FN Thomson Reuters Web of Science™ VR 1.0 PT S AU Sayir, A Berger, MH Baudin, C AF Sayir, A. Berger, M. H. Baudin, C. BE LaraCurzio, E TI MICROSTRUCTURAL AND MECHANICAL PROPERTIES OF DIRECTIONALLY SOLIDIFIED CERAMIC IN Al(2)O(3)-Al(2)TiO(5) SYSTEM SO MECHANICAL PROPERTIES AND PERFORMANCE OF ENGINEERING CERAMICS AND COMPOSITES SE Ceramic Engineering and Science Proceedings LA English DT Proceedings Paper CT 29th International Conference on Advanced Ceramics and Composites CY JAN 23-28, 2005 CL Cocoa Beach, FL SP Amer Ceram Soc AB The mechanical properties of two-phase and poly-phase eutectics can be superior to that of either constituent alone due to the strong constraining effects of the interlocking microstructure. The present work focuses on the solidification characteristics and mechanical properties of Al(2)O(3)-Al(2)TiO(5) system. The challenge for the development of Al(2)O(3)-Al(2)TiO(5) system is to improve the mechanical strength and toughness concurrently with a high resistance to thermal decomposition. The solidification at the invariant eutectic point and Al(2)O(3) rich region of off-eutectic compositions was studied. Critical to this effort is the correlation of mechanical properties with eutectic growth data. The strength is strongly related to the starting volume fraction of the minor phase. High strength in the order of 340 MPa is associated with high Al(2)O(3) content Bend tests showed a large displacement for all compositions studied. The off-eutectic composition had Al(2)O(3) phase, new Al(6)Ti(2)O(13) phase as a major phase and Al(2)TiO(5) as a minor phase as determined by the WDX and FEG-TEM-STEM techniques. Samples from eutectic region consisted only Al(6)Ti(2)O(13) and Al(2)TiO(5) phases that bear a resemblance to layered structured materials. The proposed structure of new Al(6)Ti(2)O(13) phase contained one more AlO(6) octahedra along [010] direction and the proposed structure was confirmed by the x-ray, HRTEM, STEM and WDX analysis. The spatial arrangement of the new Al(6)Ti(2)O(13) phase and Al(2)TiO(5) phase around the reinforcing Al(2)O(3) dendrites and microcracking were responsible for the improved toughness. C1 [Sayir, A.] NASA, GRC, CWRU, Cleveland, OH 44135 USA. RP Sayir, A (reprint author), NASA, GRC, CWRU, 21000 Brookpk Rd, Cleveland, OH 44135 USA. OI Baudin, Carmen/0000-0002-9037-0931 NR 14 TC 8 Z9 11 U1 0 U2 2 PU AMER CERAMIC SOC PI WESTERVILLE PA 735 CERAMIC PLACE, WESTERVILLE, OH 43081-8720 USA SN 0196-6219 BN 978-1-57498-232-9 J9 CERAM ENG SCI PROC PY 2005 VL 26 IS 2 BP 225 EP 233 PG 9 WC Materials Science, Ceramics; Materials Science, Characterization & Testing; Materials Science, Composites SC Materials Science GA BMU95 UT WOS:000273627200028 ER PT S AU Kalluri, S Calomino, AM Brewer, DN AF Kalluri, Sreeramesh Calomino, Anthony M. Brewer, David N. BE LaraCurzio, E TI COMPARISON OF ELEVATED TEMPERATURE TENSILE PROPERTIES AND FATIGUE BEHAVIOR OF TWO VARIANTS OF A WOVEN SiC/SiC COMPOSITE SO MECHANICAL PROPERTIES AND PERFORMANCE OF ENGINEERING CERAMICS AND COMPOSITES SE Ceramic Engineering and Science Proceedings LA English DT Proceedings Paper CT 29th International Conference on Advanced Ceramics and Composites CY JAN 23-28, 2005 CL Cocoa Beach, FL SP Amer Ceram Soc AB Tensile properties (elastic modulus, proportional limit strength, in-plane tensile strength, and strain at failure) of two variants of a woven SiC/SiC composite, manufactured during two separate time periods (9/99 and 1/01), were determined at 1038 and 1204 degrees C by conducting tensile tests on specimens machined from plates. Continuous cycling fatigue tests (R = 0.05 and 20 cpm) were also conducted at the same two temperatures on specimens from both composites. In this study, average tensile properties, 95% confidence intervals associated with the tensile properties, and geometric mean fatigue lives of both composite materials are compared. The observed similarities and differences in the tensile properties are highlighted and an attempt is made to understand the relationship, if any, between the tensile properties and the fatigue behaviors of the two woven composites. C1 [Kalluri, Sreeramesh] NASA, Glenn Res Ctr, Ohio Aerosp Inst, Brookpark, OH 44135 USA. RP Kalluri, S (reprint author), NASA, Glenn Res Ctr, Ohio Aerosp Inst, 21000 Brookpk Rd,M-S 49-7, Brookpark, OH 44135 USA. NR 5 TC 3 Z9 3 U1 0 U2 0 PU AMER CERAMIC SOC PI WESTERVILLE PA 735 CERAMIC PLACE, WESTERVILLE, OH 43081-8720 USA SN 0196-6219 BN 978-1-57498-232-9 J9 CERAM ENG SCI PROC PY 2005 VL 26 IS 2 BP 303 EP 310 PG 8 WC Materials Science, Ceramics; Materials Science, Characterization & Testing; Materials Science, Composites SC Materials Science GA BMU95 UT WOS:000273627200036 ER PT S AU McClanahan, T Straub, SG Sharp, GWG Loew, M AF McClanahan, T Straub, SG Sharp, GWG Loew, M BE Amini, AA Manduca, A TI Automated insulin granule segmentation from electron photomicrographs of rat pancreatic beta-cells SO Medical Imaging 2005: Physiology, Function, and Structure From Medical Images, Pts 1 and 2 SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Medical Imaging 2005 Conference CY FEB 15-17, 2005 CL San Diego, CA SP SPIE DE insulin; pancreas; beta-cell; granule; segmentation; cell; morphometry; stereology; automation; migration ID MORPHOLOGICAL FILTERS; GLUCOSE; SECRETION AB Increased blood glucose stimulates pancreatic beta-cells and induces an exocytotic release of insulin. The beta-cell, which contains similar to 10(boolean AND 4) insulin-containing granules, releases only a few percent of the granules during a given stimulus such as a meal. The temporal response function to a square wave increase in the concentration of glucose is characteristically biphasic. It is not known whether the granules exhibit random or directed migration patterns as a function of phase. Directed migration would suggest the development of an intracellular gradient directing the path and velocity of insulin granule movement. Our ongoing research investigates this process using manual morphometric analysis of electron micrographs of rat pancreatic beta-cells. This is a tedious and time-consuming stereological process. Consequently, we have developed an automated algorithm for accurately segmenting and deriving granule counts, areas, and measuring distance to the plasma membrane. The method is a data-driven image processing approach that implements Mahalanobis classifiers to hierarchically classify pixel candidates and subsequently pixel aggregates as insulin granules. Granule cores and halos are classified independently and fused by intersecting the convex difference of granule halos with core candidates. Once fused, total and individual granule areas and distance metrics to the beta-cell plasma membrane are obtained. This algorithm provides a rapid and accurate method for the determination of granule numbers, location, and potential gradients in the pancreatic beta-cell under different experimental conditions. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP McClanahan, T (reprint author), NASA, Goddard Space Flight Ctr, Bldg 2 Rm 166, Greenbelt, MD 20771 USA. RI McClanahan, Timothy/C-8164-2012 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 0-8194-5720-5 J9 P SOC PHOTO-OPT INS PY 2005 VL 5746 BP 706 EP 717 DI 10.1117/12.595637 PN 1-2 PG 12 WC Radiology, Nuclear Medicine & Medical Imaging SC Radiology, Nuclear Medicine & Medical Imaging GA BCH30 UT WOS:000229312100075 ER PT S AU Mayes, TJ Foley, TT Hamilton, JA Duncavage, TC AF Mayes, Terrence J. Foley, Theodore T. Hamilton, Joseph A. Duncavage, Tom C. BE Westwood, JD Haluck, RS Hoffman, HM Mogel, GT Phillips, R Robb, RA Vosburgh, KG TI Real-time Visualization of Cross-sectional Data in Three Dimensions SO MEDICINE MEETS VIRTUAL REALITY 13: THE MAGICAL NEXT BECOMES THE MEDICAL NOW SE Studies in Health Technology and Informatics LA English DT Proceedings Paper CT 13th Conference on Medicine Meets Virtual Reality CY JAN 26-29, 2005 CL Long Beach, CA AB This paper describes a technique for viewing and interacting with 2-D medical data in three dimensions. The approach requires little pre-processing, runs on personal computers, and has a wide range of application. Implementation details are discussed, examples are presented, and results are summarized. C1 [Mayes, Terrence J.; Foley, Theodore T.; Hamilton, Joseph A.; Duncavage, Tom C.] NASA, Concept Explorat Lab, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. RP Mayes, TJ (reprint author), NASA, Concept Explorat Lab, Lyndon B Johnson Space Ctr, 2101 NASA Rd 1,Mail Code SF12, Houston, TX 77058 USA. NR 5 TC 0 Z9 0 U1 0 U2 0 PU I O S PRESS PI AMSTERDAM PA NIEUWE HEMWEG 6B, 1013 BG AMSTERDAM, NETHERLANDS SN 0926-9630 BN 978-1-58603-498-6 J9 ST HEAL T PY 2005 VL 111 BP 321 EP 324 PG 4 WC Biotechnology & Applied Microbiology; Computer Science, Interdisciplinary Applications; Engineering, Biomedical; Medicine, Research & Experimental SC Biotechnology & Applied Microbiology; Computer Science; Engineering; Research & Experimental Medicine GA BMX46 UT WOS:000273828700065 PM 15718752 ER PT S AU Bae, SY Yoon, KW George, T AF Bae, SY Yoon, KW George, T GP IEEE TI Fabrication and preliminary test results of BICEP[1,2,3] (Background imaging of cosmic extragalactic polarization) bolometer SO MEMS 2005 MIAMI: TECHNICAL DIGEST SE Proceedings IEEE Micro Electro Mechanical Systems LA English DT Proceedings Paper CT 18th IEEE International Conference on Micro Electro Mechanical Systems (MEMS) CY JAN 30-FEB 03, 2005 CL Miami Beach, FL SP IEEE, Robot & Automat Soc ID INFRARED BOLOMETERS; ASTROPHYSICS AB We report the results of fabrication and testing for the world's most sensitive MEMS bolometer. Our bolometer is designed to map temperature gradients within the Cosmic Microwave Background (CMB). The bolometer is capable of differentiating temperature differences in the CMB that are less than 10 parts per million. The key to this ultrahigh sensitivity is the "spider web" architecture fabricated from a suspended, metallized silicon nitride film. We report the results of fabrication and characterization of a novel spider web bolometer, the so-called BICEP (Background Imaging of Cosmic Extragalactic Polarization), capable of detecting the polarization as well as the intensity of the incident microwave radiation. The bolometer was characterized over a range of sub-Kelvin ambient temperatures. We report the results of the voltage response, time constant, and the "leakage" in the bolometer's responsivity to incident microwave polarizations. Finally, from our experimental results we have determined that the bolometer has a low Noise Equivalent Power of 2(.)10(-17)W/Hz(-1/2) C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. 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 1084-6999 BN 0-7803-8732-5 J9 PROC IEEE MICR ELECT PY 2005 BP 60 EP 63 PG 4 WC Engineering, Electrical & Electronic; Engineering, Mechanical SC Engineering GA BBZ90 UT WOS:000228430000015 ER PT S AU Toda, R Yang, EH AF Toda, R Yang, EH BE Henning, AK TI Fabrication and characterization of vertical travel linear microactuator SO MEMS/MOEMS Components and Their Applications II SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on MEMS/MOEMS Components and Their Applications II CY JAN 24-25, 2005 CL San Jose, CA SP SPIE, Semiconduct Equipment and Mat Int, Soild State Technol, Sandia Natl Lab DE actuator; piezoelectric; electrostatic; bistable beam AB This paper describes design, fabrication and characterization of a proof-of-concept vertical travel linear microactuator designed to provide out-of-plane actuation for high precision positioning applications in space. The microactuator is designed to achieve vertical actuation travel by incorporating compliant beam structures within a SOI (Silicon on Insulator) wafer. Device structure except for the piezoelectric actuator is fabricated on the SOI wafer using Deep Reactive Ion Etch (DRIE) process. Incremental travel distance of the piezoelectric actuator is adjustable at nanometer level by controlling voltage. Bistable beam geometry is employed to minimize initial gaps between electrodes. The footprint of an actuator is approximately 2 mm x 4 mm. Actuation is characterized with LabVIEW-based test bed. Actuation voltage sequence is generated by the LabVIEW controlled power relays. Vertical actuation in the range of 500 nm over 10-cycle was observed using WYKO RST Plus Optical Profiler. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Toda, R (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. OI Yang, Eui-Hyeok/0000-0003-4893-1691 NR 8 TC 0 Z9 0 U1 0 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 0-8194-5691-8 J9 P SOC PHOTO-OPT INS PY 2005 VL 5717 BP 14 EP 20 DI 10.1117/12.591128 PG 7 WC Instruments & Instrumentation; Optics SC Instruments & Instrumentation; Optics GA BCE48 UT WOS:000228860900005 ER PT S AU Hishinuma, Y Yang, EH Levine, BM Bloemhof, E AF Hishinuma, Y Yang, EH Levine, BM Bloemhof, E BE Henning, AK TI Piezoelectric unimorph MEMS deformable nfirror for ultra-large telescopes SO MEMS/MOEMS Components and Their Applications II SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on MEMS/MOEMS Components and Their Applications II CY JAN 24-25, 2005 CL San Jose, CA SP SPIE, Semiconduct Equipment and Mat Int, Soild State Technol, Sandia Natl Lab ID FABRICATION AB This paper describes the results of our demonstration on a proof-of-concept piezoelectric unimorph-based deformable mirror (DM) with continuous single-crystal silicon membrane. A PZT unimorph actuator of 2.5 mm in diameter with optimized PZT/Si thickness and design showed a deflection of 5 mu m at 50 V. DMs consisting of 10 pm thick single-crystal silicon membranes supported by 4x4 actuator arrays were fabricated and optically characterized. An assembled DM showed a stroke of 2.5 mu m at 50 V with a resonant frequency of 42 kHz and influence function of approximately 25%. C1 Jet Prop Lab, Pasadena, CA 91109 USA. RP Hishinuma, Y (reprint author), Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. OI Yang, Eui-Hyeok/0000-0003-4893-1691 NR 17 TC 0 Z9 0 U1 0 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 0-8194-5691-8 J9 P SOC PHOTO-OPT INS PY 2005 VL 5717 BP 21 EP 29 DI 10.1117/12.591275 PG 9 WC Instruments & Instrumentation; Optics SC Instruments & Instrumentation; Optics GA BCE48 UT WOS:000228860900006 ER PT S AU Bar-Cohen, Y AF Bar-Cohen, Y BE Henning, AK TI Biologically inspired technologies using artificial muscles SO MEMS/MOEMS Components and Their Applications II SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on MEMS/MOEMS Components and Their Applications II CY JAN 24-25, 2005 CL San Jose, CA SP SPIE, Semiconduct Equipment and Mat Int, Soild State Technol, Sandia Natl Lab DE biomimetics; biologically inspired technologies; EAP; electroactive polymers; artificial muscles AB After billions of years of evolution, nature developed inventions that work, which are appropriate for the intended tasks and that last. The evolution of nature led to the introduction of highly effective and power efficient biological mechanisms that are scalable from micron to many meters in size. Imitating these mechanisms offers enormous potentials for the improvement of our life and the tools we use. Humans have always made efforts to imitate nature and we are increasingly reaching levels of advancement where it becomes significantly easier to imitate, copy, and adapt biological methods, processes and systems. Some of the biomimetic technologies that have emerged include artificial muscles, artificial intelligence, and artificial vision to which significant advances in materials science, mechanics, electronics, and computer science have contributed greatly. One of the newest fields of biomimetics is the electroactive polymers (EAP) that are also known as artificial muscles. To take advantage of these materials, efforts are made worldwide to establish a strong infrastructure addressing the need for comprehensive analytical modeling of their operation mechanism and develop effective processing and characterization techniques. The field is still in its emerging state and robust materials are not readily available however in recent years significant progress has been made and commercial products have already started to appear. This paper covers the state-of-the-art and challenges to making artificial muscles and their potential biomimetic applications. C1 CALTECH, Jet Prop Lab, Pasadena, CA 90740 USA. RP Bar-Cohen, Y (reprint author), CALTECH, Jet Prop Lab, MS 125-224 4800 Oak Grove Dr, Pasadena, CA 90740 USA. NR 8 TC 0 Z9 0 U1 3 U2 6 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-5691-8 J9 P SOC PHOTO-OPT INS PY 2005 VL 5717 BP XXXV EP XLI DI 10.1117/12.609696 PG 7 WC Instruments & Instrumentation; Optics SC Instruments & Instrumentation; Optics GA BCE48 UT WOS:000228860900003 ER PT J AU Minitti, ME Lane, MD Bishop, JL AF Minitti, ME Lane, MD Bishop, JL TI A new hematite formation mechanism for Mars SO METEORITICS & PLANETARY SCIENCE LA English DT Article ID THERMAL EMISSION SPECTROMETER; HAWAIIAN PALAGONITIC SOIL; IRON-OXIDES; ALUMINOSILICATE GLASS; MAGNETIC-PROPERTIES; CHEMICAL DIFFUSION; MERIDIANI-PLANUM; MARTIAN SURFACE; OXIDATION; WATER AB The origin of hematite detected in Martian surface materials is commonly attributed to weathering processes or aqueous precipitation. Here, we present a new hematite formation mechanism that requires neither water nor weathering. Glass-rich basalts with Martian meteorite-like chemistry (high FeO, low Al2O3) oxidized at high (700 and 900 degrees C) temperatures in air and CO2, respectively, form thin (< 1 mu m) hematite coatings on their outermost surfaces. Hematite is manifested macroscopically by development of magnetism and a gray, metallic sheen on the glass surface and microscopically by Fe enrichment at the glass surface observed in element maps. Visible and near-infrared, thermal infrared, and Raman spectroscopy confirm that the Fe enrichment at the oxidized glass surfaces corresponds to hematite mineralization. Hematite formation on basaltic glass is enabled by a mechanism that induces migration of Fe2+ to the surface of an oxidizing glass and subsequent oxidation to form hematite. A natural example of the hematite formation mechanism is provided by a Hawaiian basalt hosting a gray, metallic sheen that corresponds to a thin hematite coating. Hematite coating development on the Hawaiian basalt demonstrates that Martian meteorite-like FeO contents are not required for hematite coating formation on basalt glass and that such coatings form during initial extrusion of the glassy basalt flows. If gray hematite originating as coatings on glassy basalt flows is an important source of Martian hematite, which is feasible given the predominance of igneous features on Mars, then the requirement of water as an agent of hematite formation is eliminated. C1 Arizona State Univ, Ctr Meteorite Studies, Tempe, AZ 85287 USA. Planetary Sci Inst, Tucson, AZ 85719 USA. NASA, ARC, SETI Inst, Mountain View, CA 94043 USA. RP Minitti, ME (reprint author), Arizona State Univ, Ctr Meteorite Studies, Box 871404, Tempe, AZ 85287 USA. EM minitti@asu.edu NR 49 TC 11 Z9 11 U1 2 U2 7 PU METEORITICAL SOC PI FAYETTEVILLE PA DEPT CHEMISTRY/BIOCHEMISTRY, UNIV ARKANSAS, FAYETTEVILLE, AR 72701 USA SN 1086-9379 J9 METEORIT PLANET SCI JI Meteorit. Planet. Sci. PD JAN PY 2005 VL 40 IS 1 BP 55 EP 69 PG 15 WC Geochemistry & Geophysics SC Geochemistry & Geophysics GA 913XW UT WOS:000228189900004 ER PT J AU Garber, DP Minnis, P Costulis, PK AF Garber, DP Minnis, P Costulis, PK TI A commercial flight track database for upper tropospheric aircraft emission studies over the USA and southern Canada SO METEOROLOGISCHE ZEITSCHRIFT LA English DT Article; Proceedings Paper CT European Conference on Aviation, Atmosphere and Climate CY JUN 30-JUL 03, 2003 CL Friedrichshafen, GERMANY AB A new air traffic database over the contiguous United States of America (USA) and southern Canada has been developed from a commercially available real-time product for 2001-2003 for all non-military IFR flights above 25,000 ft. Both individual flight tracks and gridded spatially integrated flight legs are available. On average, approximately 27,350 high-altitude flights were recorded each day. The diurnal cycle of air traffic over the USA is characterized by a broad daytime maximum with a 0130-LT minimum and a mean day-night air traffic ratio of 2.4. Each week, the air traffic typically peaks on Thursday and Friday and drops to a low during Sunday with a range of 18 %. Flight density is greatest during late summer and least during winter. The database records the disruption of air traffic after the air traffic shutdown during September 2001. The dataset should be valuable for realistically simulating the atmospheric effects of aircraft in the upper troposphere. C1 NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Minnis, P (reprint author), NASA, Langley Res Ctr, MS 420, Hampton, VA 23681 USA. EM p.minnis@nasa.gov RI Minnis, Patrick/G-1902-2010; Garber, Donald/D-7427-2015 OI Minnis, Patrick/0000-0002-4733-6148; NR 8 TC 11 Z9 11 U1 0 U2 0 PU GEBRUDER BORNTRAEGER PI STUTTGART PA JOHANNESSTR 3A, D-70176 STUTTGART, GERMANY SN 0941-2948 J9 METEOROL Z JI Meteorol. Z. PY 2005 VL 14 IS 4 BP 445 EP 452 DI 10.1127/0941-2948/2005/0061 PG 8 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA 982HI UT WOS:000233148300002 ER PT J AU Minnis, P Palikonda, R Walter, BJ Ayers, JK Mannstein, H AF Minnis, P Palikonda, R Walter, BJ Ayers, JK Mannstein, H TI Contrail properties over the eastern North Pacific from AVHRR data SO METEOROLOGISCHE ZEITSCHRIFT LA English DT Article; Proceedings Paper CT European Conference on Aviation, Atmosphere and Climate CY JUN 30-JUL 03, 2003 CL Friedrichshafen, GERMANY ID GLOBAL DISTRIBUTION; CLIMATE AB An increase of air traffic over the North Pacific during the last 30 years has been accompanied by an increase in cirrus coverage. To help alleviate the uncertainty in the contribution of air traffic to the cirrus increase, an analysis of linear contrail coverage over the region has been initiated using afternoon NOAA-16 AVHRR data taken during 4 months in 2002 and 2003. Manual evaluation of the automated contrail detection method revealed that it misclassified, on average, 32 % of the pixels as contrails and missed 15 % of the contrail pixels. After correction for detection errors, the contrail coverage over the domain between 25 degrees and 55 degrees N and between 120 degrees and 150 degrees W varied from a minimum of 0.37% in February to a maximum of 0.56% in May, respectively. The annual mean coverage, after correcting for the diurnal cycle of air traffic, is 0.31%, a value very close to earlier theoretical estimates for the region. Contrail optical depths for the 4 months average 0.24 resulting in a mean unit contrail longwave radiative forcing of 14.2 Wm(-2). The contrail optical depths are twice the mean value expected from theoretical estimates. C1 NASA, Langley Res Ctr, Sci Directorate, Hampton, VA 23681 USA. AS & M Inc, Hampton, VA USA. DLR, Inst Atmospher Phys, Wessling, Germany. RP Minnis, P (reprint author), NASA, Langley Res Ctr, Sci Directorate, MS 420, Hampton, VA 23681 USA. EM p.minnis@nasa.gov RI Minnis, Patrick/G-1902-2010 OI Minnis, Patrick/0000-0002-4733-6148 NR 15 TC 28 Z9 28 U1 0 U2 1 PU GEBRUDER BORNTRAEGER PI STUTTGART PA JOHANNESSTR 3A, D-70176 STUTTGART, GERMANY SN 0941-2948 J9 METEOROL Z JI Meteorol. Z. PY 2005 VL 14 IS 4 BP 515 EP 523 DI 10.1127/0941-2948/2005/0056 PG 9 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA 982HI UT WOS:000233148300009 ER PT J AU Palikonda, R Minnis, P Duda, DP Mannstein, H AF Palikonda, R Minnis, P Duda, DP Mannstein, H TI Contrail coverage derived from 2001 AVHRR data over the continental United States of America and surrounding areas SO METEOROLOGISCHE ZEITSCHRIFT LA English DT Article; Proceedings Paper CT European Conference on Aviation, Atmosphere and Climate CY JUN 30-JUL 03, 2003 CL Friedrichshafen, GERMANY ID GLOBAL DISTRIBUTION; CLOUD PROPERTIES; CIRRUS; SUCCESS; CLIMATE; FIELDS AB Linear contrail coverage, optical depth, and longwave radiative forcing are derived from NOAA-15 and NOAA-16 Advanced Very High Resolution Radiometer data taken during daytime over the continental United States of America (USA), southern Canada, northern Mexico, and the adjacent oceans. Analyses were performed for all available overpasses during 2001, but for NOAA-15 were primarily limited to the eastern half and the northwestern corner of the domain. Contrail coverage averaged 1.17% and 0.65% from the early morning NOAA-15 and midafternoon NOAA-16, respectively, for the areas and month common to both satellites. The NOAA-16 contrail coverage and radiative properties for the limited NOAA-15 domain are, on average, nearly identical to those for the entire domain. The estimated combined maximum coverage for the entire domain was similar to 1.05% during February, while the minimum of 0.57% occurred during August. Mean optical depths varied by similar to 20% with winter minima and summer maxima. The annual mean optical depth of 0.27 translated to a normalized contrail longwave radiative forcing of 15.5 Wm(-2). The overall daytime longwave radiative forcing for the domain is 0.11 Wm(-2). The normalized radiative forcing peaked during summer while the overall forcing was at a maximum during winter because of the greater contrail coverage. A detailed error analysis showed that the linear contrail coverage was overestimated by similar to 40% for both satellites the true coverage is closer to 0.70 and 0.40% for NOAA-15 and 16, respectively. Errors in the mean NOAA-15 optical depths and radiative forcing were negligible while their NOAA-16 counterparts were overestimated by approximately 13%. Contrail coverage was dramatically lower than expected from previous studies, but is most likely due to the significant decrease in upper tropospheric humidity observed in numerical weather analysis data. Contrail optical depths are much greater than both theoretical estimates for this part of North America and empirical retrievals over Europe. The cause of the morning-afternoon difference in contrail coverage is not yet known. Further modelling studies and additional satellite analyses are needed to understand this diurnal cycle and to explain the differences between the present and previous results. C1 Analyt Sci & Mat Inc, Hampton, VA USA. NASA, Langley Res Ctr, Sci Directorate, Hampton, VA 23665 USA. Hampton Univ, Hampton, VA 23668 USA. DLR, Inst Atmospher Phys, Wessling, Germany. RP Palikonda, R (reprint author), Analyt Sci & Mat Inc, Hampton, VA USA. RI Minnis, Patrick/G-1902-2010 OI Minnis, Patrick/0000-0002-4733-6148 NR 19 TC 33 Z9 33 U1 0 U2 1 PU E SCHWEIZERBARTSCHE VERLAGSBUCHHANDLUNG PI STUTTGART PA NAEGELE U OBERMILLER, SCIENCE PUBLISHERS, JOHANNESSTRASSE 3A, D 70176 STUTTGART, GERMANY SN 0941-2948 EI 1610-1227 J9 METEOROL Z JI Meteorol. Z. PY 2005 VL 14 IS 4 BP 525 EP 536 DI 10.1127/0941-2948/2005/0051 PG 12 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA 982HI UT WOS:000233148300010 ER PT J AU Duda, DP Minnis, P Palikonda, R AF Duda, DP Minnis, P Palikonda, R TI Estimated contrail frequency and coverage over the contiguous United States from numerical weather prediction analyses and flight track data SO METEOROLOGISCHE ZEITSCHRIFT LA English DT Article; Proceedings Paper CT European Conference on Aviation, Atmosphere and Climate CY JUN 30-JUL 03, 2003 CL Friedrichshafen, GERMANY ID GLOBAL DISTRIBUTION; CLIMATE; CIRRUS; TEMPERATURES AB Estimates of contrail frequency and coverage over the contiguous United States (CONUS) are developed using hourly meteorological analyses from the Rapid Update Cycle (RUC) numerical weather prediction model and commercial air traffic data for 2 months during 2001. The potential contrail frequency over the CON-US is computed directly from RUC analyses using several modified forms of the classical Appleman criteria for persistent contrail formation. Various schemes for diagnosing contrails from the RUC analyses were tested by first tuning each model to mean satellite estimates of contrail coverage for the domain and then comparing the resulting distributions to those from the satellite retrievals. The most accurate method for forming persistent contrails for both months uses a fourth root relationship between flight lengths and contrail coverage, accounts for contrail overlap and for the dry bias in the humidity profiles, and assumes that contrails can be detected in all cloudiness conditions. The differences between the simulated and satellite-derived contrail amounts are due to errors in the satellite observations, possible diurnally dependent saturation effects, and uncertainties in the numerical weather analysis humidity fields and other input variables. The algorithms developed here are suitable for eventual application to real-time predictions of potential contrail outbreaks. When refined, the methodology could be useful for both contrail mitigation and for contrail-climate effects assessment. C1 NASA, Langley Res Ctr, Sci Directorate, Hampton, VA 23681 USA. Analyt Serv & Mat Inc, Hampton, VA 23666 USA. RP Duda, DP (reprint author), NASA, Langley Res Ctr, Sci Directorate, Mail Stop 420, Hampton, VA 23681 USA. EM d.p.duda@larc.nasa.gov RI Minnis, Patrick/G-1902-2010 OI Minnis, Patrick/0000-0002-4733-6148 NR 28 TC 10 Z9 10 U1 0 U2 0 PU GEBRUDER BORNTRAEGER PI STUTTGART PA JOHANNESSTR 3A, D-70176 STUTTGART, GERMANY SN 0941-2948 J9 METEOROL Z JI Meteorol. Z. PY 2005 VL 14 IS 4 BP 537 EP 548 DI 10.1127/0941-2948/2005/0050 PG 12 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA 982HI UT WOS:000233148300011 ER PT S AU Namkung, M Williams, PA Mayweather, CD Wincheski, B Park, C Namkung, JS AF Namkung, M Williams, PA Mayweather, CD Wincheski, B Park, C Namkung, JS BE Ozkan, CS LaVan, DA McNie, M Prasad, S TI Chirality characterization of dispersed single wall carbon nanottibes SO Micro- and Nanosystems-Materials and Devices SE MATERIALS RESEARCH SOCIETY SYMPOSIUM PROCEEDINGS LA English DT Proceedings Paper CT Symposium on Micro- and Nanosystems held at the 2005 MRS Spring Meeting CY MAR 28-APR 01, 2005 CL San Francisco, CA SP Mat Res Soc ID NANOTUBES; RAMAN; FLUORESCENCE AB Raman scattering and optical absorption spectroscopy are used for the chirality characterization of HiPco single wall carbon nanotubes (SWNTs) dispersed in aqueous solution with the surfactant sodium dodecylbenzene sulfonate. Radial breathing mode (RBM) Raman peaks for semiconducting and metallic SWNTs are identified by directly comparing the Raman spectra with the Kataura plot. The SWNT diameters are calculated from these resonant peak positions. Next, a list of (n, m) pairs, yielding the SWNT diameters within a few percent of that obtained from each resonant peak position, is established. The interband transition energies for the list of SWNT (n, m) pairs are calculated based on the tight binding energy expression for each list of the (n, m) pairs, and the pairs yielding the closest values to the corresponding experimental optical absorption peaks are selected. The results reveal (1, 11), (4, 11), (5, 12), and (5, 9) among the most probable chiralities for the semiconducting nanotubes. The results also reveal that (4, 16), (6, 12) and (8, 8) are the most probable chiralities for the metallic nanotubes. Directly relating the Raman scattering data to the optical absorption spectra, the present method is considered the simplest technique currently available. Another advantage of this technique is the use of the E-11(S), E-33(S) and E-22(M) peaks in the optical absorption spectrum in the analysis to enhance the accuracy in the results. C1 NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Namkung, M (reprint author), NASA, Langley Res Ctr, Hampton, VA 23681 USA. RI Namkung, Min/E-1533-2012 NR 13 TC 0 Z9 0 U1 0 U2 0 PU MATERIALS RESEARCH SOCIETY PI WARRENDALE PA 506 KEYSTONE DRIVE, WARRENDALE, PA 15088-7563 USA SN 0272-9172 BN 1-55899-826-8 J9 MATER RES SOC SYMP P PY 2005 VL 872 BP 497 EP 502 PG 6 WC Instruments & Instrumentation; Materials Science, Multidisciplinary; Materials Science, Characterization & Testing SC Instruments & Instrumentation; Materials Science GA BDN45 UT WOS:000234461000075 ER PT S AU Li, MJ Acuna, N Amatucci, E Beamesderfer, M Boucarut, R Babu, S Bajikar, S Ewin, A Fettig, R Franz, D Hess, L Hu, R Jhabvala, M Kelly, D King, T Kletetschka, G Kotechi, C Kutyrev, A Loughlin, J Lynch, BA Moseley, H Mott, B Newell, B Oh, L Rapchun, D Ray, C Sappington, C Schulte, E Schwinger, S Smith, W Snodgrass, S Sparr, L Steptoe-Jackson, R Wang, LQ Zheng, Y Zincke, C AF Li, MJ Acuna, N Amatucci, E Beamesderfer, M Boucarut, R Babu, S Bajikar, S Ewin, A Fettig, R Franz, D Hess, L Hu, R Jhabvala, M Kelly, D King, T Kletetschka, G Kotechi, C Kutyrev, A Loughlin, J Lynch, BA Moseley, H Mott, B Newell, B Oh, L Rapchun, D Ray, C Sappington, C Schulte, E Schwinger, S Smith, W Snodgrass, S Sparr, L Steptoe-Jackson, R Wang, LQ Zheng, Y Zincke, C BE Chiao, JC Jamieson, DN Faraone, L Dzurak, AS TI Microshutter array development for the James Webb space telescope SO MICRO- AND NANOTECHNOLOGY: MATERIALS, PROCESSES, PACKAGING, AND SYSTEMS II SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Micro- and Nanotechnology - Materials , Processes, Packaging, and Systems II CY DEC 13-15, 2004 CL Sydney, AUSTRALIA SP SPIE, Univ New S Wales, Australian Govt Dept Def, Def Sci &Technol Org, Cochlear, Minist Sci & Med Res, Univ Adelaide, Ctr Biomed Engn DE microshutter; magnetic actuation; MEMS; RIE; DRIE; micro-optics; near-infrared; space telescope AB Micro Electromechanical System (MEMS) microshutter arrays are being developed at NASA Goddard Space Flight Center for Use as a field selector of the Near Infrared Spectrograph (NIRSpec) on the James Webb Space Telescope (JWST). The microshutter arrays are designed for the spontaneous selection of a large number of objects in the sky and the transmission of light to the NIRSpec detector with high contrast. The JWST environment requires cryogenic operation at 35K. Microshutter arrays are fabricated out of silicon-on-insulator (SOI) silicon wafers. Arrays are close-packed silicon nitride membranes with a pixel size of 100x200 mu m. Individual shutters are patterned with a torsion flexure permitting shutters to open 90 degrees with a minimized mechanical stress concentration. Light shields are processed for blocking light from gaps between shutters and frames. The mechanical shutter arrays are fabricated Using MEMS technologies. The processing includes multi-layer metal depositions, the patterning of magnetic stripes and shutter electrodes a reactive ion etching (RIE) to form shutters out of the nitride membrane, an anisotropic back-etch for wafer thinning, followed by a deep RIE (DRIE) back-etch to form mechanical supporting grids and release shutters from the silicon substrate. An additional metal deposition is used to form back electrodes. Shutters are actuated by a magnetic force and latched Using an electrostatic force. Optical tests, addressing tests, and life tests are conducted to evaluate the performance and the reliability of microshutter arrays. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Li, MJ (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. EM mary.j.li@nasa.gov RI Kletetschka, Gunther/C-9996-2011 OI Kletetschka, Gunther/0000-0002-0645-9037 NR 11 TC 20 Z9 20 U1 1 U2 10 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-5610-1 J9 PROC SPIE PY 2005 VL 5650 BP 9 EP 16 DI 10.1117/12.581861 PG 8 WC Materials Science, Multidisciplinary; Materials Science, Characterization & Testing; Optics SC Materials Science; Optics GA BCD14 UT WOS:000228693800005 ER PT B AU Lynch, BA Jamieson, BG Roman, PA Zakrzwski, CM AF Lynch, Bernard A. Jamieson, Brian G. Roman, Patrick A. Zakrzwski, Charles M. GP ASME TI An empirical study of boss/seat materials and geometries for ultra low-leakage MEMS micro-valves SO Micro-Electro-Mechanical Systems - 2005 SE Micro-Electro-Mechanical Systems Division of the American Society of Mechanical Engineers LA English DT Proceedings Paper CT ASME International Mechanical Engineering Congress and Exposition CY NOV 05-11, 2005 CL Orlando, FL SP ASME, Proc Ind Div, ASME, Rail Transportat Div, ASME, Noise Control & Acoust Div, ASME, Triol Div, ASME, Pressure Vessels & Piping Div, ASME, Bioengn Div, ASME, Mat Div, ASME, Appl Mech Div, ASME, Fluids Engn Div, ASME, Micro Elect Mech Syst Div, ASME, Heat Transfer Div, ASME, Nucl Engn Div, ASME, Power Div, ASME, Solar Energy Div, ASME, Safety Engn & Risk Anal Div, ASME, Technol & Soc Div, ASME, Adv Energy Syst Div, ASME, Aerosp Div, ASME, Comp & Informat Engn Div AB We report work on the testing and characterization of the seating properties of various micro-valve seat/boss interfaces. Using a custom test set-up, we have measured helium leak rates for a variety of boss materials and seat geometries. The seat geometries are micro-machined in silicon, and an orifice is DRIE etched through the chip. The test fixture allows for leak-tight edge sealing of seat chips against a viton o-ring, independent of the force used to seal the boss against the seat. Bosses are sealed against the various seat chips with forces up to 400 mN by using a precision micrometer to deflect a small spring that is coupled to the boss chip. Soft metals, such as copper and gold, and polymers such as polydimethylsiloxane (PDMS) and parylene-c, coated on silicon boss chips have been tested on hard silicon seats. In all cases, leak rates were determined as a function of sealing pressure. Seat geometries include a concentric o-ring configuration, and a silicon knife-edge. Both seats have orifice diameters varying from 60 to 110 pm. Experimental results indicate that practical MEMS-scale forces (up to several hundred mN) are sufficient to cause deformation of the soft materials coating the bosses given the small loading area, which can improve sealing capacity but not repeatability. However, uneven loading of the boss prevented a tight seal across the entire seat, which is reflected in the leak rates detected. Soft boss-materials, like PDMS, however, have shown promising results for obtaining ultra-low leak rates. Leak rates as low as 1X10(4) atm-cc/sec were obtained on knifeedge seats with 110 mu m diameter orifices. C1 NASA, Goddard Space Flight Ctr, Detectro Syst Branch, Greenbelt, MD 20771 USA. RP Lynch, BA (reprint author), NASA, Goddard Space Flight Ctr, Detectro Syst Branch, Greenbelt, MD 20771 USA. NR 7 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 0-7918-4224-X J9 MICROELECT MECH SYST PY 2005 VL 7 BP 263 EP 267 PG 5 WC Engineering, Electrical & Electronic; Engineering, Mechanical; Instruments & Instrumentation SC Engineering; Instruments & Instrumentation GA BFM28 UT WOS:000243038100044 ER PT S AU Bar-Cohen, Y AF Bar-Cohen, Y BE Papautsky, I TI Biologically inspired technologies using artificial muscles SO MICROFLUIDICS, BIOMEMS, AND MEDICAL MICROSYSTEMS III SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Microfludics, BioMEMS, and Medical Microsystems III CY JAN 24-26, 2005 CL San Jose, CA SP SPIE, Semiconduct Equipment and Mat Int, Soild State Technol, Sandia Natl Lab DE biomimetics; biologically inspired technologies; EAP; electroactive polymers; artificial muscles AB After billions of years of evolution, nature developed inventions that work, which are appropriate for the intended tasks and that last. The evolution of nature led to the introduction of highly effective and power efficient biological mechanisms that are scalable from micron to many meters in size. Imitating these mechanisms offers enormous potentials for the improvement of our life and the tools we use. Humans have always made efforts to imitate nature and we are increasingly reaching levels of advancement where it becomes significantly easier to imitate, copy, and adapt biological methods, processes and systems. Some of the biomimetic technologies that have emerged include artificial muscles, artificial intelligence, and artificial vision to which significant advances in materials science, mechanics, electronics, and computer science have contributed greatly. One of the newest fields of biomimetics is the electroactive polymers (EAP) that are also known as artificial muscles. To take advantage of these materials, efforts are made worldwide to establish a strong infrastructure addressing the need for comprehensive analytical modeling of their operation mechanism and develop effective processing and characterization techniques. The field is still in its emerging state and robust materials are not readily available however in recent years significant progress has been made and commercial products have already started to appear. This paper covers the state-of-the-art and challenges to making artificial muscles and their potential biomimetic applications. C1 CALTECH, Jet Prop Lab, Pasadena, CA 90740 USA. RP CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,MS 125-224, Pasadena, CA 90740 USA. EM yosi@jpl.nasa.gov NR 11 TC 0 Z9 0 U1 0 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 0-8194-5692-6 J9 PROC SPIE PY 2005 VL 5718 BP XXXV EP XLI DI 10.1117/12.609696 PG 7 WC Engineering, Biomedical; Instruments & Instrumentation SC Engineering; Instruments & Instrumentation GA BCE50 UT WOS:000228863400003 ER PT S AU Bar-Cohen, Y AF Bar-Cohen, Y BE Maher, MA Stewart, HD TI Biologically inspired technologies using artificial muscles SO MICROMACHINING AND MICROFABRICATION PROCESS TECHNOLOGY X SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Micromachining and Microfabrication Process Technology X CY JAN 25-27, 2005 CL San Jose, CA SP SPIE DE biomimetics; biologically inspired technologies; EAP; electroactive polymers; artificial muscles AB After billions of years of evolution, nature developed inventions that work, which are appropriate for the intended tasks and that last. The evolution of nature led to the introduction of highly effective and power efficient biological mechanisms that are scalable from micron to many meters in size. Imitating these mechanisms offers enormous potentials for the improvement of our life and the tools we use. Humans have always made efforts to imitate nature and we are increasingly reaching levels of advancement where it becomes significantly easier to imitate, copy, and adapt biological methods, processes and systems. Some of the biomimetic technologies that have emerged include artificial muscles, artificial intelligence, and artificial vision to which significant advances in materials science, mechanics, electronics, and computer science have contributed greatly. One of the newest fields of biomimetics is the electroactive polymers (EAP) that are also known as artificial muscles. To take advantage of these materials, efforts are made worldwide to establish a strong infrastructure addressing the need for comprehensive analytical modeling of their operation mechanism and develop effective processing and characterization techniques. The field is still in its emerging state and robust materials are not readily available however in recent years significant progress has been made and commercial products have already started to appear. This paper covers the state-of-the-art and challenges to making artificial muscles and their potential biomimetic applications. C1 CALTECH, Jet Prop Lab, Pasadena, CA 90740 USA. RP CALTECH, Jet Prop Lab, MS 125-224,4800 Oak Grove Dr, Pasadena, CA 90740 USA. EM yosi@jpl.nasa.gov NR 13 TC 0 Z9 0 U1 0 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 0-8194-5689-6 J9 PROC SPIE PY 2005 VL 5715 BP 26 EP 32 DI 10.1117/12.609696 PG 7 WC Instruments & Instrumentation; Optics SC Instruments & Instrumentation; Optics GA BCE32 UT WOS:000228834900003 ER PT S AU Bar-Cohen, Y AF Bar-Cohen, Y BE Johnson, EG Nordin, GP Suleski, TJ TI Biologically inspired technologies using artificial muscles SO MICROMACHINING TECHNOLOGY FOR MICRO-OPTICS AND NANO-OPTICS III SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Micromachining Technology for Micro-Optics and Nano-Optics III CY JAN 25-27, 2005 CL San Jose, CA SP SPIE, Semicond Equipment and Mat Int, Solid State Technol, Sandia Natl Lab DE biomimetics; biologically inspired technologies; EAP; electroactive polymers; artificial muscles AB After billions of years of evolution, nature developed inventions that work, which are appropriate for the intended tasks and that last. The evolution of nature led to the introduction of highly effective and power efficient biological mechanisms that are scalable from micron to many meters in size. Imitating these mechanisms offers enormous potentials for the improvement of our life and the tools we use. Humans have always made efforts to imitate nature and we are increasingly reaching levels of advancement where it becomes significantly easier to imitate, copy, and adapt biological methods, processes and systems. Some of the biomimetic technologies that have emerged include artificial muscles, artificial intelligence, and artificial vision to which significant advances in materials science, mechanics, electronics, and computer science have contributed greatly. One of the newest fields of biomimetics is the electroactive polymers (EAP) that are also known as artificial muscles. To take advantage of these materials, efforts are made worldwide to establish a strong infrastructure addressing the need for comprehensive analytical modeling of their operation mechanism and develop effective processing and characterization techniques. The field is still in its emerging state and robust materials are not readily available however in recent years significant progress has been made and commercial products have already started to appear. This paper covers the state-of-the-art and challenges to making artificial muscles and their potential biomimetic applications. C1 CALTECH, Jet Prop Lab, Pasadena, CA 90740 USA. RP CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,MS 125-224, Pasadena, CA 90740 USA. EM yosi@jpl.nasa.gov 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 0-8194-5694-2 J9 PROC SPIE PY 2005 VL 5720 BP XXXIV EP XL DI 10.1117/12.609696 PG 7 WC Optics SC Optics GA BCE51 UT WOS:000228863700003 ER PT S AU Wilson, DW Muller, RE Echternach, PM Backlund, JP AF Wilson, DW Muller, RE Echternach, PM Backlund, JP BE Johnson, EG Nordin, GP Suleski, TJ TI Electron-beam lithography for micro and nano-optical applications SO Micromachining Technology for Micro-Optics and Nano-Optics III SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Micromachining Technology for Micro-Optics and Nano-Optics III CY JAN 25-27, 2005 CL San Jose, CA SP SPIE, Semicond Equipment and Mat Int, Solid State Technol, Sandia Natl Lab DE electron-beam lithography; nanostructure fabrication; diffractive optics; micro optics ID FABRICATION AB Direct-write electron-beam lithography has proven to be a powerful technique for fabricating a variety of micro and nano-optical devices. Binary E-beam lithography is the workhorse technique for fabricating optical devices that require complicated precision nano-scale features. We describe a bi-layer resist system and virtual-mark height measurement for improving the reliability of fabricating binary patterns. Analog E-beam lithography is a newer technique that has found significant application in the fabrication of diffractive optical elements. We describe our techniques for fabricating analog surface-relief profiles in E-beam resist, including a technique for overcoming the problem of resist heating. We also describe a multiple field size exposure scheme for suppression of diffraction orders produced field-stitch errors in blazed diffraction gratings on non-flat substrates. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Wilson, DW (reprint author), 4800 Oak Grove Dr,MS 302-231, Pasadena, CA 91109 USA. NR 17 TC 14 Z9 14 U1 1 U2 8 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-5694-2 J9 P SOC PHOTO-OPT INS PY 2005 VL 5720 BP 68 EP 77 DI 10.1117/12.600784 PG 10 WC Optics SC Optics GA BCE51 UT WOS:000228863700011 ER PT S AU Divsalar, D Jones, C AF Divsalar, Dariush Jones, Christopher GP IEEE TI Protograph based low error floor LDPC coded modulation SO MILCOM 2005 - 2005 IEEE MILITARY COMMUNICATIONS CONFERENCE, VOLS 1-5 SE IEEE Military Communications Conference LA English DT Proceedings Paper CT IEEE Military Communications Conference (MILCOM 2005) CY OCT, 2005 CL Atlantic City, NJ SP IEEE ID PARITY-CHECK CODES; DISTANCE DISTRIBUTIONS; SHANNON LIMIT; DESIGN; ENSEMBLES; CAPACITY; GRAPHS AB In this paper we propose an innovative LDPC coded modulation scheme. We design binary Low Density Parity Check (LDPC) codes that are combined with high level modulations such as 8PSK and 16QAM with and without a channel interleaves At the receiver a demapper transforms the received inphase and quadrature samples to produce reliability information that feeds the binary LDPC decoder. Using this scheme, the same encoder and decoder can support various modulations. Analysis of ensemble average weight enumerators shows that the minimum distance of the proposed LDPC codes grows linearly with block size. Our constructions are based on protograph structures that support high-speed decoder implementations. We also show that precoding can be used to lower the threshold of LDPC codes. The decoding thresholds of the proposed codes, which have linearly increasing minimum distance in block size, outperform that of regular LDPC codes. Furthermore, a family of low to high rate codes, with thresholds that adhere closely to their respective channel capacity thresholds, is presented. For maximum variable node degree 6, the iterative decoding thresholds of these codes outperform the best known unstructured irregular LDPC codes reported in the literature. Iterative decoding simulation results are provided for BPSK QPSK 8PSK, and 16QAM modulations over the additive white Gaussian noise channel. FPGA simulation results for the proposed LDPC codes with input block size of 4096 and QPSK modulation (throughput=1 bps/Hz) show that a frame error rate of 10(-8) and a bit error rate of 10(-10) can be achieved at E-b/N-o=1.50 dB. C1 CALTECH, Jet Prop Lab, 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; christop@jpl.nasa.gov NR 28 TC 1 Z9 1 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2155-7578 BN 0-7803-9393-7 J9 IEEE MILIT COMMUN C PY 2005 BP 378 EP 385 PG 8 WC Telecommunications SC Telecommunications GA BFL76 UT WOS:000242920500059 ER PT S AU Simon, M Divsalar, D AF Simon, Marvin Divsalar, Dariush GP IEEE TI Data format classification for autonomous software defined radios SO MILCOM 2005 - 2005 IEEE MILITARY COMMUNICATIONS CONFERENCE, VOLS 1-5 SE IEEE Military Communications Conference LA English DT Proceedings Paper CT IEEE Military Communications Conference (MILCOM 2005) CY OCT, 2005 CL Atlantic City, NJ SP IEEE AB We present maximum-likelihood (ML) coherent and noncoherent classifiers for discriminating between NRZ and Manchester coded (biphase-L) data formats for binary phase-shift-keying (BPSK) modulation. Such classification of the data format is an essential element of so-called autonomous software defined radio (SDR) receivers (similar to so-called cognitive SDR receivers in the military application) where it is desired that the receiver perform each of its functions by extracting the appropriate knowledge from the received signal and, if possible, with as little information of the other signal parameters as possible. Small and large SNR approximations to the ML classifiers are also proposed that lead to simpler implementation with comparable performance in their respective SNR regions. Numerical performance results obtained by a combination of computer simulation and, wherever possible, theoretical analyses, are presented and comparisons are made among the various configurations based on the probability of misclassification as a performance criterion. Extensions to other modulations such as QPSK are readily accomplished using the same methods described in the paper. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Simon, M (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Marvin.K.Simon@jpl.nasa.gov; Dariush.Divsalar@jpl.nasa.gov NR 2 TC 1 Z9 1 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2155-7578 BN 0-7803-9393-7 J9 IEEE MILIT COMMUN C PY 2005 BP 386 EP 392 PG 7 WC Telecommunications SC Telecommunications GA BFL76 UT WOS:000242920500060 ER PT S AU Jones, KH Lodding, KN Olariu, S Wilson, L Xin, CS AF Jones, Kennie H. Lodding, Kenneth N. Olariu, Stephan Wilson, Larry Xin, Chunsheng GP IEEE TI Sensor networks for situation management: A biomimetic model SO MILCOM 2005 - 2005 IEEE MILITARY COMMUNICATIONS CONFERENCE, VOLS 1-5 SE IEEE Military Communications Conference LA English DT Proceedings Paper CT IEEE Military Communications Conference (MILCOM 2005) CY OCT, 2005 CL Atlantic City, NJ SP IEEE AB Promises of ubiquitous control of the physical environment by massively-deployed wireless sensor networks open avenues for new applications in support of situation management. Recent sensor network research has concentrated on developing techniques for performing relatively simple tasks with minimal energy expense, assuming some form of centralized control. Unfortunately, centralized control is not conducive to situation management as it allows single points of failure and does not scale to massive size networks. We propose a new way of looking, at massively-deployed sensor networks motivated by lessons learned from the way biological ecosystems are organized. We demonstrate that in our model fully distributed data aggregation and integration can be performed in a scalable fashion where individual motes operate based on local information, making local decisions that are aggregated across the network to achieve globally-meaningful effects. This exemplifies the robust, fault-tolerant infrastructure required for successful situation management systems. C1 NASA, Hampton, VA USA. RP Jones, KH (reprint author), NASA, Hampton, VA 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 SN 2155-7578 BN 0-7803-9393-7 J9 IEEE MILIT COMMUN C PY 2005 BP 1787 EP 1793 PG 7 WC Telecommunications SC Telecommunications GA BFL76 UT WOS:000242920502070 ER PT S AU Shambayati, S Jones, CR Divsalar, D AF Shambayati, Shervin Jones, Christopher R. Divsalar, Dariush GP IEEE TI Maximizing throughput for satellite communication in a hybrid FEC/ARQ scheme using LDPC codes SO MILCOM 2005 - 2005 IEEE MILITARY COMMUNICATIONS CONFERENCE, VOLS 1-5 SE IEEE Military Communications Conference LA English DT Proceedings Paper CT IEEE Military Communications Conference (MILCOM 2005) CY OCT, 2005 CL Atlantic City, NJ SP IEEE ID PARITY-CHECK CODES; SHANNON LIMIT; PERFORMANCE; CAPACITY; DESIGN; GRAPHS AB A hybrid forward error correction (FEC)/Automatic Repeat Request (ARQ) has been considered as a mechanism for providing reliable communication between NASA orbiters and landers at the planet Mars. On such a link it is proposed to use a family of capacity achieving LDPC channel codes for FEC and Go-back-N protocols for ARQ. In this paper, we analyze such a system and derive equations for its performance. We then use these equations to optimize the performance of the link in terms of information throughput subject to limitations on maximum channel baud rate and spacecraft power and select the best channel code and packet size accordingly at different link path lengths. In this optimization, first the frame error rate of the channel code is expressed in terms of a simple exponential function of the transmitted bit signal-to-noise ratio (Eb/No), obtained through curve-fitting. Then the standard throughput equation for the Go-back-N protocol in terms of the channel codes frame error rate is derived. Next, using the equations for the throughput and the frame error rate, the received Eb/No is calculated as a function of transmitted E(b)/N(0). By minimizing this function, the throughput of the system is maximized for a given available spacecraft power In the course of this optimization, we quantify the advantage afforded by a system that supports a set of possible code rates and bandwidths as opposed to a system that uses a single rate at different link path lengths. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Shambayati, S (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Shervin.Shambayati@jpl.nasa.gov; Christopher.R.Jones@jpl.nasa.gov; Dariush.Divsalar@jpl.nasa.gov NR 21 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2155-7578 BN 0-7803-9393-7 J9 IEEE MILIT COMMUN C PY 2005 BP 3289 EP 3298 PG 10 WC Telecommunications SC Telecommunications GA BFL76 UT WOS:000242920504093 ER PT S AU Simon, M AF Simon, Marvin GP IEEE TI Noncoherent symbol synchronization techniques SO MILCOM 2005 - 2005 IEEE MILITARY COMMUNICATIONS CONFERENCE, VOLS 1-5 SE IEEE Military Communications Conference LA English DT Proceedings Paper CT IEEE Military Communications Conference (MILCOM 2005) CY OCT, 2005 CL Atlantic City, NJ SP IEEE AB Traditional methods for establishing symbol synchronization (sync) in digital communication receivers assume that carrier sync has already been established, i.e., the problem is addressed at the baseband level assuming that a 'perfect " estimate of carrier phase is available. We refer to this approach as coherent symbol sync. Since, for NRZ signaling, a suppressed carrier sync loop such as an I-Q Costas loop includes integrate-and-dump (I&D) filters in its in-phase (I) and quadrature (Q) arms, the traditional approach is to first track the carrier in the absence of symbol sync information, then feed back the symbol sync estimate to these filters, and then iterate between the two to a desirable operating level. In this paper, we revisit the symbol sync problem by examining methods for obtaining such sync in the absence of carrier phase information, i.e., so-called noncoherent symbol sync loops. We compare the performance of these loops with that of a well-known coherent symbol sync loop and examine the conditions under which one is preferable over the other. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Simon, M (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 2155-7578 BN 0-7803-9393-7 J9 IEEE MILIT COMMUN C PY 2005 BP 3321 EP 3327 PG 7 WC Telecommunications SC Telecommunications GA BFL76 UT WOS:000242920504098 ER PT B AU Lee, C AF Lee, C BE Arabnia, HR Kozerenko, EB Shaumyan, S TI Faults discovery using mined data SO MLMTA '05: Proceedings of the International Conference on Machine Learning Models Technologies and Applications LA English DT Proceedings Paper CT International Conference on Machine Learning, Models, Technologies and Applications CY JUN 27-30, 2005 CL Las Vegas, NV AB Fault discovery in the complex systems consist of model based reasoning, fault tree analysis, rule based inference methods, and other approaches. Model based reasoning builds models for the systems either by mathematic formulations or by results of experiments. Fault Tree Analysis shows the possible causes of a system malfunction by enumerating the suspect components and their respective failure modes that may have induced the problem. The rule based inference build the model based on the expert knowledge. Those models and methods have one thing in common; they have presumed some prior-conditions. Complex systems often use fault trees to analyze the faults. Fault diagnosis, when an error occurs, is performed by engineers and analysts performing extensive examination of all data gathered during the mission. International Space Station (ISS) control center operates on the data feedback from the system and decisions are made based on threshold values by using fault trees. Since those decision-making tasks are safety critical and must be done promptly, the engineers who manually analyze the data are facing the challenge of time limit. To automate this process, this paper presents an approach that uses decision trees to discover faults from data in real-time and capture the contents of fault trees as the initial state of the trees. C1 NASA, Ames Res Ctr, SAIC, Moffett Field, CA 94035 USA. RP Lee, C (reprint author), NASA, Ames Res Ctr, SAIC, Moffett Field, CA 94035 USA. NR 9 TC 0 Z9 0 U1 0 U2 0 PU C S R E A PRESS PI ATHENS PA 115 AVALON DR, ATHENS, GA 30606 USA BN 1-932415-73-4 PY 2005 BP 127 EP 133 PG 7 WC Computer Science, Artificial Intelligence SC Computer Science GA BDZ95 UT WOS:000236381500018 ER PT S AU Visser, W Mehlitz, P AF Visser, W Mehlitz, P BE Godefroid, P TI Model checking programs with Java PathFinder SO MODEL CHECKING SOFTWARE, PROCEEDINGS SE LECTURE NOTES IN COMPUTER SCIENCE LA English DT Article; Proceedings Paper CT 12th International SPIN Workshop on Model Checking Software CY AUG 22-24, 2005 CL San Francisco, CA C1 NASA, Ames Res Ctr, RIACS, Moffett Field, CA 94035 USA. NASA, Ames Res Ctr, CSC, Moffett Field, CA 94035 USA. RP Visser, W (reprint author), NASA, Ames Res Ctr, RIACS, Moffett Field, CA 94035 USA. EM wvisser@email.arc.nasa.gov; pcmehlitz@email.arc.nasa.gov NR 0 TC 4 Z9 4 U1 0 U2 0 PU SPRINGER-VERLAG BERLIN PI BERLIN PA HEIDELBERGER PLATZ 3, D-14197 BERLIN, GERMANY SN 0302-9743 BN 3-540-28195-9 J9 LECT NOTES COMPUT SC PY 2005 VL 3639 BP 27 EP 27 PG 1 WC Computer Science, Software Engineering; Computer Science, Theory & Methods SC Computer Science GA BDA42 UT WOS:000232261100004 ER PT S AU Bosnacki, D Holzmann, GJ AF Bosnacki, D Holzmann, GJ BE Godefroid, P TI Improving spin's partial-order reduction for breadth-first search SO MODEL CHECKING SOFTWARE, PROCEEDINGS SE Lecture Notes in Computer Science LA English DT Article; Proceedings Paper CT 12th International SPIN Workshop on Model Checking Software CY AUG 22-24, 2005 CL San Francisco, CA ID MODEL-CHECKING AB We describe an improvement of the partial-order reduction algorithm for breadth-first search which was introduced in Spin version 4.0. Our improvement is based on the algorithm by Alur et al. for symbolic state model checking for local safety properties [1]. The crux of the improvement is an optimization in the context of explicit state model checking of the condition that prevents action ignoring, also known as the cycle proviso. There is an interesting duality between the cycle provisos for the breadth-first search (BFS) and depth first search (DFS) exploration of the state space, which is reflected in the role of the BFS queue and the DFS stack, respectively. The improved version of the algorithm is supported in the current version of Spin and can be shown to perform significantly better than the initial version. C1 Eindhoven Univ Technol, NL-5612 MB Eindhoven, Netherlands. CALTECH, NASA, JPL, Lab Reliable Software, Pasadena, CA 91006 USA. RP Eindhoven Univ Technol, Den Dolech 2,POB 513, NL-5612 MB Eindhoven, Netherlands. NR 19 TC 6 Z9 6 U1 0 U2 1 PU SPRINGER-VERLAG BERLIN PI BERLIN PA HEIDELBERGER PLATZ 3, D-14197 BERLIN, GERMANY SN 0302-9743 BN 3-540-28195-9 J9 LECT NOTES COMPUT SC PY 2005 VL 3639 BP 91 EP 105 PG 15 WC Computer Science, Software Engineering; Computer Science, Theory & Methods SC Computer Science GA BDA42 UT WOS:000232261100009 ER PT S AU Giannakopoulou, D Pasareanu, CS AF Giannakopoulou, D Pasareanu, CS BE Godefroid, P TI Learning-based assume-guarantee verification (Tool paper) SO MODEL CHECKING SOFTWARE, PROCEEDINGS SE Lecture Notes in Computer Science LA English DT Article; Proceedings Paper CT 12th International SPIN Workshop on Model Checking Software CY AUG 22-24, 2005 CL San Francisco, CA C1 RIACS, Moffett Field, CA 94035 USA. NASA Ames, QSS, Moffett Field, CA 94035 USA. RP RIACS, Moffett Field, CA 94035 USA. EM dimitra@email.arc.nasa.gov; pcorina@email.arc.nasa.gov NR 12 TC 7 Z9 7 U1 0 U2 0 PU SPRINGER-VERLAG BERLIN PI BERLIN PA HEIDELBERGER PLATZ 3, D-14197 BERLIN, GERMANY SN 0302-9743 BN 3-540-28195-9 J9 LECT NOTES COMPUT SC PY 2005 VL 3639 BP 282 EP 287 PG 6 WC Computer Science, Software Engineering; Computer Science, Theory & Methods SC Computer Science GA BDA42 UT WOS:000232261100023 ER PT S AU Bardina, JE Thirumalainambi, R Davis, RD AF Bardina, JE Thirumalainambi, R Davis, RD BE Motaghedi, P TI Business intelligence modeling in launch operations SO Modeling, Simulation, and Verification of Space-Based Systems II SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Modeling, Simulation and Verification of Space-based Systems II CY MAR 31, 2005 CL Orlando, FL SP SPIE DE business intelligence; cost modeling; risk and reliability model; planning and scheduling; space vehicle launch operations C1 NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Bardina, JE (reprint author), NASA, Ames Res Ctr, Mail Stop 269-2, Moffett Field, CA 94035 USA. NR 0 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 0-8194-5784-1 J9 P SOC PHOTO-OPT INS PY 2005 VL 5799 BP 28 EP 37 DI 10.1117/12.604875 PG 10 WC Engineering, Aerospace SC Engineering GA BCS52 UT WOS:000231050600004 ER PT S AU Howard, RT Johnston, AS Bryan, TC Book, ML AF Howard, RT Johnston, AS Bryan, TC Book, ML BE Motaghedi, P TI Simulation and ground testing with the AVGS SO Modeling, Simulation, and Verification of Space-Based Systems II SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Modeling, Simulation and Verification of Space-based Systems II CY MAR 31, 2005 CL Orlando, FL SP SPIE DE Automated Rendezvous and Docking; Video Guidance Sensor; AR&C; AR&D; VGS; AVGS C1 NASA, George C Marshall Space Flight Ctr, EV21 Automated Rendezvouis & Docking Branch, Huntsville, AL 35812 USA. RP Howard, RT (reprint author), NASA, George C Marshall Space Flight Ctr, EV21 Automated Rendezvouis & Docking Branch, Huntsville, AL 35812 USA. NR 0 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 0-8194-5784-1 J9 P SOC PHOTO-OPT INS PY 2005 VL 5799 BP 56 EP 65 DI 10.1117/12.604132 PG 10 WC Engineering, Aerospace SC Engineering GA BCS52 UT WOS:000231050600007 ER PT S AU Thirumalainambi, R Bardina, JE Miyazawa, O AF Thirumalainambi, R Bardina, JE Miyazawa, O BE Motaghedi, P TI Non-intrusive techniques of inspections during the pre-launch phase of space vehicle SO Modeling, Simulation, and Verification of Space-Based Systems II SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Modeling, Simulation and Verification of Space-based Systems II CY MAR 31, 2005 CL Orlando, FL SP SPIE DE micro flying robot; ground operations; space vehicle inspection; health monitoring of space vehicle; non-intrusive techniques of inspection C1 NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Thirumalainambi, R (reprint author), NASA, Ames Res Ctr, Mail Stop 269-2, Moffett Field, CA 94035 USA. NR 0 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 0-8194-5784-1 J9 P SOC PHOTO-OPT INS PY 2005 VL 5799 BP 92 EP 99 DI 10.1117/12.605653 PG 8 WC Engineering, Aerospace SC Engineering GA BCS52 UT WOS:000231050600010 ER PT B AU Yee, HC Sjogreen, B AF Yee, HC Sjogreen, B BE Bock, HG Kostina, E Phu, HX Rannacher, R TI Divergence free high order filter methods for the compressible MHD equations SO MODELLING, SIMULATION AND OPTIMIZATION OF COMPLEX PROCESSES LA English DT Proceedings Paper CT International Conference on High Performance Scientific Computing CY MAR 10-14, 2003 CL Hanoi, VIETNAM SP German Res Fdn, Abdus Salam Int Ctr Theoret Phys, Hanoi Inst Math, Natl Council Nat Sci Vietnam, Mercedes-Benz Vietnam, Gottlieb Daimler & Karl Benz Stift, Vietnamese Acad Sci & Technol, Deutsch Akad Austauschdienst ID TANG VORTEX SYSTEM; CONSERVATION-LAWS; IDEAL MAGNETOHYDRODYNAMICS; EVOLUTION; FLOWS; SCHEME AB The generalization of a class of low-dissipative high order filter finite difference methods for long time wave propagation of shock/turbulence /combustion compressible viscous gas dynamic flows to compressible MHD equations for structured curvilinear grids has been achieved. The new scheme is shown to provide a natural and efficient way for the minimization of the divergence of the magnetic field numerical error. Standard divergence cleaning is not required by the present filter approach. For certain MHD test cases, divergence free preservation of the magnetic fields has been achieved. C1 NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Yee, HC (reprint author), NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. NR 33 TC 0 Z9 0 U1 0 U2 0 PU SPRINGER PI NEW YORK PA 233 SPRING STREET, NEW YORK, NY 10013, UNITED STATES BN 3-540-23027-0 PY 2005 BP 559 EP 575 DI 10.1007/3-540-27170-8_42 PG 17 WC Computer Science, Theory & Methods; Mathematics, Applied SC Computer Science; Mathematics GA BBR95 UT WOS:000227493900042 ER PT S AU Bar-Cohen, Y AF Bar-Cohen, Y BE Urey, H Dickensheets, DL TI Biologically inspired technologies using artificial muscles SO MOEMS DISPLAY AND IMAGING SYSTEMS III SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on MOEMS Display and Imaging Systems III CY JAN 24-25, 2005 CL San Jose, CA SP SPIE DE biomimetics; biologically inspired technologies; EAP; electroactive polymers; artificial muscles AB After billions of years of evolution, nature developed inventions that work, which are appropriate for the intended tasks and that last. The evolution of nature led to the introduction of highly effective and power efficient biological mechanisms that are scalable from micron to many meters in size. Imitating these mechanisms offers enormous potentials for the improvement of our life and the tools we use. Humans have always made efforts to imitate nature and we are increasingly reaching levels of advancement where it becomes significantly easier to imitate, copy, and adapt biological methods, processes and systems. Some of the biomimetic technologies that have emerged include artificial muscles, artificial intelligence, and artificial vision to which significant advances in materials science, mechanics, electronics, and computer science have contributed greatly. One of the newest fields of biomimetics is the electroactive polymers (EAP) that are also known as artificial muscles. To take advantage of these materials, efforts are made worldwide to establish a strong infrastructure addressing the need for comprehensive analytical modeling of their operation mechanism and develop effective processing and characterization techniques. The field is still in its emerging state and robust materials are not readily available however in recent years significant progress has been made and commercial products have already started to appear. This paper covers the state-of-the-art and challenges to making artificial muscles and their potential biomimetic applications. C1 CALTECH, Jet Prop Lab, Pasadena, CA 90740 USA. RP Bar-Cohen, Y (reprint author), CALTECH, Jet Prop Lab, MS 125-224 4800 Oak Grove Dr, Pasadena, CA 90740 USA. EM yosi@jpl.nasa.gov NR 10 TC 0 Z9 0 U1 1 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 0-8194-5695-0 J9 PROC SPIE PY 2005 VL 5721 BP XXXV EP XLI DI 10.1117/12.609696 PG 7 WC Engineering, Electrical & Electronic; Optics; Imaging Science & Photographic Technology; Radiology, Nuclear Medicine & Medical Imaging SC Engineering; Optics; Imaging Science & Photographic Technology; Radiology, Nuclear Medicine & Medical Imaging GA BCD76 UT WOS:000228764100003 ER PT S AU Wolpert, DH Bieniawski, S AF Wolpert, DH Bieniawski, S BE DuninKeplicz, B Jankowski, A Skowron, A Szczuka, M TI Distributed adaptive control: Beyond single-instant, discrete control variables SO Monitoring, Security, and Rescue Techniques in Multiagent Systems SE ADVANCES IN SOFT COMPUTING LA English DT Proceedings Paper CT International Workshop on Monitoring, Security, and Rescue Techniques in Multiagent Systems CY JUN 07-09, 2004 CL Plock, POLAND AB In extensive form noncooperative game theory, at each instant t, each agent i sets its state xi independently of the other agents, by sampling an associated distribution, q(i) (Xi). The coupling between the agents arises in the joint evolution of those distributions. Distributed control problems can be cast the same way. In those problems the system designer sets aspects of the joint evolution of the distributions to try to optimize the goal for the overall system. Now information theory tells us what the separate qi of the agents are most likely to be if the system were to have a particular expected value of the objective function G(x(1), x(2),...). so one can view the job of the system designer as speeding an iterative process. Each step of that process starts with a specified value of E(G), and the convergence of the qi to the most likely set of distributions consistent with that value. After this the target value for E, (G) is lowered, and then the process repeats. Previous work has elaborated many schemes for implementing this process when the underlying variables xi all have a finite number of possible values and G does not extend to multiple instants in time. That work also is based on a fixed mapping from agents to control devices, so that the the statistical independence of the agents' moves means independence of the device states. This paper also extends that work to relax all of these restrictions. This extends the applicability of that work to include continuous spaces and Reinforcement Learning. This paper also elaborates how some of that earlier work can be viewed as a first-principles justification of evolution-based search algorithms. C1 NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Wolpert, DH (reprint author), NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. NR 32 TC 0 Z9 0 U1 0 U2 2 PU SPRINGER-VERLAG BERLIN PI BERLIN PA HEIDELBERGER PLATZ 3, D-14197 BERLIN, GERMANY SN 1615-3871 BN 3-540-23245-1 J9 ADV SOFT COMP PY 2005 BP 31 EP 52 DI 10.1007/3-540-32370-8_3 PG 22 WC Computer Science, Artificial Intelligence; Computer Science, Theory & Methods SC Computer Science GA BCA70 UT WOS:000228476800003 ER PT J AU Soria, R Cropper, M Pakull, M Mushotzky, R Wu, K AF Soria, R Cropper, M Pakull, M Mushotzky, R Wu, K TI The star-forming environment of an ultraluminous X-ray source in NGC 4559: an optical study SO MONTHLY NOTICES OF THE ROYAL ASTRONOMICAL SOCIETY LA English DT Review DE accretion, accretion discs; black hole physics; galaxies : individual : NGC 4559; X-rays : galaxies; X-rays : stars ID ANTENNAE GALAXIES NGC-4038/4039; HUBBLE-SPACE-TELESCOPE; INITIAL MASS FUNCTION; HIGH-VELOCITY CLOUDS; BLACK-HOLE BINARIES; EQUATION-OF-STATE; H-ALPHA EMISSION; CHANDRA OBSERVATIONS; PHOTOMETRIC SYSTEMS; IRREGULAR GALAXIES AB We have studied the candidate optical counterparts and the stellar population in the star-forming complex around the bright ultraluminous X-ray source (ULX) in the western part of the spiral galaxy NGC 4559, using the HST Wide Field Planetary Camera 2 (WFPC2), XMM-Newton/Optical Monitor and ground-based data. We find that the ULX is located near a small group of OB stars, but is not associated with any massive young clusters nor with any extraordinary massive stars. The brightest point source in the Chandra error circle is consistent with a single blue supergiant (BSG) of mass approximate to20 M(circle dot) and age approximate to10 Myr. A few other stars are resolved inside the error circle: mostly BSGs and red supergiants (RSGs) with inferred masses approximate to10-15 M(circle dot) and ages approximate to20 Myr. This is consistent with the interpretation of this ULX as a black hole (BH) accreting from a high-mass donor star in its supergiant phase, with mass transfer occurring via Roche-lobe overflow. The observed optical colours and the blue-to-red supergiant ratio suggest a low metal abundance for the stellar population: 0.2 less than or similar toZ/Z(circle dot)less than or similar to 0.4 (using the Padua tracks), or 0.05 less than or similar toZ/Z(circle dot)less than or similar to 0.2 (using the Geneva tracks). The age of the star-forming complex is less than or similar to30 Myr. Halpha images show that this star-forming region has a ring-like appearance. We propose that it is an expanding wave of star formation, triggered by an initial density perturbation, in a region where the gas was only marginally stable to gravitational collapse. We also suggest that the most likely trigger was a collision with a satellite dwarf galaxy going through the gas-rich outer disc of NGC 4559 less than 30 Myr ago. The culprit could be the dwarf galaxy visible a few arcsec north-west of the complex. If this is the case, this system is a scaled-down version of the Cartwheel galaxy. The X-ray data favour a BH more massive (M > 50 M(circle dot)) than typical Milky Way BH candidates. The optical data favour a young BH originating in the recent episode of massive star formation; however, they also rule out an association with young massive star clusters (none are present in the X7 field). We speculate that other mechanisms may lead to the formation of relatively massive BHs (perhaps Msimilar to 50-100 M(circle dot)) from stellar evolution processes in low-metallicity environments, or when star formation is triggered by galactic collisions. C1 UCL, Mullard Space Sci Lab, Dorking RH5 6NT, Surrey, England. Harvard Smithsonian Ctr Astrophys, Cambridge, MA 02138 USA. Observ Strasbourg, F-67000 Strasbourg, France. NASA, Goddard Space Flight Ctr, High Energy Astrophys Lab, Greenbelt, MD 20771 USA. RP Soria, R (reprint author), UCL, Mullard Space Sci Lab, Holmbury St Mary, Dorking RH5 6NT, Surrey, England. EM Roberto.Soria@mssl.ucl.ac.uk RI Cropper, Mark/C-1574-2008 NR 130 TC 63 Z9 63 U1 0 U2 2 PU WILEY-BLACKWELL PI MALDEN PA COMMERCE PLACE, 350 MAIN ST, MALDEN 02148, MA USA SN 0035-8711 J9 MON NOT R ASTRON SOC JI Mon. Not. Roy. Astron. Soc. PD JAN 1 PY 2005 VL 356 IS 1 BP 12 EP 28 DI 10.1111/j.1365-2966.2004.08438.x PG 17 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 879WG UT WOS:000225749300002 ER PT B AU Stroupe, A Huntsberger, T Okon, A Aghazarian, H AF Stroupe, A Huntsberger, T Okon, A Aghazarian, H BE Parker, LE Schneider, FE Schultz, AC TI Precision manipulation with cooperative robots SO Multi-Robot Systems - From Swarms to Intelligent Automata Vol III LA English DT Proceedings Paper CT 3rd International Workshop on Multi-Robot Systems CY MAR, 2005 CL Naval Res Lab, Washington, DC HO Naval Res Lab DE cooperative robots; cooperative transport; robot construction ID MULTIROBOT SYSTEMS AB We present a cooperative approach to robotic precision manipulation tasks in the context of autonomous robotic construction. Precision manipulation requires a firm grasp, which constraints the team to rigidly maintain formation during transport and manipulation. A leader/follower approach with force sensing to provide relative formation information and vision to provide team position relative to construction components is applied. Our approach demonstrates successful, reliable performance of a construction task requiring cooperative transport and placement of structure components. Qualitative and quantitative performance results are provided. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Stroupe, A (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 14 TC 0 Z9 0 U1 0 U2 1 PU SPRINGER PI DORDRECHT PA PO BOX 17, 3300 AA DORDRECHT, NETHERLANDS BN 1-4020-3388-5 PY 2005 BP 235 EP 248 DI 10.1007/1-4020-3389-3_19 PG 14 WC Robotics SC Robotics GA BCO50 UT WOS:000230416300019 ER PT B AU Kessel, M Shao, X AF Kessel, M Shao, X BE Lui, ATY Kamide, Y Consolini, G TI How does the solar wind power the magnetosphere during geo-effective high speed streams? SO Multiscale Coupling of Sun-Earth Processes LA English DT Proceedings Paper CT Conference on Sun-Earth Connection - Multiscale Coupling in Sun-Earth Processes CY FEB 09-13, 2004 CL Kailua Kona, HI SP Johns Hopkins Univ Appl Phys Lab, Nagoya Univ, Solar Terrestrial Environm Lab, Comm Space Res, Int Assoc Geomagnetism & Aeron, NASA, Natl Sci Fdn, Sci Comm Solar Terrestrial Phys ID KELVIN-HELMHOLTZ INSTABILITY; UPSTREAM PRESSURE VARIATIONS; MAGNETOTAIL BOUNDARY; GEOTAIL OBSERVATIONS; GEOMAGNETIC STORMS; WAVE POWER; MAGNETOSHEATH; PHASE AB We show two types of solar energy flux that with high probability, couple to the Earth's magnetosphere and cause enhanced magnetospheric fluctuations. 70-80 R-E upstream from Earth, Wind observations show significant, sustained power at Pc5 frequencies intrinsic to a high speed stream starting March 29, 2002. The enhanced power is evident in dynamic pressure fluctuations and to a lesser extent in compressional magnetic field fluctuations. This high speed stream is not associated with a large magnetic storm, but strong Pc5 pulsations are observed at geostationary orbit. Geotail observations near the magnetopause show enhanced compressional power at Pc5 frequencies, especially at the nose and on the dawn flank, both in the magnetosheath and the adjacent boundary layer. The observations suggest that more energy may be transferred across the nose than at the flanks during high speed streams. The sustained dynamic pressure fluctuations may be responsible for the sustained geomagnetic pulsations Seen at GOES 8 in the noon and midnight sectors, although the midnight sector might have additional sources. GOES 8 observations of dawn pulsations follow the trend of the compressional magnetic field fluctuations, that is higher at first and then reduced. Compressional magnetic field fluctuations may control the level of Pc5 pulsations on the dawn side. Northward IMF along with Geotail observations of magnetopause motion and MHD simulations of vortices along the flanks suggest that a Kelvin-Helmholtz (K-H) instability may contribute to transport of the compressional energy into the magnetosphere. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Kessel, M (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. NR 38 TC 0 Z9 0 U1 0 U2 1 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA SARA BURGERHARTSTRAAT 25, PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS BN 0-444-51881-9 PY 2005 BP 39 EP 53 DI 10.1016/B978-044451881-1/50004-6 PG 15 WC Geochemistry & Geophysics SC Geochemistry & Geophysics GA BDL68 UT WOS:000234140700004 ER PT B AU Brekke, P Fleck, B Haugan, SV van Overbeek, T Schweitzer, H Simonin, B AF Brekke, P Fleck, B Haugan, SV van Overbeek, T Schweitzer, H Simonin, B BE Lui, ATY Kamide, Y Consolini, G TI Space weather effects on SOHO and its leading role as a space weather watchdog SO Multiscale Coupling of Sun-Earth Processes LA English DT Proceedings Paper CT Conference on Sun-Earth Connection - Multiscale Coupling in Sun-Earth Processes CY FEB 09-13, 2004 CL Kailua Kona, HI SP Johns Hopkins Univ Appl Phys Lab, Nagoya Univ, Solar Terrestrial Environm Lab, Comm Space Res, Int Assoc Geomagnetism & Aeron, NASA, Natl Sci Fdn, Sci Comm Solar Terrestrial Phys AB Since its launch on 2 December 1995, the Solar and Heliospheric Observatory (SOHO) has provided an unparalleled breadth and depth of information about the Sun, from its interior, through the hot and dynamic atmosphere, and out to the solar wind. In addition SOHO has several times demonstrated its leading role in the early-warning system for space weather. SOHO is in a halo orbit around L1 Lagrangian point where it views the Sun 24 hours a day. Thus, it is situated outside the Earth's protective magnetosphere, which shields other satellites from high-energy particles and the solar wind. We present a summary of the observed effects on the instruments and electronics on SOHO throughout the mission. In particular we focus on a number of large particle events during the recent years while the Sun was near maximum activity, and how they affected both the scientific data as well as hardware components. C1 GSFC, European Space Agcy, Greenbelt, MD 20771 USA. RP Brekke, P (reprint author), GSFC, European Space Agcy, Greenbelt, MD 20771 USA. RI Fleck, Bernhard/C-9520-2012 NR 9 TC 0 Z9 0 U1 0 U2 0 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA SARA BURGERHARTSTRAAT 25, PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS BN 0-444-51881-9 PY 2005 BP 83 EP 97 DI 10.1016/B978-044451881-1/50007-1 PG 15 WC Geochemistry & Geophysics SC Geochemistry & Geophysics GA BDL68 UT WOS:000234140700007 ER PT B AU Mannucci, AJ Tsurutani, BT Iijima, BA Gonzalez, WD Guarnieri, FL Yumoto, K AF Mannucci, AJ Tsurutani, BT Iijima, BA Gonzalez, WD Guarnieri, FL Yumoto, K BE Lui, ATY Kamide, Y Consolini, G TI Global dayside ionospheric response to interplanetary electric fields: Plasma uplift and increases in total electron content SO Multiscale Coupling of Sun-Earth Processes LA English DT Proceedings Paper CT Conference on Sun-Earth Connection - Multiscale Coupling in Sun-Earth Processes CY FEB 09-13, 2004 CL Kailua Kona, HI SP Johns Hopkins Univ Appl Phys Lab, Nagoya Univ, Solar Terrestrial Environm Lab, Comm Space Res, Int Assoc Geomagnetism & Aeron, NASA, Natl Sci Fdn, Sci Comm Solar Terrestrial Phys ID DISTURBANCE DYNAMO; MAGNETIC STORMS; MAGNETOSPHERIC DISTURBANCES; SUBSTORMS; SYSTEM; CONVECTION; DEPENDENCE; LATITUDES; ORIGIN; CLOUDS AB The interplanetary shock/electric field event of 5-6 November 2001 is analyzed using ACE interplanetary data. The consequential ionospheric effects are studied using GPS receiver data from the CHAMP satellite and data from similar to 100 ground-based GPS receivers. The dawn-to-dusk interplanetary electric field was initially similar to 33 mV/m just after a forward shock (IMF B-Z = -48 nT), reaching a peak value of similar to 54 mV/m one hour and 40 minutes later (B-Z = -78 nT). The electric field was similar to 45 mV/m (B-Z = -65 nT) two hours after the shock and a magnetic storm intensity of D-ST = -275 nT was reached. The dayside satellite GPS receiver data plus ground-based GPS data indicate that the entire equatorial and midlatitude (up to +/- 50 degrees MLAT) dayside ionosphere was uplifted, significantly increasing the column-integrated electron content at altitudes above the CHAMP orbital altitude of 430 kin. Based on the total electron content (TEC), this uplift appeared to peak similar to 2 1/2 hours after the shock passage. The effect of the uplift leading to TEC increase lasted for 4 to 5 hours. We suggest that the interplanetary electric field "promptly penetrated" to the ionosphere, and the dayside plasma was convected (by E x B drift) to higher altitudes. Upward plasma transport led to a similar to 55-60% increase in equatorial ionospheric TEC measured from altitudes of similar to 430 km (at 1930 LT). This inferred vertical transport plus photoionization of atmospheric neutrals at lower altitudes caused a 21% TEC increase in equatorial ionospheric TEC at similar to 14 LT (from ground based measurements). Data from an equatorial magnetometer confirms the electric field behavior inferred from the TEC changes on the dayside. Seven to nine hours after the beginning of the electric field event, the dayside ionospheric TEC above similar to 430 kin decreased to values approximately 45% lower than quiet day values. The ground-based equatorial ionospheric TEC decrease was similar to 16%. This decrease occurred both at midlatitudes and at the equator. We presume that thermospheric winds and neutral composition changes produced by the storm-time frictional heating and disturbance dynamo electric fields are responsible for these decreases. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Mannucci, AJ (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 37 TC 0 Z9 0 U1 0 U2 0 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA SARA BURGERHARTSTRAAT 25, PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS BN 0-444-51881-9 PY 2005 BP 157 EP 171 DI 10.1016/B978-044451881-1/50013-7 PG 15 WC Geochemistry & Geophysics SC Geochemistry & Geophysics GA BDL68 UT WOS:000234140700013 ER PT B AU Zhou, XY Mende, SB AF Zhou, XY Mende, SB BE Lui, ATY Kamide, Y Consolini, G TI Substorm auroral morphology during geomagnetic storms on 19-20 April 2002 SO MULTISCALE COUPLING OF SUN-EARTH PROCESSES LA English DT Proceedings Paper CT Conference on Sun-Earth Connection - Multiscale Coupling in Sun-Earth Processes CY FEB 09-13, 2004 CL Kailua Kona, HI SP Johns Hopkins Univ Appl Phys Lab, Nagoya Univ, Solar Terrestrial Environm Lab, Comm Space Res, Int Assoc Geomagnetism & Aeron, NASA, Natl Sci Fdn, Sci Comm Solar Terrestrial Phys DE auroral morphology; substorm expansion phase; geomagnetic storm ID SOLAR-WIND; MAGNETOSPHERIC SUBSTORMS; POLAR-CAP; ENERGY AB In this paper, we report on a study of the auroral activity during three substorm expansion phases that occurred prior to, during and after the magnetic storm main phase on April 20 during which the SYM-H index decreased from -75 to -185 nT. The first substorm actually occurred in the recovery phase of a previous storm on April 19. The IMAGE WIC (the Wideband Imaging Camera) data showed that auroral morphologies of the three events were almost identical. In the first 10 - 20 min after substorm expansion phase onsets, there were significant auroral brightenings and abrupt expansions. In each case, double auroral oval occurred during the later substorm expansion phases and early substorm recovery phases. South-north orientated auroral patches and torches filled in the space between the two ovals. It was found that even with very similar auroral patterns, the three substorm expansion phases may have been very different in terms of auroral electrojet intensity and energy transport from the solar wind into the magnetosphere/ionosphere system. The first substorm event may have been generated by the release of energy stored in the magnetotail, although the trigger was an external IMF northward turning. The second substorm was more likely driven by the intense solar wind dawn-dusk electric field. The third substorm might have been internally triggered by a steady-loading process. Our argument is that the similar auroral morphologies may have been manifestations of different substorm processes, i.e., loading-unloading and/or being directly driven. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 31 TC 0 Z9 0 U1 0 U2 0 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA SARA BURGERHARTSTRAAT 25, PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS BN 0-444-51881-9 PY 2005 BP 253 EP 263 DI 10.1016/B978-044451881-1/50018-6 PG 11 WC Geochemistry & Geophysics SC Geochemistry & Geophysics GA BDL68 UT WOS:000234140700018 ER PT B AU Goldstein, ML Roberts, DA Usmanov, AV AF Goldstein, ML Roberts, DA Usmanov, AV BE Lui, ATY Kamide, Y Consolini, G TI Numerical simulations of solar wind turbulence SO MULTISCALE COUPLING OF SUN-EARTH PROCESSES LA English DT Proceedings Paper CT Conference on Sun-Earth Connection - Multiscale Coupling in Sun-Earth Processes CY FEB 09-13, 2004 CL Kailua Kona, HI SP Johns Hopkins Univ Appl Phys Lab, Nagoya Univ, Solar Terrestrial Environm Lab, Comm Space Res, Int Assoc Geomagnetism & Aeron, NASA, Natl Sci Fdn, Sci Comm Solar Terrestrial Phys DE solar wind; magnetohydrodynamic turbulence; global heliospheric structure ID INTERPLANETARY MAGNETIC-FIELD; FLUX-CORRECTED TRANSPORT; WKB ALFVEN WAVES; MAGNETOHYDRODYNAMIC TURBULENCE; LOW-FREQUENCY; MHD MODEL; HYDROMAGNETIC-WAVES; VELOCITY SHEAR; FLUCTUATIONS; DRIVEN AB Alfvenic fluctuations are a ubiquitous component of the solar wind. Evidence from many spacecraft indicates that the fluctuations are convected out of the solar corona with relatively flat power spectra and constitute a source of free energy for a turbulent cascade of magnetic and kinetic energy to high wave numbers. Observations and simulations support the conclusion that the cascade evolves most rapidly in the vicinity of velocity shears and current sheets. Numerical solutions of the magnetohydrodynamic equations are clarifying not only how a turbulent cascade develops, but also the nature of the symmetries of the turbulence. Of particular interest is the origin of the Maltese cross two-dimensional correlation function of magnetic fluctuations that was deduced from ISEE 3 data. A central issue to be resolved is whether the correlation function indicates the existence of a quasi-two-dimensional component of the turbulence, or reflects another origin, such as pressure-balanced structures or small velocity shears. This paper reviews the current status of our simulations of turbulence in the solar wind. These simulations include a tilted rotating current sheet as well as variety of waves (e.g., Alfvenic, quasi-two-dimensional, pressure balance structures) and '' microstreams ''. Some aspects of our global models of heliospheric structure are also covered. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RI Goldstein, Melvyn/B-1724-2008; Usmanov, Arcadi/A-9860-2013 NR 72 TC 2 Z9 3 U1 0 U2 0 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA SARA BURGERHARTSTRAAT 25, PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS BN 0-444-51881-9 PY 2005 BP 301 EP 320 DI 10.1016/B978-044451881-1/50021-6 PG 20 WC Geochemistry & Geophysics SC Geochemistry & Geophysics GA BDL68 UT WOS:000234140700021 ER PT B AU Curtis, SA Clark, PE Cheung, CY AF Curtis, SA Clark, PE Cheung, CY BE Lui, ATY Kamide, Y Consolini, G TI The central role of reconnection in space plasma phenomena targeted by the magnetospheric multiscale mission SO Multiscale Coupling of Sun-Earth Processes LA English DT Proceedings Paper CT Conference on Sun-Earth Connection - Multiscale Coupling in Sun-Earth Processes CY FEB 09-13, 2004 CL Kailua Kona, HI SP Johns Hopkins Univ Appl Phys Lab, Nagoya Univ, Solar Terrestrial Environm Lab, Comm Space Res, Int Assoc Geomagnetism & Aeron, NASA, Natl Sci Fdn, Sci Comm Solar Terrestrial Phys DE magnetospheric multiscale; mission; multi-platform; formation; reconnection; space plasma processes; observations; temporal; spatial; 3D structure; dynamics; electron inertial length ID MAGNETIC RECONNECTION AB The Magnetospheric Multiscale Mission, which consists of four identically instrumented spacecraft flying in close formation, will allow the first extensive characterization of the 3D structure and dynamic variations of the magnetosphere on scales down to electron inertial length. By targeting the magnetopause and magnetotail, two regions already known to provide observations crucial to understanding the reconnection process, the mission will determine the spatial and temporal scales of basic plasma processes. C1 NASA, Goddard Space Flight Ctr, Magnetospher Phys Branch, Extraterr Phys Lab, Greenbelt, MD 20771 USA. RP Curtis, SA (reprint author), NASA, Goddard Space Flight Ctr, Magnetospher Phys Branch, Extraterr Phys Lab, Greenbelt, MD 20771 USA. RI NASA MMS, Science Team/J-5393-2013 OI NASA MMS, Science Team/0000-0002-9504-5214 NR 15 TC 0 Z9 0 U1 0 U2 2 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA SARA BURGERHARTSTRAAT 25, PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS BN 0-444-51881-9 PY 2005 BP 473 EP 486 DI 10.1016/B978-044451881-1/50035-6 PG 14 WC Geochemistry & Geophysics SC Geochemistry & Geophysics GA BDL68 UT WOS:000234140700035 ER PT S AU Martin, G Comenye, G Asrar, G Paules, G Grigsby, EC Maxwell, MS Criscione, J Coakley, MM Cauffman, SA Davis, MA AF Martin, G Comenye, G Asrar, G Paules, G Grigsby, EC Maxwell, MS Criscione, J Coakley, MM Cauffman, SA Davis, MA BE Larar, AM Suzuki, M Tong, Q TI Hyperspectral environmental suite (HES) formulation and implementation overview SO MULTISPECTRAL AND HYPERSPECTRAL REMOTE SENSING INSTRUMENTS AND APPLICATIONS II SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Multispectral and Hyperspectral Remote Sensing Instruments and Applications II CY NOV 09-11, 2004 CL Honolulu, HI SP SPIE, NASA, Natl Ocean & Atmospher Adm, Natl Polar-Orbiting Operat Environm Satellite Syst, Integrated Program Off, Japan Aerosp Explorat Agcy, Chinese Soc Oceanog, Chinese Meterol Adm DE GOES-R; infrared; hyperspectral; geostationary; sounding; instrument AB This paper outlines the requirements., methodologies, and implementation approach for development of the NOAA/NASA GOES-R Hyperspectral Environmental Suite (HES), which is scheduled to fly in the 2012 timeframe. The HES is currently being developed within the framework of the GOES Program to fulfill the future needs and requirements flowed down through the National Environmental Satellite, Data, and Information Service (NESDIS). As an integral component of the GOES-R series satellites, HES will provide measurements of the traditional temperature and water vapor vertical profiles with higher accuracy and finer vertical resolution than the current GOES sounder series as well as coastal water properties. HES will have approximately 1500 spectral channels for sounding in this suite, compared to the current GOES Sounder series with its 18 spectral channels, leading to improved vertical resolution and reducing temperature error. HES will also have approximately five times faster coverage rate. As a suite, HES is planned with new capabilities for coastal ocean coverage with the goal of including open ocean coverage. These new planned imaging applications, which will be either multispectral or hyperspectral, will also be discussed. An overview of the HES requirements will be presented along with how these requirements fit into goals and objectives at an Earth Science level, the GOES-R mission level, the spacecraft level, and the instrument suite level and will include an overview of the GOES-R project methodologies for achieving the advanced functional objectives of the GOES Program partnership(s). C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Martin, G (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. NR 3 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 0-8194-5616-0 J9 P SOC PHOTO-OPT INS PY 2005 VL 5655 BP 12 EP 23 DI 10.1117/12.579735 PG 12 WC Instruments & Instrumentation; Remote Sensing SC Instruments & Instrumentation; Remote Sensing GA BBT08 UT WOS:000227663600002 ER PT S AU Hearty, T Gaiser, S Pagano, T Aumann, H AF Hearty, T Gaiser, S Pagano, T Aumann, H BE Larar, AM Suzuki, M Tong, Q TI The precision and accuracy of AIRS level 1B radiances for climate studies SO MULTISPECTRAL AND HYPERSPECTRAL REMOTE SENSING INSTRUMENTS AND APPLICATIONS II SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Multispectral and Hyperspectral Remote Sensing Instruments and Applications II CY NOV 09-11, 2004 CL Honolulu, HI SP SPIE, NASA, Natl Ocean & Atmospher Adm, Natl Polar-Orbiting Operat Environm Satellite Syst, Integrated Program Off, Japan Aerosp Explorat Agcy, Chinese Soc Oceanog, Chinese Meterol Adm DE AIRS; climate; calibration AB We investigate uncertainties in the Atmospheric Infrared Sounder (AIRS) radiances; based on in-flight and preflight calibration algorithms and observations. The global coverage and spectral resolution (lambda/Delta lambda similar to 1200) of AIRS enable it to produce a data set that can be used as a climate data record over the lifetime of the instrument. Therefore, we examine the effects of the uncertainties in the calibration and the detector stability on future climate studies. The uncertainties of the parameters that go into the AIRS radiometric calibration are propagated to estimate the accuracy of the radiances and any climate data record created from AIRS measurements. The calculated radiance uncertainties are consistent with observations. Algorithm enhancements may be able to reduce the radiance uncertainties by as much as 7%. We find that the orbital variation of the gain contributes a brightness temperature bias of < 0.01 K. Although this can be removed by algorithm. enhancements, it is smaller than uncertainty of the gain for most channels. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Hearty, T (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 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 0-8194-5616-0 J9 P SOC PHOTO-OPT INS PY 2005 VL 5655 BP 54 EP 65 DI 10.1117/12.578991 PG 12 WC Instruments & Instrumentation; Remote Sensing SC Instruments & Instrumentation; Remote Sensing GA BBT08 UT WOS:000227663600006 ER PT S AU Liu, X Smith, WL Zhou, DK Larar, A AF Liu, X Smith, WL Zhou, DK Larar, A BE Larar, AM Suzuki, M Tong, Q TI A principal component-based radiative transfer forward model (PCRTM) for hyper spectral sensors SO MULTISPECTRAL AND HYPERSPECTRAL REMOTE SENSING INSTRUMENTS AND APPLICATIONS II SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Multispectral and Hyperspectral Remote Sensing Instruments and Applications II CY NOV 09-11, 2004 CL Honolulu, HI SP SPIE, NASA, Natl Ocean & Atmospher Adm, Natl Polar-Orbiting Operat Environm Satellite Syst, Integrated Program Off, Japan Aerosp Explorat Agcy, Chinese Soc Oceanog, Chinese Meterol Adm DE Radiative Transfer Model; Remote sensing; forward model; hyper spectra ID ACCURATE TRANSMITTANCE MODEL; INHOMOGENEOUS ATMOSPHERES; ABSORBING GAS; COMPUTATIONALLY FAST; MIXING RATIOS; SATELLITE; SPECTROMETER; IMPROVEMENTS; ABSORPTION; RETRIEVAL AB Modem Infrared satellite sensors(1-5) such as AIRS, CrIS, TES, GIFTS and IASI are all capable of providing high spatial and spectral resolution infrared spectra. To fully exploit the vast amount of spectral information from these instruments, super fast radiative transfer models are needed. This paper presents a novel radiative transfer model based on principal component analysis. The model is very accurate and flexible. Its execution speed is a factor of 3-30 times faster than channel-based fast models. Due to its high speed and compressed spectral, information format, it has great potential for super fast one-dimensional physical retrievals and for Numerical Weather Prediction (NWP) large volume radiance data assimilation applications. The model has been successfully developed for the NAST-I and AIRS instruments. The PCRTM model performs monochromatic radiative transfer calculations and is suitable to include multiple scattering calculations to account for clouds and aerosols. C1 NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Liu, X (reprint author), NASA, Langley Res Ctr, MS401A, Hampton, VA 23681 USA. NR 41 TC 10 Z9 10 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 0-8194-5616-0 J9 P SOC PHOTO-OPT INS PY 2005 VL 5655 BP 96 EP 105 DI 10.1117/12.578996 PG 10 WC Instruments & Instrumentation; Remote Sensing SC Instruments & Instrumentation; Remote Sensing GA BBT08 UT WOS:000227663600010 ER PT S AU Larar, AM Cook, WB Mills, CS Flood, MA Puschell, JJ Skinner, WR AF Larar, AM Cook, WB Mills, CS Flood, MA Puschell, JJ Skinner, WR BE Larar, AM Suzuki, M Tong, Q TI Tropospheric trace species sensing FPI: Program overview and measurement concept validation SO MULTISPECTRAL AND HYPERSPECTRAL REMOTE SENSING INSTRUMENTS AND APPLICATIONS II SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Multispectral and Hyperspectral Remote Sensing Instruments and Applications II CY NOV 09-11, 2004 CL Honolulu, HI SP SPIE, NASA, Natl Ocean & Atmospher Adm, Natl Polar-Orbiting Operat Environm Satellite Syst, Integrated Program Off, Japan Aerosp Explorat Agcy, Chinese Soc Oceanog, Chinese Meterol Adm DE Fabry-Perot interferometry; geostationary observations; tropospheric chemistry; tropospheric ozone ID FABRY-PEROT-INTERFEROMETER; OZONE AB Monitoring tropospheric chemistry from space is the next frontier for advancing present-day remote sensing capabilities to meet future high-priority atmospheric science measurement needs. The Tropospheric Trace Species Sensing Fabry-Perot Interferometer (TTSS-FPI) is a NASA Instrument Incubator Program (UP) project for risk mitigation of enabling concepts and technology applicable to future Office of Earth Science (OES) atmospheric chemistry measurements. While the intended implementation for future science missions is a geostationary-based measurement of tropospheric ozone and other trace species, a multispectral imaging airborne sensor system is being developed within UP to demonstrate the instrument concept and enabling technologies that are also applicable to space-based configurations. The concept is centered about an imaging Fabry-Perot interferometer (FPI) observing a narrow spectral interval within the strong 9.6 micron ozone infrared band with a spectral resolution similar to 0.07 cm(-1). This concept is also applicable to and could simplify designs associated with atmospheric chemistry sensors targeting other trace species (which typically require spectral resolutions in the range of 0.01 - 0.1 cm(-1)), since such an FPI approach could be implemented for those spectral bands requiring the highest spectral resolution and thus simplify overall design complexity. An overview of this UP project addressing the measurement and instrument concepts, enabling technologies, approach for development and demonstration, and a summary of progress-to-date will all be reported. This will include sensor radiometric, spectral, and spatial characterization activities relevant to measurement concept validation. Subsequent manuscripts following in these proceedings will focus on the airborne prototype system under development and a corresponding spaceflight concept study, respectively. C1 NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Larar, AM (reprint author), NASA, Langley Res Ctr, Hampton, VA 23681 USA. NR 10 TC 0 Z9 0 U1 0 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 0-8194-5616-0 J9 P SOC PHOTO-OPT INS PY 2005 VL 5655 BP 163 EP 171 DI 10.1117/12.579924 PG 9 WC Instruments & Instrumentation; Remote Sensing SC Instruments & Instrumentation; Remote Sensing GA BBT08 UT WOS:000227663600017 ER PT S AU Cook, WB Larar, AM Mills, CS Flood, MA Puschell, JJ Skinner, WR AF Cook, WB Larar, AM Mills, CS Flood, MA Puschell, JJ Skinner, WR BE Larar, AM Suzuki, M Tong, Q TI TTSS-FPI: airborne prototype development and performance verification SO MULTISPECTRAL AND HYPERSPECTRAL REMOTE SENSING INSTRUMENTS AND APPLICATIONS II SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Multispectral and Hyperspectral Remote Sensing Instruments and Applications II CY NOV 09-11, 2004 CL Honolulu, HI SP SPIE, NASA, Natl Ocean & Atmospher Adm, Natl Polar-Orbiting Operat Environm Satellite Syst, Integrated Program Off, Japan Aerosp Explorat Agcy, Chinese Soc Oceanog, Chinese Meterol Adm DE remote sensing; multiple etalon; infrared; ozone ID FABRY-PEROT-INTERFEROMETER; TROPOSPHERIC OZONE AB The Tropospheric Trace Species Sounder is a spatially imaging, spectrally tunable airborne sensor focused on demonstrating a new capability to make important measurements of tropospheric ozone. The sensor system is based upon a cryogenically cooled dual etalon infrared Fabry-Perot interferometer. The instrument package is designed to operate autonomously on a high altitude aircraft platform. We present herein details of the airborne instrument's hardware and component test results. C1 NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Cook, WB (reprint author), NASA, Langley Res Ctr, Hampton, VA 23681 USA. NR 9 TC 0 Z9 0 U1 0 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 0-8194-5616-0 J9 P SOC PHOTO-OPT INS PY 2005 VL 5655 BP 172 EP 180 DI 10.1117/12.580452 PG 9 WC Instruments & Instrumentation; Remote Sensing SC Instruments & Instrumentation; Remote Sensing GA BBT08 UT WOS:000227663600018 ER PT S AU Bruce, CF Bingham, A Carr, ME DiGiacomo, P Green, RO AF Bruce, CF Bingham, A Carr, ME DiGiacomo, P Green, RO BE Larar, AM Suzuki, M Tong, Q TI Mission concept and technology for spectroscopic observations of the coastal oceans from geosynchronous orbit. SO MULTISPECTRAL AND HYPERSPECTRAL REMOTE SENSING INSTRUMENTS AND APPLICATIONS II SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Multispectral and Hyperspectral Remote Sensing Instruments and Applications II CY NOV 09-11, 2004 CL Honolulu, HI SP SPIE, NASA, Natl Ocean & Atmospher Adm, Natl Polar-Orbiting Operat Environm Satellite Syst, Integrated Program Off, Japan Aerosp Explorat Agcy, Chinese Soc Oceanog, Chinese Meterol Adm DE ocean; spectroscopy; geostationary; ocean color ID CARBON AB Space-based, multispectral, ocean color measurements of the earth's oceans have significantly added to our understanding of the oceans over the past 25 years. All of these past and current space based sensors have operated in low earth orbit with moderate temporal resolution. We describe a mission concept for improved temporal and spectroscopic measurement of the ocean from geosynchronous orbit. This orbit requires that specific, available technologies be integrated into the instrument and spacecraft. For an instrument and spacecraft configured with these technologies this vantage point offers a unique opportunity when viewing dynamic, low reflectance components of the deep-ocean and coastal areas. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91001 USA. RP Bruce, CF (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91001 USA. RI DiGiacomo, Paul/F-5584-2010 OI DiGiacomo, Paul/0000-0003-4550-1899 NR 11 TC 0 Z9 0 U1 0 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 0-8194-5616-0 J9 P SOC PHOTO-OPT INS PY 2005 VL 5655 BP 364 EP 370 DI 10.1117/12..579289 PG 7 WC Instruments & Instrumentation; Remote Sensing SC Instruments & Instrumentation; Remote Sensing GA BBT08 UT WOS:000227663600038 ER PT B AU Heap, SR Lanz, T AF Heap, SR Lanz, T BE Renzini, A Bender, R TI Mid-ultraviolet spectral diagnostics of galaxy evolution SO MULTIWAVELENGTH MAPPING OF GALAXY FORMATION AND EVOLUTION SE ESO ASTROPHYSICS SYMPOSIA LA English DT Proceedings Paper CT ESO Workshop on Multiwavelength Mapping of Galaxy Formation and Evolution CY OCT 13-16, 2003 CL Venice, ITALY SP European So Observ, Max Planck Inst Extraterrestr Phys, Observ Ludwig Maximilians Univ ID STARS; POPULATIONS; AGES AB We describe how optical spectra of z = 1 - 2 galaxies can help test the hypothesis of hierarchical galaxy formation. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. NR 8 TC 1 Z9 1 U1 0 U2 0 PU SPRINGER-VERLAG BERLIN PI BERLIN PA HEIDELBERGER PLATZ 3, D-14197 BERLIN, GERMANY BN 3-540-25665-2 J9 ESO ASTROPHY SYMP PY 2005 BP 210 EP 215 DI 10.1007/10995020_32 PG 6 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BCW16 UT WOS:000231503500032 ER PT B AU de Mello, DF Gardner, JP Dahlen, T Conselice, CJ Grogin, NA Koekemoer, AM AF de Mello, DF Gardner, JP Dahlen, T Conselice, CJ Grogin, NA Koekemoer, AM BE Renzini, A Bender, R TI The nature of UV-selected galaxies in the CDFS SO Multiwavelength Mapping of Galaxy Formation and Evolution SE ESO ASTROPHYSICS SYMPOSIA LA English DT Proceedings Paper CT ESO Workshop on Multiwavelength Mapping of Galaxy Formation and Evolution CY OCT 13-16, 2003 CL Venice, ITALY SP European So Observ, Max Planck Inst Extraterrestr Phys, Observ Ludwig Maximilians Univ ID HIGH-REDSHIFT GALAXIES; STAR-FORMATION C1 NASA, Goddard Space Flight Ctr, LASP, Greenbelt, MD 20771 USA. RP de Mello, DF (reprint author), NASA, Goddard Space Flight Ctr, LASP, Code 681, Greenbelt, MD 20771 USA. RI Conselice, Christopher/B-4348-2013; OI Koekemoer, Anton/0000-0002-6610-2048 NR 7 TC 0 Z9 0 U1 0 U2 0 PU SPRINGER-VERLAG BERLIN PI BERLIN PA HEIDELBERGER PLATZ 3, D-14197 BERLIN, GERMANY BN 3-540-25665-2 J9 ESO ASTROPHY SYMP PY 2005 BP 376 EP 377 PG 2 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BCW16 UT WOS:000231503500068 ER PT B AU Gardner, JP AF Gardner, JP BE Renzini, A Bender, R TI Multi-wavelength luminosity functions of galaxies SO Multiwavelength Mapping of Galaxy Formation and Evolution SE ESO ASTROPHYSICS SYMPOSIA LA English DT Proceedings Paper CT ESO Workshop on Multiwavelength Mapping of Galaxy Formation and Evolution CY OCT 13-16, 2003 CL Venice, ITALY SP European So Observ, Max Planck Inst Extraterrestr Phys, Observ Ludwig Maximilians Univ C1 GSFC, Greenbelt, MD 20771 USA. RP Gardner, JP (reprint author), GSFC, Code 681, Greenbelt, MD 20771 USA. NR 3 TC 0 Z9 0 U1 0 U2 0 PU SPRINGER-VERLAG BERLIN PI BERLIN PA HEIDELBERGER PLATZ 3, D-14197 BERLIN, GERMANY BN 3-540-25665-2 J9 ESO ASTROPHY SYMP PY 2005 BP 386 EP 387 DI 10.1007/10995020_73 PG 2 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BCW16 UT WOS:000231503500073 ER PT B AU Grady, CA AF Grady, CA BE Ignace, R Gayley, KG TI The circumstellar disks of Herbig Ae/Be stars SO Nature and Evolution of Disks Around Hot Stars SE ASTRONOMICAL SOCIETY OF THE PACIFIC CONFERENCE SERIES LA English DT Proceedings Paper CT Meeting on the Nature and Evolution of Disks Around Hot Stars CY JUL 07-09, 2004 CL Johnson City, TN ID INTERMEDIATE-MASS STARS; X-RAY-EMISSION; BETA-PICTORIS; AB-AURIGAE; AE STAR; YOUNG STARS; TW-HYDRAE; PROTOPLANETARY DISKS; FUSE OBSERVATIONS; HIGH-RESOLUTION AB Currently our most complete view of protoplanetary disks, the place where planets form, and where the building blocks of life-bearing worlds are produced, is for disks around Herbig Ae stars. We review the data for the presence of circumstellar disks, the characteristic disk constituents, the coupling between the disk and the star, and the evolution of activity signatures over the first 10 Myr of the Herbig Ae star's lifetime. The more fragmentary data for Herbig Be stars is reviewed with implications for detection of x-rays from these stars, and for survival of circumstellar disks. C1 NASA, Eureka Sci, Greenbelt, MD 20771 USA. RP Grady, CA (reprint author), NASA, Eureka Sci, Code 681, Greenbelt, MD 20771 USA. NR 84 TC 3 Z9 3 U1 0 U2 0 PU ASTRONOMICAL SOC PACIFIC PI SAN FRANCISCO PA 390 ASHTON AVE, SAN FRANCISCO, CA 94112 USA BN 1-58381-203-2 J9 ASTR SOC P PY 2005 VL 337 BP 155 EP 168 PG 14 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BDN82 UT WOS:000234511900012 ER PT B AU Kallman, T AF Kallman, T BE Ignace, R Gayley, KG TI Winds from hot star disks SO Nature and Evolution of Disks Around Hot Stars SE ASTRONOMICAL SOCIETY OF THE PACIFIC CONFERENCE SERIES LA English DT Proceedings Paper CT Meeting on the Nature and Evolution of Disks Around Hot Stars CY JUL 07-09, 2004 CL Johnson City, TN ID ACTIVE GALACTIC NUCLEI; RADIATION-DRIVEN WINDS; YOUNG STELLAR OBJECTS; ACCRETION DISKS; PROTOSTELLAR DISKS; HYDRODYNAMICAL MODELS; PHOTOEVAPORATION; ULTRAVIOLET; DYNAMICS; FORCE AB Disk winds can account for some of the outflow features observed in spectra of a variety of different types of objects. In addition, winds can have a substantial effect on the mass budget of the disk, and can play a role in the evolution of accreting objects. In this article I will review some of the mechanisms which can cause disk winds and describe recent numerical simulations of these winds. C1 NASA, Goddard Space Flight Ctr, LHEA, Greenbelt, MD 20771 USA. RP Kallman, T (reprint author), NASA, Goddard Space Flight Ctr, LHEA, Greenbelt, MD 20771 USA. NR 30 TC 1 Z9 1 U1 0 U2 0 PU ASTRONOMICAL SOC PACIFIC PI SAN FRANCISCO PA 390 ASHTON AVE, SAN FRANCISCO, CA 94112 USA BN 1-58381-203-2 J9 ASTR SOC P PY 2005 VL 337 BP 169 EP 177 PG 9 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BDN82 UT WOS:000234511900013 ER PT S AU Song, M Shetty, S Wu, U AF Song, M Shetty, S Wu, U BE Lu, X Zhao, W TI Fair and smooth scheduling for virtual output queuing switches achieving 100% throughput SO NETWORKING AND MOBILE COMPUTING, PROCEEDINGS SE LECTURE NOTES IN COMPUTER SCIENCE LA English DT Article; Proceedings Paper CT 3rd International Conference on Computer Networks and Mobile Computing (ICCNMC 2005) CY AUG 02-04, 2005 CL Zhangjiajie, PEOPLES R CHINA SP China Comp Federat, IEEE Comp Soc Beijing Chapter, Hunan Comp Soc, IEEE TC Distributed Proc ID QUEUED SWITCH; ALGORITHMS; NETWORKS AB Cell scheduling has received extensive attention. Most recent studies, however, focus on achieving a 100% switch throughput under the uniform arrivals. As the demand for quality of service increases, two important goals are to provide predictive cell latency and to reduce the output burstiness. This paper presents a new scheduling algorithm, Worst-case Iterative Longest Port First (WiLPF), which improves the performance of the well-known scheduler Iterative Longest Port First (iLPF) such that both cell latency and output burstiness are well controlled. Simulation results are provided to verify how WiLPF outperforms iLPF. C1 Old Dominion Univ, Dept Elect & Comp Engn, Norfolk, VA 23508 USA. NASA, Langley Res Ctr, Multidisciplinary Optimizat Branch, Hampton, VA 23681 USA. RP Song, M (reprint author), Old Dominion Univ, Dept Elect & Comp Engn, 231 Kaufmann Hall, Norfolk, VA 23508 USA. EM msong@odu.edu; sshetty@odu.edu; w.li@larc.nasa.gov OI Shetty, Sachin/0000-0002-8789-0610 NR 9 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 3-540-28102-9 J9 LECT NOTES COMPUT SC PY 2005 VL 3619 BP 405 EP 413 PG 9 WC Computer Science, Information Systems; Computer Science, Software Engineering; Computer Science, Theory & Methods; Telecommunications SC Computer Science; Telecommunications GA BCT45 UT WOS:000231116600042 ER PT S AU Andrews, RJ AF Andrews, RJ BE Slikker, W Andrews, RJ Trembly, B TI Neuroprotection trek - The next generation - The measurement is the message SO NEUROPROTECTIVE AGENTS SE ANNALS OF THE NEW YORK ACADEMY OF SCIENCES LA English DT Article; Proceedings Paper CT 7th International Conference on Neuroprotective Agents CY NOV 14-19, 2004 CL Pacific Grove, CA SP Cent Arkansas Chapter SIGMA XI, Natl Ctr Toxicol Res, FDA, US EPA DE cancer diagnosis; deep brain stimulation; electrical stimulation; nanotechnology; neuromodulation; neuroprotection; optical spectroscopy AB Animal trials of many pharmacological neuroprotective agents have been quite successful, whereas trials in humans have been uniformly disappointing. A major difference between laboratory research in animals and clinical research in humans is the amount and/or quality of data obtained. The goal of this presentation is to argue that when clinical studies consist of more valid, objective data-that is, as our measurement capabilities in clinical research become as robust as they are in laboratory research-we are likely to gain new insights into both (1) injury to the nervous system and (2) neuroprotective treatment strategies. Technological advances (in data acquisition and analysis)-often novel even in the laboratory-will be the "scale" that will enable progress in measurement. As examples of such technological advances, two projects initiated at NASA Ames Research Center are cited. The NASA Smart Probe Project, with the goal of combining multiple microsensors and neural networks for real-time tissue identification (e.g., for tumor detection), has recently moved into the clinical realm, with a prototype being used to diagnose breast cancer in women "on the spot". The NASA Nanoelectrode Array Project has fabricated nanoscale devices that can simultaneously monitor electrical activity and neurotransmitter concentrations, while providing electrical stimulation focally and precisely (and potentially in a closed-loop fashion based on the input from the nanosensors). The large amounts of data that such techniques can acquire and analyze separated spatially and temporally throughout the nervous system, if necessary-will provide insights not only into neuroprotective strategies, but also into the workings of the nervous system itself. C1 NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Andrews, RJ (reprint author), 555 Knowles Dr 112, Los Gatos, CA 95032 USA. EM rja@russelljandrews.org; rja@russelljandrews.org NR 7 TC 3 Z9 3 U1 0 U2 2 PU NEW YORK ACAD SCIENCES PI NEW YORK PA 2 EAST 63RD ST, NEW YORK, NY 10021 USA SN 0077-8923 BN 1-57331-578-8 J9 ANN NY ACAD SCI JI Ann.NY Acad.Sci. PY 2005 VL 1053 BP 1 EP 11 DI 10.1196/annals.1344.001 PG 11 WC Multidisciplinary Sciences; Clinical Neurology; Neurosciences; Pharmacology & Pharmacy SC Science & Technology - Other Topics; Neurosciences & Neurology; Pharmacology & Pharmacy GA BDR63 UT WOS:000235109800001 PM 16179500 ER PT B AU Dick, SJ AF Dick, SJ BE Orchiston, W TI The biological universe revisited SO New Astronomy: Opening the Electromagnetic Window and Expanding our View of Planet Earth: A MEETING TO HONOR WOODY SULLIVAN ON HIS 60TH BIRTHDAY SE ASTROPHYSICS AND SPACE SCIENCE LIBRARY LA English DT Proceedings Paper CT Woodfest Meeting on Astrobiology, History of Astronomy and Sundials held in Honor of Woody Sullivan on his 60th Birthday CY JUN 16-18, 2004 CL Seattle, WA SP UW Kammeyer Fund DE artificial intelligence; biological universe; cosmic evolution; cultural evolution; Drake Equation; postbiological universe; Shapley ID CIVILIZATIONS AB Cosmic Evolution has been seen as leading to two possible world views: a physical universe in which life is rare or unique to Earth, and a biological universe, in which the processes of cosmic evolution commonly end in life. These two worldviews now hang in the balance, in the same way that the heliocentrie and geocentric worldviews were in the balance four hundred years ago when Galileo wrote his Dialogue on the Two Chief World Systems (1632). Astrobiology is the science that will decide which of the two modem astronomical worldviews is true. A third world view, the postbiological universe, is also possible and deserves more discussion. The confirmation of one of these worldviews will have profound implications for human destiny. C1 NASA Headquarters, Washington, DC 20546 USA. NR 35 TC 1 Z9 1 U1 0 U2 1 PU SPRINGER PI DORDRECHT PA PO BOX 17, 3300 AA DORDRECHT, NETHERLANDS BN 1-4020-3723-6 J9 ASTROPHYS SPACE SC L PY 2005 VL 334 BP 15 EP 26 PG 12 WC Astronomy & Astrophysics; History & Philosophy Of Science SC Astronomy & Astrophysics; History & Philosophy of Science GA BDP58 UT WOS:000234789700002 ER PT J AU Miyoshi, K Takeuchi, S Suzuki, M Watanabe, M AF Miyoshi, K Takeuchi, S Suzuki, M Watanabe, M TI Solid lubrication by novel carbon-derived materials SO NEW DIAMOND AND FRONTIER CARBON TECHNOLOGY LA English DT Review DE lubrication; friction; nanocarbons; carbon-base films ID FRICTION; DIAMOND AB This paper concerns the specific subject of nanotubes, diamonds, and diamondlike carbons for solid lubrication. It reviews studies and observation on the adhesion, friction, wear, and lubrication behavior of these carbon-derived materials and related solid films, emphasizing environmental effects and basic friction and wear properties. The production of carbon nanotubes and related nanocarbons on a large scale, large-area diamond films or sheets designed for engineering materials at low cost, and thick diamondlike carbon films or sheets, a distinct possibility in the not-too-distant future, may drastically change tribology technology. It will soon be possible to take advantage of demanding properties of novel carbon-derived materials to develop a myriad of new applications such as innovative solid lubricants and durable, protective coatings. Nanotubes may create their own revolution in the development of an entirely new branch of solid lubrication. C1 NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. Nippon Inst Technol, Miyashiro Machi, Saitama 3458501, Japan. Inst Mol Sci, Natl Inst Nat Sci, Okazaki, Aichi 4448585, Japan. RP Miyoshi, K (reprint author), NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. EM Kazuhisa.Miyoshi-1@nasa.gov NR 9 TC 1 Z9 1 U1 2 U2 10 PU MYU PI TOKYO PA 1-23-3-303 SENDAGI, TOKYO, BUNKYO-KU 113-0022, JAPAN SN 1344-9931 J9 NEW DIAM FRONT C TEC JI New Diam. Front. Carbon Technol. PY 2005 VL 15 IS 1 BP 37 EP 49 PG 13 WC Materials Science, Multidisciplinary; Materials Science, Coatings & Films SC Materials Science GA 909LW UT WOS:000227862400008 ER PT S AU Serizawa, H Lewinsohn, CA Singh, M Murakawa, H AF Serizawa, H Lewinsohn, CA Singh, M Murakawa, H BE Naka, M Yamane, T TI Evaluation of fracture behavior of ceramic composite joints by using a new interface potential SO NEW FRONTIERS OF PROCESSING AND ENGINEERING IN ADVANCED MATERIALS SE Materials Science Forum LA English DT Article; Proceedings Paper CT International Conference on New Frontiers of Process Science and Engineering in Advanced Materials/ 14th Iketani Conference CY NOV 24-26, 2004 CL Kyoto, JAPAN SP High Temp Soc Japan, Osaka Univ, Joining & Welding Res Inst, Iketani Sci & Technol Fdn, Murata Sci Fdn DE SiC/SiC composite; finite element method; interface element; surface energy; fracture; ceramics ID HIGH-TEMPERATURE; STRENGTH; ENERGY AB In order to examine mode-I & II type fracture behavior of ceramic joints, the interface element was proposed as a simple model which represents the mechanism of failure in an explicit manner. It was applied to the analyses of four point bending test and asymmetrical four point bending test for SiC/SiC composite specimen joined by ARCJoinT (TM). By using a new type interface potential, which is a coupled function of opening and shear deformations, both the bending and asymmetrical bending tests were simulated. From comparison with experiments, surface energy at the interface between the joint and composite was estimated to be about 30 N/m regardless of the fracture mode. Also, from the comparison between the predicted strength and the experiments for the tensile test of lap joint of SiC/SiC composites, it was found that the proposed method was considered to have a great potential as a tool to study the failure problems whose fracture type was a mixture of mode-I & II. C1 Osaka Univ, Joining & Welding Res Inst, Ibaraki, Osaka 5670047, Japan. Ceramatec Inc, Salt Lake City, UT 84119 USA. NASA, Glenn Res Ctr, QSS Grp Inc, Ceram Branch, Cleveland, OH 44135 USA. RP Osaka Univ, Joining & Welding Res Inst, 11-1 Mihogaoka, Ibaraki, Osaka 5670047, Japan. EM serizawa@jwri.osaka-u.ac.jp; clewinsohn@ceramatec.com; mrityunjay.singh@grc.nasa.gov; murakawa@jwri.osaka-u.ac.jp NR 13 TC 1 Z9 1 U1 0 U2 0 PU TRANS TECH PUBLICATIONS LTD PI DURNTEN-ZURICH PA KREUZSTRASSE 10, 8635 DURNTEN-ZURICH, SWITZERLAND SN 0255-5476 BN 0-87849-980-6 J9 MATER SCI FORUM PY 2005 VL 502 BP 69 EP 74 PG 6 WC Materials Science, Multidisciplinary; Metallurgy & Metallurgical Engineering; Materials Science, Characterization & Testing SC Materials Science; Metallurgy & Metallurgical Engineering GA BDL89 UT WOS:000234200300012 ER PT S AU Millis, MG AF Millis, Marc G. BE Belbruno, E TI Assessing potential propulsion breakthroughs SO NEW TRENDS IN ASTRODYNAMICS AND APPLICATIONS SE ANNALS OF THE NEW YORK ACADEMY OF SCIENCES LA English DT Article; Proceedings Paper CT Conference on New Trends in Astrodynamics and Applications II CY JUN 03-05, 2005 CL Princeton Univ, Princeton, NJ SP NASA Headquarters, Aviat Week & Space Technol Magazine, Wilmer Cutler Pickering Hale Dorr LLP, Natl Space Soc, NY City Chapter HO Princeton Univ DE spacecraft propulsion; physics; project management; relativity; antigravity ID GENERAL-RELATIVITY; POLARIZABLE-VACUUM; SPACE DRIVE; WARP DRIVE; GRAVITY; INERTIA; TRAVEL; WORMHOLES; MOTION; ORIGIN AB The term, propulsion breakthrough, refers to concepts like propel-lantless space drives and faster-than-light travel, the kind of breakthroughs that would make interstellar exploration practical. Although no such breakthroughs appear imminent, a variety of investigations have begun. During 1996-2002 NASA supported the breakthrough propulsion physics project to examine physics in the context of breakthrough spaceflight. Three facets of these assessments are now reported: (1) predicting benefits, (2) selecting research, and (3) recent technical progress. Predicting benefits is challenging, since the breakthroughs are still only notional concepts, but energy can serve as a basis for comparison. A hypothetical space drive would require many orders of magnitude less energy than a rocket for journeys to our nearest neighboring star. Assessing research options is challenging when the goals are beyond known physics and when the implications of success are profound. To mitigate the challenges, a selection process is described where: (1) research tasks are constrained to only address the immediate unknowns, curious effects, or critical issues; (2) reliability of assertions is more important than their implications; and (3) reviewers judge credibility rather than feasibility. The recent findings of a number of tasks, some selected using this process, are discussed. Of the 14 tasks included, six reached null conclusions, four remain unresolved, and four have opportunities for sequels. A dominant theme with the sequels is research about the properties of space, inertial frames, and the quantum vacuum. C1 NASA, John H Glenn Res Ctr, Lewis Field, Cleveland, OH 44135 USA. RP Millis, MG (reprint author), NASA, John H Glenn Res Ctr, Lewis Field, 21000 Brookpk Rd,MS 86-2, Cleveland, OH 44135 USA. EM marc.g.millis@nasa.gov NR 64 TC 8 Z9 8 U1 1 U2 7 PU NEW YORK ACAD SCIENCES PI NEW YORK PA 2 EAST 63RD ST, NEW YORK, NY 10021 USA SN 0077-8923 BN 1-57331-630-X J9 ANN NY ACAD SCI JI Ann.NY Acad.Sci. PY 2005 VL 1065 BP 441 EP 461 DI 10.1196/annals.1370.023 PG 21 WC Engineering, Aerospace; Mechanics; Multidisciplinary Sciences SC Engineering; Mechanics; Science & Technology - Other Topics GA BEC73 UT WOS:000236816300027 PM 16510425 ER PT J AU Koch, LD Bridges, J Brown, C Brown, C Khavaran, A AF Koch, LD Bridges, J Brown, C Brown, C Khavaran, A TI Experimental and analytical determination of the geometric far field for round jets SO NOISE CONTROL ENGINEERING JOURNAL LA English DT Article AB An investigation was conducted at the NASA Glenn Research Center using a set of three round jets operating under unheated subsonic conditions to address the question: "How close is too close?" Although sound sources are distributed at various distances throughout a jet plume downstream of the nozzle exit, at great distances from the nozzle the sound will appear to emanate from a point and the inverse-square law can be properly applied. Examination of normalized sound spectra at different distances from a jet, from experiments and from computational tools, established the required minimum distance for valid far-field measurements of the sound from subsonic round jets. Experimental data were acquired in the Aeroacoustic Propulsion Laboratory at the NASA Glenn Research Center. The WIND computer program solved the Reynolds-Averaged Navier-Stokes equations for aerodynamic computations; the MGBK jet-noise-prediction computer code was used to predict the sound pressure levels. Results from both the experiments and the analytical exercises indicated that while the shortest measurement arc (with radius similar to 8 nozzle diameters) was already in the geometric far field for high-frequency sound (Strouhal number > 5), low-frequency sound (Strouhal number < 0.2) reached the geometric far field at a measurement radius of at least 50 nozzle diameters because of its extended source distribution. (c) 2005 Institute of Noise Control Engineering. C1 NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. QSS Grp Inc, Cleveland, OH 44135 USA. RP Koch, LD (reprint author), NASA, Glenn Res Ctr, 21000 Brookpk Rd,Mail Stop 54-3, Cleveland, OH 44135 USA. EM Danielle.Koch@nasa.gov; James.E.Bridges@nasa.gov; Clifford.A.Brown@nasa.gov; Abbas.Khavaran@grc.nasa.gov NR 14 TC 6 Z9 6 U1 0 U2 1 PU INST NOISE CONTROL ENGINEERING PI AMES PA IOWA STATE UNIV, COLLEGE ENGINEERING, 212 MARSTON HALL, AMES, IA 50011-2152 USA SN 0736-2501 J9 NOISE CONTROL ENG J JI Noise Control Eng. J. PD JAN-FEB PY 2005 VL 53 IS 1 BP 20 EP 28 DI 10.3397/1.2839242 PG 9 WC Acoustics; Engineering, Multidisciplinary SC Acoustics; Engineering GA 933VU UT WOS:000229661800003 ER PT S AU Luchinsky, DG Smelyanskiy, VN Millonas, M McClintock, PVE AF Luchinsky, DG Smelyanskiy, VN Millonas, M McClintock, PVE BE Kish, LB Lindenberg, K Gingl, Z TI Reconstruction of stochastic nonlinear dynamical models from trajectory measurements SO Noise in Complex Systems and Stochastic Dynamics III SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Noise in Complex Systems and Stochastic Dynamics III CY MAY 24-26, 2005 CL Austin, TX DE Bayesian inference; nonlinear model reconstruction ID TIME-SERIES; SYSTEMS; NOISE AB We consider the following general problem of applied stochastic nonlinear dynamics (see e.g.(1)). We observe a time series of signals y(t) = y(t(0) + hn) corrupted by noise. The actual state and the nonlinear vector field of the dynamical system is not known. The question is how and with what accuracy can we determine x(t) and functional form of f (x). In this talk we discuss a novel approach to the solution of this problem based on the application of the path-integral approach to the full Bayesian inference. We demonstrate a reconstruction of a dynamical state of a system from corrupted by noise measurements. Next we reconstruct the corresponding nonlinear vector field. The emphasis are on the theoretical analysis. The results are compared with the results of earlier research. C1 NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Luchinsky, DG (reprint author), NASA, Ames Res Ctr, Mail Stop 269-2, Moffett Field, CA 94035 USA. RI Luchinsky, Dmitry/N-4177-2014 NR 22 TC 3 Z9 3 U1 0 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 0-8194-5840-6 J9 P SOC PHOTO-OPT INS PY 2005 VL 5845 BP 173 EP 181 DI 10.1117/12.610457 PG 9 WC Statistics & Probability SC Mathematics GA BCU86 UT WOS:000231348500020 ER PT S AU Ghosn, LJ Abdul-Aziz, A Young, PG Rauser, RW AF Ghosn, LJ Abdul-Aziz, A Young, PG Rauser, RW BE Shull, PJ Gyekenyesi, AL Mufti, AA TI Structural assessment of metal foam using combined NDE and FEA SO Nondestructive Evaluation and Health Monitoring of Aerospace Materials, Composites, and Civil Infrastructure IV SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT 4th Conference on Nondestructive Evaluation and Health Monitoring of Aerospace Materials, Composites, and Civil Infrastructure CY MAR 08-10, 2005 CL San Diego, CA SP SPIE DE finite element analysis; computed topography; metal foam; stress analysis; non destructive evaluation AB Metal foams are expected to find use in structural applications where weight is of particular concern, such as space vehicles, rotorcraft blades, car bodies or portable electronic devices. The obvious structural application of metal foam is for light weight sandwich panels, made up of thin solid face sheets and a metallic foam core. The stiffness of the sandwich structure is increased by separating the two face sheets by a light weight foam core. The resulting high-stiffness structure is lighter than that constructed only out of the solid metal material. Since the face sheets carry the applied in-plane and bending loads, the sandwich architecture is a viable engineering concept. However, the metal foam core must resist transverse shear loads and compressive loads while remaining integral with the face sheets. Challenges relating to the fabrication and testing of these metal foam panels remain due to some mechanical properties falling short of their theoretical potential. Theoretical mechanical properties are based on an idealized foam microstructure and assumed cell geometry. But the actual testing is performed on as fabricated foam microstructure. Hence in this study, a high fidelity finite element analysis is conducted on as fabricated metal foam microstructures, to compare the calculated mechanical properties with the idealized theory. The high fidelity geometric models for the FEA are generated using series of 2D CT scans of the foam structure to reconstruct the 31) metal foam geometry. The metal foam material is an aerospace grade precipitation hardened 17-4 PH stainless steel with high strength and high toughness. Tensile, compressive, and shear mechanical properties are deduced from the FEA model and compared with the theoretical values. The combined NDE/FEA provided insight in the variability of the mechanical properties compared to idealized theory. C1 NASA, Glenn Res Ctr, Ohio Aerosp Inst, Cleveland, OH 44135 USA. RP Ghosn, LJ (reprint author), NASA, Glenn Res Ctr, Ohio Aerosp Inst, 21000 Brook Pk Rd MS 49-7, Cleveland, OH 44135 USA. NR 13 TC 1 Z9 1 U1 0 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 0-8194-5748-5 J9 P SOC PHOTO-OPT INS PY 2005 VL 5767 BP 248 EP 254 DI 10.1117/12.601753 PG 7 WC Engineering, Aerospace; Engineering, Civil; Materials Science, Multidisciplinary; Materials Science, Characterization & Testing; Materials Science, Composites SC Engineering; Materials Science GA BCO18 UT WOS:000230386000025 ER PT S AU Abdul-Aziz, A Trudell, JJ Baakilini, GY AF Abdul-Aziz, A Trudell, JJ Baakilini, GY BE Shull, PJ Gyekenyesi, AL Mufti, AA TI Finite element design study of a bladed, flat rotating disk to simulate cracking in a typical turbine disk SO Nondestructive Evaluation and Health Monitoring of Aerospace Materials, Composites, and Civil Infrastructure IV SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT 4th Conference on Nondestructive Evaluation and Health Monitoring of Aerospace Materials, Composites, and Civil Infrastructure CY MAR 08-10, 2005 CL San Diego, CA SP SPIE DE health monitoring; finite element; Crack initiation; flat disk; NDE; Aviation Safety; Center of mass; rotor damage; unbalances AB Developing health management and ultrasafe engine technologies are the primary goals of NASA's Aviation Safety Program. Besides improving safety, health monitoring can also reduce maintenance costs. A unique disk spin simulation system was assembled by the Nondestructive Evaluation (NDE) Group at NASA Glenn Research Center to verify and study a crack detection technique based upon observing center of mass changes of the rotor system using various sensing technologies. Ibis paper describes the finite element analysis results of low cost, a 25.4 cm (10 in.) diameter, flat turbine disk used to evaluate the detection techniques by simulating typical cracks observed in turbine engine disks. Changes in radial tip displacement and center of mass are presented as a function of speed, crack size and location. C1 Cleveland State Univ, NASA, Glenn Res Ctr, Dept Civil & Environm Engn, Cleveland, OH 44135 USA. RP Abdul-Aziz, A (reprint author), Cleveland State Univ, NASA, Glenn Res Ctr, Dept Civil & Environm Engn, 21000 Brookpk Rd MS 6-1, Cleveland, OH 44135 USA. NR 8 TC 2 Z9 3 U1 0 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 0-8194-5748-5 J9 P SOC PHOTO-OPT INS PY 2005 VL 5767 BP 298 EP 307 DI 10.1117/12.601896 PG 10 WC Engineering, Aerospace; Engineering, Civil; Materials Science, Multidisciplinary; Materials Science, Characterization & Testing; Materials Science, Composites SC Engineering; Materials Science GA BCO18 UT WOS:000230386000030 ER PT S AU Anastasi, RF Madaras, EI AF Anastasi, RF Madaras, EI BE Shull, PJ Gyekenyesi, AL Mufti, AA TI Application of Hilbert-Huang transform for improved defect detection in terahertz NDE of shuttle tiles SO NONDESTRUCTIVE EVALUATION AND HEALTH MONITORING OF AEROSPACE MATERIALS, COMPOSITES, AND CIVIL INFRASTRUCTURE IV SE Proceedings of SPIE-The International Society for Optical Engineering LA English DT Proceedings Paper CT 4th Conference on Nondestructive Evaluation and Health Monitoring of Aerospace Materials, Composites, and Civil Infrastructure CY MAR 08-10, 2005 CL San Diego, CA SP SPIE DE terahertz; Hilbert-Huang transform; signal processing; nondestructive evaluation AB Terahertz NDE is being examined as a method to inspect the adhesive bond-line of Space Shuttle tiles for defects. Terahertz signals are generated and detected, using optical excitation of biased semiconductors with femtosecond laser pulses. Shuttle tile samples were manufactured with defects that included repair regions unbond regions, and other conditions that occur in Shuttle structures. These samples were inspected with a commercial terahertz NDE system that scanned a tile and generated a data set of RF signals. The signals were post processed to generate C-scan type images that are typically seen in ultrasonic NDE. To improve defect visualization the Hilbert-Huang Transform, a transform that decomposes a signal into oscillating components called intrinsic mode functions, was applied to test signals identified as being in and out of the defect regions and then on a complete data set. As expected with this transform, the results showed that the decomposed low-order modes correspond to signal noise while the high-order modes correspond to low frequency oscillations in the signal and mid-order modes correspond to local signal oscillations. The local oscillations compare well with various reflection interfaces and the defect locations in the original signal. C1 USA, Res Lab, Vehicle Technol Directorate,AMSRD,ARL,VT,SM, Nondestruct Evaluat Sci Branch,NASA Langley Res C, Hampton, VA 23681 USA. RP Anastasi, RF (reprint author), USA, Res Lab, Vehicle Technol Directorate,AMSRD,ARL,VT,SM, Nondestruct Evaluat Sci Branch,NASA Langley Res C, Hampton, VA 23681 USA. EM robert.f.anastasi@nasa.gov NR 12 TC 3 Z9 3 U1 3 U2 8 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-5748-5 J9 P SOC PHOTO-OPT INS PY 2005 VL 5767 BP 356 EP 362 DI 10.1117/12.600570 PG 7 WC Engineering, Aerospace; Engineering, Civil; Materials Science, Multidisciplinary; Materials Science, Characterization & Testing; Materials Science, Composites SC Engineering; Materials Science GA BCO18 UT WOS:000230386000036 ER PT S AU Klimas, AJ Uritsky, VM Vassiliadis, D Baker, DN AF Klimas, AJ Uritsky, VM Vassiliadis, D Baker, DN BE Sharma, AS Kaw, PK TI Simulation study of SoC dynamics in driven current-sheet models SO NONEQUILIBRIUM PHENOMENA IN PLASMAS SE Astrophysics and Space Science Library LA English DT Proceedings Paper CT Workshop on Nonequilibrium Phenomena in Plasmas CY MAR, 2001 CL Ahmedabad, INDIA DE self-organized criticality; current-sheet; numerical simulation ID SELF-ORGANIZED CRITICALITY; EARTHWARD FLOW BURSTS; INDEX TIME-SERIES; AURORAL ELECTROJET INDEX; NONLINEAR SURROGATE DATA; AE-INDEX; CURRENT DISRUPTION; PLASMA SHEET; MULTIFRACTAL STRUCTURE; MAGNETIC FLUCTUATIONS AB Evidence is reviewed that suggests the presence self-organized critically dynamics in Earth's Magnetotail. It has been proposed that scale-free avalanching and spreading critical dynamics observed in auroral emissions are a reflection of these behaviors in the tail plasma sheet. Localized reconnection in the turbulent plasma sheet has been proposed as the local instability that collectively enables the avalanching process. A numerical simulation study of reconnection and magnetic field annihilation in driven current-sheet models is reviewed. Each of the models is composed of a resistive MHD component coupled to an idealized representation of an anomalous resistivity generating current-driven instability. Models in one- and two-dimensions are discussed. Behavior that indicates both models can evolve into self-organized criticality under steady driving is reviewed. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. NR 47 TC 2 Z9 2 U1 0 U2 0 PU SPRINGER PI DORDRECHT PA PO BOX 17, 3300 AA DORDRECHT, NETHERLANDS SN 0067-0057 BN 1-4020-3108-4 J9 ASTROPHYS SPACE SC L PY 2005 VL 321 BP 71 EP 89 PG 19 WC Astronomy & Astrophysics; Physics, Fluids & Plasmas SC Astronomy & Astrophysics; Physics GA BCV67 UT WOS:000231442300004 ER PT J AU Lind, R Prazenica, RJ Brenner, MJ AF Lind, R Prazenica, RJ Brenner, MJ TI Estimating nonlinearity using Volterra kernels in feedback with linear models SO NONLINEAR DYNAMICS LA English DT Article DE aeroelastic; limit cycle oscillation; system identification; Volterra kernel ID SYSTEMS; FIGHTER; MEMORY AB Aeroelastic dynamics must be accurately known to ensure safe and efficient flight testing. Unfortunately, most models of aircraft systems typically describe only the linear dynamics. These models are inadequate for predicting behaviors, such as limit cycle oscillations, resulting from nonlinearities. This paper presents an approach to augment a linear model by identifying associated nonlinear operators. Essentially, the difference between a flight data measurement and a simulated measurement indicates the unmodeled dynamics. Volterra kernels are computed to represent the difference in measurement and, consequently, represent the unmodeled dynamics. The approach is applied to a nonlinear pitch-plunge system for which only a linear model is assumed available. The method is able to characterize errors due to incorrect parameters in the linear model and errors due to unmodeled nonlinearities of the dynamics. C1 Univ Florida, Dept Mech & Aerosp Engn, Gainesville, FL 32611 USA. NASA, Dryden Flight Res Ctr, Edwards AFB, CA 93523 USA. RP Lind, R (reprint author), Univ Florida, Dept Mech & Aerosp Engn, 231 MAE-A Bldg, Gainesville, FL 32611 USA. EM rick@mae.ufl.edu NR 18 TC 11 Z9 13 U1 0 U2 0 PU SPRINGER PI DORDRECHT PA VAN GODEWIJCKSTRAAT 30, 3311 GZ DORDRECHT, NETHERLANDS SN 0924-090X J9 NONLINEAR DYNAM JI Nonlinear Dyn. PD JAN PY 2005 VL 39 IS 1-2 BP 3 EP 23 DI 10.1007/s11071-005-1906-0 PG 21 WC Engineering, Mechanical; Mechanics SC Engineering; Mechanics GA 899PT UT WOS:000227157600002 ER PT J AU Silva, W AF Silva, W TI Identification of nonlinear aeroelastic systems based on the Volterra theory: Progress and opportunities SO NONLINEAR DYNAMICS LA English DT Review DE nonlinear aeroelasticity; system identification; Volterra theory ID WAVE INTERACTIONS; KERNELS; PHASE; ORDER AB The identification of nonlinear aeroelastic systems based on the Volterra theory of nonlinear systems is presented. Recent applications of the theory to problems in computational and experimental aeroelasticity are reviewed. Computational results include the development of computationally efficient reduced-order models (ROMs) using an Euler/Navier-Stokes flow solver and the analytical derivation of Volterra kernels for a nonlinear aeroelastic system. Experimental results include the identification of aerodynamic impulse responses, the application of higher-order spectra (HOS) to wind-tunnel flutter data, and the identification of nonlinear aeroelastic phenomena from flight flutter test data of the active aeroelastic wing (AAW) aircraft. C1 NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Silva, W (reprint author), NASA, Langley Res Ctr, 218 Dodd Blvd,Mail Stop 340, Hampton, VA 23681 USA. EM walter.a.silva@nasa.gov NR 110 TC 76 Z9 78 U1 2 U2 24 PU SPRINGER PI DORDRECHT PA VAN GODEWIJCKSTRAAT 30, 3311 GZ DORDRECHT, NETHERLANDS SN 0924-090X J9 NONLINEAR DYNAM JI Nonlinear Dyn. PD JAN PY 2005 VL 39 IS 1-2 BP 25 EP 62 DI 10.1007/s11071-005-1907-z PG 38 WC Engineering, Mechanical; Mechanics SC Engineering; Mechanics GA 899PT UT WOS:000227157600003 ER PT J AU Juang, JN AF Juang, JN TI Continuous-time bilinear system identification SO NONLINEAR DYNAMICS LA English DT Article DE bilinear system; Markov parameters; nonlinear system; system identification; system realization ID NONLINEAR-SYSTEMS AB The objective of this paper is to describe a new method for identification of a continuous-time multi-input and multi-output bilinear system. The approach is to make judicious use of the linear-model properties of the bilinear system when subjected to a constant input. Two steps are required in the identification process. The first step is to use a set of pulse responses resulting from a constant input of one sample period to identify the state matrix, the output matrix, and the direct transmission matrix. The second step is to use another set of pulse responses with the same constant input over multiple sample periods to identify the input matrix and the coefficient matrices associated with the coupling terms between the state and the inputs. Numerical examples are given to illustrate the concept and the computational algorithm for the identification method. C1 NASA, Langley Res Ctr, Struct Dynam Branch, Hampton, VA 23681 USA. RP Juang, JN (reprint author), NASA, Langley Res Ctr, Struct Dynam Branch, Hampton, VA 23681 USA. EM jer-nan.juang-1@nasa.gov NR 19 TC 22 Z9 23 U1 0 U2 5 PU SPRINGER PI DORDRECHT PA VAN GODEWIJCKSTRAAT 30, 3311 GZ DORDRECHT, NETHERLANDS SN 0924-090X J9 NONLINEAR DYNAM JI Nonlinear Dyn. PD JAN PY 2005 VL 39 IS 1-2 BP 79 EP 94 DI 10.1007/s11071-005-1915-z PG 16 WC Engineering, Mechanical; Mechanics SC Engineering; Mechanics GA 899PT UT WOS:000227157600005 ER PT J AU Pickett, JS Chen, LJ Kahler, SW Santolik, O Goldstein, ML Lavraud, B Decreau, PME Kessel, R Lucek, E Lakhina, GS Tsurutani, BT Gurnett, DA Cornilleau-Wehrlin, N Fazakerley, A Reme, H Balogh, A AF Pickett, JS Chen, LJ Kahler, SW Santolik, O Goldstein, ML Lavraud, B Decreau, PME Kessel, R Lucek, E Lakhina, GS Tsurutani, BT Gurnett, DA Cornilleau-Wehrlin, N Fazakerley, A Reme, H Balogh, A TI On the generation of solitary waves observed by Cluster in the near-Earth magnetosheath SO NONLINEAR PROCESSES IN GEOPHYSICS LA English DT Article ID BOW SHOCK; LION ROARS; SATELLITE-OBSERVATIONS; ELECTROSTATIC NOISE; UNUSUAL LOCATIONS; AURORAL-ZONE; POLAR; INSTABILITIES; MAGNETOPAUSE; SPACECRAFT AB Through case studies involving Cluster waveform observations, solitary waves in the form of bipolar and tripolar pulses have recently been found to be quite abundant in the near-Earth dayside magnetosheath. We expand on the results of those previous studies by examining the distribution of solitary waves from the bow shock to the magnetopause using Cluster waveform data. Cluster's orbit allows for the measurement of solitary waves in the magnetosheath from about 10 R(E) to 19.5 R(E). Our results clearly show that within the magnetosheath, solitary waves are likely to be observed at any distance from the bow shock and that this distance has no dependence on the time durations and amplitudes of the solitary waves. In addition we have found that these same two quantities show no dependence on either the ion velocity or the angle between the ion velocity and the local magnetic field direction. These results point to the conclusion that the solitary waves are probably created locally in the magnetosheath at multiple locations, and that the generation mechanism is most likely not solely related to ion dynamics, if at all. To gain insight into a possible local generation mechanism, we have examined the electron differential energy flux characteristics parallel and perpendicular to the magnetic field, as well as the local electron plasma and cyclotron frequencies and the type of bow shock that Cluster is behind, for several time intervals where solitary waves were observed in the magnetosheath. We have found that solitary waves are most likely to be observed when there are counterstreaming (similar to parallel and anti-parallel to the magnetic field) electrons at or below about 100 eV. However, there are times when these counterstreaming electrons are present when solitary waves are not. During these times the background magnetic field strength is usually very low (< 10nT), implying that the amplitudes of the solitary waves, if present, would be near or below those of other waves and electrostatic fluctuations in this region making it impossible to isolate or clearly distinguish them from these other emissions in the waveform data. Based on these results, we have concluded that some of the near-Earth magnetosheath solitary waves, perhaps in the form of electron phase-space holes, may be generated locally by a two-stream instability involving electrons based on the counterstreaming electrons that are often observed when solitary waves are present. We have not ruled out the possibility that the solitary waves could be generated as a result of the lower-hybrid Buneman instability in the presence of an electron beam, through the electron acoustic mode or through processes involving turbulence, which is almost always present in the magnetosheath, but these will be examined in a more comprehensive study in the future. C1 Univ Iowa, Dept Phys & Astron, Iowa City, IA 52242 USA. Charles Univ Prague, Fac Math & Phys, Prague, Czech Republic. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Los Alamos Natl Lab, Los Alamos, NM USA. LPCE, Orleans, France. Univ Orleans, Orleans, France. Univ London Imperial Coll Sci Technol & Med, Blackett Lab, London, England. Indian Inst Geomagnetism, Bombay 400005, Maharashtra, India. CALTECH, Jet Propuls Lab, Pasadena, CA 91125 USA. UVSQ, CETP, Velizy Villacoublay, France. UCL, Mullard Space Sci Lab, London, England. CESR, F-32018 Toulouse, France. RP Pickett, JS (reprint author), Univ Iowa, Dept Phys & Astron, Iowa City, IA 52242 USA. EM pickett@uiowa.edu RI Chen, Li-Jen/C-2106-2012; Lakhina, Gurbax /C-9295-2012; Goldstein, Melvyn/B-1724-2008; Santolik, Ondrej/F-7766-2014; OI Lakhina, Gurbax /0000-0002-8956-486X NR 44 TC 44 Z9 44 U1 0 U2 6 PU COPERNICUS GESELLSCHAFT MBH PI GOTTINGEN PA BAHNHOFSALLEE 1E, GOTTINGEN, 37081, GERMANY SN 1023-5809 J9 NONLINEAR PROC GEOPH JI Nonlinear Process Geophys. PY 2005 VL 12 IS 2 BP 181 EP 193 PG 13 WC Geochemistry & Geophysics; Meteorology & Atmospheric Sciences SC Geochemistry & Geophysics; Meteorology & Atmospheric Sciences GA 910QG UT WOS:000227946300004 ER PT J AU Tsurutani, BT Lakhina, GS Pickett, JS Guarnieri, FL Lin, N Goldstein, BE AF Tsurutani, BT Lakhina, GS Pickett, JS Guarnieri, FL Lin, N Goldstein, BE TI Nonlinear Alfven waves, discontinuities, proton perpendicular acceleration, and magnetic holes/decreases in interplanetary space and the magnetosphere: intermediate shocks? SO NONLINEAR PROCESSES IN GEOPHYSICS LA English DT Review ID COMPRESSIBLE MAGNETOHYDRODYNAMIC TURBULENCE; STEEPENED MAGNETOSONIC WAVES; ELECTROMAGNETIC PLASMA-WAVES; COMET GIACOBINI-ZINNER; MIRROR-MODE STRUCTURES; BOUNDARY-LAYER WAVES; P GRIGG-SKJELLERUP; SOLAR-WIND; DIRECTIONAL DISCONTINUITIES; ROTATIONAL DISCONTINUITIES AB Alfven waves, discontinuities, proton perpendicular acceleration and magnetic decreases (MDs) in interplanetary space are shown to be interrelated. Discontinuities are the phase-steepened edges of Alfven waves. Magnetic decreases are caused by a diamagnetic effect from perpendicularly accelerated (to the magnetic field) protons. The ion acceleration is associated with the dissipation of phase-steepened Alfven waves, presumably through the Ponderomotive Force. Proton perpendicular heating, through instabilities, lead to the generation of both proton cyclotron waves and mirror mode structures. Electromagnetic and electrostatic electron waves are detected as well. The Alfven waves are thus found to be both dispersive and dissipative, conditions indicting that they may be intermediate shocks. The resultant "turbulence" created by the Alfven wave dissipation is quite complex. There are both propagating (waves) and nonpropagating (mirror mode structures and MDs) byproducts. Arguments are presented to indicate that similar processes associated with Alfven waves are occurring in the magnetosphere. In the magnetosphere, the "turbulence" is even further complicated by the damping of obliquely propagating proton cyclotron waves and the formation of electron holes, a form of solitary waves. Interplanetary Alfven waves are shown to rapidly phase-steepen at a distance of 1 AU from the Sun. A steepening rate of similar to 35 times per wavelength is indicated by Cluster-ACE measurements. Interplanetary (reverse) shock compression of Alfven waves is noted to cause the rapid formation of MDs on the sunward side of corotating interaction regions (CIRs). Although much has been learned about the Alfven wave phase-steepening process from space plasma observations, many facets are still not understood. Several of these topics are discussed for the interested researcher. Computer simulations and theoretical developments will be particularly useful in making further progress in this exciting new area. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. Univ So Calif, Space Sci Ctr, Los Angeles, CA USA. Indian Inst Geomagnet, Bombay, Maharashtra, India. Univ Iowa, Dept Phys & Astron, Iowa City, IA USA. INPE, BR-12227010 Sao Jose Dos Campos, Brazil. Univ Calif Berkeley, Space Sci Lab, Berkeley, CA USA. RP CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM bruce.tsurutani@jpl.nasa.gov RI Lakhina, Gurbax /C-9295-2012; OI Lakhina, Gurbax /0000-0002-8956-486X NR 103 TC 63 Z9 66 U1 0 U2 7 PU COPERNICUS GESELLSCHAFT MBH PI GOTTINGEN PA BAHNHOFSALLEE 1E, GOTTINGEN, 37081, GERMANY SN 1023-5809 J9 NONLINEAR PROC GEOPH JI Nonlinear Process Geophys. PY 2005 VL 12 IS 3 BP 321 EP 336 PG 16 WC Geochemistry & Geophysics; Meteorology & Atmospheric Sciences SC Geochemistry & Geophysics; Meteorology & Atmospheric Sciences GA 915DK UT WOS:000228277700003 ER PT J AU Keppenne, CL Rienecker, MM Kurkowski, NP Adamec, DA AF Keppenne, CL Rienecker, MM Kurkowski, NP Adamec, DA TI Ensemble Kalman filter assimilation of temperature and altimeter data with bias correction and application to seasonal prediction SO NONLINEAR PROCESSES IN GEOPHYSICS LA English DT Article ID GENERAL-CIRCULATION MODEL; OCEAN MODEL; PACIFIC-OCEAN; FORECAST BIAS; ERROR; IMPLEMENTATION; FLUX AB To compensate for a poorly known geoid, satellite altimeter data is usually analyzed in terms of anomalies from the time mean record. When such anomalies are assimilated into an ocean model, the bias between the climatologies of the model and data is problematic. An ensemble Kalman filter (EnKF) is modified to account for the presence of a forecast-model bias and applied to the assimilation of TOPEX/Poseidon (T/P) altimeter data. The online bias correction (OBC) algorithm uses the same ensemble of model state vectors to estimate biased-error and unbiased-error co-variance matrices. Covariance localization is used but the bias covariances have different localization scales from the unbiased-error covariances, thereby accounting for the fact that the bias in a global ocean model could have much larger spatial scales than the random error. The method is applied to a 27-layer version of the Poseidon global ocean general circulation model with about 30-million state variables. Experiments in which T/P altimeter anomalies are assimilated show that the OBC reduces the RMS observation minus forecast difference for sea-surface height (SSH) over a similar EnKF run in which OBC is not used. Independent in situ temperature observations show that the temperature field is also improved. When the T/P data and in situ temperature data are assimilated in the same run and the configuration of the ensemble at the end of the run is used to initialize the ocean component of the GMAO coupled forecast model, seasonal SSH hindcasts made with the coupled model are generally better than those initialized with optimal interpolation of temperature observations without altimeter data. The analysis of the corresponding sea-surface temperature hindcasts is not as conclusive. C1 Sci Applicat Int Corp, Beltsville, MD 20705 USA. NASA, Goddard Space Flight Ctr, Global Modeling & Assimilat Off, Greenbelt, MD 20771 USA. NASA, Goddard Space Flight Ctr, Oceans & Ice Branch, Lab Hydrospher Proc, Greenbelt, MD 20771 USA. RP Keppenne, CL (reprint author), Sci Applicat Int Corp, 4600 Powder Mill Rd, Beltsville, MD 20705 USA. EM keppenne@gsfc.nasa.gov NR 30 TC 39 Z9 42 U1 1 U2 3 PU EUROPEAN GEOSCIENCES UNION PI KATLENBURG-LINDAU PA MAX-PLANCK-STR 13, 37191 KATLENBURG-LINDAU, GERMANY SN 1023-5809 J9 NONLINEAR PROC GEOPH JI Nonlinear Process Geophys. PY 2005 VL 12 IS 4 BP 491 EP 503 PG 13 WC Geochemistry & Geophysics; Meteorology & Atmospheric Sciences SC Geochemistry & Geophysics; Meteorology & Atmospheric Sciences GA 959GO UT WOS:000231506400008 ER PT J AU Uritsky, VM Klimas, AJ AF Uritsky, VM Klimas, AJ TI Hysteresis-controlled instability waves in a scale-free driven current sheet model SO NONLINEAR PROCESSES IN GEOPHYSICS LA English DT Article ID SELF-ORGANIZED CRITICALITY; AURORAL STREAMERS; PLASMA SHEET; MAGNETOSPHERE; EQUILIBRIUM; MAGNETOTAIL; AVALANCHES AB Magnetospheric dynamics is a complex multiscale process whose statistical features can be successfully reproduced using high-dimensional numerical transport models exhibiting the phenomenon of self-organized criticality (SOC). Along this line of research, a 2-dimensional driven current sheet (DCS) model has recently been developed that incorporates an idealized current-driven instability with a resistive MHD plasma system (Klimas et al., 2004a, b). The dynamics of the DCS model is dominated by the scale-free diffusive energy transport characterized by a set of broadband power-law distribution functions similar to those governing the evolution of multiscale precipitation regions of energetic particles in the nighttime sector of aurora (Uritsky et al., 2002b). The scale-free DCS behavior is supported by localized current-driven instabilities that can communicate in an avalanche fashion over arbitrarily loner distances thus producing current sheet waves (CSW). In this paper we derive the analytical expression for CSW speed as a function of plasma parameters controlling local anomalous resistivity dynamics. The obtained relation indicates that the CSW propagation requires sufficiently high initial current densities, and predicts a deceleration of CSWs moving from inner plasma sheet regions toward its northern and southern boundaries. We also show that the shape of time-averaged current density profile in the DCS model is in agreement with steady-state spatial configuration of critical avalanching models as described by the singular diffusion theory of the SOC. Over shorter time scales, SOC dynamics is associated with rather complex spatial patterns and, in particular, can produce bifurcated current sheets often seen in multi-satellite observations. C1 St Petersburg State Univ, Inst Phys, St Petersburg 198904, Russia. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP St Petersburg State Univ, Inst Phys, St Petersburg 198904, Russia. EM uritsky@geo.phys.spbu.ru NR 23 TC 2 Z9 2 U1 0 U2 0 PU COPERNICUS GESELLSCHAFT MBH PI GOTTINGEN PA BAHNHOFSALLEE 1E, GOTTINGEN, 37081, GERMANY SN 1023-5809 J9 NONLINEAR PROC GEOPH JI Nonlinear Process Geophys. PY 2005 VL 12 IS 6 BP 827 EP 833 PG 7 WC Geochemistry & Geophysics; Meteorology & Atmospheric Sciences SC Geochemistry & Geophysics; Meteorology & Atmospheric Sciences GA 004JR UT WOS:000234749600007 ER PT B AU O'Bryan, MV LaBel, KA Kniffin, SD Poivey, C Howard, JW Ladbury, RL Buchner, SP Oldham, TR Marshall, PW Sanders, AB Kim, HS Hawkins, DK Carts, MA Forney, JD Irwin, T Seidleck, CM Cox, SR Palor, C Petrick, D Powell, W Willits, BL AF O'Bryan, MV LaBel, KA Kniffin, SD Poivey, C Howard, JW Ladbury, RL Buchner, SP Oldham, TR Marshall, PW Sanders, AB Kim, HS Hawkins, DK Carts, MA Forney, JD Irwin, T Seidleck, CM Cox, SR Palor, C Petrick, D Powell, W Willits, BL GP IEEE TI Recent single event effects results for candidate spacecraft electronics for NASA SO NSREC: 2005 IEEE Radiation Effects Data Workshop, Workshop Record LA English DT Proceedings Paper CT IEEE Radiation Effects Data Workshop CY JUL 11-15, 2005 CL Seattle, WA SP IEEE DE Single Event Effects; spacecraft electronics; digital; linear bipolar; and hybrid devices ID PULSED-LASER AB Vulnerability of a variety of candidate spacecraft electronics to proton and heavy ion induced single event effects is studied. Devices tested include digital, linear bipolar, and hybrid devices. C1 NASA, Goddard Space Flight Ctr, Muniz Engn Inc, Greenbelt, MD 20771 USA. RP O'Bryan, MV (reprint author), NASA, Goddard Space Flight Ctr, Muniz Engn Inc, Code 561-4,Bldg 22,Rm 062A, Greenbelt, MD 20771 USA. NR 30 TC 1 Z9 1 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 0-7803-9367-8 PY 2005 BP 26 EP 35 PG 10 WC Engineering, Aerospace; Engineering, Electrical & Electronic; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BDP04 UT WOS:000234645600005 ER PT B AU Irom, F Miyahira, TF AF Irom, F Miyahira, TF GP IEEE TI Test results of single-event effects conducted by the jet propulsion laboratory SO NSREC: 2005 IEEE Radiation Effects Data Workshop, Workshop Record LA English DT Proceedings Paper CT IEEE Radiation Effects Data Workshop CY JUL 11-15, 2005 CL Seattle, WA SP IEEE DE cyclotron; heavy ion; SEE; latchup AB This paper reports recent single-event effects results for a variety of microelectronic devices that include ADC, DAC, DDS, MOSFET driver, analog switch, oscillator, and zero delay buffer. The data was collected to evaluate these devices for possible use in NASA spacecraft. Six of ten devices under study were sensitive to SEL, and the latchup was destructive. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Irom, F (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. 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 0-7803-9367-8 PY 2005 BP 36 EP 41 PG 6 WC Engineering, Aerospace; Engineering, Electrical & Electronic; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BDP04 UT WOS:000234645600006 ER PT B AU Howard, JW LaBel, KA Carts, MA Seidleck, C Gambles, JW Ruggles, SL AF Howard, JW LaBel, KA Carts, MA Seidleck, C Gambles, JW Ruggles, SL GP IEEE TI Validation and testing of design hardening for single event effects using the 8051 microcontroller SO NSREC: 2005 IEEE Radiation Effects Data Workshop, Workshop Record LA English DT Proceedings Paper CT IEEE Radiation Effects Data Workshop CY JUL 11-15, 2005 CL Seattle, WA SP IEEE DE Single Event Effects; Hardened-By-Design; microcontroller; radiation effects AB With the dearth of dedicated radiation hardened foundries, new and novel techniques are being developed for hardening designs using non-dedicated foundry services. In this paper, we will discuss the implications of validating these methods for the single event effects (SEE) in the space environment. Topics include the types of tests that are required and the design coverage (i.e., design libraries: do they need validating for each application?). Finally, an 8051 microcontroller core from NASA Institute of Advanced Microelectronics (IA mu E) CMOS Ultra Low Power Radiation Tolerant (CULPRiT) design is evaluated for SEE mitigative techniques against two commercial 8051 devices. C1 NASA, Goddard Space Flight Ctr, Jackson & Tull Chartered Engineers, Greenbelt, MD 20771 USA. RP Howard, JW (reprint author), NASA, Goddard Space Flight Ctr, Jackson & Tull Chartered Engineers, Code 561-4, Greenbelt, MD 20771 USA. NR 7 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 0-7803-9367-8 PY 2005 BP 85 EP 92 PG 8 WC Engineering, Aerospace; Engineering, Electrical & Electronic; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BDP04 UT WOS:000234645600014 ER PT B AU Koontz, SL Boeder, PA Pankop, C Reddell, B AF Koontz, SL Boeder, PA Pankop, C Reddell, B GP IEEE TI The ionizing radiation environment on the International Space Station: Performance vs. expectations for avionics and materials SO NSREC: 2005 IEEE Radiation Effects Data Workshop, Workshop Record LA English DT Proceedings Paper CT IEEE Radiation Effects Data Workshop CY JUL 11-15, 2005 CL Seattle, WA SP IEEE DE cosmic rays; ionizing radiation; single event upset; spacecraft reliability; total ionizing dose ID FIGURE; MERIT; MODEL AB The role of structural shielding mass in the design, verification, and in-flight performance of International Space Station (ISS), in both the natural and induced orbital ionizing radiation (IR) environments, is reported. C1 NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. RP Koontz, SL (reprint author), NASA, Lyndon B Johnson Space Ctr, Mail Code ES4,2010 NASA Rd 1, Houston, TX 77058 USA. NR 37 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 0-7803-9367-8 PY 2005 BP 110 EP 116 PG 7 WC Engineering, Aerospace; Engineering, Electrical & Electronic; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BDP04 UT WOS:000234645600018 ER PT B AU Miyahira, TF Rax, BG Johnston, AH AF Miyahira, TF Rax, BG Johnston, AH GP IEEE TI Total dose degradation of low-dropout voltage regulators SO NSREC: 2005 IEEE Radiation Effects Data Workshop, Workshop Record LA English DT Proceedings Paper CT IEEE Radiation Effects Data Workshop CY JUL 11-15, 2005 CL Seattle, WA SP IEEE AB A low dropout voltage regulator that uses a lateral pnp transistor as a pass transistor in the output stage is evaluated for total dose degradation. Degradation occurs from two different mechanisms, one involving gradual degradation due to changes in internal reference voltage resulting in small changes in output voltage saturation characteristics; and the other causing the output voltage to fall to nearly zero because of gain degradation in the lateral pup output transistor. Additionally, wide variability was observed between two different lots of devices, produced approximately 18 months apart. This illustrates the importance of lot-sample testing when these highly sensitive devices are considered for use in space. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Miyahira, TF (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 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 BN 0-7803-9367-8 PY 2005 BP 127 EP 131 PG 5 WC Engineering, Aerospace; Engineering, Electrical & Electronic; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BDP04 UT WOS:000234645600021 ER PT B AU Chavez, RM Rax, BG Scheick, LZ Johnston, AH AF Chavez, RM Rax, BG Scheick, LZ Johnston, AH GP IEEE TI Total ionizing dose effects in bipolar and BiCMOS devices SO NSREC: 2005 IEEE Radiation Effects Data Workshop, Workshop Record LA English DT Proceedings Paper CT IEEE Radiation Effects Data Workshop CY JUL 11-15, 2005 CL Seattle, WA SP IEEE DE bipolar; complementary metal oxide semiconductor (CMOS); enhanced low dose rate sensitivity (ELDRS); low dose level (LDL); and total ionizing dose (TID) AB This paper describes Total Ionizing Dose (TID) test results performed at JPL. Bipolar and BiCMOS device samples were tested exhibiting significant degradation and failures at different irradiation levels. Linear technology which is susceptible to low-dose dependency (ELDRS) exhibited greater damage for devices tested under zero bias condition. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Chavez, RM (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. 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 BN 0-7803-9367-8 PY 2005 BP 144 EP 148 PG 5 WC Engineering, Aerospace; Engineering, Electrical & Electronic; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BDP04 UT WOS:000234645600024 ER PT B AU Cochran, DJ Kniffin, SD Ladbury, RL O'Bryan, MV Poivey, CF Kim, H Irwin, TL Phan, AM Carts, MA Forney, JD Howard, JW DiBari, RC Buchner, SP Palor, CD Label, KA Reed, RA Sanders, AB Hawkins, DK Cox, SR AF Cochran, DJ Kniffin, SD Ladbury, RL O'Bryan, MV Poivey, CF Kim, H Irwin, TL Phan, AM Carts, MA Forney, JD Howard, JW DiBari, RC Buchner, SP Palor, CD Label, KA Reed, RA Sanders, AB Hawkins, DK Cox, SR GP IEEE TI Recent total ionizing dose results and displacement damage results for candidate spacecraft electronics for NASA SO NSREC: 2005 IEEE Radiation Effects Data Workshop, Workshop Record LA English DT Proceedings Paper CT IEEE Radiation Effects Data Workshop CY JUL 11-15, 2005 CL Seattle, WA SP IEEE AB We present data on the vulnerability of a variety of candidate spacecraft electronics to total ionizing dose and displacement damage. Devices tested include optoelectronics, digital, analog, linear bipolar devices, hybrid devices, Analog-to-Digital Converters (ADCs), and Digital-to-Analog Converters (DACs), among others. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Cochran, DJ (reprint author), NASA, Goddard Space Flight Ctr, Code 561-4, Greenbelt, MD 20771 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 0-7803-9367-8 PY 2005 BP 149 EP 155 PG 7 WC Engineering, Aerospace; Engineering, Electrical & Electronic; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BDP04 UT WOS:000234645600025 ER PT J AU Bell, NF AF Bell, NF TI Neutrino mixing and cosmology SO NUCLEAR PHYSICS B-PROCEEDINGS SUPPLEMENTS LA English DT Article; Proceedings Paper CT 8th International Workshop on Topics in Astroparticle and Underground Physics CY SEP 05-09, 2003 CL Seattle, WA ID FLAVOR OSCILLATIONS; EARLY UNIVERSE; DEGENERACY AB We review the consequences of neutrino mixing in the early universe. For both active-sterile mixing or mixing between three active neutrinos only, the consequences of oscillations depend crucially upon the size of the universe's lepton number (relic neutrino asymmetry.) C1 NASA, Fermi Natl Accelerator Lab, Fermilab Astrophys Ctr, Batavia, IL 60510 USA. RP Bell, NF (reprint author), NASA, Fermi Natl Accelerator Lab, Fermilab Astrophys Ctr, POB 500, Batavia, IL 60510 USA. EM nfb@fnal.gov NR 22 TC 1 Z9 1 U1 0 U2 0 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS SN 0920-5632 J9 NUCL PHYS B-PROC SUP JI Nucl. Phys. B-Proc. Suppl. PD JAN PY 2005 VL 138 BP 76 EP 78 DI 10.1016/j.nuclphysbps.2004.11.018 PG 3 WC Physics, Particles & Fields SC Physics GA 895FA UT WOS:000226845100018 ER PT J AU Beck-Winchatz, BN AF Beck-Winchatz, BN TI Involvement of scientists in the NASA Office of Space Science education and public outreach program SO NUCLEAR PHYSICS B-PROCEEDINGS SUPPLEMENTS LA English DT Article; Proceedings Paper CT 8th International Workshop on Topics in Astroparticle and Underground Physics CY SEP 05-09, 2003 CL Seattle, WA AB Since the mid-1990's NASA's Office of Space Science (OSS) has embarked on an astronomy and space science education and public outreach (E/PO) program. Its goals are to share the excitement of space science discoveries with the public, and to enhance the quality of science, mathematics and technology education, particularly at the precollege level. A key feature of the OSS program is the direct involvement of space scientists. The majority of the funding for E/PO is allocated to flight missions, which spend 1%-2% of their total budget on E/PO, and to individual research grants. This paper presents an overview of the program's goals, objectives, philosophy, and infrastructure. C1 De Paul Univ, NASA, Space Sci Ctr Educ & Publ Outreach, Chicago, IL 60614 USA. RP Beck-Winchatz, BN (reprint author), De Paul Univ, NASA, Space Sci Ctr Educ & Publ Outreach, 990 W Fullerton,Suite 4400, Chicago, IL 60614 USA. NR 7 TC 1 Z9 1 U1 0 U2 0 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS SN 0920-5632 J9 NUCL PHYS B-PROC SUP JI Nucl. Phys. B-Proc. Suppl. PD JAN PY 2005 VL 138 BP 451 EP 453 DI 10.1016/j.nuclphysbps.2004.11.104 PG 3 WC Physics, Particles & Fields SC Physics GA 895FA UT WOS:000226845100104 ER PT J AU Hart, CE Sharenbroich, L Bornstein, BJ Trout, D King, B Mjolsness, E Wold, BJ AF Hart, CE Sharenbroich, L Bornstein, BJ Trout, D King, B Mjolsness, E Wold, BJ TI A mathematical and computational framework for quantitative comparison and integration of large-scale gene expression data SO NUCLEIC ACIDS RESEARCH LA English DT Article ID CELL-CYCLE; SACCHAROMYCES-CEREVISIAE; HO GENE; YEAST; TRANSCRIPTION; PATTERNS; CLASSIFICATION; ALGORITHM; CANCER AB Analysis of large-scale gene expression studies usually begins with gene clustering. A ubiquitous problem is that different algorithms applied to the same data inevitably give different results, and the differences are often substantial, involving a quarter or more of the genes analyzed. This raises a series of important but nettlesome questions: How are different clustering results related to each other and to the underlying data structure? Is one clustering objectively superior to another? Which differences, if any, are likely candidates to be biologically important? A systematic and quantitative way to address these questions is needed, together with an effective way to integrate and leverage expression results with other kinds of large-scale data and annotations. We developed a mathematical and computational framework to help quantify, compare, visualize and interactively mine clusterings. We show that by coupling confusion matrices with appropriate metrics ( linear assignment and normalized mutual information scores), one can quantify and map differences between clusterings. A version of receiver operator characteristic analysis proved effective for quantifying and visualizing cluster quality and overlap. These methods, plus a flexible library of clustering algorithms, can be called from a new expandable set of software tools called CompClust 1.0 (http://woldlab.caltech.edu/compClust/). CompClust also makes it possible to relate expression clustering patterns to DNA sequence motif occurrences, protein-DNA interaction measurements and various kinds of functional annotations. Test analyses used yeast cell cycle data and revealed data structure not obvious under all algorithms. These results were then integrated with transcription motif and global protein-DNA interaction data to identify G(1) regulatory modules. C1 CALTECH, Div Biol, Pasadena, CA 91125 USA. Jet Prop Lab, Machine Learning Syst Grp, Pasadena, CA 91109 USA. Univ Calif Irvine, Sch Informat & Comp Sci, Irvine, CA 92697 USA. Univ Calif Irvine, Inst Genom & Bioinformat, Irvine, CA 92697 USA. RP Wold, BJ (reprint author), CALTECH, Div Biol, Pasadena, CA 91125 USA. EM woldb@caltech.edu NR 31 TC 7 Z9 7 U1 0 U2 4 PU OXFORD UNIV PRESS PI OXFORD PA GREAT CLARENDON ST, OXFORD OX2 6DP, ENGLAND SN 0305-1048 J9 NUCLEIC ACIDS RES JI Nucleic Acids Res. PY 2005 VL 33 IS 8 BP 2580 EP 2594 DI 10.1093/nar/gki536 PG 15 WC Biochemistry & Molecular Biology SC Biochemistry & Molecular Biology GA 926HC UT WOS:000229113100033 PM 15886390 ER PT J AU Canuto, VM Dubovikov, MS AF Canuto, VM Dubovikov, MS TI Modeling mesoscale eddies SO OCEAN MODELLING LA English DT Article ID OCEAN CIRCULATION MODELS; RESIDUAL-MEAN VELOCITY; EDDY KINETIC-ENERGY; POTENTIAL VORTICITY; DYNAMICAL MODEL; GENERAL-CIRCULATION; SATELLITE ALTIMETRY; TRACER TRANSPORTS; STOCHASTIC-THEORY; BOLUS VELOCITY AB Mesoscale eddies are not resolved in coarse resolution ocean models and must be modeled. They affect both mean momentum and scalars. At present, no generally accepted model exists for the former; in the latter case, mesoscales are modeled with a bolus velocity u(*) to represent a sink of mean potential energy. However, comparison of u(*)(model) vs. u(*)(eddy resolving code, [J. Phys. Ocean. 29 (1999) 2442]) has shown that u(*)(model) is incomplete and that additional terms, "unrelated to thickness source or sinks", are required. Thus far, no form of the additional terms has been suggested. To describe mesoscale eddies, we employ the Navier-Stokes and scalar equations and a turbulence model to treat the non-linear interactions. We then show that the problem reduces to an eigenvalue problem for the mesoscale Bernoulli potential. The solution, which we derive in analytic form, is used to construct the momentum and thickness fluxes. In the latter case, the bolus velocity u(*) is found to contain two types of terms: the first type entails the gradient of the mean potential vorticity and represents a positive contribution to the production of mesoscale potential energy; the second type of terms, which is new, entails the velocity of the mean flow and represents a negative contribution to the production of mesoscale potential energy, or equivalently, a backscatter process whereby a fraction of the mesoscale potential energy is returned to the original reservoir of mean potential energy. This type of terms satisfies the physical description of the additional terms given by [J. Phys. Ocean. 29 (1999) 2442]. The mesoscale flux that enters the momentum equations is also contributed by two types of terms of the same physical nature as those entering the thickness flux. The potential vorticity flux is also shown to contain two types of terms: the first is of the gradient-type while the other terms entail the velocity of the mean flow. An expression is derived for the mesoscale diffusivity kappa(M) and for the mesoscale kinetic energy K in terms of the large-scale fields. The predicted kappa(M)(z) agrees with that of heuristic models. The complete mesoscale model in isopycnal coordinates is presented in Appendix D and can be used in coarse resolution ocean global circulation models. (C) 2003 Elsevier Ltd. All rights reserved. C1 NASA, Goddard Inst Space Studies, New York, NY 10025 USA. Columbia Univ, Dept Appl Phys & Math, New York, NY 10027 USA. Columbia Univ, Ctr Climate Syst Res, New York, NY 10025 USA. RP Canuto, VM (reprint author), NASA, Goddard Inst Space Studies, 2880 Broadway, New York, NY 10025 USA. EM vcanuto@giss.nasa.gov NR 62 TC 15 Z9 16 U1 0 U2 5 PU ELSEVIER SCI LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD OX5 1GB, OXON, ENGLAND SN 1463-5003 J9 OCEAN MODEL JI Ocean Model. PY 2005 VL 8 IS 1-2 BP 1 EP 30 DI 10.1016/j.ocemod.2003.11.003 PG 30 WC Meteorology & Atmospheric Sciences; Oceanography SC Meteorology & Atmospheric Sciences; Oceanography GA 862TX UT WOS:000224515100001 ER PT S AU Moisan, TA Atkinson, LP Blanco, JL Boicourt, W Hooker, S Makinen, C Moisan, JR Mannino, A Mitra, M Mulholland, M Nolan, J Russ, M Swift, RW Tester, PA AF Moisan, Tiffany A. Atkinson, Larry P. Blanco, Jose Luis Boicourt, William Hooker, Stanford Makinen, Carla Moisan, John R. Mannino, Antonio Mitra, Madhumi Mulholland, Margaret Nolan, Jessica Russ, Mary Swift, Robert W. Tester, Patricia A. TI Bio-physical interactions in ocean margin ecosystems (BIOME): Understanding coastal dynamics in the southern Mid-Atlantic Bight SO OCEANS 2005, VOLS 1-3 SE OCEANS-IEEE LA English DT Proceedings Paper CT Oceans 2005 Conference CY SEP 17-23, 2005 CL Washington, DC SP IEEE AB Coastal regions within the Mid-Atlantic Bight (MAB) are significantly influenced by regional freshwater fluxes emanating from several large bay systems, most notably the Hudson-Raritan river systems, the Delaware and Chesapeake Bays. The outflows from these bays have high sediment loads and high levels of nutrients, particulate and dissolved organic matter (POM and DOM) associated with them which strongly influence the adjacent coastal margin ecosystems. Our research and observational effort includes the development and deployment of an observing system aimed at characterizing and monitoring the influence of the Chesapeake Bay on the adjacent coastal ocean margin ecosystem. A primary focus of this effort is to develop and apply state-of-the-art technologies and methodologies to support research, observation, monitoring, and management applications in the coastal ocean. We have developed a program that addresses coastal spatial and temporal scales. Our observing system consists of four components including 1) High Frequency (HF) Radar: 3 long-range HF Radar systems for mapping coastal ocean surface currents along Delmarva and 2 standard-range systems for the Chesapeake Bay mouth region, 2) a Coastal Ocean Biooptical buoY (COBY), which will be deployed southeast of the Maryland-Virginia border at about 40m water depth, and will be instrumented with an above-water spectroradiometer (19 channel UV-VIS-NM 10nm BW, sea- and sky-viewing radiometers plus solar reference) on a robotic arm to measure water-leaving radiances, meteorological package, in-water mooring instruments with ADCP, CTD, nitrate sensor, ac-9, ac-s. and fluorometers for chlorophyll, colored dissolved organic matter (CDOM) and phycoerythrin detection; 3) seasonal cruises in the Mid-Atlantic Bight collecting optical, biological, and chemical data; and 4) the Ocean-Atmosphere Sensor Integration System (OASIS), which is comprised of a fleet (6-12) of solar-powered surface autonomous vehicles deployed offshore to measure surface ocean currents, meteorological measurements, surface ocean salinity and temperature, air-sea CO(2) fluxes, waterleaving radiances, chlorophyll and CDOM fluorescence, HAB detection, etc. The HF radars, COBY and OASIS are being deployed this summer, with plans for a fully deployed observing system by the end of 2005 or early 2006. C1 NASA, Goddard Space Flight Ctr, Wallops Isl, VA 23337 USA. RP Moisan, TA (reprint author), NASA, Goddard Space Flight Ctr, Wallops Isl, VA 23337 USA. RI Hooker, Stanford/E-2162-2012; Mulholland, Margaret/E-8480-2011; Moisan, John/B-8762-2016 OI Mulholland, Margaret/0000-0001-8819-189X; Moisan, John/0000-0002-8078-8939 NR 9 TC 1 Z9 1 U1 0 U2 4 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 0197-7385 BN 0-933957-34-3 J9 OCEANS-IEEE PY 2005 BP 2830 EP 2837 PG 8 WC Engineering, Ocean; Oceanography SC Engineering; Oceanography GA BEQ88 UT WOS:000238978702163 ER PT J AU Sellar, RG Boreman, GD AF Sellar, RG Boreman, GD TI Classification of imaging spectrometers for remote sensing applications SO OPTICAL ENGINEERING LA English DT Article DE imaging spectrometry; imaging spectrometer; hyperspectral imaging; hyperspectral imagery; hyperspectral imager; remote sensing ID DESIGN; ARRAY AB The continuing development of new and fundamentally different classes of imaging spectrometers has increased the complexity of the field of imaging spectrometry. The rapid pace at which new terminology is introduced to describe the new types of imaging spectrometers sometimes leads to confusion, particularly in discussions of the relative merits of the different types. In some cases, multiple different terms are commonly used to describe the same fundamental approach, and it is not always clear when these terms are synonymous. Other terminology in common use is overly broad. When a single term may encompass instruments that operate in fundamentally different ways, important distinctions may be obscured. In the interest of clarifying the terminology used in imaging spectrometry, we present a comprehensive system for classification of imaging spectrometers based on two fundamental properties: the method by which they scan the object spatially, and the method by which they obtain spectral information. (C) 2005 Society of PhotoOptical Instrumentation Engineers. C1 Univ Cent Florida, Dept Phys, Orlando, FL 32826 USA. Univ Cent Florida, CREOL, Sch Opt, Orlando, FL 32816 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 9 TC 56 Z9 58 U1 4 U2 19 PU SPIE-INT SOCIETY OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98225 USA SN 0091-3286 J9 OPT ENG JI Opt. Eng. PD JAN PY 2005 VL 44 IS 1 AR 013602 DI 10.1117/1.1813441 PG 3 WC Optics SC Optics GA 904IP UT WOS:000227489600006 ER PT S AU Chao, TH Hanan, J Zhou, HY Reyes, G AF Chao, TH Hanan, J Zhou, HY Reyes, G BE Casasent, DP Chao, TH TI Portable 512 x 512 grayscale optical correlator SO OPTICAL PATTERN RECOGNITION XVI SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Optical Pattern Recognition XVI CY MAR 31-APR 01, 2005 CL Orlando, FL SP SPIE DE 512 x 512 Grayscale Optical Correlator; automatic target recognition AB JPL has developed a compact portable 512 x 512 Grayscale Optical Correlator [1-4] by integrating a pair of 512 x 512 Ferroelectric Spatial Light Modulator (FLCSLM), a red diode laser, Fourier optics, a CMOS photodetector array. The system is designed to operate at the maximum speed of 1000 frames per second. A FPGA card was custom programmed to perform peak-detection post-processing to accommodate the system throughput rate. Custom mechanical mounting brackets were designed miniaturized the optics head of the GOC into a 6" x 3.5" x 2" volume. The device driver HW/SW is installed in a customized PC. The GOC system's portability has been demonstrated by shipping it to various locations for target recognition testing. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Tien-Hsin.Chao@jpl.nasa.gov NR 6 TC 2 Z9 2 U1 0 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 0-8194-5801-5 J9 PROC SPIE PY 2005 VL 5816 BP 23 EP 31 DI 10.1117/12.607965 PG 9 WC Computer Science, Artificial Intelligence; Optics SC Computer Science; Optics GA BCK97 UT WOS:000229800200003 ER PT S AU Zhou, HY Huglet, C Hanan, JC Lu, T Chao, TH AF Zhou, HY Huglet, C Hanan, JC Lu, T Chao, TH BE Casasent, DP Chao, TH TI Development of streamlined OT-MACH based ATR algorithm for grayscale optical correlator SO Optical Pattern Recognition XVI SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Optical Pattern Recognition XVI CY MAR 31-APR 01, 2005 CL Orlando, FL SP SPIE DE filter synthesis; gray-scale optical correlator ID FILTERS AB JPL is developing an Advanced Autonomous Target Recognition (AATR) technology to significantly reduce broad area search workload for imagery analysts. One of the algorithms to be delivered, as part of JPL ATR Development and Evaluation (JADE) project, is the OT-MACH based ATR algorithm software package for grayscale optical correlator. In this paper we describe the basic features and functions of the software package as currently implemented. Automation of filter synthesis and test for GOC, particularly the automation of OT-MACH parameter optimization, is discussed. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Zhou, HY (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 9 TC 7 Z9 7 U1 0 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 0-8194-5801-5 J9 P SOC PHOTO-OPT INS PY 2005 VL 5816 BP 78 EP 83 DI 10.1117/12.607969 PG 6 WC Computer Science, Artificial Intelligence; Optics SC Computer Science; Optics GA BCK97 UT WOS:000229800200008 ER PT S AU Chao, TH Zhou, HY Xia, XW Serati, S AF Chao, TH Zhou, HY Xia, XW Serati, S BE Casasent, DP Chao, TH TI Near IR electro-optic imaging Fourier transform spectrometer SO Optical Pattern Recognition XVI SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Optical Pattern Recognition XVI CY MAR 31-APR 01, 2005 CL Orlando, FL SP SPIE DE hyperspectral imaging; solid-state imaging Fourier transform spectrometer; birefringent phase retarder; liquid crystal achromatic phase switch AB JPL and BNS Inc. are jointly developing a compact, low mass, Electro-Optic Imaging Fourier Transform Spectrometer (E-O IFTS) for hyperspectral imaging applications [6]. The spectral region of this spectrometer is in the near IR spectral band of 1 - 2.5 mu m (1000 - 4000 cm(-1)) to allow high-resolution, high-speed hyperspectral imaging applications. The specific applications for NASA's missions will focus on the measurement of a large number of different atmospheric gases simultaneously in the same airmass. Due to the use of a combination of birefringent phase retarders (YVO4) and multiple achromatic phase switches to achieve phase delay, this spectrometer is capable of hyperspectral measurements similar to that of the conventional Fourier transform spectrometer but without any moving parts. In this paper, the principle of operations, system architecture and recent technical progress will be presented. C1 Jet Prop Lab, Pasadena, CA 91109 USA. RP Chao, TH (reprint author), Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 6 TC 9 Z9 9 U1 0 U2 5 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-5801-5 J9 P SOC PHOTO-OPT INS PY 2005 VL 5816 BP 163 EP 172 DI 10.1117/12.607968 PG 10 WC Computer Science, Artificial Intelligence; Optics SC Computer Science; Optics GA BCK97 UT WOS:000229800200017 ER PT S AU Gubarev, M Alexander, C Ramsey, B AF Gubarev, Mikhail Alexander, Cheryl Ramsey, Brian BE Citterio, O ODell, SL TI Alignment, Assembly and Testing of High-Energy X-Ray Optics SO OPTICS FOR EUV, X-RAY, AND GAMMA-RAY ASTRONOMY II SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Optics for EUV, X-Ray and Gamma-Ray Astronomy II CY AUG 03, 2005 CL San Diego, CA DE x-ray astronomy instrumentation; x-ray optics; x-ray optics alignment AB We are developing grazing incidence x-ray imaging optics for a balloon-borne hard x-ray telescope ( HERO). The HERO payload, scheduled for launch in May 2006, consists of 8 mirror modules with 12 mirror shells each fabricated using electroform-nickel replication off super polished cylindrical mandrels. An optical system for alignment and assembly of the shells into their modules will be described together with an assessment of the systematic errors associated with this process. Full details of the assembly procedures and results of the on-ground x-ray testing of the HERO modules will be provided. C1 [Gubarev, Mikhail] NASA MSFC, Univ Space Res Assoc, XD 30, Huntsville, AL 35812 USA. RP Gubarev, M (reprint author), NASA MSFC, Univ Space Res Assoc, XD 30, Huntsville, AL 35812 USA. EM Mikhail.Gubarev@msfc.nasa.gov NR 3 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 978-0-8194-5905-3 J9 PROC SPIE PY 2005 VL 5900 AR 59000T DI 10.1117/12.614997 PG 7 WC Astronomy & Astrophysics; Optics SC Astronomy & Astrophysics; Optics GA BRX39 UT WOS:000283844000027 ER PT S AU Lehan, JP Hadjimichael, T Content, DA Zhang, WW AF Lehan, J. P. Hadjimichael, T. Content, D. A. Zhang, W. W. BE Citterio, O ODell, SL TI Design and fabrication of refractive nulls for testing the segmented mirrors of the Constellation-X spectroscopy x-ray telescope (SXT) SO OPTICS FOR EUV, X-RAY, AND GAMMA-RAY ASTRONOMY II SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Optics for EUV, X-Ray and Gamma-Ray Astronomy II CY AUG 03, 2005 CL San Diego, CA DE Optical testing; lens design; Constellation-X; x-ray telescope; OAP AB We designed a refractive null lens for (visible) optical testing of the segmented mirrors for the Constellation-X spectroscopy x-ray telescope. We explored two solution families and identified the trade-offs. We also present some initial results of the realization of one solution family. C1 [Lehan, J. P.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Lehan, JP (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. EM lehan@lheapop.gsfc.nasa.gov NR 6 TC 3 Z9 3 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 978-0-8194-5905-3 J9 PROC SPIE PY 2005 VL 5900 AR 59001D DI 10.1117/12.615316 PG 7 WC Astronomy & Astrophysics; Optics SC Astronomy & Astrophysics; Optics GA BRX39 UT WOS:000283844000046 ER PT S AU Owens, SM Gum, JS Tarrio, C Grantham, S Dvorak, J Kjornrattanawanich, B Keski-Kuha, R Thomas, RJ Kankelborg, CC AF Owens, Scott M. Gum, Jeffery S. Tarrio, Charles Grantham, Steven Dvorak, Joseph Kjornrattanawanich, Benjawan Keski-Kuha, Ritva Thomas, Roger J. Kankelborg, Charles C. BE Citterio, O ODell, SL TI Narrow-band EUV multilayer coating for the MOSES sounding rocket SO OPTICS FOR EUV, X-RAY, AND GAMMA-RAY ASTRONOMY II SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Optics for EUV, X-Ray and Gamma-Ray Astronomy II CY AUG 03, 2005 CL San Diego, CA DE EUV multilayers; narrow band multilayers; B(4)C/Mg(2)Si ID SPECTROGRAPH; FILMS AB The Multi-order Solar EUV Spectrograph (MOSES) is a slitless spectrograph designed to study solar He II emission at 303.8 angstrom (1 angstrom = 0.1 nm), to be launched on a sounding rocket payload. One difference between MOSES and other slitless spectrographs is that the images are recorded simultaneously at three spectral orders, m = -1, 0, +1. Another is the addition of a narrow-band multilayer coating on both the grating and the fold flat, which will reject out-of-band lines that normally contaminate the image of a slitless instrument. The primary metrics for the coating were high peak reflectivity and suppression of Fe XV and XVI emission lines at 284 angstrom and 335 angstrom, respectively. We chose B(4)C/Mg(2)Si for our material combination since it provides excellent peak reflectivity and rejection of out-of-band wavelengths. Measurements of witness flats at NIST indicate the peak reflectivity at 303.8 is 39.0% for a 15 bilayer stack, while suppression ranges from 7.5x to 12.9x at 284 angstrom and from 3.4x to 15.1x at 335 angstrom for the individual reflections in the optical path. We present the results of coating the MOSES flight gratings and fold flat, including the spectral response of the fold flat and grating as measured at NIST's SURF III and Brookhaven's X24C beamline, respectively. C1 [Owens, Scott M.; Gum, Jeffery S.; Keski-Kuha, Ritva; Thomas, Roger J.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Owens, SM (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. EM Scott.Owens@nasa.gov NR 9 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 978-0-8194-5905-3 J9 PROC SPIE PY 2005 VL 5900 AR 590003 DI 10.1117/12.617520 PG 9 WC Astronomy & Astrophysics; Optics SC Astronomy & Astrophysics; Optics GA BRX39 UT WOS:000283844000002 ER PT S AU Petre, R Lehan, J O'Dell, S Owens, S Reid, PB Saha, T Stewart, J Jones, WD Zhang, W AF Petre, Robert Lehan, John O'Dell, Stephen Owens, Scott Reid, Paul B. Saha, Timo Stewart, Jeff Jones, William D. Zhang, William BE Citterio, O ODell, SL TI Technology Development for the Constellation-X Spectroscopy X-Ray Telescope SO OPTICS FOR EUV, X-RAY, AND GAMMA-RAY ASTRONOMY II SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Optics for EUV, X-Ray and Gamma-Ray Astronomy II CY AUG 03, 2005 CL San Diego, CA DE X-ray mirrors; Constellation-X ID MISSION AB The Constellation-X Spectroscopy X-ray Telescope (SXT) is a large diameter, high throughput, grazing incidence imaging mirror system, designed to perform high sensitivity spectroscopy of cosmic X-ray sources in the 0.2-10.0 keV band. The baseline effective area requirement is similar to 3 m(2) at 1 keV. The system-level angular-resolution requirement is a 15-arcseconds half-power diameter, with a 5-arcsecond goal. The effective area is attained through a modular design, involving the nesting of many confocal, thin-walled Wolter I mirror segments. Considerable progress has been made in developing thin, thermally formed, glass mirror substrates that meet or better the angular-resolution requirement. Several approaches to mounting and aligning reflector segments into a mirror system are under investigation. We report here on the progress of the SXT technology development program toward reaching the performance goals. C1 [Petre, Robert; Lehan, John; Zhang, William] NASA GSFC, Xray Astrophys Lab, Greenbelt, MD 20771 USA. RP Petre, R (reprint author), NASA GSFC, Xray Astrophys Lab, Code 662, Greenbelt, MD 20771 USA. EM robert.petre-1@nasa.gov RI Zhang, William/D-3535-2012; OI O'Dell, Stephen/0000-0002-1868-8056 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 978-0-8194-5905-3 J9 PROC SPIE PY 2005 VL 5900 AR 59000U DI 10.1117/12.615172 PG 8 WC Astronomy & Astrophysics; Optics SC Astronomy & Astrophysics; Optics GA BRX39 UT WOS:000283844000028 ER PT S AU Zhang, WW Content, DA Lehan, JP Petre, R Saha, TT Gubarev, M Jones, WD O'Dell, SL AF Zhang, William W. Content, David A. Lehan, John P. Petre, Robert Saha, Timo T. Gubarev, Mikhail Jones, William D. O'Dell, Stephen L. BE Citterio, O ODell, SL TI Development of Lightweight X-Ray Mirrors for the Constellation-X Mission SO OPTICS FOR EUV, X-RAY, AND GAMMA-RAY ASTRONOMY II SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Optics for EUV, X-Ray and Gamma-Ray Astronomy II CY AUG 03, 2005 CL San Diego, CA DE X-ray optics; lightweight optics; Constellation-X; space optics ID PERFORMANCE; DESIGN; OPTICS AB The Constellation-X mission's Spectroscopic X-Ray Telescopes (SXT) [1] require an angular resolution of 15" half-power diameter (HPD) with extremely lightweight grazing incidence mirrors. The areal density of the mirror must be about 1 kg/m(2) or less. In comparison with the state of the art X-ray mirrors represented by the XMM/Newton telescopes, this is approximately an order of magnitude less in mass areal density while maintaining the same angular resolution. We use a precision glass forming technique to fabricate mirrors that are 0.4mm thick and optical metrology to demonstrate that these mirrors can meet the stringent figure and micro-roughness requirements of the Constellation-X mission. We expect in the next few years to significantly improve the production yield and mirror quality to meet the goal of the mission, which is 5" HPD for two reflections at the same mass. C1 [Zhang, William W.; Content, David A.; Lehan, John P.; Petre, Robert; Saha, Timo T.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Zhang, WW (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. OI O'Dell, Stephen/0000-0002-1868-8056 NR 12 TC 1 Z9 1 U1 0 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 978-0-8194-5905-3 J9 PROC SPIE PY 2005 VL 5900 AR 59000V DI 10.1117/12.614462 PG 11 WC Astronomy & Astrophysics; Optics SC Astronomy & Astrophysics; Optics GA BRX39 UT WOS:000283844000029 ER PT J AU Love, GD Bowden, SA Jahnke, LL Snape, CE Campbell, CN Day, JG Summons, RE AF Love, GD Bowden, SA Jahnke, LL Snape, CE Campbell, CN Day, JG Summons, RE TI A catalytic hydropyrolysis method for the rapid screening of microbial cultures for lipid biomarkers SO ORGANIC GEOCHEMISTRY LA English DT Article ID COCCOLITHOPHORID EMILIANIA-HUXLEYI; TEMPERATURE-PROGRAMMED REDUCTION; ALGA BOTRYOCOCCUS-BRAUNII; RESISTANT BIO-POLYMER; ORGANIC SULFUR FORMS; LONG-CHAIN ALKENES; FATTY-ACID; L-RACE; HALOBACTERIUM-SACCHAROVORUM; ALIPHATIC POLYALDEHYDE AB A catalytic hydropyrolysis procedure was developed for rapidly assessing the relative abundances and variety of different biomarker lipid structures in microbial cultures by reductively converting free functionalised and polymeric lipids within whole cells into hydrocarbons. High pressure hydrogen gas and a molybdenum catalyst were used to target and cleave carbon-oxygen covalent bonds (particularly ester, alcohol. acid and ether) and the pyrolysis process was conducted in an open-system reactor configuration to minimise structural and stereochemical rearrangements in the products. A revised experimental protocol, involving a modified catalyst-loading procedure. careful use of a silica support substrate and a revised temperature program was tested and optimised for handling biomass. Partial hydrogenation of double bonds inevitably did occur although it was found that some unsaturation was preserved, particularly within branched and polycyclic hydrocarbon structures. This experimental approach aids our ability to optimally correlate fossil biomarker signals found in the sedimentary record with their lipid precursors found in extant organisms. Our technique complements more rigorous, but time-consuming, chemical approaches used for elucidating the exact chemical structures of intact functionalised lipids by providing a rapid means by which to screen microbial cultures. (C) 2004 Elsevier Ltd. All rights reserved. C1 MIT, Dept Earth Atmospher & Planetary Sci, Cambridge, MA 01239 USA. Univ Newcastle Upon Tyne, Sch Civil Engn & Geosci, Fossil Fuels & Environm Geochem, Newcastle Upon Tyne NE1 7RU, Tyne & Wear, England. NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. Univ Nottingham, Sch Chem Environm & Min Engn, Nottingham NG7 2RD, England. Scottish Assoc Marine Sci, Dunstaffnage Marine Lab Culture Collect Algae & P, Oban PA37 1QA, Argyll, Scotland. RP Love, GD (reprint author), MIT, Dept Earth Atmospher & Planetary Sci, E34-550, Cambridge, MA 01239 USA. EM glove@mit.edu RI Day, John/N-5913-2014; OI Snape, Colin/0000-0002-6671-8766 NR 83 TC 22 Z9 23 U1 0 U2 8 PU PERGAMON-ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0146-6380 J9 ORG GEOCHEM JI Org. Geochem. PY 2005 VL 36 IS 1 BP 63 EP 82 DI 10.1016/j.orggeochem.2004.07.010 PG 20 WC Geochemistry & Geophysics SC Geochemistry & Geophysics GA 888WT UT WOS:000226405600005 ER PT J AU Vrtovec, B Sinkovec, M Starc, V Radovancevic, B Schlegel, TT AF Vrtovec, B Sinkovec, M Starc, V Radovancevic, B Schlegel, TT TI Coronary artery disease alters ventricular repolarization dynamics in type 2 diabetes SO PACE-PACING AND CLINICAL ELECTROPHYSIOLOGY LA English DT Article; Proceedings Paper CT Cardiostim 2004 Meeting CY JUN 16-19, 2004 CL Nice, FRANCE DE diabetes; coronary artery disease; ventricular repolarization; QT-interval ID QT INTERVAL VARIABILITY; AUTONOMIC NEUROPATHY; HEART-DISEASE; DISPERSION; DURATION; INSULIN; PROLONGATION; PREVALENCE; ISCHEMIA; IDENTIFY AB Ventricular repolarization dynamics (VRD) is an important predictor of outcome in diabetes. We examined the potential impact of coronary artery disease (CAD) on VRD in type 2 diabetic patients. We recorded 5-minute high-resolution resting electrocardiograms in 38 diabetic patients undergoing elective coronary angiography, and in 38 age- and gender-matched apparently healthy subjects (controls). Using leads-I and -II, time-domain indices of VRD were calculated. Coronary angiography was regarded as positive if greater than or equal to 50% stenosis was found. Angiography was positive in 21 diabetic patients (55%). Patients with CAD had a significantly higher degree of VRD than controls (SDNN(QT): 15.81 +/- 7.22 ms versus 8.94 +/- 6.04 ms; P < 0.001, rMSSD(QT): 21.02 +/- 7.07 ms versus 11.18 +/- 7.45 ms; P < 0.001). Ventricular repolarization dynamics in diabetic patients with negative angiograms did not differ from VRD in controls (SDNN(QT): 8.94 +/- 6.04 ms versus 7.44 +/- 5.72 ms; P = 0.67, rMSSD(QT): 11.18 +/- 7.45 ms versus 10.22 +/- 5.35 ms; P = 0.82). CAD increases VRD in patients with type 2 diabetes. Therefore, changes in ventricular repolarization in diabetic patients may be due to silent CAD rather than due to diabetes per se. C1 Univ Ljubljana, Med Ctr, Div Cardiol, Ljubljana 1000, Slovenia. Univ Ljubljana, Inst Physiol, Ljubljana, Slovenia. Texas Heart Inst, Div Cardiopulm Transplantat, Houston, TX 77025 USA. NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. RP Vrtovec, B (reprint author), Univ Ljubljana, Med Ctr, Div Cardiol, Ljubljana 1000, Slovenia. EM bojan.vrtovec@mf.uni-lj.si NR 18 TC 6 Z9 6 U1 0 U2 0 PU BLACKWELL FUTURA PUBLISHING, INC PI MALDEN PA 350 MAIN STREET, MALDEN, MA 01248-5018 USA SN 0147-8389 J9 PACE JI PACE-Pacing Clin. Electrophysiol. PD JAN PY 2005 VL 28 SU 1 BP S178 EP S181 DI 10.1111/j.1540-8159.2005.00076.x PG 4 WC Cardiac & Cardiovascular Systems; Engineering, Biomedical SC Cardiovascular System & Cardiology; Engineering GA 902EW UT WOS:000227338100044 PM 15683491 ER PT S AU Jones, KH Lodding, KN Olariu, S Wilson, L Xin, CS AF Jones, KH Lodding, KN Olariu, S Wilson, L Xin, CS BE Chen, G Pan, Y Guo, M Lu, J TI Energy usage in biomimetic models for massively-deployed sensor networks SO PARALLEL AND DISTRIBUTED PROCESSING AND APPLICATIONS - ISPA 2005 WORKSHOPS SE Lecture Notes in Computer Science LA English DT Article; Proceedings Paper CT ISPA 2005 International Workshops AEPP, ASTED, BIOS, GCIC, IASD, MASN, SGCA and WISA CY NOV 02-05, 2005 CL Nanjing, PEOPLES R CHINA SP Nanjing Univ, State Key Lab Novel Software Technol AB Promises of ubiquitous control of the physical environment by sensor networks open avenues that will redefine the way we live and work. Due to the small size and low cost of sensors, visionaries promise smart systems enabled by deployment of huge numbers of sensors working in concert. At the moment, sensor network research is concentrating on developing techniques for performing simple tasks with minimal energy expense, assuming some form of centralized control. Centralized control does not scale to large networks and simple tasks in small-scale networks will not lead to the sophisticated applications predicted. Recently, the authors have proposed a new way of looking at sensor networks, motivated by lessons learned from the way biological ecosystems are organized. Here we demonstrate that in such a model, fully distributed data aggregation can be performed efficiently, without synchronization, in a scalable fashion, where individual motes operate autonomously based on local information, cooperating with neighbors to make local decisions that are aggregated across the network achieving globally-meaningful effects. C1 NASA, Langley Res Ctr, Hampton, VA 23681 USA. Old Dominion Univ, Norfolk, VA 23529 USA. Norfolk State Univ, Norfolk, VA 23504 USA. RP Jones, KH (reprint author), NASA, Langley Res Ctr, Hampton, VA 23681 USA. EM k.h.jones@nasa.gov; Kenneth.n.lodding@nasa.gov; olariu@cs.odu.edu; wilson@cs.odu.edu; cxin@nsu.edu NR 18 TC 1 Z9 1 U1 0 U2 0 PU SPRINGER-VERLAG BERLIN PI BERLIN PA HEIDELBERGER PLATZ 3, D-14197 BERLIN, GERMANY SN 0302-9743 BN 3-540-29770-7 J9 LECT NOTES COMPUT SC PY 2005 VL 3759 BP 434 EP 443 PG 10 WC Computer Science, Information Systems; Computer Science, Theory & Methods SC Computer Science GA BDJ16 UT WOS:000233739300048 ER PT B AU Kadota, K Stewart, ED AF Kadota, K Stewart, ED BE Alverson, G Barberis, E Nath, P Vaughn, MT TI Inflation model building in moduli space SO PASCOS 2004: Proceedings of the 10th International Symposium on Particles, Strings and Cosmology, Pt 1 LA English DT Proceedings Paper CT 10th International Symposium on Particles, Strings and Cosmology (PASCOS 2004) CY AUG 16-22, 2004 CL NE Univ, Boston, MA SP US Natl Sci Fdn, US DOE HO NE Univ AB A self-consistent modular cosmology scenario and its testability in view of future CMB experiments are discussed. Particular attention is drawn to the enhanced symmetric points in moduli space which play crucial roles in our scenario. The running and moreover the running of running for the cosmic perturbation spectrum are also analyzed. C1 NASA, Fermilab Theoret Astrophys Ctr, Batavia, IL 60510 USA. RP Kadota, K (reprint author), NASA, Fermilab Theoret Astrophys Ctr, POB 500, Batavia, IL 60510 USA. NR 7 TC 0 Z9 0 U1 0 U2 0 PU WORLD SCIENTIFIC PUBL CO PTE LTD PI SINGAPORE PA PO BOX 128 FARRER RD, SINGAPORE 9128, SINGAPORE BN 981-256-391-1 PY 2005 BP 48 EP 52 DI 10.1142/9789812701756_0007 PG 5 WC Physics, Multidisciplinary SC Physics GA BDM88 UT WOS:000234374500007 ER PT B AU Lee, C Alena, RL AF Lee, C Alena, RL BE Arabnia, HR TI Sensor data distribution with robustness and reliability - Toward distributed components model SO PDPTA '05: Proceedings of the 2005 International Conference on Parallel and Distributed Processing Techniques and Applications, Vols 1-3 LA English DT Proceedings Paper CT International Conference on Parallel and Distributed Processing Techniques and Applications CY JUN 27-30, 2005 CL Las Vegas, NV ID MIDDLEWARE AB In planetary surface exploration mission, sensor data distribution is required in many aspects, for example, in navigation, scheduling, planning, monitoring, diagnostics, and automation of the field tasks. The challenge is to distribute such data in the robust and reliable way so that we can minimize the errors caused by miscalculations, and misjudgments that based on the error data input in the mission. The ad-hoc wireless network on planetary surface is not constantly connected because of the nature of the rough terrain and lack of permanent establishments on the surface. There are some disconnected moments that the computation nodes will re-associate with different repeaters or access points until connections are reestablished. Such a nature requires our sensor data distribution software robust and reliable with ability to tolerant disconnected moments. This paper presents a distributed components model as a framework to accomplish such tasks. The software is written in Java and utilized the available Java Message Services schema and the JBoss implementation. The results of field experimentations show that the model is very effective in completing the tasks. C1 NASA, Ames Res Ctr, SAIC, Moffett Field, CA 94035 USA. RP Lee, C (reprint author), NASA, Ames Res Ctr, SAIC, Moffett Field, CA 94035 USA. NR 7 TC 0 Z9 0 U1 0 U2 0 PU C S R E A PRESS PI ATHENS PA 115 AVALON DR, ATHENS, GA 30606 USA BN 1-932415-61-0 PY 2005 BP 897 EP 903 PG 7 WC Computer Science, Theory & Methods SC Computer Science GA BDY80 UT WOS:000236257900131 ER PT J AU Peters, RD AF Peters, Randall D. BE Matthews, MR Gauld, CF Stinner, A TI The Pendulum in the 21st Century-Relic or Trendsetter SO PENDULUM: SCIENTIFIC, HISTORICAL, PHILOSOPHICAL AND EDUCATIONAL PERSPECTIVES LA English DT Article; Book Chapter AB When identifying instruments that have had great influence on the history of physics, none comes to mind more quickly than the pendulum. Though first treated scientifically by Galileo in the 16th century, and in some respects nearly 'dead' by the middle of the 20th century; the pendulum experienced 'rebirth' by becoming an archetype of chaos. With the resulting acclaim for its surprising behavior at large amplitudes, one might expect that there would already be widespread interest in another of its significant nonlinearities. Such is not the case, however, and the complex motions of small amplitude physical pendula are barely known. The present paper shows that a simply-constructed metallic rod pendulum is capable of demonstrating rich physics in a largely unstudied area. C1 [Peters, Randall D.] Mercer Univ, Dept Phys, Macon, GA 31207 USA. [Peters, Randall D.] NASA, Washington, DC USA. [Peters, Randall D.] US Mil Acad, West Point, NY USA. RP Peters, RD (reprint author), Mercer Univ, Dept Phys, 1400 Coleman Ave, Macon, GA 31207 USA. EM peters_rd@mercer.edu NR 10 TC 0 Z9 0 U1 0 U2 0 PU SPRINGER PI DORDRECHT PA PO BOX 17, 3300 AA DORDRECHT, NETHERLANDS BN 978-1-4020-3526-5 PY 2005 BP 19 EP 35 DI 10.1007/1-4020-3526-8_2 D2 10.1007/1-4020-3526-8 PG 17 WC Education & Educational Research; Education, Scientific Disciplines SC Education & Educational Research GA BKP29 UT WOS:000268860800002 ER PT J AU Peters, RD AF Peters, Randall D. BE Matthews, MR Gauld, CF Stinner, A TI Soup-can Pendulum SO PENDULUM: SCIENTIFIC, HISTORICAL, PHILOSOPHICAL AND EDUCATIONAL PERSPECTIVES LA English DT Article; Book Chapter AB In these studies, a vegetable can containing fluid was swung as a pendulum by supporting its end-lips with a pair of knife edges. The motion was measured with a capacitive sensor and the logarithmic decrement in free decay was estimated from computer-collected records. Measurements performed with nine different homogeneous liquids, distributed through six decades in the viscosity eta, showed that the damping of the system is dominated by eta rather than external forces from air or the knife edges. The log decrement was found to be maximum (0.28) in the vicinity of eta = 0.7 Pa s and fell off more than 15 fold ( below 2 x 10(-2)) for both small viscosity (eta < 1 x 10(-3) Pa s) and also for large viscosity (eta > 1 x 10(3) Pa s). A simple model has been formulated, which yields reasonable agreement between theory and experiment by approximating the relative rotation of can and liquid. C1 [Peters, Randall D.] Mercer Univ, Dept Phys, Macon, GA 31207 USA. [Peters, Randall D.] NASA, Washington, DC USA. [Peters, Randall D.] US Mil Acad, West Point, NY USA. RP Peters, RD (reprint author), Mercer Univ, Dept Phys, 1400 Coleman Ave, Macon, GA 31207 USA. EM peters_rd@mercer.edu NR 7 TC 0 Z9 0 U1 0 U2 0 PU SPRINGER PI DORDRECHT PA PO BOX 17, 3300 AA DORDRECHT, NETHERLANDS BN 978-1-4020-3526-5 PY 2005 BP 77 EP 88 DI 10.1007/1-4020-3526-8_6 D2 10.1007/1-4020-3526-8 PG 12 WC Education & Educational Research; Education, Scientific Disciplines SC Education & Educational Research GA BKP29 UT WOS:000268860800006 ER PT J AU Ahumada, AJ AF Ahumada, AJ TI A local contrast metric SO PERCEPTION LA English DT Meeting Abstract C1 NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. EM al.ahumada@nasa.gov NR 0 TC 0 Z9 0 U1 0 U2 0 PU PION LTD PI LONDON PA 207 BRONDESBURY PARK, LONDON NW2 5JN, ENGLAND SN 0301-0066 J9 PERCEPTION JI Perception PY 2005 VL 34 SU S BP 99 EP 99 PG 1 WC Ophthalmology; Psychology; Psychology, Experimental SC Ophthalmology; Psychology GA 976IE UT WOS:000232726000240 ER PT J AU Scharff, LFV Ahumada, AJ AF Scharff, LFV Ahumada, AJ TI Understanding text polarity effects SO PERCEPTION LA English DT Meeting Abstract C1 Stephen F Austin State Univ, Dept Psychol, Nacogdoches, TX 75962 USA. NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. EM lscharff@sfasu.edu NR 0 TC 0 Z9 0 U1 0 U2 0 PU PION LTD PI LONDON PA 207 BRONDESBURY PARK, LONDON NW2 5JN, ENGLAND SN 0301-0066 J9 PERCEPTION JI Perception PY 2005 VL 34 SU S BP 133 EP 133 PG 1 WC Ophthalmology; Psychology; Psychology, Experimental SC Ophthalmology; Psychology GA 976IE UT WOS:000232726000326 ER PT J AU Mizokami, Y Crognale, MA Ahumada, AJ AF Mizokami, Y Crognale, MA Ahumada, AJ TI Detection model predictions for aircraft targets on natural backgrounds SO PERCEPTION LA English DT Meeting Abstract C1 Univ Nevada, Dept Psychol, Reno, NV 89557 USA. NASA, Ames Res Ctr, Moffett Field, CA 94034 USA. EM yoko@unr.edu RI Crognale, Michael/K-4462-2012; Mizokami, Yoko/R-6982-2016 NR 0 TC 0 Z9 0 U1 0 U2 0 PU PION LTD PI LONDON PA 207 BRONDESBURY PARK, LONDON NW2 5JN, ENGLAND SN 0301-0066 J9 PERCEPTION JI Perception PY 2005 VL 34 SU S BP 141 EP 141 PG 1 WC Ophthalmology; Psychology; Psychology, Experimental SC Ophthalmology; Psychology GA 976IE UT WOS:000232726000349 ER PT J AU Snyder, JL Mulligan, JB Maloney, LT AF Snyder, JL Mulligan, JB Maloney, LT TI A reaction time model of self-terminating configural search in complex displays SO PERCEPTION LA English DT Meeting Abstract C1 NYU, Dept Psychol, New York, NY 10003 USA. NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. EM jacqueline.snyder@nyu.edu NR 0 TC 0 Z9 0 U1 0 U2 0 PU PION LTD PI LONDON PA 207 BRONDESBURY PARK, LONDON NW2 5JN, ENGLAND SN 0301-0066 J9 PERCEPTION JI Perception PY 2005 VL 34 SU S BP 150 EP 151 PG 2 WC Ophthalmology; Psychology; Psychology, Experimental SC Ophthalmology; Psychology GA 976IE UT WOS:000232726000374 ER PT J AU Shan, J Yoon, JS Lee, DS Kirk, RL Neumann, GA Acton, CH AF Shan, J Yoon, JS Lee, DS Kirk, RL Neumann, GA Acton, CH TI Photogrammetric analysis of the Mars Global Surveyor mapping data SO PHOTOGRAMMETRIC ENGINEERING AND REMOTE SENSING LA English DT Article ID ORBITER LASER ALTIMETER; CONTROL-POINT NETWORK; TOPOGRAPHY; CAMERA AB This paper studies the photogrammetric mapping properties and capabilities of the Mars Global Surveyor (MGS) mapping data. Starting from the raw MGS data, we decompress the MOC narrow angle images, extract, and calculate their exterior orientation from the SPICE kernels, and calculate the 3D coordinates of MOLA footprints from MOLA PEDR files. A new approach is proposed that registers a MOLA profile to stereo MOC images over the same area with robust and faster convergence. Intersection is conducted to determine the 3D positions of image points measured on MOC stereo pairs. It is shown that there is a nearly constant uncertainty of one MOLA ground spacing distance (approximately 325 m) along the flight direction in MOC and MOLA registration. This is caused by the uncertainties in SPICE kernels, MOLA points, and the determination of time tags for MOC scan lines, which possibly constitutes the dominant error source for the registration. Intersection calculation reaches an optimal balance by distributing the uncertainty evenly in the two images of a stereo pair. As for the photogrammetric mapping capabilities, an uncertainty of 180.8 m in planimetric distance and 30.8 m in elevation difference is estimated. A number of numerical and graphic results over three of the selected candidate landing sites for the Mars Exploration Rover mission are presented for analysis and illustration. C1 Purdue Univ, Sch Civil Engn, W Lafayette, IN 47907 USA. US Geol Survey, Astrogeol Team, Flagstaff, AZ 86001 USA. MIT, Cambridge, MA 02139 USA. CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Shan, J (reprint author), Purdue Univ, Sch Civil Engn, 550 Stadium Mall Dr, W Lafayette, IN 47907 USA. EM jshan@ecn.purdue.edu RI Neumann, Gregory/I-5591-2013 OI Neumann, Gregory/0000-0003-0644-9944 NR 38 TC 8 Z9 12 U1 1 U2 1 PU AMER SOC PHOTOGRAMMETRY PI BETHESDA PA 5410 GROSVENOR LANE SUITE 210, BETHESDA, MD 20814-2160 USA SN 0099-1112 J9 PHOTOGRAMM ENG REM S JI Photogramm. Eng. Remote Sens. PD JAN PY 2005 VL 71 IS 1 BP 97 EP 108 PG 12 WC Geography, Physical; Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Physical Geography; Geology; Remote Sensing; Imaging Science & Photographic Technology GA 886IX UT WOS:000226221600011 ER PT S AU Malkova, N Ning, CZ AF Malkova, N Ning, CZ BE Adibi, A Lin, SY Scherer, A TI Control of light propagation through sharp bend waveguide based on two-dimensional photonic crystal SO Photonic Crystal Materials and Devices III SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Photonic Crystal Materials and Devices III CY JAN 24-27, 2005 CL San Jose, CA SP SPIE DE photonic hand gap materials; coupled-cavity waveguide; resonant coupling ID TRANSMISSION AB Lion propagation through the sharp 45 degrees end coupled cavity waveguide is analyzed theoretically and numerically. We design the waveguide device based on two-dimensional photonic crystal with square lattice. The degenerate defect state is used as a guided mode of the device. In order to control the light propagation through the corner a splitting of the de-enerate defect state is used. C1 NASA, Ames Res Ctr, Ctr Nanotechnol, Moffett Field, CA 94035 USA. RP Malkova, N (reprint author), NASA, Ames Res Ctr, Ctr Nanotechnol, Mail Stop 229-1, Moffett Field, CA 94035 USA. NR 11 TC 1 Z9 1 U1 0 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 0-8194-5707-8 J9 P SOC PHOTO-OPT INS PY 2005 VL 5733 BP 159 EP 165 DI 10.1117/12.589431 PG 7 WC Crystallography; Optics SC Crystallography; Optics GA BCI25 UT WOS:000229438000018 ER PT J AU Lakhina, GS Tsurutani, BT Pickett, JS AF Lakhina, GS Tsurutani, BT Pickett, JS TI Generation of electric solitary structures (electron holes) by nonlinear low-frequency waves SO PHYSICA SCRIPTA LA English DT Article; Proceedings Paper CT International Workshop on Theoretical Plasma Physics CY JUL 05-16, 2004 CL Trieste, ITALY SP Abdus Salam ICTP ID TURBULENT-BOUNDARY-LAYER; PROTON CYCLOTRON WAVES; MAGNETIC-FIELD; ALFVEN WAVES; PLASMA-WAVES; MAGNETOPAUSE; POLAR; GEOTAIL; INSTABILITIES; MAGNETOTAIL AB High resolution electric and magnetic wave data, obtained by Polar during its passage through the polar cap/cusp boundary layer, show large amplitude low-frequency electromagnetic waves and electric bipolar pulses (electron holes). It is proposed that nonlinear low-frequency waves, consisting of Alfven and/or proton cyclotron waves, can drive high-frequency electrostatic modes which saturate by trapping electrons, thereby leading to the generation of electron holes. The free energy sources for these electrostatic instabilities are the parallel currents, which are produced due to relative motion of electrons and ions in the presence of large amplitude low-frequency waves. C1 Indian Inst Geomagnetism, Bombay 400005, Maharashtra, India. CALTECH, Jet Propuls Lab, Pasadena, CA USA. Univ Iowa, Dept Phys & Astron, Iowa City, IA 52242 USA. RP Lakhina, GS (reprint author), Indian Inst Geomagnetism, Bombay 400005, Maharashtra, India. EM lakhina@iig.iigm.res.in RI Lakhina, Gurbax /C-9295-2012; OI Lakhina, Gurbax /0000-0002-8956-486X NR 29 TC 0 Z9 0 U1 0 U2 0 PU ROYAL SWEDISH ACAD SCIENCES PI STOCKHOLM PA PUBL DEPT BOX 50005, S-104 05 STOCKHOLM, SWEDEN SN 0031-8949 J9 PHYS SCRIPTA JI Phys. Scr. PY 2005 VL T116 BP 79 EP 82 DI 10.1238/Physica.Topical.116a00079 PG 4 WC Physics, Multidisciplinary SC Physics GA 034BC UT WOS:000236898400017 ER PT J AU Weisman, JL Mattioda, A Lee, TJ Hudgins, DM Allamandola, LJ Bauschlicher, CW Head-Gordon, M AF Weisman, JL Mattioda, A Lee, TJ Hudgins, DM Allamandola, LJ Bauschlicher, CW Head-Gordon, M TI Electronic transitions in the IR: Matrix isolation spectroscopy and electronic structure theory calculations on polyacenes and dibenzopolyacenes SO PHYSICAL CHEMISTRY CHEMICAL PHYSICS LA English DT Article ID DENSITY-FUNCTIONAL THEORY; POLYCYCLIC AROMATIC-HYDROCARBONS; INFRARED-SPECTROSCOPY; CORRELATION-ENERGY; EMISSION FEATURES; APPROXIMATION; SPECTRA; PAHS; EXCITATION; MOLECULES AB We present the argon matrix isolated and theoretical spectra of the dibenzo[fg, op] tetracene, dibenzo[hi, uv] hexacene and dibenzo[jk, a1b1] octacene ions. Low-lying electronic absorptions are observed experimentally with significant intensity in the radical anion species. These electronic features in the IR region are confirmed with time dependent density functional theory calculations. We investigate the origin of these IR electronic transitions with orbital mixing considerations. C1 Univ Calif Berkeley, Dept Chem, Berkeley, CA 94720 USA. Univ Calif Berkeley, Lawrence Berkeley Lab, Div Chem Sci, Berkeley, CA 94720 USA. NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. SETI Inst, Mountain View, CA 94043 USA. RP Head-Gordon, M (reprint author), Univ Calif Berkeley, Dept Chem, Berkeley, CA 94720 USA. EM mhg@cchem.berkeley.edu RI Lee, Timothy/K-2838-2012 NR 24 TC 26 Z9 27 U1 1 U2 8 PU ROYAL SOC CHEMISTRY PI CAMBRIDGE PA THOMAS GRAHAM HOUSE, SCIENCE PARK, MILTON RD, CAMBRIDGE CB4 0WF, CAMBS, ENGLAND SN 1463-9076 J9 PHYS CHEM CHEM PHYS JI Phys. Chem. Chem. Phys. PY 2005 VL 7 IS 1 BP 109 EP 118 DI 10.1039/b415502e PG 10 WC Chemistry, Physical; Physics, Atomic, Molecular & Chemical SC Chemistry; Physics GA 881GX UT WOS:000225852500013 ER PT J AU Brindle, CA Chaban, GM Gerber, RB Janda, KC AF Brindle, CA Chaban, GM Gerber, RB Janda, KC TI Anharmonic vibrational spectroscopy calculations for (NH3)(HF) and (NH3)(DF): fundamental, overtone, and combination transitions SO PHYSICAL CHEMISTRY CHEMICAL PHYSICS LA English DT Article ID SELF-CONSISTENT-FIELD; POTENTIAL-ENERGY SURFACE; AB-INITIO CALCULATIONS; HYDROGEN-BOND; COMPLEXES; CLUSTERS; SPECTRA; SYSTEMS; STATES; N=1 AB In order to study the effects of hydrogen bonding on the spectroscopic properties of (NH3)(HF) and (NH3)(DF) complexes, vibrational spectra ( including fundamental, overtone and combination transitions) were calculated using the vibrational self consistent field (VSCF) method. This ab initio VSCF method accounts for both one-dimensional anharmonicity and pair-wise mode-mode couplings for all vibrational modes of the molecule, using points on the potential energy surface (at the MP2/TZP level of theory in this study). An analysis of the coupling strength shows surprisingly important coupling effects from pair-wise interactions not expected to be major. This indicates the benefits of including all pair- wise mode-mode couplings for weakly bound systems. Hydrogen bonding induces similar to20% red shifts for the HF and DF stretch frequencies. The corrections due to anharmonicity for these modes are -6% and -5%, respectively. The anharmonic corrections for the intermolecular stretch of (NH3)(HF) and (NH3)( DF) are each about -5%. The NH3 umbrella motion has virtually no anharmonic correction in the complex, whereas free ammonia experiences a -15% correction. Also, the closing motion as well as the opening motion is restricted. The 1 + 1 combination transition of the proton stretching and intermolecular stretching modes has remarkably large intensity, larger even than the intensities for the first overtone of the proton stretching modes. The anharmonic frequency for the fundamental HF stretch, 3268 cm(-1), is in good agreement with the experimental gas phase result, 3215 cm(-1). A comparison to solid rare-gas matrix data shows that the VSCF frequencies are a consistent improvement over the harmonic approximation. The experimental data also support the use of the MP2 level of theory for the associated electronic structure calculations. C1 Univ Calif Irvine, Dept Chem, Irvine, CA 92697 USA. Univ Calif Irvine, Dept Phys, Irvine, CA 92697 USA. Univ Calif Irvine, Inst Surface & Interface Sci, Irvine, CA 92697 USA. NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. Hebrew Univ Jerusalem, Dept Phys Chem, IL-91904 Jerusalem, Israel. Hebrew Univ Jerusalem, Fritz Haber Res Ctr, IL-91904 Jerusalem, Israel. RP Janda, KC (reprint author), Univ Calif Irvine, Dept Chem, Irvine, CA 92697 USA. NR 40 TC 12 Z9 12 U1 0 U2 6 PU ROYAL SOC CHEMISTRY PI CAMBRIDGE PA THOMAS GRAHAM HOUSE, SCIENCE PARK, MILTON RD, CAMBRIDGE CB4 0WF, CAMBS, ENGLAND SN 1463-9076 J9 PHYS CHEM CHEM PHYS JI Phys. Chem. Chem. Phys. PY 2005 VL 7 IS 5 BP 945 EP 954 DI 10.1039/b413678k PG 10 WC Chemistry, Physical; Physics, Atomic, Molecular & Chemical SC Chemistry; Physics GA 902WF UT WOS:000227386700033 PM 19791384 ER PT J AU Cartoixa, X Ting, DZY Chang, YC AF Cartoixa, X Ting, DZY Chang, YC TI Suppression of the D'yakonov-Perel' spin-relaxation mechanism for all spin components in [111]zincblende quantum wells SO PHYSICAL REVIEW B LA English DT Article ID SEMICONDUCTORS; HETEROSTRUCTURES; TRANSISTOR; ANISOTROPY; ELECTRONS AB We apply the D'yakonov-Perel' (DP) formalism to [111]-grown zinc blende quantum wells (QW's) to compute the spin lifetimes of electrons in the two-dimensional electron gas. We account for both bulk and structural inversion asymmetry (Rashba) effects. We see that, under certain conditions, the spin splitting vanishes to first order in k, which effectively suppresses the DP spin relaxation mechanism for all three spin components. We predict extended spin lifetimes as a result, giving rise to the possibility of enhanced spin storage. We also study [110]-grown QW's, where the effect of structural inversion asymmetry is to augment the spin relaxation rate of the component perpendicular to the well. We derive analytical expressions for the spin lifetime tensor and its proper axes, and see that they are dependent on the relative magnitude of the BIA- and SIA-induced splittings. C1 Univ Illinois, Dept Phys, Urbana, IL 61801 USA. CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Cartoixa, X (reprint author), Univ Calif Berkeley, Lawrence Berkeley Lab, Computat Res Div, Berkeley, CA 94720 USA. EM XCartoixa-Soler@lbl.gov RI Chang, Yia-Chung/F-4239-2011 NR 31 TC 56 Z9 57 U1 1 U2 5 PU AMERICAN PHYSICAL SOC PI COLLEGE PK PA ONE PHYSICS ELLIPSE, COLLEGE PK, MD 20740-3844 USA SN 1098-0121 J9 PHYS REV B JI Phys. Rev. B PD JAN PY 2005 VL 71 IS 4 AR 045313 DI 10.1103/PhysRevB.71.045313 PG 5 WC Physics, Condensed Matter SC Physics GA 893RF UT WOS:000226736200079 ER PT J AU Matzner, RA AF Matzner, RA TI Hyperbolicity and constrained evolution in linearized gravity SO PHYSICAL REVIEW D LA English DT Article ID NEUTRON-STAR BINARIES; RELATIVITY AB Solving the 4-d Einstein equations as evolution in time requires solving equations of two types: the four elliptic initial data (constraint) equations, followed by the six second order evolution equations. Analytically the constraint equations remain solved under the action of the evolution, and one approach is to simply monitor them (unconstrained evolution). Since computational solution of differential equations introduces almost inevitable errors, it is clearly "more correct" to introduce a scheme which actively maintains the constraints by solution (constrained evolution). This has shown promise in computational settings, but the analysis of the resulting mixed elliptic hyperbolic method has not been completely carried out. We present such an analysis for one method of constrained evolution, applied to a simple vacuum system, linearized gravitational waves. We begin with a study of the hyperbolicity of the unconstrained Einstein equations. (Because the study of hyperbolicity deals only with the highest derivative order in the equations, linearization loses no essential details.) We then give explicit analytical construction of the effect of initial data setting and constrained evolution for linearized gravitational waves. While this is clearly a toy model with regard to constrained evolution, certain interesting features are found which have relevance to the full nonlinear Einstein equations. C1 Univ Texas, Ctr Relat, Austin, TX 78712 USA. NASA, High Energy Astrophys Lab, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Univ Texas, Ctr Relat, Austin, TX 78712 USA. NR 18 TC 3 Z9 3 U1 0 U2 0 PU AMER PHYSICAL SOC PI COLLEGE PK PA ONE PHYSICS ELLIPSE, COLLEGE PK, MD 20740-3844 USA SN 2470-0010 EI 2470-0029 J9 PHYS REV D JI Phys. Rev. D PD JAN PY 2005 VL 71 IS 2 AR 024011 DI 10.1103/PhysRevD.71.024011 PG 7 WC Astronomy & Astrophysics; Physics, Particles & Fields SC Astronomy & Astrophysics; Physics GA 893ES UT WOS:000226702700049 ER PT J AU Vallisneri, M AF Vallisneri, M TI Synthetic LISA: Simulating time delay interferometry in a model LISA SO PHYSICAL REVIEW D LA English DT Article ID GRAVITATIONAL-RADIATION; SEARCH; MOTION; BAND AB We report on three numerical experiments on the implementation of Time-Delay Interferometry (TDI) for LISA, performed with Synthetic LISA, a C++/Python package that we developed to simulate the LISA science process at the level of scientific and technical requirements. Specifically, we study the laser-noise residuals left by first-generation TDI when the LISA armlengths have a realistic time dependence; we characterize the armlength-measurement accuracies that are needed to have effective laser-noise cancellation in both first- and second-generation TDI; and we estimate the quantization and telemetry bitdepth needed for the phase measurements. Synthetic LISA generates synthetic time series of the LISA fundamental noises, as filtered through all the TDI observables; it also provides a streamlined module to compute the TDI responses to gravitational waves according to a full model of TDI, including the motion of the LISA array and the temporal and directional dependence of the armlengths. We discuss the theoretical model that underlies the simulation, its implementation, and its use in future investigations on system-characterization and data-analysis prototyping for LISA. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Michele.Vallisneri@jpl.nasa.gov NR 46 TC 43 Z9 43 U1 2 U2 3 PU AMER PHYSICAL SOC PI COLLEGE PK PA ONE PHYSICS ELLIPSE, COLLEGE PK, MD 20740-3844 USA SN 2470-0010 EI 2470-0029 J9 PHYS REV D JI Phys. Rev. D PD JAN PY 2005 VL 71 IS 2 AR 022001 DI 10.1103/PhysRevD.71.022001 PG 18 WC Astronomy & Astrophysics; Physics, Particles & Fields SC Astronomy & Astrophysics; Physics GA 893ES UT WOS:000226702700006 ER PT J AU Jelenkovic, BA Phelps, AV AF Jelenkovic, BA Phelps, AV TI Excitation in low-current discharges and breakdown in He at low pressures and very high electric field to gas density ratios E/N SO PHYSICAL REVIEW E LA English DT Review ID ENERGY DISTRIBUTION-FUNCTIONS; COLLISIONAL RELAXATION PROCESSES; STROM-SPANNUNGS-CHARAKTERISTIK; SECONDARY-EMISSION COEFFICIENT; PARALLEL-PLANE ELECTRODES; MONTE-CARLO CALCULATIONS; RESONANT CHARGE-TRANSFER; VOLTAGE GLOW-DISCHARGE; CROSS-SECTIONS; POSITIVE-IONS AB We investigate optical emission from low-current discharges in He at very high electric field to gas density ratios. E/N between parallel plate electrodes. We also determine the electrical breakdown and the voltage-current behavior at low currents. The E/N are 300 Td to 9 kTd (1 Td = 10(-21) V m(2)) at pressures times electrode separations p(0)d from 3 to 0.9 Torr cm. Absolute optical emission probabilities versus distance are determined for the 501.6 nm line (3 P-1 --> 2 S-1) and for the 5 87.6 nm line (3 D-3 --> 2 P-3) by reference to Boltzmann calculations at our lowest E/N and to published pressure dependent electron beam experiments. At E/N below I kTd, the emission follows the exponential growth of the electron density, while at above 7 kTd heavy particle excitation is evident near the cathode. Collisional transfer of excitation from the singlet to the triplet system dominates the 587.6 urn excitation. Comparisons of models with experiments show the importance of excitation and of electron production at the cathode by fast He atoms produced by charge transfer collisions of He+ with He. The breakdown voltage versus p(0)d is multivalued for p(0)d similar to 1.5 Torr cm. At currents below. 100 muA and our lower E/N, the discharge voltage decreases linearly with current as expected for an increasing electron yield with ion energy and E/N at the cathode. C1 Univ Colorado, Joint Inst Lab Astrophys, Boulder, CO 80309 USA. Natl Inst Stand & Technol, Boulder, CO 80309 USA. Inst Phys, YU-11001 Belgrade, Serbia Monteneg, Serbia Monteneg. RP CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 109 TC 11 Z9 11 U1 0 U2 4 PU AMER PHYSICAL SOC PI COLLEGE PK PA ONE PHYSICS ELLIPSE, COLLEGE PK, MD 20740-3844 USA SN 2470-0045 EI 2470-0053 J9 PHYS REV E JI Phys. Rev. E PD JAN PY 2005 VL 71 IS 1 AR 016410 DI 10.1103/PhysRevE.71.016410 PN 2 PG 15 WC Physics, Fluids & Plasmas; Physics, Mathematical SC Physics GA 903XR UT WOS:000227459400100 PM 15697738 ER PT S AU Szabo, A AF Szabo, A BE Li, G Zank, GP Russell, CT TI Multi-spacecraft observations of interplanetary shocks SO Physics of Collisionless Shocks SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 4th Annual IGPP International Astrophysics Conference CY FEB 26-MAR 03, 2005 CL Palm Springs, CA SP IGPP, Univ Calif, Riverside, IGPP, Univ Calif, Los Angeles, IGPP, Los Alamos Natl Lab DE interplanetary shocks; shock fitting techniques ID RANKINE-HUGONIOT PROBLEM; MAGNETOPAUSE AB This paper presents the analysis of a number of interplanetary shocks observed by near-Earth solar wind monitors. Single and four-spacecraft shock normal determination methods are compared and it is demonstrated that the four-spacecraft timing method is not generally more accurate than the single-spacecraft Rankine-Hugoniot fit. Moreover, the single-spacecraft methods, unlike the four-spacecraft ones, allow the determination of possible shock surface curvatures. Examples are presented where significant shock curvature are observed that can lead to 5-10 minutes forecast error for bow shock arrival times. C1 NASA, Goddard Space Flight Ctr, Lab Solar & Space Phys, Greenbelt, MD 20771 USA. RP Szabo, A (reprint author), NASA, Goddard Space Flight Ctr, Lab Solar & Space Phys, Greenbelt, MD 20771 USA. NR 14 TC 5 Z9 5 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 0-7354-0268-X J9 AIP CONF PROC PY 2005 VL 781 BP 37 EP 41 PG 5 WC Astronomy & Astrophysics; Physics, Particles & Fields SC Astronomy & Astrophysics; Physics GA BDG24 UT WOS:000233337400006 ER PT S AU Ogilvie, KW AF Ogilvie, KW BE Li, G Zank, GP Russell, CT TI Electrons at shocks SO Physics of Collisionless Shocks SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 4th Annual IGPP International Astrophysics Conference CY FEB 26-MAR 03, 2005 CL Palm Springs, CA SP IGPP, Univ Calif, Riverside, IGPP, Univ Calif, Los Angeles, IGPP, Los Alamos Natl Lab AB Moderate strength quasi-perpendicular shocks have been observed by the Wind Spacecraft in the interplanetary medium. Both electron heating and acceleration have been inferred from these observations. We discuss electron heating and acceleration in this paper. C1 Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Ogilvie, KW (reprint author), Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. NR 3 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 0-7354-0268-X J9 AIP CONF PROC PY 2005 VL 781 BP 72 EP 76 PG 5 WC Astronomy & Astrophysics; Physics, Particles & Fields SC Astronomy & Astrophysics; Physics GA BDG24 UT WOS:000233337400011 ER PT S AU Jones, FC AF Jones, FC BE Li, G Zank, GP Russell, CT TI Simulated 2D vs. 3D shock waves: Implications for particle acceleration SO Physics of Collisionless Shocks SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 4th Annual IGPP International Astrophysics Conference CY FEB 26-MAR 03, 2005 CL Palm Springs, CA SP IGPP, Univ Calif, Riverside, IGPP, Univ Calif, Los Angeles, IGPP, Los Alamos Natl Lab DE particle orbits; Hamiltonian mechanics; ignorable coordinates; conservation theoroms ID MOTION; FIELDS AB We have given a rigorous derivation of a theorem showing that charged particles in an arbitrary electromagnetic field with at least one ignorable spatial coordinate remain forever tied to a given magnetic-field line. Such a situation contrasts the significant motions normal to the magnetic field that are expected in most real three-dimensional systems. While the significance of the theorem was not widely appreciated until recently, it has important consequences for a number of problems and is of particular relevance for the acceleration of cosmic rays by shocks. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Jones, FC (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. NR 6 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 0-7354-0268-X J9 AIP CONF PROC PY 2005 VL 781 BP 165 EP 169 PG 5 WC Astronomy & Astrophysics; Physics, Particles & Fields SC Astronomy & Astrophysics; Physics GA BDG24 UT WOS:000233337400025 ER PT J AU Jimenez, J Kawahara, G Simens, MP Nagata, M Shiba, M AF Jimenez, J Kawahara, G Simens, MP Nagata, M Shiba, M TI Characterization of near-wall turbulence in terms of equilibrium and "bursting" solutions SO PHYSICS OF FLUIDS LA English DT Article ID PLANE COUETTE-FLOW; EXACT COHERENT STRUCTURES; BOUNDARY-LAYER; CHANNEL FLOW; SHEAR FLOWS; REYNOLDS-NUMBER; COROTATING CYLINDERS; DYNAMICS; REGION; GENERATION AB Near-wall turbulence in the buffer region of Couette and Poiseuille flows is characterized in terms of recently-found nonlinear three-dimensional solutions to the incompressible Navier-Stokes equations for wall-bounded shear flows. The data suggest that those solutions can be classified into two families, of which one is dominated by streamwise vortices, and the other one by streaks. They can be associated with the upper and lower branches of the equilibrium solutions for Couette flow found by Nagata ["Three-dimensional finite-amplitude solutions in plane Couette flow: Bifurcation from infinity," J. Fluid Mech. 217, 519 (1990)]. The quiescent structures of near-wall turbulence are shown to correspond to the vortex-dominated family, but evidence is presented that they burst intermittently both in minimal and in fully turbulent flows. The intensity and period of the bursts are Reynolds-number dependent, but they saturate at high enough Reynolds numbers. The time-periodic exact solution found for Couette flow by Kawahara and Kida ["Periodic motion embedded in plane Couette turbulence: Regeneration cycle and burst," J. Fluid Mech. 449, 291 (2001)] can be used as a simplified model for the bursting process. (C) 2005 American Institute of Physics. C1 Univ Politecn Madrid, Sch Aeronaut, E-28040 Madrid, Spain. Stanford Univ, Ctr Turbulence Res, Stanford, CA 94305 USA. Kyoto Univ, Adv Res Inst Fluid Sci & Engn, Dept Aeronaut & Astronaut, Kyoto 6068501, Japan. Ehime Univ, Dept Mech Engn, Matsuyama, Ehime 7908577, Japan. NASA Ames, Moffett Field, CA USA. RP Univ Politecn Madrid, Sch Aeronaut, E-28040 Madrid, Spain. EM jimenez@torroja.dmt.upm.es RI jimenez, javier/A-6691-2008 OI jimenez, javier/0000-0003-0755-843X NR 50 TC 56 Z9 57 U1 2 U2 11 PU AMER INST PHYSICS PI MELVILLE PA 1305 WALT WHITMAN RD, STE 300, MELVILLE, NY 11747-4501 USA SN 1070-6631 EI 1089-7666 J9 PHYS FLUIDS JI Phys. Fluids PD JAN PY 2005 VL 17 IS 1 AR 015105 DI 10.1063/1.1825451 PG 16 WC Mechanics; Physics, Fluids & Plasmas SC Mechanics; Physics GA 888EW UT WOS:000226358000024 ER PT S AU Li, JZ Ning, CZ AF Li, JZ Ning, CZ BE Menendez, J VanDeWalle, CG TI Transparency induced by coupling of intersubband plasmons in a quantum well SO PHYSICS OF SEMICONDUCTORS, PTS A AND B SE AIP Conference Proceedings LA English DT Proceedings Paper CT 27th International Conference on the Physics of Semiconductors (ICPS-27) CY JUL 26-30, 2004 CL Flagstaff, AZ SP Int Union Pure & Appl Phys, Natl Sci Fdn, AF Off Sci Res, Off Naval Res, Army Res Off, Defense Adv Res Project Agcy, European Off Aerosp Res Dev, Asian Off Aerosp Res & Dev, Lawrence Berkeley Natl Lab, Natl Inst Standards & Technol, Amer Phys Soc, Forum Ind & Appl Phys AB Coupling of intersubband plasmons associated with two cascading transitions in a quantum well has been studied. It is shown that the coupling can lead to the disappearance of the lower resonance amidst an anti-crossing behavior. Such spectral anomalies are of collective and resonant nature and provide the first example of Coulomb interaction induced transparency. The results from a microscopic theory are confirmed by an analytical model. C1 NASA, Ames Res Ctr, Ctr Nanotechnol, Moffett Field, CA 94035 USA. RP NASA, Ames Res Ctr, Ctr Nanotechnol, Moffett Field, CA 94035 USA. NR 8 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 0-7354-0257-4 J9 AIP CONF PROC PY 2005 VL 772 BP 1139 EP 1140 PG 2 WC Physics, Condensed Matter SC Physics GA BCQ42 UT WOS:000230723900526 ER PT S AU Ting, DZY Cartoixa, X Chang, YC AF Ting, DZY Cartoixa, X Chang, YC BE Menendez, J VanDeWalle, CG TI Electrically controlled spin device concepts SO Physics of Semiconductors, Pts A and B SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 27th International Conference on the Physics of Semiconductors (ICPS-27) CY JUL 26-30, 2004 CL Flagstaff, AZ SP Int Union Pure & Appl Phys, Natl Sci Fdn, AF Off Sci Res, Off Naval Res, Army Res Off, Defense Adv Res Project Agcy, European Off Aerosp Res Dev, Asian Off Aerosp Res & Dev, Lawrence Berkeley Natl Lab, Natl Inst Standards & Technol, Amer Phys Soc, Forum Ind & Appl Phys ID HETEROSTRUCTURES; TRANSISTOR AB We discuss spin device concepts that exploit spin-orbit coupling in nonmagnetic semiconductor heterostructures, including the resonant interband tunneling spin filter, the bi-directional spin pump, the bulk inversion asymmetry enhanced spin filter, and resonant spin lifetime devices. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Ting, DZY (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. NR 15 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 0-7354-0257-4 J9 AIP CONF PROC PY 2005 VL 772 BP 1421 EP 1422 PG 2 WC Physics, Condensed Matter SC Physics GA BCQ42 UT WOS:000230723900662 ER PT S AU Yang, RQ AF Yang, RQ BE Menendez, J VanDeWalle, CG TI Type-II interband cascade lasers: From concept to devices SO Physics of Semiconductors, Pts A and B SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 27th International Conference on the Physics of Semiconductors (ICPS-27) CY JUL 26-30, 2004 CL Flagstaff, AZ SP Int Union Pure & Appl Phys, Natl Sci Fdn, AF Off Sci Res, Off Naval Res, Army Res Off, Defense Adv Res Project Agcy, European Off Aerosp Res Dev, Asian Off Aerosp Res & Dev, Lawrence Berkeley Natl Lab, Natl Inst Standards & Technol, Amer Phys Soc, Forum Ind & Appl Phys ID RECENT PROGRESS AB I briefly discuss the underlying physics of type-II interband cascade lasers and review their development from concept to high performance devices. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Yang, RQ (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 12 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 0-7354-0257-4 J9 AIP CONF PROC PY 2005 VL 772 BP 1553 EP 1554 PG 2 WC Physics, Condensed Matter SC Physics GA BCQ42 UT WOS:000230723900723 ER PT J AU Bertone, G Hooper, D Silk, J AF Bertone, G Hooper, D Silk, J TI Particle dark matter: evidence, candidates and constraints SO PHYSICS REPORTS-REVIEW SECTION OF PHYSICS LETTERS LA English DT Review ID ENERGY COSMIC-RAYS; DYNAMICAL SUPERSYMMETRY BREAKING; INTERACTING MASSIVE PARTICLES; MICROWAVE BACKGROUND ANISOTROPIES; STABLE SUPERSTRING RELICS; SAGITTARIUS A-ASTERISK; CHARGED HIGGS BOSONS; NEUTRALINO ANNIHILATION; E(+)E(-) COLLISIONS; GALACTIC-CENTER AB In this review article, we discuss the current status of particle dark matter, including experimental evidence and theoretical motivations. We discuss a wide array of candidates for particle dark matter, but focus on neutralinos in models of supersymmetry and Kaluza-Klein dark matter in models of universal extra dimensions. We devote much of our attention to direct and indirect detection techniques, the constraints placed by these experiments and the reach of future experimental efforts. (C) 2004 Published by Elsevier B.V. C1 NASA, Fermilab Theoret Astrophys Grp, Batavia, IL 60510 USA. Univ Oxford, Dept Astrophys, Oxford OX1 3RH, England. RP Univ Oxford, Dept Phys, Denys Wilkinson Lab, Oxford OX1 3RH, England. EM hooper@astro.ox.ac.uk OI silk, joe/0000-0002-1566-8148 NR 479 TC 1855 Z9 1870 U1 17 U2 131 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS SN 0370-1573 EI 1873-6270 J9 PHYS REP JI Phys. Rep.-Rev. Sec. Phys. Lett. PD JAN PY 2005 VL 405 IS 5-6 BP 279 EP 390 DI 10.1016/j.physrep.2004.08.031 PG 112 WC Physics, Multidisciplinary SC Physics GA 886HS UT WOS:000226218100001 ER PT J AU Kudela, K Lutsenko, VN Sarris, ET Sibeck, DG Slivka, M AF Kudela, K Lutsenko, VN Sarris, ET Sibeck, DG Slivka, M TI DOK-2 ion fluxes upstream from the bow shock: characteristics from 4 years of Interball-1 measurements SO PLANETARY AND SPACE SCIENCE LA English DT Article; Proceedings Paper CT Conference on Magnetospheric Response to Solar Activity CY SEP 09-12, 2003 CL Prague, CZECH REPUBLIC SP NATO Sci Affairs Div, COSPAR DE bow shock; foreshock; energetic particles; geomagnetic activity ID ENERGETIC IONS; SOLAR-WIND; PROTONS; EVENTS; MAGNETOSHEATH; ELECTRONS; CAVITIES; REGION AB The spectrometer DOK-2 on Interball-1 provided energetic (similar to20-similar to600 keV) ion fluxes and spectra for various geomagnetic and interplanetary conditions during the spacecraft's 5-year mission. From April to July in 1996-2000, the spacecraft's apogee lay upstream from the dayside bow shock. We present observations of the diffusive ion flux in the upstream region as a function of energy, magnetic field connection and distance to the position of a model bow shock, solar wind velocity, and geomagnetic activity for years 1996-1998 and a part of year 1999. Measurements by both ion detectors combined into 14 energy ranges are used for the analysis. Although fluxes of ions with energies up to similar to150keV depend primarily upon the geometry of the connection to the bow shock. the dependence of fluxes on geomagnetic activity, indicating the important contribution of particles leaking the magnetosphere, increases with the energy. (C) 2004 Elsevier Ltd. All rights reserved. C1 Slovak Acad Sci, Inst Expt Phys, Kosice 04353, Slovakia. Russian Acad Sci, Inst Space Res, Moscow 117997, Russia. Democritus Univ Thrace, GR-67100 Xanthi, Greece. NASA, Goddard Space Flight Ctr, Extraterr Phys Lab, Greenbelt, MD 20771 USA. RP Kudela, K (reprint author), Slovak Acad Sci, Inst Expt Phys, Watsonova Str 47, Kosice 04353, Slovakia. EM kkudela@kosice.upjs.sk RI Sibeck, David/D-4424-2012 NR 24 TC 3 Z9 3 U1 0 U2 0 PU PERGAMON-ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0032-0633 J9 PLANET SPACE SCI JI Planet Space Sci. PD JAN-MAR PY 2005 VL 53 IS 1-3 BP 59 EP 64 DI 10.1016/j.pss.2004.09.029 PG 6 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 893ZV UT WOS:000226760500008 ER PT J AU Merka, J Szabo, A Narock, TW Richardson, JD King, JH AF Merka, J Szabo, A Narock, TW Richardson, JD King, JH TI Three decades of bow shock observations by IMP 8 and model predictions SO PLANETARY AND SPACE SCIENCE LA English DT Article; Proceedings Paper CT Conference on Magnetospheric Response to Solar Activity CY SEP 09-12, 2003 CL Prague, CZECH REPUBLIC SP NATO Sci Affairs Div, COSPAR DE terrestrial bow shock; models; IMP-8 observations ID MACH NUMBER; UNUSUAL LOCATIONS; SHAPE; POSITION; MAGNETOSPHERE; MAGNETOPAUSE; ORIENTATION AB During almost three decades of operation, the IMP 8 satellite collected an extensive amount of both plasma and magnetic field measurements. The entire data set has been searched for all Earth's bow shock crossings observed by IMP 8. We have recorded total 11,455 single and multiple bow shock crossings and for 5870 of the crossings complete upstream interplanetary magnetic field and so wind parameters, measured by the same spacecraft, were available allowing us to test empirical models predicting the bow shock position as a function of upstream parameters. The chosen models were F79, NS91, FR94, CL95, P95 and V01 (Planet. Space Sci. 27(9) (1979) 1151: J. Atmos. Terr. Phys. 53 (1991) 1049; J. Geophys. Res. 99(A9) (1994) 17,681; J. Geophys. Res. 100(A9) (1995) 17,173; J. Geophys. Res. 100(A5) (1995) 7907; Earth Planets Space 53 (2001) 1001). This study investigates these models' accuracy not only for average upstream conditions but also for unusual conditions and as a result points out some deficiencies of these models. We demonstrate that most of the models underestimate bow shock distance for low Mach numbers and/or high magnitudes of IMF components. (C) 2004 Elsevier Ltd. All rights reserved. C1 L3 Commun Govt Serv Inc, Vienna, VA USA. MIT, Ctr Space Res, Cambridge, MA 02139 USA. NASA, Natl Space Sci Data Ctr, Greenbelt, MD USA. RP Merka, J (reprint author), NASA, Goddard Space Flight Ctr, Extraterr Phys Lab, Code 696, Greenbelt, MD 20705 USA. EM jan.merka@gsfc.nasa.gov OI Narock, Tom/0000-0002-9785-4496 NR 14 TC 11 Z9 12 U1 0 U2 2 PU PERGAMON-ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0032-0633 J9 PLANET SPACE SCI JI Planet Space Sci. PD JAN-MAR PY 2005 VL 53 IS 1-3 BP 79 EP 84 DI 10.1016/j.pss.2004.09.031 PG 6 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 893ZV UT WOS:000226760500010 ER PT J AU Jerab, M Nemecek, Z Safrankova, J Jelinek, K Merka, J AF Jerab, M Nemecek, Z Safrankova, J Jelinek, K Merka, J TI Improved bow shock model with dependence on the IMF strength SO PLANETARY AND SPACE SCIENCE LA English DT Article; Proceedings Paper CT Conference on Magnetospheric Response to Solar Activity CY SEP 09-12, 2003 CL Prague, CZECH REPUBLIC SP NATO Sci Affairs Div, COSPAR DE solar wind interaction; upstream conditions; magnetopause; bow shock; bow shock models ID MAGNETIC-FIELD ORIENTATION; LOW MACH NUMBERS; STANDOFF DISTANCE; UNUSUAL LOCATIONS; MHD THEORY; MAGNETOPAUSE; SHAPE; MAGNETOSHEATH; POSITION; MAGNETOSPHERE AB The presence of the bow shock in front of an obstacle immersed into a supersonic flow of collisionless plasma has been theoretically predicted and experimentally confirmed more than 40 years ago. However, in spite of a great effort of theoreticians and experimenters, we are still not able to predict the bow shock location under varying upstream conditions with a sufficient accuracy. Gasdynamic and MHD models cannot account for kinetics effects, whereas the kinetic models can be used only to study particular phenomena due to limited computer capacity. Models based on fits of experimental data usually expect that the bow shock location is a simple function of several upstream parameters as the solar wind dynamic pressure, upstream Mach number, and direction or magnitude of the interplanetary magnetic field. Since the bow shock location would be determined by the downstream parameters, these models implicitly assume that these parameters are unambiguously determined by the upstream conditions. The uncertainty of the bow shock prediction is usually attributed to the uncertainty in determination of the upstream state or to an irregular bow shock motion. We have accumulated a large set of bow shock crossings observed by INTERBALL-1 MAGION-4, GEOTAIL, IMP 8, and CLUSTER-2 spacecraft and complemented this set with upstream measurements of WIND with motivation to improve the accuracy of a prediction of the bow shock location provided by the Nmecek and Safrankova (J. Atmos. Terr. Phys. 53 (1991) 1049) model. Although proposed corrections conserve a simplicity of the original model, they decrease significantly the most probable error of the prediction. (C) 2004 Elsevier Ltd. All rights reserved. C1 Charles Univ Prague, Fac Math & Phys, CR-18000 Prague 2, Czech Republic. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Charles Univ Prague, Fac Math & Phys, Holesovickach 2, CR-18000 Prague 2, Czech Republic. EM zdenek.nemecek@mff.cuni.cz NR 28 TC 31 Z9 31 U1 0 U2 4 PU PERGAMON-ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0032-0633 J9 PLANET SPACE SCI JI Planet Space Sci. PD JAN-MAR PY 2005 VL 53 IS 1-3 BP 85 EP 93 DI 10.1016/j.pss.2004.09.032 PG 9 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 893ZV UT WOS:000226760500011 ER PT S AU Breus, TK Ness, NF Kryrnskii, AM Crider, DH Acuna, MH Connerney, JEP Hinson, D Barashyan, KK AF Breus, TK Ness, NF Kryrnskii, AM Crider, DH Acuna, MH Connerney, JEP Hinson, D Barashyan, KK BE Witasse, O Shea, MA TI The effects of crustal magnetic fields and the pressure balance in the high latitude ionosphere/atmosphere at Mars SO PLANETARY ATMOSPHERES, IONOSPHERES, AND MAGNETOSPHERES SE ADVANCES IN SPACE RESEARCH LA English DT Article; Proceedings Paper CT 35th COSPAR Scientific Assembly CY JUL 18-25, 2004 CL Paris, FRANCE SP Comm Space Res DE crustal magnetic fields; mini-magnetospheres; thermal pressure; plasma convection ID SOLAR-WIND INTERACTION; MARTIAN IONOSPHERE; GLOBAL SURVEYOR; MODEL AB The strongest crustal magnetic fields at Mars are located in certain regions in the Southern hemisphere and lead to the formation of large-scale mini-magnetospheres. In the Northern hemisphere, the crustal fields are rather weak and usually do not prevent direct interaction between the SW and an ionosphere/atmosphere. Exceptions occur in the isolated mini-magnetospheres formed by the crustal anomalies. Electron density profiles derived from radio occultation data obtained by the Radio Science Mars Global Surveyor (MGS) experiment have been compared with the crustal magnetic fields measured by the MGS Magnetometer/Electron reflectometer (MAG/ER) experiment. The effective scale-height of the electron density for two altitude ranges, 145-165 km and 165-185 km have been derived for each of the profiles studied. For the regions outside of the mini-magnetospheres the thermal pressure of the ionospheric plasma for the altitude range 145-185 km has been derived. The pressure balance in the high latitude ionosphere at Mars has been studied. In the Northern hemisphere average pressure at the altitude 160 km p, 60 is practically independent of SZA. In the Northern hemisphere B-2/8 pi can exceed p(160) in half the cases at altitudes 170-180 km, and magnetic forces can drive effective convection. In large scale mini-magnetospheres in the Southern hemisphere the ratio H145-165/H165-185 on average, larger and more variable than in the Northern hemisphere. This suggests that plasma convection at altitudes above 165 km is effective. Within the Martian mini-magnetospheres plasma convection has to be primarily a drift of charged particles across the strong crustal magnetic fields and in this regard Martian mini-magnetospheres are similar to the terrestrial magnetosphere. (c) 2005 COSPAR. Published by Elsevier Ltd. All rights reserved. C1 Space Res Inst IKI, Moscow 117997, Russia. Univ Delaware, Bartol Res Inst, Newark, DE 19716 USA. Rostov State Univ, Rostov Na Donu 344090, Russia. Catholic Univ Amer, Washington, DC 20064 USA. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Stanford Univ, Ctr Radar Astron, Stanford, CA 94305 USA. RP Breus, TK (reprint author), Space Res Inst IKI, Profsoyznaya 84-32, Moscow 117997, Russia. EM breus@space.ru; nfness@bartol.udel.edu; amkrym@yahoo.com; mha@lepmon.gsfc.nasa.gov RI connerney, john/I-5127-2013; Hurley, Dana/F-4488-2015 OI Hurley, Dana/0000-0003-1052-1494 NR 16 TC 5 Z9 5 U1 0 U2 1 PU ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD 0X5 1GB, OXON, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2005 VL 36 IS 11 SI 2005 BP 2043 EP 2048 DI 10.1016/j.asr.2005.01.100 PG 6 WC Engineering, Aerospace; Astronomy & Astrophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Engineering; Astronomy & Astrophysics; Geology; Meteorology & Atmospheric Sciences GA BDT68 UT WOS:000235252300003 ER PT S AU Bertucci, C Mazelle, C Acuna, M AF Bertucci, C Mazelle, C Acuna, M BE Witasse, O Shea, MA TI Structure and variability of the Martian magnetic pileup boundary and bow shock from MGS MAG/ER observations SO PLANETARY ATMOSPHERES, IONOSPHERES, AND MAGNETOSPHERES SE ADVANCES IN SPACE RESEARCH-SERIES LA English DT Article; Proceedings Paper CT 35th COSPAR Scientific Assembly CY JUL 18-25, 2004 CL Paris, FRANCE SP Comm Space Res DE solar wind interactions with unmagnetized bodies; bow shock; magnetic pileup boundary; discontinuities; planetary magnetospheres; Mars ID SOLAR-WIND INTERACTION; MARS GLOBAL SURVEYOR; FIELD DRAPING ENHANCEMENT; UP BOUNDARY; VENUS; LOCATION; PHOBOS-2; HALLEY; POSITION; SHAPE AB During the first 1.5 years of an ongoing successful mission, the Mars Global Surveyor Magnetometer and Electron Reflectometer (MAG/ER) has provided unprecedented information on different boundaries and regions of the Mars-solar wind interaction. This article discusses the magnetic structure and variability of two major plasma boundaries: the bow shock and the magnetic pileup boundary (MPB). MAG/ER observations conclude that the Martian bow shock is a fast bow shock, strongly affected by kinetic effects. The Martian bow shock position is highly variable on the daily basis, but it does not depend on the solar cycle phase. In addition, the bow shock position shows a slight asymmetry related to the convection electric field but no evidence for influence by crustal fields has been found. The MPB is a permanent, well-defined plasma boundary which is characterized by strong changes in the magnetic field and drastic changes in the dominant ion population. Studies on the magnetic structure of the MPB from MGS MAG/ER have led to the conclusion that this boundary is a well-defined current sheet whose normal vector agrees with the normal to the fit obtained from Mars Global Surveyor crossings. Similar boundaries have been observed around Venus and comets, suggesting that the MPB could be a common feature for all atmospheric unmagnetized bodies. At Mars, the MPB position varies on the daily basis and correlates with the bow shock position. On the other hand, the MPB position does not seem to be influenced by the solar cycle, although a small north-south asymmetry in its position suggests a weak influence by crustal magnetic fields. (c) 2005 COSPAR. Published by Elsevier Ltd. All rights reserved. C1 CESR, Toulouse, France. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Univ London Imperial Coll Sci & Technol, London, England. EM c.bertucci@imperial.ac.uk OI Bertucci, Cesar/0000-0002-2540-5384 NR 43 TC 3 Z9 3 U1 1 U2 1 PU ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD 0X5 1GB, OXON, ENGLAND SN 0273-1177 J9 ADV SPACE RES-SERIES PY 2005 VL 36 IS 11 SI 2005 BP 2066 EP 2076 DI 10.1016/j.asr.2005.05.096 PG 11 WC Engineering, Aerospace; Astronomy & Astrophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Engineering; Astronomy & Astrophysics; Geology; Meteorology & Atmospheric Sciences GA BDT68 UT WOS:000235252300006 ER PT S AU Litvak, ML Mitrofanov, IG Kozyrev, AS Sanin, AB Tretyakov, VI Boynton, WV Hamara, D Shinohara, C Saunders, RS AF Litvak, ML Mitrofanov, IG Kozyrev, AS Sanin, AB Tretyakov, VI Boynton, WV Hamara, D Shinohara, C Saunders, RS BE Witasse, O Shea, MA TI Modeling of Martian seasonal caps from HEND/ODYSSEY data SO PLANETARY ATMOSPHERES, IONOSPHERES, AND MAGNETOSPHERES SE ADVANCES IN SPACE RESEARCH LA English DT Article; Proceedings Paper CT 35th COSPAR Scientific Assembly CY JUL 18-25, 2004 CL Paris, FRANCE SP Comm Space Res DE neutron spectroscopy; Martian atmosphere; Martian seasonal cycle ID MARS-ODYSSEY SPACECRAFT; HEND INSTRUMENT ONBOARD; NEUTRON MEASUREMENTS; CARBON-DIOXIDE; SNOW DEPTH; POLAR CAPS; ICE; WATER; TEMPERATURES; HYDROGEN AB In this paper, we have analyzed neutron spectroscopy data gathered by the high energy neutron detector instrument onboard Mars Odyssey in order to study the behavior of CO2 condensed mass at the polar regions of Mars. It is known that observation of the neutron albedo of Mars provides not only information on distribution of water ice/bounded water through Martian subsurface but is also sensitive to the condensation/sublimation of atmospheric CO, at the Martian poles. Analysis of temporal variations of neutron flux between summer and winter seasons allowed the creation of multidimensional model of CO2 deposition describing behavior of CO2 condensed mass as a function of longitude, latitude and time. Based on this model, we have estimated the total masses of north seasonal cap ((3.8 +/- 0.4) x 10(15) kg), south seasonal cap ((6.3 +/- 0.6) x 10(15) kg) and compared our estimations with predictions of General Circulation Model. Furthermore, using the data gathered during second Martian year on the orbit, we have conducted preliminary comparison between seasonal cycles of two successive Martian years. (c) 2005 COSPAR. Published by Elsevier Ltd. All rights reserved. C1 Space Res Inst, Lab Gamma Ray Spect, Moscow 117997, Russia. Univ Arizona, Lunar & Planetary Lab, Tucson, AZ 85721 USA. NASA HQ, Washington, DC 20514 USA. RP Litvak, ML (reprint author), Space Res Inst, Lab Gamma Ray Spect, Profsojuznaya St 84-32, Moscow 117997, Russia. EM max@cgrsmx.iki.rssi.ru NR 24 TC 6 Z9 6 U1 0 U2 1 PU ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD 0X5 1GB, OXON, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2005 VL 36 IS 11 SI 2005 BP 2156 EP 2161 DI 10.1016/j.asr.2005.09.007 PG 6 WC Engineering, Aerospace; Astronomy & Astrophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Engineering; Astronomy & Astrophysics; Geology; Meteorology & Atmospheric Sciences GA BDT68 UT WOS:000235252300017 ER PT S AU Dwek, E AF Dwek, E BE Szczerba, R Stasinska, G Gorny, SK TI The chemical evolution of interstellar dust SO Planetary Nebulae as Astronomical Tools SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT International Conference on Planetary Nebulae as Astronomical Tools CY JUN 28-JUL 02, 2005 CL Gdansk, POLAND SP LEA Astronome Pologne-France, Polish Acad Sci, Nicolaus Copernicus Astron Ctr, Lab Univers Theories, Observat Paris, Polish State Comm Sci Res, City Gdansk, Gdansk Univ Technol, Acad Comp Ctr TASK, TeleAdreson ID GRAINS; CONSTRAINTS; CASSIOPEIA; SUPERNOVA; GALAXIES; EMISSION; STARS AB Interstellar dust particles undergo a complex series of processes starting with their formation in quiescent or explosive sources, followed by their injection into the interstellar medium, their processing by thermal sputtering and evaporative grain-grain collisions behind interstellar shock waves, and their growth by accretion and coagulation in molecular clouds. These evolutionary processes can be quantitatively described in the framework of a chemical evolution model which follows the fraction of a given element present in the gas or solid phase of the interstellar medium. Such models must be subject to strict cosmic abundances constraints. We describe here the general outline for constructing such models. In particular, such models predict the delayed injection of carbon dust that formed in AGB winds into the interstellar medium, an effect manifested in Spitzer IRAC and MIPS observations of PAH emission from galaxies of different metallicities. C1 NASA, Goddard Space Flight Ctr, Observat Cosmol Lab, Greenbelt, MD 20771 USA. RP Dwek, E (reprint author), NASA, Goddard Space Flight Ctr, Observat Cosmol Lab, Code 661, Greenbelt, MD 20771 USA. NR 22 TC 4 Z9 4 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 0-7354-0294-9 J9 AIP CONF PROC PY 2005 VL 804 BP 197 EP 203 PG 7 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BDP15 UT WOS:000234674000061 ER PT S AU Meibom, A Sleep, NH Zahnle, K Anderson, DL AF Meibom, Anders Sleep, Norman H. Zahnle, Kevin Anderson, Don L. BA Anderson, DL BF Anderson, DL BE Foulger, GR Natland, JH Presnall, DC TI Models for noble gases in mantle geochemistry: Some observations and alternatives SO PLATES, PLUMES AND PARADIGMS SE Geological Society of America Special Papers LA English DT Article; Book Chapter DE noble gases; mantle geochemistry; reservoirs; SUMA; plumes ID SOUTHEAST INDIAN RIDGE; HIGH HE-3/HE-4 RATIOS; EAST PACIFIC RISE; MAUNA-KEA VOLCANO; HELIUM-ISOTOPES; MIDOCEAN RIDGE; DEEP-MANTLE; EARTHS MANTLE; OLIVINE PHENOCRYSTS; VOLATILE EVOLUTION AB Models for noble gases in the Earth's mantle are evaluated against a number of observational constraints: (1) high (3)He/(4)He ratios do not correlate with high ( initial) (3)He concentrations; (2) the (3)He/(4)He data for mid-ocean ridge basalts and ocean island basalts do not represent two different distributions (4Anderson 2001); (3) globally robust correlations between (3)He/(4)He ratios and lithophile isotopic systems are not observed; (4) diverse local correlations exist that are broadly linear; (5) large, local geographical (3)He/(4)He variations are observed, which are inconsistent with a strongly localized (i.e., plume-stem) flux of high-(3)He/(4)He material; and (6) dramatic temporal (3)He/(4)He variations are observed on very short time scales (10(2) years). Layered (reservoir) models for noble gases, in which a deep and radially constrained region of the Earth's mantle preserves unradiogenic He and Ne isotopic compositions because of a high noble gas concentration, do not seem consistent with these observations. Heterogeneous (nonlayered) mantle models for noble gases, in which the carrier of unradiogenic He is a relatively noble gas-poor component scattered in the (upper) mantle, appear more consistent with the constraints. We propose that the carrier of unradiogenic noble gases is primarily olivine. Olivine-rich lithologies, produced in previous partial melting events, are a natural part of the statistical upper mantle assemblage (SUMA), a highly heterogeneous assemblage of small-to moderate-scale (similar to 1-100 km) enriched and depleted lithologies with a wide range of chemical composition, fertility, age, and isotopic signatures (Meibom and Anderson, 2004). The isotopic signatures of oceanic basalts, including noble gases, are obtained by partial melting of the SUMA under slightly different pressure and temperature (P-T) conditions, i.e., different degrees of partial melting and different degrees of homogenization prior to eruption (Morgan and Morgan, 1999; Meibom and Anderson, 2004; Rudge et al., 2005; Ito and Mahoney, 2005). Unradiogenic noble gas isotopic compositions are not tracers of deep-mantle components in the source materials of oceanic basalts. Noble gas isotopic compositions may, however, indirectly indicate potential temperature, because the order in which different upper-mantle lithologies melt depends on the P-T conditions. C1 [Meibom, Anders] Stanford Univ, Dept Geol & Environm Sci, Stanford, CA 94305 USA. [Sleep, Norman H.] Stanford Univ, Dept Geophys, Stanford, CA 94305 USA. [Zahnle, Kevin] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Anderson, Don L.] CALTECH, Pasadena, CA 91125 USA. RP Meibom, A (reprint author), Museum Natl Hist Nat, LEME, USM 0205, Case Postale 52,57 Rue Cuvier, F-75005 Paris, France. EM meibom@mnhn.fr NR 140 TC 0 Z9 0 U1 0 U2 0 PU GEOLOGICAL SOC AMER INC PI BOULDER PA 3300 PENROSE PL, PO BOX 9140, BOULDER, CO 80301 USA SN 0072-1077 BN 978-0-8137-2388-4 J9 GEOL SOC AM SPEC PAP PY 2005 VL 388 DI 10.1130/2005.2388(21) PG 17 WC Geochemistry & Geophysics; Geology; Geosciences, Multidisciplinary SC Geochemistry & Geophysics; Geology GA BLX99 UT WOS:000271372500022 ER PT S AU Stofan, ER Smrekar, SE AF Stofan, Ellen R. Smrekar, Suzanne E. BA Anderson, DL BF Anderson, DL BE Foulger, GR Natland, JH Presnall, DC TI Large topographic rises, coronae, large flow fields, and large volcanoes on Venus: Evidence for mantle plumes? SO PLATES, PLUMES AND PARADIGMS SE Geological Society of America Special Papers LA English DT Article; Book Chapter DE Venus; coronae; volcanoes; hotspots; mantle plumes ID IMPACT CRATER DENSITIES; STAGNANT LID CONVECTION; OF-SIGHT ACCELERATIONS; BETA-REGIO; HOT-SPOT; LITHOSPHERIC PROPERTIES; GLOBAL DISTRIBUTION; MAGMA TRANSPORT; EISTLA REGIO; HOTSPOT VOLCANISM AB Voluminous volcanic deposits at topographic rises, coronae, large flow fields, and large volcanoes have led researchers to link these features to mantle plumes. Topographic rises have broad, swell-like topography, large positive gravity anomalies, and associated volcanism. Coronae are circular to irregular features defined by their fracture annuli and associated with uplift and volcanism, followed by subsidence. Large volcanic flow fields (>30,000 km(2)) and large volcanoes (>100 km in diameter) are sites of voluminous outpourings of lava. We interpret the variations in types of volcanism, surface deformation, topography, and gravity signatures to indicate differences in the nature of the underlying thermal upwellings that formed these features. Most topographic rises are likely to be formed by primary or deep-seated plumes, whereas coronae and probably most volcanoes result from shallower upwellings or secondary plumes. Extension clearly plays a critical role in the formation of large flow fields, coronae, and some large volcanoes. We do not interpret large flow fields to be related to plumes. There are a similar number of primary plumes on Earth and Venus, but Venus has a much larger number of secondary plumes. The increased number of secondary plumes on Venus may result from the lack of slab cooling at the core-mantle boundary, the planet's lack of a low-viscosity zone, or its stronger lithosphere. C1 [Stofan, Ellen R.] Proxemy Res, Laytonville, MD 20882 USA. [Smrekar, Suzanne E.] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Stofan, ER (reprint author), POB 338, Rectortown, VA 20140 USA. EM ellen@proxemy.com NR 138 TC 3 Z9 3 U1 0 U2 6 PU GEOLOGICAL SOC AMER INC PI BOULDER PA 3300 PENROSE PL, PO BOX 9140, BOULDER, CO 80301 USA SN 0072-1077 BN 978-0-8137-2388-4 J9 GEOL SOC AM SPEC PAP PY 2005 VL 388 DI 10.1130/2005.2388(47) PG 21 WC Geochemistry & Geophysics; Geology; Geosciences, Multidisciplinary SC Geochemistry & Geophysics; Geology GA BLX99 UT WOS:000271372500048 ER PT S AU Deamer, DW Dworkin, JP AF Deamer, DW Dworkin, JP BE Walde, P TI Chemistry and physics of primitive membranes SO PREBIOTIC CHEMISTRY: FROM SIMPLE AMPHIPHILES TO PROTOCELL MODELS SE Topics in Current Chemistry LA English DT Review; Book Chapter DE artificial cells; encapsulation; lipid vesicles; membranes ID MURCHISON CARBONACEOUS CHONDRITE; MONOCARBOXYLIC ACIDS; AMINO-ACIDS; PHOSPHOLIPID-BILAYERS; ORGANIC-MOLECULES; CELL-MEMBRANES; ENERGY YIELDS; ICE ANALOGS; LIFE; INTERSTELLAR AB A membrane boundary structure was essential for the advent of cellular life. The membranes of contemporary cells are composed of a mosaic of proteins embedded in a bimolecular layer of phospholipids, each of which requires a complex enzymatic pathway for its synthesis. The earliest forms of life could not have had such a highly evolved pathway in place. Amphiphilic monocarboxylic acids are present in carbonaceous meteorites and can be synthesized under simulated geochemical conditions. Such compounds have physical and chemical properties that allow them to assemble into bilayer membranes and are therefore plausible components of the first cellular membranes. C1 Univ Calif Santa Cruz, Dept Biomol Engn, Santa Cruz, CA 95060 USA. NASA, Goddard Space Flight Ctr, Lab Astrochem, Solar Syst Explorat Div, Greenbelt, MD 20771 USA. RP Deamer, DW (reprint author), Univ Calif Santa Cruz, Dept Biomol Engn, Santa Cruz, CA 95060 USA. EM deamer@hydrogen.ucsc.edu; Jason.P.Dworkin@nasa.gov RI Dworkin, Jason/C-9417-2012 OI Dworkin, Jason/0000-0002-3961-8997 NR 88 TC 45 Z9 46 U1 2 U2 25 PU SPRINGER-VERLAG BERLIN PI BERLIN PA HEIDELBERGER PLATZ 3, D-14197 BERLIN, GERMANY SN 0340-1022 BN 3-540-27759-5 J9 TOP CURR CHEM JI Top. Curr. Chem. PY 2005 VL 259 BP 1 EP 27 DI 10.1007/b136806 D2 10.1007/b105128 PG 27 WC Biochemistry & Molecular Biology; Chemistry, Multidisciplinary SC Biochemistry & Molecular Biology; Chemistry GA BDO84 UT WOS:000234567400001 ER PT S AU Yu, B Meyyappan, M AF Yu, B Meyyappan, M BE Ghibaudo, G Skotnicki, T Cristoloveanu, S Brillouet, M TI Nanotechnology: Potential challenger to silicon CMOS? SO PROCEEDINGS OF ESSDERC 2005: 35TH EUROPEAN SOLID-STATE DEVICE RESEARCH CONFERENCE SE Proceedings of the European Solid-State Device Research Conference LA English DT Proceedings Paper CT 35th European Solid-State Device Research Conference CY SEP 12-16, 2005 CL Grenoble, FRANCE SP imep, Leti, IEEE, European Device Soc, ST, LA METRO, CNRS, Soitec, isere, RhoneAlpes, Infineon Technol, Freescale, Atmel, Texas Instruments, Intel, Nanocmos, PHILIPS, Mentor Graph, SAMSUNG, Leti, Minatec, INP Grenoble, Minist Delegue Rech, DGA, Univ Joseph Fourier, AEPI ID NANOWIRE BUILDING-BLOCKS AB We discuss the potential "challenger" of silicon chip technology at or before the end of the Roadmap. These disruptive technologies are rooted in the nanoscale materials or structures, synthesized by the inexpensive bottom-tip chemistry methods, which exhibit exceptional materials and electrical properties. The new technologies will help the continued advancement, not necessary through conventional geometry scaling, of solid-state chip technology in several mainstream applications such as computing and data storage. C1 NASA, Ames Res Ctr, Ctr Nanotechnol, Moffett Field, CA 94035 USA. RP Yu, B (reprint author), NASA, Ames Res Ctr, Ctr Nanotechnol, Moffett Field, CA 94035 USA. EM byu@arc.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 1930-8876 BN 0-7803-9203-5 J9 PROC EUR S-STATE DEV PY 2005 BP 157 EP 160 DI 10.1109/ESSDER.2005.1546609 PG 4 WC Engineering, Electrical & Electronic; Instruments & Instrumentation; Physics, Condensed Matter SC Engineering; Instruments & Instrumentation; Physics GA BDY50 UT WOS:000236176200032 ER PT B AU Mehr, AF Turner, IY Barrientos, F Ullman, D AF Mehr, Ali Farhang Turner, Irem Y. Barrientos, Francesca Ullman, David GP ASME TI An information-exchange tool for capturing and communicating decisions during early-phase design and concept evaluation SO Proceedings of IMECE 2005: Engineering/Technology Management LA English DT Proceedings Paper CT ASME International Mechanical Engineering Congress and Exposition CY NOV 05-11, 2005 CL Orlando, FL SP ASME, Proc Ind Div, ASME, Rail Transportat Div, ASME, Noise Control & Acoust Div, ASME, Triol Div, ASME, Pressure Vessels & Piping Div, ASME, Bioengn Div, ASME, Mat Div, ASME, Appl Mech Div, ASME, Fluids Engn Div, ASME, Micro Elect Mech Syst Div, ASME, Heat Transfer Div, ASME, Nucl Engn Div, ASME, Power Div, ASME, Solar Energy Div, ASME, Safety Engn & Risk Anal Div, ASME, Technol & Soc Div, ASME, Adv Energy Syst Div, ASME, Aerosp Div, ASME, Comp & Informat Engn Div AB Capturing and communicating risk and uncertainty for NASA's low-volume high-cost exploration missions have become the subject of intensive research in the past few years. As a result, a variety of quantitative and qualitative methodologies were developed, some of which have been adopted and implemented by various NASA centers in the form of risk management tools, procedures, or guidelines. Most of these methodologies, however, aim at the later stages of the design process or during the operational phase of the mission and therefore, are not applicable to the earlier stages of design. In practice, however, uncertainties in the decisions made during the early stages of design introduce a significant amount of risk to the concepts that are being evaluated. In this paper, we aim to capture and quantify uncertainty and risk due to the lack of knowledge as well as those associated with potential system failures. We present an information exchange tool (X-Change) that enables various subsystem designers to capture, quantify, and communicate the uncertainties due to their lack of knowledge as well as those due to failures that might not be readily available or easily-quantifiable. A key piece in this work is to incorporate risk and uncertainty due to the lack of knowledge during the early design phase, and combining it with the potential failure modes. The challenges we face in accomplishing this goal are: 1) lack of a unified ontology defining risk, uncertainty and failure in order to enable their use on common grounds; 2) difficulty in expressing and capturing risk and uncertainty due to the designers' lack of knowledge at the early stages of design; 3) difficulty in accounting for potential failure modes and their associated risks at the functional design level, before a form or solution has been determined. In order to address these challenges, this paper first attempts to provide a definition for risk and uncertainty. Then, we present the results of an ongoing effort to develop a risk-based design tool for the concurrent mission design environment at NASA. We propose a framework that enables multiple subsystems to capture and communicate the relevant risk and uncertainty in their decisions. The application of the proposed framework is further elaborated using a satellite design example. C1 NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Turner, IY (reprint author), NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. NR 13 TC 0 Z9 0 U1 0 U2 2 PU AMER SOC MECHANICAL ENGINEERS PI NEW YORK PA THREE PARK AVENUE, NEW YORK, NY 10016-5990 USA BN 0-7918-4230-4 PY 2005 BP 125 EP 131 PG 7 WC Engineering, Multidisciplinary; Engineering, Mechanical SC Engineering GA BFM61 UT WOS:000243097500018 ER PT S AU Cushing, MC Marley, MS Roellig, TL AF Cushing, MC Marley, MS Roellig, TL BE Favata, F Hussain, GAJ Battrick, B TI Spitzer spectroscopy of low-mass stars and brown dwarfs SO PROCEEDINGS OF THE 13TH CAMBRIDGE WORKSHOP ON COOL STARS, STELLAR SYSTEMS AND THE SUN - PROCEEDINGS, VOLS 1 AND 2 SE ESA Special Publications LA English DT Proceedings Paper CT 13th Cambridge Workshop on Cool Stars, Stellar Systems and the Sun CY JUL 05-09, 2004 CL Hamburg, GERMANY DE stars : late-type; stars : low-mass; brown dwarfs; infrared : stars ID INFRARED SPECTROGRAPH IRS; T-DWARFS; SPECTRAL CLASSIFICATION; SPACE-TELESCOPE; CLOUDS; TEMPERATURE; ATMOSPHERES; PHOTOMETRY; CHEMISTRY; SEQUENCE AB We present the first results of a spectroscopic survey of M, L, and T dwarfs being conducted with the Infrared Spectrograph onboard the Spitzer Space Telescope. We observed GJ 1001 A (M3.5 V), DENIS 0255-4700 (L8.0 V), and is an element of Ind Ba/Bb (T1/T6 V). As expected from the predictions of model atmospheres, the spectra show absorption features of H2O, CH4 at 7.8 mu m, and NH3 at 10.5 mu m. This is the first detection of the 7.8 mu m CH4 band and the first secure detection of NH3 in the spectra of brown dwarfs. Finally, we compute the bolometric luminosities of three of the dwarfs in our sample by combining 0.6-4.1 mu m spectra with the Spitzer spectra and find good agreement with previous results that use L'-and M'-band photometry to account for the flux emitted between 2.5 and 5 mu m. C1 NASA, Ames Res Ctr, SETI Inst, Moffett Field, CA 94043 USA. RP NASA, Ames Res Ctr, SETI Inst, MS 245-3, Moffett Field, CA 94043 USA. EM mcushing@mail.arc.nasa.gov RI Marley, Mark/I-4704-2013 NR 28 TC 0 Z9 0 U1 0 U2 1 PU EUROPEAN SPACE AGENCY PI PARIS PA 8-10 RUE MARIO NIKIS, 75738 PARIS, FRANCE SN 0379-6566 BN 92-9092-871-9 J9 ESA SPEC PUBL PY 2005 VL 560 BP 245 EP 248 PG 4 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BCU73 UT WOS:000231306900032 ER PT S AU Marley, MS Cushing, MC Saumon, D AF Marley, MS Cushing, MC Saumon, D BE Favata, F Hussain, GAJ Battrick, B TI The L to T dwarf transition SO PROCEEDINGS OF THE 13TH CAMBRIDGE WORKSHOP ON COOL STARS, STELLAR SYSTEMS AND THE SUN - PROCEEDINGS, VOLS 1 AND 2 SE ESA Special Publications LA English DT Proceedings Paper CT 13th Cambridge Workshop on Cool Stars, Stellar Systems and the Sun CY JUL 05-09, 2004 CL Hamburg, GERMANY DE stars : brown dwarfs ID PHOTOSPHERIC ENVIRONMENT; MODEL ATMOSPHERES; BROWN DWARFS; DUST; CHEMISTRY; CLOUDS; PHOTOMETRY; SPECTRA AB While the precise mechanism responsible for the L to T dwarf transition remains unclear, it is clearly caused by changing cloud characteristics. Here we briefly review data relevant to understanding the nature of the transition and argue that changing atmospheric dynamics produce the transition by opening holes through the global iron and silicate cloud decks. Other possibilities, such as a sudden vertical collapse in these cloud decks axe also considered. Any acceptable model of the L to T transition must ultimately connect changing cloud properties to the underlying atmospheric dynamics. C1 NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP NASA, Ames Res Ctr, Mail Stop 245-3, Moffett Field, CA 94035 USA. EM msutherlund@mail.arc.nasa.gov; mcushing@mail.arc.nasa.gov RI Marley, Mark/I-4704-2013 NR 19 TC 2 Z9 2 U1 0 U2 0 PU EUROPEAN SPACE AGENCY PI PARIS PA 8-10 RUE MARIO NIKIS, 75738 PARIS, FRANCE SN 0379-6566 BN 92-9092-871-9 J9 ESA SPEC PUBL PY 2005 VL 560 BP 791 EP 794 PG 4 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BCU73 UT WOS:000231306900151 ER PT B AU Andrews, R Li, J Chen, H Cassell, A Koehne, J Meyyappan, M Nguyen-Vu, R Huang, N Chen, L AF Andrews, R Li, J Chen, H Cassell, A Koehne, J Meyyappan, M Nguyen-Vu, R Huang, N Chen, L BE Khamlichi, AE TI Nanoelectrode arrays for deep brain stimulation SO Proceedings of the 13th World Congress of Neurological Surgery, Vols 1 and 2 LA English DT Proceedings Paper CT 13th World Congress of Neurological Surgery CY JUN 19-24, 2005 CL Marrakech, MOROCCO SP Neurosurg Soc Morocco, World Federat Neurosurg Soc AB Deep brain stimulation (DBS, neuromodulation) has recently been established as a treatment for advanced Parkinson's disease, but the techniques to date utilize macroelectrodes under open-loop conditions (i.e. no internal feedback to guide the stimulation). Multi-walled carbon nanotubule nanoelectrode arrays not only improve the resolution of focal brain electrical activity monitoring, but add monitoring of neurotransmitters (e.g. dopamine) as well - in addition to more focal electrical stimulation under closed-loop conditions. An overview of the characteristics and potential of nanoelectrode arrays for DBS, as well as on-going work with the PC12 cell line (in preparation for in vivo studies using animal models of Parkinson's disease), are presented. C1 NASA, Ames Nanotechnol, Moffett Field, CA USA. RP Andrews, R (reprint author), NASA, Ames Nanotechnol, Moffett Field, CA USA. NR 5 TC 0 Z9 0 U1 0 U2 0 PU MEDIMOND S R L PI 40128 BOLOGNA PA VIA MASERATI 5, 40128 BOLOGNA, 00000, ITALY BN 88-7587-160-4 PY 2005 BP 803 EP 806 PG 4 WC Clinical Neurology; Surgery SC Neurosciences & Neurology; Surgery GA BDG84 UT WOS:000233429700156 ER PT B AU Andrews, R Mah, R Papasin, R Guerrero, M DaSilva, L AF Andrews, R Mah, R Papasin, R Guerrero, M DaSilva, L BE Khamlichi, AE TI Real-time tissue identification - The NASA 'Smart Probe' SO Proceedings of the 13th World Congress of Neurological Surgery, Vols 1 and 2 LA English DT Proceedings Paper CT 13th World Congress of Neurological Surgery CY JUN 19-24, 2005 CL Marrakech, MOROCCO SP Neurosurg Soc Morocco, World Federat Neurosurg Soc ID SCATTERING SPECTROSCOPY; RECOGNITION; PROJECT AB Critical intraoperative tissue decisions in neurosurgery include: Is this normal brain or tumor? Are all tumor margins clear? Is this disc or nerve root? Where does the aneurysm neck end? The NASA Smart Probe uses neural networks to integrate data from multiple microsensors in real-time - to create unique tissue "signatures". We review the Smart Probe concept and summarize data from women with suspected breast cancer (by the NASA licensee, BioLuminate Inc.). The sensors in the breast cancer Smart Probe include electrical impedance and optical spectroscopy (both broadband or white light, and laser light (infrared and blue/fluorescence)). Data are acquired 100 per second; a breast "biopsy" typically generates 500 MB of data. The multiparameter 'Smart Probe' - one millimeter in diameter - readily differentiates both normal tissues and carcinoma. C1 NASA, Ames Smart Syst, Moffett Field, CA 94035 USA. RP Andrews, R (reprint author), NASA, Ames Smart Syst, Moffett Field, CA 94035 USA. NR 6 TC 0 Z9 0 U1 0 U2 1 PU MEDIMOND S R L PI 40128 BOLOGNA PA VIA MASERATI 5, 40128 BOLOGNA, 00000, ITALY BN 88-7587-160-4 PY 2005 BP 969 EP 974 PG 6 WC Clinical Neurology; Surgery SC Neurosciences & Neurology; Surgery GA BDG84 UT WOS:000233429700186 ER PT S AU Burt, EA Klipstein, WM Jefferts, SR AF Burt, EA Klipstein, WM Jefferts, SR BE Yuhas, MP TI The cesium physics package design for the PARCS experiment SO PROCEEDINGS OF THE 2004 IEEE INTERNATIONAL FREQUENCY CONTROL SYMPOSIUM AND EXPOSITION SE IEEE International Frequency Control Symposium LA English DT Proceedings Paper CT IEEE International Frequency Control Symposium and Exposition CY AUG 23-27, 2004 CL Montreal, CANADA SP IEEE ID NONEVAPORABLE GETTER FILMS; OUTGASSING RATE; COATINGS; CHAMBER; COPPER AB The Primary Atomic Reference Clock in Space (PARCS) is a collaboration between the National Institute of Standards and Technology (NIST), the Jet Propulsion Laboratory (JPL) and the University of Colorado to build a laser-cooled cesium-beam atomic clock as a science payload for the International Space Station (ISS). The three primary goals of the PARCS experiment are (1) to demonstrate laser cooling of atoms in space, (2) to use laser cooling to build the most accurate space clock, and (3) to use the clock to test fundamental assumptions and predictions of relativity theory. In this paper we will discuss aspects of the PARC cesium physics package subsystem design addressing magnetic, microwave and vacuum requirements as well as operational scenarios. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 22 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1075-6787 BN 0-7803-8413-X J9 P IEEE INT FREQ CONT PY 2005 BP 71 EP 79 PG 9 WC Engineering, Electrical & Electronic; Instruments & Instrumentation; Physics, Applied SC Engineering; Instruments & Instrumentation; Physics GA BCB56 UT WOS:000228522000012 ER PT S AU Strekalov, D Savchenkov, A Matsko, A Yu, N Maleki, L AF Strekalov, D Savchenkov, A Matsko, A Yu, N Maleki, L BE Yuhas, MP TI All-optical atomic clock on a chip: Progress report SO Proceedings of the 2004 IEEE International Frequency Control Symposium and Exposition SE PROCEEDINGS OF THE IEEE INTERNATIONAL FREQUENCY CONTROL SYMPOSIUM LA English DT Proceedings Paper CT IEEE International Frequency Control Symposium and Exposition CY AUG 23-27, 2004 CL Montreal, CANADA SP IEEE ID ELECTROMAGNETICALLY INDUCED TRANSPARENCY; OPTOELECTRONIC MICROWAVE-OSCILLATOR; PERFORMANCE AB We report on progress in the development of atomic clocks based on the opto-electronic oscillator stabilized with an atomic cell. For a demonstration setup, the short term (1 second) stability of 5 - 10(-10) and the long term stability (100 seconds) of 6 - 10(-11) is reported. Also discussed is the physics of a low power electro-optical modulator utilizing the whispering gallery modes in a segnetoelectric disk. This modulator is an important element of the designed clock. It is shown that our approach allows for multi-function application of the designed clocks, that can also operate in the magnetometer regime. C1 CALTECH, Jet Prop Lab, Quantum Sci & Technol Grp, Pasadena, CA 91125 USA. RP Strekalov, D (reprint author), CALTECH, Jet Prop Lab, Quantum Sci & Technol Grp, Pasadena, CA 91125 USA. NR 15 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1075-6787 BN 0-7803-8413-X J9 P IEEE INT FREQ CONT PY 2005 BP 104 EP 108 PG 5 WC Engineering, Electrical & Electronic; Instruments & Instrumentation; Physics, Applied SC Engineering; Instruments & Instrumentation; Physics GA BCB56 UT WOS:000228522000018 ER PT S AU Chung, SK Prestage, JD Tjoelker, RL Maleki, L AF Chung, SK Prestage, JD Tjoelker, RL Maleki, L BE Yuhas, MP TI Buffer gas experiments in mercury (Hg+) ion clock SO Proceedings of the 2004 IEEE International Frequency Control Symposium and Exposition SE PROCEEDINGS OF THE IEEE INTERNATIONAL FREQUENCY CONTROL SYMPOSIUM LA English DT Proceedings Paper CT IEEE International Frequency Control Symposium and Exposition CY AUG 23-27, 2004 CL Montreal, CANADA SP IEEE AB We report measured buffer gas collision shifts of the 40.507347996xx GHz mercury ion clock transition using inert helium, neon, and argon gases and getterable molecular hydrogen and nitrogen gases. The frequency shift due to methane was also examined. At low partial pressures methane gas did not impact the trapped ion number but was observed to strongly relax the population difference in the two hyperfine clock states thereby reducing the clock resonance signal. A similar population relaxation was also observed for other molecular buffer gases (N-2, H-2) but at much reduced rate. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Chung, SK (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. 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 1075-6787 BN 0-7803-8413-X J9 P IEEE INT FREQ CONT PY 2005 BP 130 EP 133 PG 4 WC Engineering, Electrical & Electronic; Instruments & Instrumentation; Physics, Applied SC Engineering; Instruments & Instrumentation; Physics GA BCB56 UT WOS:000228522000023 ER PT S AU Nan, Y Salik, E Maleki, L AF Nan, Y Salik, E Maleki, L BE Yuhas, MP TI Photonic microwave oscillator using mode-locked laser as the high Q resonator SO PROCEEDINGS OF THE 2004 IEEE INTERNATIONAL FREQUENCY CONTROL SYMPOSIUM AND EXPOSITION SE IEEE International Frequency Control Symposium LA English DT Proceedings Paper CT IEEE International Frequency Control Symposium and Exposition CY AUG 23-27, 2004 CL Montreal, CANADA SP IEEE ID FIBER RING LASER; TIMING JITTER; NOISE; SYSTEMS AB We show that an actively mode-locked laser can serve as a high Q microwave resonator in a photonic oscillator. The high Q is due to the high regenerative gain of the optical modes which generate the beat note at a photodetector as the microwave signal. In a fiber mode-locked laser setup, we have demonstrated the generation of 10 GHz microwave signal with the phase noise of -140 dBc/Hz at the offset frequency of 10 kHz. We have also found that the effective Q of the resonator depends on the optical pulse width. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM nan.yu@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 1075-6787 BN 0-7803-8413-X J9 P IEEE INT FREQ CONT PY 2005 BP 219 EP 223 PG 5 WC Engineering, Electrical & Electronic; Instruments & Instrumentation; Physics, Applied SC Engineering; Instruments & Instrumentation; Physics GA BCB56 UT WOS:000228522000038 ER PT S AU Dick, GJ AF Dick, GJ BE Yuhas, MP TI Pound circuit-induced frequency sensitivities in ultra-stable cryogenic oscillators SO PROCEEDINGS OF THE 2004 IEEE INTERNATIONAL FREQUENCY CONTROL SYMPOSIUM AND EXPOSITION SE IEEE International Frequency Control Symposium LA English DT Proceedings Paper CT IEEE International Frequency Control Symposium and Exposition CY AUG 23-27, 2004 CL Montreal, CANADA SP IEEE ID STABILIZATION; PHASE AB The Pound technique is widely used in ultra-stable cryogenic oscillators to prevent frequency drifts due to variation in the path delay between room-temperature electronics and the cryogenic resonator. In this paper we calculate frequency sensitivities to several other microwave signal corruptions that are not rejected by the Pound technique. Considering only linear circuit elements, we identify a quadratic variation of phase with frequency and a linear variation of amplitude with frequency as the lowest order processes that can induce frequency offsets. As an example we evaluate the consequence of this frequency sensitivity for thermally induced frequency variation in an image-rejection filter. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM john.dick@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 1075-6787 BN 0-7803-8413-X J9 P IEEE INT FREQ CONT PY 2005 BP 224 EP 228 PG 5 WC Engineering, Electrical & Electronic; Instruments & Instrumentation; Physics, Applied SC Engineering; Instruments & Instrumentation; Physics GA BCB56 UT WOS:000228522000039 ER PT S AU Salik, E Yu, N Maleki, L Rubiola, E AF Salik, E Yu, N Maleki, L Rubiola, E BE Yuhas, MP TI Dual photonic-delay line cross correlation method for phase noise measurement SO Proceedings of the 2004 IEEE International Frequency Control Symposium and Exposition SE PROCEEDINGS OF THE IEEE INTERNATIONAL FREQUENCY CONTROL SYMPOSIUM LA English DT Proceedings Paper CT IEEE International Frequency Control Symposium and Exposition CY AUG 23-27, 2004 CL Montreal, CANADA SP IEEE AB We describe the application cross-correlation method with dual photonic delay-line for homodyne phase noise measurement of the low-noise microwave oscillators. This method combines delay-fine discriminator and cross correlation with use of low-loss kilometer-long photonic delay. By using 4.5 km optical fiber as photonic delay, we demonstrated a measurement noise floor of -158 dBc/Hz at 10 kHz offset without a reference oscillator. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Salik, E (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 10 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1075-6787 BN 0-7803-8413-X J9 P IEEE INT FREQ CONT PY 2005 BP 303 EP 306 PG 4 WC Engineering, Electrical & Electronic; Instruments & Instrumentation; Physics, Applied SC Engineering; Instruments & Instrumentation; Physics GA BCB56 UT WOS:000228522000051 ER PT S AU Wang, RT Dick, GJ Diener, WA AF Wang, RT Dick, GJ Diener, WA BE Yuhas, MP TI Progress on 10 Kelvin Cryo-cooled Sapphire Oscillator SO PROCEEDINGS OF THE 2004 IEEE INTERNATIONAL FREQUENCY CONTROL SYMPOSIUM AND EXPOSITION SE IEEE International Frequency Control Symposium LA English DT Proceedings Paper CT IEEE International Frequency Control Symposium and Exposition CY AUG 23-27, 2004 CL Montreal, CANADA SP IEEE AB We present recent progress on the 10 Kelvin Cryocooled Sapphire Oscillator (10K CSO.). Included are incorporation of a new pulse tube cryocooler, cryocooler vibration comparisons between G-M and pulse-tube types, phase noise, and frequency stability tests. For the advantage of a single stage pulse tube cryocooler. we also present results for a 40K Compensated Sapphire Oscillator (40K CSO). C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. 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 1075-6787 BN 0-7803-8413-X J9 P IEEE INT FREQ CONT PY 2005 BP 752 EP 756 PG 5 WC Engineering, Electrical & Electronic; Instruments & Instrumentation; Physics, Applied SC Engineering; Instruments & Instrumentation; Physics GA BCB56 UT WOS:000228522000142 ER PT S AU Enzer, DG Klipstein, WM AF Enzer, DG Klipstein, WM BE Yuhas, MP TI Performance of the PARCS testbed cesium fountain frequency standard SO PROCEEDINGS OF THE 2004 IEEE INTERNATIONAL FREQUENCY CONTROL SYMPOSIUM AND EXPOSITION SE IEEE International Frequency Control Symposium LA English DT Proceedings Paper CT IEEE International Frequency Control Symposium and Exposition CY AUG 23-27, 2004 CL Montreal, CANADA SP IEEE DE cesium; fountain; light shift; frequency standard; atomic clock AB A cesium fountain frequency standard has been developed as a ground testbed for the PARCS (Primary Atomic Reference Clock in Space) experiment -- an experiment intended to fly on the International Space Station. We report on the Performance of the fountain and describe some of the implementations motivated in large part by flight considerations, but of relevance for around fountains. In particular, we report on a new technique for delivering cooling and trapping laser beams to the atom collection region, in which a given beam is recirculated three times effectively providing much more optical power than traditional configurations. Allan deviations down to 10(-15) have been achieved with this method. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. RP CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91125 USA. EM Daphna.G.Enzer@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 1075-6787 BN 0-7803-8413-X J9 P IEEE INT FREQ CONT PY 2005 BP 775 EP 780 PG 6 WC Engineering, Electrical & Electronic; Instruments & Instrumentation; Physics, Applied SC Engineering; Instruments & Instrumentation; Physics GA BCB56 UT WOS:000228522000147 ER PT B AU Jones, KH Lodding, KN Olariu, S Wilson, L Xin, C AF Jones, KH Lodding, KN Olariu, S Wilson, L Xin, C GP IEEE TI An ecosystem model for massively-deployed sensor networks SO Proceedings of the 2005 Intelligent Sensors, Sensor Networks & Information Processing Conference LA English DT Proceedings Paper CT Intelligent Sensors, Sensor Networks and Information Processing Conference CY DEC 05-08, 2005 CL Melbourne, AUSTRALIA SP Univ Melbourne, Australian Govt, Australian Res Council, ARC Res Networks Intelligent Sensors, Sensor Networks & Informat Proc, DARPA, Australian Govt, Dept Def, Def Sci & Technol Org, IEEE, IEEE Sensors Council AB Research in wireless sensor network technology has accelerated rapidly in the last decade. Promises of ubiquitous control of the physical environment by these networks open avenues for new applications that will redefine the way we live and work. Due to the small size and low cost of sensor devices, visionaries promise systems enabled by deployment of massive numbers of sensors working in concert. Recent sensor network research has concentrated on developing techniques for performing relatively simple tasks with minimal energy expense, assuming some from of centralized control. Unfortunately, centralized control does not scale to massive size networks and execution of simple tasks in sparse networks will not lead to the sophisticated applications predicted. The contribution of this work is to continue our work in looking at massively-deployed sensor networks, motivated by lessons learned from the way biological ecosystems are organized. We demonstrate that in such a model, fully distributed synchronization can be performed in a scalable fashion in massively deployed sensor networks, where individual motes operate based on local information, making local decisions that are aggregated across the network to achieve a globally-meaningful effect. C1 NASA, Langley Res Ctr, Hampton, VA 23665 USA. RP Jones, KH (reprint author), NASA, Langley Res Ctr, Hampton, VA 23665 USA. NR 23 TC 7 Z9 7 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 0-7803-9399-6 PY 2005 BP 1 EP 6 PG 6 WC Computer Science, Artificial Intelligence; Instruments & Instrumentation; Telecommunications SC Computer Science; Instruments & Instrumentation; Telecommunications GA BDT72 UT WOS:000235261200001 ER PT B AU Lee, SM Ravinder, U Johnston, JC AF Lee, SM Ravinder, U Johnston, JC BE Kuhl, ME Steiger, NM Armstrong, FB Joines, JA TI Developing an agent model of human performance in air traffic control operations using apex cognitive architecture SO Proceedings of the 2005 Winter Simulation Conference, Vols 1-4 LA English DT Proceedings Paper CT 2005 Winter Simulation Conference (WSC 05) CY DEC 04-07, 2005 CL Orlando, FL SP Amer Stat Assoc, ACM SIGSIM, IEEE Comp Soc, IEEE SMC, Inst Ind Engineers, INFORMS SIM, NIST, Soc Modeling & Simulat Int AB For the analysis of large-scale complex systems, agent-based modeling and simulation has proven to provide a valuable research tool. The emphasis has, however, typically been on representing the dynamic behavior of physical entities such as aircraft. Simulation of human operators has often been minimal even though human behavior has an enormous impact on overall system performance and safety. Therefore, human capabilities and limitations need to be taken into account early in the system design process before irrevocable choices have been made. This paper reports on the development of agent models with human-like performance characteristics using a cognitive architecture. We present an agent model of an air traffic controller that is developed and incorporated into an agent-based simulation of the national airspace to support the design and evaluation of advanced air transportation concepts. C1 NASA, Ames Res Ctr, Human Factors Sci & Technol Div, Moffett Field, CA 94035 USA. RP Lee, SM (reprint author), NASA, Ames Res Ctr, Human Factors Sci & Technol Div, Mail Stop 262-4, Moffett Field, CA 94035 USA. NR 25 TC 6 Z9 6 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 0-7803-9519-0 PY 2005 BP 979 EP 987 PG 9 WC Computer Science, Interdisciplinary Applications; Computer Science, Software Engineering; Operations Research & Management Science SC Computer Science; Operations Research & Management Science GA BDY77 UT WOS:000236253401041 ER PT B AU Bardina, JE Thirumalainambi, R AF Bardina, JE Thirumalainambi, R BE Kuhl, ME Steiger, NM Armstrong, FB Joines, JA TI Distributed web-based expert system for launch operations SO Proceedings of the 2005 Winter Simulation Conference, Vols 1-4 LA English DT Proceedings Paper CT 2005 Winter Simulation Conference (WSC 05) CY DEC 04-07, 2005 CL Orlando, FL SP Amer Stat Assoc, ACM SIGSIM, IEEE Comp Soc, IEEE SMC, Inst Ind Engineers, INFORMS SIM, NIST, Soc Modeling & Simulat Int AB The simulation and modeling of launch operations is based on a representation of the organization of the operations suitable to experiment of the physical, procedural, software, hardware and psychological aspects of space flight operations. The virtual test bed consists of a weather expert system to advice on the effect of weather to the launch operations. It also simulates toxic gas dispersion model, and the risk impact on human health. Since all modeling and simulation is based on the internet, it could reduce the cost of operations of launch and range safety by conducting extensive research before a particular launch. Each model has an independent decision making module to derive the best decision for launch. C1 NASA Ames Res Ctr, Intelligent Syst Div, Moffett Field, CA 94035 USA. RP Bardina, JE (reprint author), NASA Ames Res Ctr, Intelligent Syst Div, Moffett Field, CA 94035 USA. NR 17 TC 2 Z9 2 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 0-7803-9519-0 PY 2005 BP 1291 EP 1297 DI 10.1109/WSC.2005.1574389 PG 7 WC Computer Science, Interdisciplinary Applications; Computer Science, Software Engineering; Operations Research & Management Science SC Computer Science; Operations Research & Management Science GA BDY77 UT WOS:000236253401082 ER PT B AU von Rosenvinge, TT Cohen, CMS Cummings, AC Leske, RA Mewaldt, RA Stone, EC Wiedenbeck, ME AF von Rosenvinge, T. T. Cohen, C. M. S. Cummings, A. C. Leske, R. A. Mewaldt, R. A. Stone, E. C. Wiedenbeck, M. E. GP Tata Institute Fundamental Res TI Gradual solar energetic particle events with 'impulsive' composition SO Proceedings of the 29th International Cosmic Ray Conference Vol 1: SH1 and SH2 LA English DT Proceedings Paper CT 29th International Cosmic Ray Conference CY AUG 03-10, 2005 CL Pune, INDIA SP Forsch Zentrum Karsruhe Inst Kernphys, Univ Karlsruhe, Inst Expt Kemphys, Tata Inst Fundamental Res, Int Union Pure & Appl Phys C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP von Rosenvinge, TT (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. NR 3 TC 0 Z9 0 U1 0 U2 0 PU TATA INST FUNDAMENTAL RESEARCH PI MUMBAI PA HOMI BHABHA MARG, NAVY NAGAR, COLABA, MUMBAI, MH-400005, INDIA PY 2005 BP 115 EP 115 PG 1 WC Astronomy & Astrophysics; Instruments & Instrumentation; Physics, Particles & Fields SC Astronomy & Astrophysics; Instruments & Instrumentation; Physics GA BFO78 UT WOS:000243504300030 ER PT B AU Wiedenbeck, ME Mason, GM Cohen, CMS Cummings, AC Dwyer, JR Gold, RE Krimigis, SM Leske, RA Mazur, JE Mewaldt, RA Stone, EC von Rosenvinge, TT AF Wiedenbeck, M. E. Mason, G. M. Cohen, C. M. S. Cummings, A. C. Dwyer, J. R. Gold, R. E. Krimigis, S. M. Leske, R. A. Mazur, J. E. Mewaldt, R. A. Stone, E. C. von Rosenvinge, T. T. GP Tata Institute Fundamental Res TI The time variation of energetic He-3 in interplanetary space from 1997 to 2005 SO Proceedings of the 29th International Cosmic Ray Conference Vol 1: SH1 and SH2 LA English DT Proceedings Paper CT 29th International Cosmic Ray Conference CY AUG 03-10, 2005 CL Pune, INDIA SP Forsch Zentrum Karsruhe Inst Kernphys, Univ Karlsruhe, Inst Expt Kemphys, Tata Inst Fundamental Res, Int Union Pure & Appl Phys C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Wiedenbeck, ME (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. NR 3 TC 5 Z9 5 U1 0 U2 0 PU TATA INST FUNDAMENTAL RESEARCH PI MUMBAI PA HOMI BHABHA MARG, NAVY NAGAR, COLABA, MUMBAI, MH-400005, INDIA PY 2005 BP 117 EP 120 PG 4 WC Astronomy & Astrophysics; Instruments & Instrumentation; Physics, Particles & Fields SC Astronomy & Astrophysics; Instruments & Instrumentation; Physics GA BFO78 UT WOS:000243504300031 ER PT B AU Gopalswamy, N Xie, H Yashiro, S Usoskin, I AF Gopalswamy, N. Xie, H. Yashiro, S. Usoskin, I. GP Tata Institute Fundamental Res TI Coronal mass ejections and ground level enhancements SO Proceedings of the 29th International Cosmic Ray Conference Vol 1: SH1 and SH2 LA English DT Proceedings Paper CT 29th International Cosmic Ray Conference CY AUG 03-10, 2005 CL Pune, INDIA SP Forsch Zentrum Karsruhe Inst Kernphys, Univ Karlsruhe, Inst Expt Kemphys, Tata Inst Fundamental Res, Int Union Pure & Appl Phys C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Gopalswamy, N (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RI Gopalswamy, Nat/D-3659-2012; Usoskin, Ilya/E-5089-2014; OI Usoskin, Ilya/0000-0001-8227-9081; Gopalswamy, Nat/0000-0001-5894-9954 NR 7 TC 1 Z9 2 U1 0 U2 0 PU TATA INST FUNDAMENTAL RESEARCH PI MUMBAI PA HOMI BHABHA MARG, NAVY NAGAR, COLABA, MUMBAI, MH-400005, INDIA PY 2005 BP 169 EP 172 PG 4 WC Astronomy & Astrophysics; Instruments & Instrumentation; Physics, Particles & Fields SC Astronomy & Astrophysics; Instruments & Instrumentation; Physics GA BFO78 UT WOS:000243504300044 ER PT B AU Adams, JH Barghouty, AF Bhattacharya, M Lin, ZW AF Adams, J. H., Jr. Barghouty, A. F. Bhattacharya, M. Lin, Zi-Wei GP Tata Institute Fundamental Res TI Human exploration of the Moon and Mars: Space radiation data, modeling and instrumentation needs SO Proceedings of the 29th International Cosmic Ray Conference Vol 1: SH1 and SH2 LA English DT Proceedings Paper CT 29th International Cosmic Ray Conference CY AUG 03-10, 2005 CL Pune, INDIA SP Forsch Zentrum Karsruhe Inst Kernphys, Univ Karlsruhe, Inst Expt Kemphys, Tata Inst Fundamental Res, Int Union Pure & Appl Phys C1 NASA, George C Marshall Space Flight Ctr, Huntsville, AL 35812 USA. RP Adams, JH (reprint author), NASA, George C Marshall Space Flight Ctr, Mail Stop XD12, Huntsville, AL 35812 USA. NR 0 TC 0 Z9 0 U1 0 U2 1 PU TATA INST FUNDAMENTAL RESEARCH PI MUMBAI PA HOMI BHABHA MARG, NAVY NAGAR, COLABA, MUMBAI, MH-400005, INDIA PY 2005 BP 301 EP 302 PG 2 WC Astronomy & Astrophysics; Instruments & Instrumentation; Physics, Particles & Fields SC Astronomy & Astrophysics; Instruments & Instrumentation; Physics GA BFO78 UT WOS:000243504300077 ER PT B AU Saganti, P Cucinotta, F Cleghorn, T Zeitlin, C Lee, K Hu, X Pinsky, L Anderson, V Riman, F Flanders, J Atwell, W Turner, R AF Saganti, P. Cucinotta, F. Cleghorn, T. Zeitlin, C. Lee, K. Hu, X. Pinsky, L. Anderson, V. Riman, F. Flanders, J. Atwell, W. Turner, R. GP Tata Institute Fundamental Res TI MARIE measurements and model predictions of solar modulation of galactic cosmic rays at Mars SO Proceedings of the 29th International Cosmic Ray Conference Vol 1: SH1 and SH2 LA English DT Proceedings Paper CT 29th International Cosmic Ray Conference CY AUG 03-10, 2005 CL Pune, INDIA SP Forsch Zentrum Karsruhe Inst Kernphys, Univ Karlsruhe, Inst Expt Kemphys, Tata Inst Fundamental Res, Int Union Pure & Appl Phys ID PARTICLE-FLUX; RADIATION; SURFACE; VISUALIZATION; RISKS C1 NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. RP Saganti, P (reprint author), NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. NR 9 TC 0 Z9 0 U1 0 U2 0 PU TATA INST FUNDAMENTAL RESEARCH PI MUMBAI PA HOMI BHABHA MARG, NAVY NAGAR, COLABA, MUMBAI, MH-400005, INDIA PY 2005 BP 319 EP 322 PG 4 WC Astronomy & Astrophysics; Instruments & Instrumentation; Physics, Particles & Fields SC Astronomy & Astrophysics; Instruments & Instrumentation; Physics GA BFO78 UT WOS:000243504300082 ER PT B AU Jones, WV AF Jones, W. V. GP Tata Inst Fundamental Res TI Evolution of scientific research ballooning SO Proceedings of the 29th International Cosmic Ray Conference, Vol 10 LA English DT Proceedings Paper CT 29th International Cosmic Ray Conference CY AUG 03-10, 2005 CL Pune, INDIA SP Forsch Zentrum Karsruhe Inst Kernphys, Univ Karlsruhe, Inst Expt Kemphys, Tata Inst Fundamental Res, Int Union Pure & Appl Phys AB Balloons have been used for scientific research since they were invented in France approximately 220 years ago. The last major change in balloon design occurred in 1950 with the introduction of the so-called natural shape balloon with integral load tapes. The National Aeronautics and Space Administration (NASA) is currently pursuing development of a super-pressure balloon that would enable extended duration missions above 99.5% of the Earth's atmosphere at any latitude. The ultra-long-duration balloon (ULDB) flights enabled by this constant-volume balloon should result in an even greater sea change in scientific ballooning than the inauguration of long-duration balloon (LDB) flights in Antarctica during the 1990 - 91 austral summer. The ULDB technology advancements include utilization of a new structural design, a co-extruded film for the balloon envelope, and structural integrity provided by the highest strength-to-weight fibers commercially available. The ULDB vehicle development is complemented by a new ballooncraft support system that provides power, data handling and communications via a Tracking and Data Relay Satellite System (TDRSS) high gain antenna capable of 100 Kb/s real-time telemetry. Another technology key to realizing the full ULDB potential is an active balloon trajectory control system, which is now only in the design stage. C1 NASA Headquarters, Sci Mission Directorate, Washington, DC 20546 USA. RP Jones, WV (reprint author), NASA Headquarters, Sci Mission Directorate, Washington, DC 20546 USA. NR 8 TC 1 Z9 1 U1 0 U2 0 PU TATA INST FUNDAMENTAL RESEARCH PI MUMBAI PA HOMI BHABHA MARG, NAVY NAGAR, COLABA, MUMBAI, MH-400005, INDIA PY 2005 BP 173 EP 184 PG 12 WC Astronomy & Astrophysics; Instruments & Instrumentation; Physics, Particles & Fields SC Astronomy & Astrophysics; Instruments & Instrumentation; Physics GA BFO88 UT WOS:000243522500011 ER PT B AU Wiedenbeck, ME Davis, AJ Leske, RA Binns, WR Cohen, CMS Cummings, AC de Nolfo, G Israel, MH Labrador, AW Mewaldt, RA Scott, LM Stone, EC von Rosenvinge, TT AF Wiedenbeck, M. E. Davis, A. J. Leske, R. A. Binns, W. R. Cohen, C. M. S. Cummings, A. C. de Nolfo, G. Israel, M. H. Labrador, A. W. Mewaldt, R. A. Scott, L. M. Stone, E. C. von Rosenvinge, T. T. GP Tata Institute Fundamental Res TI The level of solar modulation of galactic cosmic rays from 1997 to 2005 as derived from ACE measurements of elemental energy spectra SO Proceedings of the 29th International Cosmic Ray Conference, Vol 2: SH3 LA English DT Proceedings Paper CT 29th International Cosmic Ray Conference CY AUG 03-10, 2005 CL Pune, INDIA SP Forsch Zentrum Karsruhe Inst Kernphys, Univ Karlsruhe, Inst Expt Kemphys, Tata Inst Fundamental Res, Int Union Pure & Appl Phys C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Wiedenbeck, ME (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RI de Nolfo, Georgia/E-1500-2012 NR 8 TC 0 Z9 0 U1 0 U2 1 PU TATA INST FUNDAMENTAL RESEARCH PI MUMBAI PA HOMI BHABHA MARG, NAVY NAGAR, COLABA, MUMBAI, MH-400005, INDIA PY 2005 BP 277 EP 280 PG 4 WC Astronomy & Astrophysics; Instruments & Instrumentation; Physics, Particles & Fields SC Astronomy & Astrophysics; Instruments & Instrumentation; Physics GA BFP18 UT WOS:000243556700075 ER PT B AU Tripathi, RK AF Tripathi, R. K. GP Tata Institute Fundamental Res TI Space exploration: Where we have been, where we are and where we are going - A human perspective SO Proceedings of the 29th International Cosmic Ray Conference, Vol 2: SH3 LA English DT Proceedings Paper CT 29th International Cosmic Ray Conference CY AUG 03-10, 2005 CL Pune, INDIA SP Forsch Zentrum Karsruhe Inst Kernphys, Univ Karlsruhe, Inst Expt Kemphys, Tata Inst Fundamental Res, Int Union Pure & Appl Phys AB NASA is moving forward towards the agency's new vision for space exploration in the 21(st) Century encompassing a broad range of human and robotic missions including missions to Moon, Mars and beyond. Exposure from the hazards of severe space radiation in deep space long duration missions is 'the show stopper.' Langley has developed state-of-the-art radiation protection and shielding technology for space missions. The payload penalty demands a very stringent requirement on the design of the spacecrafts for human deep space missions. The exploration beyond low Earth orbit (LEO) to enable routine access to more interesting regions of space will require protection from-the hazards of the accumulated exposures of space radiation, Galactic Cosmic Rays (GCR) and Solar Particle Events (SPE), and minimizing the production of secondary radiation is a great advantage. The better understanding of radiation environment (GCR & SPE) and their interaction is a key to the success of the program due to the vital role and importance of cosmic rays for space missions. C1 NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Tripathi, RK (reprint author), NASA, Langley Res Ctr, Hampton, VA 23681 USA. NR 5 TC 0 Z9 0 U1 1 U2 1 PU TATA INST FUNDAMENTAL RESEARCH PI MUMBAI PA HOMI BHABHA MARG, NAVY NAGAR, COLABA, MUMBAI, MH-400005, INDIA PY 2005 BP 437 EP 440 PG 4 WC Astronomy & Astrophysics; Instruments & Instrumentation; Physics, Particles & Fields SC Astronomy & Astrophysics; Instruments & Instrumentation; Physics GA BFP18 UT WOS:000243556700116 ER PT B AU De Nolfo, GA Barbier, LM Binns, WR Cummings, JR Geier, S Israel, MH Link, JT Mewaldt, RA Mitchell, JW Rauch, BF Schindler, SM Scott, LM Stone, EC Streitmatter, RE Waddington, CJ Wiedenbeck, ME AF de Nolfo, G. A. Barbier, L. M. Binns, W. R. Cummings, J. R. Geier, S. Israel, M. H. Link, J. T. Mewaldt, R. A. Mitchell, J. W. Rauch, B. F. Schindler, S. M. Scott, L. M. Stone, E. C. Streitmatter, R. E. Waddington, C. J. Wiedenbeck, M. E. GP Tata Institut Fundamental Res TI Co/Ni Ratio Between 0.8-5 GeV/nucleon from TIGER-2001 SO Proceedings of the 29th International Cosmic Ray Conference, Vol 3: OG1 LA English DT Proceedings Paper CT 29th International Cosmic Ray Conference CY AUG 03-10, 2005 CL Pune, INDIA SP Forsch Zentrum Karsruhe Inst Kernphys, Univ Karlsruhe, Inst Expt Kemphys, Tata Inst Fundamental Res, Int Union Pure & Appl Phys ID COSMIC-RAY NUCLEI; ISOTOPIC COMPOSITION; CROSS-SECTIONS; TIME-DELAY; NUCLEOSYNTHESIS; ACCELERATION; CONSTRAINTS; ABUNDANCES; HYDROGEN; NICKEL AB The 2001 flight of TIGER lasted 31.8 days and collected sufficient statistics to study the Co/Ni elemental ratio over a wide range in energies. We present the elemental ratio of Co/Ni in galactic cosmic rays between similar to 0.80-5 GeV/nucleon and compare our results with previous measurements and propagation models. C1 Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP De Nolfo, GA (reprint author), Goddard Space Flight Ctr, Code 661, Greenbelt, MD 20771 USA. RI de Nolfo, Georgia/E-1500-2012 NR 16 TC 0 Z9 0 U1 0 U2 0 PU TATA INST FUNDAMENTAL RESEARCH PI MUMBAI PA HOMI BHABHA MARG, NAVY NAGAR, COLABA, MUMBAI, MH-400005, INDIA PY 2005 BP 61 EP 64 PG 4 WC Astronomy & Astrophysics; Instruments & Instrumentation; Physics, Particles & Fields SC Astronomy & Astrophysics; Instruments & Instrumentation; Physics GA BFO86 UT WOS:000243522100016 ER PT B AU Hams, T Abe, K Fuke, H Haino, S Kim, KC Kumazawa, T Lee, MH Makida, Y Matsuda, S Matsumoto, H Matsumoto, K Mitchell, JW Moiseev, AA Myers, ZD Nishimura, J Nozaki, M Ogata, A Oikawa, M Ormes, JF Sasaki, M Seo, ES Shikaze, Y Streitmatter, RE Suzuki, J Takeuchi, K Tanaka, K Taniguci, T Yamagami, T Yamamoto, A Yoshida, T Yoshimura, K AF Hams, T. Abe, K. Fuke, H. Haino, S. Kim, K. C. Kumazawa, T. Lee, M. H. Makida, Y. Matsuda, S. Matsumoto, H. Matsumoto, K. Mitchell, J. W. Moiseev, A. A. Myers, Z. D. Nishimura, J. Nozaki, M. Ogata, A. Oikawa, M. Ormes, J. F. Sasaki, M. Seo, E. S. Shikaze, Y. Streitmatter, R. E. Suzuki, J. Takeuchi, K. Tanaka, K. Taniguci, T. Yamagami, T. Yamamoto, A. Yoshida, T. Yoshimura, K. GP Tata Institut Fundamental Res TI Flight performance of the BESS-Polar aerogel Cherenkov counter SO Proceedings of the 29th International Cosmic Ray Conference, Vol 3: OG1 LA English DT Proceedings Paper CT 29th International Cosmic Ray Conference CY AUG 03-10, 2005 CL Pune, INDIA SP Forsch Zentrum Karsruhe Inst Kernphys, Univ Karlsruhe, Inst Expt Kemphys, Tata Inst Fundamental Res, Int Union Pure & Appl Phys AB The BESS-Polar balloon payload had its first flight on December 13th-21st, 2004 (UTC) from McMurdo Station, Antarctica. The flight duration was over eight days and more than 9 x 108 cosmic-ray events were recorded. An overview of the BESS-Polar flight, the status of the antiproton analysis, and a discussion of the low-power readout electronics and data acquisition system can be found elsewhere in these proceedings. In this paper we discuss the design, testing, and flight performance of the BESS-Polar Cherenkov counter, which operated in ambient conditions outside a pressure vessel. The silica-aerogel Cherenkov radiator had a nominal index-of-refraction, n = 1.02, yielding an lower limit for the most likely photoelectron (PE) number of 7 in the center of the counter and 9 near the photomultiplier tubes. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Hams, T (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. OI Seo, Eun-Suk/0000-0001-8682-805X NR 6 TC 0 Z9 0 U1 0 U2 0 PU TATA INST FUNDAMENTAL RESEARCH PI MUMBAI PA HOMI BHABHA MARG, NAVY NAGAR, COLABA, MUMBAI, MH-400005, INDIA PY 2005 BP 69 EP 72 PG 4 WC Astronomy & Astrophysics; Instruments & Instrumentation; Physics, Particles & Fields SC Astronomy & Astrophysics; Instruments & Instrumentation; Physics GA BFO86 UT WOS:000243522100018 ER PT B AU Streitmatter, RE Jones, FC AF Streitmatter, R. E. Jones, F. C. GP Tata Institut Fundamental Res TI Superbubbles and local cosmic rays SO Proceedings of the 29th International Cosmic Ray Conference, Vol 3: OG1 LA English DT Proceedings Paper CT 29th International Cosmic Ray Conference CY AUG 03-10, 2005 CL Pune, INDIA SP Forsch Zentrum Karsruhe Inst Kernphys, Univ Karlsruhe, Inst Expt Kemphys, Tata Inst Fundamental Res, Int Union Pure & Appl Phys ID MAGNETIC-FIELD AB Soon after the discovery of supershells in the late 1970s, it was suggested that the Solar system was located in the interior of such a shell, and that some features of the observed cosmic radiation might be explained by this fact [1], [2], [3]. Since that time, evidence from low-energy isotopic composition and K-capture nuclei [4], [5] has lent strength to models [6] of cosmic ray origin in which acceleration takes place in the environment of a superbubble. In the same period, observations of high-energy spectra have been dramatically improved, e.g. [7]. Here, we reconsider the possible consequences of generation and confinement of cosmic radiation within a superbubble. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Streitmatter, RE (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. NR 16 TC 0 Z9 0 U1 0 U2 0 PU TATA INST FUNDAMENTAL RESEARCH PI MUMBAI PA HOMI BHABHA MARG, NAVY NAGAR, COLABA, MUMBAI, MH-400005, INDIA PY 2005 BP 157 EP 160 PG 4 WC Astronomy & Astrophysics; Instruments & Instrumentation; Physics, Particles & Fields SC Astronomy & Astrophysics; Instruments & Instrumentation; Physics GA BFO86 UT WOS:000243522100040 ER PT B AU Jones, FC Streitmatter, RE AF Jones, F. C. Streitmatter, R. E. GP Tata Institut Fundamental Res TI Statistical mechanics of supernovae revisited SO Proceedings of the 29th International Cosmic Ray Conference, Vol 3: OG1 LA English DT Proceedings Paper CT 29th International Cosmic Ray Conference CY AUG 03-10, 2005 CL Pune, INDIA SP Forsch Zentrum Karsruhe Inst Kernphys, Univ Karlsruhe, Inst Expt Kemphys, Tata Inst Fundamental Res, Int Union Pure & Appl Phys AB We have performed Monte Carlo calculations to study the spectrum arising from supernovae occuring at random times and positions. Each supernova injects an E-2.2 power law spectrum and the diffusion coefficient varies as E-0.5. The resulting spectrum appears normal for energies below 10(16) eV but above this energy the spectrum shows considerable variation from one realization to another and shows a lack of ultra high energy particles. It appears that obtaining ultra high energy particles requires a large number of supernovae at large distances from the observation point. C1 NASA, Goddard Space Flight Ctr, Explorat Universe Div, Greenbelt, MD 20771 USA. RP Jones, FC (reprint author), NASA, Goddard Space Flight Ctr, Explorat Universe Div, Greenbelt, MD 20771 USA. NR 7 TC 0 Z9 0 U1 0 U2 0 PU TATA INST FUNDAMENTAL RESEARCH PI MUMBAI PA HOMI BHABHA MARG, NAVY NAGAR, COLABA, MUMBAI, MH-400005, INDIA PY 2005 BP 217 EP 220 PG 4 WC Astronomy & Astrophysics; Instruments & Instrumentation; Physics, Particles & Fields SC Astronomy & Astrophysics; Instruments & Instrumentation; Physics GA BFO86 UT WOS:000243522100055 ER PT B AU Jones, WV Pierce, D Gregory, D Said, M Fairbrother, D Stuchlik, D Reddish, J Thompson, L Estep, R Merritt, B Cathey, H Bohaboj, T Garde, G Young, L AF Jones, W. V. Pierce, D. Gregory, D. Said, M. Fairbrother, D. Stuchlik, D. Reddish, J. Thompson, L. Estep, R. Merritt, B. Cathey, H. Bohaboj, T. Garde, G. Young, L. GP Tata Institut Fundamental Res TI Meeting the challenge of balloon-borne science missions SO Proceedings of the 29th International Cosmic Ray Conference, Vol 3: OG1 LA English DT Proceedings Paper CT 29th International Cosmic Ray Conference CY AUG 03-10, 2005 CL Pune, INDIA SP Forsch Zentrum Karsruhe Inst Kernphys, Univ Karlsruhe, Inst Expt Kemphys, Tata Inst Fundamental Res, Int Union Pure & Appl Phys AB The National Aeronautics and Space Administration (NASA) Balloon Program is committed to meeting the challenge of the science community to enable extended duration and global scientific investigations based on the development of advanced balloon vehicles and support systems. It is also committed to inspiring future generations of scientists and engineers through active educational outreach activities and student launch programs. The Swedish Space Corporation/Esrange and NASA inaugurated a joint capability for medium-duration heavy-load scientific balloon flights from Sweden to Canada or Alaska beginning in June 2005. This capability will complement the NASA/U.S. National Science Foundation (NSF) Office of Polar Programs achievement of more than a decade of successful long-duration flights around Antarctica. Typically, Antarctic flights circumnavigate the South Pole one time, in 8 to 20 days using conventional zero differential pressure balloons. One flight has circumnavigated twice in 31 days, and another went three times around in 42 days. A new super-pressure (constant volume) balloon is currently under development for future flights of 60 to 100 days at any latitude. C1 NASA, Sci Miss Directorate, Washington, DC 20546 USA. RP Jones, WV (reprint author), NASA, Sci Miss Directorate, Washington, DC 20546 USA. NR 5 TC 0 Z9 0 U1 1 U2 1 PU TATA INST FUNDAMENTAL RESEARCH PI MUMBAI PA HOMI BHABHA MARG, NAVY NAGAR, COLABA, MUMBAI, MH-400005, INDIA PY 2005 BP 401 EP 404 PG 4 WC Astronomy & Astrophysics; Instruments & Instrumentation; Physics, Particles & Fields SC Astronomy & Astrophysics; Instruments & Instrumentation; Physics GA BFO86 UT WOS:000243522100101 ER PT B AU Jones, WV Pierce, D Gregory, D Said, M Fairbrother, D Stuchlik, D Reddish, J Thompson, L Estep, R Merritt, B Cathey, H Bohaboj, T Garde, G Young, L AF Jones, W. V. Pierce, D. Gregory, D. Said, M. Fairbrother, D. Stuchlik, D. Reddish, J. Thompson, L. Estep, R. Merritt, B. Cathey, H. Bohaboj, T. Garde, G. Young, L. GP Tata Institut Fundamental Res TI Ultra long duration ballooning technology development SO Proceedings of the 29th International Cosmic Ray Conference, Vol 3: OG1 LA English DT Proceedings Paper CT 29th International Cosmic Ray Conference CY AUG 03-10, 2005 CL Pune, INDIA SP Forsch Zentrum Karsruhe Inst Kernphys, Univ Karlsruhe, Inst Expt Kemphys, Tata Inst Fundamental Res, Int Union Pure & Appl Phys AB The National Aeronautics and Space Administration (NASA) Balloon Program is pursuing development of a super-pressure balloon that offers a new capability for balloon-borne science investigations by enabling extended duration missions at non-polar latitudes. The key development is an Ultra Long Duration Balloon (ULDB) system capable of flying at a nearly constant density altitude for up to 100 days at any latitude. The technology advancements include utilization of a new structural design, a co-extruded film for the balloon envelope, and structural integrity provided by the highest strength-to-weight fibers commercially available. The ULDB vehicle will be complemented with a newly developed and flight-tested ballooncraft support system. The system will provide power, data handling and communications via a Tracking and Data Relay Satellite System (TDRSS) high gain antenna capable of 100 Kb/s real-time telemetry. Another technology key to realizing this new capability is an active balloon trajectory control system, now in the design stage. ULDB missions would continue the ballooning tradition of training the next generation of instrument builders while facilitating world-class science investigations by a large community of scientists. C1 NASA, Sci Miss Directorate, Washington, DC 20546 USA. RP Jones, WV (reprint author), NASA, Sci Miss Directorate, Washington, DC 20546 USA. NR 6 TC 0 Z9 0 U1 1 U2 1 PU TATA INST FUNDAMENTAL RESEARCH PI MUMBAI PA HOMI BHABHA MARG, NAVY NAGAR, COLABA, MUMBAI, MH-400005, INDIA PY 2005 BP 405 EP 408 PG 4 WC Astronomy & Astrophysics; Instruments & Instrumentation; Physics, Particles & Fields SC Astronomy & Astrophysics; Instruments & Instrumentation; Physics GA BFO86 UT WOS:000243522100102 ER PT B AU Sasaki, M Goodwin, PA Haino, S Hams, T Ikeda, N Matsuda, S Mitchell, JW Nozaki, M Ryan, LF Singh, S Streitmatter, RE Takasugi, Y Takeuchi, K Tanizaki, K Yamato, K Yoshida, T AF Sasaki, M. Goodwin, P. A. Haino, S. Hams, T. Ikeda, N. Matsuda, S. Mitchell, J. W. Nozaki, M. Ryan, L. F. Singh, S. Streitmatter, R. E. Takasugi, Y. Takeuchi, K. Tanizaki, K. Yamato, K. Yoshida, T. GP Tata Institut Fundamental Res TI Low power front-end electronics for the BESS-polar time-of-flight counter and aerogel Cherenkov counter SO Proceedings of the 29th International Cosmic Ray Conference, Vol 3: OG1 LA English DT Proceedings Paper CT 29th International Cosmic Ray Conference CY AUG 03-10, 2005 CL Pune, INDIA SP Forsch Zentrum Karsruhe Inst Kernphys, Univ Karlsruhe, Inst Expt Kemphys, Tata Inst Fundamental Res, Int Union Pure & Appl Phys AB The BESS experiment has measured cosmic-rays at low geomagnetic cutoff for more than a decade and has found suggestive and important results. To study these phenomena further, we planned a long duration flight in Antarctica to accumulate statistics with an instrument built specifically for that purpose. To adapt to the particular requirements of the Antarctica flight, we developed low-power Front-End-Electronics (FEE) using techniques originally developed for space instruments at Goddard Space Flight Center. A Digital Signal Processor (DSP) was resident on each FEE board and controlled each board independently to maximize the data throughput rate. The power consumption of the time-to-digital converter was about 0.5 W per channel and data processing time of one event was less than 30 microseconds. The data obtained by the FEE were sent to an event-builder subsystem board which converted the data format to be handled by a USB 2.0 controller chip. A Compact PCI embedded computing system gathered these data through USB 2.0 ports and built the complete event data including the tracking information. The event data were recorded on an array of hard disk drives (HDD) with total capacity of 3.6 terabytes. This system was flown nearly 9 days over Antarctica successfully recording cosmic-ray events. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Sasaki, M (reprint author), NASA, Goddard Space Flight Ctr, Code 661, Greenbelt, MD 20771 USA. NR 7 TC 0 Z9 0 U1 0 U2 0 PU TATA INST FUNDAMENTAL RESEARCH PI MUMBAI PA HOMI BHABHA MARG, NAVY NAGAR, COLABA, MUMBAI, MH-400005, INDIA PY 2005 BP 421 EP 424 PG 4 WC Astronomy & Astrophysics; Instruments & Instrumentation; Physics, Particles & Fields SC Astronomy & Astrophysics; Instruments & Instrumentation; Physics GA BFO86 UT WOS:000243522100106 ER PT B AU Watts, J Adams, JH Bashindzhagyan, G Batkov, KE Chang, J Christl, M Fazely, AR Ganel, O Gunasingha, RM Guzik, TG Isbert, J Kim, KC Kouznetsov, E Panasyuk, M Panov, A Schmidt, WKH Seo, ES Sina, R Sokolskaya, NV Wang, JZ Wefel, JP Wu, J Zatsepin, V AF Watts, J. Adams, J. H. Bashindzhagyan, G. Batkov, K. E. Chang, J. Christl, M. Fazely, A. R. Ganel, O. Gunasingha, R. M. Guzik, T. G. Isbert, J. Kim, K. C. Kouznetsov, E. Panasyuk, M. Panov, A. Schmidt, W. K. H. Seo, E. S. Sina, R. Sokolskaya, N. V. Wang, J. Z. Wefel, J. P. Wu, J. Zatsepin, V. GP Tata Inst Fundamental Res TI Simulation of the ATIC-2 silicon matrix for protons and helium GCR primaries at 0.3, 10, and 25 TeV/nucleon SO Proceedings of the 29th International Cosmic Ray Conference, Vol 6: HE 1.1, 1.2 & 1.3 LA English DT Proceedings Paper CT 29th International Cosmic Ray Conference CY AUG 03-10, 2005 CL Pune, INDIA SP Forsch Zentrum Karsruhe Inst Kernphys, Univ Karlsruhe, Inst Expt Kemphys, Tata Inst Fundamental Res, Int Union Pure & Appl Phys AB The energy deposition distribution for protons and helium galactic cosmic ray primaries at 0.3, 10, and 25 TeV/nucleon in the ATIC-2 silicon matrix detector are simulated with GEANT4. C1 NASA, George C Marshall Space Flight Ctr, Huntsville, AL 35812 USA. RP Watts, J (reprint author), NASA, George C Marshall Space Flight Ctr, XD12, Huntsville, AL 35812 USA. OI Seo, Eun-Suk/0000-0001-8682-805X NR 1 TC 0 Z9 0 U1 0 U2 0 PU TATA INST FUNDAMENTAL RESEARCH PI MUMBAI PA HOMI BHABHA MARG, NAVY NAGAR, COLABA, MUMBAI, MH-400005, INDIA PY 2005 BP 89 EP 92 PG 4 WC Astronomy & Astrophysics; Instruments & Instrumentation; Physics, Particles & Fields SC Astronomy & Astrophysics; Instruments & Instrumentation; Physics GA BFO89 UT WOS:000243522600023 ER PT B AU Freeh, JE Steffen, CJ Larosiliere, LM AF Freeh, Joshua E. Steffen, Christopher J., Jr. Larosiliere, Louis M. BE Shah, RK Ubong, EU Samuelsen, S TI Off-design performance analysis of a solid-oxide fuel celugas turbine hybrid for auxiliary aerospace power SO Proceedings of the 3rd International Conference on Fuel Cell Science, Engineering, and Technology LA English DT Proceedings Paper CT 3rd International Conference on Fuel Cell Science, Engineering and Technology CY MAY 23-25, 2005 CL Ypsilanti, MI SP ASME, Nanotechnol Inst, Rochester Inst Technol AB A solid-oxide fuel cell/gas turbine hybrid system for auxiliary aerospace power is analyzed using 0-D and 1-D system-level models. The system is designed to produce 440kW of net electrical power, sized for a typical long-range 300-passenger civil airplane, at both sea level and cruise flight level (12,500m). In addition, a part power level of 250kW is analyzed at the cruise condition, a requirement of the operating power profile. The challenge of creating a balanced system for the three distinct conditions is presented, along with the compromises necessary for each case. A parametric analysis is described for the cruise part power operating point, in which the system efficiency is maximized by varying the air flow rate. The system is compared to an earlier version that was designed solely for cruise operation. The results show that it is necessary to size the turbomachinery, fuel cell, and heat exchangers at sea level full power rather than cruise full power. The resulting estimated mass of the system is 1912 kg, which is significantly higher than the original cruise design point mass, 1396 kg. The net thermal efficiencies with respect to the fuel LHV are calculated to be 42.4% at sea level full power, 72.6% at cruise full power, and 72.8% at cruise part power. The cruise conditions take advantage of pre-compressed air from the onboard Environmental Control System, which accounts for a portion of the unusually high thermal efficiency at those conditions. These results show that it is necessary to include several operating points in the overall assessment of an aircraft power system due to the variations throughout the operating profile. C1 NASA, John N Glenn Res Ctr Lewis Field, Cleveland, OH 44135 USA. RP Freeh, JE (reprint author), NASA, John N Glenn Res Ctr Lewis Field, Cleveland, OH 44135 USA. NR 12 TC 1 Z9 1 U1 2 U2 3 PU AMER SOC MECHANICAL ENGINEERS PI NEW YORK PA THREE PARK AVENUE, NEW YORK, NY 10016-5990 USA BN 0-7918-3764-5 PY 2005 BP 265 EP 272 PG 8 WC Electrochemistry; Energy & Fuels SC Electrochemistry; Energy & Fuels GA BFO19 UT WOS:000243400200037 ER PT S AU Johnson, NL AF Johnson, NL BE Danesy, D TI Orbital debris research in the US SO Proceedings of the 4th European Conference on Space Debris SE ESA SPECIAL PUBLICATIONS LA English DT Proceedings Paper CT 4th European Conference on Space Debris CY APR 18-20, 2005 CL Darmstadt, GERMANY SP European Space Agcy, ESOC AB Considerations in the U.S. of the hazards of orbital debris date back to the 1960's, and formal research into the origins and character of the orbital debris population, as well as the means to mitigate its growth, has now been underway for more than 25 years. From a fledgling endeavor at the NASA Johnson Space Center, orbital debris research in the U.S. now encompasses activities by multiple U.S. Government agencies and academia, utilizing a wide variety of terrestrial- and space-based sensors and taking advantage of the examinations of satellite surfaces, to measure, to model, and to mitigate the current and potential future orbital debris population. These labors have led to the development of national orbital debris mitigation policies and guidelines and the promotion by the U.S. of orbital debris mitigation within the international aerospace community. C1 NASA, Johnson Space Ctr, Houston, TX 77058 USA. RP Johnson, NL (reprint author), NASA, Johnson Space Ctr, 2101 NASA Pkway,Mail Code KX, Houston, TX 77058 USA. NR 0 TC 0 Z9 0 U1 0 U2 0 PU ESA PUBLICATIONS DIVISION C/O ESTEC PI 2200 AG NOORDWIJK PA PO BOX 299, 2200 AG NOORDWIJK, NETHERLANDS SN 0379-6566 BN 92-9092-898-0 J9 ESA SP PUBL PY 2005 VL 587 BP 5 EP 10 PG 6 WC Engineering, Aerospace SC Engineering GA BDY71 UT WOS:000236213600001 ER PT S AU Matney, MJ AF Matney, MJ BE Danesy, D TI Uncertainty in orbital debris measurements and models SO Proceedings of the 4th European Conference on Space Debris SE ESA SPECIAL PUBLICATIONS LA English DT Proceedings Paper CT 4th European Conference on Space Debris CY APR 18-20, 2005 CL Darmstadt, GERMANY SP European Space Agcy, ESOC ID SMALL SIGNALS AB The orbital debris environment is described in the form of mathematical models. However, all models and the measurements they are based upon are subject to uncertainty. Measuring instruments never really measure exactly what it is we want to know - they always measure some auxiliary quantity. Knowledge of the limitations of the instruments (measurement uncertainty) is only half the problem. The actual transformation of the data into models adds more uncertainty to the final model result. In this paper, I provide examples of the basic types of uncertainties that we encounter in making orbital debris measurements. I outline the distinctions between Bayesian and frequentist interpretations of statistics and how this influences the types of conclusions one should or should not draw from uncertainty assessments. I also outline how uncertainties tie into such calculations as probabilistic risk assessments (PRAs), and the benefits and pitfalls of such analyses. C1 NASA, Johnson Space Ctr, Houston, TX 77058 USA. RP Matney, MJ (reprint author), NASA, Johnson Space Ctr, 2101 NASA Pkway,Mail Code KX, Houston, TX 77058 USA. NR 7 TC 0 Z9 0 U1 0 U2 0 PU ESA PUBLICATIONS DIVISION C/O ESTEC PI 2200 AG NOORDWIJK PA PO BOX 299, 2200 AG NOORDWIJK, NETHERLANDS SN 0379-6566 BN 92-9092-898-0 J9 ESA SP PUBL PY 2005 VL 587 BP 47 EP 52 PG 6 WC Engineering, Aerospace SC Engineering GA BDY71 UT WOS:000236213600007 ER PT S AU Stansbery, G Foster, JL AF Stansbery, G Foster, JL BE Danesy, D TI Completeness of measurements of the orbital debris environment SO Proceedings of the 4th European Conference on Space Debris SE ESA SPECIAL PUBLICATIONS LA English DT Proceedings Paper CT 4th European Conference on Space Debris CY APR 18-20, 2005 CL Darmstadt, GERMANY SP European Space Agcy, ESOC AB A great amount of effort has gone into making measurements of the orbital debris environment using a variety of methods and instruments. The aggregate of measurements provides a good overall characterization of the environment. However, each instrument or technique has inherent limitations. In situ measurements using returned surfaces, such as LDEF, are limited by finite surface area and discrete altitudes and time on orbit. Statistical measurements using radars and telescopes are limited by sensitivity and geographical location. The U.S. Space Surveillance Network catalog is incomplete since it also relies on radar and optical measurements as well. Understanding the limitations with each technique can provide insight into the limitations in the broad characterization of the debris environment. This paper will explore the major limitations of individual measurement techniques and their implications for understanding the overall orbital debris environment. C1 NASA, Johnson Space Ctr, Houston, TX 77058 USA. RP Stansbery, G (reprint author), NASA, Johnson Space Ctr, 2101 NASA Pkway,Mail Code KX, Houston, TX 77058 USA. NR 5 TC 4 Z9 4 U1 1 U2 1 PU ESA PUBLICATIONS DIVISION C/O ESTEC PI 2200 AG NOORDWIJK PA PO BOX 299, 2200 AG NOORDWIJK, NETHERLANDS SN 0379-6566 BN 92-9092-898-0 J9 ESA SP PUBL PY 2005 VL 587 BP 95 EP 100 PG 6 WC Engineering, Aerospace SC Engineering GA BDY71 UT WOS:000236213600015 ER PT S AU Barker, E Jarvis, K Africano, J Jorgensen, K Parr-Thumm, T Matney, M Stansbery, G AF Barker, E Jarvis, K Africano, J Jorgensen, K Parr-Thumm, T Matney, M Stansbery, G BE Danesy, D TI The GEO environment as determined by the CDT between 1998 and 2002 SO Proceedings of the 4th European Conference on Space Debris SE ESA SPECIAL PUBLICATIONS LA English DT Proceedings Paper CT 4th European Conference on Space Debris CY APR 18-20, 2005 CL Darmstadt, GERMANY SP European Space Agcy, ESOC AB The National Aeronautics and Space Administration (NASA) observed the geosynchronous environment (GEO similar to 36000 km) with the 0.6m CCD Debris Telescope (CDT) at Cloudcroft, NM, between January 1998 and December 2001. The datasets have been analyzed on a year-to-year basis; this paper will intercompare the datasets to examine similarities and differences of the annual results. The CDT was operated in a GEO stare mode reaching a limiting magnitude of 17(th) which corresponds to a limiting diameter for a similar to 60 cm sphere (assuming a specular reflection and a 0.2 albedo). Observational and reduction techniques have improved over the CDT performance and analysis period. The entire CDT dataset has now been uniformly corrected for observed range, phase angle, and solar distance. The complete GEO dataset for the CDT will be presented in the context of distributions such as inclination, Right Ascension of the Ascending Node (RAAN), mean motion, and magnitude (size). Fluxes will be addressed in a subsequent paper. C1 NASA, Johnson Space Ctr, Houston, TX 77058 USA. RP Barker, E (reprint author), NASA, Johnson Space Ctr, 2101 NASA Pkway,Mail Code KX, Houston, TX 77058 USA. NR 10 TC 0 Z9 0 U1 0 U2 0 PU ESA PUBLICATIONS DIVISION C/O ESTEC PI 2200 AG NOORDWIJK PA PO BOX 299, 2200 AG NOORDWIJK, NETHERLANDS SN 0379-6566 BN 92-9092-898-0 J9 ESA SP PUBL PY 2005 VL 587 BP 135 EP 140 PG 6 WC Engineering, Aerospace SC Engineering GA BDY71 UT WOS:000236213600022 ER PT S AU Johnson, NL AF Johnson, NL BE Danesy, D TI A new look at nuclear power sources and space debris SO Proceedings of the 4th European Conference on Space Debris SE ESA SPECIAL PUBLICATIONS LA English DT Proceedings Paper CT 4th European Conference on Space Debris CY APR 18-20, 2005 CL Darmstadt, GERMANY SP European Space Agcy, ESOC AB The last satellite containing a nuclear power source (NPS) and intended for operations in Earth orbit was launched in 1988. However, a renewed interest in radioisotope power systems (RPS) and nuclear propulsion could lead to new NPS in orbit about the Earth. Previous NPS risk assessments, particularly those performed for the Scientific and Technical Subcommittee of the United Nations' Committee on the Peaceful Uses of Outer Space, have employed older space debris environment models. The present paper employs current environment models and examines the potential effects of collisions between NPS satellites and space debris to both the near-Earth space environment and the terrestrial environment. Harmful collisions between NPS and space debris are unlikely on an annual basis, but the long durations of most NPS in Earth orbit lead to significantly higher total collision probabilities. Disposal plans for new spacecraft with NPS designed to remain in Earth orbit should be developed early in the design phase and should be compatible with internationally accepted space debris mitigation guidelines. C1 NASA, Johnson Space Ctr, Houston, TX 77058 USA. RP Johnson, NL (reprint author), NASA, Johnson Space Ctr, 2101 NASA Pkway,Mail Code KX, Houston, TX 77058 USA. NR 14 TC 0 Z9 0 U1 0 U2 1 PU ESA PUBLICATIONS DIVISION C/O ESTEC PI 2200 AG NOORDWIJK PA PO BOX 299, 2200 AG NOORDWIJK, NETHERLANDS SN 0379-6566 BN 92-9092-898-0 J9 ESA SP PUBL PY 2005 VL 587 BP 551 EP 555 PG 5 WC Engineering, Aerospace SC Engineering GA BDY71 UT WOS:000236213600089 ER PT S AU Ratliff, JM AF Ratliff, JM BE Danesy, D TI Approaches to assessing spacecraft survival in the space debris environment SO Proceedings of the 4th European Conference on Space Debris SE ESA SPECIAL PUBLICATIONS LA English DT Proceedings Paper CT 4th European Conference on Space Debris CY APR 18-20, 2005 CL Darmstadt, GERMANY SP European Space Agcy, ESOC AB An assessment of potential damage to a spacecraft is necessary in order to estimate the risk to mission objectives from meteoroid and orbital debris impacts. A comprehensive assessment may be beyond a flight project's scope for technical, cost, or schedule reasons, thereby encouraging flight-projects' inclinations to completely ignore the risk from particle impact. However, there is a middle ground: approaches that bound the answer, or that concentrate on only the spacecraft subsystems that are most vulnerable, can contribute valuable information to an over-all project risk assessment. Several aspects of a debris damage assessment will be discussed, including the use of bounding estimates to determine areas of the spacecraft that can be ignored, the appropriateness of simplifying assumptions, calculation techniques for obtaining different levels of assessment, and advantages of different procedural options. C1 Caltech, Jet Propuls Lab, Pasadena, CA 91109 USA. RP Ratliff, JM (reprint author), Caltech, Jet Propuls Lab, Pasadena, CA 91109 USA. NR 3 TC 0 Z9 0 U1 0 U2 1 PU ESA PUBLICATIONS DIVISION C/O ESTEC PI 2200 AG NOORDWIJK PA PO BOX 299, 2200 AG NOORDWIJK, NETHERLANDS SN 0379-6566 BN 92-9092-898-0 J9 ESA SP PUBL PY 2005 VL 587 BP 713 EP 716 PG 4 WC Engineering, Aerospace SC Engineering GA BDY71 UT WOS:000236213600123 ER PT B AU Hutcheson, RS Tumer, IY AF Hutcheson, Ryan S. Tumer, Irem Y. GP ASME TI Function-based design of a spacecraft power system diagnostics testbed SO Proceedings of the ASME Design Engineering Division 2005, Pts A and B LA English DT Proceedings Paper CT ASME International Mechanical Engineering Congress and Exposition CY NOV 05-11, 2005 CL Orlando, FL SP ASME, Proc Ind Div, ASME, Rail Transportat Div, ASME, Noise Control & Acoust Div, ASME, Triol Div, ASME, Pressure Vessels & Piping Div, ASME, Bioengn Div, ASME, Mat Div, ASME, Appl Mech Div, ASME, Fluids Engn Div, ASME, Micro Elect Mech Syst Div, ASME, Heat Transfer Div, ASME, Nucl Engn Div, ASME, Power Div, ASME, Solar Energy Div, ASME, Safety Engn & Risk Anal Div, ASME, Technol & Soc Div, ASME, Adv Energy Syst Div, ASME, Aerosp Div, ASME, Comp & Informat Engn Div AB NASA's Ames Research center is currently designing a testbed to validate and compare potential Integrated System Health Management (ISHM) technologies. The proposed testbed represents a typical power system for a spacecraft and includes components such as a fuel cell, solar cells and redundant batteries. To fulfill design requirements, the testbed must be capable of hosting a wide variety of ISHM technologies including those developed by NASA as well as those developed in the aerospace industry abroad. An internal fault injection subsystem must be built into the system to provide a common interface for evaluating these different ISHM technologies. Additionally, to ensure robust operation of the testbed, the capability to detect and manage external faults must also be present. In order to develop a set of requirements for the internal fault injection subsystems as well as predict external faults, a comprehensive set of potential failures must be identified for all of the components of the testbed. To best aid the development of the testbed, these failures needed to be identified as early as the conceptual design phase, where little is known about the actual components that would comprise the finished system. This paper demonstrates the use a function-based failure mode identification method to identify the potential failures of the testbed during the conceptual design phase. Using this approach, designers can explore the potential failure modes at the functional design stage, before a form or solution has been determined. A function-failure database is used to associate the failures of components from previous design efforts to the testbed based on common functionality. The result is a list of potential failure modes and associated failure rates, which are used to improve the design of the testbed as well as provide a framework for the fault injection subsystem. C1 NASA, Ames Res Ctr, Complex Syst Design Grp, Intelligent Syst Div,Mission Crit Tech, Moffett Field, CA 94035 USA. RP Tumer, IY (reprint author), NASA, Ames Res Ctr, Complex Syst Design Grp, Intelligent Syst Div,Mission Crit Tech, Moffett Field, CA 94035 USA. NR 24 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 0-7918-4215-0 PY 2005 BP 837 EP 844 PG 8 WC Engineering, Mechanical SC Engineering GA BFI29 UT WOS:000241987200098 ER PT B AU Son, SY Allen, JS AF Son, Sang Young Allen, Jeffrey S. GP ASME TI Visualization and predictive modeling of two-phase flow regime transition with application towards water management in the gas-flow channels of PEM fuel cells SO Proceedings of the ASME Fluids Engineering Division SE FLUIDS ENGINEERING DIVISION OF THE AMERICAN SOCIETY OF MECHANICAL ENGINEERS LA English DT Proceedings Paper CT ASME International Mechanical Engineering Congress and Exposition CY NOV 05-11, 2005 CL Orlando, FL SP ASME, Proc Ind Div, ASME, Rail Transportat Div, ASME, Noise Control & Acoust Div, ASME, Triol Div, ASME, Pressure Vessels & Piping Div, ASME, Bioengn Div, ASME, Mat Div, ASME, Appl Mech Div, ASME, Fluids Engn Div, ASME, Micro Elect Mech Syst Div, ASME, Heat Transfer Div, ASME, Nucl Engn Div, ASME, Power Div, ASME, Solar Energy Div, ASME, Safety Engn & Risk Anal Div, ASME, Technol & Soc Div, ASME, Adv Energy Syst Div, ASME, Aerosp Div, ASME, Comp & Informat Engn Div ID THIN ANNULAR FILM; CYLINDRICAL CAPILLARIES; INSTABILITY; THREAD; FLUID AB Understanding the behavior of gas and water vapor flow through the microchannel gas flow passages of a proton-exchange membrane (PEM) fuel cells is critical to reliable fuel cell operation. Recent research efforts have illustrated the importance of capillarity on the behavior of two-phase flow (gas-liquid) in low Bond number systems; that is, systems where capillary forces are important relative to gravitational forces. Such systems include capillary tubes and microchannels as well as the gas flow channels of a PEM fuel cell. The key characteristic scaling factors for two-phase flow in capillaries have been determined. The choice of length scales and velocity scales in dimensionless groups used to characterize two-phase flow is critical to correctly delineating phase distribution. Traditional scaling for these types of flows have considered the interaction between gas and liquid phases to be primarily inertial in nature. The role of liquid film stability where the phase interaction is a combination of viscous and capillary effects is shown to be a more appropriate scaling for low-Bond number, low-Suratman number two-phase flows. Microscopic visualization at high frame rates has been used to identify the flow regime under various gas-liquid mass ratios, channel geometries and surface energies. The observations collected via high speed microscopy and corresponding pressure measurements are reported for square and circular cross-sectional microchannels with contact angles of 20 degrees (hydrophilic) and 70 degrees (hydrophobic). The effect of geometry and contact angle on the phase distribution and the pressure drop are dramatic. C1 NASA, Natl Ctr Space Explorat Res, Glenn Res Ctr Lewis Field, Cleveland, OH 44135 USA. RP Son, SY (reprint author), NASA, Natl Ctr Space Explorat Res, Glenn Res Ctr Lewis Field, 21000 Brookpk Rd, Cleveland, OH 44135 USA. NR 13 TC 1 Z9 1 U1 0 U2 2 PU AMER SOC MECHANICAL ENGINEERS PI NEW YORK PA THREE PARK AVENUE, NEW YORK, NY 10016-5990 USA BN 0-7918-4219-3 J9 FLUID ENG D PY 2005 VL 261 BP 461 EP 469 PG 9 WC Engineering, Mechanical SC Engineering GA BFM29 UT WOS:000243038600060 ER PT B AU McQuillen, J Sankovic, J Hall, NR AF McQuillen, John Sankovic, John Hall, Nancy Rabel GP ASME TI Multiphase flow separators in reduced gravity SO Proceedings of the ASME Fluids Engineering Division SE FLUIDS ENGINEERING DIVISION OF THE AMERICAN SOCIETY OF MECHANICAL ENGINEERS LA English DT Proceedings Paper CT ASME International Mechanical Engineering Congress and Exposition CY NOV 05-11, 2005 CL Orlando, FL SP ASME, Proc Ind Div, ASME, Rail Transportat Div, ASME, Noise Control & Acoust Div, ASME, Triol Div, ASME, Pressure Vessels & Piping Div, ASME, Bioengn Div, ASME, Mat Div, ASME, Appl Mech Div, ASME, Fluids Engn Div, ASME, Micro Elect Mech Syst Div, ASME, Heat Transfer Div, ASME, Nucl Engn Div, ASME, Power Div, ASME, Solar Energy Div, ASME, Safety Engn & Risk Anal Div, ASME, Technol & Soc Div, ASME, Adv Energy Syst Div, ASME, Aerosp Div, ASME, Comp & Informat Engn Div AB Gas phase and liquid phase separation is necessary for one of two reasons. First, system-critical components are designed to specifically operate in a single phase mode only. Pumps, especially centrifugal pumps, lose their prime when gas bubbles accumulate in the impellor housing. Turbines and compressors suffer from erosion problems when exposed to vapor laden with liquid droplets. The second reason is that system performance can be significantly enhanced by operating in a single phase mode. The condensation heat transfer coefficient can be enhanced when the liquid of an entering two-phase stream is stripped thus permitting initial direct contact of the vapor with the cold walls of the condenser. High efficiency and low mass Environmental Control and Life Support Systems invariably require multiphase processes. These systems consist of water filtration and purification via bioreactors that encounter two phase flow at the inlets from drainage streams associated with the humidity condensate, urine, food processing, and with tillage bubble effluent from storage tanks. Entrained gases in the liquid feed, could have deleterious effects on the performance of many of these systems by cavitating pumps and poisoning catalytic packed bed bioreactors. Phase separation is required in thermal management and power systems whereby it is necessary to have all vapor entering the turbine and all liquid exiting the condenser and entering the pump in order to obtain the highest reliability and performance of these systems. Power systems which utilize Proton Exchange Membrane Fuel Cells generate a humidified oxygen exit stream whereby the water vapor needs to be condensed and removed to insure reliable and efficient system operation. Gas-liquid separation can be achieved by a variety of means in low gravity. Several active and passive techniques are examined and evaluated. Ideally, a system that functions well in all gravity environments that the system experiences is a requirement. C1 NASA Glenn Res Ctr Lewis Field, Cleveland, OH 44135 USA. RP McQuillen, J (reprint author), NASA Glenn Res Ctr Lewis Field, 21000 Brookpk Rd, Cleveland, OH 44135 USA. NR 12 TC 0 Z9 0 U1 0 U2 2 PU AMER SOC MECHANICAL ENGINEERS PI NEW YORK PA THREE PARK AVENUE, NEW YORK, NY 10016-5990 USA BN 0-7918-4219-3 J9 FLUID ENG D PY 2005 VL 261 BP 737 EP 743 PG 7 WC Engineering, Mechanical SC Engineering GA BFM29 UT WOS:000243038600094 ER PT B AU Zhang, NL Chao, DF Sankovic, JM McQuillen, JB Lekan, JF AF Zhang, Nengli Chao, David F. Sankovic, John M. McQuillen, John B. Lekan, John F. GP ASME TI On analog simulation of liquid-metal flows in space Rankine-cycle power-systems SO PROCEEDINGS OF THE ASME FLUIDS ENGINEERING DIVISION SE FLUIDS ENGINEERING DIVISION OF THE AMERICAN SOCIETY OF MECHANICAL ENGINEERS LA English DT Proceedings Paper CT ASME International Mechanical Engineering Congress and Exposition CY NOV 05-11, 2005 CL Orlando, FL SP ASME, Proc Ind Div, ASME, Rail Transportat Div, ASME, Noise Control & Acoust Div, ASME, Triol Div, ASME, Pressure Vessels & Piping Div, ASME, Bioengn Div, ASME, Mat Div, ASME, Appl Mech Div, ASME, Fluids Engn Div, ASME, Micro Elect Mech Syst Div, ASME, Heat Transfer Div, ASME, Nucl Engn Div, ASME, Power Div, ASME, Solar Energy Div, ASME, Safety Engn & Risk Anal Div, ASME, Technol & Soc Div, ASME, Adv Energy Syst Div, ASME, Aerosp Div, ASME, Comp & Informat Engn Div ID BOILING HEAT-TRANSFER; THERMAL-CONDUCTIVITY; NANO-FLUIDS; NANOFLUIDS; NANOPARTICLES; ENHANCEMENT; WATER AB In the development of liquid metal Rankine cycle system, experiments using liquid metals generally cannot be conducted on the International Space Station (ISS) or the space shuttles due to a number of issues including safety. Some other fluids must be used to simulate potassium flows in a Rankine cycle. In this paper an analysis for the simulation using surrogate fluids is made. The results of the analysis indicate that single-phase liquid metal flows, either liquid or vapor, can be simulated using surrogate fluids both in ground and space experiments. For two-phase liquid-metal flow, a credible simulation with a surrogate fluid is currently not possible. For the problem of vapor-production efficiency in a boiler, a simulation using a surrogate fluid whose properties are similar to potassium is workable. A high concentration of copper nanoparticles in water (Cu-water nanofluid) is considered a potential possibility for a fluid to simulate liquid-metal turbulent flow and the boiling process. In the final stage of developing the liquid-metal Rankine-cycle system, experimental tests in a subscale liquid-metal system are still indispensable. C1 NASA Glenn Res Ctr Lewis Field, Micrograv Div, Cleveland, OH 44135 USA. RP Zhang, NL (reprint author), NASA Glenn Res Ctr Lewis Field, Micrograv Div, Cleveland, OH 44135 USA. NR 32 TC 0 Z9 0 U1 0 U2 2 PU AMER SOC MECHANICAL ENGINEERS PI NEW YORK PA THREE PARK AVENUE, NEW YORK, NY 10016-5990 USA BN 0-7918-4219-3 J9 FLUID ENG D PY 2005 VL 261 BP 755 EP 761 PG 7 WC Engineering, Mechanical SC Engineering GA BFM29 UT WOS:000243038600096 ER PT B AU Vu, BT Zysko, JA AF Vu, B. T. Zysko, J. A. GP ASME TI A CFD analysis of easterly wind flow impacting the vehicle assembly building SO Proceedings of the ASME Fluids Engineering Division Summer Conference, Vol 2 SE FLUIDS ENGINEERING DIVISION OF THE AMERICAN SOCIETY OF MECHANICAL ENGINEERS LA English DT Proceedings Paper CT ASME Fluids Engineering Division Summer Meeting CY JUN 19-23, 2005 CL Houston, TX SP ASME, Fluids Engn Div AB In an attempt to explain the high loss of panels from the south face of the Vehicle Assembly Building (VAB) during Hurricane Frances, a three-dimensional computational fluid dynamics (3-D CFD) model was developed to simulate local velocity and pressure distributions resulting from such a storm. A preconditioned compressible Navier-Stokes flow solver I was used to compute the flow field around the VAB complex, including the Launch Control Center, the Low and High Bays of the VAB, and several outbuildings in the immediate LC-39 area. The mapping of the forces and velocities on and along the affected faces of the VAB correlated surprisingly well with the extensive damage areas realized on both on the south face and on the southeast section of the roof. The model results were also consistent with the minimal damage seen on the east, north, and west faces of the structure. C1 NASA, Kennedy Space Ctr, Spaceport Engn & Technol, Kennedy Space Ctr, FL 32899 USA. RP Vu, BT (reprint author), NASA, Kennedy Space Ctr, Spaceport Engn & Technol, Kennedy Space Ctr, FL 32899 USA. NR 2 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 0-7918-4199-5 J9 FLUID ENG D PY 2005 BP 631 EP 635 PG 5 WC Engineering, Mechanical; Instruments & Instrumentation SC Engineering; Instruments & Instrumentation GA BFO76 UT WOS:000243502400091 ER PT B AU Ahmad, JU Pandya, SA Chan, WM Chaderjian, NM AF Ahmad, Jasim U. Pandya, Shishir A. Chan, William M. Chaderjian, Neal M. GP ASME TI Navier-Stokes simulation of air-conditioning facility of a large modern computer room SO Proceedings of the ASME Fluids Engineering Division Summer Conference, Vol 2 SE FLUIDS ENGINEERING DIVISION OF THE AMERICAN SOCIETY OF MECHANICAL ENGINEERS LA English DT Proceedings Paper CT ASME Fluids Engineering Division Summer Meeting CY JUN 19-23, 2005 CL Houston, TX SP ASME, Fluids Engn Div AB A 3-D full Navier-Stokes simulation of a large scale computing facility at NASA Ames Research center was carried out to assess the adequacy of the existing air handling and conditioning system. The flow simulation of this modem facility was modeled with a viscous, compressible flow solver code OVER-FLOW-2 with low Mach number pre-conditioning. A script was created to automate geometry modeling, grid generation, and flow solver input preparation. A new set of air-conditioning boundary conditions was developed and added to the flow solver. Detailed flow visualization was performed to show temperature distribution, air-flow streamlines and velocities in the computer room. C1 ELORET Inc, NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Ahmad, JU (reprint author), ELORET Inc, NASA, Ames Res Ctr, M-S T27B, Moffett Field, CA 94035 USA. NR 8 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 0-7918-4199-5 J9 FLUID ENG D PY 2005 BP 651 EP 656 PG 6 WC Engineering, Mechanical; Instruments & Instrumentation SC Engineering; Instruments & Instrumentation GA BFO76 UT WOS:000243502400095 ER PT B AU Majumdar, A Cole, H Chen, CP AF Majumdar, Alok Cole, Helen Chen, C. P. GP ASME TI Numerical modeling of flow distribution in microfluidics systems SO Proceedings of the ASME Fluids Engineering Division Summer Conference, Vol 2 SE FLUIDS ENGINEERING DIVISION OF THE AMERICAN SOCIETY OF MECHANICAL ENGINEERS LA English DT Proceedings Paper CT ASME Fluids Engineering Division Summer Meeting CY JUN 19-23, 2005 CL Houston, TX SP ASME, Fluids Engn Div AB This paper describes an application of a general purpose computer program, GFSSP (Generalized Fluid System Simulation Program) for calculating flow distribution in a network of micro-channels. GFSSP employs a finite volume formulation of mass and momentum conservation equations in a network consisting of nodes and branches. Mass conservation equation is solved for pressures at the nodes while the momentum conservation equation is solved at the branches to calculate flowrate. The system of equations describing the fluid network is solved by a numerical method that is a combination of the Newton-Raphson and successive substitution methods. The numerical results have been compared with test data and detailed CFD (computational Fluid Dynamics) calculations. The agreement between test data and predictions is satisfactory. The discrepancies between the predictions and test data can be attributed to the frictional correlation which does not include the effect of surface tension or electro-kinetic effect. C1 NASA, George C Marshall Space Flight Ctr, Huntsville, AL 35812 USA. RP Majumdar, A (reprint author), NASA, George C Marshall Space Flight Ctr, Huntsville, AL 35812 USA. NR 11 TC 0 Z9 0 U1 0 U2 3 PU AMER SOC MECHANICAL ENGINEERS PI NEW YORK PA THREE PARK AVENUE, NEW YORK, NY 10016-5990 USA BN 0-7918-4199-5 J9 FLUID ENG D PY 2005 BP 753 EP 760 PG 8 WC Engineering, Mechanical; Instruments & Instrumentation SC Engineering; Instruments & Instrumentation GA BFO76 UT WOS:000243502400112 ER PT B AU Son, SY AF Son, Sang Young GP ASME TI A visualization study of heterogeneous condensation on nano-particles in fully saturated microchannel SO Proceedings of the ASME Heat Transfer Division 2005, Vol 2 SE Heat Transfer Division of the American Society of Mechanical Engineers LA English DT Proceedings Paper CT ASME International Mechanical Engineering Congress and Exposition CY NOV 05-11, 2005 CL Orlando, FL SP ASME, Proc Ind Div, ASME, Rail Transportat Div, ASME, Noise Control & Acoust Div, ASME, Triol Div, ASME, Pressure Vessels & Piping Div, ASME, Bioengn Div, ASME, Mat Div, ASME, Appl Mech Div, ASME, Fluids Engn Div, ASME, Micro Elect Mech Syst Div, ASME, Heat Transfer Div, ASME, Nucl Engn Div, ASME, Power Div, ASME, Solar Energy Div, ASME, Safety Engn & Risk Anal Div, ASME, Technol & Soc Div, ASME, Adv Energy Syst Div, ASME, Aerosp Div, ASME, Comp & Informat Engn Div AB The high heat transfer rate and compactness of micro/minichannel mutiphase flow system associated with phase change phenomena have been increasingly attractive in thermal management and microfluidic sensor development for applications which demand requirements such as small, light, and efficient systems. In this paper, quarts square microchannels with a hydraulic diameter of 1000 pm and a length of 20 mm are used for the path of fully saturated forced convection air flow with nano-particles (Theta similar to 100 nm). The outside of microchannel wall is cooled by natural convection of room air. Two distinctive heterogeneous condensation modes are observed as of droplet condensation on the channel wall and nano-particle nucleate condensation in the core air stream. At the exit of microchannel, liquid droplets with an order of micrometer diameter are observed by microscopic visualization using Nd:YAG (532 nm) Laser sheet illumination. The droplet growth visualization data show a influence of gas mixture mass flux, local vapor concentration, and wall surface condition either on wall droplet condensation and nucleate condensation droplet. C1 NASA, GRC, Natl Ctr Space Explorat Res, Cleveland, OH USA. RP Son, SY (reprint author), NASA, GRC, Natl Ctr Space Explorat Res, Cleveland, OH USA. NR 10 TC 0 Z9 0 U1 0 U2 1 PU AMER SOC MECHANICAL ENGINEERS PI NEW YORK PA THREE PARK AVENUE, NEW YORK, NY 10016-5990 USA BN 0-7918-4221-5 J9 HEAT TRANSF DIV ASME PY 2005 VL 376-2 BP 679 EP 683 PG 5 WC Thermodynamics; Engineering, Mechanical SC Thermodynamics; Engineering GA BFM39 UT WOS:000243059900080 ER PT B AU Mehr, AF Tumer, IY AF Mehr, Ali Farhang Tumer, Irem Y. GP ASME TI A new approach to probabilistic risk analysis in concurrent and distributed design of aerospace systems SO PROCEEDINGS OF THE ASME INTERNATIONAL DESIGN ENGINEERING TECHNICAL CONFERENCES AND COMPUTERS AND INFORMATION IN ENGINEERING CONFERENCE, 2005, VOL 2, PTS A AND B LA English DT Proceedings Paper CT ASME International Design Engineering Technical Conference/Computers and Information in Engineering Conference CT 31st Design Automation Conference CY SEP 24-28, 2005-2006 CY SEP 24-28, 2005 CL Long Beach, CA CL Long Beach, CA SP ASME, Design Engn Div, ASME, Comp & Informat Engn Div ID FAILURE MODE AB NASA's space exploration vehicles, like any other complex engineering system, are susceptible to failure and ultimately loss of mission. Researchers, therefore, have devised a variety of quantitative and qualitative techniques to mitigate risk and uncertainty associated with such low-volume high-cost missions. These techniques are often adopted and implemented by various NASA centers in the form of risk management tools, procedures, or guidelines. Most of these techniques, however, aim at the later stages of the design process or during the operational phase of the mission and therefore, are not applicable to the early stages of design. In particular, since the early conceptual design is often conducted by concurrent engineering teams (and sometimes in distributed environments), most risk management methods cannot effectively capture different types of failure in both subsystem and system levels. The current risk management practice in such environments is mostly ad-hoe and based on asking "what can go wrong?" from the team members. As such, this paper presents a new approach to risk management during the initial phases of concurrent and distributed engineering design. The proposed approach, hereafter referred to as Risk and Uncertainty Based Integrated Concurrent Design (or RUBIC-Design), provides a solid rigor for using functional failure data to guide the design process throughout the design cycle. The new approach is based on the functional model of space exploration systems (or any other mission-critical engineering system for that matter) and has the capability of adjusting in real-time as the overall system evolves throughout the design process. The application of the proposed approach to both single-subsystem and multi-subsystem designs is demonstrated using a satellite reaction wheel example. C1 NASA, Ames Res Ctr, Intelligent Syst Div, Complex Syst Design Grp, Moffett Field, CA 94035 USA. RP Tumer, IY (reprint author), NASA, Ames Res Ctr, Intelligent Syst Div, Complex Syst Design Grp, Moffett Field, CA 94035 USA. EM amehr@email.arc.nasa.gov; itumer@mail.arc.nasa.gov NR 16 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 0-7918-4739-X PY 2005 BP 1215 EP 1224 PG 10 WC Computer Science, Artificial Intelligence; Engineering, Manufacturing; Engineering, Mechanical SC Computer Science; Engineering GA BFI44 UT WOS:000242014000118 ER PT B AU Sun, GY AF Sun, Guangyoung GP ASME TI Orbit motion tracking control for rotating machine with magnetic suspensions SO Proceedings of the ASME International Design Engineering Technical Conferences and Computers and Information in Engineering Conference, Vol 1, Pts A-C LA English DT Proceedings Paper CT 20th Biennial Conference on Mechanical Vibration and Noise CY SEP 24-28, 2005 CL Long Beach, CA SP ASME, Design Engn Div, ASME, Comp & Informat Engn Div ID FUZZY-LOGIC; BEARINGS AB Conventional use of active magnetic bearings (AMB) focuses on keeping a rotor centered at the zero reference. In this research, a control algorithm is developed for an alternate task of tracking high-bandwidth sinusoidal targets: whirling and conical motions. To increase robustness to the parametric uncertainty and the nonlinearity of inherent AMB dynamics, the sliding mode control is developed based on an original nonlinear AMB model with an uncertain magnetic force constant. Performance indices, such as the (IR)-R-2 power loss, the tracking error and the phase lag, are compared for the two target motions, and they are also utilized to find an optimal bias current of the actuators. Simulation results show that the rotor follows the two high-bandwidth large motion targets with low tracking error and phase lag in the presence of parametric uncertainty. Orbit motion tracking control has a variety of potential applications in rotating machinery such as active rotating stall control, in which seal clearance is required to follow a sinusoidal dynamic motion. C1 NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Sun, GY (reprint author), NASA, Glenn Res Ctr, 21000 Brookpk Rd MS 301-5, Cleveland, OH 44135 USA. NR 12 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 0-7918-4738-1 PY 2005 BP 995 EP 1002 PG 8 WC Automation & Control Systems; Engineering, Mechanical SC Automation & Control Systems; Engineering GA BFM59 UT WOS:000243093201013 ER PT B AU Mosher, M AF Mosher, Marianne GP ASME TI Results from a new separation algorithm for planetary gear system vibration measurements SO Proceedings of the ASME International Design Engineering Technical Conferences and Computers and Information in Engineering Conference, Vol 5 LA English DT Proceedings Paper CT 17th International Conference on Design Theory and Methodology/Power Transmission and Gearing Conference CY SEP 24-28, 2005 CL Long Beach, CA SP ASME, Design Engn Div, ASME, Comp & Informat Engn Div DE planetary gear system; signal decomposition; synthetic data; helicopter; vibration ID TIME-DOMAIN AVERAGES; EPICYCLIC GEARBOX; SUN GEAR AB Results are presented from a new algorithm developed for separating the vibration signals from a planetary gear system into separate signals attributable to each planet gear. From the separate signals, time synchronous average signals are produced for each planet gear and for the sun gear meshing with each planet gear. Assessments of the individual planet and sun gears can be made from these new vibration signals. These new separated signals match very well with noise-free synthetic data with and without characteristics indicative of faults. In a planet system, distortions planted in synthetic signals are easily distinguished over a wide range of signal-to-noise (S/N) values. In an 8-planet system, distortions are easily detected for high S/N with degradation at low S/N. Spectra from separated signals from vibration measurements made in flight on the transmissions of OH-58C and AH1S helicopters are consistent with what would be expected based upon the transmission geometries. C1 NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Mosher, M (reprint author), NASA, Ames Res Ctr, MC 269-3, Moffett Field, CA 94035 USA. NR 21 TC 0 Z9 0 U1 0 U2 2 PU AMER SOC MECHANICAL ENGINEERS PI NEW YORK PA THREE PARK AVENUE, NEW YORK, NY 10016-5990 USA BN 0-7918-4742-X PY 2005 BP 747 EP 754 PG 8 WC Engineering, Industrial; Engineering, Mechanical SC Engineering GA BFM52 UT WOS:000243076200071 ER PT B AU Balaram, J AF Balaram, J. (Bob) GP ASME TI Sherpa moving mass entry descent landing system SO Proceedings of the ASME International Design Engineering Technical Conferences and Computers and Information in Engineering Conference, Vol 6, Pts A-C LA English DT Proceedings Paper CT 5th International Conference on Multibody Systems, Nonlinear Dynamics, and Control CY SEP 24-28, 2005 CL Long Beach, CA SP ASME Design Engn Div, ASME Comp & Informat Engn Div AB We describe Sherpa - a Strap-on High-altitude Entry Reconnaissance & Precision Aeromaneuver system that utilizes a moving mass system within an entry capsule to land a spacecraft precisely onto the surface of Mars. Sherpa uses two sets of "strap-on" assemblies, one for high-altitude sensing using a terrain imager, and another for agile hypersonic flight using a moving-mass steering device. In this paper we focus on the moving mass system - a steering device that provides an agile trajectory control capability that is mechanically simple, completely internal to the vehicle, has high control authority, and is robust to mechanism failure. The Sherpa system takes a small fraction (5-10%) of the total system mass, and is capable of delivering payloads to within the proximity (similar to 5 km) of a wide variety of landing sites including those at high-altitude (2.5+ km above the reference geoid). C1 CALTECH, Jet Prop Lab, Pasadena, CA USA. RP Balaram, J (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA USA. NR 13 TC 1 Z9 1 U1 0 U2 0 PU AMER SOC MECHANICAL ENGINEERS PI NEW YORK PA THREE PARK AVENUE, NEW YORK, NY 10016-5990 USA BN 0-7918-4743-8 PY 2005 BP 63 EP 79 PG 17 WC Engineering, Multidisciplinary; Engineering, Mechanical; Mathematics, Interdisciplinary Applications; Mechanics SC Engineering; Mathematics; Mechanics GA BFJ36 UT WOS:000242326200006 ER PT B AU Quiocho, LJ Huynh, A Crues, EZ AF Quiocho, Leslie J. Huynh, An Crues, Edwin Z. GP ASME TI Application of multibody dynamics to on-orbit manipulator simulations SO Proceedings of the ASME International Design Engineering Technical Conferences and Computers and Information in Engineering Conference, Vol 6, Pts A-C LA English DT Proceedings Paper CT 5th International Conference on Multibody Systems, Nonlinear Dynamics, and Control CY SEP 24-28, 2005 CL Long Beach, CA SP ASME Design Engn Div, ASME Comp & Informat Engn Div AB This paper discuses a generic multibody dynamics formulation and associated computer algorithm that addresses the variety of manipulator simulation requirements for engineering analysis, procedures development, and crew familiarization/training at the NASA Johnson Space Center (JSC). The formulation is based on body to body relationships with no concept of branched tree topologies. This important notion results in a single recursion pass to construct a system level mass matrix as opposed to the traditional inbound/outbound passes required by the other recursive methods. Moreover, the formulation can be augmented to account for closed loop topologies. The base body of the structure can be fixed or free; each subsequent body, if any, is attached to its parent body via any combination of rotational or translational degrees of freedom (DOFs). Furthermore, each body in the multibody system can be defined as rigid or flexible. The algorithm is designed to partition the data variables and associated computations for multi-frequency or multi-process computation. The resulting algorithm requires approximately one third the computations (in terms of additions and multiplications) of techniques previously used at the NASA JSC. C1 NASA, Lyndon B Johnson Space Ctr, Automat Robot & Simulat Div, Houston, TX 77058 USA. RP Quiocho, LJ (reprint author), NASA, Lyndon B Johnson Space Ctr, Automat Robot & Simulat Div, Houston, TX 77058 USA. NR 12 TC 0 Z9 0 U1 0 U2 1 PU AMER SOC MECHANICAL ENGINEERS PI NEW YORK PA THREE PARK AVENUE, NEW YORK, NY 10016-5990 USA BN 0-7918-4743-8 PY 2005 BP 81 EP 87 PG 7 WC Engineering, Multidisciplinary; Engineering, Mechanical; Mathematics, Interdisciplinary Applications; Mechanics SC Engineering; Mathematics; Mechanics GA BFJ36 UT WOS:000242326200007 ER PT B AU Sohl, G Jain, A AF Sohl, Garett Jain, Abhinandan GP ASME TI Wheel-terrain contact modeling in the roams planetary rover simulation SO Proceedings of the ASME International Design Engineering Technical Conferences and Computers and Information in Engineering Conference, Vol 6, Pts A-C LA English DT Proceedings Paper CT 5th International Conference on Multibody Systems, Nonlinear Dynamics, and Control CY SEP 24-28, 2005 CL Long Beach, CA SP ASME Design Engn Div, ASME Comp & Informat Engn Div AB This paper describes wheel-terrain contact modeling in the ROAMS physics-based simulator for planetary surface exploration rover vehicles. ROAMS models a wide range of rover systems and provides a user interface to a simulated rover. The wheel-terrain interaction is of primary interest during rover motion over rough terrain. The wheel-terrain contact model must provide physically realistic behavior without being too computationally intensive for real-time simulation. Physically realistic behavior may be defined using empirical data and ROAMS provides mechanisms for tuning the contact model parameters to match this data. In cases where empirical data is non-existent or there are large amounts of uncertainty, ROAMS can be used to extrapolate a range of behaviors based on physical parameters. The ROAMS simulator can be used in stand-alone mode, for closed-loop simulation with on-board software or for operator-in-the-loop simulations. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Sohl, G (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,M-S 198-235, Pasadena, CA 91109 USA. NR 16 TC 2 Z9 4 U1 0 U2 0 PU AMER SOC MECHANICAL ENGINEERS PI NEW YORK PA THREE PARK AVENUE, NEW YORK, NY 10016-5990 USA BN 0-7918-4743-8 PY 2005 BP 89 EP 97 PG 9 WC Engineering, Multidisciplinary; Engineering, Mechanical; Mathematics, Interdisciplinary Applications; Mechanics SC Engineering; Mathematics; Mechanics GA BFJ36 UT WOS:000242326200008 ER PT B AU Lindemann, R AF Lindemann, Randel GP ASME TI Dynamic testing and simulation of the Mars Exploration Rover SO Proceedings of the ASME International Design Engineering Technical Conferences and Computers and Information in Engineering Conference, Vol 6, Pts A-C LA English DT Proceedings Paper CT 5th International Conference on Multibody Systems, Nonlinear Dynamics, and Control CY SEP 24-28, 2005 CL Long Beach, CA SP ASME Design Engn Div, ASME Comp & Informat Engn Div ID MERIDIANI-PLANUM; GUSEV CRATER; LOCALIZATION; OPPORTUNITY; SPIRIT AB In January of 2004, NASA landed two mobile robotic spacecraft on the surface of Mars as part of the Mars Exploration Rover (MER) project. Named Spirit and Opportunity, each of these rovers is performing their separate scientific missions of exploration more than a year after landing. The Mars Exploration Rovers represent a great advance in planetary rover technology. Part of that advance is represented by the mobility capabilities of these vehicles. At the 1.5 year mark, the two vehicles have traversed more than 10 km over broad plains, craters, rocks, and hills. In order to assess the mobility characteristics of the rovers in the Mars environment, an engineering model vehicle was tested before the mission launches in a representative environment of slopes, rock obstacles, and soft soil. In addition, to gain better insight into the rovers' capabilities, a dynamic model of the rovers was created in the software package ADAMS. The rover model was then used to simulate many of the test cases, which provided a means for model correction and correlation. The results and lessons learned of the test and dynamic simulation of the MER vehicles is provided in this paper. The results from the test and simulation program allowed Spirit and Opportunity to be used in terrain well outside of the original mission requirements. The resulting increase in terrain access, led to substantial additions to the missions science return. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Lindemann, R (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 7 TC 1 Z9 1 U1 0 U2 0 PU AMER SOC MECHANICAL ENGINEERS PI NEW YORK PA THREE PARK AVENUE, NEW YORK, NY 10016-5990 USA BN 0-7918-4743-8 PY 2005 BP 99 EP 106 PG 8 WC Engineering, Multidisciplinary; Engineering, Mechanical; Mathematics, Interdisciplinary Applications; Mechanics SC Engineering; Mathematics; Mechanics GA BFJ36 UT WOS:000242326200009 ER PT B AU Lorenzo, CF Hartley, TT AF Lorenzo, Carl F. Hartley, Tom T. GP ASME TI The fractional hyperbolic functions: With application to fractional differential equations SO Proceedings of the ASME International Design Engineering Technical Conferences and Computers and Information in Engineering Conference, Vol 6, Pts A-C LA English DT Proceedings Paper CT 5th International Conference on Multibody Systems, Nonlinear Dynamics, and Control CY SEP 24-28, 2005 CL Long Beach, CA SP ASME Design Engn Div, ASME Comp & Informat Engn Div DE fractional hyperboletry; fractional trigonometry; fractional hyperbolic ftinctions; fractional calculus; R-function; fractional differential equations AB This paper develops the fractional hyperbolic functions based on fractional generalization of the exponential function, the R-function. The fractional hyperbolic functions contain the traditional hyperbolic functions as proper subsets. Laplace transforms and various identities are derived for the new functions and are used to generate solution sets for various classes of fractional differential equations. Also developed are relationships between the R-function and the fractional hyperbolic functions. C1 NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Lorenzo, CF (reprint author), NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. NR 6 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 0-7918-4743-8 PY 2005 BP 1505 EP 1512 PG 8 WC Engineering, Multidisciplinary; Engineering, Mechanical; Mathematics, Interdisciplinary Applications; Mechanics SC Engineering; Mathematics; Mechanics GA BFJ36 UT WOS:000242326201092 ER PT B AU Tahmasebi, F AF Tahmasebi, Farhad GP ASME TI Kinematics of a new high precision three degree-of-freedom parallel manipulator SO Proceedings of the ASME International Design Engineering Technical Conferences and Computers and Information in Engineering Conference, Vol 7, Pts A and B LA English DT Proceedings Paper CT 29th Mechanisms and Robotics Conference CY SEP 24-28, 2005 CL Long Beach, CA SP ASME Design Engn Div, ASME Comp & Informat Engn Div ID MECHANISM; PLATFORMS AB Closed-form direct and inverse kinematics of a new three degree-of-freedom (DOF) parallel manipulator with inextensible limbs and base-mounted actuators are presented. The manipulator has higher resolution and precision than the existing three DOF mechanisms with extensible limbs. Since all of the manipulator actuators are base-mounted; higher payload capacity, smaller actuator sizes, and lower power dissipation can be obtained. The manipulator is suitable for alignment applications where only tip, tilt, and piston motions are significant. The direct kinematics of the manipulator is reduced to solving an eighth-degree polynomial in the square of tangent of half-angle between one of the limbs and the base plane. Hence, there are at most sixteen assembly configurations for the manipulator. In addition, it is shown that the sixteen solutions are eight pairs of reflected configurations with respect to the base plane. Numerical examples for the direct and inverse kinematics of the manipulator are also presented. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Tahmasebi, F (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. NR 25 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 0-7918-4744-6 PY 2005 BP 939 EP 947 PG 9 WC Robotics SC Robotics GA BFJ38 UT WOS:000242330500105 ER PT B AU Choi, SR Racz, Z Bhatt, RT Brewer, DN Gyekenyesi, JP AF Choi, Sung R. Racz, Zsolt Bhatt, Rarnakrishna T. Brewer, David N. Gyekenyesi, John P. GP ASME TI Effect of projectile materials on foreign object damage of a gas-turbine grade silicon nitride SO Proceedings of the ASME Turbo Expo 2005, Vol 1 LA English DT Proceedings Paper CT 50th ASME Turbo-Expo CY JUN 06-09, 2005 CL Reno, NV SP Amer Soc Mech Engineers DE foreign object damage (FOD); silicon nitride ID IMPACT DAMAGE; STRENGTH DEGRADATION; STRUCTURAL CERAMICS; TEMPERATURE; PARTICLES; SURFACES; SPHERES; MODEL AB Foreign object damage (FOD) behavior of AS800 silicon nitride was determined using four different projectile materials at ambient temperature. The target test specimens rigidly supported were impacted at their centers by spherical projectiles with a diameter of 1.59 mm. Four different types of projectiles were used including hardened steel balls, annealed steel balls, silicon nitride balls, and brass balls. Post-impact strength of each target specimen impacted was determined as a function of impact velocity to better understand the severity of local impact damage. The critical impact velocity where target specimens fail upon impact was highest with brass balls, lowest with ceramic ball, and intermediate with annealed and hardened steel balls. Degree of strength degradation upon impact followed the same order as in the critical impact velocity with respect to projectile materials. For steel balls, hardened projectiles yielded more significant impact damage than annealed counterparts. The most important material parameter affecting FOD was identified as hardness of projectiles and was correlated in terms of critical impact velocity, impact deformation, and impact load. C1 NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Choi, SR (reprint author), NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. NR 25 TC 0 Z9 0 U1 0 U2 1 PU AMER SOC MECHANICAL ENGINEERS PI NEW YORK PA THREE PARK AVENUE, NEW YORK, NY 10016-5990 USA BN 0-7918-4699-7 PY 2005 BP 339 EP 349 PG 11 WC Engineering, Aerospace; Engineering, Mechanical; Materials Science, Ceramics SC Engineering; Materials Science GA BFN84 UT WOS:000243375800041 ER PT B AU Litt, JS AF Litt, Jonathan S. GP ASME TI An optimal orthogonal decomposition method for Kalman filter-based turbofan engine thrust estimation SO Proceedings of the ASME Turbo Expo 2005, Vol 1 LA English DT Proceedings Paper CT 50th ASME Turbo-Expo CY JUN 06-09, 2005 CL Reno, NV SP Amer Soc Mech Engineers DE thrust estimation; Kalman filter; gas path analysis; diagnostics; engine deterioration ID GAS-TURBINE PERFORMANCE; ALGORITHM; SELECTION; SYSTEM AB A new linear point design technique is presented for the determination of tuning parameters that enable the optimal estimation of unmeasured engine outputs such as thrust. The engine's performance is affected by its level of degradation, generally described in terms of unmeasurable health parameters related to each major engine component. Accurate thrust reconstruction depends upon knowledge of these health parameters, but there are usually too few sensors to be able to estimate their values. In this new technique, a set of tuning parameters is determined which accounts for degradation by representing the overall effect of the larger set of health parameters as closely as possible in a least squares sense. The technique takes advantage of the properties of the singular value decomposition of a matrix to generate a tuning parameter vector of low enough dimension that it can be estimated by a Kalman filter. A concise design procedure to generate a tuning vector that specifically takes into account the variables of interest is presented. An example demonstrates the tuning parameters' ability to facilitate matching of both measured and unmeasured engine outputs, as well as state variables. Additional properties of the formulation are shown to lend themselves well to diagnostics. C1 USA, Res Lab, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Litt, JS (reprint author), USA, Res Lab, Glenn Res Ctr, 21000 Brookpk Rd,MS 77-1, Cleveland, OH 44135 USA. NR 18 TC 0 Z9 0 U1 0 U2 3 PU AMER SOC MECHANICAL ENGINEERS PI NEW YORK PA THREE PARK AVENUE, NEW YORK, NY 10016-5990 USA BN 0-7918-4699-7 PY 2005 BP 745 EP 756 PG 12 WC Engineering, Aerospace; Engineering, Mechanical; Materials Science, Ceramics SC Engineering; Materials Science GA BFN84 UT WOS:000243375800084 ER PT B AU Lepicovsky, J AF Lepicovsky, J. GP ASME TI Effects of transducer installation on unsteady pressure measurements on oscillating blades SO Proceedings of the ASME Turbo Expo 2005, Vol 1 LA English DT Proceedings Paper CT 50th ASME Turbo-Expo CY JUN 06-09, 2005 CL Reno, NV SP Amer Soc Mech Engineers ID CASCADE AB Unsteady pressures were measured above the suction side of a blade that was oscillated to simulate blade stall flutter. Measurements were made at blade oscillation frequencies up to 500 Hi. Two types of miniature pressure transducers were used: surface-mounted flat custom-made, and commercial miniature, body-mounted transducers. The signals of the surface-mounted transducers are significantly affected by blade acceleration, whereas the signals of body-mounted transducers are practically free of this distortion. A procedure was introduced to correct the signals of surface-mounted transducers to rectify the signal distortion due to blade acceleration. The signals from body-mounted transducers, and corrected signals from surface-mounted transducers represent true unsteady pressure signals on the surface of a blade subjected to forced oscillations. However, the use of body-mounted commercial transducers is preferred for the following reasons: no signal corrections are needed for blade acceleration, the conventional transducers are noticeably less expensive than custom-made flat transducers, the survival rate of body-mounted transducers is much higher, and finally installation of body-mounted transducers does not disturb the blade surface of interest. C1 NASA, QSS Grp Inc, GRC, Cleveland, OH 44135 USA. RP Lepicovsky, J (reprint author), NASA, QSS Grp Inc, GRC, Cleveland, OH 44135 USA. NR 10 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 0-7918-4699-7 PY 2005 BP 793 EP 803 PG 11 WC Engineering, Aerospace; Engineering, Mechanical; Materials Science, Ceramics SC Engineering; Materials Science GA BFN84 UT WOS:000243375800089 ER PT B AU Boyle, RJ Senyitko, RG AF Boyle, R. J. Senyitko, R. G. GP ASME TI Effects of surface roughness on turbine vane heat transfer SO Proceedings of the ASME Turbo Expo 2005, Vol 3 Pts A and B LA English DT Proceedings Paper CT 50th ASME Turbo-Expo CY JUN 06-09, 2005 CL Reno, NV SP Amer Soc Mech Engineers ID BOUNDARY-LAYER; FLOWS; TRANSITION; TURBULENCE AB Turbine vane surface temperatures were measured in a linear cascade using an infrared non-contact thermal detector. A thermal barrier coating (TBC) was applied to the vane surface to give a rough surface. The temperature drop across the relatively thick TBC was used to determine heat transfer coefficients. Tests were conducted over a range of Reynolds and Mach numbers, resulting in large variations in hydraulic roughness. The measured heat transfer rates were significantly higher than were expected for a smooth vane. The detector was mounted in a probe holder, and traversed in a manner similar to that used for pneumatic or hot wire probes. The results showed that this approach gave useful information, and should be considered when non-contact surface temperatures are desired. C1 NASA, Glenn Res Ctr, Cleveland, OH USA. RP Boyle, RJ (reprint author), NASA, Glenn Res Ctr, Cleveland, OH USA. NR 37 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 0-7918-4726-8 PY 2005 BP 931 EP 942 PG 12 WC Thermodynamics; Engineering, Mechanical SC Thermodynamics; Engineering GA BFK77 UT WOS:000242531300083 ER PT B AU Tornabene, R Wang, XY Steffen, CJ Freeh, JE AF Tornabene, Robert Wang, Xiao-yen Steffen, Christopher J., Jr. Freeh, Joshua E. GP ASME TI Development of parametric mass and volume models for an aerospace SOFC/gas turbine hybrid system SO Proceedings of the ASME Turbo Expo 2005, Vol 5 LA English DT Proceedings Paper CT 50th ASME Turbo-Expo CY JUN 06-09, 2005 CL Reno, NV SP Amer Soc Mech Engineers DE solid oxide fuel cell (SOFC); hybrid gas turbine system; auxiliary power unit AB In aerospace power systems, mass and volume are key considerations to produce a viable design. The utilization of fuel cells is being studied for a commercial aircraft electrical power unit. Based on preliminary analyses [1.2] a SOFC/gas turbine system may be a potential solution. This paper describes the parametric mass and volume models that are used to assess an aerospace hybrid system design. The design tool utilizes input from the thermodynamic system model and produces component sizing. performance and mass estimates. The software is designed such that the thermodynamic model is linked to the mass and volume model to provide immediate feedback during the design process. It allows for automating an optimization process that accounts for mass and volume in its figure of merit. Each component in the system is modeled with a combination of theoretical and empirical approaches. A description of the assumptions and design analyses is presented. C1 NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Tornabene, R (reprint author), NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. NR 11 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 0-7918-4728-4 PY 2005 BP 135 EP 144 PG 10 WC Energy & Fuels; Engineering, Mechanical SC Energy & Fuels; Engineering GA BFN87 UT WOS:000243376900014 ER PT B AU Steffen, CJ Freeh, JE Larosiliere, LM AF Steffen, Christopher J., Jr. Freeh, Joshua E. Larosiliere, Louis M. GP ASME TI Solid oxide fuel cell/gas turbine hybrid cycle technology for auxiliary aerospace power SO Proceedings of the ASME Turbo Expo 2005, Vol 5 LA English DT Proceedings Paper CT 50th ASME Turbo-Expo CY JUN 06-09, 2005 CL Reno, NV SP Amer Soc Mech Engineers DE solid oxide fuel cell; SOFC/GT hybrid; auxiliary power unit; aerospace power; specific energy AB A notional 440 kW auxiliary power unit has been developed for 300 passenger commercial transport aircraft in 2015AD. A hybrid engine using solid-oxide fuel cell stacks and a gas turbine bottoming cycle has been considered. Steady-state performance analysis during cruise operation has been presented. Trades between performance efficiency and system mass were conducted with system specific energy as the discriminator. Fuel cell performance was examined with an area specific resistance. The ratio of fuel cell versus turbine power was explored through variable fuel utilization. Area specific resistance, fuel utilization, and mission length had interacting effects upon system specific energy. During cruise operation, the simple cycle fuel cell/gas turbine hybrid was not able to outperform current turbine-driven generators for system specific energy, despite a significant improvement in system efficiency. This was due in part to the increased mass of the hybrid engine, and the increased water flow required for on-board fuel reformation. Two planar, anode-supported cell design concepts were considered. Designs that seek to minimize the metallic interconnect layer mass were seen to have a large effect upon the system mass estimates. C1 NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Steffen, CJ (reprint author), NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. NR 17 TC 0 Z9 0 U1 2 U2 3 PU AMER SOC MECHANICAL ENGINEERS PI NEW YORK PA THREE PARK AVENUE, NEW YORK, NY 10016-5990 USA BN 0-7918-4728-4 PY 2005 BP 253 EP 260 PG 8 WC Energy & Fuels; Engineering, Mechanical SC Energy & Fuels; Engineering GA BFN87 UT WOS:000243376900026 ER PT B AU Van Zante, D Chen, JP Hathaway, M Chriss, R AF Van Zante, Dale Chen, Jenping Hathaway, Michael Chriss, Randall GP ASME TI The influence of compressor blade row interaction modeling on performance estimates from time-accurate, multi-stage, Navier-Stokes simulations SO Proceedings of the ASME Turbo Expo 2005, Vol 6, Pts A and B LA English DT Proceedings Paper CT 50th ASME Turbo-Expo CY JUN 06-09, 2005 CL Reno, NV SP Amer Soc Mech Engineers DE blade row interaction; numerical modeling; multi-stage compressor AB The time-accurate, multi-stage, Navier-Stokes, turbomachinery solver TURBO was used to calculate the aero performance of a 2 1/2 stage, highly-loaded, high-speed, axial compressor. The goals of the research project. were to demonstrate completion times for multi-stage, time-accurate simulations that are consistent with inclusion in the design process, and to assess the influence of differing approaches to modeling the effects of blade row interactions on aero performance estimates. Three different simulation setups were used to model blade row interactions: 1.) single passage per blade row with phase lag boundaries, 2.) multiple passages per blade row with phase lag boundaries, and 3.) a periodic sector (1/2 annulus sector). The simulations used identical inlet and exit boundary conditions and identical meshes. To add more blade passages to the domain, the single passage meshes were copied and rotated. This removed any issues of differing mesh topology or mesh density from the following results. The 1/2 annulus simulation utilizing periodic boundary conditions required an order of magnitude less iterations to converge when all three simulations were converged to the same level as assessed by monitoring changes in overall adiabatic efficiency. When using phase lag boundary conditions the need to converge the time history information necessitates more iterations to obtain the same convergence level. In addition to convergence differences, the three simulations gave different overall performance estimates where the 1/2 annulus case was 1.0 point lower in adiabatic efficiency than the single passage phase lag case. The interaction between blade rows in the same frame of reference set up spatial variations of properties in the circumferential direction which are stationary in that reference frame. The phase lag boundary condition formulation will not capture this effect because the blade rows are not moving relative to each other. Thus for simulations of more than two blade rows and strong interactions, a periodic simulation is necessary to estimate the correct aero performance. C1 NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Van Zante, D (reprint author), NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. NR 26 TC 0 Z9 0 U1 0 U2 1 PU AMER SOC MECHANICAL ENGINEERS PI NEW YORK PA THREE PARK AVENUE, NEW YORK, NY 10016-5990 USA BN 0-7918-4729-2 PY 2005 BP 1067 EP 1079 PG 13 WC Engineering, Mechanical SC Engineering GA BFK59 UT WOS:000242493400099 ER PT J AU Takahashi, F Katta, VR AF Takahashi, F Katta, VR TI Structure of propagating edge diffusion flames in hydrocarbon fuel jets SO PROCEEDINGS OF THE COMBUSTION INSTITUTE LA English DT Article; Proceedings Paper CT 30th International Symposium on Combustion CY JUL 25-30, 2004 CL Univ Illinois Chicago, Chicago, IL SP Combust Inst HO Univ Illinois Chicago DE diffusion flame; edge flame propagation; triple flame; reaction kernel; microgravity combustion ID TRIPLE FLAMES; REACTION KERNEL AB Direct numerical simulations with a C-3-chemistry model have been performed to investigate the transient behavior and internal structure of flames propagating in an axisymmetric fuel jet of methane, ethane, ethylene, acetylene, or propane in normal earth gravity (1g) and zero gravity (0g). The fuel issued from a 3-mm-i.d. tube into quasi-quiescent air for a fixed mixing time of 0.3 s before it was ignited along the centerline where the fuel-air mixture was at stoichiometry. The edge of the flame formed a vigorously burning peak reactivity spot, i.e., reaction kernel, and propagated through a flammable mixture layer, leaving behind a trailing diffusion flame. The reaction kernel broadened laterally across the flammable mixture layer and possessed characteristics of premixed flames in the direction of propagation and unique flame structure in the transverse direction. The reaction kernel grew wings on both fuel and air sides to form a triple-flame-like structure, particularly for ethylene and acetylene, whereas for alkanes, the fuel-rich wing tended to merge with the main diffusion flame zone, particularly methane. The topology of edge diffusion flames depend on the properties of fuels, particularly the rich flammability limit, and the mechanistic oxidation pathways. The transit velocity of edge diffusion flames, determined from a time series of calculated temperature field, equaled to the measured laminar flame speed of the stoichiometric fuel-air mixtures, available in the literature, independent of the gravity level. (c) 2004 The Combustion Institute. Published by Elsevier Inc. All rights reserved. C1 NASA, Glenn Res Ctr, Natl Ctr Micrograv Res Fluids & Combust, Cleveland, OH 44135 USA. Innovat Sci Solut Inc, Dayton, OH 45440 USA. RP Takahashi, F (reprint author), NASA, Glenn Res Ctr, Natl Ctr Micrograv Res Fluids & Combust, Cleveland, OH 44135 USA. EM Fumiaki.Takahashi@grc.nasa.gov NR 30 TC 19 Z9 19 U1 0 U2 2 PU COMBUSTION INST PI PITTSBURGH PA 5001 BAUM BOULEVARD, STE 635, PITTSBURGH, PA 15213-1851 USA SN 0082-0784 J9 P COMBUST INST JI Proc. Combust. Inst. PY 2005 VL 30 BP 375 EP 382 DI 10.1016/j.proci.2004.08.227 PN 1 PG 8 WC Thermodynamics; Energy & Fuels; Engineering, Chemical; Engineering, Mechanical SC Thermodynamics; Energy & Fuels; Engineering GA 937RW UT WOS:000229944200035 ER PT J AU Takahashi, F Katta, VR AF Takahashi, F Katta, VR TI Further studies of the reaction kernel structure and stabilization of jet diffusion flames SO PROCEEDINGS OF THE COMBUSTION INSTITUTE LA English DT Article; Proceedings Paper CT 30th International Symposium on Combustion CY JUL 25-30, 2004 CL Univ Illinois Chicago, Chicago, IL SP Combust Inst HO Univ Illinois Chicago DE diffusion flame; flame stability; flame structure; reaction kernel; microgravity combustion ID METHANE; STABILITY; REGION AB The structure of axisymmetric laminar jet diffusion flames of ethane, ethylene, acetylene, and propane in quasi-quiescent air has been studied numerically in normal earth gravity (1g) and zero gravity (0g). The time-dependent full Navier-Stokes equations with buoyancy were solved using an implicit, third-order accurate numerical scheme, including a C-3-chemistry model and an optically thin-media radiation model for heat losses. Observations of the flames were also made at the NASA Glenn 2.2-Second Drop Tower. For all cases of the fuels and gravity levels investigated, a peak reactivity spot, i.e., reaction kernel, was formed in the flame base, thereby holding a trailing diffusion flame. The location of the reaction kernel with respect to the burner rim depended inversely on the reaction-kernel reactivity or velocity. In the C-2 and C-3 hydrocarbon flames, the H-2-O-2 chain reactions were important at the reaction kernel, yet the CH3 + O -> CH2O + H reaction, a dominant contributor to the heat-release rate in methane flames studied previously, did not outweigh other exothermic reactions. Instead of the Cl-route oxidation pathway in methane flames, the C-2 and C-3 hydrocarbon fuels dehydrogenated on the fuel side and acetylene was a major hydrocarbon fragment burning at the reaction kernel. The reaction-kernel correlations between the reactivity (the heat-release or oxygen-consumption rate) and the velocity, obtained previously for methane, were developed further for various fuels in more universal forms using variables related to local Damkohler numbers and Peclet numbers. (c) 2004 The Combustion Institute. Published by Elsevier Inc. All rights reserved. C1 NASA, Glenn Res Ctr, Natl Ctr Micrograv Res Fluids & Combust, Cleveland, OH 44135 USA. Innovat Sci Solut Inc, Dayton, OH 45440 USA. RP Takahashi, F (reprint author), NASA, Glenn Res Ctr, Natl Ctr Micrograv Res Fluids & Combust, Cleveland, OH 44135 USA. EM Fumiaki.Takahashi@grc.nasa.gov NR 24 TC 13 Z9 13 U1 1 U2 3 PU COMBUSTION INST PI PITTSBURGH PA 5001 BAUM BOULEVARD, STE 635, PITTSBURGH, PA 15213-1851 USA SN 0082-0784 J9 P COMBUST INST JI Proc. Combust. Inst. PY 2005 VL 30 BP 383 EP 390 DI 10.1016/j.proci.2004.08.225 PN 1 PG 8 WC Thermodynamics; Energy & Fuels; Engineering, Chemical; Engineering, Mechanical SC Thermodynamics; Energy & Fuels; Engineering GA 937RW UT WOS:000229944200036 ER PT J AU Le Clercq, PC Bellan, J AF Le Clercq, PC Bellan, J TI Modeling of multicomponent-fuel drop-laden mixing layers having a multitude of species SO PROCEEDINGS OF THE COMBUSTION INSTITUTE LA English DT Article; Proceedings Paper CT 30th International Symposium on Combustion CY JUL 25-30, 2004 CL Univ Illinois Chicago, Chicago, IL SP Combust Inst HO Univ Illinois Chicago DE multicomponet-fuel sprays ID DIRECT NUMERICAL-SIMULATION; CONTINUOUS THERMODYNAMICS; FLOW SIMULATIONS; MIXTURES; VAPORIZATION; EVAPORATION; TURBULENCE; COMPONENTS; PARTICLES AB A formulation representing multicomponent-fuel (MC-fuel) composition Lis a probability distribution function (PDF) depending on the molar mass is used to construct a model of a large number Of MC-fuel drops evaporating in a gas flow, so as to assess the extent of fuel specificity on the vapor composition. The PDF is a combination of two Gamma PDFs, which was previously shown to duplicate the behavior of a fuel composed of many species during single drop evaporation. The conservation equations are Eulerian for the flow and Lagrangian for the physical drops, all of which are individually followed. The gas conservation equations for mass, momentum, species, and energy are complemented by differential conservation equations for the first four moments of the gas-corn position PDF; all coupled to the perfect gas equation of state. Source terms in all conservation equations couple the gas phase to the drops. The drop conservation equations for mass, position, momentum, and energy are complemented by differential equations for four moments of the liquid-composition PDF. The simulations are performed for a three-dimensional mixing layer whose lower stream is initially laden with drops. Initial perturbations excite the layer to promote the double pairing of its four initial spanwise vortices to an ultimate vortex. The drop temperature is initially lower than that of the surrounding gas, initiating drop heating and evaporation. The results focus on both evolution and the state of the drops and gas when layers reach a momentum-thickness maximum past the double vortex pairing-, particular emphasis is on the gas composition. Comparisons between simulations with n-decane, diesel, and three kerosenes show that at same initial Reynolds number and Stokes number distribution, a single-component fuel cannot represent MC fuels. Substantial differences among the MC-fuel vapor composition indicate that fuel specificity must be captured for the prediction of combustion. (c) 2004 The Combustion Institute. Published by Elsevier Inc. All rights reserved. C1 CALTECH, Pasadena, CA 91125 USA. CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Bellan, J (reprint author), CALTECH, Pasadena, CA 91125 USA. EM josette.bellan@jpl.nasa.gov NR 28 TC 2 Z9 2 U1 1 U2 5 PU COMBUSTION INST PI PITTSBURGH PA 5001 BAUM BOULEVARD, STE 635, PITTSBURGH, PA 15213-1851 USA SN 0082-0784 J9 P COMBUST INST JI Proc. Combust. Inst. PY 2005 VL 30 BP 2011 EP 2019 DI 10.1016/j.proci.2004.07.023 PN 2 PG 9 WC Thermodynamics; Energy & Fuels; Engineering, Chemical; Engineering, Mechanical SC Thermodynamics; Energy & Fuels; Engineering GA 937RX UT WOS:000229944300035 ER PT J AU Bar-Ilan, A Putzeys, OM Rein, G Fernandez-Pello, AC Urban, DL AF Bar-Ilan, A Putzeys, OM Rein, G Fernandez-Pello, AC Urban, DL TI Transition from forward smoldering to flaming in small polyurethane foam samples SO PROCEEDINGS OF THE COMBUSTION INSTITUTE LA English DT Article; Proceedings Paper CT 30th International Symposium on Combustion CY JUL 25-30, 2004 CL Univ Illinois Chicago, Chicago, IL SP Combust Inst HO Univ Illinois Chicago DE smoldering; transition to flaming; polyurethane foam ID COMBUSTION PROPAGATION AB Experimental observations are presented of the effect of flow velocity, oxygen concentration, and a thermal radiant flux on the transition from smoldering to flaming in forward smoldering of small samples of polyurethane foam with a gas/solid interface. The experiments are part of a project studying the transition from smoldering to flaming under conditions encountered in spacecraft facilities, i.e., microgravity, low velocity variable oxygen concentration flows. Because the microgravity experiments are planned for the International Space Station, the foam samples had to be limited in size for safety and launch mass reasons. The feasible sample size is too small for smolder to self-propagate because of heat losses to the surroundings. Thus. the smolder propagation and the transition to flaming had to be assisted by reducing heat losses to the surroundings and increasing the oxygen concentration. The experiments are conducted with small parallelepiped samples vertically placed in a wind tunnel. Three of the sample lateral-sides are maintained at elevated temperature, and the fourth side is exposed to an upward flow and a radiant flux. It is found that decreasing the flow velocity and increasing its oxygen concentration, and/or increasing the radiant flux enhances the transition to flaming and reduces the time delay to transition. Limiting external conditions for the transition to flaming are reported for this experimental Configuration. The results show that smolder propagation and transition to flaming can Occur in relatively small fuel samples if the external conditions are appropriate. The results also indicate that transition to flaming Occurs in the char region left behind by the smolder reaction, and it has the characteristics of a gas-phase ignition induced by the smolder reaction, which acts as the source of both gaseous fuel and heat. A simplified energy balance analysis is able to predict the boundaries between the transition/no transition regions. (c) 2004 Published by Elsevier Inc. on behalf of The Combustion Institute. C1 Univ Calif Berkeley, Berkeley, CA 94720 USA. NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Fernandez-Pello, AC (reprint author), Univ Calif Berkeley, Berkeley, CA 94720 USA. EM ferpello@me.berkeley.edu OI Rein, Guillermo/0000-0001-7207-2685 NR 21 TC 11 Z9 14 U1 1 U2 5 PU COMBUSTION INST PI PITTSBURGH PA 5001 BAUM BOULEVARD, STE 635, PITTSBURGH, PA 15213-1851 USA SN 0082-0784 J9 P COMBUST INST JI Proc. Combust. Inst. PY 2005 VL 30 BP 2295 EP 2302 DI 10.1016/j.proci.2004.08.233 PN 2 PG 8 WC Thermodynamics; Energy & Fuels; Engineering, Chemical; Engineering, Mechanical SC Thermodynamics; Energy & Fuels; Engineering GA 937RX UT WOS:000229944300068 ER PT J AU Nakamura, Y Kashiwagi, T Olson, SL Nishizawa, K Fujita, O Ito, K AF Nakamura, Y Kashiwagi, T Olson, SL Nishizawa, K Fujita, O Ito, K TI Two-sided ignition of a thin PMMA sheet in microgravity SO PROCEEDINGS OF THE COMBUSTION INSTITUTE LA English DT Article; Proceedings Paper CT 30th International Symposium on Combustion CY JUL 25-30, 2004 CL Univ Illinois Chicago, Chicago, IL SP Combust Inst HO Univ Illinois Chicago DE ignition; microgravity; PMMA ID POLY(METHYL METHACRYLATE); SOLID-FUEL; DEGRADATION; OXYGEN; VAPOR; MODEL AB Numerical computations and a series of experiments were conducted in microgravity to study the ignition characteristics of a thin polymethylmethacrylate (PMMA) sheet (thicknesses of 0.2 and 0.4 mm) using a CO, laser as an external radiant source. Two separate ignition events were observed, including ignition over the irradiated surface (frontside ignition), and ignition, after some delay, over the backside surface (backside ignition). The backside ignition was achieved in two different modes. In the first mode, after the laser was turned off, the flame shrank and stabilized closer to the fuel surface. This allowed the flame to travel from the frontside to the backside through the small, open hole generated by the laser's vaporization of PMMA. In the second mode, backside ignition was achieved during the laser irradiation. The numerical calculation simulating this second process predicts fresh oxygen supply flows from the backside gas phase to the frontside gas phase through the open hole, which mixes with accumulated hot NIMA fuel vapor which is ignited as a second flame in the frontside gas phase above the hole. Then, the flame initiated from the second ignition travels through the hole to ignite the accumulated flammable mixture in the backside gas phase near the hole, attaining backside ignition. The first backside ignition mode was observed in 21% oxygen and the second backside ignition mode in 35%. The duration of the laser irradiation appears to have important effects on the onset of backside ignition. For example, in 21% oxygen, the backside ignition was attained after a 3 s laser duration but was not observed after a 6 s laser duration (within the available test time of 10 s). Longer laser duration might prevent two-sided ignition in low oxygen concentrations. (c) 2004 The Combustion Institute. Published by Elsevier Inc. All rights reserved. C1 Nagoya Univ, EcoTopia Sci Inst, Nagoya, Aichi, Japan. NIST, Fire Res Div, Gaithersburg, MD 20899 USA. NASA, Glenn Res Ctr, Micrograv Combust Sci Branch, Cleveland, OH 44135 USA. Hokkaido Univ, Dept Mech Engn, Sapporo, Hokkaido 060, Japan. RP Nakamura, Y (reprint author), Nagoya Univ, EcoTopia Sci Inst, Nagoya, Aichi, Japan. EM yuji@mech.nagoya-u.ac.jp RI Fujita, Osamu/D-6797-2012 NR 12 TC 12 Z9 12 U1 0 U2 2 PU COMBUSTION INST PI PITTSBURGH PA 5001 BAUM BOULEVARD, STE 635, PITTSBURGH, PA 15213-1851 USA SN 0082-0784 J9 P COMBUST INST JI Proc. Combust. Inst. PY 2005 VL 30 BP 2319 EP 2325 DI 10.1016/j.proci.2004.07.037 PN 2 PG 7 WC Thermodynamics; Energy & Fuels; Engineering, Chemical; Engineering, Mechanical SC Thermodynamics; Energy & Fuels; Engineering GA 937RX UT WOS:000229944300071 ER PT J AU Olson, SL Beeson, HD Haas, JP Baas, JS AF Olson, SL Beeson, HD Haas, JP Baas, JS TI An Earth-based equivalent low stretch apparatus for material flammability assessment in microgravity and extraterrestrial environments SO PROCEEDINGS OF THE COMBUSTION INSTITUTE LA English DT Article; Proceedings Paper CT 30th International Symposium on Combustion CY JUL 25-30, 2004 CL Univ Illinois Chicago, Chicago, IL SP Combust Inst HO Univ Illinois Chicago DE cone calorimeter; gravity; flammability; PMMA; ignition delay ID FLAME SPREAD; COMBUSTION; POLYMETHYLMETHACRYLATE; EXTINCTION; PMMA; FUEL AB The standard oxygen consumption (cone) calorimeter (described in ASTM E 1354 and NASA STD 6001 Test 2) is modified to provide a bench-scale test environment that simulates the low velocity buoyant or ventilation flow generated by or around a burning surface in a spacecraft or extraterrestrial gravity level. The equivalent low stretch apparatus (ELSA) uses an inverted cone geometry with the sample burning in a ceiling fire (stagnation flow) configuration. For a fixed radiant flux, ignition delay times for characterization material PMMA are shown to decrease by a factor of 3 at low stretch, demonstrating that ignition delay times determined from normal cone tests significantly underestimate the risk in microgravity. The critical heat flux for ignition is found to be lowered at low stretch as the convective cooling is reduced. At the limit of no stretch, any heat flux that exceeds the surface radiative loss at the surface ignition temperature is sufficient for ignition. Regression rates for PMMA increase with heat flux and stretch rate, but regression rates are much more sensitive to heat flux at the low stretch rates, where a modest increase in heat flux of 25 kW/m(2) increases the burning rates by an order of magnitude. The global equivalence ratio of these flames is very fuel rich, and the quantity of CO produced in this configuration is significantly higher than standard cone tests. These results demonstrate that the ELSA apparatus allows us to conduct normal gravity experiments that accurately and quantifiably evaluate a material's flammability characteristics in the real-use environment of spacecraft or extraterrestrial gravitational acceleration. These results also demonstrate that current NASA STD 6001 Test 2 (standard cone) is not conservative since it evaluates a material's flammability with a much higher inherent buoyant convective flow. Published by Elsevier Inc. on behalf of The Combustion Institute. C1 NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. NASA, White Sands Test Facil, Las Cruces, NM USA. RP Olson, SL (reprint author), NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. EM Sandra.l.olson@nasa.gov NR 16 TC 5 Z9 5 U1 2 U2 2 PU COMBUSTION INST PI PITTSBURGH PA 5001 BAUM BOULEVARD, STE 635, PITTSBURGH, PA 15213-1851 USA SN 0082-0784 J9 P COMBUST INST JI Proc. Combust. Inst. PY 2005 VL 30 BP 2335 EP 2343 DI 10.1016/j.proci.2004.08.044 PN 2 PG 9 WC Thermodynamics; Energy & Fuels; Engineering, Chemical; Engineering, Mechanical SC Thermodynamics; Energy & Fuels; Engineering GA 937RX UT WOS:000229944300073 ER PT J AU Boyarko, GA Sung, CJ Schneider, SJ AF Boyarko, GA Sung, CJ Schneider, SJ TI Catalyzed combustion of hydrogen-oxygen in platinum tubes for micro-propulsion applications SO PROCEEDINGS OF THE COMBUSTION INSTITUTE LA English DT Article; Proceedings Paper CT 30th International Symposium on Combustion CY JUL 25-30, 2004 CL Univ Illinois Chicago, Chicago, IL SP Combust Inst HO Univ Illinois Chicago DE catalytic combustion; micro-propulsion; micro-combustor ID FLOW AB The present investigation addresses the need to understand the physics and chemistry involved in propellant combustion processes in micro-scale combustors for propulsion systems on micro-spacecraft. These spacecraft are planned to have a mass less than 50 kg with attitude control estimated to be in the 1-10 mN thrust class. Micro-propulsion devices behave differently than macro-scale devices because of the differences in magnitude of flow rates and heat transfer. Reducing the combustor size increases the relative surface area, increasing the heat loss, and as combustors are continuously reduced in size, they approach the quenching dimensions of the propellants. Combustors of this size are expected to significantly benefit from surface catalysis processes. A miniature flame tube apparatus is chosen for this study because microtubes can be easily fabricated from known catalyst materials, and their simplicity in geometry can be used in fundamental simulations for validation purposes. Experimentally, we investigated the role of catalytically active surfaces within 0.4 and 0.8 mm internal diameter microtubes, with special emphases on ignition processes in fuel rich gaseous hydrogen and gaseous oxygen. Calculations of flame thickness and reaction zone thickness predict that the diameters of our test apparatus are below the quenching diameter of the propellants in most atmospheric test conditions. The temperature and pressure rise in resistively heated platinum microtubes and the exit hydrogen concentration were used as an indication of exothermic reactions. Data on imposed heat flux/preheat temperature required to achieve ignition versus mass flow rate are presented. With a plug flow model, the experimental conditions were simulated with detailed gas-phase chemistry and surface kinetics. Computational results, in general, support the experimental findings. (c) 2004 The Combustion Institute. Published by Elsevier Inc. All rights reserved. C1 Case Western Reserve Univ, Dept Mech & Aerosp Engn, Cleveland, OH 44106 USA. NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Sung, CJ (reprint author), Case Western Reserve Univ, Dept Mech & Aerosp Engn, 10900 Euclid Ave, Cleveland, OH 44106 USA. EM cjs15@cwru.edu NR 14 TC 51 Z9 59 U1 2 U2 13 PU COMBUSTION INST PI PITTSBURGH PA 5001 BAUM BOULEVARD, STE 635, PITTSBURGH, PA 15213-1851 USA SN 0082-0784 J9 P COMBUST INST JI Proc. Combust. Inst. PY 2005 VL 30 BP 2481 EP 2488 DI 10.1016/j.proci.2004.08.203 PN 2 PG 8 WC Thermodynamics; Energy & Fuels; Engineering, Chemical; Engineering, Mechanical SC Thermodynamics; Energy & Fuels; Engineering GA 937RX UT WOS:000229944300087 ER PT J AU Owens, ZC Mattison, DW Barbour, EA Morris, CI Hanson, RK AF Owens, ZC Mattison, DW Barbour, EA Morris, CI Hanson, RK TI Flowfield characterization and simulation validation of multiple-geometry PDEs using cesium-based velocimetry SO PROCEEDINGS OF THE COMBUSTION INSTITUTE LA English DT Article; Proceedings Paper CT 30th International Symposium on Combustion CY JUL 25-30, 2004 CL Univ Illinois Chicago, Chicago, IL SP Combust Inst HO Univ Illinois Chicago DE pulse detonation engine; laser diagnostics; velocimetry; PDE modeling; cesium-based velocimetry AB A diode-laser velocimeter based on cesium absorption spectroscopy has been used to measure the axial burned gas velocity in a pulse detonation engine (PDE) configured with and without a converging-diverging nozzle. These data are compared to simulation data from a Frozen-chemistry computational model, Lis wall Lis a finite-rate chemistry model with and without the effects of heat transfer included. Discrepancies between the data and the models are discussed and conclusions are drawn on the validity of each model. The velocity diagnostic requires cesium to be seeded into the PDE flowfield where it is then detected using a fixed-wavelength diode laser tuned to monitor the D-2 transition of atomic cesium near 852 nm. Due to the unsteady nature of the PDE flowfield, the deposition of the cesium absorber into the flowfield occurs in a pulsating manner. The unsteady nature of this seeding process enables a time-of-flight measurement to be made as the absorber passes two parallel laser beams spaced 2-3 mm apart in the streamwise direction. Using this technique, PDE gas velocities ranging from - 100 to 1000 m/s are measured with 20-100 mu s time resolution over the duration of a single cycle. Results are presented for a C2H4/O-2 (phi = 1) fueled PDE operating both with and Without a converging-diverging nozzle. Comparison of velocity data to each computational model Suggests that for the case of the straight tube PDE, velocity can be accurately predicted over the thrust producing range of the engine cycle via an idealized, frozen-chemistry computational model. For the PDE outfitted with a converging-diverging nozzle, the blowdown time for a single cycle is substantially longer, and a less-idealized, finite-rate chemistry model which accounts for heat loss effects is required to capture the more complex wave dynamics. (c) 2004 The Combustion Institute. Published by Elsevier Inc. All rights reserved. C1 Stanford Univ, Dept Mech Engn, High Temp Gasdynam Lab, Stanford, CA 94305 USA. NASA, George C Marshall Space Flight Ctr, Huntsville, AL USA. RP Owens, ZC (reprint author), Stanford Univ, Dept Mech Engn, High Temp Gasdynam Lab, Stanford, CA 94305 USA. EM zowens@stanford.edu NR 12 TC 10 Z9 10 U1 0 U2 2 PU COMBUSTION INST PI PITTSBURGH PA 5001 BAUM BOULEVARD, STE 635, PITTSBURGH, PA 15213-1851 USA SN 0082-0784 J9 P COMBUST INST JI Proc. Combust. Inst. PY 2005 VL 30 BP 2791 EP 2798 DI 10.1016/j.proci.2004.08.050 PN 2 PG 8 WC Thermodynamics; Energy & Fuels; Engineering, Chemical; Engineering, Mechanical SC Thermodynamics; Energy & Fuels; Engineering GA 937RX UT WOS:000229944300122 ER PT J AU Mattison, DW Oehischlaeger, MA Morris, CI Owens, ZC Barbour, EA Jeffries, JB Hanson, RK AF Mattison, DW Oehischlaeger, MA Morris, CI Owens, ZC Barbour, EA Jeffries, JB Hanson, RK TI Evaluation of pulse detonation engine modeling using laser-based temperature and OH concentration measurements SO PROCEEDINGS OF THE COMBUSTION INSTITUTE LA English DT Article; Proceedings Paper CT 30th International Symposium on Combustion CY JUL 25-30, 2004 CL Univ Illinois Chicago, Chicago, IL SP Combust Inst HO Univ Illinois Chicago DE pulsed detonations; absorption diagnostics; temperature measurements ID HIGH-PRESSURE; SHOCK-TUBE; ABSORPTION; PERFORMANCE; PARAMETERS; SENSORS; FLOWS; BAND AB Two novel, laser-based sensors employing ultraviolet (UV) wavelengths are developed and applied to measure time-resolved temperature and OH concentration in a pulse detonation tube. These results, along with pressure data, are employed to evaluate two computational simulations utilizing different chemistry and heat transfer models to predict Pulse detonation engine (PDE) flowfields. The first sensor applies 266 and 306 nm UV laser absorption to infer temperature from 2000 to 4000 K because of broadband CO, absorption. These results represent the first thermometry based on line-of-sight, cw UV laser absorption by M. The second sensor utilizes a single 306 nm UV laser to probe an individual OH absorption feature. Time-resolved OH concentration is inferred from the measured absorption, temperature. and pressure. These two sensors provide microsecond time-resolved measurements, over a dynamic range of temperatures and pressures (2000-4000 K. and 0.5-30 atm), of two important parameters needed for evaluation of PDE computational models. The first computational model evaluated utilizes a frozen gas composition assumption; the second model incorporates finite-rate chemistry and includes losses due to heat transfer and friction. The results show that the frozen gas composition simulation can successfully predict temperature and pressure profiles, although the agreement is artificial in that inclusion of heat transfer effects would negate this agreement. The simulation including finite-rate chemistry and no heat transfer overpredicts the measured temperature and OH concentration. However, with the proper inclusion of losses due to heat transfer, the finite-rate chemistry code accurately predicts all three measured parameters. We conclude that both finite-rate chemistry and heat transfer are important for correct modeling of PDE flowfields. (c) 2004 The Combustion Institute. Published by Elsevier Inc. All rights reserved. C1 Stanford Univ, Dept Mech Engn, Stanford, CA 94305 USA. NASA, George C Marshall Space Flight Ctr, Huntsville, AL 35812 USA. RP Mattison, DW (reprint author), Stanford Univ, Dept Mech Engn, Stanford, CA 94305 USA. EM dinattiso@stanford.edu NR 27 TC 12 Z9 14 U1 0 U2 4 PU COMBUSTION INST PI PITTSBURGH PA 5001 BAUM BOULEVARD, STE 635, PITTSBURGH, PA 15213-1851 USA SN 0082-0784 J9 P COMBUST INST JI Proc. Combust. Inst. PY 2005 VL 30 BP 2799 EP 2807 DI 10.1016/j.proci.2004.08.026 PN 2 PG 9 WC Thermodynamics; Energy & Fuels; Engineering, Chemical; Engineering, Mechanical SC Thermodynamics; Energy & Fuels; Engineering GA 937RX UT WOS:000229944300123 ER PT S AU Cane, HV AF Cane, HV BE Lacoste, H TI Are there direct flare particles in large solar particle events? SO Proceedings of the Conference Solar Wind 11 - SOHO 16: CONNECTING SUN AND HELIOSPHERE SE ESA SPECIAL PUBLICATIONS LA English DT Proceedings Paper CT Solar Wind 11 - SOHO 16 Conference CY JUN 12-17, 2005 CL Whistler, CANADA SP European Space Agcy, NASA, CSA ASC, NSF, Univ Michigan DE energetic particles; flares; coronal mass ejections; shocks ID ADVANCED COMPOSITION EXPLORER; III RADIO-BURSTS; ELECTRON; ABUNDANCES; HE-3 AB Enhanced abundances of heavy ions in large solar energetic particle (SEP) events indicate the presence of particles accelerated in flare processes. In this paper it is argued that these flare particles have their origins in the energetic flare that occurs shortly prior to each particle increase. The arguments that have been proffered against this proposal are discussed; they do not pose a serious challenge. Large SEP events comprise a combination of flare and shock accelerated particles with the latter being dominant at low energies. C1 NASA, Goddard Space Flight Ctr, High Energy Astrophys Lab, Greenbelt, MD 20771 USA. RP Cane, HV (reprint author), NASA, Goddard Space Flight Ctr, High Energy Astrophys Lab, Greenbelt Rd, Greenbelt, MD 20771 USA. NR 16 TC 1 Z9 1 U1 0 U2 0 PU ESA PUBLICATIONS DIVISION C/O ESTEC PI 2200 AG NOORDWIJK PA PO BOX 299, 2200 AG NOORDWIJK, NETHERLANDS SN 0379-6566 BN 92-9092-903-0 J9 ESA SP PUBL PY 2005 VL 592 BP 71 EP 75 PG 5 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BDU58 UT WOS:000235471300011 ER PT S AU Burlaga, LF Ness, NF Acuna, MH Lepping, RP Connerney, JEP AF Burlaga, LF Ness, NF Acuna, MH Lepping, RP Connerney, JEP BE Lacoste, H TI Voyager 1 observations of the heliospheric magnetic field: Crossing the termination shock into the heliosheath SO PROCEEDINGS OF THE CONFERENCE SOLAR WIND 11 - SOHO 16: CONNECTING SUN AND HELIOSPHERE SE ESA Special Publications LA English DT Proceedings Paper CT Solar Wind 11 - SOHO 16 Conference CY JUN 12-17, 2005 CL Whistler, CANADA SP European Space Agcy, NASA, CSA ASC, NSF, Univ Michigan ID SOLAR-WIND AB Magnetic field measurements by Voyager 1 (V1) show that the termination shock was crossed on approximate to December 16, 2004 at 94.0 AU. Subsequently, V1 was in heliosheath from day 352, 2004 through at least day 110,2005. C1 NASA Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP NASA Goddard Space Flight Ctr, Bldg 21,Rm 244,Code 612-2, Greenbelt, MD 20771 USA. EM Leonord.F.Burlaga@nasa.gov; nfnudel@yahoo.com; Mario.H.Acuna@nasa.gov; rpl@leprpll.gsfc.nasa.gov; John.E.Connerney@gsfc.nasa.gov RI connerney, john/I-5127-2013 NR 16 TC 0 Z9 0 U1 0 U2 0 PU ESA PUBLICATIONS DIVISION C/O ESTEC PI 2200 AG NOORDWIJK PA PO BOX 299, 2200 AG NOORDWIJK, NETHERLANDS SN 0379-6566 BN 92-9092-903-0 J9 ESA SPEC PUBL PY 2005 VL 592 BP 255 EP 257 PG 3 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BDU58 UT WOS:000235471300038 ER PT S AU Ruzmaikin, A Li, G Zank, G Feynman, J Jun, I AF Ruzmaikin, A Li, G Zank, G Feynman, J Jun, I BE Lacoste, H TI The radial dependence of solar energetic particle fluxes SO Proceedings of the Conference Solar Wind 11 - SOHO 16: CONNECTING SUN AND HELIOSPHERE SE ESA SPECIAL PUBLICATIONS LA English DT Proceedings Paper CT Solar Wind 11 - SOHO 16 Conference CY JUN 12-17, 2005 CL Whistler, CANADA SP European Space Agcy, NASA, CSA ASC, NSF, Univ Michigan ID PROTON FLUENCE MODEL; EVENTS; ACCELERATION; SHOCKS AB We evaluate the radial dependence of solar energetic particles peak fluxes derived from a model of particle acceleration in gradual events. These particles are accelerated at shocks driven from the Sun by coronal mass ejections (CME). The acceleration and transport of particles at the propagating and evolving interplanetary shock is calculated for a strong shock using the dynamical model developed by Li, Zank, and Rice (2003). We found that radial profiles of the particle peak fluxes depend on particle energy. Current models for interplanetary space environment assume that radial dependence is the same for all particle energies. Our results require that new models of the interplanetary space environment be developed. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Ruzmaikin, A (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,M-S 169-506, Pasadena, CA 91109 USA. NR 19 TC 6 Z9 6 U1 0 U2 2 PU ESA PUBLICATIONS DIVISION C/O ESTEC PI 2200 AG NOORDWIJK PA PO BOX 299, 2200 AG NOORDWIJK, NETHERLANDS SN 0379-6566 BN 92-9092-903-0 J9 ESA SP PUBL PY 2005 VL 592 BP 441 EP 444 PG 4 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BDU58 UT WOS:000235471300077 ER PT S AU Sittler, EC Skoug, R Ofman, L Fludra, A AF Sittler, EC Skoug, R Ofman, L Fludra, A BE Lacoste, H TI Semi-empirical model of electron heat flux: SOHO and Ulysses observations SO Proceedings of the Conference Solar Wind 11 - SOHO 16: CONNECTING SUN AND HELIOSPHERE SE ESA SPECIAL PUBLICATIONS LA English DT Proceedings Paper CT Solar Wind 11 - SOHO 16 Conference CY JUN 12-17, 2005 CL Whistler, CANADA SP European Space Agcy, NASA, CSA ASC, NSF, Univ Michigan ID HELIOS PLASMA-EXPERIMENT; SOLAR CORONA; SUPRATHERMAL ELECTRONS; INTERPLANETARY MEDIUM; WIND; DISTRIBUTIONS; GENERATION; TAILS AB A semi-empirical model of the electron heat conduction which is based on both theoretical and observational considerations is presented. The model is applied to the polar regions of the Sun during solar minimum. This model is a 'local model' which uses the Krook's anzatz for the collision term in the Boltzmann equation. A hybrid collision term is used with Coulomb collision and wave scattering terms, respectively. Coulomb collisions cannot scatter suprathermal electrons effectively, while waves can. The model assumes a kappa distribution for the background electron gas. A semi-empirical MHD model of the corona and solar wind are used to constrain the model solutions. If the effective heat flux derived from the semi-empirical MHD model is dominated by electrons, then they can produce high speed flows over the Sun's poles and that wave scattering is needed to regulate the heat flux within experimental constraints. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Sittler, EC (reprint author), NASA, Goddard Space Flight Ctr, Code 612-2,8800 Greenbelt Rd, Greenbelt, MD 20771 USA. NR 19 TC 0 Z9 0 U1 0 U2 0 PU ESA PUBLICATIONS DIVISION C/O ESTEC PI 2200 AG NOORDWIJK PA PO BOX 299, 2200 AG NOORDWIJK, NETHERLANDS SN 0379-6566 BN 92-9092-903-0 J9 ESA SP PUBL PY 2005 VL 592 BP 445 EP 448 PG 4 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BDU58 UT WOS:000235471300078 ER PT S AU Szabo, A AF Szabo, A BE Lacoste, H TI Determination of interplanetary shock characteristics SO Proceedings of the Conference Solar Wind 11 - SOHO 16: CONNECTING SUN AND HELIOSPHERE SE ESA SPECIAL PUBLICATIONS LA English DT Proceedings Paper CT Solar Wind 11 - SOHO 16 Conference CY JUN 12-17, 2005 CL Whistler, CANADA SP European Space Agcy, NASA, CSA ASC, NSF, Univ Michigan ID RANKINE-HUGONIOT PROBLEM AB This paper presents the analysis of a number of interplanetary shocks observed by near-Earth solar wind monitors. Single and four-spacecraft shock normal determination methods are compared and it is demonstrated that the four-spacecraft timing method is not generally more accurate than the single-spacecraft Rankine-Hugoniot fit. Moreover, the single-spacecraft methods, unlike the four-spacecraft ones, allow the determination of possible shock surface curvatures. A case study of the August 10, 1998 interplanetary shock observed by five solar wind monitors is presented. It is suggested that small-scale (few RE) ripples exist on the surface of this shock. C1 NASA, Goddard Space Flight Ctr, Lab Solar & Space Phys, Greenbelt, MD 20771 USA. RP Szabo, A (reprint author), NASA, Goddard Space Flight Ctr, Lab Solar & Space Phys, Code 661, Greenbelt, MD 20771 USA. NR 9 TC 2 Z9 2 U1 0 U2 0 PU ESA PUBLICATIONS DIVISION C/O ESTEC PI 2200 AG NOORDWIJK PA PO BOX 299, 2200 AG NOORDWIJK, NETHERLANDS SN 0379-6566 BN 92-9092-903-0 J9 ESA SP PUBL PY 2005 VL 592 BP 449 EP 452 PG 4 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BDU58 UT WOS:000235471300079 ER PT S AU Murphy, N Smith, E Rodgers, W Jefferies, S AF Murphy, N Smith, E Rodgers, W Jefferies, S BE Lacoste, H TI Chromospheric observations in the helium 1083nm line - A new instrument SO Proceedings of the Conference Solar Wind 11 - SOHO 16: CONNECTING SUN AND HELIOSPHERE SE ESA SPECIAL PUBLICATIONS LA English DT Proceedings Paper CT Solar Wind 11 - SOHO 16 Conference CY JUN 12-17, 2005 CL Whistler, CANADA SP European Space Agcy, NASA, CSA ASC, NSF, Univ Michigan ID SOLAR OSCILLATIONS; HIGH-PRECISION; FILTER; NM; ANGSTROM AB Photometric, spectroscopic and polarimetric observations in the Helium 1083 nm line provide important diagnostic information on the structure and dynamics of the chromosphere. We describe an imaging instrument designed to probe the chromosphere in the Helium 1083nm line, based on a Helium magnetooptical filter. The instrument has two narrow passbands (approximate to 0.006 nm) in the wings of each line of the Helium 1083nm triplet, high throughput and stability, making it ideal for making high cadence observations in support of studies of chromospheric dynamics and wave propagation. We describe the characteristics of the instrument and present preliminary observations and discuss future plans. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Murphy, N (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 27 TC 0 Z9 0 U1 0 U2 0 PU ESA PUBLICATIONS DIVISION C/O ESTEC PI 2200 AG NOORDWIJK PA PO BOX 299, 2200 AG NOORDWIJK, NETHERLANDS SN 0379-6566 BN 92-9092-903-0 J9 ESA SP PUBL PY 2005 VL 592 BP 511 EP 514 PG 4 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BDU58 UT WOS:000235471300094 ER PT S AU Podesta, JJ Roberts, DA AF Podesta, JJ Roberts, DA BE Lacoste, H TI Statistical stationarity of solar wind time series SO Proceedings of the Conference Solar Wind 11 - SOHO 16: CONNECTING SUN AND HELIOSPHERE SE ESA SPECIAL PUBLICATIONS LA English DT Proceedings Paper CT Solar Wind 11 - SOHO 16 Conference CY JUN 12-17, 2005 CL Whistler, CANADA SP European Space Agcy, NASA, CSA ASC, NSF, Univ Michigan AB Viewed as a stochastic process, the solar wind is approximately stationary over time periods spanning several solar cycles. For shorter time periods the solar wind is modulated by solar cycle variations which give rise to a slowly moving trend in the data. In this study, analyses performed using solar wind data obtained at 1 AU by NASA's Advanced Composition Explorer (ACE) during the 7 year period 1998-2004 are used to argue that the solar wind is approximately stationary over long times (similar to 100 years). The results suggest that power spectra obtained using data records from one to ten years in length yield an approximation of the true power spectrum of the underlying stochastic process for frequencies greater than approximately 5 x 10(-6) Hz. C1 NASA, Goddard Space Flight Ctr, Lab Solar & Space Phys, Greenbelt, MD 20771 USA. RP Podesta, JJ (reprint author), NASA, Goddard Space Flight Ctr, Lab Solar & Space Phys, Code 661, Greenbelt, MD 20771 USA. NR 2 TC 0 Z9 0 U1 0 U2 0 PU ESA PUBLICATIONS DIVISION C/O ESTEC PI 2200 AG NOORDWIJK PA PO BOX 299, 2200 AG NOORDWIJK, NETHERLANDS SN 0379-6566 BN 92-9092-903-0 J9 ESA SP PUBL PY 2005 VL 592 BP 531 EP 534 PG 4 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BDU58 UT WOS:000235471300099 ER PT S AU Suess, ST Nerney, S AF Suess, ST Nerney, S BE Lacoste, H TI Flow in thin streamer boundaries, streamer stalks, and plumes between 2 and 10 solar RADII SO Proceedings of the Conference Solar Wind 11 - SOHO 16: CONNECTING SUN AND HELIOSPHERE SE ESA SPECIAL PUBLICATIONS LA English DT Proceedings Paper CT Solar Wind 11 - SOHO 16 Conference CY JUN 12-17, 2005 CL Whistler, CANADA SP European Space Agcy, NASA, CSA ASC, NSF, Univ Michigan DE streamers; slow wind; MHD ID WIND AB Slow solar wind is believed to arise inside the brightness boundary of streamers. In two recent studies, we describe analytic models of flow in this layer that are designed to analyze the effect of the magnetic field on the geometry of the flow (Suess & Nerney, 2002; Nerney & Suess, 2005). The first study described conditions that lead to a decrease of the flow speed with increasing height near the top of the closed magnetic helmet. The second study generalized the model to permit outflow in an arbitrarily thin layer inside the brightness boundary and the flow geometry to be constrictive or divergent above the helmet. A diverging streamer or ray above 2-3 solar radii occurs if the plasma beta is greater than unity inside the streamer and less than unity outside. The same argument can be used to discover the height above which the plasma beta in plumes, inside coronal holes, is greater than unity. The utility of this result is further examined here. C1 NASA, George C Marshall Space Flight Ctr, Huntsville, AL 35812 USA. RP Suess, ST (reprint author), NASA, George C Marshall Space Flight Ctr, Huntsville, AL 35812 USA. NR 10 TC 0 Z9 0 U1 0 U2 0 PU ESA PUBLICATIONS DIVISION C/O ESTEC PI 2200 AG NOORDWIJK PA PO BOX 299, 2200 AG NOORDWIJK, NETHERLANDS SN 0379-6566 BN 92-9092-903-0 J9 ESA SP PUBL PY 2005 VL 592 BP 559 EP 562 PG 4 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BDU58 UT WOS:000235471300106 ER PT S AU Usmanov, AV Goldstein, ML AF Usmanov, AV Goldstein, ML BE Lacoste, H TI Three-dimensional solar wind model with pickup protons SO Proceedings of the Conference Solar Wind 11 - SOHO 16: CONNECTING SUN AND HELIOSPHERE SE ESA SPECIAL PUBLICATIONS LA English DT Proceedings Paper CT Solar Wind 11 - SOHO 16 Conference CY JUN 12-17, 2005 CL Whistler, CANADA SP European Space Agcy, NASA, CSA ASC, NSF, Univ Michigan DE solar wind structure; MHD simulation; pickup protons; Voyager ID LOCAL INTERSTELLAR-MEDIUM; NEUTRAL HYDROGEN; HELIOSPHERE; TERMINATION; ULYSSES AB We have developed a three-dimensional steady-state MHD model of the solar corona and solar wind. The model covers the region from the coronal base to 100 AU and accounts for the effects of pickup protons in the distant heliosphere. To attain these ends, the two-region model of Usmanov and Goldstein (2003) was modified to include a region III that extends from 1-100 AU and incorporates a population of interstellar pickup protons and its interaction with the solar wind protons. We compute the global structure of the solar wind from the coronal base out to 100 AU and compare our results with Voyager 2 observations. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Usmanov, AV (reprint author), NASA, Goddard Space Flight Ctr, Code 612-2, Greenbelt, MD 20771 USA. RI Goldstein, Melvyn/B-1724-2008; Usmanov, Arcadi/A-9860-2013 NR 15 TC 0 Z9 0 U1 0 U2 0 PU ESA PUBLICATIONS DIVISION C/O ESTEC PI 2200 AG NOORDWIJK PA PO BOX 299, 2200 AG NOORDWIJK, NETHERLANDS SN 0379-6566 BN 92-9092-903-0 J9 ESA SP PUBL PY 2005 VL 592 BP 563 EP 566 PG 4 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BDU58 UT WOS:000235471300107 ER PT S AU Goldstein, ML Roberts, DA AF Goldstein, ML Roberts, DA BE Lacoste, H TI Simulations of solar wind turbulence SO Proceedings of the Conference Solar Wind 11 - SOHO 16: CONNECTING SUN AND HELIOSPHERE SE ESA SPECIAL PUBLICATIONS LA English DT Proceedings Paper CT Solar Wind 11 - SOHO 16 Conference CY JUN 12-17, 2005 CL Whistler, CANADA SP European Space Agcy, NASA, CSA ASC, NSF, Univ Michigan DE solar wind structure; MHD simulation ID MINIMUM-VARIANCE; OUTER HELIOSPHERE; ALFVEN WAVES; FLUCTUATIONS; ANISOTROPY; FLOWS AB Simulations of magnetofluid turbulence using a variety of techniques for solving the equations of magnetohydrodynamics have elucidated many aspects of the evolution and properties of the solar wind. In particular, the simulations have shown the important role of velocity shear in driving the evolution of turbulence. MHD simulations have demonstrated the initiation of turbulent cascades arising from an initial packet of Alfven waves, the evolution of cross helicity (the correlation between the fluctuating magnetic and velocity field components), and the formation and evolution of corotating interaction regions. Puzzles remain, however. For example, simulations to date have not provided a satisfactory explanation of the observation that the direction of minimum variance of magnetic fluctuations tends to be oriented along the direction of the background magnetic field. We report preliminary studies indicating that transverse structures, including velocity shear, are essential to explain satisfactorily the evolution of the minimum variance of solar wind magnetic fluctuations. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Goldstein, ML (reprint author), NASA, Goddard Space Flight Ctr, Code 612-2, Greenbelt, MD 20771 USA. RI Goldstein, Melvyn/B-1724-2008 NR 15 TC 0 Z9 0 U1 0 U2 0 PU ESA PUBLICATIONS DIVISION C/O ESTEC PI 2200 AG NOORDWIJK PA PO BOX 299, 2200 AG NOORDWIJK, NETHERLANDS SN 0379-6566 BN 92-9092-903-0 J9 ESA SP PUBL PY 2005 VL 592 BP 617 EP 620 PG 4 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BDU58 UT WOS:000235471300120 ER PT S AU Zhou, XY Smith, EJ Winterhalter, D McComas, DJ Skoug, RM Goldstein, BE Smith, CW AF Zhou, XY Smith, EJ Winterhalter, D McComas, DJ Skoug, RM Goldstein, BE Smith, CW BE Lacoste, H TI Morphology and evolution of the heliospheric current and plasma sheets from 1 to 5 AU SO PROCEEDINGS OF THE CONFERENCE SOLAR WIND 11 - SOHO 16: CONNECTING SUN AND HELIOSPHERE SE ESA Special Publications LA English DT Proceedings Paper CT Solar Wind 11 - SOHO 16 Conference CY JUN 12-17, 2005 CL Whistler, CANADA SP European Space Agcy, NASA, CSA ASC, NSF, Univ Michigan AB Spacecraft reaching 5 AU and beyond present an opportunity to study the thickness of the heliospheric current sheet (HCS) and plasma sheet (HPS), how they change with distance and what determines their thickness. To answer these questions, we studied HCS/HPS thickness at several distances using field and plasma data obtained by Ulysses and ACE. The Ulysses data were obtained in 1991 en-route to Jupiter near 3 AU and in 2004 near 5 AU. The same current-plasma sheets analyzed at similar to 5 AU were then identified and studied in ACE data at I AU. The median thickness of the HCS decreased slightly with distance from the sun (1700 to 1450 km). The HPS medians also decreased with distance (3x 10(6) to 1.4x 10(6) km). However, individual HCS thicknesses appear to be uncorrelated with the associated HPS thickness. No obvious controllers of the HCS or HPS thickness have been identified. Polarity reversals in electron heat flux were well correlated with the HCS at 5 AU. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Zhou, XY (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Xiaoyan.Zhou@jpl.nasa.gov; Edward.J.Smith@jpl.nasa.gov; Daniel.Winterhalter@jpl.nasa.gov; DMcComas@swri.edu; rskoug@lanl.gov; Bruce.Goldstein@jpl.nasa.gov; chuck@briaxa.sr.unh.edu NR 4 TC 4 Z9 4 U1 0 U2 1 PU ESA PUBLICATIONS DIVISION C/O ESTEC PI 2200 AG NOORDWIJK PA PO BOX 299, 2200 AG NOORDWIJK, NETHERLANDS SN 0379-6566 BN 92-9092-903-0 J9 ESA SPEC PUBL PY 2005 VL 592 BP 659 EP 662 PG 4 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BDU58 UT WOS:000235471300130 ER PT S AU Roberts, A Rezapkin, V King, J AF Roberts, A Rezapkin, V King, J BE Lacoste, H TI The virtual space physics observatory: Integrated access to present and future solar and space physics data and services SO Proceedings of the Conference Solar Wind 11 - SOHO 16: CONNECTING SUN AND HELIOSPHERE SE ESA SPECIAL PUBLICATIONS LA English DT Proceedings Paper CT Solar Wind 11 - SOHO 16 Conference CY JUN 12-17, 2005 CL Whistler, CANADA SP European Space Agcy, NASA, CSA ASC, NSF, Univ Michigan AB Virtual Observatories represent a new paradigm for research in many fields. Recent advances in this area for Space and Solar Physics have led to operational systems and the promise of a highly integrated research environment in which a fleet of spacecraft and ground facilities function as a virtual "great observatory." The Virtual Space Physics Observatory is one of a number of efforts in this direction. C1 NASA, Goddard Space Flight Ctr, Lab Solar & Space Phys, Greenbelt, MD 20771 USA. RP Roberts, A (reprint author), NASA, Goddard Space Flight Ctr, Lab Solar & Space Phys, Code 612-2, Greenbelt, MD 20771 USA. NR 0 TC 0 Z9 0 U1 0 U2 0 PU ESA PUBLICATIONS DIVISION C/O ESTEC PI 2200 AG NOORDWIJK PA PO BOX 299, 2200 AG NOORDWIJK, NETHERLANDS SN 0379-6566 BN 92-9092-903-0 J9 ESA SP PUBL PY 2005 VL 592 BP 701 EP 704 PG 4 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BDU58 UT WOS:000235471300141 ER PT S AU Richardson, IG Cane, HV AF Richardson, IG Cane, HV BE Lacoste, H TI A survey of interplanetary coronal mass ejections in the near-Earth solar wind during 1996-2005 SO PROCEEDINGS OF THE CONFERENCE SOLAR WIND 11 - SOHO 16: CONNECTING SUN AND HELIOSPHERE SE ESA Special Publications LA English DT Proceedings Paper CT Solar Wind 11 - SOHO 16 Conference CY JUN 12-17, 2005 CL Whistler, CANADA SP European Space Agcy, NASA, CSA ASC, NSF, Univ Michigan AB We have extended our comprehensive survey of interplanetary coronal mass ejections (ICMEs) in the near-Earth solar wind since 1996 up to near-present, and have incorporated solar wind compositional data from ACE/SWICS into the identification of these events. We discuss the variations in the ICME occurrence rate, including evidence for a similar to 160 day periodicity, the average properties of the ICMEs, the fraction that are magnetic clouds, and the relationship between ICME properties and geomagnetic storms. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Richardson, IG (reprint author), NASA, Goddard Space Flight Ctr, Code 661, Greenbelt, MD 20771 USA. EM Ian.Richardson@gsfc.nasa.gov; hilary.cane@utas.edu.au OI Richardson, Ian/0000-0002-3855-3634 NR 10 TC 6 Z9 6 U1 0 U2 0 PU ESA PUBLICATIONS DIVISION C/O ESTEC PI 2200 AG NOORDWIJK PA PO BOX 299, 2200 AG NOORDWIJK, NETHERLANDS SN 0379-6566 BN 92-9092-903-0 J9 ESA SPEC PUBL PY 2005 VL 592 BP 755 EP 758 PG 4 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BDU58 UT WOS:000235471300154 ER PT S AU Erickson, EF AF Erickson, EF BE Wilson, A TI The SOFIA program SO PROCEEDINGS OF THE DUSTY AND MOLECULAR UNIVERSE: A PRELUDE TO HERSCHEL AND ALMA SE ESA SPECIAL PUBLICATIONS LA English DT Proceedings Paper CT Conference on the Dusty and Molecular Universe CY OCT 27-29, 2004 CL Paris, FRANCE SP Minist Rech, Observ Paris, Minist Educ Natl, CNES, Inst Natl Sci Univers, CNRS, European So Observ, European Space Agcy AB SOFIA, the Stratospheric Observatory for Infrared Astronomy, is a joint project of NASA in the U.S. and the DLR in Germany. It is designed to operate at altitudes from 12 to 14 km and wavelengths from 0.3 pm to 1.6 mm over a 20 year lifetime. Its 2.5 m effective diameter telescope will be diffraction limited at wavelengths beyond roughly 15 pm, for example producing a point-spread function similar to 8.5 arc seconds FWHM at 100 mu m. SOFIA's Boeing 747SP aircraft platform will allow coverage of the entire sky and enable unique observations of ephemeral events. Nine first-generation focal plane instruments are being built, with more to be added later. These attributes assure SOFIA a vital role in future studies of the interstellar medium and the solar system, as well as in other disciplines. Topics discussed here are: scientific motivation, the observatory and its relation to other facilities, the science instruments, some science examples, status, and the planned observing program. C1 NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Erickson, EF (reprint author), NASA, Ames Res Ctr, MS 245-6, Moffett Field, CA 94035 USA. NR 9 TC 2 Z9 2 U1 0 U2 0 PU ESA PUBLICATIONS DIVISION C/O ESTEC PI 2200 AG NOORDWIJK PA PO BOX 299, 2200 AG NOORDWIJK, NETHERLANDS SN 0379-6566 J9 ESA SP PUBL PY 2005 VL 577 BP 69 EP 74 PG 6 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BBR24 UT WOS:000227350800011 ER PT S AU Staguhn, JG Schinnerer, E Eckart, A Scharwachter, J AF Staguhn, JG Schinnerer, E Eckart, A Scharwachter, J BE Wilson, A TI Sub-arcsecond multi-transition molecular line observations of the nearby QSO I Zw 1 SO PROCEEDINGS OF THE DUSTY AND MOLECULAR UNIVERSE: A PRELUDE TO HERSCHEL AND ALMA SE ESA SPECIAL PUBLICATIONS LA English DT Proceedings Paper CT Conference on the Dusty and Molecular Universe CY OCT 27-29, 2004 CL Paris, FRANCE SP Minist Rech, Observ Paris, Minist Educ Natl, CNES, Inst Natl Sci Univers, CNRS, European So Observ, European Space Agcy DE galaxies : ISM; nuclei-quasars : individual (I Zw 1). ID HOST; GAS AB We present the first sub-kpc (similar to 0.7" approximate to 850 pc) resolution (CO)-C-12(1-0) molecular line observations of the ISM in the host galaxy of the QSO I Zw 1. The observations were obtained with the BIMA mm-interferometer in its compact A configuration. The BIMA data are complemented by new observations of the (CO)-C-12(2-1) and (CO)-C-13(1-0) line with IRAM Plateau de Bure mm-interferometer (PdBI) at 0.9" and 2.1" resolution, respectively. Our images of the (CO)-C-12(1-0) line emission show a ring-like structure in the circumnuclear molecular gas distribution with an inner radius of about 1.2 kpc. A comparison of the BIMA data with IRAM PdBI (CO)-C-12(2-1) observations shows variations in the excitation conditions of the molecular gas in the innermost 1.5" comprising the nuclear re-ion of I Zw 1. The observed properties of the molecular cloud complexes in the disk of the host galaxy suggest that they can be the sites of massive circumnuclear star formation, and show no indications of excitation by the nuclear AGN. This all indicates that the molecular gas in a QSO host,galaxy has similar properties to the gas observed in nearby low luminosity AGNs. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Staguhn, JG (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. NR 3 TC 0 Z9 0 U1 0 U2 0 PU ESA PUBLICATIONS DIVISION C/O ESTEC PI 2200 AG NOORDWIJK PA PO BOX 299, 2200 AG NOORDWIJK, NETHERLANDS SN 0379-6566 J9 ESA SP PUBL PY 2005 VL 577 BP 331 EP 332 PG 2 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BBR24 UT WOS:000227350800077 ER PT S AU Vassberg, N AF Vassberg, Nathan BE Lacoste, H TI Making safety matter SO Proceedings of the First IAASS Conference on Space Safety, a New Beginning SE ESA SPECIAL PUBLICATIONS LA English DT Proceedings Paper CT 1st IAASS Conference on Space Safety, A New Beginning CY OCT 25-27, 2005 CL Nice, FRANCE SP IAASS AB Safety organizations stereotypically consist of conservative hand wringers who antagonize program managers and make outlandish recommendations without regard for schedule or cost. Safety must transcend this conventional wisdom, defy this typecast, and guide programs in making risk decisions. To do this effectively requires a critical balance of technical expertise, understanding of the program goals and requirements, consideration for the program cost and schedule, and political savvy in determining when to force an issue and when to compromise. The Columbia Accident Investigation Board (CAIB) Report states, "Organizations that successfully deal with high-risk technologies create and sustain a disciplined safety system capable of identifying, analyzing, and controlling hazards throughout a technology's lifecycle." [1]. Essentially, safety must sift through facts, data, and conjecture to separate the critical from the trivial when making risk decisions. An examination of components of successful safety organizations and their key attributes prove necessary to understand their functions. This discussion defines what matters building a powerful safety organization valued by a program manager. That organization will be neither an overbearing force in the program nor a "silent safety organization" that the Roger's Commission warns against in its study. [2]. C1 NASA, Houston, TX 77058 USA. RP Vassberg, N (reprint author), NASA, 2101 NASA Pkwy, Houston, TX 77058 USA. NR 5 TC 0 Z9 0 U1 0 U2 0 PU ESA PUBLICATIONS DIVISION C/O ESTEC PI 2200 AG NOORDWIJK PA PO BOX 299, 2200 AG NOORDWIJK, NETHERLANDS SN 0379-6566 BN 92-9092-910-3 J9 ESA SP PUBL PY 2005 VL 599 BP 3 EP 8 PG 6 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BEG36 UT WOS:000237218500001 ER PT S AU Goodin, R AF Goodin, Ronnie BE Lacoste, H TI Safety auditing and assessments SO Proceedings of the First IAASS Conference on Space Safety, a New Beginning SE ESA SPECIAL PUBLICATIONS LA English DT Proceedings Paper CT 1st IAASS Conference on Space Safety, A New Beginning CY OCT 25-27, 2005 CL Nice, FRANCE SP IAASS AB Safety professionals typically do not engage in audits and independent assessments with the vigor as do our quality brethren. Taking advantage of industry and government experience conducting value added Independent Assessments or Audits benefits a safety program. Most other organizations simply call this process "internal audits." Sources of audit training are presented and compared. A relation of logic between audit techniques and mishap investigation is discussed. An example of an audit process is offered. Shortcomings and pitfalls of auditing are covered. C1 NASA, SAF, Kennedy Space Ctr, FL 32899 USA. RP Goodin, R (reprint author), NASA, SAF, Kennedy Space Ctr, FL 32899 USA. NR 3 TC 0 Z9 0 U1 0 U2 0 PU ESA PUBLICATIONS DIVISION C/O ESTEC PI 2200 AG NOORDWIJK PA PO BOX 299, 2200 AG NOORDWIJK, NETHERLANDS SN 0379-6566 BN 92-9092-910-3 J9 ESA SP PUBL PY 2005 VL 599 BP 17 EP 24 PG 8 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BEG36 UT WOS:000237218500003 ER PT S AU Newman, JS Wander, SM Vecellio, D AF Newman, J. Steven Wander, Stephen M. Vecellio, Don BE Lacoste, H TI Assurance process mapping SO Proceedings of the First IAASS Conference on Space Safety, a New Beginning SE ESA SPECIAL PUBLICATIONS LA English DT Proceedings Paper CT 1st IAASS Conference on Space Safety, A New Beginning CY OCT 25-27, 2005 CL Nice, FRANCE SP IAASS AB Assurance Process (AP) Mapping is a means to graphically depict the multi-dimensional assurance processes implemented on organizationally complex NASA aerospace programs. AP Mapping helps to better understand and manage program/project complexity, particularly as it relates to managing key assurance activities and functions. Ultimately, the AP Map assists decision makers by providing knowledge of the governing assurance requirements, a baseline understanding of the assurance processes implemented on the program, and visibility into their implementation. NASA and international space programs often involve multiple: development and implementation phases; project elements; flight elements; contractors; subcontractors; governments; and governmental agencies. Assurance processes must be implemented throughout the program life cycle and across all levels of the program organization. Supporting this life cycle framework are a myriad of "assurance agents," individuals accountable for implementation of governing assurance requirements and the organizations that review them, each with some element of the overall assurance picture. This paper provides a high-level tutorial and examples of the AP Mapping protocol and graphical techniques that have been most recently applied to the Space Shuttle Program in preparation for Return to Flight. C1 NASA Headquarters, Washington, DC 20546 USA. RP Newman, JS (reprint author), NASA Headquarters, 300 E St SW, Washington, DC 20546 USA. NR 0 TC 0 Z9 0 U1 0 U2 0 PU ESA PUBLICATIONS DIVISION C/O ESTEC PI 2200 AG NOORDWIJK PA PO BOX 299, 2200 AG NOORDWIJK, NETHERLANDS SN 0379-6566 BN 92-9092-910-3 J9 ESA SP PUBL PY 2005 VL 599 BP 25 EP 31 PG 7 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BEG36 UT WOS:000237218500004 ER PT S AU Huls, DT Meehan, KM AF Huls, Dale T. Meehan, Kevin M. BE Lacoste, H TI Implementation of programmatic quality and the impact on safety SO Proceedings of the First IAASS Conference on Space Safety, a New Beginning SE ESA SPECIAL PUBLICATIONS LA English DT Proceedings Paper CT 1st IAASS Conference on Space Safety, A New Beginning CY OCT 25-27, 2005 CL Nice, FRANCE SP IAASS AB The implementation of an inadequate programmatic quality assurance discipline has the potential to adversely affect safety and mission success. This is best demonstrated in the lessons provided by the Apollo I Apollo 13 Challenger, and Columbia accidents; NASA Safety and Mission Assurance (S&MA) benchmarking exchanges; and conclusions reached by the Shuttle Return-to-Flight Task Group established following the Columbia Shuttle accident. Examples from the ISS Program demonstrate continuing issues with programmatic quality. Failure to adequately address programmatic quality assurance issues has a real potential to lead to continued inefficiency, increases in program costs, and additional catastrophic accidents. C1 NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. RP Huls, DT (reprint author), NASA, Lyndon B Johnson Space Ctr, Code OE,2101 NASA Pkwy, Houston, TX 77058 USA. NR 9 TC 0 Z9 0 U1 0 U2 0 PU ESA PUBLICATIONS DIVISION C/O ESTEC PI 2200 AG NOORDWIJK PA PO BOX 299, 2200 AG NOORDWIJK, NETHERLANDS SN 0379-6566 BN 92-9092-910-3 J9 ESA SP PUBL PY 2005 VL 599 BP 33 EP 41 PG 9 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BEG36 UT WOS:000237218500005 ER PT S AU Whiteman, DE Valencia, LM Simpson, JC AF Whiteman, Donald E. Valencia, Lisa M. Simpson, James C. BE Lacoste, H TI Space-based range safety and future space range applications SO Proceedings of the First IAASS Conference on Space Safety, a New Beginning SE ESA SPECIAL PUBLICATIONS LA English DT Proceedings Paper CT 1st IAASS Conference on Space Safety, A New Beginning CY OCT 25-27, 2005 CL Nice, FRANCE SP IAASS AB The National Aeronautics and Space Administration (NASA) Space-Based Telemetry and Range Safety (STARS) study is a multiphase project to demonstrate the performance, flexibility and cost savings that can be realized by using space-based assets for the Range Safety [global positioning system (GPS) metric tracking data, flight termination command and range safety data relay] and Range User (telemetry) functions during vehicle launches and landings. Phase 1 included flight testing S-band Range Safety and Range User hardware in 2003 onboard a high-dynamic aircraft platform at Dryden Flight Research Center (Edwards, California, USA) using the NASA Tracking and Data. Re-lay Satellite System (TDRSS) as the communications link. The current effort, Phase 2, includes hardware and packaging upgrades to the S-band Range Safety system and development of a high data rate Ku-band Range User system. The enhanced Phase 2 Range Safety Unit (RSU) provided real-time video for three days during the historic GlobalFlyer (Scaled Composites, Mojave, California, USA) flight in March, 2005. Additional Phase 2 testing will include a sounding rocket test of the Range Safety system and aircraft flight testing of both systems. Future testing will include a flight test on a launch vehicle platform. This paper discusses both Range Safety and Range User developments and testing with emphasis on the Range Safety system. The operational concept of a future space-based range is also discussed. C1 NASA, Dryden Flight Res Ctr, Edwards AFB, CA 93523 USA. RP Whiteman, DE (reprint author), NASA, Dryden Flight Res Ctr, Code RI, Edwards AFB, CA 93523 USA. NR 6 TC 0 Z9 0 U1 0 U2 0 PU ESA PUBLICATIONS DIVISION C/O ESTEC PI 2200 AG NOORDWIJK PA PO BOX 299, 2200 AG NOORDWIJK, NETHERLANDS SN 0379-6566 BN 92-9092-910-3 J9 ESA SP PUBL PY 2005 VL 599 BP 131 EP 136 PG 6 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BEG36 UT WOS:000237218500018 ER PT S AU Jeevarajan, JA AF Jeevarajan, Judith A. BE Lacoste, H TI Certification of COTS and non-COTS batteries for crewed space vehicles SO Proceedings of the First IAASS Conference on Space Safety, a New Beginning SE ESA SPECIAL PUBLICATIONS LA English DT Proceedings Paper CT 1st IAASS Conference on Space Safety, A New Beginning CY OCT 25-27, 2005 CL Nice, FRANCE SP IAASS AB The certification process for the use of COTS (Commercial-off-the-Shelf) and non-COTS batteries has undergone changes and improvements in the past two years. Bilateral meetings of NASA independently with the European Space Agency (ESA) and the Russian Space Agency (RSC-E), have resulted in agreements that clarified the certification process. The processes agreed upon will be discussed in this paper. C1 NASA Johnson Space Ctr, Houston, TX 77058 USA. RP Jeevarajan, JA (reprint author), NASA Johnson Space Ctr, 2101 NASA Pkwy,Mail Stop EP5, Houston, TX 77058 USA. NR 7 TC 0 Z9 0 U1 2 U2 3 PU ESA PUBLICATIONS DIVISION C/O ESTEC PI 2200 AG NOORDWIJK PA PO BOX 299, 2200 AG NOORDWIJK, NETHERLANDS SN 0379-6566 BN 92-9092-910-3 J9 ESA SP PUBL PY 2005 VL 599 BP 229 EP 231 PG 3 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BEG36 UT WOS:000237218500033 ER PT S AU Parke, B Mishkin, A AF Parke, Bonny Mishkin, Andrew BE Lacoste, H TI Best practices in shift handover communication: Mars Exploration Rover surface operations SO Proceedings of the First IAASS Conference on Space Safety, a New Beginning SE ESA SPECIAL PUBLICATIONS LA English DT Proceedings Paper CT 1st IAASS Conference on Space Safety, A New Beginning CY OCT 25-27, 2005 CL Nice, FRANCE SP IAASS AB During its prime mission, Mars Exploration Rover (MER) had many shift handovers in its surface operations. Because of the increased rates of accidents and errors historically associated with shift handovers, MER Mission management paid close attention to shift handovers and, when possible, developed them in accordance with best handover practices. We review the most important of these best practices, and include a generic "Checklist for Effective Handovers" to aid in the development of handovers. We present charts that depict structured information transfer across shifts. These charts show personnel schedules, meetings attended, handovers, and hand-offs on both the MER and on the earlier Mars Pathfinder Mission (MPF). It is apparent from these charts that although the MER Mission had a much larger number of surface operations personnel than MPF (approximately 300 vs. 178), and had three shifts instead of two, that it used many of the successful MPF communication strategies. Charts such as these can be helpful to those designing complicated and unique mission surface operations. C1 San Jose State Univ, Fdn NASA Ames, NASA Ames Res Ctr, Moffett Field, CA 94035 USA. RP Parke, B (reprint author), San Jose State Univ, Fdn NASA Ames, NASA Ames Res Ctr, MS 262-4, Moffett Field, CA 94035 USA. NR 27 TC 0 Z9 0 U1 0 U2 1 PU ESA PUBLICATIONS DIVISION C/O ESTEC PI 2200 AG NOORDWIJK PA PO BOX 299, 2200 AG NOORDWIJK, NETHERLANDS SN 0379-6566 BN 92-9092-910-3 J9 ESA SP PUBL PY 2005 VL 599 BP 259 EP 264 PG 6 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BEG36 UT WOS:000237218500038 ER PT S AU Kirkpatrick, PD Trinchero, JP AF Kirkpatrick, Paul D. Trinchero, Jean-Pierre BE Lacoste, H TI A common approach for the certifying of international Space Station (ISS) basic hardware for ground safety SO Proceedings of the First IAASS Conference on Space Safety, a New Beginning SE ESA SPECIAL PUBLICATIONS LA English DT Proceedings Paper CT 1st IAASS Conference on Space Safety, A New Beginning CY OCT 25-27, 2005 CL Nice, FRANCE SP IAASS C1 NASA, SA C3, Kennedy Space Ctr, FL 32899 USA. RP Kirkpatrick, PD (reprint author), NASA, SA C3, Kennedy Space Ctr, FL 32899 USA. NR 0 TC 0 Z9 0 U1 0 U2 0 PU ESA PUBLICATIONS DIVISION C/O ESTEC PI 2200 AG NOORDWIJK PA PO BOX 299, 2200 AG NOORDWIJK, NETHERLANDS SN 0379-6566 BN 92-9092-910-3 J9 ESA SP PUBL PY 2005 VL 599 BP 279 EP 282 PG 4 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BEG36 UT WOS:000237218500041 ER PT S AU Safie, FM Nguyen, SC AF Safie, Fayassal M. Nguyen, Son C. BE Lacoste, H TI Role of process control in improving space vehicle safety a Space Shuttle external tank example SO Proceedings of the First IAASS Conference on Space Safety, a New Beginning SE ESA SPECIAL PUBLICATIONS LA English DT Proceedings Paper CT 1st IAASS Conference on Space Safety, A New Beginning CY OCT 25-27, 2005 CL Nice, FRANCE SP IAASS AB Developing a safe and reliable space vehicle requires good design and good manufacturing, or in other words "design it right and build it right". A great design can be hard to build or manufacture mainly due to process control challenges. Difficulties with process control can lead to lower quality. As a result, the system suffers from low quality which leads to low reliability and high system risk. The Space Shuttle has experienced some of those cases, but has overcome these difficulties through extensive redesign efforts and process enhancements. The most recent example is the Space Shuttle External Tank (ET) Thermal Protection System (TPS) reliability issues that contributed to the Columbia accident. As a result, extensive redesign and process enhancement activities have been performed over the last two years to minimize the sensitivities and difficulties of the manual TPS application process. This paper discusses the importance of quality in system design, and the relationship between quality, reliability, and system safety for space vehicles. C1 NASA MSFC, Huntsville, AL 35812 USA. RP Safie, FM (reprint author), NASA MSFC, Huntsville, AL 35812 USA. NR 6 TC 0 Z9 0 U1 0 U2 0 PU ESA PUBLICATIONS DIVISION C/O ESTEC PI 2200 AG NOORDWIJK PA PO BOX 299, 2200 AG NOORDWIJK, NETHERLANDS SN 0379-6566 BN 92-9092-910-3 J9 ESA SP PUBL PY 2005 VL 599 BP 285 EP 288 PG 4 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BEG36 UT WOS:000237218500042 ER PT S AU Goodin, R AF Goodin, Ronnie BE Lacoste, H TI Art World's concept of negative space applied to system safety management SO Proceedings of the First IAASS Conference on Space Safety, a New Beginning SE ESA SPECIAL PUBLICATIONS LA English DT Proceedings Paper CT 1st IAASS Conference on Space Safety, A New Beginning CY OCT 25-27, 2005 CL Nice, FRANCE SP IAASS AB Tools from several different disciplines can improve system safety management. This paper relates the Art World with our system safety world showing useful art schools of thought applied to system safety management; developing an art theory-system safety bridge. This bridge is then used to demonstrate relations with risk management, the legal system, personnel management and basic management (establishing priorities.) One goal of this presentation/paper is simply to be a fun diversion from the many technical topics presented during the conference. C1 NASA, SAF, Kennedy Space Ctr, FL 32899 USA. RP Goodin, R (reprint author), NASA, SAF, Kennedy Space Ctr, FL 32899 USA. NR 5 TC 0 Z9 0 U1 0 U2 0 PU ESA PUBLICATIONS DIVISION C/O ESTEC PI 2200 AG NOORDWIJK PA PO BOX 299, 2200 AG NOORDWIJK, NETHERLANDS SN 0379-6566 BN 92-9092-910-3 J9 ESA SP PUBL PY 2005 VL 599 BP 339 EP 343 PG 5 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BEG36 UT WOS:000237218500050 ER PT S AU Jeevarajan, JA AF Jeevarajan, Judith A. BE Lacoste, H TI Comparison of safety of two primary lithium batteries for the orbiter wing leading edge impact sensors SO Proceedings of the First IAASS Conference on Space Safety, a New Beginning SE ESA SPECIAL PUBLICATIONS LA English DT Proceedings Paper CT 1st IAASS Conference on Space Safety, A New Beginning CY OCT 25-27, 2005 CL Nice, FRANCE SP IAASS AB The Orbiter Wing Leading Edge Impact Sensors were powered by lithium primary batteries. The batteries were of the Lithium irondisulfide chemistry. Due to the thermal environments during the flight, this type of cell was chosen and the issues faced during the certification process are described in this paper. C1 NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. RP Jeevarajan, JA (reprint author), NASA, Lyndon B Johnson Space Ctr, 2101 NASA Pkwy,Mail Stop EP5, Houston, TX 77058 USA. NR 1 TC 0 Z9 0 U1 0 U2 0 PU ESA PUBLICATIONS DIVISION C/O ESTEC PI 2200 AG NOORDWIJK PA PO BOX 299, 2200 AG NOORDWIJK, NETHERLANDS SN 0379-6566 BN 92-9092-910-3 J9 ESA SP PUBL PY 2005 VL 599 BP 375 EP 378 PG 4 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BEG36 UT WOS:000237218500055 ER PT S AU Wade, J AF Wade, James BE Lacoste, H TI Safety and mission assurance analyses supporting crewing options for the International Space Station SO Proceedings of the First IAASS Conference on Space Safety, a New Beginning SE ESA SPECIAL PUBLICATIONS LA English DT Proceedings Paper CT 1st IAASS Conference on Space Safety, A New Beginning CY OCT 25-27, 2005 CL Nice, FRANCE SP IAASS AB In the wake of the Columbia accident, the ISS Program and NASA were faced with deciding whether the station should be manned with three crew, two crew, or demanned completely. Initially, several analyses were conducted across the ISS Program which identified the logistics, reliability, science, and safety aspects of the various crew options. However, no one analysis could completely determine which crew option was best. The ISS team was able to identify the relevant information such that an informed, balanced decision could be made. This was accomplished by directing a reliability analysis which identified specific risks with subsystem performance, as well as the logistics analysis which identified the projected spares which would be required to maintain acceptable performance. Additionally, the safety team performed an assessment of hazard reports in order to identify any controls with a dependency on crew size. In parallel with this effort, the reliability & maintainability team performed a review of critical items (CILs) in order to identify any CIL operational workarounds which would be affected by crew size. Finally, the ISS probabilistic risk assessment (PRA) tool provided a risk versus risk comparison between the various crew options. The assessment showed little change in risk to crew when crew size was reduced from 3 to 2 crewmembers. However, the assessment showed an increase in the probability of loss of ISS should the station be demanned. C1 NASA, Lyndon B Johnson Space Ctr, Houston, TX 77059 USA. RP Wade, J (reprint author), NASA, Lyndon B Johnson Space Ctr, NASA Pkwy, Houston, TX 77059 USA. NR 5 TC 0 Z9 0 U1 0 U2 0 PU ESA PUBLICATIONS DIVISION C/O ESTEC PI 2200 AG NOORDWIJK PA PO BOX 299, 2200 AG NOORDWIJK, NETHERLANDS SN 0379-6566 BN 92-9092-910-3 J9 ESA SP PUBL PY 2005 VL 599 BP 419 EP 422 PG 4 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BEG36 UT WOS:000237218500061 ER PT S AU Newman, JS Wander, SM Vecellio, D Miller, AJ AF Newman, J. Steven Wander, Stephen M. Vecellio, Don Miller, Andrew J. BE Lacoste, H TI NASA post-columbia safety and mission assurance, review and assessment initiatives SO Proceedings of the First IAASS Conference on Space Safety, a New Beginning SE ESA SPECIAL PUBLICATIONS LA English DT Proceedings Paper CT 1st IAASS Conference on Space Safety, A New Beginning CY OCT 25-27, 2005 CL Nice, FRANCE SP IAASS AB On February 1, 2003, NASA again experienced a tragic accident as the Space Shuttle Columbia broke apart upon reentry, resulting in the loss of seven astronauts. Several of the findings and observations of the Columbia Accident Investigation Board addressed the need to strengthen the safety and mission assurance function at NASA. This paper highlights key steps undertaken by the NASA Office of Safety and Mission Assurance (OSMA) to establish a stronger and more-robust safety and mission assurance function for NASA programs, projects, facilities and operations. This paper provides an overview of the interlocking OSMA Review and Assessment Division (RAD) institutional and programmatic processes designed to 1) educate, inform, and prepare for audits, 2) verify requirements flow-down, 3) verify process capability, 4) verify compliance with requirements, 5) support risk management decision making, 6) facilitate secure web-based collaboration, and 7) foster continual improvement and the use of lessons learned. C1 NASA Headquarters, Washington, DC 20546 USA. RP Newman, JS (reprint author), NASA Headquarters, 300 E St SW, Washington, DC 20546 USA. NR 2 TC 0 Z9 0 U1 0 U2 0 PU ESA PUBLICATIONS DIVISION C/O ESTEC PI 2200 AG NOORDWIJK PA PO BOX 299, 2200 AG NOORDWIJK, NETHERLANDS SN 0379-6566 BN 92-9092-910-3 J9 ESA SP PUBL PY 2005 VL 599 BP 431 EP 436 PG 6 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BEG36 UT WOS:000237218500063 ER PT S AU Perera, J Holsomback, J AF Perera, Jeevan Holsomback, Jerry BE Lacoste, H TI Implementation of risk management in NASA'S cev project - Ensuring mission success SO Proceedings of the First IAASS Conference on Space Safety, a New Beginning SE ESA SPECIAL PUBLICATIONS LA English DT Proceedings Paper CT 1st IAASS Conference on Space Safety, A New Beginning CY OCT 25-27, 2005 CL Nice, FRANCE SP IAASS AB Most project managers know that Risk Management (RM) is essential to good project management. At NASA, standards and procedures to manage risk through a tiered approach have been developed - from the global agency-wide requirements down to a program or project's implementation. The basic methodology for NASA's risk management strategy includes processes to identify, analyze, plan, track, control, communicate and document risks. The identification, characterization, mitigation plan, and mitigation responsibilities associated with specific risks are documented to help communicate, manage, and effectuate appropriate closure. This approach helps to ensure more consistent documentation and assessment and provides a means of archiving lessons learned for future identification or mitigation activities. A new risk database and management tool was developed by NASA in 2002 and since has been used successfully to communicate, document and manage a number of diverse risks for the International Space Station, Space Shuttle, and several other NASA projects and programs including at the Johnson Space Center. Organizations use this database application to effectively manage and track each risk and gain insight into impacts from other organization's viewpoint to develop integrated solutions. Schedule, cost, technical and safety issues are tracked in detail through this system. Risks are tagged within the system to ensure proper review, coordination and management at the necessary management level. The database is intended as a day-today tool for organizations to manage their risks and elevate those issues that need coordination from above. Each risk is assigned to a managing organization and a specific risk owner who generates mitigation plans as appropriate. In essence, the risk owner is responsible for shepherding the risk through closure. The individual that identifies a new risk does not necessarily get assigned as the risk owner. Whoever is in the best position to effectuate comprehensive closure is assigned as the risk owner. Each mitigation plan includes the specific tasks that will be conducted to either decrease the likelihood of the risk occurring and/or lessen the severity of the consequences if they do occur. As each mitigation task is completed, the responsible managing organization records the completion of the task in the risk database and then re-scores the risk considering the task's results. By keeping scores updated, a managing organization's current top risks and risk posture can be readily identified including the status of any risk in the system. A number of metrics measure risk process trends from data contained in the database. This allows for trend analysis to further identify improvements to the process and assist in the management of all risks. The metrics will also scrutinize both the effectiveness and compliance of risk management requirements. The risk database is an evolving tool and will be continuously improved with capabilities requested by the NASA project community. This paper presents the basic foundations of risk management, the elements necessary for effective risk management, and the capabilities of this new risk database and how it is implemented to support NASA's risk management needs. C1 NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. RP Perera, J (reprint author), NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. NR 4 TC 0 Z9 0 U1 0 U2 0 PU ESA PUBLICATIONS DIVISION C/O ESTEC PI 2200 AG NOORDWIJK PA PO BOX 299, 2200 AG NOORDWIJK, NETHERLANDS SN 0379-6566 BN 92-9092-910-3 J9 ESA SP PUBL PY 2005 VL 599 BP 453 EP 458 PG 6 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BEG36 UT WOS:000237218500066 ER PT S AU Ramsay, CM AF Ramsay, Christopher M. BE Lacoste, H TI NASA'S software safety standard SO Proceedings of the First IAASS Conference on Space Safety, a New Beginning SE ESA SPECIAL PUBLICATIONS LA English DT Proceedings Paper CT 1st IAASS Conference on Space Safety, A New Beginning CY OCT 25-27, 2005 CL Nice, FRANCE SP IAASS AB NASA (National Aeronautics and Space Administration), relies more and more on software to control, monitor, and verify its safety critical systems, facilities and operations. Since the 1960's there has hardly been a spacecraft (manned or unmanned) launched that did not have a computer on board that provided vital command and control services. Despite this growing dependence on software control and monitoring, there has been no consistent application of software safety practices and methodology to NASA's projects with safety critical software. Led by the NASA Headquarters Office of Safety and Mission Assurance, the NASA Software Safety Standard (STD-1819.13B) has recently undergone a significant update in an attempt to provide that consistency. This paper will discuss the key features of the new NASA Software Safety Standard. It will start with a brief history of the use and development of software in safety critical applications at NASA. It will then give a brief overview of the NASA Software Working Group and the approach it took to revise the software engineering process at NASA.. Lastly, it will provide a summary of the major features of the update. C1 NASA, Lyndon B Johnson Space Ctr, Space Shuttle Safety Div, Houston, TX 77058 USA. RP Ramsay, CM (reprint author), NASA, Lyndon B Johnson Space Ctr, Space Shuttle Safety Div, 2101 NASA Pkwy, Houston, TX 77058 USA. NR 4 TC 0 Z9 0 U1 0 U2 0 PU ESA PUBLICATIONS DIVISION C/O ESTEC PI 2200 AG NOORDWIJK PA PO BOX 299, 2200 AG NOORDWIJK, NETHERLANDS SN 0379-6566 BN 92-9092-910-3 J9 ESA SP PUBL PY 2005 VL 599 BP 507 EP 512 PG 6 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BEG36 UT WOS:000237218500074 ER PT S AU Parke, B Orasanu, J Castle, R Hanley, J AF Parke, Bonny Orasanu, Judith Castle, Robert Hanley, Jeff BE Lacoste, H TI Identifying organizational vulnerabilities in space operations with collaborative, tailored, anonymous surveys SO Proceedings of the First IAASS Conference on Space Safety, a New Beginning SE ESA SPECIAL PUBLICATIONS LA English DT Proceedings Paper CT 1st IAASS Conference on Space Safety, A New Beginning CY OCT 25-27, 2005 CL Nice, FRANCE SP IAASS AB Organizational problems have contributed to many aerospace accidents. Because of the unforgiving environment of aerospace, it is crucial to eliminate as many of these problems as possible. Collaborative, tailored, anonymous surveys can identify organizational problems early on. In this paper, we discuss how to develop this type of survey in space support environments, using as an example a survey with International Space Station (ISS) flight controllers. We then discuss some results of this survey to demonstrate how such a survey can identify organizational problems. Finally, we discuss ways in which the survey results were used to address problems and reduce risk. C1 San Jose State Univ, Fdn NASA Ames, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Parke, B (reprint author), San Jose State Univ, Fdn NASA Ames, Ames Res Ctr, MS 262-4, Moffett Field, CA 94035 USA. NR 10 TC 1 Z9 1 U1 0 U2 0 PU ESA PUBLICATIONS DIVISION C/O ESTEC PI 2200 AG NOORDWIJK PA PO BOX 299, 2200 AG NOORDWIJK, NETHERLANDS SN 0379-6566 BN 92-9092-910-3 J9 ESA SP PUBL PY 2005 VL 599 BP 577 EP 582 PG 6 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BEG36 UT WOS:000237218500084 ER PT S AU Lee, AR Bacus, TH Bowersox, AM Newman, JS AF Lee, Arthur R. Bacus, Thomas H. Bowersox, Alexandra M. Newman, J. Steven BE Lacoste, H TI NASA case sensitive review and audit approach SO Proceedings of the First IAASS Conference on Space Safety, a New Beginning SE ESA SPECIAL PUBLICATIONS LA English DT Proceedings Paper CT 1st IAASS Conference on Space Safety, A New Beginning CY OCT 25-27, 2005 CL Nice, FRANCE SP IAASS AB As an Agency involved in high-risk endeavors NASA continually reassesses its commitment to engineering excellence and compliance to requirements. As a component of NASA's continual process improvement, the Office of Safety and Mission Assurance (OSMA) established the Review and Assessment Division (RAD) [1] to conduct independent audits to verify compliance with Agency requirements that impact safe and reliable operations. In implementing its responsibilities, RAD benchmarked various approaches for conducting audits, focusing on organizations that, like NASA, operate in high-risk environments - where seemingly inconsequential departures from safety, reliability, and quality requirements can have catastrophic impact to the public, NASA personnel, high-value equipment, and the environment. The approach used by the U.S. Navy Submarine Program [2] was considered the most fruitful framework for the invigorated OSMA audit processes. Additionally, the results of benchmarking activity revealed that not all audits are conducted using just one approach or even with the same objectives. This led to the concept of discrete, unique "audit cases.". C1 NASA Headquarters, Washington, DC 20546 USA. RP Lee, AR (reprint author), NASA Headquarters, Washington, DC 20546 USA. NR 7 TC 0 Z9 0 U1 0 U2 0 PU ESA PUBLICATIONS DIVISION C/O ESTEC PI 2200 AG NOORDWIJK PA PO BOX 299, 2200 AG NOORDWIJK, NETHERLANDS SN 0379-6566 BN 92-9092-910-3 J9 ESA SP PUBL PY 2005 VL 599 BP 589 EP 594 PG 6 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BEG36 UT WOS:000237218500086 ER PT S AU Huls, DT AF Huls, Dale Thomas BE Lacoste, H TI Use of new communication technologies to change NASA safety culture: Incorporating the use of blogs as a fundamental communications tool SO Proceedings of the First IAASS Conference on Space Safety, a New Beginning SE ESA SPECIAL PUBLICATIONS LA English DT Proceedings Paper CT 1st IAASS Conference on Space Safety, A New Beginning CY OCT 25-27, 2005 CL Nice, FRANCE SP IAASS AB Blogs are an increasingly dominant new communication function on the internet. The power of this technology has forced media, corporations and government organizations to begin to incorporate blogging into their normal business practices. Blogs could be a key component to overcoming NASA's "silent safety culture." As a communications tool, blogs are used to establish trust primarily through the use of a personal voice style of writing. Dissenting voices can be raised and thoroughly vetted via a diversity of participation and experience without peer pressure or fear of retribution. Furthermore, the benefits of blogging as a technical resource to enhance safety are also discussed. The speed and self-vetting nature of blogging can allow managers and decision-makers to make more informed and therefore potentially better decisions with regard to technical and safety issues. Consequently, it is recommended that NASA utilize this new technology as an agent for cultural change. C1 NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. RP Huls, DT (reprint author), NASA, Lyndon B Johnson Space Ctr, Code OE,2101 NASA Pkwy, Houston, TX 77058 USA. NR 12 TC 1 Z9 1 U1 0 U2 1 PU ESA PUBLICATIONS DIVISION C/O ESTEC PI 2200 AG NOORDWIJK PA PO BOX 299, 2200 AG NOORDWIJK, NETHERLANDS SN 0379-6566 BN 92-9092-910-3 J9 ESA SP PUBL PY 2005 VL 599 BP 595 EP 602 PG 8 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BEG36 UT WOS:000237218500087 ER PT S AU Sirota, LB Mulvihill, R Schweitzer, N AF Sirota, Leonard B. Mulvihill, Robert Schweitzer, Nathan BE Lacoste, H TI Communicating safety and mission success risks using risk matrices SO Proceedings of the First IAASS Conference on Space Safety, a New Beginning SE ESA SPECIAL PUBLICATIONS LA English DT Proceedings Paper CT 1st IAASS Conference on Space Safety, A New Beginning CY OCT 25-27, 2005 CL Nice, FRANCE SP IAASS AB In an effort to improve oversight into safety and mission assurance (SMA) on programs and projects, NASA has established a review process that places greater emphasis on communicating risk to senior decision-making officials. One of the first applications of this Safety and Mission Assurance Readiness Review (SMARR) was the Space Shuttle's return-to-flight in July of 2005. The SMARR is chaired by NASA's Chief Safety and Mission Assurance Officer, and is held to independently assess the readiness to proceed with high-risk program or project activities. All risks are summarized using a risk matrix, identifying both the undesired consequence associated with a particular scenario and the likelihood of the scenario's occurrence. Presenters describe causes and effects, mitigations, and open work associated with each risk scenario, and provide an overall recommendation whether to accept the risk or pursue additional mitigations. This paper examines some of the methods NASA programs and projects currently use to communicate risks to safety and mission success. Referencing best practices, NASA documentation, and government standards, it provides a short critique of each of these methods. Finally, the paper provides recommendations for creating risk matrices for safety and mission success, and advocates a greater degree of standardization in reporting, tracking, and communicating these risks across the Agency. C1 NASA Headquarters, Washington, DC USA. RP Sirota, LB (reprint author), NASA Headquarters, Washington, DC USA. NR 5 TC 0 Z9 0 U1 1 U2 1 PU ESA PUBLICATIONS DIVISION C/O ESTEC PI 2200 AG NOORDWIJK PA PO BOX 299, 2200 AG NOORDWIJK, NETHERLANDS SN 0379-6566 BN 92-9092-910-3 J9 ESA SP PUBL PY 2005 VL 599 BP 613 EP 618 PG 6 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BEG36 UT WOS:000237218500089 ER PT B AU Wallcraft, AJ Hurlburt, HE Townsend, TL Chassignet, EP AF Wallcraft, AJ Hurlburt, HE Townsend, TL Chassignet, EP GP IEEE Comp Soc TI 1/25 degrees Atlantic ocean simulation using HYCOM SO Proceedings of the HPCMP, Users Group Conference 2005 LA English DT Proceedings Paper CT Annual Conference on High Performance Computing Modernization Program CY JUN 27, 2005-JUN 30, 2006 CL Nashville, TN SP DoD Sci & Technol Comm, User Advocacy Grp, HPCMPO Outreach Team, US Dept Defense, UGC ID 1/64-DEGREES RESOLUTION; CURRENT SYSTEM; MODELS; 1/8-DEGREES; DYNAMICS; IMPACT C1 USN, Res Lab, SSC, Stennis Space Ctr, MS 39529 USA. RP Wallcraft, AJ (reprint author), USN, Res Lab, SSC, Stennis Space Ctr, MS 39529 USA. NR 13 TC 0 Z9 0 U1 1 U2 1 PU IEEE COMPUTER SOC PI LOS ALAMITOS PA 10662 LOS VAQUEROS CIRCLE, PO BOX 3014, LOS ALAMITOS, CA 90720-1264 USA BN 0-7695-2496-6 PY 2005 BP 222 EP 225 PG 4 WC Computer Science, Interdisciplinary Applications; Multidisciplinary Sciences SC Computer Science; Science & Technology - Other Topics GA BEA11 UT WOS:000236397600033 ER PT B AU Wallcraft, AJ Metzger, EJ Hurlburt, HE Chassignet, EP Garraffo, ZD Smedstad, OM AF Wallcraft, AJ Metzger, EJ Hurlburt, HE Chassignet, EP Garraffo, ZD Smedstad, OM GP IEEE Comp Soc TI Global ocean prediction using HYCOM SO Proceedings of the HPCMP, Users Group Conference 2005 LA English DT Proceedings Paper CT Annual Conference on High Performance Computing Modernization Program CY JUN 27, 2005-JUN 30, 2006 CL Nashville, TN SP DoD Sci & Technol Comm, User Advocacy Grp, HPCMPO Outreach Team, US Dept Defense, UGC C1 USN, Res Lab, SSC, Stennis Space Ctr, MS 39529 USA. RP Wallcraft, AJ (reprint author), USN, Res Lab, SSC, Stennis Space Ctr, MS 39529 USA. NR 6 TC 0 Z9 0 U1 0 U2 0 PU IEEE COMPUTER SOC PI LOS ALAMITOS PA 10662 LOS VAQUEROS CIRCLE, PO BOX 3014, LOS ALAMITOS, CA 90720-1264 USA BN 0-7695-2496-6 PY 2005 BP 231 EP 233 PG 3 WC Computer Science, Interdisciplinary Applications; Multidisciplinary Sciences SC Computer Science; Science & Technology - Other Topics GA BEA11 UT WOS:000236397600035 ER PT J AU Queipo, NV Haftka, RT Shyy, W Goel, T Vaidyanathan, R Tucker, PK AF Queipo, NV Haftka, RT Shyy, W Goel, T Vaidyanathan, R Tucker, PK TI Surrogate-based analysis and optimization SO PROGRESS IN AEROSPACE SCIENCES LA English DT Review ID EFFICIENT GLOBAL OPTIMIZATION; MODELING-BASED OPTIMIZATION; SENSITIVITY ANALYSIS; COMPUTER EXPERIMENTS; DESIGN OPTIMIZATION; LATIN HYPERCUBES; CONFIDENCE-INTERVALS; SHAPE OPTIMIZATION; CROSS-VALIDATION; INVERSE PROBLEMS AB A major challenge to the successful full-scale development of modern aerospace systems is to address competing objectives such as improved performance, reduced costs, and enhanced safety. Accurate, high-fidelity models are typically time consuming and computationally expensive. Furthermore, informed decisions should be made with an understanding of the impact (global sensitivity) of the design variables on the different objectives. In this context, the so-called surrogate-based approach for analysis and optimization can play a very valuable role. The surrogates are constructed using data drawn from high-fidelity models, and provide fast approximations of the objectives and constraints at new design points, thereby making sensitivity and optimization studies feasible. This paper provides a comprehensive discussion of the fundamental issues that arise in surrogate-based analysis and optimization (SBAO), highlighting concepts, methods, techniques, as well as practical implications. The issues addressed include the selection of the loss function and regularization criteria for constructing the surrogates, design of experiments, surrogate selection and construction, sensitivity analysis, convergence, and optimization. The multi-objective optimal design of a liquid rocket injector is presented to highlight the state of the art and to help guide future efforts. (c) 2005 Elsevier Ltd. All rights reserved. C1 Univ Florida, Dept Mech & Aerosp Engn, Gainesville, FL 32611 USA. NASA, George C Marshall Space Flight Ctr, Huntsville, AL 35812 USA. RP Shyy, W (reprint author), Univ Michigan, Dept Aerosp Engn, Ann Arbor, MI 48109 USA. EM weishyy@umich.edu RI UF, MDO/G-8720-2012; OI Shyy, Wei/0000-0001-6670-5394 NR 106 TC 690 Z9 728 U1 17 U2 131 PU PERGAMON-ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0376-0421 J9 PROG AEROSP SCI JI Prog. Aeosp. Sci. PD JAN PY 2005 VL 41 IS 1 BP 1 EP 28 DI 10.1016/j.paerosci.2005.02.001 PG 28 WC Engineering, Aerospace SC Engineering GA 926OV UT WOS:000229133400001 ER PT B AU Stoica, A Zebulum, R Keymeulen, D Guo, X AF Stoica, A Zebulum, R Keymeulen, D Guo, X BE Lishan, K Zhihua, C Xuesong, Y TI Reconfiguration of analog electronics for extreme environments: Problem or solution? SO Progress in Intelligence Computation & Applications LA English DT Proceedings Paper CT International Symposium on Intelligence Computation and Applications CY APR 04-06, 2005 CL Wuhan, PEOPLES R CHINA SP China Assoc Aerosp, Natl Nat Sci Fdn China, China Univ Geosci, China Univ Geosci Press DE self-reconfiguration; evolvable hardware; extreme environment; electronic devices AB This paper argues in favor of adaptive reconfiguration as a technique to expand the operational envelope of analog electronics for extreme environments(EE). In addition to hardening-by-process and hardening-by-design, "hardening-by-reconfigura-tion", when applicable, could be used to mitigate drifts, degradation, or damage on electronic devices (chips) in EE, by using re-configurable devices and an adaptive self-reconfiguration of their circuit topology. Conventional circuit design exploits device characteristics within a certain temperature/radiation range; when that is exceeded, the circuit function degrades. On a reconfigurable device, although component parameters change in EE, as long as devices still operate, albeit degraded, a new circuit design, suitable for new parameter values, may be mapped into the reconfigurable structure to recover the initial circuit function. Partly degraded resources are still used, while completely damaged resources are bypassed. Designs suitable for various environmental conditions can be determined prior to operation or can be determined in-situ, by adaptive reconfiguration algorithms running on built-in digital controllers. Laboratory demonstrations of this technique were performed by JPL in several independent experiments in which bulk CMOS reconfigurable devices were exposed to, and degraded by, low temperatures (similar to-196 degrees C), high temperatures (similar to 300 degrees C) or radiation (300 kRad TID), and then recovered by adaptive reconfiguration using evolutionary search algorithms. Taking this technology from Technology Readiness Level (TRL) 3 to TRL 5 is the target of a current NASA project. C1 Jet Propuls Lab, Pasadena, CA 91109 USA. RP Stoica, A (reprint author), Jet Propuls Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 7 TC 0 Z9 0 U1 0 U2 0 PU CHINA UNIV GEOSCIENCES PRESS PI WUHAN PA 388 LUMO ROAD, WUHAN, HUBEI 430074, PEOPLES R CHINA BN 7-5625-1983-8 PY 2005 BP 125 EP 132 PG 8 WC Computer Science, Artificial Intelligence; Computer Science, Theory & Methods SC Computer Science GA BCS66 UT WOS:000231083700020 ER PT J AU White, WB Cayan, DR Niiler, PP Moisan, J Lagerloef, G Bonjean, F Legler, D AF White, WB Cayan, DR Niiler, PP Moisan, J Lagerloef, G Bonjean, F Legler, D TI The seasonal cycle of diabatic heat storage in the Pacific Ocean SO PROGRESS IN OCEANOGRAPHY LA English DT Review DE seasonal cycle; Pacific Ocean; heat storage budget ID SEA-SURFACE TEMPERATURE; NORTH PACIFIC; EL-NINO; BOUNDARY-LAYER; BARRIER LAYER; GLOBAL OCEAN; WIND STRESS; FLUXES; VARIABILITY; COEFFICIENTS AB This study quantifies uncertainties in closing the seasonal cycle of diabatic heat storage (DHS) over the Pacific Ocean from 20 degrees S to 60 degrees N through the synthesis of World Ocean Circulation Experiment (WOCE) reanalysis products from 1993 to 1999. These products are DHS from Scripps Institution of Oceanography (SIO); near-surface geostrophic and Ekman currents from Earth and Space Research (ESR); and air-sea heat fluxes from Comprehensive Ocean-Atmosphere Data Set (COADS), National Centers for Environmental Prediction (NCEP), and European Center for Mid-Range Weather Forecasts (ECMWF). With these products, we compute residual heat budget components by differencing long-term monthly means from the long-term annual mean. This allows the seasonal cycle of the DHS tendency to be modeled. Everywhere latent heat flux residuals dominate sensible heat flux residuals, shortwave heat flux residuals dominate longwave heat flux residuals, and residual Ekman heat advection dominates residual geostrophic heat advection, with residual dissipation significant only in the Kuroshio-Oyashio current extension. The root-mean-square (RMS) of the differences between observed and model residual DHS tendencies (averaged over 10 degrees latitude-by-20 degrees longitude boxes) is < 20 W m(-2) in the interior ocean and < 100 W m(-2) in the Kuroshio-Oyashio current extension. This reveals that the residual DHS tendency is driven everywhere by some mix of residual latent heat flux, shortwave heat flux, and Ekman heat advection. Suppressing bias errors in residual air-sea turbulent heat fluxes and Ekman heat advection through minimization of the RMS differences reduces the latter to < 10 W m(-2) over the interior ocean and < 25 W m(-2) in the Kuroshio-Oyashio current extension. This reveals air-sea temperature and specific humidity differences from in situ surface marine weather observations to be a principal source of bias error, overestimated over most of ocean but underestimated near the Intertropical Convergence Zone. (c) 2005 Elsevier Ltd. All rights reserved. C1 Univ Calif San Diego, Scripps Inst Oceanog, La Jolla, CA 92037 USA. US Geol Survey, La Jolla, CA 92037 USA. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Earth & Space Res, Seattle, WA 98102 USA. US CLIVAR Off, Washington, DC 20024 USA. RP White, WB (reprint author), Univ Calif San Diego, Scripps Inst Oceanog, La Jolla, CA 92037 USA. EM wbwhite@ucsd.edu RI Moisan, John/B-8762-2016 OI Moisan, John/0000-0002-8078-8939 NR 61 TC 2 Z9 2 U1 0 U2 1 PU PERGAMON-ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0079-6611 J9 PROG OCEANOGR JI Prog. Oceanogr. PY 2005 VL 64 IS 1 BP 1 EP 29 DI 10.1016/j.pocean.2004.06.012 PG 29 WC Oceanography SC Oceanography GA 918JA UT WOS:000228536900001 ER PT B AU Valdez, TI Narayanan, SR AF Valdez, TI Narayanan, SR BE Murthy, M Fuller, TF VanZee, JW Gottesfeld, S TI Effect of fabrication technique on direct methanol fuel cells designed to operate at low airflow SO Proton Conducting Membrane Fuel Cells III, Proceedings SE ELECTROCHEMICAL SOCIETY SERIES LA English DT Proceedings Paper CT 3rd Symposium on Proton Conducting Membrane Fuel Cells CY OCT, 2002 CL Salt Lake City, UT SP Electrochem Soc, Ind Electrolysis & Electrochem Engn Div, Electrochem Soc, Energy Technol Div, Electrochem Soc, Phys Electrochem Div AB Various fabrication techniques for Direct Methanol Fuel Cell (DMFC) Membrane Electrode Assemblies (MEAs) have been studied. The addition of hydrophobic particles to the cathode improves the cathode water rejection characteristics and thus mitigates the effects of crossover. A DMFC with hydrophobic particles concentrated at the gas diffusion backing is capable of producing a cell power density of 70 mW/cm(2) and a cell efficiency of 29% while operating at 60 degrees C, 0.5 M methanol, 1.76 times stoichiometric airflow. The addition of hydrous RuO2 to the anode catalyst/proton exchange membrane (PEM) interface reduces the anodic overpotential and improves catalyst utilization. The anode potential of a cell with 4 mg/cm(2) loading and a hydrous RuO2 enhanced catalyst/membrane interface is 0.224 V versus NHE at 100 mA/cm(2) operating with 90 degrees C 1 M methanol which is comparable to the anode performance of an MEA with 8 mg/cm(2) anode loading. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Valdez, TI (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 12 TC 0 Z9 0 U1 0 U2 0 PU ELECTROCHEMICAL SOCIETY INC PI PENNINGTON PA 65 S MAIN ST, PENNINGTON, NJ 08534-2839 USA BN 1-56677-455-1 J9 ELEC SOC S PY 2005 VL 2002 IS 31 BP 506 EP 517 PG 12 WC Electrochemistry SC Electrochemistry GA BCF79 UT WOS:000229108600039 ER PT J AU Offenberg, JD Fixsen, DJ Mather, JC AF Offenberg, JD Fixsen, DJ Mather, JC TI Memory-efficient up-the-ramp processing with cosmic-ray rejection SO PUBLICATIONS OF THE ASTRONOMICAL SOCIETY OF THE PACIFIC LA English DT Article AB We introduce a memory-efficient method for processing up-the-ramp sampled data to reduce noise and remove cosmic-ray events. The method we describe includes initial processing in the readout electronics (onboard, in the case of a space mission) plus postprocessing downstream. This data processing approach can be used to record or downlink high-quality science data using a small fraction of the bits required to transmit the full data, potentially reducing the volume to 0.01-0.001 of its original size. The onboard component has the advantage that it "processes as you go," reducing the online memory requirements. The processing and memory requirements are modest and are within the scope of current-generation avionics systems. We discuss the requirements and the performance of the algorithm. We also demonstrate the quality of the resulting data. C1 Sci Syst & Applicat Inc, Lanham, MD 20706 USA. NASA, Astron & Solar Phys Lab, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Offenberg, JD (reprint author), Sci Syst & Applicat Inc, 10210 Greenbelt Rd,Suite 600, Lanham, MD 20706 USA. EM Joel.D.Offenberg.1@gsfc.nasa.gov NR 4 TC 2 Z9 2 U1 0 U2 1 PU UNIV CHICAGO PRESS PI CHICAGO PA 1427 E 60TH ST, CHICAGO, IL 60637-2954 USA SN 0004-6280 J9 PUBL ASTRON SOC PAC JI Publ. Astron. Soc. Pac. PD JAN PY 2005 VL 117 IS 827 BP 94 EP 103 DI 10.1086/427566 PG 10 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 888ZP UT WOS:000226413400008 ER PT S AU Gunapala, SD Bandara, SV Liu, JK Hill, CJ Rafol, SB Mumolo, JM Trinh, JT Tidrow, MZ LeVan, PD AF Gunapala, SD Bandara, SV Liu, JK Hill, CJ Rafol, SB Mumolo, JM Trinh, JT Tidrow, MZ LeVan, PD BE Razeghi, M Brown, GJ TI Megapixel QWIP focal plane array and 320x256 pixel co-located mid-wave and long-wave dual-band QWIP focal plane array SO Quantum Sensing and Nanophotonic Devices II SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Quantum Sensing and Nanophotonic Devices II CY JAN 23-27, 2005 CL San Jose, CA SP SPIE DE infrared detectors; quantum wells; QWIP; infrared imaging; focal plane arrays ID WELL INFRARED DETECTORS; NARROW-BAND; BROAD-BAND; CAMERA AB Mid-wavelength infrared (MWIR) and long-wavelength infrared (LWIR) 1024 x 1024 pixel quantum well infrared photodetector (QWIP) focal planes have been demonstrated with excellent imaging performance. The MWIR QWIP detector array has demonstrated a noise equivalent differential temperature (NE Delta T) of 17 mK at a 95K operating temperature with f/2.5 optics at 300K background and the LWIR detector array has demonstrated a NE Delta T of 13 mK at a 70K operating temperature with the same optical and background conditions as the MWIR detector array. Both MWIR and LWIR focal planes have shown background limited performance (BLIP) at 90K and 70K operating temperatures respectively, with similar optical and background conditions. In this paper, we will discuss the performance in terms of quantum efficiency, NE Delta T, uniformity, operability, and modulation transfer functions. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Gunapala, SD (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 19 TC 1 Z9 2 U1 0 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 0-8194-5706-X J9 P SOC PHOTO-OPT INS PY 2005 VL 5732 BP 295 EP 308 DI 10.1117/12.586043 PG 14 WC Instruments & Instrumentation; Optics; Spectroscopy SC Instruments & Instrumentation; Optics; Spectroscopy GA BCF41 UT WOS:000229036500029 ER PT J AU Lahoz, WA Brugge, R Jackson, DR Migliorini, S Swinbank, R Lary, D Lee, A AF Lahoz, WA Brugge, R Jackson, DR Migliorini, S Swinbank, R Lary, D Lee, A TI An observing system simulation experiment to evaluate the scientific merit of wind and ozone measurements from the future SWIFT instrument SO QUARTERLY JOURNAL OF THE ROYAL METEOROLOGICAL SOCIETY LA English DT Article DE data assimilation; satellite; OSSE; remote sensing ID RESOLUTION DOPPLER IMAGER; MODEL; SATELLITE; WAVES AB An observing system simulation experiment was performed to assess the impact and scientific merit of SWIFT stratospheric wind and ozone observations. The SWIFT instrument is being considered for launch later this decade, and is expected to provide unprecedented global information on key aspects of the stratosphere, including tropical winds, ozone fluxes and wintertime variability. It was found that SWIFT wind observations will have a significant impact on analyses in the tropical stratosphere (except the lowermost levels), and could have a significant impact in the extratropics when the SWIFT observations are available and the flow regime is changing relatively fast. Results indicate that SWIFT ozone observations will have a significant impact when the vertical gradient of ozone is relatively high. The experiments indicate that SWIFT wind observations would improve the analysis of both tropical wind and wintertime variability. The results of this study strongly indicate a beneficial impact from the proposed SWIFT instrument. C1 Univ Reading, Data Assimilat Res Ctr, Dept Meteorol, Reading RG6 6BB, Berks, England. Met Off, Exeter, Devon, England. NASA, Goddard Space Flight Ctr, Global Modeling & Assimilat Off, Greenbelt, MD 20771 USA. Singapore Univ, Singapore, Singapore. RP Lahoz, WA (reprint author), Univ Reading, Data Assimilat Res Ctr, Dept Meteorol, POB 243,Earley Gate, Reading RG6 6BB, Berks, England. EM wal@met.rdg.ac.uk RI Lary, David/A-6163-2010; Migliorini, Stefano/J-5211-2012 OI Migliorini, Stefano/0000-0002-9489-9867 NR 24 TC 31 Z9 32 U1 1 U2 9 PU ROYAL METEOROLOGICAL SOC PI READING PA 104 OXFORD ROAD, READING RG1 7LJ, BERKS, ENGLAND SN 0035-9009 J9 Q J ROY METEOR SOC JI Q. J. R. Meteorol. Soc. PD JAN PY 2005 VL 131 IS 606 BP 503 EP 523 DI 10.1256/qj.03.109 PN B PG 21 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA 910ZR UT WOS:000227971200006 ER PT J AU Emfietzoglou, D Nikjoo, H AF Emfietzoglou, D Nikjoo, H TI The effect of model approximations on single-collision distributions of low-energy electrons in liquid water SO RADIATION RESEARCH LA English DT Article ID MONTE-CARLO-SIMULATION; X-RAY-SCATTERING; INELASTIC CROSS-SECTIONS; TRACK STRUCTURE CODES; STOPPING POWER; CHARGED-PARTICLES; OPTICAL-DATA; RADIATION ENERGY; CONDENSED MATTER; BETHE SURFACE AB The development of cross sections for the inelastic interaction of low-energy electrons with condensed tissue-like media is best accomplished within the framework of the dielectric theory. In this work we investigate the degree to which various model approximations, used in the above methodology, influence electron single-collision distributions. These distributions are of major importance to Monte Carlo track structure codes, namely, the energy-loss spectrum, the inelastic inverse mean free path, and the ionization efficiency. In particular, we make quantitative assessment of the influence of (1) the optical data set, (2) the dispersion algorithm, and (3) the perturbation and exchange Born corrections. It is shown that, although the shape and position of the energy-loss spectrum remains almost fixed, its peak height may vary by up to a factor of 1.5. Discrepancies in the calculated inelastic inverse mean free path are largely within 20-30% above 100 eV; they increase drastically, though, at lower energies. Exchange and perturbation Born corrections increase gradually below 1 keV leading to a similar to30 to 40% reduction of the inverse mean free path at 100 eV. The perturbation effect contributes more than the exchange effect to this reduction. Similar to the dispersion situation, the effect of Born corrections at lower energies is also unclear since the models examined disagree strongly below 100 eV. In comparison, the vapor data are higher than the liquid calculations by 20 to 50% as the energy decreases from 1 to 0.1 keV, respectively. The excitation contribution is the main cause of this difference, since the ionization efficiency in the liquid levels off at similar to90%, whereas the plateau value for the vapor is similar to70%. It is concluded that electron inelastic distributions for liquid water, although in some respects distinctively different from the vapor phase, have associated uncertainties that are comparable in magnitude to the phase differences. The situation below 100 eV is uncertain. (C) 2005 by Radiation Research Society. C1 Univ Ioannina, Sch Med, Med Phys Lab, GR-45110 Ioannina, Greece. Univ Nottingham, Sch Pharm, Nottingham NG7 2RD, England. RP Nikjoo, H (reprint author), NASA, Lyndon B Johnson Space Ctr, USRA, NASA Rd 1,Mail Code SK,Bldg 37, Houston, TX 77058 USA. EM hooshang.nikjoo@jsc.nasa.gov RI Emfietzoglou, Dimitris/G-7168-2012 NR 64 TC 83 Z9 83 U1 0 U2 7 PU RADIATION RESEARCH SOC PI LAWRENCE PA 810 E TENTH STREET, LAWRENCE, KS 66044 USA SN 0033-7587 J9 RADIAT RES JI Radiat. Res. PD JAN PY 2005 VL 163 IS 1 BP 98 EP 111 DI 10.1667/RR3281 PG 14 WC Biology; Biophysics; Radiology, Nuclear Medicine & Medical Imaging SC Life Sciences & Biomedicine - Other Topics; Biophysics; Radiology, Nuclear Medicine & Medical Imaging GA 882QV UT WOS:000225954300011 PM 15606313 ER PT S AU Squire, JP AF Squire, JP CA VASIMR Team BE Wukitch, SJ Bonoli, PT TI Acceleration of dense flowing plasmas using ICRF power in the VASIMR experiment SO Radio Frequency Power in Plasmas SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 16th Topical Conference on Radio Frequency Power in Plasmas CY APR 11-13, 2005 CL Park City, UT SP Amer Phys Soc DE ICRF; single pass; magnetic beach; helicon; plasma propulsion; experiment ID HELICON PLASMA AB ICRF power in the Variable Specific Impulse Magnetoplasma Rocket (VASIMR) concept energizes ions (> 100 eV) in a diverging magnetic field to accelerate a dense (similar to 10(19) m(-3)) flowing plasma to velocities useful for space propulsion (similar to 100 km/s), Theory predicts that an ICRF slow wave launched from the high field side of the resonance will propagate in the magnetic beach to absorb nearly all of the power at the resonance, thus efficiently converting the RF power to ion kinetic energy. The plasma flows through the resonance only once, so the ions are accelerated in a single pass. This process has proven efficient (similar to 70%) with an ICRF power level of 1.5 kW at about 3.6 MHz in the VASIMR experiment, VX-30, using deuterium plasma created by a helicon operating in flowing mode. We have measured ICRF plasma loading up to 2 ohms, consistent with computational predictions made using Oak Ridge National Laboratory's EMIR code. Recent helicon power upgrades (20 kW at 13.56 MHz) have enabled a 5 cm diameter target plasma for ICRF with an ion flux of over 3x10 (20) s(-1) and a high degree of ionization. This paper summarizes our ICRF results and presents the latest helicon developments in VX-30. C1 Muniz Engn Inc, NASA, Lyndon B Johnson Space Ctr, Adv Space Propuls Lab, Houston, TX 77058 USA. RP Squire, JP (reprint author), Muniz Engn Inc, NASA, Lyndon B Johnson Space Ctr, Adv Space Propuls Lab, Houston, TX 77058 USA. 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 0-7354-0276-0 J9 AIP CONF PROC PY 2005 VL 787 BP 421 EP 428 PG 8 WC Physics, Fluids & Plasmas SC Physics GA BDC31 UT WOS:000232634700083 ER PT J AU Domack, MS Baughman, JM AF Domack, MS Baughman, JM TI Development of nickel-titanium graded composition components SO RAPID PROTOTYPING JOURNAL LA English DT Article; Proceedings Paper CT 15th Annual Solid Freeform Fabrication Symposium CY AUG, 2004 CL Austin, TX DE coating processes; composite materials; metals AB Purpose - Three layer-additive manufacturing methods were evaluated to producing nickel-titanium graded composition material. One potential application is fabrication of attachment clips that join thermal protection systems to launch vehicle structure. Thermal gradients during flight generate excessive bending and shear loads that limit the service lifetime of the Inconel clips currently used. It is envisioned that a graded composition component could be tailored to reduce the stress concentrations. Design/methodology/approach - Deposits with nearly continuous composition grade were built from Ti-6-4 and Inconel 718 powder using laser direct metal deposition. Layered deposits were produced by flat wire welding from Ti-6-4 and Inconel 718 wire. Ultrasonic consolidation was used to produce layered deposits from pure nickel and commercially pure titanium foils. Microstructure, bond line morphology, chemical composition, and reaction phases were characterized. Findings - All three manufacturing methods require further development before graded composition material can be reliably produced. Laser direct metal deposition samples exhibited coarse dendritic microstructures and significant elemental segregation. Chemistries varied from calculated targets by up to 20 percent and macroscopic cracking occurred for chemistries greater than 60 percent Inconel 718. Flat wire welded deposits exhibited good mixing between the wire layers, however brittle cracking occurred adjacent to a 5 mum thick reaction layer. Ultrasonically-consolidated samples demonstrated metallurgical bonding between pure Ni and commercially pure (CP) Ti foils, with material reaction limited to a 1 mum layer. Originality/value - Producing nickel-titanium graded composition materials had not been attempted by the selected manufacturing methods. A refined experimental program is needed to resolve the remaining technical issues. C1 NASA, Langley Res Ctr, Hampton, VA 23665 USA. Lockheed Martin Space Operat, Hampton, VA USA. RP Domack, MS (reprint author), NASA, Langley Res Ctr, Hampton, VA 23665 USA. NR 5 TC 38 Z9 48 U1 7 U2 31 PU EMERALD GROUP PUBLISHING LIMITED PI BRADFORD PA 60/62 TOLLER LANE, BRADFORD BD8 9BY, W YORKSHIRE, ENGLAND SN 1355-2546 J9 RAPID PROTOTYPING J JI Rapid Prototyping J. PY 2005 VL 11 IS 1 SI SI BP 41 EP 51 DI 10.1108/13552540510573383 PG 11 WC Engineering, Mechanical; Materials Science, Multidisciplinary SC Engineering; Materials Science GA 899GN UT WOS:000227133000007 ER PT S AU Moss, JN Bird, GA Markelov, GN AF Moss, JN Bird, GA Markelov, GN BE Capitelli, M TI DSMC Simulations of hypersonic flows and comparison with experiments SO RAREFIED GAS DYNAMICS SE AIP Conference Proceedings LA English DT Proceedings Paper CT 24th International Symposium on Rarefied Gas Dynamics (RGD24) CY JUL 10-16, 2004 CL Monopoli, ITALY SP Inst Metodol Inorgan Plasmi, Univ Bari & Dept Chem, USAF UK, European Off Aerosp Res & Dev, European Space Agcy, ESTEC, Grp Nazl Fis Matemat, ALTA-CENTROSPAZIO, Assessorato Turismo-Reg Puglia, Comune Alberobello, COMPULAB-Rivenditore Autozzato Apple, Fond Cassa Risparm Pugl AB This paper presents computational results obtained with the direct simulation Monte Carlo (DSMC) method for several biconic test cases in which shock interactions and flow separation-reattachment are key features of the flow. Recent ground-based experiments have been performed for several biconic configurations, and surface heating rate and pressure measurements have been proposed for code validation studies. The present focus is to expand on the current validating activities for a relatively new DSMC code called DS2V that Bird (second author) has developed. Comparisons with experiments and other computations help clarify the agreement currently being achieved between computations and experiments and to identify the range of measurement variability of the proposed validation data when benchmarked with respect to the current computations. For the test cases with significant vibrational nonequilibrium, the effect of the vibrational energy surface accommodation on heating and other quantities is demonstrated. C1 NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Moss, JN (reprint author), NASA, Langley Res Ctr, MS 408A, Hampton, VA 23681 USA. NR 16 TC 1 Z9 1 U1 0 U2 3 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 0-7354-0247-7 J9 AIP CONF PROC PY 2005 VL 762 BP 547 EP 552 PG 6 WC Physics, Fluids & Plasmas SC Physics GA BCQ51 UT WOS:000230775600087 ER PT B AU Mobasser, S Liebe, CC Naegle, J Lee, C AF Mobasser, S Liebe, CC Naegle, J Lee, C BE Kurnaz, S Ince, F Inbasioglu, S Basturk, S TI Flight qualified micro sun sensor for Mars applications SO RAST 2005: Proceedings of the 2nd International Conference on Recent Advances in Space Technologies LA English DT Proceedings Paper CT 2nd International Conference on Recent Advances in Space Technologies CY JUN 09-11, 2005 CL Istanbul, TURKEY SP IEEE, AIAA, isprs, Turkish AF Acad, Istanbul Tech Univ, Bogazici Univ, Marmara Univ AB A flight qualified micro sun sensor is being developed and flight qualified for future Mars missions. The micro sun sensor, which is basically a small pinhole camera, consists of a small mask with pinholes, placed on top of an image detector. Images of the sun are formed on the image detector when the sun illuminates the mask. Image processing is performed in the sun sensor that outputs sun centroids. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Mobasser, S (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,MS 198-235, Pasadena, CA 91109 USA. NR 7 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 0-7803-8977-8 PY 2005 BP 234 EP 239 PG 6 WC Engineering, Aerospace; Remote Sensing SC Engineering; Remote Sensing GA BDF26 UT WOS:000233198100045 ER PT B AU Fijany, A Vatan, F AF Fijany, A Vatan, F BE Kurnaz, S Ince, F Inbasioglu, S Basturk, S TI New approach for efficient diagnosis of large and complex space systems SO RAST 2005: Proceedings of the 2nd International Conference on Recent Advances in Space Technologies LA English DT Proceedings Paper CT 2nd International Conference on Recent Advances in Space Technologies CY JUN 09-11, 2005 CL Istanbul, TURKEY SP IEEE, AIAA, isprs, Turkish AF Acad, Istanbul Tech Univ, Bogazici Univ, Marmara Univ AB We present a novel algorithmic approach and a new algorithm for solving the diagnosis problem. We report the results of the performance of the new algorithm and compare them with the traditional and standard algorithms. These results show the strong performance of our new algorithm with more than an order of magnitude improvement over the traditional approach. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Fijany, A (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 BN 0-7803-8977-8 PY 2005 BP 271 EP 276 PG 6 WC Engineering, Aerospace; Remote Sensing SC Engineering; Remote Sensing GA BDF26 UT WOS:000233198100052 ER PT S AU Young, LA Pisanich, G Ippolito, C Alena, R AF Young, LA Pisanich, G Ippolito, C Alena, R BE Kehtarnavaz, N Laplante, PA TI Aerial vehicle surveys of other planetary atmospheres and surfaces: imaging, remote-sensing, and autonomy technology requirements SO Real-Time Imaging IX SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Real-Time Imaging IX CY JAN 18-20, 2005 CL San Jose, CA SP Soc Imaging Sci & Technol, SPIE DE aerial imaging; surveys; planetary aerial vehicles; aerial explorers; UAV; simulation AB The objective of this paper is to review the anticipated imaging and remote-sensing technology requirements for aerial vehicle survey missions to other planetary bodies in our Solar system that can support in-atmosphere flight. In the not too distant future such planetary aerial vehicle (a.k.a. aerial explorers) exploration missions will become feasible. Imaging and remote-sensing observations will be a key objective for these missions. Accordingly, it is imperative that optimal solutions in terms of imaging acquisition and real-time autonomous analysis of image data sets be developed for such vehicles. C1 NASA, Rotorcraft Div, Moffett Field, CA 94035 USA. RP Young, LA (reprint author), NASA, Rotorcraft Div, MS 243-12, Moffett Field, CA 94035 USA. 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 0-8194-5644-6 J9 P SOC PHOTO-OPT INS PY 2005 VL 5671 BP 183 EP 199 DI 10.1117/12.595353 PG 17 WC Imaging Science & Photographic Technology SC Imaging Science & Photographic Technology GA BCC95 UT WOS:000228668200020 ER PT S AU Springer, PL AF Springer, PL BE DiMartino, B Kranzlmuller, D Dongarra, J TI Enhancements to PVM's BEOLIN architecture SO RECENT ADVANCES IN PARALLEL VIRTUAL MACHINE AND MESSAGE PASSING INTERFACE, PROCEEDINGS SE LECTURE NOTES IN COMPUTER SCIENCE LA English DT Article; Proceedings Paper CT 12th European Parallel-Virtual-Machine-and-Message-Passing-Interface-Users-Group Meeting (PVM/MPI) CY SEP 18-21, 2005 CL Sorrento, ITALY SP Parallel Virtual Machine & Message Passing Interface Users Grp, Second Univ Naples, Dipartimento Ingegneria Informaz, HP, IBM, Intel, Microsoft, Myricom, Quadrics, NEC, Centro Competenza ICT, Reg Campania AB Version 3.4.3 of PVM had previously been enhanced by the addition of a new architecture, BEOLIN, which allowed a PVM user to abstract a Beowulf class computer with a private network to appear as a single system, visible to the outside world, which could spawn tasks on different internal nodes. This new enhancement to PVM handles the case where each node on the Beowulf system may be composed of multiple processors. In this case, the software will, at the user's request, spawn multiple jobs to each node, to be run on the individual processors. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Springer, PL (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 1 TC 1 Z9 1 U1 0 U2 0 PU SPRINGER-VERLAG BERLIN PI BERLIN PA HEIDELBERGER PLATZ 3, D-14197 BERLIN, GERMANY SN 0302-9743 BN 3-540-29009-5 J9 LECT NOTES COMPUT SC PY 2005 VL 3666 BP 250 EP 257 PG 8 WC Computer Science, Theory & Methods SC Computer Science GA BDF44 UT WOS:000233236700034 ER PT S AU Bar-Cohen, Y AF Bar-Cohen, Y BE Tanner, DM Ramesham, R TI Biologically inspired technologies using artificial muscles SO RELIABILITY, PACKAGING, TESTING, AND CHARACTERIZATION OF MEMS/MOEMS IV SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Reliability, Packaging, Testing, and Characterization of MEMS/MOEMS IV CY JAN 24-25, 2005 CL San Jose, CA SP SPIE DE biomimetics; biologically inspired technologies; EAP; clectroactive polymers; artificial muscles AB After billions of years of evolution, nature developed inventions that work, which are appropriate for the intended tasks and that last. The evolution of nature led to the introduction of highly effective and power efficient biological mechanisms that are scalable from micron to many meters in size. Imitating these mechanisms offers enormous potentials for the improvement of our life and the tools we use. Humans have always made efforts to imitate nature and we are increasingly reaching levels of advancement where it becomes significantly easier to imitate, copy, and adapt biological methods, processes and systems. Some of the biomimetic technologies that have emerged include artificial muscles, artificial intelligence, and artificial vision to which significant advances in materials science, mechanics, electronics, and computer science have contributed greatly. One of the newest fields of biomimetics is the electroactive polymers (EAP) that are also known as artificial muscles. To take advantage of these materials, efforts are made worldwide to establish a strong infrastructure addressing the need for comprehensive analytical modeling of their operation mechanism and develop effective processing and characterization techniques. The field is still in its emerging state and robust materials are not readily available however in recent years significant progress has been made and commercial products have already started to appear. This paper covers the state-of-the-art and challenges to making artificial muscles and their potential biomimetic applications. C1 CALTECH, Jet Prop Lab, Pasadena, CA 90740 USA. RP CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,MS 125-224, Pasadena, CA 90740 USA. EM yosi@jpl.nasa.gov NR 11 TC 0 Z9 0 U1 0 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 0-8194-5690-X J9 PROC SPIE PY 2005 VL 5716 BP XXXVII EP XLIII DI 10.1117/12.609696 PG 7 WC Engineering, Electrical & Electronic; Engineering, Mechanical; Instruments & Instrumentation; Materials Science, Characterization & Testing; Optics SC Engineering; Instruments & Instrumentation; Materials Science; Optics GA BCE35 UT WOS:000228835200003 ER PT S AU Cantrell, JH AF Cantrell, JH BE Thompson, DO Chimenti, DE TI Acoustic nonlinearity in polycrystalline nickel from fatigue-generated microstructures SO Review of Progress in Quantitative Nondestructive Evaluation, Vols 24A and 24B SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 31st Annual Review of Progress in Quantitative Nondestructive Evaluation CY JUL 25-30, 2004 CL Colorado Sch Mines, Golden, CO HO Colorado Sch Mines ID HARMONIC-GENERATION AB An analytical model of the nonlinear interaction of ultrasonic waves with dislocation substructures formed during the fatigue of wavy slip metals is presented. The model is applied to the calculation of the acoustic nonlinearity parameters beta of polycrystalline nickel for increasingly higher levels of fatigue from the virgin state. The values calculated for stress-controlled loading at 345 MPa predict a monotonic increase in beta of more than 390 percent as a function of percent life to fracture due to substructural evolution. C1 NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Cantrell, JH (reprint author), NASA, Langley Res Ctr, Mail Stop 231, Hampton, VA 23681 USA. NR 11 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 0-7354-0245-0 J9 AIP CONF PROC PY 2005 VL 760 BP 337 EP 344 PG 8 WC Acoustics; Engineering, Electrical & Electronic; Materials Science, Multidisciplinary; Materials Science, Characterization & Testing; Optics SC Acoustics; Engineering; Materials Science; Optics GA BCE68 UT WOS:000228893300042 ER PT S AU Yost, WT AF Yost, WT BE Thompson, DO Chimenti, DE TI Use of capacitive detection to measure harmonic generation and the nonlinearity parameter in liquids SO Review of Progress in Quantitative Nondestructive Evaluation, Vols 24A and 24B SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 31st Annual Review of Progress in Quantitative Nondestructive Evaluation CY JUL 25-30, 2004 CL Colorado Sch Mines, Golden, CO HO Colorado Sch Mines ID SOLIDS AB Capacitive detectors have been employed for some time for absolute measurement of compressional wave particle displacement amplitudes in solids. The solid's surface has been used as one of the capacitor's plates, and a conductor riding within a few microns above the surface as the other plate. In the arrangement discussed here a conductive membrane is placed in contact with the liquid and the other electrode is placed a few microns above the membrane. Using this device the particle displacement amplitude in the picometer range of fundamental and harmonic waves in water were successfully measured. Measurements of fundamental and harmonic waves are presented and analyzed. Membrane effects and corrections related to liquid measurements are presented. The nonlinearity parameter for water is calculated, presented, and discussed. C1 NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Yost, WT (reprint author), NASA, Langley Res Ctr, MS 231, Hampton, VA 23681 USA. 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 0-7354-0245-0 J9 AIP CONF PROC PY 2005 VL 760 BP 345 EP 352 PG 8 WC Acoustics; Engineering, Electrical & Electronic; Materials Science, Multidisciplinary; Materials Science, Characterization & Testing; Optics SC Acoustics; Engineering; Materials Science; Optics GA BCE68 UT WOS:000228893300043 ER PT S AU Johnston, PH AF Johnston, PH BE Thompson, DO Chimenti, DE TI Measurement of angle-dependent ultrasonic backscatter from textile composites SO Review of Progress in Quantitative Nondestructive Evaluation, Vols 24A and 24B SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 31st Annual Review of Progress in Quantitative Nondestructive Evaluation CY JUL 25-30, 2004 CL Colorado Sch Mines, Golden, CO HO Colorado Sch Mines AB Textile fiber architecture composite materials present new measurement challenges for ultrasonic NDE. The large degree of spatial variability of the highly anisotropic fiber violates assumptions underlying a one-dimensional interpretation of ultrasonic interrogations. In this work, a long linear array is used to measure the spatial variation of scattered ultrasound arising from the fiber architecture in unidirectional and three-dimensional braided composite panels. The angular scattering signature can potentially be used as the basis for improved and more complete ultrasonic characterization of these types of composite materials. C1 NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Johnston, PH (reprint author), NASA, Langley Res Ctr, Hampton, VA 23681 USA. NR 0 TC 0 Z9 0 U1 0 U2 2 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 0-7354-0245-0 J9 AIP CONF PROC PY 2005 VL 760 BP 1073 EP 1080 PG 8 WC Acoustics; Engineering, Electrical & Electronic; Materials Science, Multidisciplinary; Materials Science, Characterization & Testing; Optics SC Acoustics; Engineering; Materials Science; Optics GA BCE68 UT WOS:000228893301003 ER PT S AU Roth, DJ Cosgriff, LM Martin, RE Burns, EA Teemer, L AF Roth, DJ Cosgriff, LM Martin, RE Burns, EA Teemer, L BE Thompson, DO Chimenti, DE TI Signal processing effects for ultrasonic guided wave scanning of composites SO Review of Progress in Quantitative Nondestructive Evaluation, Vols 24A and 24B SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 31st Annual Review of Progress in Quantitative Nondestructive Evaluation CY JUL 25-30, 2004 CL Colorado Sch Mines, Golden, CO HO Colorado Sch Mines AB The goal of this ongoing work is to optimize experimental variables for a guided wave scanning method to obtain the most revealing and accurate images of defect conditions in composite materials. This study focuses on signal processing effects involved in forming guided wave scan images. Signal processing is involved at two basic levels for deriving ultrasonic guided wave scan images. At the primary level, NASA GRC has developed algorithms to extract over 30 parameters from the multimode signal and its power spectral density. At the secondary level, there are many variables for which values must be chosen that affect actual computation of these parameters. In this study, a ceramic matrix composite sample having a delamination is characterized using the ultrasonic guided wave scan method. Energy balance and decay rate parameters of the guided wave at each scan location are calculated to form images. These images are compared with ultrasonic c-scan and thermography images. The effect of the time portion of the waveform processed on image quality is assessed by comparing with images formed using the total waveform acquired. C1 NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Roth, DJ (reprint author), NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. NR 7 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 0-7354-0245-0 J9 AIP CONF PROC PY 2005 VL 760 BP 1087 EP 1093 PG 7 WC Acoustics; Engineering, Electrical & Electronic; Materials Science, Multidisciplinary; Materials Science, Characterization & Testing; Optics SC Acoustics; Engineering; Materials Science; Optics GA BCE68 UT WOS:000228893301005 ER PT S AU Madaras, EI Prosser, WH Gorman, MR AF Madaras, EI Prosser, WH Gorman, MR BE Thompson, DO Chimenti, DE TI Detection of impact damage on Space Shuttle structures using acoustic emission SO Review of Progress in Quantitative Nondestructive Evaluation, Vols 24A and 24B SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 31st Annual Review of Progress in Quantitative Nondestructive Evaluation CY JUL 25-30, 2004 CL Colorado Sch Mines, Golden, CO HO Colorado Sch Mines AB Studies of the acoustic signals originating from impact damage on Space Shuttle components were undertaken. Sprayed on foam insulation and small aluminum spheres were used as impactors. Shuttle reinforced carbon-carbon panels, panels with Shuttle thermal protection tiles, and Shuttle main landing gear doors with tiles were targets. Ballistic speed and hypervelocity impacts over a wide range of impactor sizes, energies, and angles were tested. Additional tests were conducted to correlate the acoustic response of the test articles to actual Shuttle structures. C1 NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Madaras, EI (reprint author), NASA, Langley Res Ctr, MS 231, Hampton, VA 23681 USA. NR 5 TC 3 Z9 3 U1 0 U2 3 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 0-7354-0245-0 J9 AIP CONF PROC PY 2005 VL 760 BP 1113 EP 1120 PG 8 WC Acoustics; Engineering, Electrical & Electronic; Materials Science, Multidisciplinary; Materials Science, Characterization & Testing; Optics SC Acoustics; Engineering; Materials Science; Optics GA BCE68 UT WOS:000228893301009 ER PT S AU Matthies, L Bergh, C Castano, A Macedo, J Manduchi, R AF Matthies, L Bergh, C Castano, A Macedo, J Manduchi, R BE Dario, P Chatila, R TI Obstacle detection in foliage with ladar and radar SO Robotics Research SE SPRINGER TRACTS IN ADVANCED ROBOTICS LA English DT Proceedings Paper CT 11th International Symposium on Robotics Research CY OCT 19-22, 2003 CL Siena, ITALY AB Autonomous off-road navigation is central to several important applications of unmanned ground vehicles. This requires the ability to detect obstacles in vegetation. We examine the prospects for doing so with scanning ladar and with a linear array of 2.2 GHz micro-impulse radar transceivers. For ladar, we summarize our work to date on algorithms for detecting obstacles in tall grass with single-axis ladar, then present a simple probabilistic model of the distance into tall grass that ladar-based obstacle detection is possible. This model indicates that the ladar "penetration depth" can range from on the order of 10 cm to several meters, depending on the plant type. We also present an experimental investigation of mixed pixel phenomenology for a time-of-flight, SICK ladar and discuss briefly how this bears on the problem. For radar, we show results of applying an existing algorithm for multi-frequency diffraction tomography to a set of 45 scans taken with one sensor translating laterally 4 cm/scan to mimic a linear array of transceivers. This produces a high resolution, 2-D map of scattering surfaces in front of the array and clearly reveals a large tree trunk behind over 2.5 m of thick foliage. Both types of sensor warrant further development and exploitation for this problem. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Matthies, L (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 17 TC 2 Z9 3 U1 0 U2 0 PU SPRINGER-VERLAG BERLIN PI BERLIN PA HEIDELBERGER PLATZ 3, D-14197 BERLIN, GERMANY SN 1610-7438 BN 3-540-23214-1 J9 SPR TRA ADV ROBOT PY 2005 VL 15 BP 291 EP 300 PG 10 WC Robotics SC Robotics GA BCE49 UT WOS:000228862600025 ER PT S AU Tavernier, G Fagard, H Feissel-Vernier, M Lemoine, F Noll, C Ries, J Soudarin, L Willis, P AF Tavernier, G Fagard, H Feissel-Vernier, M Lemoine, F Noll, C Ries, J Soudarin, L Willis, P BE Moore, P TI The International DORIS Service SO SATELLITE DYNAMICS IN THE ERA OF INTERDISCIPLINARY SPACE GEODESY SE ADVANCES IN SPACE RESEARCH-SERIES LA English DT Article; Proceedings Paper CT 35th COSPAR Scientific Assembly CY JUL 18-25, 2004 CL Paris, FRANCE SP Comm Space Res DE satellite geodesy; precise orbit determination; DORIS; International DORIS Service; Global Geodetic Observing System ID TERRESTRIAL REFERENCE FRAME; GEODETIC OBSERVING SYSTEM; SURFACE LOADING DATA; ORBIT DETERMINATION; GPS; JASON-1; EARTHQUAKE; MISSION; MOTION; SLR AB The DORIS system was initially developed for precise orbit determination and precise positioning on the Earth. In continuation of the DORIS Pilot Experiment initiated in 1999, the International DORIS Service (IDS) officially started on July 1, 2003 as an IAG Service after an official acceptance from the IAG Executive Committee at the IUGG General Assembly in Sapporo, Japan. Following this decision, the IERS Directing board accepted the DORIS Service as a new IERS external service. Six satellites carrying DORIS receivers are currently in orbit, permanently observed by 56 well-distributed tracking stations. Among these, three satellites (Jason-1, ENVISAT and SPOT5) are equipped with the new generation of DORIS receivers and were launched between December 2001 and May 2002. The DORIS receivers on these three spacecraft include a navigation function, called DIODE. The permanent tracking network has been constantly improved and specific campaigns of observations have been conducted in Wettzell, Gads and in Antarctica. Recent DORIS performances for precise positioning were improved by this large increase in the satellite constellation, leading to almost I cm precision for weekly station coordinates. Significant improvements were also obtained in Polar Motion estimations, leading to 1.0-1.5 mas daily results. In 2003 and 2004, several steps were taken to improve the operations of the IDS, as well as its international cooperation, by organizing several specific analysis campaigns. The International DORIS Service has now started its scientific activity on a routine basis for the International Earth Rotation and Reference Systems Service (IERS) and the Global Geodetic Observing System (GGOS). (c) 2005 COSPAR. Published by Elsevier Ltd. All rights reserved. C1 Ctr Natl Etud Spatiales, F-31055 Toulouse, France. Inst Geog Natl, St Mande, France. Observ Paris, F-75014 Paris, France. Inst Geog Natl, Marne La Vallee, France. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Univ Texas, Ctr Space Res, Austin, TX 78712 USA. CLS, Ramonville St Agne, France. CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Tavernier, G (reprint author), Ctr Natl Etud Spatiales, 18 Ave Edouard Belin, F-31055 Toulouse, France. EM Gilles.Tavernier@cnes.fr RI Willis, Pascal/A-8046-2008; Noll, Carey/D-8884-2012; Lemoine, Frank/D-1215-2013 OI Willis, Pascal/0000-0002-3257-0679; NR 45 TC 34 Z9 36 U1 0 U2 0 PU ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD 0X5 1GB, OXON, ENGLAND SN 0273-1177 J9 ADV SPACE RES-SERIES PY 2005 VL 36 IS 3 SI 2005 BP 333 EP 341 DI 10.1016/j.asr.2005.03.102 PG 9 WC Engineering, Aerospace; Astronomy & Astrophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Engineering; Astronomy & Astrophysics; Geology; Meteorology & Atmospheric Sciences GA BDT66 UT WOS:000235247800003 ER PT S AU Morel, L Willis, P AF Morel, L Willis, P BE Moore, P TI Terrestrial reference frame effects on global sea level rise determination from TOPEX/Poseidon altimetric data SO SATELLITE DYNAMICS IN THE ERA OF INTERDISCIPLINARY SPACE GEODESY SE ADVANCES IN SPACE RESEARCH-SERIES LA English DT Article; Proceedings Paper CT 35th COSPAR Scientific Assembly CY JUL 18-25, 2004 CL Paris, FRANCE SP Comm Space Res DE satellite geodesy; terrestrial reference frame; DORIS; TOPEX/Poseidon; satellite altimetry; mean sea level; error budget ID PRECISION ORBIT DETERMINATION; DORIS; JASON-1; GPS; SATELLITE; SYSTEM; CHALLENGE; TRACKING; MOTIONS; SLR AB Over the past years, satellite altimetry has produced several significant improvements in our scientific understanding of the oceans. However, several results related to global or regional sea level changes still too often rely on the assumption that orbit errors coming from station coordinates adoption can be neglected in the total error budget. The goal of this paper is to specifically study this general assumption and to assess its limitation. In a first step, in the case of the TOPEX/Poseidon satellite, we first characterized orbital errors coming from the adoption of a specific Terrestrial Reference Frame using a Monte-Carlo-based simulation method using DORIS data. In a second step, we analyzed the effect of these systematic orbital errors on the mean sea level derived from altimeter data. From these results, we derived linear transfer functions that can be used for several purposes like error budget estimation in altimetry or local tie specifications for the implementation of new tracking stations. These simulations show that the main source of errors comes from current imprecision in the Z-axis realization of the frame. A 10 mm error in the TZ realization can create a -1.2 mm of systematic errors in the derived mean sea level due to the North-South asymmetric distribution of the oceans all over the world. Significant sea level rise could erroneously be attributed to a possible warming of the biosphere while they just come from systematic errors in the Terrestrial Reference Frame used to generate the satellite operational orbits. Finally, we assessed the accuracy of present Terrestrial Reference Frame realizations and derived a realistic error budget for this specific source of error. For the ITRF97 realization, a current precision of 3.0 mm in sea level and 0.37 mm/yr in sea level rise was obtained. These precisions should gradually improve with future Terrestrial Reference Frame realizations. (c) 2005 COSPAR. Published by Elsevier Ltd. All rights reserved. C1 Inst Geog Natl, Direct Tech, F-94160 St Mande, France. Ecole Super Geometres Topographes, F-72000 Le Mans, France. CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Willis, P (reprint author), Inst Geog Natl, Direct Tech, 2 Ave Pasteur,BP 68, F-94160 St Mande, France. EM laurent.morel@esgt.cnam.fr; willis@jpl.nasa.gov RI Willis, Pascal/A-8046-2008; Morel, Laurent/C-1211-2008 OI Willis, Pascal/0000-0002-3257-0679; NR 45 TC 47 Z9 48 U1 1 U2 2 PU ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD 0X5 1GB, OXON, ENGLAND SN 0273-1177 J9 ADV SPACE RES-SERIES PY 2005 VL 36 IS 3 SI 2005 BP 358 EP 368 DI 10.1016/j.asr.2005.05.113 PG 11 WC Engineering, Aerospace; Astronomy & Astrophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Engineering; Astronomy & Astrophysics; Geology; Meteorology & Atmospheric Sciences GA BDT66 UT WOS:000235247800006 ER PT S AU Willis, P Desai, SD Bertiger, WI Haines, BJ Auriol, A AF Willis, P Desai, SD Bertiger, WI Haines, BJ Auriol, A BE Moore, P TI DORIS satellite antenna maps derived from long-term residuals time series SO SATELLITE DYNAMICS IN THE ERA OF INTERDISCIPLINARY SPACE GEODESY SE ADVANCES IN SPACE RESEARCH-SERIES LA English DT Article; Proceedings Paper CT 35th COSPAR Scientific Assembly CY JUL 18-25, 2004 CL Paris, FRANCE SP Comm Space Res DE geodesy; DORIS; antenna phase center variations; PCV; precise orbit determination ID TERRESTRIAL REFERENCE FRAME; ORBIT DETERMINATION; TOPEX POSEIDON; GPS; TOPEX/POSEIDON; SYSTEM; PHASE AB Recent studies have shown that phase pattern models for the Jason-1 GPS antenna significantly benefit GPS-based precise orbit determination (POD) for the satellite. We have used a similar technique to derive DORIS receiver antenna maps, using all available DORIS tracking data over long time periods (from 1993.0 to 2004.0). We demonstrate that the derived correction models are satellite specific. For a given satellite, year-to-year estimations show clear systematic patterns. Some of these systematic patterns are attributable to the derivative of the multi-path effects in the direction of the satellite velocity. For early SPOT data, the patterns can be explained by an offset in the TAI time tagging (typically 8 mu s). In a second step, we have applied the SPOT2 antenna correction models in precise orbit determination and in the positioning of ground beacons. Preliminary results on DORIS/SPOT2 show that application of the DORIS antenna maps lead to a slight improvement of the derived POD and geodetic results (typically less than 5%). (c) 2005 COSPAR. Published by Elsevier Ltd. All rights reserved. C1 Inst Geog Natl, Direct Tech, F-94160 St Mande, France. CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. Ctr Natl Etud Spatiales, F-31401 Toulouse, France. RP Willis, P (reprint author), Inst Geog Natl, Direct Tech, 2 Ave Pasteur,BP 68, F-94160 St Mande, France. EM pascal.willis@ign.fr RI Willis, Pascal/A-8046-2008 OI Willis, Pascal/0000-0002-3257-0679 NR 33 TC 18 Z9 19 U1 0 U2 5 PU ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD 0X5 1GB, OXON, ENGLAND SN 0273-1177 J9 ADV SPACE RES-SERIES PY 2005 VL 36 IS 3 SI 2005 BP 486 EP 497 DI 10.1016/j.asr.2005.03.095 PG 12 WC Engineering, Aerospace; Astronomy & Astrophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Engineering; Astronomy & Astrophysics; Geology; Meteorology & Atmospheric Sciences GA BDT66 UT WOS:000235247800022 ER PT S AU Willis, P Deleflie, F Barlier, F Bar-Sever, YE Romans, LJ AF Willis, P Deleflie, F Barlier, F Bar-Sever, YE Romans, LJ BE Moore, P TI Effects of thermosphere total density perturbations on LEO orbits during severe geomagnetic conditions (Oct-Nov 2003) using DORIS and SLR data SO SATELLITE DYNAMICS IN THE ERA OF INTERDISCIPLINARY SPACE GEODESY SE ADVANCES IN SPACE RESEARCH-SERIES LA English DT Article; Proceedings Paper CT 35th COSPAR Scientific Assembly CY JUL 18-25, 2004 CL Paris, FRANCE SP Comm Space Res DE satellite geodesy; DORIS; SLR; air drag effects; thermosphere DTM models; precise orbit determination ID UPPER-ATMOSPHERE; SATELLITE DRAG; MODEL; GPS; SYSTEM; INDEXES; SERVICE; SOLAR; CYCLE AB An exceptional solar activity event occurred at the end of October 2003. On October 29th, seven groups of sunspots were visible on the Sun's surface and the geomagnetic index K, reached the extreme value of 9, leading to beautiful auroras, among other effects. Similar events also occurred in November 2003. These events have been an exceptional opportunity to estimate effects of the thermosphere total density perturbations in extreme conditions on a Low Earth Orbit (LEO orbit corresponding in this study at altitudes ranging from 800 km up to 1400 km). Specifically, we study the best way to get reliable geodetic products even during such solar events, and how well the thermosphere models (DTM-78, DTM-94, DTM-2000, and MSIS-86 models) allow us to accomplish this and to predict the observed perturbations on the orbital elements. Thus our analysis is twofold. First, we have computed orbits of satellites equipped with the on-board DORIS tracking system, at an altitude ranging from 800 to 1330 km and for periods of time including these exceptional events (October 29-31 and November 20, 2003). We have computed 30-hour arc orbits, estimating the drag coefficient parameter very frequently (every minute) using a tight random-walk constraint or using a white noise reset in the Gipsy/Oasis software. We show that significant errors are obtained for the considered thermosphere models, but can be greatly improved using a more sophisticated data processing. We also investigated how these proposed processing strategies affect the quality of the DORIS geodetic products. Significant improvements were found for weekly stations coordinates estimations as well as for polar motion determination. In addition, we have investigated the global quality of the modeling of the variations of the mean orbital elements in using thermosphere models over long periods of time including such severe geomagnetic events. This original approach is based on averaging techniques implemented in the CODIOR software. We have analyzed the continuous long-term evolution of the semi-major axis of the geodetic satellites Starlette, Stella and Ajisai tracked by the Satellite Laser Ranging (SLR) network. In this second part, we give: (i) a single global empirical coefficient per satellite, to validate the models over the whole duration of the orbital arc, including the exceptional solar activity events, and (ii) one coefficient per a period of about 2 months to quantify the seasonal differences between the models and the observations. As a result of both investigations, we compare the capability of recent models of thermosphere to allow us to get reliable geodetic products and mean orbital elements variations over short and long periods of time as well as for the recent exceptional geomagnetic events. Different altitudes are considered: around 800-900 km for the Stella and Starlette satellites tracked by laser ranging systems and SPOT tracked by DORIS; around also 1300-1400 km for the Ajisai satellite tracked by laser techniques and TOPEX and Jason also tracked by DORIS. It appears in our study that laser and DORIS data are complementary to probe the thermosphere, and to test the quality of thermosphere models in specific conditions for getting accurate geodetic products. (c) 2005 COSPAR. Published by Elsevier Ltd. All rights reserved. C1 Inst Geog Natl, Direct Tech, F-94160 St Mande, France. CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. Observ Cote Azur, Dept GEMINI, F-06130 Grasse, France. Fac Univ Notre Dame Paix, Dept Math, B-5000 Namur, Belgium. RP Willis, P (reprint author), Inst Geog Natl, Direct Tech, 2 Ave Pasteur,BP 68, F-94160 St Mande, France. EM pascal.willis@ign.fr RI Willis, Pascal/A-8046-2008 OI Willis, Pascal/0000-0002-3257-0679 NR 46 TC 41 Z9 45 U1 2 U2 6 PU ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD 0X5 1GB, OXON, ENGLAND SN 0273-1177 J9 ADV SPACE RES-SERIES PY 2005 VL 36 IS 3 SI 2005 BP 522 EP 533 DI 10.1016/j.asr.2005.03.029 PG 12 WC Engineering, Aerospace; Astronomy & Astrophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Engineering; Astronomy & Astrophysics; Geology; Meteorology & Atmospheric Sciences GA BDT66 UT WOS:000235247800026 ER PT S AU Fedrizzi, M de Paula, ER Langley, RB Komjathy, A Batista, IS Kantor, IJ AF Fedrizzi, M de Paula, ER Langley, RB Komjathy, A Batista, IS Kantor, IJ BE Moore, P TI Study of the March 31, 2001 magnetic storm effects on the ionosphere using GPS data SO SATELLITE DYNAMICS IN THE ERA OF INTERDISCIPLINARY SPACE GEODESY SE ADVANCES IN SPACE RESEARCH-SERIES LA English DT Article; Proceedings Paper CT 35th COSPAR Scientific Assembly CY JUL 18-25, 2004 CL Paris, FRANCE SP Comm Space Res DE GPS; TEC; total electron content; ionospheric disturbance; ionospheric storm; magnetic storm ID INTERNATIONAL REFERENCE IONOSPHERE; ELECTRON-CONTENT; DISTURBANCE DYNAMO; SATELLITE; SYSTEM; FIELDS AB Despite the fact that much has been learned about the Sun-Earth relationship during disturbed conditions, understanding the effects of magnetic storms on the neutral and ionized upper atmosphere is still one of the most challenging topics remaining in the physics of this atmospheric region. In order to investigate the magnetospheric and ionospheric-thermospheric coupling processes, many researchers are taking advantage of the dispersive nature of the ionosphere to compute total electron content (TEC) from global positioning system (GPS) dual-frequency data. Even though there are currently a large number of GPS receivers in continuous operation, they are unevenly distributed for ionosphere study purposes, being situated mostly in the Northern Hemisphere. The relatively smaller number of GPS receivers located in the Southern Hemisphere and, consequently, the reduced number of available TEC measurements, cause ionospheric modelling to be less accurate in this region. In the work discussed in this paper, the University of New Brunswick Ionospheric Modelling Technique (UNB-IMT) has been used to describe the local time and geomagnetic latitude dependence of the TEC during the March 31, 2001 magnetic storm with an emphasis on the effects in the Southern Hemisphere. Data collected from several GPS networks worldwide, including the Brazilian network for continuous monitoring, have been used along with ionosonde measurements to investigate the global ionospheric response to this severe storm. Data analysis revealed interesting ionospheric effects, which are shown to be dependent on the local time at the storm commencement and the magnetic conditions previous to and during the storm period. The southward turning of the interplanetary magnetic field during the recovery phase of the storm began a process of substorm. activity and development and intensification of electrojet activity over broad regions. Observed effects on the ionosphere during that storm are analysed and the mechanisms that gave rise to the ionospheric behaviour are discussed. (c) 2005 COSPAR. Published by Elsevier Ltd. All rights reserved. C1 Inst Nacl Pesquisas Espaciais, Div Aeronom, BR-12245970 Sao Jose Dos Campos, Brazil. Univ New Brunswick, Dept Geodesy & Geomat Engn, Geodet Res Lab, Fredericton, NB E3B 5A3, Canada. CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP NOAA, Space Environm Ctr, Div Res & Dev, 325 Broadway, Broadway, CO 80305 USA. EM Mariangel.Fedrizzi@noaa.gov RI Fedrizzi, Mariangel/C-6493-2012; Batista, Inez/F-2899-2012; de Paula, Eurico/O-1709-2013 OI de Paula, Eurico/0000-0003-2756-3826 NR 27 TC 18 Z9 18 U1 1 U2 4 PU ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD 0X5 1GB, OXON, ENGLAND SN 0273-1177 J9 ADV SPACE RES-SERIES PY 2005 VL 36 IS 3 SI 2005 BP 534 EP 545 DI 10.1016/j.asr.2005.07.019 PG 12 WC Engineering, Aerospace; Astronomy & Astrophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Engineering; Astronomy & Astrophysics; Geology; Meteorology & Atmospheric Sciences GA BDT66 UT WOS:000235247800027 ER PT S AU Dow, JM Neilan, RE Gendt, G AF Dow, JM Neilan, RE Gendt, G BE Moore, P TI The International GPS Service: Celebrating the 10th anniversary and looking to the next decade SO SATELLITE DYNAMICS IN THE ERA OF INTREDISCIPLINARY SPACE GEODESY SE ADVANCES IN SPACE RESEARCH LA English DT Article; Proceedings Paper CT 35th COSPAR Scientific Assembly CY JUL 18-25, 2004 CL Paris, FRANCE SP Comm Space Res DE International GPS service; IGS; GPS; GLONASS; Galileo; GNSS AB After 10 years as a service of the International Association of Geodesy, the International GPS Service IGS is preparing for the future use of multiple integrated global navigation satellite systems: GPS and its modernisation, Galileo and GLONASS. Since 1994, the IGS produces GPS data and products at the highest level of precision and accuracy available anywhere: it provides GPS orbits with 3-5 cm accuracy, sub-centimetre station positions and velocities, and station and satellite clocks at the sub-nanosecond level for users world-wide. A similar suite of data and products is available for GLONASS, demonstrating the ability of the IGS to incorporate observations from other GNSSs, such as Galileo. IGS affirms its interest to contribute to the development and applications of the Galileo programme and other GNSS. IGS currently consists of over 200 actively contributing organizations in more than 80 countries and a global network of more than 350 stations. The working groups and pilot projects of the IGS demonstrate IGS involvement in applications related to the precise global reference frame, timing, ionosphere, atmospheric water vapour, low Earth orbiter precise orbit determination (LEO POD), sea level change measurements, real-time GPS applications, and GNSS developments. (c) 2005 COSPAR. Published by Elsevier Ltd. All rights reserved. C1 ESA, European Space Operat Ctr, D-64293 Darmstadt, Germany. NASA, IGS Cent Bur, JPL, Pasadena, CA USA. Geoforschungszentrum Potsdam, D-14473 Potsdam, Germany. RP Dow, JM (reprint author), ESA, European Space Operat Ctr, Robert Bosch Str 5, D-64293 Darmstadt, Germany. EM john.dow@esa.int NR 5 TC 197 Z9 205 U1 4 U2 28 PU ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD 0X5 1GB, OXON, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2005 VL 36 IS 3 SI 2005 BP 320 EP 326 DI 10.1016/j.asr.2005.05.125 PG 7 WC Engineering, Aerospace; Astronomy & Astrophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Engineering; Astronomy & Astrophysics; Geology; Meteorology & Atmospheric Sciences GA BDT66 UT WOS:000235247800001 ER PT S AU Yang, RQ Hill, CJ Christensen, LE Webster, CR AF Yang, RQ Hill, CJ Christensen, LE Webster, CR BE Zah, CE Lou, Y Tsuji, S TI Mid-IR type-II interband cascade lasers and their applications SO SEMICONDUCTOR AND ORGANIC OPTOELECTRONIC MATERIALS AND DEVICES SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Semiconductor and Organic Optoelectronic Materials and Devices CY NOV 09-11, 2004 CL Beijing, PEOPLES R CHINA SP SPIE, Chinese Opt Soc, China Inst Commun, Beijing Assoc Commun & Informat, Beijing Univ Posts & Telecommun, IEEE COMSOC, IEEE LEOS, Commun Inst China, Opt Commun Tech Comm, Opt Soc Amer, Tsinghua Univ DE mid-infrared; lasers; semiconductors; quantum wells ID CONTINUOUS-WAVE OPERATION; HEAT-SINKING; TEMPERATURE AB Type-II interband cascade lasers are efficient and compact mid-infrared. (3-5 mu m) light sources with many applications such as gas sensing and environmental monitoring. Significant progress toward such a goal has recently been made in terms of achieving low threshold current densities (e.g. similar to 8 A/cm(2) at 80 K), high temperature operation (e.g. 325 K in pulsed and 217 K in cw modes), and continuous wave operation of single-mode distributed feedback (DFB) lasers. These DFB lasers have been integrated into laboratory spectrometers for detection of gases such as CH(4) and HCl. One laser was flown on a high-altitude balloon instrument and measured HCl profiles in the stratosphere as part of Aura satellite instrument validation. We review the recent progress of Sb-based mid-IR IC lasers and address the requirements for further improvements in their performance. C1 CALTECH, Jet Propuls Lab, Pasadena, CA 91125 USA. RP Yang, RQ (reprint author), CALTECH, Jet Propuls Lab, Pasadena, CA 91125 USA. NR 27 TC 8 Z9 8 U1 0 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 0-8194-5578-4 J9 P SOC PHOTO-OPT INS PY 2005 VL 5624 BP 413 EP 422 DI 10.1117/12.581109 PG 10 WC Engineering, Electrical & Electronic; Materials Science, Multidisciplinary; Optics; Physics, Condensed Matter SC Engineering; Materials Science; Optics; Physics GA BBR40 UT WOS:000227356100053 ER PT J AU Delin, KA Jackson, SP Johnson, DW Burleigh, SC Woodrow, RR McAuley, JM Dohm, JM Ip, F Ferre, TPA Rucker, DF Baker, VR AF Delin, KA Jackson, SP Johnson, DW Burleigh, SC Woodrow, RR McAuley, JM Dohm, JM Ip, F Ferre, TPA Rucker, DF Baker, VR TI Environmental studies with the Sensor Web: Principles and practice SO SENSORS LA English DT Article DE Sensor Web; network; wireless; hydrology; flood AB In 1997, the Sensor Web was conceived at the NASA/ Jet Propulsion Laboratory (JPL) to take advantage of the increasingly inexpensive, yet sophisticated, mass consumer-market chips for the computer and telecommunication industries and use them to create platforms that share information among themselves and act in concert as a single instrument. This instrument would be embedded into an environment to monitor and even control it. The Sensor Web's purpose is to extract knowledge from the data it collects and use this information to intelligently react and adapt to its surroundings. It links a remote end-user's cognizance with the observed environment. Here, we examine not only current progress in the Sensor Web technology, but also its recent application to problems in hydrology to illustrate the general concepts involved. C1 NASA, Jet Propuls Lab, Pasadena, CA 91109 USA. Univ Arizona, Dept Hydrol & Water Resources, Tucson, AZ 85721 USA. RP Delin, KA (reprint author), NASA, Jet Propuls Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM kevin.delin@jpl.nasa.gov RI Dohm, James/A-3831-2014; OI Rucker, Dale/0000-0002-8930-2747 NR 6 TC 41 Z9 46 U1 1 U2 8 PU MOLECULAR DIVERSITY PRESERVATION INTERNATIONAL PI BASEL PA MATTHAEUSSTRASSE 11, CH-4057 BASEL, SWITZERLAND SN 1424-8220 J9 SENSORS-BASEL JI Sensors PD JAN-FEB PY 2005 VL 5 IS 1-2 BP 103 EP 117 DI 10.3390/s5010103 PG 15 WC Chemistry, Analytical; Electrochemistry; Instruments & Instrumentation SC Chemistry; Electrochemistry; Instruments & Instrumentation GA 913GS UT WOS:000228140200009 ER PT S AU Woodell, G Jobson, DJ Rahman, ZU Hines, G AF Woodell, G Jobson, DJ Rahman, ZU Hines, G BE Carapezza, EM TI Enhancement of imagery in poor visibility conditions SO Sensors, and Command, Control, Communications, and Intelligence (C31) Technologies for Homeland Security and Homeland Defense IV, Pts 1 and 2 SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Sensors, and Command, Control, Communications, and Intelligence (C31) Technologies for Homeland Security and Homeland Defense IV CY MAR 28-APR 01, 2005 CL Orlando, FL DE Retinex; visual servo; image enhancement; poor visibility ID RETINEX AB Current still image and video systems are typically of limited use in poor visibility conditions such as in rain, fog, smoke, and haze. These conditions severely limit the range and effectiveness of imaging systems because of the severe reduction in contrast. The NASA Langley Research Center's Visual Information Processing Group has developed an image enhancement technology based on the concept of a visual servo that has direct applications to the problem of poor visibility conditions. Ibis technology has been used in cases of severe image turbidity in air as well as underwater with dramatic results. Use of this technology could result in greatly improved performance of perimeter surveillance systems, military, security, and law enforcement operations, port security, both on land and below water, and air and sea rescue services, resulting in improved public safety. C1 NASA, Langley Res Ctr, Hampton, VA 23665 USA. RP Woodell, G (reprint author), NASA, Langley Res Ctr, Hampton, VA 23665 USA. NR 13 TC 5 Z9 5 U1 0 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 0-8194-5763-9 J9 P SOC PHOTO-OPT INS PY 2005 VL 5778 BP 673 EP 683 DI 10.1117/12.601965 PN 1-2 PG 11 WC Engineering, Multidisciplinary SC Engineering GA BCR48 UT WOS:000230925700070 ER PT B AU Truszkowski, W Rouff, C Bailin, S Rilee, M AF Truszkowski, W Rouff, C Bailin, S Rilee, M BE Arabnia, HR Reza, H TI Progressive autonomy - An incremental agent-based approach SO SERP '05: Proceedings of the 2005 International Conference on Software Engineering Research and Practice, Vols 1 and 2 LA English DT Proceedings Paper CT International Conference on Software Engineering Research and Practice (SERP 05) CY JUN 27-29, 2005 CL Las Vegas, NV SP CSREA, Int Technol Inst, World Acad Sci & Informat Technol, HPCwire, GRIDtoday AB This paper presents a method under development for introducing autonomy and agent-based software into future space and ground-based missions while reducing the risk of mission failure. This is done using a mechanism to support dynamic agent-community evolution called "progressive autonomy". This paper will also address an application of progressive autonomy through spectral analysis automation (SAA). The SAA system will be a multi-agent system designed to provide automated support for: (1) automatic onboard filtering of spectral image data based on Principal Investigator (PI) guidance, goals and science agenda, and (2) the packing and transmission of the selected data to the PI for further processing. Additional v, the SAA can be generalized to support progressive autonomy for adaptive and growing autonomy for other spacecraft or robotic subsystems. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Truszkowski, W (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. NR 8 TC 0 Z9 0 U1 0 U2 0 PU C S R E A PRESS PI ATHENS PA 115 AVALON DR, ATHENS, GA 30606 USA BN 1-932415-51-3 PY 2005 BP 9 EP 15 PG 7 WC Computer Science, Software Engineering SC Computer Science GA BDY23 UT WOS:000236081000002 ER PT B AU Mandl, D Frye, S AF Mandl, D Frye, S BE Arabnia, HR Reza, H TI Experimenting with an evolving ground/space-based software architecture to enable sensor webs SO SERP '05: Proceedings of the 2005 International Conference on Software Engineering Research and Practice, Vols 1 and 2 LA English DT Proceedings Paper CT International Conference on Software Engineering Research and Practice (SERP 05) CY JUN 27-29, 2005 CL Las Vegas, NV SP CSREA, Int Technol Inst, World Acad Sci & Informat Technol, HPCwire, GRIDtoday DE n AB A series of ongoing experiments are being conducted at NASA Goddard Space Flight Center to explore integrated ground and space-based software architectures to enable sensor webs. A sensor web as defined by Steve Talabac at NASA Goddard Space Flight Center(GSFC), is a coherent set of distributed nodes interconnected by a communications fabric, that collectively behave as a single, dynamically adaptive, observing system. The nodes can be comprised of satellites, ground instruments, computing nodes etc. Sensor web capability requires autonomous management of constellation resources. This becomes progressively more important as more and more satellites share resources such as communication channels and ground stations while automatically coordinating their activities. There have been five ongoing activities along which include an effort to standardize a set of middleware to facilitate this vision. This paper will describe one set of activities using the Earth Observing I satellite, which used a variety of ground and flight software along with other satellites and ground sensors to prototype a sensor web. This activity allowed us to explore where the difficulties occurred in assembling sensor webs given today's technology. We will present an overview of the software system architecture, some key experiments and lessons learned to facilitate better sensor webs in the future. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Mandl, D (reprint author), NASA, Goddard Space Flight Ctr, Code 584, Greenbelt, MD 20771 USA. NR 9 TC 0 Z9 0 U1 0 U2 0 PU C S R E A PRESS PI ATHENS PA 115 AVALON DR, ATHENS, GA 30606 USA BN 1-932415-51-3 PY 2005 BP 23 EP 28 PG 6 WC Computer Science, Software Engineering SC Computer Science GA BDY23 UT WOS:000236081000004 ER PT B AU Hinchey, MG Rash, JL Truszkowski, WF Rouff, CA Sterritt, R AF Hinchey, MG Rash, JL Truszkowski, WF Rouff, CA Sterritt, R BE Arabnia, HR Reza, H TI Autonomous and autonomic swarms SO SERP '05: PROCEEDINGS OF THE 2005 INTERNATIONAL CONFERENCE ON SOFTWARE ENGINEERING RESEARCH AND PRACTICE, VOLS 1 AND 2 LA English DT Proceedings Paper CT International Conference on Software Engineering Research and Practice (SERP 05) CY JUN 27-29, 2005 CL Las Vegas, NV SP CSREA, Int Technol Inst, World Acad Sci & Informat Technol, HPCwire, GRIDtoday AB A watershed in systems engineering is represented by the advent of swarm-based systems that accomplish missions through cooperative action by a (large) group of autonomous individuals each having simple capabilities and no global knowledge of the group's objective. Such systems, with individuals capable of surviving in hostile environments, pose unprecedented challenges to system developers. Design and testing and verification at much higher levels will be required, together with the corresponding tools, to bring such systems to fruition. Concepts for possible future NASA space exploration missions include autonomous, autonomic swarms. Engineering swarm-based missions begins with understanding autonomy and autonomicity and how to design, test, and verify, systems that have those properties and, simultaneously, the capability to accomplish prescribed mission goals. Formal methods-based technologies, both projected and in development, are described in terms of their potential utility to swarm-based system developers. C1 NASA, Goddard Space Flight Ctr, Informat Syst Div, Greenbelt, MD 20771 USA. RP NASA, Goddard Space Flight Ctr, Informat Syst Div, Greenbelt, MD 20771 USA. EM michael.g.hinchey@nasa.gov; james.l.rash@nasa.gov; walter.f.truszkowski@nasa.gov; rouffc@saic.com; r.sterritt@ulster.ac.uk NR 27 TC 3 Z9 3 U1 0 U2 0 PU C S R E A PRESS PI ATHENS PA 115 AVALON DR, ATHENS, GA 30606 USA BN 1-932415-51-3 PY 2005 BP 36 EP 42 PG 7 WC Computer Science, Software Engineering SC Computer Science GA BDY23 UT WOS:000236081000006 ER PT S AU Jost, G Labarta, J Gimenez, J AF Jost, G Labarta, J Gimenez, J BE Chapman, BM TI What multilevel parallel programs do when you are not watching: A performance analysis case study comparing MPI/OpenMP, MIT, and nested OpenMP SO SHARED MEMORY PARALLEL PROGRAMMING WITH OPENMP SE LECTURE NOTES IN COMPUTER SCIENCE LA English DT Article; Proceedings Paper CT 5th International Workshop on OpenMP Applications and Tools (WOMPAT 2004) CY MAY 17-18, 2004 CL Univ Houston, Houston, TX SP OpenMP Architecture Review Board, OpenMP Users Grp cOMPunity, Intel Corp, Portland Grp, Texas Learning & Computat Ctr, Univ Houston HO Univ Houston AB In this paper we present a performance analysis case study of two multilevel parallel benchmark codes implemented in three different programming paradigms applicable to shared memory computer architectures. We describe how detailed analysis techniques help to differentiate between the influences of the programming model itself and other factors, such as implementation specific behavior of the operating system or architectural issues. C1 NASA, Ames Res Ctr, NAS Div, Moffett Field, CA 94035 USA. Tech Univ Catalonia, European Ctr Parallelism Barcelona, Barcelona 08034, Spain. RP Jost, G (reprint author), NASA, Ames Res Ctr, NAS Div, Moffett Field, CA 94035 USA. EM gjost@nas.nasa.gov; jesus@cepba.upc.es; judit@cepba.upc.es RI Labarta, Jesus/G-5256-2015 OI Labarta, Jesus/0000-0002-7489-4727 NR 15 TC 1 Z9 1 U1 0 U2 0 PU SPRINGER-VERLAG BERLIN PI BERLIN PA HEIDELBERGER PLATZ 3, D-14197 BERLIN, GERMANY SN 0302-9743 BN 3-540-24560-X J9 LECT NOTES COMPUT SC PY 2005 VL 3349 BP 29 EP 40 PG 12 WC Computer Science, Theory & Methods SC Computer Science GA BCB82 UT WOS:000228549100004 ER PT S AU Johnson, S Evans, E Jin, HQ Ierotheou, C AF Johnson, S Evans, E Jin, HQ Ierotheou, C BE Chapman, BM TI The ParaWise expert assistant - Widening accessibility to efficient and scalable tool generated OpenMP code SO SHARED MEMORY PARALLEL PROGRAMMING WITH OPENMP SE Lecture Notes in Computer Science LA English DT Article; Proceedings Paper CT 5th International Workshop on OpenMP Applications and Tools (WOMPAT 2004) CY MAY 17-18, 2004 CL Univ Houston, Houston, TX SP OpenMP Architecture Review Board, OpenMP Users Grp cOMPunity, Intel Corp, Portland Grp, Texas Learning & Computat Ctr, Univ Houston HO Univ Houston AB Despite the apparent simplicity of the OpenMP directive shared memory programming model and the sophisticated dependence analysis and code generation capabilities of the ParaWise/CAPO tools, experience shows that a level of expertise is required to produce efficient parallel code. In a real world application the investigation of a single loop in a generated parallel code can soon become an in-depth inspection of numerous dependencies in many routines. The additional understanding of dependencies is also needed to effectively interpret the information provided and supply the required feedback. The ParaWise Expert Assistant has been developed to automate this investigation and present questions to the user about, and in the context of, their application code. In this paper, we demonstrate that knowledge of dependence information and OpenMP are no longer essential to produce efficient parallel code with the Expert Assistant. It is hoped that this will enable a far wider audience to use the tools and subsequently, exploit the benefits of large parallel systems. C1 Univ Greenwich, Old Royal Vavy Coll, Parallel Proc Res Grp, London SE10 9LS, England. NASA, Ames Res Ctr, NAS Div, Moffett Field, CA 94035 USA. RP Johnson, S (reprint author), Univ Greenwich, Old Royal Vavy Coll, Parallel Proc Res Grp, Pk Row, London SE10 9LS, England. EM s.johnson@gre.ac.uk; e.w.evans@gre.ac.uk; hjin@nas.nasa.gov; c.ierotheou@gre.ac.uk NR 20 TC 3 Z9 3 U1 0 U2 1 PU SPRINGER-VERLAG BERLIN PI BERLIN PA HEIDELBERGER PLATZ 3, D-14197 BERLIN, GERMANY SN 0302-9743 BN 3-540-24560-X J9 LECT NOTES COMPUT SC PY 2005 VL 3349 BP 67 EP 82 PG 16 WC Computer Science, Theory & Methods SC Computer Science GA BCB82 UT WOS:000228549100007 ER PT J AU Kisin, E Murray, AR Johnson, V Gorelik, O Arepalli, S Gandelsman, VZ Hubbs, AF Mercer, RR Baron, P Kagan, VE Potapovich, AI Castranova, V Shvedova, AA AF Kisin, E Murray, AR Johnson, V Gorelik, O Arepalli, S Gandelsman, VZ Hubbs, AF Mercer, RR Baron, P Kagan, VE Potapovich, AI Castranova, V Shvedova, AA TI Pulmonary oxidative stress, inflammation, and fibrosis induced by carbon nanotubes. SO SHOCK LA English DT Meeting Abstract CT 11th Congress of the European-Shock-Society CY JAN 27-30, 2005 CL Vienna, AUSTRIA SP European Shock Soc, Soc Advancement Res Traumat & Sept Shock C1 NIOSH, Pathol & Physiol Res Branch, HELD, Morgantown, WV USA. NIOSH, Toxicol & Mol Biol Branch, HELD, Morgantown, WV USA. W Virginia Univ, Morgantown, WV 26506 USA. Lockheed Martin Corp, Engn Directorate, Mat & Proc Branch, Bethesda, MD 20817 USA. NASA, Nanotube Team, GBTech Inc, JSC, Houston, TX USA. NIOSH, Monitoring Res & Stat Act, DART, Cincinnati, OH 45226 USA. Univ Pittsburgh, Pittsburgh, PA USA. NR 0 TC 0 Z9 0 U1 1 U2 2 PU LIPPINCOTT WILLIAMS & WILKINS PI PHILADELPHIA PA 530 WALNUT ST, PHILADELPHIA, PA 19106-3621 USA SN 1073-2322 J9 SHOCK JI Shock PY 2005 VL 23 SU 2 MA 177 BP 65 EP 65 PG 1 WC Critical Care Medicine; Hematology; Surgery; Peripheral Vascular Disease SC General & Internal Medicine; Hematology; Surgery; Cardiovascular System & Cardiology GA 884QP UT WOS:000226101200151 ER PT J AU Ghoshal, A Martin, WN Schulz, MJ Prosser, WH Chattopadhyay, A AF Ghoshal, A Martin, WN Schulz, MJ Prosser, WH Chattopadhyay, A TI Simulation of asymmetric Lamb waves for sensing and actuation in plates SO SHOCK AND VIBRATION LA English DT Article ID PIEZOELECTRIC ACTUATORS; COMPOSITE STRUCTURES; SENSORS AB Two approaches used for monitoring the health of thin aerospace structures are active interrogation and passive monitoring. The active interrogation approach generates and receives diagnostic Lamb waves to detect damage, while the passive monitoring technique listens for acoustic waves caused by damage growth. For the application of both methods, it is necessary to understand how Lamb waves propagate through a structure. In this paper, a Physics-Based Model (PBM) using classical plate theory is developed to provide a basic understanding of the actual physical process of asymmetric Lamb mode wave generation and propagation in a plate. The closed-form model uses modal superposition to simulate waves generated by piezoceramic patches and by simulated acoustic emissions. The generation, propagation, reflection, interference, and the sensing of the waves are represented in the model, but damage is not explicitly modeled. The developed model is expected to be a useful tool for the Structural Health Monitoring (SHM) community, particularly for studying high frequency acoustic wave generation and propagation in lieu of Finite Element models and other numerical models that require significant computational resources. The PBM is capable of simulating many possible scenarios including a variety of test cases, whereas experimental measurements of all of the cases can be costly and time consuming. The model also incorporates the sensor measurement effect, which is an important aspect in damage detection. Continuous and array sensors are modeled, which are efficient for measuring waves because of their distributed nature. C1 United Technol Res Ctr, Struct Integr Grp, E Hartford, CT 06108 USA. NASA, Langley Res Ctr, Natl Res Council, Hampton, VA 23665 USA. USN, Undersea Warfare Ctr, Newport, RI 02841 USA. Univ Cincinnati, Dept Mech Engn, Cincinnati, OH 45221 USA. NASA, Langley Res Ctr, NESB, Hampton, VA 23681 USA. Arizona State Univ, Dept Aerosp Engn & Engn Mech, Tempe, AZ 85287 USA. RP Ghoshal, A (reprint author), United Technol Res Ctr, Struct Integr Grp, E Hartford, CT 06108 USA. EM anindo_ghoshal@yahoo.com; MartinWN@Npt.NUWC.Navy.Mil; mark.j.schulz@uc.edu; William.H.Prosser@nasa.gov; aditi@asu.edu NR 35 TC 11 Z9 11 U1 0 U2 4 PU IOS PRESS PI AMSTERDAM PA NIEUWE HEMWEG 6B, 1013 BG AMSTERDAM, NETHERLANDS SN 1070-9622 J9 SHOCK VIB JI Shock Vib. PY 2005 VL 12 IS 4 BP 243 EP 271 PG 29 WC Acoustics; Engineering, Mechanical; Mechanics SC Acoustics; Engineering; Mechanics GA 973EB UT WOS:000232504600001 ER PT B AU Liou, MS Takayama, K AF Liou, MS Takayama, K BE Jiang, Z TI Aerodynamic characteristics of high Mach, low Reynolds numbers flow past micro spheres SO Shock Waves, Vols 1 and 2, Proceedings LA English DT Proceedings Paper CT 24th International Symposium on Shock Waves CY JUL 11-16, 2004 CL Beijing, PEOPLES R CHINA SP Chinese Acad Sci, Inst Mech, Nat Sci Fdn China, Chinese Soc Shock Waves, Chinese Soc Theoret & Appl Mech, Chinese Soc Aerodynam AB conducted a numerical study of low Reynolds and high Mach numbers flows over micro spheres with the aim of clarifying their aerodynamic characteristics. First, the flow over a single sphere was studied in detail for a range of Mach and Reynolds numbers and the results were validated with experimental data. Then, multiple orderly-configured spheres were studied, showing that the mutual interference effects are long range, owing to the shock waves and strong diffusion in the flow. Finally, we considered transient behavior induced by a moving shock over the particles. C1 NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Liou, MS (reprint author), NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. NR 6 TC 0 Z9 0 U1 0 U2 1 PU SPRINGER-VERLAG BERLIN PI BERLIN PA HEIDELBERGER PLATZ 3, D-14197 BERLIN, GERMANY BN 3-540-22497-1 PY 2005 BP 1169 EP 1174 DI 10.1007/978-3-540-27009-6_180 PG 6 WC Mechanics SC Mechanics GA BCU24 UT WOS:000231243300180 ER PT J AU Diskin, B Thomas, JL Mineck, RE AF Diskin, B Thomas, JL Mineck, RE TI On quantitative analysis methods for multigrid solutions SO SIAM JOURNAL ON SCIENTIFIC COMPUTING LA English DT Article DE multigrid methods; quantitative analysis; partial differential equations ID CONVECTION; DISCRETIZATIONS; EQUATIONS; SOLVERS; FLOWS AB Limitations of the classical local-mode Fourier (LMF) analysis in application to multigrid solutions of variable-coefficient problems are well known. This paper introduces alternative, very general, quantitative analysis methods for multigrid solutions of partial differential equations. The methods are applied to available, nonperfect multigrid solvers that deal with practical problems. The analysis methods considered in this paper focus on the main complementary parts of a multigrid cycle: relaxation and coarse-grid correction. Tasks for these parts, e.g., error smoothing for relaxation and reduction of smooth errors for coarse-grid correction, are assumed to be assigned in advance. Idealized relaxation (IR) and idealized coarse-grid (ICG) iterations are introduced. In these iterations, one part of the cycle (relaxation for IR iterations and coarse-grid correction for ICG iterations) is replaced with an idealized imitation known to be efficient for the assigned task; its complementary part is the actual part of a two-grid cycle. The analysis compares performances of the actual cycle and idealized iterations. The IR and ICG iterations are very general and can be directly applied in the most complicated simulations including highly variable (or nonlinear) coefficients, complex geometries, and unstructured grids. The results of this analysis are not single-number estimates; they are rather convergence patterns of the iterations that may either confirm or refute expectations indicating what part of the actual solver is inefficient in carrying out the assigned task. The generality of the analysis makes it a valuable tool for analyzing complicated large-scale computational problems, where no other analysis methods are currently available. In this paper, the IR and ICG iterations are applied to model problems of progressive complexity. The analysis proved sensitive to very delicate details of the actual multigrid cycle, pointing clearly to each instance when a part of the algorithm was inefficient. C1 Natl Inst Aerosp, Hampton, VA 23681 USA. NASA, Langley Res Ctr, Computat Modeling & Simulat Branch, Hampton, VA 23681 USA. RP Diskin, B (reprint author), Natl Inst Aerosp, 144 Res Dr, Hampton, VA 23681 USA. EM bdiskin@nianet.org; James.L.Thomas@nasa.gov; Raymond.E.Mineck@nasa.gov NR 30 TC 7 Z9 7 U1 0 U2 0 PU SIAM PUBLICATIONS PI PHILADELPHIA PA 3600 UNIV CITY SCIENCE CENTER, PHILADELPHIA, PA 19104-2688 USA SN 1064-8275 J9 SIAM J SCI COMPUT JI SIAM J. Sci. Comput. PY 2005 VL 27 IS 1 BP 108 EP 129 DI 10.1137/030601521 PG 22 WC Mathematics, Applied SC Mathematics GA 971BA UT WOS:000232354900006 ER PT J AU Bryson, S Levy, D AF Bryson, S Levy, D TI Balanced central schemes for the shallow water equations on unstructured grids SO SIAM JOURNAL ON SCIENTIFIC COMPUTING LA English DT Article DE shallow water equations; central schemes; balance laws; unstructured grids ID HYPERBOLIC CONSERVATION-LAWS; CENTRAL-UPWIND SCHEMES; SAINT-VENANT SYSTEM; SOURCE TERMS; EXTENSION AB We present a two- dimensional, well-balanced, central-upwind scheme for approximating solutions of the shallow water equations in the presence of a stationary bottom topography on triangular meshes. Our starting point is the recent central scheme of Kurganov and Petrova ( KP) for approximating solutions of conservation laws on triangular meshes. In order to extend this scheme from systems of conservation laws to systems of balance laws one has to find an appropriate discretization of the source terms. We first show that for general triangulations there is no discretization of the source terms that corresponds to a well- balanced form of the KP scheme. We then derive a new variant of a central scheme that can be balanced on triangular meshes. We note in passing that it is straightforward to extend the KP scheme to general unstructured conformal meshes. This extension allows us to recover our previous well- balanced scheme on Cartesian grids. We conclude with several simulations, verifying the second-order accuracy of our scheme as well as its well- balanced properties. C1 Stanford Univ, Program Sci Comp Computat Math, Stanford, CA 94305 USA. NASA, Ames Res Ctr, Adv Supercomp Div, Moffett Field, CA 94035 USA. Stanford Univ, Dept Math, Stanford, CA 94305 USA. RP Stanford Univ, Program Sci Comp Computat Math, Stanford, CA 94305 USA. EM bryson@nas.nasa.gov; dlevy@math.stanford.edu NR 24 TC 13 Z9 14 U1 1 U2 2 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 2005 VL 27 IS 2 BP 532 EP 552 DI 10.1137/040605539 PG 21 WC Mathematics, Applied SC Mathematics GA 988GG UT WOS:000233579900009 ER PT J AU Ryan, J Shu, CW Atkins, H AF Ryan, J Shu, CW Atkins, H TI Extension of a postprocessing technique for the discontinuous Galerkin method for hyperbolic equations with application to an aeroacoustic problem SO SIAM JOURNAL ON SCIENTIFIC COMPUTING LA English DT Article DE accuracy enhancement; postprocessing; discontinuous Galerkin method; hyperbolic equations ID FINITE-ELEMENT-METHOD; SUPERCONVERGENT PATCH RECOVERY; POSTERIORI ERROR ESTIMATOR; CONSERVATION-LAWS; ACCURACY; SYSTEMS AB In this paper we further explore a local postprocessing technique, originally developed by Bramble and Schatz [ Math. Comp., 31 ( 1977), pp. 94-111] using continuous finite element methods for elliptic problems and later by Cockburn et al. [ Math. Comp., 72 ( 2003), pp. 577-606] using discontinuous Galerkin methods for hyperbolic equations. We investigate the technique in the context of superconvergence of the derivatives of the numerical solution, two space dimensions for both tensor product local basis and the usual kth degree polynomials basis, multidomain problems with different mesh sizes, variable coefficient linear problems including those with discontinuous coefficients, and linearized Euler equations applied to an aeroacoustic problem. We demonstrate through extensive numerical examples that the technique is very effective in all these situations in enhancing the accuracy of the discontinuous Galerkin solutions. C1 Brown Univ, Div Appl Math, Providence, RI 02912 USA. NASA, Langley Res Ctr, Computat Modeling & Simulat Branch, Hampton, VA 23681 USA. RP Oak Ridge Natl Lab, POB 2008,MS6367, Oak Ridge, TN 37831 USA. EM ryanjk@ornl.gov; shu@dam.brown.edu; h.l.atkins@larc.nasa.gov RI Shu, Chi-Wang/A-3216-2013 OI Shu, Chi-Wang/0000-0001-7720-9564 NR 24 TC 26 Z9 29 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 2005 VL 26 IS 3 BP 821 EP 843 DI 10.1137/S1064827503423998 PG 23 WC Mathematics, Applied SC Mathematics GA 908BE UT WOS:000227761300005 ER PT S AU Powell, JA Neudeck, PG Trunek, AJ Abel, PB AF Powell, JA Neudeck, PG Trunek, AJ Abel, PB BE Nipoti, R Poggi, A Scorzoni, A TI Step structures produced by hydrogen etching of initially step-free (0001) 4H-SiC mesas SO SILICON CARBIDE AND RELATED MATERIALS 2004 SE MATERIALS SCIENCE FORUM LA English DT Article; Proceedings Paper CT 5th European Conference on Silicon Carbide and Related Materials CY AUG 31-SEP 04, 2004 CL Bologna, ITALY SP Comune Bologna, Giunta Reg Emilia Romagna, Prov Biologna, Univ Bologna, President Italian Consiglio Nazl Ric DE 4H-SiC; AFM; hydrogen etching; step-free surface; stepflow etching ID SILICON-CARBIDE; 6H-SIC(0001); SURFACES; DEFECTS; GROWTH AB This paper presents new observations resulting from in-situ high temperature hydrogen etching of 4H-SiC mesas that were step-free prior to initiation of etching. In particular, it was found that well-ordered pyramidal-shaped step train structures could be produced on mesa top surfaces via stepflow etching proceeding inward from the sides of mesas. In many cases, the height of steps etched inward from {1(1) over bar 01} mesa sides is 0.5 nm (2 Si-C bilayers), while the height of steps etched inward from {1(1) over bar 00} sides of the same mesa is 1.0 nm (4 Si-C bilayers, the repeat distance of the 4H-SiC polytype). We propose that stepflow etching starting from the mesa sidewall and involving step-to-step repulsive forces produces the observed step train structures. C1 NASA, Sest Inc, Cleveland, OH 44135 USA. NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. NASA, OAI, Cleveland, OH 44135 USA. NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Powell, JA (reprint author), NASA, Sest Inc, 21000 Brookpk Rd,MS 77-1, Cleveland, OH 44135 USA. EM J.A.Powell@grc.nasa.gov; Neudeck@nasa.gov; Andrew.J.Trunek@grc.nasa.gov; Phillip.B.Abel@nasa.gov NR 12 TC 7 Z9 7 U1 0 U2 2 PU TRANS TECH PUBLICATIONS LTD PI ZURICH-UETIKON PA BRANDRAIN 6, CH-8707 ZURICH-UETIKON, SWITZERLAND SN 0255-5476 BN 0-87849-963-6 J9 MATER SCI FORUM PY 2005 VL 483 BP 753 EP 756 PG 4 WC Materials Science, Multidisciplinary; Materials Science, Characterization & Testing SC Materials Science GA BCB85 UT WOS:000228549600178 ER PT J AU Arsintescu, L Nguyen, TT Colletti, LM Pritchett, AR Mallis, LL AF Arsintescu, L Nguyen, TT Colletti, LM Pritchett, AR Mallis, LL TI Impact of fatigue related scheduling factors on sleepiness in aviators SO SLEEP LA English DT Meeting Abstract CT 19th Annual Meeting of the Associated-Professional-Sleep-Societies CY JUN 18-23, 2005 CL Denver, CO SP Associated Profess Sleep Soc C1 NASA, Ames Res Ctr, San Jose State Univ Fdn, Moffett Field, CA 94035 USA. NASA, Ames Res Ctr, QSS Grp Inc, Moffett Field, CA 94035 USA. Georgia Inst Technol, Atlanta, GA 30332 USA. NR 0 TC 0 Z9 0 U1 0 U2 0 PU AMER ACADEMY SLEEP MEDICINE PI WESTCHESTER PA ONE WESTBROOK CORPORATE CENTER STE 920, WESTCHESTER, IL 60154 USA SN 0161-8105 J9 SLEEP JI Sleep PY 2005 VL 28 SU S MA 1038 BP A352 EP A352 PG 1 WC Clinical Neurology; Neurosciences SC Neurosciences & Neurology GA 923JL UT WOS:000228906101545 ER PT J AU Brandt, SL Colletti, LM Van Dongen, H Dinges, DF Mallis, MM AF Brandt, SL Colletti, LM Van Dongen, H Dinges, DF Mallis, MM TI Transitioning from a Mars day to an Earth day: Effects on psychomotor vigilance performance SO SLEEP LA English DT Meeting Abstract CT 19th Annual Meeting of the Associated-Professional-Sleep-Societies CY JUN 18-23, 2005 CL Denver, CO SP Associated Profess Sleep Soc C1 San Jose State Univ, Moffett Field, CA USA. NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. QSS Grp Inc, Moffett Field, CA USA. Univ Penn, Div Sleep & Chronobiol, Dept Psychiat, Philadelphia, PA 19104 USA. Univ Penn, Ctr Sleep & Resp Neurobiol, Philadelphia, PA 19104 USA. NR 0 TC 0 Z9 0 U1 0 U2 0 PU AMER ACADEMY SLEEP MEDICINE PI WESTCHESTER PA ONE WESTBROOK CORPORATE CENTER STE 920, WESTCHESTER, IL 60154 USA SN 0161-8105 J9 SLEEP JI Sleep PY 2005 VL 28 SU S MA 1050 BP A356 EP A356 PG 1 WC Clinical Neurology; Neurosciences SC Neurosciences & Neurology GA 923JL UT WOS:000228906101557 ER PT J AU Colletti, LM Mejdal, S Dinges, DF Van Dongen, H Mallis, MM AF Colletti, LM Mejdal, S Dinges, DF Van Dongen, H Mallis, MM TI Comparing a biomathernatical model of alertness with pilot performance data during a simulated ultra-long-range flight SO SLEEP LA English DT Meeting Abstract CT 19th Annual Meeting of the Associated-Professional-Sleep-Societies CY JUN 18-23, 2005 CL Denver, CO SP Associated Profess Sleep Soc C1 QSS Grp Inc, Moffett Field, CA USA. Usabil Matters, Sunnyvale, CA USA. NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. Univ Penn, Dept Psychiat, Div Sleep & Chronobiol, Philadelphia, PA 19104 USA. Univ Penn, Ctr Sleep & Resp Neurobiol, Philadelphia, PA 19104 USA. NR 0 TC 0 Z9 0 U1 0 U2 0 PU AMER ACADEMY SLEEP MEDICINE PI WESTCHESTER PA ONE WESTBROOK CORPORATE CENTER STE 920, WESTCHESTER, IL 60154 USA SN 0161-8105 J9 SLEEP JI Sleep PY 2005 VL 28 SU S MA 197 BP A66 EP A67 PG 2 WC Clinical Neurology; Neurosciences SC Neurosciences & Neurology GA 923JL UT WOS:000228906100198 ER PT J AU DeRoshia, CW Oyung, RL Colletti, LM Mallis, MM AF DeRoshia, CW Oyung, RL Colletti, LM Mallis, MM TI Detection of fatigue states by analysis of cireadian rhythms in locomotor activity SO SLEEP LA English DT Meeting Abstract CT 19th Annual Meeting of the Associated-Professional-Sleep-Societies CY JUN 18-23, 2005 CL Denver, CO SP Associated Profess Sleep Soc C1 NASA, Ames Res Ctr, Human Factors & Technol Div, Moffett Field, CA 94035 USA. NR 0 TC 0 Z9 0 U1 0 U2 0 PU AMER ACADEMY SLEEP MEDICINE PI WESTCHESTER PA ONE WESTBROOK CORPORATE CENTER STE 920, WESTCHESTER, IL 60154 USA SN 0161-8105 J9 SLEEP JI Sleep PY 2005 VL 28 SU S MA 173 BP A58 EP A59 PG 2 WC Clinical Neurology; Neurosciences SC Neurosciences & Neurology GA 923JL UT WOS:000228906100174 ER PT J AU Oyung, RL Chapman, PM Laura, CM Reduta, DD Mallis, MM AF Oyung, RL Chapman, PM Laura, CM Reduta, DD Mallis, MM TI Are pilots well-rested upon entering a NASA flight simulation protocol? SO SLEEP LA English DT Meeting Abstract CT 19th Annual Meeting of the Associated-Professional-Sleep-Societies CY JUN 18-23, 2005 CL Denver, CO SP Associated Profess Sleep Soc C1 San Jose State Univ, Moffett Field, CA USA. QSS Grp Inc, Moffett Field, CA USA. NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. NR 0 TC 0 Z9 0 U1 0 U2 0 PU AMER ACADEMY SLEEP MEDICINE PI WESTCHESTER PA ONE WESTBROOK CORPORATE CENTER STE 920, WESTCHESTER, IL 60154 USA SN 0161-8105 J9 SLEEP JI Sleep PY 2005 VL 28 SU S MA 413 BP A140 EP A140 PG 1 WC Clinical Neurology; Neurosciences SC Neurosciences & Neurology GA 923JL UT WOS:000228906100415 ER PT S AU Sokolowski, W AF Sokolowski, W BE Wilson, AR TI Potential bio-medical and commercial applications of cold hibernated elastic memory (CHEM) self-deployable foam structures SO Smart Materials III SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Smart Materials III CY DEC 13-15, 2004 CL Sydney, AUSTRALIA SP SPIE, Univ New S Wales, Australian Govt Dept Def, Def Sci & Technol Org, Cochlear, NSW Minist Sci & Med Res DE expandable structures; shape memory polymers; open cellular structures; glass transition temperature Tg AB A cold hibernated elastic memory (CHEM) foam structure is one of the most recent results of the quest for simple, reliable and low-cost expandable space structures. The CHEM technology utilizes shape memory polymers in open cellular (foam) structure or sandwich structures made of shape memory polymer foam cores and polymeric composite skins. It takes advantage of the polymer's heat activated shape memory in addition to the foam's elastic recovery to deploy a compacted structure. The glass transition temperature T-g is tailored to rigidize the structure in the fully deployed configuration. Previous experimental and analytical results were very encouraging and indicated that the CHEM foam technology can perform robustly in space as well as in the Earth environment. CHEM structures are described here and their major advantages are identified over other expandable/deployable structures. Although the space community is the original major beneficiary, a number of potential applications are also anticipated for the "earth environment". CHEM developers strongly believe that this technology, has great promise for a host of commercial and bio-medical applications. Some of these potential and already investigated CHEM applications are described in this paper. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Sokolowski, W (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 18 TC 3 Z9 3 U1 0 U2 5 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-5608-X J9 P SOC PHOTO-OPT INS PY 2005 VL 5648 BP 397 EP 405 DI 10.1117/12.593931 PG 9 WC Materials Science, Multidisciplinary SC Materials Science GA BBX91 UT WOS:000228294600050 ER PT S AU Kelly, DP Chuang, WH Hess, L Hu, R Jhabvala, M King, T Li, MJ Loughlin, J Moseley, SH Ray, C AF Kelly, DP Chuang, WH Hess, L Hu, R Jhabvala, M King, T Li, MJ Loughlin, J Moseley, SH Ray, C BE Cane, C Chiao, JC Verdu, FV TI Thermal-stress control of microshutter arrays in cryogfenic applications for the James Webb Space Telescope SO SMART SENSORS, ACTUATORS, AND MEMS II SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference Sensors, Actuators, and MEMS II CY MAY 09-11, 2005 CL Seville, SPAIN SP Amer Soc Regional Anesthesia DE microshutters; James Webb Space Telescope (JWST); optical MEMS; micro-optics; programmable masks; spatial light modulator AB We report on methods to minimize thermally-induced deformation in a MEMS-based reconfigurable aperture. The device is an enabling component of the Near-Infrared Spectrometer. a principle instrument on NASA's James Webb Space Telescope. The Microshutter Array consists of 384 x 175 individually addressable shutters which can be magnetically rotated 90 degrees into the plane of the array and electrostatically latched open. Each shutter is a 100 x 200 mu m rectangular membrane suspended by a small neck region and torsion flexure. The primary materials in the shutter are a 5000 angstrom Si3N4 layer for mechanical rigidity, 2000 angstrom Al for opacity and electrostatic latching. and 2200 angstrom Co90Fe10 for magnetic actuation. This multi-layer stack presents a challenge due to the operating temperatures required for the device: both room temperature (300K) and cryogenic temperature (30K). Thermal expansion of the materials causes the shutters to bow out of plane excessively, which can prevent actuation of the shutters. cause damage to portions of the array, and allow light leakage around closed shutters. Here we present our investigation of several methods to prevent microshutter bowing including deposition of additional materials on the shutters to create a symmetrical layer stack and replacing the current stack with low-coefficient of thermal expansion materials. Using shutter-size suspended cantilever beams as a rapid-development test bed, we have reduced out-of-plane bowing between 300K and 30K to 10% or better. We are currently applying these results to microshutter arrays to develop shutters that remain flat from room temperature to cryogenic temperature while retaining the required mechanical, optical, and magnetic properties. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP NASA, Goddard Space Flight Ctr, Code 661, Greenbelt, MD 20771 USA. NR 10 TC 3 Z9 3 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 0-8194-5831-7 J9 PROC SPIE PY 2005 VL 5836 BP 171 EP 178 DI 10.1117/12.608754 PG 8 WC Instruments & Instrumentation; Optics SC Instruments & Instrumentation; Optics GA BCX90 UT WOS:000231822100017 ER PT S AU George, T Urgiles, E Toda, R Wilcox, JZ Douglas, S Lee, CS Son, K Miller, D Myung, N Madsen, L Leskowitz, G El-Gammal, R Weitekamp, D AF George, T Urgiles, E Toda, R Wilcox, JZ Douglas, S Lee, CS Son, K Miller, D Myung, N Madsen, L Leskowitz, G El-Gammal, R Weitekamp, D BE Cane, C Chiao, JC Verdu, FV TI MEMS-based micro instruments for in-situ planetary exploration SO Smart Sensors, Actuators, and MEMS II SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference Sensors, Actuators, and MEMS II CY MAY 09-11, 2005 CL Seville, SPAIN SP Amer Soc Regional Anesthesia DE MEMS; in-situ; planetary exploration; micro-instrument; NASA; JPL; x-ray fluorescence; cathodoluminescence; ELXS; NMR; FDNMR; life detection AB NASA's planetary exploration strategy is primarily targeted to the detection of extant or extinct signs of life. Thus, the agency is moving towards more in-situ landed missions as evidenced by the recent, successful demonstration of twin Mars Exploration Rovers. Also, future robotic exploration platforms are expected to evolve towards sophisticated analytical laboratories composed of multi-instrument suites. MEMS technology is very attractive for in-situ planetary exploration because of the promise of a diverse and capable set of advanced, low mass and low-power devices and instruments. At JPL, we are exploiting this diversity of MEMS for the development of a new class of miniaturized instruments for planetary exploration. In particular, two examples of this approach are the development of an Electron Luminescence X-ray Spectrometer (ELXS), and a Force-Detected Nuclear Magnetic Resonance (FDNMR) Spectrometer. The ELXS is a compact (< 1 kg) electron-beam based microinstrument that can determine the chemical composition of samples in air via electron-excited x-ray fluorescence and cathodoluminescence. The enabling technology is a 200-nm-thick, MEMS-fabricated silicon nitride membrane that encapsulates the evacuated electron column while yet being thin enough to allow electron transmission into the ambient atmosphere. The MEMS FDNMR spectrometer, at 2-mm diameter, will be the smallest NMR spectrometer in the world. The significant innovation in this technology is the ability to immerse the sample in a homogenous, uniform magnetic field required for high-resolution NMR spectroscopy. The NMR signal is detected using the principle of modulated dipole-dipole interaction between the sample's nuclear magnetic moment and a 60-micron-diameter detector magnet. Finally, the future development path for both of these technologies, culminating ultimately in infusion into space missions, is discussed. C1 Jet Prop Lab, Pasadena, CA 91109 USA. RP George, T (reprint author), Jet Prop Lab, Mailstop 302-306,4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 15 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 0-8194-5831-7 J9 P SOC PHOTO-OPT INS PY 2005 VL 5836 BP 188 EP 199 DI 10.1117/12.608381 PG 12 WC Instruments & Instrumentation; Optics SC Instruments & Instrumentation; Optics GA BCX90 UT WOS:000231822100019 ER PT S AU Sherrit, S AF Sherrit, S BE Armstrong, WD TI Smart material/actuator needs in extreme environments in space SO Smart Structures and Materials 2005: Active Materials: Behavior and Mechanics SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Smart Structures and Materials 2005 Conference CY MAR 07-10, 2005 CL San Diego, CA SP SPIE, Amer Soc Mech Engineers, Boeing Co, Journal Intelligent Mat Syst & Struct, Sage Publicat, Rhombus Consultants Grp, CSA Engn Inc, ISIS Canada, KAIST, Smart Infra Struct Technol Ctr DE actuators; positioners; motors; space exploration; extreme temperatures; pressure ID PIEZOELECTRIC ACTUATOR; INCHWORM MOTOR; TECHNOLOGY AB Future missions to the planets and moons in our Solar System will require new technology. Missions with surface or atmospheric mobility or sample acquisition requirements will need advanced actuation technology to operate in the extreme environments found in the Solar System. Depending on the specific mission this technology may be required to withstand 10's of Kelvin environments or temperatures exceeding that of Venus (460 degrees C). In addition the technology may have to withstand high radiation and corrosive environments and pressures ranging from high vacuum to 100's of MPa. These challenging mission requirements push the limit in performance even under terrestrial conditions. Motors for mobility platforms, deployment devices or actuators for sampling tools are required that can operate reliably and deliver substantial torque and power. These devices must be lightweight, compact and operate effectively under extreme conditions. This paper will focus on a range of actuators based on electromechanical materials used for the applications discussed above and will present some of the challenges of developing these systems for space applications. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Sherrit, S (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. NR 46 TC 4 Z9 4 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 0-8194-5742-6 J9 P SOC PHOTO-OPT INS PY 2005 VL 5761 BP 335 EP 346 DI 10.1117/12.606475 PG 12 WC Instruments & Instrumentation; Materials Science, Characterization & Testing; Materials Science, Composites SC Instruments & Instrumentation; Materials Science GA BCN81 UT WOS:000230337500037 ER PT S AU Noebe, R Gaydosh, D Padula, S Garg, A Biles, T Nathal, M AF Noebe, R Gaydosh, D Padula, S Garg, A Biles, T Nathal, M BE Armstrong, WD TI Properties and potential of two (Ni,Pt)Ti alloys for use as high-temperature actuator materials SO Smart Structures and Materials 2005: Active Materials: Behavior and Mechanics SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Smart Structures and Materials 2005 Conference CY MAR 07-10, 2005 CL San Diego, CA SP SPIE, Amer Soc Mech Engineers, Boeing Co, Journal Intelligent Mat Syst & Struct, Sage Publicat, Rhombus Consultants Grp, CSA Engn Inc, ISIS Canada, KAIST, Smart Infra Struct Technol Ctr DE high-temperature shape memory alloy; NiTi; NiPtTi; tensile properties; work output; shape memory effect; transformation strain; transformation temperatures; differential scanning calorimetry ID SHAPE-MEMORY ALLOYS AB The microstructure, transformation temperatures, basic tensile properties, shape memory behavior, and work output for two (Ni,Ti)Pt high-temperature shape memory alloys have been characterized. One was a Ni30Pt20Ti50 alloy (referred to as 20Pt) with transformation temperatures above 230 degrees C and the other was a Ni20Pt30Ti50 alloy (30Pt) with transformation temperatures above 530 degrees C. Both materials displayed shape memory behavior and were capable of 100% (no-load) strain recovery for strain levels up to their fracture limit (3-4%) when deformed at room temperature. For the 20Pt alloy, the tensile strength, modulus, and ductility dramatically increased when the material was tested just above the austenite finish (A(f)) temperature. For the 30Pt alloy, a similar change in yield behavior at temperatures above the Af was not observed. In this case the strength of the austenite phase was at best comparable and generally much weaker than the martensite phase. A ductility minimum was also observed just below the A, temperature in this alloy. As a result of these differences in tensile behavior, the two alloys performed completely different when thermally cycled under constant load. The 20Pt alloy behaved similar to conventional binary NiTi alloys with work output due to the martensite-to-austenite transformation initially increasing with applied stress. The maximum work output measured in the 20Pt alloy was nearly 9 J/cm(3) and was limited by the tensile ductility of the material. In contrast, the martensite-to-austenite transformation in the 30Pt alloy was not capable of performing work against any bias load. The reason for this behavior was traced back to its basic mechanical properties, where the yield strength of the austenite phase was similar to or lower than that of the martensite phase, depending on temperature. Hence, the recovery or transformation strain for the 30Pt alloy under load was essentially zero, resulting in zero work output. C1 NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Noebe, R (reprint author), NASA, Glenn Res Ctr, 21000 Brookpk Rd, Cleveland, OH 44135 USA. NR 14 TC 39 Z9 39 U1 2 U2 9 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-5742-6 J9 P SOC PHOTO-OPT INS PY 2005 VL 5761 BP 364 EP 375 DI 10.1117/12.598492 PG 12 WC Instruments & Instrumentation; Materials Science, Characterization & Testing; Materials Science, Composites SC Instruments & Instrumentation; Materials Science GA BCN81 UT WOS:000230337500040 ER PT S AU Bar-Cohen, Y AF Bar-Cohen, Y BE Cohen, YB TI Biomimetics: mimicking and inspired-by biology SO SMART STRUCTURES AND MATERIALS 2005: ELECTROACTIVE POLYMER ACTUATORS AND DEVICES( EAPAD) SE Proceedings of SPIE LA English DT Proceedings Paper CT Smart Structures and Materials 2005 Conference CY MAR 07-10, 2005 CL San Diego, CA SP SPIE, Amer Soc Mech Engineers, Boeing Co, Journal Intelligent Mat Syst & Struct, Sage Publicat, Rhombus Consultants Grp, CSA Engn Inc, ISIS Canada, KAIST, Smart Infra Struct Technol Ctr DE biomimetics; biologically inspired technologies; robotics; EAP; electroactive polymers AB The evolution of nature led to the introduction of highly effective and power efficient biological mechanisms. Imitating these mechanisms offers enormous potentials for the improvement of our life and the tools we use. Humans have always made efforts to imitate nature and we are increasingly reaching levels of advancement that it becomes significantly easier to imitate, copy, and adapt biological methods, processes and systems. Advances in science and technology are leading to knowledge and capabilities that are multiplying every year. This brought us to act beyond the simple mimicking of nature. Having better tools to understand and to implement nature's principles we are now equipped like never before to be inspired by nature and to employ our tools in far superior ways. Effectively, by bio-inspiration we can have a better view and value of nature capability while studying its models to learn what can be extracted, copied or adapted. EAP as artificial muscles are adding an important element in the development of biologically inspired technologies. This paper reviews the various aspects of the field of biomimetics and the role that EAP play and the outlook for its evolution. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM yosi@jpl.nasa.gov NR 14 TC 6 Z9 6 U1 1 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 0-8194-5740-X J9 PROC SPIE PY 2005 VL 5759 BP 1 EP 8 DI 10.1117/12.597436 PG 8 WC Instruments & Instrumentation; Materials Science, Composites; Polymer Science SC Instruments & Instrumentation; Materials Science; Polymer Science GA BCN04 UT WOS:000230111000001 ER PT S AU Su, J Xu, TB AF Su, J Xu, TB BE Cohen, YB TI A modified electroactive polymer-ceramic hybrid actuation system (HYBAS) for aerodynamic control applications SO Smart Structures and Materials 2005: Electroactive Polymer Actuators and Devices( EAPAD) SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Smart Structures and Materials 2005 Conference CY MAR 07-10, 2005 CL San Diego, CA SP SPIE, Amer Soc Mech Engineers, Boeing Co, Journal Intelligent Mat Syst & Struct, Sage Publicat, Rhombus Consultants Grp, CSA Engn Inc, ISIS Canada, KAIST, Smart Infra Struct Technol Ctr DE hybrid actuation system; HYBAS; electroactive polymer; electroactive single crystal; and synthetic jet ID POLY(VINYLIDENE FLUORIDE-TRIFLUOROETHYLENE) COPOLYMER; ELECTROMECHANICAL PROPERTIES; ELECTROSTRICTION; PERFORMANCE AB As previously reported, a NASA Langley-developed electroactive polymer-ceramic hybrid system (HYBAS) has demonstrated significant enhancement in actuating displacement. The displacement of the system is derived from both the electrostrictive polymer and from single crystal elements. The electroactive elements are driven by a single power source. Recently, a modification of HYBAS has been made to increase the capability of air driving for synthetic jet devices (SJ) used in aerodynamic control technologies. The dependence of the air driving capability of the modified HYBAS on the configuration of the actuating device has been investigated. For this particular application, the modified HYBAS demonstrated a 50% increase in the volume change in the synthetic jet air chamber, as compared with that of the HYBAS without the modification. C1 NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Su, J (reprint author), NASA, Langley Res Ctr, Hampton, VA 23681 USA. 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 0-8194-5740-X J9 P SOC PHOTO-OPT INS PY 2005 VL 5759 BP 94 EP 101 DI 10.1117/12.600020 PG 8 WC Instruments & Instrumentation; Materials Science, Composites; Polymer Science SC Instruments & Instrumentation; Materials Science; Polymer Science GA BCN04 UT WOS:000230111000011 ER PT S AU Bao, XQ Bar-Cohen, Y Chang, ZS Sherrit, S Badescu, M AF Bao, XQ Bar-Cohen, Y Chang, ZS Sherrit, S Badescu, M BE Cohen, YB TI Wirelessly controllable inflated electroactive polymer (EAP) reflectors SO Smart Structures and Materials 2005: Electroactive Polymer Actuators and Devices( EAPAD) SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Smart Structures and Materials 2005 Conference CY MAR 07-10, 2005 CL San Diego, CA SP SPIE, Amer Soc Mech Engineers, Boeing Co, Journal Intelligent Mat Syst & Struct, Sage Publicat, Rhombus Consultants Grp, CSA Engn Inc, ISIS Canada, KAIST, Smart Infra Struct Technol Ctr DE electroactive polymer; EAP; inflatable membrane mirror; thin film antenna; controllable reflector ID ACTUATOR; MIRRORS; IPMC AB Inflatable membrane reflectors are attractive for deployable, large aperture, lightweight optical and microwave systems in micro-gravity space environment. However, any fabrication flaw or temperature variation may results in significant aberration of the surface. Even for a perfectly fabricated inflatable membrane mirror with uniform thickness, theory shows it will form a Hencky curve surface rather than the desired parabolic or spherical surface. Precision control of the surface shape of extremely flexible membrane structures is a critical challenge for the success of this technology. Wirelessly controllable inflated reflectors made of electroactive polymers (EAP) are proposed in this paper. A finite element model was configured to predict the behavior of the inflatable EAP membranes under pre-strains, pressures and distributed electric charges on the surface. To explore the controllability of the inflatable EAP reflectors, an iteration algorithm was developed to find the required applied electric field distribution for correcting the aberration of a Hencky curve to the desired parabolic curve. The correction capability of the reflectors with available EAP materials was explored numerically and is presented in this paper. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Bao, XQ (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 15 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 0-8194-5740-X J9 P SOC PHOTO-OPT INS PY 2005 VL 5759 BP 371 EP 378 DI 10.1117/12.599787 PG 8 WC Instruments & Instrumentation; Materials Science, Composites; Polymer Science SC Instruments & Instrumentation; Materials Science; Polymer Science GA BCN04 UT WOS:000230111000041 ER PT S AU Chang, ZS Sherrit, S Badescu, M Bao, XQ Bar-Cohen, Y AF Chang, ZS Sherrit, S Badescu, M Bao, XQ Bar-Cohen, Y BE White, EV TI Design and analysis of ultrasonic actuator in consideration of length-reduction for a USDC (Ultrasonic/Sonic Driller/Corer) SO Smart Structures and Materials 2005: Industrial and Commercial Applications of Smart Structures Technologies SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Smart Structures and Materials 2005 Conference CY MAR 07-10, 2005 CL San Diego, CA SP SPIE, Amer Soc Mech Engineers, Boeing Co, Journal Intelligent Mat Syst & Struct, Sage Publicat, Rhombus Consultants Grp, CSA Engn Inc, ISIS Canada, KAIST, Smart Infra Struct Technol Ctr DE ultrasonic/sonic driller/corer (USDC); ultrasonic horn; planetary exploration; piezoelectric devices AB Sample return and in-situ sampling and analysis is one of the major objectives of future NASA exploration missions. Existing drilling techniques are limited by the need for large axial forces, holding torques, and high power consumption. Lightweight robots and rovers have difficulties accommodating these requirements. To address these key challenges to the NASA objective of planetary in-situ rock sampling and analysis, a drilling technology called ultrasonic/sonic driller/corer (USDC) was developed. The USDC uses a novel driving mechanism, transferring ultrasonic vibration to sonic frequency impacts with the aid of a free-flying mass block (firee-mass). The free mass then drives the drill bit. The actuator consists of a stack of piezoelectric disks with a horn that amplifies the induced vibration amplitudes. The standard USDC is a slender device, and some times its length is too long for specific NASA missions. It is of current interest to have novel designs that reduce the length of the device. For this purpose, two novel horn designs were examined analytically. One is the flipped horn, the other is the planar folded horn. The new designs of the horn were analyzed using finite element modeling and the results allow for the determination of the control parameters that can optimize the performance of the ultrasonic horn in terms of the tip displacement and velocity. The results of the modeling are described and discussed in this paper. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Chang, ZS (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 4 TC 0 Z9 0 U1 2 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 0-8194-5743-4 J9 P SOC PHOTO-OPT INS PY 2005 VL 5762 BP 72 EP 79 DI 10.1117/12.598851 PG 8 WC Instruments & Instrumentation; Materials Science, Multidisciplinary SC Instruments & Instrumentation; Materials Science GA BCN14 UT WOS:000230112600009 ER PT S AU Bar-Cohen, Y Chang, Z Sherrit, S Badescu, M Bao, X AF Bar-Cohen, Y Chang, Z Sherrit, S Badescu, M Bao, X BE White, EV TI The Ultrasonic/Sonic Driller/Corer (USDC) as a subsurface drill, sampler and lab-on-a-drill for planetary exploration applications SO Smart Structures and Materials 2005: Industrial and Commercial Applications of Smart Structures Technologies SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Smart Structures and Materials 2005 Conference CY MAR 07-10, 2005 CL San Diego, CA SP SPIE, Amer Soc Mech Engineers, Boeing Co, Journal Intelligent Mat Syst & Struct, Sage Publicat, Rhombus Consultants Grp, CSA Engn Inc, ISIS Canada, KAIST, Smart Infra Struct Technol Ctr DE sampling; drilling; Ultrasonic/Sonic Driller/Corer (USDC); URAT; subsurface exploration AB The search for existing or past life in the Universe is one of the most important objectives of NASA's mission. For this purpose, effective instruments that can sample and conduct in-situ astrobiology analysis are being sought. In support of this objective, a novel Ultrasonic/Sonic Driller/Corer (USDC) based mechanism has been developed to probe and sample rocks, ice and soil. The USDC consists of an ultrasonic actuator that impacts a coring or drilling bit at sonic frequencies through the use of an intermediate free-mass. The USDC can produce both a core and powdered cuttings as well as emit elastic waves into the penetrated medium. For planetary exploration, this mechanism has the important advantage of requiring low axial force, virtually no torque, and can be duty cycled to require low average power. This low axial load advantage overcomes a major limitation of planetary sampling in low gravity environments and when operating from lightweight robots and rovers. The low average power operation produces a minimum temperature rise which is important for the acquisition of biologically meaningful samples. The development of the USDC is being pursued on various fronts ranging from analytical modeling to improvements of the mechanism while seeking a wide range of applications. In this paper, the latest status of the USDC development and applications that are underway is reviewed and discussed. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Bar-Cohen, Y (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. NR 1 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 0-8194-5743-4 J9 P SOC PHOTO-OPT INS PY 2005 VL 5762 BP 152 EP 159 DI 10.1117/12.599703 PG 8 WC Instruments & Instrumentation; Materials Science, Multidisciplinary SC Instruments & Instrumentation; Materials Science GA BCN14 UT WOS:000230112600017 ER PT S AU Badescu, M Bao, XQ Bar-Cohen, Y Chang, ZS Dabiri, BE Kennedy, B Sherrit, S AF Badescu, M Bao, XQ Bar-Cohen, Y Chang, ZS Dabiri, BE Kennedy, B Sherrit, S BE White, EV TI Adapting the ultrasonic/sonic driller/corer for walking/climbing robotic applications SO Smart Structures and Materials 2005: Industrial and Commercial Applications of Smart Structures Technologies SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Smart Structures and Materials 2005 Conference CY MAR 07-10, 2005 CL San Diego, CA SP SPIE, Amer Soc Mech Engineers, Boeing Co, Journal Intelligent Mat Syst & Struct, Sage Publicat, Rhombus Consultants Grp, CSA Engn Inc, ISIS Canada, KAIST, Smart Infra Struct Technol Ctr DE ultrasonic drilling; limbed robot; soil drill; piezoelectric devices AB Future NASA's missions include the search for past and existing life in the Universe and evidence on how the planets in the Solar system formed and evolved. In order to fulfill these goals sampling systems that meet the stringent requirements of the various environments are required to be developed. To support these objectives an ultrasonic/sonic driller/corer (USDC) device has been developed at Jet Propulsion Laboratory (JPL) to allow drilling and coring rocks for in-situ planetary analysis [Bar-Cohen et al, 2001]. The site location and method of sampling are of vital importance to scientists. Surface rocks abrasion, small depth soil drilling, and deep drilling have been proposed. It has been suggested that another possible source of mineralogical or astrobiological. information can be found by exploring the sidewall of canyons. The exploration of such sites requires the development of a limbed robotic system capable of walking and climbing slopes up to and including vertical faces and overhangs. An anchor/drilling mechanism is currently under development and is being installed on each leg of the four-legged Steep Terrain Access Robot (STAR). This paper presents the modeling, design, and preliminary testing results of the USDC for use as end-effectors of walking/climbing robots. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Badescu, M (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 11 TC 3 Z9 3 U1 0 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 0-8194-5743-4 J9 P SOC PHOTO-OPT INS PY 2005 VL 5762 BP 160 EP 168 DI 10.1117/12.598870 PG 9 WC Instruments & Instrumentation; Materials Science, Multidisciplinary SC Instruments & Instrumentation; Materials Science GA BCN14 UT WOS:000230112600018 ER PT S AU Bar-Cohen, Y Wu, JJ Olorunsola, AK Rivellini, TP Bley, S Wincentsen, J Gershman, R AF Bar-Cohen, Y Wu, JJ Olorunsola, AK Rivellini, TP Bley, S Wincentsen, J Gershman, R BE White, EV TI Simultaneous separation, seaming and sealing using brazing ((SB)-B-3) for sample containerization and planetary protection SO Smart Structures and Materials 2005: Industrial and Commercial Applications of Smart Structures Technologies SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Smart Structures and Materials 2005 Conference CY MAR 07-10, 2005 CL San Diego, CA SP SPIE, Amer Soc Mech Engineers, Boeing Co, Journal Intelligent Mat Syst & Struct, Sage Publicat, Rhombus Consultants Grp, CSA Engn Inc, ISIS Canada, KAIST, Smart Infra Struct Technol Ctr DE sample return; planetary exploration; simultaneous separation; seaming and sealing using brazing; containerization; planetary protection AB Any future NASA mission would require protection of our planet from the risk of possibly returning uncontrolled biological materials. For this purpose, it is necessary to contain the acquired samples and destroy any potential biological materials that may contaminate the external surface of the container while protecting the sample itself for further analysis. A novel method that allows simultaneous separation, seaming and sealing using brazing ((SB)-B-3) process for sample containerization and planetary protection has been conceived and demonstrated. A double wall container is used with clean inner-walls allowing brazing the container base (containing the sample) to its lid while separating it from the support mount and assuring its seal. The use of brazing materials that melt at temperatures that are higher than 500 degrees C assures sterilization of the exposed areas that can potentially be contaminated by biological materials from Mars and other planets. The results of this study and the issues that were identified to require attention will be described and discussed. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Bar-Cohen, Y (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 3 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 0-8194-5743-4 J9 P SOC PHOTO-OPT INS PY 2005 VL 5762 BP 261 EP 266 DI 10.1117/12.598921 PG 6 WC Instruments & Instrumentation; Materials Science, Multidisciplinary SC Instruments & Instrumentation; Materials Science GA BCN14 UT WOS:000230112600029 ER PT S AU Tai, H AF Tai, H BE Smith, RC TI Shape sensing a morphed wing with an optical fiber Bragg grating SO Smart Structures and Materials 2005: Modeling, Signal Processing, and Control SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Smart Structures and Materials 2005 Conference CY MAR 07-10, 2005 CL San Diego, CA SP SPIE, Amer Soc Mech Engineers, Boeing Co, Journal Intelligent Mat Syst & Struct, Sage Publicat, Rhombus Consultants Grp, CSA Engn Inc, ISIS Canada, KAIST, Smart Infra Struct Technol Ctr AB We suggest using distributed fiber Bragg sensors systems which were developed locally at Langley Research Center carefully placed on the wing surface to collect strain component information at each location. Then we used the fact that the rate change of slope in the definition of linear strain is very small and can be treated as a constant. Thereby the strain distribution information of a morphed surface can be reduced into a distribution of local slope information of a flat surface. In other words a morphed curve surface is replaced by the collection of individual flat surface of different slope. By assembling the height of individual flat surface, the morphed curved surface can be approximated. A more sophisticated graphic routine can be utilized to restore the curved morphed surface. With this information, the morphed wing can be further adjusted and controlled. A numerical demonstration is presented. C1 NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Tai, H (reprint author), NASA, Langley Res Ctr, Hampton, VA 23681 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 0-8194-5738-8 J9 P SOC PHOTO-OPT INS PY 2005 VL 5757 BP 239 EP 245 DI 10.1117/12.592764 PG 7 WC Automation & Control Systems; Instruments & Instrumentation; Materials Science, Composites SC Automation & Control Systems; Instruments & Instrumentation; Materials Science GA BCO39 UT WOS:000230407700022 ER PT S AU Choi, SH Kim, JW Chu, SH Park, Y King, GC Lillehei, PT Kim, SJ Elliott, JR AF Choi, SH Kim, JW Chu, SH Park, Y King, GC Lillehei, PT Kim, SJ Elliott, JR BE Varadan, VK TI Ferritin-templated quantum-dots for quantum logic gates SO SMART STRUCTURES AND MATERIALS 2005: SMART ELECTRONICS, MEMS, BIOMEMS, AND NANOTECHNOLOGY SE Proceedings of SPIE LA English DT Proceedings Paper CT Smart Structures and Materials 2005 Conference CY MAR 07-10, 2005 CL San Diego, CA SP SPIE, Amer Soc Mech Engineers, Boeing Co, Journal Intelligent Mat Syst & Struct, Sage Publicat, Rhombus Consultants Grp, CSA Engn Inc, ISIS Canada, KAIST, Smart Infra Struct Technol Ctr ID 2-IMINOTHIOLANE METHYL 4-MERCAPTOBUTYRIMIDATE; BIOMIMETIC SYNTHESIS; MAGNETIC PROTEINS; HORSE SPLEEN; MAGNETOFERRITIN; COMPUTATION; COMPUTERS; HARDWARE; OXIDE; CAGE AB Quantum logic gates (QLGs) or other logic systems are based on quantum-dots (QD) with a stringent requirement of size uniformity. The QD are widely known building units for QLGs. The size control of QD is a critical issue in quantum-dot fabrication. The work presented here offers a new method to develop quantum-dots using a bio-template, called ferritin, that ensures QD production in uniform size of nano-scale proportion. This technology is essential for NASA, Dol), and industrial nanotechnology applications such as: ultra-high density data storage, quantum electronic devices, biomedical nanorobots, molecular tagging, terahertz radiation sources, nanoelectromechanical systems (NEMS), etc. The bio-template for uniform yield of QD is based on a ferritin protein that allows reconstitution of core material through the reduction and chelation processes. By either the magnetic or electrical property of reconstituted core materials, the QD can be used for logic gates which are fundamental building blocks for quantum computing. However, QLGs are in an incubation stage and still have many potential obstacles that need to be addressed, such as an error collection, a decoherence, and a hardware architecture. One of the biggest challenges for developing QLG is the requirement of ordered and uniform size of QD for arrays on a substrate with nanometer precision. The other methods known so far, such as self-assembled QD grown in the Stranski-Krastanov mode, are usually randomly organized. The QD development by bio-template includes the electrochentical/chemical reconsitution of ferridris with different core materials, such as iron, cobalt, manganese, platinum, and nickel. The other bio-template method used in our laboratory is dendrimers, precisely defined chemical structures. With ferritin-templated QD, we fabricated the heptagon-shaped patterned array via direct nano manipulation of the ferritin molecules with a tip of atomic force microscope (AFM). We also designed various nanofabrication methods of QD arrays using a wide range manipulation techniques. The precise control of the ferritin-templated QD for a patterned arrangement are offered by various methods, such as a site-specific immobilization of thiolated ferritins through local oxidation using the AFM tip, ferritin arrays induced by gold nanoparticle manipulation, thiolated ferritin positioning by shaving method, etc. In the signal measurements, the current-voltage curve is obtained by measuring the current through the ferritin, between the tip and the substrate for potential sweeping or at constant potential. The measured resistance near zero bias was 1.8 teraohm for single holoferritin and 5.7 teraohm for single apoferritin, respectively. C1 NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP NASA, Langley Res Ctr, Hampton, VA 23681 USA. RI Kim, Jae-Woo/A-8314-2008 NR 35 TC 0 Z9 0 U1 0 U2 10 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 0-8194-5744-2 J9 PROC SPIE PY 2005 VL 5763 BP 213 EP 232 DI 10.1117/12.625319 PG 20 WC Engineering, Electrical & Electronic; Instruments & Instrumentation; Materials Science, Multidisciplinary SC Engineering; Instruments & Instrumentation; Materials Science GA BCN83 UT WOS:000230338300025 ER PT S AU Adamovsky, G Juergens, J Floyd, B AF Adamovsky, G Juergens, J Floyd, B BE Udd, E Inaudi, D TI Processing of signals from fiber Bragg gratings using unbalanced interferometers SO Smart Structures and Materials 2005: Smart Sensor Technology and Measurement Systems SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Smart Structures and Materials 2005 Conference CY MAR 07-10, 2005 CL San Diego, CA SP SPIE, Amer Soc Mech Engineers, Boeing Co, Journal Intelligent Mat Syst & Struct, Sage Publicat, Rhombus Consultants Grp, CSA Engn Inc, ISIS Canada, KAIST, Smart Infra Struct Technol Ctr DE Fiber Bragg gratings; temperature sensors; fiber optics; interferometer AB Fiber Bragg gratings (FBG) have become preferred sensory structures in fiber optic sensing system. High sensitivity, embedability, and multiplexing capabilities make FBGs superior to other sensor configurations. The main feature of FBGs is that they respond in the wavelength domain with the wavelength of the returned signal as the indicator of the measured parameter. The wavelength is then converted to optical intensity by a photodetector to detect corresponding changes in intensity. This wavelength-to-intensity conversion is a crucial part in any FBG-based sensing system. Among the various types of wavelength-to-intensity converters, unbalanced interferometers are especially attractive because of their small weight and volume, lack of moving parts, easy integration, and good stability. C1 NASA, Glenn Res Ctr Lewis Field, Brookpark, OH 44135 USA. RP Adamovsky, G (reprint author), NASA, Glenn Res Ctr Lewis Field, 21000 Brookpk Rd, Brookpark, OH 44135 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 0-8194-5739-6 J9 P SOC PHOTO-OPT INS PY 2005 VL 5758 BP 38 EP 45 DI 10.1117/12.601808 PG 8 WC Instruments & Instrumentation SC Instruments & Instrumentation GA BCO41 UT WOS:000230408200005 ER PT S AU Grant, J AF Grant, J BE Udd, E Inaudi, D TI Distributed sensing of composite over-wrapped pressure vessel using fiber Bragg gratings at ambient and cryogenic temperatures SO Smart Structures and Materials 2005: Smart Sensor Technology and Measurement Systems SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Smart Structures and Materials 2005 Conference CY MAR 07-10, 2005 CL San Diego, CA SP SPIE, Amer Soc Mech Engineers, Boeing Co, Journal Intelligent Mat Syst & Struct, Sage Publicat, Rhombus Consultants Grp, CSA Engn Inc, ISIS Canada, KAIST, Smart Infra Struct Technol Ctr DE Bragg sensor; carbon-epoxy; composite; embedded FBG; carbon composite overwrap pressure vessel ID SENSORS AB Fiber Bragg gratings are use to monitor the structural properties of composite pressure vessels. These gratings optically inscribed into the core of a single mode fiber are used as a tool to monitor the stress strain relation in laminate structure. The fiber Bragg sensors are both embedded within the composite laminates and bonded to the surface of the vessel with varying orientations with respect to the carbon fiber in the epoxy matrix. The response of these fiber-optic sensors is investigated by pressurizing the cylinder up to its burst pressure of around 2800 psi. This is done at both ambient and cryogenic temperatures using water and liquid nitrogen. The recorded response is compared with the response from conventional strain gauge also present on the vessel. Additionally, several vessels were tested that had been damaged to simulate different type of events, such as cut tow, delimitation and impact damage. C1 NASA, George C Marshall Space Flight Ctr, Huntsville, AL 35805 USA. RP Grant, J (reprint author), NASA, George C Marshall Space Flight Ctr, Huntsville, AL 35805 USA. NR 4 TC 3 Z9 3 U1 0 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 0-8194-5739-6 J9 P SOC PHOTO-OPT INS PY 2005 VL 5758 BP 201 EP 208 DI 10.1117/12.612060 PG 8 WC Instruments & Instrumentation SC Instruments & Instrumentation GA BCO41 UT WOS:000230408200022 ER PT S AU Bar-Cohen, Y Lih, SS Bao, XQ Sherrit, S AF Bar-Cohen, Y Lih, SS Bao, XQ Sherrit, S BE Udd, E Inaudi, D TI Ferroelectric base multiple radiations source for in-situ multifunctional analytical instruments SO Smart Structures and Materials 2005: Smart Sensor Technology and Measurement Systems SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Smart Structures and Materials 2005 Conference CY MAR 07-10, 2005 CL San Diego, CA SP SPIE, Amer Soc Mech Engineers, Boeing Co, Journal Intelligent Mat Syst & Struct, Sage Publicat, Rhombus Consultants Grp, CSA Engn Inc, ISIS Canada, KAIST, Smart Infra Struct Technol Ctr DE ferrosource; multiple radiation type; planetary exploration; X-ray AB A ferroelectric based multiple radiation source is being developed and tested at JPL. This device has the potential to emit five radiation types enabling a new generation of compact, low power, low mass in-situ analysis instruments. These radiation types include visible light, ultraviolet, X-ray, as well as electron and ion beams. These types of emitted radiation can support multiple instruments that may potentially be used in future NASA missions to detect water, perform mineralogical/chemistry analysis and identify biological signatures. The source consists of a ferroelectric wafer having a continuous ground electrode on one side and a grid-shaped cathode on the other side. This source is placed in a vacuum tube and is used to generate plasma by switching high voltage pulses. A series of experiments were performed to evaluate the characteristics of the generated radiation and the results are described and discussed in this paper. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Bar-Cohen, Y (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 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 0-8194-5739-6 J9 P SOC PHOTO-OPT INS PY 2005 VL 5758 BP 356 EP 361 DI 10.1117/12.598930 PG 6 WC Instruments & Instrumentation SC Instruments & Instrumentation GA BCO41 UT WOS:000230408200038 ER PT S AU Sherrit, S Badescu, M Bao, XQ Bar-Cohen, Y Chang, ZS AF Sherrit, S Badescu, M Bao, XQ Bar-Cohen, Y Chang, ZS BE Udd, E Inaudi, D TI Efficient electromechanical network models for wireless acoustic-electric feed-throughs SO Smart Structures and Materials 2005: Smart Sensor Technology and Measurement Systems SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Smart Structures and Materials 2005 Conference CY MAR 07-10, 2005 CL San Diego, CA SP SPIE, Amer Soc Mech Engineers, Boeing Co, Journal Intelligent Mat Syst & Struct, Sage Publicat, Rhombus Consultants Grp, CSA Engn Inc, ISIS Canada, KAIST, Smart Infra Struct Technol Ctr DE ultrasonic; bulk acoustic waves; power conversion; isolation; pressure vessels ID PIEZOELECTRIC TRANSDUCERS; PERFORMANCE; CERAMICS AB There are numerous engineering design problems where the use of wires to transfer power and communicate data thru the walls of a structure is prohibitive or significantly difficult that it may require a complex design. Such systems may be concerned with the leakage of chemicals or gasses, loss of pressure or vacuum, as well as difficulties in providing adequate thermal or electrical insulation. Moreover, feeding wires thru a wall of a structure reduces the strength of the structure and makes the structure susceptibility to cracking due to fatigue that can result from cyclic loading. Two areas have already been identified to require a wireless alternative capability and they include (a) the container of the Mars Sample Return Mission will need the use of wireless sensors to sense pressure leak and to avoid potential contamination; and (b) the Navy is seeking the capability to communicate with the crew or the instrumentation inside marine structures without the use of wires that will weaken the structure. The idea of using elastic or acoustic waves to transfer power was suggested recently by Y.Hu,eta1.(1). However, the disclosed model was developed directly from the wave equation and the linear equations of piezoelectricity. This model restricted by an inability to incorporate head and tail mass and account for loss in all the mechanisms. In addition there is no mechanism for connecting the model to actual power processing circuitry (diode bridge, capacitors, rectifiers etc.). An alternative approach which is to be presented is a network equivalent circuit that can easily be modified to account for additional acoustic elements and connected directly to other networks or circuits. All the possible loss mechanisms of the disclosed solution can be accounted for and introduced into the model. The circuit model allows for both power and data transmission in the forward and reverse directions through acoustic signals at the harmonic and higher order resonances. This system allows or the avoidance of cabling or wiring. The technology is applicable to the transfer of power for actuation, sensing and other tasks inside sealed containers and vacuum/pressure vessels. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. RP Sherrit, S (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91125 USA. NR 11 TC 15 Z9 17 U1 0 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 0-8194-5739-6 J9 P SOC PHOTO-OPT INS PY 2005 VL 5758 BP 362 EP 372 DI 10.1117/12.598300 PG 11 WC Instruments & Instrumentation SC Instruments & Instrumentation GA BCO41 UT WOS:000230408200039 ER PT S AU Ott, MN AF Ott, MN BE Udd, E Inaudi, D TI Validation of commercial fiber optic components for aerospace environments SO Smart Structures and Materials 2005: Smart Sensor Technology and Measurement Systems SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Smart Structures and Materials 2005 Conference CY MAR 07-10, 2005 CL San Diego, CA SP SPIE, Amer Soc Mech Engineers, Boeing Co, Journal Intelligent Mat Syst & Struct, Sage Publicat, Rhombus Consultants Grp, CSA Engn Inc, ISIS Canada, KAIST, Smart Infra Struct Technol Ctr DE components; environmental; space; flight; qualification; photonic; fiber; optic; radiation ID LASER ALTIMETER AB Full qualification for commercial photonic parts as defined by the Military specification system in the past, is not feasible. Due to changes in the photonic components industry and the Military specification system that NASA had relied upon so heavily in the past, an approach to technology validation of commercial off the shelf parts had to be devised. This approach involves knowledge of system requirements, environmental requirements and failure modes of the particular components under consideration. Synthesizing the criteria together with the major known failure modes to formulate a test plan is an effective way of establishing knowledge based "qualification". Although this does not provide the type of reliability assurance that the Military specification system did in the past, it is an approach that allows for increased risk mitigation. The information presented will introduce the audience to the technology validation approach that is currently applied at NASA for the usage of commercial-off-the-shelf (COTS) fiber optic components for space flight environments. The focus will be on how to establish technology validation criteria for commercial fiber products such that continued reliable performance is assured under the harsh environmental conditions of typical missions. The goal of this presentation is to provide the audience with an approach to formulating a COTS qualification test plan for these devices. Examples from past NASA missions will be discussed. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Ott, MN (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. NR 21 TC 5 Z9 5 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 0-8194-5739-6 J9 P SOC PHOTO-OPT INS PY 2005 VL 5758 BP 427 EP 439 DI 10.1117/12.606846 PG 13 WC Instruments & Instrumentation SC Instruments & Instrumentation GA BCO41 UT WOS:000230408200046 ER PT S AU Badescu, M Bao, XQ Bar-Cohen, Y Chang, ZS Sherrit, S AF Badescu, M Bao, XQ Bar-Cohen, Y Chang, ZS Sherrit, S BE Flatou, AB TI Integrated modeling of the ultrasonic/sonic drill/corer - Procedure and analysis results SO SMART STRUCTURES AND MATERIALS 2005: SMART STRUCTURES AND INTEGRATED SYSTEMS SE Proceedings of SPIE LA English DT Proceedings Paper CT Smart Structures and Materials 2005 Conference CY MAR 07-10, 2005 CL San Diego, CA SP SPIE, Amer Soc Mech Engineers, Boeing Co, Journal Intelligent Mat Syst & Struct, Sage Publicat, Rhombus Consultants Grp, CSA Engn Inc, ISIS Canada, KAIST, Smart Infra Struct Technol Ctr DE ultrasonic horn; ultrasonic drilling; soil drill; piezoelectric devices AB Rock and soil penetration by coring, drilling or abrading is of great importance for a large number of space and earth applications. An Ultrasonic/Sonic Drill/Corer (USDC) has been developed as an adaptable toot for many of these applications [Bar-Cohen et al, 2001]. The USDC uses a novel drive mechanism to transform the ultrasonic or sonic vibrations of the tip of a horn into a sonic hammering of a drill bit through an intermediate free-flying mass. As the pace of adapting the USDC to various applications has increased, it has become more critical to develop a efficient simulation tool to predict the performance of various designs. A series of computer programs that model the function and performance of the USDC device were previously developed and tested against experimental data [Bao et al, 2003]. The combination of these programs into an integrated modeling package and the analysis of simulated results will be described in this paper. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Badescu, M (reprint author), CALTECH, Jet Prop Lab, MS 67-119,4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Mircea.Badescu@jpl.nasa.gov NR 6 TC 1 Z9 1 U1 0 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 0-8194-5745-0 J9 PROC SPIE PY 2005 VL 5764 BP 312 EP 323 DI 10.1117/12.598886 PG 12 WC Instruments & Instrumentation; Materials Science, Multidisciplinary SC Instruments & Instrumentation; Materials Science GA BCN84 UT WOS:000230338800031 ER PT S AU Harra, LK Kankelborg, CC Thomas, RJ Fox, JL Winter, B AF Harra, LK Kankelborg, CC Thomas, RJ Fox, JL Winter, B BE Harra, LK Culhane, JL Harruson, RA TI An imager with added value for the Solar Orbiter mission SO SOLAR ENCOUNTER, SOLAR-B AND STEREO SE ADVANCES IN SPACE RESEARCH-SERIES LA English DT Article; Proceedings Paper CT 35th COSPAR Scientific Assembly CY JUL 18-25, 2004 CL Paris, FRANCE SP Comm Space Res DE solar physics; spectroscopy; imaging AB Our current ways of observing the Sun with spectrometers and imagers are limited. With a slit spectrometer, we require time to build Lip a 2-D image which results in temporal blurring. When we use a traditional imager, we have no ability to measure and detect line-of-sight flows or to discriminate contributions from gas at different temperatures in the imager passband, causing spectral confusion of the images. For Solar Orbiter, the combination of an exciting new viewpoint of the Sun, and the best resolution of the corona ever seen, means that we require the best time cadence and velocity information that we can get. The spatial resolution expected from the imager on Solar Orbiter will reach approximately 70 km. At such a resolution in the corona, we expect to see the fundamental magnetic flux tubes, which are predicted to have high velocities. This is also the scale at which we will be able to search for evidence basic physical processes such as magnetic reconnection. We will describe the design of an imager that gives not only high quality images, but also provides simultaneous information about plasma flows and temperature. A prototype instrument is being flown on a NASA sounding rocket next year. The concept will be described, along with some methods of extracting the spectroscopic information. (c) 2005 Published by Elsevier Ltd on behalf of COSPAR. C1 UCL, Mullard Space Sci Lab, Dorking RH5 6NT, Surrey, England. Montana State Univ, Bozeman, MT 59717 USA. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP UCL, Mullard Space Sci Lab, Holmbury St Mary, Dorking RH5 6NT, Surrey, England. EM lkh@mssl.ucl.ac.uk OI Harra, Louise/0000-0001-9457-6200 NR 3 TC 2 Z9 2 U1 0 U2 0 PU ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD 0X5 1GB, OXON, ENGLAND SN 0273-1177 J9 ADV SPACE RES-SERIES PY 2005 VL 36 IS 8 SI 2005 BP 1422 EP 1425 DI 10.1016/j.asr.2005.02.080 PG 4 WC Engineering, Aerospace; Astronomy & Astrophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Engineering; Astronomy & Astrophysics; Geology; Meteorology & Atmospheric Sciences GA BEC66 UT WOS:000236807600009 ER PT S AU Kaiser, ML AF Kaiser, ML BE Harra, LK Culhane, JL Harruson, RA TI The STEREO mission: an overview SO SOLAR ENCOUNTER, SOLAR-B AND STEREO SE ADVANCES IN SPACE RESEARCH LA English DT Article; Proceedings Paper CT 35th COSPAR Scientific Assembly CY JUL 18-25, 2004 CL Paris, FRANCE SP Comm Space Res DE solar; STEREO, space weather AB In February 2006, NASA will launch the twin STEREO spacecraft from Kennedy Space Center aboard a Delta 7925 launch vehicle. After a series of highly eccentric Earth orbits with apogees beyond the moon, each spacecraft will use close flybys of the moon to escape into heliocentric orbits at 1 AU, with one spacecraft trailing Earth and the other leading Earth. As viewed from the Still, the two spacecraft will separate at approximately 45 degrees per year. The purposes of the STEREO Mission are to understand the causes and mechanisms of coronal mass ejection initiation and to follow the propagation of CMEs through the heliosphere. Additionally, STEREO will study the mechanisms and sites of energetic particle acceleration and develop 3D time-dependent models of the magnetic topology, temperature, density and velocity of the solar wind between the Sun and Earth. To accomplish these goals, each STEREO spacecraft will be equipped with a set of optical, radio and in situ particles and fields instruments. The SEC-CHI suite of instruments includes two white light coronagraphs covering the range from 1.4 to 15 solar radii, an extreme ultra violet imager covering the chromosphere and inner corona, and two heliospheric white light imagers covering the outer corona from 12 solar radii to I AU. The IMPACT suite of instruments will measure in situ solar wind electrons in the energy range from essentially 0 to 100 keV, energetic electrons to 6 MeV, and protons and heavier ions to 100 MeV/nucleon. IMPACT also contains a magnetometer to measure the in situ magnetic field strength and direction. The PLASTIC instrument will measure the composition of heavy ions as well as protons and alpha particles. The SWAVES instrument will use radio waves to track the location of CME-driven shocks and the 3D topology of open field lines along which energetic particles flow. Additionally, SWAVES will measure in situ plasma waves to provide an independent estimate of the local plasma density and temperature. Each of the four instruments will produce a small real-time stream of selected data for purposes of predicting space weather events at Earth, primarily for NOAA forecasters. In addition to the four instrument teams, there will be substantial participation by modeling and theory oriented teams. All STEREO data will be freely available through individual Web sites at the four Principal Investigator institutions as well as at the STEREO Science Center located at NASA Goddard Space Flight Center. (c) 2005 Published by Elsevier Ltd on behalf of COSPAR. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Kaiser, ML (reprint author), NASA, Goddard Space Flight Ctr, Code 695, Greenbelt, MD 20771 USA. EM michael.kaiser@nasa.gov NR 0 TC 87 Z9 88 U1 0 U2 1 PU ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD 0X5 1GB, OXON, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2005 VL 36 IS 8 SI 2005 BP 1483 EP 1488 DI 10.1016/j.asr.2004.12.066 PG 6 WC Engineering, Aerospace; Astronomy & Astrophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Engineering; Astronomy & Astrophysics; Geology; Meteorology & Atmospheric Sciences GA BEC66 UT WOS:000236807600020 ER PT S AU Rucker, HO Macher, W Fischer, G Oswald, T Bougeret, JL Kaiser, ML Goetz, K AF Rucker, HO Macher, W Fischer, G Oswald, T Bougeret, JL Kaiser, ML Goetz, K BE Harra, LK Culhane, JL Harruson, RA TI Analysis of spacecraft antenna systems: Implications for STEREO/WAVES SO SOLAR ENCOUNTER, SOLAR-B AND STEREO SE ADVANCES IN SPACE RESEARCH LA English DT Article; Proceedings Paper CT 35th COSPAR Scientific Assembly CY JUL 18-25, 2004 CL Paris, FRANCE SP Comm Space Res DE STEREO/WAVES experiment; antenna system calibration; effective length vector determination AB The STEREO/WAVES experiment is considered to provide measurements of the non-thermal radio spectrum from a few kHz up to about 16 MHz, performed by three 6-m long orthogonal monopole antennas and a set of receivers (fixed-, high-, and low frequency receiver). This system performs real-time calculation of antenna voltage coherence products and, then, enables the determination of direction of arrival and polarization state of incident radio waves. Analysis of such kind of antenna system is necessary in order to define the reception properties which crucially depend on the overall spacecraft configuration. The concept of effective length vector (h(eff)) determination is applied to yield corresponding information on the deviation of h(eff) from the physical rods, in dependence of frequency. Various methods are evaluated (rheometry for frequencies up to 1 MHz), wire-grid modelling and in-flight calibration, and their implication to the SWAVES experiment are discussed. (c) 2005 Published by Elsevier Ltd on behalf of COSPAR. C1 Austrian Acad Sci, Space Res Inst, Dept Extraterr Phys, A-8010 Graz, Austria. Observ Paris, DESPA, F-92195 Meudon, France. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Univ Minnesota, Sch Phys & Astron, Minneapolis, MN 55455 USA. RP Rucker, HO (reprint author), Austrian Acad Sci, Space Res Inst, Dept Extraterr Phys, Schmedlstr 6, A-8010 Graz, Austria. EM rucker@oeaw.ac.at NR 6 TC 11 Z9 11 U1 0 U2 0 PU ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD 0X5 1GB, OXON, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2005 VL 36 IS 8 SI 2005 BP 1530 EP 1533 DI 10.1016/j.asr.2005.07.060 PG 4 WC Engineering, Aerospace; Astronomy & Astrophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Engineering; Astronomy & Astrophysics; Geology; Meteorology & Atmospheric Sciences GA BEC66 UT WOS:000236807600026 ER PT S AU Luhmann, JG Curtis, DW Lin, RP Larson, D Schroeder, P Cummings, A Mewaldt, RA Stone, EC Davis, A von Rosenvinge, T Acuna, MH Rearnes, D Ng, C Ogilvie, K Mueller-Mellin, R Kunow, H Mason, GM Wiedenbeck, M Sauvaud, A Aoustin, C Louarn, P Dandouras, J Korth, A Bothmer, V Vasyliunas, V Sanderson, T Marsden, RG Russell, CT Gosling, JT Bougeret, JL McComas, DJ Linker, JA Riley, P Odstrcil, D Pizzo, VJ Gombosi, T DeZeeuw, D Gombosi, T DeZeeuw, D Kecskemety, K AF Luhmann, JG Curtis, DW Lin, RP Larson, D Schroeder, P Cummings, A Mewaldt, RA Stone, EC Davis, A von Rosenvinge, T Acuna, MH Rearnes, D Ng, C Ogilvie, K Mueller-Mellin, R Kunow, H Mason, GM Wiedenbeck, M Sauvaud, A Aoustin, C Louarn, P Dandouras, J Korth, A Bothmer, V Vasyliunas, V Sanderson, T Marsden, RG Russell, CT Gosling, JT Bougeret, JL McComas, DJ Linker, JA Riley, P Odstrcil, D Pizzo, VJ Gombosi, T DeZeeuw, D Gombosi, T DeZeeuw, D Kecskemety, K BE Harra, LK Culhane, JL Harruson, RA TI IMPACT: Science goals and firsts with STEREO SO SOLAR ENCOUNTER, SOLAR-B AND STEREO SE ADVANCES IN SPACE RESEARCH LA English DT Article; Proceedings Paper CT 35th COSPAR Scientific Assembly CY JUL 18-25, 2004 CL Paris, FRANCE SP Comm Space Res DE STEREO; coronal mass ejections; space weather; solar activity; space missions ID CORONAL MASS EJECTIONS; SOLAR ENERGETIC PARTICLES; INTERPLANETARY SHOCKS; MAGNETIC CLOUDS; ACCELERATION; TOPOLOGY; HELIOS-1; EVENTS; MODEL; WIND AB The in situ measurements of particles and CME transients (I M PACT) investigation on the twin STEREO spacecraft focuses oil the solar energetic particle, solar wind and suprathermal electron, and magnetic field measurements needed to address STEREO's goals. IMPACT will provide regular, identical, in situ multipoint measurements bracketing Earth as each spacecraft separates from it at a rate of similar to 22 degrees/yr along Earth's orbit. Combined with the PLASTIC and SWAVES investigations, IMPACT fills a critical role in the STEREO quest to connect SECCHI's 3D coronal images to their interplanetary consequences. (c) 2005 COSPAR. Published by Elsevier Ltd. All rights reserved. C1 Univ Calif Berkeley, Space Sci Lab, Berkeley, CA 94720 USA. CALTECH, Pasadena, CA 91125 USA. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Univ Kiel, Inst Expt & Angew Phys, D-24118 Kiel, Germany. Univ Maryland, Dept Phys, College Pk, MD 20742 USA. Univ Maryland, IPST, College Pk, MD 20742 USA. Jet Prop Lab, Pasadena, CA 91109 USA. Univ Toulouse 3, CNRS, Ctr Etud Spatiale Rayonnements, F-31028 Toulouse 4, France. Max Planck Inst Solar Syst Res, D-37191 Katlenburg Duhm, Germany. European Space Agcy, Estec, NL-2200 AG Noordwijk, Netherlands. Univ Calif Los Angeles, Inst Geophys & Planetary Phys, Los Angeles, CA 90095 USA. Los Alamos Natl Lab, Los Alamos, NM 87545 USA. Observ Paris, F-92195 Meudon, France. SW Res Inst, Space Sci & Engn Div, San Antonio, TX 78228 USA. Sci Applicat Int Corp, San Diego, CA 92121 USA. Univ Colorado, CIRES, Boulder, CO 80305 USA. NOAA, Space Environm Ctr, Boulder, CO 80305 USA. Univ Michigan, Space Phys Res Lab, Dept Atmospher Ocean & Space Sci, Ann Arbor, MI 48109 USA. KFKI Res Inst Part & Nucl Phys, H-1525 Budapest, Hungary. RP Luhmann, JG (reprint author), Univ Calif Berkeley, Space Sci Lab, Grizzly Peak Blvd,Centennial Dr, Berkeley, CA 94720 USA. EM jgluhmann@ssl.berkeley.edu RI De Zeeuw, Darren/F-3667-2011; Gombosi, Tamas/G-4238-2011; OI Gombosi, Tamas/0000-0001-9360-4951; Dandouras, Iannis/0000-0002-7121-1118; Russell, Christopher/0000-0003-1639-8298 NR 29 TC 16 Z9 16 U1 0 U2 0 PU ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD 0X5 1GB, OXON, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2005 VL 36 IS 8 SI 2005 BP 1534 EP 1543 DI 10.1016/j.asr.2005.03.033 PG 10 WC Engineering, Aerospace; Astronomy & Astrophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Engineering; Astronomy & Astrophysics; Geology; Meteorology & Atmospheric Sciences GA BEC66 UT WOS:000236807600027 ER PT S AU Blush, LM Allegrini, F Bochsler, P Daoudi, H Galvin, A Karrer, R Kistler, L Klecker, B Mobius, E Opitz, A Popecki, M Thompson, B Wimmer-Schweingruber, RF Wurz, P AF Blush, LM Allegrini, F Bochsler, P Daoudi, H Galvin, A Karrer, R Kistler, L Klecker, B Mobius, E Opitz, A Popecki, M Thompson, B Wimmer-Schweingruber, RF Wurz, P BE Harra, LK Culhane, JL Harruson, RA TI Development and calibration of major components for the STEREO/PLASTIC (plasma and suprathermal ion composition) instrument SO SOLAR ENCOUNTER, SOLAR-B AND STEREO SE ADVANCES IN SPACE RESEARCH LA English DT Article; Proceedings Paper CT 35th COSPAR Scientific Assembly CY JUL 18-25, 2004 CL Paris, FRANCE SP Comm Space Res DE solar wind; in situ instrumentation; mass spectrometry; electrostatic energy analyzer; ion energy measurement; solid-state detector ID MASS SPECTROMETERS; SYSTEM AB The plasma and suprathermal ion composition (PLASTIC) instrument will measure kinetic properties and charge states of solar wind ions and suprathermal ions as part of the solar terrestrial relations observatory (STEREO) mission. Two identical instruments located on separate spacecraft will provide in situ plasma measurements at similar to 1 AU to study physical processes low in the corona and in the inner heliosphere. In conjunction with the other in situ and remote sensing instruments of STEREO, as well as existing near-Earth observatories, the PLASTIC instrument measurements will contribute to the understanding of the three-dimensional structure of the heliosphere, with particular focus on Coronal Mass Ejections. As the primary solar wind instrument aboard STEREO, PLASTIC will measure bulk solar wind plasma parameters (density, velocity, temperature, temperature anisotropy, and alpha/proton ratio) and the distribution functions and charge state distributions of major heavy solar wind ions (e.g., C, O, Ne, Mg, Si, Fe) The measurement apparatus includes an electrostatic deflection analyzer for energy per charge measurement (E/q), a time-of-flight section utilizing carbon foils and microchannel plate detectors for time of flight measurement (TOF), and solid-state detectors for energy measurement (E). The instrument will provide a large instantaneous field of view (in-ecliptic and out-of-ecliptic angles distinguished) with measurements taken at high time resolution (1-5 min) spanning an ion energy range of 0.25-87 keV/e. To accommodate a large range of particle fluxes, the PLASTIC Entrance System employs collection apertures with different geometric factors for the bulk solar wind (H similar to 96%, He similar to 4%) and for the heavy, less-abundant ions (< 1) and suprathermal ions. This paper focuses on the hardware development of major components for the PLASTIC instrument The PLASTIC measurement principle is explained along with a presentation of the ion optic calibrations of the flight model Entrance Systems as well as calibrations of the microchannel plates and solid-state detectors. (c) 2005 Published by Elsevier Ltd on behalf of COSPAR. C1 Univ Bern, Inst Phys, CH-3012 Bern, Switzerland. Univ New Hampshire, Ctr Space Sci, Durham, NH 03824 USA. Max Planck Inst Extraterr Phys, D-85741 Garching, Germany. Univ Kiel, Inst Expt & Angew Phys, D-24118 Kiel, Germany. Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Blush, LM (reprint author), Univ Bern, Inst Phys, Sidlerstr 5, CH-3012 Bern, Switzerland. EM lblush@phim.unibe.ch RI Galvin, Antoinette/A-6114-2013; Thompson, Barbara/C-9429-2012; OI Moebius, Eberhard/0000-0002-2745-6978 NR 12 TC 6 Z9 6 U1 0 U2 0 PU ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD 0X5 1GB, OXON, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2005 VL 36 IS 8 SI 2005 BP 1544 EP 1556 DI 10.1016/j.asr.2005.07.028 PG 13 WC Engineering, Aerospace; Astronomy & Astrophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Engineering; Astronomy & Astrophysics; Geology; Meteorology & Atmospheric Sciences GA BEC66 UT WOS:000236807600028 ER PT S AU Haugan, SVH AF Haugan, SVH BE Harra, LK Culhane, JL Harruson, RA TI Coordinating with SOHO SO SOLAR ENCOUNTER, SOLAR-B AND STEREO SE ADVANCES IN SPACE RESEARCH LA English DT Article; Proceedings Paper CT 35th COSPAR Scientific Assembly CY JUL 18-25, 2004 CL Paris, FRANCE SP Comm Space Res DE SOHO; coordinated observations; technical constraints; scheduling constraints AB I describe how to maximise the chances of achieving a successful coordinated observation campaign together with SOHO instruments (and TRACE). The ground rules, common pitfalls, useful resources and some essential "tricks of the trade" are covered. The most important hints are: start early, make contact with the instrument teams and the SOCs (soc@soc.nascom.nasa.gov), ask whenever in doubt, check the calendar, and be specific. (c) 2004 COSPAR. Published by Elsevier Ltd. All rights reserved. C1 ESA, GSFC, RSSD, Greenbelt, MD 20771 USA. RP Haugan, SVH (reprint author), ESA, GSFC, RSSD, Mail Code 682-3,SOHO EAF, Greenbelt, MD 20771 USA. EM soc@soc.nascom.nasa.gov NR 1 TC 0 Z9 0 U1 0 U2 0 PU ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD 0X5 1GB, OXON, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2005 VL 36 IS 8 SI 2005 BP 1557 EP 1560 DI 10.1016/j.asr.2004.12.021 PG 4 WC Engineering, Aerospace; Astronomy & Astrophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Engineering; Astronomy & Astrophysics; Geology; Meteorology & Atmospheric Sciences GA BEC66 UT WOS:000236807600029 ER PT S AU Ofman, L AF Ofman, L BE Harra, LK Culhane, JL Harruson, RA TI Three dimensional MHD models of active region loops SO SOLAR ENCOUNTER, SOLAR-B AND STEREO SE ADVANCES IN SPACE RESEARCH LA English DT Article; Proceedings Paper CT 35th COSPAR Scientific Assembly CY JUL 18-25, 2004 CL Paris, FRANCE SP Comm Space Res DE solar corona; STEREO spacecraft; coronal loops; coronal active regions; MHD; waves; numerical simulation studies ID CORONAL LOOPS; TRANSVERSE OSCILLATIONS; RESONANT ABSORPTION; TRANSITION-REGION; ALFVEN WAVES; EIT WAVES; TRACE; PARAMETERS; EXPLORER; SUMER AB Present imaging and spectroscopic observations of active region loops allow to determine many physical parameters of the coronal loops, such as the density, temperature, velocity of flows in loops, and the magnetic field. However, due to projection effects many of these parameters remain ambiguous. Three dimensional (3D) imaging in EUV by the STEREO spacecraft will help to resolve the projection ambiguities, and the observations could be used to setup 3D MHD models of active region loops to study the dynamics and stability of active regions. Here the results of 3D MHD models of active region loops, and the progress towards more realistic 3D MHD models of active regions are presented. In particular the effects of impulsive events on the excitation of active region loop oscillations, and the generation, propagations and reflection of EIT waves are shown. It is demonstrated how 3D MHD models together with 3D EUV observations can be used as a diagnostic tool for active region loop physical parameters, and to advance the science of the sources of solar coronal activity. (c) 2005 COSPAR. Published by Elsevier Ltd. All rights reserved. C1 Catholic Univ Amer, NASA, Goddard Space Flight Ctr, Dept Phys, Greenbelt, MD 20771 USA. RP Ofman, L (reprint author), Catholic Univ Amer, NASA, Goddard Space Flight Ctr, Dept Phys, Code 682, Greenbelt, MD 20771 USA. EM ofman@waves.gsfc.nasa.gov NR 28 TC 22 Z9 22 U1 0 U2 1 PU ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD 0X5 1GB, OXON, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2005 VL 36 IS 8 SI 2005 BP 1572 EP 1578 DI 10.1016/j.asr.2004.12.068 PG 7 WC Engineering, Aerospace; Astronomy & Astrophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Engineering; Astronomy & Astrophysics; Geology; Meteorology & Atmospheric Sciences GA BEC66 UT WOS:000236807600031 ER PT S AU Jensen, EA Bird, MK Asmar, SW Iess, L Anderson, JD Russell, CT AF Jensen, EA Bird, MK Asmar, SW Iess, L Anderson, JD Russell, CT BE Harra, LK Culhane, JL Harruson, RA TI The Cassini solar Faraday rotation experiment SO SOLAR ENCOUNTER, SOLAR-B AND STEREO SE ADVANCES IN SPACE RESEARCH LA English DT Article; Proceedings Paper CT 35th COSPAR Scientific Assembly CY JUL 18-25, 2004 CL Paris, FRANCE SP Comm Space Res DE coronal magnetic field; Faraday rotation; Cassini; X-band; K-band ID MAGNETIC FIELDS AB The Cassini Faraday rotation experiment improves the current understanding of the coronal magnetic field by making the first measurements of the magnetic field within two solar radii of the south pole and by allowing the separation of the changing electron density from the magnetic field during transient crossings of the line of sight. Simultaneous ranging data to Cassini also contributes to the growing body of empirical electron density models by providing electron density data at solar maximum at varying latitudes including over the poles. Faraday rotation data in the solar corona were collected in 2002 and 2003 using the Cassini spacecraft in cruise to Saturn. Although Cassini primarily transmits in right-hand polarization, enough left-hand is produced to enable polarization measurements. We show that during solar conjunction Faraday rotation is measurable with Cassini. In the X- and Ka-bands both datasets currently show an asymmetric diurnal pattern in polarization not associated with the ionosphere. The Ka-band is much more sensitive to pointing accuracy and experienced periods of power drop outs which caused the left-circularly polarized signal to drop into the noise on occasion during the 2003 conjunction. Interpretation of the dataset is deferred to future papers. (c) 2005 COSPAR. Published by Elsevier Ltd. All rights reserved. C1 Univ Calif Los Angeles, Inst Geophys & Planetary Phys, IGPP, ESS, Los Angeles, CA 90095 USA. Univ Bonn, Radio Astron Inst, D-53121 Bonn, Germany. Jet Prop Lab, Pasadena, CA 91109 USA. Univ Roma La Sapienza, IAA Dept, I-00184 Rome, Italy. RP Russell, CT (reprint author), Univ Calif Los Angeles, Inst Geophys & Planetary Phys, IGPP, ESS, 603 Charles Young Dr E,3845 Shchter Hall, Los Angeles, CA 90095 USA. EM nina@igpp.ucla.edu RI IESS, Luciano/F-4902-2011; OI IESS, Luciano/0000-0002-6230-5825; Russell, Christopher/0000-0003-1639-8298 NR 12 TC 11 Z9 11 U1 0 U2 0 PU ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD 0X5 1GB, OXON, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2005 VL 36 IS 8 SI 2005 BP 1587 EP 1594 DI 10.1016/j.asr.2005.09.039 PG 8 WC Engineering, Aerospace; Astronomy & Astrophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Engineering; Astronomy & Astrophysics; Geology; Meteorology & Atmospheric Sciences GA BEC66 UT WOS:000236807600033 ER PT B AU Fleck, B AF Fleck, B BE Hanslmeier, A Veronig, A Messerotti, M TI Eight years of Soho: Some highlights SO Solar Magnetic Phenomena SE ASTROPHYSICS AND SPACE SCIENCE LIBRARY LA English DT Proceedings Paper CT Summerschool and Workshop on Solar Magnetic Phenomena CY AUG 25-SEP 05, 2003 CL Solar Observ Kanzelhohe, Karnten, AUSTRIA SP Austrian Bundesminist Wissensch & Forsch, European Space Agcy, Italian Space Agcy, Univ Graz, INAF Trieste Astron Observ, Marktgemeinde Treffen, Land Steiermark, Raiffeisenbank Karnten HO Solar Observ Kanzelhohe ID CORONAL DIAGNOSTIC SPECTROMETER; TIME-DISTANCE HELIOSEISMOLOGY; FAST SOLAR-WIND; R-CIRCLE-DOT; LYMAN-ALPHA; ISOTOPIC COMPOSITION; TRANSITION REGION; CONVECTION ZONE; MAGNETIC-FIELD; MASS EJECTIONS AB Since its launch on 2 December 1995, the joint ESA/NASA SOHO mission has provided a. wealth of information about the Sun, from its interior, through the hot and dynamic atmosphere, to the solar wind and its interaction with the interstellar medium. Analysis of the helioseismology data from SOHO has provided the first images of structures and flows below the Sun's surface and has shed new light on a number of structural and dynamic phenomena in the solar interior, such as the absence of differential rotation in the radiative zone, subsurface zonal and meridional flows, and sub-convection-zone mixing. Evidence for an upward transfer of magnetic energy from the Sun's surface toward the corona has been established. The ultraviolet imagers and spectrometers have revealed an extremely dynamic solar atmosphere where plasma flows play an important role. Electrons in coronal holes were found to be relatively "cool", whereas heavy ions are extremely hot and have highly anisotropic velocity distributions. The source regions for the high speed solar wind have been identified and the acceleration profiles of both the slow and fast solar wind have been measured. SOHO has also revolutionized our space weather forecasting capabilities by providing a continuous stream of images of the dynamic atmosphere, extended corona; and activity on the far side of the Sun. At the same time; SOHO's easily accessible images and movies have captured the imagination of the science community and the general public alike. This article summarizes some of the key, findings from eight years of SOHO. C1 NASA, Goddard Space Flight Ctr, ESA Res & Sci Support Dept, Greenbelt, MD 20771 USA. RP Fleck, B (reprint author), NASA, Goddard Space Flight Ctr, ESA Res & Sci Support Dept, Mailcode 682-3, Greenbelt, MD 20771 USA. RI Fleck, Bernhard/C-9520-2012 NR 86 TC 2 Z9 2 U1 0 U2 2 PU SPRINGER PI DORDRECHT PA PO BOX 17, 3300 AA DORDRECHT, NETHERLANDS BN 1-4020-2961-6 J9 ASTROPHYS SPACE SC L PY 2005 VL 320 BP 139 EP 166 PG 28 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BCE07 UT WOS:000228807700006 ER PT J AU Malanushenko, OV Jones, HP AF Malanushenko, OV Jones, HP TI Differentiating coronal holes from the quiet Sun by He 1083 nm imaging spectroscopy SO SOLAR PHYSICS LA English DT Article ID TRANSITION REGION; SOLAR CORONA; LINES AB The locations of coronal holes are usually based on equivalent-width images in the He I 1083 nm line. However, it is difficult to differentiate coronal holes from the centers of quiet chromospheric network without complementary data and the skill of an experienced observer. Analysis of imaging spectroscopy shows that line half-width and central intensity are correlated differently in coronal holes and a quiet Sun. This fact can be used to form linear combinations of these images in which coronal holes are better separated from the quiet Sun. Coronal hole borders agree well with SOHO/EIT data but can show significant differences from National Solar Observatory maps. C1 Natl Opt Astron Observ, Natl Solar Observ, Tucson, AZ 85726 USA. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Malanushenko, OV (reprint author), Natl Opt Astron Observ, Natl Solar Observ, POB 26732, Tucson, AZ 85726 USA. EM elena@noao.edu; hjones@noao.edu NR 21 TC 11 Z9 11 U1 0 U2 2 PU SPRINGER PI DORDRECHT PA VAN GODEWIJCKSTRAAT 30, 3311 GZ DORDRECHT, NETHERLANDS SN 0038-0938 J9 SOL PHYS JI Sol. Phys. PD JAN PY 2005 VL 226 IS 1 BP 3 EP 16 DI 10.1007/s11207-005-4972-z PG 14 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 923FT UT WOS:000228895900001 ER PT J AU Sylwester, J Gaicki, I Kordylewski, Z Kowalinski, M Nowak, S Plocieniak, S Siarkowski, M Sylwester, B Trzebinski, W Bakala, J Culhane, J Whyndham, M Bentley, R Guttridge, P Phillips, K Lang, J Brown, C Doschek, G Kuznetsov, V Oraevsky, V Stepanov, A Lisin, D AF Sylwester, J Gaicki, I Kordylewski, Z Kowalinski, M Nowak, S Plocieniak, S Siarkowski, M Sylwester, B Trzebinski, W Bakala, J Culhane, J Whyndham, M Bentley, R Guttridge, P Phillips, K Lang, J Brown, C Doschek, G Kuznetsov, V Oraevsky, V Stepanov, A Lisin, D TI RESIK: A bent crystal X-ray spectrometer for studies of solar coronal plasma composition SO SOLAR PHYSICS LA English DT Article ID EMISSION-LINES; ABUNDANCES; ATMOSPHERES; POTASSIUM; SATELLITE; SPECTRA; CALCIUM; SULFUR; ARGON AB We describe the RESIK (REntgenovsky Spektrometr s Izognutymi Kristalami) instrument, consisting of two double-channel X-ray spectrometers, designed to observe solar active region and flare plasmas. RESIK is one of the instruments making up the scientific payload of the Russian CORONAS-F solar mission. The uncollimated spectrometer uses two silicon and two quartz bent crystals observing flare, active region and coronal spectra in four wavelength bands with a resolving power (lambda/Delta lambda) of similar to 1000. The wavelength coverage, 3.3 - 6.1 angstrom, includes emission lines of Si, S, Cl, Ar, and K and in the third diffraction order, the wavelength range includes He-like Fe lines ( 1.85 angstrom) and Ni lines ( 1.55 angstrom) with dielectronic satellites, emitted during intense, hot flares. The instrument is believed to be the best calibrated space-borne crystal spectrometer flown to date. The spectrometer dynamically adjusts the data gathering intervals from 1 s to 5 minutes, depending on the level of solar X-ray emission at the time of observation. The principal aims of RESIK are the measurements of relative and absolute element abundances in the emitting plasma and the temperature distribution of plasma ( differential emission measure) over the temperature interval 3 and 50 MK. This paper summarizes the scientific objectives of RESIK and describes the design, characteristics, and performance of the instrument. C1 Polish Acad Sci, Space Res Ctr, PL-51622 Wroclaw, Poland. UCL, Mullard Space Sci Lab, Dorking RH5 6NT, Surrey, England. NASA, Natl Res Council, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Rutherford Appleton Lab, Space Sci & Technol Dept, Didcot OX11 0QX, Oxon, England. USN, EO Hulburt Ctr Space Res, Res Lab, Washington, DC 20375 USA. IZMIRAN, Moscow, Russia. RP Sylwester, J (reprint author), Polish Acad Sci, Space Res Ctr, Kopernika 11, PL-51622 Wroclaw, Poland. EM js@cbk.pan.wroc.pl NR 32 TC 62 Z9 66 U1 1 U2 6 PU SPRINGER PI DORDRECHT PA VAN GODEWIJCKSTRAAT 30, 3311 GZ DORDRECHT, NETHERLANDS SN 0038-0938 J9 SOL PHYS JI Sol. Phys. PD JAN PY 2005 VL 226 IS 1 BP 45 EP 72 DI 10.1007/s11207-005-6392-5 PG 28 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 923FT UT WOS:000228895900004 ER PT S AU Tanskanen, EI Palmroth, M Pulkkinen, TI Koskinen, HEJ Janhunen, P Ostgaard, N Slavin, JA Liou, K AF Tanskanen, EI Palmroth, M Pulkkinen, TI Koskinen, HEJ Janhunen, P Ostgaard, N Slavin, JA Liou, K BE Mukai, T Lopez, R Maezawa, K Grande, M Fennell, JF Heynderickx, D TI Energetics of a substorm on 15 August, 2001: Comparing empirical methods and a global MHD simulation SO SOLAR WIND-MAGNETOSPHERE-IONOSPHERE DYNAMICS AND RADIATION MODELS SE ADVANCES IN SPACE RESEARCH LA English DT Article; Proceedings Paper CT 2nd World Space Congress/34th COSPAR Scientific Assembly CY OCT 10-19, 2002 CL HOUSTON, TX SP Comm Space Res DE substrom; substrom energetics; global MHD simulation; substrom on 15 August 2001 ID PLASMA SHEET; SOLAR-WIND; ENERGY; CONDUCTANCES; MAGNETOTAIL; FLUX AB Energy transferred from the solar wind into the magnetosphere-ionosphere system is dissipated largely through the occurrence of substorms. In this paper, a substorm that occurred on 15 August, 2001, between 0220 and 0620 UT is analyzed using several empirical estimates for energy input, for Joule heating and for electron precipitation. The total energy input is estimated in terms of Akasofu's epsilon parameter, with original scaling parameter l(0) = 7R(E) and revised scaling l(0) = 10R(E). Empirically estimated energy input is compared to the results of a GUMICS-4 global MHD simulation. Temporal variation of the input curves compare favorably during substorm growth and expansion phases, while there are differences during the substorm recovery phase. Global electron energy dissipation given by PIXIE on board the POLAR spacecraft matches nicely to the results of the GUMICS-4 simulation in temporal variations, but the absolute levels of dissipation are quite different. (c) 2005 Published by Elsevier Ltd on behalf of COSPAR. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20770 USA. Finnish Meteorol Inst, Geophys Res Space Res Unit, Helsinki 00101, Finland. Univ Helsinki, Dept Phys Sci, FIN-00014 Helsinki, Finland. Univ Calif Berkeley, Space Sci Lab, Berkeley, CA 94720 USA. Johns Hopkins Univ, Appl Phys Lab, Laurel, MD 20723 USA. RP Tanskanen, EI (reprint author), NASA, Goddard Space Flight Ctr, Code 696, Greenbelt, MD 20770 USA. EM eija.tanskanen@fmi.fi RI Slavin, James/H-3170-2012; Pulkkinen, Tuija/D-8403-2012; Koskinen, Hannu/B-4971-2017; Liou, Kan/C-2089-2016 OI Slavin, James/0000-0002-9206-724X; Pulkkinen, Tuija/0000-0002-6317-381X; Koskinen, Hannu/0000-0003-3839-6461; Liou, Kan/0000-0001-5277-7688 NR 21 TC 6 Z9 6 U1 0 U2 1 PU ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD 0X5 1GB, OXON, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2005 VL 36 IS 10 SI 2005 BP 1825 EP 1829 DI 10.1016/j.asr.2004.05.013 PG 5 WC Engineering, Aerospace; Astronomy & Astrophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Engineering; Astronomy & Astrophysics; Geology; Meteorology & Atmospheric Sciences GA BDY96 UT WOS:000236277300012 ER PT S AU Kotova, G Verigin, M Zastenker, G Nikolaeva, N Smolkin, B Slavin, J Szabo, A Merka, J Nemechek, Z Safrankova, J AF Kotova, G Verigin, M Zastenker, G Nikolaeva, N Smolkin, B Slavin, J Szabo, A Merka, J Nemechek, Z Safrankova, J BE Mukai, T Lopez, R Maezawa, K Grande, M Fennell, JF Heynderickx, D TI Bow shock observations by Prognoz-Prognoz 11 data: analysis and model comparison SO SOLAR WIND-MAGNETOSPHERE-IONOSPHERE DYNAMICS AND RADIATION MODELS SE ADVANCES IN SPACE RESEARCH LA English DT Article; Proceedings Paper CT 2nd World Space Congress/34th COSPAR Scientific Assembly CY OCT 10-19, 2002 CL HOUSTON, TX SP Comm Space Res ID MAGNETIC-FIELD ORIENTATION; STANDOFF DISTANCE; 3-D SHAPE; MAGNETOSPHERE; FLOW AB Observations of the terrestrial bow shock by the Prognoz' orbiters are collected since 1972 (Prognoz) till 2000 (Prognoz 11 = Interball 1 with Magion 4 subsatellite). Data from the different spacecraft are organized into a uniform database for detailed analysis of the terrestrial bow shock position and shape and their variations. A previously developed analytical bow shock model is used to Study the motions of this boundary in response to variations of the solar wind pressure, sonic and Alfvenic Mach numbers, and the angle between the plasma flow and magnetic field directions theta(bv). It is shown experimentally that the bow shock is located closer to the obstacle for small theta(bv) and farther for theta(bv) approximate to 90 degrees for fixed values of rho V-2, M-a, M-s. The asymmetry of the terrestrial bow shock in the terminator plane is confirmed, which was found earlier in the Wind bow shock observations for non field-aligned flow with anisotropic Friedrichs diagrams. (c) 2004 COSPAR. Published by Elsevier Ltd. All rights reserved. C1 Russian Acad Sci, Space Res Inst, Moscow 117997, Russia. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Charles Univ, CR-18000 Prague, Czech Republic. RP Kotova, G (reprint author), Russian Acad Sci, Space Res Inst, Profsoyuznaya 84-32, Moscow 117997, Russia. EM kotova@iki.rssi.ru RI Slavin, James/H-3170-2012 OI Slavin, James/0000-0002-9206-724X NR 20 TC 2 Z9 2 U1 0 U2 1 PU ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD 0X5 1GB, OXON, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2005 VL 36 IS 10 SI 2005 BP 1958 EP 1963 DI 10.1016/j.asr.2004.09.007 PG 6 WC Engineering, Aerospace; Astronomy & Astrophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Engineering; Astronomy & Astrophysics; Geology; Meteorology & Atmospheric Sciences GA BDY96 UT WOS:000236277300037 ER PT S AU Fung, SF Bell, EV Tan, LC Candey, RM Golightly, MJ Huston, SL King, JH McGuire, RE AF Fung, SF Bell, EV Tan, LC Candey, RM Golightly, MJ Huston, SL King, JH McGuire, RE BE Mukai, T Lopez, R Maezawa, K Grande, M Fennell, JF Heynderickx, D TI Development of a magnetospheric state-based trapped radiation database SO SOLAR WIND-MAGNETOSPHERE-IONOSPHERE DYNAMICS AND RADIATION MODELS SE ADVANCES IN SPACE RESEARCH LA English DT Article; Proceedings Paper CT 2nd World Space Congress/34th COSPAR Scientific Assembly CY OCT 10-19, 2002 CL HOUSTON, TX SP Comm Space Res DE radiation belt modeling; trapped particles; magnetospheric states ID ELECTRONS; BELT; PARAMETER; PARTICLES AB At the core of any empirical trapped radiation model is a database containing energetic particle observations. The usefulness of such a database and the performance of the resulting models depend on the database flexibility to respond to queries based on differing magnetospheric conditions, and the ability to locate, select, retrieve and analyze the relevant particle data. Current empirical trapped radiation models, such as the NASA AE-8 and AP-8 models, are essentially flux lookup tables on (E, B/B-0, L) grids based on processed data. Such lookup tables are inherently static, non-updateable, and non-extensible. Consequently, the models constructed from them would have limited performance. As an initial effort to construct a new generation of empirical trapped radiation models, a new magnetospheric state-based trapped radiation database is being constructed in order to overcome existing model limitations. We have adopted an object-oriented database design to accommodate the complex and dynamic space radiation environment. The technique encapsulates the particle data, ancillary data, and metadata into abstract objects in a common framework to handle heterogeneous data sources. The new database structure will allow users to query the database using combinations of geophysical, temporal and spatial parameters. In this paper, we will focus on the implementation issues that arise in integrating heterogeneous data sets. To mitigate against early obsolescence when updated or new data become available, the models' underlying database must be updateable and extensible. In addition, to ensure high model performance, the database must be parameterizeable, so that the selection of data from the database for analysis or modeling can vary with magnetospheric conditions or states that vary with solar wind and IMF driving conditions and geomagnetic responses (see Fung, S. F. Recent development in the NASA trapped radiation models, in: Radiation Belts: Models and Standards, Geophys. Monogr. Ser., vol. 97, American Geophysical Union, Washington, DC, pp. 79-91, 1996). By following an object-oriented design, the new trapped-radiation database can be easily updated, extended and re-parameterized. Our effort in constructing a prototype particle radiation database will be applicable to the NASA Living With a Star Program. Published by Elsevier Ltd on behalf of COSPAR. C1 NASA, Goddard Space Flight Ctr, Space Phys Data Facil, Greenbelt, MD 20771 USA. Raytheon ITSS, GSFC, Greenbelt, MD 20771 USA. NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. SAIC, Seal Beach, CA USA. RP Fung, SF (reprint author), NASA, Goddard Space Flight Ctr, Space Phys Data Facil, Greenbelt, MD 20771 USA. EM shing.fung@gsfc.nasa.gov RI Candey, Robert/D-4639-2012; Fung, Shing/F-5647-2012 NR 25 TC 7 Z9 7 U1 0 U2 1 PU ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD 0X5 1GB, OXON, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2005 VL 36 IS 10 SI 2005 BP 1984 EP 1991 DI 10.1016/j.asr.2004.04.020 PG 8 WC Engineering, Aerospace; Astronomy & Astrophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Engineering; Astronomy & Astrophysics; Geology; Meteorology & Atmospheric Sciences GA BDY96 UT WOS:000236277300041 ER PT S AU Foster, JL Benbrook, JR Stansbery, EG AF Foster, JL Benbrook, JR Stansbery, EG BE Anselmo, L TI Detection of small radar cross-section orbital debris with the Haystack radar SO SPACE DEBRIS SE ADVANCES IN SPACE RESEARCH LA English DT Article; Proceedings Paper CT Scientific Meeting on Space Debris held at the 35th COSPAR Scientific Assembly CY JUL 22-24, 2004 CL Paris, FRANCE SP European Space Agcy, Int Acad Astronaut, Int Astronaut Federat, Int Astron Union, UN Off Outer Space Affairs DE Space debris measurements AB NASA has been making statistical measurements of the orbital debris environment for more than a decade using the MIT Lincoln Laboratory Haystack radar. The goal has been to characterize the environment for debris sizes as small as possible. Like all sensors which operate in the presence of noise, the Haystack radar has limited sensitivity. As the returned energy from small targets begins to approach the sensitivity limit of the radar, the probability-of-detection decreases, eventually approaching zero. The slope of the cumulative size distribution of debris begins to flatten out. This paper explores the possibility of extending the cumulative size distribution to smaller sizes by adjusting the distribution for probability-of-detection. (c) 2005 Published by Elsevier Ltd on behalf of COSPAR. C1 GB Tech Inc, Houston, TX 77058 USA. NASA, Johnson Space Ctr, Houston, TX 77058 USA. RP Foster, JL (reprint author), GB Tech Inc, 2200 Space Pk Dr, Houston, TX 77058 USA. EM james.i.foster1@jsc.nasa.gov NR 7 TC 5 Z9 6 U1 1 U2 1 PU PERGAMON-ELSEVIER SCIENCE LTD PI KIDLINGTON PA THE BOULEVARD, LANGFORD LANE,, KIDLINGTON OX5 1GB, OXFORD, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2005 VL 35 IS 7 BP 1210 EP 1213 DI 10.1016/j.asr.2005.05.041 PG 4 WC Engineering, Aerospace; Astronomy & Astrophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Engineering; Astronomy & Astrophysics; Geology; Meteorology & Atmospheric Sciences GA BDA59 UT WOS:000232300700002 ER PT S AU Johnson, NL AF Johnson, NL BE Anselmo, L TI Space debris mitigation strategies and practices in geosynchronous transfer orbits SO SPACE DEBRIS SE ADVANCES IN SPACE RESEARCH LA English DT Article; Proceedings Paper CT Scientific Meeting on Space Debris held at the 35th COSPAR Scientific Assembly CY JUL 22-24, 2004 CL Paris, FRANCE SP European Space Agcy, Int Acad Astronaut, Int Astronaut Federat, Int Astron Union, UN Off Outer Space Affairs DE space debris; mitigation; geosynchronous transfer orbit AB Missions to geosynchronous orbits remain one of the most important elements of space launch traffic, accounting for 40% of all missions to Earth orbit and beyond during the four-year period 2000-2003. The vast majority of these missions leave one or more objects in geosynchronous transfer orbits (GTOs), contributing oil a short-term or long-term basis to the space debris population. National and international space debris mitigation guidelines seek to curtail the accumulation of debris in orbits which penetrate the regions of low Earth orbit and of geosynchronous orbit. The orbital lifetime of objects in GTO can be greatly influenced by the initial values of perigee, inclination, and right ascension of the orbital plane, leading to orbital lifetimes of from less than one month to more than 100 years. An examination of the characteristic GTOs employed by launch vehicles from around the world has been conducted. The consequences of using perigees above 300 km and super-synchronous apogees, typically above 40,000 km, have been identified. In addition, the differences in orbital behavior of launch vehicle stages and mission-related debris in GTOs have been investigated. Greater coordination and cooperation between space launch service providers and spacecraft designers and owners could significantly improve overall compliance with guidelines to mitigate the accumulation of debris in Earth orbit. Published by Elsevier Ltd on behalf of COSPAR. C1 NASA, Lyndon B Johnson Space Ctr, Orbital Debris Program Off, Houston, TX 77058 USA. RP Johnson, NL (reprint author), NASA, Lyndon B Johnson Space Ctr, Orbital Debris Program Off, 2101 NASA Pkwy, Houston, TX 77058 USA. EM nicholas.l.johnson@nasa.gov NR 5 TC 1 Z9 1 U1 0 U2 1 PU PERGAMON-ELSEVIER SCIENCE LTD PI KIDLINGTON PA THE BOULEVARD, LANGFORD LANE,, KIDLINGTON OX5 1GB, OXFORD, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2005 VL 35 IS 7 BP 1328 EP 1334 DI 10.1016/j.asr.2004.11.037 PG 7 WC Engineering, Aerospace; Astronomy & Astrophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Engineering; Astronomy & Astrophysics; Geology; Meteorology & Atmospheric Sciences GA BDA59 UT WOS:000232300700016 ER PT S AU Matney, M AF Matney, M BE Bendisch, J TI Dynamic orbital debris collision risk mitigation SO Space Debris and Space Traffic Management Symposium 2004 SE SCIENCE AND TECHNOLOGY SERIES LA English DT Proceedings Paper CT Symposium on Space Debris and Space Traffic Management CY OCT 04-08, 2004 CL Vancouver, CANADA SP Int Acad Astronaut AB Historically, calculations of orbital debris risks have used the debris flux time-averaged over the spacecraft orbit to assess hazard and to design shielding. This method gives the average flux as a function of debris size, direction, and impact speed, and works well for spacecraft that maintain orientation to the velocity vector. However, the debris flux is not constant - either in magnitude or in direction over the progress of the spacecraft through its orbit. For instance. as the spacecraft crosses the equator going north, typically there is an enhanced flux on the port side (relative to the local horizontal). The opposite holds true on southbound transits of the equator, with the maximum flux typically coming from the starboard side. This behavior opens up the possibility of designing missions to dynamically mitigate debris, by turning "dumb" structure or shielding toward the varying direction of maximum flux at different points along the spacecraft orbit. This paper will examine this effect using NASA's Orbital Debris Engineering model ORDEM2000 and show how such knowledge could be used in potential mitigation strategies. C1 NASA, Lyndon B Johnson Space Ctr, Orbital Debris Program Off, Houston, TX 77058 USA. RP Matney, M (reprint author), NASA, Lyndon B Johnson Space Ctr, Orbital Debris Program Off, 2101 NASA Pkwy,Mail Code KX, Houston, TX 77058 USA. NR 3 TC 0 Z9 0 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 0278-4017 BN 0-87703-523-7 J9 SCI TECH PY 2005 VL 110 BP 399 EP 403 PG 5 WC Engineering, Aerospace; Geosciences, Multidisciplinary SC Engineering; Geology GA BDM87 UT WOS:000234370300031 ER PT S AU Charnley, SB AF Charnley, SB BE Bernstein, M NavarroGonzalez, R Raulin, R TI A note on the kinetics of heavy atom reactions on interstellar grains SO SPACE LIFE SCIENCES: ASTROBIOLOGY: STEPS TOWARD ORIGIN OF LIFE AND TITAN BEFORE CASSINI SE ADVANCES IN SPACE RESEARCH-SERIES LA English DT Article; Proceedings Paper CT 35th COSPAR Scientific Assembly CY JUL 18-25, 2004 CL Paris, FRANCE SP Comm Space Res DE ISM; astrochemistry; dust grains; molecular processes ID MOLECULAR COMPOSITION; ORGANIC-MOLECULES; SURFACE-CHEMISTRY; MASTER EQUATION; CLOUDS; ADSORPTION; MODELS; DUST; RECOMBINATION; PHYSICS AB The assumption made in many surface chemistry models, that the reactive population of heavy atoms and/or molecules on a grain surface at any instant can be restricted to only zero, one, or two, species, is most likely in serious error. It is shown that the validity of this restriction is based upon the combination of an optimistic selection of the parameters governing the surface diffusion of heavy atoms and, more importantly, upon an erroneous application of results from the theory of random walks on regular lattices. It is shown that the latter leads to a gross overestimate of the importance of surface reactions involving heavy atoms unless interstellar grains are fractal and have a spectral dimension greater than two. Diffusion-controlled reactions involving C, O and N atoms are much less efficient on grain surfaces, and the predicted abundances of several molecules, formed in many published models of grain surface chemistry have to be revised downwards. (c) 2005 Published by Elsevier Ltd on behalf of COSPAR. C1 NASA, Ames Res Ctr, Div Space Sci, Moffett Field, CA 94035 USA. RP Charnley, SB (reprint author), NASA, Ames Res Ctr, Div Space Sci, MS 245-3, Moffett Field, CA 94035 USA. EM charnley@dusty.arc.nasa.gov RI Charnley, Steven/C-9538-2012 NR 37 TC 5 Z9 5 U1 0 U2 1 PU ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD 0X5 1GB, OXON, ENGLAND SN 0273-1177 J9 ADV SPACE RES-SERIES PY 2005 VL 36 IS 2 SI 2005 BP 132 EP 136 DI 10.1016/j.asr.2005.09.004 PG 5 WC Engineering, Aerospace; Astronomy & Astrophysics; Biology; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Engineering; Astronomy & Astrophysics; Life Sciences & Biomedicine - Other Topics; Geology; Meteorology & Atmospheric Sciences GA BDT05 UT WOS:000235191500001 ER PT S AU Charnley, SB Kuan, YJ Huang, HC Botta, O Butner, HM Cox, N Despois, D Ehrenfreund, P Kisiel, Z Lee, YY Markwick, AJ Peeters, Z Rodgers, SD AF Charnley, SB Kuan, YJ Huang, HC Botta, O Butner, HM Cox, N Despois, D Ehrenfreund, P Kisiel, Z Lee, YY Markwick, AJ Peeters, Z Rodgers, SD BE Bernstein, M NavarroGonzalez, R Raulin, R TI Astronomical searches for nitrogen heterocycles SO SPACE LIFE SCIENCES: ASTROBIOLOGY: STEPS TOWARD ORIGIN OF LIFE AND TITAN BEFORE CASSINI SE ADVANCES IN SPACE RESEARCH-SERIES LA English DT Article; Proceedings Paper CT 35th COSPAR Scientific Assembly CY JUL 18-25, 2004 CL Paris, FRANCE SP Comm Space Res DE astrobiology; astrochemistry; ISM : chemistry; ISM : molecules; stars : AGB and post-AGB ID POLYCYCLIC AROMATIC-HYDROCARBONS; INTERSTELLAR-MOLECULES; ROTATIONAL SPECTRUM; ORGANIC-MOLECULES; EARLY EARTH; METEORITES; PYRIMIDINE; PYRIDINE; MECHANISMS; CONSTANTS AB We have conducted extensive astronomical searches for the N-bearing ring molecules pyridine, quinoline and isoquinoline towards the circurnstellar envelopes of carbon-rich stars, and for interstellar pyrimidine in hot molecular cores. Here we report the derived upper limits oil the column densities of these molecules, and summarize the current status of these observations. (c) 2005 Published by Elsevier Ltd oil behalf of COSPAR. C1 NASA, Ames Res Ctr, Space Sci & Astrobiol Div, Moffett Field, CA 94035 USA. Natl Taiwan Normal Univ, Taipei 116, Taiwan. Int Space Sci Inst, Bern, Switzerland. Joint Astron Ctr, Hilo, HI 96720 USA. Univ Amsterdam, Astron Inst Anton Pannekoek, Amsterdam, Netherlands. Observ Bordeaux, INSU, CNRS, Floirac, France. Leiden Univ, Leiden Inst Chem, Astrobiol Lab, NL-2300 RA Leiden, Netherlands. Polish Acad Sci, Inst Phys, PL-02668 Warsaw, Poland. Acad Sinica, Inst Astron & Astrophys, ASIAA, Taipei 106, Taiwan. RP Charnley, SB (reprint author), NASA, Ames Res Ctr, Space Sci & Astrobiol Div, Moffett Field, CA 94035 USA. EM charnley@dusty.arc.nasa.gov RI Charnley, Steven/C-9538-2012; Kisiel, Zbigniew/K-8798-2016; OI Kisiel, Zbigniew/0000-0002-2570-3154; Butner, Harold/0000-0003-4899-2064 NR 40 TC 47 Z9 47 U1 0 U2 24 PU ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD 0X5 1GB, OXON, ENGLAND SN 0273-1177 J9 ADV SPACE RES-SERIES PY 2005 VL 36 IS 2 SI 2005 BP 137 EP 145 DI 10.1016/j.asr.2005.09.005 PG 9 WC Engineering, Aerospace; Astronomy & Astrophysics; Biology; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Engineering; Astronomy & Astrophysics; Life Sciences & Biomedicine - Other Topics; Geology; Meteorology & Atmospheric Sciences GA BDT05 UT WOS:000235191500002 ER PT S AU Huang, HC Kuan, YJ Charnley, SB Hirano, N Takakuwa, S Bourke, TL AF Huang, HC Kuan, YJ Charnley, SB Hirano, N Takakuwa, S Bourke, TL BE Bernstein, M NavarroGonzalez, R Raulin, R TI Organic molecules in the hot corinos and circumstellar disks of IRAS 16293-2422 SO SPACE LIFE SCIENCES: ASTROBIOLOGY: STEPS TOWARD ORIGIN OF LIFE AND TITAN BEFORE CASSINI SE ADVANCES IN SPACE RESEARCH LA English DT Article; Proceedings Paper CT 35th COSPAR Scientific Assembly CY JUL 18-25, 2004 CL Paris, FRANCE SP Comm Space Res DE astrochemistry; ISM : abundances; ISM : individual (IRAS 16293-2422); ISM : molecules; radio lines; ISM - stars : formation ID PROTOSTAR IRAS 16293-2422; MASS STAR-FORMATION; YOUNG BINARY-SYSTEM; LINE SURVEY; DEUTERATED METHANOL; FORMING REGIONS; EARLY EARTH; CORE; ABUNDANCES; EMISSION AB Using the recently commissioned Submillimeter Array (SMA), we have detected several complex organic molecules, including (CH3)(2)O, C2H5OH, C2H5CN, and tentatively CH2CDCN, toward the protostellar hot cores of IRAS 16293-2422 at arcsecond-resolution (<= 400 AU in radius). Vibrationally excited transitions of SO, SO2 and HCN with energy levels up to 1800 K were also observed. In addition to the other organic molecules (HC3N, CH2CO, CH3OH, CH2CHCN and HCOOCH3) previously reported by us (Kuan, Y.-J., Huang, H.-C., Charnley, S.B., Hirano, H., Takakuwa, S., et al. Organic molecules in low-mass protostellar hot cores: submillitimeter imaging of IRAS 16293-2422. Astrophys. J. 616, 127-L30, 2004) these results clearly indicate the existence of a rich organic chemistry in low-mass 'hot corinos'. From the observation of optically thin (HCN)-N-15 emission, we conclude 116293A is a rotating circumstellar disk lying along the north-south direction similar to 10 degrees to the east and with an inclination similar to 30 degrees to the sky. We suggest that the observed vibrational SO and SO, emission may originate from shock waves near or in the circumstellar disks. Between the two cores, we find a strong anticorrelation in emission from C2H5OH and CH5CN. The relative contribution of gas phase and grain-surface chemistries to the production of the observed complex molecules is discussed. We point out the shortcomings underlying recent claims that all the O-bearing organics are formed on grains. The presence of so many well-known interstellar molecules in solar-type hot corinos strengthens the link between molecular cloud chemistry, the starting materials of protoplanetary disks such as the protosolar nebula.. and the composition of comets. Establishing the fine details of this connection is crucial in answering fundamental questions concerning the importance of galactic astrochemistry for astrobiology. (c) 2005 COSPAR. Published by Elsevier Ltd. All rights reserved. C1 Natl Taiwan Normal Univ, Dept Earth Sci, Taipei 116, Taiwan. NASA, Ames Res Ctr, Div Space Sci, Moffett Field, CA 94035 USA. Acad Sinica, Inst Astron & Astrophys, Taipei 106, Taiwan. Harvard Smithsonian Ctr Astrophys, Submillimeter Array Project, Hilo, HI 96721 USA. Acad Sinica, Inst Astron & Astrophys, Taipei 115, Taiwan. RP Huang, HC (reprint author), Natl Taiwan Normal Univ, Dept Earth Sci, 88 Sec 4 Tug Chou Rd, Taipei 116, Taiwan. EM hspring@sgrb2.geos.ntnu.edu.tw RI Charnley, Steven/C-9538-2012 NR 41 TC 13 Z9 13 U1 0 U2 2 PU ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD 0X5 1GB, OXON, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2005 VL 36 IS 2 SI 2005 BP 146 EP 155 DI 10.1016/j.asr.2005.03.115 PG 10 WC Engineering, Aerospace; Astronomy & Astrophysics; Biology; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Engineering; Astronomy & Astrophysics; Life Sciences & Biomedicine - Other Topics; Geology; Meteorology & Atmospheric Sciences GA BDT05 UT WOS:000235191500003 ER PT S AU Mattioda, AL Hudgins, DM Bauschlicher, CW Allamandola, LJ AF Mattioda, AL Hudgins, DM Bauschlicher, CW Allamandola, LJ BE Bernstein, M NavarroGonzalez, R Raulin, R TI Infrared spectroscopy of matrix-isolated polycyclic aromatic compounds and their ions. 7. Phenazine, a dual substituted polycyclic aromatic nitrogen heterocycle SO SPACE LIFE SCIENCES: ASTROBIOLOGY: STEPS TOWARD ORIGIN OF LIFE AND TITAN BEFORE CASSINI SE ADVANCES IN SPACE RESEARCH LA English DT Article; Proceedings Paper CT 35th COSPAR Scientific Assembly CY JUL 18-25, 2004 CL Paris, FRANCE SP Comm Space Res DE phenazine; PANHs; PAHs; polycyclic aromatic hydrocarbons; nitrogen heterocycles; unidentified infrared bands ID ISOLATED NAPHTHALENE; VIBRATIONAL-SPECTRA; HYDROCARBON CATIONS; PAHS; MOLECULES; CARRIERS AB The matrix-isolation technique has been employed to measure the mid-infrared spectra of phenazine (C12H8N2), a dual substituted polycyclic aromatic nitrogen heterocycle (PANH), in the neutral, cationic and anionic forms. The experimentally measured band frequencies and intensities are tabulated and compared with their calculated values as well as those of the non-substituted parent molecule, anthracene. The theoretical band positions and intensities were calculated using both the 4-31G as well as the larger 6-31G* basis sets. A comparison of the results can be found in the tables. The spectroscopic properties of phenazine and its cation are similar to those observed in mono-substituted PANHs, with one exception. The presence of a second nitrogen atom results in an additional enhancement of the cation's total integrated intensity, for the 1500-1000 cm(-1) (6.7-10 mu m) region, over that observed for a mono-substituted PANH cation. The significance of this enhancement and the astrobiological implications of these results are discussed. (c) 2005 COSPAR. Published by Elsevier Ltd. All rights reserved. C1 NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. SETI Inst, Mountain View, CA 94043 USA. RP Mattioda, AL (reprint author), NASA, Ames Res Ctr, MS245-6, Moffett Field, CA 94035 USA. EM amattioda@mail.arc.nasa.gov NR 30 TC 17 Z9 17 U1 1 U2 9 PU ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD 0X5 1GB, OXON, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2005 VL 36 IS 2 SI 2005 BP 156 EP 165 DI 10.1016/j.asr.2005.03.127 PG 10 WC Engineering, Aerospace; Astronomy & Astrophysics; Biology; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Engineering; Astronomy & Astrophysics; Life Sciences & Biomedicine - Other Topics; Geology; Meteorology & Atmospheric Sciences GA BDT05 UT WOS:000235191500004 ER PT S AU Bernstein, MP Sandford, SA Walker, RL AF Bernstein, MP Sandford, SA Walker, RL BE Bernstein, M NavarroGonzalez, R Raulin, R TI Laboratory IR spectra of 4-azachrysene in solid H2O SO SPACE LIFE SCIENCES: ASTROBIOLOGY: STEPS TOWARD ORIGIN OF LIFE AND TITAN BEFORE CASSINI SE ADVANCES IN SPACE RESEARCH LA English DT Article; Proceedings Paper CT 35th COSPAR Scientific Assembly CY JUL 18-25, 2004 CL Paris, FRANCE SP Comm Space Res DE IR spectroscopy; dense molecular cloud; H2O; aromatic; PAH; PANH ID POLYCYCLIC AROMATIC-HYDROCARBONS; INFRARED-SPECTROSCOPY; ABSORPTION; ICE; METEORITE; MOLECULES; DUST AB We present the mid-IR spectrum of 4-azachrysene (C17H11N) frozen in solid H2O at 14 K, data directly comparable to astronomical observations along dense cloud lines of sight. We tabulate the positions, profiles, and relative intensities of those 4-azachrysene peaks not obscured by strong H2O absorptions and note some significant changes in position and/or intensity relative to the previously published values for 4-azachrysene isolated in an argon matrix. In contrast to simple PAHs that do not interact strongly with solid H2O, PANHs, with their nitrogen atom(s), are potentially capable of hydrogen bonding with H2O, and this presumably gives rise to some of the spectral changes. This demonstrates that observers will not always be able to rely on peak positions of matrix isolated PANHs to correctly reflect the actual absorption band positions of PANHs along lines of sight where they will exist as pure solids or be frozen in H2O. In general these nitrogen heterocycles are of astrobiological interest since this class of molecules has been detected in meteorites, they could be pre-biotically important, and/or they could act as false biomarkers. (c) 2005 COSPAR. Published by Elsevier Ltd. All rights reserved. C1 NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Bernstein, MP (reprint author), NASA, Ames Res Ctr, MS 245-6, Moffett Field, CA 94035 USA. EM mbernstein@mail.nasa.gov NR 24 TC 0 Z9 0 U1 0 U2 1 PU ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD 0X5 1GB, OXON, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2005 VL 36 IS 2 SI 2005 BP 166 EP 172 DI 10.1016/j.asr.2005.05.050 PG 7 WC Engineering, Aerospace; Astronomy & Astrophysics; Biology; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Engineering; Astronomy & Astrophysics; Life Sciences & Biomedicine - Other Topics; Geology; Meteorology & Atmospheric Sciences GA BDT05 UT WOS:000235191500005 ER PT S AU Cruikshank, DP Imanaka, H Ore, CMD AF Cruikshank, DP Imanaka, H Ore, CMD BE Bernstein, M NavarroGonzalez, R Raulin, R TI Tholins as coloring agents on outer Solar System bodies SO SPACE LIFE SCIENCES: ASTROBIOLOGY: STEPS TOWARD ORIGIN OF LIFE AND TITAN BEFORE CASSINI SE ADVANCES IN SPACE RESEARCH-SERIES LA English DT Article; Proceedings Paper CT 35th COSPAR Scientific Assembly CY JUL 18-25, 2004 CL Paris, FRANCE SP Comm Space Res DE titan; tholin; organic chemistry; outer Solar System; infrared spectroscopy ID SURFACE-COMPOSITION; OPTICAL-PROPERTIES; INFRARED-SPECTROSCOPY; TITANS ATMOSPHERE; TROJAN ASTEROIDS; SATURNS RINGS; X-RAY; CONSTRAINTS; CENTAURS; HAZE AB The red colors of many solid bodies in outer Solar System may be caused by tholins, which are refractory organic complexes, incorporated in their surface materials. Tholins synthesized in the laboratory are shown to match the colors of these bodies when their optical properties are used in rigorous scattering models. We review recent successes in modeling the spectra of icy outer Solar System bodies with tholins as the coloring agents. New work on the systematic laboratory synthesis and analysis of tholins made by cold plasma discharge in mixtures of gaseous CH(4)/N(2) shows that the composition of the tholin depends strongly on the pressure in the reaction chamber, and only weakly on the mixing fraction of CH(4) relative to N(2). In tholins made at high pressure (e.g., 23 hPa) the abundance of aliphatic hydrocarbons is greater and the abundance of aromatic hydrocarbons is less than in tholins made at low pressure (e.g., 0.13 hPa). Tholins made at low deposition pressures show a greater abundance of N-H bonds. (c) 2005 COSPAR. Published by Elsevier Ltd. All rights reserved. C1 NASA, Ames Res Ctr, Astrophys Branch, Moffett Field, CA 94035 USA. SETI Inst, Mountain View, CA 94043 USA. RP Cruikshank, DP (reprint author), NASA, Ames Res Ctr, Astrophys Branch, MS 245-6, Moffett Field, CA 94035 USA. EM Dale.P.Cruikshank@nasa.gov RI Imanaka, Hiroshi/E-7816-2012 NR 40 TC 48 Z9 49 U1 0 U2 5 PU ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD 0X5 1GB, OXON, ENGLAND SN 0273-1177 J9 ADV SPACE RES-SERIES PY 2005 VL 36 IS 2 SI 2005 BP 178 EP 183 DI 10.1016/j.asr.2005.07.026 PG 6 WC Engineering, Aerospace; Astronomy & Astrophysics; Biology; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Engineering; Astronomy & Astrophysics; Life Sciences & Biomedicine - Other Topics; Geology; Meteorology & Atmospheric Sciences GA BDT05 UT WOS:000235191500007 ER PT S AU Hudson, RL Moore, MH Cook, AM AF Hudson, RL Moore, MH Cook, AM BE Bernstein, M NavarroGonzalez, R Raulin, R TI IR characterization and radiation chemistry of glycolaldehyde and ethylene glycol ices SO SPACE LIFE SCIENCES: ASTROBIOLOGY: STEPS TOWARD ORIGIN OF LIFE AND TITAN BEFORE CASSINI SE ADVANCES IN SPACE RESEARCH LA English DT Article; Proceedings Paper CT 35th COSPAR Scientific Assembly CY JUL 18-25, 2004 CL Paris, FRANCE SP Comm Space Res DE organic chemistry; ices; comets; interstellar medium; radiation chemistry ID ABINITIO CALCULATIONS; TEMPERATURE; SPECTRA; ANALOGS AB Motivated by detections of glycolalclehyde and ethylene glycol in the interstellar medium and, for ethylene glycol, in comet Hale-Bopp, we report the low-temperature mid-IR spectra of these two molecules, including selected band strengths and positions. Each molecule has also been irradiated with 0.8 MeV protons to simulate cosmic-ray exposure, to measure each molecule's radiation lifetime, and to determine radiation chemical products. Evidence is presented that glycolaldehyde is readily formed from irradiated ethylene glycol ices, both in the presence and absence of H2O ice. (c) 2005 Published by Elsevier Ltd on behalf of COSPAR. C1 Eckerd Coll, Dept Chem, St Petersburg, FL 33711 USA. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Connecticut Coll, Dept Phys Astron & Geophys, New London, CT 06320 USA. RP Hudson, RL (reprint author), Eckerd Coll, Dept Chem, 4200 54th Ave S, St Petersburg, FL 33711 USA. EM hudsonrl@eckerd.edu RI Hudson, Reggie/E-2335-2012 NR 17 TC 33 Z9 33 U1 1 U2 11 PU ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD 0X5 1GB, OXON, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2005 VL 36 IS 2 SI 2005 BP 184 EP 189 DI 10.1016/j.asr.2005.01.017 PG 6 WC Engineering, Aerospace; Astronomy & Astrophysics; Biology; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Engineering; Astronomy & Astrophysics; Life Sciences & Biomedicine - Other Topics; Geology; Meteorology & Atmospheric Sciences GA BDT05 UT WOS:000235191500008 ER PT S AU Rodier, C Sternberg, R Szopa, C Buch, A Cabane, M Raulin, F AF Rodier, C Sternberg, R Szopa, C Buch, A Cabane, M Raulin, F BE Bernstein, M NavarroGonzalez, R Raulin, R TI Search for organics in extraterrestrial environments by in situ gas chromatography analysis SO SPACE LIFE SCIENCES: ASTROBIOLOGY: STEPS TOWARD ORIGIN OF LIFE AND TITAN BEFORE CASSINI SE ADVANCES IN SPACE RESEARCH LA English DT Article; Proceedings Paper CT 35th COSPAR Scientific Assembly CY JUL 18-25, 2004 CL Paris, FRANCE SP Comm Space Res DE organic molecules; in situ GC analysis; thermochemolysis ID MASS-SPECTROMETRY; PYROLYTIC METHYLATION; AMINO-ACIDS; DERIVATIZATION; ENANTIOMERS; HYDROLYSIS; SEPARATION; MOLECULES AB Many organic molecules are present in interstellar clouds and might have been carried to the early Earth by comets and meteorites during the heavy bombardment phase in the first few hundred million years of the solar system. It has been Suggested that extraterrestrial organic material may represent a part of the organic material available for the origin of life. Until samples, brought by future space missions, are available on Earth, in situ measurements are the only way to get unaltered samples for analysis. The analytical technique has to be robust, Sensitive and non-specific due to the large scope of target molecules. Currently the only flight qualified technique of analysis of organic molecules in space is gas chromatography (GC). The main objective of this work is to present the capabilities of a GC based subsystem, developed in our laboratory and including sample treatment and capillary column analysis, for the in Situ analysis of volatile and refractory organics in atmospheric (Titan) and/or Surface or SUb-surface samples (Mars, comets). (c) 2005 COSPAR. Published by Elsevier Ltd. All rights reserved. C1 Lab Synth & React Subst Nat, UMR 6514, F-86022 Poitiers, France. Univ Paris 07, UMR 7583, Lab Interuniv Syst Atmospher, F-94010 Creteil, France. Univ Paris 12, UMR 7583, Lab Interuniv Syst Atmospher, F-94010 Creteil, France. Univ Paris 06, UMR 7620, IPSL, CNRS,Serv Aeron, F-75005 Paris, France. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20777 USA. RP Rodier, C (reprint author), Lab Synth & React Subst Nat, UMR 6514, BP 633, F-86022 Poitiers, France. EM claude.rodier@univ-poitiers.fr RI szopa, cyril/C-6865-2015 OI szopa, cyril/0000-0002-0090-4056 NR 28 TC 4 Z9 4 U1 0 U2 6 PU ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD 0X5 1GB, OXON, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2005 VL 36 IS 2 SI 2005 BP 195 EP 200 DI 10.1016/j.asr.2004.12.072 PG 6 WC Engineering, Aerospace; Astronomy & Astrophysics; Biology; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Engineering; Astronomy & Astrophysics; Life Sciences & Biomedicine - Other Topics; Geology; Meteorology & Atmospheric Sciences GA BDT05 UT WOS:000235191500010 ER PT S AU Lorenz, RD Lunine, JI Zimmerman, W AF Lorenz, RD Lunine, JI Zimmerman, W BE Bernstein, M NavarroGonzalez, R Raulin, R TI Post-Cassini exploration of Titan: Science goals, instrumentation and mission concepts SO SPACE LIFE SCIENCES: ASTROBIOLOGY: STEPS TOWARD ORIGIN OF LIFE AND TITAN BEFORE CASSINI SE ADVANCES IN SPACE RESEARCH LA English DT Article; Proceedings Paper CT 35th COSPAR Scientific Assembly CY JUL 18-25, 2004 CL Paris, FRANCE SP Comm Space Res DE Titan; astrobiology; prebiotic chemistry; exploration ID SURFACE AB Titan promises to be a priority target for planetary and astrobiological exploration in the next decades. We survey the likely scientific objectives, instrumentation and mission architectures that may characterize the next visit to Titan. A near-surface airborne platform, perhaps an airship with some kind of surface sampling capability, appears most promising. We review recent work in the understanding of impact melt sheets and cryovolcanic flows as astrobiological 'incubators' wherein tholins produced in the atmosphere may interact with liquid water for prolonged periods, and survey technological developments that Support a near-term return to Titan. (c) 2005 COSPAR. Published by Elsevier Ltd. All rights reserved. C1 Univ Arizona, Lunar & Planetary Lab, Tucson, AZ 85721 USA. Jet Prop Lab, Pasadena, CA 91109 USA. RP Lorenz, RD (reprint author), Univ Arizona, Lunar & Planetary Lab, 1629 E Univ Blvd, Tucson, AZ 85721 USA. EM rlorenz@lpl.arizona.edu RI Lorenz, Ralph/B-8759-2016 OI Lorenz, Ralph/0000-0001-8528-4644 NR 13 TC 10 Z9 10 U1 0 U2 0 PU ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD 0X5 1GB, OXON, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2005 VL 36 IS 2 SI 2005 BP 281 EP 285 DI 10.1016/j.asr.2005.03.080 PG 5 WC Engineering, Aerospace; Astronomy & Astrophysics; Biology; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Engineering; Astronomy & Astrophysics; Life Sciences & Biomedicine - Other Topics; Geology; Meteorology & Atmospheric Sciences GA BDT05 UT WOS:000235191500022 ER PT S AU Levine, HG Piastuch, WC AF Levine, HG Piastuch, WC BE Hasenstein, KH Levine, H Porterfield, DM TI Growth patterns for etiolated soybeans germinated under spaceflight conditions SO SPACE LIFE SCIENCES: GRAVITY-RELATED EFFECTS ON PLANTS AND SPACEFLIGHT AND MAN-MADE ENVIRONMENTS ON BIOLOGICAL SYSTEMS SE ADVANCES IN SPACE RESEARCH LA English DT Article; Proceedings Paper CT 35th COSPAR Scientific Assembly CY JUL 18-25, 2004 CL Paris, FRANCE SP Comm Space Res DE spaceflight; plants; soybean; roots; space shuttle; GENEX AB In the GENEX (GENe EXpression) spaceflight experiment (flown oil STS-87), six surface sterilized soybean seeds (Glycine max cv McCall) were inserted into each of 32 autoclaved plastic seed growth pouches containing an inner germination paper sleeve (for a total of 192 seeds). The pouches were stowed within a mid-deck locker until Mission Flight Day 10, at which time an astronaut added water to initiate the process of seed germination on-orbit and Subsequently transferred them to four light-tight aluminum canisters called BRIC-60s (Biological Research In Canisters). We report here on the morphological characteristics of. (1) the recovered flight plants (N = 177), (2) the corresponding ground control Population (N = 183), plus (3) additional controls grown on the ground under clinostat conditions (N = 93). No significant morphological differences were found between the flight, ground control and clinorotated treatments for either the cotyledons or hypocotyls. There were, however, significantly longer primary roots produced in the flight population relative to the ground control population, which ill turn had significantly longer primary roots than the clinorotated population. This same pattern was observed relative to the production of lateral roots (flight > control > clinorotated). Taken together with previous literature reports, we believe that there is now sufficient evidence to conclude that plants grown under conditions of microgravity will generally exhibit enhanced root production relative to their ground control counterparts. Some causes underlying this phenomenon are speculated oil. Published by Elsevier Ltd oil behalf of COSPAR. C1 NASA, Biol Sci Off, Space Life Sci Lab, Kennedy Space Ctr, FL 32899 USA. Execusys Inc, Kennedy Space Ctr, FL 32899 USA. RP Levine, HG (reprint author), NASA, Biol Sci Off, Space Life Sci Lab, Mail Code YA-E4-B, Kennedy Space Ctr, FL 32899 USA. EM howard.g.levine@nasa.gov NR 5 TC 3 Z9 4 U1 0 U2 5 PU ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD 0X5 1GB, OXON, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2005 VL 36 IS 7 SI 2005 BP 1237 EP 1243 DI 10.1016/j.asr.2005.02.050 PG 7 WC Engineering, Aerospace; Astronomy & Astrophysics; Biophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Engineering; Astronomy & Astrophysics; Biophysics; Geology; Meteorology & Atmospheric Sciences GA BDT11 UT WOS:000235192100013 ER PT S AU Wilson, JW Tweed, J Walker, SA Cucinotta, FA Tripathi, RK Blattnig, S Mertens, CJ AF Wilson, JW Tweed, J Walker, SA Cucinotta, FA Tripathi, RK Blattnig, S Mertens, CJ BE Hei, TK Miller, J TI A procedure for benchmarking laboratory exposures with 1 A GeV iron ions SO SPACE LIFE SCIENCES: GROUND-BASED IRON-ION BIOLOGY AND PHYSICS, INCLUDING SHIELDING SE ADVANCES IN SPACE RESEARCH LA English DT Article; Proceedings Paper CT 35th COSPAR Scientific Assembly CY JUL 18-25, 2004 CL Paris, FRANCE SP Comm Space Res DE benchmark; iron ion beams; characterization ID INTERNATIONAL-SPACE-STATION; HZE PROPAGATION; TRANSPORT; FRAGMENTATION; ATMOSPHERE; DATABASES; DEPTH; WATER; NE-20; MODEL AB A new version of the HZETRN code capable of simulating HZE ions with either laboratory or space boundary conditions is under development. The computational model consists of combinations of physical perturbation expansions based on the scales of atomic interaction, multiple scattering, and nuclear reactive processes with use of asymptotic/Neumann expansions with nonperturbative corrections. The code contains energy loss with straggling, nuclear attenuation, nuclear fragmentation with energy dispersion and downshifts, and off-axis dispersion with multiple scattering under preparation. The present benchmark is for a broad directed beam for 1A GeV iron ion beams with 2A MeV width and four targets of polyethylene, polymethyl metachrylate, aluminum, and lead of varying thickness from 5 to 30 g/cm(2). The benchmark quantities will be dose, track averaged LET, dose averaged LET, fraction of iron ion remaining, and fragment energy spectra after 23 g/cm(2) of polymethyl metachrylate. (c) 2005 Published by Elsevier Ltd on behalf of COSPAR. C1 NASA, Langley Res Ctr, Hampton, VA 23681 USA. Old Dominion Univ, Norfolk, VA 23529 USA. NASA, Johnson Space Ctr, Houston, TX 77058 USA. RP Wilson, JW (reprint author), NASA, Langley Res Ctr, Hampton, VA 23681 USA. EM John.W.Wilson@Larc.Nasa.Gov NR 34 TC 4 Z9 4 U1 0 U2 0 PU PERGAMON-ELSEVIER SCIENCE LTD PI KIDLINGTON PA THE BOULEVARD, LANGFORD LANE,, KIDLINGTON OX5 1GB, OXFORD, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2005 VL 35 IS 2 BP 185 EP 193 DI 10.1016/j.asr.2005.03.108 PG 9 WC Engineering, Aerospace; Astronomy & Astrophysics; Biophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences; Physics, Applied SC Engineering; Astronomy & Astrophysics; Biophysics; Geology; Meteorology & Atmospheric Sciences; Physics GA BCO31 UT WOS:000230402100003 PM 15934193 ER PT S AU Tweed, J Walker, SA Wilson, JW Cucinotta, FA Tripathi, RK Blattnig, B Mertens, CJ AF Tweed, J Walker, SA Wilson, JW Cucinotta, FA Tripathi, RK Blattnig, B Mertens, CJ BE Hei, TK Miller, J TI Computational methods for the HZETRN code SO SPACE LIFE SCIENCES: GROUND-BASED IRON-ION BIOLOGY AND PHYSICS, INCLUDING SHIELDING SE ADVANCES IN SPACE RESEARCH LA English DT Article; Proceedings Paper CT 35th COSPAR Scientific Assembly CY JUL 18-25, 2004 CL Paris, FRANCE SP Comm Space Res DE Boltzmann's equation; Green's function; ion transport; high charge and energy ions; shielding ID PROPAGATION AB Asymptotic expansion has been used to simplify the transport of high charge and energy ions for broad beam applications in the laboratory and space. The solution of the lowest order asymptotic term is then related to a Green's function for energy loss and straggling coupled to nuclear attenuation providing the lowest order term in a rapidly converging Neumann series for which higher order collisions terms are related to the fragmentation events including energy dispersion and downshift. The first and second Neumann corrections were evaluated numerically as a standard for further analytic approximation. The first Neumann correction is accurately evaluated over the saddle point whose width is determined by the energy dispersion and located at the downshifted ion collision energy. Introduction of the first Neumann correction leads to significant simplification of the second correction term allowing application of the mean value theorem and a second saddle point approximation. The regular dependence of the second correction spectral dependence lends hope to simple approximation to higher corrections. At sufficiently high energy nuclear crosssection variations are small allowing non-perturbative methods to all orders and renormalization of the second corrections allow accurate evaluation of the full Neumann series. (c) 2005 COSPAR. Published by Elsevier Ltd. All rights reserved. C1 Old Dominion Univ, Dept Math, Norfolk, VA 23529 USA. NASA, Langley Res Ctr, Hampton, VA 23681 USA. NASA, Johnson Space Ctr, Hampton, TX 77058 USA. RP Tweed, J (reprint author), Old Dominion Univ, Dept Math, Hampton Bldg, Norfolk, VA 23529 USA. EM jtweed@odu.edu NR 9 TC 3 Z9 4 U1 0 U2 0 PU PERGAMON-ELSEVIER SCIENCE LTD PI KIDLINGTON PA THE BOULEVARD, LANGFORD LANE,, KIDLINGTON OX5 1GB, OXFORD, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2005 VL 35 IS 2 BP 194 EP 201 DI 10.1016/j.asr.2005.03.019 PG 8 WC Engineering, Aerospace; Astronomy & Astrophysics; Biophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences; Physics, Applied SC Engineering; Astronomy & Astrophysics; Biophysics; Geology; Meteorology & Atmospheric Sciences; Physics GA BCO31 UT WOS:000230402100004 PM 15934194 ER PT S AU Walker, SA Tweed, J Wilson, JW Cucinotta, FA Tripathi, RK Blattnig, S Zeitlin, C Heilbronn, L Miller, J AF Walker, SA Tweed, J Wilson, JW Cucinotta, FA Tripathi, RK Blattnig, S Zeitlin, C Heilbronn, L Miller, J BE Hei, TK Miller, J TI Validation of the HZETRN code for laboratory exposures with 1A GeV iron ions in several targets SO SPACE LIFE SCIENCES: GROUND-BASED IRON-ION BIOLOGY AND PHYSICS, INCLUDING SHIELDING SE ADVANCES IN SPACE RESEARCH LA English DT Article; Proceedings Paper CT 35th COSPAR Scientific Assembly CY JUL 18-25, 2004 CL Paris, FRANCE SP Comm Space Res DE ion transport; high charge and energy ions; Boltzmann's equation; Green's function ID MEV/NUCLEON FE-56; CROSS-SECTIONS; FRAGMENTATION; PROPAGATION; MODEL AB A new version of the HZETRN code capable of validation with HZE ions in either the laboratory or the space environment is under development. The computational model consists of the lowest order asymptotic approximation followed by a Neumann series expansion with non-perturbative corrections. The physical description includes energy loss with straggling, nuclear attenuation, nuclear fragmentation with energy dispersion and downshift. Measurements to test the model were performed at the Alternating Gradient Synchrotron and the NASA Space Radiation Laboratory at Brookhaven National Laboratory with iron ions. Surviving beam particles and produced fragments were measured with solid-state detectors. Beam analysis software has been written to relate the computational results to the measured energy loss spectra of the incident ions for rapid validation of modeled target transmission functions. (c) 2005 COSPAR. Published by Elsevier Ltd. All rights reserved. C1 Old Dominion Univ, Dept Math & Stat, Norfolk, VA 23529 USA. NASA, Langley Res Ctr, Hampton, VA 23681 USA. NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. Lawrence Berkeley Natl Lab, Berkeley, CA 94720 USA. RP Tweed, J (reprint author), Old Dominion Univ, Dept Math & Stat, Hampton Bvld, Norfolk, VA 23529 USA. EM jtweed@odu.edu RI Heilbronn, Lawrence/J-6998-2013 OI Heilbronn, Lawrence/0000-0002-8226-1057 NR 14 TC 11 Z9 11 U1 0 U2 1 PU PERGAMON-ELSEVIER SCIENCE LTD PI KIDLINGTON PA THE BOULEVARD, LANGFORD LANE,, KIDLINGTON OX5 1GB, OXFORD, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2005 VL 35 IS 2 BP 202 EP 207 DI 10.1016/j.asr.2005.02.077 PG 6 WC Engineering, Aerospace; Astronomy & Astrophysics; Biophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences; Physics, Applied SC Engineering; Astronomy & Astrophysics; Biophysics; Geology; Meteorology & Atmospheric Sciences; Physics GA BCO31 UT WOS:000230402100005 PM 15934195 ER PT S AU Aiginger, H Andersen, V Ballarini, F Battistoni, G Campanella, M Carboni, M Cerutti, F Empl, A Enghardt, W Fasso, A Ferrari, A Gadioli, E Garzelli, MV Lee, K Ottolenghi, A Parodi, K Pelliccioni, M Pinsky, L Ranft, J Roesler, S Sala, PR Scannicchio, D Smirnov, G Sommerer, F Wilson, T Zapp, N AF Aiginger, H Andersen, V Ballarini, F Battistoni, G Campanella, M Carboni, M Cerutti, F Empl, A Enghardt, W Fasso, A Ferrari, A Gadioli, E Garzelli, MV Lee, K Ottolenghi, A Parodi, K Pelliccioni, M Pinsky, L Ranft, J Roesler, S Sala, PR Scannicchio, D Smirnov, G Sommerer, F Wilson, T Zapp, N BE Hei, TK Miller, J TI The FLUKA code: New developments and application to 1 GeV/n iron beams SO SPACE LIFE SCIENCES: GROUND-BASED IRON-ION BIOLOGY AND PHYSICS, INCLUDING SHIELDING SE ADVANCES IN SPACE RESEARCH LA English DT Article; Proceedings Paper CT 35th COSPAR Scientific Assembly CY JUL 18-25, 2004 CL Paris, FRANCE SP Comm Space Res DE Monte Carlo simulations; heavy ion interactions; therapeutic beams; space dosimetry ID PET AB The modeling of ion transport and interactions in matter is a subject of growing interest, driven by the continuous increase of possible application fields. These include hadron therapy, dosimetry, and space missions, but there are also several issues involving fundamental research, accelerator physics, and cosmic ray physics, where a reliable description of heavy ion induced cascades is important. In the present work, the capabilities of the FLUKA code for ion beams will be briefly recalled and some recent developments presented. Applications of the code to the simulation of therapeutic carbon, nitrogen and oxygen ion beams, and of iron beams, which are of direct interest for space mission related experiments, will be also presented together with interesting consideration relative to the evaluation of dosimetric quantities. Both applications involve ion beams in the AGeV range. (c) 2005 Published by Elsevier Ltd on behalf of COSPAR. C1 CERN, CH-1211 Geneva, Switzerland. Univ Milan, Milan, Italy. INFM, Milan, Italy. Univ Pavia, I-27100 Pavia, Italy. Ist Nazl Fis Nucl, I-27100 Pavia, Italy. Univ Houston, Houston, TX USA. SLAC, Stanford, CA USA. Univ Siegen, Siegen, Germany. Joint Inst Nucl Res Dubna, Dubna, Russia. Forschungszentrum Rossendorf, Dresden, Germany. Tech Univ Vienna, A-1060 Vienna, Austria. NASA, JSC, Houston, TX 77058 USA. Ist Nazl Fis Nucl, Nazl Frascati Lab, I-00044 Frascati, Italy. RP Ferrari, A (reprint author), CERN, CH-1211 Geneva, Switzerland. EM alfredo.ferrari@cern.ch RI Garzelli, Maria Vittoria/G-8055-2011; sala, paola/E-2868-2013; Ballarini, Francesca/J-7293-2013; Battistoni, Giuseppe/B-5264-2012; OI sala, paola/0000-0001-9859-5564; Ballarini, Francesca/0000-0002-6629-3382; Battistoni, Giuseppe/0000-0003-3484-1724; Carboni, Massimo/0000-0003-4296-3799 NR 22 TC 19 Z9 19 U1 0 U2 3 PU PERGAMON-ELSEVIER SCIENCE LTD PI KIDLINGTON PA THE BOULEVARD, LANGFORD LANE,, KIDLINGTON OX5 1GB, OXFORD, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2005 VL 35 IS 2 BP 214 EP 222 DI 10.1016/j.asr.2005.01.090 PG 9 WC Engineering, Aerospace; Astronomy & Astrophysics; Biophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences; Physics, Applied SC Engineering; Astronomy & Astrophysics; Biophysics; Geology; Meteorology & Atmospheric Sciences; Physics GA BCO31 UT WOS:000230402100007 PM 15934197 ER PT S AU Desai, N Durante, M Lin, ZW Cucinotta, F Wu, H AF Desai, N Durante, M Lin, ZW Cucinotta, F Wu, H BE Hei, TK Miller, J TI High LET-induced H2AX phosphorylation around the Bragg curve SO SPACE LIFE SCIENCES: GROUND-BASED IRON-ION BIOLOGY AND PHYSICS, INCLUDING SHIELDING SE ADVANCES IN SPACE RESEARCH LA English DT Article; Proceedings Paper CT 35th COSPAR Scientific Assembly CY JUL 18-25, 2004 CL Paris, FRANCE SP Comm Space Res DE shielding; space radiation; high LET; heavy ions; Bragg curve; H2AX ID DOUBLE-STRAND BREAKS; LINEAR-ENERGY-TRANSFER; TRACK STRUCTURE; RADIATION; CELLS; INACTIVATION; INDUCTION; FIBROBLASTS; IRRADIATION; PROTECTION AB We investigated the spatial distribution of the induction of the phosphorylated form of the historic protein MAX (gamma-H2AX), known to be activated by DSBs. Following irradiation of human fibroblast cells with 600MeV/nucleon silicon and 600MeV/ nucleon iron ions we observed the formation of gamma-H2AX aggregates in the shape of streaks stretching over several micrometers in an x/y plane. Polyethylene shielding was used to achieve a Bragg curve distribution with beam geometry parallel to the monolayer of cells. We present data that highlights the formation of immunofluorescent gamma-H2AX tracks showing the ion trajectories across the Bragg peak of irradiated human fibroblast cells. Qualitative analyses of these distributions indicated potentially increased clustering of DNA damage before the Bragg peak, enhanced gamma-H2AX distribution at the peak, and provided visual evidence of high-linear energy transfer particle traversal of cells beyond the Bragg peak in agreement with one-dimensional transport approximations. Spatial assessment of gamma-H2AX fluorescence may provide direct insights into DNA damage across the Bragg curve for high charge and energy ions including the biological consequences of shielding and possible contributors to bystander effects. (c) 2005 Published by Elsevier Ltd on behalf of COSPAR. C1 NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. Univ Naples, Naples, Italy. Univ Alabama, Huntsville, AL 35805 USA. RP Wu, H (reprint author), NASA, Lyndon B Johnson Space Ctr, 2101 NASA Pkwy,NASA Rd 1, Houston, TX 77058 USA. EM honglu.wu-1@nasa.gov RI Durante, Marco/K-1315-2014; OI Durante, Marco/0000-0002-4615-553X NR 34 TC 16 Z9 17 U1 0 U2 2 PU PERGAMON-ELSEVIER SCIENCE LTD PI KIDLINGTON PA THE BOULEVARD, LANGFORD LANE,, KIDLINGTON OX5 1GB, OXFORD, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2005 VL 35 IS 2 BP 236 EP 242 DI 10.1016/j.asr.2005.01.010 PG 7 WC Engineering, Aerospace; Astronomy & Astrophysics; Biophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences; Physics, Applied SC Engineering; Astronomy & Astrophysics; Biophysics; Geology; Meteorology & Atmospheric Sciences; Physics GA BCO31 UT WOS:000230402100010 PM 15934200 ER PT S AU Behravesh, E Emami, K Wu, H Gonda, S AF Behravesh, E Emami, K Wu, H Gonda, S BE Hei, TK Miller, J TI Comparison of genotoxic damage in monolayer cell cultures and three-dimensional tissue-like cell assemblies SO SPACE LIFE SCIENCES: GROUND-BASED IRON-ION BIOLOGY AND PHYSICS, INCLUDING SHIELDING SE ADVANCES IN SPACE RESEARCH LA English DT Article; Proceedings Paper CT 35th COSPAR Scientific Assembly CY JUL 18-25, 2004 CL Paris, FRANCE SP Comm Space Res DE mutagenesis; radiation biology; in vitro culture; 3D tissue-like models ID LACI TRANSGENIC MICE; HUMAN LYMPHOID-CELLS; MUTATION-INDUCTION; HEAVY-IONS; MUTAGENESIS; RADIATION; MOUSE; CARCINOGENESIS; SPECTRA; SPACE AB Assessing the biological risks associated with exposure to the high-energy charged particles encountered in space is essential for the success of long-term space exploration. Although prokaryotic and eukaryotic cell models developed in our laboratory and others have advanced our understanding of many aspects of genotoxicity, in vitro models are needed to assess the risk to humans from space radiation insults. Such models must be representative of the cellular interactions present in tissues and capable of quantifying genotoxic damage. Toward this overall goal, the objectives of this study were to examine the effect of the localized microenvironment of cells, cultured as either 2-dimensional (2D) monolayers or 3-dimensional (3D) aggregates, on the rate and type of genotoxic damage resulting from exposure to Fe-charged particles, a significant portion of space radiation. We used rodent transgenic cell lines containing 50-70 copies of a LacI transgene to provide the enhanced sensitivity required to quantify mutational frequency and type in the 1100-bp LacI target as well as assessment of DNA damage to the entire 45-kbp construct. Cultured cells were exposed to high-energy Fe charged particles at Brookhaven National Laboratory's Alternating Gradient Synchrotron facility for a total dose ranging from 0.1 to 2 Gy and allowed to recover for 0-7 days, after which mutational type and frequency were evaluated. The mutational frequency was found to be higher in 3D samples than in 2D samples at all radiation doses. Mutational frequency also was higher at 7 days after irradiation than immediately after exposure. DNA sequencing of the mutant targets revealed that deletional mutations contributed an increasingly high percentage (up to 27%) of all mutations in cells as the dose was increased from 0.5 to 2 Gy. Several mutants also showed large and complex deletions in multiple locations within the Lacl target. However, no differences in mutational type were found between the 2D and the 3D samples. These 3D tissue-like model systems can reduce the uncertainty involved in extrapolating risk between in vitro cellular and in vivo models. (c) 2005 Published by Elsevier Ltd on behalf of COSPAR. C1 NASA, Johnson Space Ctr, Houston, TX 77058 USA. Univ Space Res Assoc, Div Space & Life Sci, Houston, TX 77058 USA. Wyle Labs Inc, Life Sci Syst & Serv, Houston, TX 77058 USA. RP Gonda, S (reprint author), NASA, Johnson Space Ctr, 2101 NASA Rd 1,Mail Code SJ, Houston, TX 77058 USA. EM ebehrave@emsjsc.nasa.gov; sgonda@ems.jsc.nasa.gov NR 28 TC 10 Z9 12 U1 0 U2 1 PU PERGAMON-ELSEVIER SCIENCE LTD PI KIDLINGTON PA THE BOULEVARD, LANGFORD LANE,, KIDLINGTON OX5 1GB, OXFORD, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2005 VL 35 IS 2 BP 260 EP 267 DI 10.1016/j.asr.2005.01.066 PG 8 WC Engineering, Aerospace; Astronomy & Astrophysics; Biophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences; Physics, Applied SC Engineering; Astronomy & Astrophysics; Biophysics; Geology; Meteorology & Atmospheric Sciences; Physics GA BCO31 UT WOS:000230402100014 PM 15934204 ER PT J AU Ofman, L AF Ofman, L TI MHD waves and heating in coronal holes SO SPACE SCIENCE REVIEWS LA English DT Review DE MHD; waves; coronal holes; solar wind ID SLOW MAGNETOSONIC WAVES; KINETIC ALFVEN WAVES; SPEED SOLAR-WIND; INTERPLANETARY SCINTILLATION MEASUREMENTS; OPEN MAGNETIC CONFIGURATIONS; LONG-PERIOD OSCILLATIONS; MAGNETOACOUSTIC WAVES; MAGNETOHYDRODYNAMIC TURBULENCE; RAPID ACCELERATION; OPEN ATMOSPHERE AB Coronal holes have been identified as source regions of the fast solar wind, and MHD wave activity has been detected in coronal holes by remote sensing, and in situ in fast solar wind streams. I review some of the most suggestive wave observations, and discuss the theoretical aspects of MHD wave heating and solar wind acceleration in coronal holes. I review the results of single fluid 2.5D MHD, as well as multi-fluid 2.5D MHD models of waves in coronal holes, the heating, and the acceleration of the solar wind be these waves. C1 Catholic Univ Amer, NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Ofman, L (reprint author), Catholic Univ Amer, NASA, Goddard Space Flight Ctr, Code 661, Greenbelt, MD 20771 USA. EM leon.ofman@gsfc.nasa.gov NR 97 TC 52 Z9 53 U1 1 U2 4 PU SPRINGER PI DORDRECHT PA VAN GODEWIJCKSTRAAT 30, 3311 GZ DORDRECHT, NETHERLANDS SN 0038-6308 EI 1572-9672 J9 SPACE SCI REV JI Space Sci. Rev. PY 2005 VL 120 IS 1-2 BP 67 EP 94 DI 10.1007/s11214-005-5098-1 PG 28 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 005NR UT WOS:000234831600003 ER PT J AU Roming, PWA Kennedy, TE Mason, KO Nousek, JA Ahr, L Bingham, RE Broos, PS Carter, MJ Hancock, BK Huckle, HE Hunsberger, SD Kawakami, H Killough, R Koch, TS Mclelland, MK Smith, K Smith, PJ Soto, JC Boyd, PT Breeveld, AA Holland, ST Ivanushkina, M Pryzby, MS Still, MD Stock, J AF Roming, PWA Kennedy, TE Mason, KO Nousek, JA Ahr, L Bingham, RE Broos, PS Carter, MJ Hancock, BK Huckle, HE Hunsberger, SD Kawakami, H Killough, R Koch, TS Mclelland, MK Smith, K Smith, PJ Soto, JC Boyd, PT Breeveld, AA Holland, ST Ivanushkina, M Pryzby, MS Still, MD Stock, J TI The Swift Ultra-Violet/Optical Telescope SO SPACE SCIENCE REVIEWS LA English DT Review DE Swift; Ultra-Violet/Optical Telescope; gamma-ray burst; afterglow; spectroscopy; imaging ID GAMMA-RAY BURST; PHOTON-COUNTING DETECTORS; UV/OPTICAL TELESCOPE; OPTICAL AFTERGLOWS; MIDEX MISSION; HOST GALAXY; GRB 990123; UVOT; EXTINCTION; REDSHIFT AB The Ultra-Violet/Optical Telescope (UVOT) is one of three instruments flying aboard the Swift Gamma-ray Observatory. It is designed to capture the early (similar to 1 min) UV and optical photons from the afterglow of gamma-ray bursts in the 170-600 nm hand as well as long term observations of these afterglows. This is accomplished through the use of UV and optical broadband filters and grisms. The UVOT has a modified Ritchey-Chretien design with micro-channel plate intensified charged-coupled device detectors that record the arrival time of individual photons and provide sub-arcsecond positioning of sources. We discuss some of the science to be pursued by the UVOT and the overall design of the instrument. C1 Penn State Univ, Dept Astron & Astrophys, Davey Lab 525, University Pk, PA 16802 USA. UCL, Mullard Space Sci Lab, Dorking RH5 6NT, Surrey, England. SW Res Inst, San Antonio, TX 78228 USA. UCL, Opt Sci Lab, London WC1E 6BT, England. Starsys Res Corp, Boulder, CO 80301 USA. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Swales Aerosp, Beltsville, MD 20705 USA. RP Penn State Univ, Dept Astron & Astrophys, Davey Lab 525, University Pk, PA 16802 USA. EM roming@astro.psu.edu RI Boyd, Patricia/D-3274-2012 NR 61 TC 782 Z9 783 U1 1 U2 13 PU SPRINGER PI DORDRECHT PA VAN GODEWIJCKSTRAAT 30, 3311 GZ DORDRECHT, NETHERLANDS SN 0038-6308 EI 1572-9672 J9 SPACE SCI REV JI Space Sci. Rev. PY 2005 VL 120 IS 3-4 BP 95 EP 142 DI 10.1007/s11214-005-5095-4 PG 48 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 011PM UT WOS:000235280600001 ER PT J AU Barthelmy, SD Barbier, LM Cummings, JR Fenimore, EE Gehrels, N Hullinger, D Krimm, HA Markwardt, CB Palmer, DM Parsons, A Sato, G Suzuki, M Takahashi, T Tashiro, M Tueller, J AF Barthelmy, SD Barbier, LM Cummings, JR Fenimore, EE Gehrels, N Hullinger, D Krimm, HA Markwardt, CB Palmer, DM Parsons, A Sato, G Suzuki, M Takahashi, T Tashiro, M Tueller, J TI The burst alert telescope (BAT) on the Swift MIDEX mission SO SPACE SCIENCE REVIEWS LA English DT Review DE gamma-ray; GRB; hard X-ray; survey; burst; afterglow; CZT; coded aperture; astrophysics; cosmology ID GAMMA-RAY BURST; 28 FEBRUARY 1997 AB The burst alert telescope (BAT) is one of three instruments on the Swift MIDEX spacecraft to study gamma-ray bursts (GRBs). The BAT first detects the GRB and localizes the burst direction to an accuracy of 1-4 arcmin within 20s after the start of the event. The GRB trigger initiates an autonomous spacecraft slew to point the two narrow field-of-view (FOV) instruments at the burst location within 20-70 s so to make follow-up X-ray and optical observations. The BAT is a wide-FOV, coded-aperture instrument with a CdZnTe detector plane. The detector plane is composed of 32,768 pieces of CdZnTe (4x4x2 mm), and the coded-aperture mask is composed of similar to 52,000 pieces of lead (5x5x1 mm) with a 1-m separation between mask and detector plane. The BAT operates over the 15-150 keV energy range with similar to 7 keV resolution, a sensitivity of similar to 10(-8) ergg s(-1) cm(-2), and a 1.4 sr (half-coded) FOV. We expect to detect >100 GRBs/year for a 2-year mission. The BAT also performs an all-sky hard X-ray survey with a sensitivity of similar to 2 m Crab (systematic limit) and it serves as a hard X-ray transient monitor. C1 NASA, Goddard Space Flight Ctr, High Energy Phys Lab, Greenbelt, MD 20771 USA. CNR, Washington, DC 20418 USA. Los Alamos Natl Lab, Los Alamos, NM 87545 USA. Univ Maryland, Dept Astron, College Pk, MD 20742 USA. Univ Space Res Assoc, Columbia, MD 21044 USA. Inst Space & Astronaut Sci, Kanagawa 2298510, Japan. Univ Tokyo, Dept Phys, Bunkyo Ku, Tokyo 113, Japan. RP Barthelmy, SD (reprint author), NASA, Goddard Space Flight Ctr, High Energy Phys Lab, Greenbelt, MD 20771 USA. EM scott@milkyway.gsfc.nasa.gov RI Gehrels, Neil/D-2971-2012; Tueller, Jack/D-5334-2012; Barthelmy, Scott/D-2943-2012; Parsons, Ann/I-6604-2012; Tashiro, Makoto/J-4562-2012 NR 9 TC 811 Z9 814 U1 5 U2 19 PU SPRINGER PI DORDRECHT PA VAN GODEWIJCKSTRAAT 30, 3311 GZ DORDRECHT, NETHERLANDS SN 0038-6308 J9 SPACE SCI REV JI Space Sci. Rev. PY 2005 VL 120 IS 3-4 BP 143 EP 164 DI 10.1007/s11214-005-5096-3 PG 22 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 011PM UT WOS:000235280600002 ER PT J AU Burrows, DN Hill, JE Nousek, JA Kennea, JA Wells, A Osborne, JP Abbey, AF Beardmore, A Mukerjee, K Short, ADT Chincarini, G Campana, S Citterio, O Moretti, A Pagani, C Tagliaferri, G Giommi, P Capalbi, M Tamburelli, F Angelini, L Cusumano, G Brauninger, HW Burkert, W Hartner, GD AF Burrows, DN Hill, JE Nousek, JA Kennea, JA Wells, A Osborne, JP Abbey, AF Beardmore, A Mukerjee, K Short, ADT Chincarini, G Campana, S Citterio, O Moretti, A Pagani, C Tagliaferri, G Giommi, P Capalbi, M Tamburelli, F Angelini, L Cusumano, G Brauninger, HW Burkert, W Hartner, GD TI The Swift X-ray telescope SO SPACE SCIENCE REVIEWS LA English DT Review DE gamma-ray burst; X-ray telescope; Swift; X-ray instrumentation; X-ray CCD detector; X-ray mirrors ID TO-END TESTS; AFTERGLOW; PERFORMANCE; SPECTRUM; MISSION; BURSTS; EJECTA; XMM AB The Swift Gamma-Ray Explorer is designed to make prompt multiwavelength observations of gamma-ray bursts (GRBs) and GRB afterglows. The X-ray telescope (XRT) enables Swift to determine GRB positions with a few arcseconds accuracy within 100 s of the burst onset. The XRT utilizes a mirror set built for JET-X and an XMM-Newton/EPIC MOS CCD detector to provide a sensitive broad-band (0.2-10 keV) X-ray imager with effective area of >= 120 cm(2) at 1.5 keV, field of view of 23.6x23.6 arcminutes, and angular resolution of 18 arcseconds (HPD). The detection sensitivity is 2x10(-14) erg cm(-2) s(-1) in 10(4) s. The instrument is designed to provide automated source detection and position reporting within 5 s of target acquisition. It can also measure the redshifts of GRBs with Fe line emission or other spectral features. The XRT operates in an auto-exposure mode, adjusting the CCD readout mode automatically to optimize the science return for each frame as the source intensity fades. The XRT will measure spectra and lightcurves of the GRB afterglow beginning about a minute after the burst and will follow each burst for days or weeks. C1 Univ Leicester, Space Res Ctr, Leicester LE1 7RH, Leics, England. Osserv Astron Brera, INAF, I-23807 Merate, Italy. ASI Sci Data Ctr, I-00044 Frascati, Italy. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20071 USA. INAF, Ist Astrofis Spaziale & fis Cosm, Sez Palermo, I-90146 Palermo, Italy. Max Planck Inst Extraterr Phys, D-37075 Garching, Germany. RP Penn State Univ, Davey Lab 525, University Pk, PA 16802 USA. EM barrows@astro.psu.edu OI moretti, alberto/0000-0002-9770-0315 NR 27 TC 1170 Z9 1171 U1 3 U2 20 PU SPRINGER PI DORDRECHT PA VAN GODEWIJCKSTRAAT 30, 3311 GZ DORDRECHT, NETHERLANDS SN 0038-6308 EI 1572-9672 J9 SPACE SCI REV JI Space Sci. Rev. PY 2005 VL 120 IS 3-4 BP 165 EP 195 DI 10.1007/s11214-005-5097-2 PG 31 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 011PM UT WOS:000235280600003 ER PT J AU Lissauer, JJ AF Lissauer, JJ TI Formation of the outer planets SO SPACE SCIENCE REVIEWS LA English DT Review DE planet formation; giant planets; solar nebula ID T-TAURI STARS; GIANT PLANETS; SOLAR NEBULA; DYNAMICAL INSTABILITIES; PLANETESIMAL FORMATION; PROTOPLANET FORMATION; ORBITAL MIGRATION; SYSTEMS; ACCRETION; DISKS AB Models of the origins of gas giant planets and 'ice' giant planets are discussed and related to formation theories of both smaller objects (terrestrial planets) and larger bodies (stars). The most detailed models of planetary formation are based upon observations of our own Solar System, of young stars and their environments, and of extrasolar planets. Stars form from the collapse, and sometimes fragmentation, of molecular cloud cores. Terrestrial planets are formed within disks around young stars via the accumulation of small dust grains into larger and larger bodies until the planetary orbits become well enough separated that the configuration is stable for the lifetime of the system. Uranus and Neptune almost certainly formed via a bottom-up (terrestrial planet-like) mechanism; such a mechanism is also the most likely origin scenario for Saturn and Jupiter. C1 NASA, Ames Res Ctr, Div Space Sci, Moffett Field, CA 94035 USA. RP NASA, Ames Res Ctr, Div Space Sci, MS 245-3, Moffett Field, CA 94035 USA. NR 79 TC 10 Z9 10 U1 3 U2 5 PU SPRINGER PI DORDRECHT PA VAN GODEWIJCKSTRAAT 30, 3311 GZ DORDRECHT, NETHERLANDS SN 0038-6308 EI 1572-9672 J9 SPACE SCI REV JI Space Sci. Rev. PY 2005 VL 116 IS 1-2 BP 11 EP 24 DI 10.1007/s11214-005-1945-3 PG 14 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 932VJ UT WOS:000229582300003 ER PT J AU Johnson, TV AF Johnson, TV TI Geology of the icy satellites SO SPACE SCIENCE REVIEWS LA English DT Review DE outer planets; icy satellites; cratering; oceans; cryovolcanism; tectonic resurfacing ID INFRARED MAPPING SPECTROMETER; DIFFERENTIATED INTERNAL STRUCTURE; OUTER SOLAR-SYSTEM; SUBSURFACE OCEAN; GALILEAN SATELLITES; EUROPAS SURFACE; CALLISTO; TITAN; EVOLUTION; ENCOUNTERS AB In the last 25 years, the explorations of the Voyager and Galileo missions have resulted in an entirely new view of the icy worlds orbiting the giant outer planets. These objects show a huge diversity in their characteristics, resulting from their formation histories, internal processes and interactions with their space environments. This paper will review the current state of knowledge about the icy satellites and discuss the exciting prospects for the upcoming Cassini/Huygens mission as it begins a new era of exploration of the Saturn satellite system. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM torrence.v.johnson@jpl.nasa.gov NR 50 TC 7 Z9 8 U1 0 U2 2 PU SPRINGER PI DORDRECHT PA VAN GODEWIJCKSTRAAT 30, 3311 GZ DORDRECHT, NETHERLANDS SN 0038-6308 EI 1572-9672 J9 SPACE SCI REV JI Space Sci. Rev. PY 2005 VL 116 IS 1-2 BP 401 EP 420 DI 10.1007/s11214-005-1963-1 PG 20 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 932VJ UT WOS:000229582300021 ER PT J AU Cruikshank, DP AF Cruikshank, DP TI Triton, Pluto, Centaurs, and trans-Neptunian bodies SO SPACE SCIENCE REVIEWS LA English DT Review DE Triton; Pluto; Centaurs; Kuiper Belt Objects; ice; infrared spectroscopy ID KUIPER-BELT OBJECTS; NEAR-INFRARED SPECTROSCOPY; SURFACE-COMPOSITION; OPTICAL-CONSTANTS; SOLAR-SYSTEM; WATER ICE; ATMOSPHERE; ASTEROIDS; BINARIES; METHANE AB The diverse populations of icy bodies of the outer Solar System (OSS) give critical information on the composition and structure of the solar nebula and the early phases of planet formation. The two principal repositories of icy bodies are the Kuiper belt or disk, and the Oort Cloud. both of which are the source regions of the comets. Nearly 1000 individual Kuiper belt objects have been discovered, their dynamical distribution is a clue to the early outward migration and gravitational scattering power of Neptune. Pluto is perhaps the largest Kuiper belt object. Pluto is distinguished by its large satellite, a variable atmosphere, and a Surface composed of several ices and probable organic solid materials that give it color. Triton is probably a former member of the Kuiper belt population, suggested by its retrograde orbit as a satellite of Neptune. Like Pluto, Triton has a variable atmosphere, compositionally diverse icy surface, and an organic atmospheric haze. Centaur objects appear to come from the Kuiper belt and Occupy temporary orbits in the planetary zone, the compositional similarity of one well studied Centaur (5145 Pholus) to comets is notable. New discoveries continue apace, as observational surveys reveal new objects and refined observing techniques yield more physical information about specific bodies. C1 NASA, Ames Res Ctr, Astrophys Branch, Moffett Field, CA 94035 USA. RP NASA, Ames Res Ctr, Astrophys Branch, Mail Stop 245-6, Moffett Field, CA 94035 USA. EM Dale.P.Cruikshank@nasa.gov NR 72 TC 11 Z9 11 U1 1 U2 3 PU SPRINGER PI DORDRECHT PA VAN GODEWIJCKSTRAAT 30, 3311 GZ DORDRECHT, NETHERLANDS SN 0038-6308 EI 1572-9672 J9 SPACE SCI REV JI Space Sci. Rev. PY 2005 VL 116 IS 1-2 BP 421 EP 439 DI 10.1007/s11214-005-1964-0 PG 19 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 932VJ UT WOS:000229582300022 ER PT S AU Douglas, DM Ku, JT Ottenstein, L Swanson, T Hess, S Darrin, A AF Douglas, DM Ku, JT Ottenstein, L Swanson, T Hess, S Darrin, A BE ElGenk, MS TI Effect of variable emittance coatings on the operation of a miniature loop heat pipe SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM-STAIF 2005 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum CY FEB 13-17, 2005 CL Albuquerque, NM SP Boeing Co, Lockheed Martin, Los Alamos Natl Lab, Sandia Natl Labs, Northrop Grumman Space Technol, Stirling Technol Co, US DOE, Amer Astronaut Soc, Amer Inst Aeronaut & Astronaut, Natl & Local Sect, Amer Inst Chem Engineers, Amer Soc Mech Engineers, Heat Transfer Div, NASA Natl Space Grant Coll & Fellowship Program, Profess Aerosp Contractors Assoc, Inst Space & Nucl Power Studies AB As the size of spacecraft shrink to accommodate small and more efficient instruments, smaller launch vehicles, and constellation missions, all subsystems must also be made smaller. Under NASA NRA 03-OSS-02, Space Technology-8 (ST 8), NASA Goddard Space Flight Center and Jet Propulsion Laboratory jointly conducted a Concept Definition study to develop a miniature loop heat pipe (loop heat pipe) thermal management system design suitable for future small spacecraft. The proposed loop heat pipe thermal management system consists of a miniature loop heat pipe (LHP) and deployable radiators that are coated with variable emittance coatings (VECs). As part of the Phase A study and proof of the design concept, variable emittance coatings were integrated with a breadboard miniature loop heat pipe. The entire system was tested under vacuum at various temperature extremes and power loads. This paper summarizes the results of this testing and shows the effect of the VEC on the operation of a miniature loop heat pipe. C1 NASA, Goddard Space Flight Ctr, Thermal Engn Branch, Greenbelt, MD 20771 USA. RP Douglas, DM (reprint author), NASA, Goddard Space Flight Ctr, Thermal Engn Branch, MS 545, Greenbelt, MD 20771 USA. RI Darrin, Margaret/H-4305-2011 NR 6 TC 3 Z9 3 U1 1 U2 2 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 0-7354-0230-2 J9 AIP CONF PROC PY 2005 VL 746 BP 82 EP 89 PG 8 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BBS02 UT WOS:000227496400010 ER PT S AU Martin, J Mireles, O Reid, R AF Martin, J Mireles, O Reid, R BE ElGenk, MS TI Multiple restart testing of a stainless steel sodium heat pipe module SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM-STAIF 2005 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum CY FEB 13-17, 2005 CL Albuquerque, NM SP Boeing Co, Lockheed Martin, Los Alamos Natl Lab, Sandia Natl Labs, Northrop Grumman Space Technol, Stirling Technol Co, US DOE, Amer Astronaut Soc, Amer Inst Aeronaut & Astronaut, Natl & Local Sect, Amer Inst Chem Engineers, Amer Soc Mech Engineers, Heat Transfer Div, NASA Natl Space Grant Coll & Fellowship Program, Profess Aerosp Contractors Assoc, Inst Space & Nucl Power Studies ID TECHNOLOGY; SUPPORT; SYSTEM AB A heat pipe cooled reactor is one of several candidate reactor concepts being considered for space power and propulsion systems to support future space exploration activities. Long life heat pipe modules, with concepts verified through a combination of theoretical analysis and experimental evaluations, would be necessary to establish the viability of this option. A number of stainless steel/sodium heat pipe modules have been designed and fabricated to support experimental testing of a Safe Affordable Fission Engine (SAFE) project, a 100-kWt core design pursued jointly by the Marshall Space Flight Center and the Los Alamos National Laboratory. One of the SAFE heat pipe modules was successfully subjected to over 200 restarts, examining the behavior of multiple passive freeze/thaw operations. Typical operation included a 1-hour startup to an average evaporator temperature of 1000 K followed by a 15-minute hold at temperature. Nominal maximum input power to the evaporator (measured at the power supply) during the hold period was 1.9 kW, with approximately 1.6 kW calculated as the axial power transfer to the condenser (the 300W difference was lost to environment at the evaporator surface). Between heating cycles the module was cooled to less than 325 K, returning the sodium to a frozen state in preparation for the next startup cycle. C1 NASA, George C Marshall Space Flight Ctr, Huntsville, AL 35812 USA. RP Martin, J (reprint author), NASA, George C Marshall Space Flight Ctr, TD40, Huntsville, AL 35812 USA. NR 15 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 0-7354-0230-2 J9 AIP CONF PROC PY 2005 VL 746 BP 150 EP 157 PG 8 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BBS02 UT WOS:000227496400018 ER PT S AU Devarakonda, A Xiong, DX Beach, DE AF Devarakonda, A Xiong, DX Beach, DE BE ElGenk, MS TI Intermediate temperature water heat pipe tests SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM-STAIF 2005 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum CY FEB 13-17, 2005 CL Albuquerque, NM SP Boeing Co, Lockheed Martin, Los Alamos Natl Lab, Sandia Natl Labs, Northrop Grumman Space Technol, Stirling Technol Co, US DOE, Amer Astronaut Soc, Amer Inst Aeronaut & Astronaut, Natl & Local Sect, Amer Inst Chem Engineers, Amer Soc Mech Engineers, Heat Transfer Div, NASA Natl Space Grant Coll & Fellowship Program, Profess Aerosp Contractors Assoc, Inst Space & Nucl Power Studies AB Heat pipes are among the most promising technologies for space radiator systems. Water heat pipes are explored in the intermediate temperature range of 400 to above 500 K. The thermodynamic and thermo-physical properties of water are reviewed in this temperature range. Test data are reported for a copper-water heat pipe. The heat pipe was tested under different orientations. Water heat pipes show promise in this temperature range. Fabrication and testing issues are being addressed. C1 NASA, Glenn Res Ctr, SEST, Cleveland, OH 44135 USA. RP Devarakonda, A (reprint author), NASA, Glenn Res Ctr, SEST, Mail Stop 301-2,21000 Brookpk Rd, Cleveland, OH 44135 USA. NR 3 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 0-7354-0230-2 J9 AIP CONF PROC PY 2005 VL 746 BP 158 EP 163 PG 6 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BBS02 UT WOS:000227496400019 ER PT S AU Devarakonda, A Anderson, WG AF Devarakonda, A Anderson, WG BE ElGenk, MS TI Thermo-physical properties of intermediate temperature heat pipe fluids SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM-STAIF 2005 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum CY FEB 13-17, 2005 CL Albuquerque, NM SP Boeing Co, Lockheed Martin, Los Alamos Natl Lab, Sandia Natl Labs, Northrop Grumman Space Technol, Stirling Technol Co, US DOE, Amer Astronaut Soc, Amer Inst Aeronaut & Astronaut, Natl & Local Sect, Amer Inst Chem Engineers, Amer Soc Mech Engineers, Heat Transfer Div, NASA Natl Space Grant Coll & Fellowship Program, Profess Aerosp Contractors Assoc, Inst Space & Nucl Power Studies AB Heat pipes are among the most promising technologies for space radiator systems. The paper reports further evaluation of potential heat pipe fluids in the intermediate temperature range of 400 to 700 K in continuation of two recent reports. More thermo-physical property data are examined. Organic, inorganic and elemental substances are considered. The evaluation of surface tension and other fluid properties are examined. Halides are evaluated as potential heat pipe fluids. Reliable data are not available for all fluids and further database development is necessary. Many of the fluids considered are promising candidates as heat pipe fluids. Water is promising as a heat pipe fluid up to 500-550 K. Life test data for thermo-chemical compatibility are almost non-existent. C1 NASA, Glenn Res Ctr, SEST, Cleveland, OH 44135 USA. RP Devarakonda, A (reprint author), NASA, Glenn Res Ctr, SEST, Mail Stop 302-1,21000 Brookpk Rd, Cleveland, OH 44135 USA. NR 16 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 0-7354-0230-2 J9 AIP CONF PROC PY 2005 VL 746 BP 179 EP 186 PG 8 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BBS02 UT WOS:000227496400022 ER PT S AU Maize, EH AF Maize, EH BE ElGenk, MS TI The Cassini-Huygens mission to Saturn and Titan SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM-STAIF 2005 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum CY FEB 13-17, 2005 CL Albuquerque, NM SP Boeing Co, Lockheed Martin, Los Alamos Natl Lab, Sandia Natl Labs, Northrop Grumman Space Technol, Stirling Technol Co, US DOE, Amer Astronaut Soc, Amer Inst Aeronaut & Astronaut, Natl & Local Sect, Amer Inst Chem Engineers, Amer Soc Mech Engineers, Heat Transfer Div, NASA Natl Space Grant Coll & Fellowship Program, Profess Aerosp Contractors Assoc, Inst Space & Nucl Power Studies AB The Cassini-Huygens mission is an international collaboration whose goal is an intense and detailed study of Saturn and its system. This paper provides an overview of the mission, the two spacecraft, their instruments, and scientific objectives. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91011 USA. RP Maize, EH (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91011 USA. NR 3 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 0-7354-0230-2 J9 AIP CONF PROC PY 2005 VL 746 BP 223 EP 231 PG 9 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BBS02 UT WOS:000227496400027 ER PT S AU Edgington, SG AF Edgington, SG BE ElGenk, MS TI The Cassini-Huygens Mission: Its science and instruments SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM-STAIF 2005 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum CY FEB 13-17, 2005 CL Albuquerque, NM SP Boeing Co, Lockheed Martin, Los Alamos Natl Lab, Sandia Natl Labs, Northrop Grumman Space Technol, Stirling Technol Co, US DOE, Amer Astronaut Soc, Amer Inst Aeronaut & Astronaut, Natl & Local Sect, Amer Inst Chem Engineers, Amer Soc Mech Engineers, Heat Transfer Div, NASA Natl Space Grant Coll & Fellowship Program, Profess Aerosp Contractors Assoc, Inst Space & Nucl Power Studies ID SATURNIAN SYSTEM AB The Cassini-Huygens Mission is the first return to the Saturnian system since it was last visited in 1981. While Voyager provided our first detailed glimpse of the planet, Cassini goes far beyond with a suite of modem instrumentation covering large spectral and particle energy ranges and a 4-year tour. The Huygens probe will provide our first in-situ observations of a moon other than our own. This paper provides an overview of the mission's science objectives along with the discoveries that have already created much excitement in the scientific and non-scientific communities. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Edgington, SG (reprint author), CALTECH, Jet Prop Lab, MS 230-205,Oak Grove Dr, Pasadena, CA 91109 USA. NR 7 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 0-7354-0230-2 J9 AIP CONF PROC PY 2005 VL 746 BP 240 EP 248 PG 9 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BBS02 UT WOS:000227496400029 ER PT S AU Satter, CM AF Satter, CM BE ElGenk, MS TI JIMO follow-on mission studies SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM-STAIF 2005 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum CY FEB 13-17, 2005 CL Albuquerque, NM SP Boeing Co, Lockheed Martin, Los Alamos Natl Lab, Sandia Natl Labs, Northrop Grumman Space Technol, Stirling Technol Co, US DOE, Amer Astronaut Soc, Amer Inst Aeronaut & Astronaut, Natl & Local Sect, Amer Inst Chem Engineers, Amer Soc Mech Engineers, Heat Transfer Div, NASA Natl Space Grant Coll & Fellowship Program, Profess Aerosp Contractors Assoc, Inst Space & Nucl Power Studies AB Team Prometheus is a geographically-distributed, collaborative engineering team composed of representatives from several NASA centers and the Department of Energy (DOE). During the months of April through September 2004, Team Prometheus performed studies of representative Saturn/Titan and Neptune/Triton science missions based on proposed Jupiter Icy Moons Orbiter (JIMO) technology. The principal objectives of these studies were: 1) to assess the feasibility of using direct copies of the baseline JIMO flight system designs to perform these follow-on missions, and 2) to identify and assess technologies or potential enhancements or alterations to the baseline JIMO designs which could reduce the cruise durations to meet NASA Headquarters-specified programmatic goals. A tertiary objective was to provide feedback to the JIMO Project on the suitability of the JIMO reference designs for potential follow-on applications. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91001 USA. RP Satter, CM (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91001 USA. NR 2 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 0-7354-0230-2 J9 AIP CONF PROC PY 2005 VL 746 BP 249 EP 257 PG 9 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BBS02 UT WOS:000227496400030 ER PT S AU Randolph, JE Davis, MR Leavens, TJ Miyake, RN AF Randolph, JE Davis, MR Leavens, TJ Miyake, RN BE ElGenk, MS TI A waverider application of an advanced nuclear power source SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM-STAIF 2005 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum CY FEB 13-17, 2005 CL Albuquerque, NM SP Boeing Co, Lockheed Martin, Los Alamos Natl Lab, Sandia Natl Labs, Northrop Grumman Space Technol, Stirling Technol Co, US DOE, Amer Astronaut Soc, Amer Inst Aeronaut & Astronaut, Natl & Local Sect, Amer Inst Chem Engineers, Amer Soc Mech Engineers, Heat Transfer Div, NASA Natl Space Grant Coll & Fellowship Program, Profess Aerosp Contractors Assoc, Inst Space & Nucl Power Studies AB The development of an aerodynamic vehicle (waverider) for interplanetary trajectories would include the application of an advanced Radioisotope Power Source (RPS) for power. The RPS would supply power during interplanetary cruise as well as during the planetary atmospheric passes that are part of the Aero-Gravity Assist (AGA) interplanetary trajectory. The operational systems of the spacecraft would be enclosed within the waverider airframe structure, including the RPS units to protect the components from the extreme thermal environment encountered during the atmospheric passes. The waverider operates by riding on its own hypersonic shock on its lower surface. This surface must survive the extreme operational temperatures during an atmospheric pass. However, the upper surface of the waverider remains relatively cool and would be the location of the thermal radiator for the RPS that would be mounted within the spacecraft structure. It is this remote relationship between the RPS and its radiator that makes this application so unique. The paper would describe the configuration of the waverider spacecraft and its accommodation of an RPS power source. In addition, a Pluto mission would be discussed as an example of a scientific exploration mission that is enabled by an AGA trajectory using a waverider. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Randolph, JE (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 20 TC 1 Z9 1 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 0-7354-0230-2 J9 AIP CONF PROC PY 2005 VL 746 BP 258 EP 270 PG 13 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BBS02 UT WOS:000227496400031 ER PT S AU Spilker, TR AF Spilker, TR BE ElGenk, MS TI A non-NEP implementation of NASA's "Neptune Orbiter with Probes" vision mission SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM-STAIF 2005 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum CY FEB 13-17, 2005 CL Albuquerque, NM SP Boeing Co, Lockheed Martin, Los Alamos Natl Lab, Sandia Natl Labs, Northrop Grumman Space Technol, Stirling Technol Co, US DOE, Amer Astronaut Soc, Amer Inst Aeronaut & Astronaut, Natl & Local Sect, Amer Inst Chem Engineers, Amer Soc Mech Engineers, Heat Transfer Div, NASA Natl Space Grant Coll & Fellowship Program, Profess Aerosp Contractors Assoc, Inst Space & Nucl Power Studies AB The "Neptune Orbiter with Probes" (NOP) mission concept is one of the 17 Vision Mission cases for study in NASA's 2003 Vision Missions Studies NRA (NRA-03-OSS-01-VM). Its primary science goals are to provide detailed information about the composition and internal structure of the "ice giant" planet Neptune, for comparison to the gas giant planets Jupiter and Saturn. NASA selected two teams to study the mission concept, one using a Nuclear Electric Power and Propulsion (NEPP) implementation for transfer to and orbit insertion at Neptune, one using Solar Electric Propulsion (SEP) and/or gravity assist (GA) for transfer to Neptune, aerocapture for orbit insertion, and a Radioisotope Power Source (RPS) for electric power. Prof Andy Ingersoll of Caltech is the PI of the non-NEPP team, which includes a nine-member science team covering the major science objectives to be addressed in the Neptune system and an engineering team with experts from Caltech, JPL and its "Team X", and three NASA centers. Various combinations of SEP and GA yield relatively short similar to 12-year transfers to Neptune, and high Neptune approach V. and orbit insertion delta-V (similar to 7 km/s) that is better done using aerocapture than using chemical propulsion. After probe delivery and capture into orbit, Triton, perhaps a former Kuiper Belt object, is the "tour engine" that drives a three-year (minimum) tour, much as Cassini uses Titan. In different phases over the science mission lifetime the evolving orbit optimizes investigation of Neptune's magnetosphere, rings, and inner satellite system, as well as structure, composition, and dynamics of the planet itself Team X and our team members, including aerocapture experts from NASA's Aerocapture Systems Analysis Team and students, studied ground and flight systems designs and technology needs. This paper discusses the innovative process by which the NOP mission concept was studied, the team performing the studies, science objectives, and high-level results. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Spilker, TR (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 4 TC 0 Z9 0 U1 2 U2 4 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 0-7354-0230-2 J9 AIP CONF PROC PY 2005 VL 746 BP 271 EP 278 PG 8 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BBS02 UT WOS:000227496400032 ER PT S AU Schmidt, GR Abelson, RD Wiley, RL AF Schmidt, GR Abelson, RD Wiley, RL BE ElGenk, MS TI Benefit of small radioisotope power systems for NASA exploration missions SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM-STAIF 2005 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum CY FEB 13-17, 2005 CL Albuquerque, NM SP Boeing Co, Lockheed Martin, Los Alamos Natl Lab, Sandia Natl Labs, Northrop Grumman Space Technol, Stirling Technol Co, US DOE, Amer Astronaut Soc, Amer Inst Aeronaut & Astronaut, Natl & Local Sect, Amer Inst Chem Engineers, Amer Soc Mech Engineers, Heat Transfer Div, NASA Natl Space Grant Coll & Fellowship Program, Profess Aerosp Contractors Assoc, Inst Space & Nucl Power Studies AB The increased use of smaller spacecraft over the last decade, in combination with studies of potential science applications, has suggested the need for Radioisotope Power Systems (RPSs) yielding much lower power levels than the 100 watt-scale devices used in the past. Small milliwatt to multiwatt-scale RPS units have the potential to extend the capability of small science payloads and instruments, and to enable many new mission applications. Such units could also find application in future human exploration missions involving use of monitoring stations and autonomous devices, similar to the ALSEP units deployed on the Moon during the Apollo program. Although flight-qualified RPS units in this size and power range do not presently exist, their potential to support a broad range of exploration tasks has led NASA and the Department of Energy (DOE) to consider the development of small-RPS units such that they might be available for missions by the early part of next decade. This paper summarizes the results of activities to date and provides possible options for future development. C1 NASA, Sci Miss Directorate, Washington, DC 20546 USA. RP Schmidt, GR (reprint author), NASA, Sci Miss Directorate, Washington, DC 20546 USA. NR 10 TC 0 Z9 0 U1 0 U2 1 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 0-7354-0230-2 J9 AIP CONF PROC PY 2005 VL 746 BP 295 EP 302 PG 8 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BBS02 UT WOS:000227496400035 ER PT S AU Abelson, RD Shirley, JH AF Abelson, RD Shirley, JH BE ElGenk, MS TI Exploring europa with a surface lander powered by a small radioisotope power system (RPS) SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM-STAIF 2005 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum CY FEB 13-17, 2005 CL Albuquerque, NM SP Boeing Co, Lockheed Martin, Los Alamos Natl Lab, Sandia Natl Labs, Northrop Grumman Space Technol, Stirling Technol Co, US DOE, Amer Astronaut Soc, Amer Inst Aeronaut & Astronaut, Natl & Local Sect, Amer Inst Chem Engineers, Amer Soc Mech Engineers, Heat Transfer Div, NASA Natl Space Grant Coll & Fellowship Program, Profess Aerosp Contractors Assoc, Inst Space & Nucl Power Studies AB Europa is a high-priority target for future exploration because of the possibility that it may possess a subsurface liquid ocean that could sustain life. Exploring the surface of this Galilean moon, however, represents a formidable technical challenge due to the great distances involved, the high ambient radiation, and the extremely low surface temperatures. A design concept is presented for a Europa Lander Mission (ELM) powered by a small radioisotope power system (RPS) that could fly aboard the proposed Jupiter Icy Moons Orbiter (JIMO). The ELM would perform in-situ science measurements for a minimum of 30 Earth days, equivalent to approximately 8.5 Europa days. The primary science goals for the Europa lander would include astrobiology and geophysics experiments and determination of surface composition. Science measurements would include visual imagery, microseismometry, Raman spectroscopy, Laser Induced Breakdown Spectroscopy (LIBS), and measurements of surface temperature and radiation levels. The ELM spacecraft would be transported to Europa via the JIMO spacecraft as an auxiliary payload with an extended duration cruise phase (up to 13 years). After arriving at Europa, ELM would separate from JIMO and land on the moon's surface to conduct the nominal science mission. In addition to transportation, the JIMO mothership would be used to relay all lander data back to Earth, thus reducing the size and power requirement of the lander communications system. Conventional power sources were evaluated and found to be impractical for this mission due to the extended duration, low level of solar insolation (similar to 3.7% of Earth's), the low surface temperatures (as low as 85K), and the 1.75 days of eclipse every Europa day. In contrast, a small-RPS would enable the ELM mission by powering the lander and keeping all key instrumentation and subsystems warm during the cruise and landed phases of the mission. The conceptual small-RPS is based on the existing General Purpose Heat Source (GPHS) module using thermoelectric conversion. This would generate 225 Wt (thermal) and 10.1 We (electric) at the end of the mission, and would provide an energy margin exceeding 100%. A small rechargeable lithium-ion battery would be used to handle peak load demands during the short-duration communication events and while using the higher-power instrumentation (LIBS and Raman). In summary, small-RPS technology could enable an exciting, scientifically valuable Europa lander mission designed to verify the existence of a subsurface ocean, and to search for signs of past or present life. C1 CALTECH, Miss & Syst Architecture Sect, Jet Prop Lab, Pasadena, CA 91109 USA. RP Abelson, RD (reprint author), CALTECH, Miss & Syst Architecture Sect, Jet Prop Lab, 4800 Oak Grove Dr,Mail Stop 301-445, Pasadena, CA 91109 USA. NR 12 TC 0 Z9 0 U1 0 U2 4 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 0-7354-0230-2 J9 AIP CONF PROC PY 2005 VL 746 BP 303 EP 317 PG 15 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BBS02 UT WOS:000227496400036 ER PT S AU Randolph, JE Abelson, RD Alkalai, L Collins, DH Moore, WV AF Randolph, JE Abelson, RD Alkalai, L Collins, DH Moore, WV BE ElGenk, MS TI An adjunct Galilean Satellite Orbiter concept using a small nuclear power source SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM-STAIF 2005 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum CY FEB 13-17, 2005 CL Albuquerque, NM SP Boeing Co, Lockheed Martin, Los Alamos Natl Lab, Sandia Natl Labs, Northrop Grumman Space Technol, Stirling Technol Co, US DOE, Amer Astronaut Soc, Amer Inst Aeronaut & Astronaut, Natl & Local Sect, Amer Inst Chem Engineers, Amer Soc Mech Engineers, Heat Transfer Div, NASA Natl Space Grant Coll & Fellowship Program, Profess Aerosp Contractors Assoc, Inst Space & Nucl Power Studies AB An adjunct spacecraft concept known as the Galilean Satellite Orbiter (GSO) could gather and return significant science data using a payload consisting of plasma science and other instruments in orbit around each of three Galilean satellites using many advanced technology elements. The key to the viability of this concept is the existence of a small Radioisotope Power System (RPS) (single GPHS) and a mother spacecraft that could deliver the GSO to its final orbit and act as a relay communications path back to the Earth. Thus, the GSO would be dependant at Jupiter on the proposed Jupiter Icy Moons Orbiter (JIMO) or similar spacecraft for orbit insertion, propulsion to its target, and communications while at its target. Because of this highly capable supporting vehicle, the energy requirements for daily operations of GSO could be easily met with a small RPS system, which is now being studied by NASA and DOE,, joined with a secondary battery system. The science payload would consist of a plasma instrument set (magnetometer, plasma spectrometer, plasma wave detector, and high energy particle detector), a wide angle camera, and a Doppler extractor for gravity field measurements. A small RPS now under study that would have a cylindrical shape and reject its internal heat through an end of the cylinder could enable this concept. This topology lends itself to a unique configuration concept for the GSO spacecraft using a long cylinder as the heat rejection (radiator) system for the RPS. This long cylinder has another application - it creates a long thin configuration that would enable gravity gradient attitude control of the spacecraft. This architecture would place the instruments at one end of the spacecraft and the RPS at the other allowing the maximum separation between them. Another technology element used in this design would be the Low Cost Adjunct Microspacecraft (LCAM), originally intended as a free-flying Earth orbiting inspector spacecraft. The LCAM is configured as a small circular disk containing an extensive computational and data handling capability as well as a suite of attitude control sensors. Two of these LCAM modules could be used in the configuration - one at each end. One would act as a science support platform at the nadir end and the other would support the RPS and communications system at the zenith end. Because the LCAM communications system is designed for use in Earth orbit, a high-power X-band system would be required for the GSO concept mission including an advanced technology phased array antenna. Because the attitude would be known instantaneously based on the knowledge of attitude sensors, the beam would be pointed in real time in the direction of its communications' station. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Randolph, JE (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,MS 301-170U, Pasadena, CA 91109 USA. NR 6 TC 0 Z9 0 U1 0 U2 1 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 0-7354-0230-2 J9 AIP CONF PROC PY 2005 VL 746 BP 318 EP 331 PG 14 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BBS02 UT WOS:000227496400037 ER PT S AU Balint, TS AF Balint, TS BE ElGenk, MS TI Small-RPS enabled Mars rover concept SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM-STAIF 2005 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum CY FEB 13-17, 2005 CL Albuquerque, NM SP Boeing Co, Lockheed Martin, Los Alamos Natl Lab, Sandia Natl Labs, Northrop Grumman Space Technol, Stirling Technol Co, US DOE, Amer Astronaut Soc, Amer Inst Aeronaut & Astronaut, Natl & Local Sect, Amer Inst Chem Engineers, Amer Soc Mech Engineers, Heat Transfer Div, NASA Natl Space Grant Coll & Fellowship Program, Profess Aerosp Contractors Assoc, Inst Space & Nucl Power Studies AB Both the MER and the Mars Pathfinder rovers operated on Mars in an energy-limited mode, since the solar panels generated power during daylight hours only. At other times the rovers relied on power stored in batteries. In comparison, Radioisotope Power Systems (RPS) offer a power-enabled paradigm, where power can be generated for long mission durations (measured in years), independently from the Sun, and on a continuous basis. A study was performed at JPL to assess the feasibility of a small-RPS enabled MER-class rover concept and any associated advantages of its mission on Mars. The rover concept relied on design heritage from MER with two significant changes. First, the solar panels were replaced with two single GPHS module based small-RPSs. Second, the Mossbauer spectroscope was substituted with a laser Raman spectroscope, in order to move towards MEPAG defined astrobiology driven science goals. The highest power requirements were contributed to mobility and telecommunication type operating modes, hence influencing power system sizing. The resulting hybrid power system included two small-RPSs and two batteries. Each small-RPS was assumed to generate 50 We of power or 620 Wh/sol of energy (BOL), comparable to that of MER. The two 8 Ah batteries were considered available during peak power usage. Mission architecture, power trades, science instruments, data, communication, thermal and radiation environments, mobility, and mass issues were also addressed. The study demonstrated that a new set of RPS-enabled rover missions could be envisioned for Mars exploration within the next decade, targeting astrobiology oriented science objectives, while powered by 2 to 4 GPHS modules. C1 CALTECH, Jet Prop Lab, Pre Projects & Adv Miss Studies, Off 610, Pasadena, CA 91109 USA. RP Balint, TS (reprint author), CALTECH, Jet Prop Lab, Pre Projects & Adv Miss Studies, Off 610, 4800 Oak Grove Dr,MS 301-170U, Pasadena, CA 91109 USA. NR 8 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 0-7354-0230-2 J9 AIP CONF PROC PY 2005 VL 746 BP 332 EP 344 PG 13 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BBS02 UT WOS:000227496400038 ER PT S AU Randolph, JE Abelson, RD Oxnevad, KI Shirley, JH AF Randolph, JE Abelson, RD Oxnevad, KI Shirley, JH BE ElGenk, MS TI Searching for subsurface lunar water ice using a nuclear-powered rover SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM-STAIF 2005 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum CY FEB 13-17, 2005 CL Albuquerque, NM SP Boeing Co, Lockheed Martin, Los Alamos Natl Lab, Sandia Natl Labs, Northrop Grumman Space Technol, Stirling Technol Co, US DOE, Amer Astronaut Soc, Amer Inst Aeronaut & Astronaut, Natl & Local Sect, Amer Inst Chem Engineers, Amer Soc Mech Engineers, Heat Transfer Div, NASA Natl Space Grant Coll & Fellowship Program, Profess Aerosp Contractors Assoc, Inst Space & Nucl Power Studies AB The Vision for Space Exploration has identified the Earth's moon as a future destination for human explorers as a stepping-stone for further manned deep space exploration. The feasibility of building and maintaining a human presence on the moon could be directly related to whether in-situ resources, especially water ice, can be obtained and utilized by astronauts. With the recent success of both Mars Exploration Rovers (MERs), it is clear that a lunar rover could be a desirable platform with which to search for evidence of lunar water prior to the arrival of astronauts. However, since surface water can only exist in permanently shadowed areas of the moon (i.e., deep craters near the poles), conventionally powered rovers would not be practical for exploring these areas for extended periods. Thus, a study was performed to assess the feasibility of a lunar rover mission enabled by small radioisotope power systems (R-PS), i.e., systems that use single GPHSs. Small RPSs, the feasibility of which has been looked at by the Department of Energy, would be capable of providing sufficient electrical and thermal power to allow scientific measurements and operations of a small rover on the floor of dark lunar craters. A conceptual study was completed that considered the science instruments that could be accommodated on a MER-type rover using RPS power. To investigate the subsurface characteristics of the crater floor, a pulsed gamma ray/neutron spectrometer and a ground-penetrating radar would be used. Also, a drill would provide core samples from a depth of I meter. A rover architecture consistent with MER capabilities included a mast with panoramic cameras and navigation cameras as well as an instrument deployment device (IDD) that allowed direct contact between the instrument head and surface materials to be measured. Because the crater floor is eternally dark, artificial illumination must be used for both landing and roving operations. The rover design included of dual headlights that would be operated during visual imaging observations. During the landing approach, the lander would use a laser imaging technique to image the approaching surface and react to that image to avoid hazards. The baseline rover concept used four GPHS power sources for a total of about 50 We in conjunction with a 25 A hr battery to supply power during peak loads. A detailed analysis of energy usage for various operational scenarios (e.g. roving, science instrument operations, and telecommunications) was completed using an elaborate power simulation tool. The results show that very demanding activities are possible on a daily basis while maintaining the battery charging. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Randolph, JE (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 14 TC 0 Z9 0 U1 1 U2 5 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 0-7354-0230-2 J9 AIP CONF PROC PY 2005 VL 746 BP 354 EP 366 PG 13 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BBS02 UT WOS:000227496400040 ER PT S AU Abelson, RD Satter, CM AF Abelson, RD Satter, CM BE ElGenk, MS TI Deployable mini-payload missions enabled by small radioisotope power systems (RPSs) SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM-STAIF 2005 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum CY FEB 13-17, 2005 CL Albuquerque, NM SP Boeing Co, Lockheed Martin, Los Alamos Natl Lab, Sandia Natl Labs, Northrop Grumman Space Technol, Stirling Technol Co, US DOE, Amer Astronaut Soc, Amer Inst Aeronaut & Astronaut, Natl & Local Sect, Amer Inst Chem Engineers, Amer Soc Mech Engineers, Heat Transfer Div, NASA Natl Space Grant Coll & Fellowship Program, Profess Aerosp Contractors Assoc, Inst Space & Nucl Power Studies AB Deployable mini-payloads are envisioned as small, simple, standalone instruments that could be deployed from a mother vehicle such as a rover or the proposed Jupiter Icy Moons Orbiter to key points of interest within the solar system. Used in conjunction with a small radioisotope power system (RPS), these payloads could potentially be used for long-duration science missions or as positional beacons for rovers or other spacecraft. The RPS power source would be suitable for deployable mini-payload missions that would take place anywhere there is limited, intermittent, or no solar insolation. This paper introduces two such concepts: (1) a seismic monitoring station deployed by a rover or aerobot, and (2) a passive fields and particles station delivered by a mother spacecraft to the Jupiter system. C1 CALTECH, Jet Prop Lab, Miss & Syst Architecture Sect, Pasadena, CA 91109 USA. RP Abelson, RD (reprint author), CALTECH, Jet Prop Lab, Miss & Syst Architecture Sect, 4800 Oak Grove Dr,Mail Stop 301-445, Pasadena, CA 91109 USA. NR 9 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 0-7354-0230-2 J9 AIP CONF PROC PY 2005 VL 746 BP 378 EP 385 PG 8 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BBS02 UT WOS:000227496400042 ER PT S AU Balint, TS Emis, N AF Balint, TS Emis, N BE ElGenk, MS TI Thermal analysis of a small-RPS concept for the Mars NetLander network mission SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM-STAIF 2005 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum CY FEB 13-17, 2005 CL Albuquerque, NM SP Boeing Co, Lockheed Martin, Los Alamos Natl Lab, Sandia Natl Labs, Northrop Grumman Space Technol, Stirling Technol Co, US DOE, Amer Astronaut Soc, Amer Inst Aeronaut & Astronaut, Natl & Local Sect, Amer Inst Chem Engineers, Amer Soc Mech Engineers, Heat Transfer Div, NASA Natl Space Grant Coll & Fellowship Program, Profess Aerosp Contractors Assoc, Inst Space & Nucl Power Studies AB The NetLander Network mission concept was designed with up to 10 small landers to perform environmental monitoring on the surface of Mars over a long duty cycle. Each lander would utilize a small Radioisotope Power System (RPS) to generate about 20 to 25 We of electric power. Each small-RPS would use a single General Purpose Heat Source (GPHS) module to generate about 250 Wt of thermal power (BOL), which must be dissipated throughout all phases of the mission. This paper describes a custom concept for a small-RPS, specifically suited for the NetLander, and discusses an analysis of the thermal environment for five phases of the mission. On Earth and on Mars the small-RPS would operate in planetary atmospheres and the waste heat would be removed through a passive radiator. During the cruise phase, including the launch, a fluid loop would provide active cooling to the radiator of the small-RPS and would reject the excess heat through an external radiator. For the entry, descent and landing (EDL) phase the lander would accumulate the excess heat, while building up thermal inertia inside. This analysis provides an initial step towards developing an end-to-end systems approach to better understand the operation of a small-RPS, and to account for the relevant operating phases and environments encountered during a mission. C1 CALTECH, Jet Prop Lab, Pre Projects & Adv Miss Studies, Off 610, Pasadena, CA 91109 USA. RP Balint, TS (reprint author), CALTECH, Jet Prop Lab, Pre Projects & Adv Miss Studies, Off 610, 4800 Oak Grove Dr,MS 301-170U, Pasadena, CA 91109 USA. NR 8 TC 3 Z9 3 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 0-7354-0230-2 J9 AIP CONF PROC PY 2005 VL 746 BP 402 EP 409 PG 8 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BBS02 UT WOS:000227496400045 ER PT S AU Anderson, DJ AF Anderson, DJ BE ElGenk, MS TI NASA radioisotope power conversion technology NRA overview SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM-STAIF 2005 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum CY FEB 13-17, 2005 CL Albuquerque, NM SP Boeing Co, Lockheed Martin, Los Alamos Natl Lab, Sandia Natl Labs, Northrop Grumman Space Technol, Stirling Technol Co, US DOE, Amer Astronaut Soc, Amer Inst Aeronaut & Astronaut, Natl & Local Sect, Amer Inst Chem Engineers, Amer Soc Mech Engineers, Heat Transfer Div, NASA Natl Space Grant Coll & Fellowship Program, Profess Aerosp Contractors Assoc, Inst Space & Nucl Power Studies AB The focus of the National Aeronautics and Space Administration's (NASA) Radioisotope Power Systems (RPS) Development program is aimed at developing nuclear power and technologies that would improve the effectiveness of space science missions. The Radioisotope Power Conversion Technology (RPCT) NASA Research Announcement (NRA) is an important mechanism through which research and technology activities are supported in the Advanced Power Conversion Research and Technology project of the Advanced Radioisotope Power Systems Development program. The purpose of the RPCT NRA is to advance the development of radioisotope power conversion technologies to provide higher efficiencies and specific powers than existing systems. These advances would enable a factor of 2 to 4 decrease in the amount of fuel and a reduction of waste heat required to generate electrical power, and thus could result in more cost effective science missions for NASA. The RPCT NRA selected advanced RPS power conversion technology research and development proposals in the following three areas: innovative RPS power conversion research, RPS power conversion technology development in a nominal 100W(e) scale; and, milliwatt/multi-watt RPS (mWRPS) power conversion research. Ten RPCT NRA contracts were awarded in 2003 in the areas of Brayton, Stirling, thermoelectric (TE), and thermophotovoltaic (TPV) power conversion technologies. This paper will provide an overview of the RPCT NRA, a summary of the power conversion technologies approaches being pursued, and a brief digest of first year accomplishments. C1 NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Anderson, DJ (reprint author), NASA, Glenn Res Ctr, 21000 Brookpk Rd, Cleveland, OH 44135 USA. NR 4 TC 1 Z9 1 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 0-7354-0230-2 J9 AIP CONF PROC PY 2005 VL 746 BP 421 EP 428 PG 8 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BBS02 UT WOS:000227496400047 ER PT S AU Schmidt, GR Wiley, RL Richardson, RL Furlong, RR AF Schmidt, GR Wiley, RL Richardson, RL Furlong, RR BE ElGenk, MS TI NASA's program for radioisotope power system research and development SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM-STAIF 2005 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum CY FEB 13-17, 2005 CL Albuquerque, NM SP Boeing Co, Lockheed Martin, Los Alamos Natl Lab, Sandia Natl Labs, Northrop Grumman Space Technol, Stirling Technol Co, US DOE, Amer Astronaut Soc, Amer Inst Aeronaut & Astronaut, Natl & Local Sect, Amer Inst Chem Engineers, Amer Soc Mech Engineers, Heat Transfer Div, NASA Natl Space Grant Coll & Fellowship Program, Profess Aerosp Contractors Assoc, Inst Space & Nucl Power Studies AB Radioisotope Power System (RPS) research and development is vital to a variety of future NASA space science and exploration missions. The objectives of NASA's current RPS activities are threefold: (1) develop new radioisotope power sources for missions that would launch by the end of the decade; (2) advance promising power conversion technologies to increase the specific power and performance of future RPS units; and (3) assess and facilitate the use of advanced RPS technologies for new mission applications. The program consists of two flight unit development projects, a set of 10 competitively-selected research and development efforts in power conversion technology, focused research tasks on thermoelectric and Stirling energy conversion, and system analyses to support selection of technologies and evaluation of RPS for promising mission applications. This paper describes the content of the program, and discusses its future direction. C1 NASA, Sci Miss Directorate, Washington, DC 20546 USA. RP Schmidt, GR (reprint author), NASA, Sci Miss Directorate, Washington, DC 20546 USA. NR 7 TC 5 Z9 5 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 0-7354-0230-2 J9 AIP CONF PROC PY 2005 VL 746 BP 429 EP 436 PG 8 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BBS02 UT WOS:000227496400048 ER PT S AU Mondt, J Johnson, K Fleurial, JP El Genk, M Frye, P Determan, B AF Mondt, J Johnson, K Fleurial, JP El Genk, M Frye, P Determan, B BE ElGenk, MS TI Segmented thermoelectric multicouple converter technology development SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM-STAIF 2005 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum CY FEB 13-17, 2005 CL Albuquerque, NM SP Boeing Co, Lockheed Martin, Los Alamos Natl Lab, Sandia Natl Labs, Northrop Grumman Space Technol, Stirling Technol Co, US DOE, Amer Astronaut Soc, Amer Inst Aeronaut & Astronaut, Natl & Local Sect, Amer Inst Chem Engineers, Amer Soc Mech Engineers, Heat Transfer Div, NASA Natl Space Grant Coll & Fellowship Program, Profess Aerosp Contractors Assoc, Inst Space & Nucl Power Studies AB The primary objectives of the segmented thermoelectric multicouple converter (STMC) technology development effort are: to define a conceptual design for a passive, low mass (3000 kg), long life (15 years) thermoelectric advanced Space Reactor Power System that provides 100kWe 400 Volt dc power for a 6000 volt dc electric propulsion system, to prepare a preliminary design of the power conversion system and to prepare technology development plan to advance power conversion system technology to TRL 6. The SRPS consists of a heat pipe cooled reactor radiatively couple to high efficiency solid-state segmented thermoelectric multicouple converters which are conductively coupled to a low mass heat pipe radiator. The SRPS conceptual design as well as the Power Conversion System preliminary design is complete and their description reported in this paper. C1 CALTECH, Jet Prop Lab, Space Power Grp, Pasadena, CA 91109 USA. RP Mondt, J (reprint author), CALTECH, Jet Prop Lab, Space Power Grp, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 4 TC 4 Z9 4 U1 0 U2 2 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 0-7354-0230-2 J9 AIP CONF PROC PY 2005 VL 746 BP 495 EP 502 PG 8 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BBS02 UT WOS:000227496400054 ER PT S AU Tew, RC Dyson, RW Wilson, SD Demko, R AF Tew, RC Dyson, RW Wilson, SD Demko, R BE ElGenk, MS TI Overview 2004 of NASA-stirling convertor CFD model development and regenerator R&D efforts SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM-STAIF 2005 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum CY FEB 13-17, 2005 CL Albuquerque, NM SP Boeing Co, Lockheed Martin, Los Alamos Natl Lab, Sandia Natl Labs, Northrop Grumman Space Technol, Stirling Technol Co, US DOE, Amer Astronaut Soc, Amer Inst Aeronaut & Astronaut, Natl & Local Sect, Amer Inst Chem Engineers, Amer Soc Mech Engineers, Heat Transfer Div, NASA Natl Space Grant Coll & Fellowship Program, Profess Aerosp Contractors Assoc, Inst Space & Nucl Power Studies AB This paper reports on accomplishments in 2004 in (1) development of Stirling-convertor CFD models at NASA GRC and via a NASA grant, (2) a Stirling regenerator-research effort being conducted via a NASA grant (a follow-on effort to an earlier DOE contract), and (3) a regenerator-microfabrication contract for development of a "next-generation Stirling regenerator." Cleveland State University is the lead organization for all three grant/contractual efforts, with the University of Minnesota and Gedeon Associates as subcontractors. Also, the Stirling Technology Co. and Sunpower, Inc. are both involved in all three efforts, either as funded or unfunded participants. International Mezzo Technologies of Baton Rouge, LA is the regenerator fabricator for the regenerator-microfabrication contract. Results of the efforts in these three areas are summarized. C1 NASA, Glenn Res Ctr, Thermal Energy Convers Branch, Cleveland, OH 44135 USA. RP Tew, RC (reprint author), NASA, Glenn Res Ctr, Thermal Energy Convers Branch, Mail Stop 301-2,21000 Brookpk Rd, Cleveland, OH 44135 USA. NR 42 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 0-7354-0230-2 J9 AIP CONF PROC PY 2005 VL 746 BP 648 EP 657 PG 10 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BBS02 UT WOS:000227496400072 ER PT S AU Geng, SM Niedra, JA Schwarze, GE AF Geng, SM Niedra, JA Schwarze, GE BE ElGenk, MS TI Overview of NASA magnet and linear alternator research efforts SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM-STAIF 2005 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum CY FEB 13-17, 2005 CL Albuquerque, NM SP Boeing Co, Lockheed Martin, Los Alamos Natl Lab, Sandia Natl Labs, Northrop Grumman Space Technol, Stirling Technol Co, US DOE, Amer Astronaut Soc, Amer Inst Aeronaut & Astronaut, Natl & Local Sect, Amer Inst Chem Engineers, Amer Soc Mech Engineers, Heat Transfer Div, NASA Natl Space Grant Coll & Fellowship Program, Profess Aerosp Contractors Assoc, Inst Space & Nucl Power Studies AB The Department of Energy, Lockheed Martin, Stirling Technology Company, and NASA Glenn Research Center are developing a high-efficiency, 110 watt Stirling Radioisotope Generator (SRG110) for NASA Space Science missions. NASA Glenn is conducting in-house research on rare earth permanent magnets and on linear alternators to assist in developing a free-piston Stirling convertor for the SRG110 and for developing advanced technology. The permanent magnet research efforts include magnet characterization, short-term magnet aging tests, and long-term magnet aging tests. Linear alternator research efforts have begun just recently at GRC with the characterization of a moving iron type linear alternator using GRC's alternator test rig. This paper reports on the progress and future plans of GRC's magnet and linear alternator research efforts. C1 NASA, Glenn Res Ctr, Thermal Energy Convers Branch, Cleveland, OH 44135 USA. RP Geng, SM (reprint author), NASA, Glenn Res Ctr, Thermal Energy Convers Branch, 21000 Brookpk Rd, Cleveland, OH 44135 USA. NR 4 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 0-7354-0230-2 J9 AIP CONF PROC PY 2005 VL 746 BP 666 EP 673 PG 8 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BBS02 UT WOS:000227496400074 ER PT S AU Thieme, LG Schreiber, JG AF Thieme, LG Schreiber, JG BE ElGenk, MS TI Supporting development for the Stirling Radioisotope Generator and advanced Stirling technology development at NASA GRC SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM-STAIF 2005 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum CY FEB 13-17, 2005 CL Albuquerque, NM SP Boeing Co, Lockheed Martin, Los Alamos Natl Lab, Sandia Natl Labs, Northrop Grumman Space Technol, Stirling Technol Co, US DOE, Amer Astronaut Soc, Amer Inst Aeronaut & Astronaut, Natl & Local Sect, Amer Inst Chem Engineers, Amer Soc Mech Engineers, Heat Transfer Div, NASA Natl Space Grant Coll & Fellowship Program, Profess Aerosp Contractors Assoc, Inst Space & Nucl Power Studies AB A high-efficiency, 110-W-e (watts electric) Stirling Radioisotope Generator (SRG110) for possible use on future NASA Space Science missions is being developed by the Department of Energy, Lockheed Martin, Stirling Technology Company (STC), and NASA Glenn Research Center (GRC). Potential mission use includes providing spacecraft onboard electric power for deep space missions and power for unmanned Mars rovers. GRC is conducting an in-house supporting technology project to assist in SRG110 development. One-, three-, and six-month heater head structural benchmark tests have been completed in support of a heater head life assessment. Testing is underway to evaluate the key epoxy bond of the permanent magnets to the linear alternator stator lamination stack. GRC has completed over 10,000 hours of extended duration testing of the Stirling convertors for the SRG110, and a three-year test of two Stirling convertors in a thermal vacuum environment will be starting shortly. GRC is also developing advanced technology for Stirling convertors, aimed at substantially improving the specific power and efficiency of the convertor and the overall generator. Sunpower, Inc. has began the development of a lightweight Stirling convertor, under a NASA Research Announcement (NRA) award, that has the potential to double the system specific power to about 8 W-e/kg. GRC has performed random vibration testing of a lower-power version of this convertor to evaluate robustness for surviving launch vibrations. STC has also completed the initial design of a lightweight convertor. Status of the development of a multi-dimensional computational fluid dynamics code and high-temperature materials work on advanced superalloys, refractory metal alloys, and ceramics are also discussed. C1 NASA, Glenn Res Ctr Lewis Field, Cleveland, OH 44135 USA. RP Thieme, LG (reprint author), NASA, Glenn Res Ctr Lewis Field, MS 301-2,21000 Brookpk Rd, Cleveland, OH 44135 USA. NR 10 TC 3 Z9 3 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 0-7354-0230-2 J9 AIP CONF PROC PY 2005 VL 746 BP 674 EP 681 PG 8 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BBS02 UT WOS:000227496400075 ER PT S AU Ludwiczak, DR Le, DK McNelis, AM Yu, AC Samorezov, S Hervol, DS AF Ludwiczak, DR Le, DK McNelis, AM Yu, AC Samorezov, S Hervol, DS BE ElGenk, MS TI Validation of a 2 kWe closed-Brayton-cycle power conversion system mechanical dynamics model SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM-STAIF 2005 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum CY FEB 13-17, 2005 CL Albuquerque, NM SP Boeing Co, Lockheed Martin, Los Alamos Natl Lab, Sandia Natl Labs, Northrop Grumman Space Technol, Stirling Technol Co, US DOE, Amer Astronaut Soc, Amer Inst Aeronaut & Astronaut, Natl & Local Sect, Amer Inst Chem Engineers, Amer Soc Mech Engineers, Heat Transfer Div, NASA Natl Space Grant Coll & Fellowship Program, Profess Aerosp Contractors Assoc, Inst Space & Nucl Power Studies AB Vibration test data from an operating 2-kWe closed-Brayton-cycle (CBC) power conversion system (PCS) located at the NASA Glenn Research Center was used for a comparison with a dynamic disturbance model of the same unit. This effort was performed to show that a dynamic disturbance model of a CBC PCS can be developed that can accurately predict the torque and vibration disturbance fields of such class of rotating machinery. The ability to accurately predict these disturbance fields is required before such hardware can be confidently integrated onto a spacecraft mission. Accurate predictions of CBC disturbance fields will be used for spacecraft control/structure interaction analyses and for understanding the vibration disturbances affecting the scientific instrumentation onboard. This paper discusses how test cell data measurements for the 2-kWe CBC PCS were obtained and the development of a dynamic disturbance model used to predict the vibration fields of the same unit. C1 NASA, Glenn Res Ctr, Struct Syst Dynam Branch, Cleveland, OH 44135 USA. RP Ludwiczak, DR (reprint author), NASA, Glenn Res Ctr, Struct Syst Dynam Branch, Cleveland, OH 44135 USA. NR 4 TC 1 Z9 1 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 0-7354-0230-2 J9 AIP CONF PROC PY 2005 VL 746 BP 750 EP 761 PG 12 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BBS02 UT WOS:000227496400083 ER PT S AU Van Dyke, M Martin, J AF Van Dyke, M Martin, J BE ElGenk, MS TI Hardware progress made in the Early Flight Fission Test Facilities (EFF-TF) to support near-term space fission systems SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM-STAIF 2005 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum CY FEB 13-17, 2005 CL Albuquerque, NM SP Boeing Co, Lockheed Martin, Los Alamos Natl Lab, Sandia Natl Labs, Northrop Grumman Space Technol, Stirling Technol Co, US DOE, Amer Astronaut Soc, Amer Inst Aeronaut & Astronaut, Natl & Local Sect, Amer Inst Chem Engineers, Amer Soc Mech Engineers, Heat Transfer Div, NASA Natl Space Grant Coll & Fellowship Program, Profess Aerosp Contractors Assoc, Inst Space & Nucl Power Studies AB The NASA Marshall Space Flight Center's Early Flight Fission Test Facility (EFF-TF), provides a facility to experimentally evaluate nuclear reactor related thermal hydraulic issues through the use of non-nuclear testing. This facility provides a cost effective method to evaluate concepts/designs and support mitigation of developmental risk. Electrical resistance thermal simulators can be used to closely mimic the heat deposition of the fission process, providing axial and radial profiles. A number of experimental and design programs were underway in 2004 which include the following. Initial evaluation of the Department of Energy Los Alamos National Laboratory 19 module stainless steel/sodium heat pipe reactor with integral gas heat exchanger was operated at up to 17.5 kW of input power at core temperatures of 1000 K. A stainless steel sodium heat pipe module was placed through repeated freeze/thaw cyclic testing accumulating over 200 restarts to a temperature of 1000 K. Additionally, the design of a 37- pin stainless steel pumped sodium/potassium (NaK) loop was finalized and components procured. Ongoing testing at the EFF-TF is geared towards facilitating both research and development necessary to support future decisions regarding potential use of space nuclear systems for space exploration. All efforts are coordinated with DOE laboratories, industry, universities, and other NASA centers. This paper describes some of the 2004 efforts. C1 NASA, George C Marshall Space Flight Ctr, Huntsville, AL 35812 USA. RP Van Dyke, M (reprint author), NASA, George C Marshall Space Flight Ctr, Huntsville, AL 35812 USA. NR 5 TC 1 Z9 1 U1 0 U2 1 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 0-7354-0230-2 J9 AIP CONF PROC PY 2005 VL 746 BP 895 EP 902 PG 8 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BBS02 UT WOS:000227496400102 ER PT S AU Glover, TW Diaz, FRC Squire, JP Jacobson, VP Chavers, DG Carter, MD AF Glover, TW Diaz, FRC Squire, JP Jacobson, VP Chavers, DG Carter, MD BE ElGenk, MS TI Principal VASIMR results and present objectives SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM-STAIF 2005 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum CY FEB 13-17, 2005 CL Albuquerque, NM SP Boeing Co, Lockheed Martin, Los Alamos Natl Lab, Sandia Natl Labs, Northrop Grumman Space Technol, Stirling Technol Co, US DOE, Amer Astronaut Soc, Amer Inst Aeronaut & Astronaut, Natl & Local Sect, Amer Inst Chem Engineers, Amer Soc Mech Engineers, Heat Transfer Div, NASA Natl Space Grant Coll & Fellowship Program, Profess Aerosp Contractors Assoc, Inst Space & Nucl Power Studies AB Principal achievements of the Variable Specific Impulse Magnetoplasma Rocket (VASIMR) project at the NASA Johnson Space Center's Advanced Space Propulsion Laboratory (ASPL) are reviewed and objectives for continuing development are described. The evolution of the VASIMR design from the 1994 concept to the present device is summarized. In its present configuration (VX-10), the VASIMR device consists of a 10 kW helicon plasma source and a 1.5 kW radio-frequency booster stage. At modest power levels, the measured plasma exhaust velocity implies a specific impulse spanning the range of 5,000 - 12,000 seconds using deuterium propellant. Experimental results indicate very high efficiency for the RF booster stage. Given sufficient power, the helicon source approaches 100 % mass utilization (ionization); however, the ionization cost of the present source must be reduced for satisfactory overall system efficiency. Immediate goals are measurement of thrust in the exhaust plume, reduction of ionization cost, and observation of detachment of the plasma from the magnetic field of the thruster. C1 NASA, Adv Space Prop Lab, MSASPL, Sonny Carter Training Facil, Houston, TX 77059 USA. RP Glover, TW (reprint author), NASA, Adv Space Prop Lab, MSASPL, Sonny Carter Training Facil, 13000 Space Ctr Blvd, Houston, TX 77059 USA. NR 11 TC 2 Z9 2 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 0-7354-0230-2 J9 AIP CONF PROC PY 2005 VL 746 BP 976 EP 982 PG 7 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BBS02 UT WOS:000227496400111 ER PT S AU Esper, J AF Esper, J BE ElGenk, MS TI Modular, adaptive, reconfigurable systems: Technology for sustainable, reliable, effective, and affordable space exploration SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM-STAIF 2005 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum CY FEB 13-17, 2005 CL Albuquerque, NM SP Boeing Co, Lockheed Martin, Los Alamos Natl Lab, Sandia Natl Labs, Northrop Grumman Space Technol, Stirling Technol Co, US DOE, Amer Astronaut Soc, Amer Inst Aeronaut & Astronaut, Natl & Local Sect, Amer Inst Chem Engineers, Amer Soc Mech Engineers, Heat Transfer Div, NASA Natl Space Grant Coll & Fellowship Program, Profess Aerosp Contractors Assoc, Inst Space & Nucl Power Studies AB In order to execute the Vision for Space Exploration, we must find ways to reduce cost, system complexity, design, build, and test times, and at the same time increase flexibility to satisfy multiple functions. Modular, Adaptive, Reconfigurable System (MARS) technologies promise to set the stage for the delivery of system elements that form the building blocks of increasingly ambitious missions involving humans and robots. Today, space systems are largely specialized and built on a case-by-case basis. The notion of modularity however, is nothing new to NASA. The 1970's saw the development of the Multi-Mission Modular spacecraft (MMS). From 1980 to 1992 at least six satellites were built under this paradigm, and included such Goddard Space Flight Center missions as SSM, EUVE, UARS, and Landsat 4 and 5. Earlier versions consisted of standard subsystem "module" or "box" components that could be replaced within a structure based on predefined form factors. Although the primary motivation for MMS was faster/cheaper integration and test, standardization of interfaces, and ease of incorporating new subsystem technology, it lacked the technology maturity and programmatic "upgrade infrastructure" needed to satisfy varied mission requirements, and ultimately it lacked user buy-in. Consequently, it never evolved and was phased out. Such concepts as the Rapid Spacecraft Development Office (RSDO) with its regularly updated catalogue of pre-qualified busses became the preferred method for acquiring satellites. Notwithstanding, over the past 30 years since MMS inception, technology has advanced considerably and now modularity can be extended beyond the traditional MMS module or box to cover levels of integration, from the chip, card, box, subsystem, to the space system and to the system-of-systems. This paper will present the MARS architecture, cast within the historical context of MMS. Its application will be highlighted by comparing a state-of-the-art point design vs. a MARS-enabled lunar mission, as a representative robotic case design. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Esper, J (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. NR 9 TC 3 Z9 3 U1 0 U2 3 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 0-7354-0230-2 J9 AIP CONF PROC PY 2005 VL 746 BP 1033 EP 1043 PG 11 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BBS02 UT WOS:000227496400116 ER PT S AU Bhasin, K Hayden, JL AF Bhasin, K Hayden, JL BE ElGenk, MS TI Creating communications, computing, and networking technology development road maps for future NASA human and robotic missions SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM-STAIF 2005 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum CY FEB 13-17, 2005 CL Albuquerque, NM SP Boeing Co, Lockheed Martin, Los Alamos Natl Lab, Sandia Natl Labs, Northrop Grumman Space Technol, Stirling Technol Co, US DOE, Amer Astronaut Soc, Amer Inst Aeronaut & Astronaut, Natl & Local Sect, Amer Inst Chem Engineers, Amer Soc Mech Engineers, Heat Transfer Div, NASA Natl Space Grant Coll & Fellowship Program, Profess Aerosp Contractors Assoc, Inst Space & Nucl Power Studies AB For human and robotic exploration missions envisioned in the Vision for Exploration, roadmaps are needed for capability development and investments based on advanced technology developments. A roadmap development process was undertaken for the needed communications, computing, and networking capabilities and technologies for the future human and robotics missions. The underlying processes are derived from work carried out during development of the future space communications architecture, and NASA's Space Architect Office (SAO) defined formats and structures for accumulating data. Interrelationships were established among emerging requirements, the capability analysis and technology status, and performance data. After developing an architectural communications and networking framework structured around the assumed needs for human and robotic exploration, in the vicinity of Earth, Moon, along the path to Mars, and in the vicinity of Mars, information was gathered from expert participants. This information was used to identify the capabilities expected from the new infrastructure and the technological gaps in the way of obtaining them. We define realistic, long-term space communication architectures based on emerging needs and translate the needs into interfaces, functions, and computer processing that will be required. In developing our roadmapping process, we defined requirements for achieving end-to-end activities that will be carried out by future NASA human and robotic missions. This paper describes: 1) the architectural framework developed for analysis; 2) our approach to gathering and analyzing data from NASA, industry, and academia; 3) an outline of the technology research to be done, including milestones for technology research and demonstrations with timelines; and 4) the technology roadmaps themselves. C1 NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Bhasin, K (reprint author), NASA, Glenn Res Ctr, 21000 Brook Pk Rd, Cleveland, OH 44135 USA. NR 12 TC 0 Z9 0 U1 0 U2 1 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 0-7354-0230-2 J9 AIP CONF PROC PY 2005 VL 746 BP 1051 EP 1062 PG 12 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BBS02 UT WOS:000227496400118 ER PT S AU Jaap, J Maxwell, T AF Jaap, J Maxwell, T BE ElGenk, MS TI Enabling new operations concepts for lunar and Mars exploration SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM-STAIF 2005 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum CY FEB 13-17, 2005 CL Albuquerque, NM SP Boeing Co, Lockheed Martin, Los Alamos Natl Lab, Sandia Natl Labs, Northrop Grumman Space Technol, Stirling Technol Co, US DOE, Amer Astronaut Soc, Amer Inst Aeronaut & Astronaut, Natl & Local Sect, Amer Inst Chem Engineers, Amer Soc Mech Engineers, Heat Transfer Div, NASA Natl Space Grant Coll & Fellowship Program, Profess Aerosp Contractors Assoc, Inst Space & Nucl Power Studies AB The planning and scheduling of human space activities is an expensive and time-consuming task that seldom provides the crew with the control, flexibility, or insight that they need. During the past thirty years, scheduling software has seen only incremental improvements; however, software limitations continue to prevent even evolutionary improvements in the "operations concept" that is used for human space missions. Space missions are planned on the ground long before they are executed in space, and the crew has little input or influence on the schedule. In recent years the crew has been presented with a "job jar" of activities that they can do whenever they have time, but the contents of the jar is limited to tasks that do not use scarce shared resources and do not have external timing constraints. Consequently, the crew has no control over the schedule of the majority of their own tasks. As humans venture farther from earth for longer durations, it will become imperative that they have the ability to plan and schedule not only their own activities, but also the unattended activities of the systems, equipment, and robots on the journey with them. Significant software breakthroughs are required to enable the change in the operations concept. The crew does not have the time to build or modify the schedule by hand. They only need to issue a request to schedule a task and the system should automatically do the rest. Of course, the crew should not be required to build the complete schedule. Controllers on the ground should contribute the models and schedules where they have the better knowledge. The system must allow multiple simultaneous users, some on earth and some in space. The Mission Operations Laboratory at NASA's Marshall Space Flight Center has been researching and prototyping a modeling schema, scheduling engine, and system architecture that can enable the needed paradigm shift - it can make the crew autonomous. This schema and engine can be the core of a planning and scheduling system that would enable multiple planners, some on the earth and some in space, to build one integrated timeline. Its modeling schema can capture all the task requirements; its scheduling engine can build the schedule automatically; and its architecture can allow those (on earth and in space) with the best knowledge of the tasks to schedule them. This paper describes the enabling technology and proposes an operations concept for astronauts autonomously scheduling their activities and the activities around them. C1 George C Marshall Space Flight Ctr, Miss Operat Lab, MSFC, Huntsville, AL 35812 USA. RP Jaap, J (reprint author), George C Marshall Space Flight Ctr, Miss Operat Lab, MSFC, Huntsville, AL 35812 USA. NR 6 TC 0 Z9 0 U1 0 U2 1 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 0-7354-0230-2 J9 AIP CONF PROC PY 2005 VL 746 BP 1063 EP 1069 PG 7 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BBS02 UT WOS:000227496400119 ER PT S AU Smitherman, D Rais-Rohani, M Dunn, D Perkinson, D AF Smitherman, D Rais-Rohani, M Dunn, D Perkinson, D BE ElGenk, MS TI Hybrid robotic habitat for lunar exploration SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM-STAIF 2005 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum CY FEB 13-17, 2005 CL Albuquerque, NM SP Boeing Co, Lockheed Martin, Los Alamos Natl Lab, Sandia Natl Labs, Northrop Grumman Space Technol, Stirling Technol Co, US DOE, Amer Astronaut Soc, Amer Inst Aeronaut & Astronaut, Natl & Local Sect, Amer Inst Chem Engineers, Amer Soc Mech Engineers, Heat Transfer Div, NASA Natl Space Grant Coll & Fellowship Program, Profess Aerosp Contractors Assoc, Inst Space & Nucl Power Studies AB During the summer of 2004, several studies were conducted in the Advanced Projects office at the NASA Marshall Space Flight Center (MSFC) related to the development of walking habitats for lunar exploration. This work included conceptual designs for a walker based on existing technology for the robotics as well as the International Space Station (ISS) hardware for pressurized modules; engineering simulations for the overall architectural configuration and mission architecture development; preliminary designs for the pressure vessel and shielding using new composite technologies (as opposed to aluminum); and, ongoing development of computer models containing mass statements for various architecture options. This paper provides a brief summary of some of the key findings from these studies, and identifies areas for future work that will lead to more robust lunar exploration architectures in the future. In conclusion, it is recommended that lunar walking technology be developed for future exploration missions and that polyethylene and carbon reinforced polymer composite materials be used to develop lightweight structures and space environmental shielding. C1 NASA, George C Marshall Space Flight Ctr, Adv Projects Off, Huntsville, AL 35812 USA. RP Smitherman, D (reprint author), NASA, George C Marshall Space Flight Ctr, Adv Projects Off, Huntsville, AL 35812 USA. NR 8 TC 2 Z9 2 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 0-7354-0230-2 J9 AIP CONF PROC PY 2005 VL 746 BP 1078 EP 1087 PG 10 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BBS02 UT WOS:000227496400121 ER PT S AU Figueroa, F Schmalzel, J Duncavage, D AF Figueroa, F Schmalzel, J Duncavage, D BE ElGenk, MS TI Integrated system health management with networked intelligent elements SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM-STAIF 2005 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum CY FEB 13-17, 2005 CL Albuquerque, NM SP Boeing Co, Lockheed Martin, Los Alamos Natl Lab, Sandia Natl Labs, Northrop Grumman Space Technol, Stirling Technol Co, US DOE, Amer Astronaut Soc, Amer Inst Aeronaut & Astronaut, Natl & Local Sect, Amer Inst Chem Engineers, Amer Soc Mech Engineers, Heat Transfer Div, NASA Natl Space Grant Coll & Fellowship Program, Profess Aerosp Contractors Assoc, Inst Space & Nucl Power Studies ID SENSOR; MODEL AB Evolving aerospace systems to include distributed intelligence can improve performance, further safety, and enhance quality, while offering improved cost-benefits. The opportunity addressed by this paper is the development of an Integrated System Health Management (ISHM) architecture and basic technologies, to provide order-of-magnitude improvements in operations strongly dependent on sensors, data acquisition, and condition management. From this new Integrated Health Management with Networked Intelligent Elements (IHNIE) approach, NASA gains the technology to better manage complexity, lower cost, and improve safety, reliability, and quality of space platforms, space vehicles, rocket engine testing, and flight operations. C1 NASA, Stennis Space Ctr, MS 39529 USA. RP Figueroa, F (reprint author), NASA, Bldg 8306, Stennis Space Ctr, MS 39529 USA. NR 19 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 0-7354-0230-2 J9 AIP CONF PROC PY 2005 VL 746 BP 1088 EP 1095 PG 8 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BBS02 UT WOS:000227496400122 ER PT S AU Schowengerdt, FD AF Schowengerdt, FD BE ElGenk, MS TI Toward sustainable and affordable space exploration: The role of NASA's space product development program SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM-STAIF 2005 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum CY FEB 13-17, 2005 CL Albuquerque, NM SP Boeing Co, Lockheed Martin, Los Alamos Natl Lab, Sandia Natl Labs, Northrop Grumman Space Technol, Stirling Technol Co, US DOE, Amer Astronaut Soc, Amer Inst Aeronaut & Astronaut, Natl & Local Sect, Amer Inst Chem Engineers, Amer Soc Mech Engineers, Heat Transfer Div, NASA Natl Space Grant Coll & Fellowship Program, Profess Aerosp Contractors Assoc, Inst Space & Nucl Power Studies AB The National Vision for Space Exploration calls for sustainable and affordable human and robotic missions to explore the solar system. Sustainability requires that the program produce visible benefits to the public, along with scientific and technological advances in support of exploration that would be expected from a program of this magnitude. Affordability requires that the private sector be heavily involved, not just as contractors to NASA, but as sources of investment and direct beneficiaries of returns; in short, full participants in a long-term program that can transform the future of mankind. In order to make the vision both sustainable and affordable, true partnerships involving industry, academia and government must exist to create Earth benefits while working on needed exploration technologies and, at the same time, provide the added investments that will inevitably be required in extended periods of fiscal restraint. Such partnership programs, embodied in the Research Partnership Centers, have long existed within NASA. They have recently been realigned to more fully support the exploration vision and brought into the Exploration Systems Mission Directorate. This program and its past and potential contributions to the exploration vision will be described in detail at the conference. C1 NASA, Space Prod Dev, Washington, DC 20546 USA. RP Schowengerdt, FD (reprint author), NASA, Space Prod Dev, 300 E St SW, Washington, DC 20546 USA. NR 3 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 0-7354-0230-2 J9 AIP CONF PROC PY 2005 VL 746 BP 1108 EP 1114 PG 7 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BBS02 UT WOS:000227496400125 ER PT S AU Valentine, PG Lawrence, TW Gubert, MK Milos, FS Levine, SR Ohlhorst, CW Koenig, JR AF Valentine, PG Lawrence, TW Gubert, MK Milos, FS Levine, SR Ohlhorst, CW Koenig, JR BE ElGenk, MS TI Lightweight nonmetallic thermal protection materials technology SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM-STAIF 2005 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum CY FEB 13-17, 2005 CL Albuquerque, NM SP Boeing Co, Lockheed Martin, Los Alamos Natl Lab, Sandia Natl Labs, Northrop Grumman Space Technol, Stirling Technol Co, US DOE, Amer Astronaut Soc, Amer Inst Aeronaut & Astronaut, Natl & Local Sect, Amer Inst Chem Engineers, Amer Soc Mech Engineers, Heat Transfer Div, NASA Natl Space Grant Coll & Fellowship Program, Profess Aerosp Contractors Assoc, Inst Space & Nucl Power Studies AB To fulfill President George W. Bush's "Vision for Space Exploration" (NASA, 2004).-- successful human and robotic missions to and from other solar system bodies in order to explore their atmospheres and surfaces - the National Aeronautics and Space Administration (NASA) must reduce the trip time, cost, and vehicle weight so that the payload and scientific experiments' capabilities can be maximized. The new project described in this paper will generate thermal protection system (TPS) products that will enable greater fidelity in mission/vehicle design trade studies, support risk reduction for material selections, assist in the optimization of vehicle weights, and provide materials and processes templates for use in the development of human-rated TPS qualification and certification plans. C1 NASA, George C Marshall Space Flight Ctr, Engn Directorate, Huntsville, AL 35812 USA. RP Valentine, PG (reprint author), NASA, George C Marshall Space Flight Ctr, Engn Directorate, Huntsville, AL 35812 USA. NR 13 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 0-7354-0230-2 J9 AIP CONF PROC PY 2005 VL 746 BP 1115 EP 1120 PG 6 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BBS02 UT WOS:000227496400126 ER PT S AU Alhorn, DC AF Alhorn, DC BE ElGenk, MS TI Autonomous assembly of modular structures in space and on extraterrestrial locations SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM-STAIF 2005 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum CY FEB 13-17, 2005 CL Albuquerque, NM SP Boeing Co, Lockheed Martin, Los Alamos Natl Lab, Sandia Natl Labs, Northrop Grumman Space Technol, Stirling Technol Co, US DOE, Amer Astronaut Soc, Amer Inst Aeronaut & Astronaut, Natl & Local Sect, Amer Inst Chem Engineers, Amer Soc Mech Engineers, Heat Transfer Div, NASA Natl Space Grant Coll & Fellowship Program, Profess Aerosp Contractors Assoc, Inst Space & Nucl Power Studies AB The new U.S. National Vision for Space Exploration requires many new enabling technologies to accomplish the goals of space commercialization and returning humans to the moon and extraterrestrial environments. Traditionally, flight elements are complete sub-systems requiring humans to complete the integration and assembly. These bulky structures also require the use of heavy launch vehicles to send the units to a desired location. This philosophy necessitates a high degree of safety, numerous space walks at a significant cost. Future space mission costs must be reduced and safety increased to reasonably achieve exploration goals. One proposed concept is the autonomous assembly of space structures. This concept is an affordable, reliable solution to in-space and extraterrestrial assembly. Assembly is autonomously performed when two components join after determining that specifications are correct. Local sensors continue monitor joint integrity post assembly, which is critical for safety and structural reliability. Achieving this concept requires a change in space structure design philosophy and the development of innovative technologies to perform autonomous assembly. Assembly of large space structures will require significant numbers of integrity sensors. Thus simple, low-cost sensors are integral to the success of this concept. This paper addresses these issues and proposes a novel concept for assembling space structures autonomously. Core technologies required to achieve in space assembly are presented. These core technologies are critical to the goal of utilizing space in a cost efficient and safe manner. Additionally, these novel technologies can be applied to other systems both on earth and extraterrestrial environments. C1 NASA, George C Marshall Space Flight Ctr, Huntsville, AL 35812 USA. RP Alhorn, DC (reprint author), NASA, George C Marshall Space Flight Ctr, ED17, Huntsville, AL 35812 USA. NR 7 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 0-7354-0230-2 J9 AIP CONF PROC PY 2005 VL 746 BP 1121 EP 1128 PG 8 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BBS02 UT WOS:000227496400127 ER PT S AU Brown, KK Nelson, KW AF Brown, KK Nelson, KW BE ElGenk, MS TI Technology challenges for deep-throttle cryogenic engines for space exploration SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM-STAIF 2005 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum CY FEB 13-17, 2005 CL Albuquerque, NM SP Boeing Co, Lockheed Martin, Los Alamos Natl Lab, Sandia Natl Labs, Northrop Grumman Space Technol, Stirling Technol Co, US DOE, Amer Astronaut Soc, Amer Inst Aeronaut & Astronaut, Natl & Local Sect, Amer Inst Chem Engineers, Amer Soc Mech Engineers, Heat Transfer Div, NASA Natl Space Grant Coll & Fellowship Program, Profess Aerosp Contractors Assoc, Inst Space & Nucl Power Studies AB Historically, cryogenic rocket engines have not been used for in-space applications due to their additional complexity, the mission need for high reliability, and the challenges of propellant boil-off. While the mission and vehicle architectures are not yet defined for the lunar and Martian robotic and human exploration objectives, cryogenic rocket engines offer the potential for higher performance and greater architecture/mission flexibility. In-situ cryogenic propellant production could enable a more robust exploration program by significantly reducing the propellant mass delivered to low earth orbit, thus warranting the evaluation of cryogenic rocket engines versus the hypergolic bi-propellant engines used in the Apollo program. A multi-use engine, one which can provide the functionality that separate engines provided in the Apollo mission architecture, is desirable for lunar and Mars exploration missions because it increases overall architecture effectiveness through commonality and modularity. The engine requirement derivation process must address each unique mission application and each unique phase within each mission. The resulting requirements, such as thrust level, performance, packaging, bum duration, number of operations; required impulses for each trajectory phase; operation after extended space or surface exposure; availability for inspection and maintenance; throttle range for planetary descent, ascent, acceleration limits and many more must be addressed. Within engine system studies, the system and component technology, capability, and risks must be evaluated and a balance between the appropriate amount of technology-push and technology-pull must be addressed. This paper will summarize many of the key technology challenges associated with using high-performance cryogenic liquid propellant rocket engine systems and components in the exploration program architectures. The paper is divided into two areas. The first area describes how the mission requirements affect the engine system requirements and create system level technology challenges. An engine system architecture for multiple applications or a family of engines based upon a set of core technologies, design, and fabrication approaches may reduce overall programmatic cost and risk. The engine system discussion will also address the characterization of engine cycle figures of merit, configurations, and design approaches for some in-space vehicle alternatives under consideration. The second area evaluates the component-level technology challenges induced from the system requirements. Component technology issues are discussed addressing injector, thrust chamber, ignition system, turbopump assembly, and valve design for the challenging requirements of high reliability, robustness, fault tolerance, deep throttling, reasonable performance (with respect to weight and specific impulse). C1 NASA, George C Marshall Space Flight Ctr, Liquid Engine & MPS Syst Branch, Huntsville, AL 35812 USA. RP Brown, KK (reprint author), NASA, George C Marshall Space Flight Ctr, Liquid Engine & MPS Syst Branch, Huntsville, AL 35812 USA. NR 2 TC 0 Z9 0 U1 0 U2 1 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 0-7354-0230-2 J9 AIP CONF PROC PY 2005 VL 746 BP 1137 EP 1144 PG 8 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BBS02 UT WOS:000227496400129 ER PT S AU Crawford, JM Weisbin, CR AF Crawford, JM Weisbin, CR BE ElGenk, MS TI Autonomous operations for the crew exploration vehicle - Trade study design considerations SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM-STAIF 2005 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum CY FEB 13-17, 2005 CL Albuquerque, NM SP Boeing Co, Lockheed Martin, Los Alamos Natl Lab, Sandia Natl Labs, Northrop Grumman Space Technol, Stirling Technol Co, US DOE, Amer Astronaut Soc, Amer Inst Aeronaut & Astronaut, Natl & Local Sect, Amer Inst Chem Engineers, Amer Soc Mech Engineers, Heat Transfer Div, NASA Natl Space Grant Coll & Fellowship Program, Profess Aerosp Contractors Assoc, Inst Space & Nucl Power Studies AB In the design of the operational concept for the CEV there are numerous choices regarding the locus of command and control. Systems such as power, propulsion, GN&C, life support, C&DH, etc. can be monitored and controlled by the flight crew, by onboard autonomous systems, by ground crew, or by ground autonomous systems. The decision of how to distribute control must be based on a complex trade-off between development and validation costs, operations costs, and reliability/risks. Getting these trade-offs wrong can lead to unnecessary growth in mission cost and risk, and unnecessary decreases in the time the crew has available for core exploration tasks. Over the next two years we will be performing an in depth analysis of the return on investment that we can expect from software tools that automate, or partially automate, the operation of CEV systems. In this paper we preview the issues in performing a trade study of this type, and the technical approach that will be used to gather and analyze the data required to perform this, and other similar, trade studies. C1 NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Crawford, JM (reprint author), NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. NR 6 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 0-7354-0230-2 J9 AIP CONF PROC PY 2005 VL 746 BP 1145 EP 1152 PG 8 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BBS02 UT WOS:000227496400130 ER PT S AU Marzwell, NI Waterman, RD KrishnaKumar, K Waterman, SJ AF Marzwell, NI Waterman, RD KrishnaKumar, K Waterman, SJ BE ElGenk, MS TI How to extend the capabilities of space systems for long duration space exploration systems SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM-STAIF 2005 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum CY FEB 13-17, 2005 CL Albuquerque, NM SP Boeing Co, Lockheed Martin, Los Alamos Natl Lab, Sandia Natl Labs, Northrop Grumman Space Technol, Stirling Technol Co, US DOE, Amer Astronaut Soc, Amer Inst Aeronaut & Astronaut, Natl & Local Sect, Amer Inst Chem Engineers, Amer Soc Mech Engineers, Heat Transfer Div, NASA Natl Space Grant Coll & Fellowship Program, Profess Aerosp Contractors Assoc, Inst Space & Nucl Power Studies AB For sustainable Exploration Missions the need exists to assemble systems-of-systems in space, on the Moon or on other planetary surfaces. To fulfill this need new and innovative system architectures must be developed to be modularized and launched with the present lift capability of existing rocket technology. To enable long duration missions with minimal redundancy and mass, system software and hardware must be reconfigurable. This will enable increased functionality and multiple use of launched assets while providing the capability to quickly overcome components failures. Additional required capability includes the ability to dynamically demate and reassemble individual system elements during a mission in order to recover from failed hardware or to adapt to changes in mission requirements. To meet the Space Exploration goals of Interoperability and Reconfigurability, many challenges must be addressed to transform the traditional static avionics architectures into architectures with dynamic capabilities. The objective of this paper is to introduce concepts associated with reconfigurable computer systems; to review the various needs and challenges associated with reconfigurable avionics space systems; to provide an operational example that illustrates the application to both the Crew Exploration Vehicle and a collection of "Habot-like" mobile surface elements; to summarize the approaches that address key challenges to the acceptance of a Flexible, Intelligent, Modular, Affordable and Reconfigurable avionics space system. C1 NASA, Jet Prop Lab, Pasadena, CA 91109 USA. RP Marzwell, NI (reprint author), NASA, Jet Prop Lab, M-S 180-603, Pasadena, CA 91109 USA. NR 8 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 0-7354-0230-2 J9 AIP CONF PROC PY 2005 VL 746 BP 1153 EP 1159 PG 7 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BBS02 UT WOS:000227496400131 ER PT S AU Wilkinson, RA Behringer, RP Jenkins, JT Louge, MY AF Wilkinson, RA Behringer, RP Jenkins, JT Louge, MY BE ElGenk, MS TI Granular materials and the risks they pose for success on the Moon and Mars SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM-STAIF 2005 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum CY FEB 13-17, 2005 CL Albuquerque, NM SP Boeing Co, Lockheed Martin, Los Alamos Natl Lab, Sandia Natl Labs, Northrop Grumman Space Technol, Stirling Technol Co, US DOE, Amer Astronaut Soc, Amer Inst Aeronaut & Astronaut, Natl & Local Sect, Amer Inst Chem Engineers, Amer Soc Mech Engineers, Heat Transfer Div, NASA Natl Space Grant Coll & Fellowship Program, Profess Aerosp Contractors Assoc, Inst Space & Nucl Power Studies ID PRESSURIZED CIRCULATING FLUIDIZATION; PARTICLES; FLOWS; GAS AB Working with soil, sand, powders, ores, cement and sintered bricks, excavating, grading construction sites, driving off-road, transporting granules in chutes and pipes, sifting gravel, separating solids from gases, and using hoppers are so routine that it seems straightforward to do it on the Moon and Mars as we do it on Earth. This paper brings to the fore how little these processes are understood and the millennia-long trial-and-error practices that lead to today's massive over-design, high failure rate, and extensive incremental scaling up of industrial processes because of the inadequate predictive tools for design. We present a number of pragmatic scenarios where granular materials play a role, the risks involved, and what understanding is needed to greatly reduce the risks. C1 NASA, Glenn Res Ctr, Micrograv Fluid Phys Branch, Cleveland, OH 44135 USA. RP Wilkinson, RA (reprint author), NASA, Glenn Res Ctr, Micrograv Fluid Phys Branch, Cleveland, OH 44135 USA. NR 22 TC 1 Z9 1 U1 2 U2 3 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 0-7354-0230-2 J9 AIP CONF PROC PY 2005 VL 746 BP 1216 EP 1223 PG 8 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BBS02 UT WOS:000227496400137 ER PT S AU Moses, RW AF Moses, RW BE ElGenk, MS TI Regenerative aerobraking SO SPACE TECHNOLOGY AND APPLICATIONS INTERNATIONAL FORUM-STAIF 2005 SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT Space Technology and Applications International Forum CY FEB 13-17, 2005 CL Albuquerque, NM SP Boeing Co, Lockheed Martin, Los Alamos Natl Lab, Sandia Natl Labs, Northrop Grumman Space Technol, Stirling Technol Co, US DOE, Amer Astronaut Soc, Amer Inst Aeronaut & Astronaut, Natl & Local Sect, Amer Inst Chem Engineers, Amer Soc Mech Engineers, Heat Transfer Div, NASA Natl Space Grant Coll & Fellowship Program, Profess Aerosp Contractors Assoc, Inst Space & Nucl Power Studies AB NASA's exploration goals for Mars and Beyond will require new power systems and in situ resource utilization technologies. Regenerative aerobraking may offer a revolutionary approach for in situ power generation and oxygen harvesting during these exploration missions. In theory, power and oxygen can be collected during aerobraking and stored for later use in orbit or on the planet. This technology would capture energy and oxygen from the plasma field that occurs naturally during hypersonic entry using well understood principles of magnetohydrodynamics and oxygen filtration. This innovative approach generates resources upon arrival at the operational site, and thus greatly differs from the traditional approach of taking everything you need with you from Earth. Fundamental analysis, computational fluid dynamics, and some testing of experimental hardware have established the basic feasibility of generating power during a Mars entry. Oxygen filtration at conditions consistent with spacecraft entry parameters at Mars has been studied to a lesser extent. Other uses of the MHD power are presented. This paper illustrates how some features of regenerative aerobraking may be applied to support human and robotic missions at Mars. C1 NASA, Langley Res Ctr, Explorat Syst Engn Branch, Hampton, VA 23681 USA. RP Moses, RW (reprint author), NASA, Langley Res Ctr, Explorat Syst Engn Branch, Hampton, VA 23681 USA. NR 21 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 0-7354-0230-2 J9 AIP CONF PROC PY 2005 VL 746 BP 1361 EP 1370 PG 10 WC Engineering, Aerospace; Nuclear Science & Technology SC Engineering; Nuclear Science & Technology GA BBS02 UT WOS:000227496400155 ER PT J AU Gopalswamy, N Lara, A Manoharan, PK Howard, RA AF Gopalswamy, N Lara, A Manoharan, PK Howard, RA TI An empirical model to predict the 1-AU arrival of interplanetary shocks SO SPACE WEATHER SE ADVANCES IN SPACE RESEARCH LA English DT Article DE space weather; interplanetary shocks; predicting interplanetary shock arrival; coronal mass ejections ID CORONAL MASS EJECTIONS; ACCELERATION AB We extend the empirical coronal mass ejection (CME) arrival model of Gopalswamy et al. [Gopalswamy, N. et al. Predicting the 1-AU arrival times of coronal mass ejections, J. Geophys. Res. 106, 29207, 2001] to predict the 1-AU arrival of interplanetary (IP) shocks. A set of 29 IP shocks and the associated magnetic clouds observed by the Wind spacecraft are used for this study. The primary input to this empirical shock arrival model is the initial speed of white-light CMEs obtained using coronagraphs. We use the gas dynamic piston-shock relationship to derive the ESA model which provides a simple means of obtaining the 1-AU speed and arrival times of interplanetary shocks using CME speeds. (c) 2005 COSPAR. Published by Elsevier Ltd. All rights reserved. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Catholic Univ Amer, Washington, DC 20064 USA. USN, Res Lab, Washington, DC 20064 USA. RP Gopalswamy, N (reprint author), NASA, Goddard Space Flight Ctr, Mail Code 695, Greenbelt, MD 20771 USA. EM n_gopalswamy@yahoo.com RI Gopalswamy, Nat/D-3659-2012; OI Lara, Alejandro/0000-0001-6336-5291; Manoharan, Periasamy K/0000-0003-4274-211X NR 13 TC 54 Z9 57 U1 0 U2 0 PU ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD 0X5 1GB, OXON, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2005 VL 36 IS 12 SI 2005 BP 2289 EP 2294 DI 10.1016/j.asr.2004.07.014 PG 6 WC Engineering, Aerospace; Astronomy & Astrophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Engineering; Astronomy & Astrophysics; Geology; Meteorology & Atmospheric Sciences GA BDS48 UT WOS:000235183100008 ER PT J AU Tulunay, Y Sibeck, DG Senalp, ET Tulunay, E AF Tulunay, Y Sibeck, DG Senalp, ET Tulunay, E TI Forecasting magnetopause crossing locations by using Neural Networks SO SPACE WEATHER SE ADVANCES IN SPACE RESEARCH LA English DT Article DE Neural Network; magnetopause; forecast ID INTERPLANETARY MAGNETIC-FIELD; WIND DYNAMIC PRESSURE; DAYSIDE MAGNETOSPHERE; TIME-SERIES; SHAPE; EROSION; SIZE; AE AB Given the highly complex and nonlinear nature of Near Earth Space processes, mathematical modeling of these processes is usually difficult or impossible. In such cases, modeling methods involving Artificial Intelligence may be employed. We demonstrate that data driven models, such as the Neural Network based approach, shows promise in its ability to forecast or predict the behavior of these processes. In this paper, modeling studies for forecasting magnetopause crossing locations are summarized and a Neural Network algorithm is presented to describe the nonlinear time-dependent response of the subsolar region of the magnetopause to varying solar wind conditions. In our approach the past history of the solar wind has, for the first time to the best knowledge of the authors, been included in forecasting the subsolar region of the magnetopause. It is proposed that the data driven approach is a valid approach to understanding and modeling the physical phenomena of Near Earth Space. The only basic requirement for the data driven approach is the availability of representative data for the phenomena. The objective of this paper is to demonstrate that by using WIND and GEOTAIL satellite data a Neural Network based model can be adapted to the modeling of the Earth's magnetopause. (c) 2004 COSPAR. Published by Elsevier Ltd. All rights reserved. C1 Middle E Tech Univ, Dept Aerosp Engn, TR-06531 Ankara, Turkey. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Middle E Tech Univ, Dept Elect & Elect Engn, TR-06531 Ankara, Turkey. TUBITAK Marmara Res Ctr, Informat Technol Res Inst, TR-41470 Kocaeli, Turkey. RP Tulunay, Y (reprint author), Middle E Tech Univ, Dept Aerosp Engn, TR-06531 Ankara, Turkey. EM ytulunay@metu.edu.tr RI Sibeck, David/D-4424-2012 NR 23 TC 4 Z9 4 U1 0 U2 3 PU ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD 0X5 1GB, OXON, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2005 VL 36 IS 12 SI 2005 BP 2378 EP 2383 DI 10.1016/j.asr.2004.04.015 PG 6 WC Engineering, Aerospace; Astronomy & Astrophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Engineering; Astronomy & Astrophysics; Geology; Meteorology & Atmospheric Sciences GA BDS48 UT WOS:000235183100024 ER PT J AU Rigler, EJ Baker, DN Weigel, RS Vassilladis, D AF Rigler, EJ Baker, DN Weigel, RS Vassilladis, D TI Solar wind-driven electron radiation belt response functions at 100-min time scales SO SPACE WEATHER SE ADVANCES IN SPACE RESEARCH LA English DT Article DE linear prediction filter; electron radiation belt; finite impulse response; autoregressive filter ID SPACE WEATHER; PREDICTION; SAMPEX; MAGNETOSPHERE; STORM; INNER; ORBIT AB We present a simple yet numerically robust technique, using autoregressive linear filters, to remove unwanted "colored noise" from solar wind and radiation belt electron data at sub-daily resolution. The remaining signal is then studied using finite impulse response linear prediction filters to represent the driven portion of the linear dynamics that describe the coupling between solar wind speed and electron flux. Sub-daily resolution response profiles covering magnetic L-shells between 1.1 and 8.0 R-E are presented which are consistent with daily resolution response functions. Namely, while there is strong global coherence governing electron flux dynamics, there are at least two distinct responses. The first response is an immediate dropout of electrons between L = 4 and L = 7 that is at least a partly adiabatic effect associated with enhancements in the ring current. This is followed by a 1-2 day delayed enhancement across the same L-shells that is likely a result of increased radial diffusion. The second response is an immediate enhancement seen between L = 3 and L = 4 with a typical duration of less than one day. Plausible explanations for this second response are briefly discussed, but neither empirical nor theoretical evidence can establish conclusively a definite physical cause. Finally, the response profiles show significant solar cycle and seasonal dependencies, indicating that better model output might be achieved with: (1) additional simultaneous solar wind inputs; (2) more sophisticated dynamical model structures capable of incorporating non-linear feedback; and/or (3) time-adaptive linear filters that can track non-stationary dynamics in time. (c) 2004 COSPAR. Published by Elsevier Ltd. All rights reserved. C1 Univ Colorado, LASP, Boulder, CO 80303 USA. NASA, Goddard Space Flight Ctr, USRA, Greenbelt, MD 20771 USA. RP Rigler, EJ (reprint author), Univ Colorado, LASP, 1234 Innovat Dr, Boulder, CO 80303 USA. EM jrigler@colorado.edu NR 19 TC 2 Z9 2 U1 0 U2 0 PU ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD 0X5 1GB, OXON, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2005 VL 36 IS 12 SI 2005 BP 2401 EP 2406 DI 10.1016/j.asr.2003.09.070 PG 6 WC Engineering, Aerospace; Astronomy & Astrophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Engineering; Astronomy & Astrophysics; Geology; Meteorology & Atmospheric Sciences GA BDS48 UT WOS:000235183100028 ER PT J AU Johnson, AS Golightly, MJ Weyland, MD Lin, T Zapp, EN AF Johnson, AS Golightly, MJ Weyland, MD Lin, T Zapp, EN TI Minimizing space radiation exposure during extra-vehicular activity SO SPACE WEATHER SE ADVANCES IN SPACE RESEARCH LA English DT Article AB Continued assembly of the International Space Station (ISS) requires numerous extra-vehicular activities (EVAs). Prudent radiological safety practices require minimizing additional exposures to crewmen during these periods. The spatial distribution of the "normal" trapped proton and electron radiation sources in low Earth orbit is strongly governed by the geomagnetic field. It is possible to use ISS trajectory information to estimate crew exposures during EVAs and to identify periods that can result in minimal EVA crew exposures through avoidance of these trapped radiation regions. Such exposure minimization planning can also accommodate the unforeseen development of a solar proton event. An EVA exposure estimation tool, EVADOSE, is described and applied to various EVA exposure scenarios. Procedures and parameters that influence EVA exposures are discussed along with techniques to minimize crew exposures. Published by Elsevier Ltd on behalf of COSPAR. C1 NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. RP Johnson, AS (reprint author), NASA, Lyndon B Johnson Space Ctr, 2004 NASA Rd 1,Mail Code C23,Lockheed Martin, Houston, TX 77058 USA. EM a.s.johnson1@jsc.nasa.gov NR 4 TC 3 Z9 3 U1 1 U2 1 PU ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD 0X5 1GB, OXON, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2005 VL 36 IS 12 SI 2005 BP 2524 EP 2529 DI 10.1016/j.asr.2004.05.008 PG 6 WC Engineering, Aerospace; Astronomy & Astrophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Engineering; Astronomy & Astrophysics; Geology; Meteorology & Atmospheric Sciences GA BDS48 UT WOS:000235183100050 ER PT S AU Habib, S AF Habib, S BE Tchoryk, P Holz, B TI Understanding what's critical in protecting our society: can satellite observations help? SO Spaceborne Sensors II SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Spaceborne Sensors II CY MAR 28-29, 2005 CL Orlando, FL SP SPIE, Optech Inc AB There are many vital issues which are impacting our daily lives and will continue to haunt us as long as we live on this planet of ours. These issues range from food supply availability, drought, coastal zone erosion, volcanoes, hurricanes, terrorism, global warming, earthquakes, water resources, air quality, public health, and agriculture production. Such societal needs are directly linked to our geometric population growth, and abundance of automobiles, industrial emissions, industrial waste and extensive fishing of our oceans and elimination of our ecology. The questions which require serious thoughts, research, coordination, and resources to understand, plan and strike a sensible balance in our daily lives and the above issues are tough to deal with. However, with the advent of remote sensing technologies, tremendous progress has been made in applying space-based and airborne data and products in solving real societal problems. Several of these problems, such as coastal zone erosion, air quality, severe weather, water availability and quality, public health, fires, land slides and others are intricately related; and in the long run can have serious consequences if not properly addressed by scientists, regulatory bodies and policy makers. Although it is a much involved and tangled web to unravel, nevertheless we have an excellent start in understanding some of the phenomena and hopefully can mitigate some of the severe effects by advancing our scientific knowledge. This paper briefly discusses the applications of remote sensing data from Terra, Aqua, and other NASA satellites how to deal with such complex problems; it provides an excellent start. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Habib, S (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. NR 3 TC 1 Z9 1 U1 0 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 0-8194-5783-3 J9 P SOC PHOTO-OPT INS PY 2005 VL 5798 BP 1 EP 6 DI 10.1117/12.606587 PG 6 WC Engineering, Aerospace SC Engineering GA BCR83 UT WOS:000230974000001 ER PT S AU Karasik, BS Wadsworth, M AF Karasik, BS Wadsworth, M BE Tchoryk, P Holz, B TI Large CMOS imager using Hadamard Transform based multiplexing SO Spaceborne Sensors II SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Spaceborne Sensors II CY MAR 28-29, 2005 CL Orlando, FL SP SPIE, Optech Inc DE CMOs imager; Hadamard Transform; code-division multiplexing AB We have developed a concept design for a large (similar to 10k x 10k) CMOs imaging array whose elements are grouped in small subarrays with N pixels in each. The subarrays are code-division multiplexed using the Hadamard Transform (HT) based encoding. The Hadamard code improves the signal-to-noise (SNR) ratio to the reference of the read-out amplifier noise by a factor of N-1/2. This way of grouping pixels reduces the number of hybridization bumps by N. A single chip layout has been designed and the architecture of the imager has been developed to accommodate the HT based multiplexing into the existing CMOs technology. The imager architecture allows for a trade-off between the speed and the sensitivity. The envisioned imager would operate at a speed > 100 fps with the pixel noise < 20 e(-). The power dissipation would be similar to 100 pW/pixel. The combination of the large format, high speed, high sensitivity and low power dissipation are very attractive for space applications. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Karasik, BS (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 0-8194-5783-3 J9 P SOC PHOTO-OPT INS PY 2005 VL 5798 BP 83 EP 90 DI 10.1117/12.602840 PG 8 WC Engineering, Aerospace SC Engineering GA BCR83 UT WOS:000230974000010 ER PT S AU West, JL AF West, JL BE Coffey, SL Coffey, SL Mazzoleni, AP Luu, KK Glover, RA TI The geostorm warning mission: Enhanced opportunities based on new technology SO Spaceflight Mechanics 2004, Vol 119, Pt 1-3 SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT AAS/AIAA 14th Space Flight Mechanics Meeting CY FEB 08-12, 2004 CL Maui, HI SP AAS, Amer Inst Aeronaut & Astronaut AB The Geostorm Warning Mission is a potential future National Ocean and Atmospheric Administration (NOAA) mission with the objective of obtaining solar storm warning data from a satellite positioned at an unnatural station slightly displaced from the Earth-Sun line at or nearer to the Sun than 0.98 AU inside the Earth's natural L1 point at 0.993 AU. The satellite would achieve this unnatural station by merging solar sail and small satellite technology. Utilizing technology available at the time, the most recent formal mission proposal to perform the Geostorm Warning Mission, and the only formal mission proposal to date, the Jet Propulsion Laboratory's (JPL) Space Technology-5 (ST-5) proposal developed in response to the NASA New Millenium Program's (NMP) ST-5 call in 1999, could enable a factor of 2 increase in warning time compared to a conventional satellite stationed at the L1 point. This increase in warning time, which required artificially displacing the L1 equilibrium point from 0.993 AU to 0.984 AU, was achieved utilizing a sail concept developed by L'Garde, Inc. of Tustin, CA which utilized an inflatable UV-rigidized Kevlar boom and a sailcraft and sailcraft bus concept developed by Ball Aerospace Corp., Boulder, CO, in conjunction with JPL. The sail utilized 0.33-mil (8-micron) thick Kapton for the sail membrane material, and the sailcraft utilized a conventional monopropellant hydrazine propulsion subsystem for attitude control of the spin-stablized sailcraft vehicle. The overall sailcraft system thus designed could achieve beginning-of-life and end-of-life sailcraft loadings of 42.1 and 36.3 grams/m(2), respectively, sufficient to achieve an operational station location between 0.984 and 0.983 AU. While not selected by NASA for flight demonstration, the ST-5 sailcraft concept, and a subsequent sailcraft concept proposed by JPL in response to the NMP ST-7 proposal call in 2001, effectively highlighted the performance potential and mission-enabling capabilities of solar sails, helping to galvanize support for the development of sails under NASA's 2002-launched, NASA Marshall-Space-Flight-Center (MSFC)-managed, In-Space Propulsion Technology (ISPT) Program. This new NASA Program has the objective of developing and ground demonstrating emerging new propulsion technologies that show promise for substantially enhancing NASA mission opportunities and mission performance. In specific, the program is designed to bring propulsion technologies currently at a technology readiness level (TRL) of 3 on NASA's 10-level readiness scale to 6. Early work under this new NASA Program has already yielded promising results for enhanced Geostorm Warning Mission performance, as this paper discusses. What the early results of the ISPT Program show for Geostorm Warning Mission performance is the potential for ground demonstration within two years of an overall saileraft loading of 9.48 g/m(2) compared to the 1999 ST-5 proposal's 42.1 g/m(2) at beginning-of-life and 36.3 g/m(2) at end-of-life. Sailcraft loadings of 9.48 g/ml can enable achievement of a stable equilibrium station at 0.974 AU, equivalent to an increase in warning time of nearly a factor of 4 compared to the factor of 2 for the 1999 ST-5 proposal compared to a conventional satellite stationed at the L-point. This enhanced performance is achievable principally through improvement in the sail areal density, through use of lower linear mass density booms, a thinner membrane, and increased sail area, with some new ideas pertaining to sailcraft vehicle system design also offering potential mass reduction and hence improved performance. The sail design uses a new inflatable boom design developed by L'Garde, Inc. with sub-Tg rigidization and very low sail stresses, that is, sail stresses << 10 psi. The sailcraft makes use of a unique Ball-Aerospace-Corp.-developed approach to sailcraft vehicle system design which uses a separable sailcraft carrier module to accommodate launch loads and provide saileraft vehicle stabilization during post-launch sail deployment. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP West, JL (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 6 TC 2 Z9 2 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 0-87703-515-6 J9 ADV ASTRONAUT SCI PY 2005 VL 119 BP 29 EP 42 PN 1-3 PG 14 WC Automation & Control Systems; Engineering, Aerospace; Mechanics SC Automation & Control Systems; Engineering; Mechanics GA BBZ98 UT WOS:000228444908003 ER PT S AU Boain, RJ AF Boain, RJ BE Coffey, SL Coffey, SL Mazzoleni, AP Luu, KK Glover, RA TI A-B-Cs of sun-synchronous orbit mission design SO Spaceflight Mechanics 2004, Vol 119, Pt 1-3 SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT AAS/AIAA 14th Space Flight Mechanics Meeting CY FEB 08-12, 2004 CL Maui, HI SP AAS, Amer Inst Aeronaut & Astronaut AB The sun-synchronous orbit is one of the most frequently used orbits for earth science missions. Generally within the field of astrodynamics and mission analysis, the sun-synchronous orbit is understood to be a near polar orbit where the nodal precession rate is matched to the earth's mean orbital rate around the sun. This has the effect of maintaining the orbit's geometry with respect to the sun roughly fixed such that the sun lighting along the groundtrack remains approximately the same over the mission's duration. But many engineers still lack the intuitive understanding of how to go about selecting the basic orbit parameters to meet their science mission needs and what exactly are the subtle effects that drive important small-scale geometric variations associated with the synsynchronous orbit that relate to satellite and science instrument design. The existing literature and various references are tentative and even ambiguous from source to source. This paper is intended to provide a tutorial for practicing engineers wanting deeper insight into the key characteristics of sun-synchronous orbits. The paper will develop the background and information necessary to explain what a sun-synchronous orbit is and how it works. Handy back of the envelope equations will be provided to enable the mission analyst and system engineer to do quick and simple calculations for the orbit parameters selection and to compute mission parameters important to satellite design without having to resort to sophisticated computer programs. C1 CALTECH, Jet Prop Lab, Miss & Syst Architecture Sect, Pasadena, CA 91109 USA. RP Boain, RJ (reprint author), CALTECH, Jet Prop Lab, Miss & Syst Architecture Sect, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 15 TC 4 Z9 4 U1 0 U2 1 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 0-87703-515-6 J9 ADV ASTRONAUT SCI PY 2005 VL 119 BP 85 EP 104 PN 1-3 PG 20 WC Automation & Control Systems; Engineering, Aerospace; Mechanics SC Automation & Control Systems; Engineering; Mechanics GA BBZ98 UT WOS:000228444908007 ER PT S AU Queen, EM AF Queen, EM BE Coffey, SL Coffey, SL Mazzoleni, AP Luu, KK Glover, RA TI Angle-of-attack-modulated terminal point control for neptune aerocapture SO Spaceflight Mechanics 2004, Vol 119, Pt 1-3 SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT AAS/AIAA 14th Space Flight Mechanics Meeting CY FEB 08-12, 2004 CL Maui, HI SP AAS, Amer Inst Aeronaut & Astronaut AB An aerocapture guidance algorithm based on a calculus of variations approach is developed, using angle of attack as the primary control variable. Bank angle is used as a secondary control to alleviate angle of attack extremes and to control inclination. The guidance equations are derived in detail. The controller has very small onboard computational requirements and is robust to atmospheric and aerodynamic dispersions. The algorithm is applied to aerocapture at Neptune. Three versions of the controller are considered with varying angle of attack authority. The three versions of the controller are evaluated using Monte Carlo simulations with expected dispersions. C1 NASA, Langley Res Ctr, Hampton, VA 23665 USA. RP Queen, EM (reprint author), NASA, Langley Res Ctr, Hampton, VA 23665 USA. NR 9 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 0-87703-515-6 J9 ADV ASTRONAUT SCI PY 2005 VL 119 BP 417 EP 425 PN 1-3 PG 9 WC Automation & Control Systems; Engineering, Aerospace; Mechanics SC Automation & Control Systems; Engineering; Mechanics GA BBZ98 UT WOS:000228444908027 ER PT S AU Ryne, M Nandi, S AF Ryne, M Nandi, S BE Coffey, SL Coffey, SL Mazzoleni, AP Luu, KK Glover, RA TI Nozomi earth swingby orbit determination SO Spaceflight Mechanics 2004, Vol 119, Pt 1-3 SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT AAS/AIAA 14th Space Flight Mechanics Meeting CY FEB 08-12, 2004 CL Maui, HI SP AAS, Amer Inst Aeronaut & Astronaut AB The Nozomi mission has been disrupted by several anomalies, including a maneuver under bum, loss of the low gain S-band transponder and a large solar flare that damaged many spacecraft subsystems. These anomalies placed constraints on the Nozomi operation that resulted in sever degradation of navigation data collected during critical mission phases. Resultant large navigation errors could potentially have resulted in the loss of scientific return from the mission. This paper describes the Jet Propulsion Laboratory effort to navigate Nozomi, in conjunction with Japan's Institute of Space and Astronautical Science, past two Earth swingbys using differential tracking techniques to successfully place the spacecraft on a trajectory reaching Mars in December 2003. C1 CALTECH, Jet Prop Lab, Navigat & Flight Mech Sect, Pasadena, CA 91109 USA. RP Ryne, M (reprint author), CALTECH, Jet Prop Lab, Navigat & Flight Mech Sect, 4800 Oak Grove Dr, Pasadena, CA 91109 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 0-87703-515-6 J9 ADV ASTRONAUT SCI PY 2005 VL 119 BP 443 EP 461 PN 1-3 PG 19 WC Automation & Control Systems; Engineering, Aerospace; Mechanics SC Automation & Control Systems; Engineering; Mechanics GA BBZ98 UT WOS:000228444908029 ER PT S AU Kennedy, BM Carranza, E Williams, K AF Kennedy, BM Carranza, E Williams, K BE Coffey, SL Coffey, SL Mazzoleni, AP Luu, KK Glover, RA TI 1-AU calibration activities for stardust earth return SO Spaceflight Mechanics 2004, Vol 119, Pt 1-3 SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT AAS/AIAA 14th Space Flight Mechanics Meeting CY FEB 08-12, 2004 CL Maui, HI SP AAS, Amer Inst Aeronaut & Astronaut AB In January 2006, the Stardust spacecraft will deliver its Sample Return Capsule (SRC) to the recovery site at the Utah Test and Training Range (UTTR) in N. Utah. Stardust will return dust samples from comet Wild 2 collected in January 2004, as well as interstellar dust collected at earlier epochs in heliocentric orbit. During Earth return, the trajectory will be perturbed by small firings of the spacecraft reaction control thrusters. Calibration of these firings is essential to ensure meeting Earth entry requirements. This paper will describe such calibrations performed between superior conjunctions in June-July 2003 when Stardust was about 1 AU from the Sun. Results of their subsequent analysis indicate that although more work remains to be done, modifications of the maneuver execution sequences and attitude transition strategies greatly increase the chances of mission success. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Williams, K (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,M-S 301-125J, Pasadena, CA 91109 USA. NR 3 TC 1 Z9 1 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 0-87703-515-6 J9 ADV ASTRONAUT SCI PY 2005 VL 119 BP 491 EP 508 PN 1-3 PG 18 WC Automation & Control Systems; Engineering, Aerospace; Mechanics SC Automation & Control Systems; Engineering; Mechanics GA BBZ98 UT WOS:000228444908032 ER PT S AU Olsen, C Fowler, W AF Olsen, C Fowler, W BE Coffey, SL Coffey, SL Mazzoleni, AP Luu, KK Glover, RA TI Characterization of the relative motion of rendezvous between vehicles in proximate, highly elliptic orbits SO Spaceflight Mechanics 2004, Vol 119, Pt 1-3 SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT AAS/AIAA 14th Space Flight Mechanics Meeting CY FEB 08-12, 2004 CL Maui, HI SP AAS, Amer Inst Aeronaut & Astronaut AB This paper deals with rendezvous between two vehicles in highly elliptic orbits with eccentricities between 0.6 and 0.9. Due to the varying orbital speeds of the two vehicles, the relative motion during elliptic rendezvous is highly initial condition-dependent and differs significantly from the relative motion seen in circular rendezvous. Relative motion targeting and propagation procedures which output relative coordinates in a suitable curvilinear coordinate system are used. Parametric studies employing a genetic algorithm are used to span the solution spare. The resulting solutions are further limited by real world operational constraints. Typical results are presented and generalizations are drawn from the many solutions studied. C1 NASA, Marshall Spaceflight Ctr, Huntsville, AL USA. RP Olsen, C (reprint author), NASA, Marshall Spaceflight Ctr, Huntsville, AL USA. NR 29 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 0-87703-515-6 J9 ADV ASTRONAUT SCI PY 2005 VL 119 BP 879 EP 895 PN 1-3 PG 17 WC Automation & Control Systems; Engineering, Aerospace; Mechanics SC Automation & Control Systems; Engineering; Mechanics GA BBZ98 UT WOS:000228444908054 ER PT S AU Jah, MK Lisano, ME AF Jah, MK Lisano, ME BE Coffey, SL Coffey, SL Mazzoleni, AP Luu, KK Glover, RA TI 6-DOF aerobraking trajectory reconstruction by use of Inertial Measurement Unit (IMU) data for the improvement of aerobraking navigation SO Spaceflight Mechanics 2004, Vol 119, Pt 1-3 SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT AAS/AIAA 14th Space Flight Mechanics Meeting CY FEB 08-12, 2004 CL Maui, HI SP AAS, Amer Inst Aeronaut & Astronaut AB For any interplanetary mission, there are certain types of data that are used as a means of determining both the position and velocity of a spacecraft. NASA's Deep Space Network (DSN) is employed for the purpose of transmitting and receiving data to and from the spacecraft, respectively. For this exchange of information to take place, both the DSN and spacecraft antennae must be pointed towards each other. This mutual geometry is not maintained throughout aerobraking, specifically while the spacecraft is within the atmosphere. Some spacecraft are equipped with an Inertial Measurement Unit (IMU), which typically is comprised of gyroscopes and accelerometers. The IMU provides information about the spacecraft's non-conservative acceleration and angular motion. Since the spacecraft loses telemetry during the drag pass, this research focuses upon the possibility of using IMU data as a means of augmenting the current state knowledge of the spacecraft. This knowledge could also assist in obtaining best estimates for subsequent periapse times and altitudes (integral aspect of aerobraking operations). This research focuses upon the use of the IMU data (collected during the radiometric data gap) as a means of augmenting aerobraking navigation capabilities. C1 CALTECH, Jet Prop Lab, Navigat & Mission Design Sect, Pasadena, CA 91109 USA. RP Jah, MK (reprint author), CALTECH, Jet Prop Lab, Navigat & Mission Design Sect, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. OI Jah, Moriba/0000-0003-1109-0374 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 0-87703-515-6 J9 ADV ASTRONAUT SCI PY 2005 VL 119 BP 1733 EP 1752 PN 1-3 PG 20 WC Automation & Control Systems; Engineering, Aerospace; Mechanics SC Automation & Control Systems; Engineering; Mechanics GA BBZ98 UT WOS:000228444901037 ER PT S AU Wilson, RS Barden, BT Chung, MJ AF Wilson, RS Barden, BT Chung, MJ BE Coffey, SL Coffey, SL Mazzoleni, AP Luu, KK Glover, RA TI Trajectory design for the Genesis backup orbit and proposed extended mission SO Spaceflight Mechanics 2004, Vol 119, Pt 1-3 SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT AAS/AIAA 14th Space Flight Mechanics Meeting CY FEB 08-12, 2004 CL Maui, HI SP AAS, Amer Inst Aeronaut & Astronaut ID EARTH AB In September 2004, the Genesis spacecraft will return to Earth with its collection of solar wind samples. If for some reason there axe any difficulties with returning the samples to Earth during the nominal entry sequence, a contingency plan is in place for a second chance at a successful recovery. This paper will detail the processes used to generate possible backup trajectories, and provide a comparison of the contingency options examined through the course of the study. After the sample return capsule separates from the rest of the spacecraft, the remaining portion is still fully functional. It has been proposed to use this very functional spacecraft to continue to study the solar wind, albeit in a different regime than about the libration points. The remainder of the paper will discuss the design of the trajectory for this proposed extended mission. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Wilson, RS (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 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 0-87703-515-6 J9 ADV ASTRONAUT SCI PY 2005 VL 119 BP 1945 EP 1959 PN 1-3 PG 15 WC Automation & Control Systems; Engineering, Aerospace; Mechanics SC Automation & Control Systems; Engineering; Mechanics GA BBZ98 UT WOS:000228444901050 ER PT S AU Fink, DR Coyle, SE AF Fink, DR Coyle, SE BE Coffey, SL Coffey, SL Mazzoleni, AP Luu, KK Glover, RA TI WMAP shadow avoidance maneuver analysis SO Spaceflight Mechanics 2004, Vol 119, Pt 1-3 SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT AAS/AIAA 14th Space Flight Mechanics Meeting CY FEB 08-12, 2004 CL Maui, HI SP AAS, Amer Inst Aeronaut & Astronaut AB The Wilkinson Microwave Anisotropy Probe (WMAP) satellite, maintained in orbit about the Sun Earth/Moon L2, would need to avoid Earth and Moon shadows for a possible extended mission. This paper describes the method for predicting the specific probable set of shadows that would occur to WMAP were no Shadow Avoidance Maneuvers (SAM) performed, then shows how these shadows can be avoided through relatively small, appropriately timed maneuvers that adjust the phase of the Lissajous orbit geometry while minimizing impact to the mission science objectives and satisfying all spacecraft health and safety constraints. C1 Comp Sci Corp, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Fink, DR (reprint author), Comp Sci Corp, Goddard Space Flight Ctr, Bldg 3,Room S003,Mail Code 582-0, Greenbelt, MD 20771 USA. NR 3 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 0-87703-515-6 J9 ADV ASTRONAUT SCI PY 2005 VL 119 BP 1961 EP 1972 PN 1-3 PG 12 WC Automation & Control Systems; Engineering, Aerospace; Mechanics SC Automation & Control Systems; Engineering; Mechanics GA BBZ98 UT WOS:000228444901051 ER PT S AU Desai, PN Conway, BA AF Desai, PN Conway, BA BE Coffey, SL Coffey, SL Mazzoleni, AP Luu, KK Glover, RA TI A two-timescale discretization scheme for collocation SO Spaceflight Mechanics 2004, Vol 119, Pt 1-3 SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT AAS/AIAA 14th Space Flight Mechanics Meeting CY FEB 08-12, 2004 CL Maui, HI SP AAS, Amer Inst Aeronaut & Astronaut AB The development of a two-timescale discretization scheme for collocation is presented. This scheme allows a larger discretization to be utilized for smoothly varying state variables and a second finer discretization to be utilized for state variables having higher frequency dynamics. As such, the discretization scheme can be tailored to the dynamics of the particular state variables. In so doing, the size of the overall Nonlinear Programming (NLP) problem can be reduced significantly. Two two-timescale discretization architecture schemes are described. Comparison of results between the two-timescale method and conventional collocation show very good agreement. Differences of less than 0.5 percent are observed. Consequently, a significant reduction (by two-thirds) in the number of NLP parameters and iterations required for convergence can be achieved without sacrificing solution accuracy. C1 NASA, Langley Res Ctr, Aerosp Syst & Concepts Competency, Hampton, VA 23665 USA. RP Desai, PN (reprint author), NASA, Langley Res Ctr, Aerosp Syst & Concepts Competency, Hampton, VA 23665 USA. NR 4 TC 1 Z9 1 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 0-87703-515-6 J9 ADV ASTRONAUT SCI PY 2005 VL 119 BP 2053 EP 2063 PN 1-3 PG 11 WC Automation & Control Systems; Engineering, Aerospace; Mechanics SC Automation & Control Systems; Engineering; Mechanics GA BBZ98 UT WOS:000228444901056 ER PT S AU Bhaskaran, S Riedel, JE Synnott, SP AF Bhaskaran, S Riedel, JE Synnott, SP BE Coffey, SL Coffey, SL Mazzoleni, AP Luu, KK Glover, RA TI Autonomous target tracking of small bodies during flybys SO Spaceflight Mechanics 2004, Vol 119, Pt 1-3 SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT AAS/AIAA 14th Space Flight Mechanics Meeting CY FEB 08-12, 2004 CL Maui, HI SP AAS, Amer Inst Aeronaut & Astronaut AB Spacecraft flybys of small solar system bodies provide important science return in the form of images of the target body taken around closest approach. In order to maximize the number of images taken of the target, an autonomous closed-loop tracking system has been developed to maintain lock on the target during the flyby. The system uses images to estimate the spacecrafts target-relative position and attitude, which is then used to point, the camera. The system has been successfully used three times: the Deep Space I flyby of comet Borrelly and the STARDUST flybys of asteroid Annefrank and comet Wild 2. This paper describes in detail the tracking algorithms and flight results. C1 CALTECH, Jet Prop Lab, Navigat & Flight Mech Sect, Pasadena, CA 91109 USA. RP Bhaskaran, S (reprint author), CALTECH, Jet Prop Lab, Navigat & Flight Mech Sect, 4800 Oak Grove Dr,MS 264-380, Pasadena, CA 91109 USA. NR 7 TC 1 Z9 1 U1 0 U2 1 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 0-87703-515-6 J9 ADV ASTRONAUT SCI PY 2005 VL 119 BP 2079 EP 2096 PN 1-3 PG 18 WC Automation & Control Systems; Engineering, Aerospace; Mechanics SC Automation & Control Systems; Engineering; Mechanics GA BBZ98 UT WOS:000228444901058 ER PT S AU Roithmayr, CM Kay-Bunnell, L AF Roithmayr, CM Kay-Bunnell, L BE Coffey, SL Coffey, SL Mazzoleni, AP Luu, KK Glover, RA TI Keeping a spacecraft on the sun-earth line SO Spaceflight Mechanics 2004, Vol 119, Pt 1-3 SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT AAS/AIAA 14th Space Flight Mechanics Meeting CY FEB 08-12, 2004 CL Maui, HI SP AAS, Amer Inst Aeronaut & Astronaut ID ORBITS AB Measurements of Earth's atmosphere as it occults sunlight can be obtained advantageously from a spacecraft placed in the proximity of the Sun-Earth Lagrange point L2. Maintaining the condition of continuous solar occultation by all parts of the atmospheric disk requires that the displacement of the spacecraft perpendicular to the Sun-Earth line remains less than 200 km. However, the gravitational force exerted by the Earth's moon must be negated by propulsion in order to meet this rather tight constraint. We provide an estimate of propulsive force needed to keep the spacecraft coincident with L2, and a second estimate in which the spacecraft is allowed to move along the Sun-Earth line. C1 NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Roithmayr, CM (reprint author), NASA, Langley Res Ctr, 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 0-87703-515-6 J9 ADV ASTRONAUT SCI PY 2005 VL 119 BP 2249 EP 2261 PN 1-3 PG 13 WC Automation & Control Systems; Engineering, Aerospace; Mechanics SC Automation & Control Systems; Engineering; Mechanics GA BBZ98 UT WOS:000228444902004 ER PT S AU Quadrelli, MB AF Quadrelli, MB BE Coffey, SL Coffey, SL Mazzoleni, AP Luu, KK Glover, RA TI Modeling of proof mass self-gravity field for the laser interferometry space antenna (LISA) SO Spaceflight Mechanics 2004, Vol 119, Pt 1-3 SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT AAS/AIAA 14th Space Flight Mechanics Meeting CY FEB 08-12, 2004 CL Maui, HI SP AAS, Amer Inst Aeronaut & Astronaut AB This paper describes the development of the self-gravity modeling tool used to predict and control the motion of one of the proof masses of the orbiting LISA gravitational wave detector. LISA is a space-borne gravitational wave detector, which is formed by three spacecraft orbiting the Sun and forming the vertices of an equilateral triangle with a side of 5 million km in length. Requirements on the forces and moments, and the force gradients and moment gradients, applied to the proof mass exist. This paper computes these quantities analytically, so that gravitational balancing considerations can now be done effectively. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Quadrelli, MB (reprint author), CALTECH, Jet Prop Lab, MS-198-326,4800 Oak Grove Dr, Pasadena, CA 91109 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 0-87703-515-6 J9 ADV ASTRONAUT SCI PY 2005 VL 119 BP 2335 EP 2352 PN 1-3 PG 18 WC Automation & Control Systems; Engineering, Aerospace; Mechanics SC Automation & Control Systems; Engineering; Mechanics GA BBZ98 UT WOS:000228444902009 ER PT S AU Lock, RE Xaypraseuth, P Johnston, MD Halsell, CA Bowes, AL Lyons, DT You, T Highsmith, DE Jah, M AF Lock, RE Xaypraseuth, P Johnston, MD Halsell, CA Bowes, AL Lyons, DT You, T Highsmith, DE Jah, M BE Coffey, SL Coffey, SL Mazzoleni, AP Luu, KK Glover, RA TI The Mars Reconnaissance Orbiter Mission Plan SO Spaceflight Mechanics 2004, Vol 119, Pt 1-3 SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT AAS/AIAA 14th Space Flight Mechanics Meeting CY FEB 08-12, 2004 CL Maui, HI SP AAS, Amer Inst Aeronaut & Astronaut AB This paper describes the Mars Reconnaissance Orbiter Mission Plan with emphasis on major mission activities and key challenges in mission design, spacecraft design, and science data acquisition. An overview of the mission will be provided which includes: the mission objectives, a description of the orbiter and its payloads, and the basic concept of operations. Also included will be a description of the science orbit at Mars and mission data return strategies. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. RP Lock, RE (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91125 USA. OI Jah, Moriba/0000-0003-1109-0374 NR 4 TC 0 Z9 0 U1 0 U2 1 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 0-87703-515-6 J9 ADV ASTRONAUT SCI PY 2005 VL 119 BP 2629 EP 2647 PN 1-3 PG 19 WC Automation & Control Systems; Engineering, Aerospace; Mechanics SC Automation & Control Systems; Engineering; Mechanics GA BBZ98 UT WOS:000228444902026 ER PT S AU Guinn, J Ely, T AF Guinn, J Ely, T BE Coffey, SL Coffey, SL Mazzoleni, AP Luu, KK Glover, RA TI Preliminary results of Mars Exploration Rover in-situ radio navigation SO Spaceflight Mechanics 2004, Vol 119, Pt 1-3 SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT AAS/AIAA 14th Space Flight Mechanics Meeting CY FEB 08-12, 2004 CL Maui, HI SP AAS, Amer Inst Aeronaut & Astronaut ID PATHFINDER AB Preliminary results are presented from the first ever use of in-situ radio navigation measurements at Mars. NASA's two Mars Exploration Rover (MER) spacecraft carry UHF-band radios for trajectory reconstructions of atmospheric descent and surface positioning phases. Reconstructions based on in-situ Doppler measurements between each MER and either the Mars Global Surveyor or Mars Odyssey orbiters are compared with traditional Direct-To-Earth Doppler and range measurements estimates. Accuracy improvements and reduced time-to-solution are realized by using in-situ radiometric measurements. In-situ measurement processing can be extended to future mission applications such as near real-time onboard trajectory determination and pinpoint landing. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Guinn, J (reprint author), CALTECH, Jet Prop Lab, 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 0-87703-515-6 J9 ADV ASTRONAUT SCI PY 2005 VL 119 BP 2649 EP 2660 PN 1-3 PG 12 WC Automation & Control Systems; Engineering, Aerospace; Mechanics SC Automation & Control Systems; Engineering; Mechanics GA BBZ98 UT WOS:000228444902027 ER PT S AU Raiszadeh, B Queen, EM AF Raiszadeh, B Queen, EM BE Coffey, SL Coffey, SL Mazzoleni, AP Luu, KK Glover, RA TI Mars Exploration Rover terminal descent mission modeling and simulation SO Spaceflight Mechanics 2004, Vol 119, Pt 1-3 SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT AAS/AIAA 14th Space Flight Mechanics Meeting CY FEB 08-12, 2004 CL Maui, HI SP AAS, Amer Inst Aeronaut & Astronaut AB Because of NASA's added reliance on simulation for successful interplanetary missions, the MER mission has developed a detailed EDL trajectory modeling and simulation. This paper summarizes how the MER EDL sequence of events are modeled, verification of the methods used, and the inputs. This simulation is built upon a multibody parachute trajectory simulation tool that has been developed in POST II that accurately simulates the trajectory of multiple vehicles in flight with interacting forces. In this model the parachute and the suspended bodies are treated as 6 Degree-of-Freedom (6 DOF) bodies. The terminal descent phase of the mission consists of several Entry, Descent, Landing (EDL) events, such as parachute deployment, heatshield separation, deployment of the lander from the backshell, deployment of the airbags, RAD firings, TIRS firings, etc. For an accurate, reliable simulation these events need to be modeled seemlessly and robustly so that the simulations will remain numerically stable during Monte-Carlo simulations. This paper also summarizes how the events have been modeled, the numerical issues, and modeling challenges. C1 NASA, Langley Res Ctr, Hampton, VA 23665 USA. RP Raiszadeh, B (reprint author), NASA, Langley Res Ctr, Hampton, VA 23665 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 0-87703-515-6 J9 ADV ASTRONAUT SCI PY 2005 VL 119 BP 2661 EP 2676 PN 1-3 PG 16 WC Automation & Control Systems; Engineering, Aerospace; Mechanics SC Automation & Control Systems; Engineering; Mechanics GA BBZ98 UT WOS:000228444902028 ER PT S AU Wolf, AA Graves, C Powell, R Johnson, W AF Wolf, AA Graves, C Powell, R Johnson, W BE Coffey, SL Coffey, SL Mazzoleni, AP Luu, KK Glover, RA TI Systems for pinpoint landing at Mars SO Spaceflight Mechanics 2004, Vol 119, Pt 1-3 SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT AAS/AIAA 14th Space Flight Mechanics Meeting CY FEB 08-12, 2004 CL Maui, HI SP AAS, Amer Inst Aeronaut & Astronaut AB Mars landers have been able to land only within tens to hundreds of km of a target site due to uncertainties in approach navigation, atmospheric modeling, and vehicle aerodynamics; as well as due to map-tie error and wind drift. The Mars Science Laboratory mission will improve this to 5 - 10 km using optical navigation and entry guidance. To achieve "pinpoint landing" (within 100m) for future missions, ways of addressing the remaining error sources (approach navigation, wind drift and map-tie error) must be found. This work analyzes performance and cost trades for pinpoint landing systems, identifying the most promising areas for technology investment. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Wolf, AA (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. NR 13 TC 13 Z9 13 U1 0 U2 3 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 0-87703-515-6 J9 ADV ASTRONAUT SCI PY 2005 VL 119 BP 2677 EP 2696 PN 1-3 PG 20 WC Automation & Control Systems; Engineering, Aerospace; Mechanics SC Automation & Control Systems; Engineering; Mechanics GA BBZ98 UT WOS:000228444902029 ER PT S AU Neelon, J Wallace, M Craig, L AF Neelon, J Wallace, M Craig, L BE Coffey, SL Coffey, SL Mazzoleni, AP Luu, KK Glover, RA TI Coordination of Mars orbiting assets to support entry, descent, & landing (EDL) activities SO Spaceflight Mechanics 2004, Vol 119, Pt 1-3 SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT AAS/AIAA 14th Space Flight Mechanics Meeting CY FEB 08-12, 2004 CL Maui, HI SP AAS, Amer Inst Aeronaut & Astronaut AB NASA policy requires continuous telemetry with missions during the execution of their critical events, which implies constraints on where missions to other planets may land or inject into orbit. JPL is working to establish a telecommunications network at Mars to provide contact with inbound missions to Mars and assets that have landed on the Martian surface, thus reducing the constraints on where critical events may be performed. Coordination of network assets is required to cover an inbound mission's critical event, such as EDL. This paper describes the development of a tool to evaluate EDL coverage capability of Mars network assets over a specified launch date/arrival date space. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Neelon, J (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. NR 3 TC 0 Z9 0 U1 0 U2 1 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 0-87703-515-6 J9 ADV ASTRONAUT SCI PY 2005 VL 119 BP 2697 EP 2716 PN 1-3 PG 20 WC Automation & Control Systems; Engineering, Aerospace; Mechanics SC Automation & Control Systems; Engineering; Mechanics GA BBZ98 UT WOS:000228444902030 ER PT S AU Sarani, SS AF Sarani, SS BE Coffey, SL Coffey, SL Mazzoleni, AP Luu, KK Glover, RA TI Assessment of per-axis thruster control authority of Cassini spacecraft for low-altitude Titan flybys SO Spaceflight Mechanics 2004, Vol 119, Pt 1-3 SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT AAS/AIAA 14th Space Flight Mechanics Meeting CY FEB 08-12, 2004 CL Maui, HI SP AAS, Amer Inst Aeronaut & Astronaut AB Upon arrival at Saturn, Cassini will execute numerous low-attitude flybys of Titan and a few targeted icy satellite flybys. At the closest approach altitudes, the spacecraft must use its thrusters in order to overcome the external torques, maintain attitude control, and perform the required science stews. Because of the uncertainties associated with Titan atmospheric density model, as well as other uncertainties, the adequacy of thruster control authority at the closest approach must carefully be assessed to ensure that Cassini will not tumble out of control. The results indicate that even with conservative assumptions, there still exists adequate control authority margin. C1 CALTECH, Jet Prop Lab, Avion Syst Engn Sect, Pasadena, CA 91109 USA. RP Sarani, SS (reprint author), CALTECH, Jet Prop Lab, Avion Syst Engn Sect, 4800 Oak Grove Dr,Mail Stop 104D, Pasadena, CA 91109 USA. NR 17 TC 0 Z9 0 U1 0 U2 1 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 0-87703-515-6 J9 ADV ASTRONAUT SCI PY 2005 VL 119 BP 2743 EP 2766 PN 1-3 PG 24 WC Automation & Control Systems; Engineering, Aerospace; Mechanics SC Automation & Control Systems; Engineering; Mechanics GA BBZ98 UT WOS:000228444902032 ER PT S AU Quadrelli, MB Chang, J Kowalchuck, S AF Quadrelli, MB Chang, J Kowalchuck, S BE Coffey, SL Coffey, SL Mazzoleni, AP Luu, KK Glover, RA TI Dynamics and control of a herd of sondes guided by a blimp on Titan SO Spaceflight Mechanics 2004, Vol 119, Pt 1-3 SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT AAS/AIAA 14th Space Flight Mechanics Meeting CY FEB 08-12, 2004 CL Maui, HI SP AAS, Amer Inst Aeronaut & Astronaut ID ROBOTS AB This paper describes the model and the algorithm developed for an aerobot blimp guiding and controlling a herd of sondes on the surface of Titan. The paper summarizes the derivation of the equations of motion used in simulations, and the features of the simulation model. A potential field controller is used for autonomous guidance and navigation around terrain features on the surface, and hazard avoidance. The results of simulation studies demonstrate that the method used for control is feasible even if significant uncertainty exists in the dynamics and environmental models, and that the control method provides the autonomy needed to enable surface science data collection. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Quadrelli, MB (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,Mail Stop 198-326, Pasadena, CA 91109 USA. NR 7 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 0-87703-515-6 J9 ADV ASTRONAUT SCI PY 2005 VL 119 BP 2767 EP 2788 PN 1-3 PG 22 WC Automation & Control Systems; Engineering, Aerospace; Mechanics SC Automation & Control Systems; Engineering; Mechanics GA BBZ98 UT WOS:000228444902033 ER PT S AU Ellis, J Lisano, M Wolff, P Evans, J Bladt, J Scheeres, D Rios-Reyes, L Lawrence, D AF Ellis, J Lisano, M Wolff, P Evans, J Bladt, J Scheeres, D Rios-Reyes, L Lawrence, D BE Coffey, SL Coffey, SL Mazzoleni, AP Luu, KK Glover, RA TI A solar sail integrated simulation toolkit SO Spaceflight Mechanics 2004, Vol 119, Pt 1-3 SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT AAS/AIAA 14th Space Flight Mechanics Meeting CY FEB 08-12, 2004 CL Maui, HI SP AAS, Amer Inst Aeronaut & Astronaut AB This paper describes an integrated set of high fidelity software tools that are being developed for the design of solar sail missions and analysis of the guidance, navigation and control (GNC) of these missions. This integrated set of simulation tools will be able to predict, re-calibrate and optimize the trajectory, maneuvers and propulsive performance of a sail during a representative flight mission. This tool has capabilities for mission design and for simulation of the sail attitude determination and control, navigation based on ground based and on board tracking, feedback control performance evaluation, parameter estimation and covariance analysis and analysis of attitude control systems. It is capable of evaluating the sail performance accounting for structural dynamic effects, billowing, bending and material degradation effects.. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91107 USA. RP Ellis, J (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91107 USA. NR 7 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 0-87703-515-6 J9 ADV ASTRONAUT SCI PY 2005 VL 119 BP 2875 EP 2891 PN 1-3 PG 17 WC Automation & Control Systems; Engineering, Aerospace; Mechanics SC Automation & Control Systems; Engineering; Mechanics GA BBZ98 UT WOS:000228444902039 ER PT S AU Lo, MW Anderson, RL Whiffen, G Romans, L AF Lo, MW Anderson, RL Whiffen, G Romans, L BE Coffey, SL Coffey, SL Mazzoleni, AP Luu, KK Glover, RA TI The role of invariant manifolds in low thrust trajectory design SO Spaceflight Mechanics 2004, Vol 119, Pt 1-3 SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT AAS/AIAA 14th Space Flight Mechanics Meeting CY FEB 08-12, 2004 CL Maui, HI SP AAS, Amer Inst Aeronaut & Astronaut ID HETEROCLINIC CONNECTIONS; PERIODIC-ORBITS; RESONANCE; COMETS; SYSTEMS; CAPTURE AB An initial study of techniques to be used in understanding how invariant manifolds are involved in low thrust trajectory design for the Jovian moon missions was performed using a baseline trajectory from the Europa Orbiter (EO) studies. Poincare sections were used in order to search for unstable resonant orbits. The unstable manifolds of these resonant orbits were computed, and they were found to provide an indication of how the EO trajectory was able to transition between resonances. A comparison with the stable and unstable manifolds of Lissajous orbits around the Jupiter-Europa L-2 Lagrange point provided evidence that the Europa capture utilizes invariant manifolds of quasi-periodic orbits. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Lo, MW (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. OI Anderson, Rodney/0000-0001-5336-2775 NR 18 TC 0 Z9 0 U1 0 U2 2 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 0-87703-515-6 J9 ADV ASTRONAUT SCI PY 2005 VL 119 BP 2971 EP 2989 PN 1-3 PG 19 WC Automation & Control Systems; Engineering, Aerospace; Mechanics SC Automation & Control Systems; Engineering; Mechanics GA BBZ98 UT WOS:000228444902044 ER PT S AU Lam, T Whiffen, GJ AF Lam, T Whiffen, GJ BE Vallado, DA Gabor, MJ Desai, PN TI Exploration of Distant Retrograde Orbits around Europa SO Spaceflight Mechanics 2005, Vol 120, Pts 1 and 2 SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT AAS/AIAA 15th Space Flight Mechanics Meeting CY JAN 23-27, 2005 CL Copper Mt, CO SP AAS, AIAA ID PLANE RESTRICTED PROBLEM; PERIODIC ORBITS; MASS RATIO; NUMERICAL EXPLORATION; VERTICAL STABILITY; SATELLITES; EXISTENCE AB This paper explores the applications of Distant Retrograde Orbits (DROs) around Europa, a class of orbit which can be stable for a very long time. These orbits exist due to a larger perturbation from Jupiter, and are of particular interest due to proposed missions such as NASA's Jupiter Icy Moon Orbiter (JIMO). Preliminary investigation has found DROs to be ideal quarantine orbits due to their long-term stability and their existence at a large range of distances away from Europa. The paper also demonstrates that continuous families of DROs provide instantaneously stable transfer paths for both escape and capture around Europa. C1 CALTECH, Jet Prop Lab, Small Body Flight Dynam Sect, Pasadena, CA 91109 USA. RP Lam, T (reprint author), CALTECH, Jet Prop Lab, Small Body Flight Dynam Sect, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 18 TC 5 Z9 5 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 0-87703-520-2 J9 ADV ASTRONAUT SCI PY 2005 VL 120 BP 135 EP 153 PN 1-2 PG 19 WC Engineering, Aerospace SC Engineering GA BCU60 UT WOS:000231281700009 ER PT S AU Parcher, DW Sims, JA AF Parcher, DW Sims, JA BE Vallado, DA Gabor, MJ Desai, PN TI Venus and Mars gravity-assist trajectories to Jupiter using nuclear electric propulsion SO Spaceflight Mechanics 2005, Vol 120, Pts 1 and 2 SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT AAS/AIAA 15th Space Flight Mechanics Meeting CY JAN 23-27, 2005 CL Copper Mt, CO SP AAS, AIAA ID MISSIONS AB Optimal low-thrust gravity-assist trajectories to Jupiter using nuclear electric propulsion are presented. Venus, double Venus, and Mars gravity-assist cases are examined. For each of these cases, two locally optimal trajectory families, differentiated by number of heliocentric revolutions, are considered. The solutions that use fewer heliocentric revolutions perform better at short flight times, but do not perform as well at long flight times. Of the gravity-assist types examined, the Mars gravity-assist offers the most delivered mass to Jupiter for most flight times. C1 CALTECH, Jet Prop Lab, Outer Planet Small Body Flight Dynam Sect, Pasadena, CA 91109 USA. RP Parcher, DW (reprint author), CALTECH, Jet Prop Lab, Outer Planet Small Body Flight Dynam Sect, Mail Stop 301-1401,1800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 9 TC 0 Z9 1 U1 0 U2 1 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 0-87703-520-2 J9 ADV ASTRONAUT SCI PY 2005 VL 120 BP 169 EP 184 PN 1-2 PG 16 WC Engineering, Aerospace SC Engineering GA BCU60 UT WOS:000231281700011 ER PT S AU Roundhill, IM Antreasian, PG Criddle, KE Ionasescu, R Meek, MC Stauch, JR AF Roundhill, IM Antreasian, PG Criddle, KE Ionasescu, R Meek, MC Stauch, JR BE Vallado, DA Gabor, MJ Desai, PN TI Orbit determination results for the Cassini Titan-a flyby SO Spaceflight Mechanics 2005, Vol 120, Pts 1 and 2 SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT AAS/AIAA 15th Space Flight Mechanics Meeting CY JAN 23-27, 2005 CL Copper Mt, CO SP AAS, AIAA AB This paper describes Cassini orbit determination results from the first targeted flyby of Titan. The orbit determination model is outlined including the radiometric and optical data and the parameter estimation for the Cassini, Saturn, and satellite trajectories. The solutions computed to support maneuver decision points are described along with alternate solution used to gain confidence in the baseline strategy. Finally, the reconstructed flyby conditions are compared to the prediction to reveal a Titan ephemeris error. The optical data model is then examined to reveal why this error was not observable. C1 CALTECH, Jet Prop Lab, Outer Planet Flight Dynam, Pasadena, CA 91109 USA. RP Roundhill, IM (reprint author), CALTECH, Jet Prop Lab, Outer Planet Flight Dynam, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 0 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 0-87703-520-2 J9 ADV ASTRONAUT SCI PY 2005 VL 120 BP 185 EP 202 PN 1-2 PG 18 WC Engineering, Aerospace SC Engineering GA BCU60 UT WOS:000231281700012 ER PT S AU Quadrelli, MB Mettler, E Langmaier, JK Gromov, K AF Quadrelli, MB Mettler, E Langmaier, JK Gromov, K BE Vallado, DA Gabor, MJ Desai, PN TI Thrust vector control of the Jupiter Icy Moons Orbiter spacecraft SO Spaceflight Mechanics 2005, Vol 120, Pts 1 and 2 SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT AAS/AIAA 15th Space Flight Mechanics Meeting CY JAN 23-27, 2005 CL Copper Mt, CO SP AAS, AIAA AB In NASA's proposed Jupiter Icy Moons Orbiter mission's baseline spacecraft, attitude and orbital dynamics interactions are present due to the designed low-thrust trajectory. In order to investigate this coupling, which originates due to the thrust vectoring control, sensitivity analyses and simulation studies were carried out using complex orbital and attitude dynamics models describing the vehicle's dynamics arising during the low-thrust spiraling maneuvers of the spacecraft. The results of these studies point out that a new approach is needed to integrate the trajectory design and the attitude control. C1 CALTECH, Jet Prop Lab, Guidance & Control Anal Grp, Pasadena, CA 91109 USA. RP Quadrelli, MB (reprint author), CALTECH, Jet Prop Lab, Guidance & Control Anal Grp, Mail Stop 198-326,4800 Oak Grove Dr, Pasadena, CA 91109 USA. RI Langmaier, Jan/F-5150-2014 OI Langmaier, Jan/0000-0003-0251-8463 NR 3 TC 0 Z9 0 U1 0 U2 2 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 0-87703-520-2 J9 ADV ASTRONAUT SCI PY 2005 VL 120 BP 203 EP 228 PN 1-2 PG 26 WC Engineering, Aerospace SC Engineering GA BCU60 UT WOS:000231281700013 ER PT S AU Quadrelli, MB AF Quadrelli, MB BE Vallado, DA Gabor, MJ Desai, PN TI A novel approach to planetary precision landing using parafoils SO Spaceflight Mechanics 2005, Vol 120, Pts 1 and 2 SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT AAS/AIAA 15th Space Flight Mechanics Meeting CY JAN 23-27, 2005 CL Copper Mt, CO SP AAS, AIAA AB In this paper, we address the problem of how to achieve precision landing, in an autonomous manner, through an actively controlled parafoil. By precision landing we mean the capability of steering the vehicle to a pre-specified target area on the ground. The mechanization to achieve this maneuverability is provided by a parafoil, i.e. a high glide parachute characterized by airfoil type canopy cross-sections and wing type plan forms, which can actively be steered to control the trajectory. The preliminary results obtained so far indicate that precision control of these types of vehicles can be achieved provided enough control authority, and enough knowledge of the atmospheric parameters (density, wind magnitude and direction) are available. C1 CALTECH, Jet Prop Lab, Guidance & Control Anal Grp, Pasadena, CA 91109 USA. RP Quadrelli, MB (reprint author), CALTECH, Jet Prop Lab, Guidance & Control Anal Grp, Mail Stop 198-326,4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 8 TC 0 Z9 0 U1 0 U2 1 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 0-87703-520-2 J9 ADV ASTRONAUT SCI PY 2005 VL 120 BP 229 EP 245 PN 1-2 PG 17 WC Engineering, Aerospace SC Engineering GA BCU60 UT WOS:000231281700014 ER PT S AU Wawrzyniak, G Han, D Lewis, G Graat, E Baird, D Craig, D AF Wawrzyniak, G Han, D Lewis, G Graat, E Baird, D Craig, D BE Vallado, DA Gabor, MJ Desai, PN TI Genesis orbit determination for Earth return and atmospheric entry SO Spaceflight Mechanics 2005, Vol 120, Pts 1 and 2 SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT AAS/AIAA 15th Space Flight Mechanics Meeting CY JAN 23-27, 2005 CL Copper Mt, CO SP AAS, AIAA AB After collecting solar-wind samples for more than two years while orbiting the Sun-Earth Libration point (L1), the Genesis spacecraft closed it collection apparatus at the beginning of April 2004. Following a five-month cruise from L1, to the opposite side of the Earth (L2), and then back to Earth, the Genesis spacecraft released its Sample Return Capsule (SRC) containing the science samples on September 8, 2004. The Genesis return to Earth was the first such event since the days of Apollo, and the first ever unmanned sample return from a Lissajous/Lagrange Point orbit to an Earth touchdown. The navigation infrastructure used for this return is significantly better than what was available in the Apollo era, both in terms of measurement quality and in terms of computing resources. Nevertheless, there were new challenges that the navigation team had to address. The final location of the landed SRC, which was well within the allowed recovery area in the Utah Test and Training Range, showed that the operation of the Genesis spacecraft, including the navigation, leading up to the SRC's atmospheric entry was successful, and the navigation was accurate. This not only met navigation requirements, but enabled Earth-based tracking assets to easily observe the returning spacecraft days before it was anticipated, which did much to relieve concerns about this first-time event. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Wawrzyniak, G (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 7 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 0-87703-520-2 J9 ADV ASTRONAUT SCI PY 2005 VL 120 BP 269 EP 282 PN 1-2 PG 14 WC Engineering, Aerospace SC Engineering GA BCU60 UT WOS:000231281700016 ER PT S AU Desai, PN Lyons, DT AF Desai, PN Lyons, DT BE Vallado, DA Gabor, MJ Desai, PN TI Entry, descent, and landing operations analysis for the Genesis re-entry capsule SO Spaceflight Mechanics 2005, Vol 120, Pts 1 and 2 SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT AAS/AIAA 15th Space Flight Mechanics Meeting CY JAN 23-27, 2005 CL Copper Mt, CO SP AAS, AIAA AB On September 8, 2004, the Genesis spacecraft retuned to Earth after spending 29 months about the sun-Earth libration point collecting solar wind particles. Four hours prior to Earth arrival, the entry capsule containing the samples was released for entry and subsequent landing at the Utah Test and Training Range. This paper provides an overview of the entry, descent, and landing trajectory analysis that was performed during the Mission Operations Phase leading up to final approach to Earth. The operations effort accurately delivered the entry capsule to the desired landing site. The final landing location was 8.3 km from the target, and was well within the allowable landing area. Preliminary reconstruction analyses indicate that the actual entry trajectory was very close to the pre-entry prediction. C1 NASA, Langley Res Ctr, Hampon, VA 23681 USA. RP Desai, PN (reprint author), NASA, Langley Res Ctr, Hampon, VA 23681 USA. NR 8 TC 0 Z9 0 U1 0 U2 1 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 0-87703-520-2 J9 ADV ASTRONAUT SCI PY 2005 VL 120 BP 283 EP 295 PN 1-2 PG 13 WC Engineering, Aerospace SC Engineering GA BCU60 UT WOS:000231281700017 ER PT S AU Cangahuala, LA AF Cangahuala, LA BE Vallado, DA Gabor, MJ Desai, PN TI Augmentations to the polyhedral gravity model to facilitate small body navigation SO Spaceflight Mechanics 2005, Vol 120, Pts 1 and 2 SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT AAS/AIAA 15th Space Flight Mechanics Meeting CY JAN 23-27, 2005 CL Copper Mt, CO SP AAS, AIAA ID OPTIMUM EXPRESSION; COMPUTATION; FIELD AB One of the challenges in modeling low-altitude mission scenarios at small bodies is the need to minimize the computation time penalty for more detailed shape models, especially when the scale of the detail is on the order of the spacecraft trajectory. This paper describes variants of the polyhedral model and their relative performance. Variations include (a) using approximations to the more computationally intensive terms in the acceleration and partial calculations, (b) using approximations for sums of terms that are disproportionately detailed, and (c) simply using a simpler reference polyhedron. Accuracy and speed performance assessments are made for these variations for three cases: (a) an aggressive mapping orbit, (b) low altitude hovering, and (c) disturbances of regolith material at the surface of an asteroid. Analogous results are also shown for spherical harmonics and a three-axis ellipsoid. The results show that the benefits to using Taylor series approximations and carrying the history of calculations from a previous call to a nearby point can range from 30 to 60 percent for each augmentation. The accuracy penalty for these augmentations is smaller than the uncertainties in the gravity field itself, so they warrant being included in gravity model software sets. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Cangahuala, LA (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 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 0-87703-520-2 J9 ADV ASTRONAUT SCI PY 2005 VL 120 BP 685 EP 698 PN 1-2 PG 14 WC Engineering, Aerospace SC Engineering GA BCU60 UT WOS:000231281700039 ER PT S AU Hughes, SP Cooley, DS Guzman, JJ AF Hughes, SP Cooley, DS Guzman, JJ BE Vallado, DA Gabor, MJ Desai, PN TI A direct method for fuel optimal-maneuvers of distributed spacecraft in multiple flight regimes SO Spaceflight Mechanics 2005, Vol 120, Pts 1 and 2 SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT AAS/AIAA 15th Space Flight Mechanics Meeting CY JAN 23-27, 2005 CL Copper Mt, CO SP AAS, AIAA AB We present a method to solve the impulsive minimum fuel maneuver problem for a distributed set of spacecraft. We develop the method assuming a non-linear dynamics model and parameterize the problem to allow the method to be applicable to multiple flight regimes including low-Earth orbits, highly-elliptic orbits (HEO), Lagrange point orbits, and interplanetary trajectories. Furthermore, the approach is not limited by the inter-spacecraft separation distances and is applicable to both small formations as well as large constellations. Semianalytical derivatives are derived for the changes in the total AV with respect to changes in the independent variables. We also apply a set of constraints to ensure that the fuel expenditure is equalized over the spacecraft in formation. We conclude with several examples and present optimal maneuver sequences for both a HEO and libration point formation. C1 NASA, Goddard Space Flight Ctr, Flight Dynam Anal Branch, Greenbelt, MD 20771 USA. RP Hughes, SP (reprint author), NASA, Goddard Space Flight Ctr, Flight Dynam Anal Branch, Greenbelt, MD 20771 USA. NR 10 TC 2 Z9 2 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 0-87703-520-2 J9 ADV ASTRONAUT SCI PY 2005 VL 120 BP 869 EP 897 PN 1-2 PG 29 WC Engineering, Aerospace SC Engineering GA BCU60 UT WOS:000231281700051 ER PT S AU Quadrelli, MB AF Quadrelli, MB BE Vallado, DA Gabor, MJ Desai, PN TI Dynamic stability and gravitational balancing of multiple extended bodies SO Spaceflight Mechanics 2005, Vol 120, Pts 1 and 2 SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT AAS/AIAA 15th Space Flight Mechanics Meeting CY JAN 23-27, 2005 CL Copper Mt, CO SP AAS, AIAA ID DRAG-FREE SATELLITES AB This paper considers a non-invasive compensation scheme for precise positioning of a massive extended body in free fall using gravitational forces caused by surrounding source masses in close proximity. The stability characteristics of the linearized forced N-body problem are examined. A set of feedback plus feed-forward control schemes are also considered as possible control laws for the nonlinear forced N-body problem, and demonstrate effective control of a proof mass sensitive to gravitational waves within the specified requirements. C1 CALTECH, Jet Prop Lab, Guidance & Control Anal Grp, Pasadena, CA 91109 USA. RP Quadrelli, MB (reprint author), CALTECH, Jet Prop Lab, Guidance & Control Anal Grp, 4800 Oak Grove Dr,Mail Stop 198-326, Pasadena, CA 91109 USA. NR 14 TC 0 Z9 0 U1 0 U2 4 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 0-87703-520-2 J9 ADV ASTRONAUT SCI PY 2005 VL 120 BP 1399 EP 1419 PN 1-2 PG 21 WC Engineering, Aerospace SC Engineering GA BCU60 UT WOS:000231281700079 ER PT S AU Highsmith, D You, TH Halsell, A Jah, M Long, S Demcak, S Higa, E AF Highsmith, D You, TH Halsell, A Jah, M Long, S Demcak, S Higa, E BE Vallado, DA Gabor, MJ Desai, PN TI Atmosphere variability at Mars Reconnaissance Orbiter science orbit altitudes based on Mars Express reconstructions SO Spaceflight Mechanics 2005, Vol 120, Pts 1 and 2 SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT AAS/AIAA 15th Space Flight Mechanics Meeting CY JAN 23-27, 2005 CL Copper Mt, CO SP AAS, AIAA AB This paper describes the orbit reconstruction of Mars Express (MEX) with the specific goal of estimating the atmospheric density near periapsis and evaluating its variability and predictability. The desired outcome is to validate the covariance analysis assumption of atmospheric variability for the 2005 NASA Mars Reconnaissance Orbiter (MRO), as well as evaluate the accuracy of the density estimates output from the atmosphere model used by MRO. Topics covered include the MRO atmosphere model, MEX orbit determination and post-fit Doppler residuals, and atmosphere trending statistics gleaned from the orbit reconstructions. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. RP Highsmith, D (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. OI Jah, Moriba/0000-0003-1109-0374 NR 4 TC 0 Z9 0 U1 0 U2 1 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 0-87703-520-2 J9 ADV ASTRONAUT SCI PY 2005 VL 120 BP 1767 EP 1785 PN 1-2 PG 19 WC Engineering, Aerospace SC Engineering GA BCU60 UT WOS:000231281700100 ER PT S AU Prince, JLH Striepe, SA AF Prince, JLH Striepe, SA BE Vallado, DA Gabor, MJ Desai, PN TI NASA Langley trajectory simulation and analysis capabilities for Mars Reconnaissance Orbiter SO Spaceflight Mechanics 2005, Vol 120, Pts 1 and 2 SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT AAS/AIAA 15th Space Flight Mechanics Meeting CY JAN 23-27, 2005 CL Copper Mt, CO SP AAS, AIAA AB Mars Reconnaissance Orbiter will launch in August 2005 and will achieve Mars Orbit Insertion in March of 2006. It will then take approximately six months to use the process of aerobraking to shape its orbit into the desired science mapping orbit. This six-month period is arguably the phase of the Mars Reconnaissance Orbiter mission with the highest risk to the spacecraft, dipping to within 100 kin of the planet. This process requires enough atmospheric drag to slow the spacecraft and circularize the orbit while remaining high enough in the Mars atmosphere as to not risk thermal degradation of spacecraft components. This paper will discuss the trajectory simulation and several analyses performed at NASA Langley Research Center to support a successful aerobraking phase of the Mars Reconnaissance Orbiter mission. C1 NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Prince, JLH (reprint author), NASA, Langley Res Ctr, MS 365, Hampton, VA 23681 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 0-87703-520-2 J9 ADV ASTRONAUT SCI PY 2005 VL 120 BP 1807 EP 1822 PN 1-2 PG 16 WC Engineering, Aerospace SC Engineering GA BCU60 UT WOS:000231281700102 ER PT S AU Lisano, M Lawrence, D Piggott, S AF Lisano, M Lawrence, D Piggott, S BE Vallado, DA Gabor, MJ Desai, PN TI Solar sail transfer trajectory design and stationkeeping control for missions to the sub-L1 equilibrium region SO Spaceflight Mechanics 2005, Vol 120, Pts 1 and 2 SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT AAS/AIAA 15th Space Flight Mechanics Meeting CY JAN 23-27, 2005 CL Copper Mt, CO SP AAS, AIAA AB The design of solar sail trajectories is treated, along with the associated thrust vector control history that transfers a solar-sail-propelled spacecraft, or sailcraft, from the Earth/Sun L1 libration point to a sub-L1 region nearer the Sun. A novel combination of trajectory design and optimization, and new sailcraft trajectory control methods are employed to produce minimum time transfers and robust trajectory tracking and stationkeeping. First, a trajectory to the sub-L1 region is targeted, where solar pressure and gravitational forces approximately balance. The nominal thrust vector control sequence that produces minimum final target state error for a given time of flight is generated using a first-order gradient-search optimization tool. Then, feedback control is applied to reduce trajectory-tracking errors along the transfer trajectory and to stabilize the (normally unstable) motion in the sub-L1 region, attracting and maintaining the spacecraft on a stationkeeping orbit. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91107 USA. RP Lisano, M (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91107 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 0-87703-520-2 J9 ADV ASTRONAUT SCI PY 2005 VL 120 BP 1837 EP 1854 PN 1-2 PG 18 WC Engineering, Aerospace SC Engineering GA BCU60 UT WOS:000231281700104 ER PT S AU Wawrzyniak, GG Wahl, TE AF Wawrzyniak, GG Wahl, TE BE Vallado, DA Gabor, MJ Desai, PN TI Human safety analysis for the Genesis Sample Return Mission SO Spaceflight Mechanics 2005, Vol 120, Pts 1 and 2 SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT AAS/AIAA 15th Space Flight Mechanics Meeting CY JAN 23-27, 2005 CL Copper Mt, CO SP AAS, AIAA AB In order for the Sample Return Capsule from the Genesis spacecraft to return to Earth, it had to be determined that the casualty risk of the capsule's return would be minimal. Under stringent NASA and USAF requirements, JPL engineers developed a statistical analysis of the collective and individual casualty risks based on a regional population survey and Gaussian landing distributions. Additionally, other assessments of property damage and unacceptable zones were studied. These analyses were updated through the final hours of the mission as the navigation team produced new assessments of the landing distributions based on updated orbit determination solutions and maneuver designs. This analysis showed that the capsule was targeted to a region of minimal casualty risk: northeastern Nevada prior to the capsule release sequence and the Utah Test and Training range in northwestern Utah before the final maneuver and after the capsule-release sequence. Had this analysis not been performed, NASA would not have allowed the capsule to return. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Wawrzyniak, GG (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,MS 264-370, 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 0-87703-520-2 J9 ADV ASTRONAUT SCI PY 2005 VL 120 BP 1905 EP 1922 PN 1-2 PG 18 WC Engineering, Aerospace SC Engineering GA BCU60 UT WOS:000231281700107 ER PT S AU Mendeck, GF Kadwa, B AF Mendeck, GF Kadwa, B BE Vallado, DA Gabor, MJ Desai, PN TI Public risk assessment of off-nominal Genesis entries SO Spaceflight Mechanics 2005, Vol 120, Pts 1 and 2 SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT AAS/AIAA 15th Space Flight Mechanics Meeting CY JAN 23-27, 2005 CL Copper Mt, CO SP AAS, AIAA AB Public risk estimations were among the preparations for the entry of the Genesis sample return capsule. Personnel at the Johnson Space Center were requested to provide estimates of the public risk of off-nominal entries, These scenarios dealt with an incomplete trajectory maneuver that would result in the capsule landing outside of the controlled Utah Test and Training Range. Using a conservative approach to the inputs and assumptions, such off-nominal entries were demonstrated to fall within the project risk limits. C1 NASA, Flight Design & Dynam Div, Johnson Space Ctr, Houston, TX 77058 USA. RP Mendeck, GF (reprint author), NASA, Flight Design & Dynam Div, Johnson Space Ctr, Houston, TX 77058 USA. NR 6 TC 1 Z9 1 U1 0 U2 0 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 0-87703-520-2 J9 ADV ASTRONAUT SCI PY 2005 VL 120 BP 1923 EP 1938 PN 1-2 PG 16 WC Engineering, Aerospace SC Engineering GA BCU60 UT WOS:000231281700108 ER PT S AU Haw, R Wilson, M Wilson, R Williams, K AF Haw, R Wilson, M Wilson, R Williams, K BE Vallado, DA Gabor, MJ Desai, PN TI Genesis backup orbit contingency analysis SO Spaceflight Mechanics 2005, Vol 120, Pts 1 and 2 SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT AAS/AIAA 15th Space Flight Mechanics Meeting CY JAN 23-27, 2005 CL Copper Mt, CO SP AAS, AIAA AB The Genesis spacecraft returned its sample return capsule to Earth on Sept 8, 2004. Before releasing the capsule however, the spacecraft was uniquely positioned to be able to offer an alternate, backup return-strategy (subsequent to the first attempt) should the initial sequence of events be unsatisfactory in establishing the requisite conditions for the capsule's release. So as part of the preparation for the capsule's return, Genesis planners also designed a delayed, six month Earth-return trajectory as a contingent strategy in case of a possible capsule-release abort. The contingent-return option existed because Genesis, in returning from the Sun-Earth L, Lagrange point, did not follow a hyperbolic trajectory with respect to Earth. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Haw, R (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 7 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 0-87703-520-2 J9 ADV ASTRONAUT SCI PY 2005 VL 120 BP 1939 EP 1948 PN 1-2 PG 10 WC Engineering, Aerospace SC Engineering GA BCU60 UT WOS:000231281700109 ER PT S AU Wilson, RS AF Wilson, RS BE Vallado, DA Gabor, MJ Desai, PN TI Genesis extended mission trajectory design SO Spaceflight Mechanics 2005, Vol 120, Pts 1 and 2 SE ADVANCES IN THE ASTRONAUTICAL SCIENCES LA English DT Proceedings Paper CT AAS/AIAA 15th Space Flight Mechanics Meeting CY JAN 23-27, 2005 CL Copper Mt, CO SP AAS, AIAA AB As the fifth Discovery mission, the Genesis spacecraft was launched on August 8, 2001 with a science objective to collect solar wind samples for a period of approximately two and a half years while in orbit in the vicinity of the Sun-Earth L1 libration point. On September 8, 2004, the Genesis sample return capsule returned to Earth with its collection of solar wind samples. Although the capsule did not get captured in the intended manner, from a mission design and navigation perspective the mission was a complete success. Now that the samples have been delivered, the remaining portion of the spacecraft is still fully functional, and has a generous amount of maneuver capability remaining. Various proposals for how to use this very functional and proven spacecraft have been suggested, for instance, continuing to study the solar wind using the on-board instrumentation in a libration point orbit. This paper will discuss the design of the various trajectory options for some of these proposed extended missions. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Wilson, RS (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 12 TC 0 Z9 0 U1 0 U2 1 PU UNIVELT INC PI SAN DIEGO PA PO BOX 28130, SAN DIEGO, CA 92128 USA SN 1081-6003 BN 0-87703-520-2 J9 ADV ASTRONAUT SCI PY 2005 VL 120 BP 1949 EP 1961 PN 1-2 PG 13 WC Engineering, Aerospace SC Engineering GA BCU60 UT WOS:000231281700110 ER PT S AU Dwek, E AF Dwek, E BE Popescu, CC Tuffs, RJ TI Interstellar dust: what is it, how does it evolve, and what are its observational consequences? SO Spectral Energy Distributions of Gas-Rich Galaxies: Confronting Models with Data SE AIP CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT International Workshop on Spectral Energy Distributions of Gas-Rich Galaxies CY OCT 04-08, 2004 CL Max Planck Inst, Nucl Phys, Heidelberg, GERMANY HO Max Planck Inst, Nucl Phys ID SUPERNOVA REMNANT CASSIOPEIA; TO-GAS RATIO; ABUNDANCE CONSTRAINTS; INFRARED-EMISSION; SIZE DISTRIBUTION; ALPHA SYSTEMS; COLD DUST; GRAINS; GALAXIES; EVOLUTION AB The presence of dust in the interstellar medium of galaxies dramatically affects their spectral appearance, and the interpretation of their underlying physical properties. Consequently, the diagnostic of galaxy spectra depends crucially on our understanding of the nature and properties of these dust particles. Models of interstellar dust particles must be able to reproduce a basic set of observational constraints, including the general interstellar extinction and infrared emission observed in the diffuse interstellar medium (ISM). Recent analysis of the solar spectrum have resulted in a convergence between the solar and B star abundances. This development, and the steadiness in the solar abundance determination of the primary refractory elements Mg, Si, and Fe, strongly suggest that any viable dust model must also obey interstellar abundances constraints. Fifteen dust models that differ in composition and size distribution and that simultaneously satisfy the local extinction, infrared emission, and abundances constraints have been shown to exist. This multitude of viable dust models provides us with an increased flexibility in understanding dust evolution and the many variations in dust properties in different phases of the ISM and stellar environments. The evolution of stars, the primary sources of dust, and the general ISM, in which the dust is processed, change the abundance of dust as a function of time. In particular, the delayed injection of dust from low mass stars, which are the primary sources of carbon dust, into the ISM gives rise to a changing silicate-to-carbon dust mass ratio, which will affect the UV-visual extinction in galaxies. If PAHs are only produced in AGB stars, the delayed injection of these molecules into the ISM may be in part responsible for the absence of PAH features in young star forming regions, or for the existence of a metallicity threshold below which PAHs have not yet formed. On a cosmological scale, an epoch of rapid and efficient dust formation is needed to account for the presence of dust-enshrouded star forming regions at high redshift. We show that the first opacity is probably produce by SN-condensed carbon dust that formed in less than similar to 100 Myr after the onset of galaxy formation. C1 NASA, Goddard Space Flight Ctr, Astron & Solar Phys Lab, Greenbelt, MD 20771 USA. RP Dwek, E (reprint author), NASA, Goddard Space Flight Ctr, Astron & Solar Phys Lab, Greenbelt, MD 20771 USA. NR 67 TC 34 Z9 34 U1 0 U2 2 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 0-7354-0246-9 J9 AIP CONF PROC PY 2005 VL 761 BP 103 EP 122 PG 20 WC Astronomy & Astrophysics; Spectroscopy SC Astronomy & Astrophysics; Spectroscopy GA BCE89 UT WOS:000228963700011 ER PT B AU McCrady, N Graham, JR Vacca, WD AF McCrady, N Graham, JR Vacca, WD BE DeGrijs, R Delgado, RMG TI IMF variation in M82 super star clusters - A population study SO Starbursts: From 30 Doradus to Lyman Break Galaxies SE ASTROPHYSICS AND SPACE SCIENCE LIBRARY LA English DT Proceedings Paper CT Conference on Starbursts - From 30 Doradus to Lyman Break Galaxies CY SEP 06-10, 2004 CL Cambridge, ENGLAND AB The nuclear starburst in M82 is host to over 20 infrared-bright, dense, young super star clusters (SSCs). We use high-resolution near-infrared Keck/NIRSPEC echelle spectroscopy to measure the stellar velocity dispersions. The SSCs are resolved in Hubble Space Telescope images, from which we measure half-light radii and integrated luminosities. We calculate virial masses for the SSCs, and compare the observed light-to-mass ratios to population synthesis models to constrain the initial mass function. There are apparent variations of the IMF within this single starburst galaxy. We present evidence for mass segregation despite the young ages, and discuss implications for the interpretation of the IMF. C1 Univ Calif Berkeley, Berkeley, CA 94720 USA. NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP McCrady, N (reprint author), Univ Calif Berkeley, Berkeley, CA 94720 USA. NR 8 TC 0 Z9 0 U1 0 U2 0 PU SPRINGER PI NEW YORK PA 233 SPRING STREET, NEW YORK, NY 10013, UNITED STATES BN 1-4020-3538-1 J9 ASTROPHYS SPACE SC L PY 2005 VL 329 BP 75 EP 78 PG 4 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BCX24 UT WOS:000231722600014 ER PT B AU de Mello, D AF de Mello, D CA K20 Teams BE DeGrijs, R Delgado, RMG TI K-luminous galaxies at Z similar to 2 - Metallicity and B stars SO Starbursts: From 30 Doradus to Lyman Break Galaxies SE ASTROPHYSICS AND SPACE SCIENCE LIBRARY LA English DT Proceedings Paper CT Conference on Starbursts - From 30 Doradus to Lyman Break Galaxies CY SEP 06-10, 2004 CL Cambridge, ENGLAND ID ULTRAVIOLET-SPECTRA; FORMING GALAXIES; HIGH-REDSHIFT AB We present the results from the analysis of the composite spectrum of five near-IR luminous (K < 20) galaxies at z similar to 2. Several of the strongest absorption lines are present in the UV spectrum of the merging galaxy NGC 6090 and not in the spectra of Lyman Break Galaxies at z similar to 3. They were identified as SiIII lambda 1296, CIII lambda 1428, SiII lambda 1485, and Fe similar to lambda 1380 angstrom, which are photospheric lines typical of B stars. A metallicity higher than solar is suggested by comparing the pure photospheric lines known as the 1425 A index (SiIII, CIII, Fev) with STARBURST99 models. The evidence of high metallicity, together with the high masses, high star-formation rates, and possibly strong clustering, suggest that these galaxies are candidates to become massive spheroids. C1 Catholic Univ Amer, NASA, GSFC, Astron & Solar Phys Lab, Washington, DC 20064 USA. RP de Mello, D (reprint author), Catholic Univ Amer, NASA, GSFC, Astron & Solar Phys Lab, Washington, DC 20064 USA. NR 11 TC 0 Z9 0 U1 0 U2 0 PU SPRINGER PI NEW YORK PA 233 SPRING STREET, NEW YORK, NY 10013, UNITED STATES BN 1-4020-3538-1 J9 ASTROPHYS SPACE SC L PY 2005 VL 329 BP 323 EP 326 PG 4 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BCX24 UT WOS:000231722600059 ER PT S AU Ellis, SR Fishman, JM Hasser, CJ Stern, JD AF Ellis, SR Fishman, JM Hasser, CJ Stern, JD BE Woods, AJ Bolas, MT Merritt, JO McDowall, IE TI Effect of reduced stereoscopic camera separation on ring placement with a surgical telerobot SO Stereoscopic Displays and Virtual Reality Systems XII SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Stereoscopic Display and Virtural Reality Systems XII CY JAN 17-20, 2005 CL San Jose, CA SP SPIE, Soc Imaging Sci & Technol DE stereoscopic display; laparoscopic surgery; inter-camera distance; human factors ID PERFORMANCE AB A custom, stereoscopic video camera was built to study the impact of decreased camera separation on a stereoscopically viewed, visual-manual task resembling some aspects of surgery. The camera's field of view was matched to that of a stereoscopic laparoscope by adjusting focal length and viewing distance so that the viewer could see equivalent image content at a plane orthogonal to their view. This plane contained the point at which the left and right viewing axes converged. This geometry only exactly matches the images from both the laparoscope and the stereo-camera at this point. This condition was considered a useful approximation for a match between the two image sources. Twelve naive subjects and one of the experimenters were first trained in a ring placement task using the stereo-laparoscope and subsequently switched to the stereo-camera. It was used with differing camera separations ranging from 100% of the laparoscope's separation to a biocular view corresponding to no separation. The results suggest that camera separation may be reduced 20-35% without appreciably degrading user performance. Even a 50% reduction in separation shows stereoscopically supported performance much better than the biocular condition. The results suggest that existing laparoscopes which use 5 mm camera separation may well be significantly miniaturized without causing substantial performance degradation. C1 NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Ellis, SR (reprint author), NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. NR 8 TC 3 Z9 3 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 0-8194-5637-3 J9 P SOC PHOTO-OPT INS PY 2005 VL 5664 BP 372 EP 379 DI 10.1117/12.588811 PG 8 WC Imaging Science & Photographic Technology SC Imaging Science & Photographic Technology GA BCD86 UT WOS:000228784400040 ER PT J AU Kletetschka, G Kontny, A AF Kletetschka, G Kontny, A TI Identification of magnetic minerals by scanning electron microscope and application of ferrofluid SO STUDIA GEOPHYSICA ET GEODAETICA LA English DT Article DE magnetic mineralogy; ferrofluid; SEM; magnetism; magnetic; susceptibility; titanomagnetite; ilmenohematite ID VARIABLE TI-CONTENT; TITANOMAGNETITE; PYRRHOTITE; TRANSITION; PARTICLES; BEHAVIOR; BASALTS; DOMAIN AB Magnetic minerals are mostly identified by a combination of rock magnetic and microscopic techniques and the ferrofluid method in combination with an optical microscope was applied during the last decades. But today, scanning electron microscopy (SEM) is preferred for the observation of mineral phases because its depth of focus and resolving capability at the same magnification. In this study, we report on a method, which allows ferrofluid application under the SEM. We coated a polished basalt sample containing titanomagnetite grains with high demagnetizing fields, with a colloidal suspension containing magnetite particles (ferrofluid) ranging in size between 11 and 20 nm. Due to large gradients of multidomain grains the ferrofluid particles adhered to their surfaces. Other grains of similar composition present (ilmenohematite) but with low demagnetizing fields do not generate large magnetic gradients and therefore do not attract the colloidal particles. Upon. evaporation of the ferrofluid and covering the sample with conducting material the magnetic grains with high demagnetizing field are easily identifiable under the scanning electron microscope. The different mineralogy observed by this method is confirmed by temperature dependent variation of magnetic susceptibility, revealing titanomagnetite and ilmenohematite as magnetic carriers in the basaltic samples. C1 Catholic Univ Amer, Dept Phys, Washington, DC 20064 USA. Acad Sci Czech Republ, Inst Geol, Prague 16000 6, Czech Republic. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Univ Heidelberg, Inst Geol Palaontol, Heidelberg, Germany. RP Kletetschka, G (reprint author), Catholic Univ Amer, Dept Phys, Washington, DC 20064 USA. EM gunther.kletetschka@gsfc.nasa.gov; agnes.kontny@urz.uni-heidelberg.de RI Kletetschka, Gunther/C-9996-2011 OI Kletetschka, Gunther/0000-0002-0645-9037 NR 23 TC 7 Z9 7 U1 0 U2 8 PU SPRINGER PI NEW YORK PA 233 SPRING STREET, NEW YORK, NY 10013 USA SN 0039-3169 J9 STUD GEOPHYS GEOD JI Stud. Geophys. Geod. PY 2005 VL 49 IS 2 BP 153 EP 162 DI 10.1007/s11200-005-0002-8 PG 10 WC Geochemistry & Geophysics SC Geochemistry & Geophysics GA 943ZJ UT WOS:000230394400002 ER PT J AU Selbmann, L de Hoog, GS Mazzaglia, A Friedmann, EI Onofri, S AF Selbmann, L de Hoog, GS Mazzaglia, A Friedmann, EI Onofri, S TI Fungi at the edge of life: cryptoendolithic black fungi from Antarctic desert SO STUDIES IN MYCOLOGY LA English DT Article DE Antarctica; black yeasts; cryptoendolithic community; Dothideales; extremophiles; Hysteriales; ITS; lichenicolous fungi; meristematic fungi; microcolonial fungi; phylogeny; SSU; taxonomy ID EXOPHIALA WANGIELLA DERMATITIDIS; TRIMMATOSTROMA-ABIETIS; RDNA PHYLOGENY; COLD DESERT; MARBLE; TEMPERATURE; ANAMORPHS; GENERA; YEASTS; HERPOTRICHIELLACEAE AB Twenty-six strains of black, mostly meristematic fungi isolated from cryptoendolithic lichen dominated communities in the Antarctic were described by light and Scanning Electron Microscopy and sequencing of the ITS rDNA region. In addition, cultural and temperature preferences were investigated. The phylogenetic positions of species recognised were determined by SSU rDNA sequencing. Most species showed affinity to the Dothideomycefidae and constitute two main groups referred to under the generic names Friedmanniomyces and Cryomyces (gen. nov.), each characterised by a clearly distinct morphology. Two species could be distinguished in each of these genera. Six strains could not be assigned to any taxonomic group; among them strain CCFEE 457 belongs to the Hysteriales, clustering together with Mediterranean marble-inhabiting Coniosporium species in an approximate group with low bootstrap support. All strains proved to be psychrophiles with the only exception for the strain CCFEE 507 that seems to be mesophilic-psychrotolerant. All had very thick melanised cell walls, the ability to produce exopolysaccharides and to grow meristematically. They are thought to be well adapted to the harsh environment of the Antarctic cold Desert. Hypotheses concerning their origin and evolution are put forward. C1 Univ Tuscia, Dipartimento Sci Ambientali, Viterbo, Italy. Cent Bur Schimmelcultures, NL-3508 AD Utrecht, Netherlands. Univ Amsterdam, Inst Biodivers & Ecosyst Dynam, NL-1098 SM Amsterdam, Netherlands. Univ Tuscia, Dipartimento Difesa Piante, Viterbo, Italy. NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Onofri, S (reprint author), Univ Tuscia, Dipartimento Sci Ambientali, Largo Univ, Viterbo, Italy. EM onofri@unitus.it RI Mazzaglia, Angelo/I-4336-2012; Selbmann, Laura/L-3056-2013 OI Mazzaglia, Angelo/0000-0002-1295-2565; NR 99 TC 94 Z9 105 U1 7 U2 30 PU CENTRAALBUREAU SCHIMMELCULTURE PI BAARN PA PO BOX 273, 3740 AG BAARN, NETHERLANDS SN 0166-0616 J9 STUD MYCOL JI Stud. Mycol. PY 2005 IS 51 BP 1 EP 32 PG 32 WC Mycology SC Mycology GA 950PJ UT WOS:000230869100002 ER PT J AU Fritz, T Fung, S AF Fritz, T Fung, S TI Preface SO SURVEYS IN GEOPHYSICS LA English DT Editorial Material C1 Boston Univ, Ctr Space Phys, Boston, MA 02215 USA. NASA, Goddard Space Flight Ctr, Space Phys Data Facil, Greenbelt, MD 20771 USA. RP Fritz, T (reprint author), Boston Univ, Ctr Space Phys, Boston, MA 02215 USA. RI Fung, Shing/F-5647-2012 NR 0 TC 5 Z9 5 U1 0 U2 0 PU SPRINGER PI DORDRECHT PA VAN GODEWIJCKSTRAAT 30, 3311 GZ DORDRECHT, NETHERLANDS SN 0169-3298 J9 SURV GEOPHYS JI Surv. Geophys. PD JAN PY 2005 VL 26 IS 1-3 BP 1 EP 3 DI 10.1007/s10712-005-1870-8 PG 3 WC Geochemistry & Geophysics SC Geochemistry & Geophysics GA 954LX UT WOS:000231157700001 ER PT J AU Keith, WR Winningham, JD Goldstein, ML Wilber, M Fazakerley, AN Reme, H Fritz, TA Balogh, A Cornilleau-Wehrlin, N Maksimovic, M AF Keith, WR Winningham, JD Goldstein, ML Wilber, M Fazakerley, AN Reme, H Fritz, TA Balogh, A Cornilleau-Wehrlin, N Maksimovic, M TI Observations of a unique cusp signature at low and mid altitudes SO SURVEYS IN GEOPHYSICS LA English DT Article; Proceedings Paper CT Spring Meeting of the American-Geophysical-Union CY 2002 CL WASHINGTON, D.C. SP Amer Geophys Union DE cusp; true cusp; magnetosphere ID INTERPLANETARY MAGNETIC-FIELD; POLAR CUSP; MAGNETOSHEATH PLASMA; MAGNETOSPHERIC CUSP; BOUNDARY-LAYERS; OUTER CUSP; MAGNETOPAUSE; PRECIPITATION; ELECTRON; ASTRID-2 AB Observations of a unique cusp feature at low and mid altitudes are reported. This feature has a consistent double-peaked or "V"-shaped structure at the equatorward edge of high-latitude particle precipitation flux, and is predominantly present for high IMF B(y) conditions. The observations are consistent with the Crooker ('A split separator line merging model of the dayside magnetopause', J. Geophys. Res. 90 (1985) 12104, 'Mapping the merging potential from the magnetopause to the ionosphere through the dayside cusp', J. Geophys. Res. (1988) 93 7338.) antiparallel merging model, which predicts a narrow wedge-shaped cusp whose geometry depends greatly on the dawn/dusk component of the IMF. Various observations are presented at low altitudes (DE-2, Astrid-2, Munin, UARS, DMSP) and at mid altitudes (DE-1, Cluster) that suggest a highly coherent cusp feature that is consistent with the narrow, wedge-shaped cusp of Crooker (1988), and contains persistent wave signatures that are compatible with previously reported high-altitude measurements. A statistical survey of Astrid-2 and DMSP satellite data is also presented, which shows this feature to be persistent and dependent on the IMF angle at the magnetopause, as expected. Thus, the cusp signatures observed at a wide range of altitudes present a coherent picture that may be interpreted in terms of a footprint of the magnetopause current layer. C1 SW Res Inst, San Antonio, TX 78228 USA. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Univ Calif Berkeley, Space Sci Lab, Berkeley, CA 94720 USA. UCL, Mullard Space Sci Lab, Dorking RH5 6NT, Surrey, England. Ctr Etud Spatiale Rayonnements, F-31029 Toulouse, France. Boston Univ, Ctr Space Phys, Boston, MA 02215 USA. Imperial Coll Space & Atmospher Phys Grp, Blackett Lab, London, England. CETP, F-78140 Velizy Villacoublay, France. Observ Paris, LESIA, Paris, France. Observ Paris, CNRS, Paris, France. RP Keith, WR (reprint author), SW Res Inst, PO Drawer 28510, San Antonio, TX 78228 USA. EM wayne.keith@gsfc.nasa.gov RI Goldstein, Melvyn/B-1724-2008 NR 39 TC 2 Z9 3 U1 0 U2 0 PU SPRINGER PI DORDRECHT PA VAN GODEWIJCKSTRAAT 30, 3311 GZ DORDRECHT, NETHERLANDS SN 0169-3298 J9 SURV GEOPHYS JI Surv. Geophys. PD JAN PY 2005 VL 26 IS 1-3 BP 307 EP 339 DI 10.1007/s10712-005-1885-1 PG 33 WC Geochemistry & Geophysics SC Geochemistry & Geophysics GA 954LX UT WOS:000231157700013 ER PT J AU Heiskell, MR Rudd, MD Penn, BB Kautz, JA AF Heiskell, MR Rudd, MD Penn, BB Kautz, JA TI Synthesis and characterization of alkyl and aryl-(4-methyl-6-nitro-quinolin-2-yl)amines: X-ray structures of ethyl and cyclohexyl(4-methyl-6-nitro-quinolin-2-yl)amine SO SYNTHETIC COMMUNICATIONS LA English DT Article DE quinolinamines; substituted amines; X-ray structure ID OPTICAL NONLINEARITIES; 2ND-ORDER AB We have synthesized and characterized a series of alkyl and aryl-(4-methyl-6-nitro-quinolin-2-yl)amines through a high-yield, three-step procedure starting from 4-methylquinolin-2-ol. Nitration using concentrated nitric/sulfuric acids, followed by chlorination in phosphorus oxychloride, yielded 2-chloro-4-methyl-6-nitroquinoline. All of the intermediates and aminated products have been characterized by multinuclear ((1)H and (13)C) NMR spectroscopy, elemental analysis, and, in the case of the two title compounds (ethyl and cyclohexyl-(4-methyl-6-nitro-quinolin-2-yl)amine), a single crystal X-ray structure was obtained to verify the nature of the new materials. C1 Univ Wisconsin Fox Valley, Dept Chem, Menasha, WI 54952 USA. NW State Univ, Louisiana Scholars Coll, Natchitoches, LA USA. NASA, Inst Non Linear Opt, George C Marshall Space Flight Ctr, Huntsville, AL 35812 USA. Baylor Univ, Dept Chem & Biochem, Waco, TX 76798 USA. RP Rudd, MD (reprint author), Univ Wisconsin Fox Valley, Dept Chem, Menasha, WI 54952 USA. EM mrudd@uwc.edu NR 10 TC 0 Z9 0 U1 0 U2 4 PU TAYLOR & FRANCIS INC PI PHILADELPHIA PA 325 CHESTNUT ST, SUITE 800, PHILADELPHIA, PA 19106 USA SN 0039-7911 J9 SYNTHETIC COMMUN JI Synth. Commun. PY 2005 VL 35 IS 15 BP 2067 EP 2077 DI 10.1081/SCC-200066685 PG 11 WC Chemistry, Organic SC Chemistry GA 952FI UT WOS:000230989000010 ER PT J AU Bugos, G AF Bugos, G TI To reach the high frontier: A history of US launch vehicles SO TECHNOLOGY AND CULTURE LA English DT Book Review C1 NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Bugos, G (reprint author), NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. NR 1 TC 0 Z9 0 U1 0 U2 0 PU JOHNS HOPKINS UNIV PRESS PI BALTIMORE PA JOURNALS PUBLISHING DIVISION, 2715 NORTH CHARLES ST, BALTIMORE, MD 21218-4363 USA SN 0040-165X J9 TECHNOL CULT JI Technol. Cult. PD JAN PY 2005 VL 46 IS 1 BP 233 EP 234 DI 10.1353/tech.2005.0009 PG 2 WC History & Philosophy Of Science SC History & Philosophy of Science GA 909NG UT WOS:000227866000032 ER PT J AU McGreevy, MW AF McGreevy, MW TI Approaching experiential discourse iconicity from the field SO TEXT LA English DT Article DE iconicity; discourse; expertience; structure; association; Campbell AB In this paper, experiential discourse iconicity is examined, shown to be useful in practical studies of planetary exploration and aviation safety, and related to the structure of language. In his 'Philosophy of Rhetoric', first published in 1776, George Campbell offered a bold theory of experiential iconicity in discourse and language that has significant practical value. He asserted that patterns of relatedness among things in the world of experience influence patterns of relatedness among words in discourse and language. This suggests, for example, that the structures of particular experiences can be derived from the structures of corresponding discourses. In Campbell's formulation these structures are networks, which have greater representational power than conventional linear models of experiential iconicity such as that of Enkvist (1981). The experientially iconic nature of practical discourse emerged as an essential resource in studies to support NASA's missions in planetary exploration and aviation safety, leading to development of new search engine technologies called Perilog. A comparison of Campbell's experiential iconicity with Saussure's dichotomies of 'langue' versus 'parole' and associative versus syntagmatic relations suggests that, in addition to being part of discourse structure, experiential iconicity is part of the structure of language. C1 NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP McGreevy, MW (reprint author), NASA, Ames Res Ctr, Mail Stop 262-4, Moffett Field, CA 94035 USA. EM Michael.W.McGreevy@nasa.gov NR 51 TC 1 Z9 1 U1 1 U2 2 PU MOUTON DE GRUYTER PI BERLIN PA GENTHINER STRASSE 13, 10785 BERLIN, GERMANY SN 0165-4888 J9 TEXT JI Text PY 2005 VL 25 IS 1 BP 67 EP 105 DI 10.1515/text.2005.25.1.67 PG 39 WC Communication; Linguistics; Language & Linguistics SC Communication; Linguistics GA 896VT UT WOS:000226962900004 ER PT J AU Gerber, RB Chaban, GM Brauer, B Miller, Y AF Gerber, R. B. Chaban, G. M. Brauer, B. Miller, Y. BE Dykstra, CE Frenking, G Kim, KS Scuseria, GE TI First-principles calculations of anharmonic vibrational spectroscopy of large molecules SO THEORY AND APPLICATIONS OF COMPUTATIONAL CHEMISTRY: THE FIRST FORTY YEARS LA English DT Article; Book Chapter ID SELF-CONSISTENT-FIELD; QUANTUM MONTE-CARLO; PLESSET PERTURBATION-THEORY; DENSITY-FUNCTIONAL THEORY; QUARTIC FORCE-FIELD; EXCHANGE-CORRELATION FUNCTIONALS; INITIAL-VALUE REPRESENTATION; POTENTIAL-ENERGY SURFACES; DUAL-FREQUENCY 2D-IR; DER-WAALS COMPLEXES AB This review describes methods for computing directly the anharmonic vibrational spectra of polyatomic molecules from potential surface points obtained from electronic structure theory. The focus is on the state of the art of the methodology, on the approximations and the algorithms involved and their limitations, and on the scaling of the computational effort with the number of vibrational modes. The performance of different electronic structure methods in obtaining accurate vibrational spectra is assessed by comparing the theoretical predictions with experiment for various test cases. Finally, some of the many open problems and challenges in this field are discussed. C1 [Gerber, R. B.; Brauer, B.; Miller, Y.] Hebrew Univ Jerusalem, Dept Phys Chem, IL-91904 Jerusalem, Israel. [Gerber, R. B.; Brauer, B.; Miller, Y.] Hebrew Univ Jerusalem, Fritz Haber Res Ctr, IL-91904 Jerusalem, Israel. [Gerber, R. B.] Univ Calif Irvine, Dept Chem, Irvine, CA 92697 USA. [Chaban, G. M.] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Gerber, RB (reprint author), Hebrew Univ Jerusalem, Dept Phys Chem, IL-91904 Jerusalem, Israel. NR 174 TC 34 Z9 34 U1 0 U2 0 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA SARA BURGERHARTSTRAAT 25, PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS BN 978-0-08-045624-9 PY 2005 BP 165 EP 194 DI 10.1016/B978-044451719-7/50052-4 PG 30 WC Chemistry, Analytical SC Chemistry GA BCW24 UT WOS:000311646300009 ER PT J AU Bauschlicher, CW Ricca, A AF Bauschlicher, Charles W., Jr. Ricca, Alessandra BE Dykstra, CE Frenking, G Kim, KS Scuseria, GE TI Factors that affect conductance at the molecular level SO THEORY AND APPLICATIONS OF COMPUTATIONAL CHEMISTRY: THE FIRST FORTY YEARS LA English DT Article; Book Chapter ID SELF-ASSEMBLED MONOLAYERS; WALLED CARBON NANOTUBE; CURRENT-VOLTAGE CURVES; ELECTRON-TRANSPORT; GEOMETRY OPTIMIZATION; OXYGEN-ADSORPTION; JUNCTIONS; GRAPHITE; DEVICES; MECHANICS AB The current flow through molecules is discussed. We report on some recent calculations of current-voltage (I-V) curves for molecules between two metal surfaces. The change in the density of states of carbon nanotubes when molecules are allowed to interact with their sidewalls is also discussed. We speculate on the future of this area. C1 [Bauschlicher, Charles W., Jr.; Ricca, Alessandra] NASA, Ames Res Ctr, Ctr Nanotechnol, Moffett Field, CA 94035 USA. RP Bauschlicher, CW (reprint author), NASA, Ames Res Ctr, Ctr Nanotechnol, Mail Stop 230-3, Moffett Field, CA 94035 USA. NR 50 TC 0 Z9 0 U1 0 U2 0 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA SARA BURGERHARTSTRAAT 25, PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS BN 978-0-08-045624-9 PY 2005 BP 813 EP 830 DI 10.1016/B978-044451719-7/50071-8 PG 18 WC Chemistry, Analytical SC Chemistry GA BCW24 UT WOS:000311646300028 ER PT S AU Robinson, DW Rodin, B AF Robinson, D. W. Rodin, B. BE Dinwiddie, RB Mannello, R TI Development of a zero thermal expansion nano actuator system using composites and invar SO Thermal Conductivity 26: Thermal Expansion 14 SE THERMAL CONDUCTIVITY LA English DT Proceedings Paper CT 26th International Thermal Conductivity Conference/14th International Thermal Expansion Symposium CY AUG 06-08, 2001 CL Cambridge, MA SP Holometrix Micromet AB NASA's Next Generation Space Telescope project will require precise positioning of meter-sized mirror segments to form an equivalent large primary mirror of about 6 meters diameter. Thermal expansion of just a few nanometers will move these mirrors out of position and degrade the telescope's performance. ground-based research project at NASA Goddard Space Flight Center created an optical actuator assembly with a very low CTE (.04 ppm/C) using a combination Super-Invar and Graphite-Cyanate Ester composites. The theoretical CTE of the epoxied overlap joint matched the measured values closely. Also a discussion of the Super-Invar heat treatment is presented, as well as the method used to retard moisture expansion on the composite components. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Robinson, DW (reprint author), NASA, Goddard Space Flight Ctr, Code 661, Greenbelt, MD 20771 USA. NR 4 TC 0 Z9 0 U1 0 U2 1 PU DESTECH PUBLICATIONS, INC PI LANCASTER PA 439 DUKE STREET, LANCASTER, PA 17602-4967 USA SN 0163-9005 BN 978-1-932078-36-7 J9 THERM COND PY 2005 VL 26 BP 499 EP 509 PG 11 WC Thermodynamics; Materials Science, Multidisciplinary SC Thermodynamics; Materials Science GA BFS98 UT WOS:000244464900045 ER PT S AU Zhu, D Miller, RA AF Zhu, D. Miller, R. A. BE Wang, H Porter, WD Worley, G TI Thermal conductivity of advanced ceramic thermal barrier coatings determined by a steady-state laser heat-flux approach SO Thermal Conductivity 27: Thermal Expansion 15 SE THERMAL CONDUCTIVITY LA English DT Proceedings Paper CT 27th International Thermal Conductivity Conference/15th International Thermal Expansion Symposium CY OCT 26-29, 2003 CL Knoxville, TN SP Oak Ridge Natl Lab, High Temp Mat Lab ID BEHAVIOR; FATIGUE AB The development of low conductivity and high temperature capable thermal barrier coatings requires advanced testing techniques that can accurately and effectively evaluate coating thermal conductivity under future high-performance and low-emission engine heat-flux conditions. In this paper, a unique steady-state CO2 laser (wavelength 10.6 mu m) heat-flux approach is described for determining the thermal conductivity and conductivity deduced cyclic durability of ceramic thermal and environmental barrier coating systems at very high temperatures (up to 1700 degrees C) under large thermal gradients. The thermal conductivity behavior of advanced thermal and environmental barrier coatings for metallic and Si-based ceramic matrix composite (CMC) component applications has also been investigated using the laser conductivity approach. The relationships between the lattice and radiation conductivities as a function of heat flux and thermal gradient at high temperatures have been examined for the ceramic coating systems. The steady-state laser heat-flux conductivity approach has been demonstrated as a viable means for the development and life prediction of advanced thermal barrier coatings for future turbine engine applications. C1 NASA, Environm Durabil Branch, Vehicle Technol Directorate, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Zhu, D (reprint author), NASA, Environm Durabil Branch, Vehicle Technol Directorate, Glenn Res Ctr, 2100 Brookpk Rd, Cleveland, OH 44135 USA. NR 13 TC 1 Z9 1 U1 0 U2 2 PU DESTECH PUBLICATIONS, INC PI LANCASTER PA 439 DUKE STREET, LANCASTER, PA 17602-4967 USA SN 0163-9005 BN 1-932078-34-7 J9 THERM COND PY 2005 VL 27 BP 291 EP 303 PG 13 WC Thermodynamics; Materials Science, Multidisciplinary SC Thermodynamics; Materials Science GA BFS99 UT WOS:000244466800029 ER PT S AU Stephan, RA Johnson, DG Mastropietro, AJ AF Stephan, RA Johnson, DG Mastropietro, AJ BE Peacock, GR Burleigh, DD Miles, JJ TI Development of detectability limits for on-orbit inspection of space shuffle wing leading edge SO Thermosense XXVII SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Thermosense XXVII CY MAR 29-31, 2005 CL Orlando, FL SP SPIE DE infrared (IR) imaging; thermal protection system inspection; thermography; reinforced carbon-carbon (RCC); non-destructive testing (NDT) AB At the conclusion of the Columbia Accident Investigation, one of the recommendations of the Columbia Accident Investigation Board (CAIB) was that NASA develop and implement an inspection plan for the Reinforced Carbon-Carbon (RCC) system components. To address these issues, a group of scientists and engineers at NASA Langley Research Center proposed the use of an IR camera to inspect the RCC. Any crack in an RCC panel changes the thermal resistance of the material in the direction perpendicular to the crack. The change in thermal resistance can be made visible by introducing a heat flow across the crack and using an IR camera to image the resulting surface temperature distribution. The temperature difference across the crack depends on the change in the thermal resistance, the length of the crack, the local thermal gradient, and the rate of radiation exchange with the environment. The current paper describes how the authors derived the minimum thermal gradient detectability limits for a through crack in an RCC panel. This paper will also show, through the use of a transient, 3-dimensional, finite element model, that these minimum gradients naturally exist on-orbit. The results from the finite element model showed that there exists sufficient thermal gradient to detect a crack on 96% of the RCC leading edge. C1 NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Stephan, RA (reprint author), NASA, Langley Res Ctr, Hampton, VA 23681 USA. RI Johnson, David/F-2376-2015 OI Johnson, David/0000-0003-4399-5653 NR 1 TC 0 Z9 0 U1 0 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 0-8194-5767-1 J9 P SOC PHOTO-OPT INS PY 2005 VL 5782 BP 280 EP 291 DI 10.1117/12.605735 PG 12 WC Thermodynamics; Instruments & Instrumentation; Materials Science, Characterization & Testing; Imaging Science & Photographic Technology SC Thermodynamics; Instruments & Instrumentation; Materials Science; Imaging Science & Photographic Technology GA BCL44 UT WOS:000229855200028 ER PT S AU Ottens, BP Parker, B Stephan, R AF Ottens, BP Parker, B Stephan, R BE Peacock, GR Burleigh, DD Miles, JJ TI Implementing recommendations of the Columbia Accident Investigation Board - development of on-orbit IR thermography SO Thermosense XXVII SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Thermosense XXVII CY MAR 29-31, 2005 CL Orlando, FL SP SPIE DE Space Shuttle Return to Flight thermography AB One of NASA's Space Shuttle Return-to-Flight (RTF) efforts has been to develop thermography for the on-orbit inspection of the Reinforced Carbon Carbon (RCC) portion of the Orbiter Wing Leading Edge (WLE). This paper addresses the capability of thermography to detect cracks in RCC by using in-plane thermal gradients that naturally occur on-orbit. Crack damage, which can result from launch debris impact, is a detection challenge for other on-orbit sensors under consideration for RTF, such as the Intensified Television Camera and Laser Dynamic Range Imager. We studied various cracks in RCC, both natural and simulated, along with material characteristics, such as emissivity uniformity, in steady-state thermography. Severity of crack, such as those likely and unlikely to cause bum through were tested, both in-air and in-vacuum, and the goal of this procedure was to assure crew and vehicle safety during re-entry by identification and quantification of a damage condition while on-orbit. Expected thermal conditions are presented in typical shuttle orbits, and the expected damage signatures for each scenario are presented. Finally, through statistical signal detection, our results show that even at very low in-plane thermal gradients, we are able to detect damage at or below the threshold for fatality in the most critical sections of the WLE, with a confidence exceeding 1 in 10,000 probability of false negative. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Ottens, BP (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 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 0-8194-5767-1 J9 P SOC PHOTO-OPT INS PY 2005 VL 5782 BP 292 EP 302 DI 10.1117/12.602828 PG 11 WC Thermodynamics; Instruments & Instrumentation; Materials Science, Characterization & Testing; Imaging Science & Photographic Technology SC Thermodynamics; Instruments & Instrumentation; Materials Science; Imaging Science & Photographic Technology GA BCL44 UT WOS:000229855200029 ER PT S AU Gazarik, MJ Antill, CW Johnson, DG Stephan, RA Vipavetz, KG Pandolf, JE Kist, EH Tappan, ND Winfree, WP Teter, J Haakenson, D Hinds, D Backer, B Wickman, H Harris, M AF Gazarik, MJ Antill, CW Johnson, DG Stephan, RA Vipavetz, KG Pandolf, JE Kist, EH Tappan, ND Winfree, WP Teter, J Haakenson, D Hinds, D Backer, B Wickman, H Harris, M BE Peacock, GR Burleigh, DD Miles, JJ TI Infrared on-orbit RCC inspection system (IORIS) SO Thermosense XXVII SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Thermosense XXVII CY MAR 29-31, 2005 CL Orlando, FL SP SPIE DE infrared (IR) imaging; thermal protection system inspection; thermography; reinforced carbon-carbon (RCC); non-destructive test (NDT) AB Designed to fulfill a critical inspection need for the Space Shuttle Program, the Infrared On-orbit RCC Inspection System (IORIS) can detect crack and surface defects in the Reinforced Carbon-Carbon (RCC) sections of the Space Shuttle's Thermal Protection System (TPS). IORIS performs this detection by taking advantage of the natural thermal gradients induced in the RCC by solar flux and thermal emission from the Earth. IORIS is a compact, low-mass, low-power solution (1.2cm(3), 1.5kg, 5.OW) for TPS inspection that exceeds existing requirements for feature detection. Taking advantage of ground-based IR thermography techniques, IORIS provides the Space Shuttle program with a solution that can be accommodated by the existing inspection system. IORIS augments the visible and laser inspection systems and finds cracks that are not easily measurable by the other sensors, and thus fills a critical gap in the Space Shuttle's inspection needs. Based on crack IR signature predictions and on-orbit gradient expectations, IORIS can achieve crack detection over approximately 96% of the wing-leading edge RCC (using multiple inspections in an orbit period). This paper discusses the on-orbit RCC inspection measurement concept and requirements, and then presents a detailed description of the IORIS design. C1 NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Gazarik, MJ (reprint author), NASA, Langley Res Ctr, 5 N Dryden St, Hampton, VA 23681 USA. RI Johnson, David/F-2376-2015 OI Johnson, David/0000-0003-4399-5653 NR 3 TC 0 Z9 0 U1 1 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 0-8194-5767-1 J9 P SOC PHOTO-OPT INS PY 2005 VL 5782 BP 303 EP 314 DI 10.1117/12.603167 PG 12 WC Thermodynamics; Instruments & Instrumentation; Materials Science, Characterization & Testing; Imaging Science & Photographic Technology SC Thermodynamics; Instruments & Instrumentation; Materials Science; Imaging Science & Photographic Technology GA BCL44 UT WOS:000229855200030 ER PT S AU Bar-Cohen, Y AF Bar-Cohen, Y BE Quan, C Chau, FS Asundi, A Wong, BS Lim, CT TI Biologically-inspired robotic inspectors - The engineering reality and future outlook SO Third International Conference on Experimental Mechanics and Third Conference of the Asian-Committee-on-Experimental-Mechanics, Pts 1and 2 SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT 3rd International Conference on Experimental Mechanics/3rd Conference of the Asian-Committee-on-Experimental-Mechanics CY NOV 29-DEC 01, 2004 CL Singapore, SINGAPORE SP Asian Comm Expt Mech, Natl Univ Singapore, Dept Mech Engn, Nanyang Technol Univ, Sch Mech & Product Engn, Lee Fdn, USAF Off Sci Res, Asian Off Aerosp Res & Dev, SPIE AB Human errors have long been recognized as a major factor in the reliability of nondestructive evaluation results. To minimize such errors, there is an increasing reliance on automatic inspection tools that allow faster and consistent tests. Crawlers and various manipulation devices are commonly used to perform variety of inspection procedures that include C-scan with contour following capability to rapidly inspect complex structures. The emergence of robots has been the result of the need to deal with parts that are too complex to handle by a simple automatic system. Economical factors are continuing to hamper the wide use of robotics for inspection applications however technology advances are increasingly changing this paradigm. Autonomous robots, which may look like human, can potentially address the need to inspect structures with configuration that are not predetermined. The operation of such robots that mimic biology may take place at harsh or hazardous environments that are too dangerous for human presence. Biomimetic technologies such as artificial intelligence, artificial muscles, artificial vision and numerous others are increasingly becoming common engineering tools. Inspired by science fiction, making biomimetic robots is increasingly becoming an engineering reality and in this paper the state-of-the-art will be reviewed and the outlook for the future will be discussed. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Bar-Cohen, Y (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. NR 13 TC 0 Z9 0 U1 0 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 0-8194-5852-X J9 P SOC PHOTO-OPT INS PY 2005 VL 5852 BP 1 EP 9 DI 10.1117/12.621176 PN 1&2 PG 9 WC Instruments & Instrumentation; Materials Science, Biomaterials; Materials Science, Characterization & Testing; Optics; Imaging Science & Photographic Technology SC Instruments & Instrumentation; Materials Science; Optics; Imaging Science & Photographic Technology GA BCL69 UT WOS:000229932000001 ER PT S AU Clancey, WJ AF Clancey, William J. BE Ritrovato, P Cerri, SA Salerno, S Gaeta, M Allison, C Dimitrakos, T TI Towards On-Line Services Based on a Holistic Analysis of Human Activities SO TOWARDS THE LEARNING GRID: ADVANCES IN HUMAN LEARNING SERVICES SE Frontiers in Artificial Intelligence and Applications LA English DT Article; Book Chapter ID DESIGN C1 NASA, Ames Res Ctr, Computat Sci Div, Moffett Field, CA 94035 USA. RP Clancey, WJ (reprint author), NASA, Ames Res Ctr, Computat Sci Div, MS 269-3, Moffett Field, CA 94035 USA. EM William.J.Clancey@NASA.gov NR 25 TC 1 Z9 1 U1 0 U2 0 PU IOS PRESS PI AMSTERDAM PA NIEUWE HEMWEG 6B, 1013 BG AMSTERDAM, NETHERLANDS SN 0922-6389 BN 978-1-58603-534-1 J9 FRONT ARTIF INTEL AP PY 2005 VL 127 BP 3 EP 11 PG 9 WC Computer Science, Information Systems; Computer Science, Interdisciplinary Applications; Education & Educational Research SC Computer Science; Education & Educational Research GA BMB02 UT WOS:000271715400002 ER PT J AU Gharrett, AJ Matala, AP Peterson, EL Gray, AK Li, ZZ Heifetz, J AF Gharrett, AJ Matala, AP Peterson, EL Gray, AK Li, ZZ Heifetz, J TI Two genetically distinct forms of rougheye rockfish are different species SO TRANSACTIONS OF THE AMERICAN FISHERIES SOCIETY LA English DT Article ID MITOCHONDRIAL-DNA; POPULATION-STRUCTURE; NUCLEOTIDE SUBSTITUTIONS; MATERNAL INHERITANCE; SEBASTES-BOREALIS; RESTRICTION DATA; SCORPAENIDAE; EVOLUTION; INTROGRESSION; TELEOSTEI AB The variation in mitochondrial, DNA (mtDNA) and at eight microsatellite loci was analyzed in 700 rougheye rockfish Sebastes aleatiantes sampled along the Pacific Rim. from the Oregon coast to the western Aleutian Islands and Bering Sea. The program STRUCTURE was used to analyze the microsatellite genotypes and determine that the samples probably came from two genetically distinct sources (type I and type II) by minimizing the strong Hardy-Weinberg and gametic disequilibria observed in the total sample. The two types had nearly fixed differences at one microsatellite locus (muSma6 6 ), which corresponded to divergent mtDNA haplotype clusters. We conclude that these two types are distinct species. The ranges of the two types overlapped but were not coincident: in some areas, one or the other predominated. For example, most of the Aleutian Island samples were type I fish. Although both types were caught in the same hauls in some regions, often one or the other species was predominant in a haul. The differences in distributions suggest a historic vicariant or ecological basis for their divergence. No phenotypic characteristics have been confirmed that can be used to distinguish the two species visually. Rougheye rockfish have high commercial value and their incidental catch has the potential to greatly affect larger fisheries. The discovery of cryptic speciation in a commercially important species underscores our need to learn more about the distribution and biology of these and other groundfish species. C1 Univ Alaska, Juneau Ctr, Sch Fisheries & Ocean Sci, Juneau, AK 99801 USA. Natl Marine Fisheries Serv, Auke Bay Lab, Juneau, AK 99801 USA. RP Gharrett, AJ (reprint author), Univ Alaska, Juneau Ctr, Sch Fisheries & Ocean Sci, 11120 Glacier Highway, Juneau, AK 99801 USA. EM ffajg@uaf.edu NR 46 TC 23 Z9 24 U1 1 U2 3 PU AMER FISHERIES SOC PI BETHESDA PA 5410 GROSVENOR LANE SUITE 110, BETHESDA, MD 20814-2199 USA SN 0002-8487 J9 T AM FISH SOC JI Trans. Am. Fish. Soc. PD JAN PY 2005 VL 134 IS 1 BP 242 EP 260 DI 10.1577/T04-055.1 PG 19 WC Fisheries SC Fisheries GA 899PG UT WOS:000227156200021 ER PT J AU Bakan, A Deutsch, F Li, W AF Bakan, A Deutsch, F Li, W TI Strong chip, normality, and linear regularity of convex sets SO TRANSACTIONS OF THE AMERICAN MATHEMATICAL SOCIETY LA English DT Article DE Moreau-Rockafellar equality; Jameson's property (N); Jameson's property ( G); the conical hull intersection property (the CHIP); the strong conical hull intersection property (the strong CHIP); basic constraint qualification; linear regularity; bounded linear regularity; normal property; weak normal property; uniform normal property; dual normal property ID GLOBAL ERROR-BOUNDS; HULL INTERSECTION PROPERTY; HILBERT-SPACE; CONSTRAINT QUALIFICATIONS; INEQUALITY SYSTEMS; APPROXIMATION; DUALITY AB We extend the property (N) introduced by Jameson for closed convex cones to the normal property for a finite collection of convex sets in a Hilbert space. Variations of the normal property, such as the weak normal property and the uniform normal property, are also introduced. A dual form of the normal property is derived. When applied to closed convex cones, the dual normal property is the property ( G) introduced by Jameson. Normality of convex sets provides a new perspective on the relationship between the strong conical hull intersection property ( strong CHIP) and various regularity properties. In particular, we prove that the weak normal property is a dual characterization of the strong CHIP, and the uniform normal property is a characterization of the linear regularity. Moreover, the linear regularity is equivalent to the fact that the normality constant for feasible direction cones of the convex sets at x is bounded away from 0 uniformly over all points in the intersection of these convex sets. C1 Natl Acad Sci Ukraine, Inst Math, UA-01601 Kiev, Ukraine. Penn State Univ, Dept Math, University Pk, PA 16802 USA. NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Bakan, A (reprint author), Natl Acad Sci Ukraine, Inst Math, UA-01601 Kiev, Ukraine. EM andrew@bakan.kiev.ua; deutsch@math.psu.edu; w.li@nasa.gov NR 35 TC 21 Z9 21 U1 0 U2 0 PU AMER MATHEMATICAL SOC PI PROVIDENCE PA 201 CHARLES ST, PROVIDENCE, RI 02940-2213 USA SN 0002-9947 J9 T AM MATH SOC JI Trans. Am. Math. Soc. PY 2005 VL 357 IS 10 BP 3831 EP 3863 DI 10.1090/S0002-9947-05-03945-0 PG 33 WC Mathematics SC Mathematics GA 948MG UT WOS:000230719300001 ER PT B AU Okojie, RS DeLaat, JC Saus, JR AF Okojie, RS DeLaat, JC Saus, JR GP IEEE TI SiC pressure sensor for detection of combustor thermo-acoustic instabilites SO Transducers '05, Digest of Technical Papers, Vols 1 and 2 LA English DT Proceedings Paper CT 13th International Conference on Solid-State Sensors, Actuators and Microsystems CY JUN 05-09, 2005 CL Seoul, SOUTH KOREA SP Korean Sensors Soc, IEEE Electron Devices Soc, IEEE Robot & Automat Soc, IEE Japan, Sensors & Micromach Soc, Int Federat Automat Control, Inst Control, Automat & Syst Engineers, Inst Elect Engineers Korea, Korean Inst Elect Engineers, Korean Soc Mech Engineers, Korean Soc Precis Engn, Korean Robot Soc DE silicon carbide; pressure sensor; combustion; thermo-acoustics; high temperature AB We have utilized a single crystal silicon carbide (Sic) pressure sensor to validate the existence of thermo-acoustic instability at 310 Hz: in a combustor test rig operating at 420 degrees C and about 180 psia. The MEMS Sic pressure sensor was packaged by the direct chip attach (DCA) method, which eliminated the wire bonding process and the reliability issues associated with it when exposed to high temperature and high vibration environment. The result obtained by using this un-cooled Sic pressure sensor was in excellent agreement with the result obtained from a water-cooled piezoceramic pressure transducer located in close proximity to the Sic sensor. This result provides further confirmation of the viability of a robust Sic pressure sensor with less complex packaging for application in high temperature and high vibration environments. C1 NASA, Glenn Res Ctr, Cleveland, OH 44136 USA. RP Okojie, RS (reprint author), NASA, Glenn Res Ctr, Cleveland, OH 44136 USA. NR 8 TC 1 Z9 1 U1 2 U2 5 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 0-7803-8994-8 PY 2005 BP 470 EP 473 PG 4 WC Engineering, Biomedical; Engineering, Electrical & Electronic; Engineering, Mechanical SC Engineering GA BCZ93 UT WOS:000232189100113 ER PT B AU Hishinuma, Y Yang, EH AF Hishinuma, Y Yang, EH GP IEEE TI Large aperture deformable mirror with a transferred single-crystal silicon membrane actuated using large-stroke PZT unimorph actuators SO Transducers '05, Digest of Technical Papers, Vols 1 and 2 LA English DT Proceedings Paper CT 13th International Conference on Solid-State Sensors, Actuators and Microsystems CY JUN 05-09, 2005 CL Seoul, SOUTH KOREA SP Korean Sensors Soc, IEEE Electron Devices Soc, IEEE Robot & Automat Soc, IEE Japan, Sensors & Micromach Soc, Int Federat Automat Control, Inst Control, Automat & Syst Engineers, Inst Elect Engineers Korea, Korean Inst Elect Engineers, Korean Soc Mech Engineers, Korean Soc Precis Engn, Korean Robot Soc DE deformable mirror; piezoelectric unimorph; actuator; large-stroke; large-aperture AB We have demonstrated a large aperture (50 mm x 50 mm) continuous membrane deformable mirror (DM) with a large-stroke piezoelectric unimorph actuator array. The DM consists of a continuous, large aperture, silicon membrane "transferred" in its entirety onto a 20 x 20 piezoelectric unimorph actuator array. A PZT unimorph actuator, 2.5 mm in diameter with optimized PZT/Si thickness and design showed a deflection of 5.7 mu m at 20 V. An assembled DM showed an operating frequency bandwidth of 30 kHz and influence function of approximately 30 %. C1 Jet Propuls Lab, Pasadena, CA 91109 USA. RP Hishinuma, Y (reprint author), Jet Propuls Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. OI Yang, Eui-Hyeok/0000-0003-4893-1691 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 BN 0-7803-8994-8 PY 2005 BP 1167 EP 1170 PG 4 WC Engineering, Biomedical; Engineering, Electrical & Electronic; Engineering, Mechanical SC Engineering GA BCZ93 UT WOS:000232189100287 ER PT J AU Farman, M AF Farman, Mike TI Flirting with the Explicit: Euphemism and Eroticism in the Chinese Lyric SO TRANSLATION REVIEW LA English DT Article C1 NASA, Washington, DC 20546 USA. RP Farman, M (reprint author), NASA, Washington, DC 20546 USA. NR 3 TC 0 Z9 0 U1 0 U2 2 PU UNIV TEXAS PI RICHARDSON PA TRANSLATION CENTER, BOX 830688, RICHARDSON, TX 75083-0688 USA SN 0737-4836 J9 TRANSLATION REV JI Transl. Rev. PY 2005 IS 70 SI SI BP 24 EP 32 PG 9 WC Language & Linguistics; Literature SC Linguistics; Literature GA V11VD UT WOS:000207558200018 ER PT J AU Farman, M AF Farman, Mike TI Poems of the Masters: China's Classic Anthology of T'ang and Sung Dynasty Verse SO TRANSLATION REVIEW LA English DT Book Review C1 [Farman, Mike] NASA, Washington, DC 20546 USA. RP Farman, M (reprint author), NASA, Washington, DC 20546 USA. NR 1 TC 0 Z9 0 U1 0 U2 2 PU UNIV TEXAS PI RICHARDSON PA TRANSLATION CENTER, BOX 830688, RICHARDSON, TX 75083-0688 USA SN 0737-4836 J9 TRANSLATION REV JI Transl. Rev. PY 2005 IS 70 SI SI BP 68 EP 69 PG 2 WC Language & Linguistics; Literature SC Linguistics; Literature GA V11VD UT WOS:000207558200024 ER PT B AU Bur, MJ AF Bur, Michael J. GP ASME TI Engine testing of advanced materials for hypersonic applications SO Transportation - 2005 LA English DT Proceedings Paper CT ASME International Mechanical Engineering Congress and Exposition CY NOV 05-11, 2005 CL Orlando, FL SP ASME, Proc Ind Div, ASME, Rail Transportat Div, ASME, Noise Control & Acoust Div, ASME, Triol Div, ASME, Pressure Vessels & Piping Div, ASME, Bioengn Div, ASME, Mat Div, ASME, Appl Mech Div, ASME, Fluids Engn Div, ASME, Micro Elect Mech Syst Div, ASME, Heat Transfer Div, ASME, Nucl Engn Div, ASME, Power Div, ASME, Solar Energy Div, ASME, Safety Engn & Risk Anal Div, ASME, Technol & Soc Div, ASME, Adv Energy Syst Div, ASME, Aerosp Div, ASME, Comp & Informat Engn Div DE hypersonic propulsion; ceramic composites; metallic alloys and foams; test cell; hydrogen/oxygen rocket engine AB This paper describes the use of a ground based gaseous hydrogen/oxygen rocket engine to test advanced materials for rocket engine and hypersonic propulsion applications. The types of materials that have been tested include ceramic composites, metallic alloys and ceramic and metallic foams. There are various configurations in which these materials can be tested. A "square" engine is used for testing flat rectangular panels by placing the panel downstream of the rocket nozzle in the exhaust path. A more traditional "round" rocket engine is used to test axisymmetric engine components such as nozzle inserts and combustion chambers that are fabricated from either ceramic composites or metal alloys. Besides hydrogen, other engine fuels such as methane are being evaluated in order to expose test materials to a hydrocarbon environment. Various organizations from industry, academia and other government agencies have used this test cell to facilitate the development of advanced materials for use in both rocket engine and hypersonic propulsion applications. C1 NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Bur, MJ (reprint author), NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. NR 2 TC 0 Z9 0 U1 0 U2 1 PU AMER SOC MECHANICAL ENGINEERS PI NEW YORK PA THREE PARK AVENUE, NEW YORK, NY 10016-5990 USA BN 0-7918-4231-2 PY 2005 BP 121 EP 127 PG 7 WC Engineering, Aerospace; Engineering, Biomedical; Transportation Science & Technology SC Engineering; Transportation GA BFM26 UT WOS:000243036800014 ER PT J AU DellaCorte, C AF DellaCorte, C TI TLT welcomes a familiar face SO TRIBOLOGY & LUBRICATION TECHNOLOGY LA English DT Editorial Material C1 NASA Glenn Res Ctr, Cleveland, OH USA. RP DellaCorte, C (reprint author), NASA Glenn Res Ctr, Cleveland, OH USA. EM cdellacorte@stle.org NR 0 TC 0 Z9 0 U1 0 U2 1 PU SOC TRIBOLOGISTS & LUBRICATION ENGINEERS PI PARK RIDGE PA 840 BUSSE HIGHWAY, PARK RIDGE, IL 60068 USA SN 0024-7154 J9 TRIBOL LUBR TECHNOL JI Tribol. Lubr. Technol. PD JAN PY 2005 VL 61 IS 1 BP 6 EP 6 PG 1 WC Engineering, Mechanical SC Engineering GA 887ER UT WOS:000226288700002 ER PT J AU Zaretsky, EV Branzai, EV AF Zaretsky, EV Branzai, EV TI Effect of rolling bearing refurbishment and restoration on bearing life and reliability SO TRIBOLOGY TRANSACTIONS LA English DT Article; Proceedings Paper CT 59th Annual Meeting of the Society-of-Tribologists-and-Lubrication-Engineers CY MAY 17-20, 2004 CL Toronto, CANADA SP Soc Tribologists & Lubricat Engineers DE rolling-element bearings; bearing rework; life prediction; bearing life ID ELEMENT BEARINGS; ROLLER PROFILE; PREDICTION AB For nearly four decades it has been a practice in commercial and military aircraft application that rolling-element bearings removed at maintenance or overhaul be reworked and returned to service. The work presented extends previously reported bearing life analysis to consider the depth (Z(45)) to maximum shear stress (tau(45)) on stressed volume removal and the effect of replacing the rolling elements with a new set. A simple algebraic relationship was established to determine the L-10 life of bearing races subject to bearing rework. Depending on the extent of rework and based on theoretical analysis, representative life factors for bearings subject to rework ranged from 0.87 to 0.99% of the lives of new bearings. Based on bearing endurance data, 92% of the bearing sets that would be subject to rework would result in L-10 lives equaling and/or exceeding that predicted for new bearings, with the remaining 8% having the potential to achieve the analytically predicted life of new bearings when one of the rings is replaced at rework. The potential savings from bearing rework varies front 53 to 82% that of new bearings depending on the cost, size, and complexity of the bearing. C1 NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. Bearing Inspect Inc, Los Alamitos, CA 90720 USA. RP Zaretsky, EV (reprint author), NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. NR 27 TC 5 Z9 5 U1 2 U2 8 PU SOC TRIBOLOGISTS & LUBRICATION ENGINEERS PI PARK RIDGE PA 840 BUSSE HIGHWAY, PARK RIDGE, IL 60068 USA SN 1040-2004 J9 TRIBOL T JI Tribol. Trans. PD JAN-MAR PY 2005 VL 48 IS 1 BP 32 EP 44 DI 10.1080/05698190590893143 PG 13 WC Engineering, Mechanical SC Engineering GA 896UX UT WOS:000226960500005 ER PT S AU Brown, LR Naumenko, OV Polovtseva, ER AF Brown, LR Naumenko, OV Polovtseva, ER BE Zherebtsov, GA Matvienko, GG TI Absorption spectrum of H2S between 10015 and 10323 cm(-1) SO TWELFTH JOINT INTERNATIONAL SYMPOSIUM ON ATMOSPHERIC AND OCEAN OPTICS/ATMOSPHERIC PHYSICS, PTS 1 AND 2 SE Proceedings of SPIE LA English DT Proceedings Paper CT 12th Joint International Symposium on Atmospheric and Ocean Optics/Atmospheric Physics CY JUN 27-30, 2005 CL Tomsk, RUSSIA SP Russian Acad Sci SB, Inst Atmospher Opt, RAS SB, Inst Solar Terrestrial Phys, Opt Soc Amer, Russian Fdn Basic Res, SPIE Russia Chapter DE highly excited states of H2S molecule; first pentadecade; energy levels AB High resolution FT absorption spectrum of H2S in the near IR region from 100 15 to 10323 cm(-1) recorded at Kitt Peak National observatory, USA, has been analyzed for the first time. Three interacting vibrational states: (103), (004), and (400) belonging to the first pentadecade were considered. For the spectrum analysis the Watson-type rotational Hamiltonian which takes into account the resonance interaction between involved vibrational states has been used. One hundred forty four energy levels were reproduced from the fit with an average accuracy of 0.003 cm(-1) for the main isotope species using a set of 27 rotational and coupling parameters. New evaluation of the band origin of the dark (400) state: E-v = 10292.493 cm(-1) has been obtained from the fit to the upper state experimental energy levels which agrees well with the value of the band origin calculated using the effective vibrational Hamiltonian [1]. As a result, the H2S absorption spectrum was completely analyzed in region under study. The calculated line positions and transition intensities are presented in the "ATMOS" information system. The obtained data on the hydrogen sulfide absorption represent valuable information for investigation of highly excited states of H2S molecule. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. Russian Acad Sci, Siberian Branch, Inst Atmospher Opt, Tomsk, Russia. RP CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 7 TC 0 Z9 0 U1 1 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 0-8194-6212-8 J9 PROC SPIE PY 2005 VL 6160 AR 616005 DI 10.1117/12.675184 PN 1-2 PG 6 WC Meteorology & Atmospheric Sciences; Optics SC Meteorology & Atmospheric Sciences; Optics GA BDW97 UT WOS:000235907100005 ER PT B AU Behnke, J Watts, TH Kobler, B Lowe, D Fox, S Meyer, R AF Behnke, J Watts, TH Kobler, B Lowe, D Fox, S Meyer, R GP IEEE Computer Society TI EOSDIS petabyte archives: Tenth anniversary SO Twenty-Second IEEE/Thirteenth NASA Goddard Conference on Mass Storage Systems and Technologies, Proceedings: INFORMATION RETRIEVAL FROM VERY LARGE STORAGE SYSTEMS LA English DT Proceedings Paper CT 22nd IEEE Conference on Mass Storage Systems and Technologies/13th NASA Goddard Conference on Mass Storage Systems and Technologies CY APR 11-14, 2005 CL Monterey, CA SP IEEE Mass Storage Syst Tech Comm, NASA Goddard Space Flight Ctr AB One of the world's largest scientific data systems, NASA's Earth Observing System Data and Information System (EOSDIS) has stored over three petabytes of earth science data in a geographically distributed mass storage system. Design for this system began in the early 1990s and included a presentation of the design of the mass storage system at this conference in 1995. Many changes have occurred in the ten years since that presentation, much of it performed while the system was operational. In its first operational year (2000), the EOSDIS system had increased NASA's collection of earth science data holdings eight-fold. Today, EOSDIS collects over 7,000 gigabytes of data per week, almost 60 times more than the Hubble Space Telescope. This load represents major challenges for ingest into the mass storage system, as well as for timely and balanced data distribution out of the mass storage system. This paper discusses the evolution of the EOSDIS archives focusing primarily on the mass storage system component of the archive. We present the lessons that were learned over the years and some directions that we are taking for the future. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Behnke, J (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. NR 5 TC 6 Z9 10 U1 0 U2 1 PU IEEE COMPUTER SOC PI LOS ALAMITOS PA 10662 LOS VAQUEROS CIRCLE, PO BOX 3014, LOS ALAMITOS, CA 90720-1264 USA BN 0-7695-2318-8 PY 2005 BP 81 EP 93 DI 10.1109/MSST.2005.12 PG 13 WC Computer Science, Hardware & Architecture; Computer Science, Information Systems SC Computer Science GA BCE87 UT WOS:000228958000008 ER PT S AU Gogolla, M Sammut, P Whittle, J AF Gogolla, M Sammut, P Whittle, J BE Nunes, NJ Selic, B RodriguesDaSilva, A Alvarez, AT TI Essentials of the 3rd UML workshop in software model engineering (WiSME'2004) SO UML MODELING LANGUAGES AND APPLICATIONS SE LECTURE NOTES IN COMPUTER SCIENCE LA English DT Article; Proceedings Paper CT 7th Satellite Activities Conference on UML Modeling Languages and Applications CY OCT 11-15, 2004 CL Lisbon, PORTUGAL SP SINFIC, Springer, Mentor Graph, IBM, ACM SIGSoft, IEEE Comp Soc, New Univ Lisbon, Turismo Lisboa, Object Management Grp AB This paper reports on a workshop held at the 7th UML conference. It describes motivation and aims, organisational issues, abstracts of the accepted papers, and questions raised during discussion. C1 Univ Bremen, Bremen, Germany. NASA, QSS, Ames, IA USA. RP Gogolla, M (reprint author), Univ Bremen, Bremen, Germany. NR 3 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 3-540-25081-6 J9 LECT NOTES COMPUT SC PY 2005 VL 3297 BP 43 EP 51 PG 9 WC Computer Science, Software Engineering; Computer Science, Theory & Methods SC Computer Science GA BCD45 UT WOS:000228724000005 ER PT S AU Bruel, JM Georg, G Hussmann, H Ober, I Pohl, C Whittle, J Zschaler, S AF Bruel, JM Georg, G Hussmann, H Ober, I Pohl, C Whittle, J Zschaler, S BE Nunes, NJ Selic, B RodriguesDaSilva, A Alvarez, AT TI Models for non-functional aspects of component-based software (NfC'04) SO UML MODELING LANGUAGES AND APPLICATIONS SE LECTURE NOTES IN COMPUTER SCIENCE LA English DT Article; Proceedings Paper CT 7th Satellite Activities Conference on UML Modeling Languages and Applications CY OCT 11-15, 2004 CL Lisbon, PORTUGAL SP SINFIC, Springer, Mentor Graph, IBM, ACM SIGSoft, IEEE Comp Soc, New Univ Lisbon, Turismo Lisboa, Object Management Grp AB The goal of this workshop was to look at issues related to the integration of non-functional property expression, evaluation, and prediction in the context of component-based software engineering. The accepted papers looked at the issue from a very broad range of perspectives, such as development process, modelling for analysis vs for construction, or middleware componentisation. The afternoon session was completely used for discussions: discussion topics ranged from the limits of the research domain and the definition of fundamental terms and concepts to issues of compositionality. The workshop had a very inspiring and productive atmosphere, and we are looking forward to organising future instalments of the series. C1 Univ Pau, Lab Informat, F-64013 Pau, France. Colorado State Univ, Dept Comp Sci, Ft Collins, CO 80523 USA. Univ Munich, Inst Informat, D-80333 Munich, Germany. Ctr Equat, UMR Verimag, F-38610 Gi Aeres, France. Tech Univ Dresden, Fak Informat, D-01062 Dresden, Germany. NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Bruel, JM (reprint author), Univ Pau, Lab Informat, BP 1155, F-64013 Pau, France. EM bruel@univ-pau.fr; georg@cs.colostate.edu; hussmann@informatik.uni-muenchen.de; ileana.ober@imag.fr; christoph.pohl@inf.tu-dresden.de; jonathw@email.arc.nasa.gov; steffen.zschaler@inf.tu-dresden.de OI Zschaler, Steffen/0000-0001-9062-6637 NR 1 TC 1 Z9 1 U1 0 U2 0 PU SPRINGER-VERLAG BERLIN PI BERLIN PA HEIDELBERGER PLATZ 3, D-14197 BERLIN, GERMANY SN 0302-9743 BN 3-540-25081-6 J9 LECT NOTES COMPUT SC PY 2005 VL 3297 BP 62 EP 66 PG 5 WC Computer Science, Software Engineering; Computer Science, Theory & Methods SC Computer Science GA BCD45 UT WOS:000228724000007 ER PT S AU Rankin, AL Bergh, CF Goldberg, SB Bellutta, P Huertas, A Matthies, LH AF Rankin, AL Bergh, CF Goldberg, SB Bellutta, P Huertas, A Matthies, LH BE Gerhart, GR Shoemaker, CM Gage, DW TI Passive perception system for day/night autonomous off-road navigation SO Unmanned Ground Vehicle Technology VII SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Unmanned Ground Vehicle Technology VII CY MAR 29-31, 2005 CL Orlando, FL SP SPIE, Ball Aerosp & Technol Corp, Univ Cent Florida, Coll Opt & Photon, Florida Space Inst, FOI, Swedish Defense Res Agcy, Univ Cent Florida DE passive perception; stereo vision; autonomous navigation; sensor head; infrared; parallel processing; FPGA AB Passive perception of terrain features is a vital requirement for military related unmanned autonomous vehicle operations, especially under electromagnetic signature management conditions. As a member of Team Raptor, the Jet Propulsion Laboratory developed a self-contained passive perception system under the DARPA funded PerceptOR program. An environmentally protected forward-looking sensor head was designed and fabricated in-house to straddle an off-the-shelf pan-tilt unit. The sensor head contained three color cameras for multi-baseline daytime stereo ranging, a pair of cooled mid-wave infrared cameras for nighttime stereo ranging, and supporting electronics to synchronize captured imagery. Narrow-baseline stereo provided improved range data density in cluttered terrain, while wide-baseline stereo provided more accurate ranging for operation at higher speeds in relatively open areas. The passive perception system processed stereo images and outputted over a local area network terrain maps containing elevation, terrain type, and detected hazards. A novel software architecture was designed and implemented to distribute the data processing on a 533MHz quad 7410 PowerPC single board computer under the VxWorks real-time operating system. This architecture, which is general enough to operate on N processors, has been subsequently tested on Pentium-based processors under Windows and Linux, and a Sparc based-processor under Unix. The passive perception system was operated during FY04 PerceptOR program evaluations at Fort A. P. Hill, Virginia, and Yuma Proving Ground, Arizona. This paper discusses the Team Raptor passive perception system hardware and software design, implementation, and performance, and describes a road map to faster and improved passive perception. C1 Jet Prop Lab, Pasadena, CA 91109 USA. RP Rankin, AL (reprint author), Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 7 TC 5 Z9 5 U1 0 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 0-8194-5789-2 J9 P SOC PHOTO-OPT INS PY 2005 VL 5804 BP 343 EP 358 DI 10.1117/12.604064 PG 16 WC Robotics SC Robotics GA BCS54 UT WOS:000231052500034 ER PT S AU McHenry, M Cheng, Y Matthies, L AF McHenry, M Cheng, Y Matthies, L BE Gerhart, GR Shoemaker, CM Gage, DW TI Vision-based localization in urban environments SO UNMANNED GROUND VEHICLE TECHNOLOGY VII SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Unmanned Ground Vehicle Technology VII CY MAR 29-31, 2005 CL Orlando, FL SP SPIE, Ball Aerosp & Technol Corp, Univ Cent Florida, Coll Opt & Photon, Florida Space Inst, FOI, Swedish Defense Res Agcy, Univ Cent Florida DE robotics; localization; vision; unmanned-ground vehicles; urban AB As part of DARPA's MARS2020 program, the Jet Propulsion Laboratory has developed a vision-based system for localization in urban environments that requires neither GPS nor active sensors. System hardware consists of a pair of small FireWire cameras and a standard Pentium-based computer. The inputs to the software system consist of. 1) a crude grid-based map describing the positions of buildings, 2) an initial estimate of robot location and 3) the video streams produced by the stereo pair. At each step during the traverse the system: captures new image data, finds image features hypothesized to lie on the outside of a building, computes the range to those features, determines an estimate of the robot's motion since the previous step and combines that data with the map to update a probabilistic representation of the robot's location. This probabilistic representation allows the system to simultaneously represent multiple possible locations. For our testing, we have derived the a priori map manually using non-orthorectified overhead imagery, although this process could be automated. The software system consists of three primary components. The first is a stereo-based visual odometry system that calculates the 6-degree of freedom camera motion between sequential frames. The second component uses a set of heuristics to identify straight-line segments that are likely to be part of a building exterior. Ranging to these straight-line features is computed using binocular or wide-baseline stereo. The resulting features and the associated range measurements are fed to the third software component, a particle-filter based localization system. This system uses the map and the most recent results from the first two to update the estimate of the robot's location. This report summarizes the design of both the hardware and software and describes the results of applying the system to the global localization of a camera system over an approximately half-kilometer traverse across JPL's Pasadena campus. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91009 USA. RP CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91009 USA. EM MichaeI.C.McHenry@jpl.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 0-8194-5789-2 J9 PROC SPIE PY 2005 VL 5804 BP 359 EP 370 DI 10.1117/12.603973 PG 12 WC Robotics SC Robotics GA BCS54 UT WOS:000231052500035 ER PT B AU Zima, HP AF Zima, HP BE Zwieflhofer, W Mozdzynski, G TI Programming models and languages for high-productivity computing systems SO USE OF HIGH PERFORMANCE COMPUTING IN METEOROLOGY LA English DT Proceedings Paper CT 11th Workshop on the Use of High Performance Computing in Meteorology CY OCT 25-29, 2004 CL European Ctr Medium Range Weather Forecasts, Reading, ENGLAND HO European Ctr Medium Range Weather Forecasts AB High performance computing (HPC) provides the superior computational capability required for dramatic advances in key areas of science and engineering such as DNA analysis, drug design, or structural engineering. Over the past decade, progress in this area has been threatened by technology problems that pose serious challenges for continued advances in this field. One of the most important problems has been the lack of adequate language and tool support for programming HPC architectures. In today's dominating programming paradigm users are forced to adopt a low level programming style similar to assembly language if they want to fully exploit the capabilities of parallel machines. This leads to high cost for software production and error-prone programs that are difficult to write, reuse, and maintain. This paper discusses the option of providing a high-level programming interface for HPC architectures. We summarize the state of the art, describe new challenges posed by emerging peta-scale systems, and outline features of the Chapel language developed in the DARPA-funded Cascade project. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. EM zima@jpl.nasa.gov NR 16 TC 0 Z9 0 U1 0 U2 0 PU WORLD SCIENTIFIC PUBL CO PTE LTD PI SINGAPORE PA PO BOX 128 FARRER RD, SINGAPORE 9128, SINGAPORE BN 981-256-354-7 PY 2005 BP 25 EP 35 DI 10.1142/9789812701831_0003 PG 11 WC Computer Science, Interdisciplinary Applications; Computer Science, Theory & Methods; Meteorology & Atmospheric Sciences SC Computer Science; Meteorology & Atmospheric Sciences GA BDP29 UT WOS:000234714600003 ER PT S AU Gerald-Yamasaki, M AF Gerald-Yamasaki, M BE Erbacher, RF Roberts, JC Grohn, MT Borner, K TI Texture-based correspondence display SO VISUALIZATION AND DATA ANALYSIS 2005 SE Proceedings of SPIE LA English DT Proceedings Paper CT Conference on Visualization and Data Analysis 2005 CY JAN 17-18, 2005 CL San Jose, CA SP SPIE, Soc Imaging Sci & Technol DE multivariate; multiple linked views; brushing AB Texture-based correspondence display is a methodology to display corresponding data elements in visual representations of complex multidimensional, multivariate data. Texture is utilized as a persistent medium to contain a visual representation model and as a means to create multiple renditions of data where color is used to identify correspondence. Corresponding data elements are displayed over a variety of visual metaphors in a normal rendering process without adding extraneous linking metadata creation and maintenance. Texture-based correspondence display extends the effectiveness of visual representation for understanding data to the understanding and creation of visual representation models. C1 NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. 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 0-8194-5642-X J9 PROC SPIE PY 2005 VL 5669 BP 168 EP 174 DI 10.1117/12.585312 PG 7 WC Imaging Science & Photographic Technology SC Imaging Science & Photographic Technology GA BCC94 UT WOS:000228667300017 ER PT B AU Huertas, A Matthies, L Rankin, A AF Huertas, A Matthies, L Rankin, A GP ieee computer society TI Stereo-based tree traversability analysis for autonomous off-road navigation SO WACV 2005: SEVENTH IEEE WORKSHOP ON APPLICATIONS OF COMPUTER VISION, PROCEEDINGS LA English DT Proceedings Paper CT 7th IEEE Workshop on Applications of Computer Vision (WACV 2005) CY JAN 05-07, 2005 CL Breckenridge, CO SP IEEE AB Autonomous off-road navigation through forested areas is particularly challenging when there exists a mixture of densely distributed thin and thick trees. To make progress through a dense forest, the robot must decide which trees it can push over and which trees it must circumvent. This paper describes a stereo-based tree traversability algorithm implemented and tested on a robotic vehicle under the DARPA PerceptOR program. Edge detection is applied to the left view of the stereo pair to extract long and vertical edge contours. A search step matches anti parallel line pairs that correspond to the boundaries of individual trees. Stereo ranging is performed and the range data within trunk fragments are averaged. The diameters of each tree is then estimated, based on the average range to the tree, the focal length of the camera, and the distance in pixels between matched contour lines. We use the estimated tree diameters to construct a tree traversability image used in generating a terrain map. In stationary experiments, the average error in estimating the diameter of thirty mature tree trunks (having diameters ranging from 10-65 cm and a distance from the cameras ranging from 2.5-30 meters) was less than 5 cm. Tree traversability results from the daytime for short baseline (9 cm) and wide baseline (30 cm) stereo are presented. Results from nighttime using wide baseline (33.5 cm) thermal infrared stereo are also presented. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Andres.Huertas@jpl.nasa.gov NR 7 TC 0 Z9 0 U1 0 U2 0 PU IEEE COMPUTER SOC PI LOS ALAMITOS PA 10662 LOS VAQUEROS CIRCLE, PO BOX 3014, LOS ALAMITOS, CA 90720-1264 USA BN 0-7695-2271-8 PY 2005 BP 210 EP 217 PG 8 WC Computer Science, Artificial Intelligence; Computer Science, Interdisciplinary Applications SC Computer Science GA BBP05 UT WOS:000226799200031 ER PT S AU Cottam, J Boyce, KR Brown, GV Fujimoto, R Furusho, T Ishisaki, Y Kelley, RL Kilbourne, CA McCammon, D Mitsuda, K Morita, U Porter, FS Saab, T Takai, Y Yamamoto, M AF Cottam, J Boyce, KR Brown, GV Fujimoto, R Furusho, T Ishisaki, Y Kelley, RL Kilbourne, CA McCammon, D Mitsuda, K Morita, U Porter, FS Saab, T Takai, Y Yamamoto, M BE Smith, RK TI The XRS microcalorimeter on Astro-E2 SO X-RAY DIAGNOSTICS OF ASTROPHYSICAL PLASMAS: THEORY, EXPERIMENT, AND OBSERVATION SE AIP Conference Proceedings LA English DT Proceedings Paper CT Conference on X-Ray Diagnostics of Astrophysical Plasmas - Theory, Experiment, and Observation CY NOV 15-17, 2004 CL Cambridge, MA DE X-Ray instrumentation; X-Ray spectrometers; microcalorimeters AB The XRS microcalorimeter will be launched in 2005 as part of the Astro-E2 mission. It will cover the energy band from 0.3 to 10 keV with a nearly constant energy resolution of 6.0 eV and a peak effective area of 200 cm(2) at 1.5 keV. The XRS will provide unprecedented throughput and resolving power, particularly at high energies. Detailed spectral features in the Fe K region will be resolved for the first time, providing access to spectroscopic diagnostics for a wide range of astrophysical objects. In this presentation we will describe the XRS instrument, details of its spectral performance, and how it compares to the current high-resolution instruments on the Chandra and XMM-Newton observatories. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RI Porter, Frederick/D-3501-2012; Kelley, Richard/K-4474-2012 OI Porter, Frederick/0000-0002-6374-1119; NR 3 TC 2 Z9 2 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 0-7354-0259-0 J9 AIP CONF PROC PY 2005 VL 774 BP 379 EP 382 PG 4 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BCS46 UT WOS:000231041800050 ER PT S AU Hornschemeier, AE White, NE Tananbaum, H AF Hornschemeier, AE White, NE Tananbaum, H BE Smith, RK TI The frontier in X-ray spectroscopy: NASA's constellation-X mission SO X-RAY DIAGNOSTICS OF ASTROPHYSICAL PLASMAS: THEORY, EXPERIMENT, AND OBSERVATION SE AIP Conference Proceedings LA English DT Proceedings Paper CT Conference on X-Ray Diagnostics of Astrophysical Plasmas - Theory, Experiment, and Observation CY NOV 15-17, 2004 CL Cambridge, MA DE future missions ID EVOLUTION AB This paper briefly describes the Constellation-X mission, giving its basic performance parameters such as effective area and spectral resolution, describes some example science that may be conducted, and gives a general update on the mission, due for launch in 2016. Constellation-X is one of the two flagship missions for the Beyond Einstein programand was designated as a high priority, second only to JWST, in the large space observatories category of the most recent National Academy decadal. Constellation-X will present a great improvement in spectroscopic sensitivity, enabling studies at sensitivities more than 100 times greater than the best high-resolution spectrometers observing in the 0.25-10 keV band during the current decade. The spectral resolution, R = E/Delta E, will range from 300 to 3000. C1 NASA, Goddard Space Flight Ctr, Lab Xray Astrophys, Greenbelt, MD 20771 USA. RP NASA, Goddard Space Flight Ctr, Lab Xray Astrophys, Greenbelt, MD 20771 USA. RI White, Nicholas/B-6428-2012 OI White, Nicholas/0000-0003-3853-3462 NR 7 TC 9 Z9 9 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 0-7354-0259-0 J9 AIP CONF PROC PY 2005 VL 774 BP 383 EP 389 PG 7 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BCS46 UT WOS:000231041800051 ER PT S AU Sankrit, R Blair, WP DeLaney, T Rudnick, L Harrus, IM Ennis, JA AF Sankrit, R Blair, WP DeLaney, T Rudnick, L Harrus, IM Ennis, JA BE Rakowski, C Chatterjee, S TI HSTACS imaging of a Balmer-dominated shock in Kepler's supernova remnant SO YOUNG NEUTRON STARS AND SUPERNOVA REMNANTS SE ADVANCES IN SPACE RESEARCH LA English DT Article; Proceedings Paper CT 35th COSPAR Scientific Assembly CY JUL 18-25, 2004 CL Paris, FRANCE SP Comm Space Res DE supernova remnants : individual (Kepler, G4.5+6.8, SN1604); supernova remnants : shocks; narrow band imaging ID EMISSION; SPECTRUM AB Optical images of Kepler's supernova remnant obtained at two epochs, in 1987 at Las Campanas Observatory and in 2003 with the HST Advanced Camera for Surveys, show the motion of the Balmer-dominated forward shock. The measured proper motion, combined with estimates of the shock velocity, is used to derive a distance of 3.9(-)(0.9)(+)(1.4) kpc to the remnant. The optical shock is clearly identified in the 0.2-0.65 keV band Chandra X-ray image of the remnant. However, there is no correlation between the optical filaments and features seen in 4-6 keV continuum dominated X-ray emission. (c) 2004 COSPAR. Published by Elsevier Ltd. All rights reserved. C1 Johns Hopkins Univ, Dept Phys & Astron, Baltimore, MD 21218 USA. Univ Minnesota, Dept Astron, Minneapolis, MN 55455 USA. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Sankrit, R (reprint author), Johns Hopkins Univ, Dept Phys & Astron, 3400 N Charles St, Baltimore, MD 21218 USA. EM ravi@pha.jhu.edu; wpb@pha.jhu.edu; tdelaney@astro.umn.edu; larry@astro.umn.edu; imh@milkyway.gsfc.nasa.gov; jennis@astro.umn.edu NR 13 TC 21 Z9 21 U1 0 U2 0 PU PERGAMON-ELSEVIER SCIENCE LTD PI KIDLINGTON PA THE BOULEVARD, LANGFORD LANE,, KIDLINGTON OX5 1GB, OXFORD, ENGLAND SN 0273-1177 J9 ADV SPACE RES PY 2005 VL 35 IS 6 BP 1027 EP 1030 DI 10.1016/j.asr.2004.11.018 PG 4 WC Engineering, Aerospace; Astronomy & Astrophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Engineering; Astronomy & Astrophysics; Geology; Meteorology & Atmospheric Sciences GA BCX77 UT WOS:000231793600009 ER PT J AU Lynn, BH Druyan, L Hogrefe, C Dudhia, J Rosenzweig, C Goldberg, R Rind, D Healy, R Rosenthal, J Kinney, P AF Lynn, BH Druyan, L Hogrefe, C Dudhia, J Rosenzweig, C Goldberg, R Rind, D Healy, R Rosenthal, J Kinney, P TI Sensitivity of present and future surface temperatures to precipitation characteristics SO CLIMATE RESEARCH LA English DT Article DE climate change; surface temperatures; model assessment ID CONVECTIVE ADJUSTMENT SCHEME; REGIONAL CLIMATE MODEL; UNITED-STATES; PART I; MESOSCALE MODEL; HYDROLOGY MODEL; DIURNAL CYCLE; TESTS; SIMULATIONS; VALIDATION AB A model simulation study shows that different diurnal cycles of precipitation are consistent with radically different present and future climate characteristics. In projected future climate scenarios, divergence in the time of day and type of precipitation had very divergent impacts on the radiation balance and consequently on surface temperatures. The relationship between the diurnal cycle of precipitation versus the present and future climate was examined using the GISS-MM5 (Goddard Institute for Space Studies Mesoscale Model 5) regional climate modeling system with 2 alternative moist convection schemes. June-August (JJA) mean surface temperatures of the 1990s, 2050s, and 2080s were simulated over the eastern US on a double nested 108/36 km domain, with the 36 km domain centered over the eastern US. In the 1990s, one model version simulated maxima in (convective) precipitation during the early morning, while the second model simulated the hour of precipitation maxima with considerable spatial variability (in better agreement with observations). In the futuristic climate scenarios, differences in the time of day of precipitation had very important impacts on the radiation balance at the surface. One version gave more precipitation at night and fewer clouds during the day, promoting higher surface temperatures. The alternative version created more precipitation during the day, consistent with diminished absorption of solar radiation at the surface and consequently lower surface temperatures. The results demonstrate the importance of improving cumulus parameterizations in regional mesoscale and global climate models and suggest that such improvements would lead to greater confidence in model projections of climate change. C1 Columbia Univ, Earth Inst, Ctr Climate Syst Res, New York, NY 10025 USA. NASA, Goddard Inst Space Studies, New York, NY 10025 USA. New York State Dept Environm Conservat, Albany, NY 12203 USA. Natl Ctr Atmospher Res, Boulder, CO 80306 USA. Woods Hole Oceanog Inst, Woods Hole, MA 02543 USA. Columbia Univ, Sch Architecture Planning & Preservat, New York, NY 10027 USA. Columbia Univ, Sch Publ Hlth, New York, NY 10032 USA. RP Lynn, BH (reprint author), Columbia Univ, Earth Inst, Ctr Climate Syst Res, Armstrong Hall, New York, NY 10025 USA. EM ldruyan@giss.nasa.gov RI Dudhia, Jimy/B-1287-2008; Kinney, Patrick/H-7914-2012; Healy, Richard/J-9214-2015 OI Dudhia, Jimy/0000-0002-2394-6232; Healy, Richard/0000-0002-5098-8921 NR 30 TC 22 Z9 23 U1 2 U2 8 PU INTER-RESEARCH PI OLDENDORF LUHE PA NORDBUNTE 23, D-21385 OLDENDORF LUHE, GERMANY SN 0936-577X J9 CLIM RES JI Clim. Res. PD DEC 31 PY 2004 VL 28 IS 1 BP 53 EP 65 DI 10.3354/cr028053 PG 13 WC Environmental Sciences; Meteorology & Atmospheric Sciences SC Environmental Sciences & Ecology; Meteorology & Atmospheric Sciences GA 906JZ UT WOS:000227638300006 ER PT J AU Kelley, OA Stout, J Halverson, JB AF Kelley, OA Stout, J Halverson, JB TI Tall precipitation cells in tropical cyclone eyewalls are associated with tropical cyclone intensification SO GEOPHYSICAL RESEARCH LETTERS LA English DT Article ID INNER-CORE; RADAR; SATELLITE; ATLANTIC; WIND AB [ 1] The association of tall precipitation with tropical cyclone intensification may have implications for the difficult task of forecasting the destructive potential of tropical cyclones. This study uses all of the well-centered overflights of tropical cyclones from 1998 to 2003 seen by the TRMM Precipitation Radar. The chance of intensification increases when one or more extremely tall convective towers exist in the tropical cyclone's eyewall. We define an extremely tall convective tower as a convective cell with a 20 dBZ reflectivity signal that reaches an altitude of at least 14.5 km. In addition, we adapt this radar technique for use with more plentiful infrared and passive microwave data. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. George Mason Univ, Sch Computat Sci, Ctr Earth Observing & Space Res, Fairfax, VA 22030 USA. Univ Maryland Baltimore Cty, Joint Ctr Earth Syst Technol, Baltimore, MD 21228 USA. RP Kelley, OA (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. EM okelley@tsdis02.nascom.nasa.gov NR 19 TC 47 Z9 47 U1 0 U2 4 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 0094-8276 J9 GEOPHYS RES LETT JI Geophys. Res. Lett. PD DEC 31 PY 2004 VL 31 IS 24 AR L24112 DI 10.1029/2004GL021616 PG 4 WC Geosciences, Multidisciplinary SC Geology GA 885CB UT WOS:000226133300005 ER PT J AU Olsen, MA Schoeberl, MR Douglass, AR AF Olsen, MA Schoeberl, MR Douglass, AR TI Stratosphere-troposphere exchange of mass and ozone SO JOURNAL OF GEOPHYSICAL RESEARCH-ATMOSPHERES LA English DT Article DE stratosphere-troposphere exchange; ozone transport; mass transport ID GENERAL-CIRCULATION MODEL; CROSS-TROPOPAUSE EXCHANGE; PARTICLE DISPERSION MODEL; TROPICAL STRATOSPHERE; NORTHERN-HEMISPHERE; 15-YEAR CLIMATOLOGY; DOWNWARD CONTROL; TRANSPORT MODEL; 3-D MODELS; CHEMISTRY AB [ 1] This study examines the relationship between the extratropical cross-tropopause fluxes of mass and ozone. The adiabatic and diabatic components of the net fluxes are also compared. The rate of change of mass in the lowermost stratosphere and the flux across the 380 K isentropic surface are used to determine the net tropopause mass flux in the framework of a global circulation model. The diabatic mass flux is calculated from the heating rate at the tropopause, and the adiabatic component is determined by the difference of the net and diabatic fluxes. Consistent ozone fields are obtained by driving the Goddard Chemistry and Transport Model with meteorological output of the global circulation model for the same years. The ozone flux is determined by convolving the mass flux and ozone mixing ratio. The results show the following: ( 1) The seasonal cycle of the ozone mixing ratio is out of phase with the transport cycle leading to a temporal offset of the mass and ozone fluxes; ( 2) the downward net diabatic flux of mass and ozone occurs primarily at middle latitudes while the adiabatic mass flux is dominated by troposphere-to-stratosphere transport at higher latitudes; and ( 3) the Southern Hemisphere stratospheric vortex is more effective at blocking meridional transport, resulting in a phase difference of mean tropopause ozone mixing ratio in the higher Southern Hemisphere latitudes with respect to the corresponding Northern Hemisphere season and location. Finally, this study suggests that individual pathways of cross-tropopause transport are unlikely to be the result of simultaneous adiabatic and diabatic mechanisms. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Univ Maryland Baltimore Cty, Goddard Earth Sci & Technol Ctr, Baltimore, MD 21228 USA. RP Olsen, MA (reprint author), NASA, Goddard Space Flight Ctr, Code 916, Greenbelt, MD 20771 USA. EM olsen@hyperion.gsfc.nasa.gov RI Douglass, Anne/D-4655-2012 NR 52 TC 47 Z9 50 U1 2 U2 15 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 2169-897X J9 J GEOPHYS RES-ATMOS JI J. Geophys. Res.-Atmos. PD DEC 31 PY 2004 VL 109 IS D24 AR D24114 DI 10.1029/2004JD005186 PG 10 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA 885CI UT WOS:000226134100003 ER PT J AU Williams, JG Turyshev, SG Boggs, DH AF Williams, JG Turyshev, SG Boggs, DH TI Progress in lunar laser ranging tests of relativistic gravity SO PHYSICAL REVIEW LETTERS LA English DT Article ID SOLAR GRAVITATIONAL DEFLECTION; EQUIVALENCE PRINCIPLE; GENERAL-RELATIVITY; VERIFICATION; PARAMETERS; MOON AB Analyses of laser ranges to the Moon provide increasingly stringent limits on any violation of the equivalence principle (EP); they also enable several very accurate tests of relativistic gravity. These analyses give an EP test of Delta(M-G/M-I)(EP)=(-1.0+/-1.4)x10(-13). This result yields a strong equivalence principle (SEP) test of Delta(M-G/M-I)(SEP)=(-2.0+/-2.0)x10(-13). Also, the corresponding SEP violation parameter eta is (4.4+/-4.5)x10(-4), where eta=4beta-gamma-3 and both beta and gamma are post-Newtonian parameters. Using the Cassini gamma, the eta result yields beta-1=(1.2+/-1.1)x10(-4). The geodetic precession test, expressed as a relative deviation from general relativity, is K-gp=-0.0019+/-0.0064. The search for a time variation in the gravitational constant results in G/G=(4+/-9)x10(-13) yr(-1); consequently there is no evidence for local (similar to1 AU) scale expansion of the solar system. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Williams, JG (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM james.g.williams@jpl.nasa.gov; turyshev@jpl.nasa.gov; dale.h.boggs@jpl.nasa.gov NR 41 TC 302 Z9 314 U1 2 U2 7 PU AMER PHYSICAL SOC PI COLLEGE PK PA ONE PHYSICS ELLIPSE, COLLEGE PK, MD 20740-3844 USA SN 0031-9007 EI 1079-7114 J9 PHYS REV LETT JI Phys. Rev. Lett. PD DEC 31 PY 2004 VL 93 IS 26 AR 261101 DI 10.1103/PhysRevLett.93.261101 PG 4 WC Physics, Multidisciplinary SC Physics GA 883ZO UT WOS:000226054600011 PM 15697965 ER PT J AU Willis, JK Roemmich, D Cornuelle, B AF Willis, JK Roemmich, D Cornuelle, B TI Interannual variability in upper ocean heat content, temperature, and thermosteric expansion on global scales SO JOURNAL OF GEOPHYSICAL RESEARCH-OCEANS LA English DT Article DE ocean; climate; heat content ID SEA-LEVEL RISE; STORAGE AB [1] Satellite altimetric height was combined with approximately 1,000,000 in situ temperature profiles to produce global estimates of upper ocean heat content, temperature, and thermosteric sea level variability on interannual timescales. Maps of these quantities from mid-1993 through mid-2003 were calculated using the technique developed by Willis et al. [ 2003]. The time series of globally averaged heat content contains a small amount of interannual variability and implies an oceanic warming rate of 0.86 +/- 0.12 watts per square meter of ocean (0.29 +/- 0.04 pW) from 1993 to 2003 for the upper 750 m of the water column. As a result of the warming, thermosteric sea level rose at a rate of 1.6 +/- 0.3 mm/yr over the same time period. Maps of yearly heat content anomaly show patterns of warming commensurate with ENSO variability in the tropics, but also show that a large part of the trend in global, oceanic heat content is caused by regional warming at midlatitudes in the Southern Hemisphere. In addition to quantifying interannual variability on a global scale, this work illustrates the importance of maintaining continuously updated monitoring systems that provide global coverage of the world's oceans. Ongoing projects, such as the Jason/TOPEX series of satellite altimeters and the Argo float program, provide a critical foundation for characterizing variability on regional, basin, and global scales and quantifying the oceans' role as part of the climate system. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. Univ Calif San Diego, Scripps Inst Oceanog, La Jolla, CA 92093 USA. RP Willis, JK (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,MS 300-323, Pasadena, CA 91109 USA. EM jwillis@pacific.jpl.nasa.gov OI Cornuelle, Bruce/0000-0003-2110-3319 NR 17 TC 232 Z9 238 U1 4 U2 26 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 2169-9275 EI 2169-9291 J9 J GEOPHYS RES-OCEANS JI J. Geophys. Res.-Oceans PD DEC 30 PY 2004 VL 109 IS C12 AR C12036 DI 10.1029/2003JC002260 PG 13 WC Oceanography SC Oceanography GA 885CM UT WOS:000226134600001 ER PT J AU Shemesh, D Chaban, GM Gerber, RB AF Shemesh, D Chaban, GM Gerber, RB TI Photoionization dynamics of glycine: The first 10 picoseconds SO JOURNAL OF PHYSICAL CHEMISTRY A LA English DT Article ID POTENTIAL-ENERGY SURFACE; BOND FISSION REACTIONS; CIS-TRANS ISOMERIZATION; ELECTROSPRAY ION-SOURCE; SELF-CONSISTENT-FIELD; MASS-SPECTROMETRY; AB-INITIO; MULTIPHOTON IONIZATION; REACTION COORDINATE; FORCE-FIELD AB Single photon ionization dynamics of glycine is studied by classical trajectory simulations using the semiempirical PM3 potential surface in "on the fly" calculations. The glycine conformer is assumed to be in the vibrational ground state prior to ionization. Initial conditions for the trajectories are weighted according to the Wigner distribution function computed for that state. Vertical ionization in the spirit of the classical Franck-Condon principle is assumed. The main findings are as follows: (1) The photoionization triggers a fast internal rotation about the C-C bond, with the NH(2) group rotating in one direction, and the COOH group rotating in the opposite direction. For the trajectories where the fast rotation occurs, it persists till the end of the simulation (10 ps). The yield for this process is about 6%, suggesting it may be experimentally observable. (2) For many of the trajectories, the photoproduced glycine ion exhibits "hops" between two conformer structures. The rates computed from the dynamics for these conformational transitions differ considerably from RRK predictions. (3) Different behavior of vibrational energy flow is found for different types of modes. There is no significant approach to statistical distribution of the energy throughout the first 10 picoseconds. (4) The preferred dissociation channel is the C-C bond cleavage. Indeed, fragmentation is observed for a few trajectories, one of them shows H atom hopping from the amino group to the carbonyl group prior to dissociation. Another trajectory shows only this hydrogen transfer and the transfer back. Possible experimental implications of some of the findings are briefly discussed. C1 Hebrew Univ Jerusalem, Dept Phys Chem, IL-91904 Jerusalem, Israel. Hebrew Univ Jerusalem, Fritz Haber Res Ctr, IL-91904 Jerusalem, Israel. NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. Univ Calif Irvine, Dept Chem, Irvine, CA 92697 USA. RP Gerber, RB (reprint author), Hebrew Univ Jerusalem, Dept Phys Chem, IL-91904 Jerusalem, Israel. EM benny@fh.huji.ac.il NR 81 TC 15 Z9 15 U1 0 U2 6 PU AMER CHEMICAL SOC PI WASHINGTON PA 1155 16TH ST, NW, WASHINGTON, DC 20036 USA SN 1089-5639 J9 J PHYS CHEM A JI J. Phys. Chem. A PD DEC 30 PY 2004 VL 108 IS 52 BP 11477 EP 11484 DI 10.1021/jp040331o PG 8 WC Chemistry, Physical; Physics, Atomic, Molecular & Chemical SC Chemistry; Physics GA 882FP UT WOS:000225924800002 ER PT J AU Ivins, ER James, TS AF Ivins, ER James, TS TI Bedrock response to Llanquihue Holocene and present-day glaciation in southernmost South America SO GEOPHYSICAL RESEARCH LETTERS LA English DT Article ID TIERRA-DEL-FUEGO; GLACIER FLUCTUATIONS; PATAGONIA; MANTLE; ANDES; PLEISTOCENE; PREDICTIONS; QUATERNARY; MOBILITY; MAXIMUM AB [ 1] Modern geodetic techniques, such as precise Global Positioning System ( GPS) measurements and high resolution space gravity mapping, make it possible to measure the present-day rate of viscoelastic gravitational Earth response to present and past glacier mass change. Patagonia is a rapidly evolving glacial environment. Over the past decade, the local rate of surface stress unloading may be the largest anywhere on the planet. We compute the present-day land uplift rate that could be observed using bedrock GPS measurements. The Little Ice Age ( LIA) of the past half millennium generates large vertical rates since the underlying mantle material is likely to have anomalously low viscosity owing to late-Neogene ridge subduction. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. Geol Survey Canada, Pacific Geosci Ctr, Sidney, BC V8L 4B2, Canada. RP Ivins, ER (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,MS 300-233, Pasadena, CA 91109 USA. EM eri@fryxell.jpl.nasa.gov; james@pgc.nrcan.gc.ca RI James, Thomas/D-9301-2013 OI James, Thomas/0000-0001-7321-047X NR 27 TC 23 Z9 24 U1 0 U2 1 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 0094-8276 J9 GEOPHYS RES LETT JI Geophys. Res. Lett. PD DEC 29 PY 2004 VL 31 IS 24 AR L24613 DI 10.1029/2004GL021500 PG 4 WC Geosciences, Multidisciplinary SC Geology GA 885BZ UT WOS:000226133100006 ER PT J AU Noel, V Winker, DM McGill, M Lawson, P AF Noel, V Winker, DM McGill, M Lawson, P TI Classification of particle shapes from lidar depolarization ratio in convective ice clouds compared to in situ observations during CRYSTAL-FACE SO JOURNAL OF GEOPHYSICAL RESEARCH-ATMOSPHERES LA English DT Article DE cirrus; microphysics; lidar ID CIRRUS CLOUDS; MICROPHYSICAL PROPERTIES; BIDIRECTIONAL REFLECTANCE; RADIATIVE PROPERTIES; SINGLE-SCATTERING; LIGHT-SCATTERING; CLIMATE; SENSITIVITY; INSTRUMENT; FEEDBACK AB [ 1] A technique to classify ice particles into different shape categories, based on lidar depolarization ratio, is considered. This technique is applied to observations taken during the Cirrus Regional Study of Tropical Anvils and Cirrus Layers - Florida Area Cirrus Experiment ( CRYSTAL-FACE) campaign with the airborne Cloud Physics Lidar. The retrieved relative concentrations of particle shapes are compared with shape images from an airborne, in situ, cloud particle imager probe, operating in the same cloud. A first high-resolution time-based comparison, conducted over a short period of close collocation, leads to a good agreement between both techniques, with an average difference below 5% in retrieved relative concentrations. The same technique applied over the entire lifetime of three different convective ice clouds cases shows a maximum difference below 10% in average retrieved relative concentrations. The application of this technique to future spaceborne observations could lead to large-scale classification of particle shapes in ice clouds. C1 NASA, Langley Res Ctr, Hampton, VA 23681 USA. Analyt Serv & Mat, Hampton, VA USA. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. SPEC Inc, Boulder, CO 80301 USA. RP Noel, V (reprint author), NASA, Langley Res Ctr, Mail Stop 435, Hampton, VA 23681 USA. EM v.r.noel@larc.nasa.gov RI McGill, Matthew/D-8176-2012; Noel, Vincent/C-3702-2013 OI Noel, Vincent/0000-0001-9494-0340 NR 37 TC 24 Z9 24 U1 0 U2 3 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 2169-897X J9 J GEOPHYS RES-ATMOS JI J. Geophys. Res.-Atmos. PD DEC 29 PY 2004 VL 109 IS D24 AR D24213 DI 10.1029/2004JD004883 PG 13 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA 885CG UT WOS:000226133900003 ER PT J AU Krabill, W Hanna, E Huybrechts, P Abdalati, W Cappelen, J Csatho, B Frederick, E Manizade, S Martin, C Sonntag, J Swift, R Thomas, R Yungel, J AF Krabill, W Hanna, E Huybrechts, P Abdalati, W Cappelen, J Csatho, B Frederick, E Manizade, S Martin, C Sonntag, J Swift, R Thomas, R Yungel, J TI Greenland Ice Sheet: Increased coastal thinning SO GEOPHYSICAL RESEARCH LETTERS LA English DT Article ID JAKOBSHAVN ISBRAE; MASS-BALANCE; ELEVATION CHANGES; LASER ALTIMETRY; OUTLET GLACIER; ACCUMULATION; FLOW AB [ 1] Repeated laser-altimeter surveys and modelled snowfall/summer melt show average ice loss from Greenland between 1997 and 2003 was 80 +/- 12 km(3) yr(-1), compared to about 60 km(3) yr(-1) for 1993/4-1998/9. Half of the increase was from higher summer melting, with the rest caused by velocities of some glaciers exceeding those needed to balance upstream snow accumulation. Velocities of one large glacier almost doubled between 1997 and 2003, resulting in net loss from its drainage basin by about 20 km 3 of ice between 2002 and 2003. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Univ Sheffield, Dept Geog, Sheffield S10 2TN, S Yorkshire, England. Alfred Wegener Inst Polar & Meersforsch, Bremerhaven, Germany. Free Univ Brussels, Dept Geog, B-1050 Brussels, Belgium. Danish Meteorol Inst, DK-2100 Copenhagen, Denmark. Ohio State Univ, Byrd Polar Res Ctr, Columbus, OH 43210 USA. NASA, Wallops Flight Facil, EG&G Inc, Wallops Isl, VA 23337 USA. Ctr Estudios Cient, Valdivia, Chile. RP Krabill, W (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. EM william.b.krabill@nasa.gov; ehanna@sheffield.ac.uk; phuybrec@vub.ac.be; waleed.abdalati@nasa.gov; jc@dmi.dk; csatho.1@osu.edu; earlb@osb.wff.nasa.gov; manizade@osb.wff.nasa.gov; martin@osb.wff.nasa.gov; sonntag@osb.wff.nasa.gov; swift@osb.wff.nasa.gov; thomas@osb.wff.nasa.gov; yungel@osb.wff.nasa.gov RI Hanna, Edward/H-2219-2016 OI Hanna, Edward/0000-0002-8683-182X NR 21 TC 203 Z9 205 U1 2 U2 28 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 0094-8276 J9 GEOPHYS RES LETT JI Geophys. Res. Lett. PD DEC 28 PY 2004 VL 31 IS 24 AR L24402 DI 10.1029/2004GL021533 PG 4 WC Geosciences, Multidisciplinary SC Geology GA 885BY UT WOS:000226132900006 ER PT J AU Mickley, LJ Jacob, DJ Field, BD Rind, D AF Mickley, LJ Jacob, DJ Field, BD Rind, D TI Effects of future climate change on regional air pollution episodes in the United States SO GEOPHYSICAL RESEARCH LETTERS LA English DT Article ID GENERAL-CIRCULATION MODEL; GODDARD-INSTITUTE; NORTHERN-HEMISPHERE; OZONE CONCENTRATIONS; SULFATE AEROSOLS; GREENHOUSE GASES; TRANSPORT; CYCLONE; TRENDS; SPACE AB [ 1] We examine the impact of future climate change on regional air pollution meteorology in the United States by conducting a transient climate change ( 1950-2052) simulation in a general circulation model ( GCM) of the Goddard Institute of Space Studies ( GISS). We include in the GCM two tracers of anthropogenic pollution, combustion carbon monoxide ( COt) and black carbon ( BCt). Sources of both tracers and the loss frequency of COt are held constant in time, while wet deposition of BCt responds to the changing climate. Results show that the severity and duration of summertime regional pollution episodes in the midwestern and northeastern United States increase significantly relative to present. Pollutant concentrations during these episodes increase by 5-10% and the mean episode duration increases from 2 to 3-4 days. These increases appear to be driven by a decline in the frequency of mid-latitude cyclones tracking across southern Canada. The cold fronts associated with these cyclones are known to provide the main mechanism for ventilation of the midwestern and northeastern United States. Mid-latitude cyclone frequency is expected to decrease in a warmer climate; such a decrease is already apparent in long-term observations. Mixing depths over the midwest and northeast increase by 100-240 m in our future-climate simulation, not enough to compensate for the increased stagnation resulting from reduced cyclone frequency. C1 Harvard Univ, Div Engn & Appl Sci, Cambridge, MA 02138 USA. NASA, Goddard Inst Space Studies, New York, NY 10025 USA. RP Harvard Univ, Div Engn & Appl Sci, Cambridge, MA 02138 USA. EM ljm@io.harvard.edu RI Mickley, Loretta/D-2021-2012 OI Mickley, Loretta/0000-0002-7859-3470 NR 40 TC 126 Z9 128 U1 3 U2 32 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 0094-8276 EI 1944-8007 J9 GEOPHYS RES LETT JI Geophys. Res. Lett. PD DEC 28 PY 2004 VL 31 IS 24 AR L24103 DI 10.1029/2004GL021216 PG 4 WC Geosciences, Multidisciplinary SC Geology GA 885BY UT WOS:000226132900002 ER PT J AU Chang, SW Gallagher, DL Spann, JF Mende, SB Greenwald, RA Newell, PT AF Chang, SW Gallagher, DL Spann, JF Mende, SB Greenwald, RA Newell, PT TI Cusp and LLBL as sources of the isolated dayside auroral feature during northward IMF SO JOURNAL OF GEOPHYSICAL RESEARCH-SPACE PHYSICS LA English DT Article DE cusp and LLBL; magnetic merging; proton aurora ID INTERPLANETARY MAGNETIC-FIELD; HIGH-LATITUDE CONVECTION; HF-RADAR OBSERVATIONS; BOUNDARY-LAYER; PROTON AURORA; SOUTHWARD IMF; MAGNETOPAUSE RECONNECTION; PLASMA CONVECTION; LYMAN-ALPHA; SOLAR-WIND AB [1] An intense dayside proton aurora was observed by Imager for Magnetopause-to-Aurora Global Exploration Far Ultra-Violet imager ( IMAGE FUV) for an extensive period of northward interplanetary magnetic field (IMF) on 17 and 18 September 2000. This aurora partially coincided with the auroral oval and intruded farther poleward into the polar cap, and it showed longitudinal motions in response to IMF B-y variation. Intense magnetosheath-like electron and ion precipitations have been simultaneously detected by Defense Meteorological Satellite Program (DMSP) above the poleward portion of the high-latitude dayside aurora. They resemble the typical plasmas observed in the low-altitude cusp. However, less intense electrons and more energetic ions were detected over the equatorward part of the aurora. These plasmas are closer to the low-latitude boundary layer (LLBL) plasmas. Under strongly northward IMF, global ionospheric convection derived from Super Dual Auroral Radar Network (SuperDARN) radar measurements showed a four-cell pattern with sunward convection in the middle of the dayside polar cap and the dayside aurora corresponded to two different convection cells. This result further supports two source regions for the aurora. The cusp proton aurora is on open magnetic field lines convecting sunward whereas the LLBL proton aurora is on closed field lines convecting antisunward. These IMAGE, DMSP, and SuperDARN observations reveal the structure and dynamics of the aurora and provide strong evidence for magnetic merging occurring at the high-latitude magnetopause poleward from the cusp. This merging process was very likely quasi-stationary. C1 Univ Alabama, Ctr Space Plasma & Aeron Res, Huntsville, AL 35899 USA. NASA, Dept Space Sci, George C Marshall Space Flight Ctr, Huntsville, AL 35812 USA. Univ Calif Berkeley, Space Sci Lab, Berkeley, CA 94720 USA. Johns Hopkins Univ, Appl Phys Lab, Laurel, MD 20723 USA. RP Natl Space Sci & Technol Ctr, Dept Space Sci, SD50,320 Sparkman Dr, Huntsville, AL 35805 USA. EM shen.chang@msfc.nasa.gov; dennis.l.gallagher@nasa.gov; james.f.spann@nasa.gov; mende@ssl.berkeley.edu; ray.greenwald@jhuapl.edu; patrick.newell@jhuapl.edu OI Greenwald, Raymond/0000-0002-7421-5536 NR 59 TC 4 Z9 4 U1 0 U2 2 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 2169-9380 EI 2169-9402 J9 J GEOPHYS RES-SPACE JI J. Geophys. Res-Space Phys. PD DEC 28 PY 2004 VL 109 IS A12 AR A12222 DI 10.1029/2004JA010619 PG 11 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 885CV UT WOS:000226135500005 ER PT J AU Merka, J Szabo, A AF Merka, J Szabo, A TI Bow shock's geometry at the magnetospheric flanks SO JOURNAL OF GEOPHYSICAL RESEARCH-SPACE PHYSICS LA English DT Article DE terrestrial bow shock; magnetopause; solar wind-magnetosphere interaction; IMP 8; dipole tilt angle ID MAGNETIC-FIELD ORIENTATION; NEAR-EARTH MAGNETOTAIL; DAWN-DUSK ASYMMETRY; SOLAR-WIND CONTROL; MAGNETOPAUSE SHAPE; STANDOFF DISTANCE; DIPOLE TILT; DAYSIDE MAGNETOPAUSE; GEOTAIL OBSERVATIONS; UNUSUAL LOCATIONS AB [1] The database of IMP 8 bow shock crossings was used to investigate properties of the [bow shock's cross section between 10 and 15 R-E tailward of Earth in response to selected upstream and magnetospheric parameters. Best-fitted ellipses were derived for each parameter subset and analyzed. We have found that for average solar wind conditions, the shock's cross section moves in the north-south directions by 3.8 R-E when the dipole tilt changes from sunward to antisunward orientations. Comparisons with results provided by global three-dimensional MHD simulations of the magnetosphere have shown that the tilt angle effect is likely to be also important for the estimation of the dayside shock wave's position. We have found the orientation of the IMF with respect to the solar wind flow, expressed by the angle theta(Bv), to influence the size and stability of the shock shape/position. The observed Mach number dependence agreed with previous studies and no other significant IMF-induced asymmetries were found. C1 NASA, Extraterr Phys Lab, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. L3 Commun Govt Serv Inc, Vienna, VA USA. RP NASA, Extraterr Phys Lab, Goddard Space Flight Ctr, Code 696, Greenbelt, MD 20771 USA. EM jan.merka@gsfc.nasa.gov; adam.szabo@gsfc.nasa.gov NR 66 TC 10 Z9 11 U1 0 U2 1 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 2169-9380 EI 2169-9402 J9 J GEOPHYS RES-SPACE JI J. Geophys. Res-Space Phys. PD DEC 28 PY 2004 VL 109 IS A12 AR A12224 DI 10.1029/2004JA010567 PG 13 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 885CV UT WOS:000226135500003 ER PT J AU Puchalla, J Adamek, D Austin, R AF Puchalla, J Adamek, D Austin, R TI Towards measurement of the time-resolved heat release of protein conformation dynamics SO CHEMICAL PHYSICS LA English DT Article ID X-RAY-SCATTERING; APOMYOGLOBIN; CALORIMETRY; MIXER AB We present a way to observe time-resolved heat release using a laminar flow diffusional mixer coupled with a highly sensitive infrared camera which measures the temperature change of the solvent. There are significant benefits to the use of laminar flow mixers for time-resolved calorimetry: (1) The thermal signal can be made position and time-stationary to allow for signal integration; (2) Extremely small volumes (nl/s) of sample are required for a measurement; (3) The same mixing environment can be observed spectroscopically to obtain state occupation information; (4) The mixer allows one to do out of equilibrium dynamic studies. The hope is that these measurements will allow us probe the non-equilibrium thermodynamics as a protein moves along a free energy trajectory from one state to another. (C) 2004 Elsevier B.V. All rights reserved. C1 Princeton Univ, Dept Phys, Princeton, NJ 08544 USA. Princeton Univ, Lewis Thomas Lab, Dept Biol Mol, Princeton, NJ 08544 USA. NASA, George C Marshall Space Flight Ctr, Lab Struct Biol, AZ Technol, Huntsville, AL 35812 USA. RP Austin, R (reprint author), Princeton Univ, Dept Phys, 122 Jadwin Hall, Princeton, NJ 08544 USA. EM austin@princeton.edu NR 24 TC 1 Z9 1 U1 0 U2 0 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS SN 0301-0104 J9 CHEM PHYS JI Chem. Phys. PD DEC 27 PY 2004 VL 307 IS 2-3 BP 285 EP 290 DI 10.1016/j.chemphys.2004.09.006 PG 6 WC Chemistry, Physical; Physics, Atomic, Molecular & Chemical SC Chemistry; Physics GA 872NZ UT WOS:000225215200020 ER PT J AU Harvey, VL Pierce, RB Hitchman, MH Randall, CE Fairlie, TD AF Harvey, VL Pierce, RB Hitchman, MH Randall, CE Fairlie, TD TI On the distribution of ozone in stratospheric anticyclones SO JOURNAL OF GEOPHYSICAL RESEARCH-ATMOSPHERES LA English DT Article ID GENERAL-CIRCULATION MODEL; NORTHERN WINTER 1991/92; POLAR VORTEX; NOVEMBER 1994; AIR MASSES; 3-DIMENSIONAL TRANSPORT; POTENTIAL VORTICITY; SOUTHERN-HEMISPHERE; VOLCANIC AEROSOL; MIDDLE LATITUDES AB Twelve years (1991-2003) of satellite occultation ozone data are combined with a climatology of stratospheric anticyclones and polar vortices to quantify the climatological ozone differences between air mass types. Ozone data from the Stratospheric Aerosol and Gas Experiment (SAGE) II, the Halogen Occultation Experiment (HALOE), the Polar Ozone and Aerosol Measurement (POAM) II and III missions, and the Improved Limb Atmospheric Spectrometer (ILAS) sensor are used in this study. Daily ozone measurements in the 400-1600 K altitude range are categorized as being either ( 1) in an anticyclone, ( 2) in a polar vortex, or (3) in neither (hereinafter referred to as "ambient''). Monthly mean ozone is then calculated in each air mass category from data combined over all years. This study focuses on ozone differences between anticyclones and the ambient environment. A composite annual cycle of ozone in ambient regions is compared to ozone in anticyclones as a function of altitude and latitude. Ozone differences result from both anomalous transport and photochemistry in the vicinity of stratospheric anticyclones. The relative importance of transport versus chemistry is inferred from the long-term ozone anomalies observed here. In summer, ozone gradients between different air mass types are small. In other seasons, results indicate three distinct vertical regimes at high latitudes. Below approximate to600 K, anticyclones coincide with regions where ozone is reduced by 10-50% during the winter. Between 600 and 900 K from fall to midwinter, anticyclones are associated with approximate to10% more ozone than ambient air masses. Positive ozone anomalies are also observed in low-latitude anticyclones within this vertical layer; however, they are half the size of their high-latitude counterparts and peak several months later. Above 900 K the abundance of ozone in anticyclones is approximate to10% less than in the surrounding air. This upper stratospheric regime results from the formation of "low-ozone pockets'' (LOPs) in stratospheric anticyclones. All LOPs that formed between November 1991 and November 2003 and were observed by a satellite used in this study ( 108 pockets) are documented here in the most comprehensive catalog of LOPs to date. C1 Univ Colorado, Atmospher & Space Phys Lab, Boulder, CO 80309 USA. NASA, Langley Res Ctr, Hampton, VA 23681 USA. Univ Wisconsin, Dept Atmospher & Ocean Sci, Madison, WI 53706 USA. RP Harvey, VL (reprint author), Univ Colorado, Atmospher & Space Phys Lab, Campus Box 392, Boulder, CO 80309 USA. EM harvey@aura.colorado.edu RI Pierce, Robert Bradley/F-5609-2010; Randall, Cora/L-8760-2014 OI Pierce, Robert Bradley/0000-0002-2767-1643; Randall, Cora/0000-0002-4313-4397 NR 63 TC 16 Z9 16 U1 0 U2 0 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 2169-897X J9 J GEOPHYS RES-ATMOS JI J. Geophys. Res.-Atmos. PD DEC 24 PY 2004 VL 109 IS D24 AR D24308 DI 10.1029/2004JD004992 PG 16 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA 883PR UT WOS:000226027100002 ER PT J AU Glenn, S Arnone, R Bergmann, T Bissett, WP Crowley, M Cullen, J Gryzmski, J Haidvogel, D Kohut, J Moline, M Oliver, M Orrico, C Sherrell, R Song, T Weidemann, A Chant, R Schofield, O AF Glenn, S Arnone, R Bergmann, T Bissett, WP Crowley, M Cullen, J Gryzmski, J Haidvogel, D Kohut, J Moline, M Oliver, M Orrico, C Sherrell, R Song, T Weidemann, A Chant, R Schofield, O TI Biogeochemical impact of summertime coastal upwelling on the New Jersey Shelf SO JOURNAL OF GEOPHYSICAL RESEARCH-OCEANS LA English DT Article DE coastal upwelling; phytoplankton; hypoxia ID NEW-YORK BIGHT; INNER SHELF; OCEAN; SEA; PHYTOPLANKTON; ATTENUATION; CALIBRATION; ABSORPTION; EVOLUTION AB The alternative hypothesis that observed regions of recurrent hypoxia on the New Jersey inner shelf are more related to coastal upwelling than riverine inputs of nutrients was investigated through a series of multidisciplinary research programs beginning in 1993. The largest variations in ocean temperatures along the New Jersey coast, other than seasonal, are found to be caused by episodic summertime upwelling events driven by southwesterly winds associated with the atmospheric Bermuda High. Off the southern coast of New Jersey, topographic variations associated with ancient river deltas cause upwelled water to evolve into an alongshore line of recurrent upwelling centers that are colocated with historical regions of low dissolved oxygen. Recurrent upwelling centers are observed every summer in a 9-year data set. The most significant upwelling events occur in summers following colder than usual falls and winters. Size and duration of individual events are correlated and are found to depend on the wind forcing history that effects the inner side of the Middle Atlantic Cold Pool, the precipitation history that effects the strength of the Hudson River plume, and the mixing storm frequency. Upwelling results in a significant enhancement of particulate organic carbon. The typical carbon enhancement associated with the upwelling is sufficient to deplete 75% of the oxygen in the bottom water, making it borderline hypoxic. This indicates that topographically controlled coastal upwelling, rather than riverine inputs, is the more probable mechanism for generating the historical regions of recurrent hypoxia observed along the New Jersey coast. C1 Rutgers State Univ, Inst Marine & Coastal Sci, Coastal Ocean Observat Lab, New Brunswick, NJ 08901 USA. USN, Res Lab, Ocean Color Sect, Stennis Space Ctr, MS 39529 USA. Florida Environm Res Inst, Tampa, FL 33611 USA. Univ Victoria, Sch Earth & Ocean Sci, Victoria, BC V8W 3P6, Canada. Desert Res Inst, Div Earth & Ecosyst Sci, Reno, NV 89512 USA. Calif Polytech State Univ San Luis Obispo, Dept Biol Sci, San Luis Obispo, CA 93407 USA. CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Glenn, S (reprint author), Rutgers State Univ, Inst Marine & Coastal Sci, Coastal Ocean Observat Lab, New Brunswick, NJ 08901 USA. EM oscar@imcs.marine.rutgers.edu NR 52 TC 39 Z9 39 U1 2 U2 9 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 2169-9275 EI 2169-9291 J9 J GEOPHYS RES-OCEANS JI J. Geophys. Res.-Oceans PD DEC 24 PY 2004 VL 109 IS C12 AR C12S02 DI 10.1029/2003JC002265 PG 15 WC Oceanography SC Oceanography GA 883PW UT WOS:000226027600001 ER PT J AU Clark, BC Green, SF Economou, TE Sandford, SA Zolensky, ME McBride, N Brownlee, DE AF Clark, BC Green, SF Economou, TE Sandford, SA Zolensky, ME McBride, N Brownlee, DE TI Release and fragmentation of aggregates to produce heterogeneous, lumpy coma streams SO JOURNAL OF GEOPHYSICAL RESEARCH-PLANETS LA English DT Article DE cometary dust; Stardust; 81P/Wild 2; Dust Flux; DFMI ID COMETARY ICE ANALOGS; DUST COMA; HALE-BOPP; DETECTOR MEASUREMENTS; CHEMICAL-COMPOSITION; INTERSTELLAR DUST; GRIGG-SKJELLERUP; P/AREND-RIGAUX; INNER COMA; C/1996 B2 AB The unpredicted heterogeneity in particle number density in the coma of Wild 2 is consistent with delayed fragmentation to produce small particles from larger aggregates initially ejected from the cometary nucleus. The resultant heterogeneous inner coma results in stochastic variations in particle number and size distribution. Fragmentation can be accelerated after aggregate release by enhanced heating and one or more additional factors such as abrupt depressurization, phase transitions, exothermic chemical reactions, centrifugal forces, and electrostatic repulsion. Certain predicted characteristics of such in-flight disaggregation in coma particle streams correspond to known cometary phenomena. C1 Lockheed Martin, Denver, CO 80201 USA. Univ Washington, Dept Astron, Seattle, WA 98195 USA. Open Univ, Planetary & Space Sci Res Inst, Milton Keynes MK7 6AA, Bucks, England. Univ Chicago, Enrico Fermi Inst, Lab Astrophys & Space Res, Chicago, IL 60637 USA. NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. RP Clark, BC (reprint author), Lockheed Martin, POB 179,MS-S8000, Denver, CO 80201 USA. EM benton.c.clark@lmco.com RI Green, Simon/C-7408-2009 NR 75 TC 10 Z9 10 U1 0 U2 1 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 0148-0227 J9 J GEOPHYS RES-PLANET JI J. Geophys. Res.-Planets PD DEC 24 PY 2004 VL 109 IS E12 AR E12S03 DI 10.1029/2004JE002319 PG 13 WC Geochemistry & Geophysics SC Geochemistry & Geophysics GA 883PZ UT WOS:000226027900001 ER PT J AU D'Hondt, S Jorgensen, BB Miller, DJ Batzke, A Blake, R Cragg, BA Cypionka, H Dickens, GR Ferdelman, T Hinrichs, KU Holm, NG Mitterer, R Spivack, A Wang, GZ Bekins, B Engelen, B Ford, K Gettemy, G Rutherford, SD Sass, H Skilbeck, CG Aiello, IW Guerin, G House, CH Inagaki, F Meister, P Naehr, T Niitsuma, S Parkes, RJ Schippers, A Smith, DC Teske, A Wiegel, J Padilla, CN Acosta, JLS AF D'Hondt, S Jorgensen, BB Miller, DJ Batzke, A Blake, R Cragg, BA Cypionka, H Dickens, GR Ferdelman, T Hinrichs, KU Holm, NG Mitterer, R Spivack, A Wang, GZ Bekins, B Engelen, B Ford, K Gettemy, G Rutherford, SD Sass, H Skilbeck, CG Aiello, IW Guerin, G House, CH Inagaki, F Meister, P Naehr, T Niitsuma, S Parkes, RJ Schippers, A Smith, DC Teske, A Wiegel, J Padilla, CN Acosta, JLS TI Distributions of microbial activities in deep subseafloor sediments SO SCIENCE LA English DT Article ID PROKARYOTES; OXIDATION; CRUST; LIFE AB Diverse microbial communities and numerous energy-yielding activities occur in deeply buried sediments of the eastern Pacific Ocean. Distributions of metabolic activities often deviate from the standard model. Rates of activities, cell concentrations, and populations of cultured bacteria vary consistently from one subseafloor environment to another. Net rates of major activities principally rely on electron acceptors and electron donors from the photosynthetic surface world. At open-ocean sites, nitrate and oxygen are supplied to the deepest sedimentary communities through the underlying basaltic aquifer. In turn, these sedimentary communities may supply dissolved electron donors and nutrients to the underlying crustal biosphere. C1 Univ Rhode Isl, Grad Sch Oceanog, NASA Astrobiol Inst, Narragansett, RI 02882 USA. Univ Oldenburg, Inst Chem & Biol Meeres, D-26111 Oldenburg, Germany. Univ Oldenburg, Ocean Drilling Program Leg Shipboard Sci Party 20, D-26111 Oldenburg, Germany. Roger Williams Univ, Dept Environm Sci, Bristol, RI 02809 USA. RP D'Hondt, S (reprint author), Univ Rhode Isl, Grad Sch Oceanog, NASA Astrobiol Inst, S Ferry Rd, Narragansett, RI 02882 USA. EM dhondt@gso.uri.edu RI Skilbeck, Charles/M-6872-2013; Naehr, Thomas/C-2958-2008; Sass, Henrik/B-8817-2009; Hinrichs, Kai-Uwe/C-7675-2009; Cragg, Barry/D-2690-2009; Parkes, Ronald/B-1731-2010; Dickens, Gerald/G-1222-2011; Holm, Nils/H-3726-2012; Ferdelman, Timothy/A-3758-2013; Smith, David/A-8309-2013; Jorgensen, Bo/C-2214-2013; OI Sass, Henrik/0000-0001-8740-4224; Hinrichs, Kai-Uwe/0000-0002-0739-9291; Parkes, Ronald/0000-0001-9402-5943; Holm, Nils/0000-0001-8904-6053; Smith, David/0000-0003-0627-5788; Jorgensen, Bo/0000-0001-9398-8027; Wiegel, Juergen/0000-0002-6343-6464; Skilbeck, Greg/0000-0003-1634-963X NR 19 TC 369 Z9 382 U1 12 U2 117 PU AMER ASSOC ADVANCEMENT SCIENCE PI WASHINGTON PA 1200 NEW YORK AVE, NW, WASHINGTON, DC 20005 USA SN 0036-8075 J9 SCIENCE JI Science PD DEC 24 PY 2004 VL 306 IS 5705 BP 2216 EP 2221 DI 10.1126/science.1101155 PG 6 WC Multidisciplinary Sciences SC Science & Technology - Other Topics GA 882PE UT WOS:000225950000034 PM 15618510 ER PT J AU Bertone, P Stolc, V Royce, TE Rozowsky, JS Urban, AE Zhu, XW Rinn, JL Tongprasit, W Samanta, M Weissman, S Gerstein, M Snyder, M AF Bertone, P Stolc, V Royce, TE Rozowsky, JS Urban, AE Zhu, XW Rinn, JL Tongprasit, W Samanta, M Weissman, S Gerstein, M Snyder, M TI Global identification of human transcribed sequences with genome tiling arrays SO SCIENCE LA English DT Article ID TRANSCRIPTIONAL ACTIVITY; HUMAN-CHROMOSOME-22; CHROMOSOME-22; PSEUDOGENES; MICROARRAY; RESOURCES; COVERAGE; ENSEMBL; RNAS; DNA AB Elucidating the transcribed regions of the genome constitutes a fundamental aspect of human biology, yet this remains an outstanding problem. To comprehensively identify coding sequences, we constructed a series of high-density oligonucleotide tiling arrays representing sense and antisense strands of the entire nonrepetitive sequence of the human genome. Transcribed sequences were located across the genome via hybridization to complementary DNA samples, reverse-transcribed from polyadenylated RNA obtained from human liver tissue. In addition to identifying many known and predicted genes, we found 10,595 transcribed sequences not detected by other methods. A large fraction of these are located in intergenic regions distal. from previously annotated genes and exhibit significant, homology to other mammalian proteins. C1 Yale Univ, Dept Mol Cellular & Dev Biol, New Haven, CT 06520 USA. NASA, Ames Res Ctr, Ctr Nanotechnol, Moffett Field, CA 94035 USA. Yale Univ, Dept Mol Biophys & Biochem, New Haven, CT 06520 USA. Eloret Corp, Sunnyvale, CA 94087 USA. Yale Univ, Sch Med, Dept Genet, New Haven, CT 06520 USA. RP Gerstein, M (reprint author), Yale Univ, Dept Mol Cellular & Dev Biol, New Haven, CT 06520 USA. EM mark.gerstein@yale.edu; michael.snyder@yale.edu RI Bertone, Paul/A-6600-2013; OI Bertone, Paul/0000-0001-5059-4829; Rozowsky, Joel/0000-0002-3565-0762 FU NHGRI NIH HHS [P50 HG02357] NR 21 TC 595 Z9 636 U1 3 U2 32 PU AMER ASSOC ADVANCEMENT SCIENCE PI WASHINGTON PA 1200 NEW YORK AVE, NW, WASHINGTON, DC 20005 USA SN 0036-8075 J9 SCIENCE JI Science PD DEC 24 PY 2004 VL 306 IS 5705 BP 2242 EP 2246 DI 10.1126/science.1103388 PG 5 WC Multidisciplinary Sciences SC Science & Technology - Other Topics GA 882PE UT WOS:000225950000042 PM 15539566 ER PT J AU Mlynczak, MG Martin-Torres, FJ Johnson, DG Kratz, DP Traub, WA Jucks, K AF Mlynczak, MG Martin-Torres, FJ Johnson, DG Kratz, DP Traub, WA Jucks, K TI Observations of the O(P-3) fine structure line at 63 mu m in the upper mesosphere and lower thermosphere SO JOURNAL OF GEOPHYSICAL RESEARCH-SPACE PHYSICS LA English DT Article DE atomic oxygen; far-infrared; oxygen emissions; thermospheric energy balance ID ATOMIC OXYGEN; TRANSLATIONAL TEMPERATURE; TERRESTRIAL THERMOSPHERE; UPPER-ATMOSPHERE; MIDDLE; ENERGETICS; EMISSION AB Observations of the O(P-3) fine structure line at 63 mum originating in the upper mesosphere and lower thermosphere have been obtained by the far-infrared spectrometer (FIRS-2) instrument, a Fourier transform spectrometer that flies periodically on high-altitude balloons. FIRS-2 primarily observes stratospheric ozone photochemistry using the technique of limb emission spectroscopy. As part of the routine operation of FIRS-2, up-looking views are made, during which the emission from the atomic oxygen is recorded. Using the Mass Spectrometer Incoherent Scatter (MSIS) empirical model to provide temperature and atomic oxygen concentrations, we compute radiances for comparison with the FIRS-2 observations. The computed radiances agree with the FIRS-2 measurements, which encompass 31 observations during nine flights over a span of 14 years, to within 10% on average, with 23 of the 31 observations agreeing to within measurement and calculation uncertainty. The consistency between the observed and computed radiances suggests that the MSIS model provides a reasonably accurate representation of temperature and atomic oxygen in the upper mesosphere and lower thermosphere. C1 NASA, Climate Sci Branch, Langley Res Ctr, Hampton, VA 23681 USA. NASA, Analyt Mat & Serv Corp, Langley Res Ctr, Hampton, VA 23681 USA. Harvard Smithsonian Ctr Astrophys, Cambridge, MA 02138 USA. RP Mlynczak, MG (reprint author), NASA, Climate Sci Branch, Langley Res Ctr, 21 Langley Blvd,Mail Stop 420, Hampton, VA 23681 USA. EM m.g.mlynczak@nasa.gov RI Mlynczak, Martin/K-3396-2012; Johnson, David/F-2376-2015; Martin-Torres, Francisco Javier/G-6329-2015 OI Johnson, David/0000-0003-4399-5653; Martin-Torres, Francisco Javier/0000-0001-6479-2236 NR 17 TC 8 Z9 8 U1 0 U2 2 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 0148-0227 J9 J GEOPHYS RES-SPACE JI J. Geophys. Res-Space Phys. PD DEC 23 PY 2004 VL 109 IS A12 AR A12306 DI 10.1029/2004JA010595 PG 7 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 883QE UT WOS:000226028600001 ER PT J AU Gutsev, GL Mochena, MA Bauschlicher, CW AF Gutsev, GL Mochena, MA Bauschlicher, CW TI Structure and properties of Fe-4 with different coverage by C and CO SO JOURNAL OF PHYSICAL CHEMISTRY A LA English DT Article ID ELECTRONIC POPULATION ANALYSIS; MOLECULAR WAVE FUNCTIONS; WALLED CARBON NANOTUBES; DENSITY-FUNCTIONAL THEORY; GAUSSIAN-BASIS SETS; IRON CLUSTERS; HIPCO PROCESS; GAS-PHASE; PHOTOELECTRON-SPECTROSCOPY; IONIZATION ENERGIES AB The electronic and geometrical structure of neutral and singly charged Fe4C2, Fe4C(CO), Fe-4(CO)(2), Fe4C2-CO, Fe4C(CO)(2), Fe4C3, and Fe-4(CO)(3) are studied using density functional theory with a generalized gradient approximation. It is found that the Fe4C2 and Fe4C2(CO) species possess two isomers with separated and dimerized carbon atoms. The latter isomers are lower in total energy by similar to0.3 eV. The Fe4C3 species possess three isomers corresponding to: a C-2 dimer and one separated carbon atom (the lowest energies), a C-3 trimer (intermediate energies), and three separated carbon atoms (the highest energies). The lowest energy dissociation channel corresponds to the loss of CO, except for Fe-4(CO)(2) and Fe4C(CO)(2)(+), where the loss of carbon dioxide is the lowest. The computed total energies are used to estimate the energetics of the Boudouard-like disproportionation reactions, Fe4Cn(CO)(m) + CO --> Fe4Cn+1(CO)(m-1) + CO2. It is found that the most exothermic reaction in the series is Fe4C(CO)(+) + CO --> Fe4C2+ + CO2 (by similar to0.3 eV). C1 Florida A&M Univ, Dept Phys, Tallahassee, FL 32307 USA. NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Gutsev, GL (reprint author), Florida A&M Univ, Dept Phys, Tallahassee, FL 32307 USA. EM gennady.gutsev@famu.edu NR 39 TC 13 Z9 13 U1 2 U2 6 PU AMER CHEMICAL SOC PI WASHINGTON PA 1155 16TH ST, NW, WASHINGTON, DC 20036 USA SN 1089-5639 J9 J PHYS CHEM A JI J. Phys. Chem. A PD DEC 23 PY 2004 VL 108 IS 51 BP 11409 EP 11418 DI 10.1021/jp046635x PG 10 WC Chemistry, Physical; Physics, Atomic, Molecular & Chemical SC Chemistry; Physics GA 880OK UT WOS:000225798900033 ER PT J AU Ackerman, AS Kirkpatrick, MP Stevens, DE Toon, OB AF Ackerman, AS Kirkpatrick, MP Stevens, DE Toon, OB TI The impact of humidity above stratiform clouds on indirect aerosol climate forcing SO NATURE LA English DT Article ID MARINE BOUNDARY-LAYER; TOP ENTRAINMENT INSTABILITY; SHIP TRACKS; STRATOCUMULUS; MICROPHYSICS; ALBEDO; MODEL; PARAMETERIZATION; SUSCEPTIBILITY; SIMULATION AB Some of the global warming from anthropogenic greenhouse gases is offset by increased reflection of solar radiation by clouds with smaller droplets that form in air polluted with aerosol particles that serve as cloud condensation nuclei(1). The resulting cooling tendency, termed the indirect aerosol forcing, is thought to be comparable in magnitude to the forcing by anthropogenic CO2, but it is difficult to estimate because the physical processes that determine global aerosol and cloud populations are poorly understood(2). Smaller cloud droplets not only reflect sunlight more effectively, but also inhibit precipitation, which is expected to result in increased cloud water(3,4). Such an increase in cloud water would result in even more reflective clouds, further increasing the indirect forcing. Marine boundary-layer clouds polluted by aerosol particles, however, are not generally observed to hold more water(5-7). Here we simulate stratocumulus clouds with a fluid dynamics model that includes detailed treatments of cloud microphysics and radiative transfer. Our simulations show that the response of cloud water to suppression of precipitation from increased droplet concentrations is determined by a competition between moistening from decreased surface precipitation and drying from increased entrainment of overlying air. Only when the overlying air is humid or droplet concentrations are very low does sufficient precipitation reach the surface to allow cloud water to increase with droplet concentrations. Otherwise, the response of cloud water to aerosol-induced suppression of precipitation is dominated by enhanced entrainment of overlying dry air. In this scenario, cloud water is reduced as droplet concentrations increase, which diminishes the indirect climate forcing. C1 NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. Univ Tasmania, Hobart, Tas 7001, Australia. Lawrence Livermore Natl Lab, Livermore, CA 94552 USA. Univ Colorado, Boulder, CO 80309 USA. RP Ackerman, AS (reprint author), NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. EM andrew.ackerman@nasa.gov RI Ackerman, Andrew/D-4433-2012; OI Ackerman, Andrew/0000-0003-0254-6253; Kirkpatrick, Michael/0000-0002-7157-6440 NR 33 TC 266 Z9 273 U1 2 U2 37 PU NATURE PUBLISHING GROUP PI LONDON PA MACMILLAN BUILDING, 4 CRINAN ST, LONDON N1 9XW, ENGLAND SN 0028-0836 J9 NATURE JI Nature PD DEC 23 PY 2004 VL 432 IS 7020 BP 1014 EP 1017 DI 10.1038/nature03174 PG 4 WC Multidisciplinary Sciences SC Science & Technology - Other Topics GA 881RL UT WOS:000225887000038 PM 15616559 ER PT J AU Anderson, JD Lau, EL Bird, MK Asmar, SW Clark, BC Giampieri, G Gilliland, KV Patzold, M AF Anderson, JD Lau, EL Bird, MK Asmar, SW Clark, BC Giampieri, G Gilliland, KV Patzold, M TI Stardust dynamic science at comet 81P/Wild 2 SO JOURNAL OF GEOPHYSICAL RESEARCH-PLANETS LA English DT Article DE Wild 2; Stardust; dynamic science; radio science; attitude control; DSN Doppler ID INNER DUST COMA; GIOTTO SPACECRAFT; GRIGG-SKJELLERUP; ENCOUNTER; NUCLEUS; HALLEY; JETS AB Radio Doppler data at X band (similar to8.4 GHz) and spacecraft attitude control data were obtained during the encounter with comet 81P/Wild 2. The Doppler data set an upper bound of 5 x 10(15) kg on the mass of the nucleus, about 100 times larger than theoretical estimates. The attitude control data indicate that a large dust particle with a mass in the range of 20 to 40 mg impacted the spacecraft about 15.5 s before closest approach. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. Univ Bonn, Inst Radioastron, D-53121 Bonn, Germany. Lockheed Martin, Denver, CO 80201 USA. Univ London Imperial Coll Sci Technol & Med, Dept Math, London SW7 2BW, England. Univ Cologne, Inst Geophys & Meteorol, D-50923 Cologne, Germany. RP Anderson, JD (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM john.d.anderson@jpl.nasa.gov NR 17 TC 3 Z9 3 U1 0 U2 1 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 2169-9097 EI 2169-9100 J9 J GEOPHYS RES-PLANET JI J. Geophys. Res.-Planets PD DEC 22 PY 2004 VL 109 IS E12 AR E12S05 DI 10.1029/2004JE002323 PG 7 WC Geochemistry & Geophysics SC Geochemistry & Geophysics GA 883PX UT WOS:000226027700004 ER PT J AU Duxbury, TC Newburn, RL Brownlee, DE AF Duxbury, TC Newburn, RL Brownlee, DE TI Comet 81P Wild 2 size, shape, and orientation SO JOURNAL OF GEOPHYSICAL RESEARCH-PLANETS LA English DT Article DE comet; Wild 2; Stardust project; size; shape; orientation ID SURFACE; CAMERA AB Spectacular images, taken during the flyby of 81P/Wild 2 by the NASA Stardust spacecraft, were used to determine that the shape of the comet 81P/ Wild 2 nucleus can be reasonably modeled as a triaxial ellipse having radii 1.65 x 2.00 x 2.75 km +/- 0.05 km (1sigma). The shortest axis, considered the rotational axis, has a right ascension of 110degrees and a declination of -13degrees. The longest axis, used to define zero longitude, has an argument of prime meridian angle of 155degrees. All angles use the IAU definitions, are relative to the Earth Mean Equator and Vernal Equinox of J2000 and have uncertainties of +/-3degrees (1sigma). The rotational axis was pointed 65degrees from the sun during the Stardust encounter of 81P/Wild 2, making an area within 25degrees of the spin axis in continual sunlight and the apparent source of a few major jets. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. Univ Washington, Dept Astron, Seattle, WA 98195 USA. RP Duxbury, TC (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM tduxbury@jpl.nasa.gov NR 18 TC 10 Z9 10 U1 0 U2 1 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 0148-0227 J9 J GEOPHYS RES-PLANET JI J. Geophys. Res.-Planets PD DEC 22 PY 2004 VL 109 IS E12 AR E12S02 DI 10.1029/2004JE002316 PG 4 WC Geochemistry & Geophysics SC Geochemistry & Geophysics GA 883PX UT WOS:000226027700001 ER PT J AU Green, SF McDonnell, JAM McBride, N Colwell, MTSH Tuzzolino, AJ Economou, TE Tsou, P Clark, BC Brownlee, DE AF Green, SF McDonnell, JAM McBride, N Colwell, MTSH Tuzzolino, AJ Economou, TE Tsou, P Clark, BC Brownlee, DE TI The dust mass distribution of comet 81P/Wild 2 SO JOURNAL OF GEOPHYSICAL RESEARCH-PLANETS LA English DT Article DE cometary dust; Stardust; 81P/Wild 2; Dust Flux; DFMI ID FLUX MONITOR INSTRUMENT; GRIGG-SKJELLERUP; STARDUST; P/HALLEY; ENCOUNTER; NUCLEUS; GIOTTO; SPACECRAFT; MISSION; WILD-2 AB The Dust Flux Monitor Instrument ( DFMI) made direct measurements of the dust environment in the mass range 10(-14) < m < 10(-5) kg at comet 81P/Wild 2 during the Stardust flyby on 2 January 2004. We describe the techniques for derivation of the particle mass distribution, including updated calibration for the acoustic subsystem. The dust coma is characterized by "swarms'' and "bursts'' of particles with large variations of flux on small spatial scales, which may be explained by jets and fragmentation. The mass of the dust coma is dominated by larger particles, as was found for comets 1P/Halley and 26P/Grigg-Skjellerup. However, almost 80% of the particles were detected many minutes after closest approach at a distance of similar to4000 km, where small grains dominated the detected mass flux. The mass distribution varies on small spatial scales with location in the coma, consistent with the jets and fragmentation inferred from the highly heterogeneous dust spatial distribution. The cumulative mass distribution index alpha (where the number of particles of mass m or larger, N(m) proportional to m(-alpha)) in the coma ranges from 0.3 to 1.1. It is possible that jets and fragmentation occur in all comets but have not previously been well observed due to the limitations of detectors and flyby geometry. We estimate that 2800 +/- 500 particles of diameter 15 mum or larger impacted the aerogel collectors, the largest being similar to6 x 10(-7) kg (diameter similar to 1 mm), which dominates the total collected mass. Of these, only 500 +/- 200, representing just 3% of the collected mass, originated in the far postencounter region. C1 Open Univ, Planetary & Space Sci Res Inst, Milton Keynes MK7 6AA, Bucks, England. Univ Chicago, Enrico Fermi Inst, Lab Astrophys & Space Res, Chicago, IL 60637 USA. CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. Lockheed Martin Space Syst, Denver, CO 80201 USA. Univ Washington, Dept Astron, Seattle, WA 98195 USA. RP Green, SF (reprint author), Open Univ, Planetary & Space Sci Res Inst, Walton Hall, Milton Keynes MK7 6AA, Bucks, England. EM s.f.green@open.ac.uk RI Green, Simon/C-7408-2009 NR 26 TC 28 Z9 28 U1 0 U2 2 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 0148-0227 J9 J GEOPHYS RES-PLANET JI J. Geophys. Res.-Planets PD DEC 22 PY 2004 VL 109 IS E12 AR E12S04 DI 10.1029/2004JE002318 PG 13 WC Geochemistry & Geophysics SC Geochemistry & Geophysics GA 883PX UT WOS:000226027700003 ER PT J AU Tsou, P Brownlee, DE Anderson, JD Bhaskaran, S Cheuvront, AR Clark, BC Duxbury, T Economou, T Green, SF Hanner, MS Horz, F Kissel, J McDonnell, JAM Newburn, RL Ryan, RE Sandford, SA Sekanina, Z Tuzzolino, AJ Vellinga, JM Zolensky, ME AF Tsou, P Brownlee, DE Anderson, JD Bhaskaran, S Cheuvront, AR Clark, BC Duxbury, T Economou, T Green, SF Hanner, MS Horz, F Kissel, J McDonnell, JAM Newburn, RL Ryan, RE Sandford, SA Sekanina, Z Tuzzolino, AJ Vellinga, JM Zolensky, ME TI Stardust encounters comet 81P Wild 2 SO JOURNAL OF GEOPHYSICAL RESEARCH-PLANETS LA English DT Article DE comet sample return; Stardust mission; Wild 2 ID DUST FLUX MONITOR; MISSION; INSTRUMENT; ANALYZER; NUCLEUS; RETURN AB Stardust successfully encountered comet 81P/Wild 2 on 2 January 2004 at a distance of 236.4 +/- 1 km. All encounter investigations acquired valuable new and surprising findings. The time-of-flight spectrometer registered 29 spectra during flyby and measured the first negative ion mass spectra of cometary particles. The dust detectors recorded particles over a broad mass range, 10(-11) to 10(-4) g. Unexpectedly, the dust distribution along Stardust's flight path was far from uniform, but instead occurred in short "bursts,'' suggesting in-flight breakup of fragments ejected from the nucleus. High-resolution, stunning images of the Wild 2 surface show a diverse and complex variety of landforms not seen from comets 1P/Halley and 19P/Borrelly or icy satellites of the outer solar system. Longer-exposure images reveal large numbers of jets projected nearly around the entire perimeter of the nucleus, many of which appear to be highly collimated. A triaxial ellipsoidal fit of the Wild 2 nucleus images yields the principal nucleus radii of 1.65 x 2.00 x 2.75 km (+/-0.05 km). The orientations and source locations on the nucleus surface of 20 highly collimated and partially overlapping jets have been traced. There is every indication that the expected samples were successfully collected from the Wild 2 coma and are poised for a return to Earth on 15 January 2006. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. Univ Washington, Dept Astron, Seattle, WA 98195 USA. Lockheed Martin Space Syst, Denver, CO 80201 USA. Univ Chicago, Enrico Fermi Inst, Chicago, IL 60637 USA. Open Univ, Planetary & Space Sci Res Inst, Milton Keynes MK7 6AA, Bucks, England. NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. Max Planck Inst Sonnensyst Forsch, D-37191 Katlenburg Lindau, Germany. NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Tsou, P (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM peter.tsou@jpl.nasa.gov RI Green, Simon/C-7408-2009 NR 20 TC 19 Z9 20 U1 1 U2 2 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 2169-9097 EI 2169-9100 J9 J GEOPHYS RES-PLANET JI J. Geophys. Res.-Planets PD DEC 22 PY 2004 VL 109 IS E12 AR E12S01 DI 10.1029/2004JE002317 PG 8 WC Geochemistry & Geophysics SC Geochemistry & Geophysics GA 883PX UT WOS:000226027700002 ER PT J AU Jaworske, DA Raack, T AF Jaworske, DA Raack, T TI Cermet coatings for solar Stirling space power SO THIN SOLID FILMS LA English DT Article; Proceedings Paper CT 31st International Conference on Metallurgical Coatings and Thin Films CY APR 19-23, 2004 CL San Diego, CA SP AVS Sci & Technol Soc, Adv Surface Engn Div DE cermet coatings; solar Stirling space power; ceramic matrix AB Cermet coatings, molecular mixtures of metal and ceramic, are being considered for the heat inlet surface of a solar Stirling space power convertor. The role of the cermet coating is to absorb as much of the incident solar energy as possible. The ability to mix metal and ceramic at the atomic level offers the opportunity to tailor the composition and the solar absorptance of these coatings. Several candidate cermet coatings were created and their solar absorptance was characterized as-manufactured and after exposure to elevated temperatures. Coating composition was purposely varied through the thickness of the coating. As a consequence of changing composition, islands of metal are thought to form in the ceramic matrix. Computer modeling indicated that diffusion of the metal atoms played an important role in island formation while the ceramic was important in locking the islands in place. Much of the solar spectrum is absorbed as it passes through this labyrinth. (C) 2004 Elsevier B.V. All rights reserved. C1 NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. Northwestern Univ, Evanston, IL 60208 USA. RP Jaworske, DA (reprint author), NASA, Glenn Res Ctr, Mail Stop 309-2,21000 Brook Pk Rd, Cleveland, OH 44135 USA. EM Donald.A.Jaworske@nasa.gov NR 8 TC 3 Z9 3 U1 0 U2 2 PU ELSEVIER SCIENCE SA PI LAUSANNE PA PO BOX 564, 1001 LAUSANNE, SWITZERLAND SN 0040-6090 J9 THIN SOLID FILMS JI Thin Solid Films PD DEC 22 PY 2004 VL 469 SI SI BP 24 EP 30 DI 10.1016/j.tsf.2004.06.181 PG 7 WC Materials Science, Multidisciplinary; Materials Science, Coatings & Films; Physics, Applied; Physics, Condensed Matter SC Materials Science; Physics GA 879NK UT WOS:000225724300006 ER PT J AU Miller, RL Perlwitz, J Tegen, I AF Miller, RL Perlwitz, J Tegen, I TI Feedback upon dust emission by dust radiative forcing through the planetary boundary layer SO JOURNAL OF GEOPHYSICAL RESEARCH-ATMOSPHERES LA English DT Article ID GENERAL-CIRCULATION MODEL; SOIL DUST; MINERAL DUST; OPTICAL-THICKNESS; GODDARD-INSTITUTE; REFRACTIVE-INDEX; EASTERLY WAVES; SAHARAN DUST; SOURCE AREAS; GISS-GCM AB Large changes to the amount of airborne soil particles (or "mineral dust'' aerosol) inferred from the climate record raise the question of whether radiative forcing by dust particles amplifies or else diminishes these changes. A previous study with an atmospheric general circulation model (AGCM) indicates that dust radiative forcing in the present-day climate reduces emission of dust into the atmosphere. Here, we interpret this reduction as an interaction between dust radiative forcing and the planetary boundary layer (PBL). By reducing sunlight incident upon the surface, dust decreases the turbulent flux of sensible heat into the atmosphere. This reduces turbulent mixing within the PBL, along with the downward transport of momentum to the surface, resulting in a decrease of surface wind speed and dust emission. We illustrate this mechanism by comparing the diurnal cycle of emission simulated by two versions of an AGCM, one containing dust radiative forcing, and the other with this forcing set to zero. At some of the most productive source regions, morning emission is reduced in proportion to the surface radiative forcing. We suggest that this negative feedback is underestimated by the AGCM. C1 Columbia Univ, Dept Appl Phys & Appl Math, New York, NY 10025 USA. NASA, Goddard Inst Space Studies, New York, NY 10025 USA. Max Planck Inst Biogeochem, Jena, Germany. RP Columbia Univ, Dept Appl Phys & Appl Math, 2880 Broadway, New York, NY 10025 USA. EM rlm15@columbia.edu; jp544@columbia.edu; itegen@tropos.de RI Miller, Ron/E-1902-2012 NR 59 TC 55 Z9 56 U1 2 U2 7 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 2169-897X EI 2169-8996 J9 J GEOPHYS RES-ATMOS JI J. Geophys. Res.-Atmos. PD DEC 21 PY 2004 VL 109 IS D24 AR D24209 DI 10.1029/2004JD004912 PG 17 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA 883PO UT WOS:000226026800003 ER EF