge is to find features that go beyond the difference of geometrical configurations between the two types of information, and also that compensate the effect of the incidence angle on radar observables. As of today, we propose to analyse the combination of PolInSAR and lidar feature in order to see their variations depending on radar acquisition conditions and scatterer properties. We also test a support vector regression on two selected radar and lidar feature in order to draw some conclusions and improvements points. C1 [Brigot, Guillaume] Off Natl Etud & Rech Aerosp, JPL, Palaiseau, France. [Koeniguer, Elise; Dupuis, Xavier] Off Natl Etud & Rech Aerosp, Palaiseau, France. [Simard, Marc] JPL, Pasadena, CA USA. RP Brigot, G (reprint author), Off Natl Etud & Rech Aerosp, JPL, Palaiseau, France. EM guillaume.brigot@onera.fr; elise.koeniguer@onera.fr; marc.simard@jpl.nasa.gov; xavier.dupuis@onera.fr NR 11 TC 0 Z9 0 U1 2 U2 2 PU VDE VERLAG GMBH PI BERLIN PA BISMARCKSTRASSE 33, BERLIN, 10625, GERMANY SN 2197-4403 BN 978-3-8007-4228-8 J9 EUSAR PROC PY 2016 BP 558 EP 562 PG 5 WC Remote Sensing; Imaging Science & Photographic Technology SC Remote Sensing; Imaging Science & Photographic Technology GA BG3MH UT WOS:000388020600133 ER PT S AU Sainath, K Hensley, S AF Sainath, Kamalesh Hensley, Scott GP VDE VERLAG GMBH TI Numerical Modeling of Subsurface Layer Resonance-Based Interferometric SAR (InSAR) Correlation Fluctuations SO 11TH EUROPEAN CONFERENCE ON SYNTHETIC APERTURE RADAR (EUSAR 2016) SE EUSAR Proceedings LA English DT Proceedings Paper CT 11th European Conference on Synthetic Aperture Radar (EUSAR) CY JUN 07-09, 2016 CL Hamburg, GERMANY SP ITG, VDE, AIRBUS, Fraunhofer, DLR, EUREL, URSI, DGON, IEEE GRSS, IEEE AESS, TIMES Microwave Syst, GLOBES Elektronik GMBH & CO KG ID RADAR INTERFEROMETRY; DECORRELATION; PENETRATION AB We numerically explore the magnitude of the interferometric coherence (correlation) between two co-polarized SAR observations of natural scenes, examining specifically the "volumetric" correlation associated with electromagnetic ground penetration. Our scattering model quantifies the effects, on InSAR coherence, of subsurface layers guiding the incident wave via a succession of internal, specular reflections ("multi-bounce"). As the paper's first contribution, we reveal that multi-bounce engenders "interferometric" resonances that induce deep, periodic degradation (versus InSAR baseline length) of correlation. Second, the correlation's periodic variation versus InSAR spatial baseline, with period length invariant to variations in subsurface properties, allows robust multi-baseline extraction of subsurface topography. C1 [Sainath, Kamalesh] Ohio State Univ, ElectroSci Lab, Columbus, OH 43210 USA. [Hensley, Scott] NASA, Jet Prop Lab, Pasadena, CA USA. RP Sainath, K (reprint author), Ohio State Univ, ElectroSci Lab, Columbus, OH 43210 USA. EM sainath.1@osi.edu; scott.hensley@jpl.nasa.gov NR 21 TC 0 Z9 0 U1 0 U2 0 PU VDE VERLAG GMBH PI BERLIN PA BISMARCKSTRASSE 33, BERLIN, 10625, GERMANY SN 2197-4403 BN 978-3-8007-4228-8 J9 EUSAR PROC PY 2016 BP 567 EP 572 PG 6 WC Remote Sensing; Imaging Science & Photographic Technology SC Remote Sensing; Imaging Science & Photographic Technology GA BG3MH UT WOS:000388020600135 ER PT S AU Farr, TG AF Farr, Tom G. GP VDE VERLAG GMBH TI InSAR measurements of subsidence in the Central Valley, California from 2007-present SO 11TH EUROPEAN CONFERENCE ON SYNTHETIC APERTURE RADAR (EUSAR 2016) SE EUSAR Proceedings LA English DT Proceedings Paper CT 11th European Conference on Synthetic Aperture Radar (EUSAR) CY JUN 07-09, 2016 CL Hamburg, GERMANY SP ITG, VDE, AIRBUS, Fraunhofer, DLR, EUREL, URSI, DGON, IEEE GRSS, IEEE AESS, TIMES Microwave Syst, GLOBES Elektronik GMBH & CO KG ID SYNTHETIC-APERTURE RADAR; LAND SUBSIDENCE; LAS-VEGAS; INTERFEROMETRY AB Subsidence caused by groundwater pumping in the rich agricultural area of California's Central Valley has been a problem for decades. Over the last few years, interferometric synthetic aperture radar (InSAR) observations from satellite and aircraft platforms have been used to produce maps of subsidence with cm accuracy. For this study, we have obtained and analyzed Japanese PALSAR data for 2007 - 2011 and Radarsat-2 data for 2014 - 2015. We are currently processing data from the Canadian Radarsat-1 for 2011 - 2013, and ESA's Sentinel-1A for 2015 - present. As multiple scenes were acquired during these periods, we can also produce histories of subsidence at selected locations and transects showing how subsidence varies both spatially and temporally. Geographic Information System (GIS) files have been furnished to decision-makers at the California Department of Water Resources to enable better management of groundwater resources and for further analysis of the 4 dimensional subsidence time-series maps. C1 [Farr, Tom G.] CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. RP Farr, TG (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. EM tom.farr@jpl.nasa.gov NR 18 TC 0 Z9 0 U1 0 U2 0 PU VDE VERLAG GMBH PI BERLIN PA BISMARCKSTRASSE 33, BERLIN, 10625, GERMANY SN 2197-4403 BN 978-3-8007-4228-8 J9 EUSAR PROC PY 2016 BP 587 EP 589 PG 3 WC Remote Sensing; Imaging Science & Photographic Technology SC Remote Sensing; Imaging Science & Photographic Technology GA BG3MH UT WOS:000388020600139 ER PT S AU Hensley, S Mitchell, K Nunes, D Shaffer, S Deen, R Parcheta, C Rusert, M AF Hensley, Scott Mitchell, Karl Nunes, Daniel Shaffer, Scott Deen, Robert Parcheta, Carolyn Rusert, Maria GP VDE VERLAG GMBH TI Systematic Processing of High Resolution Topography of Venus from Magellan Radar Stereo Data and Science Applications SO 11TH EUROPEAN CONFERENCE ON SYNTHETIC APERTURE RADAR (EUSAR 2016) SE EUSAR Proceedings LA English DT Proceedings Paper CT 11th European Conference on Synthetic Aperture Radar (EUSAR) CY JUN 07-09, 2016 CL Hamburg, GERMANY SP ITG, VDE, AIRBUS, Fraunhofer, DLR, EUREL, URSI, DGON, IEEE GRSS, IEEE AESS, TIMES Microwave Syst, GLOBES Elektronik GMBH & CO KG AB Magellan, a NASA mission to Venus in the early 1990's, mapped nearly the entire surface of Venus with an S-band (12 cm) synthetic aperture radar and microwave radiometer and made radar altimeter measurements of the topography. These measurements revolutionized our understanding of the geomorphology, geology and geophysical processes that have shaped the evolution of the surface of Venus. However, the lack of finer resolution topography of the surface than that obtained by the Magellan mission has hampered the definitive answer to key questions concerning the processes and evolution of the surface of Venus. Cratering, surface/atmospheric interactions, volcanism and interior dynamics, to name a few, all leave their imprint on the relief of planetary surfaces in grandiose (e.g., Maxwell Montes on Venus) to subtle fashion (e.g., quasi-circular depressions on Mars). Though significant morphological work and interpretation can be done in the absence of topographic data, major assumptions and uncertainties likely remain. As part of the Magellan mission approximately 25% of the planet was mapped in radar stereo. We describe a newly NASA funded effort to systematically process all the Magellan stereo data using a rigorous stereo sensor model and automated matching routines. These results are compared to previous stereo results and some possible science applications of the stereo results are presented. C1 [Hensley, Scott; Mitchell, Karl; Nunes, Daniel; Shaffer, Scott; Deen, Robert; Parcheta, Carolyn; Rusert, Maria] CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. RP Hensley, S (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. EM scott.hensley@jpl.nasa.gov; karl.l.mitchell@jpl.nasa.gov; daniel.nunes@jpl.nasa.gov; scott.j.shaffer@jpl.nasa.gov; robert.g.deen@jpl.nasa.gov; carolyn.e.parcheta@jpl.nasa.gov; maria.d.rusert@jpl.nasa.gov NR 10 TC 0 Z9 0 U1 0 U2 0 PU VDE VERLAG GMBH PI BERLIN PA BISMARCKSTRASSE 33, BERLIN, 10625, GERMANY SN 2197-4403 BN 978-3-8007-4228-8 J9 EUSAR PROC PY 2016 BP 765 EP 768 PG 4 WC Remote Sensing; Imaging Science & Photographic Technology SC Remote Sensing; Imaging Science & Photographic Technology GA BG3MH UT WOS:000388020600180 ER PT S AU Kim, S Johnson, J Moghaddam, M Tsang, L van Zyl, J Colliander, A Dunbar, S Jackson, T Jaruwatanadilok, S West, R Berg, A Caldwell, T Cosh, M Lopez-Baeza, E Thibeault, M Walker, J Entekhabi, D Yueh, S AF Kim, S. Johnson, J. Moghaddam, M. Tsang, L. van Zyl, J. Colliander, A. Dunbar, S. Jackson, T. Jaruwatanadilok, S. West, R. Berg, A. Caldwell, T. Cosh, M. Lopez-Baeza, E. Thibeault, M. Walker, J. Entekhabi, D. Yueh, S. GP VDE VERLAG GMBH TI Global retrieval of surface soil moisture using L-band SMAP SAR data and its validation SO 11TH EUROPEAN CONFERENCE ON SYNTHETIC APERTURE RADAR (EUSAR 2016) SE EUSAR Proceedings LA English DT Proceedings Paper CT 11th European Conference on Synthetic Aperture Radar (EUSAR) CY JUN 07-09, 2016 CL Hamburg, GERMANY SP ITG, VDE, AIRBUS, Fraunhofer, DLR, EUREL, URSI, DGON, IEEE GRSS, IEEE AESS, TIMES Microwave Syst, GLOBES Elektronik GMBH & CO KG AB Surface soil moisture retrievals using radar observations have been challenging due to the strong effects by surface roughness and vegetation scattering. Physically-based forward models for radar scattering are inverted using time-series retrieval algorithm to systematically correct for the effect of the roughness and vegetation. The retrievals are performed for a top 5-cm layer soil moisture at 3-km spatial resolution using the L-band radar data acquired by the Soil Moisture Active Passive (SMAP) satellite globally every three days from mid-April to early July, 2015. These were assessed over 13 rigorously-chosen core validation sites covering a wide range of biomass types and amounts and soil conditions. The soil moisture retrieval performance had an accuracy of approaching the goal of 0.063 m(3)/m(3) unbiased-RMSE (root mean square error), a near zero bias, and a correlation of 0.56. The successful retrieval demonstrates that the physically-based retrieval method is capable of characterizing soil moisture over diverse conditions of soil moisture, surface roughness, and vegetation on a global scale. C1 [Kim, S.; van Zyl, J.; Colliander, A.; Dunbar, S.; Jaruwatanadilok, S.; West, R.; Yueh, S.] CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. [Johnson, J.] Ohio State Univ, Columbus, OH 43210 USA. [Moghaddam, M.] Univ Southern Calif, Los Angeles, CA 90089 USA. [Tsang, L.] Univ Michigan, Ann Arbor, MI 48109 USA. [Jackson, T.; Cosh, M.] USDA ARS, Hydrol & Remote Sensing Lab, Beltsville, MD USA. [Berg, A.] Univ Guelph, Guelph, ON N1G 2W1, Canada. [Caldwell, T.] Univ Texas Austin, Austin, TX 78712 USA. [Lopez-Baeza, E.] Univ Valencia, E-46003 Valencia, Spain. [Thibeault, M.] Comis Nacl Act Espaci CONAE, Caba, Argentina. [Walker, J.] Monash Univ, Clayton, Vic 3800, Australia. [Entekhabi, D.] MIT, Cambridge, MA 02139 USA. RP Kim, S (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. NR 9 TC 0 Z9 0 U1 1 U2 1 PU VDE VERLAG GMBH PI BERLIN PA BISMARCKSTRASSE 33, BERLIN, 10625, GERMANY SN 2197-4403 BN 978-3-8007-4228-8 J9 EUSAR PROC PY 2016 BP 1118 EP 1121 PG 4 WC Remote Sensing; Imaging Science & Photographic Technology SC Remote Sensing; Imaging Science & Photographic Technology GA BG3MH UT WOS:000388020600260 ER PT S AU Seu, R Smrekar, S Hensley, S Pierfnuicesco, L AF Seu, Roberto Smrekar, Suzanne Hensley, Scott Pierfnuicesco, Lombardo GP VDE VERLAG GMBH TI A SAR Interferometer Experiment to Explore the Surface of Venus SO 11TH EUROPEAN CONFERENCE ON SYNTHETIC APERTURE RADAR (EUSAR 2016) SE EUSAR Proceedings LA English DT Proceedings Paper CT 11th European Conference on Synthetic Aperture Radar (EUSAR) CY JUN 07-09, 2016 CL Hamburg, GERMANY SP ITG, VDE, AIRBUS, Fraunhofer, DLR, EUREL, URSI, DGON, IEEE GRSS, IEEE AESS, TIMES Microwave Syst, GLOBES Elektronik GMBH & CO KG AB A deep understanding of solar system evolution is limited by a great unanswered question: How Earthlike is Venus? We know that these "twin" planets formed with similar bulk composition and size. Yet Venus followed a divergent evolutionary path, losing its surface water and becoming hotter than Mercury. How did this happen? The answer has profound implications for how terrestrial planets become habitable and the potential for life in the universe. To provide an answer to these questions a proposal has been submitted to NASA in the frame of the Discovery Program, for a mission called VERITAS (Venus Emissivity, Radio science, InSAR, Topography and Spectroscopy). The VERITAS payload is formed by a Venus Interferometric Synthetic Aperture Radar (VISAR), a Venus Emissivity Mapper and a Gravity Science Investigation. Interferometric Synthetic aperture radars are well-established tools for generating topographic maps of the Earth (see among the others [1]-[2]). Two spaceborne radar interferometric mapping missions, the Shuttle Radar Topography Mission (see for example [3]) and the Tandem-X Mission (see for example [4]) have generated unprecedented measurements of the Earth's topography and informed many area of scientific investigation. Having such a comparable data set is needed to resolve the geologic evolution of the surface of Venus. Owning to the optically opaque cloud cover of Venus, radar interferometry is ideally suited to making these measurements. In this paper we provide a look at some of the system engineering and performance considerations for this instrument. C1 [Seu, Roberto; Pierfnuicesco, Lombardo] Univ Roma La Sapienza, Rome, Italy. [Smrekar, Suzanne; Hensley, Scott] Jet Prop Lab, Pasadena, CA USA. RP Seu, R (reprint author), Univ Roma La Sapienza, Rome, Italy. EM roberto.seu@uniroma1.it; suzanne.e.smrekar@jpl.nasa.gov; Scott.Hensley@jpl.nasa.gov; pierfrancesco.lombardo@uniroma1.it NR 11 TC 0 Z9 0 U1 0 U2 0 PU VDE VERLAG GMBH PI BERLIN PA BISMARCKSTRASSE 33, BERLIN, 10625, GERMANY SN 2197-4403 BN 978-3-8007-4228-8 J9 EUSAR PROC PY 2016 BP 1242 EP 1244 PG 3 WC Remote Sensing; Imaging Science & Photographic Technology SC Remote Sensing; Imaging Science & Photographic Technology GA BG3MH UT WOS:000388020600288 ER PT S AU Rincon, R Fatoyinbo, T Osmanoglu, B Lee, SK Ranson, KJ Marrero, V Yeary, M AF Rincon, Rafael Fatoyinbo, Temilola Osmanoglu, Batuhan Lee, Seung-Kuk Ranson, K. Jon Marrero, Victor Yeary, Mark GP VDE VERLAG GMBH TI DEVELOPMENT OF NASA'S NEXT GENERATION L-BAND DIGITAL BEAMFORMING SYNTHETIC APERTURE RADAR (DBSAR-2) SO 11TH EUROPEAN CONFERENCE ON SYNTHETIC APERTURE RADAR (EUSAR 2016) SE EUSAR Proceedings LA English DT Proceedings Paper CT 11th European Conference on Synthetic Aperture Radar (EUSAR) CY JUN 07-09, 2016 CL Hamburg, GERMANY SP ITG, VDE, AIRBUS, Fraunhofer, DLR, EUREL, URSI, DGON, IEEE GRSS, IEEE AESS, TIMES Microwave Syst, GLOBES Elektronik GMBH & CO KG DE Digital Beamforming; interferometry SAR; InSAR AB The Next Generation Digital Beamforming SAR (DBSAR-2) is a state-of-the- art airborne L-band radar developed at the NASA Goddard Space Flight Center (GSFC) in support of several disciplines in Earth and Planetary sciences. The instrument builds upon the architectures in NASA's DBSAR-1 and EcoSAR instruments while introducing new features that allow advanced imaging modes, higher efficiency, and compactness. DBSAR-2 employs a 16-channel radar architecture characterized by multi-mode operation, software defined waveform generation, digital beamforming, wide-band, and programmable radar parameters. The instrument was recently completed, tested and calibrated in GSFC's anechoic chamber. C1 [Rincon, Rafael; Fatoyinbo, Temilola; Osmanoglu, Batuhan; Lee, Seung-Kuk; Ranson, K. Jon; Marrero, Victor] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Osmanoglu, Batuhan] Univ Space Res Assoc, Columbia, MD USA. [Yeary, Mark] Univ Oklahoma, Norman, OK 73019 USA. RP Rincon, R (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. NR 3 TC 0 Z9 0 U1 0 U2 0 PU VDE VERLAG GMBH PI BERLIN PA BISMARCKSTRASSE 33, BERLIN, 10625, GERMANY SN 2197-4403 BN 978-3-8007-4228-8 J9 EUSAR PROC PY 2016 BP 1251 EP 1254 PG 4 WC Remote Sensing; Imaging Science & Photographic Technology SC Remote Sensing; Imaging Science & Photographic Technology GA BG3MH UT WOS:000388020600290 ER PT S AU Rincon, RF Fatoyinbo, T Osmanoglu, B Lee, S Ranson, KJ Sun, GQ Bollian, T AF Rincon, Rafael F. Fatoyinbo, Temilola Osmanoglu, Batuham Lee, Seungkuk Ranson, K. Jon Sun, Guoqing Bollian, Tobias GP VDE VERLAG GMBH TI ECOSAR: P-BAND DIGITAL BEAMFORMING POLARIMETRIC AND SINGLE PASS INTERFEROMETRIC SAR Instrument Performance SO 11TH EUROPEAN CONFERENCE ON SYNTHETIC APERTURE RADAR (EUSAR 2016) SE EUSAR Proceedings LA English DT Proceedings Paper CT 11th European Conference on Synthetic Aperture Radar (EUSAR) CY JUN 07-09, 2016 CL Hamburg, GERMANY SP ITG, VDE, AIRBUS, Fraunhofer, DLR, EUREL, URSI, DGON, IEEE GRSS, IEEE AESS, TIMES Microwave Syst, GLOBES Elektronik GMBH & CO KG DE Digital Beamforming, SAR; InSAR; Pol-InSAR; Polarimetry, P-band AB The EcoSAR beamforming synthetic aperture radar (SAR) is a state-of-the-art airborne instrument developed for the measurement of ecosystem structure and biomass. The instrument operates at a center frequency of 435 MHz (P-band) and uses a multi-channel reconfigurable radar architecture to implement fully polarimetric and "single pass" interferometric measurements of the Earth surface. The instrument conducted its first flight campaign over areas of Bahamas and Costa Rica in March 2014. During the campaign the radar operated in several experimental modes, acquiring a comprehensive data set for instrument performance analysis and science retrievals. C1 [Rincon, Rafael F.; Fatoyinbo, Temilola; Osmanoglu, Batuham; Ranson, K. Jon] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Lee, Seungkuk; Bollian, Tobias] USRA NASA GSFC, Greenbelt, MD 20771 USA. [Sun, Guoqing] UMBC NASA GSFC, Greenbelt, MD 20771 USA. RP Rincon, RF (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. EM rafael.rincon@nasa.gov; temilola.e.fatoyinbo@nasa.gov; batuhan.osmanoglu@nasa.gov; seungkuk.lee@nasa.gov; kenneth.j.ranson@nasa.gov; guoqing.sun-1@nasa.gov; tobias.bollian@nasa.gov NR 7 TC 0 Z9 0 U1 0 U2 0 PU VDE VERLAG GMBH PI BERLIN PA BISMARCKSTRASSE 33, BERLIN, 10625, GERMANY SN 2197-4403 BN 978-3-8007-4228-8 J9 EUSAR PROC PY 2016 BP 1255 EP 1259 PG 5 WC Remote Sensing; Imaging Science & Photographic Technology SC Remote Sensing; Imaging Science & Photographic Technology GA BG3MH UT WOS:000388020600291 ER PT S AU E-Martin, Y R-Moreno, MD Smith, DE AF E-Martin, Yolanda R-Moreno, Maria D. Smith, David E. BE Luaces, O Gamez, JA Barrenechea, E Troncoso, A Galar, M Quintian, H Corchado, E TI Incremental Contingency Planning for Recovering from Uncertain Outcomes SO ADVANCES IN ARTIFICIAL INTELLIGENCE, CAEPIA 2016 SE Lecture Notes in Artificial Intelligence LA English DT Proceedings Paper CT 17th Conference of the Spanish-Association-for-Artificial-Intelligence (CAEPIA) CY SEP 14-16, 2016 CL Salamanca, SPAIN SP Spanish Assoc Artificial Intelligence, BISITE, Univ Salamanca, Springer Team, AEPIA AB Incremental Contingency Planning is a framework that considers all potential failures in a plan and attempts to avoid them by incrementally adding contingency branches to the plan in order to improve the overall probability. The planner focuses its attempts on the higher probability outcomes. Precautionary planning is a form of incremental contingency planning that takes advantage of the speed of replanning for easy contingencies and only considers the unrecoverable outcomes in the plan. In this work, we present an approach to incrementally generating contingency branches to deal with uncertain outcomes. The main idea is to first generate a high probability non-branching seed plan, which is then augmented with contingency branches to handle the most critical outcomes. Any remaining outcomes are handled by runtime replanning. C1 [E-Martin, Yolanda] CSIC UPM, Ctr Automat & Robot, Madrid 28500, Spain. [R-Moreno, Maria D.] Univ Alcala De Henares, Ctra Madrid Barcelona Km 33-6, Madrid 28871, Spain. [Smith, David E.] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP E-Martin, Y (reprint author), CSIC UPM, Ctr Automat & Robot, Madrid 28500, Spain. EM yolanda.e.martin@csic.es; mdolores@aut.uah.es; david.smith@nasa.gov NR 10 TC 0 Z9 0 U1 0 U2 0 PU SPRINGER-VERLAG BERLIN PI BERLIN PA HEIDELBERGER PLATZ 3, D-14197 BERLIN, GERMANY SN 0302-9743 BN 978-3-319-44636-3; 978-3-319-44635-6 J9 LECT NOTES ARTIF INT PY 2016 VL 9868 BP 237 EP 247 DI 10.1007/978-3-319-44636-3_22 PG 11 WC Computer Science, Artificial Intelligence; Computer Science, Theory & Methods SC Computer Science GA BG2XK UT WOS:000387750600022 ER PT S AU Brooks, CB Kidder, B Grigas, M Griesmann, U Wilson, DW Muller, RE Jaffe, DT AF Brooks, Cynthia B. Kidder, Benjamin Grigas, Michelle Griesmann, Ulf Wilson, Daniel W. Muller, Richard E. Jaffe, Daniel T. BE Navarro, R Burge, JH TI Process improvements in the production of silicon immersion gratings SO ADVANCES IN OPTICAL AND MECHANICAL TECHNOLOGIES FOR TELESCOPES AND INSTRUMENTATION II SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Advances in Optical and Mechanical Technologies for Telescopes and Instrumentation II CY JUN 26-JUL 01, 2016 CL Edinburgh, UNITED KINGDOM SP SPIE DE Immersion; diffraction; gratings; infrared; spectroscopy; lithography; silicon AB We have explored a number of lithographic techniques and improvements to produce the resist lines that then define the grating groove edges of silicon immersion gratings. In addition to our lithographic process using contact printing with photomasks, which is our primary technique for the production of immersion gratings, we explored two alternative fabrication methods, direct-write electron beam and photo-lithography. We have investigated the application of antireflection (AR) coatings during our contact printing lithography method to reduce the effect of Fizeau fringes produced by the contact of the photomask on the photoresist surface. This AR coating reduces the amplitude of the periodic errors by a factor of 1.5. Electron beam (e-beam) patterning allows us to manufacture gratings that can be used in first order, with groove spacing down to 0.5 micrometer or smaller (2,000 grooves/mm), but could require significant e-beam write times of up to one week to pattern a full-sized grating. The University of Texas at Austin silicon diffractive optics group is working with Jet Propulsion Laboratory to develop an alternate e-beam method that employs chromium liftoff to reduce the write time by a factor of 10. We are working with the National Institute of Standards and Technology using laser writing to explore the possibility of creating very high quality gratings without the errors introduced during the contact-printing step. Both e-beam and laser patterning bypass the contact photolithography step and directly write the lines in photoresist on our silicon substrates, but require increased cost, time, and process complexity. C1 [Brooks, Cynthia B.; Kidder, Benjamin; Grigas, Michelle; Jaffe, Daniel T.] Univ Texas Austin, Austin, TX 78712 USA. [Griesmann, Ulf] Natl Inst Stand & Technol, Gaithersburg, MD 20899 USA. [Wilson, Daniel W.; Muller, Richard E.] CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. RP Brooks, CB (reprint author), Univ Texas Austin, Austin, TX 78712 USA. NR 7 TC 0 Z9 0 U1 1 U2 1 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0203-8; 978-1-5106-0204-5 J9 PROC SPIE PY 2016 VL 9912 AR UNSP 99123Z DI 10.1117/12.2233388 PN 1 PG 12 WC Instruments & Instrumentation; Optics SC Instruments & Instrumentation; Optics GA BG2XH UT WOS:000387747900120 ER PT S AU Galvin, M Kim, Y Kasdin, NJ Sirbu, D Vanderbei, R Echeverri, D Sagolla, G Rousing, A Balasubramanian, K Ryan, D Shaklan, S Lisman, D AF Galvin, Michael Kim, Yunjong Kasdin, N. Jeremy Sirbu, Dan Vanderbei, Robert Echeverri, Dan Sagolla, Giuseppe Rousing, Andreas Balasubramanian, Kunjithapatham Ryan, Daniel Shaklan, Stuart Lisman, Doug BE Navarro, R Burge, JH TI Design and Construction of a 76m Long-Travel Laser Enclosure for a Space Occulter Testbed SO ADVANCES IN OPTICAL AND MECHANICAL TECHNOLOGIES FOR TELESCOPES AND INSTRUMENTATION II SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Advances in Optical and Mechanical Technologies for Telescopes and Instrumentation II CY JUN 26-JUL 01, 2016 CL Edinburgh, UNITED KINGDOM SP SPIE DE occulter; starshade; testbed; enclosure; long-travel; laser; beam drift; black paint AB Princeton University is upgrading our space occulter testbed. In particular, we are lengthening it to similar to 76m to achieve flightlike Fresnel numbers. This much longer testbed required an all-new enclosure design. In this design, we prioritized modularity and the use of commercial off-the-shelf (COTS) & semi-COTS components. Several of the technical challenges encountered included an unexpected slow beam drift and black paint selection. Herein we describe the design and construction of this long-travel laser enclosure. C1 [Galvin, Michael; Kim, Yunjong; Kasdin, N. Jeremy; Vanderbei, Robert; Echeverri, Dan; Sagolla, Giuseppe; Rousing, Andreas] Princeton Univ, Princeton, NJ 08544 USA. [Sirbu, Dan] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Balasubramanian, Kunjithapatham; Ryan, Daniel; Shaklan, Stuart; Lisman, Doug] CALTECH, Jet Prop Lab, NASA, 4800 Oak Grove Dr, Pasadena, CA 91125 USA. RP Galvin, M (reprint author), Princeton Univ, Princeton, NJ 08544 USA. EM mgalvin@princeton.edu NR 5 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0203-8; 978-1-5106-0204-5 J9 PROC SPIE PY 2016 VL 9912 AR UNSP 99126N DI 10.1117/12.2231093 PN 1 PG 18 WC Instruments & Instrumentation; Optics SC Instruments & Instrumentation; Optics GA BG2XH UT WOS:000387747900199 ER PT S AU Kuzmenko, PJ Little, SL Kutyrev, AS Capone, JI AF Kuzmenko, Paul J. Little, Steve L. Kutyrev, Alexander S. Capone, John I. BE Navarro, R Burge, JH TI Technique for diamond machining large ZnSe grisms for the Rapid Infrared/Imager Spectrograph (RIMAS) SO ADVANCES IN OPTICAL AND MECHANICAL TECHNOLOGIES FOR TELESCOPES AND INSTRUMENTATION II SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Advances in Optical and Mechanical Technologies for Telescopes and Instrumentation II CY JUN 26-JUL 01, 2016 CL Edinburgh, UNITED KINGDOM SP SPIE DE grism; RIMAS; diamond machining; ZnSe; immersion grating AB The Rapid Infrared Imager/Spectrograph (RIMAS) is an instrument designed to observe gamma ray burst afterglows following initial detection by the SWIFT satellite. Operating in the near infrared between 0.9 and 2.4 mu m, it has capabilities for both low resolution (R similar to 25) and moderate resolution (R similar to 4000) spectroscopy. Two zinc selenide (ZnSe) grisms provide dispersion in the moderate resolution mode: one covers the Y and J bands and the other covers the H and K. Each has a clear aperture of 44 mm. The YJ grism has a blaze angle of 49.9 degrees with a 40 mu m groove spacing. The HK grism is blazed at 43.1 degrees with a 50 mu m grooves spacing. Previous fabrication of ZnSe grisms on the Precision Engineering Research Lathe (PERL II) at LLNL has demonstrated the importance of surface preparation, tool and fixture design, tight thermal control, and backup power sources for the machine. The biggest challenges in machining the RIMAS grisms are the large grooved area, which indicates long machining time, and the relatively steep blaze angle, which means that the grism wavefront error is much more sensitive to lathe metrology errors. Mitigating techniques are described. C1 [Kuzmenko, Paul J.; Little, Steve L.] Lawrence Livermore Natl Lab, L-183,POB 808, Livermore, CA 94551 USA. [Kutyrev, Alexander S.] NASA, Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. [Kutyrev, Alexander S.; Capone, John I.] Univ Maryland, Dept Astron, Stadium Drive, College Pk, MD 20771 USA. RP Kuzmenko, PJ (reprint author), Lawrence Livermore Natl Lab, L-183,POB 808, Livermore, CA 94551 USA. EM kuzmenko1@llnl.gov NR 14 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0203-8; 978-1-5106-0204-5 J9 PROC SPIE PY 2016 VL 9912 AR UNSP 99120C DI 10.1117/12.2231834 PN 1 PG 12 WC Instruments & Instrumentation; Optics SC Instruments & Instrumentation; Optics GA BG2XH UT WOS:000387747900012 ER PT S AU Miller, AD Scowen, PA Veach, TJ AF Miller, Alexander D. Scowen, Paul A. Veach, Todd J. BE Navarro, R Burge, JH TI Focal plane actuation by hexapod for the development of a high resolution suborbital telescope SO ADVANCES IN OPTICAL AND MECHANICAL TECHNOLOGIES FOR TELESCOPES AND INSTRUMENTATION II SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Advances in Optical and Mechanical Technologies for Telescopes and Instrumentation II CY JUN 26-JUL 01, 2016 CL Edinburgh, UNITED KINGDOM SP SPIE DE Hexapod; image stabilization; jitter; suborbital balloon AB We present a prototype hexapod image stabilization system as the key instrument for a proposed suborbital balloon mission. The unique design thermally isolates an off-the-shelf non-cryogenic hexapod from a liquid nitrogen cooled focal plane, enabling its use in a cryogenic environment. Balloon gondolas currently achieve 1-2 arcsecond pointing error, but cannot correct for unavoidable jitter movements (similar to 20 micron amplitude at 20 Hz at the worst) caused by wind rushing over balloon surfaces, thermal variations, and vibrations from cryocoolers, and reaction wheels. The jitter causes image blur during exposures and limits the resolution of the system. Removal of this final jitter term decreases pointing error by an order of magnitude and allows for true diffraction-limited observation. Tip-tilt pointing systems have been used for these purposes in the past, but require additional optics and introduce multiple reflections. The hexapod system, rather, is compact and can be plugged into the focal point of nearly any configuration. For a 0.8m telescope the improvement in resolution by this system would provide 0.1" angular resolution at 300nm, which is comparable to Hubble for a fraction of the cost. On an actual balloon, the hexapod system would actuate the focal plane to counteract the jitter using position information supplied by guidestar cameras. However, in the lab, we instead simulate guide camera tracking, using a 1024 x 1024 e2v science-grade CCD to take long exposures of a target attached to an XY stage driven with the balloon jitter signal recorded during the STO mission. Further confirmation of the positional accuracy and agility of the hexapod is achieved using a laser and fast-sampling position-sensitive diode. High-resolution time domain multispectral imaging of the gas giants, especially in the UV range, is of particular interest to the planetary community, and a suborbital telescope with the hexapod stabilization in place would provide a wealth of new data. On an Antarctic similar to 100-day Long-Duration-Balloon (LDB) mission the continued high-resolution imaging of gas giant storm systems would provide cloud formation and evolution data second to only a Flagship orbiter. C1 [Miller, Alexander D.; Scowen, Paul A.] ASU Sch Earth & Space Explorat, 781 South Terrace Rd, Tempe, AZ 85287 USA. [Veach, Todd J.] NASA, Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. RP Miller, AD (reprint author), ASU Sch Earth & Space Explorat, 781 South Terrace Rd, Tempe, AZ 85287 USA. EM alexdukemiller@gmail.com NR 12 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0203-8; 978-1-5106-0204-5 J9 PROC SPIE PY 2016 VL 9912 AR UNSP 99126B DI 10.1117/12.2230834 PN 1 PG 15 WC Instruments & Instrumentation; Optics SC Instruments & Instrumentation; Optics GA BG2XH UT WOS:000387747900188 ER PT S AU Moore, CS Hennessy, J Jewell, AD Nikzad, S France, K AF Moore, Christopher Samuel Hennessy, John Jewell, April D. Nikzad, Shouleh France, Kevin BE Navarro, R Burge, JH TI Atomic Layer Deposited (ALD) coatings for future astronomical telescopes: recent developments SO ADVANCES IN OPTICAL AND MECHANICAL TECHNOLOGIES FOR TELESCOPES AND INSTRUMENTATION II SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Advances in Optical and Mechanical Technologies for Telescopes and Instrumentation II CY JUN 26-JUL 01, 2016 CL Edinburgh, UNITED KINGDOM SP SPIE DE Ultraviolet; Visible; Infrared; mirror coatings; atomic layer deposition; thin films; aluminum fluoride; aluminum mirrors; Lyman Ultraviolet; Far Ultraviolet; high-reflectivity; astronomy ID FAR-ULTRAVIOLET; FILMS; MGF2 AB Atomic Layer Deposition (ALD) can create conformal, near stoichiometric and pinhole free transmissive metal fluoride coatings to protect reflective aluminum films. Spectral performance of astronomical mirror coatings strongly affect the science capabilities of astronomical satellite missions. We are utilizing ALD to create a transmissive overcoat to protect aluminum film mirrors from oxidation with the goal of achieving high reflectance (> 80%) from the UV (similar to 100 nm) to the IR (similar to 2,000 nm). This paper summarizes the recent developments of ALD aluminum fluoride (AlF3) coatings on Al. Reflectance measurements of aluminum mirrors protected by ALD A1F3 and future applications are discussed. These measurements demonstrate that Al + ALD AlF3, even with an interfacial oxide layer of a few nanometers, can provide higher reflectance than Al protected by traditional physical vapor deposited MgF2 without an oxide layer, below 115 nm. C1 [Moore, Christopher Samuel; France, Kevin] Univ Colorado, Astrophys & Planetary Sci Dept, Boulder, CO 80309 USA. [Moore, Christopher Samuel; France, Kevin] Univ Colorado, Ctr Astrophys & Space Astron, Campus Box 391, Boulder, CO 80309 USA. [Moore, Christopher Samuel; France, Kevin] Univ Colorado, Atmospher & Space Phys Lab, Boulder, CO 80303 USA. [Hennessy, John; Jewell, April D.; Nikzad, Shouleh] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Moore, CS (reprint author), Univ Colorado, Astrophys & Planetary Sci Dept, Boulder, CO 80309 USA.; Moore, CS (reprint author), Univ Colorado, Ctr Astrophys & Space Astron, Campus Box 391, Boulder, CO 80309 USA.; Moore, CS (reprint author), Univ Colorado, Atmospher & Space Phys Lab, Boulder, CO 80303 USA. EM Christopher.Moore-1@Colorado.edu NR 26 TC 1 Z9 1 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0203-8; 978-1-5106-0204-5 J9 PROC SPIE PY 2016 VL 9912 AR UNSP 99122U DI 10.1117/12.2232296 PN 1 PG 8 WC Instruments & Instrumentation; Optics SC Instruments & Instrumentation; Optics GA BG2XH UT WOS:000387747900085 ER PT S AU Newman, K Sirbu, D Belikov, R Guyon, O AF Newman, Kevin Sirbu, Dan Belikov, Ruslan Guyon, Olivier BE Navarro, R Burge, JH TI Development of PIAA Complex Mask Coronagraphs for large aperture ground-based telescopes SO ADVANCES IN OPTICAL AND MECHANICAL TECHNOLOGIES FOR TELESCOPES AND INSTRUMENTATION II SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Advances in Optical and Mechanical Technologies for Telescopes and Instrumentation II CY JUN 26-JUL 01, 2016 CL Edinburgh, UNITED KINGDOM SP SPIE DE Focal plane mask; Coronagraph; PIAA; PIAACMC AB The Phase Induced Amplitude Apodization Complex Mask Coronagraph (PIAACMC) is an architecture for directly observing extrasolar planets, and can achieve performance near the theoretical limits for any direct-detection instrument. The PIAACMC architecture includes aspheric PIAA optics, and a complex phase-shifting focal plane mask that provides a pi phase shift to a portion of the on-axis starlight. The phase-shifted starlight is forced to interfere destructively with the un-shifted starlight, causing the starlight to be eliminated, and allowing a region for high-contrast imaging near the star. The PIAACMC architecture can be designed for segmented and obscured apertures, so it is particularly well suited for ground-based observing with the next generation of large telescopes. There will be unique scientific opportunities for directly observing Earth-like planets around nearby low-mass stars. We will discuss design strategies for adapting PIAACMC for the next generation of large ground-based telescopes, and present progress on the development of the focal plane mask technology. We also present simulations of wavefront control with PIAACMC, and suggest directions to apply the coronagraph architecture to future telescopes. C1 [Newman, Kevin; Guyon, Olivier] Univ Arizona, Tucson, AZ 85721 USA. [Newman, Kevin; Sirbu, Dan; Belikov, Ruslan] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Newman, K (reprint author), Univ Arizona, Tucson, AZ 85721 USA.; Newman, K (reprint author), NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. NR 10 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0203-8; 978-1-5106-0204-5 J9 PROC SPIE PY 2016 VL 9912 AR UNSP 99126L DI 10.1117/12.2232164 PN 1 PG 8 WC Instruments & Instrumentation; Optics SC Instruments & Instrumentation; Optics GA BG2XH UT WOS:000387747900197 ER PT S AU Quijada, MA Travinsky, A Vorobiev, D Ninkov, Z Raisanen, A Robberto, M Heap, S AF Quijada, Manuel A. Travinsky, Anton Vorobiev, Dmitry Ninkov, Zoran Raisanen, Alan Robberto, Massimo Heap, Sara BE Navarro, R Burge, JH TI Optical evaluation of digital micromirror devices (DMDs) with UV-grade fused silica, sapphire, and magnesium fluoride windows and longterm reflectance of bare devices SO ADVANCES IN OPTICAL AND MECHANICAL TECHNOLOGIES FOR TELESCOPES AND INSTRUMENTATION II SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Advances in Optical and Mechanical Technologies for Telescopes and Instrumentation II CY JUN 26-JUL 01, 2016 CL Edinburgh, UNITED KINGDOM SP SPIE DE Digital Micromirror Device; reflectance; transmittance; Galactic Evolution Spectroscopic Explorer; digital mcromirror array; scattering; DMD; MOS AB Digital micromirror devices (DMDs) are commercial micro-electromechanical systems, consisting of millions of mirrors which can be individually addressed and tilted into one of two states (+/- 12 degrees). These devices were developed to create binary patterns in video projectors, in the visible range. Commercially available DMDs are hermetically sealed and extremely reliable. Recently, DMDs have been identified as an alternative to microshutter arrays for space-based multi-object spectrometers (MOS). Specifically, the MOS at the heart of the proposed Galactic Evolution Spectroscopic Explorer (GESE) uses the DMD as a reprogrammable slit mask. Unfortunately, the protective borosilicate windows limit the use of DMDs in the UV and IR regimes, where the glass has insufficient throughput. In this work, we present our efforts to replace standard DMD windows with custom windows made from UV-grade fused silica, low-absorption optical sapphire (LAOS) and magnesium fluoride (MgF2). We present transmission measurements of the antireflection coated windows and the reflectance of bare (window removed) DMDs. Furthermore, we investigated the long-term stability of the DMD reflectance and experiments for coating DMD active area with a layer of pure aluminum (Al) to boost reflectance performance in the UV spectral range (200-400 nm). C1 [Quijada, Manuel A.; Heap, Sara] NASA, Goddard Space Flight Ctr, Opt Branch, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. [Travinsky, Anton; Vorobiev, Dmitry; Ninkov, Zoran] Ctr Imaging Sci, 54 Lomb Mem Dr, Rochester, NY USA. [Raisanen, Alan] Rochester Inst Technol, Dept Mfg & Mech Engn Technol, Rochester, NY 14623 USA. [Robberto, Massimo] Space Telescope Sci Inst, 3700 San Martin Dr, Baltimore, MD 21218 USA. RP Quijada, MA (reprint author), NASA, Goddard Space Flight Ctr, Opt Branch, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. EM manuel.a.quijada@nasa.gov NR 6 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0203-8; 978-1-5106-0204-5 J9 PROC SPIE PY 2016 VL 9912 AR UNSP 99125V DI 10.1117/12.2233341 PN 1 PG 10 WC Instruments & Instrumentation; Optics SC Instruments & Instrumentation; Optics GA BG2XH UT WOS:000387747900172 ER PT S AU Ruane, G Jewell, J Mawet, D Pueyo, L Shaklan, S AF Ruane, Garreth Jewell, Jeffrey Mawet, Dimitri Pueyo, Laurent Shaklan, Stuart BE Navarro, R Burge, JH TI Apodized vortex coronagraph designs for segmented aperture telescopes SO ADVANCES IN OPTICAL AND MECHANICAL TECHNOLOGIES FOR TELESCOPES AND INSTRUMENTATION II SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Advances in Optical and Mechanical Technologies for Telescopes and Instrumentation II CY JUN 26-JUL 01, 2016 CL Edinburgh, UNITED KINGDOM SP SPIE DE High contrast imaging; instrumentation; exoplanets; direct detection; coronagraphs ID LABORATORY DEMONSTRATION; PIAA CORONAGRAPHY; EXTRASOLAR PLANET; MASK; LYOT; SPECTROSCOPY; PUPIL; IMAGE; STAR AB Current state-of-the-art high contrast imaging instruments take advantage of a number of elegant coronagraph designs to suppress starlight and image nearby faint objects, such as exoplanets and circumstellar disks. The ideal performance and complexity of the optical systems depends strongly on the shape of the telescope aperture. Unfortunately, large primary mirrors tend to be segmented and have various obstructions, which limit the performance of most conventional coronagraph designs. We present a new family of vortex coronagraphs with numerically-optimized gray-scale apodizers that provide the sensitivity needed to directly image faint exoplanets with large, segmented aperture telescopes, including the Thirty Meter Telescope (TMT) as well as potential next-generation space telescopes. C1 [Ruane, Garreth; Mawet, Dimitri] CALTECH, 1200 E Calif Blvd, Pasadena, CA 91125 USA. [Jewell, Jeffrey; Mawet, Dimitri; Shaklan, Stuart] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Pueyo, Laurent] Space Telescope Sci Inst, 3700 San Martin Dr, Baltimore, MD 21218 USA. RP Ruane, G (reprint author), CALTECH, 1200 E Calif Blvd, Pasadena, CA 91125 USA. EM gruane@astro.caltech.edu OI Ruane, Garreth/0000-0003-4769-1665 NR 43 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0203-8; 978-1-5106-0204-5 J9 PROC SPIE PY 2016 VL 9912 AR UNSP 99122L DI 10.1117/12.2231715 PN 1 PG 13 WC Instruments & Instrumentation; Optics SC Instruments & Instrumentation; Optics GA BG2XH UT WOS:000387747900080 ER PT S AU Sidick, E Seo, BJ Marx, D Poberezhskiy, I Nemati, B AF Sidick, Erkin Seo, Byoung-Joon Marx, David Poberezhskiy, Ilya Nemati, Bijan BE Navarro, R Burge, JH TI WFIRST/AFTA Coronagraph Contrast Performance Sensitivity Studies: Simulation versus Experiment SO ADVANCES IN OPTICAL AND MECHANICAL TECHNOLOGIES FOR TELESCOPES AND INSTRUMENTATION II SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Advances in Optical and Mechanical Technologies for Telescopes and Instrumentation II CY JUN 26-JUL 01, 2016 CL Edinburgh, UNITED KINGDOM SP SPIE DE Coronagraphy; adaptive optics; deformable mirrors; space telescopes; exoplanets AB The WFIRST/AFTA 2.4 m space telescope currently under study includes a stellar coronagraph for the imaging and the spectral characterization of extrasolar planets. The coronagraph employs sequential deformable mirrors to compensate for phase and amplitude errors. Using the optical model of an Occulting Mask Coronagraph (OMC) testbed at the Jet Propulsion Laboratory, we have investigated through modeling and simulations the sensitivity of dark hole contrast in a Hybrid Lyot Coronagraph (HLC) for several error cases, including lateral and longitudinal translation errors of two deformable mirrors, DM1 and DM2, lateral and/or longitudinal translation errors of an occulting mask and a Lyot- Stop, clocking errors of DM1 and DM2, and the mismatch errors between the testbed and the model sensitivity matrices. We also investigated the effects of a control parameter, namely the actuator regularization factor, on the control efficiency and on the final contrast floor. We found several error cases which yield contrast results comparable to that observed on the HLC testbed. We present our findings in this paper. C1 [Sidick, Erkin; Seo, Byoung-Joon; Marx, David; Poberezhskiy, Ilya; Nemati, Bijan] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Sidick, E (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Erkin.Sidick@jpl.nasa.gov NR 16 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0203-8; 978-1-5106-0204-5 J9 PROC SPIE PY 2016 VL 9912 AR UNSP 99126M DI 10.1117/12.2231763 PN 1 PG 12 WC Instruments & Instrumentation; Optics SC Instruments & Instrumentation; Optics GA BG2XH UT WOS:000387747900198 ER PT S AU Stahl, HP AF Stahl, H. Philip BE Navarro, R Burge, JH TI Advanced Mirror Technology Development (AMTD) Project: Overview and Year 4 Accomplishments SO ADVANCES IN OPTICAL AND MECHANICAL TECHNOLOGIES FOR TELESCOPES AND INSTRUMENTATION II SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Advances in Optical and Mechanical Technologies for Telescopes and Instrumentation II CY JUN 26-JUL 01, 2016 CL Edinburgh, UNITED KINGDOM SP SPIE DE space telescopes; astrophysics; astronomy; ATLAST; LUVOIR; HabEx AB The Advanced Mirror Technology Development (AMTD) project is in Phase 2 of a multiyear effort initiated in Fiscal Year (FY) 2012, to mature toward the next Technology Readiness Level (TRL) critical technologies required to enable 4-m-or-larger monolithic or segmented ultraviolet, optical, and infrared (UVOIR) space telescope primary-mirror assemblies for general astrophysics and ultra-high-contrast observations of exoplanets. Key hardware accomplishments of 2015/16 are the successful low-temperature fusion of a 1.5-meter diameter ULE mirror that is a 1/3rd scale model of a 4-meter mirror and the initiation of polishing of a 1.2-meter Extreme-Lightweight Zerodur mirror. Critical to AMTD's success is an integrated team of scientists, systems engineers, and technologists; and a science-driven systems engineering approach. C1 [Stahl, H. Philip] NASA, Marshall Space Flight Ctr, Huntsville, AL 35812 USA. RP Stahl, HP (reprint author), NASA, Marshall Space Flight Ctr, Huntsville, AL 35812 USA. NR 10 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0203-8; 978-1-5106-0204-5 J9 PROC SPIE PY 2016 VL 9912 AR UNSP 99120S DI 10.1117/12.2234082 PN 1 PG 7 WC Instruments & Instrumentation; Optics SC Instruments & Instrumentation; Optics GA BG2XH UT WOS:000387747900025 ER PT S AU Steeves, J Martin, S Webb, D Lisman, D Shaklan, S AF Steeves, John Martin, Stefan Webb, David Lisman, Douglas Shaklan, Stuart BE Navarro, R Burge, JH TI Precision Optical Edges for a Starshade External Occulter SO ADVANCES IN OPTICAL AND MECHANICAL TECHNOLOGIES FOR TELESCOPES AND INSTRUMENTATION II SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Advances in Optical and Mechanical Technologies for Telescopes and Instrumentation II CY JUN 26-JUL 01, 2016 CL Edinburgh, UNITED KINGDOM SP SPIE DE starshade; occulter; high contrast imaging AB The use of a starshade is one technique to perform high contrast imaging with space-based telescopes. The primary function of a starshade is to suppress light from a target star in order to image its orbiting planets. In order to provide the proper apodization function the edges of the starshade must follow a precise in-plane profile. However of equal importance is the issue of light from our own sun scattering off of the edges and entering the telescope. A method to alleviate this problem is to make the edges extremely sharp (< 1 pm terminal radius) such that the area available for scattering is minimized. The combination of these two requirements, along with the need to integrate the edges into a 30-40 m dia. deployable structure, present a number of significant engineering challenges. Substrate etching techniques are used to obtain both the intended profile as well as the edge sharpness. Current efforts implement an isotropic etching process on thin metal substrates. This paper discusses the progress towards producing a sharp optical edge at the coupon level. Samples have been characterized using scanning electron microscopy as well as a custom testbed to assess their scattered-light performance. C1 [Steeves, John; Martin, Stefan; Webb, David; Lisman, Douglas; Shaklan, Stuart] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Steeves, J (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM john.b.steeves@jpl.nasa.gov NR 4 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0203-8; 978-1-5106-0204-5 J9 PROC SPIE PY 2016 VL 9912 AR UNSP 99122O DI 10.1117/12.2233409 PN 1 PG 11 WC Instruments & Instrumentation; Optics SC Instruments & Instrumentation; Optics GA BG2XH UT WOS:000387747900082 ER PT S AU Steeves, J Jackson, K Pellegrino, S Redding, D Wallace, JK Bradford, SC Barbee, T AF Steeves, John Jackson, Kathryn Pellegrino, Sergio Redding, David Wallace, J. Kent Bradford, Samuel Case Barbee, Troy BE Navarro, R Burge, JH TI Multilayer active shell mirrors for space telescopes SO ADVANCES IN OPTICAL AND MECHANICAL TECHNOLOGIES FOR TELESCOPES AND INSTRUMENTATION II SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Advances in Optical and Mechanical Technologies for Telescopes and Instrumentation II CY JUN 26-JUL 01, 2016 CL Edinburgh, UNITED KINGDOM SP SPIE DE Active Mirrors; CFRP; Nanolaminate; Replication; Reverse Hartmann AB A novel active mirror technology based on carbon fiber reinforced polymer (CFRP) substrates and replication techniques has been developed. Multiple additional layers are implemented into the design serving various functions. Nanolaminate metal films are used to provide a high quality reflective front surface. A backing layer of thin active material is implemented to provide the surface-parallel actuation scheme. Printed electronics are used to create a custom electrode pattern and flexible routing layer. Mirrors of this design are thin (< 1.0 mm), lightweight (2.7 kg/m(2)), and have large actuation capabilities. These capabilities, along with the associated manufacturing processes, represent a significant change in design compared to traditional optics. Such mirrors could be used as lightweight primaries for small CubeSat-based telescopes or as meter-class segments for future large aperture observatories. Multiple mirrors can be produced under identical conditions enabling a substantial reduction in manufacturing cost and complexity. An overview of the mirror design and manufacturing processes is presented. Predictions on the actuation performance have been made through finite element simulations demonstrating correctabilities on the order of 250-300X for astigmatic modes with only 41 independent actuators. A description of the custom metrology system used to characterize the active mirrors is also presented. The system is based on a Reverse Hartmann test and can accommodate extremely large deviations in mirror figure (> 100 mu m PV) down to sub-micron precision. The system has been validated against several traditional techniques including photogrammetry and interferometry. The mirror performance has been characterized using this system, as well as closed-loop figure correction experiments on 150 mm dia. prototypes. The mirrors have demonstrated post-correction figure accuracies of 200 nm RMS (two dead actuators limiting performance). C1 [Steeves, John; Redding, David; Wallace, J. Kent; Bradford, Samuel Case] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Jackson, Kathryn; Pellegrino, Sergio] CALTECH, 1200 E Calif Blvd, Pasadena, CA 91125 USA. [Barbee, Troy] Lawrence Livermore Natl Lab, 7000 East Ave, Livermore, CA 94550 USA. RP Steeves, J (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM john.b.steeves@jpl.nasa.gov NR 19 TC 0 Z9 0 U1 3 U2 3 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0203-8; 978-1-5106-0204-5 J9 PROC SPIE PY 2016 VL 9912 AR UNSP 99121K DI 10.1117/12.2233594 PN 1 PG 15 WC Instruments & Instrumentation; Optics SC Instruments & Instrumentation; Optics GA BG2XH UT WOS:000387747900050 ER PT S AU Pham, T Thronson, H Seery, B Ganel, O AF Thai Pham Thronson, Harley Seery, Bernard Ganel, Opher BE Navarro, R Burge, JH TI NASA's Physics of the Cosmos and Cosmic Origins Programs Manage Strategic Astrophysics Technology (SAT) Development SO ADVANCES IN OPTICAL AND MECHANICAL TECHNOLOGIES FOR TELESCOPES AND INSTRUMENTATION II SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Advances in Optical and Mechanical Technologies for Telescopes and Instrumentation II CY JUN 26-JUL 01, 2016 CL Edinburgh, UNITED KINGDOM SP SPIE DE NASA; astronomy; astrophysics; technology; cosmic origins; cosmos; Hubble; SAT; decadal survey; STDT AB The strategic astrophysics missions of the coming decades will help answer the questions "How did our universe begin and evolve?" "How did galaxies, stars, and planets come to be?" and "Are we alone?" Enabling these missions requires advances in key technologies far beyond the current state of the art. NASA's Physics of the Cosmos2 (PCOS), Cosmic Origins3 (COR), and Exoplanet Exploration Program4 (ExEP) Program Offices manage technology maturation projects funded through the Strategic Astrophysics Technology (SAT) program to accomplish such advances. The PCOS and COR Program Offices, residing at the NASA Goddard Space Flight Center (GSFC), were established in 2011, and serve as the implementation arm for the Astrophysics Division at NASA Headquarters. We present an overview of the Programs' technology development activities and the current technology investment portfolio of 23 technology advancements. We discuss the process for addressing community-provided technology gaps and Technology Management Board (TMB)-vetted prioritization and investment recommendations that inform the SAT program. The process improves the transparency and relevance of our technology investments, provides the community a voice in the process, and promotes targeted external technology investments by defining needs and identifying customers. The Programs' priorities are driven by strategic direction from the Astrophysics Division, which is informed by the National Research Council's (NRC) "New Worlds, New Horizons in Astronomy and Astrophysics" (NWNH) 2010 Decadal Survey report Pi, the Astrophysics Implementation Plan (AIP) [2] as updated, and the Astrophysics Roadmap "Enduring Quests, Daring Visions" [3]. These priorities include technology development for missions to study dark energy, gravitational waves, X-ray and inflation probe science, and large far-infrared (IR) and ultraviolet (UV)/optical/IR telescopes to conduct imaging and spectroscopy studies. The SAT program is the Astrophysics Division's main investment method to mature technologies that will be identified by study teams set up to inform the 2020 Decadal Survey process on several large astrophysics mission concepts. C1 [Thai Pham; Thronson, Harley; Seery, Bernard; Ganel, Opher] NASA, Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. RP Pham, T (reprint author), NASA, Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. EM bruce.t.pham@nasa.gov NR 5 TC 0 Z9 0 U1 1 U2 1 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0203-8; 978-1-5106-0204-5 J9 PROC SPIE PY 2016 VL 9912 AR UNSP 991270 DI 10.1117/12.2231761 PN 1 PG 9 WC Instruments & Instrumentation; Optics SC Instruments & Instrumentation; Optics GA BG2XH UT WOS:000387747900209 ER PT S AU Travinsky, A Vorobiev, D Ninkov, Z Raisanen, AD Pellish, JA Robberto, M Heap, S AF Travinsky, Anton Vorobiev, Dmitry Ninkov, Zoran Raisanen, Alan D. Pellish, Jonathan A. Robberto, Massimo Heap, Sara BE Navarro, R Burge, JH TI The effects of heavy ion radiation on digital micromirror device performance SO ADVANCES IN OPTICAL AND MECHANICAL TECHNOLOGIES FOR TELESCOPES AND INSTRUMENTATION II SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Advances in Optical and Mechanical Technologies for Telescopes and Instrumentation II CY JUN 26-JUL 01, 2016 CL Edinburgh, UNITED KINGDOM SP SPIE DE DMD; digital micro-mirror device; digital micro-mirror array; MOS; multiple-object spectroscopy; heavy ion radiation ID SPECTROSCOPY; CRITIQUE; IRMOS AB There is a pressing need in the astronomical community for space-suitable multi-object spectrometers (MOSs). Several digital micromirror device (DMD)-based prototype MOSs have been developed for ground-based observatories; however, their main use will come with deployment on a space based mission. Therefore, performance of DMDs under exoatmospheric radiation needs to be evaluated. In our previous work we demonstrated that DMDs are tolerant to heavy ion irradiation in general and calculated upset rate of 4.3 micromirrors in 24 hours in orbit for 1-megapixel device. The goal of this additional experiment was to acquire more data and therefore increase the accuracy of the predicted in-orbit micromirror upset rate. Similar to the previous experiment, for this testing 0.7 XGA DMDs were re-windowed with 2 p.m thick pellicle and tested under accelerated heavy-ion radiation (with control electronics shielded from radiation) with a focus on detection of single-event upsets (SEUs). We concentrated on ions with low levels of linear energy transfer (LET) 1.8- 13 MeV.cm2.mg-1 to cover the most critical range of the Weibull curve for those devices. As during the previous experiment, we observed and documented non-destructive heavy ion-induced micromirror state changes. All SEUs were always cleared with a soft reset (that is, sending a new pattern to the device). The DMDs we tested did not experience single-event induced permanent damage or functional changes that required a hard reset (power cycle), even at high ion fluences. Based on the data obtained in the experiments we predict micromirror in-orbit upset rate of 5.6 micromirrors in 24 hours in-orbit for the tested devices. This suggests that the heavy-ion induced SEU rate burden for a DMD-based instrument will be manageable when exposed to solar particle fluxes and cosmic rays in orbit. C1 [Travinsky, Anton; Vorobiev, Dmitry; Ninkov, Zoran; Raisanen, Alan D.] Rochester Inst Technol, Rochester, NY 14623 USA. [Pellish, Jonathan A.; Heap, Sara] NASA, Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. [Robberto, Massimo] Space Telescope Sci Inst, 3700 San Martin Dr, Baltimore, MD 21218 USA. RP Travinsky, A (reprint author), Rochester Inst Technol, Rochester, NY 14623 USA. NR 27 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0203-8; 978-1-5106-0204-5 J9 PROC SPIE PY 2016 VL 9912 AR UNSP 99125W DI 10.1117/12.2233240 PN 1 PG 9 WC Instruments & Instrumentation; Optics SC Instruments & Instrumentation; Optics GA BG2XH UT WOS:000387747900173 ER PT S AU Vorobiev, D Travinsky, A Quijada, MA Ninkov, Z Raisanen, AD Robberto, M Heap, S AF Vorobiev, Dmitry Travinsky, Anton Quijada, Manuel A. Ninkov, Zoran Raisanen, Alan D. Robberto, Massimo Heap, Sara BE Navarro, R Burge, JH TI Measurements of the reflectance, contrast ratio, and scattering properties of digital micromirror devices (DMDs) SO ADVANCES IN OPTICAL AND MECHANICAL TECHNOLOGIES FOR TELESCOPES AND INSTRUMENTATION II SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Advances in Optical and Mechanical Technologies for Telescopes and Instrumentation II CY JUN 26-JUL 01, 2016 CL Edinburgh, UNITED KINGDOM SP SPIE DE Digital micromirror device; DMD; digital micromirror array; multi-object spectroscopy; MOS; reflectance; contrast; scattering AB Digital micromirror devices (DMDs) are micro-electro- mechanical systems, originally developed to display images in projector systems. A DMD in the focal plane of an imaging system can be used as a reprogrammable slit mask of a multi-object spectrometer (MOS) by tilting some of the mirrors towards the spectrometer and tilting the rest of the mirrors away, thereby rejecting the unwanted light (due to the background and foreground objects). A DMD-based MOS can generate new, arbitrary slit patterns in seconds, which significantly reduces the overhead time during astronomical observations. Critically, DMD-based slit masks are extremely lightweight, compact and mechanically robust, which makes them attractive for use in space-based telescopes. As part of a larger effort to investigate the use of DMDs in space telescopes (sponsored by a NASA Strategic Astrophysics Technologies grant), we characterized the optical performance of Texas Instruments DMDs to determine their suitability for use in multi-object spectrometers. The performance of a DMD-based MOS is significantly affected by its optical throughput (reflectance), contrast ratio (the ability of the DMD to reject unwanted light) and scattering properties (which could lead to crosstalk and reduced signal-to-noise ratio in the spectrometer). We measured and quantified the throughput and contrast ratio of a Texas Instruments DMD in several configurations (which emulate the operation of a typical DMD-based MOS) and investigated the scattering properties of the individual DMD mirrors. In this work we present the results of our analysis, describe the performance of a typical DMDbased MOS and discuss the practical limitations of these instruments (such as maximum density of sources and expected signal-to- noise ratio). C1 [Vorobiev, Dmitry; Travinsky, Anton; Ninkov, Zoran] Rochester Inst Technol, Ctr Imaging Sci, Rochester, NY 14623 USA. [Raisanen, Alan D.] Rochester Inst Technol, Dept Mfg & Mech Engn Technol, Rochester, NY 14623 USA. [Quijada, Manuel A.; Heap, Sara] NASA, Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. [Robberto, Massimo] Space Telescope Sci Inst, 3700 San Martin Dr, Baltimore, MD 21218 USA. RP Vorobiev, D (reprint author), Rochester Inst Technol, Ctr Imaging Sci, Rochester, NY 14623 USA. EM dxv2686@rit.edu NR 9 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0203-8; 978-1-5106-0204-5 J9 PROC SPIE PY 2016 VL 9912 AR UNSP 99125U DI 10.1117/12.2233638 PN 1 PG 6 WC Instruments & Instrumentation; Optics SC Instruments & Instrumentation; Optics GA BG2XH UT WOS:000387747900171 ER PT S AU Vorobiev, D Travinsky, A Raisanen, AD Ninkov, Z Schwartz, TA Robberto, M Heap, S AF Vorobiev, Dmitry Travinsky, Anton Raisanen, Alan D. Ninkov, Zoran Schwartz, Timothy A. Robberto, Massimo Heap, Sara BE Navarro, R Burge, JH TI Shock and vibration testing of digital micromirror devices (DMDs) for space-based applications SO ADVANCES IN OPTICAL AND MECHANICAL TECHNOLOGIES FOR TELESCOPES AND INSTRUMENTATION II SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Advances in Optical and Mechanical Technologies for Telescopes and Instrumentation II CY JUN 26-JUL 01, 2016 CL Edinburgh, UNITED KINGDOM SP SPIE DE DMD; MOS; vibration testing; shock testing; digital micromirror device; multi-object spectrometer AB Digital micromirror devices (DMDs) are a mature commercial technology, with several potential applications in space-based instruments. In particular, DMDs are currently the only practical alternative to microshutter arrays as slit mask generators for space-based multi-object spectrometers (MOS). A DMD is an array of micromirrors which can be addressed individually and tilted into one of two states (+/- 12 w.r.t. the device plane), which makes it a very versatile binary light modulator. These devices are widely utilized in a variety of optical systems, especially projectors. Recently, the use of DMDs for ground-based multi-object spectrometers has been demonstrated. The compact size and small weight of DMDs makes them especially attractive for a space based MOS, where the only current alternative is an array of microshutters. DMDs were originally designed for visible range applications; therefore the protective glass window they are supplied with does not have sufficient throughput in the UV or IR and has to be replaced. In this work, we describe the procedure by which we replaced the standard window with UV-grade fused silica, sapphire and magnesium fluoride. We performed initial shock and vibrational tests to evaluate the mechanical robustness of the re-windowed devices, to investigate the ability of these devices to survive launch conditions. We performed residual gas analysis to study the outgassing properties of the new DMDs and evaluate the ability of the new seals to protect the device. The tested devices show near-hermetic seals before and after the mechanical testing. C1 [Vorobiev, Dmitry; Travinsky, Anton; Ninkov, Zoran] Rochester Inst Technol, Ctr Imaging Sci, Rochester, NY 14623 USA. [Raisanen, Alan D.] Rochester Inst Technol, Dept Mfg & Mech Engn Technol, Rochester, NY 14623 USA. [Schwartz, Timothy A.; Heap, Sara] NASA, Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. [Robberto, Massimo] Space Telescope Sci Inst, 3700 San Martin Dr, Baltimore, MD 21218 USA. RP Vorobiev, D (reprint author), Rochester Inst Technol, Ctr Imaging Sci, Rochester, NY 14623 USA. EM dxv2686@rit.edu NR 6 TC 1 Z9 1 U1 1 U2 1 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0203-8; 978-1-5106-0204-5 J9 PROC SPIE PY 2016 VL 9912 AR UNSP 99125M DI 10.1117/12.2233591 PN 1 PG 13 WC Instruments & Instrumentation; Optics SC Instruments & Instrumentation; Optics GA BG2XH UT WOS:000387747900163 ER PT S AU Waddell, P Black, DS AF Waddell, Patrick Black, David S. BE Navarro, R Burge, JH TI J-Black: a stray light coating for optical and infrared systems SO ADVANCES IN OPTICAL AND MECHANICAL TECHNOLOGIES FOR TELESCOPES AND INSTRUMENTATION II SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Advances in Optical and Mechanical Technologies for Telescopes and Instrumentation II CY JUN 26-JUL 01, 2016 CL Edinburgh, UNITED KINGDOM SP SPIE DE optical absorbers; stray light; black coatings; Infrared optics; baffles AB A new stray light coating, called J-Black, has been developed for NASA's Stratospheric Observatory for Infrared Astronomy (SOFIA). The coating is a layered composition of Nextel-Suede 3101 primers and top coats and silicon carbide grit. J-Black has been applied to large areas of the SOFIA airborne telescope and is currently operating within the open cavity environment of the Boeing 747. Over a series of discrete filter bands, from 0.4 to 20 microns, J-Black optical and infrared reflectivity performance is compared with other available coatings. Measured total reflectance values are less than 2% at the longest wavelengths, including at high incidence angles. Detailed surface structure characteristics are also compared via electron and ion microscopy. Environmental tests applicable for aerospace applications are presented, as well as the detailed steps required to apply the coating. C1 [Waddell, Patrick; Black, David S.] NASA, Univ Space Res Assoc, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Waddell, P (reprint author), NASA, Univ Space Res Assoc, Ames Res Ctr, Moffett Field, CA 94035 USA. NR 7 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0203-8; 978-1-5106-0204-5 J9 PROC SPIE PY 2016 VL 9912 AR UNSP 99122T DI 10.1117/12.2232159 PN 1 PG 18 WC Instruments & Instrumentation; Optics SC Instruments & Instrumentation; Optics GA BG2XH UT WOS:000387747900084 ER PT S AU Webb, D Hirsch, B Bradford, C Steeves, J Lisman, D Shaklan, S Bach, V Thomson, M AF Webb, David Hirsch, Brian Bradford, Case Steeves, John Lisman, Douglas Shaklan, Stuart Bach, Vinh Thomson, Mark BE Navarro, R Burge, JH TI Advances in Starshade Technology Readiness for an Exoplanet Characterizing Science Mission in the 2020's SO ADVANCES IN OPTICAL AND MECHANICAL TECHNOLOGIES FOR TELESCOPES AND INSTRUMENTATION II SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Advances in Optical and Mechanical Technologies for Telescopes and Instrumentation II CY JUN 26-JUL 01, 2016 CL Edinburgh, UNITED KINGDOM SP SPIE DE starshade; occulter; high contrast imaging; WFIRST AB The discovery of thousands of exoplanets is generating increasing interest in the direct imaging and characterization of these planets. Starshade. an external occulter. could fly in formation between a telescope and distant star, blocking out the light from the star, and enabling us to focus on the light of any orbiting planets. Recent technology developments in coordination with system level design, has added much needed detail to define the technology requirements for a science mission that could launch in the 2020's. This paper addresses the mechanical architecture, the successful efforts to date, the current state of design for the mechanical system, and upcoming technology efforts. C1 [Webb, David; Hirsch, Brian; Bradford, Case; Steeves, John; Lisman, Douglas; Shaklan, Stuart; Bach, Vinh; Thomson, Mark] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Webb, D (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 10 TC 0 Z9 0 U1 1 U2 1 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0203-8; 978-1-5106-0204-5 J9 PROC SPIE PY 2016 VL 9912 AR UNSP 99126H DI 10.1117/12.2232587 PN 1 PG 13 WC Instruments & Instrumentation; Optics SC Instruments & Instrumentation; Optics GA BG2XH UT WOS:000387747900193 ER PT S AU Link, D Brinkmann, J Xiong, XX Wang, ZP AF Link, Daniel Brinkmann, Jake Xiong, Xiaoxiong Wang, Zhipeng BE VelezReyes, M Messinger, DW TI Tracking the on-orbit spatial performance of MODIS using ground targets SO ALGORITHMS AND TECHNOLOGIES FOR MULTISPECTRAL, HYPERSPECTRAL, AND ULTRASPECTRAL IMAGERY XXII SE Proceedings of SPIE LA English DT Proceedings Paper CT 22nd SPIE Conference on Algorithms and Technologies for Multispectral, Hyperspectral, and Ultraspectral Imagery XXII CY APR 18-21, 2016 CL Baltimore, MD SP SPIE DE MODIS; Terra; Aqua; SRCA; BBR; spatial characterization ID CALIBRATION ASSEMBLY SRCA AB Nearly-identical MODIS instruments are operating onboard both the NASA EOS Terra and Aqua spacecraft. Each instrument records earth-scene data using 490 detectors divided among 36 spectral bands. These bands range in center wavelength from 0.4 mu m to 14.2 mu m to benefit studies of the entire earth system including land, atmosphere, and ocean disciplines. Many of the resultant science data products are the result of multiple bands used in combination. Any mis-registration between the bands would adversely affect subsequent data products. The relative registration between MODIS bands was measured pre-launch and continues to be monitored on-orbit via the Spectro-radiometric Calibration Assembly (SRCA), an on-board calibrator. Analysis has not only shown registration differences pre-launch, but also long-term and seasonal changes. While the ability to determine registration changes on-orbit using the SRCA is unique to MODIS, the use of ground targets to determine relative registration has been used for other instruments. This paper evaluates a ground target for MODIS spatial characterization using the MODIS calibrated data product. Results are compared against previously reported findings using MODIS data and the operational on-board characterization using the SRCA. C1 [Link, Daniel; Brinkmann, Jake; Wang, Zhipeng] Sci Syst & Applicat Inc SSAI, 10210 Greenbelt Rd, Lanham, MD 20706 USA. [Xiong, Xiaoxiong] NASA, Goddard Space Flight Ctr, Sci & Explorat Directorate, Greenbelt, MD 20771 USA. RP Link, D (reprint author), Sci Syst & Applicat Inc SSAI, 10210 Greenbelt Rd, Lanham, MD 20706 USA. NR 11 TC 0 Z9 0 U1 1 U2 1 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0081-2 J9 PROC SPIE PY 2016 VL 9840 AR 984029 DI 10.1117/12.2223980 PG 10 WC Engineering, Electrical & Electronic; Optics; Imaging Science & Photographic Technology SC Engineering; Optics; Imaging Science & Photographic Technology GA BF6RJ UT WOS:000383611600063 ER PT S AU Murphy, JM Leija, ON Le Moigne, J AF Murphy, James M. Leija, Omar Navarro Le Moigne, Jacqueline BE VelezReyes, M Messinger, DW TI Agile multi-scale decompositions for automatic image registration SO ALGORITHMS AND TECHNOLOGIES FOR MULTISPECTRAL, HYPERSPECTRAL, AND ULTRASPECTRAL IMAGERY XXII SE Proceedings of SPIE LA English DT Proceedings Paper CT 22nd SPIE Conference on Algorithms and Technologies for Multispectral, Hyperspectral, and Ultraspectral Imagery XXII CY APR 18-21, 2016 CL Baltimore, MD SP SPIE DE Image registration; shearlets; multiscale representations; agile algorithms; multi-modal images ID FRAMES AB In recent works, the first and third authors developed an automatic image registration algorithm based on a multiscale hybrid image decomposition with anisotropic shearlets and isotropic wavelets. This prototype showed strong performance, improving robustness over registration with wavelets alone. However, this method imposed a strict hierarchy on the order in which shearlet and wavelet features were used in the registration process, and also involved an unintegrated mixture of MATLAB and C code. In this paper, we introduce a more agile model for generating features, in which a flexible and user-guided mix of shearlet and wavelet features are computed. Compared to the previous prototype, this method introduces a flexibility to the order in which shearlet and wavelet features are used in the registration process. Moreover, the present algorithm is now fully coded in C, making it more efficient and portable than the mixed MATLAB and C prototype. We demonstrate the versatility and computational efficiency of this approach by performing registration experiments with the fully-integrated C algorithm. In particular, meaningful timing studies can now be performed, to give a concrete analysis of the computational costs of the flexible feature extraction. Examples of synthetically warped and real multi-modal images are analyzed. Keywords: Image registration, shearlets, multiscale representations, agile C1 [Murphy, James M.] Duke Univ, Dept Math, Durham, NC 27708 USA. [Leija, Omar Navarro] Univ Nevada, Dept Comp Sci, Las Vegas, NV 89154 USA. [Le Moigne, Jacqueline] NASA, Goddard Space Flight Ctr, Software Engn Div, Code 661, Greenbelt, MD 20771 USA. RP Murphy, JM (reprint author), Duke Univ, Dept Math, Durham, NC 27708 USA. EM jmmurphy11@gmail.com; navar106@unlv.nevada.edu; jacqueline.j.lemoigne-stewart@nasa.gov NR 20 TC 0 Z9 0 U1 1 U2 1 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0081-2 J9 PROC SPIE PY 2016 VL 9840 AR 984011 DI 10.1117/12.2222182 PG 9 WC Engineering, Electrical & Electronic; Optics; Imaging Science & Photographic Technology SC Engineering; Optics; Imaging Science & Photographic Technology GA BF6RJ UT WOS:000383611600028 ER PT B AU Douglas, GL Azcarate-Peril, MA Klaenhammer, TR AF Douglas, Grace L. Azcarate-Peril, M. Andrea Klaenhammer, Todd R. BE Mozzi, F Raya, RR Vignolo, GM TI Genomic Evolution of Lactic Acid Bacteria: From Single Gene Function to the Pan-genome SO BIOTECHNOLOGY OF LACTIC ACID BACTERIA: NOVEL APPLICATIONS, 2ND EDITION LA English DT Article; Book Chapter ID LACTOBACILLUS-ACIDOPHILUS NCFM; INFLAMMATORY-BOWEL-DISEASE; SUPEROXIDE-DISMUTASE GENE; RHAMNOSUS GG REVEALS; LACTOCOCCUS-LACTIS; STREPTOCOCCUS-THERMOPHILUS; ESCHERICHIA-COLI; CHEMICAL-CHARACTERIZATION; ANTIMICROBIAL SUBSTANCE; GASTROINTESTINAL-TRACT C1 [Douglas, Grace L.] NASA Johnson Space Ctr, Human Hlth & Performance Directorate, Houston, TX USA. [Azcarate-Peril, M. Andrea] Univ North Carolina Chapel Hill, Dept Cell Biol & Physiol, Chapel Hill, NC USA. [Azcarate-Peril, M. Andrea] Univ North Carolina Chapel Hill, Microbiome Core Facil, Chapel Hill, NC USA. [Klaenhammer, Todd R.] North Carolina State Univ, Dept Food Bioproc & Nutr Sci, Raleigh, NC 27695 USA. [Klaenhammer, Todd R.] North Carolina State Univ, Southeast Dairy Foods Res Ctr, Raleigh, NC 27695 USA. RP Klaenhammer, TR (reprint author), North Carolina State Univ, Dept Food Bioproc & Nutr Sci, Raleigh, NC 27695 USA.; Klaenhammer, TR (reprint author), North Carolina State Univ, Southeast Dairy Foods Res Ctr, Raleigh, NC 27695 USA. EM trk@unity.ncsu.edu NR 181 TC 0 Z9 0 U1 0 U2 0 PU JOHN WILEY & SONS LTD PI CHICHESTER PA THE ATRIUM, SOUTHERN GATE, CHICHESTER PO19 8SQ, WEST SUSSEX, ENGLAND BN 978-1-118-86837-9; 978-1-118-86840-9 PY 2016 BP 32 EP 54 PG 23 WC Biotechnology & Applied Microbiology; Nutrition & Dietetics SC Biotechnology & Applied Microbiology; Nutrition & Dietetics GA BF8CQ UT WOS:000384712800004 ER PT J AU Strybel, TZ Vu, KPL Chiappe, DL Morgan, CA Morales, G Battiste, V AF Strybel, Thomas Z. Vu, Kim-Phuong L. Chiappe, Dan L. Morgan, Corey A. Morales, Gregory Battiste, Vernol TI Effects of NextGen Concepts of Operation for Separation Assurance and Interval Management on Air Traffic Controller Situation Awareness, Workload, and Performance SO INTERNATIONAL JOURNAL OF AVIATION PSYCHOLOGY LA English DT Article AB Objective: Determine how combinations of NextGen-automation concepts for separation assurance and spacing affect air traffic controller (ATCo) situation awareness, workload, and performance.Background: In previous research, situation awareness was not measured with valid and reliable instruments. Previous work also evaluated separation assurance and spacing concepts individually, and did not examine weather.Method: Retired ATCos worked en route and transitional sectors. Four operating concepts for separation assurance and spacing were tested based on whether automation or ATCo was responsible for each function. Standard methods for assessing workload and situation awareness were used; performance measures included safety and efficiency.Results: Workload was lowest when both functions were automated; however, situation awareness depended on operating concept and sector. In the en route sector, the highest levels of situation awareness were found for ATCo-managed separation assurance and automation-managed spacing. In the transitional sector, the highest situation awareness occurred when ATCos performed both functions. The numbers of loss of separation were highest for ATCo-managed separation assurance; sector complexity depended on weather, but only for automation-managed separation assurance. Spacing efficiency was highest for ATCo-managed separation assurance, but more communications were required.Conclusion: In air traffic management, separation assurance and spacing functions interact with each other in determining ATCo workload, situation awareness, and performance, depending on sector characteristics and weather. Therefore, evaluations of NextGen-automation solutions must include multiple concepts of operation, and involve different sectors and environmental conditions. C1 [Strybel, Thomas Z.; Vu, Kim-Phuong L.; Chiappe, Dan L.; Morgan, Corey A.; Morales, Gregory] Calif State Univ Long Beach, Dept Psychol, 1250 North Bellflower Blvd, Long Beach, CA 90840 USA. [Battiste, Vernol] San Jose State Univ Fdn, San Jose, CA 95112 USA. [Battiste, Vernol] NASA Ames Res Ctr, Moffett Field, CA 94035 USA. RP Strybel, TZ (reprint author), Calif State Univ Long Beach, Dept Psychol, 1250 North Bellflower Blvd, Long Beach, CA 90840 USA. EM Thomas.Strybel@csulb.edu FU NASA [NNX09AU66A]; Group 5 University Research Center: Center for Human Factors in Advanced Aeronautics Technologies (Brenda Collins, Technical Monitor) FX This project was supported by NASA cooperative agreement NNX09AU66A, Group 5 University Research Center: Center for Human Factors in Advanced Aeronautics Technologies (Brenda Collins, Technical Monitor). NR 15 TC 0 Z9 0 U1 1 U2 1 PU TAYLOR & FRANCIS INC PI PHILADELPHIA PA 530 WALNUT STREET, STE 850, PHILADELPHIA, PA 19106 USA SN 1050-8414 EI 1532-7108 J9 INT J AVIAT PSYCHOL JI Int. J. Aviat. Psychol. PY 2016 VL 26 IS 1-2 BP 1 EP 14 DI 10.1080/10508414.2016.1235363 PG 14 WC Psychology, Applied SC Psychology GA EC2HO UT WOS:000387932200001 ER PT B AU Xiong, XX King, MD Salomonson, VV Barnes, WL Wenny, BN Angal, A Wu, AS Madhavan, S Link, DO AF Xiong, Xiaoxiong King, Michael D. Salomonson, Vincent V. Barnes, William L. Wenny, Brian N. Angal, Amit Wu, Aisheng Madhavan, Sriharsha Link, Daniel O. BE Qian, SE TI Moderate Resolution Imaging Spectroradiometer on Terra and Aqua Missions SO OPTICAL PAYLOADS FOR SPACE MISSIONS LA English DT Article; Book Chapter ID REFLECTIVE SOLAR BANDS; THERMAL EMISSIVE BANDS; ON-ORBIT CALIBRATION; GREENLAND ICE-SHEET; SURFACE-TEMPERATURE; MODIS; PERFORMANCE; SATELLITE; OCEAN; SEA C1 [Xiong, Xiaoxiong] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [King, Michael D.] Univ Colorado Boulder, Lab Atmospher & Space Phys, Boulder, CO USA. [Salomonson, Vincent V.] Univ Utah, Salt Lake City, UT USA. [Barnes, William L.] Univ Maryland Baltimore Cty, Baltimore, MD 21228 USA. [Wenny, Brian N.; Wu, Aisheng; Link, Daniel O.] Sigma Space Corp, Lanham, MD USA. [Angal, Amit; Madhavan, Sriharsha] Sci Syst & Applicat Inc, Lanham, MD USA. [Madhavan, Sriharsha] George Mason Univ, Earth Syst & Geoinformat Sci, Fairfax, VA 22030 USA. RP Xiong, XX (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RI King, Michael/C-7153-2011 OI King, Michael/0000-0003-2645-7298 NR 53 TC 1 Z9 1 U1 0 U2 0 PU JOHN WILEY & SONS LTD PI CHICHESTER PA THE ATRIUM, SOUTHERN GATE, CHICHESTER PO19 8SQ, WEST SUSSEX, ENGLAND BN 978-1-118-94526-1; 978-1-118-94514-8 PY 2016 BP 53 EP 89 PG 37 WC Engineering, Aerospace; Instruments & Instrumentation; Optics; Imaging Science & Photographic Technology SC Engineering; Instruments & Instrumentation; Optics; Imaging Science & Photographic Technology GA BF8XK UT WOS:000385248800004 ER PT S AU Szubert, M Kodali, A Ganguly, S Das, K Bongard, JC AF Szubert, Marcin Kodali, Anuradha Ganguly, Sangram Das, Kamalika Bongard, Josh C. BE Handl, J Hart, E Lewis, PR LopezIbanez, M Ochoa, G Paechter, B TI Semantic Forward Propagation for Symbolic Regression SO PARALLEL PROBLEM SOLVING FROM NATURE - PPSN XIV SE Lecture Notes in Computer Science LA English DT Proceedings Paper CT 14th International Conference on Parallel Problem Solving from Nature (PPSN) CY SEP 17-21, 2016 CL Edinburgh, ENGLAND SP Edinburgh Napier Univ, Edinburgh Napier Univ, Sch Comp DE Genetic programming; Program semantics; Semantic backpropagation; Problem decomposition; Symbolic regression AB In recent years, a number of methods have been proposed that attempt to improve the performance of genetic programming by exploiting information about program semantics. One of the most important developments in this area is semantic backpropagation. The key idea of this method is to decompose a program into two parts-a subprogram and a context-and calculate the desired semantics of the subprogram that would make the entire program correct, assuming that the context remains unchanged. In this paper we introduce Forward Propagation Mutation, a novel operator that relies on the opposite assumption-instead of preserving the context, it retains the subprogram and attempts to place it in the semantically right context. We empirically compare the performance of semantic backpropagation and forward propagation operators on a set of symbolic regression benchmarks. The experimental results demonstrate that semantic forward propagation produces smaller programs that achieve significantly higher generalization performance. C1 [Szubert, Marcin; Bongard, Josh C.] Univ Vermont, Burlington, VT 05405 USA. [Kodali, Anuradha; Das, Kamalika] Univ Calif Santa Cruz, Santa Cruz, CA 95064 USA. [Kodali, Anuradha; Ganguly, Sangram; Das, Kamalika] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Ganguly, Sangram] Bay Area Environm Res Inst, Petaluma, CA 94952 USA. RP Szubert, M (reprint author), Univ Vermont, Burlington, VT 05405 USA. EM Marcin.Szubert@uvm.edu NR 15 TC 0 Z9 0 U1 0 U2 0 PU SPRINGER INT PUBLISHING AG PI CHAM PA GEWERBESTRASSE 11, CHAM, CH-6330, SWITZERLAND SN 0302-9743 BN 978-3-319-45823-6; 978-3-319-45822-9 J9 LECT NOTES COMPUT SC PY 2016 VL 9921 BP 364 EP 374 DI 10.1007/978-3-319-45823-6_34 PG 11 WC Computer Science, Artificial Intelligence; Computer Science, Theory & Methods SC Computer Science GA BG3KE UT WOS:000387962100034 ER PT B AU Cellucci, D Cheung, KC AF Cellucci, Daniel Cheung, Kenneth C. GP ASME TI EVALUATION OF CELLULAR SOLIDS DERIVED FROM TRIPLY PERIODIC MINIMAL SURFACES SO PROCEEDINGS OF THE ASME 11TH INTERNATIONAL MANUFACTURING SCIENCE AND ENGINEERING CONFERENCE, 2016, VOL 2 LA English DT Proceedings Paper CT 11th ASME International Manufacturing Science and Engineering Conference (MSEC 2016) CY JUN 27-JUL 01, 2016 CL Blacksburg, VA SP ASME, Mfg Engn Div ID LATTICES AB Cellular solids are a class of materials that have many interesting engineering applications, including ultralight structural materials [1]. The traditional method for analyzing these solids uses convex uniform polyhedral honeycombs to represent the geometry of the material [2], and this approach has carried over into the design of digital cellular solids [3]. However; the use of such honeycomb-derived lattices makes the problem of decomposing a three-dimensional lattice into a library of two-dimensional parts non-trivial. We introduce a method for generating periodic frameworks from Triply Periodic Minimal Surfaces (TPMS), which result in geometries that are easier to decompose into digital parts. Additionally, we perform multi scale analysis of two cellular solids generated from two TPMS, the P- and D-Schwarz, and two cellular solids, the Kelvin and Octet honeycombs. We show that the simulated behavior of these TMPS-derived structures shows the expected modulus of the cellular solid scaling linearly with relative density, and matches the behavior of the octet truss. C1 [Cellucci, Daniel] Cornell Univ, Dept Mech & Aerosp Engn, Space Syst Design Studio, Ithaca, NY 14850 USA. [Cheung, Kenneth C.] NASA, Ames Res Ctr, Coded Struct Lab, Moffett Field, CA 94035 USA. RP Cellucci, D (reprint author), Cornell Univ, Dept Mech & Aerosp Engn, Space Syst Design Studio, Ithaca, NY 14850 USA. EM dwc238@cornell.edu; kenny@nasa.gov NR 15 TC 0 Z9 0 U1 0 U2 0 PU AMER SOC MECHANICAL ENGINEERS PI NEW YORK PA THREE PARK AVENUE, NEW YORK, NY 10016-5990 USA BN 978-0-7918-4990-3 PY 2016 AR UNSP V002T01A020 PG 6 WC Engineering, Biomedical; Engineering, Manufacturing; Engineering, Mechanical; Materials Science, Multidisciplinary SC Engineering; Materials Science GA BG3QX UT WOS:000388159400020 ER PT B AU Jenett, B Cellucci, D Gregg, C Cheung, K AF Jenett, Benjamin Cellucci, Daniel Gregg, Christine Cheung, Kenneth GP ASME TI MESO-SCALE DIGITAL MATERIALS: MODULAR, RECONFIGURABLE, LATTICE-BASED STRUCTURES SO PROCEEDINGS OF THE ASME 11TH INTERNATIONAL MANUFACTURING SCIENCE AND ENGINEERING CONFERENCE, 2016, VOL 2 LA English DT Proceedings Paper CT 11th ASME International Manufacturing Science and Engineering Conference (MSEC) CY JUN 27-JUL 01, 2016 CL Blacksburg, VA SP ASME, Mfg Engn Div AB We present a modular, reconfigurable system for building large structures. This system uses discrete lattice elements, called digital materials, to reversibly assemble ultralight structures that are 99.7% air and yet maintain sufficient specific stiffness for a variety of structural applications and loading scenarios. Design, manufacturing, and characterization of modular building blocks are described, including struts, nodes, joints, and build strategies. Simple case studies are shown using the same building blocks in three different scenarios: a bridge, a boat, and a shelter. Field implementation and demonstration is supplemented by experimental data and numerical simulation. A simplified approach for analyzing these structures is presented which shows good agreement with experimental results. C1 [Jenett, Benjamin] MIT, Ctr Bits & Atoms, 77 Massachusetts Ave, Cambridge, MA 02139 USA. [Cellucci, Daniel] Cornell Univ, Dept Mech Engn, Ithaca, NY USA. [Gregg, Christine] Univ Calif Berkeley, Dept Mech Engn, Berkeley, CA USA. [Cheung, Kenneth] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Jenett, B (reprint author), MIT, Ctr Bits & Atoms, 77 Massachusetts Ave, Cambridge, MA 02139 USA. NR 27 TC 0 Z9 0 U1 0 U2 0 PU AMER SOC MECHANICAL ENGINEERS PI NEW YORK PA THREE PARK AVENUE, NEW YORK, NY 10016-5990 USA BN 978-0-7918-4990-3 PY 2016 AR UNSP V002T01A018 PG 11 WC Engineering, Biomedical; Engineering, Manufacturing; Engineering, Mechanical; Materials Science, Multidisciplinary SC Engineering; Materials Science GA BG3QX UT WOS:000388159400018 ER PT S AU Badger, J Gooding, D Ensley, K Hambuchen, K Thackston, A AF Badger, Julia Gooding, Dustin Ensley, Kody Hambuchen, Kimberly Thackston, Allison BE Koubaa, A TI ROS in Space: A Case Study on Robonaut 2 SO ROBOT OPERATING SYSTEM (ROS): THE COMPLETE REFERENCE, VOL 1 SE Studies in Computational Intelligence LA English DT Article; Book Chapter DE Space robotics; Safety architecture; Human-robot interaction AB Robonaut 2 (R2), an upper-body dexterous humanoid robot, was developed in a partnership between NASA and General Motors. R2 has been undergoing experimental trials on board the International Space Station (ISS) for more than two years, and has recently been integrated with a mobility platform. Once post-integration checkouts are complete, it will be able to maneuver around the ISS in order to complete tasks and continue to demonstrate new technical competencies for future extravehicular activities. The increase in capabilities requires a new software architecture, control and safety system. These have all been implemented in the ROS framework. This case study chapter will discuss R2's new software capabilities, user interfaces, and remote deployment and operation, and will include the safety certification path taken to be able to use ROS in space. C1 [Badger, Julia; Gooding, Dustin; Ensley, Kody; Hambuchen, Kimberly] NASA, Johnson Space Ctr, Houston, TX 77058 USA. [Thackston, Allison] Oceaneering Space Syst, Houston, TX 77058 USA. RP Badger, J (reprint author), NASA, Johnson Space Ctr, Houston, TX 77058 USA. EM julia.m.badger@nasa.gov; dustin.r.gooding@nasa.gov; kody.g.ensley@nasa.gov; kimberly.a.hambuchen@nasa.gov; allison.thackston@nasa.gov NR 10 TC 0 Z9 0 U1 1 U2 1 PU SPRINGER-VERLAG BERLIN PI BERLIN PA HEIDELBERGER PLATZ 3, D-14197 BERLIN, GERMANY SN 1860-949X BN 978-3-319-26054-9; 978-3-319-26052-5 J9 STUD COMPUT INTELL PY 2016 VL 625 BP 343 EP 373 DI 10.1007/978-3-319-26054-9_13 D2 10.1007/978-3-319-26054-9 PG 31 WC Computer Science, Artificial Intelligence; Computer Science, Software Engineering; Robotics SC Computer Science; Robotics GA BF9BB UT WOS:000385406900014 ER PT J AU Gordon, PV Hegde, UG Hicks, MC Kulis, MJ AF Gordon, Peter V. Hegde, Uday G. Hicks, Michael C. Kulis, Michael J. TI ON AUTOIGNITION OF CO-FLOW LAMINAR JETS SO SIAM JOURNAL ON APPLIED MATHEMATICS LA English DT Article DE autoignition; hydrothermal flames; diffusion flames; heat equation; blow-up; thermal runaway ID HYDROTHERMAL FLAMES; COMBUSTION; IGNITION AB This paper is concerned with the derivation and mathematical analysis of a model for autoignition of laminar co-flow jets. Such jets consist of two parts: an inner part with oxidizer that is surrounded by an outer part with fuel, or the reverse. To derive a model we use a combination of Burke Schumann theory of diffusion flames and Semenov-Frank-Kamenerskii theory of thermal explosion. The main advantage of our model is that it gives a well-defined condition for autoignition of a jet. We provide detailed analysis of the model that reveals dependency of the autoignition position on principal physical and geometric parameters involved. Moreover, we give explicit expressions for autoignition position in asymptotic regimes relevant to applications. C1 [Gordon, Peter V.] Univ Akron, Dept Math, Akron, OH 44325 USA. [Hegde, Uday G.] Case Western Reserve Univ, Dept Mech & Aerosp Engn, Cleveland, OH 44106 USA. [Hicks, Michael C.; Kulis, Michael J.] NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Gordon, PV (reprint author), Univ Akron, Dept Math, Akron, OH 44325 USA. EM pgordon@uakron.edu; uday.g.hegde@nasa.gov; michael.c.hicks@nasa.gov; michael.j.kulis@nasa.gov NR 21 TC 0 Z9 0 U1 0 U2 0 PU SIAM PUBLICATIONS PI PHILADELPHIA PA 3600 UNIV CITY SCIENCE CENTER, PHILADELPHIA, PA 19104-2688 USA SN 0036-1399 EI 1095-712X J9 SIAM J APPL MATH JI SIAM J. Appl. Math. PY 2016 VL 76 IS 5 BP 2081 EP 2098 DI 10.1137/16M1073017 PG 18 WC Mathematics, Applied SC Mathematics GA EB4DM UT WOS:000387320100016 ER PT S AU Rose, G Nguyen, D Newman, B AF Rose, Geoffrey Duc Nguyen Newman, Brett GP IEEE TI Implementing an Arc-Length Method for a Robust Approach in Solving Systems of Nonlinear Equations SO SOUTHEASTCON 2016 SE IEEE SoutheastCon-Proceedings LA English DT Proceedings Paper CT SoutheastCon CY MAR 30-APR 03, 2016 CL Norfolk, VA DE Arc-Length Method; Nonlinear Equations; Iterative Solver AB Solving systems of nonlinear equations can be challenging and analysts are often required to provide an initial guess of the solution as a starting point for use in an iterative solver. Insight into approximate solutions leading to a good initial guess can usually be obtained if equations are representative of a physical system. However, this process may not be achievable for complex systems or when the analyst lacks familiarity or experience with the system. In this case, convergence may not be achieved if the initial guess is not close to the solution. A general nonlinear solver suite based on the arc-length method with these circumstances in mind was developed for the purpose of numerical experimentation and was found to be a useful alternative to the fsolve function inherent to the MATLAB software. Due to the additional unknown variable and supplemental constraint equation used by the arc-length method, curves representing solutions to example equation sets were found by embedding the solver in a loop. Restarts in the analysis were minimized as the arc-length method is capable of solving beyond local maxima or minima on smooth curves. Several examples are provided demonstrating the unique capabilities of arc-length solvers. C1 [Rose, Geoffrey] NASA, Struct Dynam Branch, Langley Res Ctr, Hampton, VA 23681 USA. [Duc Nguyen] Old Dominion Univ, Batten Coll Engn & Technol, Dept Civil & Environm Engn, Norfolk, VA 23529 USA. [Newman, Brett] Old Dominion Univ, Batten Coll Engn & Technol, Dept Mech & Aerosp Engn, Norfolk, VA 23529 USA. [Rose, Geoffrey] Old Dominion Univ, Norfolk, VA 23529 USA. RP Rose, G (reprint author), NASA, Struct Dynam Branch, Langley Res Ctr, Hampton, VA 23681 USA.; Rose, G (reprint author), Old Dominion Univ, Norfolk, VA 23529 USA. NR 15 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1558-058X BN 978-1-5090-2246-5 J9 IEEE SOUTHEASTCON PY 2016 PG 5 WC Computer Science, Theory & Methods; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BG1SG UT WOS:000387067900047 ER PT S AU Berry, CPL Farr, B Farr, WM Haster, CJ Mandel, I Middleton, H Singer, LP Urban, AL Vecchio, A Vitale, S Cannon, K Graff, PB Hanna, C Mohapatra, S Pankow, C Price, LR Sidery, T Veitch, J AF Berry, C. P. L. Farr, B. Farr, W. M. Haster, C-J Mandel, I. Middleton, H. Singer, L. P. Urban, A. L. Vecchio, A. Vitale, S. Cannon, K. Graff, P. B. Hanna, C. Mohapatra, S. Pankow, C. Price, L. R. Sidery, T. Veitch, J. BE Lee, HM Oh, J TI Early Advanced LIGO binary neutron-star sky localization and parameter estimation SO 11TH EDOARDO AMALDI CONFERENCE ON GRAVITATIONAL WAVES (AMALDI 11) SE Journal of Physics Conference Series LA English DT Proceedings Paper CT 11th Edoardo Amaldi Conference on Gravitational Waves (AMALDI) CY JUN 21-26, 2015 CL Gwangju, SOUTH KOREA SP Int Union Pure & Appl Phys, Korean Astron Soc, Korean Phys Soc, Korean Federat Sci & Technol, Natl Res Fdn, Korea Tourism Organism, Gwangju Convent Bur ID GRAVITATIONAL-WAVES; VIRGO AB 2015 will see the first observations of Advanced LIGO and the start of the gravitational-wave (GW) advanced-detector era. One of the most promising sources for ground based GW detectors are binary neutron-star (BNS) coalescences. In order to use any detections for astrophysics, we must understand the capabilities of our parameter-estimation analysis. By simulating the GWs from an astrophysically motivated population of BNSs, we examine the accuracy of parameter inferences in the early advanced-detector era. We find that sky location, which is important for electromagnetic follow-up, can be determined rapidly ( similar to 5 s), but that sky areas may be hundreds of square degrees. The degeneracy between component mass and spin means there is significant uncertainty for measurements of the individual masses and spins; however, the chirp mass is well measured (typically better than 0.1%). C1 [Berry, C. P. L.; Farr, W. M.; Haster, C-J; Mandel, I.; Middleton, H.; Vecchio, A.; Sidery, T.; Veitch, J.] Univ Birmingham, Sch Phys & Astron, Birmingham B15 2TT, W Midlands, England. [Farr, B.] Univ Chicago, Enrico Fermi Inst, Chicago, IL 60637 USA. [Singer, L. P.] NASA, Goddard Space Flight Ctr, Astrophys Sci Div, Greenbelt, MD 20771 USA. [Urban, A. L.; Pankow, C.] Univ Wisconsin, Leonard E Parker Ctr Gravitat Cosmol & Astrophys, Milwaukee, WI 53201 USA. [Vitale, S.; Mohapatra, S.] MIT, 185 Albany St, Cambridge, MA 02139 USA. [Cannon, K.] Univ Toronto, Canadian Inst Theoret Astrophys, 60 St George St, Toronto, ON M5S 3H8, Canada. [Graff, P. B.] Univ Maryland, Dept Phys, College Pk, MD 20742 USA. [Graff, P. B.] NASA, Goddard Space Flight Ctr, Gravitat Astrophys Lab, Greenbelt, MD 20771 USA. [Hanna, C.] Perimeter Inst Theoret Phys, Waterloo, ON N2L 2Y5, Canada. [Hanna, C.] Penn State Univ, University Pk, PA 16802 USA. [Mohapatra, S.] Syracuse Univ, Syracuse, NY 13244 USA. [Price, L. R.] CALTECH, LIGO Lab, Pasadena, CA 91125 USA. RP Berry, CPL (reprint author), Univ Birmingham, Sch Phys & Astron, Birmingham B15 2TT, W Midlands, England. EM cplb@star.sr.bham.ac.uk RI Vecchio, Alberto/F-8310-2015; OI Vecchio, Alberto/0000-0002-6254-1617; Farr, Ben/0000-0002-2916-9200; Berry, Christopher/0000-0003-3870-7215; Mandel, Ilya/0000-0002-6134-8946; Veitch, John/0000-0002-6508-0713 NR 20 TC 0 Z9 0 U1 0 U2 0 PU IOP PUBLISHING LTD PI BRISTOL PA DIRAC HOUSE, TEMPLE BACK, BRISTOL BS1 6BE, ENGLAND SN 1742-6588 J9 J PHYS CONF SER PY 2016 VL 716 AR UNSP 012031 DI 10.1088/1742-6596/716/1/012031 PG 4 WC Astronomy & Astrophysics; Physics, Multidisciplinary; Physics, Particles & Fields SC Astronomy & Astrophysics; Physics GA BG1PT UT WOS:000386960500031 ER PT S AU Dolch, T Ellis, JA Chatterjee, S Cordes, JM Lam, MT Bassa, C Bhattacharyya, B Champion, DJ Cognard, I Crowter, K Demorest, PB Hessels, JWT Janssen, G Jenet, FA Jones, G Jordan, C Karuppusamy, R Keith, M Kondratiev, VI Kramer, M Lazarus, P Lazio, TJW Lorimer, DR Madison, DR McLaughlin, MA Palliyaguru, N Perrodin, D Ransom, SM Roy, J Shannon, RM Smits, R Stairs, IH Stappers, BW Stinebring, DR Stovall, K Verbiest, JPW Zhu, WW AF Dolch, T. Ellis, J. A. Chatterjee, S. Cordes, J. M. Lam, M. T. Bassa, C. Bhattacharyya, B. Champion, D. J. Cognard, I. Crowter, K. Demorest, P. B. Hessels, J. W. T. Janssen, G. Jenet, F. A. Jones, G. Jordan, C. Karuppusamy, R. Keith, M. Kondratiev, V. I. Kramer, M. Lazarus, P. Lazio, T. J. W. Lorimer, D. R. Madison, D. R. McLaughlin, M. A. Palliyaguru, N. Perrodin, D. Ransom, S. M. Roy, J. Shannon, R. M. Smits, R. Stairs, I. H. Stappers, B. W. Stinebring, D. R. Stovall, K. Verbiest, J. P. W. Zhu, W. W. CA NANOGrav Collaboration BE Lee, HM Oh, J TI Single-Source Gravitational Wave Limits From the J1713+0747 24-hr Global Campaign SO 11TH EDOARDO AMALDI CONFERENCE ON GRAVITATIONAL WAVES (AMALDI 11) SE Journal of Physics Conference Series LA English DT Proceedings Paper CT 11th Edoardo Amaldi Conference on Gravitational Waves (AMALDI) CY JUN 21-26, 2015 CL Gwangju, SOUTH KOREA SP Int Union Pure & Appl Phys, Korean Astron Soc, Korean Phys Soc, Korean Federat Sci & Technol, Natl Res Fdn, Korea Tourism Organism, Gwangju Convent Bur ID PULSAR TIMING ARRAY; BLACK-HOLE BINARIES; DATA SET; SYSTEM AB Dense, continuous pulsar timing observations over a 24-hr period provide a method for probing intermediate gravitational wave (GW) frequencies from 10 microhertz to 20 millihertz. The European Pulsar Timing Array (EPTA), the North American Nanohertz Observatory for Gravitational Waves (NANOGrav), the Parkes Pulsar Timing Array (PPTA), and the combined International Pulsar Timing Array (IPTA) all use millisecond pulsar observations to detect or constrain GWs typically at nanohertz frequencies. In the case of the IPTA's nine-telescope 24-Hour Global Campaign on millisecond pulsar J1713+0747, GW limits in the intermediate frequency regime can be produced. The negligible change in dispersion measure during the observation minimizes red noise in the timing residuals, constraining any contributions from GWs due to individual sources. At 10(-5) Hz, the 95% upper limit on strain is 10(-11) for GW sources in the pulsar's direction. C1 [Dolch, T.] Hillsdale Coll, Dept Phys, 33 E Coll St, Hillsdale, MI 49242 USA. [Dolch, T.; Chatterjee, S.; Cordes, J. M.; Madison, D. R.] Cornell Univ, Dept Astron, Ithaca, NY 14853 USA. [Ellis, J. A.; Lazio, T. J. W.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91106 USA. [Bassa, C.; Hessels, J. W. T.; Janssen, G.; Kondratiev, V. I.; Smits, R.] Netherlands Inst Radio Astron, ASTRON, Postbus 2, NL-7990 AA Dwingeloo, Netherlands. [Bassa, C.; Bhattacharyya, B.; Jordan, C.; Keith, M.; Roy, J.; Stappers, B. W.] Univ Manchester, Sch Phys & Astron, Jodrell Bank Ctr Astrophys, Manchester M13 9PL, Lancs, England. [Champion, D. J.; Karuppusamy, R.; Kramer, M.; Lazarus, P.; Zhu, W. W.] Max Planck Inst Radioastron, Hugel 69, D-53121 Bonn, Germany. [Cognard, I.] CNRS, UMR 6115 LPC2E, Lab Phys & Chim Environm & Espace, F-45071 Orleans 02, France. [Cognard, I.] CNRS INSU, Observ Paris, Stn Radioastron Nancay, F-18330 Nancay, France. [Crowter, K.; Stairs, I. H.] Univ British Columbia, Dept Phys & Astron, 6224 Agr Rd, Vancouver, BC V6T 1Z1, Canada. [Demorest, P. B.] Natl Radio Astron Observ, 1003 Lopezville Rd, Socorro, NM 87801 USA. [Hessels, J. W. T.] Univ Amsterdam, Astron Inst Anton Pannekoek, Sci Pk 904, NL-1098 XH Amsterdam, Netherlands. [Jenet, F. A.] Univ Texas Brownsville, Ctr Adv Radio Astron, Brownsville, TX 78520 USA. [Jones, G.] Columbia Univ, Columbia Astrophys Lab, New York, NY 10027 USA. [Kondratiev, V. I.] Lebedev Phys Inst, Ctr Astro Space, Profsoyuznaya Str 84-32, Moscow 117997, Russia. [Kramer, M.] Univ Manchester, Jodrell Bank Observ, Macclesfield SK11 9DL, Cheshire, England. [Lorimer, D. R.; McLaughlin, M. A.; Palliyaguru, N.] West Virginia Univ, Dept Phys & Astron, Morgantown, WV 26506 USA. [Madison, D. R.; Ransom, S. M.] Natl Radio Astron Observ, 520 Edgemont Rd, Charlottesville, VA 22901 USA. [Perrodin, D.] INAF Osservatorio Astron Cagliari, Via Sci 5, I-09047 Selargius, CA, Italy. [Roy, J.] Tata Inst Fundamental Res, Natl Ctr Radio Astrophys, Pune 411007, Maharashtra, India. [Shannon, R. M.] Australia Telescope Natl Facil, CSIRO Astron & Space Sci, POB 76, Epping, NSW 1710, Australia. [Stinebring, D. R.] Oberlin Coll, Dept Phys & Astron, Oberlin, OH 44074 USA. [Stovall, K.] Univ New Mexico, Dept Phys & Astron, 1919 Lomas Blvd NE, Albuquerque, NM 87131 USA. [Verbiest, J. P. W.] Univ Bielefeld, Fak Phys, Postfach 100131, D-33501 Bielefeld, Germany. RP Dolch, T (reprint author), Hillsdale Coll, Dept Phys, 33 E Coll St, Hillsdale, MI 49242 USA.; Dolch, T (reprint author), Cornell Univ, Dept Astron, Ithaca, NY 14853 USA. EM tdolch@hillsdale.edu NR 23 TC 0 Z9 0 U1 0 U2 0 PU IOP PUBLISHING LTD PI BRISTOL PA DIRAC HOUSE, TEMPLE BACK, BRISTOL BS1 6BE, ENGLAND SN 1742-6588 J9 J PHYS CONF SER PY 2016 VL 716 AR UNSP 012014 DI 10.1088/1742-6596/716/1/012014 PG 4 WC Astronomy & Astrophysics; Physics, Multidisciplinary; Physics, Particles & Fields SC Astronomy & Astrophysics; Physics GA BG1PT UT WOS:000386960500014 ER PT S AU Ikpe, SA Lauenstein, JM Carr, GA Hunter, D Ludwig, LL Wood, W Iannello, CJ Del Castillo, LY Fitzpatrick, FD Mojarradi, MM Chen, Y AF Ikpe, Stanley A. Lauenstein, Jean-Marie Carr, Gregory A. Hunter, Don Ludwig, Lawrence L. Wood, William Iannello, Christopher J. Del Castillo, Linda Y. Fitzpatrick, Fred D. Mojarradi, Mohammad M. Chen, Yuan GP IEEE TI Long-Term Reliability of a Hard-Switched Boost Power Processing Unit Utilizing SiC Power MOSFETs SO 2016 IEEE INTERNATIONAL RELIABILITY PHYSICS SYMPOSIUM (IRPS) SE International Reliability Physics Symposium LA English DT Proceedings Paper CT IEEE International Reliability Physics Symposium (IRPS) CY APR 17-21, 2016 CL Pasadena, CA SP IEEE DE SiC; Power MOSFETs; Boost; PPU; high temperature; HTGB; HTRB; SEE; radiation; SEB; SEGR AB Silicon carbide (SiC) power devices have demonstrated many performance advantages over their silicon (Si) counterparts. As the inherent material limitations of Si devices are being swiftly realized, wide-bandgap (WBG) materials such as SiC have become increasingly attractive for high power applications. In particular, SiC power metal oxide semiconductor field effect transistors' (MOSFETs) high breakdown field tolerance, superior thermal conductivity and low-resistivity drift regions make these devices an excellent candidate for power dense, low loss, high frequency switching applications in extreme environment conditions. In this paper, a novel power processing unit (PPU) architecture is proposed utilizing commercially available 4H-SiC power MOSFETs from CREE Inc. A multiphase straight boost converter topology is implemented to supply up to 10 kW full-scale. High Temperature Gate Bias (HTGB) and High Temperature Reverse Bias (HTRB) characterization is performed to evaluate the long-term reliability of both the gate oxide and the body diode of the SiC components. Finally, susceptibility of the CREE SiC MOSFETs to damaging effects from heavy-ion radiation representative of the on-orbit galactic cosmic ray environment are explored. The results provide the baseline performance metrics of operation as well as demonstrate the feasibility of a hard-switched PPU in harsh environments. C1 [Ikpe, Stanley A.; Wood, William; Fitzpatrick, Fred D.; Chen, Yuan] NASA, Langley Res Ctr, Hampton, VA 23681 USA. [Lauenstein, Jean-Marie] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Carr, Gregory A.; Hunter, Don; Del Castillo, Linda Y.; Mojarradi, Mohammad M.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Ludwig, Lawrence L.; Iannello, Christopher J.] NASA, Kennedy Space Ctr, FL 32899 USA. RP Ikpe, SA (reprint author), NASA, Langley Res Ctr, Hampton, VA 23681 USA. NR 23 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1541-7026 BN 978-1-4673-9136-8 J9 INT RELIAB PHY SYM PY 2016 PG 8 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BG1WP UT WOS:000387121900107 ER PT S AU Li, Y Sheldon, DJ Ramos, AS Bruck, J AF Li, Yue Sheldon, Douglas J. Ramos, Andre S. Bruck, Jehoshua GP IEEE TI Error Characterization and Mitigation for 16nm MLC NAND Flash Memory under Total Ionizing Dose Effect SO 2016 IEEE INTERNATIONAL RELIABILITY PHYSICS SYMPOSIUM (IRPS) SE International Reliability Physics Symposium LA English DT Proceedings Paper CT IEEE International Reliability Physics Symposium (IRPS) CY APR 17-21, 2016 CL Pasadena, CA SP IEEE DE Characterization; NAND flash memories; radiation effects; reliability; total ionizing dose effect AB This paper studies the system-level reliability of 16nm MLC NAND flash memories under total ionizing dose (TID) effect. Errors that occur in the parts under TID effect are characterized at multiple levels. Results show that faithful data recovery only lasts until 9k rad. Data errors observed in irradiated flash samples are strongly asymmetric. To improve the reliability of the parts, we study error mitigation methods that consider the specific properties of TID errors. First, we implement a novel data representation scheme that stores data using the relative order of cell voltages. The representation is more robust against uniform asymmetric threshold voltage shift of floating gates. Experimental results show that the scheme reduces errors at least by 50% for blocks with less than 3k program/erase cycles and 10k rad. Second, we conduct empirical evaluations of memory scrubbing schemes. Based on the results, we identify a scheme that refreshes cells without doing block erasure. Evaluation results show that parts under this scrubbing scheme survive up to 8k PECs and 57k rad total doses. C1 [Li, Yue; Ramos, Andre S.; Bruck, Jehoshua] CALTECH, EE Dept, Pasadena, CA 91125 USA. [Sheldon, Douglas J.] CALTECH, Jet Prop Lab, Pasadena, CA USA. RP Li, Y (reprint author), CALTECH, EE Dept, Pasadena, CA 91125 USA. EM yli@caltech.edu; douglas.j.sheldon@jpl.nasa.gov; asramos@caltech.edu; bruck@caltech.edu NR 11 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1541-7026 BN 978-1-4673-9136-8 J9 INT RELIAB PHY SYM PY 2016 PG 6 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BG1WP UT WOS:000387121900135 ER PT S AU Perez, R AF Perez, Reinaldo GP IEEE TI Analysis and Effects of Space Radiation Induced Single Event Transients SO 2016 IEEE INTERNATIONAL SYMPOSIUM ON ELECTROMAGNETIC COMPATIBILITY (EMC) SE IEEE International Symposium on Electromagnetic Compatibility LA English DT Proceedings Paper CT IEEE International Symposium on Electromagnetic Compatibility (EMC) CY JUL 25-29, 2016 CL Ottawa, CANADA SP IEEE Electromagnet Compatibil Soc AB Spacecraft electronics are affected by the space radiation environment. Among the different types of radiation effects that can affect spacecraft electronics is the single event transients. The space environment is responsible for many of the single event transients which can upset the performance of the spacecraft avionics hardware. In this paper we first explore the origins of single event transients, then illustrate the bahaviors of a single event transient in a digital circuit. We then provide a discussion concerning propagation of a single event transient event at the local, subsystem, and system level. The final goal of the paper is to provide a qualitatively methodology for asessing single event transients and its effects so that spacecraft avionics engineers can develop either hardware or software coutermeasures in their designs. C1 [Perez, Reinaldo] Jet Prop Lab, Elect Prod Reliabil Grp, Pasadena, CA 91109 USA. RP Perez, R (reprint author), Jet Prop Lab, Elect Prod Reliabil Grp, Pasadena, CA 91109 USA. NR 4 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2158-110X BN 978-1-5090-1441-5 J9 IEEE INT SYMP ELEC PY 2016 BP 126 EP 131 PG 6 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BG1WI UT WOS:000387117700046 ER PT S AU McCloskey, J AF McCloskey, John GP IEEE TI EMC Testing on the Integrated Science Instrument Module (ISIM) A Summary of the EMC Test Campaign for the Science Payload of the James Webb Space Telescope (JWST) SO 2016 IEEE INTERNATIONAL SYMPOSIUM ON ELECTROMAGNETIC COMPATIBILITY (EMC) SE IEEE International Symposium on Electromagnetic Compatibility LA English DT Proceedings Paper CT IEEE International Symposium on Electromagnetic Compatibility (EMC) CY JUL 25-29, 2016 CL Ottawa, CANADA SP IEEE Electromagnet Compatibil Soc AB This paper describes the electromagnetic compatibility (EMC) tests performed on the Integrated Science Instrument Module (ISIM), the science payload of the James Webb Space Telescope (JWST), at NASA's Goddard Space Flight Center (GSFC) in August 2015. By its very nature of being an integrated payload, it could be treated as neither a unit level test nor an integrated spacecraft/observatory test. Non-standard test criteria are described along with non-standard test methods that had to be developed in order to evaluate them. Results are presented to demonstrate that all test criteria were met in less than the time allocated. C1 [McCloskey, John] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP McCloskey, J (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. EM John.C.McCloskey@nasa.gov NR 0 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2158-110X BN 978-1-5090-1441-5 J9 IEEE INT SYMP ELEC PY 2016 BP 138 EP 143 PG 6 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BG1WI UT WOS:000387117700048 ER PT S AU Decrossas, E Reck, T Lee, C Jung-Kubiak, C Mehdi, I Chattopadhyay, G AF Decrossas, Emmanuel Reck, Theodore Lee, Choonsup Jung-Kubiak, Cecile Mehdi, Imran Chattopadhyay, Goutam GP IEEE TI Evaluation of 3D Printing Technology for Corrugated Horn Antenna Manufacturing SO 2016 IEEE INTERNATIONAL SYMPOSIUM ON ELECTROMAGNETIC COMPATIBILITY (EMC) SE IEEE International Symposium on Electromagnetic Compatibility LA English DT Proceedings Paper CT IEEE International Symposium on Electromagnetic Compatibility (EMC) CY JUL 25-29, 2016 CL Ottawa, CANADA SP IEEE Electromagnet Compatibil Soc DE 3-D printing; corrugated horn.; metal sintering; horn; surface roughness; waveguide attenuation; W-band; WR-10 waveguide AB We report on the performance of waveguide components at W-band manufactured with 3-D printing technology. The precision and surface roughness of the various techniques are studied to determine the applicability of millimeter-wave components. The best waveguide attenuation measured of 0.014 dB/mm is still three times higher than for metal WR-10 waveguides. Full-wave simulations and surface roughness analysis show that performance can be improved by changing the orientation of the parts in the printer. The performance of a multi flare angle and corrugated horn antennas is evaluated. C1 [Decrossas, Emmanuel; Reck, Theodore; Lee, Choonsup; Jung-Kubiak, Cecile; Mehdi, Imran; Chattopadhyay, Goutam] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Decrossas, E (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Emmanuel.Decrossas@jpl.nasa.gov NR 12 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2158-110X BN 978-1-5090-1441-5 J9 IEEE INT SYMP ELEC PY 2016 BP 251 EP 255 PG 5 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BG1WI UT WOS:000387117700068 ER PT S AU Terseck, A Trout, D AF Terseck, Alex Trout, Dawn GP IEEE TI Investigation on Improvements in Lightning Retest Criteria for Spacecraft SO 2016 IEEE INTERNATIONAL SYMPOSIUM ON ELECTROMAGNETIC COMPATIBILITY (EMC) SE IEEE International Symposium on Electromagnetic Compatibility LA English DT Proceedings Paper CT IEEE International Symposium on Electromagnetic Compatibility (EMC) CY JUL 25-29, 2016 CL Ottawa, CANADA SP IEEE Electromagnet Compatibil Soc DE nearby lightning; coupling; ring criteria; spacecraft; launch complex; transmission line matrix method AB Spacecraft are generally protected from a direct strike by launch the vehicle and ground structures, but protocols to evaluate the impact of nearby strikes are not consistent. Often spacecraft rely on the launch vehicle constraints to trigger a retest, but launch vehicles can typically evaluate the impact of a strike within minutes while spacecraft evaluation times can be on the order of hours or even days. For launches at the Kennedy Space Center where lightning activity is among the highest in the United States, this evaluation related delay could be costly with the possibility of missing the launch window altogether. This paper evaluated available data from local lightning measurements systems and computer simulations to predict the coupled effect from various nearby strikes onto a typical payload umbilical. Recommendations are provided to reduce the typical trigger criteria and costly delays. C1 [Terseck, Alex] Ai Solut, Kennedy Space Ctr, Ksc, FL 32899 USA. [Trout, Dawn] NASA, Kennedy Space Ctr, Ksc, FL USA. RP Terseck, A (reprint author), Ai Solut, Kennedy Space Ctr, Ksc, FL 32899 USA. EM alex.m.terseck@nasa.gov; dawn.h.trout@nasa.gov NR 14 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2158-110X BN 978-1-5090-1441-5 J9 IEEE INT SYMP ELEC PY 2016 BP 731 EP 736 PG 6 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BG1WI UT WOS:000387117700154 ER PT S AU Edwards, P Terseck, A Trout, D AF Edwards, Paul Terseck, Alex Trout, Dawn GP IEEE TI Evaluation of transient pin-stress requirements for spacecraft launching in Lightning environments. Pain Free Analysis to alleviate those Pin Stress Headaches SO 2016 IEEE INTERNATIONAL SYMPOSIUM ON ELECTROMAGNETIC COMPATIBILITY (EMC) SE IEEE International Symposium on Electromagnetic Compatibility LA English DT Proceedings Paper CT IEEE International Symposium on Electromagnetic Compatibility (EMC) CY JUL 25-29, 2016 CL Ottawa, CANADA SP IEEE Electromagnet Compatibil Soc DE induced transient effects; lightning coupling; re-test criteria; spacecraft; launch complex; transmission line matrix method AB Spacecraft are generally protected from direct lightning attachment by encapsulation within the payload fairing of a launch vehicle and the ground structures that exist at the launch site. Regardless of where lightning strikes, potentially damaging indirect effects prevail from the coupling of electromagnetic fields into a loop created by outer shield of the payload umbilical. The energy coupled into individual spacecraft circuits is dependent on the umbilical current drive, the cable transfer impedance and the source/ load circuitry, and the reference potential used. Lightning induced transient susceptibility of the spacecraft avionics needs to be fully understood in order to define realistic re-test criteria in the event of a lightning occurrence during the launch campaign. Use of standards such as RTCA/DO-160 & SAE 5412 has some applicability but do not represent the indirect environment adequately. This paper evaluates the launch pad environments, the measurement data available, and computer simulations to provide pain-free analysis to alleviate the transient pin-stress headaches for spacecraft launching in Lightning environments. C1 [Edwards, Paul; Terseck, Alex] Ai Solut, Kennedy Space Ctr, Ksc, FL 32899 USA. [Trout, Dawn] NASA, Kennedy Space Ctr, Ksc, FL USA. RP Edwards, P (reprint author), Ai Solut, Kennedy Space Ctr, Ksc, FL 32899 USA. EM paul.edwards@nasa.gov; alex.m.terseck@nasa.gov; dawn.h.trout@nasa.gov NR 9 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2158-110X BN 978-1-5090-1441-5 J9 IEEE INT SYMP ELEC PY 2016 BP 737 EP 742 PG 6 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BG1WI UT WOS:000387117700155 ER PT S AU Bremner, PG Vazquez, G Trout, DH Christiano, DJ AF Bremner, Paul G. Vazquez, Gabriel Trout, Dawn H. Christiano, Daniel J. GP IEEE TI Canonical Statistical Mode for Maximum Expected Immission of Wire Conductor in an Aperture Enclosure SO 2016 IEEE INTERNATIONAL SYMPOSIUM ON ELECTROMAGNETIC COMPATIBILITY (EMC) SE IEEE International Symposium on Electromagnetic Compatibility LA English DT Proceedings Paper CT IEEE International Symposium on Electromagnetic Compatibility (EMC) CY JUL 25-29, 2016 CL Ottawa, CANADA SP IEEE Electromagnet Compatibil Soc DE Statistical electromagnetics; Reverberant field; Immission; Emission; Maximum expected field strength; Stochastic EMC AB Prediction of the maximum expected electromagnetic pick-up of conductors inside a realistic shielding enclosure is an important canonical problem for system-level EMC design of space craft, launch vehicles, aircraft and automobiles. This paper introduces a simple statistical power balance model for prediction of the maximum expected current in a wire conductor inside an aperture enclosure. It calculates both the statistical mean and variance of the immission from the physical design parameters of the problem. Familiar probability density functions can then be used to predict the maximum expected immission for design purposes. The statistical power balance model requires minimal EMC design information and solves orders of magnitude faster than existing numerical models, making it ultimately viable for scaled-up, full system-level modeling. Both experimental test results and full wave simulation results are used to validate the foundational model. C1 [Bremner, Paul G.] Robust Phys, Del Mar, CA 92014 USA. [Vazquez, Gabriel; Trout, Dawn H.; Christiano, Daniel J.] NASA, Kennedy Space Ctr, Cape Canaveral, FL USA. RP Bremner, PG (reprint author), Robust Phys, Del Mar, CA 92014 USA. EM pbremner@robustphysics.com; gabriel.vazquez@nassa.gov NR 19 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2158-110X BN 978-1-5090-1441-5 J9 IEEE INT SYMP ELEC PY 2016 BP 758 EP 763 PG 6 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BG1WI UT WOS:000387117700159 ER PT S AU Gonzales, E Mewatters, D AF Gonzales, Edward Mewatters, Dalia GP IEEE TI Magnetic Shield. Design Modeling and. Validation for SWOT Spacecraft Ka-band Extended Interaction Klystron SO 2016 IEEE INTERNATIONAL SYMPOSIUM ON ELECTROMAGNETIC COMPATIBILITY (EMC) SE IEEE International Symposium on Electromagnetic Compatibility LA English DT Proceedings Paper CT IEEE International Symposium on Electromagnetic Compatibility (EMC) CY JUL 25-29, 2016 CL Ottawa, CANADA SP IEEE Electromagnet Compatibil Soc AB Two Extended Interaction klystrons (EIKs) containing strong permanent magnets were modeled magnetically in a representative spacecraft geometry using commercial finite element modeling techniques and were validated against measurements made at varying distances. Initial modeling results for the 63 A-m(2) dipole moment magnets showed that magnetic shields would be necessary in order to meet magnetic field requirements for the Surface Water and Ocean Topography (SWOT) spacecraft, which contains components that are susceptible to external DC magnetic fields. ME and the Elk vendor proposed cold rolled steel and mu-metal as potential shield materials along with proposed thicknesses of 0.5 mn and 1.5 mm. Magnetic shields made from each of these materials were designed and modeled in software, taking high field saturation into account. Prototype magnetic shields with these parameters were then built, measured with an existing EIK, and compared against modeling results. For single-axis field measurements along the dipole axis, modeling results were within 7 gauss of the measured values at 10 cm from the magnet, and converged to less than 1.5 gauss at distances greater than 14 cm from the magnet. Three-axis field measurements at locations of interest showed that model correlation improved to within 4 gauss at 11 cm and 2 gauss for distances ranging between 15 cm and 36 cm. C1 [Gonzales, Edward; Mewatters, Dalia] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91125 USA. RP Gonzales, E (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91125 USA. EM Edward.C.Gonzales@jpl.nasa.gov; Dalia.A.Mcwatters@jpl.nasa.gov NR 2 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2158-110X BN 978-1-5090-1441-5 J9 IEEE INT SYMP ELEC PY 2016 PG 6 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BG1WI UT WOS:000387117700004 ER PT S AU Huang, CCN Ghaneh, A Comandur, S AF Huang, Chi-Chien Nelson Ghaneh, Ali Comandur, Subha GP IEEE TI Electromagnetic Compatibility Design, Implementation and Test of the SMAP Spacecraft to Meet Stringent L-Band Radiated Emissions Requirements SO 2016 IEEE INTERNATIONAL SYMPOSIUM ON ELECTROMAGNETIC COMPATIBILITY (EMC) SE IEEE International Symposium on Electromagnetic Compatibility LA English DT Proceedings Paper CT IEEE International Symposium on Electromagnetic Compatibility (EMC) CY JUL 25-29, 2016 CL Ottawa, CANADA SP IEEE Electromagnet Compatibil Soc AB This paper describes the electromagnetic compatibility (EMC) requirements on the NASA SMAP mission, the implementation of EMC best practices at various levels of development in system level cabling harnesses and subsystems packaging, and the testing and results of flight hardware at the subsystem and spacecraft system levels. C1 [Huang, Chi-Chien Nelson; Ghaneh, Ali; Comandur, Subha] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91125 USA. RP Huang, CCN (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91125 USA. EM Chi-Chien.N.Huang@jpl.nasa.gov; Ali.R.Ghaneh@jpl.nasa.gov; Subha.Comandur@jpl.nasa.gov NR 3 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2158-110X BN 978-1-5090-1441-5 J9 IEEE INT SYMP ELEC PY 2016 PG 6 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BG1WI UT WOS:000387117700003 ER PT S AU Chemyakin, E Muller, D Burton, S Hostetler, C Ferrare, R AF Chemyakin, Eduard Mueller, Detlef Burton, Sharon Hostetler, Chris Ferrare, Richard BE Gross, B Moshary, F Arend, M TI ARRANGE AND AVERAGE ALGORITHM FOR MICROPHYSICAL RETRIEVALS WITH A "3 beta+3 alpha" LIDAR CONFIGURATION SO 27TH INTERNATIONAL LASER RADAR CONFERENCE (ILRC 27) SE EPJ Web of Conferences LA English DT Proceedings Paper CT 27th International Laser Radar Conference (ILRC) CY JUL 05-10, 2015 CL Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr, New York City, NY SP City Univ New York, City Coll HO Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr ID PRINCIPAL COMPONENT ANALYSIS; TROPOSPHERIC AEROSOL; PARTICLE PARAMETERS; INVERSION; REGULARIZATION; BACKSCATTER; EXTINCTION AB We present the results of a comparison study in which a simple, automated, and unsupervised algorithm, which we call the arrange and average algorithm, was used to infer microphysical parameters (complex refractive index (CRT), effective radius, total number, surface area, and volume concentrations) of atmospheric aerosol particles. The algorithm normally uses backscatter coefficients (beta) at 355, 532, and 1064 nm and extinction coefficients (a) at 355 and 532 nm as input information. We compared the performance of the algorithm for the existing "3 beta+2 alpha" and potential "3 beta+3 alpha" configurations of a multiwavelength aerosol Raman lidar or high spectral-resolution lidar (HSRL). The "3 beta+3 alpha" configuration uses an extra extinction coefficient at 1064 nm. Testing of the algorithm is based on synthetic optical data that are computed from prescribed CRIs and monomodal logarithmically normal particle size distributions that represent spherical, primarily fine mode aerosols. We investigated the degree to which the microphysical results retrieved by this algorithm benefits from the increased number of input extinction coefficients. C1 [Chemyakin, Eduard; Mueller, Detlef] Sci Syst & Applicat Inc, NASA, Langley Res Ctr, Mail Stop 475, Hampton, VA 23681 USA. [Mueller, Detlef] Univ Hertfordshire, Coll Lane, Hatfield AL10 9AB, Herts, England. [Burton, Sharon; Hostetler, Chris; Ferrare, Richard] NASA, Langley Res Ctr, Mail Stop 401 A, Hampton, VA 23681 USA. RP Chemyakin, E (reprint author), Sci Syst & Applicat Inc, NASA, Langley Res Ctr, Mail Stop 475, Hampton, VA 23681 USA. EM eduard.v.chemyakin@nasa.gov NR 9 TC 0 Z9 0 U1 0 U2 0 PU E D P SCIENCES PI CEDEX A PA 17 AVE DU HOGGAR PARC D ACTIVITES COUTABOEUF BP 112, F-91944 CEDEX A, FRANCE SN 2100-014X J9 EPJ WEB CONF PY 2016 VL 119 AR UNSP 23026 DI 10.1051/epjconf/201611923026 PG 4 WC Engineering, Electrical & Electronic; Optics; Physics, Applied SC Engineering; Optics; Physics GA BG1GC UT WOS:000386726600220 ER PT S AU Garnier, A Vaughan, M Pelon, J Winker, D Trepte, C Young, S AF Garnier, Anne Vaughan, Mark Pelon, Jacques Winker, David Trepte, Chip Young, Stuart BE Gross, B Moshary, F Arend, M TI TOWARDS IMPROVED CIRRUS CLOUD OPTICAL DEPTHS FROM CALIPSO SO 27TH INTERNATIONAL LASER RADAR CONFERENCE (ILRC 27) SE EPJ Web of Conferences LA English DT Proceedings Paper CT 27th International Laser Radar Conference (ILRC) CY JUL 05-10, 2015 CL Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr, New York City, NY SP City Univ New York, City Coll HO Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr ID RETRIEVAL; LIDAR AB This paper reviews recent advances regarding the retrieval of optical depths of semi-transparent cirrus clouds using synergetic analyses of perfectly collocated observations from the CALIOP lidar and the IIR infrared radiometer aboard the CALIPSO satellite. C1 [Garnier, Anne] Sci Syst & Applicat Inc, Hampton, VA 23666 USA. [Garnier, Anne; Vaughan, Mark; Winker, David; Trepte, Chip] NASA, Langley Res Ctr, Hampton, VA 23681 USA. [Pelon, Jacques] Univ Paris 06, CNRS, IPSL, LATMOS, F-75252 Paris, France. [Young, Stuart] CSIRO Oceans & Atmosphere, Aspendale, Vic 3195, Australia. RP Garnier, A (reprint author), Sci Syst & Applicat Inc, Hampton, VA 23666 USA.; Garnier, A (reprint author), NASA, Langley Res Ctr, Hampton, VA 23681 USA. EM anne.garnier@latmos.ipsl.fr NR 8 TC 0 Z9 0 U1 1 U2 1 PU E D P SCIENCES PI CEDEX A PA 17 AVE DU HOGGAR PARC D ACTIVITES COUTABOEUF BP 112, F-91944 CEDEX A, FRANCE SN 2100-014X J9 EPJ WEB CONF PY 2016 VL 119 AR UNSP 16014 DI 10.1051/epjconf/201611916014 PG 4 WC Engineering, Electrical & Electronic; Optics; Physics, Applied SC Engineering; Optics; Physics GA BG1GC UT WOS:000386726600145 ER PT S AU Getzewich, BJ Tackett, JL Kar, J Garnier, A Vaughan, MA Hunt, B AF Getzewich, Brian J. Tackett, Jason L. Kar, Jay Garnier, Anne Vaughan, Mark A. Hunt, Bill BE Gross, B Moshary, F Arend, M TI CALIOP CALIBRATION: VERSION 4.0 ALGORITHM UPDATES SO 27TH INTERNATIONAL LASER RADAR CONFERENCE (ILRC 27) SE EPJ Web of Conferences LA English DT Proceedings Paper CT 27th International Laser Radar Conference (ILRC) CY JUL 05-10, 2015 CL Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr, New York City, NY SP City Univ New York, City Coll HO Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr AB The Cloud-Aerosol Lidar with Orthogonal Polarization (CALIOP) lidar, onboard the Cloud Aerosol Lidar and Infrared Pathfinder Satellite Observation (CALIPSO) satellite, has been providing a near continuous record of high-resolution vertical profiles of clouds and aerosols properties since the summer of 2006. Key to the generation of these vertical profiles is proper calibration of the 532 nm and 1064 nm channels. This abstract summarizes improvements to the calibration techniques used to calibrate the 532 nm and 1064 nm signals for the recent version 4 (V4) Lidar Level 1 data release. C1 [Getzewich, Brian J.; Tackett, Jason L.; Kar, Jay; Garnier, Anne; Hunt, Bill] SSAI, 1 Enterprise Pkwy,Suite 200, Hampton, VA 23666 USA. [Vaughan, Mark A.] NASA, Langley Res Ctr, MS 475, Hampton, VA 23681 USA. RP Getzewich, BJ (reprint author), SSAI, 1 Enterprise Pkwy,Suite 200, Hampton, VA 23666 USA. EM brian.j.getzewich@nasa.gov NR 6 TC 1 Z9 1 U1 2 U2 2 PU E D P SCIENCES PI CEDEX A PA 17 AVE DU HOGGAR PARC D ACTIVITES COUTABOEUF BP 112, F-91944 CEDEX A, FRANCE SN 2100-014X J9 EPJ WEB CONF PY 2016 VL 119 AR UNSP 04013 DI 10.1051/epjconf/201611904013 PG 4 WC Engineering, Electrical & Electronic; Optics; Physics, Applied SC Engineering; Optics; Physics GA BG1GC UT WOS:000386726600031 ER PT S AU Hair, J Hostetler, C Hu, YX Behrenfeld, M Butler, C Harper, D Hare, R Berkoff, T Cook, A Collins, J Stockley, N Twardowski, M Cetinic, I Ferrare, R Mack, T AF Hair, Johnathan Hostetler, Chris Hu, Yongxiang Behrenfeld, Michael Butler, Carolyn Harper, David Hare, Rich Berkoff, Timothy Cook, Antony Collins, James Stockley, Nicole Twardowski, Michael Cetinic, Ivona Ferrare, Richard Mack, Terry BE Gross, B Moshary, F Arend, M TI COMBINED ATMOSPHERIC AND OCEAN PROFILING FROM AN AIRBORNE HIGH SPECTRAL RESOLUTION LIDAR SO 27TH INTERNATIONAL LASER RADAR CONFERENCE (ILRC 27) SE EPJ Web of Conferences LA English DT Proceedings Paper CT 27th International Laser Radar Conference (ILRC) CY JUL 05-10, 2015 CL Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr, New York City, NY SP City Univ New York, City Coll HO Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr ID SCATTERING AB First of its kind combined atmospheric and ocean profile data were collected by the recently upgraded NASA Langley Research Center's (LaRC) High Spectral Resolution Lidar (HSRL-1) during the 17 July 7 August 2014 Ship-Aircraft Bio-Optical Research Experiment (SABOR). This mission sampled over a region that covered the Gulf of Maine, open-ocean near Bermuda, and coastal waters from Virginia to Rhode Island. The HSRL-1 and the Research Scanning Polarimeter from NASA Goddard Institute for Space Studies collected data onboard the NASA LaRC King Air aircraft and flight operations were closely coordinated with the Research Vessel Endeavor that made in situ ocean optical measurements. The lidar measurements provided profiles of atmospheric backscatter and particulate depolarization at 532nm, 1064nm, and extinction (532nm) from approximately 9km altitude. In addition, for the first time HSRL seawater backscatter, depolarization, and diffuse attenuation data at 532nm were collected and compared to both the ship measurements and the Moderate Resolution Imaging Spectrometer (NASA MODIS-Aqua) satellite ocean retrievals. C1 [Hair, Johnathan; Hostetler, Chris; Hu, Yongxiang; Harper, David; Hare, Rich; Berkoff, Timothy; Cook, Antony; Ferrare, Richard] NASA, Langley Res Ctr, Hampton, VA 23681 USA. [Behrenfeld, Michael] Oregon State Univ, Corvallis, OR 97331 USA. [Butler, Carolyn; Collins, James] Sci Syst & Applicat Inc, Hampton, VA 23666 USA. [Stockley, Nicole] WET Labs Inc, Narragansett, RI 02882 USA. [Stockley, Nicole] Florida Atlantic Univ, Harbor Branch Oceanog Inst, Ft Pierce, FL 34946 USA. [Cetinic, Ivona] Univ Maine, Walpole, ME 04573 USA. [Cetinic, Ivona] NASA, Goddard Space Flight Ctr, USRA, Greenbelt, MD 20771 USA. [Mack, Terry] Analyt Mech Associates, Hampton, VA 23666 USA. RP Hair, J (reprint author), NASA, Langley Res Ctr, Hampton, VA 23681 USA. EM johnathan.w.hair@nasa.gov RI Hu, Yongxiang/K-4426-2012 NR 8 TC 0 Z9 0 U1 0 U2 0 PU E D P SCIENCES PI CEDEX A PA 17 AVE DU HOGGAR PARC D ACTIVITES COUTABOEUF BP 112, F-91944 CEDEX A, FRANCE SN 2100-014X J9 EPJ WEB CONF PY 2016 VL 119 AR UNSP 22001 DI 10.1051/epjconf/201611922001 PG 4 WC Engineering, Electrical & Electronic; Optics; Physics, Applied SC Engineering; Optics; Physics GA BG1GC UT WOS:000386726600189 ER PT S AU Hicks, M Atkinson, D Demoz, B Vermeesch, K Delgado, R AF Hicks, M. Atkinson, D. Demoz, B. Vermeesch, K. Delgado, R. BE Gross, B Moshary, F Arend, M TI The National Weather Service Ceilometer Planetary Boundary Layer Project SO 27TH INTERNATIONAL LASER RADAR CONFERENCE (ILRC 27) SE EPJ Web of Conferences LA English DT Proceedings Paper CT 27th International Laser Radar Conference (ILRC) CY JUL 05-10, 2015 CL Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr, New York City, NY SP City Univ New York, City Coll HO Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr AB The National Weather Service (NWS) is investigating the potential of utilizing the Automatic Surface Observing System's (ASOS) cloud base height indicator, the Vaisala CL31 ceilometer, to profile aerosols in the atmosphere. Field test sites of stand-alone CL31 ceilometers have been established, primarily, around the Washington DC metropolitan area, with additional systems in southwest USA and Puerto Rico. The CL31 PBL project examines the CL31 data collected for data quality, mixing height retrieval applicability, and its compliment to satellite data. This paper reviews the topics of the CL31 data quality and mixing height retrieval applicability. C1 [Hicks, M.; Atkinson, D.] NWS, Silver Spring, MD 20910 USA. [Vermeesch, K.] NASA, GSFC, Greenbelt, MD USA. [Demoz, B.; Vermeesch, K.; Delgado, R.] UMBC, Baltimore, MD USA. RP Hicks, M (reprint author), NWS, Silver Spring, MD 20910 USA. NR 3 TC 0 Z9 0 U1 0 U2 0 PU E D P SCIENCES PI CEDEX A PA 17 AVE DU HOGGAR PARC D ACTIVITES COUTABOEUF BP 112, F-91944 CEDEX A, FRANCE SN 2100-014X J9 EPJ WEB CONF PY 2016 VL 119 AR UNSP 15004 DI 10.1051/epjconf/201611915004 PG 2 WC Engineering, Electrical & Electronic; Optics; Physics, Applied SC Engineering; Optics; Physics GA BG1GC UT WOS:000386726600127 ER PT S AU Hu, YX Behrenfeld, M Hostetler, C Pelon, J Trepte, C Hair, J Slade, W Cetinic, I Vaughan, M Lu, XM Zhai, PW Weimer, C Winker, D Verhappen, CC Butler, C Liu, ZY Hunt, B Omar, A Rodier, S Lifermann, A Josset, D Hou, WL MacDonnell, D Rhew, R AF Hu, Yongxiang Behrenfeld, Mike Hostetler, Chris Pelon, Jacques Trepte, Charles Hair, John Slade, Wayne Cetinic, Ivona Vaughan, Mark Lu, Xiaomei Zhai, Pengwang Weimer, Carl Winker, David Verhappen, Carolus C. Butler, Carolyn Liu, Zhaoyan Hunt, Bill Omar, Ali Rodier, Sharon Lifermann, Anne Josset, Damien Hou, Weilin MacDonnell, David Rhew, Ray BE Gross, B Moshary, F Arend, M TI OCEAN LIDAR MEASUREMENTS OF BEAM ATTENUATION AND A ROADMAP TO ACCURATE PHYTOPLANKTON BIOMASS ESTIMATES SO 27TH INTERNATIONAL LASER RADAR CONFERENCE (ILRC 27) SE EPJ Web of Conferences LA English DT Proceedings Paper CT 27th International Laser Radar Conference (ILRC) CY JUL 05-10, 2015 CL Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr, New York City, NY SP City Univ New York, City Coll HO Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr ID DEPOLARIZATION; WATER AB Beam attenuation coefficient, c, provides an important optical index of plankton standing stocks, such as phytoplankton biomass and total particulate carbon concentration. Unfortunately, c has proven difficult to quantify through remote sensing. Here, we introduce an innovative approach for estimating c using lidar depolarization measurements and diffuse attenuation coefficients from ocean color products or lidar measurements of Brillouin scattering. The new approach is based on a theoretical formula established from Monte Carlo simulations that links the depolarization ratio of sea water to the ratio of diffuse attenuation K-d and beam attenuation C (i.e., a multiple scattering factor). On July 17, 2014, the CALIPSO satellite was tilted 30 off-nadir for one nighttime orbit in order to minimize ocean surface backscatter and demonstrate the lidar ocean subsurface measurement concept from space. Depolarization ratios of ocean subsurface backscatter are measured accurately. Beam attenuation coefficients computed from the depolarization ratio measurements compare well with empirical estimates from ocean color measurements. We further verify the beam attenuation coefficient retrievals using aircraft based high spectral resolution lidar (HSRL) data that are collocated with in-water optical measurements. C1 [Hu, Yongxiang; Hostetler, Chris; Trepte, Charles; Hair, John; Vaughan, Mark; Lu, Xiaomei; Winker, David; Verhappen, Carolus C.; Butler, Carolyn; Liu, Zhaoyan; Hunt, Bill; Omar, Ali; Rodier, Sharon; MacDonnell, David; Rhew, Ray] NASA, Langley Res Ctr, Hampton, VA 23681 USA. [Behrenfeld, Mike; Lifermann, Anne] Oregon State Univ, Corvalis, OR USA. [Pelon, Jacques] Ctr Natl Etud Spatiaes, Toulouse, France. [Slade, Wayne] Sequoia Sci Inc, St Louis, MO USA. [Cetinic, Ivona] Univ Maine, Walpole, ME 04573 USA. [Zhai, Pengwang] UMBC, Baltimore, MD USA. [Weimer, Carl] Ball Aerosp Corp, Boulder, CO USA. [Josset, Damien; Hou, Weilin] NRL Stennis, Stennis Space Ctr, MS USA. RP Hu, YX (reprint author), NASA, Langley Res Ctr, Hampton, VA 23681 USA. EM Yongxiang.hu-1@nasa.gov RI Hu, Yongxiang/K-4426-2012; Omar, Ali/D-7102-2017 OI Omar, Ali/0000-0003-1871-9235 NR 15 TC 1 Z9 1 U1 0 U2 0 PU E D P SCIENCES PI CEDEX A PA 17 AVE DU HOGGAR PARC D ACTIVITES COUTABOEUF BP 112, F-91944 CEDEX A, FRANCE SN 2100-014X J9 EPJ WEB CONF PY 2016 VL 119 AR UNSP 22003 DI 10.1051/epjconf/201611922003 PG 4 WC Engineering, Electrical & Electronic; Optics; Physics, Applied SC Engineering; Optics; Physics GA BG1GC UT WOS:000386726600191 ER PT S AU Kolgotin, A Muller, D Romanov, A Chemyakin, E AF Kolgotin, Alexei Mueller, Detlef Romanov, Anton Chemyakin, Eduard BE Gross, B Moshary, F Arend, M TI GRADIENT CORRELATION METHOD FOR THE STABILIZATION OF INVERSION RESULTS OF AEROSOL MICROPHYSICAL PROPERTIES RETRIEVED FROM PROFILES OF OPTICAL DATA SO 27TH INTERNATIONAL LASER RADAR CONFERENCE (ILRC 27) SE EPJ Web of Conferences LA English DT Proceedings Paper CT 27th International Laser Radar Conference (ILRC) CY JUL 05-10, 2015 CL Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr, New York City, NY SP City Univ New York, City Coll HO Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr ID MULTIWAVELENGTH LIDAR; REGULARIZATION; PARAMETERS AB Correlation relationships between aerosol micro physical parameters and optical data are investigated. The results show that surface-area concentrations and extinction coefficients are linearly correlated with a correlation coefficient above 0.99 for arbitrary particle size distribution. The correlation relationships that we obtained can be used as constraints in our inversion of optical lidar data. Simulation studies demonstrate a significant stabilization of aerosol microphysical data products if we apply the gradient correlation method in our traditional regularization technique. C1 [Kolgotin, Alexei] Phys Instrumentat Ctr, Troitsk 142190, Moscow Region, Russia. [Mueller, Detlef; Chemyakin, Eduard] Sci Syst & Applicat Inc, NASA LaRC, 1 Enterprise Pkwy, Hampton, VA 23666 USA. [Mueller, Detlef] Univ Hertfordshire, Hatfield AL10 9AB, Herts, England. [Romanov, Anton] Natl Univ Sci & Technol, Leninskii Av 4, Moscow 119049, Russia. RP Kolgotin, A (reprint author), Phys Instrumentat Ctr, Troitsk 142190, Moscow Region, Russia. EM alexeift@yahoo.com; d.mueller@herts.ac.uk NR 5 TC 0 Z9 0 U1 0 U2 0 PU E D P SCIENCES PI CEDEX A PA 17 AVE DU HOGGAR PARC D ACTIVITES COUTABOEUF BP 112, F-91944 CEDEX A, FRANCE SN 2100-014X J9 EPJ WEB CONF PY 2016 VL 119 AR UNSP 23020 DI 10.1051/epjconf/201611923020 PG 4 WC Engineering, Electrical & Electronic; Optics; Physics, Applied SC Engineering; Optics; Physics GA BG1GC UT WOS:000386726600214 ER PT S AU Kolgotin, A Muller, D Chemyakin, E Romanov, A AF Kolgotin, Alexei Muller, Detlef Chemyakin, Eduard Romanov, Anton BE Gross, B Moshary, F Arend, M TI PERSPECTIVES OF THE EXPLICIT RETRIEVAL OF THE COMPLEX REFRACTIVE INDEX OF AEROSOLS FROM OPTICAL DATA TAKEN WITH LIDAR SO 27TH INTERNATIONAL LASER RADAR CONFERENCE (ILRC 27) SE EPJ Web of Conferences LA English DT Proceedings Paper CT 27th International Laser Radar Conference (ILRC) CY JUL 05-10, 2015 CL Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr, New York City, NY SP City Univ New York, City Coll HO Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr ID MULTIWAVELENGTH LIDAR; PARAMETERS; REGULARIZATION; BACKSCATTER; EXTINCTION; INVERSION AB We developed an explicit approach for the retrieval of the complex refractive index from optical data, i.e. backscatter and extinction coefficients measured with lidar. In this approach we assume that we know the particle size distributions as well as the optical data. On the basis of this approach we carried out numerical simulations in order to test the uncertainty of the retrieval of the complex refractive index in dependence of the combination of extinction and backscatter coefficients, the measurement wavelengths and measurement errors. C1 [Kolgotin, Alexei] Phys Instrumentat Ctr, Troitsk 142190, Moscow Region, Russia. [Muller, Detlef; Chemyakin, Eduard] NASA LaRC, SSAI, Hampton, VA 23666 USA. [Muller, Detlef] Univ Hertfordshire, Hatfield AL10 9AB, Herts, England. [Romanov, Anton] Natl Univ Sci & Technol, Leninskii Av 4, Moscow 119049, Russia. RP Kolgotin, A (reprint author), Phys Instrumentat Ctr, Troitsk 142190, Moscow Region, Russia. EM alexeift@yahoo.com NR 9 TC 1 Z9 1 U1 0 U2 0 PU E D P SCIENCES PI CEDEX A PA 17 AVE DU HOGGAR PARC D ACTIVITES COUTABOEUF BP 112, F-91944 CEDEX A, FRANCE SN 2100-014X J9 EPJ WEB CONF PY 2016 VL 119 AR UNSP 17016 DI 10.1051/epjconf/201611917016 PG 4 WC Engineering, Electrical & Electronic; Optics; Physics, Applied SC Engineering; Optics; Physics GA BG1GC UT WOS:000386726600163 ER PT S AU Kolgotin, A Korenskiy, M Veselovskii, I Whiteman, DN AF Kolgotin, Alexei Korenskiy, Mikhail Veselovskii, Igor Whiteman, David N. BE Gross, B Moshary, F Arend, M TI DIRECT ESTIMATION OF FINE AND COARSE MODE PARTICLE PARAMETERS FROM MULTIWAVELENGTH LIDAR MEASUREMENTS SO 27TH INTERNATIONAL LASER RADAR CONFERENCE (ILRC 27) SE EPJ Web of Conferences LA English DT Proceedings Paper CT 27th International Laser Radar Conference (ILRC) CY JUL 05-10, 2015 CL Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr, New York City, NY SP City Univ New York, City Coll HO Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr AB An approach for the direct estimation (DE) of particle parameters in the fine and coarse mode from multiwavelength lidar measurements is presented. Particle size distributions in both modes are approximated by rectangular functions, so the particle density is estimated directly without solving the inverse problem. The numerical simulation demonstrates that the particle volume in both modes can be estimated from 3 beta+2 alpha lidar measurements with uncertainty of similar to 25% for a wide range of size distributions. The technique developed was applied to the observations of NASA GSFC Raman lidar. Comparison of the results obtained with DE and regularization approach applied to the same set of data demonstrates agreement between these two techniques. C1 [Kolgotin, Alexei; Korenskiy, Mikhail; Veselovskii, Igor] Phys Instrumentat Ctr, Troitsk 142190, Moscow Region, Russia. [Whiteman, David N.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Kolgotin, A (reprint author), Phys Instrumentat Ctr, Troitsk 142190, Moscow Region, Russia. EM alexeift@yahoo.com; miklekor@pic.troitsk.ru; igorv@pic.troitsk.ru; david.n.whiteman@nasa.gov NR 4 TC 0 Z9 0 U1 0 U2 0 PU E D P SCIENCES PI CEDEX A PA 17 AVE DU HOGGAR PARC D ACTIVITES COUTABOEUF BP 112, F-91944 CEDEX A, FRANCE SN 2100-014X J9 EPJ WEB CONF PY 2016 VL 119 AR UNSP 08009 DI 10.1051/epjconf/201611908009 PG 4 WC Engineering, Electrical & Electronic; Optics; Physics, Applied SC Engineering; Optics; Physics GA BG1GC UT WOS:000386726600083 ER PT S AU Kuehn, R Holz, R Eloranta, E Vaughan, M Hair, J AF Kuehn, Ralph Holz, Robert Eloranta, Edwin Vaughan, Mark Hair, Johnathan BE Gross, B Moshary, F Arend, M TI DEVELOPING A CLIMATOLOGY OF CIRRUS LIDAR RATIOS USING UNIVERISTY OF WISCONSIN HSRL OBSERVATIONS SO 27TH INTERNATIONAL LASER RADAR CONFERENCE (ILRC 27) SE EPJ Web of Conferences LA English DT Proceedings Paper CT 27th International Laser Radar Conference (ILRC) CY JUL 05-10, 2015 CL Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr, New York City, NY SP City Univ New York, City Coll HO Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr AB Measurements of ice cloud lidar ratio from the University of Wisconsin High Spectral Resolution Lidar System (UW HSRL) are shown, for the period 2013/06/18-2013/11/04 in Hunstville, AL. These data were acquired as part of the SEAC4RS campaign. The layer-averaged median lidar ratio,at 532 nm, for non-precipitating ice-clouds, 0.3 < OD < 3.0, observed during the experiment was determined to be 25.7 +/- 10.6 sr. As part of this work we've also developed an automated cloud and precipitation classification and detection algorithm. C1 [Kuehn, Ralph; Holz, Robert; Eloranta, Edwin] Univ Wisconsin, CIMSS, Madison, WI 53706 USA. [Vaughan, Mark; Hair, Johnathan] NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Kuehn, R (reprint author), Univ Wisconsin, CIMSS, Madison, WI 53706 USA. EM ralph.kuehn@ssec.wisc.edu NR 2 TC 0 Z9 0 U1 0 U2 0 PU E D P SCIENCES PI CEDEX A PA 17 AVE DU HOGGAR PARC D ACTIVITES COUTABOEUF BP 112, F-91944 CEDEX A, FRANCE SN 2100-014X J9 EPJ WEB CONF PY 2016 VL 119 AR UNSP 16009 DI 10.1051/epjconf/201611916009 PG 3 WC Engineering, Electrical & Electronic; Optics; Physics, Applied SC Engineering; Optics; Physics GA BG1GC UT WOS:000386726600140 ER PT S AU Lewis, JR Welton, EJ Campbell, JR Haftings, PC AF Lewis, Jasper R. Welton, Ellsworth J. Campbell, James R. Haftings, Phillip C. BE Gross, B Moshary, F Arend, M TI MPLNET V3 CLOUD AND PLANETARY BOUNDARY LAYER DETECTION SO 27TH INTERNATIONAL LASER RADAR CONFERENCE (ILRC 27) SE EPJ Web of Conferences LA English DT Proceedings Paper CT 27th International Laser Radar Conference (ILRC) CY JUL 05-10, 2015 CL Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr, New York City, NY SP City Univ New York, City Coll HO Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr ID LIDAR; RETRIEVALS AB The NASA Micropulse Lidar Network Version 3 algorithms for planetary boundary layer and cloud detection are described and differences relative to the previous Version 2 algorithms are highlighted. A year of data from the Goddard Space Flight Center site in Greenbelt, MD consisting of diurnal and seasonal trends is used to demonstrate the results. Both the planetary boundary layer and cloud algorithms show significant improvement of the previous version. C1 [Lewis, Jasper R.] Univ Maryland Baltimore Cty, Joint Ctr Earth Syst Technol, Baltimore, MD 21250 USA. [Lewis, Jasper R.; Welton, Ellsworth J.; Haftings, Phillip C.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Campbell, James R.] Naval Res Lab, Monterey, CA 93943 USA. [Haftings, Phillip C.] Sci Syst & Applicat Inc, Lanham, MD 20706 USA. RP Lewis, JR (reprint author), Univ Maryland Baltimore Cty, Joint Ctr Earth Syst Technol, Baltimore, MD 21250 USA.; Lewis, JR (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. EM jasper.r.lewis@nasa.gov NR 7 TC 0 Z9 0 U1 0 U2 0 PU E D P SCIENCES PI CEDEX A PA 17 AVE DU HOGGAR PARC D ACTIVITES COUTABOEUF BP 112, F-91944 CEDEX A, FRANCE SN 2100-014X J9 EPJ WEB CONF PY 2016 VL 119 AR UNSP 16011 DI 10.1051/epjconf/201611916011 PG 4 WC Engineering, Electrical & Electronic; Optics; Physics, Applied SC Engineering; Optics; Physics GA BG1GC UT WOS:000386726600142 ER PT S AU Lin, B Obland, MD Harrison, FW Nehrir, AR Browell, EV Ismail, S Campbell, J Dobler, J Meadows, B Fan, TF Kooi, SA AF Lin, Bing Obland, Michael D. Harrison, F. Wallace Nehrir, Amin R. Browell, Edward V. Ismail, Syed Campbell, Joel Dobler, Jeremy Meadows, Byron Fan, Tai-Fang Kooi, Susan A. BE Gross, B Moshary, F Arend, M TI Measurements of Atmospheric CO2 Column in Cloudy Weather Conditions using An IM-CW Lidar at 1.57 Micron SO 27TH INTERNATIONAL LASER RADAR CONFERENCE (ILRC 27) SE EPJ Web of Conferences LA English DT Proceedings Paper CT 27th International Laser Radar Conference (ILRC) CY JUL 05-10, 2015 CL Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr, New York City, NY SP City Univ New York, City Coll HO Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr C1 [Lin, Bing; Obland, Michael D.; Harrison, F. Wallace; Nehrir, Amin R.; Ismail, Syed; Campbell, Joel; Meadows, Byron] NASA, Langley Res Ctr, Hampton, VA 23681 USA. [Browell, Edward V.] NASA, STARSS Affiliate 2, Langley Res Ctr, Hampton, VA 23681 USA. [Dobler, Jeremy] Exelis Inc, Ft Wayne, IN 46818 USA. [Fan, Tai-Fang; Kooi, Susan A.] Sci Syst & Applicat Inc, Hampton, VA 23666 USA. [Fan, Tai-Fang; Kooi, Susan A.] Langley Res Ctr, Hampton, VA 23681 USA. RP Lin, B (reprint author), NASA, Langley Res Ctr, Hampton, VA 23681 USA. NR 8 TC 0 Z9 0 U1 0 U2 0 PU E D P SCIENCES PI CEDEX A PA 17 AVE DU HOGGAR PARC D ACTIVITES COUTABOEUF BP 112, F-91944 CEDEX A, FRANCE SN 2100-014X J9 EPJ WEB CONF PY 2016 VL 119 AR UNSP 03002 DI 10.1051/epjeonf/201611903002 PG 4 WC Engineering, Electrical & Electronic; Optics; Physics, Applied SC Engineering; Optics; Physics GA BG1GC UT WOS:000386726600015 ER PT S AU Liu, ZY Winker, D Omar, A Vaughan, M Kar, J Trepte, C Hu, YX Schuster, G Young, S AF Liu, Zhaoyan Winker, David Omar, Ali Vaughan, Mark Kar, Jayanta Trepte, Charles Hu, Yongxiang Schuster, Gregory Young, Stuart BE Gross, B Moshary, F Arend, M TI AEROSOL OPTICAL PROPERTIES ABOVE OPAQUE WATER CLOUDS DERIVED FROM THE CALIOP VERSION 4 LEVEL 1 DATA SO 27TH INTERNATIONAL LASER RADAR CONFERENCE (ILRC 27) SE EPJ Web of Conferences LA English DT Proceedings Paper CT 27th International Laser Radar Conference (ILRC) CY JUL 05-10, 2015 CL Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr, New York City, NY SP City Univ New York, City Coll HO Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr ID CALIPSO LIDAR AB In a previous study we evaluated the above-cloud aerosol optical depth (AOD) retrieval at 532 nm in the CALIOP version 3 (V3) data products for two selected spatial domains along the Saharan dust transport pathway and African smoke transport pathway. In that study we rescaled the V3 level-1 (L1) data to compensate for known V3 calibration biases, and then derived aerosol intrinsic properties such as lidar ratio (Sa) and particulate depolarization ratio (PDR) for comparison with the CALIOP dust and smoke aerosol models. The calibration of the recently released version 4 (V4) CALIPSO L1 data product is significantly improved over V3. So in this paper we repeat our previous analysis using the new V4 L1 data. A comparison shows that our rescaled V3 and the new V4 data are different only by 1 /0 in the two selected spatial domains. The retrieved AOD values decrease by similar to 2.6% in both domains from V3 to V4. When the data is screened to exclude weakly scattering layers, the median Sa retrieved from the V4 L1 data in the dust transport region is reduced by 1.4 sr to 43.0 +/- 8.3 sr. The median Sa value in the smoke transport region is increased by 0.8 sr to 71.2 +/- 15.1 sr. The PDR values remain almost unchanged for the screened data. C1 [Liu, Zhaoyan; Kar, Jayanta] Sci Syst & Applicat Inc, Hampton, VA 23666 USA. [Liu, Zhaoyan; Winker, David; Omar, Ali; Vaughan, Mark; Kar, Jayanta; Trepte, Charles; Hu, Yongxiang; Schuster, Gregory] NASA, Langley Res Ctr, Hampton, VA 23681 USA. [Young, Stuart] CSIRO Oceans & Atmosphere, Aspendale, Vic 3195, Australia. RP Liu, ZY (reprint author), Sci Syst & Applicat Inc, Hampton, VA 23666 USA.; Liu, ZY (reprint author), NASA, Langley Res Ctr, Hampton, VA 23681 USA. EM Zhaoyan.liu@nasa.gov RI Hu, Yongxiang/K-4426-2012; Omar, Ali/D-7102-2017 OI Omar, Ali/0000-0003-1871-9235 NR 7 TC 0 Z9 0 U1 3 U2 3 PU E D P SCIENCES PI CEDEX A PA 17 AVE DU HOGGAR PARC D ACTIVITES COUTABOEUF BP 112, F-91944 CEDEX A, FRANCE SN 2100-014X J9 EPJ WEB CONF PY 2016 VL 119 AR UNSP 04010 DI 10.1051/epjconf/201611904010 PG 4 WC Engineering, Electrical & Electronic; Optics; Physics, Applied SC Engineering; Optics; Physics GA BG1GC UT WOS:000386726600028 ER PT S AU Lolli, S Lewis, JR Welton, EJ Campbell, JR Gu, Y AF Lolli, Simone Lewis, Jasper R. Welton, Ellsworth J. Campbell, James R. Gu, Y. BE Gross, B Moshary, F Arend, M TI UNDERSTANDING SEASONAL VARIABILITY IN THIN CIRRUS CLOUDS FROM CONTINUOUS MPLNET OBSERVATIONS AT GSFC IN 2012 SO 27TH INTERNATIONAL LASER RADAR CONFERENCE (ILRC 27) SE EPJ Web of Conferences LA English DT Proceedings Paper CT 27th International Laser Radar Conference (ILRC) CY JUL 05-10, 2015 CL Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr, New York City, NY SP City Univ New York, City Coll HO Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr ID RADIATION AB Optically thin cirrus cloud (optical depth < 0.3) net radiative forcing represents one of the primary uncertainties in climate feedback, as sub-visible clouds play a fundamental role in atmospheric radiation balance and climate change. A lidar is a very sensitive optical device to detect clouds with an optical depth as low as 10(-4). In this paper we assess the daytime net radiative forcing of sub visible cirrus clouds detected at Goddard Space Flight Center, a permanent observational site of the NASA Micro Pulse Lidar Network in 2012. Depending on their height, season and hour of the day, the solar albedo effect can outweigh the infrared greenhouse effect, cooling the earth-atmosphere system rather than warming it exclusively. As result, based on latitude, the net forcing of sub-visible cirrus clouds can be more accurately parameterized in climate models. C1 [Lolli, Simone; Lewis, Jasper R.] NASA JCET, Code 612, Greenbelt, MD 20771 USA. [Welton, Ellsworth J.] NASA, Code 612, Greenbelt, MD 20771 USA. [Campbell, James R.] Naval Res Lab, Monterey, CA 93940 USA. [Gu, Y.] Univ Calif Los Angeles, Los Angeles, CA 90095 USA. RP Lolli, S (reprint author), NASA JCET, Code 612, Greenbelt, MD 20771 USA. EM simone.lolli@nasa.gov NR 15 TC 0 Z9 0 U1 0 U2 0 PU E D P SCIENCES PI CEDEX A PA 17 AVE DU HOGGAR PARC D ACTIVITES COUTABOEUF BP 112, F-91944 CEDEX A, FRANCE SN 2100-014X J9 EPJ WEB CONF PY 2016 VL 119 AR UNSP 11004 DI 10.1051/epjconf/201611911004 PG 4 WC Engineering, Electrical & Electronic; Optics; Physics, Applied SC Engineering; Optics; Physics GA BG1GC UT WOS:000386726600097 ER PT S AU Lu, XM Hu, YX Lucker, PL Trepte, C AF Lu, Xiaomei Hu, Yongxiang Lucker, Patricia L. Trepte, Charles BE Gross, B Moshary, F Arend, M TI FOREST CANOPY HEIGHT ESTIMATION FROM CALIPSO LIDAR MEASUREMENT SO 27TH INTERNATIONAL LASER RADAR CONFERENCE (ILRC 27) SE EPJ Web of Conferences LA English DT Proceedings Paper CT 27th International Laser Radar Conference (ILRC) CY JUL 05-10, 2015 CL Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr, New York City, NY SP City Univ New York, City Coll HO Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr ID ALTIMETRY AB The canopy height is an important parameter in aboveground biomass estimation. Lidar remote sensing from airborne or satellite platforms, has a unique capability for forestry applications. This study introduces an innovative concept to estimate canopy height using CALIOP two wavelengths lidar measurements. One main advantage is that the concept proposed here is dependent on the penetration depths at two wavelengths without making assumption about the last peak of waveform as the ground location, and it does not require the ancillary Digital Elevation Model (DEM) data in order to obtain the slope information of terrain. Canopy penetration depths at two wavelengths indicate moderately strong relationships for estimating the canopy height. Results show that the CALIOP-derived canopy heights were highly correlated with the ICESat/GLAS-derived values with a mean RMSE of 3.4 m and correlation coefficient (R) of 0.89. Our findings present a relationship between the penetration difference and canopy height, which can be used as another metrics for canopy height estimation, except the full waveforms. C1 [Lu, Xiaomei; Lucker, Patricia L.] Sci Syst & Applicat Inc, Hampton, VA 23666 USA. [Hu, Yongxiang; Trepte, Charles] NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Hu, YX (reprint author), NASA, Langley Res Ctr, Hampton, VA 23681 USA. EM Yongxiang.hu-1@nasa.gov RI Hu, Yongxiang/K-4426-2012 NR 15 TC 0 Z9 0 U1 4 U2 4 PU E D P SCIENCES PI CEDEX A PA 17 AVE DU HOGGAR PARC D ACTIVITES COUTABOEUF BP 112, F-91944 CEDEX A, FRANCE SN 2100-014X J9 EPJ WEB CONF PY 2016 VL 119 AR UNSP 22005 DI 10.1051/epjconf/201611922005 PG 4 WC Engineering, Electrical & Electronic; Optics; Physics, Applied SC Engineering; Optics; Physics GA BG1GC UT WOS:000386726600193 ER PT S AU McGee, TJ Twigg, LW Sumnicht, GK Leblanc, T Barnes, J AF McGee, Thomas J. Twigg, Laurence W. Sumnicht, Grant K. Leblanc, Thierry Barnes, John BE Gross, B Moshary, F Arend, M TI RESULTS OF A LONGER TERM NDACC MEASUREMENTS COMPARISON CAMPAIGN AT MAUNA LOA OBSERVATORY SO 27TH INTERNATIONAL LASER RADAR CONFERENCE (ILRC 27) SE EPJ Web of Conferences LA English DT Proceedings Paper CT 27th International Laser Radar Conference (ILRC) CY JUL 05-10, 2015 CL Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr, New York City, NY SP City Univ New York, City Coll HO Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr AB Between November, 2015 and January, 2015, the Goddard Space Flight Center operated a pair of lidar instruments at the NOAA facility at Mauna Loa on the Big Island of Hawaii (Lat. 19.5N, Lon. 155.5 W, Altitude 3.397 km). Measurements were made during six different four week periods during this time period by both the NASA GSFC Stratospheric Ozone Lidar (STROZ) and the Aerosol and Temperature (ATL) lidar. Also making measurements were the JPL Stratospheric Ozone Lidar and the NOAA Aerosol and Water Vapor Lidar. All instruments participate and archive data with the Network for the Detection of Atmospheric Composition Change. Measurement comparisons were made among various instruments in accordance with the standard intercomparison protocols of the NDACC. C1 [McGee, Thomas J.] NASA, Goddard Space Flight Ctr, Lab Atmospher Chem & Dynam, Greenbelt, MD 20771 USA. [Twigg, Laurence W.; Sumnicht, Grant K.] Sci Syst & Applicat Inc, Lanham, MD USA. [Leblanc, Thierry] Jet Prop Lab, Table Mt Facil, Wrightwood, CA USA. [Barnes, John] NOAA, Earth Sci Res Lab, Mauna Loa Observ, Global Monitoring Div, Hilo, HI USA. RP McGee, TJ (reprint author), NASA, Goddard Space Flight Ctr, Lab Atmospher Chem & Dynam, Greenbelt, MD 20771 USA. EM Thomas.j.mcgee@nasa.gov NR 0 TC 0 Z9 0 U1 0 U2 0 PU E D P SCIENCES PI CEDEX A PA 17 AVE DU HOGGAR PARC D ACTIVITES COUTABOEUF BP 112, F-91944 CEDEX A, FRANCE SN 2100-014X J9 EPJ WEB CONF PY 2016 VL 119 AR UNSP 05015 DI 10.1051/epjconf/201611905015 PG 2 WC Engineering, Electrical & Electronic; Optics; Physics, Applied SC Engineering; Optics; Physics GA BG1GC UT WOS:000386726600046 ER PT S AU Menzies, RT Spiers, GD Jacob, JC AF Menzies, Robert T. Spiers, Gary D. Jacob, Joseph C. BE Gross, B Moshary, F Arend, M TI Airborne Laser Absorption Spectrometer Measurements of CO2 Column Mixing Ratios: Source and Sink Detection in the Atmospheric Environment SO 27TH INTERNATIONAL LASER RADAR CONFERENCE (ILRC 27) SE EPJ Web of Conferences LA English DT Proceedings Paper CT 27th International Laser Radar Conference (ILRC) CY JUL 05-10, 2015 CL Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr, New York City, NY SP City Univ New York, City Coll HO Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr ID DIFFERENTIAL ABSORPTION; LIDAR AB The JPL airborne Laser Absorption Spectrometer instrument has been flown several times in the 2007-2011 time frame for the purpose of measuring CO2 mixing ratios in the lower atmosphere. The four most recent flight campaigns were on the NASA DC-8 research aircraft, in support of the NASA ASCENDS (Active Sensing of CO2 Emissions over Nights, Days, and Seasons) mission formulation studies. This instrument operates in the 2.05-nm spectral region. The Integrated Path Differential Absorption (IPDA) method is used to retrieve weighted CO2 column mixing ratios. We present key features of the CO2-LAS signal processing, data analysis, and the calibration/validation methodology. Results from flights in various U.S. locations during the past three years include observed mid-day CO2 drawdown in the Midwest, also cases of point-source and regional plume detection that enable the calculation of emission rates. C1 [Menzies, Robert T.; Spiers, Gary D.; Jacob, Joseph C.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Menzies, RT (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM rmenzies@jpl.nasa.gov NR 7 TC 0 Z9 0 U1 0 U2 0 PU E D P SCIENCES PI CEDEX A PA 17 AVE DU HOGGAR PARC D ACTIVITES COUTABOEUF BP 112, F-91944 CEDEX A, FRANCE SN 2100-014X J9 EPJ WEB CONF PY 2016 VL 119 AR UNSP 03001 DI 10.1051/epjconf/201611903001 PG 4 WC Engineering, Electrical & Electronic; Optics; Physics, Applied SC Engineering; Optics; Physics GA BG1GC UT WOS:000386726600014 ER PT S AU Newchurch, MJ Kuang, S Leblanc, T Alvarez, RJ Langford, AO Senff, CJ Burris, JF McGee, TJ Sullivan, JT DeYoung, RJ Al-Saadi, J Johnson, M Pszenny, A AF Newchurch, Michael J. Kuang, Shi Leblanc, Thierry Alvarez, Raul J., II Langford, Andrew O. Senff, Christoph J. Burris, John F. McGee, Thomas J. Sullivan, John T. DeYoung, Russell J. Al-Saadi, Jassim Johnson, Matthew Pszenny, Alex BE Gross, B Moshary, F Arend, M TI TOLNet - A Tropospheric Ozone Lidar Profiling Network for Satellite Continuity and Process Studies SO 27TH INTERNATIONAL LASER RADAR CONFERENCE (ILRC 27) SE EPJ Web of Conferences LA English DT Proceedings Paper CT 27th International Laser Radar Conference (ILRC) CY JUL 05-10, 2015 CL Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr, New York City, NY SP City Univ New York, City Coll HO Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr AB Ozone lidars measure continuous, high resolution ozone profiles critical for process studies and for satellite validation in the lower troposphere. However, the effectiveness of lidar validation by using single-station data is limited. Recently, NASA initiated an interagency ozone lidar observation network under the name TOLNet to promote cooperative multiple-station ozone-lidar observations to provide highly timeresolved (few minutes) tropospheric-ozone vertical profiles useful for air-quality studies, model evaluation, and satellite validation. This article briefly describes the concept, stations, major specifications of the TOLNet instruments, and data archiving. C1 [Newchurch, Michael J.; Kuang, Shi] Univ Alabama, Dept Atmospher Sci, Huntsville, AL 35805 USA. [Leblanc, Thierry] NASA, Jet Prop Lab, Wrightwood, CA 92397 USA. [Alvarez, Raul J., II; Langford, Andrew O.; Senff, Christoph J.] NOAA, Earth Syst Res Lab, Boulder, CO 80305 USA. [Senff, Christoph J.] Univ Colorado, Cooperat Inst Res Environm Sci, Boulder, CO 80309 USA. [Burris, John F.; McGee, Thomas J.; Sullivan, John T.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Sullivan, John T.] Univ Maryland Baltimore Cty, Dept Atmospher Phys, Baltimore, MD 21250 USA. [DeYoung, Russell J.; Al-Saadi, Jassim] NASA, Langley Res Ctr, Hampton, VA 23681 USA. [Johnson, Matthew] NASA, Ames Res Ctr, Moffett Field, CA 94031 USA. [Pszenny, Alex] NASA Headquarters, Washington, DC 20546 USA. RP Newchurch, MJ (reprint author), Univ Alabama, Dept Atmospher Sci, Huntsville, AL 35805 USA. EM mike@nsstc.uah.edu NR 8 TC 0 Z9 0 U1 1 U2 1 PU E D P SCIENCES PI CEDEX A PA 17 AVE DU HOGGAR PARC D ACTIVITES COUTABOEUF BP 112, F-91944 CEDEX A, FRANCE SN 2100-014X J9 EPJ WEB CONF PY 2016 VL 119 AR UNSP 20001 DI 10.1051/epjconf/201611920001 PG 4 WC Engineering, Electrical & Electronic; Optics; Physics, Applied SC Engineering; Optics; Physics GA BG1GC UT WOS:000386726600179 ER PT S AU Refaat, TF Singh, UN Yu, JR Petros, M AF Refaat, Tamer F. Singh, Upendra N. Yu, Jirong Petros, Mulugeta BE Gross, B Moshary, F Arend, M TI DOUBLE-PULSE TWO-MICRON IPDA LIDAR SIMULATION FOR AIRBORNE CARBON DIOXIDE MEASUREMENTS SO 27TH INTERNATIONAL LASER RADAR CONFERENCE (ILRC 27) SE EPJ Web of Conferences LA English DT Proceedings Paper CT 27th International Laser Radar Conference (ILRC) CY JUL 05-10, 2015 CL Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr, New York City, NY SP City Univ New York, City Coll HO Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr AB An advanced double-pulse 2- m integrated path differential absorption lidar has been developed at NASA Langley Research Center for measuring atmospheric carbon dioxide. The instrument utilizes a state-of-the-art 2- m laser transmitter with tunable on-line wavelength and advanced receiver. Instrument modeling and airborne simulations are presented in this paper. Focusing on random errors, results demonstrate instrument capabilities of performing precise carbon dioxide differential optical depth measurement with less than 3% random error for single-shot operation up to 11 km altitude. This study is useful for defining CO2 measurement weighting function for adaptive targeting, instrument setting, validation and sensitivity trade-offs. C1 [Refaat, Tamer F.; Singh, Upendra N.; Yu, Jirong; Petros, Mulugeta] NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Refaat, TF (reprint author), NASA, Langley Res Ctr, Hampton, VA 23681 USA. EM tamer.f.refaat@nasa.gov NR 5 TC 0 Z9 0 U1 0 U2 0 PU E D P SCIENCES PI CEDEX A PA 17 AVE DU HOGGAR PARC D ACTIVITES COUTABOEUF BP 112, F-91944 CEDEX A, FRANCE SN 2100-014X J9 EPJ WEB CONF PY 2016 VL 119 AR UNSP 05006 DI 10.1051/epjconf/201611905006 PG 4 WC Engineering, Electrical & Electronic; Optics; Physics, Applied SC Engineering; Optics; Physics GA BG1GC UT WOS:000386726600037 ER PT S AU Rodier, S Palm, S Vaughan, M Yorks, J McGill, M Jensen, M Murray, T Trepte, C AF Rodier, Sharon Palm, Steve Vaughan, Mark Yorks, John McGill, Matt Jensen, Mike Murray, Tim Trepte, Chip BE Gross, B Moshary, F Arend, M TI Laser Remote Sensing from ISS: CATS Cloud and Aerosol Level 2 Data Products (Heritage Edition) SO 27TH INTERNATIONAL LASER RADAR CONFERENCE (ILRC 27) SE EPJ Web of Conferences LA English DT Proceedings Paper CT 27th International Laser Radar Conference (ILRC) CY JUL 05-10, 2015 CL Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr, New York City, NY SP City Univ New York, City Coll HO Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr AB With the recent launch of the Cloud-Aerosol Transport System (CATS) we have the opportunity to acquire a continuous record of space based lidar measurements spanning from the Cloud-Aerosol Lidar and Infrared Pathfinder Satellite Observations (CALIPSO) era to the start of the EarthCARE mission. Utilizing existing well-validated science algorithms from the CALIPSO mission, we will ingest the CATS data stream and deliver high-quality lidar data sets to the user community at the earliest possible opportunity. In this paper we present an overview of procedures necessary to generate CALIPSOlike lidar level 2 data products from the CATS level 1 data products. C1 [Rodier, Sharon; Jensen, Mike; Murray, Tim] Sci Syst & Applicat Inc, Hampton, VA 23666 USA. [Palm, Steve; Yorks, John] Sci Syst & Applicat Inc, Greenbelt, MD USA. [Rodier, Sharon; Vaughan, Mark; Jensen, Mike; Murray, Tim; Trepte, Chip] NASA, Langley Res Ctr, Hampton, VA 23665 USA. [Palm, Steve; Yorks, John; McGill, Matt] NASA, Goddard Space Flight Ctr, Greenbelt, MD USA. RP Rodier, S (reprint author), Sci Syst & Applicat Inc, Hampton, VA 23666 USA.; Rodier, S (reprint author), NASA, Langley Res Ctr, Hampton, VA 23665 USA. EM sharon.d.rodier@nasa.gov NR 2 TC 0 Z9 0 U1 0 U2 0 PU E D P SCIENCES PI CEDEX A PA 17 AVE DU HOGGAR PARC D ACTIVITES COUTABOEUF BP 112, F-91944 CEDEX A, FRANCE SN 2100-014X J9 EPJ WEB CONF PY 2016 VL 119 AR UNSP 04012 DI 10.1051/epjconf/201611904012 PG 4 WC Engineering, Electrical & Electronic; Optics; Physics, Applied SC Engineering; Optics; Physics GA BG1GC UT WOS:000386726600030 ER PT S AU Sawamura, P Muller, D Burton, S Chemyakin, E Hostetler, C Ferrare, R Kolgotin, A Ziemba, L Beyersdorf, A Anderson, B AF Sawamura, Patricia Muller, Detlef Burton, Sharon Chemyakin, Eduard Hostetler, Chris Ferrare, Richard Kolgotin, Alexei Ziemba, Luke Beyersdorf, Andreas Anderson, Bruce BE Gross, B Moshary, F Arend, M TI Comparison of aerosol optical and microphysical retrievals from HSRL-2 and in-situ measurements during DISCOVER-AQ 2013 (California and Texas) SO 27TH INTERNATIONAL LASER RADAR CONFERENCE (ILRC 27) SE EPJ Web of Conferences LA English DT Proceedings Paper CT 27th International Laser Radar Conference (ILRC) CY JUL 05-10, 2015 CL Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr, New York City, NY SP City Univ New York, City Coll HO Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr AB The combination of backscatter coefficients measured at 355, 532 and 1064 nm and extinction coefficients at 355 and 532 nm (i.e. 3(3+2a) can be used to retrieve profiles of optical and micro physical properties of aerosols, such as effective radius, total volume concentration and total number concentration. NASA LaRC HSRL-2 is an airborne multi-wavelength high spectral resolution lidar in operation that provides the full 30+2a dataset. HSRL-2 was deployed during DISCOVER-AQ along with other airborne and ground-based instruments that also measured many aerosol parameters in close proximity to the HSRL-2 system, allowing us to evaluate the performance of an automated and unsupervised retrieval algorithm that has been recently developed. We present the results from California (Jan/Feb 2013) and Texas (Sep 2013) DISCOVER-AQ. C1 [Sawamura, Patricia; Burton, Sharon; Chemyakin, Eduard; Hostetler, Chris; Ferrare, Richard; Ziemba, Luke; Beyersdorf, Andreas; Anderson, Bruce] NASA, Langley Res Ctr, Hampton, VA 23665 USA. [Sawamura, Patricia] Oak Ridge Associated Univ, Oak Ridge, TN 37831 USA. [Muller, Detlef] Univ Hertfordshire, Hatfield AL10 9AB, Herts, England. [Chemyakin, Eduard] Sci Syst & Applicat Inc, Hampton, VA USA. [Kolgotin, Alexei] Phys Instrumentat Ctr, Troitsk, Russia. RP Sawamura, P (reprint author), NASA, Langley Res Ctr, Hampton, VA 23665 USA.; Sawamura, P (reprint author), Oak Ridge Associated Univ, Oak Ridge, TN 37831 USA. EM patricia.sawamura@nasa.gov NR 4 TC 0 Z9 0 U1 0 U2 0 PU E D P SCIENCES PI CEDEX A PA 17 AVE DU HOGGAR PARC D ACTIVITES COUTABOEUF BP 112, F-91944 CEDEX A, FRANCE SN 2100-014X J9 EPJ WEB CONF PY 2016 VL 119 AR UNSP 23014 DI 10.1051/epjconf/201611923014 PG 4 WC Engineering, Electrical & Electronic; Optics; Physics, Applied SC Engineering; Optics; Physics GA BG1GC UT WOS:000386726600208 ER PT S AU Schwemmer, G Yakshin, M Prasad, C Hanisco, T Mylapore, AR Hwang, IH Lee, S AF Schwemmer, G. Yakshin, M. Prasad, C. Hanisco, T. Mylapore, A. R. Hwang, I. H. Lee, S. BE Gross, B Moshary, F Arend, M TI INJECTION SEEDED LASER FOR FORMALDEHYDE DIFFERENTIAL FLUORESCENCE LIDAR SO 27TH INTERNATIONAL LASER RADAR CONFERENCE (ILRC 27) SE EPJ Web of Conferences LA English DT Proceedings Paper CT 27th International Laser Radar Conference (ILRC) CY JUL 05-10, 2015 CL Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr, New York City, NY SP City Univ New York, City Coll HO Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr AB We describe the design and development of an injection seeded Nd:YVO4 laser for use in a differential fluorescence lidar for measuring atmospheric formaldehyde profiles. A high repetition rate Q-switched laser is modified to accept injection seed input to spectrally narrow and tune the output. The third harmonic output is used to excite formaldehyde (HCHO) fluorescence when tuned to a HCHO absorption line. Spectral confirmation is made with the use of a photoacoustic cell and grating spectrometer. C1 [Schwemmer, G.; Yakshin, M.; Prasad, C.; Hwang, I. H.; Lee, S.] Sci & Engn Serv LLC, Columbia, MD 21076 USA. [Hanisco, T.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Mylapore, A. R.] MassTech Inc, Columbia, MD 21076 USA. RP Schwemmer, G (reprint author), Sci & Engn Serv LLC, Columbia, MD 21076 USA. EM schwemmer@sesi-md.com NR 12 TC 0 Z9 0 U1 1 U2 1 PU E D P SCIENCES PI CEDEX A PA 17 AVE DU HOGGAR PARC D ACTIVITES COUTABOEUF BP 112, F-91944 CEDEX A, FRANCE SN 2100-014X J9 EPJ WEB CONF PY 2016 VL 119 AR UNSP 02004 DI 10.1051/epjconf/201611902004 PG 4 WC Engineering, Electrical & Electronic; Optics; Physics, Applied SC Engineering; Optics; Physics GA BG1GC UT WOS:000386726600010 ER PT S AU Singh, UN Refaat, TF Petros, M Yu, JR AF Singh, Upendra N. Refaat, Tamer F. Petros, Mulugeta Yu, Jirong BE Gross, B Moshary, F Arend, M TI TRIPLE-PULSED TWO-MICRON INTEGRATED PATH DIFFERENTIAL ABSORPTION LIDAR: A NEW ACTIVE REMOTE SENSING CAPABILITY WITH PATH TO SPACE SO 27TH INTERNATIONAL LASER RADAR CONFERENCE (ILRC 27) SE EPJ Web of Conferences LA English DT Proceedings Paper CT 27th International Laser Radar Conference (ILRC) CY JUL 05-10, 2015 CL Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr, New York City, NY SP City Univ New York, City Coll HO Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr AB The two-micron wavelength is suitable for monitoring atmospheric water vapor and carbon dioxide, the two most dominant greenhouse gases. Recent advances in 2- m laser technology paved the way for constructing state-of-the-art lidar transmitters for active remote sensing applications. In this paper, a new triple-pulsed 2-mu tm integrated path differential absorption lidar is presented. This lidar is capable of measuring either two species or single specie with two different weighting functions, simultaneously and independently. Development of this instrument is conducted at NASA Langley Research Center. Instrument scaling for projected future space missions will be discussed. C1 [Singh, Upendra N.; Refaat, Tamer F.; Petros, Mulugeta; Yu, Jirong] NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Singh, UN (reprint author), NASA, Langley Res Ctr, Hampton, VA 23681 USA. EM upendra.n.singh@nasa.gov NR 6 TC 1 Z9 1 U1 0 U2 0 PU E D P SCIENCES PI CEDEX A PA 17 AVE DU HOGGAR PARC D ACTIVITES COUTABOEUF BP 112, F-91944 CEDEX A, FRANCE SN 2100-014X J9 EPJ WEB CONF PY 2016 VL 119 AR UNSP 02001 DI 10.1051/epjconf/201611902001 PG 4 WC Engineering, Electrical & Electronic; Optics; Physics, Applied SC Engineering; Optics; Physics GA BG1GC UT WOS:000386726600007 ER PT S AU Spuler, S Repasky, K Morley, B Moen, D Weckwerth, T Hayman, M Nehrir, A AF Spuler, Scott Repasky, Kevin Morley, Bruce Moen, Drew Weckwerth, Tammy Hayman, Matt Nehrir, Amin BE Gross, B Moshary, F Arend, M TI ADVANCES IN DIODE-LASER-BASED WATER VAPOR DIFFERENTIAL ABSORPTION LIDAR SO 27TH INTERNATIONAL LASER RADAR CONFERENCE (ILRC 27) SE EPJ Web of Conferences LA English DT Proceedings Paper CT 27th International Laser Radar Conference (ILRC) CY JUL 05-10, 2015 CL Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr, New York City, NY SP City Univ New York, City Coll HO Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr ID EMITTED RADIANCE INTERFEROMETER; RAMAN LIDAR; PERFORMANCE; PROFILES; DESIGN; AERI AB An advanced diode-laser-based water vapor differential absorption lidar (WV-DIAL) has been developed. The next generation design was built on the success of previous diode-laser-based prototypes and enables accurate measurement of water vapor closer to the ground surface, in rapidly changing atmospheric conditions, and in daytime cloudy conditions up to cloud base. The lidar provides up to 1 min resolution, 150 m range resolved measurements of water vapor in a broad range of atmospheric conditions. A description of the instrument and results from its initial field test in 2014 are discussed. C1 [Spuler, Scott; Morley, Bruce; Weckwerth, Tammy; Hayman, Matt] Natl Ctr Atmospher Res, Earth Observing Lab, POB 3000, Boulder, CO 80307 USA. [Repasky, Kevin; Moen, Drew] Montana State Univ, Elect & Comp Engn, Bozeman, MT 59717 USA. [Nehrir, Amin] NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Spuler, S (reprint author), Natl Ctr Atmospher Res, Earth Observing Lab, POB 3000, Boulder, CO 80307 USA. EM spuler@ucar.edu NR 17 TC 0 Z9 0 U1 3 U2 3 PU E D P SCIENCES PI CEDEX A PA 17 AVE DU HOGGAR PARC D ACTIVITES COUTABOEUF BP 112, F-91944 CEDEX A, FRANCE SN 2100-014X J9 EPJ WEB CONF PY 2016 VL 119 AR UNSP 02003 DI 10.1051/epjconf/201611902003 PG 4 WC Engineering, Electrical & Electronic; Optics; Physics, Applied SC Engineering; Optics; Physics GA BG1GC UT WOS:000386726600009 ER PT S AU Sullivan, JT McGee, TJ Hoff, RM Sumnicht, G Twigg, L AF Sullivan, John T. McGee, Thomas J. Hoff, Raymond M. Sumnicht, Grant Twigg, Laurence BE Gross, B Moshary, F Arend, M TI CHARACTERIZING THE VERTICAL PROCESSES OF OZONE IN COLORADO'S FRONT RANGE USING THE GSFC OZONE DIAL SO 27TH INTERNATIONAL LASER RADAR CONFERENCE (ILRC 27) SE EPJ Web of Conferences LA English DT Proceedings Paper CT 27th International Laser Radar Conference (ILRC) CY JUL 05-10, 2015 CL Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr, New York City, NY SP City Univ New York, City Coll HO Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr ID LIDAR; TROPOPAUSE; SYSTEM AB Although characterizing the interactions of ozone throughout the entire troposphere are important for health and climate processes, there is a lack of routine measurements of vertical profiles within the United States. In order to monitor this lower ozone more effectively, the National Aeronautics and Space Administration (NASA) Goddard Space Flight Center TROPospheric OZone DIfferential Absorption Lidar (GSFC TROPOZ DIAL) has been developed and validated within the Tropospheric Ozone Lidar Network (TOLNet). Two scientifically interesting ozone episodes are presented that were observed during the 2014 Deriving Information on Surface Conditions from Column and Vertically Resolved Observations Relevant to Air Quality (DISCOVER AQ) campaign at Ft. Collins, Colorado. The first case study, occurring between 22-23 July 2014, indicates enhanced concentrations of ozone at Ft. Collins during nighttime hours, which was due to the complex recirculation of ozone within the foothills of the Rocky Mountain region. Although quantifying the ozone increase aloft during recirculation episodes has been historically difficult, results indicate that an increase of 20 30 ppbv of ozone at the Ft. Collins site has been attributed to this recirculation. The second case, occurring between Aug 4-8th 2014, characterizes a dynamical exchange of ozone between the stratosphere and the troposphere. This case, along with seasonal model parameters from previous years, is used to estimate the stratospheric contribution to the Rocky Mountain region. Results suggest that a large amount of stratospheric air is residing in the troposphere in the summertime near Ft. Collins, CO. The results also indicate that warmer tropopauses are correlated with an increase in stratospheric air below the tropopause in the Rocky Mountain Region. C1 [Sullivan, John T.; Hoff, Raymond M.] Univ Maryland, Dept Phys, Baltimore, MD 21250 USA. [Sullivan, John T.; Hoff, Raymond M.] Joint Ctr Earth Syst Technol, Baltimore, MD 21250 USA. [McGee, Thomas J.] NASA, GSFC, Atmospher Chem & Dynam Lab, Greenbelt, MD 20771 USA. [Sumnicht, Grant; Twigg, Laurence] Sci Syst & Applicat Inc, Lanham, MD 20706 USA. RP Sullivan, JT (reprint author), Univ Maryland, Dept Phys, Baltimore, MD 21250 USA.; Sullivan, JT (reprint author), Joint Ctr Earth Syst Technol, Baltimore, MD 21250 USA. EM johnsullivan@umbc.edu NR 9 TC 0 Z9 0 U1 0 U2 0 PU E D P SCIENCES PI CEDEX A PA 17 AVE DU HOGGAR PARC D ACTIVITES COUTABOEUF BP 112, F-91944 CEDEX A, FRANCE SN 2100-014X J9 EPJ WEB CONF PY 2016 VL 119 AR UNSP 05014 DI 10.1051/epjconf/201611905014 PG 4 WC Engineering, Electrical & Electronic; Optics; Physics, Applied SC Engineering; Optics; Physics GA BG1GC UT WOS:000386726600045 ER PT S AU Suvorina, A Veselovskii, I Whiteman, DN Korenskiy, M AF Suvorina, Anastasia Veselovskii, Igor Whiteman, David N. Korenskiy, Michael BE Gross, B Moshary, F Arend, M TI SENSITIVITY OF PARTICLE EXTINCTION AND BACKSCATTERING CALCULATION FROM MIE-RAMAN LIDAR MEASUREMENTS TO THE CHOICE OF ANGSTROM EXPONENT SO 27TH INTERNATIONAL LASER RADAR CONFERENCE (ILRC 27) SE EPJ Web of Conferences LA English DT Proceedings Paper CT 27th International Laser Radar Conference (ILRC) CY JUL 05-10, 2015 CL Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr, New York City, NY SP City Univ New York, City Coll HO Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr AB Vibrational Raman scattering from nitrogen is commonly used in Mie-Raman lidars for evaluation of particle backscattering (beta) and extinction (alpha) coefficients. However, vibrational scattering is characterized by significant frequency shift of the Raman component, so for the calculation of a and the assumption about the extinction Angstrom exponent is needed. Simulation results presented in this study demonstrate that ambiguity in the choice of this exponent can be the significant source of uncertainty in the calculation of backscattering coefficients when optically thick aerosol layers are considered. Examples of lidar measurements and optical data calculated for different values of Angstrom exponent are given. C1 [Suvorina, Anastasia; Veselovskii, Igor; Korenskiy, Michael] Phys Instrumentat Ctr, Troitsk 142190, Moscow Region, Russia. [Whiteman, David N.] NASA, Mesoscale Atmospher Proc Lab, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Veselovskii, I (reprint author), Phys Instrumentat Ctr, Troitsk 142190, Moscow Region, Russia. EM igorv@pic.troitsk.ru; david.n.whiteman@nasa.gov NR 2 TC 0 Z9 0 U1 0 U2 0 PU E D P SCIENCES PI CEDEX A PA 17 AVE DU HOGGAR PARC D ACTIVITES COUTABOEUF BP 112, F-91944 CEDEX A, FRANCE SN 2100-014X J9 EPJ WEB CONF PY 2016 VL 119 AR UNSP 23019 DI 10.1051/epjconf/201611923019 PG 4 WC Engineering, Electrical & Electronic; Optics; Physics, Applied SC Engineering; Optics; Physics GA BG1GC UT WOS:000386726600213 ER PT S AU Vaughan, M Liu, ZY Hu, YX Powell, K Omar, A Rodier, S Hunt, W Kar, J Tackett, J Getzewich, B Lee, KP AF Vaughan, Mark Liu, Zhaoyan Hu, Yong-Xiang Powell, Kathleen Omar, Ali Rodier, Sharon Hunt, William Kar, Jayanta Tackett, Jason Getzewich, Brian Lee, Kam-Pui BE Gross, B Moshary, F Arend, M TI CLOUD-AEROSOL INTERACTIONS: RETRIEVING AEROSOL ANGSTROM EXPONENTS FROM CALIPSO MEASUREMENTS OF OPAQUE WATER CLOUDS SO 27TH INTERNATIONAL LASER RADAR CONFERENCE (ILRC 27) SE EPJ Web of Conferences LA English DT Proceedings Paper CT 27th International Laser Radar Conference (ILRC) CY JUL 05-10, 2015 CL Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr, New York City, NY SP City Univ New York, City Coll HO Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr AB Backscatter and extinction from water clouds are well-understood, both theoretically and experimentally, and thus changes to the expected measurement of layer-integrated attenuated back scatter can be used to infer the optical properties of overlying layers. In this paper we offer a first look at a new retrieval technique that uses CALIPSO measurements of opaque water clouds to derive optical depths and Angstrom exponents for overlying aerosol layers. C1 [Vaughan, Mark; Liu, Zhaoyan; Hu, Yong-Xiang; Powell, Kathleen; Omar, Ali; Rodier, Sharon; Hunt, William; Kar, Jayanta; Tackett, Jason; Getzewich, Brian; Lee, Kam-Pui] NASA, Langley Res Ctr, Hampton, VA 23681 USA. [Liu, Zhaoyan; Rodier, Sharon; Hunt, William; Kar, Jayanta; Tackett, Jason; Getzewich, Brian; Lee, Kam-Pui] SSAI, Hampton, VA 23666 USA. RP Vaughan, M (reprint author), NASA, Langley Res Ctr, Hampton, VA 23681 USA. EM mark.a.vaughan@nasa.gov RI Hu, Yongxiang/K-4426-2012; Omar, Ali/D-7102-2017 OI Omar, Ali/0000-0003-1871-9235 NR 7 TC 0 Z9 0 U1 1 U2 1 PU E D P SCIENCES PI CEDEX A PA 17 AVE DU HOGGAR PARC D ACTIVITES COUTABOEUF BP 112, F-91944 CEDEX A, FRANCE SN 2100-014X J9 EPJ WEB CONF PY 2016 VL 119 AR UNSP 11001 DI 10.1051/epjconf/201611911001 PG 4 WC Engineering, Electrical & Electronic; Optics; Physics, Applied SC Engineering; Optics; Physics GA BG1GC UT WOS:000386726600094 ER PT S AU Veselovskii, I Whiteman, DN Korenskiy, M Suvorina, A Perez-Ramirez, D AF Veselovskii, Igor Whiteman, David N. Korenskiy, Michael Suvorina, A. Perez-Ramirez, Daniel BE Gross, B Moshary, F Arend, M TI IMPLEMENTATION OF ROTATIONAL RAMAN CHANNEL IN MULTIWAVELENGTH AEROSOL LIDAR TO IMPROVE MEASUREMENTS OF PARTICLE EXTINCTION AND BACKSCATTERING AT 532 NM SO 27TH INTERNATIONAL LASER RADAR CONFERENCE (ILRC 27) SE EPJ Web of Conferences LA English DT Proceedings Paper CT 27th International Laser Radar Conference (ILRC) CY JUL 05-10, 2015 CL Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr, New York City, NY SP City Univ New York, City Coll HO Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr AB We describe a practical implementation of rotational Raman (RR) measurements in an existing Mie-Raman lidar to obtain measurements of aerosol extinction and backscattering at 532 nm. A 2.3 nm width interference filter was used to select a spectral range characterized by low temperature sensitivity within the anti-Stokes branch of the RR spectrum. Simulations demonstrate that the temperature dependence of the scattering cross section does not exceed 1.0% in the 230-300K range making accurate correction for this dependence quite easy. With this upgrade, the NASA/GSFC multiwavelength Raman lidar has demonstrated useful alpha(532) measurements and was used for regular observations. Examples of lidar measurements and inversion of optical data to the particle microphysics will be given in presentation. C1 [Veselovskii, Igor; Korenskiy, Michael; Suvorina, A.] Phys Instrumentat Ctr, Troitsk 142190, Moscow Region, Russia. [Whiteman, David N.; Perez-Ramirez, Daniel] NASA, Goddard Space Flight Ctr, Mesoscale Atmospher Proc Lab, Greenbelt, MD 20771 USA. [Perez-Ramirez, Daniel] Univ Granada, Dept Appl Phys, E-18071 Granada, Spain. RP Veselovskii, I (reprint author), Phys Instrumentat Ctr, Troitsk 142190, Moscow Region, Russia. EM igorv@pic.troitsk.ru; david.n.whiteman@nasa.gov NR 6 TC 0 Z9 0 U1 0 U2 0 PU E D P SCIENCES PI CEDEX A PA 17 AVE DU HOGGAR PARC D ACTIVITES COUTABOEUF BP 112, F-91944 CEDEX A, FRANCE SN 2100-014X J9 EPJ WEB CONF PY 2016 VL 119 AR UNSP 17002 DI 10.1051/epjconf/201611917002 PG 4 WC Engineering, Electrical & Electronic; Optics; Physics, Applied SC Engineering; Optics; Physics GA BG1GC UT WOS:000386726600149 ER PT S AU Winker, D Kato, S Tackett, J AF Winker, Dave Kato, Seiji Tackett, Jason BE Gross, B Moshary, F Arend, M TI GLOBAL AEROSOL DIRECT RADIATIVE EFFECT FROM CALIOP AND C3M SO 27TH INTERNATIONAL LASER RADAR CONFERENCE (ILRC 27) SE EPJ Web of Conferences LA English DT Proceedings Paper CT 27th International Laser Radar Conference (ILRC) CY JUL 05-10, 2015 CL Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr, New York City, NY SP City Univ New York, City Coll HO Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr AB Aerosols are responsible for the largest uncertainties in current estimates of climate forcing. These uncertainties are due in part to the limited abilities of passive sensors to retrieve aerosols in cloudy skies. We use a dataset which merges CALIOP observations together with other A-train observations to estimate aerosol radiative effects in cloudy skies as well as in cloud-free skies. The results can be used to quantify the reduction of aerosol radiative effects in cloudy skies relative to clear skies and to reduce current uncertainties in aerosol radiative effects. C1 [Winker, Dave; Kato, Seiji] NASA, Langley Res Ctr, Hampton, VA 23681 USA. [Tackett, Jason] SSAI, Hampton, VA 23666 USA. RP Winker, D (reprint author), NASA, Langley Res Ctr, Hampton, VA 23681 USA. EM david.m.winker@nasa.gov NR 9 TC 0 Z9 0 U1 2 U2 2 PU E D P SCIENCES PI CEDEX A PA 17 AVE DU HOGGAR PARC D ACTIVITES COUTABOEUF BP 112, F-91944 CEDEX A, FRANCE SN 2100-014X J9 EPJ WEB CONF PY 2016 VL 119 AR UNSP 21001 DI 10.1051/epjconf/201611921001 PG 4 WC Engineering, Electrical & Electronic; Optics; Physics, Applied SC Engineering; Optics; Physics GA BG1GC UT WOS:000386726600184 ER PT S AU Yu, JR Petros, M Refaat, T Reithmaier, K Remus, R Singh, U Johnson, W Boyer, C Fay, J Johnston, S Murchison, L AF Yu, Jirong Petros, Mulugeta Refaat, Tamer Reithmaier, Karl Remus, Ruben Singh, Upendra Johnson, Will Boyer, Charlie Fay, James Johnston, Susan Murchison, Luke BE Gross, B Moshary, F Arend, M TI AIRBORNE 2-MICRON DOUBLE PULSED DIRECT DETECTION IPDA LIDAR FOR ATMOSPHERIC CO2 MEASUREMENT SO 27TH INTERNATIONAL LASER RADAR CONFERENCE (ILRC 27) SE EPJ Web of Conferences LA English DT Proceedings Paper CT 27th International Laser Radar Conference (ILRC) CY JUL 05-10, 2015 CL Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr, New York City, NY SP City Univ New York, City Coll HO Natl Ocean & Atmospher Adm, Cooperat Remote Sensing Sci & Technol Ctr ID LASER AB An airborne 2-micron double-pulsed Integrated Path Differential Absorption (IPDA) lidar has been developed for atmospheric CO2 measurements. This new instrument has been flown in spring of 2014 for a total of ten flights with 27 flight hours. This IPDA lidar provides high precision measurement capability by unambiguously eliminating contamination from aerosols and clouds that can bias the results. C1 [Yu, Jirong; Petros, Mulugeta; Refaat, Tamer; Remus, Ruben; Singh, Upendra; Boyer, Charlie; Fay, James; Murchison, Luke] NASA, Langley Res Ctr, MS 468, Hampton, VA 23681 USA. [Reithmaier, Karl; Johnston, Susan] Sci Syst &Applicat Inc, One Enterprise Pkwy, Hampton, VA 23666 USA. [Johnson, Will] Michigan Aerosp Corp, 1777 Highland Dr B, Ann Arbor, MI 48108 USA. RP Yu, JR (reprint author), NASA, Langley Res Ctr, MS 468, Hampton, VA 23681 USA. EM j.yu@nasa.gov NR 5 TC 0 Z9 0 U1 0 U2 0 PU E D P SCIENCES PI CEDEX A PA 17 AVE DU HOGGAR PARC D ACTIVITES COUTABOEUF BP 112, F-91944 CEDEX A, FRANCE SN 2100-014X J9 EPJ WEB CONF PY 2016 VL 119 AR UNSP 03004 DI 10.1051/epjconf/201611903004 PG 4 WC Engineering, Electrical & Electronic; Optics; Physics, Applied SC Engineering; Optics; Physics GA BG1GC UT WOS:000386726600017 ER PT S AU Ammons, SM Garcia, EV Salama, M Neichel, B Lu, J Marois, C Macintosh, B Savransky, D Bendek, E Guyon, O Marin, E Garrel, V Sivo, G AF Ammons, S. Mark Garcia, E. Victor Salama, Maissa Neichel, Benoit Lu, Jessica Marois, Christian Macintosh, Bruce Savransky, Dmitry Bendek, Eduardo Guyon, Olivier Marin, Eduardo Garrel, Vincent Sivo, Gaetano BE Marchetti, E Close, LM Veran, JP TI Precision Astrometry with Adaptive Optics: Constraints on the Mutual Orbit of Luhman 16AB from GeMS SO ADAPTIVE OPTICS SYSTEMS V SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Adaptive Optics Systems V CY JUN 26-JUL 01, 2016 CL Edinburgh, SCOTLAND SP SPIE DE astrometry; adaptive optics; multi-conjugate; tomography; M92; NGC 1851; brown dwarf ID TELESCOPE; IMAGER AB ELTs equipped with MCAO systems will be powerful astrometric tools in the next two decades. With sparse-field precisions exceeding 30 uas for V > 18, the ELTs will surpass even GAIA's per-epoch precision for faint stars (V > 12). We present results from an ongoing astrometry program with Gemini GeMS and discuss synergies with WFIRST and GAIA. First, we present a fit to the relative orbit of the individual L/T components of Luhman16 AB, the nearest brown dwarf binary known. Exploiting GeMS' wide field of view to image reference stars, we are able to track the relative motion to better than 0.2 mas. We find that a mutual Keplerian orbit with no perturbing planets fits the binary separation to within the measurement errors, ruling out companions down to 14 earth masses for certain orbits and periods. C1 [Ammons, S. Mark; Garcia, E. Victor] Lawrence Livermore Natl Lab, 7000 East Ave, Livermore, CA 94550 USA. [Neichel, Benoit] Aix Marseille Univ, CNRS, LAM, UMR 7326, F-13388 Marseille, France. [Salama, Maissa] Univ Hawaii, Inst Astron, Honolulu, HI 96822 USA. [Lu, Jessica] Univ Calif Berkeley, Berkeley, CA 94720 USA. [Marois, Christian] Natl Res Council Canada, 5071 W Saanich Rd, Victoria, BC V9E 2E7, Canada. [Macintosh, Bruce] Stanford Univ, 450 Serra Mall, Stanford, CA USA. [Savransky, Dmitry] Cornell Univ, Ithaca, NY USA. [Bendek, Eduardo] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Guyon, Olivier] Univ Arizona, Tucson, AZ 85721 USA. [Marin, Eduardo; Garrel, Vincent; Sivo, Gaetano] Gemini Observ, La Serena, Chile. RP Ammons, SM (reprint author), Lawrence Livermore Natl Lab, 7000 East Ave, Livermore, CA 94550 USA. EM ammons1@llnl.gov RI Savransky, Dmitry/M-1298-2014; OI Savransky, Dmitry/0000-0002-8711-7206; Lu, Jessica/0000-0001-9611-0009 NR 19 TC 1 Z9 1 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0198-7 J9 PROC SPIE PY 2016 VL 9909 AR UNSP 99095T DI 10.1117/12.2233775 PG 9 WC Optics; Physics, Applied SC Optics; Physics GA BG2JZ UT WOS:000387429700165 ER PT S AU Bechter, A Crass, J Ketterer, R Crepp, JR Reynolds, RO Bechter, E Hinz, P Pedichini, F Foley, M Runburg, E Onuma, EE Gaudi, S Micela, G Pagano, I Woodward, CE AF Bechter, Andrew Crass, Jonathan Ketterer, Ryan Crepp, Justin R. Reynolds, Robert O. Bechter, Eric Hinz, Philip Pedichini, Fernando Foley, Michael Runburg, Elliott Onuma, Eleanya E. Gaudi, Scott Micela, Giuseppina Pagano, Isabella Woodward, Charles E. BE Marchetti, E Close, LM Veran, JP TI On-sky single-mode fiber coupling measurements at the Large Binocular Telescope SO ADAPTIVE OPTICS SYSTEMS V SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Adaptive Optics Systems V CY JUN 26-JUL 01, 2016 CL Edinburgh, SCOTLAND SP SPIE DE Single-Mode Fibers; Adaptive Optics; Large Binocular Telescope; iLocater; Fiber Optics AB The demonstration of efficient single-mode fiber (SMF) coupling is a key requirement for the development of a compact, ultra-precise radial velocity (RV) spectrograph. iLocater is a next generation instrument for the Large Binocular Telescope (LBT) that uses adaptive optics (AO) to inject starlight into a SMF. In preparation for commissioning iLocater, a prototype SMF injection system was installed and tested at the LBT in the Y-band (0.970-1.065 mu m). This system was designed to verify the capability of the LBT AO system as well as characterize on-sky SMF coupling efficiencies. SMF coupling was measured on stars with variable airmasses, apparent magnitudes, and seeing conditions for six half-nights using the Large Binocular Telescope Interferometer. We present the overall optical and mechanical performance of the SMF injection system, including details of the installation and alignment procedure. A particular emphasis is placed on analyzing the instrument's performance as a function of telescope elevation to inform the final design of the fiber injection system for iLocater. C1 [Bechter, Andrew; Crass, Jonathan; Ketterer, Ryan; Crepp, Justin R.; Bechter, Eric; Foley, Michael; Runburg, Elliott] Univ Notre Dame, Dept Phys, 225 Nieuwland Sci Hall, Notre Dame, IN 46556 USA. [Reynolds, Robert O.] Univ Arizona, Large Binocular Telescope Observ, 933 N Cherry Ave, Tucson, AZ 85721 USA. [Hinz, Philip] Univ Arizona, Steward Observ, Dept Astron, 933 N Cherry Ave, Tucson, AZ 85721 USA. [Pedichini, Fernando] INAF Roma, Via Frascati 33, I-00040 Monte Porzio Catone, Italy. [Onuma, Eleanya E.] NASA, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. [Gaudi, Scott] Ohio State Univ, Dept Astron, 140 W 18th Ave, Columbus, OH 43210 USA. [Micela, Giuseppina] INAF Osservatorio Astron GS Vaiana, Piazza Parlamento 1, I-90134 Palermo, Italy. [Pagano, Isabella] INAF Osservatorio Astrofis Catani, Via Santa Sofia 78, I-95125 Catania, Italy. [Woodward, Charles E.] Univ Minnesota, Minnesota Inst Astrophys, 116 Church St SE, Minneapolis, MN 55455 USA. RP Bechter, A (reprint author), Univ Notre Dame, Dept Phys, 225 Nieuwland Sci Hall, Notre Dame, IN 46556 USA. NR 10 TC 2 Z9 2 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0198-7 J9 PROC SPIE PY 2016 VL 9909 AR UNSP 99092X DI 10.1117/12.2233153 PG 11 WC Optics; Physics, Applied SC Optics; Physics GA BG2JZ UT WOS:000387429700084 ER PT S AU Bendek, E Lynch, D Pluzhnik, E Belikov, R Klamm, B Hyde, E Mumm, K AF Bendek, Eduardo Lynch, Dana Pluzhnik, Eugene Belikov, Ruslan Klamm, Benjamin Hyde, Elizabeth Mumm, Katherine BE Marchetti, E Close, LM Veran, JP TI Development of a Miniaturized Deformable Mirror Controller SO ADAPTIVE OPTICS SYSTEMS V SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Adaptive Optics Systems V CY JUN 26-JUL 01, 2016 CL Edinburgh, SCOTLAND SP SPIE DE Deformable Mirrors; Driving Electronics; Exoplanet; Direct Imaging; Coronagraphs ID SYSTEMS AB High-Performance Adaptive Optics systems are rapidly spreading as useful applications in the fields of astronomy, ophthalmology, and telecommunications. This technology is critical to enable coronagraphic direct imaging of exoplanets utilized in ground-based telescopes and future space missions such as WFIRST, EXO-C, HabEx, and LUVOIR. We have developed a miniaturized Deformable Mirror controller to enable active optics on small space imaging mission. The system is based on the Boston Micromachines Corporation Kilo-DM, which is one of the most widespread DMs on the market. The system has three main components: The Deformable Mirror, the Driving Electronics, and the Mechanical and Heat management. The system is designed to be extremely compact and have low-power consumption to enable its use not only on exoplanet missions, but also in a wide-range of applications that require precision optical systems, such as direct line-of-sight laser communications, and guidance systems. The controller is capable of handling 1,024 actuators with 220V maximum dynamic range, 16bit resolution, and 14bit accuracy, and operating at up to 1kHz frequency. The system fits in a 10x10x5cm volume, weighs less than 0.5kg, and consumes less than 8W. We have developed a turnkey solution reducing the risk for currently planned as well as future missions, lowering their cost by significantly reducing volume, weight and power consumption of the wavefront control hardware. C1 [Bendek, Eduardo; Lynch, Dana; Pluzhnik, Eugene; Belikov, Ruslan; Klamm, Benjamin; Hyde, Elizabeth] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Bendek, Eduardo] Bay Area Environm Res Inst, Petaluma, CA 94952 USA. [Mumm, Katherine] Los Altos High Sch, Los Altos, CA USA. RP Bendek, E (reprint author), NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. NR 13 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0198-7 J9 PROC SPIE PY 2016 VL 9909 AR UNSP 990984 DI 10.1117/12.2233929 PG 12 WC Optics; Physics, Applied SC Optics; Physics GA BG2JZ UT WOS:000387429700231 ER PT S AU Bottom, M Femenia, B Huby, E Mawet, D Dekany, R Milburn, J Serabyn, E AF Bottom, Michael Femenia, Bruno Huby, Elsa Mawet, Dimitri Dekany, Richard Milburn, Jennifer Serabyn, Eugene BE Marchetti, E Close, LM Veran, JP TI Speckle nulling wavefront control for Palomar and Keck SO ADAPTIVE OPTICS SYSTEMS V SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Adaptive Optics Systems V CY JUN 26-JUL 01, 2016 CL Edinburgh, SCOTLAND SP SPIE DE High contrast imaging; coronagraphy; adaptive optics; wavefront correction ID ADAPTIVE OPTICS SYSTEM AB We present a speckle nulling code currently being used for high contrast imaging at the Palomar and Keck telescopes. The code can operate in open and closed loop and is self-calibrating, requiring no system model and minimal hand-coded parameters. Written in a modular fashion, it is straightforward to port to different instruments. It has been used with systems operating in the optical through thermal infrared, and can deliver nearly an order of magnitude improvement in raw contrast. We will be releasing this code to the public in the near future. C1 [Bottom, Michael; Mawet, Dimitri; Dekany, Richard; Milburn, Jennifer] CALTECH, Pasadena, CA 91125 USA. [Femenia, Bruno] WM Keck Observ, Waimea, HI USA. [Huby, Elsa] Univ Liege, Liege, Wallonia, Belgium. [Serabyn, Eugene] Jet Prop Lab, Pasadena, CA USA. RP Bottom, M (reprint author), CALTECH, Pasadena, CA 91125 USA. EM mbottom@caltech.edu NR 15 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0198-7 J9 PROC SPIE PY 2016 VL 9909 AR UNSP 990955 DI 10.1117/12.2233025 PG 16 WC Optics; Physics, Applied SC Optics; Physics GA BG2JZ UT WOS:000387429700147 ER PT S AU Castella, BF Serabyn, E Mawet, D Absil, O Wizinowich, P Matthews, K Huby, E Bottom, M Campbell, R Chan, D Carlomagno, B Cetre, S Defrere, D Delacroix, C Gonzalez, CG Jolivet, A Karlsson, M Lanclos, K Lilley, S Milner, S Ngo, H Reggiani, M Simmons, J Tran, H Catalan, EV Wertz, O AF Castella, Bruno Femena Serabyn, Eugene Mawet, Dimitri Absil, Olivier Wizinowich, Peter Matthews, Keith Huby, Elsa Bottom, Michael Campbell, Randy Chan, Dwight Carlomagno, Brunella Cetre, Sylvian Defrere, Denis Delacroix, Christian Gonzalez, Carlos Gomez Jolivet, Aissa Karlsson, Mikael Lanclos, Kyle Lilley, Scott Milner, Steven Ngo, Henry Reggiani, Maddalena Simmons, Julia Hien Tran Catalan, Ernesto Vargas Wertz, Olivier BE Marchetti, E Close, LM Veran, JP TI Commissioning and first light results of an L'-band vortex coronagraph with the Keck II adaptive optics NIRC2 science instrument SO ADAPTIVE OPTICS SYSTEMS V SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Adaptive Optics Systems V CY JUN 26-JUL 01, 2016 CL Edinburgh, SCOTLAND SP SPIE DE WM Keck Observatory; NIRC2; high-contrast imaging; coronagraph; vortex phase mask ID HR 8799; STAR AB On March 2015 an L'-band vortex coronagraph based on an Annular Groove Phase Mask made up of a diamond sub-wavelength grating was installed on NIRC2 as a demonstration project. This vortex coronagraph operates in the L' band not only in order to take advantage from the favorable star/planet contrast ratio when observing beyond the K band, but also to exploit the fact that the Keck II Adaptive Optics (AO) system delivers nearly extreme adaptive optics image quality (Strehl ratios values near 90%) at 3.7 mu m. We describe the hardware installation of the vortex phase mask during a routine NIRC2 service mission. The success of the project depends on extensive software development which has allowed the achievement of exquisite real-time pointing control as well as further contrast improvements by using speckle nulling to mitigate the effect of static speckles. First light of the new coronagraphic mode was on June 2015 with already very good initial results. Subsequent commissioning nights were interlaced with science nights by members of the VORTEX team with their respective scientific programs. The new capability and excellent results so far have motivated the VORTEX team and the Keck Science Steering Committee (KSSC) to offer the new mode in shared risk mode for 2016B. C1 [Castella, Bruno Femena; Wizinowich, Peter; Campbell, Randy; Chan, Dwight; Cetre, Sylvian; Lanclos, Kyle; Lilley, Scott; Milner, Steven; Simmons, Julia; Hien Tran] WM Keck Observ, 65-1120 Mamalahoa Hwy, Kamuela, HI 96743 USA. [Serabyn, Eugene] Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Mawet, Dimitri; Matthews, Keith; Bottom, Michael; Ngo, Henry] CALTECH, 1200 E Calif Blvd, Pasadena, CA 91125 USA. [Absil, Olivier; Huby, Elsa; Carlomagno, Brunella; Gonzalez, Carlos Gomez; Jolivet, Aissa; Reggiani, Maddalena; Wertz, Olivier] Univ Liege, Dept Astrophys Geophys & Oceanog, 17 Alle Six Aout, B-4000 Sart Tilman Par Liege, Belgium. [Defrere, Denis] Univ Arizona, Steward Observ, 933 N Cherry Ave, Tucson, AZ 85721 USA. [Delacroix, Christian] Cornell Univ, Sibley Sch Mech & Aerosp Engn, Ithaca, NY 14853 USA. [Karlsson, Mikael; Catalan, Ernesto Vargas] Angstromlab, Lagerhyddsvagen 1, S-75237 Uppsala, Sweden. RP Castella, BF (reprint author), WM Keck Observ, 65-1120 Mamalahoa Hwy, Kamuela, HI 96743 USA. EM bfemenia@keck.hawaii.edu OI Delacroix, Christian/0000-0003-0150-4430 NR 20 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0198-7 J9 PROC SPIE PY 2016 VL 9909 AR UNSP 990922 DI 10.1117/12.2233228 PG 14 WC Optics; Physics, Applied SC Optics; Physics GA BG2JZ UT WOS:000387429700063 ER PT S AU Dennison, K Ammons, SM Garrel, V Marin, E Sivo, G Bendek, E Guyon, O AF Dennison, Kaitlin Ammons, S. Mark Garrel, Vincent Marin, Eduardo Sivo, Gaetano Bendek, Eduardo Guyon, Olivier BE Marchetti, E Close, LM Veran, JP TI An engineered design of a diffractive mask for high precision astrometry SO ADAPTIVE OPTICS SYSTEMS V SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Adaptive Optics Systems V CY JUN 26-JUL 01, 2016 CL Edinburgh, SCOTLAND SP SPIE DE diffractive; astrometry; AutoCAD; IDL; Zemax; adaptive optics; exoplanet AB AutoCAD, Zemax Optic Studio 15, and Interactive Data Language (IDL) with the Proper Library are used to computationally model and test a diffractive mask (DiM) suitable for use in the Gemini Multi-Conjugate Adaptive Optics System (GeMS) on the Gemini South Telescope. Systematic errors in telescope imagery are produced when the light travels through the adaptive optics system of the telescope. DiM is a transparent, flat optic with a pattern of miniscule dots lithographically applied to it. It is added ahead of the adaptive optics system in the telescope in order to produce diffraction spots that will encode systematic errors in the optics after it. Once these errors are encoded, they can be corrected for. DiM will allow for more accurate measurements in astrometry and thus improve exoplanet detection. The mechanics and physical attributes of the DiM are modeled in AutoCAD. Zemax models the ray propagation of point sources of light through the telescope. IDL and Proper simulate the wavefront and image results of the telescope. Aberrations are added to the Zemax and IDL models to test how the diffraction spots from the DiM change in the final images. Based on the Zemax and IDL results, the diffraction spots are able to encode the systematic aberrations. C1 [Dennison, Kaitlin] Univ Connecticut, Storrs, CT 06269 USA. [Dennison, Kaitlin; Ammons, S. Mark] Lawrence Livermore Natl Lab, Livermore, CA 94550 USA. [Garrel, Vincent; Marin, Eduardo; Sivo, Gaetano] Gemini South Observ, La Serena, Chile. [Bendek, Eduardo] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Guyon, Olivier] Univ Arizona, Tucson, AZ USA. RP Dennison, K (reprint author), Univ Connecticut, Storrs, CT 06269 USA.; Dennison, K (reprint author), Lawrence Livermore Natl Lab, Livermore, CA 94550 USA. NR 4 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0198-7 J9 PROC SPIE PY 2016 VL 9909 AR UNSP 99094E DI 10.1117/12.2233799 PG 7 WC Optics; Physics, Applied SC Optics; Physics GA BG2JZ UT WOS:000387429700126 ER PT S AU Hart, M Jefferies, S Murphy, N AF Hart, Michael Jefferies, Stuart Murphy, Neil BE Marchetti, E Close, LM Veran, JP TI Daylight Operation of a Sodium Laser Guide Star SO ADAPTIVE OPTICS SYSTEMS V SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Adaptive Optics Systems V CY JUN 26-JUL 01, 2016 CL Edinburgh, SCOTLAND SP SPIE DE sodium laser guide star; wave-front sensing; daylight observing; extremely large telescopes; thermal infrared ID TEMPERATURE; FILTER; LIDAR AB We report photometric measurements of a sodium resonance guide star against the daylight sky when observed through a tuned magneto-optical filter (MOF). The MOF comprises a sodium vapor cell in a kilogauss-level magnetic field between crossed polarizers and has a very narrow transmission profile at the sodium D-2 resonance of approximately 0.008 nm. Our observations were made with the 1.5 m Kuiper telescope on Mt. Bigelow, AZ, which has a separately mounted guide star laser projecting a circularly polarized single-frequency beam of approximately 6.5 W at 589.16 nm. Both the beam projector and the 1.5 m telescope were pointed close to zenith; the baseline between them is approximately 5 m. Measurements of the guide star were made on the morning of 2016 March 24 using an imaging camera focused on the beacon and looking through the full aperture of the telescope. The guide star flux was estimated at 1.20x10(6) photon/m(2)/s while at approximately 45 minutes after sunrise, the sky background through the MOF was 1100 photon/m(2)/s/arcsec(2). We interpret our results in terms of thermal infrared observations with adaptive optics on the next generation of extremely large telescopes now being built. C1 [Hart, Michael] Univ Arizona, Coll Opt Sci, Tucson, AZ 85721 USA. [Jefferies, Stuart] Georgia State Univ, Dept Phys & Astron, Atlanta, GA 30303 USA. [Hart, Michael; Jefferies, Stuart] Univ Hawaii, Inst Astron, 34 Ohia Ku St, Pukalani, HI 96768 USA. [Murphy, Neil] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Hart, M (reprint author), Univ Arizona, Coll Opt Sci, Tucson, AZ 85721 USA.; Hart, M (reprint author), Univ Hawaii, Inst Astron, 34 Ohia Ku St, Pukalani, HI 96768 USA. EM mhart@optics.arizona.edu NR 20 TC 0 Z9 0 U1 1 U2 1 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0198-7 J9 PROC SPIE PY 2016 VL 9909 AR UNSP 99095N DI 10.1117/12.2235080 PG 7 WC Optics; Physics, Applied SC Optics; Physics GA BG2JZ UT WOS:000387429700160 ER PT S AU Huby, E Absil, O Mawet, D Baudoz, P Castella, BF Bottom, M Ngo, H Serabyn, E AF Huby, Elsa Absil, Olivier Mawet, Dimitri Baudoz, Pierre Castella, Bruno Femena Bottom, Michael Ngo, Henry Serabyn, Eugene BE Marchetti, E Close, LM Veran, JP TI The QACITS pointing sensor: from theory to on-sky operation on Keck/NIRC2 SO ADAPTIVE OPTICS SYSTEMS V SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Adaptive Optics Systems V CY JUN 26-JUL 01, 2016 CL Edinburgh, SCOTLAND SP SPIE DE Wavefront sensing; vector vortex coronagraph; tip-tilt sensor; pointing sensor ID 1ST LIGHT; CORONAGRAPH AB Small inner working angle coronagraphs are essential to benefit from the full potential of large and future extremely large ground-based telescopes, especially in the context of the detection and characterization of exoplanets. Among existing solutions, the vortex coronagraph stands as one of the most effective and promising solutions. However, for focal-plane coronagraph, a small inner working angle comes necessarily at the cost of a high sensitivity to pointing errors. This is the reason why a pointing control system is imperative to stabilize the star on the vortex center against pointing drifts due to mechanical flexures, that generally occur during observation due for instance to temperature and/or gravity variations. We have therefore developed a technique called QACITS(1) (Quadrant Analysis of Coronagraphic Images for Tip-tilt Sensing), which is based on the analysis of the coronagraphic image shape to infer the amount of pointing error. It has been shown that the flux gradient in the image is directly related to the amount of tip-tilt affecting the beam. The main advantage of this technique is that it does not require any additional setup and can thus be easily implemented on all current facilities equipped with a vortex phase mask. In this paper, we focus on the implementation of the QACITS sensor at Keck/NIRC2, where an L-band AGPM has been recently commissioned (June and October 2015), successfully validating the QACITS estimator in the case of a centrally obstructed pupil. The algorithm has been designed to be easily handled by any user observing in vortex mode, which is available for science in shared risk mode since 2016B. C1 [Huby, Elsa; Absil, Olivier] Univ Liege, Space Sci Technol & Astrophys Res STAR Inst, 19c Allee Six Aout, B-4000 Liege, Belgium. [Mawet, Dimitri; Bottom, Michael; Ngo, Henry] CALTECH, 1200 E Calif Blvd, Pasadena, CA 91125 USA. [Baudoz, Pierre] Univ Paris Diderot, UPMC, CNRS, LESIA,Observ Paris,Paris Sci & Lettres, 5 Pl Jules Janssen, F-92195 Meudon, France. [Castella, Bruno Femena] WM Keck Observ, 65-1120 Mamalahoa Hwy, Kamuela, HI 96743 USA. [Serabyn, Eugene] Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Huby, E (reprint author), Univ Liege, Space Sci Technol & Astrophys Res STAR Inst, 19c Allee Six Aout, B-4000 Liege, Belgium. EM elsa.huby@ulg.ac.be NR 13 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0198-7 J9 PROC SPIE PY 2016 VL 9909 AR UNSP 990920 DI 10.1117/12.2233274 PG 10 WC Optics; Physics, Applied SC Optics; Physics GA BG2JZ UT WOS:000387429700061 ER PT S AU Jean-Franois, S Thierry, F Masen, L Julien, G Martin, B Andres, G Peter, W Jared, O Mamadou, N Arthur, V David, M Jean-Luc, B Markus, K Miska, L Julien, M Kjetil, D Benoit, N Pierre, B Pierre, H Dimitri, M AF Jean-Franois, Sauvage Thierry, Fusco Masen, Lamb Julien, Girard Martin, Brinkmann Andres, Guesalaga Peter, Wizinowich Jared, O'Neal Mamadou, N'Diaye Arthur, Vigan David, Mouillet Jean-Luc, Beuzit Markus, Kasper Miska, Le Louarn Julien, Milli Kjetil, Dohlen Benoit, Neichel Pierre, Bourget Pierre, Haguenauer Dimitri, Mawet BE Marchetti, E Close, LM Veran, JP TI Tackling down the Low Wind Effect on SPHERE instrument SO ADAPTIVE OPTICS SYSTEMS V SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Adaptive Optics Systems V CY JUN 26-JUL 01, 2016 CL Edinburgh, SCOTLAND SP SPIE DE High contrast imaging; adaptive optics; dome seeing AB SPHERE is the VLT second generation planet hunter instrument. Installed since may 2014 on UT3, the system has been commissionned and verified for more than one year now and routinely delivers unprecedented images of star surroundings, exoplanets and dust disks. The exceptionnal performance required for this kind of observation makes the appointment: a repeatable Strehl Ratio of 90% in H band, a rough contrast level of 10-5@0.5 arcsec, and reaches 10-6 at the same separation after differential imaging (SDI, ADI). The instrument also presents high contrast levels in the visible and an unprecedented 17mas diffraction-limited resolution at 0.65 microns wavelength. SAXO is the SPHERE XAO system, allowing the system to reach its final detectivity. Its high performance and therefore highly sensitive capacities turns a new eye on telescope environement. Even if XAO performance are reached as expected, some unexpected limitations are here described and a first work around is proposed and discussed. Spatial limitation: wave-front aberrations have been identified, deviating from kolmogorov statistics, and therefore not easily seen and compensated for by the XAO system. The impact of this limitations results in a degraded performance in some particular low wind conditions. Solutions are developped and tested on sky to propose a new operation procedure reducing this limitation. Temporal limitation: high amplitude vibrations on the low order modes have been issued, due to telescope environment and XAO behaviour. Again, a solution is developped and an assessment of its performance is dressed. The potential application of these solutions to E-ELT is proposed. C1 [Jean-Franois, Sauvage; Thierry, Fusco] Off Natl Etud & Rech Aerosp, Opt Dept, 29 Ave Div Leclerc, F-92322 Chatillon, France. [Jean-Franois, Sauvage; Thierry, Fusco; Andres, Guesalaga; Arthur, Vigan; Kjetil, Dohlen; Benoit, Neichel] Aix Marseille Univ, CNRS, LAM, UMR 7326, F-13388 Marseille, France. [Andres, Guesalaga] Pontificia Univ Catolica Chile, Sch Engn, Dept Elect Engn, Santiago, Region Metropol, Chile. [Andres, Guesalaga] Fdn IMeRA, Inst Etud Avancees Aix Marseille, 2 Pl Le Verrier, F-13004 Marseille, France. [Peter, Wizinowich] WM Keck Observ, 65-1120 Mamalahoa Hwy, Kamuela, HI 96743 USA. [Julien, Girard; Martin, Brinkmann; Jared, O'Neal; Arthur, Vigan; Markus, Kasper; Miska, Le Louarn; Julien, Milli; Pierre, Bourget; Pierre, Haguenauer] European Southern Observ, Karl Schwarzschild Str 2, D-85748 Garching, Germany. [Mamadou, N'Diaye] STScI Space Telescope Sci Inst, Baltimore, MD USA. [David, Mouillet; Jean-Luc, Beuzit] IPAG UJF Grenoble 1, IPAG, UMR 5274, CNRS INSU, F-38041 Grenoble, France. [Dimitri, Mawet] JPL, Pasadena, CA USA. [Masen, Lamb] Univ Victoria, 3800 Finnerty Rd, Victoria, BC, Canada. [Masen, Lamb] NRC Herzberg Astron, 5071 W Saanich Rd, Victoria, BC, Canada. RP Jean-Franois, S (reprint author), Off Natl Etud & Rech Aerosp, Opt Dept, 29 Ave Div Leclerc, F-92322 Chatillon, France.; Jean-Franois, S (reprint author), Aix Marseille Univ, CNRS, LAM, UMR 7326, F-13388 Marseille, France. OI Vigan, Arthur/0000-0002-5902-7828 NR 5 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0198-7 J9 PROC SPIE PY 2016 VL 9909 AR UNSP 990916 DI 10.1117/12.2232459 PG 9 WC Optics; Physics, Applied SC Optics; Physics GA BG2JZ UT WOS:000387429700036 ER PT S AU Jovanovic, N Guyon, O Lozi, J Currie, T Hagelberg, J Norris, B Singh, G Pathak, P Doughty, D Goebel, S Males, J Kuhn, J Serabyn, E Tuthill, P Schworer, G Martinache, F Kudo, T Kawahara, H Kotani, T Ireland, M Feger, T Rains, A Bento, J Schwab, C Coutts, D Cvetojevic, N Gross, S Arriola, A Lagadec, T Kasdin, J Groff, T Mazin, B Minowa, Y Takato, N Tamura, M Takami, H Hayashi, M AF Jovanovic, N. Guyon, O. Lozi, J. Currie, T. Hagelberg, J. Norris, B. Singh, G. Pathak, P. Doughty, D. Goebel, S. Males, J. Kuhn, J. Serabyn, E. Tuthill, P. Schworer, G. Martinache, F. Kudo, T. Kawahara, H. Kotani, T. Ireland, M. Feger, T. Rains, A. bento, J. Schwab, C. Coutts, D. Cvetojevic, N. Gross, S. Arriola, A. lagadec, T. Kasdin, J. Groff, T. Mazin, B. Minowa, Y. Takato, N. Tamura, M. Takami, H. Hayashi, M. BE Marchetti, E Close, LM Veran, JP TI The SCExAO high contrast imager: transitioning from commissioning to science SO ADAPTIVE OPTICS SYSTEMS V SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Adaptive Optics Systems V CY JUN 26-JUL 01, 2016 CL Edinburgh, SCOTLAND SP SPIE DE Extreme AO; Adaptive optics; High contrast imaging; Exoplanets; Sparse aperture masking; Coronagraphs; Imager; Fiber injection ID ADAPTIVE OPTICS; 1ST LIGHT; INSTRUMENT; TELESCOPE AB SCExAO is the premier high-contrast imaging platform for the Subaru Telescope. It offers high Strehl ratios at near-IR wavelengths (y-K band) with stable pointing and coronagraphs with extremely small inner working angles, optimized for imaging faint companions very close to the host. In the visible, it has several interferometric imagers which offer polarimetric and spectroscopic capabilities. A recent addition is the RHEA spectrograph enabling spatially resolved high resolution spectroscopy of the surfaces of giant stars, for example. New capabilities on the horizon include post-coronagraphic spectroscopy, spectral differential imaging, nulling interferometry as well as an integral field spectrograph and an MKID array. Here we present the new modules of SCExAO, give an overview of the current commissioning status of each of the modules and present preliminary results. C1 [Jovanovic, N.; Guyon, O.; Lozi, J.; Currie, T.; Pathak, P.; Doughty, D.; Goebel, S.; Kudo, T.; Minowa, Y.; Takato, N.] Natl Astron Observ Japan, Subaru Telescope, Hilo, HI 96720 USA. [Jovanovic, N.; Feger, T.; Schwab, C.; Coutts, D.; Gross, S.; Arriola, A.] Macquarie Univ, Dept Phys & Astron, N Ryde, NSW 2109, Australia. [Guyon, O.; Males, J.] Univ Arizona, Steward Observ, Tucson, AZ 85721 USA. [Guyon, O.; Doughty, D.] Univ Arizona, Coll Opt Sci, Tucson, AZ 85721 USA. [Guyon, O.] Astrobiol Ctr NINS, 2-21-1 Osawa, Mitaka, Tokyo 1818588, Japan. [Hagelberg, J.; Goebel, S.] Univ Hawaii, Inst Astron, Honolulu, HI 96822 USA. [Norris, B.; Tuthill, P.; Schworer, G.; Cvetojevic, N.; lagadec, T.] Univ Sydney, Sch Phys, IPOS, Sydney Inst Astron SIfA, Sydney, NSW 2006, Australia. [Singh, G.; Serabyn, E.] Jet Prop Lab, 4800 Oak Grove Dr,MS 183-901, Pasadena, CA 91109 USA. [Schworer, G.] Observ Paris, LESIA, 5 Pl Jules Janssen, F-92195 Meudon, France. [Martinache, F.] Observ Cote Azur, Bvld Observ, F-06304 Nice, France. [Kuhn, J.] Swiss Fed Inst Technol, Inst Astron, Wolfgang Pauli Str 27, CH-8093 Zurich, Switzerland. [Kawahara, H.] Univ Tokyo, Dept Earth & Planetary Sci, Tokyo 1130033, Japan. [Kawahara, H.] Univ Tokyo, Sch Sci, Res Ctr Early Universe, Tokyo 1138654, Japan. [Kotani, T.; Tamura, M.; Takami, H.; Hayashi, M.] Natl Astron Observ Japan, 2-21-1 Osawa, Mitaka, Tokyo, Japan. [bento, J.] Australian Natl Univ, Res Sch Astron & Astrophys, Canberra, ACT 2611, Australia. [Schwab, C.; Cvetojevic, N.] Australian Astron Observ, 105 Delhi Rd, N Ryde, NSW 2113, Australia. [Cvetojevic, N.; Gross, S.; Arriola, A.] Ctr Ultrahigh Bandwidth Device Opt Syst CUDOS, Sydney, NSW, Australia. [Groff, T.] Princeton Univ, Dept Mech & Aerosp Engn, Engn Quadrangle, Olden St, Princeton, NJ 08544 USA. [Mazin, B.] Univ Calif Santa Barbara, Dept Phys, Santa Barbara, CA 93106 USA. [Tamura, M.] Univ Tokyo, Tokyo 1130033, Japan. RP Jovanovic, N (reprint author), Natl Astron Observ Japan, Subaru Telescope, Hilo, HI 96720 USA.; Jovanovic, N (reprint author), Macquarie Univ, Dept Phys & Astron, N Ryde, NSW 2109, Australia. EM jovanovic.nem@gmail.com NR 31 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0198-7 J9 PROC SPIE PY 2016 VL 9909 AR UNSP 99090W DI 10.1117/12.2234294 PG 10 WC Optics; Physics, Applied SC Optics; Physics GA BG2JZ UT WOS:000387429700026 ER PT S AU Lozi, J Guyon, O Jovanovic, N Singh, G Goebel, S Norris, B Okita, H AF Lozi, Julien Guyon, Olivier Jovanovic, Nemanja Singh, Garima Goebel, Sean Norris, Barnaby Okita, Hirofumi BE Marchetti, E Close, LM Veran, JP TI Characterizing and mitigating vibrations for SCExAO SO ADAPTIVE OPTICS SYSTEMS V SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Adaptive Optics Systems V CY JUN 26-JUL 01, 2016 CL Edinburgh, SCOTLAND SP SPIE DE Extreme Adaptive Optics; Vibrations; Control; LQG; Accelerometers ID PHASE-MASK CORONAGRAPHS; ADAPTIVE OPTICS; LQG CONTROL; 1ST; VALIDATION AB The Subaru Coronagraphic Extreme Adaptive Optics (SCExAO) instrument, under development for the Subaru Telescope, has currently the fastest on-sky wavefront control loop, with a pyramid wavefront sensor running at 3.5 kHz. But even at that speed, we are still limited by low-frequency vibrations. The current main limitation was found to be vibrations attributed mainly to the rotation of the telescope. Using the fast wavefront sensors, cameras and accelerometers, we managed to identify the origin of most of the vibrations degrading our performance. Low-frequency vibrations are coming from the telescope drive in azimuth and elevation, as well as the elevation encoders when the target is at transit. Other vibrations were found at higher frequency coming from the image rotator inside Subaru's adaptive optics facility AO188. Different approaches are being implemented to take care of these issues. The PID control of the image rotator has been tuned to reduce their high-frequency contribution. We are working with the telescope team to tune the motor drives and reduce the impact of the elevation encoder. A Linear Quadratic Gaussian controller (LQG, or Kalman filter) is also being implemented inside SCExAO to control these vibrations. These solutions will not only improve significantly SCExAOs performance, but will also help all the other instruments on the Subaru Telescope, especially the ones behind A0188. Ultimately, this study will also help the development of the TMT, as these two telescopes share very similar drives. C1 [Lozi, Julien; Guyon, Olivier; Jovanovic, Nemanja; Goebel, Sean; Okita, Hirofumi] Natl Astron Observ Japan, Subaru Telescope, 650 North Aohoku Pl, Hilo, HI 96720 USA. [Guyon, Olivier] Univ Arizona, Steward Observ, Tucson, AZ 85721 USA. [Guyon, Olivier] Univ Arizona, Coll Opt Sci, Tucson, AZ 85721 USA. [Guyon, Olivier] Astrobiol Ctr NINS, 2-21-1 Osawa, Mitaka, Tokyo 1818588, Japan. [Jovanovic, Nemanja] Macquarie Univ, Dept Phys & Astron, N Ryde, NSW 2109, Australia. [Singh, Garima] Jet Prop Lab, 4800 Oak Grove Dr,MS 183-901, Pasadena, CA 91109 USA. [Goebel, Sean] Univ Hawaii, Inst Astron, 640 North Aohoku Pl, Hilo, HI 96720 USA. [Norris, Barnaby] Univ Sydney, Sch Phys, Inst Photon & Opt Sci, Sydney Inst Astron, Sydney, NSW 2006, Australia. RP Lozi, J (reprint author), Natl Astron Observ Japan, Subaru Telescope, 650 North Aohoku Pl, Hilo, HI 96720 USA. EM lozi@naoj.org NR 17 TC 0 Z9 0 U1 1 U2 1 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0198-7 J9 PROC SPIE PY 2016 VL 9909 AR UNSP 99090J DI 10.1117/12.2233040 PG 13 WC Optics; Physics, Applied SC Optics; Physics GA BG2JZ UT WOS:000387429700016 ER PT S AU Mawet, D Wizinowich, P Dekany, R Chun, M Hall, D Cetre, S Guyon, O Wallace, JK Bowler, B Liu, M Ruane, G Serabyn, E Bartos, R Wang, J Vasisht, G Fitzgerald, M Skemer, A Ireland, M Fucik, J Fortney, J Crossfield, I Hu, R Benneke, B AF Mawet, D. Wizinowich, P. Dekany, R. Chun, M. Hall, D. Cetre, S. Guyon, O. Wallace, J. K. Bowler, B. Liu, M. Ruane, G. Serabyn, E. Bartos, R. Wang, J. Vasisht, G. Fitzgerald, M. Skemer, A. Ireland, M. Fucik, J. Fortney, J. Crossfield, I. Hu, R. Benneke, B. BE Marchetti, E Close, LM Veran, JP TI Keck Planet Imager and Characterizer: concept and phased implementation SO ADAPTIVE OPTICS SYSTEMS V SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Adaptive Optics Systems V CY JUN 26-JUL 01, 2016 CL Edinburgh, SCOTLAND SP SPIE DE Exoplanets; high contrast imaging; high contrast high resolution spectroscopy; small inner working angle coronagraphy; vortex coronagraph; on-axis segmented telescopes; apodization; Extremely Large Telescopes ID BROWN DWARF; CORONAGRAPH; STARS; VLT/NACO AB The Keck Planet Imager and Characterizer (KPIC) is a cost-effective upgrade path to the W.M. Keck observatory (WMKO) adaptive optics (AO) system, building on the lessons learned from first and second-generation extreme AO (ExA0) coronagraphs. KPIC will explore new scientific niches in exoplanet science, while maturing critical technologies and systems for future ground-based (TMT, FELT, GMT) and space-based planet imagers (HabEx, LUVOIR). The advent of fast low-noise IR cameras (IR-APD, MKIDS, electron injectors), the rapid maturing of efficient wavefront sensing (WFS) techniques (Pyramid, Zernike), small inner working angle (IWA) coronagraphs (e.g., vortex) and associated low-order wavefront sensors (LOWFS), as well as recent breakthroughs in high contrast high resolution spectroscopy, open new direct exoplanet exploration avenues that are complementary to planet imagers such as VLT-SPHERE and the Gemini Planet Imager (GPI). For instance, the search and detailed characterization of planetary systems on solar-system scales around late-type stars, mostly beyond SPHERE and GPI's reaches, can be initiated now at WMKO. C1 [Mawet, D.; Dekany, R.; Ruane, G.; Wang, J.; Fucik, J.; Benneke, B.] CALTECH, Dept Astron, Pasadena, CA 91106 USA. [Mawet, D.; Wallace, J. K.; Serabyn, E.; Bartos, R.; Vasisht, G.; Hu, R.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Wizinowich, P.; Cetre, S.] WM Keck Observ, 65-1120 Mamalahoa Hwy, Kamuela, HI 96743 USA. [Chun, M.; Hall, D.] Univ Hawaii, Inst Astron, 640 N Aohoku Pl, Hilo, HI 96720 USA. [Guyon, O.] Natl Astron Observ Japan, Subaru Telescope, 650 N,Aohoku Pl, Hilo, HI 96720 USA. [Bowler, B.] Univ Texas Austin, Dept Astron, McDonald Observ, 2515 Speedway,Stop C1400, Austin, TX 78712 USA. [Liu, M.] Univ Hawaii, Inst Astron, 2680 Woodlawn Dr, Honolulu, HI 96822 USA. [Fitzgerald, M.] Univ Calif Los Angeles, Dept Phys & Astron, 430 Portola Plaza, Los Angeles, CA 90095 USA. [Skemer, A.; Fortney, J.; Crossfield, I.] Univ Calif Santa Cruz, Dept Astron & Astrophys, Santa Cruz, CA 95064 USA. [Ireland, M.] Australian Natl Univ, Res Sch Astron & Astrophys, Canberra, ACT 2611, Australia. [Crossfield, I.] Univ Arizona, Lunar & Planetary Lab, 1629 E Univ Blvd, Tucson, AZ 85721 USA. RP Mawet, D (reprint author), CALTECH, Dept Astron, Pasadena, CA 91106 USA.; Mawet, D (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM dmawet@astro.caltech.edu OI Ruane, Garreth/0000-0003-4769-1665 NR 17 TC 0 Z9 0 U1 1 U2 1 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0198-7 J9 PROC SPIE PY 2016 VL 9909 AR UNSP 99090D DI 10.1117/12.2233658 PG 7 WC Optics; Physics, Applied SC Optics; Physics GA BG2JZ UT WOS:000387429700012 ER PT S AU Singh, G Lozi, J Choquet, E Serabyn, E Guyon, O AF Singh, Garima Lozi, Julien Choquet, Elodie Serabyn, Eugene Guyon, Olivier BE Marchetti, E Close, LM Veran, JP TI PSF calibration using the Lyot-based low order wavefront sensor telemetry: First simulations SO ADAPTIVE OPTICS SYSTEMS V SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Adaptive Optics Systems V CY JUN 26-JUL 01, 2016 CL Edinburgh, SCOTLAND SP SPIE DE High contrast imaging of Exoplanets; Low-order wavefront aberrations; Extreme adaptive optics systems; Coronagraphy; Post-processing ID PHASE-MASK CORONAGRAPHS; ADAPTIVE OPTICS; PRINCIPLE; LIMITS AB One of the factors that drives the performance of small inner working angle (IWA) coronagraphs is the quality of the low-order wavefront calibration and control. The uncorrected residuals scatter the starlight and produce intensity fluctuations, which as a result creates dynamic speckle noise in the focal plane. To improve post processing of the science images, the low-order telemetry of the residuals left uncorrected by the control loop can be used to calibrate the amount of starlight leakage at small angular separations. In this proceeding, we present the preliminary simulations of point spread function calibration using the Lyot-based low-order wavefront sensor measurements (tip-tilt errors only) for a vector vortex coronagraph. C1 [Singh, Garima; Choquet, Elodie; Serabyn, Eugene] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Lozi, Julien; Guyon, Olivier] Natl Astron Observ Japan, Subaru Telescope, 650 N AOhoku Pl, Hilo, HI 96720 USA. RP Singh, G (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM garima.singh@jpl.nasa.gov NR 16 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0198-7 J9 PROC SPIE PY 2016 VL 9909 PG 10 WC Optics; Physics, Applied SC Optics; Physics GA BG2JZ UT WOS:000387429700218 ER PT S AU Frisbee, JH AF Frisbee, Joseph H., Jr. BE Majji, M Turner, JD Wawrzyniak, GG Cerven, WT TI AN UPPER BOUND ON HIGH SPEED SATELLITE COLLISION PROBABILITY WHEN ONLY ONE OBJECT HAS POSITION UNCERTAINTY INFORMATION SO ASTRODYNAMICS 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT AAS/AIAA Astrodynamics Specialist Conference CY AUG 11-13, 2015 CL Vail, CO SP Amer Astronaut Soc, Space Flight Mech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm AB Upper bounds on high speed satellite collision probability, P-C dagger, have been investigated. Previous methods assume an individual position error covariance matrix is available for each object. The two matrices being combined into a single, relative position error covariance matrix. Components of the combined error covariance are then varied to obtain a maximum P-C. If error covariance information for only one of the two objects was available, either some default shape has been used or nothing could be done. An alternative is presented that uses the known covariance information along with a critical value of the missing covariance to obtain an approximate but potentially useful P-C upper bound. C1 [Frisbee, Joseph H., Jr.] ISS Trajectory Operat & Planning Grp CM47, 2101 NASA Pkwy, Houston, TX 77058 USA. [Frisbee, Joseph H., Jr.] SGT Inc, 2101 NASA Pkwy, Houston, TX 77058 USA. [Frisbee, Joseph H., Jr.] NASA, Johnson Space Ctr, 2101 NASA Pkwy, Houston, TX 77058 USA. RP Frisbee, JH (reprint author), ISS Trajectory Operat & Planning Grp CM47, 2101 NASA Pkwy, Houston, TX 77058 USA.; Frisbee, JH (reprint author), SGT Inc, 2101 NASA Pkwy, Houston, TX 77058 USA.; Frisbee, JH (reprint author), NASA, Johnson Space Ctr, 2101 NASA Pkwy, Houston, TX 77058 USA. NR 6 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-629-6 J9 ADV ASTRONAUT SCI PY 2016 VL 156 BP 295 EP 304 PN I-IV PG 10 WC Engineering, Aerospace SC Engineering GA BG2OP UT WOS:000387517700016 ER PT S AU Lechtenberg, T Wysack, J Hasan, S Guit, W AF Lechtenberg, Travis Wysack, Joshua Hasan, Syed Guit, William BE Majji, M Turner, JD Wawrzyniak, GG Cerven, WT TI REALISTIC COVARIANCE GENERATION IN THE PRESENCE OF MANEUVERS SO ASTRODYNAMICS 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT AAS/AIAA Astrodynamics Specialist Conference CY AUG 11-13, 2015 CL Vail, CO SP Amer Astronaut Soc, Space Flight Mech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm AB Operational collision threat characterization is now an essential component of space mission operations. As the size of the space object catalog increases, more sophisticated collision threat characterization and collision avoidance strategies must be implemented. In order to accurately characterize collision risk, a realistic covariance must be used when computing collision probability. In order to generate realistic covariance, expected maneuver performance must be incorporated while modelling the spacecraft's predicted state uncertainty. This paper describes an approach for generating realistic predictive covariance for NASA's Earth Science Mission Operations (ESMO) satellite fleet. C1 [Lechtenberg, Travis; Wysack, Joshua] SpaceNav LLC, 2727 Bryant St,Suite 540, Denver, CO 80211 USA. [Hasan, Syed] Honeywell Technol Solut Inc, 14625 Baltimore Ave,277, Laurel, MD 20707 USA. [Guit, William] NASA, Goddard Space Flight Ctr, 8800 Greenbelt Rd,Code 428, Greenbelt, MD 20771 USA. RP Lechtenberg, T (reprint author), SpaceNav LLC, 2727 Bryant St,Suite 540, Denver, CO 80211 USA. EM travis@space-nay.com; josh@space-nay.com; syed.o.hasan@nasa.gov; william.j.guit@nasa.gov NR 5 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-629-6 J9 ADV ASTRONAUT SCI PY 2016 VL 156 BP 325 EP 340 PN I-IV PG 16 WC Engineering, Aerospace SC Engineering GA BG2OP UT WOS:000387517700018 ER PT S AU Roa, J Pelaez, J AF Roa, Javier Pelaez, Jesus BE Majji, M Turner, JD Wawrzyniak, GG Cerven, WT TI EFFICIENT TRAJECTORY PROPAGATION FOR ORBIT DETERMINATION PROBLEMS SO ASTRODYNAMICS 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT AAS/AIAA Astrodynamics Specialist Conference CY AUG 11-13, 2015 CL Vail, CO SP Amer Astronaut Soc, Space Flight Mech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm ID MOTION AB Regularized formulations of orbital motion apply a series of techniques to improve the numerical integration of the orbit. Despite their advantages and potential applications little attention has been paid to the propagation of the partial derivatives of the corresponding set of elements or coordinates, required in many orbit-determination scenarios and optimization problems. This paper fills this gap by presenting the general procedure for integrating the state-transition matrix of the system together with the nominal trajectory using regularized formulations and different sets of elements. The main difficulty comes from introducing an independent variable different from time, because the solution needs to be synchronized. The correction of the time delay is treated from a generic perspective not focused on any particular formulation. The synchronization using time elements is also discussed. Numerical examples include strongly-perturbed orbits in the Pluto system, motivated by the recent flyby of the New Horizons spacecraft, together with a geocentric flyby of the NEAR spacecraft. C1 [Roa, Javier; Pelaez, Jesus] Tech Univ Madrid UPM, Space Dynam Grp, Plaza Cardenal Cisneros 3, Madrid 28040, Spain. [Roa, Javier] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Roa, J (reprint author), Tech Univ Madrid UPM, Space Dynam Grp, Plaza Cardenal Cisneros 3, Madrid 28040, Spain.; Roa, J (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM javier.roa@upm.es NR 21 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-629-6 J9 ADV ASTRONAUT SCI PY 2016 VL 156 BP 361 EP 380 PN I-IV PG 20 WC Engineering, Aerospace SC Engineering GA BG2OP UT WOS:000387517700020 ER PT S AU Balducci, M Feldhacker, J Smith, J Jones, B AF Balducci, Marc Feldhacker, Juliana Smith, Jonathon Jones, Brandon BE Majji, M Turner, JD Wawrzyniak, GG Cerven, WT TI INTERPLANETARY ORBIT UNCERTAINTY PROPAGATION USING POLYNOMIAL SURROGATES SO ASTRODYNAMICS 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT AAS/AIAA Astrodynamics Specialist Conference CY AUG 11-13, 2015 CL Vail, CO SP Amer Astronaut Soc, Space Flight Mech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm ID CHAOS EXPANSIONS AB Approximations for the time-varying distribution of interplanetary orbit state uncertainty have traditionally relied on Gaussian assumptions or computationally expensive Monte Carlo (MC) methods. This generally leads to reduced accuracy of the propagated uncertainty in the first case, or an undesirable, and often intractable, number of orbit propagations in the latter. This paper considers the application of polynomial chaos (PC) for interplanetary orbit uncertainty propagation when there is one or more planetary or natural satellite flybys. The technique of compressive sampling is used in order to improve the tractability of the problem without sacrificing accuracy. The presented PC-based method of approximating the a posteriori probability density function requires no fundamental simplifying assumptions, reduces the computation time compared to MC, and produces a sensitivity analysis for the quantities of interest. C1 [Balducci, Marc; Feldhacker, Juliana; Jones, Brandon] Univ Colorado, Colorado Ctr Astrodynam Res, 431 UCB, Boulder, CO 80309 USA. [Smith, Jonathon] CALTECH, Mission Design & Nav Sect, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Balducci, M (reprint author), Univ Colorado, Colorado Ctr Astrodynam Res, 431 UCB, Boulder, CO 80309 USA. NR 26 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-629-6 J9 ADV ASTRONAUT SCI PY 2016 VL 156 BP 507 EP 525 PN I-IV PG 19 WC Engineering, Aerospace SC Engineering GA BG2OP UT WOS:000387517700029 ER PT S AU Short, C Howell, K Haapala, A Dichmann, D AF Short, Cody Howell, Kathleen Haapala, Amanda Dichmann, Donald BE Majji, M Turner, JD Wawrzyniak, GG Cerven, WT TI MODE ANALYSIS FOR LONG-TERM BEHAVIOR IN A RESONANT EARTH-MOON TRAJECTORY SO ASTRODYNAMICS 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT AAS/AIAA Astrodynamics Specialist Conference CY AUG 11-13, 2015 CL Vail, CO SP Amer Astronaut Soc, Space Flight Mech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm ID INVARIANT-MANIFOLDS; COHERENT STRUCTURES; ORBITS; PERTURBATIONS; EVOLUTION; DESIGN AB Trajectory design in chaotic regimes allows for the exploitation of system dynamics to achieve certain behaviors. For the Transiting Exoplanet Survey Satellite (TESS) mission, the selected science orbit represents a stable option well-suited to meet the mission objectives. Extended, long-term analysis of particular solutions nearby in the phase space reveals transitions into desirable terminal modes induced by natural dynamics. This investigation explores the trajectory behavior and borrows from flow-based analysis strategies to characterize modes of the motion. The goal is to identify mechanisms that drive the spacecraft into a particular mode and supply conditions necessary for such transitions. C1 [Short, Cody; Haapala, Amanda] Purdue Univ, Sch Aeronaut & Astronaut, 701 W Stadium Ave, W Lafayette, IN 47907 USA. [Howell, Kathleen] Purdue Univ, Aeronaut & Astronaut, 701 W Stadium Ave, W Lafayette, IN 47907 USA. [Haapala, Amanda] Johns Hopkins Univ, Appl Phys Lab, 11100 Johns Hopkins Rd, Laurel, MD 20723 USA. [Dichmann, Donald] NASA, Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. RP Short, C (reprint author), Purdue Univ, Sch Aeronaut & Astronaut, 701 W Stadium Ave, W Lafayette, IN 47907 USA. NR 24 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-629-6 J9 ADV ASTRONAUT SCI PY 2016 VL 156 BP 723 EP 742 PN I-IV PG 20 WC Engineering, Aerospace SC Engineering GA BG2OP UT WOS:000387517700043 ER PT S AU Anderson, RL Easton, RW Lo, MW AF Anderson, Rodney L. Easton, Robert W. Lo, Martin W. BE Majji, M Turner, JD Wawrzyniak, GG Cerven, WT TI ISOLATING BLOCKS AS COMPUTATIONAL TOOLS IN THE CIRCULAR RESTRICTED THREE-BODY PROBLEM SO ASTRODYNAMICS 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT AAS/AIAA Astrodynamics Specialist Conference CY AUG 11-13, 2015 CL Vail, CO SP Amer Astronaut Soc, Space Flight Mech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm ID INVARIANT-MANIFOLDS; PERIODIC-ORBITS AB Isolating blocks may be used as computational tools to search for the invariant manifolds of orbits and hyperbolic invariant sets associated with libration points while also giving additional insight into the dynamics of the flow in these regions. We use isolating blocks to investigate the dynamics of objects entering the Earth Moon system in the circular restricted three-body problem with energies close to the energy of the L-2 libration point. Specifically, the stable and unstable manifolds of Lyapunov orbits and the hyperbolic invariant set around the libration points are obtained by numerically computing the way orbits exit from an isolating block in combination with a bisection method. Invariant spheres of solutions in the spatial problem may then be located using the resulting manifolds. C1 [Anderson, Rodney L.; Lo, Martin W.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,M-S 301-121, Pasadena, CA 91109 USA. [Easton, Robert W.] Univ Colorado, Appl Math, Boulder, CO 80309 USA. RP Anderson, RL (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,M-S 301-121, Pasadena, CA 91109 USA. NR 16 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-629-6 J9 ADV ASTRONAUT SCI PY 2016 VL 156 BP 805 EP 824 PN I-IV PG 20 WC Engineering, Aerospace SC Engineering GA BG2OP UT WOS:000387517700047 ER PT S AU Woolley, RC Nicholas, AK AF Woolley, Ryan C. Nicholas, Austin K. BE Majji, M Turner, JD Wawrzyniak, GG Cerven, WT TI SEP MISSION DESIGN SPACE FOR MARS ORBITERS SO ASTRODYNAMICS 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT AAS/AIAA Astrodynamics Specialist Conference CY AUG 11-13, 2015 CL Vail, CO SP Amer Astronaut Soc, Space Flight Mech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm ID SOLAR ELECTRIC PROPULSION AB The advancement of solar-electric propulsion (SEP) technologies and larger, light-weight solar arrays offer a tremendous advantage to Mars orbiters in terms of both mass and timeline flexibility. These advantages are multiplied for roundtrip orbiters (e.g. potential Mars sample return) where a large total Delta V would be required. In this paper we investigate the mission design characteristics of mission concepts utilizing various combinations and types of SEP thrusters, solar arrays, launch vehicles, launch dates, arrival dates, etc. SEP allows for > 50% more mass delivered and launch periods of months to years. We also present the SEP analog to the ballistic Porkchop plot - the "Bacon" plot. C1 [Woolley, Ryan C.] CALTECH, Jet Prop Lab, Inner Planets Mission Anal Grp, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Nicholas, Austin K.] CALTECH, Jet Prop Lab, Assigned Preprojects Syst Engn Grp, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Woolley, RC (reprint author), CALTECH, Jet Prop Lab, Inner Planets Mission Anal Grp, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 17 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-629-6 J9 ADV ASTRONAUT SCI PY 2016 VL 156 BP 865 EP 883 PN I-IV PG 19 WC Engineering, Aerospace SC Engineering GA BG2OP UT WOS:000387517700050 ER PT S AU Lam, T Arrieta-Camacho, JJ Buffington, BB AF Lam, Try Arrieta-Camacho, Juan J. Buffington, Brent B. BE Majji, M Turner, JD Wawrzyniak, GG Cerven, WT TI THE EUROPA MISSION: MULTIPLE EUROPA FLYBY TRAJECTORY DESIGN TRADES AND CHALLENGES SO ASTRODYNAMICS 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT AAS/AIAA Astrodynamics Specialist Conference CY AUG 11-13, 2015 CL Vail, CO SP Amer Astronaut Soc, Space Flight Mech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm AB With potential sources of water, energy and other chemicals essential for life, Europa is a top candidate for finding current life in our Solar System outside of Earth. This paper describes the current trajectory design concept for a multiple Europa flyby mission and discusses several trajectory design challenges. The candidate reference trajectory utilizes multiple Europa flybys while around Jupiter to enable near global coverage of Europa while balancing science requirements, radiation dose, propellant usage, and flight time. Trajectory design trades and robustness are also discussed. C1 [Lam, Try; Arrieta-Camacho, Juan J.; Buffington, Brent B.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Lam, T (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 12 TC 0 Z9 0 U1 1 U2 1 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-629-6 J9 ADV ASTRONAUT SCI PY 2016 VL 156 BP 905 EP 924 PN I-IV PG 20 WC Engineering, Aerospace SC Engineering GA BG2OP UT WOS:000387517700052 ER PT S AU Armellin, R Di Lizia, P Zanetti, R AF Armellin, Roberto Di Lizia, Pierluigi Zanetti, Renato BE Majji, M Turner, JD Wawrzyniak, GG Cerven, WT TI DEALING WITH UNCERTAINTIES IN INITIAL ORBIT DETERMINATION SO ASTRODYNAMICS 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT AAS/AIAA Astrodynamics Specialist Conference CY AUG 11-13, 2015 CL Vail, CO SP Amer Astronaut Soc, Space Flight Mech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm AB A method to deal with uncertainties in initial orbit determination (IOD) is presented. This is based on the use of Taylor differential algebra (DA) to nonlinearly map the observation uncertainties from the observation space to the state space. When a minimum set of observations is available, DA is used to expand the solution of the IOD problem in Taylor series with respect to measurement errors. When more observations are available, high order inversion tools are exploited to obtain full state pseudo-observations at a common epoch. The mean and covariance of these pseudo-observations are nonlinearly computed by evaluating the expectation of high order Taylor polynomials. Finally, a linear scheme is employed to update the current knowledge of the orbit. Angles-only observations are considered and simplified Keplerian dynamics adopted to ease the explanation. Three test cases of orbit determination of artificial satellites in different orbital regimes are presented to discuss the feature and performances of the proposed methodology. C1 [Armellin, Roberto] Univ La Rioja, Dept Matemat & Comp, Logrono 26006, Spain. [Di Lizia, Pierluigi] Politecn Milan, Dept Aerosp Sci & Technol, I-20156 Milan, Italy. [Zanetti, Renato] NASA, Johnson Space Ctr, 2101 NASA Rd 1, Houston, TX 77058 USA. RP Armellin, R (reprint author), Univ La Rioja, Dept Matemat & Comp, Logrono 26006, Spain. EM roberto.armellin@unirioja.es; pierluigi.dilizia@esa.int; renato.zanetti@nasa.gov NR 22 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-629-6 J9 ADV ASTRONAUT SCI PY 2016 VL 156 BP 1085 EP 1103 PN I-IV PG 19 WC Engineering, Aerospace SC Engineering GA BG2OP UT WOS:000387517700063 ER PT S AU Brown, J Petersen, J Villac, B Yu, W AF Brown, Jonathan Petersen, Jeremy Villac, Benjamin Yu, Wayne BE Majji, M Turner, JD Wawrzyniak, GG Cerven, WT TI SEASONAL VARIATIONS OF THE JAMES WEBB SPACE TELESCOPE ORBITAL DYNAMICS SO ASTRODYNAMICS 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT AAS/AIAA Astrodynamics Specialist Conference CY AUG 11-13, 2015 CL Vail, CO SP Amer Astronaut Soc, Space Flight Mech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm AB While spacecraft orbital variations due to the Earth's tilt and orbital eccentricity are well-known phenomena, the implications for the James Webb Space Telescope present unique features. We investigate the variability of the observatory trajectory characteristics, and present an explanation of some of these effects using invariant manifold theory and local approximation of the dynamics in terms of the restricted three-body problem. C1 [Brown, Jonathan; Petersen, Jeremy; Villac, Benjamin] Ai Solut Inc, Mission Engn & Technol Div, 10001 Derekwood Lane,Suite 215, Lanham, MD 20706 USA. [Yu, Wayne] NASA, Nav & Mission Design Branch, Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. RP Brown, J (reprint author), Ai Solut Inc, Mission Engn & Technol Div, 10001 Derekwood Lane,Suite 215, Lanham, MD 20706 USA. NR 8 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-629-6 J9 ADV ASTRONAUT SCI PY 2016 VL 156 BP 1191 EP 1210 PN I-IV PG 20 WC Engineering, Aerospace SC Engineering GA BG2OP UT WOS:000387517700069 ER PT S AU DeHart, R Phenneger, M AF DeHart, Russell Phenneger, Milton BE Majji, M Turner, JD Wawrzyniak, GG Cerven, WT TI DECREASING THE FREQUENCY OF LUNAR RECONNAISSANCE ORBITER MOMENTUM UNLOADS USING SOLAR ARRAY POINTING AND ATTITUDE MANEUVERS TO CONTROL ANGULAR MOMENTUM SO ASTRODYNAMICS 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT AAS/AIAA Astrodynamics Specialist Conference CY AUG 11-13, 2015 CL Vail, CO SP Amer Astronaut Soc, Space Flight Mech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm AB The Lunar Reconnaissance Orbiter (LRO) is a three-axis stabilized spacecraft that uses hydrazine thrusters during reaction wheel assembly (RWA) momentum unloads. Some instrument activities and solar array configurations have been observed to be constructive or destructive to trends in spacecraft angular momentum. This analysis explores these as alternate methods to unload RWA angular momentum. On average, system body coordinate system (BCS) Y angular momentum, H-Y, either increases by approximately 3.9 Nms/day or decreases by approximately 1.1 Nms/day, depending on spacecraft configuration. On average, H-X and H-Z each increase by 2.3 Nms/day. Systems engineers with the Space Science Mission Operations project at NASA Goddard Space Flight Center are developing the LRO Angular Momentum Simulation (LAMS), which predicts the RWA angular momentum over a user-defined period of time. For parked so-lar array configurations, LAMS data suggest offsets of +2.4 degrees and +5.0 degrees to the inner gimbal would nullify growth in RWA H-Y for the (-90 degrees, +45 degrees) and (-90 degrees, +15 degrees) solar array (inner, outer) configurations, respectively. Larger offsets are necessary when using the outer gimbal to control RWA H-XZ. For the (-90 degrees, +45 degrees) and (-90 degrees, +15 degrees) configurations, offsets of +22 degrees and +60 degrees, respectively, were necessary. Operational constraints limit the application of the full offsets, though, especially for the (-90 degrees, +45 degrees) configuration. Removing overall angular momentum trends in the vicinity of attitude maneuvers allows the measurement of maneuver-induced changes in system angular momentum. This trending analysis identifies -90 degrees CRaTER instrument calibration roll and +/- 45 degrees LROC exospheric measurement pitch slews as candidates for angular momentum control. CRaTER roll maneuvers increased system BCS H-Y by up to 2.8 Nms. The magnitude of changes in system in-plane angular momentum was limited to less than 1 Nms. Each +/- 45 degrees LROC exosphere measurement pitch slew changes the system BCS H-Y by approximately 0.5 Nms, while leaving H-XZ essentially unchanged. Once the LAMS has been fully verified, it can be used to explore notional scenarios, instead of relying on trending analysis which is limited to measuring the effects of activities that have actually been performed. C1 [DeHart, Russell] Honeywell Technol Solut Inc, NASA, Goddard Space Flight Ctr, Space Sci Mission Operat, 8800 Greenbelt Rd,Mail Code 444, Greenbelt, MD 20771 USA. [Phenneger, Milton] ASRC Aerosp Corp, NASA, Goddard Space Flight Ctr, Space Sci Mission Operat, 8800 Greenbelt Rd,Mail Code 444, Greenbelt, MD 20771 USA. RP DeHart, R (reprint author), Honeywell Technol Solut Inc, NASA, Goddard Space Flight Ctr, Space Sci Mission Operat, 8800 Greenbelt Rd,Mail Code 444, Greenbelt, MD 20771 USA. NR 5 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-629-6 J9 ADV ASTRONAUT SCI PY 2016 VL 156 BP 1379 EP 1398 PN I-IV PG 20 WC Engineering, Aerospace SC Engineering GA BG2OP UT WOS:000387517700080 ER PT S AU Karpenko, M Ross, IM Stoneking, ET Lebsock, KL Dennehy, N AF Karpenko, Mark Ross, I. Michael Stoneking, Eric T. Lebsock, Kenneth L. Dennehy, Neil BE Majji, M Turner, JD Wawrzyniak, GG Cerven, WT TI A MICRO-SLEW CONCEPT FOR PRECISION POINTING OF THE KEPLER SPACECRAFT SO ASTRODYNAMICS 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT AAS/AIAA Astrodynamics Specialist Conference CY AUG 11-13, 2015 CL Vail, CO SP Amer Astronaut Soc, Space Flight Mech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm ID FLIGHT AB In light of the failure of two of four reaction wheels, the pointing precision of the Kepler spacecraft became so severely degraded that its original mission of hunting planets near the Cygnus constellation could not be continued. Since the scientific instrument remained fully functional, a new mission for Kepler called the K2 mission was proposed. In the K2 mission, Kepler uses a hybrid control architecture for pointing in the ecliptic plane. With the hybrid control architecture, the achievable pointing precision depends on the minimum impulse bit of the spacecraft reaction control system. This paper describes an alternative control strategy called the micro-slew which can be executed with reaction wheels only and used to reduce the control deadband associated with a hybrid control architecture. The new idea may therefore improve the pointing precision of the Kepler spacecraft beyond the K2 mission. The micro-slew concept is based on the observation that the solar radiation pressure acting on Kepler as a disturbance torque can be repurposed as a control torque in order to eliminate reliance on thrusters for three axis control. This is done by designing a three-axis attitude maneuver over small angles (less than 10(-4) rad) using concepts from optimal control. C1 [Karpenko, Mark; Ross, I. Michael] Naval Postgrad Sch, Dept Mech & Aerosp Engn, 700 Dyer Rd, Monterey, CA 93943 USA. [Stoneking, Eric T.] NASA, Goddard Spaceflight Ctr, Code 591, Greenbelt, MD 20771 USA. [Lebsock, Kenneth L.] Orbital Sci Corp, Tech Serv Div, 7500 Greenway Ctr Dr,Suite 1500, Greenbelt, MD 20770 USA. [Dennehy, Neil] NASA, Guidance Nav & Control, Engn Safety Ctr, Langley Res Ctr, Mail Stop 118, Hampton, VA 23681 USA. RP Karpenko, M (reprint author), Naval Postgrad Sch, Dept Mech & Aerosp Engn, 700 Dyer Rd, Monterey, CA 93943 USA. EM mkarpenk@nps.edu NR 13 TC 0 Z9 0 U1 1 U2 1 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-629-6 J9 ADV ASTRONAUT SCI PY 2016 VL 156 BP 1463 EP 1478 PN I-IV PG 16 WC Engineering, Aerospace SC Engineering GA BG2OP UT WOS:000387517700085 ER PT S AU Queen, SZ Shah, N Benegalrao, SS Blackman, K AF Queen, Steven Z. Shah, Neerav Benegalrao, Suyog S. Blackman, Kathie BE Majji, M Turner, JD Wawrzyniak, GG Cerven, WT TI GENERALIZED MOMENTUM CONTROL OF THE SPIN STABILIZED MAGNETOSPHERIC MULTISCALE FORMATION SO ASTRODYNAMICS 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT AAS/AIAA Astrodynamics Specialist Conference CY AUG 11-13, 2015 CL Vail, CO SP Amer Astronaut Soc, Space Flight Mech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm AB The Magnetospheric Multiscale (MMS) mission consists of four identically instrumented, spin-stabilized observatories elliptically orbiting the Earth in a tetrahedron formation. The on-board attitude control system adjusts the angular momentum of the system using a generalized thruster-actuated control system that simultaneously manages precession, nutation and spin. Originally developed using Lyapunov control-theory with rate-feedback, a published algorithm has been augmented to provide a balanced attitude/rate response using a single weighting parameter. This approach overcomes an orientation sign-ambiguity in the existing formulation, and also allows for a smoothly tuned-response applicable to both a compact/agile spacecraft, as well as one with large articulating appendages. C1 [Queen, Steven Z.; Shah, Neerav; Benegalrao, Suyog S.] NASA, Goddard Spaceflight Ctr, Attitude Control Syst Engn Branch, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. [Blackman, Kathie] Hammers Co, 7500 Greenway Ctr Dr,Suite 1500, Greenbelt, MD 20770 USA. RP Queen, SZ (reprint author), NASA, Goddard Spaceflight Ctr, Attitude Control Syst Engn Branch, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. NR 12 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-629-6 J9 ADV ASTRONAUT SCI PY 2016 VL 156 BP 2265 EP 2281 PN I-IV PG 17 WC Engineering, Aerospace SC Engineering GA BG2OP UT WOS:000387517700132 ER PT S AU Qu, M Merrill, RG Chai, P Komar, DR AF Qu, Min Merrill, Raymond G. Chai, Patrick Komar, David R. BE Majji, M Turner, JD Wawrzyniak, GG Cerven, WT TI TRAJECTORY DESIGNS FOR A MARS HYBRID TRANSPORTATION ARCHITECTURE SO ASTRODYNAMICS 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT AAS/AIAA Astrodynamics Specialist Conference CY AUG 11-13, 2015 CL Vail, CO SP Amer Astronaut Soc, Space Flight Mech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm AB NASA's Human spaceflight Architecture Team (HAT) team is developing a reusable hybrid transportation architecture in which both chemical and electric propulsion systems are used to send crew and cargo to Mars destinations such as Phobos, Deimos, the surface of Mars, and other orbits around Mars. By combining chemical and electrical propulsions into a single spaceship and applying each where it is the most effective, the hybrid architecture enables a series of Mars trajectories that are more fuel-efficient than an all chemical architecture without significant increases in flight times. This paper documents the methods and techniques used for the trajectory designs of the architecture, some of which have shown to provide propellant or delta-V savings over traditional methods. C1 [Qu, Min] Analyt Mech Associates Inc, 21 Enterprise Pkwy,Suite 300, Hampton, VA 23666 USA. [Merrill, Raymond G.; Chai, Patrick; Komar, David R.] NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Qu, M (reprint author), Analyt Mech Associates Inc, 21 Enterprise Pkwy,Suite 300, Hampton, VA 23666 USA. NR 8 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-629-6 J9 ADV ASTRONAUT SCI PY 2016 VL 156 BP 2319 EP 2332 PN I-IV PG 14 WC Engineering, Aerospace SC Engineering GA BG2OP UT WOS:000387517700135 ER PT S AU Englander, JA Vavrina, MA Hinckley, D AF Englander, Jacob A. Vavrina, Matthew A. Hinckley, David, Jr. BE Majji, M Turner, JD Wawrzyniak, GG Cerven, WT TI MULTI-OBJECTIVE HYBRID OPTIMAL CONTROL FOR MULTIPLE-FLYBY INTERPLANETARY MISSION DESIGN USING CHEMICAL PROPULSION SO ASTRODYNAMICS 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT AAS/AIAA Astrodynamics Specialist Conference CY AUG 11-13, 2015 CL Vail, CO SP Amer Astronaut Soc, Space Flight Mech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm ID GRAVITY-ASSIST TRAJECTORIES; GLOBAL OPTIMIZATION; GENETIC ALGORITHM AB Preliminary design of high-thrust interplanetary missions is a highly complex process. The mission designer must choose discrete parameters such as the number of flybys and the bodies at which those flybys are performed. For some missions, such as surveys of small bodies, the mission designer also contributes to target selection. In addition, real-valued decision variables, such as launch epoch, flight times, maneuver and flyby epochs, and flyby altitudes must be chosen. There are often many thousands of possible trajectories to be evaluated. The customer who commissions a trajectory design is not usually interested in a point solution, but rather the exploration of the trade space of trajectories between several different objective functions. This can be a very expensive process in terms of the number of human analyst hours required. An automated approach is therefore very desirable. This work presents such an approach by posing the impulsive mission design problem as a multi-objective hybrid optimal control problem. The method is demonstrated on several real-world problems. C1 [Englander, Jacob A.] NASA, Goddard Space Flight Ctr, Nav & Mission Design Branch, Greenbelt, MD 20771 USA. [Vavrina, Matthew A.] Ai Solut Inc, 10001 Derekwood Lane,Suite 215, Lanham, MD 20706 USA. [Hinckley, David, Jr.] Univ Vermont, Dept Mech Engn, Burlington, VT 05405 USA. RP Englander, JA (reprint author), NASA, Goddard Space Flight Ctr, Nav & Mission Design Branch, Greenbelt, MD 20771 USA. NR 36 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-629-6 J9 ADV ASTRONAUT SCI PY 2016 VL 156 BP 2333 EP 2352 PN I-IV PG 20 WC Engineering, Aerospace SC Engineering GA BG2OP UT WOS:000387517700136 ER PT S AU Hinckley, DW Englander, JA Hitt, DL AF Hinckley, David W., Jr. Englander, Jacob A. Hitt, Darren L. BE Majji, M Turner, JD Wawrzyniak, GG Cerven, WT TI GLOBAL OPTIMIZATION OF INTERPLANETARY TRAJECTORIES IN THE PRESENCE OF REALISTIC MISSION CONSTRAINTS SO ASTRODYNAMICS 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT AAS/AIAA Astrodynamics Specialist Conference CY AUG 11-13, 2015 CL Vail, CO SP Amer Astronaut Soc, Space Flight Mech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm AB Interplanetary missions are often subject to difficult constraints, like solar phase angle upon arrival at the destination, velocity at arrival, and altitudes for flybys. Preliminary design of such missions is often conducted by solving the unconstrained problem and then filtering away solutions which do not naturally satisfy the constraints. However this can bias the search into non-advantageous regions of the solution space, so it can be better to conduct preliminary design with the full set of constraints imposed. In this work a stochastic global search method is developed which is well suited to the constrained global interplanetary trajectory optimization problem. C1 [Hinckley, David W., Jr.; Hitt, Darren L.] Univ Vermont, Dept Mech Engn, Burlington, VT 05405 USA. [Englander, Jacob A.] NASA, Goddard Space Flight Ctr, Nav & Mission Design Branch, Greenbelt, MD 20771 USA. RP Hinckley, DW (reprint author), Univ Vermont, Dept Mech Engn, Burlington, VT 05405 USA. NR 8 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-629-6 J9 ADV ASTRONAUT SCI PY 2016 VL 156 BP 2407 EP 2426 PN I-IV PG 20 WC Engineering, Aerospace SC Engineering GA BG2OP UT WOS:000387517700140 ER PT S AU Landau, D AF Landau, Damon BE Majji, M Turner, JD Wawrzyniak, GG Cerven, WT TI EFFICIENT MANEUVER PLACEMENT FOR AUTOMATED TRAJECTORY DESIGN SO ASTRODYNAMICS 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT AAS/AIAA Astrodynamics Specialist Conference CY AUG 11-13, 2015 CL Vail, CO SP Amer Astronaut Soc, Space Flight Mech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm AB When designing a mission, the addition of a maneuver at the right spot often improves the utility of an otherwise mediocre trajectory. However, the additional degrees of freedom of finding the best maneuver location can severely complicate automated broad-search algorithms. A computationally-efficient formulation that reduces the maneuver design space to a single dimension is presented, where the efficacy of additional maneuvers along previously computed transfers is calculated explicitly via Lawden's "primer vector." Examples include leveraging maneuvers to ease capture at Europa, phasing maneuvers to enable resonant-hopping among Saturn's moons, and broken-plane maneuvers on transfers to Mars. C1 [Landau, Damon] CALTECH, Jet Prop Lab, Syst Engn Sect, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Landau, D (reprint author), CALTECH, Jet Prop Lab, Syst Engn Sect, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 11 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-629-6 J9 ADV ASTRONAUT SCI PY 2016 VL 156 BP 2427 EP 2446 PN I-IV PG 20 WC Engineering, Aerospace SC Engineering GA BG2OP UT WOS:000387517700141 ER PT S AU De Smet, S Parker, JS Herman, JFC Aziz, J Barbee, BW Englander, JA AF De Smet, Stijn Parker, Jeffrey S. Herman, Jonathan F. C. Aziz, Jonathan Barbee, Brent W. Englander, Jacob A. BE Majji, M Turner, JD Wawrzyniak, GG Cerven, WT TI IDENTIFYING ACCESSIBLE NEAR-EARTH OBJECTS FOR CREWED MISSIONS WITH SOLAR ELECTRIC PROPULSION SO ASTRODYNAMICS 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT AAS/AIAA Astrodynamics Specialist Conference CY AUG 11-13, 2015 CL Vail, CO SP Amer Astronaut Soc, Space Flight Mech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm AB This paper discusses the expansion of the Near-Earth Object Human Space Flight Accessible Targets Study (NHATS)(1) with Solar Electric Propulsion (SEP). The research investigates the existence of new launch seasons that would have been impossible to achieve using only chemical propulsion. Furthermore, this paper shows that SEP can be used to significantly reduce the launch mass and in some cases the flight time of potential missions as compared to the current, purely chemical trajectories identified by the NHATS project. C1 [De Smet, Stijn; Parker, Jeffrey S.; Herman, Jonathan F. C.; Aziz, Jonathan] Univ Colorado, Colorado Ctr Astrodynam Res, 431 UCB, Boulder, CO 80309 USA. [Barbee, Brent W.; Englander, Jacob A.] NASA GSFC, Code 595,8800 Greenbelt Rd, Greenbelt, MD 20771 USA. RP De Smet, S (reprint author), Univ Colorado, Colorado Ctr Astrodynam Res, 431 UCB, Boulder, CO 80309 USA. NR 21 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-629-6 J9 ADV ASTRONAUT SCI PY 2016 VL 156 BP 2523 EP 2541 PN I-IV PG 19 WC Engineering, Aerospace SC Engineering GA BG2OP UT WOS:000387517700146 ER PT S AU Roberts, CE Case, S Reagoso, J Webster, C AF Roberts, Craig E. Case, Sara Reagoso, John Webster, Cassandra BE Majji, M Turner, JD Wawrzyniak, GG Cerven, WT TI EARLY MISSION MANEUVER OPERATIONS FOR THE DEEP SPACE CLIMATE OBSERVATORY SUN-EARTH L1 LIBRATION POINT MISSION SO ASTRODYNAMICS 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT AAS/AIAA Astrodynamics Specialist Conference CY AUG 11-13, 2015 CL Vail, CO SP Amer Astronaut Soc, Space Flight Mech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm AB The Deep Space Climate Observatory mission launched on February 11, 2015, and inserted onto a transfer trajectory toward a Lissajous orbit around the Sun Earth L1 libration point. This paper presents an overview of the baseline transfer orbit and early mission maneuver operations leading up to the start of nominal science orbit operations. In particular, the analysis and performance of the spacecraft insertion, mid-course correction maneuvers, and the deep-space Lissajous orbit insertion maneuvers are discussed, comparing the baseline orbit with actual mission results and highlighting mission and operations constraints. C1 [Roberts, Craig E.; Case, Sara; Reagoso, John] Ai Solut Inc, 10001 Derekwood Lane,Suite 215, Lanham, MD 20706 USA. [Webster, Cassandra] NASA, Goddard Space Flight Ctr, Nav & Mission Design Branch, Code 595,8800 Greenbelt Rd, Greenbelt, MD 20771 USA. RP Roberts, CE (reprint author), Ai Solut Inc, 10001 Derekwood Lane,Suite 215, Lanham, MD 20706 USA. EM craig.roberts@ai-solutions.com; sara.case@ai-solutions.com; john.reagoso@ai-solutions.com; cassandra.m.alberding@nasa.gov NR 11 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-629-6 J9 ADV ASTRONAUT SCI PY 2016 VL 156 BP 2635 EP 2654 PN I-IV PG 20 WC Engineering, Aerospace SC Engineering GA BG2OP UT WOS:000387517700152 ER PT S AU Pinson, R Lu, P AF Pinson, Robin Lu, Ping BE Majji, M Turner, JD Wawrzyniak, GG Cerven, WT TI RAPID GENERATION OF OPTIMAL ASTEROID POWERED DESCENT TRAJECTORIES VIA CONVEX OPTIMIZATION SO ASTRODYNAMICS 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT AAS/AIAA Astrodynamics Specialist Conference CY AUG 11-13, 2015 CL Vail, CO SP Amer Astronaut Soc, Space Flight Mech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm ID GUIDANCE AB This paper investigates a convex optimization based method that can rapidly generate the fuel optimal asteroid powered descent trajectory. The ultimate goal is to autonomously design the optimal powered descent trajectory on-board the spacecraft immediately prior to the descent burn. Compared to a planetary powered landing problem, the major difficulty is the complex gravity field near the surface of an asteroid that cannot be approximated by a constant gravity field. This paper uses relaxation techniques and a successive solution process that seeks the solution to the original nonlinear, nonconvex problem through the solutions to a sequence of convex optimal control problems. C1 [Pinson, Robin] NASA, Marshall Space Flight Ctr, Guidance Nav & Mission Anal Branch, Mail Stop EV42, Msfc, AL 35812 USA. [Lu, Ping] Iowa State Univ, Dept Aerosp Engn, 537 Bissell Rd, Ames, IA 50011 USA. RP Pinson, R (reprint author), NASA, Marshall Space Flight Ctr, Guidance Nav & Mission Anal Branch, Mail Stop EV42, Msfc, AL 35812 USA. NR 20 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-629-6 J9 ADV ASTRONAUT SCI PY 2016 VL 156 BP 2655 EP 2672 PN I-IV PG 18 WC Engineering, Aerospace SC Engineering GA BG2OP UT WOS:000387517700153 ER PT S AU McElrath, TP Anderson, RL AF McElrath, Timothy P. Anderson, Rodney L. BE Majji, M Turner, JD Wawrzyniak, GG Cerven, WT TI SWITCHING PATHS AT THE LUNAR 'ROUTER': FINDING VERY LOW-COST TRANSFERS BETWEEN USEFUL TRAJECTORY SEQUENCES IN THE EARTH-MOON SYSTEM SO ASTRODYNAMICS 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT AAS/AIAA Astrodynamics Specialist Conference CY AUG 11-13, 2015 CL Vail, CO SP Amer Astronaut Soc, Space Flight Mech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm ID CYCLER TRAJECTORIES; MARS CYCLER; ORBIT AB The Earth-Moon system allows many types of transfers between lunar encounters, including orbits with low perigees. Combinations of transfers can produce several different useful ballistic trajectory sequences. With the right orbit types (particularly backflips) included, a low thrust vehicle can cheaply switch between sequences that have very different characteristics. Several useful repeat sequences are presented in the circular restricted 3-body problem (CR3BP) model, and examples of these are demonstrated in the full ephemeris. These trajectory sequences would be particularly applicable for returned asteroids (in the near term) and lunar-derived resource transport (in the long term), where only very limited delta-V is available due to the large mass of the vehicle. C1 [McElrath, Timothy P.; Anderson, Rodney L.] CALTECH, Jet Prop Lab, Mission Design & Nav Sect, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP McElrath, TP (reprint author), CALTECH, Jet Prop Lab, Mission Design & Nav Sect, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 23 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-629-6 J9 ADV ASTRONAUT SCI PY 2016 VL 156 BP 2687 EP 2705 PN I-IV PG 19 WC Engineering, Aerospace SC Engineering GA BG2OP UT WOS:000387517700155 ER PT S AU Litton, DK Lugo, RA Qu, M Craig, AS Shidner, JD Adebonojo, BO Winski, RG Powell, RW AF Litton, Daniel K. Lugo, Rafael A. Qu, Min Craig, Anthony S. Shidner, Jeremy D. Adebonojo, Badejo O., Jr. Winski, Richard G. Powell, Richard W. BE Majji, M Turner, JD Wawrzyniak, GG Cerven, WT TI CREATING AN END-TO-END SIMULATION FOR THE MULTIPURPOSE CREWED VEHICLE AND SPACE LAUNCH SYSTEM SO ASTRODYNAMICS 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT AAS/AIAA Astrodynamics Specialist Conference CY AUG 11-13, 2015 CL Vail, CO SP Amer Astronaut Soc, Space Flight Mech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm AB The NASA Engineering & Safety Center (NESC) has commissioned a study to determine the benefits of combining the Space Launch System (SLS) high fidelity trajectory simulations for ascent, the Multi-Purpose Crew Vehicle's (MPCV) simulations for on-orbit operations, and Earth re-entry simulation using a Multidisciplinary Design Optimization (MDO) approach. A commercially available program, Isight, has been selected to combine and optimize all the facets for the Exploration Mission 1 (EM-1). This seamless integration of all the aspects will enable Mission Planners to directly determine the interactions between all phases of the mission. Mission Planners will have more insight in determining overall mission feasibility, margins, and vehicle sizing. The end-to-end integration enables investigation of mission design parameters such as only launching during the day. The ability to easily modify parameters such as launch time and main engine cut-off (MECO) targets not only help determine mission feasibility but also facilitate saving on operation and mission design costs. C1 [Litton, Daniel K.] NASA, Langley Res Ctr, Atmospher Flight & Entry Syst Branch, Hampton, VA 23681 USA. [Lugo, Rafael A.; Qu, Min; Shidner, Jeremy D.; Winski, Richard G.; Powell, Richard W.] Analyt Mech Associates Inc, 21 Enterprise Pkwy Suite 300, Hampton, VA 23666 USA. [Craig, Anthony S.] ERC Inc, Jacobs ESSSA Grp, Huntsville, AL 35812 USA. [Adebonojo, Badejo O., Jr.] Jacobs Technol, Jacobs ESSSA Grp, Huntsville, AL 35812 USA. RP Litton, DK (reprint author), NASA, Langley Res Ctr, Atmospher Flight & Entry Syst Branch, Hampton, VA 23681 USA. NR 11 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-629-6 J9 ADV ASTRONAUT SCI PY 2016 VL 156 BP 2727 EP 2743 PN I-IV PG 17 WC Engineering, Aerospace SC Engineering GA BG2OP UT WOS:000387517700157 ER PT S AU Whitley, R Gutkowski, J Craig, S Dawn, T Williams, J Ocampo, C Stein, WB Litton, D Lugo, R Qu, M AF Whitley, Ryan Gutkowski, Jeffrey Craig, Scott Dawn, Tim Williams, Jacob Ocampo, Cesar Stein, William B. Litton, Daniel Lugo, Rafael Qu, Min BE Majji, M Turner, JD Wawrzyniak, GG Cerven, WT TI COMBINING SIMULATION TOOLS FOR END-TO-END TRAJECTORY OPTIMIZATION SO ASTRODYNAMICS 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT AAS/AIAA Astrodynamics Specialist Conference CY AUG 11-13, 2015 CL Vail, CO SP Amer Astronaut Soc, Space Flight Mech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm AB Trajectory simulations with advanced optimization algorithms are invaluable tools in the process of designing spacecraft. Due to the need for complex models, simulations are often highly tailored to the needs of the particular program or mission. NASA's Orion and SLS programs are no exception. While independent analyses are valuable to assess individual spacecraft capabilities, a complete end-to-end trajectory from launch to splashdown maximizes potential performance and ensures a continuous solution. In order to obtain end-to-end capability, Orion's in-space tool (Copernicus) was made to interface directly with the SLS's ascent tool (POST2) and a new tool to optimize the full problem by operating both simulations simultaneously was born. C1 [Whitley, Ryan] NASA JSC, Explorat Mission Planning Off, Houston, TX 77058 USA. [Gutkowski, Jeffrey] NASA JSC, Flight Mech & Trajectory Design Branch, Houston, TX 77058 USA. [Craig, Scott; Dawn, Tim] ERC Inc, NASA MSFC, Jacobs ESSSA Grp, Huntsville, AL 35812 USA. [Williams, Jacob] ERC Inc, Houston, TX 77058 USA. [Ocampo, Cesar] Univ Sergio Arboleda, Engn, Bogota, Colombia. [Ocampo, Cesar] Colombia & Odyssey Space Res LLC, Houston, TX 77058 USA. [Stein, William B.] NASA MSFC, Jacobs Technol, Jacobs ESSSA Grp, Huntsville, AL 35812 USA. [Litton, Daniel; Qu, Min] NASA LaRC, Atmospher Flight & Syst Branch, Hampton, VA 23681 USA. [Lugo, Rafael] Analyt Mech Associates, 21 Enterprise Pkwy,Suite 300, Hampton, VA 23666 USA. RP Whitley, R (reprint author), NASA JSC, Explorat Mission Planning Off, Houston, TX 77058 USA. NR 15 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-629-6 J9 ADV ASTRONAUT SCI PY 2016 VL 156 BP 2811 EP 2826 PN I-IV PG 16 WC Engineering, Aerospace SC Engineering GA BG2OP UT WOS:000387517700162 ER PT S AU Strange, N Longuski, J AF Strange, Nathan Longuski, James BE Majji, M Turner, JD Wawrzyniak, GG Cerven, WT TI COMPARISON OF OVERALL PROPULSION SYSTEM EFFECTIVENESS FOR ORBIT INSERTION AND ESCAPE SO ASTRODYNAMICS 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT AAS/AIAA Astrodynamics Specialist Conference CY AUG 11-13, 2015 CL Vail, CO SP Amer Astronaut Soc, Space Flight Mech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm AB Although specific impulse is often used as the primary measure of propulsion system efficiency, lower specific impulse systems with a smaller inert masses can often provide better performance than higher specific impulse systems. In addition, chemical propulsion systems can outperform much higher specific impulse electric propulsion systems when they can take advantage of the Oberth effect, i.e. an impulsive maneuver deep in a gravity well. We show that for many cases solid rockets would outperform higher specific impulse liquid systems. We also show that for low v-infinities, chemical systems would outperform electric propulsion systems for orbit insertion and escape maneuvers. C1 [Strange, Nathan] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Longuski, James] Purdue Univ, Sch Aeronaut & Astronaut, 701 W Stadium Ave, W Lafayette, IN 47907 USA. RP Strange, N (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 11 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-629-6 J9 ADV ASTRONAUT SCI PY 2016 VL 156 BP 2955 EP 2964 PN I-IV PG 10 WC Engineering, Aerospace SC Engineering GA BG2OP UT WOS:000387517700172 ER PT S AU Roa, J Pelaez, J AF Roa, Javier Pelaez, Jesus BE Majji, M Turner, JD Wawrzyniak, GG Cerven, WT TI GENERALIZED LOGARITHMIC SPIRALS FOR LOW-THRUST TRAJECTORY DESIGN SO ASTRODYNAMICS 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT AAS/AIAA Astrodynamics Specialist Conference CY AUG 11-13, 2015 CL Vail, CO SP Amer Astronaut Soc, Space Flight Mech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm AB Shape-based approaches are practical for finding sub-optimal solutions during the preliminary design of low-thrust trajectories. Logarithmic spirals are the simplest, but of little practical interest due to having a constant flight-path angle. We prove that the same tangential thrust profile that generates a logarithmic spiral yields an entire family of generalized spirals. The system admits two integrals of motion, which are equivalent to the energy and the angular momentum equations. Three different subfamilies of spiral trajectories are obtained depending on the sign of the constant of the generalized energy: elliptic, parabolic, and hyperbolic. Parabolic spirals are equivalent to logarithmic spirals. Elliptic spirals are bounded; never escape to infinity and the trajectory is symmetric. Two types of hyperbolic spirals have been found: the first has only one asymptote; the second has two asymptotes, the trajectory is symmetric and never falls to the origin. The solution is obtained when solving rigorously the equations of motion with no prior assumptions. Closed-form expressions for both the trajectory and the time of flight are provided. C1 [Roa, Javier; Pelaez, Jesus] Tech Univ Madrid UPM, Space Dynam Grp, Plaza Cardenal Cisneros 3, Madrid 28040, Spain. [Roa, Javier] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Roa, J (reprint author), Tech Univ Madrid UPM, Space Dynam Grp, Plaza Cardenal Cisneros 3, Madrid 28040, Spain.; Roa, J (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM javier.roa@upm.es NR 10 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-629-6 J9 ADV ASTRONAUT SCI PY 2016 VL 156 BP 2977 EP 2996 PN I-IV PG 20 WC Engineering, Aerospace SC Engineering GA BG2OP UT WOS:000387517700174 ER PT S AU Stuart, J McElrath, T Petropoulos, A AF Stuart, Jeffrey McElrath, Tim Petropoulos, Anastassios BE Majji, M Turner, JD Wawrzyniak, GG Cerven, WT TI MISSION DESIGN ANALYSIS FOR THE MARTIAN MOON PHOBOS: CLOSE FLYBYS, MISSED THRUSTS, AND OTHER IN-FLIGHT ENTERTAINMENT SO ASTRODYNAMICS 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT AAS/AIAA Astrodynamics Specialist Conference CY AUG 11-13, 2015 CL Vail, CO SP Amer Astronaut Soc, Space Flight Mech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm ID EXPLORATION; SATELLITES; ORBITS AB A robotic mission to the Martian moons Phobos and Deimos would offer a wealth of scientific information and serve as a useful precursor to potential human missions. In this paper, we investigate a prospective mission enabled by solar electric propulsion that would explore Phobos via a series of flybys followed by capture into orbit around the moon. Of particular interest are low 6.7 options for capture and walkdown to the target science orbits aided by multi-body effects due to the mutual gravitational interaction of Phobos and Mars. We also consider contingency operations in the event of missed thrust or maneuver execution errors. C1 [Stuart, Jeffrey] CALTECH, Jet Prop Lab, Nav & Mission Design Syst Engn Grp, Mission Design & Nav Sect, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [McElrath, Tim] CALTECH, Jet Prop Lab, Mission Design & Nav Sect, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Petropoulos, Anastassios] CALTECH, Jet Prop Lab, Mission Design & Nav Sect, Outer Planet Mission Anal Grp, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Stuart, J (reprint author), CALTECH, Jet Prop Lab, Nav & Mission Design Syst Engn Grp, Mission Design & Nav Sect, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM jeffrey.r.stuart@jpl.nasa.gov; timothy.p.mcelrath@jpl.nasa.gov; anastassios.e.petropoulos@jpl.nasa.gov NR 11 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-629-6 J9 ADV ASTRONAUT SCI PY 2016 VL 156 BP 2997 EP 3016 PN I-IV PG 20 WC Engineering, Aerospace SC Engineering GA BG2OP UT WOS:000387517700175 ER PT S AU Arora, N Strange, N Alkalai, L AF Arora, Nitin Strange, Nathan Alkalai, Leon BE Majji, M Turner, JD Wawrzyniak, GG Cerven, WT TI TRAJECTORIES FOR A NEAR TERM MISSION TO THE INTERSTELLAR MEDIUM SO ASTRODYNAMICS 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT AAS/AIAA Astrodynamics Specialist Conference CY AUG 11-13, 2015 CL Vail, CO SP Amer Astronaut Soc, Space Flight Mech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm ID HYPERBOLIC ASYMPTOTES; EXPLORER; DESIGN; TRANSFERS AB Trajectories for rapid access to the interstellar medium (ISM) with a Kuiper Belt Object (KBO) flyby, launching between 2022 and 2030, are described. An impulsive-patched-conic broad search algorithm combined with a local optimizer is used for the trajectory computations. Two classes of trajectories, (1) with a powered Jupiter flyby and (2) with a perihelion maneuver, are studied and compared. Planetary flybys combined with leveraging maneuvers reduce launch C-3 requirements (by factor of 2 or more) and help satisfy mission-phasing constraints. Low launch C-3 combined with leveraging and a perihelion maneuver is found to be enabling for a near-term mission to the ISM. C1 [Arora, Nitin; Strange, Nathan; Alkalai, Leon] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Arora, N (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Nitin.Arora@jpl.nasa.gov; Nathan.J.Strange@jpl.nasa.gov; leon.alkalai@jpl.nasa.gov NR 35 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-629-6 J9 ADV ASTRONAUT SCI PY 2016 VL 156 BP 3037 EP 3055 PN I-IV PG 19 WC Engineering, Aerospace SC Engineering GA BG2OP UT WOS:000387517700177 ER PT S AU Genova, AL Aldrin, B AF Genova, Anthony L. Aldrin, Buzz BE Majji, M Turner, JD Wawrzyniak, GG Cerven, WT TI CIRCUMLUNAR FREE-RETURN CYCLER ORBITS FOR A MANNED EARTH-MOON SPACE STATION SO ASTRODYNAMICS 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT AAS/AIAA Astrodynamics Specialist Conference CY AUG 11-13, 2015 CL Vail, CO SP Amer Astronaut Soc, Space Flight Mech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm ID WATER ICE AB Multiple free-return circumlunar cycler orbits were designed to allow regular travel between the Earth and Moon by a manned space station. The presented cycler orbits contain circumlunar free-return "figure-8" segments and yield lunar encounters every month. Smaller space "taxi" vehicles can rendezvous with (and depart from) the cycling Earth-Moon space station to enter lunar orbit (and/or land on the lunar surface), return to Earth, or reach destinations including Earth Moon halo orbits, near-Earth objects (NEOs), and Mars. To assess the practicality of the selected orbits, relevant cycler characteristics (including AV maintenance requirements) are presented and compared. C1 [Genova, Anthony L.] NASA, Ames Res Ctr, Mission Design Div, Moffett Field, CA 94035 USA. [Aldrin, Buzz] Buzz Aldrin Enterprises LLC, Satellite Beach, FL 32937 USA. RP Genova, AL (reprint author), NASA, Ames Res Ctr, Mission Design Div, Moffett Field, CA 94035 USA. NR 49 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-629-6 J9 ADV ASTRONAUT SCI PY 2016 VL 156 BP 3143 EP 3162 PN I-IV PG 20 WC Engineering, Aerospace SC Engineering GA BG2OP UT WOS:000387517700183 ER PT S AU Wagner, SV Menon, PR Chung, MKJ Williams, JL AF Wagner, Sean V. Menon, Premkumar R. Chung, Min-Kun J. Williams, Jessica L. BE Majji, M Turner, JD Wawrzyniak, GG Cerven, WT TI MARS RECONNAISSANCE ORBITER NAVIGATION STRATEGY FOR DUAL SUPPORT OF INSIGHT AND EXOMARS ENTRY, DESCENT AND LANDING DEMONSTRATOR MODULE IN 2016 SO ASTRODYNAMICS 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT AAS/AIAA Astrodynamics Specialist Conference CY AUG 11-13, 2015 CL Vail, CO SP Amer Astronaut Soc, Space Flight Mech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm AB Mars Reconnaissance Orbiter (MRO) will support NASA's InSight Mission and ESA's ExoMars Entry, Descent and Landing Demonstrator Module (EDM) in the fall of 2016 when both landers arrive at Mars. MRO provided relay support during the Entry, Descent and Landing (EDL) sequences of the Mars Phoenix Lander in May 2008 and the Mars Science Laboratory in August 2012. Unlike these missions, MRO will coordinate between two EDL events separated by only three weeks: InSight on September 28, 2016 and EDM on October 19, 2016. This paper describes the MRO Navigation Team's maneuver strategy to move the spacecraft's ascending node for InSight EDL support and to adjust the orbit timing (phasing) to meet InSight and EDM phasing requirements. C1 [Wagner, Sean V.; Menon, Premkumar R.; Chung, Min-Kun J.; Williams, Jessica L.] Jet Prop Lab, Mars Reconnaissance Orbiter Nav, Mail Stop 230-205,4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Wagner, Sean V.; Menon, Premkumar R.; Chung, Min-Kun J.; Williams, Jessica L.] Jet Prop Lab, Mission Design & Nav Sect, Mail Stop 230-205,4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Wagner, SV (reprint author), Jet Prop Lab, Mars Reconnaissance Orbiter Nav, Mail Stop 230-205,4800 Oak Grove Dr, Pasadena, CA 91109 USA.; Wagner, SV (reprint author), Jet Prop Lab, Mission Design & Nav Sect, Mail Stop 230-205,4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 12 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-629-6 J9 ADV ASTRONAUT SCI PY 2016 VL 156 BP 3197 EP 3214 PN I-IV PG 18 WC Engineering, Aerospace SC Engineering GA BG2OP UT WOS:000387517700186 ER PT S AU Menon, PR Wagner, SV Martin-Mur, TJ Jefferson, DC Ardalan, SM Chung, MKJ Lee, KJ Schulze, WB AF Menon, Premkumar R. Wagner, Sean V. Martin-Mur, Tomas J. Jefferson, David C. Ardalan, Shadan M. Chung, Min-Kun J. Lee, Kyong J. Schulze, William B. BE Majji, M Turner, JD Wawrzyniak, GG Cerven, WT TI MARS RECONNAISSANCE ORBITER NAVIGATION STRATEGY FOR THE COMET SIDING SPRING ENCOUNTER SO ASTRODYNAMICS 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT AAS/AIAA Astrodynamics Specialist Conference CY AUG 11-13, 2015 CL Vail, CO SP Amer Astronaut Soc, Space Flight Mech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm ID DUST AB Comet Siding Spring encountered Mars on October 19, 2014 at a distance of about 140,500 km - the nearest comet flyby of a planet in recorded history. Mars Reconnaissance Orbiter (MRO) was able to detect the comet, gather science data, and capture images of the comet as it approached Mars. To help protect MRO from the incoming comet particles, two propulsive maneuvers were performed to position the spacecraft behind Mars at the arrival time of the expected peak particle fluency. This paper documents the strategy that the MRO Navigation Team executed to mitigate risk from the comet particles while allowing scientific observations of the comet flyby. C1 [Menon, Premkumar R.; Wagner, Sean V.; Martin-Mur, Tomas J.; Jefferson, David C.; Ardalan, Shadan M.; Chung, Min-Kun J.; Lee, Kyong J.] Jet Prop Lab, Mars Reconnaissance Orbiter Nav Team, Mail Stop 264-282,4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Schulze, William B.] CALTECH, Jet Prop Lab, Mission Design & Nav Sect, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Menon, PR (reprint author), Jet Prop Lab, Mars Reconnaissance Orbiter Nav Team, Mail Stop 264-282,4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Premkumar.R.Menon@jpl.nasa.gov NR 12 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-629-6 J9 ADV ASTRONAUT SCI PY 2016 VL 156 BP 3215 EP 3230 PN I-IV PG 16 WC Engineering, Aerospace SC Engineering GA BG2OP UT WOS:000387517700187 ER PT S AU Williams, B Pelletier, F Stanbridge, D Bauman, J Williams, K Jackman, C Nelson, D Dumont, P Wolff, P Bryan, C Taylor, A Guo, Y Rogers, G Jensen, R Stern, SA Weaver, HA Young, LA Ennico, K Olkin, CB AF Williams, B. Pelletier, F. Stanbridge, D. Bauman, J. Williams, K. Jackman, C. Nelson, D. Dumont, P. Wolff, P. Bryan, C. Taylor, A. Guo, Y. Rogers, G. Jensen, R. Stern, S. A. Weaver, H. A. Young, L. A. Ennico, K. Olkin, C. B. BE Majji, M Turner, JD Wawrzyniak, GG Cerven, WT TI NAVIGATION STRATEGY AND RESULTS FOR NEW HORIZONS' APPROACH AND FLYBY OF THE PLUTO SYSTEM SO ASTRODYNAMICS 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT AAS/AIAA Astrodynamics Specialist Conference CY AUG 11-13, 2015 CL Vail, CO SP Amer Astronaut Soc, Space Flight Mech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm ID MISSION; CHARON; DESIGN AB The New Horizons mission, the first mission in NASA's New Frontiers Program, is also the first mission with primary science objectives to explore the Pluto/Charon system. After launch in January 2006 and an interplanetary cruise of more than 9.5 years, New Horizons has completed the approach and flyby of Pluto. This paper presents an overview of the analysis and operational constraints that led to the navigation strategy used. Also presented are operational results for that strategy during this final phase of the prime mission. C1 [Williams, B.; Pelletier, F.; Stanbridge, D.; Bauman, J.; Williams, K.; Jackman, C.; Nelson, D.; Dumont, P.; Wolff, P.; Bryan, C.; Taylor, A.] KinetX Aerosp, Space Nav & Flight Dynam Practice, 21 W Easy St,Suite 108, Simi Valley, CA 93065 USA. [Guo, Y.; Rogers, G.; Jensen, R.; Weaver, H. A.] Johns Hopkins Univ, Appl Phys Lab, 11100 Johns Hopkins Rd, Laurel, MD 20723 USA. [Stern, S. A.; Young, L. A.; Olkin, C. B.] Southwest Res Inst, 1050 Walnut St,Suite 300, Boulder, CO 80302 USA. [Ennico, K.] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Williams, B (reprint author), KinetX Aerosp, Space Nav & Flight Dynam Practice, 21 W Easy St,Suite 108, Simi Valley, CA 93065 USA. NR 14 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-629-6 J9 ADV ASTRONAUT SCI PY 2016 VL 156 BP 3271 EP 3290 PN I-IV PG 20 WC Engineering, Aerospace SC Engineering GA BG2OP UT WOS:000387517700190 ER PT S AU D'Souza, C Zanetti, R AF D'Souza, Christopher Zanetti, Renato BE Majji, M Turner, JD Wawrzyniak, GG Cerven, WT TI NAVIGATION AND DISPERSION ANALYSIS OF THE FIRST ORION EXPLORATION MISSION SO ASTRODYNAMICS 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT AAS/AIAA Astrodynamics Specialist Conference CY AUG 11-13, 2015 CL Vail, CO SP Amer Astronaut Soc, Space Flight Mech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm AB This paper presents the Orion EM-1 Linear Covariance Analysis for the DRO mission. The vertical bar Delta V vertical bar statistics for each maneuver are presented. In particular, the statistics of the lunar encounters and the Entry Interface are presented. C1 [D'Souza, Christopher; Zanetti, Renato] NASA, Johnson Space Ctr, Code EG6, Houston, TX 77058 USA. RP D'Souza, C (reprint author), NASA, Johnson Space Ctr, Code EG6, Houston, TX 77058 USA. NR 4 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-629-6 J9 ADV ASTRONAUT SCI PY 2016 VL 156 BP 3311 EP 3330 PN I-IV PG 20 WC Engineering, Aerospace SC Engineering GA BG2OP UT WOS:000387517700192 ER PT S AU Wallace, MS AF Wallace, Mark S. BE Majji, M Turner, JD Wawrzyniak, GG Cerven, WT TI A MASSIVELY PARALLEL BAYESIAN APPROACH TO PLANETARY PROTECTION TRAJECTORY ANALYSIS AND DESIGN SO ASTRODYNAMICS 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT AAS/AIAA Astrodynamics Specialist Conference CY AUG 11-13, 2015 CL Vail, CO SP Amer Astronaut Soc, Space Flight Mech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm AB The NASA Planetary Protection Office has levied a requirement that the upper stage of future planetary launches have a less than le chance of impacting Mars within 50 years after launch. A brute-force approach requires a decade of computer time to demonstrate compliance. By using a Bayesian approach and taking advantage of the demonstrated reliability of the upper stage, the required number of fifty-year propagations can be massively reduced. By spreading the remaining embarrassingly parallel Monte Carlo simulations across multiple computers, compliance can be demonstrated in a reasonable time frame. The method used is described here. C1 [Wallace, Mark S.] CALTECH, Jet Prop Lab, Mission Design & Nav Sect, M-S 301-121,4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Wallace, MS (reprint author), CALTECH, Jet Prop Lab, Mission Design & Nav Sect, M-S 301-121,4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 6 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-629-6 J9 ADV ASTRONAUT SCI PY 2016 VL 156 BP 3333 EP 3346 PN I-IV PG 14 WC Engineering, Aerospace SC Engineering GA BG2OP UT WOS:000387517700193 ER PT S AU Arora, N Petropoulos, A AF Arora, Nitin Petropoulos, Anastassios BE Majji, M Turner, JD Wawrzyniak, GG Cerven, WT TI EXPERIMENTS WITH JULIA FOR ASTRODYNAMICS APPLICATIONS SO ASTRODYNAMICS 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT AAS/AIAA Astrodynamics Specialist Conference CY AUG 11-13, 2015 CL Vail, CO SP Amer Astronaut Soc, Space Flight Mech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm AB Julia's potential for solving complex astrodynamics problems is studied. Julia is a high-level, new, dynamic programming language with performance approaching C/Fortran and has features like inbuilt parallelism, variable accuracy, integrated numerical libraries and direct C and Fortran interfaces. Two astrodynamics problems are solved in Julia: 1) Lambert's problem, using the vercosine formulation and 2) trajectory integration. Implemented algorithms are compared with C and Fortran based counterparts on key performance parameters (speed, development effort, etc.). Using Julia for fast and reliable astrodynamics software development is also discussed. C1 [Arora, Nitin; Petropoulos, Anastassios] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Arora, N (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Nitin.Arora@jpl.nasa.gov; anastassios.e.petropoulos@jpl.nasa.gov NR 15 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-629-6 J9 ADV ASTRONAUT SCI PY 2016 VL 156 BP 3453 EP 3464 PN I-IV PG 12 WC Engineering, Aerospace SC Engineering GA BG2OP UT WOS:000387517700201 ER PT S AU Barbee, BW Chodas, PW AF Barbee, Brent W. Chodas, Paul W. BE Majji, M Turner, JD Wawrzyniak, GG Cerven, WT TI NEAR-EARTH ASTEROIDS 2006 RH120 AND 2009 BD: PROXIES FOR MAXIMALLY ACCESSIBLE OBJECTS? SO ASTRODYNAMICS 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT AAS/AIAA Astrodynamics Specialist Conference CY AUG 11-13, 2015 CL Vail, CO SP Amer Astronaut Soc, Space Flight Mech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm AB NASA's Near-Earth Object Human Space Flight Accessible Targets Study (NHATS) has identified over 1,400 of the approximately 12,800 currently known near-Earth asteroids (NEAs) as more astrodynamically accessible, round-trip, than Mars. Hundreds of those approximately 1,400 NEAs can be visited round-trip for less change-in-velocity than the lunar surface, and dozens can be visited round-trip for less change-in-velocity than low lunar orbit. How accessible might the millions of undiscovered NEAs be? We probe that question by investigating the hypothesis that NEAs 2006 RH120 and 2009 BD are proxies for the most accessible NEAs we would expect to find, and describing possible future NEA population model studies. C1 [Barbee, Brent W.] NASA, Goddard Space Flight Ctr, Code 595,8800 Greenbelt Rd, Greenbelt, MD 20771 USA. [Chodas, Paul W.] NASA, NEO Program Off, Jet Prop Lab, Solar Syst Dynam Grp, Mail Stop 301-121,4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Barbee, BW (reprint author), NASA, Goddard Space Flight Ctr, Code 595,8800 Greenbelt Rd, Greenbelt, MD 20771 USA. EM brent.w.barbee@nasa.gov; paul.chodas@jpl.nasa.gov NR 4 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-629-6 J9 ADV ASTRONAUT SCI PY 2016 VL 156 BP 3651 EP 3661 PN I-IV PG 11 WC Engineering, Aerospace SC Engineering GA BG2OP UT WOS:000387517700212 ER PT S AU Henning, A Maddock, R Samareh, J AF Henning, Allen Maddock, Robert Samareh, Jamshid BE Majji, M Turner, JD Wawrzyniak, GG Cerven, WT TI PASSIVE VS. PARACHUTE SYSTEM TRADE APPLIED TO THE MULTI-MISSION EARTH ENTRY VEHICLE CONCEPT SO ASTRODYNAMICS 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT AAS/AIAA Astrodynamics Specialist Conference CY AUG 11-13, 2015 CL Vail, CO SP Amer Astronaut Soc, Space Flight Mech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm AB The Multi-Mission Earth Entry Vehicle (MMEEV) is a flexible vehicle concept based on the Mars Sample Return (MSR) EEV design which can be used in the preliminary sample return mission study phase to parametrically investigate any trade space of interest to determine the best design approach for that particular mission concept. In addition to the trade space dimensions often considered (e.g. entry conditions, payload size and mass, vehicle size, etc.), the MMEEV trade space considers whether it might be more beneficial for the vehicle to utilize a parachute system during descent/landing or not (i.e. fully passive). In order to evaluate this trade space dimension, a simplified parachute system model, based on inputs such as vehicle size/mass, the payload size/mass and the landing requirements, has been developed. This model is then used in conjunction with analytical approximations of a mission trade space dataset provided by the MMEEV System Analysis for Planetary EDL (M-SAPE) trade space tool, to help quantify the differences between a passive and an active (with parachute) vehicle concept. Preliminary results over a range of EEV vehicle and mission constraints (including entry conditions, vehicle size, payload mass, and landing requirement) are provided. For most sample return missions, this latter constraint (landing velocity and/or load) is ultimately determined by science considerations (e.g. sample preservation or containment). Regions of the trade space where including a parachute system is clearly more beneficial versus those where a passive vehicle clearly provides a more mass efficient approach, are identified. Where the choice between the two architectures may be less clear, additional considerations, including factors such as overall system reliability; system risk and complexity; and development and testing costs, must also be taken in account. C1 [Henning, Allen] Virginia Polytech & State Univ, Aerosp & Ocean Engn, 460 Old Turner St, Blacksburg, VA 24060 USA. [Maddock, Robert] NASA, Langley Res Ctr, Atmospher Flight & Entry Syst Branch, Engn Directorate, Hampton, VA 23681 USA. [Samareh, Jamshid] NASA, Langley Res Ctr, Vehicle Anal Branch, Syst Anal & Concepts Directorate, Hampton, VA 23681 USA. RP Henning, A (reprint author), Virginia Polytech & State Univ, Aerosp & Ocean Engn, 460 Old Turner St, Blacksburg, VA 24060 USA. NR 11 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-629-6 J9 ADV ASTRONAUT SCI PY 2016 VL 156 BP 3701 EP 3715 PN I-IV PG 15 WC Engineering, Aerospace SC Engineering GA BG2OP UT WOS:000387517700215 ER PT S AU Shen, HJ Roithmayr, CM AF Shen, Haijun Roithmayr, Carlos M. BE Majji, M Turner, JD Wawrzyniak, GG Cerven, WT TI TOWING ASTEROIDS WITH GRAVITY TRACTORS ENHANCED BY TETHERS AND SOLAR SAILS SO ASTRODYNAMICS 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT AAS/AIAA Astrodynamics Specialist Conference CY AUG 11-13, 2015 CL Vail, CO SP Amer Astronaut Soc, Space Flight Mech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm ID NEAR-EARTH ASTEROIDS; DEFLECTION; SPACECRAFT; 433-EROS AB Material collected from an asteroid's surface can be used to increase gravitational attraction between the asteroid and a Gravity Tractor (GT); the spacecraft therefore operates more effectively and is referred to as an Enhanced Gravity Tractor (EGT). The use of tethers and solar sails to further improve effectiveness and simplify operations is investigated. By employing a tether, the asteroidal material can be placed close to the asteroid while the spacecraft is stationed farther away, resulting in a better safety margin and improved thruster efficiency. A solar sail on a spacecraft can naturally provide radial offset and inter-spacecraft separation required for multiple EGTs. C1 [Shen, Haijun] Analyt Mech Associates Inc, 21 Enterprise Pkwy,Suite 300, Hampton, VA 23666 USA. [Roithmayr, Carlos M.] NASA, Langley Res Ctr, Vehicle Anal Branch, MS 451,1 North Dryden St, Hampton, VA 23681 USA. RP Shen, HJ (reprint author), Analyt Mech Associates Inc, 21 Enterprise Pkwy,Suite 300, Hampton, VA 23666 USA. EM shen@ama-inc.com; carlos.m.roithmayr@nasa.gov NR 19 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-629-6 J9 ADV ASTRONAUT SCI PY 2016 VL 156 BP 3717 EP 3728 PN I-IV PG 12 WC Engineering, Aerospace SC Engineering GA BG2OP UT WOS:000387517700216 ER PT S AU Villac, BF Anderson, RL Pini, AJ AF Villac, Benjamin F. Anderson, Rodney L. Pini, Alex J. BE Majji, M Turner, JD Wawrzyniak, GG Cerven, WT TI ORGANIZING BALLISTIC ORBIT CLASSES AROUND SMALL BODIES SO ASTRODYNAMICS 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT AAS/AIAA Astrodynamics Specialist Conference CY AUG 11-13, 2015 CL Vail, CO SP Amer Astronaut Soc, Space Flight Mech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm ID INVARIANT-MANIFOLDS; TRAJECTORY DESIGN; RESONANCE; TRANSFERS; ASTEROIDS; VESTA AB Orbital dynamics around small bodies are as varied as the shape and dynamical states of these bodies. While various classes of orbits have been analyzed in detail, the global overview of relevant ballistic orbits at particular bodies is not easily computed or organized. Yet, correctly categorizing these orbits will ease their future use in the overall trajectory design process. This paper overviews methods that have been used to organize orbits, focusing on periodic orbits in particular, and introduces new methods based on clustering approaches. C1 [Villac, Benjamin F.] Ai Solut Inc, Mission Engn & Technol Div, 10001 Derekwood Lane,Suite 215, Lanham, MD 20706 USA. [Anderson, Rodney L.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,M-S 301-121, Pasadena, CA 91109 USA. [Pini, Alex J.] NASA, GSFC, Ai Solut Inc, B28 N278, Greenbelt, MD 20771 USA. RP Villac, BF (reprint author), Ai Solut Inc, Mission Engn & Technol Div, 10001 Derekwood Lane,Suite 215, Lanham, MD 20706 USA. NR 50 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-629-6 J9 ADV ASTRONAUT SCI PY 2016 VL 156 BP 3787 EP 3808 PN I-IV PG 22 WC Engineering, Aerospace SC Engineering GA BG2OP UT WOS:000387517700220 ER PT S AU McMahon, JW Scheeres, DJ Farnocchia, D Chesley, SR AF McMahon, Jay W. Scheeres, Daniel J. Farnocchia, Davide Chesley, Steven R. BE Majji, M Turner, JD Wawrzyniak, GG Cerven, WT TI OPTIMIZING SMALL BODY GRAVITY FIELD ESTIMATION OVER SHORT ARCS SO ASTRODYNAMICS 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT AAS/AIAA Astrodynamics Specialist Conference CY AUG 11-13, 2015 CL Vail, CO SP Amer Astronaut Soc, Space Flight Mech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm ID ASTEROID 101955 BENNU; DENSITY; ORBIT AB This paper examines the factors that influence the accuracy to which the gravity field of a small near-Earth asteroid can be estimated based on only a short period of time for dedicated radio science data collection. This is a difficult problem for a number of reasons, including the fact that the gravity field is very weak, the non-gravitational perturbations are relatively more significant, and time and measurement quantity are limited by mission constraints. Therefore it is key that the radio science experiment is designed to be as efficient as possible at obtaining information about the gravity field of the asteroid. The key focus in this analysis is on the orbit size/shape, the measurement quantity, and placement. C1 [McMahon, Jay W.] Univ Colorado, Dept Aerosp Engn Sci, 431 UCB, Boulder, CO 80309 USA. [Scheeres, Daniel J.] Univ Colorado, Dept Aerosp Engn Sci, 429 UCB, Boulder, CO 80309 USA. [Farnocchia, Davide; Chesley, Steven R.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP McMahon, JW (reprint author), Univ Colorado, Dept Aerosp Engn Sci, 431 UCB, Boulder, CO 80309 USA. NR 10 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-629-6 J9 ADV ASTRONAUT SCI PY 2016 VL 156 BP 3889 EP 3905 PN I-IV PG 17 WC Engineering, Aerospace SC Engineering GA BG2OP UT WOS:000387517700226 ER PT S AU Williams, TW Hughes, KM Mashiku, AK Longuski, JM AF Williams, Trevor W. Hughes, Kyle M. Mashiku, Alinda K. Longuski, James M. BE Majji, M Turner, JD Wawrzyniak, GG Cerven, WT TI ORBIT STABILITY OF OSIRIS-REX IN THE VICINITY OF BENNU USING A HIGH-FIDELITY SOLAR RADIATION MODEL SO ASTRODYNAMICS 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT AAS/AIAA Astrodynamics Specialist Conference CY AUG 11-13, 2015 CL Vail, CO SP Amer Astronaut Soc, Space Flight Mech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm AB Solar radiation pressure is one of the largest perturbing forces on the OSIRIS-Rex trajectory as it orbits the asteroid Bennu. In this work, we investigate how forces due to solar radiation perturb the OSIRIS-REx trajectory in a high-fidelity model. The model accounts for Bennu's non-spherical gravity field, third-body gravity forces from the Sun and Jupiter, as well as solar radiation forces acting on a simplified spacecraft model. Such high-fidelity simulations indicate significant solar radiation pressure perturbations from the nominal orbit. Modifications to the initial design of the nominal orbit are found using a variation of parameters approach that reduce the perturbation in eccentricity by a factor of one-half. C1 [Williams, Trevor W.; Mashiku, Alinda K.] NASA, Goddard Space Flight Ctr, Nav & Mission Design Branch, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. [Hughes, Kyle M.; Longuski, James M.] Purdue Univ, Sch Aeronaut & Astronaut, 701 W Stadium Ave, W Lafayette, IN 47907 USA. RP Williams, TW (reprint author), NASA, Goddard Space Flight Ctr, Nav & Mission Design Branch, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. EM trevor.w.williams@nasa.gov; kylehughes@purdue.edu; alinda.k.mashiku@nasa.gov; longuski@purdue.edu NR 14 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-629-6 J9 ADV ASTRONAUT SCI PY 2016 VL 156 BP 3907 EP 3926 PN I-IV PG 20 WC Engineering, Aerospace SC Engineering GA BG2OP UT WOS:000387517700227 ER PT S AU Bowden, EL Kupelian, CG Tibbetts, BR AF Bowden, Ernest L. Kupelian, Charles G. Tibbetts, Brian R. BE Majji, M Turner, JD Wawrzyniak, GG Cerven, WT TI USING IN-FLIGHT NAVIGATION INFORMATION TO CREATE A DEFINED 3-D FORMATION OF TWENTY-FOUR DEPLOYED SUB-PAYLOADS SO ASTRODYNAMICS 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT AAS/AIAA Astrodynamics Specialist Conference CY AUG 11-13, 2015 CL Vail, CO SP Amer Astronaut Soc, Space Flight Mech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm AB The C-REX (Cusp Region EXperiment) sounding rocket mission launched November 24th, 2014, successfully demonstrating a new technique for deploying and releasing a formation of trackable chemicals in a defined 3-dimensional spatial grid comprised of twenty-four sub-payloads. This paper describes the new systems required to create this 3-D formation of sub-payloads in the face of the large trajectory dispersions associated with high altitude sounding rockets and achieve adequate separation within the short 12 minute total flight time. Preliminary results from the C-REX mission show separations of upwards of 40km from the main body, with the formation of sub-payloads being successfully implemented. C1 [Bowden, Ernest L.; Kupelian, Charles G.; Tibbetts, Brian R.] Orbital ATK, Guidance Nav & Control Dept, Wallops Flight Facil, F10-N230, Wallops Isl, VA 23337 USA. RP Bowden, EL (reprint author), Orbital ATK, Guidance Nav & Control Dept, Wallops Flight Facil, F10-N230, Wallops Isl, VA 23337 USA. NR 1 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-629-6 J9 ADV ASTRONAUT SCI PY 2016 VL 156 BP 4127 EP 4145 PN I-IV PG 19 WC Engineering, Aerospace SC Engineering GA BG2OP UT WOS:000387517700239 ER PT S AU Jedrey, R Landau, D Whitley, R AF Jedrey, Ricky Landau, Damon Whitley, Ryan BE Majji, M Turner, JD Wawrzyniak, GG Cerven, WT TI HYPERBOLIC RENDEZVOUS AT MARS: RISK ASSESSMENTS AND MITIGATION STRATEGIES SO ASTRODYNAMICS 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT AAS/AIAA Astrodynamics Specialist Conference CY AUG 11-13, 2015 CL Vail, CO SP Amer Astronaut Soc, Space Flight Mech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm AB Given the current interest in the use of flyby trajectories for human Mars exploration, a key requirement is the capability to execute hyperbolic rendezvous. Hyperbolic rendezvous is used to transport crew from a Mars centered orbit, to a transiting Earth bound habitat that does a flyby. Representative cases are taken from future potential missions of this type, and a thorough sensitivity analysis of the hyperbolic rendezvous phase is performed. This includes early engine cutoff, missed burn times, and burn misalignment. A finite burn engine model is applied that assumes the hyperbolic rendezvous phase is done with at least two burns. C1 [Jedrey, Ricky] NASA, Flight Mech & Trajectory Design, Johnson Space Ctr, 2101 NASA Pkwy, Houston, TX 77058 USA. [Landau, Damon] Jet Prop Lab, Project Syst Engn & Formulat, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Whitley, Ryan] NASA, Explorat Miss Planning Off, Johnson Space Ctr, 2101 NASA Pkwy, Houston, TX 77058 USA. RP Jedrey, R (reprint author), NASA, Flight Mech & Trajectory Design, Johnson Space Ctr, 2101 NASA Pkwy, Houston, TX 77058 USA. NR 10 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-629-6 J9 ADV ASTRONAUT SCI PY 2016 VL 156 BP 4325 EP 4346 PN I-IV PG 22 WC Engineering, Aerospace SC Engineering GA BG2OP UT WOS:000387517700250 ER PT S AU Queen, SZ Chai, DJ Placanica, S AF Queen, Steven Z. Chai, Dean J. Placanica, Sam BE Majji, M Turner, JD Wawrzyniak, GG Cerven, WT TI ORBITAL MANEUVERING SYSTEM DESIGN AND PERFORMANCE FOR THE MAGNETOSPHERIC MULTISCALE FORMATION SO ASTRODYNAMICS 2015 SE Advances in the Astronautical Sciences LA English DT Proceedings Paper CT AAS/AIAA Astrodynamics Specialist Conference CY AUG 11-13, 2015 CL Vail, CO SP Amer Astronaut Soc, Space Flight Mech Comm, Amer Inst Aeronaut & Astronaut, Astrodynam Tech Comm AB The Magnetospheric Multiscale (MMS) mission consists of four identically instrumented, spin-stabilized observatories elliptically orbiting the Earth in a tetrahedron formation. A requirement for the operational success of the mission is the ability for the on-board systems to deliver precise maneuver adjustments. A six degree-of-freedom (6-DOF), closed-loop control system was developed that tracks a time-varying, inertial velocity-target with less than 1% error down to a five millimeter-per-second lower-threshold (3 sigma). This level of performance is achieved in-part through integrated and dynamically-compensated accelerometer feedback with micro-gravity resolution. System performance is bounded through an extensive Monte Carlo simulation campaign that exercises the multi-body dynamics and non-linear sensitivities, and supported by some initial flight results. C1 [Queen, Steven Z.; Chai, Dean J.; Placanica, Sam] NASA, Goddard Space Flight Ctr, Attitude Control Syst Engn Branch, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. RP Queen, SZ (reprint author), NASA, Goddard Space Flight Ctr, Attitude Control Syst Engn Branch, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. NR 18 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 978-0-87703-629-6 J9 ADV ASTRONAUT SCI PY 2016 VL 156 BP 4385 EP 4404 PN I-IV PG 20 WC Engineering, Aerospace SC Engineering GA BG2OP UT WOS:000387517700254 ER PT J AU Wittrock, JM Kane, SR Horch, EP Hirsch, L Howell, SB Ciardi, DR Everett, ME Teske, JK AF Wittrock, Justin M. Kane, Stephen R. Horch, Elliott P. Hirsch, Lea Howell, Steve B. Ciardi, David R. Everett, Mark E. Teske, Johanna K. TI STELLAR COMPANIONS TO THE EXOPLANET HOST STARS HD 2638 AND HD 164509 SO ASTRONOMICAL JOURNAL LA English DT Article DE planetary systems; stars: individual (HD 2638, HD 164509); techniques: high angular resolution ID ELLIPTIC RESTRICTED PROBLEM; BINARY STARS; PLANETARY ORBITS; EXTRASOLAR PLANETS; HIPPARCOS STARS; MULTIPLICITY; KEPLER; SYSTEM; TELESCOPE; VALIDATION AB An important aspect of searching for exoplanets is understanding the binarity of the host stars. It is particularly important, because nearly half of the solar-like stars within our own Milky Way are part of binary or multiple systems. Moreover, the presence of two or more stars within a system can place further constraints on planetary formation, evolution, and orbital dynamics. As part of our survey of almost a hundred host stars, we obtained images at 692 and 880 nm bands using the Differential Speckle Survey Instrument (DSSI) at the Gemini-North Observatory. From our survey, we detect stellar companions to HD 2638 and HD 164509. The stellar companion to HD 2638 has been previously detected, but the companion to HD 164509 is a newly discovered companion. The angular separation for HD 2638 is 0.512 +/- 0.'' 002 and for HD 164509 is 0.697 +/- 0.'' 002. This corresponds to a projected separation of 25.6 +/- 1.9 au and 36.5 +/- 1.9 au, respectively. By employing stellar isochrone models, we estimate the mass of the stellar companions of HD 2638 and HD 164509 to be 0.483 +/- 0.007 M-circle dot and 0.416 +/- 0.007 M-circle dot, respectively, and their effective temperatures to be 3570 +/- 8 K and 3450 +/- 7 K, respectively. These results are consistent with the detected companions being late-type M dwarfs. C1 [Wittrock, Justin M.; Kane, Stephen R.] San Francisco State Univ, Dept Phys & Astron, 1600 Holloway Ave, San Francisco, CA 94132 USA. [Horch, Elliott P.] Southern Connecticut State Univ, Dept Phys, New Haven, CT 06515 USA. [Hirsch, Lea] Univ Calif Berkeley, Dept Astron, Berkeley, CA 94720 USA. [Howell, Steve B.] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Ciardi, David R.] CALTECH, NASA Exoplanet Sci Inst, MS 100-22,770 South Wilson Ave, Pasadena, CA 91125 USA. [Everett, Mark E.] Natl Opt Astron Observ, 950 N Cherry Ave, Tucson, AZ 85719 USA. [Teske, Johanna K.] Carnegie Dept Terr Magnetism, 5241 Broad Branch Rd, Washington, DC 20015 USA. RP Wittrock, JM (reprint author), San Francisco State Univ, Dept Phys & Astron, 1600 Holloway Ave, San Francisco, CA 94132 USA. EM jwittroc@mail.sfsu.edu OI Ciardi, David/0000-0002-5741-3047 FU NASA's Science Mission Directorate FX Based on observations obtained at the Gemini Observatory, which is operated by the Association of Universities for Research in Astronomy, Inc., under a cooperative agreement with the NSF on behalf of the Gemini partnership: the National Science Foundation (United States), the National Research Council (Canada), CONICYT (Chile), the Australian Research Council (Australia), Ministerio da Ciencia, Tecnologia e Inovacao (Brazil) and Ministerio de Ciencia, Tecnologia e Innovacion Productiva (Argentina). This research has made use of the NASA Exoplanet Archive, which is operated by the California Institute of Technology, under contract with the National Aeronautics and Space Administration under the Exoplanet Exploration Program. The results reported herein benefited from collaborations and/or information exchange within NASA's Nexus for Exoplanet System Science (NExSS) research coordination network sponsored by NASA's Science Mission Directorate. NR 37 TC 1 Z9 1 U1 2 U2 2 PU IOP PUBLISHING LTD PI BRISTOL PA TEMPLE CIRCUS, TEMPLE WAY, BRISTOL BS1 6BE, ENGLAND SN 0004-6256 EI 1538-3881 J9 ASTRON J JI Astron. J. PY 2016 VL 152 IS 6 AR 149 DI 10.3847/0004-6256/152/5/149 PG 7 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA EB7HJ UT WOS:000387557200003 ER PT J AU Mahoney, C Hopkinson, C Held, A Simard, M AF Mahoney, Craig Hopkinson, Christopher Held, Alex Simard, Marc TI Continental-Scale Canopy Height Modeling by Integrating National, Spaceborne, and Airborne LiDAR Data SO CANADIAN JOURNAL OF REMOTE SENSING LA English DT Article ID LEAF-AREA INDEX; SATELLITE LIDAR; RANDOM FORESTS; VEGETATION STRUCTURE; VERTICAL STRUCTURE; LASER ALTIMETRY; BIOMASS; CLASSIFICATION; ICESAT/GLAS; RETRIEVAL AB Canopy height estimates are widely used in forest biomass and carbon assessment modeling applications with the goal of mitigating climate change through the modification of forest sustainability strategies. As a result, large-scale accurate estimates of contemporary forest conditions are required. The current study utilizes Random Forest (RF) algorithms to integrate land cover, vegetation, soil, and other supplementary data with Geoscience Laser Altimeter System (GLAS) data to predict a wall-to-wall canopy height model (CHM) across Australia. Multiple CHMs are predicted from RF models trained from unique permutations of 6 predictor variables. Each 250m resolution CHM is independently validated against airborne laser scanning (ALS) heights from 18 countrywide sites; the best CHM yielding R-2 = 0.72, and RMSE = 7.43m. The best countrywide CHM is compared against 2 similar products from the literature, both of which are subject to intersecting ALS performance assessment also. The developed CHM product utilizes up-to-date data, and is tailored to Australia, complementing the National Ecosystem Surveillance Monitoring project mandated to the Terrestrial Ecosystem Research Network (TERN) by the Australian Department of Environment. Furthermore, with future altimetry-based Earth observation missions due for launch, the developed CHM will act as a baseline from which monitoring investigations can be executed. C1 [Mahoney, Craig; Hopkinson, Christopher] Univ Lethbridge, Dept Geog, Lethbridge, AB T1K 3M4, Canada. [Held, Alex] CSIRO, Land & Water, Canberra, ACT 2601, Australia. [Simard, Marc] NASA Jet Prop Lab, Pasadena, CA 91109 USA. RP Mahoney, C (reprint author), Univ Lethbridge, Dept Geog, Lethbridge, AB T1K 3M4, Canada. EM craig.mahoney@uleth.ca NR 59 TC 1 Z9 1 U1 2 U2 2 PU CANADIAN AERONAUTICS & SPACE INST PI KANATA PA 350 TERRY FOX DR, STE 104, KANATA, ON K2K 2W5, CANADA SN 0703-8992 EI 1712-7971 J9 CAN J REMOTE SENS JI Can. J. Remote Sens. PY 2016 VL 42 IS 5 SI SI BP 574 EP 590 DI 10.1080/07038992.2016.1196580 PG 17 WC Remote Sensing SC Remote Sensing GA EB3VT UT WOS:000387297600013 ER PT B AU Garai, A Diosady, LT Murman, SM Madavan, NK AF Garai, Anirban Diosady, Laslo T. Murman, Scott M. Madavan, Nateri K. GP ASME TI DNS OF LOW-PRESSURE TURBINE CASCADE FLOWS WITH ELEVATED INFLOW TURBULENCE USING A DISCONTINUOUS GALERKIN SPECTRAL-ELEMENT METHOD SO PROCEEDINGS OF THE ASME TURBO EXPO: TURBINE TECHNICAL CONFERENCE AND EXPOSITION, 2016, VOL 2C LA English DT Proceedings Paper CT ASME Turbo Expo: Turbine Technical Conference and Exposition CY JUN 13-17, 2016 CL Seoul, SOUTH KOREA SP Int Gas Turbine Inst ID NUMERICAL SIMULATIONS; ISOTROPIC TURBULENCE; NAVIER-STOKES; FORMULATION; EQUATIONS; MODEL AB Recent progress towards developing a new computational capability for accurate and efficient high-fidelity direct numerical simulation (DNS) and large-eddy simulation (LES) of turbo-machinery is described. This capability is based on an entropy stable Discontinuous Galerkin spectral-element approach that extends to arbitrarily high orders of spatial and temporal accuracy, and is implemented in a computationally efficient manner on a modern high performance computer architecture. An inflow turbulence generation procedure based on a linear forcing approach has been incorporated in this framework and DNS conducted to study the effect of inflow turbulence on the suction-side separation bubble in low pressure turbine (LPT) cascades. The T106 series of airfoil cascades in both lightly (T106A) and highly loaded (T106C) configurations at exit isentropic Reynolds numbers of 60,000 and 80,000, respectively, are considered. The numerical simulations are performed using 8th order accurate spatial and 4th order accurate temporal discretizations. The changes in separation bubble topology due to elevated inflow turbulence are captured by the present method and the physical mechanisms leading to the changes are explained. The present results are in good agreement with prior numerical simulations but some expected discrepancies with the experimental data for the T106C case are noted and discussed. C1 [Garai, Anirban] Oak Ridge Associated Univ, NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Diosady, Laslo T.] NASA, Ames Res Ctr, Sci & Technol Corp, Moffett Field, CA 94035 USA. [Murman, Scott M.; Madavan, Nateri K.] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Garai, A (reprint author), Oak Ridge Associated Univ, NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. NR 42 TC 0 Z9 0 U1 0 U2 0 PU AMER SOC MECHANICAL ENGINEERS PI NEW YORK PA THREE PARK AVENUE, NEW YORK, NY 10016-5990 USA BN 978-0-7918-4971-2 PY 2016 AR UNSP V02CT39A025 PG 16 WC Engineering, Mechanical SC Engineering GA BG2FA UT WOS:000387297500025 ER PT J AU Parsani, M Carpenter, MH Fisher, TC Nielsen, EJ AF Parsani, Matteo Carpenter, Mark H. Fisher, Travis C. Nielsen, Eric J. TI ENTROPY STABLE STAGGERED GRID DISCONTINUOUS SPECTRAL COLLOCATION METHODS OF ANY ORDER FOR THE COMPRESSIBLE NAVIER-STOKES EQUATIONS SO SIAM JOURNAL ON SCIENTIFIC COMPUTING LA English DT Article DE high-order accurate discontinuous methods; entropy stability; SBP-SAT; compressible Navier-Stokes; staggered grid; conservation ID NONLINEAR CONSERVATION-LAWS; FINITE-DIFFERENCE SCHEMES; WALL BOUNDARY-CONDITIONS; GALERKIN METHOD; ELEMENT METHODS; FLOWS; APPROXIMATIONS; QUADRATURE; SYSTEMS; VORTEX AB Staggered grid, entropy stable discontinuous spectral collocation operators of any order are developed for the compressible Euler and Navier-Stokes equations on unstructured hexahedral elements. This generalization of previous entropy stable spectral collocation work [M. H. Carpenter, T. C. Fisher, E. J. Nielsen, and S. H. Frankel, SIAM T. Sci. Comput., 36 (2014), pp. B835-B867, M. Parsani, M. H. Carpenter, and E. J. Nielsen, T. Comput. Phys., 292 (2015), pp. 88-113], extends the applicable set of points from tensor product, Legendre-Gauss-Lobatto (LGL), to a combination of tensor product Legendre-Gauss (LG) and LGL points. The new semidiscrete operators discretely conserve mass, momentum, energy, and satisfy a mathematical entropy inequality for the compressible Navier-Stokes equations in three spatial dimensions. They are valid for smooth as well as discontinuous flows. The staggered LG and conventional LGL point formulations are compared on several challenging test problems. The staggered LG operators are significantly more accurate, although more costly from a theoretical point of view. The LG and LGL operators exhibit similar robustness, as is demonstrated using test problems known to be problematic for operators that lack a nonlinear stability proof for the compressible Navier Stokes equations (e.g., discontinuous Galerkin, spectral difference, or flux reconstruction operators). C1 [Parsani, Matteo] KAUST, ECRC, CEMSE, AMCS, Thuwal 239556900, Saudi Arabia. [Carpenter, Mark H.] NASA Langley Res Ctr LaRC, Computat AeroSci Branch CASB, Hampton, VA 23681 USA. [Fisher, Travis C.] Sandia Natl Labs, Computat Thermal & Fluid Mech, POB 5800, Albuquerque, NM 87185 USA. [Nielsen, Eric J.] NASA LaRC, CASB, Hampton, VA 23681 USA. RP Parsani, M (reprint author), KAUST, ECRC, CEMSE, AMCS, Thuwal 239556900, Saudi Arabia. EM matteo.parsani@kaust.edu.sa; mark.h.carpenter@nasa.gov; tcfishe@sandia.gov; eric.j.nielsen@nasa.gov FU King Abdullah University of Science & Technology (KAUST) in Thuwal, Saudi Arabia FX This work was partially supported by King Abdullah University of Science & Technology (KAUST) in Thuwal, Saudi Arabia. NR 44 TC 0 Z9 0 U1 0 U2 0 PU SIAM PUBLICATIONS PI PHILADELPHIA PA 3600 UNIV CITY SCIENCE CENTER, PHILADELPHIA, PA 19104-2688 USA SN 1064-8275 EI 1095-7197 J9 SIAM J SCI COMPUT JI SIAM J. Sci. Comput. PY 2016 VL 38 IS 5 BP A3129 EP A3162 DI 10.1137/15M1043510 PG 34 WC Mathematics, Applied SC Mathematics GA EB4ND UT WOS:000387347700069 ER PT J AU Gallardo, L Henriquez, A Thompson, AM Rondanelli, R Carrasco, J Orfanoz-Cheuquelaf, A Velasquez, P AF Gallardo, Laura Henriquez, Adolfo Thompson, Anne M. Rondanelli, Roberto Carrasco, Jorge Orfanoz-Cheuquelaf, Andrea Velasquez, Patricio TI The first twenty years (1994-2014) of ozone soundings from Rapa Nui (27 degrees S, 109 degrees W, 51 m a.s.l.) SO TELLUS SERIES B-CHEMICAL AND PHYSICAL METEOROLOGY LA English DT Article DE Ozone sondes; Rapa Nui; climatology; self-organizing maps; Global Atmospheric Watch ID TROPOSPHERIC OZONE; SOUTHERN-HEMISPHERE; SATELLITE MEASUREMENTS; GLOBAL CLIMATOLOGY; TROPICAL BELT; SPLIT JET; EL-NINO; AFRICA; CHILE; VARIABILITY AB Ozone (O-3) soundings have been performed on Easter Island or Rapa Nui (27 degrees S, 109 degrees W, 51 m a.s.l.) since 1994 as part of the Global Atmospheric Watch Programme of the World Meteorological Organization. In this work, we analyse 260 soundings compiled over the period 1994-2014, and make the data available for the international community. We characterise O-3 profiles over this remote area of the Pacific by means of statistical analyses that consider, on the one hand, a traditional climatology that describes the data in terms of seasonal cycles based on monthly averages and, on the other hand, a process-oriented analysis based on self-organising maps. Our analyses show the influence of both tropical and subtropical/mid-latitude air masses at Rapa Nui. The former occurs in summer and fall when convective conditions prevail, and the latter in late winter and spring when subsiding conditions are recurrent. The occurrence of stratospheric intrusions in late winter and spring in connection with deep troughs and the presence of the subtropical jet stream is also apparent in the data set. The tropospheric ozone column is in good agreement with the corresponding data derived from satellites but with a systematic overestimate of summer and fall values. There is evidence of an upward trend in ozone near the surface, which suggests the impact of local pollution. We look forward to an enhancement of the Rapa Nui observing site, given its location that offers a privileged position to observe climate change over the sparsely sampled and vast South Pacific Ocean. C1 [Gallardo, Laura; Henriquez, Adolfo; Rondanelli, Roberto; Orfanoz-Cheuquelaf, Andrea] Univ Chile, Dept Geofis, Blanco Encalada 2002,Piso 4, Santiago, Chile. [Gallardo, Laura; Henriquez, Adolfo; Rondanelli, Roberto; Orfanoz-Cheuquelaf, Andrea; Velasquez, Patricio] CR2, Blanco Encalada 2002, Santiago, Chile. [Thompson, Anne M.] NASA, Goddard Space Flight Ctr, Atmospher Chem & Dynam Lab, Greenbelt, MD 20771 USA. [Carrasco, Jorge] Univ Magallanes, Ave Bulnes 08155, Punta Arenas, Chile. [Velasquez, Patricio] Direcc Meteorol Chile, Ave Portales 3450, Santiago, Chile. RP Gallardo, L (reprint author), Univ Chile, Dept Geofis, Blanco Encalada 2002,Piso 4, Santiago, Chile.; Gallardo, L (reprint author), CR2, Blanco Encalada 2002, Santiago, Chile. EM laura@dgf.uchile.cl RI Gallardo, Laura/H-4370-2013; Thompson, Anne /C-3649-2014; Rondanelli, Roberto/A-4717-2012 OI Gallardo, Laura/0000-0001-7605-3721; Thompson, Anne /0000-0002-7829-0920; Rondanelli, Roberto/0000-0002-7440-7810 FU FONDECYT [1030809]; FONDAP [15110009]; Pennsylvania State University [NNX09AJ23G] FX Initially this work was supported by grant FONDECYT 1030809 and finished under FONDAP 15110009. We are grateful for the provision of ozone profiles by the Chilean Weather Office, and the ancillary data collected from various sources. CO data were obtained from WMO/WDCGG data base and collected by NOAA/ESRL. We are also grateful for 7 Be provided by the Chilean Commission on Nuclear Energy. A. M. Thompson's participation is courtesy of SHADOZ (NASA Upper Air Research Program) and was initially sponsored through a Grant to the Pennsylvania State University: NNX09AJ23G. NR 66 TC 0 Z9 0 U1 2 U2 2 PU CO-ACTION PUBLISHING PI JARFALLA PA RIPVAGEN 7, JARFALLA, SE-175 64, SWEDEN SN 0280-6509 EI 1600-0889 J9 TELLUS B JI Tellus Ser. B-Chem. Phys. Meteorol. PY 2016 VL 68 AR 29484 DI 10.3402/tellusb.v68.29484 PG 16 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA EB2IJ UT WOS:000387181900001 ER PT S AU Alessi, N Burleigh, S Caini, C De Cola, T AF Alessi, N. Burleigh, S. Caini, C. De Cola, T. GP IEEE TI LTP Robustness Enhancements to Cope with High Losses on Space Channels SO 2016 8TH ADVANCED SATELLITE MULTIMEDIA SYSTEMS CONFERENCE AND THE 14TH SIGNAL PROCESSING FOR SPACE COMMUNICATIONS WORKSHOP (ASMS/SPSC) SE Advanced Satellite Multimedia Systems Conference and the Signal Processing for Space Communications Workshop LA English DT Proceedings Paper CT 8th Advanced Satellite Multimedia Systems Conference (ASMS) / 14th Signal Processing for Space Communications Workshop (SPSC) CY SEP 05-07, 2016 CL Palma de Mallorca, SPAIN DE component; Licklider Transmission Protocol; Space Communications; Interplanetary Networking; Delay-/Disruption-Tolerant Networking; Performance evaluation ID TOLERANT NETWORKING; PERFORMANCE; DTN AB This paper addresses the performance of Licklider Transmission Protocol (LTP) in space environments. We have observed that the loss of signaling segments can significantly increase the delivery time of LTP blocks, and potentially undermine overall LTP performance. To cope with this degradation, the paper proposes two simple enhancements which make the transmission of signaling data more robust. Both enhancements have been inserted as optional features in the Interplanetary Overlay Network LTP implementation, in order to evaluate their effectiveness on a GNU/Linux testbed running the full protocol stack. The preliminary results presented in the paper show that the proposed enhancements can significantly improve LTP performance in the presence of high losses with respect to regular LTP implementations. C1 [Alessi, N.; Caini, C.] Univ Bologna, DEI ARCES, I-40126 Bologna, Italy. [Burleigh, S.] CALTECH, Jet Prop Lab, NASA, Pasadena, CA USA. [De Cola, T.] DLR German Aerosp Ctr, Inst Commun & Nav, Wessling, Germany. RP Alessi, N (reprint author), Univ Bologna, DEI ARCES, I-40126 Bologna, Italy. EM nicola.alessi@studio.unibo.it; Scott.Burleigh@jpl.nasa.gov; carlo.caini@unibo.it; tomaso.decola@dlr.de NR 18 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2329-7093 BN 978-1-5090-1682-2 J9 ADV SAT MULTMED SYS PY 2016 PG 6 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BG1FD UT WOS:000386706200012 ER PT S AU Ranganathan, SVS Vakilinia, K Divsalar, D Wesel, RD AF Ranganathan, Sudarsan V. S. Vakilinia, Kasra Divsalar, Dariush Wesel, Richard D. GP IEEE TI Universal Rate-Compatible LDPC Code Families for Any Increment Ordering SO 2016 9TH INTERNATIONAL SYMPOSIUM ON TURBO CODES AND ITERATIVE INFORMATION PROCESSING (ISTC) SE International Symposium on Turbo Codes and Iterative Information Processing LA English DT Proceedings Paper CT 9th International Symposium on Turbo Codes and Iterative Information Processing (ISTC) CY SEP 05-09, 2016 CL Brest, FRANCE SP IEEE, IEEE France Sect, IEEE Informat Theory Soc, URSI, Inst Mines Telecom ID PARITY-CHECK CODES; DESIGN AB Rate-compatible (RC) codes are at the core of systems with incremental redundancy. Usually, an RC code family supports successively lower code rates by sending specific increments of additional redundancy at each rate. That is, the order of the increments is fixed. However, in some multi-hop communication systems and also in recently proposed inter-frame coding, the order in which the decoder of the RC code receives the increments is not predetermined. A different ordering of the increments at the decoder may change the codes of various rates. This paper seeks RC codes that are universally good over all increment orderings. We call RC codes satisfying this requirement universal for any increment ordering (UIO) codes. We design protograph-based Raptor-Iike (PBRL) low-density parity-check (LDPC) code ensembles for UIO codes using protograph thresholds as components of two design metrics. One metric seeks codes that, at each code rate, have exactly the same frame error rate for all increment orderings. The other metric sacrifices strictly identical performance for every ordering to seek codes that achieve the best possible throughput in a variable-length setting with random increment ordering, as would occur with inter-frame coding. Simulation results of UIO-PBRL codes from the new ensembles show that our designs satisfy the two metrics. C1 [Ranganathan, Sudarsan V. S.; Vakilinia, Kasra; Wesel, Richard D.] Univ Calif Los Angeles, Dept Elect Engn, Los Angeles, CA 90095 USA. [Divsalar, Dariush] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Ranganathan, SVS (reprint author), Univ Calif Los Angeles, Dept Elect Engn, Los Angeles, CA 90095 USA. EM sudarsanvsr@ucla.edu; vakiliniak@ucla.edu; Dariush.Divsalar@jpl.nasa.gov; wesel@g.ucla.edu NR 11 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2165-4700 BN 978-1-5090-3401-7 J9 INT SYM TURBO CODES PY 2016 BP 101 EP 105 PG 5 WC Computer Science, Theory & Methods; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BG1CK UT WOS:000386655300021 ER PT S AU Chang, BC Bayram, M Kwatny, H Belcastro, CM AF Chang, Bor-Chin Bayram, Mevlut Kwatny, Harry Belcastro, Christine M. GP IEEE TI Flight Path and Altitude Tracking Control Of An Impaired Nonlinear Generic Transport Model (GTM) Aircraft With Elevator Jam Failures SO 2016 IEEE CONFERENCE ON CONTROL APPLICATIONS (CCA) SE IEEE International Conference on Control Applications LA English DT Proceedings Paper CT IEEE Conference on Control Applications (CCA) CY SEP 19-22, 2016 CL Buenos Aires, ARGENTINA SP IEEE AB In this paper, a challenging control system design problem is considered to mitigate the aircraft safety threat posted by elevator jam anywhere within the feasible level flight trim region. A new fixed linear servomechanism- based tracking controller with a nonlinear parameter adaptation was designed to achieve stability, maintain a level flight, and perform accurate altitude tracking for an impaired GTM aircraft with elevator jam failure at any position within the feasible trim region. C1 [Chang, Bor-Chin; Bayram, Mevlut; Kwatny, Harry] Drexel Univ, Dept Mech Engn & Mech, Philadelphia, PA 19104 USA. [Belcastro, Christine M.] NASA, Langley Res Ctr, MS161, Hampton, VA 23681 USA. RP Chang, BC (reprint author), Drexel Univ, Dept Mech Engn & Mech, Philadelphia, PA 19104 USA. EM bchang@drexel.edu; mb3242@coe.drexel.edu; hkwatny@coe.drexel.edu; Christine.M.Belcastro@nasa.gov NR 23 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1085-1992 BN 978-1-5090-0755-4 J9 IEEE INTL CONF CONTR PY 2016 PG 6 WC Automation & Control Systems; Computer Science, Theory & Methods; Engineering, Electrical & Electronic SC Automation & Control Systems; Computer Science; Engineering GA BG1EW UT WOS:000386696600003 ER PT J AU Sukhwani, H Alonso, J Trivedi, KS Mcginnis, I AF Sukhwani, Harish Alonso, Javier Trivedi, Kishor S. Mcginnis, Issac GP IEEE TI Software Reliability Analysis of NASA Space Flight Software: A Practical Experience SO 2016 IEEE INTERNATIONAL CONFERENCE ON SOFTWARE QUALITY, RELIABILITY AND SECURITY (QRS 2016) LA English DT Proceedings Paper CT IEEE International Conference on Software Quality, Reliability and Security (QRS) CY AUG 01-03, 2016 CL Vienna, AUSTRIA SP IEEE, IEEE Comp Soc, Reliabil Soc, UT DALLAS, Microsoft, SBA Res, TU Graz DE Defect Reports; Flight Software; Incremental Development; Software Reliability; Software Reliability Growth Models AB In this paper, we present the software reliability analysis of the flight software of a recently launched space mission. For our analysis, we use the defect reports collected during the flight software development. We find that this software was developed in multiple releases, each release spanning across all software life-cycle phases. We also find that the software releases were developed and tested for four different hardware platforms, spanning from off-the-shelf or emulation hardware to actual flight hardware. For releases that exhibit reliability growth or decay, we fit Software Reliability Growth Models (SRGM); otherwise we fit a distribution function. We find that most releases exhibit reliability growth, with Log-Logistic (NHPP) and S-Shaped (NHPP) as the best-fit SRGMs. For the releases that experience reliability decay, we investigate the causes for the same. We find that such releases were the first software releases to be tested on a new hardware platform, and hence they encountered major hardware integration issues. Also such releases seem to have been developed under time pressure in order to start testing on the new hardware platform sooner. Such releases exhibit poor reliability growth, and hence exhibit high predicted failure rate. Other problems include hardware specification changes and delivery delays from vendors. Thus, our analysis provides critical insights and inputs to the management to improve the software development process. As NASA has moved towards a product line engineering for its flight software development, software for future space missions will be developed in a similar manner and hence the analysis results for this mission can be considered as a baseline for future flight software missions. C1 [Sukhwani, Harish; Alonso, Javier; Trivedi, Kishor S.] Duke Univ, Dept Elect & Comp Engn, Durham, NC 27706 USA. [Alonso, Javier] Univ Leon, Res Inst Adv Studies Cybersecur, Leon, Spain. [Mcginnis, Issac] NASA, Goddard Space Flight Ctr, Greenbelt, MD USA. RP Sukhwani, H (reprint author), Duke Univ, Dept Elect & Comp Engn, Durham, NC 27706 USA. NR 30 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-5090-4127-5 PY 2016 BP 386 EP 397 DI 10.1109/QRS.2016.50 PG 12 WC Computer Science, Software Engineering; Computer Science, Theory & Methods; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BG1HG UT WOS:000386751700040 ER PT J AU Gopalswamy, N AF Gopalswamy, N. GP IEEE TI Low-Frequency Radio Bursts and Space Weather SO 2016 URSI ASIA-PACIFIC RADIO SCIENCE CONFERENCE (URSI AP-RASC) LA English DT Proceedings Paper CT URSI Asia-Pacific Radio Science Conference (URSI AP-RASC) CY AUG 21-25, 2016 CL Seoul, SOUTH KOREA SP KIEES, URSI, Natl Radio Res Agcy, Elect & Telecommunicat Res Inst, Korea Astron & Space Sci Inst, NFRI, EiC, IEEE Antennas & Propagat Soc, IEEE Antennas & Propagat Soc Seoul Chapter, KICS, IEIE, KOFST, SEOUL Metropolitan Govt, Korea Tourism Org, Samsung, LG Innotek, LIG, LG Elect, SK Telecom, Hanwha Thales, Kt, MTG DE interplanetary radio emission; coronal mass ejection; type III storm; type II radio burst; type IV radio burst ID CORONAL MASS EJECTIONS; ENERGETIC PARTICLE EVENTS; ACTIVE REGIONS; PROPAGATION; STORMS; WIND AB Low-frequency radio phenomena are due to the presence of nonthermal electrons in the interplanetary (IP) medium. Understanding these phenomena is important in characterizing the space environment near Earth and other destinations in the solar system. Substantial progress has been made in the past two decades, because of the continuous and uniform data sets available from space: based radio and white light instrumentation. This paper highlights some recent results obtained on IP radio phenomena. In particular, the source of type IV radio bursts, the behavior of type III storms, shock propagation in the IP medium, and the solar-cycle variation of type II radio bursts are considered. All these phenomena are closely related to solar eruptions and active region evolution. The results presented were obtained by combining data from the Wind and SOHO missions. C1 [Gopalswamy, N.] NASA, Goddard Space Flight Ctr, Solar Phys Lab, Heliophys Div, Greenbelt, MD 20771 USA. RP Gopalswamy, N (reprint author), NASA, Goddard Space Flight Ctr, Solar Phys Lab, Heliophys Div, Greenbelt, MD 20771 USA. EM nat.gopalswamy@nasa.gov NR 25 TC 0 Z9 0 U1 8 U2 8 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4673-8801-6 PY 2016 BP 471 EP 474 PG 4 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BG0TH UT WOS:000386515800053 ER PT J AU Gopalswamy, N AF Gopalswamy, N. GP IEEE TI Solar Activity Studies using Microwave Imaging Observations SO 2016 URSI ASIA-PACIFIC RADIO SCIENCE CONFERENCE (URSI AP-RASC) LA English DT Proceedings Paper CT URSI Asia-Pacific Radio Science Conference (URSI AP-RASC) CY AUG 21-25, 2016 CL Seoul, SOUTH KOREA SP KIEES, URSI, Natl Radio Res Agcy, Elect & Telecommunicat Res Inst, Korea Astron & Space Sci Inst, NFRI, EiC, IEEE Antennas & Propagat Soc, IEEE Antennas & Propagat Soc Seoul Chapter, KICS, IEIE, KOFST, SEOUL Metropolitan Govt, Korea Tourism Org, Samsung, LG Innotek, LIG, LG Elect, SK Telecom, Hanwha Thales, Kt, MTG DE microwave radio emission; prominence eruption; coronal hole; brightness temperature; butterfly diagram; polarity reversal ID CORONAL MASS EJECTION; POLAR MAGNETIC-FIELD; NOBEYAMA RADIOHELIOGRAPH; CYCLE 24; REVERSAL; TRANSPORT; HOLES; SUN AB We report on the status of solar cycle 24 based on polar prominence eruptions (PEs) and microwave brightness enhancement (MBE) information obtained by the Nobeyama radioheliograph. The north polar region of the Sun had near-zero field strength for more than three years (2012-2015) and ended only in September 2015 as indicated by the presence of polar PEs and the lack of MBE. The zero-polar-field condition in the south started only around 2013, but it ended by June 2014. Thus the asymmetry in the times of polarity reversal switched between cycle 23 and 24. The polar MBE is a good proxy for the polar magnetic field strength as indicated by the high degree of correlation between the two. The cross-correlation between the high- and low-latitude MBEs is significant for a lag of similar to 5.5 to 7.3 years, suggesting that the polar field of one cycle indicates the sunspot number of the next cycle in agreement with the Babcock-Leighton mechanism of solar cycles. The extended period of near-zero field in the north-polar region should result in a weak and delayed sunspot activity in the northern hemisphere in cycle 25. C1 [Gopalswamy, N.] NASA, Goddard Space Flight Ctr, Heliophys Div, Solar Phys Lab, Greenbelt, MD 20771 USA. RP Gopalswamy, N (reprint author), NASA, Goddard Space Flight Ctr, Heliophys Div, Solar Phys Lab, Greenbelt, MD 20771 USA. EM nat.gopalswamy@nasa.gov NR 26 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4673-8801-6 PY 2016 BP 1075 EP 1078 PG 4 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BG0TH UT WOS:000386515800134 ER PT J AU Gopalswamy, N Akiyama, S Makela, P Yashiro, S Cairns, IH AF Gopalswamy, N. Akiyama, S. Makela, P. Yashiro, S. Cairns, I. H. GP IEEE TI On the Directivity of Low-Frequency Type IV Radio Bursts SO 2016 URSI ASIA-PACIFIC RADIO SCIENCE CONFERENCE (URSI AP-RASC) LA English DT Proceedings Paper CT URSI Asia-Pacific Radio Science Conference (URSI AP-RASC) CY AUG 21-25, 2016 CL Seoul, SOUTH KOREA SP KIEES, URSI, Natl Radio Res Agcy, Elect & Telecommunicat Res Inst, Korea Astron & Space Sci Inst, NFRI, EiC, IEEE Antennas & Propagat Soc, IEEE Antennas & Propagat Soc Seoul Chapter, KICS, IEIE, KOFST, SEOUL Metropolitan Govt, Korea Tourism Org, Samsung, LG Innotek, LIG, LG Elect, SK Telecom, Hanwha Thales, Kt, MTG DE type IV radio burst; coronal mass ejection; directivity; type H radio burst; solar eruption ID WAVES AB An intense type IV radio burst was observed by the STEREO Behind (STB) spacecraft located about 144 degrees behind Earth. The burst was associated with a large solar eruption that occurred on the backside of the Sun (N05E151) close to the disk center in the STB view. The eruption was also observed by the STEREO Ahead (STA) spacecraft (located at 149 ahead of Earth) as an eruption close to the west limb (N05W60) in that view. The type IV burst was complete in STB observations in that the envelope reached the lowest frequency and then receded to higher frequencies. The burst was partial viewed from STA, revealing only the edge coming down to the lowest frequency. The type IV burst was not observed at all near Earth because the source was 61 degrees behind the east limb. The eruption was associated with a low -frequency type II burst observed in all three views, although it was not very intense. Solar energetic particles were also observed at both STEREOs and at SOHO, suggesting that the shock was much extended, consistent with the very high speed of the CME (similar to 2048 km/s). These observations suggest that the type IV emission is directed along a narrow cone above the flare site. We confirm this result statistically using the type IV bursts of solar cycle 23. C1 [Gopalswamy, N.; Akiyama, S.; Makela, P.; Yashiro, S.] NASA, Goddard Space Flight Ctr, Solar Phys Lab, Heliophys Div, Greenbelt, MD 20771 USA. [Cairns, I. H.] Univ Sydney, Sch Phys, Sydney, NSW, Australia. RP Gopalswamy, N (reprint author), NASA, Goddard Space Flight Ctr, Solar Phys Lab, Heliophys Div, Greenbelt, MD 20771 USA. EM nat.gopalswamy@nasa.gov; iver.cairns@sydney.edu.au NR 10 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4673-8801-6 PY 2016 BP 1247 EP 1249 PG 3 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BG0TH UT WOS:000386515800153 ER PT J AU Teklu, TB Gholap, A Gopalswamy, N Yashiro, S Makela, P Akiyama, S Thakur, N Xie, H AF Teklu, T. B. Gholap, A. V. Gopalswamy, N. Yashiro, S. Makela, P. Akiyama, S. Thakur, N. Xie, H. GP IEEE TI A Study of the 2012 January 19 Complex Type II Radio Burst Using Wind, SOHO, and STEREO Observations SO 2016 URSI ASIA-PACIFIC RADIO SCIENCE CONFERENCE (URSI AP-RASC) LA English DT Proceedings Paper CT URSI Asia-Pacific Radio Science Conference (URSI AP-RASC) CY AUG 21-25, 2016 CL Seoul, SOUTH KOREA SP KIEES, URSI, Natl Radio Res Agcy, Elect & Telecommunicat Res Inst, Korea Astron & Space Sci Inst, NFRI, EiC, IEEE Antennas & Propagat Soc, IEEE Antennas & Propagat Soc Seoul Chapter, KICS, IEIE, KOFST, SEOUL Metropolitan Govt, Korea Tourism Org, Samsung, LG Innotek, LIG, LG Elect, SK Telecom, Hanwha Thales, Kt, MTG DE coronal mass ejection; type II radio burst; shock ID CORONAL MASS EJECTIONS; SPACECRAFT; SUN AB We report on a case study of the complex type II radio burst of 2012 January 19 and its association with a white light coronal mass ejection (CME). The complexity can be described as the appearance of an additional type H burst component and strong intensity variation. The dynamic spectrum shows a pair of type II bursts with fundamental harmonic structures, one confined to decameter-hectometric (DH) wavelengths and the other extending to kilometric (km) wavelengths. By comparing the speeds obtained from white-light images with that speed of the shock inferred from the drift rate, we show that the source of the short-lived DH component is near the nose. C1 [Teklu, T. B.; Gholap, A. V.] Univ Addis Ababa, Dept Phys, Addis Ababa, Ethiopia. [Gopalswamy, N.; Yashiro, S.; Makela, P.; Akiyama, S.; Thakur, N.; Xie, H.] NASA, Goddard Space Flight Ctr, Heliospher Div, Solar Phys Lab, Greenbelt, MD USA. RP Teklu, TB (reprint author), Univ Addis Ababa, Dept Phys, Addis Ababa, Ethiopia. EM selameykulu@gmail.com; nat.gopalswamy@nasa.gov; Seiji.Yashiro@nasa.gov; pertti.a.makela@nasa.gov; Sachiko.Akiyama@nasa.gov; necharika.thakur@nasa.gov; hong.xie-l@nasa.gov NR 14 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4673-8801-6 PY 2016 BP 1250 EP 1253 PG 4 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BG0TH UT WOS:000386515800154 ER PT J AU Carter, D Freesland, D Tadikonda, SK Kronenwetter, J Todirita, M Dahya, M Chu, D AF Carter, Delano Freesland, Douglas Tadikonda, Sivakumara K. Kronenwetter, Jeffrey Todirita, Monica Dahya, Melissa Chu, Donald BE Ouwehand, L TI CORRECTING GOES-R MAGNETOMETER DATA FOR STRAY FIELDS SO PROCEEDINGS OF 2016 ESA WORKSHOP ON AEROSPACE EMC (AEROSPACE EMC) LA English DT Proceedings Paper CT ESA Workshop on Aerospace EMC (Aerospace EMC) CY MAY 23-25, 2016 CL Valencia, SPAIN SP European Space Agcy, IEEE EMC Soc, European Test Serv, R & S Shop, Montena AB Time-varying spacecraft magnetic fields, i.e. stray fields, are a problem for magnetometer systems. While constant fields can be removed by calibration, stray fields are difficult to distinguish from ambient field variations. Putting two magnetometers on a long boom and solving for both the ambient and stray fields can help, but this gradiometer solution is more sensitive to noise than a single magnetometer. As shown here for the R-series Geostationary Operational Environmental Satellites (GOES-R), unless the stray fields are larger than the noise, simply averaging the two magnetometer readings gives a more accurate solution. If averaging is used, it may be worthwhile to estimate and remove stray fields explicitly. Models and estimation algorithms to do so are provided for solar array, arcjet and reaction wheel fields. C1 [Carter, Delano] NASA, Thearal, GSFC, Code 417-0, Greenbelt, MD 20771 USA. [Freesland, Douglas] NASA, ACS Engn, GSFC, Code 417-0, Greenbelt, MD 20771 USA. [Tadikonda, Sivakumara K.] NASA, Constellat Software Engn, GSFC, Code 417-0, Greenbelt, MD 20771 USA. [Kronenwetter, Jeffrey; Chu, Donald] NASA, Chesapeake Aerosp, GSFC, Code 417-0, Greenbelt, MD 20771 USA. [Todirita, Monica] NASA, NOAA, GSFC, Code 417-0, Greenbelt, MD 20771 USA. [Dahya, Melissa] NASA, ASRC Fed, GSFC, Code 417-0, Greenbelt, MD 20771 USA. RP Carter, D (reprint author), NASA, Thearal, GSFC, Code 417-0, Greenbelt, MD 20771 USA. EM delano.r.carter@nasa.gov; douglas.c.freesland@nasa.gov; sivakumara.k.tadikonda@nasa.gov; jeffrey.a.kronenwettet@nasa.gov; monica.todirila-1@nasa.gov; melissa.dahya@noaa.gov; donald.chu-1@nasa.gov NR 7 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-9-2922-1303-9 PY 2016 PG 6 WC Engineering, Aerospace; Engineering, Electrical & Electronic SC Engineering GA BG0KT UT WOS:000386313000058 ER PT J AU Perez, R AF Perez, Reinaldo BE Ouwehand, L TI ANALYSIS AND SIMULATIONS OF SPACE RADIATION INDUCED SINGLE EVENT TRANSIENTS SO PROCEEDINGS OF 2016 ESA WORKSHOP ON AEROSPACE EMC (AEROSPACE EMC) LA English DT Proceedings Paper CT ESA Workshop on Aerospace EMC (Aerospace EMC) CY MAY 23-25, 2016 CL Valencia, SPAIN SP European Space Agcy, IEEE EMC Soc, European Test Serv, R & S Shop, Montena AB Spacecraft electronics are affected by the space radiation environment. Among the different types of radiation effects that can affect spacecraft electronics is the single event transients. The space environment is responsible for many of the single event transients which can upset the performance of the spacecraft avionics hardware. In this paper we first explore the origins of single event transients, then explore the modeling of a single event transient in digital and analog circuit. The paper also addresses the concept of crosstalk that could develop among digital circuits in the present of a SET event. The paper ends with a brief discussion of SET hardening. The goal of the paper is to provide methodologies for assessing single event transients and their effects so that spacecraft avionics engineers can develop either hardware or software countermeasures in their designs C1 [Perez, Reinaldo] Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Perez, R (reprint author), Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Reinaldo.j.perez@jpl.nasa.gov NR 6 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-9-2922-1303-9 PY 2016 PG 6 WC Engineering, Aerospace; Engineering, Electrical & Electronic SC Engineering GA BG0KT UT WOS:000386313000030 ER PT S AU Massa, GD Wheeler, RM Morrow, RC Levine, HG AF Massa, G. D. Wheeler, R. M. Morrow, R. C. Levine, H. G. BE Currey, CJ Lopez, RG Runkle, ES TI Growth chambers on the International Space Station for large plants SO VIII INTERNATIONAL SYMPOSIUM ON LIGHT IN HORTICULTURE SE Acta Horticulturae LA English DT Proceedings Paper CT 8th International Symposium on Light in Horticulture CY MAY 22-26, 2016 CL East Lansing, MI SP Int Soc Hort Sci AB The International Space Station (ISS) now has platforms for conducting research on horticultural plant species under LED lighting, and those capabilities continue to expand. The 'Veggie' vegetable production system was deployed to the ISS as an applied research platform for food production in space. Veggie is capable of growing a wide array of horticultural crops. It was designed for low power usage, low launch mass and stowage volume, and minimal crew time requirements. The Veggie flight hardware consists of a light cap containing red (630 nm), blue, (455 nm) and green (530 nm) LEDs. Interfacing with the light cap is an extendable bellows/baseplate for enclosing the plant canopy. A second large plant growth chamber, the Advanced Plant Habitat (APH), will fly to the ISS in 2017. APH will be a fully controllable environment for high-quality plant physiological research. APH will control light (quality, level, and timing), temperature, CO2, relative humidity, and irrigation, while scrubbing any cabin or plant-derived ethylene and other volatile organic compounds. Additional capabilities include sensing of leaf temperature and root zone moisture, root zone temperature, and oxygen concentration. The light cap will have red (630 nm), blue (450 nm), green (525 nm), far red (730 nm) and broad spectrum white LEDs (4100 K). There will be several internal cameras (visible and IR) to monitor and record plant growth and operations. Veggie and APH are available for research proposals. C1 [Massa, G. D.; Wheeler, R. M.; Levine, H. G.] NASA, Kennedy Space Ctr, FL 32899 USA. [Morrow, R. C.] ORBITEC, Madison, WI 53717 USA. RP Massa, GD (reprint author), NASA, Kennedy Space Ctr, FL 32899 USA. EM gioia.massa@nasa.gov NR 4 TC 0 Z9 0 U1 6 U2 6 PU INT SOC HORTICULTURAL SCIENCE PI LEUVEN 1 PA PO BOX 500, 3001 LEUVEN 1, BELGIUM SN 0567-7572 BN 978-94-62611-09-2 J9 ACTA HORTIC PY 2016 VL 1134 BP 215 EP 221 DI 10.17660/ActaHortic.2016.1134.29 PG 7 WC Horticulture SC Agriculture GA BG0MF UT WOS:000386327100029 ER PT S AU Scardelletti, MC Jordan, JL Meredith, RD Harsh, K Pilant, E Ursey, MW Beheim, GM Hunter, GW Zorman, CA AF Scardelletti, Maximilian C. Jordan, Jennifer L. Meredith, Roger D. Harsh, Kevin Pilant, Evan Ursey, Michael W. Beheim, Glenn M. Hunter, Gary W. Zorman, Christian A. GP IEEE Computer Soc TI Demonstration of a Packaged Capacitive Pressure Sensor System Suitable for Jet Turbofan Engine Health Monitoring SO 2016 IEEE 66TH ELECTRONIC COMPONENTS AND TECHNOLOGY CONFERENCE (ECTC) SE Electronic Components and Technology Conference LA English DT Proceedings Paper CT 66th IEEE Electronic Components and Technology Conference (ECTC) CY MAY 31-JUN 03, 2016 CL Las Vegas, NV SP IEEE, IEEE Components Packaging & Mfg Technol Soc DE component; Capacitvr pressure sensor; Clapp-type oscillator; passive components; turbofan engine ID SILICOALUMINUM CARBONITRIDE; OXIDATION; RESIST AB In this paper, the development and characterization of a packaged pressure sensor system suitable for jet engine health monitoring is demonstrated. The sensing system operates from 97 to 117 MHz over a pressure range from 0 to 350 psi and a temperature range from 25 to 500 degrees C. The sensing system consists of a Clapp-type oscillator that is fabricated on an alumina substrate and is comprised of a Cree SiC MESFET, MIM capacitors, a wire-wound inductor, chip resistors and a SiCN capacitive pressure sensor. The pressure sensor is located in the LC tank circuit of the oscillator so that a change in pressure causes a change in capacitance, thus changing the resonant frequency of the sensing system. The chip resistors, wire-wound inductors and MIM capacitors have all been characterized at temperature and operational frequency, and perform with less than 5% variance in electrical performance. The measured capacitive pressure sensing system agrees very well with simulated results. The packaged pressure sensing system is specifically designed to measure the pressure on a jet turbofan engine. The packaged system can be installed by way of borescope plug adaptor fitted to a borescope port exposed to the gas path of a turbofan engine. C1 [Scardelletti, Maximilian C.; Jordan, Jennifer L.; Meredith, Roger D.; Beheim, Glenn M.; Hunter, Gary W.] NASA, Glenn Reseach Ctr, Cleveland, OH 44135 USA. [Harsh, Kevin; Pilant, Evan; Ursey, Michael W.] Sporian Microsyst, Lafayette, CO 80026 USA. [Zorman, Christian A.] Case Western Reserve Univ, Cleveland, OH 44106 USA. RP Scardelletti, MC (reprint author), NASA, Glenn Reseach Ctr, Cleveland, OH 44135 USA. OI Zorman, Christian/0000-0001-9773-9351 NR 14 TC 0 Z9 0 U1 2 U2 2 PU IEEE COMPUTER SOC PI LOS ALAMITOS PA 10662 LOS VAQUEROS CIRCLE, PO BOX 3014, LOS ALAMITOS, CA 90720-1264 USA SN 0569-5503 BN 978-1-5090-1204-6 J9 ELEC COMP C PY 2016 BP 877 EP 888 DI 10.1109/ECTC.2016.380 PG 12 WC Engineering, Electrical & Electronic SC Engineering GA BG0BA UT WOS:000386103500129 ER PT J AU Dalton, J Keyawa, M Settember, M Botvinnik, I Ruitberg, AP AF Dalton, Jerry Keyawa, Matthew Settember, Michael Botvinnik, Igor Ruitberg, Arthur P. GP IEEE TI High Voltage Grid Modulator for Extended Interaction Klystron (EIK) SO 2016 IEEE INTERNATIONAL VACUUM ELECTRONICS CONFERENCE (IVEC) SE IEEE International Vacuum Electronics Conference IVEC LA English DT Proceedings Paper CT 17th IEEE International Vacuum Electronics Conference (IVEC) CY APR 19-21, 2016 CL Monterey, CA SP IEEE, Army Res Off, L 3, Electron Energy Corp, Ceradyne Inc, Appl Phys Technologies, Colorado Power Elect, Lockheed Martin, Commun & Power Ind, Leidos, Northrop Grumman, SSL, Teledyne Microwave Solut, Raytheon, Bridge 12, Beam Wave Res Inc, CBL Ceram Ltd, CST Amer Inc, HRC, e beam Incorporated, SMI, Tech X DE EIK; grid modulator; high voltage; MOSFET AB High voltage solid state modulator was designed and optimized for EIK used in High Power Amplifier (HPA) for space application. The modulator switches the EIK electron beam on and off with rise/fall times in order of 100 ns to 200 ns. The modulator floats at cathode potential close to -14 KV and commutates the EIK grid between potentials of -20 V and -2.8 KV respectively to cathode with pulse width in order of several microseconds and PRF around 9 KHz. C1 [Dalton, Jerry; Keyawa, Matthew; Settember, Michael; Botvinnik, Igor] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. [Ruitberg, Arthur P.] Space Power Elect Inc, Kathleen, GA 31047 USA. RP Dalton, J (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. NR 4 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4673-9217-4 J9 IEEE INT VAC ELECT C PY 2016 PG 2 WC Engineering, Electrical & Electronic SC Engineering GA BG0DO UT WOS:000386185700085 ER PT J AU Harvey, W Tope, M Esteban-Fernandez, D Roitman, A Sokol, E Berry, D AF Harvey, Wayne Tope, Michael Esteban-Fernandez, Daniel Roitman, Albert Sokol, Ed Berry, Dave GP IEEE TI Development Path of a Ka-Band Extended Interaction Klystron for Space-borne Interferometer SO 2016 IEEE INTERNATIONAL VACUUM ELECTRONICS CONFERENCE (IVEC) SE IEEE International Vacuum Electronics Conference IVEC LA English DT Proceedings Paper CT 17th IEEE International Vacuum Electronics Conference (IVEC) CY APR 19-21, 2016 CL Monterey, CA SP IEEE, Army Res Off, L 3, Electron Energy Corp, Ceradyne Inc, Appl Phys Technologies, Colorado Power Elect, Lockheed Martin, Commun & Power Ind, Leidos, Northrop Grumman, SSL, Teledyne Microwave Solut, Raytheon, Bridge 12, Beam Wave Res Inc, CBL Ceram Ltd, CST Amer Inc, HRC, e beam Incorporated, SMI, Tech X DE Extended Interaction Klystron; EIK; Ka-Band; phase stability; group delay; Interferometer; Surface Water and Ocean Topography (SWOT) AB An Extended Interaction Klystron (EIK) design has been developed to the support extreme signal stability requirements of space-borne interferometric applications. This is an unprecedented set of requirements for an EIK. In conjunction with the Canadian Space Agency (ASC/CSA) and Jet Propulsion Laboratory, Communications and Power Industries, Canada (CPI) advanced this development through testing of a heritage design EIK, testing a dedicated Demonstration Model EIK and an Engineering Model EIK. Each step of testing provided guidance in the development of the EIK Design, finally providing confidence in the EIK's ability to support the needs of the interferometric radar. C1 [Harvey, Wayne; Tope, Michael; Esteban-Fernandez, Daniel] CALTECH, Jet Prop Lab, Pasadena, CA 90808 USA. [Roitman, Albert; Sokol, Ed; Berry, Dave] Commun & Power Ind, 45 River Dr, Georgetown, ON L7G 2J4, Canada. RP Harvey, W (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 90808 USA. EM wayne.l.haryey@jpl.nasa.gov NR 0 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4673-9217-4 J9 IEEE INT VAC ELECT C PY 2016 PG 2 WC Engineering, Electrical & Electronic SC Engineering GA BG0DO UT WOS:000386185700028 ER PT S AU Davarian, F Chan, S Naudet, C Oudrhiri, K AF Davarian, F. Chan, S. Naudet, C. Oudrhiri, K. GP IEEE TI Satellite-Aided Radar Imaging (SARI) SO 2016 IEEE RADAR CONFERENCE (RADARCONF) SE IEEE Radar Conference LA English DT Proceedings Paper CT IEEE Radar Conference (RadarConf) CY MAY 02-06, 2016 CL Philadelphia, PA SP IEEE AB This paper describes a novel technique for radar imaging of space objects. The approach is founded on using a small satellite near the target of interest as the receive end of a high power ground-based radar transmitter for imaging. The small satellite is equipped with an open loop receiver for sampling and processing the observed wideband signal and a GPS receiver for orbit determination. It also contains appropriate algorithms for signal processing and receive and transmit antennas for collecting the radar signal and transmitting telemetry to the ground. The discussion in this paper is limited mainly to a point design for simplicity. It should be noted that the reach and capability of the proposed approach go beyond the example presented in this paper. C1 [Davarian, F.; Chan, S.; Naudet, C.; Oudrhiri, K.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91125 USA. RP Davarian, F (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91125 USA. NR 3 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1097-5764 BN 978-1-5090-0863-6 J9 IEEE RAD CONF PY 2016 BP 350 EP 354 PG 5 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BG0MM UT WOS:000386327800067 ER PT S AU Venkatesh, V Li, L McLinden, M Heymsfield, G Coon, M AF Venkatesh, V. Li, L. McLinden, M. Heymsfield, G. Coon, M. GP IEEE TI A Frequency Diversity Pulse-Pair Algorithm for Extending Doppler Radar Velocity Nyquist Range SO 2016 IEEE RADAR CONFERENCE (RADARCONF) SE IEEE Radar Conference LA English DT Proceedings Paper CT IEEE Radar Conference (RadarConf) CY MAY 02-06, 2016 CL Philadelphia, PA SP IEEE ID POLARIZATION DIVERSITY; CLOUD AB Millimeter wave radars have been widely used for atmospheric remote sensing and tracking hard-targets from airborne platforms. For these radars, the product of the unambiguous range and Doppler velocity is limited by the radar wavelength. This work focuses on a novel method to extend the Nyquist rate of millemeter radars, which uses frequency diversity pulse-pairs for Doppler phase estimation. Two short pulses with center-frequencies of f(1) followed by f(2) are transmitted during the first pulse repetition interval (PRI). During the next PRI, the pulses transmitted are in the order f(2) followed by f(1) respectively. There are two mechanisms for error reduction. First, the "beat" phases of the f(1)/f(2) and f(2)/f(1) pairs cancel out in the expected value sense. Second, since the f(1)/f(2) and f(2)/f(1) phase estimates are highly anti-correlated, the sum of the two phase estimates has a much smaller variance than the individual phase estimates. Based on Monte-Carlo simulations, the feasibility of this method is demonstrated herein. Ongoing data analysis is discussed. C1 [Venkatesh, V.] Sci Syst & Applicat Inc, Greenbelt, MD 20771 USA. [Venkatesh, V.; Li, L.; McLinden, M.; Heymsfield, G.; Coon, M.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Venkatesh, V (reprint author), Sci Syst & Applicat Inc, Greenbelt, MD 20771 USA.; Venkatesh, V (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. EM vijay.venkatesh@nasa.gov NR 13 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1097-5764 BN 978-1-5090-0863-6 J9 IEEE RAD CONF PY 2016 BP 685 EP 690 PG 6 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BG0MM UT WOS:000386327800132 ER PT S AU Chuang, CL Shaffer, S Niamsuwan, N Li, S Liao, E Lim, C Duong, V Volain, B Vines, K Yang, MW Wheeler, K AF Chuang, Chung-Lun Shaffer, Scott Niamsuwan, Noppasin Li, Samuel Liao, Eric Lim, Chester Duong, Vu Volain, Barry Vines, Ken Yang, Muh-Wang Wheeler, Kevin GP IEEE TI NISAR L-band Digital Electronics Subsystem A Multichannel System with Distributed Processors for Digital Beam Forming and Mode Dependent Filtering SO 2016 IEEE RADAR CONFERENCE (RADARCONF) SE IEEE Radar Conference LA English DT Proceedings Paper CT IEEE Radar Conference (RadarConf) CY MAY 02-06, 2016 CL Philadelphia, PA SP IEEE DE SweepSAR; Digital Beamforming; Distributed Processing; SCORE; PRF Dithering; Staggered SAR; HRWS SAR AB The NASA-ISRO Synthetic Aperture Radar (NISAR) L-band SAR instrument employs multiple digital channels to optimize resolution while keeping a large swath on a single pass. High-speed digitization with fine synchronization and digital beam forming are necessary in order to facilitate this new technique called SweepSAR. An architecture employing multiple FPGA based digital signal processors has been conceived to facilitate digital calibration on an individual channel basis as well as digital signal processing to optimize the receive signal. On-board processing and data compression has been implemented to reduce the volume of data in order to satisfy the operational requirements of near global coverage for the desired science targets. A novel command and timing architecture was developed to manage this complex system to meet the challenging project requirements. The NISAR L-band Digital Electronics Subsystem is the combination of the hardware, firmware and software components architected and implemented to operate this radar and return the desired quantity and quality of data for the science community. C1 [Chuang, Chung-Lun; Shaffer, Scott; Niamsuwan, Noppasin; Li, Samuel; Liao, Eric; Lim, Chester; Duong, Vu; Volain, Barry; Vines, Ken; Yang, Muh-Wang; Wheeler, Kevin] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91125 USA. RP Chuang, CL (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91125 USA. EM Ernie.Chuang@jpl.nasa.gov NR 11 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1097-5764 BN 978-1-5090-0863-6 J9 IEEE RAD CONF PY 2016 BP 839 EP 843 PG 5 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BG0MM UT WOS:000386327800163 ER PT J AU Fries, M Christou, A Archer, D Conrad, P Cooke, W Eigenbrode, J ten Kate, IL Matney, M Niles, P Sykes, M Steele, A Treiman, A AF Fries, M. Christou, A. Archer, D. Conrad, P. Cooke, W. Eigenbrode, J. ten Kate, I. L. Matney, M. Niles, P. Sykes, M. Steele, A. Treiman, A. TI A cometary origin for martian atmospheric methane SO GEOCHEMICAL PERSPECTIVES LETTERS LA English DT Article ID DUST TRAILS; METEOR OUTBURSTS; PERIODIC COMETS; MARS; EARTH; IMPACTS; STREAMS; SEARCH; SWARM; FLUX AB Methane has been reported repeatedly in the martian atmosphere but its origin remains an obstinate mystery. Possible sources include aqueous alteration of igneous rocks, release from ancient deposits of methane/water ice clathrates, infall from exogenous sources such as background interplanetary dust, or biological activity. All of these sources are problematic, however. We hypothesise that delivery of cometary material includes meteor outbursts, commonly known as "meteor showers", may explain martian methane plumes. Correlations exist between the appearance of methane and near-approaches between Mars and cometary orbits. Additional correlations are seen between these interactions and the appearance of high-altitude dust clouds on Mars, showing that large amounts of material may be deposited on Mars during these encounters. Methane is released by UV breakdown of delivered cometary material. This hypothesis is testable in future Mars/cometary encounters. A cometary origin for methane would reveal formation of methane through processes that are separate from any geological or biological processes on Mars. C1 [Fries, M.; Matney, M.; Niles, P.] NASA, Johnson Space Ctr, ARES, Houston, TX 77059 USA. [Christou, A.] Armagh Observ, Coll Hill, Armagh BT61 9DG, North Ireland. [Archer, D.] NASA, Jacobs, Johnson Space Ctr, Houston, TX 77059 USA. [Conrad, P.; Eigenbrode, J.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Cooke, W.] NASA, Marshall Space Flight Ctr, Huntsville, AL 35812 USA. [ten Kate, I. L.] Univ Utrecht, Dept Earth Sci, NL-3508 TC Utrecht, Netherlands. [Sykes, M.] Planetary Sci Inst, Tucson, AZ 85719 USA. [Steele, A.] Carnegie Inst Sci, Geophys Lab, 5251 Broad Branch Rd NW, Washington, DC 20015 USA. [Treiman, A.] Lunar & Planetary Inst, 3303 NASA Rd 1, Houston, TX 77058 USA. RP Fries, M (reprint author), NASA, Johnson Space Ctr, ARES, Houston, TX 77059 USA. EM marc.d.fries@nasa.gov NR 51 TC 3 Z9 3 U1 0 U2 0 PU EUROPEAN ASSOC GEOCHEMISTRY PI PARIS CEDEX 05 PA IPGP-GOPEL-BUREAU 566, 1 RUE JUSSIEU, PARIS CEDEX 05, 75238, FRANCE SN 2410-339X EI 2410-3403 J9 GEOCHEM PERSPECT LET JI Geochem. Perspect. Lett. PY 2016 VL 2 IS 1 BP 10 EP 22 DI 10.7185/geochemlet.1602 PG 7 WC Geochemistry & Geophysics SC Geochemistry & Geophysics GA EA1JL UT WOS:000386348300002 ER PT S AU Munoz, C Narkawicz, A AF Munoz, Cesar Narkawicz, Anthony BE Rayadurgam, S Tkachuk, O TI Formal Analysis of Extended Well-Clear Boundaries for Unmanned Aircraft SO NASA FORMAL METHODS, NFM 2016 SE Lecture Notes in Computer Science LA English DT Proceedings Paper CT 8th NASA Formal Methods (NFM) International Symposium CY JUN 07-09, 2016 CL Minneapolis, MN SP NASA Ames Res Ctr, Univ Minnesota Software Engn Ctr AB This paper concerns the application of formal methods to the definition of a detect and avoid concept for unmanned aircraft systems (UAS). In particular, it illustrates how formal analysis was used to explain and correct unexpected behaviors of the logic that issues alerts when two aircraft are predicted not to be well clear from one another. As a result of this analysis, a recommendation was proposed to, and subsequently adopted by, the US standards organization that defines the minimum operational requirements for the UAS detect and avoid concept. C1 [Munoz, Cesar; Narkawicz, Anthony] NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Munoz, C (reprint author), NASA, Langley Res Ctr, Hampton, VA 23681 USA. EM cesar.a.munoz@nasa.gov; anthony.narkawicz@nasa.gov NR 7 TC 0 Z9 0 U1 0 U2 0 PU SPRINGER INT PUBLISHING AG PI CHAM PA GEWERBESTRASSE 11, CHAM, CH-6330, SWITZERLAND SN 0302-9743 BN 978-3-319-40648-0; 978-3-319-40647-3 J9 LECT NOTES COMPUT SC PY 2016 VL 9690 BP 221 EP 226 DI 10.1007/978-3-319-40648-0_17 PG 6 WC Computer Science, Software Engineering; Computer Science, Theory & Methods SC Computer Science GA BG0LH UT WOS:000386324800017 ER PT S AU Guarro, S Ozguner, U Aldemir, T Knudson, M Kurt, A Yau, M Hejase, M Kwon, S AF Guarro, Sergio Ozguner, Umit Aldemir, Tunc Knudson, Matt Kurt, Arda Yau, Michael Hejase, Mohammad Kwon, Steve BE Rayadurgam, S Tkachuk, O TI Formal Validation and Verification Framework for Model-Based and Adaptive Control Systems SO NASA FORMAL METHODS, NFM 2016 SE Lecture Notes in Computer Science LA English DT Proceedings Paper CT 8th NASA Formal Methods (NFM) International Symposium CY JUN 07-09, 2016 CL Minneapolis, MN SP NASA Ames Res Ctr, Univ Minnesota Software Engn Ctr DE Validation and verification; Safety case; Model based control system; Adaptive control system; Unmanned aircraft system AB This paper presents the interim results of a three-year NASA project for the development of a comprehensive framework for the validation and verification (V&V) of model-based control systems and adaptive control systems (MBCSs/ACSs), with focus on Unmanned Aircraft Systems (UAS) applications. The framework applies a formal V&V methodology based on a combination of logic-dynamic model constructs and associated analysis processes, to support the generation of a documentable assurance case for a UAS control system, and to demonstrate its compliance with applicable aviation system certification standards. C1 [Guarro, Sergio; Yau, Michael] ASCA Inc, Redondo Beach, CA 90277 USA. [Ozguner, Umit; Aldemir, Tunc; Kurt, Arda; Hejase, Mohammad; Kwon, Steve] Ohio State Univ, Columbus, OH 43210 USA. [Knudson, Matt] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Guarro, S (reprint author), ASCA Inc, Redondo Beach, CA 90277 USA. EM sergio.guarro@ascainc.com; ozguner.1@osu.edu; aldemir.1@osu.edu; matt.knudson@nasa.gov; kurt.12@osu.edu; mike.yau@ascainc.com; hejase.1@osu.edu; kwon.317@osu.edu NR 8 TC 0 Z9 0 U1 1 U2 1 PU SPRINGER INT PUBLISHING AG PI CHAM PA GEWERBESTRASSE 11, CHAM, CH-6330, SWITZERLAND SN 0302-9743 BN 978-3-319-40648-0; 978-3-319-40647-3 J9 LECT NOTES COMPUT SC PY 2016 VL 9690 BP 227 EP 233 DI 10.1007/978-3-319-40648-0_18 PG 7 WC Computer Science, Software Engineering; Computer Science, Theory & Methods SC Computer Science GA BG0LH UT WOS:000386324800018 ER PT S AU De Bernardis, F Stevens, JR Hasselfield, M Alonso, D Bond, JR Calabrese, E Choi, SK Crowley, KT Devlin, M Dunkley, J Gallardo, PA Henderson, SW Hilton, M Hlozek, R Ho, SP Huffenberger, K Koopman, BJ Kosowsky, A Louis, T Madhavacheril, MS McMahonn, J Naess, S Nati, F Newburgh, L Niemack, MD Page, LA Salatino, M Schillaci, A Schmitt, BL Sehgal, N Sievers, JL Simon, SM Spergel, DN Staggs, ST van Engelen, A Vavagiakis, EM Wollack, EJ AF De Bernardis, F. Stevens, J. R. Hasselfield, M. Alonso, D. Bond, J. R. Calabrese, E. Choi, S. K. Crowley, K. T. Devlin, M. Dunkley, J. Gallardo, P. A. Henderson, S. W. Hilton, M. Hlozek, R. Ho, S. P. Huffenberger, K. Koopman, B. J. Kosowsky, A. Louis, T. Madhavacheril, M. S. McMahonn, J. Naess, S. Nati, F. Newburgh, L. Niemack, M. D. Page, L. A. Salatino, M. Schillaci, A. Schmitt, B. L. Sehgal, N. Sievers, J. L. Simon, S. M. Spergel, D. N. Staggs, S. T. van Engelen, A. Vavagiakis, E. M. Wollack, E. J. BE Peck, AB Seaman, RL Benn, CR TI Survey strategy optimization for the Atacama Cosmology Telescope SO OBSERVATORY OPERATIONS: STRATEGIES, PROCESSES, AND SYSTEMS VI SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Observatory Operations - Strategies, Processes, and Systems VI CY JUN 27-JUL 01, 2016 CL Edinburgh, SCOTLAND SP SPIE AB In recent years there have been significant improvements in the sensitivity and the angular resolution of the instruments dedicated to the observation of the Cosmic Microwave Background (CMB). ACTPo1 is the first polarization receiver for the Atacama Cosmology Telescope (ACT) and is observing the CMB sky with arcmin resolution over 2000 sq. deg. Its upgrade, Advanced ACTPo1 (AdvACT), will observe the CMB in five frequency bands and over a larger area of the sky. We describe the optimization and implementation of the ACTPo1 and AdvACT surveys. The selection of the observed fields is driven mainly by the science goals, that is, small angular scale CMB measurements, B-mode measurements and cross-correlation studies. For the ACTPo1 survey we have observed patches of the southern galactic sky with low galactic foreground emissions which were also chosen to maximize the overlap with several galaxy surveys to allow unique cross-correlation studies. A wider field in the northern galactic cap ensured significant additional overlap with the BOSS spectroscopic survey. The exact shapes and footprints of the fields were optimized to achieve uniform coverage and to obtain cross-linked maps by observing the fields with different scan directions. We have maximized the efficiency of the survey by implementing a close to 24 hour observing strategy, switching between daytime and nighttime observing plans and minimizing the telescope idle time. We describe the challenges represented by the survey optimization for the significantly wider area observed by AdvACT, which will observe roughly half of the low-foreground sky. The survey strategies described here may prove useful for planning future ground-based CMB surveys, such as the Simons Observatory and CMB Stage IV surveys. C1 [De Bernardis, F.; Stevens, J. R.; Gallardo, P. A.; Henderson, S. W.; Koopman, B. J.; Niemack, M. D.; Vavagiakis, E. M.] Cornell Univ, Dept Phys, Ithaca, NY 14850 USA. [Hasselfield, M.] Penn State Univ, Dept Astron & Astrophys, University Pk, PA 16802 USA. [Hasselfield, M.] Penn State Univ, Inst Gravitat & Cosmos, University Pk, PA 16802 USA. [Alonso, D.; Calabrese, E.; Dunkley, J.; Naess, S.] Univ Oxford, Denys Wilkinson Bldg,Keble Rd, Oxford OX1 3RH, England. [Bond, J. R.; van Engelen, A.] Univ Toronto, CITA, 60 St George St, Toronto, ON M55 3H8, Canada. [Choi, S. K.; Crowley, K. T.; Ho, S. P.; Page, L. A.; Salatino, M.; Simon, S. M.; Staggs, S. T.] Princeton Univ, Dept Phys, Princeton, NJ 08544 USA. [Devlin, M.; Nati, F.; Schmitt, B. L.] Univ Penn, Dept Phys & Astron, Philadelphia, PA 19104 USA. [Hilton, M.; Sievers, J. L.] Univ KwaZulu Natal, Westville Campus, ZA-4041 Durban, South Africa. [Hlozek, R.; Newburgh, L.] Univ Toronto, Dunlap Inst Astron & Astrophys, Toronto, ON M55 3H4, Canada. [Huffenberger, K.] Florida State Univ, Tallahassee, FL 32306 USA. [Kosowsky, A.] Univ Pittsburgh, Dept Phys & Astron, Pittsburgh, PA 15260 USA. [Louis, T.] Univ Paris 06, UMR7095, Inst Astrophys Paris, F-75014 Paris, France. [Madhavacheril, M. S.; Sehgal, N.] SUNY Stony Brook, Stony Brook, NY 11794 USA. [McMahonn, J.] Univ Michigan, Dept Phys, Ann Arbor, MI 48109 USA. [Schillaci, A.] Ponticia Univ Cattolica Chile, Fac Fis, Inst Astrofis, Santiago, Chile. [Schillaci, A.] Ponticia Univ Cattolica Chile, Fac Fis, Ctr Astroingn, Santiago, Chile. [Spergel, D. N.] Princeton Univ, Dept Astrophys Sci, Peyton Hall, Princeton, NJ 08544 USA. [Wollack, E. J.] NASA, Goddard Space Flight Ctr, 8800 Greenbelt Rd, Greenbelt, MD 20771 USA. RP De Bernardis, F (reprint author), Cornell Univ, Dept Phys, Ithaca, NY 14850 USA. RI Wollack, Edward/D-4467-2012 OI Wollack, Edward/0000-0002-7567-4451 NR 19 TC 0 Z9 0 U1 1 U2 1 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0199-4; 978-1-5106-0200-7 J9 PROC SPIE PY 2016 VL 9910 AR 991014 DI 10.1117/12.2232824 PG 14 WC Astronomy & Astrophysics; Optics SC Astronomy & Astrophysics; Optics GA BF9PO UT WOS:000385793600036 ER PT S AU Diehl, HT Neilsen, E Gruendl, R Yanny, B Abbott, TMC Aleksic, J Allam, S Annis, J Balbinot, E Baumer, M Beaufore, L Bechtol, K Bernstein, G Birrer, S Bonnett, C Brout, D Bruderer, C Buckley-Geer, EJ Capozzi, D Rosell, AC Castander, FJ Cawthon, R Chang, C Clerkin, L Covarrubias, R Cuhna, C D'Andrea, C da Costa, L Das, R Davis, C Dietrich, J Drlica-Wagner, A Elliott, A Eifler, TF Etherington, J Flaugher, BL Frieman, J Neto, AF Fernandez, MG Furlanetto, C Gangkofne, D Gerdes, DW Goldstein, DA Grabowski, K Gupta, RR Hamilton, S Head, H Helsby, J Hollowood, D Honscheid, K James, D Johnson, M Johnson, MWG Jouvel, S Kacprzac, T Kent, S Kessler, R Kim, A Krause, E Krawiec, CI Kremin, A Kron, R Kuhlmann, S Kuropatkin, N Lahav, O Lasker, J Li, TS Luque, E Maccrann, N March, M Marshall, J Mondrik, NP Morganson, EP Mudd, D Nadolski, A Nugent, P Melchior, P Menanteau, F Nagasawa, DQ Nord, B Ogando, R Old, L Palmese, A Petravick, D Plazas, AA Pujol, A Queiroz, ABA Reil, K Romer, AK Rosenfeld, R Roodman, A Rooney, P Sako, M Salvador, AI Sanchez, C Alvaro, ES Santiago, BX Schooneveld, A Schubnell, M Sheldon, E Smith, A Smith, RC Soares-Santos, M Sobreira, F Soumagnac, M Spinka, H Tie, SS Tucker, D Vikram, V Vivas, K Walker, AR Wester, W Wiesner, M Wilcox, H Williams, P Zenteno, A Zhang, Y Zhang, Z AF Diehl, H. T. Neilsen, E. Gruendl, R. Yanny, B. Abbott, T. M. C. Aleksic, J. Allam, S. Annis, J. Balbinot, E. Baumer, M. Beaufore, L. Bechtol, K. Bernstein, G. Birrer, S. Bonnett, C. Brout, D. Bruderer, C. Buckley-Geer, E. J. Capozzi, D. Rosell, A. Carnero Castander, F. J. Cawthon, R. Chang, C. Clerkin, L. Covarrubias, R. Cuhna, C. D'Andrea, C. da Costa, L. Das, R. Davis, C. Dietrich, J. Drlica-Wagner, A. Elliott, A. Eifler, T. F. Etherington, J. Flaugher, B. L. Frieman, J. Fausti Neto, A. Fernandez, M. G. Furlanetto, C. Gangkofne, D. Gerdes, D. W. Goldstein, D. A. Grabowski, K. Gupta, R. R. Hamilton, S. Head, H. Helsby, J. Hollowood, D. Honscheid, K. James, D. Johnson, M. Johnson, M. W. G. Jouvel, S. Kacprzac, T. Kent, S. Kessler, R. Kim, A. Krause, E. Krawiec, C. I. Kremin, A. Kron, R. Kuhlmann, S. Kuropatkin, N. Lahav, O. Lasker, J. Li, T. S. Luque, E. Maccrann, N. March, M. Marshall, J. Mondrik, N. P. Morganson, E. P. Mudd, D. Nadolski, A. Nugent, P. Melchior, P. Menanteau, F. Nagasawa, D. Q. Nord, B. Ogando, R. Old, L. Palmese, A. Petravick, D. Plazas, A. A. Pujol, A. Queiroz, A. B. A. Reil, K. Romer, A. K. Rosenfeld, R. Roodman, A. Rooney, P. Sako, M. Salvador, A. I. Sanchez, C. Sanchez Alvaro, E. Santiago, B. X. Schooneveld, A. Schubnell, M. Sheldon, E. Smith, A. Smith, R. C. Soares-Santos, M. Sobreira, F. Soumagnac, M. Spinka, H. Tie, S. S. Tucker, D. Vikram, V. Vivas, K. Walker, A. R. Wester, W. Wiesner, M. Wilcox, H. Williams, P. Zenteno, A. Zhang, Y. Zhang, Z. BE Peck, AB Seaman, RL Benn, CR TI The Dark Energy Survey and Operations: Years 1 to 3 SO OBSERVATORY OPERATIONS: STRATEGIES, PROCESSES, AND SYSTEMS VI SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Observatory Operations - Strategies, Processes, and Systems VI CY JUN 27-JUL 01, 2016 CL Edinburgh, SCOTLAND SP SPIE DE Cosmology; Dark Energy Survey; Dark Energy Camera; Operations; CTIO AB The Dark Energy Survey (DES) is an operating optical survey aimed at understanding the accelerating expansion of the universe using four complementary methods: weak gravitational lensing, galaxy cluster counts, baryon acoustic oscillations, and Type la supernovae. To perform the 5000 sq-degree wide field and 30 sq-degree supernova surveys, the DES Collaboration built the Dark Energy Camera (DECam), a 3 square-degree, 570-Megapixel CCD camera that was installed at the prime focus of the Blanco 4-meter telescope at the Cerro Tololo Inter-American Observatory (CTIO). DES has completed its third observing season out of a nominal five. This paper describes DES "Year 1" (Y1) to "Year 3" (Y3), the strategy, an outline of the survey operations procedures, the efficiency of operations and the causes of lost observing time. It provides details about the quality of the first three season's data, and describes how we are adjusting the survey strategy in the face of the El Niflo Southern Oscillation. C1 [Diehl, H. T.; Neilsen, E.; Yanny, B.; Allam, S.; Annis, J.; Buckley-Geer, E. J.; Drlica-Wagner, A.; Flaugher, B. L.; Frieman, J.; Grabowski, K.; Kent, S.; Kron, R.; Kuropatkin, N.; Nord, B.; Soares-Santos, M.; Sobreira, F.; Tucker, D.; Wester, W.; Wiesner, M.] Fermilab Natl Accelerator Lab, POB 500, Batavia, IL 60510 USA. [Gruendl, R.; Covarrubias, R.; Johnson, M.; Johnson, M. W. G.; Morganson, E. P.; Menanteau, F.; Petravick, D.] Natl Ctr Supercomp Applicat, 1205 West Clark St, Urbana, IL 61801 USA. [Gruendl, R.; Morganson, E. P.; Nadolski, A.; Menanteau, F.] Univ Illinois, Dept Astron, W Green St, Urbana, IL 61801 USA. [Abbott, T. M. C.; James, D.; Smith, R. C.; Vivas, K.; Walker, A. R.; Zenteno, A.] Natl Opt Astron Observ, Cerro Tololo Interamer Observ, Casilla 603, La Serena, Chile. [Aleksic, J.; Bonnett, C.; Sanchez, C.] Barcelona Inst Sci & Technol, IFAE, Bellaterra 08193, Barcelona, Spain. [Balbinot, E.] Univ Surrey, Dept Phys, Guildford GU2 7XH, Surrey, England. [Baumer, M.; Rosell, A. Carnero] Stanford Univ, Dept Phys, 382 Via Pueblo Mall, Stanford, CA 94305 USA. [Beaufore, L.; Elliott, A.; Honscheid, K.] Ohio State Univ, Dept Phys, Columbus, OH 43210 USA. [Bechtol, K.; Cawthon, R.; Helsby, J.; Kessler, R.; Krause, E.; Lasker, J.; Williams, P.] Univ Chicago, Kavli Inst Cosmol Phys, Chicago, IL 60637 USA. [Bechtol, K.] Univ Wisconsin, Dept Phys, Madison, WI 53706 USA. [Bernstein, G.; Brout, D.; Drlica-Wagner, A.; Eifler, T. F.; Krause, E.; Krawiec, C. I.; March, M.; Sako, M.; Santiago, B. X.] Univ Penn, Dept Phys & Astron, Philadelphia, PA 19104 USA. [Birrer, S.; Bruderer, C.; Chang, C.] Swiss Fed Inst Technol, Dept Phys, Inst Astron, Wolfgang Pauli Str 27, CH-8093 Zurich, Switzerland. [Capozzi, D.; Rosell, A. Carnero; D'Andrea, C.; Etherington, J.; Wilcox, H.] Univ Portsmouth, Inst Cosmol & Gravitat, Portsmouth PO1 3FX, Hants, England. [Castander, F. J.; Fernandez, M. G.; Pujol, A.] IEEC CSIC, ICE, E-08193 Bellaterra, Barcelona, Spain. [Clerkin, L.; Jouvel, S.; Kacprzac, T.; Lahav, O.; Palmese, A.; Soumagnac, M.] UCL, Dept Phys & Astron, Gower St, London WC1E 6BT, England. [Cuhna, C.; Davis, C.; Reil, K.; Roodman, A.] Stanford Univ, Kavli Inst Particle Astrophys & Cosmol, 452 Lomita Mall, Stanford, CA 94305 USA. [D'Andrea, C.] Univ Southampton, Dept Phys & Astron, Southampton SO17 1BJ, Hants, England. [da Costa, L.; Fausti Neto, A.; Luque, E.; Ogando, R.; Queiroz, A. B. A.] LIneA, Rua Gal Jose Cristino 77, BR-20921400 Rio De Janeiro, RJ, Brazil. [Das, R.; Gerdes, D. W.; Hamilton, S.; Kremin, A.; Schubnell, M.; Zhang, Y.] Univ Michigan, Dept Phys, Ann Arbor, MI 48109 USA. [Dietrich, J.; Gangkofne, D.] Univ Observ Munich, Scheinerstr 1, D-81679 Munich, Germany. [Dietrich, J.; Gangkofne, D.; Melchior, P.] Excellence Cluster Universe, D-85748 Garching, Germany. [Eifler, T. F.; Plazas, A. A.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Furlanetto, C.; Old, L.] Univ Nottingham, Sch Phys & Astron, Univ Pk, Nottingham NG7 2RD, England. [Goldstein, D. A.; Kim, A.; Nugent, P.] Lawrence Berkeley Natl Lab, 1 Cyclotron Rd, Berkeley, CA 94720 USA. [Goldstein, D. A.] Univ Calif Berkeley, Dept Astron, 501 Campbell Hall, Berkeley, CA 94720 USA. [Gupta, R. R.; Kuhlmann, S.; Spinka, H.; Vikram, V.] Argonne Natl Lab, 9700 South Cass Ave, Lemont, IL 60439 USA. [Head, H.; Smith, A.] Austin Peay State Univ, Dept Phys & Astron, Clarksville, TN 37044 USA. [Hollowood, D.] Univ Calif Santa Cruz, Dept Phys, Santa Cruz, CA 95064 USA. [Hollowood, D.] Univ Calif Santa Cruz, Santa Cruz Inst Particle Phys, Santa Cruz, CA 95064 USA. [Li, T. S.; Marshall, J.; Mondrik, N. P.; Nagasawa, D. Q.] Texas A&M Univ, George P & Cynthia Woods Mitchell Inst Fundamenta, College Stn, TX 77843 USA. [Li, T. S.; Marshall, J.; Mondrik, N. P.; Nagasawa, D. Q.] Texas A&M Univ, Dept Phys & Astron, College Stn, TX 77843 USA. [Luque, E.; Queiroz, A. B. A.; Santiago, B. X.] Univ Fed Rio Grande do Sul, Inst Fis, Caixa Postal 15051, BR-91501970 Porto Alegre, RS, Brazil. [Maccrann, N.] Univ Manchester, Sch Phys & Astron, Jodrell Bank Ctr Astrophys, Oxford Rd, Manchester M13 9P1, Lancs, England. [Mudd, D.; Tie, S. S.] Ohio State Univ, Dept Astron, Columbus, OH 43210 USA. [Melchior, P.] Ohio State Univ, Ctr Cosmol & Astroparticle Phys, Columbus, OH 43210 USA. [Ogando, R.] Observ Nacl, R Gal Jose Cristino 77, BR-20921400 Rio De Janeiro, RJ, Brazil. [Plazas, A. A.; Sheldon, E.] Brookhaven Natl Lab, Bldg 510, Upton, NY 11973 USA. [Reil, K.; Roodman, A.; Zhang, Z.] SLAC Natl Accelerator Lab, Menlo Pk, CA 94025 USA. [Romer, A. K.; Rooney, P.] Univ Sussex, Dept Phys & Astron, Brighton BN1 9RH, E Sussex, England. [Rosenfeld, R.; Sobreira, F.] Univ Estadual Paulista, Inst Fis Teor, Rua Dr Bento T Ferraz 271, BR-01140070 Sao Paulo, SP, Brazil. [Salvador, A. I.] UAM CSIC, Inst Fis Teor, Madrid, Spain. [Salvador, A. I.] CIEMAT, Madrid, Spain. [Schooneveld, A.] Univ Cambridge, Inst Astron, Madingley Rd, Cambridge CB3 0HA, England. RP Diehl, HT (reprint author), Fermilab Natl Accelerator Lab, POB 500, Batavia, IL 60510 USA. EM Diehl@FNAL.GOV RI Ogando, Ricardo/A-1747-2010; OI Ogando, Ricardo/0000-0003-2120-1154; Stern, Corvin/0000-0003-4406-6127 NR 43 TC 0 Z9 0 U1 4 U2 4 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0199-4; 978-1-5106-0200-7 J9 PROC SPIE PY 2016 VL 9910 AR 99101D DI 10.1117/12.2233157 PG 19 WC Astronomy & Astrophysics; Optics SC Astronomy & Astrophysics; Optics GA BF9PO UT WOS:000385793600043 ER PT S AU Fischer, C Bryant, A Beckman, S Colditz, S Fumi, F Geis, N Henning, T Honle, R Iserlohe, C Klein, R Krabbe, A Looney, LW Poglitsch, A Raab, W Rebell, F Trinh, C AF Fischer, Christian Bryant, Aaron Beckman, Simon Colditz, Sebastian Fumi, Fabio Geis, Norbert Henning, Thomas Hoenle, Rainer Iserlohe, Christof Klein, Randolf Krabbe, Alfred Looney, Leslie W. Poglitsch, Albrecht Raab, Walfried Rebell, Felix Trinh, Christopher BE Peck, AB Seaman, RL Benn, CR TI Observing with FIFI-LS on SOFIA - Time estimates and strategies to use a field imaging spectrometer on an airborne observatory SO OBSERVATORY OPERATIONS: STRATEGIES, PROCESSES, AND SYSTEMS VI SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Observatory Operations - Strategies, Processes, and Systems VI CY JUN 27-JUL 01, 2016 CL Edinburgh, SCOTLAND SP SPIE DE Integral Field Spectroscopy; Spectrometer; Far-infrared; FIFI LS; FIFI-LS; SOFIA; Observing Modes AB Observing on the Stratospheric Observatory for Infrared Astronomy (SOFIA) requires a strategy that takes the specific circumstances of an airborne platform into account. Observations of a source cannot be extended or shortened on the spot due to flight path constraints. Still, no exact prediction of the time on source is available since there are always wind and weather conditions, and sometimes technical issues. Observations have to be planned to maximize the observing efficiency while maintaining full flexibility for changes during the observation. The complex nature of observations with FIFI-LS such as the interlocking cycles of the mechanical gratings, telescope nodding and dithering - is considered in the observing strategy as well. Since SOFIA Cycle 3 FIFI-LS is available to general investigators. Therefore general investigators must be able to define the necessary parameters simply, without being familiar with the instrument, still resulting in efficient and flexible observations. We describe the observing process with FIFI-LS including the integration time estimate, the mapping and dithering setup and aspects of the scripting for the actual observations performed in flight. We also give an overview of the observing scenarios, which have proven to be useful for FIFI-LS. C1 [Fischer, Christian; Beckman, Simon; Colditz, Sebastian; Iserlohe, Christof; Krabbe, Alfred] Deutsch SOFIA Inst, Pfaffenwaldring 29, D-70569 Stuttgart, Germany. [Bryant, Aaron; Fumi, Fabio; Hoenle, Rainer; Krabbe, Alfred; Rebell, Felix] Univ Stuttgart, Inst Space Syst, Pfaffenwaldring 29, D-70569 Stuttgart, Germany. [Geis, Norbert; Poglitsch, Albrecht; Trinh, Christopher] Max Planck Inst Extraterr Phys, Giessenbachstr, D-85748 Garching, Germany. [Henning, Thomas] Max Planck Inst Astron, Konigstuhl 17, D-69117 Heidelberg, Germany. [Klein, Randolf] NASA, Ames Res Ctr, SOFIA USRA, N232, Moffett Field, CA 94035 USA. [Looney, Leslie W.] Univ Illinois, Dept Astron, 1002 W Green St, Urbana, IL 61801 USA. [Raab, Walfried] European Space Agcy, ESTEC, Keplerlaan 1, NL-2201 AZ Noordwijk, Netherlands. RP Fischer, C (reprint author), Deutsch SOFIA Inst, Pfaffenwaldring 29, D-70569 Stuttgart, Germany. EM fischer@dsi.uni-stuttgart.de NR 7 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-1-5106-0199-4; 978-1-5106-0200-7 J9 PROC SPIE PY 2016 VL 9910 AR 991027 DI 10.1117/12.2232148 PG 11 WC Astronomy & Astrophysics; Optics SC Astronomy & Astrophysics; Optics GA BF9PO UT WOS:000385793600072 ER EF