FN Thomson Reuters Web of Science™ VR 1.0 PT J AU Zlotnicki, V Wahr, J Fukumori, I Song, YT AF Zlotnicki, Victor Wahr, John Fukumori, Ichiro Song, Yuhe T. TI Antarctic circumpolar current transport variability during 2003-05 from GRACE SO JOURNAL OF PHYSICAL OCEANOGRAPHY LA English DT Article ID BOTTOM PRESSURE MEASUREMENTS; GLOBAL OCEAN CIRCULATION; TIME-VARIABLE GRAVITY; DRAKE PASSAGE; CLIMATE EXPERIMENT; ANNULAR MODE; SEA-LEVEL; WIND; SURFACE; EARTH AB Gravity Recovery and Climate Experiment ( GRACE) gravity data spanning January 2003 - November 2005 are used as proxies for ocean bottom pressure ( BP) averaged over 1 month, spherical Gaussian caps 500 km in radius, and along paths bracketing the Antarctic Circumpolar Current's various fronts. The GRACE BP signals are compared with those derived from the Estimating the Circulation and Climate of the Ocean ( ECCO) ocean modeling - assimilation system, and to a non-Boussinesq version of the Regional Ocean Model System ( ROMS). The discrepancy found between GRACE and the models is 1.7 cm(H2O) ( 1 cm(H2O) similar to 1 hPa), slightly lower than the 1.9 cm(H2O) estimated by the authors independently from propagation of GRACE errors. The northern signals are weak and uncorrelated among basins. The southern signals are strong, with a common seasonality. The seasonal cycle GRACE data observed in the Pacific and Indian Ocean sectors of the ACC are consistent, with annual and semiannual amplitudes of 3.6 and 0.6 cm(H2O) ( 1.1 and 0.6 cm(H2O) with ECCO), the average over the full southern path peaks ( stronger ACC) in the southern winter, on days of year 197 and 97 for the annual and semiannual components, respectively; the Atlantic Ocean annual peak is 20 days earlier. An approximate conversion factor of 3.1 Sv ( Sv equivalent to 106 m(3) s(-1)) of barotropic transport variability per cm(H2O) of BP change is estimated. Wind stress data time series from the Quick Scatterometer ( QuikSCAT), averaged monthly, zonally, and over the latitude band 40 degrees - 65 degrees S, are also constructed and subsampled at the same months as with the GRACE data. The annual and semiannual harmonics of the wind stress peak on days 198 and 82, respectively. A decreasing trend over the 3 yr is observed in the three data types. C1 CALTECH, Jet Propuls Lab, Pasadena, CA 91125 USA. Univ Colorado, Cooperat Inst Res Environm Sci, Boulder, CO 80309 USA. Univ Colorado, Dept Phys, Boulder, CO 80309 USA. RP Zlotnicki, V (reprint author), JPL 300-323,4800 Oak Grp Dr, Pasadena, CA 91109 USA. EM victor.zlotnicki@jpl.nasa.gov NR 58 TC 26 Z9 28 U1 0 U2 3 PU AMER METEOROLOGICAL SOC PI BOSTON PA 45 BEACON ST, BOSTON, MA 02108-3693 USA SN 0022-3670 EI 1520-0485 J9 J PHYS OCEANOGR JI J. Phys. Oceanogr. PD FEB PY 2007 VL 37 IS 2 BP 230 EP 244 DI 10.1175/JPO3009.1 PG 15 WC Oceanography SC Oceanography GA 141DP UT WOS:000244558000009 ER PT J AU Fukumori, I Menemenlis, D Lee, T AF Fukumori, Ichiro Menemenlis, Dimitris Lee, Tong TI A near-uniform basin-wide sea level fluctuation of the Mediterranean Sea SO JOURNAL OF PHYSICAL OCEANOGRAPHY LA English DT Article ID STRAIT-OF-GIBRALTAR; ATMOSPHERIC-PRESSURE; FLOW-THROUGH; GENERAL-CIRCULATION; PACIFIC-OCEAN; BLACK-SEA; VARIABILITY; EXCHANGE; MODEL; ATLANTIC AB A new basin-wide oscillation of the Mediterranean Sea is identified and analyzed using sea level observations from the Ocean Topography Experiment ( TOPEX)/Poseidon satellite altimeter and a numerical ocean circulation model. More than 50% of the large-scale, nontidal, and non-pressure-driven variance of sea level can be attributed to this oscillation, which is nearly uniform in phase and amplitude across the entire basin. The oscillation has periods ranging from 10 days to several years and has a magnitude as large as 10 cm. The model suggests that the fluctuations are driven by winds at the Strait of Gibraltar and its neighboring region, including the Alboran Sea and a part of the Atlantic Ocean immediately to the west of the strait. Winds in this region force a net mass flux through the Strait of Gibraltar to which the Mediterranean Sea adjusts almost uniformly across its entire basin with depth-independent pressure perturbations. The wind-driven response can be explained in part by wind setup; a near-stationary balance is established between the along-strait wind in this forcing region and the sea level difference between the Mediterranean Sea and the Atlantic Ocean. The amplitude of this basin-wide wind-driven sea level fluctuation is inversely proportional to the setup region's depth but is insensitive to its width including that of Gibraltar Strait. The wind-driven fluctuation is coherent with atmospheric pressure over the basin and contributes to the apparent deviation of the Mediterranean Sea from an inverse barometer response. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Fukumori, I (reprint author), CALTECH, Jet Prop Lab, M-S 300-323,4800 Oak Grp Dr, Pasadena, CA 91109 USA. EM fukumori@jpl.nasa.gov NR 54 TC 36 Z9 36 U1 0 U2 3 PU AMER METEOROLOGICAL SOC PI BOSTON PA 45 BEACON ST, BOSTON, MA 02108-3693 USA SN 0022-3670 J9 J PHYS OCEANOGR JI J. Phys. Oceanogr. PD FEB PY 2007 VL 37 IS 2 BP 338 EP 358 DI 10.1175/JPO3016.1 PG 21 WC Oceanography SC Oceanography GA 141DP UT WOS:000244558000015 ER PT J AU Menemenlis, D Fukumori, I Lee, T AF Menemenlis, Dimitris Fukumori, Ichiro Lee, Tong TI Atlantic to Mediterranean sea level difference driven by winds near Gibraltar strait SO JOURNAL OF PHYSICAL OCEANOGRAPHY LA English DT Article ID ATMOSPHERIC-PRESSURE; MODEL; CIRCULATION; OCEAN; FLUCTUATIONS; VARIABILITY; TOPOGRAPHY; ALTIMETRY; EXCHANGE; FLOWS AB Observations and numerical simulations show that winds near Gibraltar Strait cause an Atlantic Ocean to Mediterranean Sea sea level difference of 20 cm peak to peak with a 3-cm standard deviation for periods of days to years. Theoretical arguments and numerical experiments establish that this wind-driven sea level difference is caused in part by storm surges due to alongshore winds near the North African coastline on the Atlantic side of Gibraltar. The fraction of the Moroccan coastal current offshore of the 284-m isobath is deflected across Gibraltar Strait, west of Camarinal Sill, resulting in a geostrophic surface pressure gradient that contributes to a sea level difference at the stationary limit. The sea level difference is also caused in part by the along-strait wind setup, with a contribution proportional to the along- strait wind stress and to the length of Gibraltar Strait and adjoining regions and inversely proportional to its depth. In the 20 - 360-day band, average transfer coefficients between the Atlantic - Alboran sea level difference and surface wind stress at 36 degrees N, 6.5 degrees W, estimated from barometrically corrected Ocean Topography Experiment ( TOPEX)/Poseidon data and NCEP - NCAR reanalysis data, are 0.10 +/- 0.04 m Pa(-1) with 1 +/- 5-day lag and 0.19 +/- 0.08 m Pa(-1) with 5 +/- 4-day lag for the zonal and meridional wind stresses, respectively. This transfer function is consistent with equivalent estimates derived from a 1992 - 2003 high-resolution barotropic simulation forced by the NCEP - NCAR wind stress. The barotropic simulation explains 29% of the observed Atlantic - Alboran sea level difference in the 20 - 360-day band. In turn, the Alboran and Mediterranean mean sea level time series are highly correlated, rho = 0.7 in the observations and rho = 0.8 in the barotropic simulation, hence providing a pathway for winds near Gibraltar Strait to affect the mean sea level of the entire Mediterranean. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Menemenlis, D (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,300-323 Mail Stop, Pasadena, CA 91109 USA. EM menemenlis@jpl.nasa.gov NR 40 TC 23 Z9 23 U1 1 U2 3 PU AMER METEOROLOGICAL SOC PI BOSTON PA 45 BEACON ST, BOSTON, MA 02108-3693 USA SN 0022-3670 J9 J PHYS OCEANOGR JI J. Phys. Oceanogr. PD FEB PY 2007 VL 37 IS 2 BP 359 EP 376 DI 10.1175/JPO3015.1 PG 18 WC Oceanography SC Oceanography GA 141DP UT WOS:000244558000016 ER PT J AU Niu, JG Yang, P Huang, HL Davies, JE Li, J Baum, BA Hu, YX AF Niu, Jianguo Yang, Ping Huang, Hung-Lung Davies, James E. Li, Jun Baum, Bryan A. Hu, Yong X. TI A fast infrared radiative transfer model for overlapping clouds SO JOURNAL OF QUANTITATIVE SPECTROSCOPY & RADIATIVE TRANSFER LA English DT Article DE infrared radiative transfer; fast code; cloud; single scattering properties of cloud ID LIGHT-SCATTERING; DIELECTRIC PARTICLES; MULTIPLE-SCATTERING; OPTICAL-THICKNESS; ICE PARTICLES; ATMOSPHERES; RETRIEVAL; ABSORPTION; CIRRUS; MEDIA AB A fast infrared radiative transfer model (FIRTM2) appropriate for application to both single-layered and overlapping cloud situations is developed for simulating the outgoing infrared spectral radiance at the top of the atmosphere (TOA). In FIRTM2 a pre-computed library of cloud reflectance and transmittance values is employed to account for one or two cloud layers, whereas the background atmospheric optical thickness due to gaseous absorption can be computed from a clear-sky radiative transfer model. FIRTM2 is applicable to three atmospheric conditions: (1) clear-sky, (2) single-layered ice or water cloud, and (3) two simultaneous cloud layers in a column (e.g., ice cloud overlying water cloud). Moreover, F1RTM2 outputs the derivatives (i.e., Jacobians) of the TOA brightness temperature with respect to cloud optical thickness and effective particle size. Sensitivity analyses have been carried out to assess the performance of FIRTM2 for two spectral regions, namely the longwave (LW) band (587.3-1179.5 cm(-1)) and the short-to-medium wave (SMW) band (1180.1-2228.9 cm(-1)). The assessment is carried out in terms of brightness temperature differences (BTD) between FIRTM2 and the well-known discrete ordinates radiative transfer model (DISORT), henceforth referred to as BTD (F-D). The BTD (F-D) values for single-layered clouds are generally less than 0.8 K. For the case of two cloud layers (specifically ice cloud over water cloud), the BTD (F-D) values are also generally less than 0.8 K except for the SMW band for the case of a very high altitude (> 15 km) cloud comprised of small ice particles. Note that for clear-sky atmospheres, FIRTM2 reduces to the clear-sky radiative transfer model that is incorporated into FIRTM2, and the errors in this case are essentially those of the clear-sky radiative transfer model. (c) 2006 Elsevier Ltd. All rights reserved. C1 Texas A&M Univ, Dept Atmospher Sci, College Stn, TX 77843 USA. Univ Wisconsin, Cooperat Inst Satellite Study, Madison, WI 53706 USA. NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Yang, P (reprint author), Texas A&M Univ, Dept Atmospher Sci, College Stn, TX 77843 USA. EM pyang@ariel.met.tamu.edu RI Yang, Ping/B-4590-2011; Baum, Bryan/B-7670-2011; Niu, Jianguo/G-1325-2012; Hu, Yongxiang/K-4426-2012 OI Baum, Bryan/0000-0002-7193-2767; NR 27 TC 19 Z9 19 U1 0 U2 1 PU PERGAMON-ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0022-4073 J9 J QUANT SPECTROSC RA JI J. Quant. Spectrosc. Radiat. Transf. PD FEB PY 2007 VL 103 IS 3 BP 447 EP 459 DI 10.1016/j.jqsrt.2006.05.009 PG 13 WC Optics; Spectroscopy SC Optics; Spectroscopy GA 112XU UT WOS:000242562100002 ER PT J AU Drouin, BJ AF Drouin, Brian J. TI Submillimeter measurements of N-2 and air broadening of hypochlorous acid SO JOURNAL OF QUANTITATIVE SPECTROSCOPY & RADIATIVE TRANSFER LA English DT Article DE hypochlorous acid; linewidths; pressure broadening; atmospheric spectra; lineshape ID MICROWAVE SPECTRUM; INFRARED-SPECTRUM; HOCL; HO2; SPECTROSCOPY; TEMPERATURE; MILLIMETER; HCL; CLO AB The pressure induced broadening of a several 'Q(0) pure rotational transitions of hypochlorous acid, HOCl, have been measured as a function of temperature. This set of rotational transitions is the dominant feature of the submillimeter spectrum in the 500 mu m range where several remote sensing instruments currently operate. Additional features throughout the submillimeter spectrum have been recorded at the full-resolution of the room temperature Doppler linewidth using multiplier chains in the 110-500 mu m wavelengths. (c) 2006 Elsevier Ltd. All rights reserved. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Drouin, BJ (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. EM brian.j.drouin@jpl.nasa.gov NR 21 TC 5 Z9 5 U1 0 U2 0 PU PERGAMON-ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0022-4073 J9 J QUANT SPECTROSC RA JI J. Quant. Spectrosc. Radiat. Transf. PD FEB PY 2007 VL 103 IS 3 BP 558 EP 564 DI 10.1016/j.jqsrt.2006.07.007 PG 7 WC Optics; Spectroscopy SC Optics; Spectroscopy GA 112XU UT WOS:000242562100009 ER PT J AU Ma, Q Tipping, RH Boulet, C AF Ma, Q. Tipping, R. H. Boulet, C. TI Modification of the Robert-Bonamy formalism in calculating Lorentzian half-widths and shifts SO JOURNAL OF QUANTITATIVE SPECTROSCOPY & RADIATIVE TRANSFER LA English DT Article DE Lorentzian half-widths and shifts; Robert-Bonamy formalism ID ASYMMETRIC-TOP MOLECULES; ROTATION-VIBRATION LINES; TEMPERATURE-DEPENDENCE; FUNDAMENTAL BANDS; SPECTRAL-LINES; LINEWIDTHS; H2O; HCL; RELAXATION; RANGE AB We have found an invalid assumption in the Robert-Bonamy formalism that has been widely used for calculating Lorentzian spectral line half-widths and shifts for decades. The problem results in their derivation where they assumed the cumulant expansion can be used to evaluate the Liouville matrix element << j2i2 vertical bar(S) over cap vertical bar j2i2 >>. At first sight, their assumption appears to be correct because this matrix element is diagonal in the Liouville space and as a result, it looks like that a basic requirement in applying the cumulant expansion is satisfied. However, by decomposing it into two Hilbert matrix elements associated with S-1 and S-F ((S) over cap = S1S*(F)), respectively, we have found that neither of these is diagonal in Hilbert space. Therefore, their assumption is not valid and their expressions for the half-widths and shifts are incorrect. We have found by choosing an average over the internal degrees of the bath molecule as the average in the cumulant expansion, one is able to apply this expansion properly and obtain the correct expressions. Numerical calculations show new half-width and shift values differ from previous ones, and the stronger the interaction between two molecules is, the larger these differences are. (c) 2006 Elsevier Ltd. All rights reserved. C1 Univ Alabama, Dept Phys & Astron, Tuscaloosa, AL 35487 USA. NASA, Goddard Inst Space Studies, New York, NY 10025 USA. Columbia Univ, Dept Appl Phys & Appl Math, New York, NY 10025 USA. Univ Paris 11, CNRS, UPR 3361, Photophys Mol Lab, F-91405 Orsay, France. RP Tipping, RH (reprint author), Univ Alabama, Dept Phys & Astron, Tuscaloosa, AL 35487 USA. EM rtipping@bama.ua.edu NR 22 TC 26 Z9 27 U1 1 U2 5 PU PERGAMON-ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0022-4073 J9 J QUANT SPECTROSC RA JI J. Quant. Spectrosc. Radiat. Transf. PD FEB PY 2007 VL 103 IS 3 BP 588 EP 596 DI 10.1016/j.jqsrt.2006.08.001 PG 9 WC Optics; Spectroscopy SC Optics; Spectroscopy GA 112XU UT WOS:000242562100012 ER PT J AU Stoner, AW Spencer, ML Ryer, CH AF Stoner, Allan W. Spencer, Mara L. Ryer, Clifford H. TI Flatfish-habitat associations in Alaska nursery grounds: Use of continuous video records for multi-scale spatial analysis SO JOURNAL OF SEA RESEARCH LA English DT Article; Proceedings Paper CT 6th International Symposium on Flatfish Ecology CY OCT 20-25, 2005 CL Kyoto, JAPAN DE habitat complexity; sediment; rock sole; generalized additive models; GIS ID GENERALIZED ADDITIVE-MODELS; WINTER FLOUNDER; BERING-SEA; PSEUDOPLEURONECTES-AMERICANUS; ESTIMATING ABUNDANCE; JUVENILE FLATFISHES; CONTINENTAL-SHELF; ROCK SOLE; FISHES; AREA AB Flatfish distributions have traditionally been described in terms of depth, temperature, and sediment characteristics, but other environmental variables may be important depending upon spatial scale. Surveys for age-0 northern rock sole (Lepidopsetta polyxystra) were conducted in five near-shore nursery sites at Kodiak Island, Alaska, using a towed camera sled integrated with navigational data. The continuous record of fish density and habitat features made possible a spatially comprehensive analysis of fish-habitat associations at several spatial scales, ranging from tens of kilometres to less than I in. A combination of multivariate statistical interpretation and geographic information systems (GIS) revealed that the distribution of juvenile rock sole was associated with environmental variables and spatial scales that are not normally detectable with usual flatfish- and habitat-sampling methods (i.e., trawls and grabs). Generalized additive models (GAM) incorporating habitat variables determined from video provided large improvements over models using only the traditional variables such as depth and sediment type. At the broadest (regional) scale of analysis, combinations of sediment composition, surface bedform, temperature, and density of worm tubes provided the best model for rock sole density. Within-nursery variation in fish density was modelled best with depth, habitat structural complexity created by emergent fauna and macroalgae, and worm tube density. At the microhabitat scale (< I in), there was little evidence of direct contact between rock sole and structures such as shell or algae. Rather, they were loosely associated on a scale tens of metres. This study showed that spatially comprehensive surveys can be conducted with towed camera systems and without the need for sediment grab samples. This approach yields detailed habitat information for fishes and the opportunity for landscape analysis of spatial patterns that will be important in conserving critical habitats for flatfishes and other fish species. (c) 2006 Elsevier B.V. All rights reserved. C1 NOAA, Fisheries Behav Ecol Program, Alaska Fisheries Sci Ctr, Natl Marine Fisheries Serv, Newport, OR 97365 USA. RP Stoner, AW (reprint author), NOAA, Fisheries Behav Ecol Program, Alaska Fisheries Sci Ctr, Natl Marine Fisheries Serv, 2030 S Marine Sci Dr, Newport, OR 97365 USA. EM al.stoner@noaa.gov NR 39 TC 40 Z9 44 U1 1 U2 22 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS SN 1385-1101 J9 J SEA RES JI J. Sea Res. PD FEB PY 2007 VL 57 IS 2-3 BP 137 EP 150 DI 10.1016/j.seares.2006.08.005 PG 14 WC Marine & Freshwater Biology; Oceanography SC Marine & Freshwater Biology; Oceanography GA 142GC UT WOS:000244636400006 ER PT J AU Wales, RC Shalin, VL Bass, DS AF Wales, Roxana C. Shalin, Valerie L. Bass, Deborah S. TI Requesting distant robotic action: An ontology for naming and action identification for planning on the Mars Exploration Rover mission. SO JOURNAL OF THE ASSOCIATION FOR INFORMATION SYSTEMS LA English DT Article DE ethnography; grounded theory; domain model; work practice; distributed work; planning technology; knowledge elicitation ID KNOWLEDGE ACQUISITION; EXPERT SYSTEMS AB This paper focuses on the development of a naming convention and the use of abbreviated names and a related ontology for science work and distant robotic action that comprise requests for a robotic rover during the NASA Mars Exploration Rover (MER) mission, run by the Jet Propulsion Laboratory (JPL). We demonstrate how abbreviated names and an associated ontology support sharing and identifying information among teams and software tools. An ontology of distant action must take into account a dynamic environment, changing in response to physical events and intentional actions, and reflect the influence of context on the meaning of action. The nascent domain of Martian tele-robotic science, in which specialists request work from a rover moving through a distant landscape, as well as the need to consider the interdisciplinary teams involved in completing that work, required an empirical approach. The formulation of this ontology used ethnographic methods and grounded theory to study human behavior and work practice with software tools. C1 NASA, Ames Res Ctr, SAIC, Moffett Field, CA 94035 USA. Wright State Univ, Dept Psychol, Dayton, OH 45435 USA. CALTECH, NASA, Jet Prop Lab, Pasadena, CA 91125 USA. SUNY Buffalo, Dept Ind Engn, Buffalo, NY 14260 USA. RP Wales, RC (reprint author), NASA, Ames Res Ctr, SAIC, Moffett Field, CA 94035 USA. EM rwales@google.com NR 46 TC 2 Z9 2 U1 0 U2 6 PU ASSOC INFORMATION SYSTEMS PI ATLANTA PA GEORGIA STATE UNIV, 35 BROAD STREET, STE 916-917, ATLANTA, GA 30303 USA SN 1536-9323 J9 J ASSOC INF SYST JI J. Assoc. Inf. Syst. PD FEB PY 2007 VL 8 IS 2 BP 75 EP 104 PG 30 WC Computer Science, Information Systems; Information Science & Library Science SC Computer Science; Information Science & Library Science GA 171MZ UT WOS:000246741400002 ER PT J AU Wang, JJ Li, XF Carey, LD AF Wang, Jian-Jian Li, Xiaofan Carey, Lawrence D. TI Evolution, structure, cloud microphysical, and surface rainfall processes of monsoon convection during the South China Sea monsoon experiment SO JOURNAL OF THE ATMOSPHERIC SCIENCES LA English DT Article ID ASIAN SUMMER MONSOON; SQUALL-LINE SYSTEM; TROPICAL CONVECTION; OCEANIC CONVECTION; MICROSCALE STRUCTURE; FRONTAL RAINBANDS; TOGA COARE; PHASE-III; PRECIPITATION; MODEL AB A two-dimensional cloud-resolving simulation is combined with dual-Doppler and polarimetric radar analysis to study the evolution, dynamic structure, cloud microphysics, and rainfall processes of monsoon convection observed during the South China Sea ( SCS) summer monsoon onset. Overall, the model simulations show many similarities to the radar observations. The rainband associated with the convection remains at a very stable position throughout its life cycle in the northern SCS. The reflectivity pattern exhibits a straight upward structure with little tilt. The positions of the convective, transition, and stratiform regions produced by the model are consistent with the observations. The major difference from the observations is that the model tends to overestimate the magnitude of updraft. As a result, the maximum reflectivity generated by the model appears at an elevated altitude. The surface rainfall processes and associated thermodynamic, dynamic, and cloud microphysical processes are examined by the model in terms of surface rainfall, temperature and moisture perturbations, circulations, and cloud microphysical budget. At the preformation and dissipating stages, although local vapor change and vapor convergence terms are the major contributors in determining rain rate, they cancel each other out and cause little rain. The vapor convergence/divergence is closely related to the lower-tropospheric updraft/subsidence during the early/late stages of the convection. During the formation and mature phases, vapor convergence term is in control of the rainfall processes. Meanwhile, water microphysical processes are dominant in these stages. The active vapor condensation process causes a large amount of raindrops through the collection of cloud water by raindrops. Ice microphysical processes including riming are negligible up to the mature phase but are dominant during the weakening stage. Cloud source/sink terms make some contributions to the rain rate at the formation and weakening stages, while the role of surface evaporation term is negligible throughout the life cycle of the convection. C1 NASA, Goddard Space Flight Ctr, Mesoscale Atmospher Proc Branch, Greenbelt, MD 20771 USA. Univ Maryland Baltimore Cty, Goddard Ctr Earth Sci & Technol, Baltimore, MD 21228 USA. NOAA, NESDIS, Ctr Satellite Applicat & Res, Camp Springs, MD USA. Joint Ctr Satellite Data Assimilat, Camp Springs, MD USA. Texas A&M Univ, Dept Atmospher Sci, College Stn, TX USA. RP Wang, JJ (reprint author), NASA, Goddard Space Flight Ctr, Mesoscale Atmospher Proc Branch, Greenbelt, MD 20771 USA. EM jjwang@agnes.gsfc.nasa.gov RI Li, Xiaofan/F-5605-2010; Li, Xiaofan/G-2094-2014 NR 43 TC 35 Z9 40 U1 2 U2 8 PU AMER METEOROLOGICAL SOC PI BOSTON PA 45 BEACON ST, BOSTON, MA 02108-3693 USA SN 0022-4928 J9 J ATMOS SCI JI J. Atmos. Sci. PD FEB PY 2007 VL 64 IS 2 BP 360 EP 380 DI 10.1175/JAS3852.1 PG 21 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA 137EU UT WOS:000244276600006 ER PT J AU Weinman, JA Kim, MJ AF Weinman, J. A. Kim, M. -J. TI A simple model of the millimeter-wave scattering parameters of randomly oriented aggregates of finite cylindrical ice hydrometeors SO JOURNAL OF THE ATMOSPHERIC SCIENCES LA English DT Article ID ANOMALOUS DIFFRACTION THEORY; CIRCULAR-CYLINDERS; SINGLE-SCATTERING; MICROWAVE-FREQUENCIES; NATURAL CLOUDS; PARTICLES; CRYSTALS; APPROXIMATION; PRECIPITATION; DIMENSION AB Spaceborne millimeter-wave radiometric measurements offer the potential to observe snowfall at high latitudes. A spaceborne W-band cloud radar on CloudSat has been able to observe snow. There is thus a need for a relatively simple representation of millimeter-wave scattering parameters of snow that can be incorporated into algorithms to retrieve snowfall from remotely sensed millimeter-wave brightness temperature measurements and for computing the millimeter-wave backscatter phase function of randomly oriented aggregates of ice prisms or columns. The extinction coefficients, asymmetry factors, and backscatter phase functions describing scattering by randomly oriented aggregates of elongated cylinders were computed from the discrete dipole approximation. These parameters were also computed by means of a T-matrix model applied to single blunt cylinders by employing a phase delay that only depended on the frequency and the ratio of the volume to the projected area of the cylindrical aggregates. These scattering parameters were fitted by empirical analytical functions that only depended on that phase delay. This permitted consideration of numerous aggregate shapes with far less computational effort than that required by the discrete dipole approximation. The results of this analysis were applied to measurements of millimeter-wave extinction, radar reflectivity, and snow size distributions obtained during the SNOW-TWO field experiment conducted by the U. S. Army in 1984. Although the simultaneity of the various measurements was not well documented, the theoretical results fell within the range of measurement uncertainty. Model results of the extinction coefficient and asymmetry factor needed to compute 183-GHz brightness temperatures measured by the NOAA Advanced Microwave Sounding Unit-B ( AMSU-B) radiometers are presented in the appendix. C1 Univ Washington, Dept Atmospher Sci, Seattle, WA 98195 USA. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Weinman, JA (reprint author), Univ Washington, Dept Atmospher Sci, Box 351640, Seattle, WA 98195 USA. EM Weinman@atmos.washington.edu NR 31 TC 12 Z9 12 U1 0 U2 3 PU AMER METEOROLOGICAL SOC PI BOSTON PA 45 BEACON ST, BOSTON, MA 02108-3693 USA SN 0022-4928 J9 J ATMOS SCI JI J. Atmos. Sci. PD FEB PY 2007 VL 64 IS 2 BP 634 EP 644 DI 10.1175/JAS3841.1 PG 11 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA 137EU UT WOS:000244276600022 ER PT J AU Yang, K Rasmy, M Rauniyar, S Koike, T Taniguchi, K Tamagawa, K Koudelova, P Kitsuregawa, M Nemoto, T Yasukawa, M Ikoma, E Bosilovich, MG Williams, S AF Yang, Kun Rasmy, Mohamed Rauniyar, Surendra Koike, Toshio Taniguchi, Kenji Tamagawa, Katsunori Koudelova, Petra Kitsuregawa, Masaru Nemoto, Toshihiro Yasukawa, Masaki Ikoma, Eiji Bosilovich, Michael G. Williams, Steve TI Initial CEOP-based review of the prediction skill of operational general circulation models and land surface models SO JOURNAL OF THE METEOROLOGICAL SOCIETY OF JAPAN LA English DT Article ID DIURNAL CYCLE; HYDROLOGIC-CYCLE; RADIATION; RAINFALL; PRECIPITATION; VARIABILITY; SCHEMES; CLIMATE; PROJECT; TAIWAN AB Using data archived in the Coordinated Enhanced Observing Period (CEOP) project, this study presents an initial evaluation of the prediction skill of five General Circulation Models (GCMs) and three Land Surface Models (LSMs). Comparisons between observations and the GCMs show that all the models are able to produce an afternoon peak in precipitation, but other major features are not well produced, including the total amount of precipitation, onset time of the afternoon peak, the early-evening low (around 1800 LST), and the partition between convective and stratiform rainfall. The ratios of evaporation to precipitation differ among the GCMs. Evaporation in some of the GCMs is even greater than precipitation, perhaps due to the model spin-up effect. In terms of the surface radiation budget, the GCMs generally over-predict downward shortwave radiation and under-predict downward longwave radiation; further investigations of the causes of these trends require cloudiness observations. In terms of the surface energy budget, the GCMs generally over-predict nighttime downward sensible heat fluxes and under-predict diurnal ranges of surface-air temperature difference, as heat transfer resistances are under-predicted. Finally, three offline LSMs driven by identical forcing are evaluated, and we note that the reproduction of surface temperature is not a sufficient condition for a LSM to reproduce surface energy partition. C1 Univ Tokyo, Dept Civil Engn, River Lab, Bunkyo Ku, Tokyo 1138656, Japan. Univ Tokyo, Dept Ind Sci, Tokyo 1138656, Japan. Univ Tokyo, Ctr Spatial Informat Sci, Tokyo 1138656, Japan. NASA, Data Assimilat Off, Greenbelt, MD USA. RP Yang, K (reprint author), Univ Tokyo, Dept Civil Engn, River Lab, Bunkyo Ku, Hongo 7-3-1, Tokyo 1138656, Japan. EM yangk@hydra.t.u-tokyo.ac.jp RI Bosilovich, Michael/F-8175-2012; Yang, Kun/G-8390-2011; Taniguchi, Kenji/C-3429-2015 OI Yang, Kun/0000-0002-0809-2371; NR 51 TC 20 Z9 26 U1 4 U2 10 PU METEOROLOGICAL SOC JPN PI TOKYO PA C/O JPN METEOROL AGENCY 1-3-4 OTE-MACHI, CHIYODA-KU, TOKYO, 100-0004, JAPAN SN 0026-1165 J9 J METEOROL SOC JPN JI J. Meteorol. Soc. Jpn. PD FEB PY 2007 VL 85A BP 99 EP 116 DI 10.2151/jmsj.85A.99 PG 18 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA 163FM UT WOS:000246144200006 ER PT J AU Kato, H Rodell, M Beyrich, F Cleugh, H van Gorsel, E Liu, HZ Meyers, TP AF Kato, Hiroko Rodell, Matthew Beyrich, Frank Cleugh, Helen van Gorsel, Eva Liu, Huizhi Meyers, Tilden P. TI Sensitivity of land surface simulations to model physics, land characteristics, and forcings, at four CEOP sites SO JOURNAL OF THE METEOROLOGICAL SOCIETY OF JAPAN LA English DT Article ID DATA ASSIMILATION SYSTEM; RIVER-BASIN EXPERIMENT; SOIL WETNESS PROJECT; PARAMETERIZATION SCHEMES; MULTICRITERIA METHODS; WATER FLUXES; ETA-MODEL; PHASE; CLIMATE; PRECIPITATION AB Numerical land surface models (LSMs) are abundant and in many cases highly sophisticated, yet their output has not converged towards a consensus depiction of reality. Addressing this matter is complicated by the huge number of possible combinations of input land characteristics, forcings, and physics packages available. The Global Land Data Assimilation System (GLDAS) and its sister project the Land Information System (LIS) have made it straightforward to test a variety of configurations with multiple LSMs. In order to compare the impacts of the choice of LSM, land cover, soil, and elevation information, and precipitation and downward radiation forcing datasets on simulated evapotranspiration, sensible heat flux, and top layer soil moisture, a set of experiments was designed which made use of high quality, physically coherent, 1-year datasets from four reference sites of the Coordinated Enhanced Observing Period (CEOP) initiative. As in previous studies, it was shown that the LSM itself is generally the most important factor governing output. Beyond that, evapotranspiration seems to be most sensitive to precipitation, land cover, and radiation (in that order); sensible heat flux is most sensitive to radiation, precipitation, and land cover; and soil moisture is most sensitive to precipitation, soil, and land cover. Various seasonal and model specific dependencies and other caveats are discussed. Output fields were also compared with observations in order to test whether the LSMs are capable of simulating an observed reality given a plausible set of inputs. In general, that potential was fair for evapotranspiration, good for sensible heat flux but problematic given its strong sensitivity to the inputs, and poor for soil moisture. The results emphasize that improving the LSMs themselves, and not just the inputs, will be essential if we hope to model land surface water and energy processes accurately. C1 NASA, Goddard Space Flight Ctr, Hydrol Sci Branch, Greenbelt, MD 20771 USA. Univ Maryland, Earth Syst Sci Interdisciplinary Ctr, College Pk, MD 20742 USA. Richard Assmann Observatorium, Meteorol Observatorium Lindenberg, DWD, D-15848 OT Lindenberg, Germany. CSIRO Marine & Atmospher Res, Canberra, ACT 2601, Australia. Chinese Acad Sci, Inst Atmospher Phys, Beijing 100029, Peoples R China. Atmospher Turbulence & Diffus Div, Oak Ridge, TN 37830 USA. RP Rodell, M (reprint author), NASA, Goddard Space Flight Ctr, Hydrol Sci Branch, Code 614-3, Greenbelt, MD 20771 USA. EM Matthew.Rodell@nasa.gov RI van Gorsel, Eva/A-1699-2012; Rodell, Matthew/E-4946-2012; Wang, ZF/D-7202-2012; Cleugh, Helen/B-3591-2014; Meyers, Tilden/C-6633-2016 OI van Gorsel, Eva/0000-0002-9939-7217; Rodell, Matthew/0000-0003-0106-7437; Wang, ZF/0000-0002-7062-6012; NR 42 TC 49 Z9 52 U1 2 U2 11 PU METEOROLOGICAL SOC JPN PI TOKYO PA C/O JPN METEOROL AGENCY 1-3-4 OTE-MACHI, CHIYODA-KU, TOKYO, 100-0004, JAPAN SN 0026-1165 J9 J METEOROL SOC JPN JI J. Meteorol. Soc. Jpn. PD FEB PY 2007 VL 85A BP 187 EP 204 DI 10.2151/jmsj.85A.187 PG 18 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA 163FM UT WOS:000246144200010 ER PT J AU Bosilovich, MG Radakovich, JD da Silva, A Todling, R Verter, F AF Bosilovich, Michael G. Radakovich, Jon D. da Silva, Arlindo Todling, Ricardo Verter, Frances TI Skin temperature analysis and bias correction in a coupled land-atmosphere data assimilation system SO JOURNAL OF THE METEOROLOGICAL SOCIETY OF JAPAN LA English DT Article ID COMMUNITY CLIMATE MODEL; SURFACE SOIL-MOISTURE; ECMWF REANALYSIS; BOUNDARY-LAYER; VARIATIONAL ASSIMILATION; SATELLITE-OBSERVATIONS; ENERGY BUDGETS; WATER-VAPOR; FIFE DATA; MICROWAVE AB In an initial investigation, remotely sensed surface temperature is assimilated into a coupled atmosphere/land global data assimilation system, with explicit accounting for biases in the model state. In this scheme, a incremental bias correction term is introduced in the model's surface energy budget. In its simplest form, the algorithm estimates and corrects a constant time mean bias for each gridpoint; additional benefits are attained with a refined version of the algorithm which allows for a correction of the mean diurnal cycle. The method is validated against the assimilated observations, as well as independent near-surface air temperature observations. In many regions, not accounting for the diurnal cycle of bias caused degradation of the diurnal amplitude of background model air temperature. Energy fluxes collected through the Coordinated Enhanced Observing Period (CEOP) are used to more closely inspect the surface energy budget. In general, sensible heat flux is improved with the surface temperature assimilation, and two stations show a reduction of bias by as much as 30 W m(-2). At the Rondonia station in Amazonia, the Bowen ratio changes direction in an improvement related to the temperature assimilation. However, at many stations the monthly latent heat flux bias is slightly increased. These results show the impact of univariate assimilation of surface temperature observations on the surface energy budget, and suggest the need for multivariate land data assimilation. The results also show the need for independent validation data, especially flux stations in varied climate regimes. C1 NASA, Goddard Space Flight Ctr, Global Modeling & Assimilat Off, Greenbelt, MD 20771 USA. RP Bosilovich, MG (reprint author), NASA, Goddard Space Flight Ctr, Global Modeling & Assimilat Off, Code 610-1, Greenbelt, MD 20771 USA. EM Michael.Bosilovich@nasa.gov RI da Silva, Arlindo/D-6301-2012; Bosilovich, Michael/F-8175-2012 OI da Silva, Arlindo/0000-0002-3381-4030; NR 69 TC 43 Z9 44 U1 1 U2 7 PU METEOROLOGICAL SOC JPN PI TOKYO PA C/O JPN METEOROL AGENCY 1-3-4 OTE-MACHI, CHIYODA-KU, TOKYO, 100-0004, JAPAN SN 0026-1165 J9 J METEOROL SOC JPN JI J. Meteorol. Soc. Jpn. PD FEB PY 2007 VL 85A BP 205 EP 228 DI 10.2151/jmsj.85A.205 PG 24 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA 163FM UT WOS:000246144200011 ER PT J AU Lau, WKM Kim, KM Lee, MI AF Lau, William K. M. Kim, Kyu-Myong Lee, Myong-In TI Characteristics of diurnal and seasonal cycles in global monsoon systems SO JOURNAL OF THE METEOROLOGICAL SOCIETY OF JAPAN LA English DT Article ID WEST-AFRICAN MONSOON; ASIAN SUMMER MONSOON; CUMULUS CONVECTION; WARM-SEASON; EAST-ASIA; PRECIPITATION; VARIABILITY; RAINFALL; TRMM; CLIMATOLOGY AB In this paper, we characterize the climatological diurnal cycles over monsoon land and ocean regions, and seasonal cycles for six major monsoon systems around the world, from observations and outputs of the NASA Seasonal-to-Interannual Prediction Project (NSIPP) general circulation model outputs. Over monsoon land regions, the diurnal cycle has a pronounced late afternoon peak in rainfall and over the oceans a much weak diurnal signal with an early morning peak. The NSIPP model produces a daily peak in rainfall about 2-3 hours earlier than observed, possibly attributed to a cumulus parameterization which does not include cloud life cycle effects, and which lack detailed treatment of boundary layer processes. The seasonal cycles of all monsoon rain systems are controlled by an ITCZ and a subtropical and/or extratropical component due to the presence of contiguous large continental land mass. Strong climatological intraseasonal oscillations (CISO) are found in the monsoon systems of South Asia and East Asia, Australia, and South America, and to a lesser degree for West Africa and Mexico/North America. The NSIPP model captures the slow component seasonal component reasonably well, but the CISO's are not well simulated. Analysis with reference to a new monsoon index shows that the major monsoon systems can be classified into three major groups (M1-3) according to the relative strength of continental vs. oceanic controls. East Asian and South Asian monsoons belong to a group (MI), where the continental influence is stronger than that from the ITCZ. The North America and South America monsoons show similar characteristics with the ITCZ influence slight stronger than continental influence (M2). The West Africa and Australia monsoons are found to be essentially ITCZ-monsoon systems (M3), with strong oceanic control, and limited poleward excursion of the monsoon rainbelt. We also find a clear trend associated with an increase in continentality for M3 monsoons, i.e., the West African and the Australian monsoons in the last two decades. We speculate that the former is linked to the partially recovery of the Sahel drought since the 1980's. C1 NASA, Goddard Space Flight Ctr, Atmospheres Lab, Greenbelt, MD 20771 USA. UMBC, Goddard Earth Sci & Technol Ctr, Baltimore, MD USA. RP Lau, WKM (reprint author), NASA, Goddard Space Flight Ctr, Atmospheres Lab, Greenbelt, MD 20771 USA. EM lau@climate.gsfc.nasa.gov RI Kim, Kyu-Myong/G-5398-2014; Lau, William /E-1510-2012; OI Lau, William /0000-0002-3587-3691; Lee, Myong-In/0000-0001-8983-8624 NR 39 TC 6 Z9 6 U1 0 U2 11 PU METEOROLOGICAL SOC JPN PI TOKYO PA C/O JPN METEOROL AGENCY 1-3-4 OTE-MACHI, CHIYODA-KU, TOKYO, 100-0004, JAPAN SN 0026-1165 J9 J METEOROL SOC JPN JI J. Meteorol. Soc. Jpn. PD FEB PY 2007 VL 85A BP 403 EP 416 DI 10.2151/jmsj.85A.403 PG 14 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA 163FM UT WOS:000246144200022 ER PT J AU Burford, B Ochiai, O Enloe, Y Mcdonald, K AF Burford, Benjamin Ochiai, Osamu Enloe, Yonsook Mcdonald, Ken TI Distributed data integration services provided by the WGISS Test Facility for CEOP SO JOURNAL OF THE METEOROLOGICAL SOCIETY OF JAPAN LA English DT Article AB The Coordinated Enhanced Observing Period (CEOP) is an initial step towards establishing an integrated observation system for the global water cycle, bringing together the capabilities of both satellite based and ground based (remote and insitu) observing systems. The CEOP program initiated a discussion with the Committee on Earth Observation Satellites (CEOS) Working Group on Information Systems and Services (WGISS) for assistance in the development of advanced tools for integrated access, visualization and comparison of the multiple types of data being gathered by the CEOP project. CEOS WGISS initiated a project to collaboratively prototype a set of tools and services needed to provide user-friendly, efficient and effective integrated access to the CEOP (insitu, satellite and model output) data to support global water cycle research. The design and development of the prototypes in the WGISS Test Facility for CEOP, including its current capabilities and planned future developments, are presented here. C1 Remote Sensing Technol Ctr Japan, Tokyo, Japan. JAXA, EORC, Chuo Ku, Tokyo 1046023, Japan. SGT Inc, Greenbelt, MD 20770 USA. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Ochiai, O (reprint author), JAXA, EORC, Chuo Ku, 1-8-10 Harumi, Tokyo 1046023, Japan. EM ochiai.osamu@jaxa.jp NR 6 TC 1 Z9 1 U1 1 U2 1 PU METEOROLOGICAL SOC JPN PI TOKYO PA C/O JPN METEOROL AGENCY 1-3-4 OTE-MACHI, CHIYODA-KU, TOKYO, 100-0004, JAPAN SN 0026-1165 J9 J METEOROL SOC JPN JI J. Meteorol. Soc. Jpn. PD FEB PY 2007 VL 85A BP 519 EP 527 DI 10.2151/jmsj.85A.519 PG 9 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA 163FM UT WOS:000246144200028 ER PT J AU Singh, V Desta, Y Datta, P Guy, J Clarke, M Feedback, DL Weimert, J Goettert, J AF Singh, Varshni Desta, Yohannes Datta, Proyag Guy, Jason Clarke, Mark Feedback, Daniel L. Weimert, J. Goettert, Jost TI A hybrid approach for fabrication of polymeric BIOMEMS devices SO MICROSYSTEM TECHNOLOGIES-MICRO-AND NANOSYSTEMS-INFORMATION STORAGE AND PROCESSING SYSTEMS LA English DT Article; Proceedings Paper CT 6th Biennial International Workshop on High Aspect Ratio Micro Structure Technology CY JUN 10-13, 2005 CL Gyenogju, SOUTH KOREA SP Pohang Univ Sci & Technol, Korean Soc Medh Engineers AB Polymeric microfluidic chips are an enabling component for cost-effective, point of care analytical devices for pharmaceutical, agriculture, health, biological and medical applications. The microfluidic structures can be completed with active elements like pumps and valves as well as sensor components for more complex so called total analysis systems. Often, systems are designed as reader and disposable cartridge where the fluidic structures are simple devices that will be inserted into the reader, which executes the analytical protocol and displays the information in digital form, and disposed after completion of the analysis. In this paper, a hybrid fabrication approach was employed to build a polymeric microfluidic device, so-called sweatstick, suitable for collecting small, precise amounts (600 mu l) of human sweat, which were further analyzed for the amount of calcium ions indicating bone mass loss. The device was assembled from different parts fabricated by ultra deep X-ray lithography, precision micro-milling, and molding. Surface treatment of liquid exposed surfaces by oxygen plasma ensures hydrophilic behavior and proper capillary action. Preliminary testing of the device was performed by collecting defined amounts of sweat simulant and determining the calcium ion content using a fluorescent technique. The results for low calcium ion concentration typical for human sweat were excellent and repeatable with variation less than 5% demonstrating the ability to perform indirect bone loss measurements. C1 Louisiana State Univ, Ctr Adv Microstruct & Devices, Baton Rouge, LA 70802 USA. Univ Houston, Lab Integrated Physiol, Dept Hlth & Human Performance, Houston, TX 77204 USA. NASA, Lyndon B Johnson Space Ctr, Life Sci Directorate, Houston, TX 77058 USA. RP Singh, V (reprint author), Louisiana State Univ, Ctr Adv Microstruct & Devices, 6980 Jefferson Highway, Baton Rouge, LA 70802 USA. EM vsingh2@lsu.edu NR 6 TC 6 Z9 6 U1 1 U2 3 PU SPRINGER PI NEW YORK PA 233 SPRING STREET, NEW YORK, NY 10013 USA SN 0946-7076 J9 MICROSYST TECHNOL JI Microsyst. Technol. PD FEB PY 2007 VL 13 IS 3-4 BP 369 EP 377 DI 10.1007/s00542-006-0222-z PG 9 WC Engineering, Electrical & Electronic; Nanoscience & Nanotechnology; Materials Science, Multidisciplinary; Physics, Applied SC Engineering; Science & Technology - Other Topics; Materials Science; Physics GA 119XT UT WOS:000243048500027 ER PT J AU Beardmore, AP Page, KL O'Brien, PT Osborne, JP Kobayashi, S Zhang, B Burrows, DN Capalbi, M Goad, MR Godet, O Hill, JE La Parola, V Marshall, F Wells, AA AF Beardmore, A. P. Page, K. L. O'Brien, P. T. Osborne, J. P. Kobayashi, S. Zhang, B. Burrows, D. N. Capalbi, M. Goad, M. R. Godet, O. Hill, J. E. La Parola, V. Marshall, F. Wells, A. A. TI The Swift gamma-ray burst GRB 050422 SO MONTHLY NOTICES OF THE ROYAL ASTRONOMICAL SOCIETY LA English DT Article DE gamma-rays : bursts ID AFTERGLOW EMISSION; ENGINE ACTIVITY; LIGHT CURVES; TELESCOPE; SPECTRA; EVOLUTION; BRIGHT; ENERGETICS; MISSION; FLARE AB We describe observations of GRB 050422, a Swift-discovered gamma-ray burst. The prompt gamma-ray emission had a T-90 duration of 59 s and was multipeaked, with the main peak occurring at T + 53 s. Swift was able to follow the X-ray afterglow within 100 s of the burst trigger. The X-ray light curve, which shows a steep early decline, can be described by a broken power law with an initial decay slope of alpha(1)similar to 5.0, a break time t(b) similar to 270 s and a post-break decay slope of alpha(2) similar to 0.9, when the zero time of the X-ray emission is taken to be the burst trigger time. However, if the zero time is shifted to coincide with the onset of main peak in the gamma-ray light curve then the initial decay slope is shallower with alpha(1) similar to 3.2. The initial gamma-ray spectrum can be modelled by a power law with a spectral index of beta(B) = 0.50 +/- 0.19. However, the early time X-ray spectrum is significantly steeper than this and requires a spectral index of beta(X) = 2.33(-0.55)(+0.58). In comparison with other Swift bursts, GRB 050422 was unusually X-ray faint, had a soft X-ray spectrum, and had an unusually steep early X-ray decline. Even so, its behaviour can be accommodated by standard models. The combined BAT/XRT light curve indicates that the initial, steeply declining, X-ray emission is related to the tail of the prompt gamma-ray emission. The shallower decay seen after the break is consistent with the standard afterglow model. C1 Univ Leicester, Dept Phys & Astron, Leicester LE1 7RH, Leics, England. Liverpool John Moores Univ, Astrophys Res Inst, Birkenhead CH41 1LD, Merseyside, England. Univ Nevada, Dept Phys, Las Vegas, NV 89154 USA. Penn State Univ, Dept Astron & Astrophys, Davey Lab 517, University Pk, PA 16802 USA. ASI Sci Data Ctr, I-00044 Frascati, Italy. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Univ Space Res Assoc, Columbia, MD 21044 USA. INAF, Ist Astrofis Spaziale & Fis Cosm Palermo, I-90146 Palermo, Italy. RP Beardmore, AP (reprint author), Univ Leicester, Dept Phys & Astron, Leicester LE1 7RH, Leics, England. EM apb@star.le.ac.uk OI La Parola, Valentina/0000-0002-8087-6488 NR 44 TC 1 Z9 1 U1 0 U2 0 PU BLACKWELL PUBLISHING PI OXFORD PA 9600 GARSINGTON RD, OXFORD OX4 2DQ, OXON, ENGLAND SN 0035-8711 J9 MON NOT R ASTRON SOC JI Mon. Not. Roy. Astron. Soc. PD FEB 1 PY 2007 VL 374 IS 4 BP 1473 EP 1478 DI 10.1111/j.1365-2966.2006.11249.x PG 6 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 128DB UT WOS:000243636300026 ER PT J AU Worden, J Noone, D Bowman, K AF Worden, John Noone, David Bowman, Kevin CA Tropospheric Emission Spect TI Importance of rain evaporation and continental convection in the tropical water cycle SO NATURE LA English DT Article ID ISOTOPE COMPOSITION; PRECIPITATION; ENVIRONMENT; BALANCE; CLOUDS; OXYGEN; MODEL AB Atmospheric moisture cycling is an important aspect of the Earth's climate system, yet the processes determining atmospheric humidity are poorly understood(1-4). For example, direct evaporation of rain contributes significantly to the heat and moisture budgets of clouds(5), but few observations of these processes are available(6). Similarly, the relative contributions to atmospheric moisture over land from local evaporation and humidity from oceanic sources are uncertain(3,7). Lighter isotopes of water vapour preferentially evaporate whereas heavier isotopes preferentially condense(8-10) and the isotopic composition of ocean water is known. Here we use this information combined with global measurements of the isotopic composition of tropospheric water vapour from the Tropospheric Emission Spectrometer (TES) aboard the Aura spacecraft(11,12), to investigate aspects of the atmospheric hydrological cycle that are not well constrained by observations of precipitation or atmospheric vapour content. Our measurements of the isotopic composition of water vapour near tropical clouds suggest that rainfall evaporation contributes significantly to lower troposphere humidity, with typically 20% and up to 50% of rainfall evaporating near convective clouds. Over the tropical continents the isotopic signature of tropospheric water vapour differs significantly from that of precipitation(8,10,13), suggesting that convection of vapour from both oceanic sources and evapotranspiration are the dominant moisture sources. Our measurements allow an assessment of the intensity of the present hydrological cycle and will help identify any future changes as they occur. C1 Univ Colorado, Dept Atmospher & Ocean Sci, Boulder, CO 80309 USA. Univ Colorado, Cooperat Inst Res Environm Sci, Boulder, CO USA. CALTECH, Jet Prop Lab, Pasadena, CA USA. RP Noone, D (reprint author), Univ Colorado, Dept Atmospher & Ocean Sci, Boulder, CO 80309 USA. EM david.noone@colorado.edu NR 25 TC 190 Z9 198 U1 3 U2 61 PU NATURE PUBLISHING GROUP PI LONDON PA MACMILLAN BUILDING, 4 CRINAN ST, LONDON N1 9XW, ENGLAND SN 0028-0836 J9 NATURE JI Nature PD FEB 1 PY 2007 VL 445 IS 7127 BP 528 EP 532 DI 10.1038/nature05508 PG 5 WC Multidisciplinary Sciences SC Science & Technology - Other Topics GA 131KI UT WOS:000243867300041 PM 17268467 ER PT J AU Rodehacke, CB Hellmer, HH Huhn, O Beckmann, A AF Rodehacke, Christian B. Hellmer, Hartmut H. Huhn, Oliver Beckmann, Aike TI Ocean/ice shelf interaction in the southern Weddell Sea: results of a regional numerical helium/neon simulation SO OCEAN DYNAMICS LA English DT Article DE tracers; Ice shelf water; Antarctic bottom water; Southern ocean; numerical model ID RONNE ICE SHELF; CIRCULATION BENEATH; DISTILLED WATER; MODEL; NEON; ANTARCTICA; SOLUBILITY; SEAWATER; TRACERS; VARIABILITY AB Ocean/ice interaction at the base of deep-drafted Antarctic ice shelves modifies the physical properties of inflowing shelf waters to become Ice Shelf Water (ISW). In contrast to the conditions at the atmosphere/ocean interface, the increased hydrostatic pressure at the glacial base causes gases embedded in the ice to dissolve completely after being released by melting. Helium and neon, with an extremely low solubility, are saturated in glacial meltwater by more than 1000%. At the continental slope in front of the large Antarctic caverns, ISW mixes with ambient waters to form different precursors of Antarctic Bottom Water. A regional ocean circulation model, which uses an explicit formulation of the ocean/ice shelf interaction to describe for the first time the input of noble gases to the Southern Ocean, is presented. The results reveal a long-term variability of the basal mass loss solely controlled by the interaction between waters of the continental shelf and the ice shelf cavern. Modeled helium and neon supersaturations from the Filchner-Ronne Ice Shelf front show a "low-pass" filtering of the inflowing signal due to cavern processes. On circumpolar scales, the simulated helium and neon distributions allow us to quantify the ISW contribution to bottom water, which spreads with the coastal current connecting the major formation sites in Ross and Weddell Seas. C1 Univ Bremen, Bremen, Germany. Alfred Wegener Inst Polar & Marine Res, D-2850 Bremerhaven, Germany. RP Rodehacke, CB (reprint author), NASA, Goddard Inst Space Studies, New York, NY 10025 USA. EM crodehacke@giss.nasa.gov OI Rodehacke, Christian/0000-0003-3110-3857 NR 48 TC 8 Z9 8 U1 1 U2 7 PU SPRINGER HEIDELBERG PI HEIDELBERG PA TIERGARTENSTRASSE 17, D-69121 HEIDELBERG, GERMANY SN 1616-7341 J9 OCEAN DYNAM JI Ocean Dyn. PD FEB PY 2007 VL 57 IS 1 BP 1 EP 11 DI 10.1007/s10236-006-0073-2 PG 11 WC Oceanography SC Oceanography GA 137OQ UT WOS:000244302300001 ER PT J AU Mercier, JA Schowengerdt, RA Storey, JC Smith, JL AF Mercier, Jeffrey A. Schowengerdt, Robert A. Storey, James C. Smith, Jody L. TI Geometric correction and digital elevation extraction using multiple MTI datasets SO PHOTOGRAMMETRIC ENGINEERING AND REMOTE SENSING LA English DT Article AB Digital Elevation Models (DEMs) are traditionally acquired from a stereo pair of aerial photographs sequentially captured by an airborne metric camera. Standard DEM extraction techniques can be naturally extended to satellite imagery, but the particular characteristics of satellite imaging can cause difficulties. The spacecraft ephemeris with respect to the ground site during image collects is the most important factor in the elevation extraction process. When the angle of separation between the stereo images is small, the extraction process typically produces measurements with low accuracy, while a large angle of separation can cause an excessive number of erroneous points in the DEM from occlusion of ground areas. The use of three or more images registered to the same ground area can potentially reduce these problems and improve the accuracy of the extracted DEM. The pointing capability of some sensors, such as the Multispectral Thermal Imager (MTI), allows for multiple collects of the same area from different perspectives. This functionality of mu makes it a good candidate for the implementation of a DEM extraction algorithm using multiple images for improved accuracy. Evaluation of this capability and development of algorithms to geometrically model the MTI sensor and extract DEMs from multi-look MTI imagery are described in this paper. An RMS elevation error of 6.3-meters is achieved using 11 ground test points, while the MTI band has a 5-meter ground sample distance. C1 Sandia Natl Labs, Albuquerque, NM 87185 USA. Univ Arizona, Dept Elect & Comp Engn, Tucson, AZ 85721 USA. NASA, Goddard Space Flight Ctr, EROS Data Ctr SAIC, Greenbelt, MD 20771 USA. RP Mercier, JA (reprint author), Sandia Natl Labs, POB 5800, Albuquerque, NM 87185 USA. EM jamerci@sandia.gov NR 6 TC 0 Z9 0 U1 0 U2 3 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 FEB PY 2007 VL 73 IS 2 BP 133 EP 142 PG 10 WC Geography, Physical; Geosciences, Multidisciplinary; Remote Sensing; Imaging Science & Photographic Technology SC Physical Geography; Geology; Remote Sensing; Imaging Science & Photographic Technology GA 132EE UT WOS:000243924300005 ER PT J AU Pandey, RB Reed, AH Braithwaite, E Seyfarth, R Gettrust, JF AF Pandey, R. B. Reed, Allen H. Braithwaite, Edward Seyfarth, Ray Gettrust, J. F. TI Flow through a laboratory sediment sample by computer simulation modeling SO PHYSICA A-STATISTICAL MECHANICS AND ITS APPLICATIONS LA English DT Article DE porous medium formed by quartz sands; interacting lattice gas; computer simulation; driven flow ID OPEN POROUS-MEDIUM AB A laboratory sediment sample is digitized by X-ray computed tomography system to obtain a host matrix of size 1003 of porosity 0.282. Flow through the porous medium is studied by an interacting lattice gas model for fluid driven by pressure bias. The bias H(0 <= H <= 1) is implemented via soft and hard pressure constraints in selecting the stochastic movement of fluid particles. The response of fluid flux density to bias H is nearly linear with soft pressure; it becomes nonmonotonic with the hard pressure. (c) 2006 Elsevier B.V. All rights reserved. C1 Univ So Mississippi, Dept Phys & Astron, Hattiesburg, MS 39406 USA. USN, Res Lab, Stennis Space Ctr, Stennis Space Ctr, MS 39529 USA. Univ So Mississippi, Sch Comp, Hattiesburg, MS 39406 USA. RP Pandey, RB (reprint author), Univ So Mississippi, Dept Phys & Astron, Hattiesburg, MS 39406 USA. EM ras.pandey@usm.edu NR 16 TC 1 Z9 1 U1 0 U2 0 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS SN 0378-4371 J9 PHYSICA A JI Physica A PD FEB 1 PY 2007 VL 374 IS 2 BP 501 EP 506 DI 10.1016/j.physa.2006.08.030 PG 6 WC Physics, Multidisciplinary SC Physics GA 127XZ UT WOS:000243621000001 ER PT J AU Di Rienzi, J Drachman, RJ AF Di Rienzi, Joseph Drachman, Richard J. TI Nonradiative formation of the positron-helium triplet bound state SO PHYSICAL REVIEW A LA English DT Article AB We have previously calculated the cross section for radiative formation of the interesting bound state consisting of a positron bound to helium, where the atomic electrons are in the triplet spin state. That process uses the metastable triplet helium system as target, and, as expected, it has a very small cross section. In this paper we examine a more probable process in which the state of interest is produced in an exchange rearrangement collision between a positronium atom and the singlet helium ground state: Ps+He(S-1(e))-> PsHe(+)(S-3(e))+e(-). The present calculation is done in the plane-wave Born approximation, using simple initial and final wave functions and compares post and prior forms. C1 Coll Notre Dame Maryland, Baltimore, MD 21210 USA. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Di Rienzi, J (reprint author), Coll Notre Dame Maryland, Baltimore, MD 21210 USA. NR 11 TC 2 Z9 2 U1 0 U2 1 PU AMERICAN PHYSICAL SOC PI COLLEGE PK PA ONE PHYSICS ELLIPSE, COLLEGE PK, MD 20740-3844 USA SN 1050-2947 J9 PHYS REV A JI Phys. Rev. A PD FEB PY 2007 VL 75 IS 2 AR 024501 DI 10.1103/PhysRevA.75.024501 PG 4 WC Optics; Physics, Atomic, Molecular & Chemical SC Optics; Physics GA 140UN UT WOS:000244532300152 ER PT J AU Hossain, S Tayal, SS Smith, SJ Raymond, JC Chutjian, A AF Hossain, S. Tayal, S. S. Smith, S. J. Raymond, J. C. Chutjian, A. TI Measurement and calculation of absolute cross sections for excitation of the 3s(2)3p P-2(1/2)o-3s(2)3p P-2(3/2)o fine-structure transition in Fe13+ SO PHYSICAL REVIEW A LA English DT Article ID ELECTRON-EXCITATION; SEYFERT-GALAXIES; CORONAL LINE; FE-XIV; IRON; PROGRAM; REGION AB Experimental cross sections are reported for the Fe13+ coronal green line transition 3s(2)3p P-2(1/2)o-3s(2)3p P-2(3/2)o at lambda 5303 A (2.338 eV). The center-of-mass interaction energies are in the range 1.7 eV (below threshold) through threshold, to 6.6 eV (2.9xthreshold). Data are compared with results of a 135-level Breit-Pauli R-matrix theory. Present experiment detects a strong maximum in the excitation cross section of magnitude 15x10(-16) cm(2) at 2.6 eV. Smaller structures are observed between 3 eV and 6.6 eV, with a maximum cross section never exceeding about 1.2x10(-16) cm(2). All features are due to enhancement of the direct excitation via a multitude of narrow, closely-spaced resonances calculated by the theory, the effects of which are convoluted by the 125 meV energy resolution of the present experiment. Iron is present in practically every astrophysical object, as well as being an impurity in fusion plasmas. Present results are the highest charge state in any ion for which an absolute excitation cross section has been measured. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. Clark Atlanta Univ, Dept Phys, Atlanta, GA 30314 USA. Harvard Smithsonian Ctr Astrophys, Cambridge, MA 02138 USA. RP Hossain, S (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 23 TC 9 Z9 9 U1 0 U2 2 PU AMERICAN PHYSICAL SOC PI COLLEGE PK PA ONE PHYSICS ELLIPSE, COLLEGE PK, MD 20740-3844 USA SN 1050-2947 J9 PHYS REV A JI Phys. Rev. A PD FEB PY 2007 VL 75 IS 2 AR 022709 DI 10.1103/PhysRevA.75.022709 PG 6 WC Optics; Physics, Atomic, Molecular & Chemical SC Optics; Physics GA 140UN UT WOS:000244532300077 ER PT J AU Wu, H Zhou, W Udovic, TJ Rush, JJ Yildirim, T Huang, Q Bowman, RC AF Wu, H. Zhou, W. Udovic, T. J. Rush, J. J. Yildirim, T. Huang, Q. Bowman, R. C., Jr. TI Structure and interstitial deuterium sites of beta-phase ZrNi deuteride SO PHYSICAL REVIEW B LA English DT Article ID INTERMETALLIC COMPOUNDS; SORPTION CRYOCOOLERS; NEUTRON-SCATTERING; SPACE APPLICATIONS; H SYSTEM; HYDRIDE; DEGRADATION; OCCUPATION; HYDROGEN; GROWTH AB beta-ZrNiD1-x (for x approximate to 0.1, near the beta-gamma phase boundary) was found to possess a triclinic P1 structure as determined by high-resolution neutron powder diffraction. This is very different from the widely accepted orthorhombic and distorted orthorhombic Cmcm structures previously proposed. In contrast to the single type of D site associated with these latter structures, the true beta-ZrNiD1-x structure contains two crystallographically distinct interstitial D sites: "Zr4Ni2" octahedral sites and "Zr-4" tetrahedral sites, alternately ordered along the a direction. From first-principles calculations, the total energy of the P1 structure was found to be approximate to 0.24 eV per unit cell lower than Cmcm-symmetry ZrNiD and could be rationalized in terms of different D local-bonding configurations and metal-deuterium interactions. Resultant phonon calculations based on this structure were also consistent with the measured neutron vibrational spectrum. C1 Natl Inst Stand & Technol, NIST Ctr Neutron Res, Gaithersburg, MD 20899 USA. Univ Maryland, Dept Mat Sci & Engn, College Pk, MD 20742 USA. Univ Penn, Dept Mat Sci & Engn, Philadelphia, PA 19104 USA. CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Wu, H (reprint author), Natl Inst Stand & Technol, NIST Ctr Neutron Res, 100 Bur Dr,MS 8562, Gaithersburg, MD 20899 USA. EM huiwu@nist.gov RI Wu, Hui/C-6505-2008; Zhou, Wei/C-6504-2008; yildirim, taner/A-1290-2009 OI Wu, Hui/0000-0003-0296-5204; Zhou, Wei/0000-0002-5461-3617; NR 31 TC 4 Z9 4 U1 1 U2 4 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 FEB PY 2007 VL 75 IS 6 AR 064105 DI 10.1103/PhysRevB.75.064105 PG 7 WC Physics, Condensed Matter SC Physics GA 140UU UT WOS:000244533000018 ER PT J AU Barack, L Cutler, C AF Barack, Leor Cutler, Curt TI Using LISA extreme-mass-ratio inspiral sources to test off-Kerr deviations in the geometry of massive black holes SO PHYSICAL REVIEW D LA English DT Article ID GRAVITATIONAL-WAVES; MULTIPOLE MOMENTS; COMPACT BINARIES; POINT MASSES; BODY; PARAMETERS; RADIATION; SPACETIME; ORBIT AB Inspirals of stellar-mass compact objects (COs) into similar to 10(6)M black holes are especially interesting sources of gravitational waves for the planned Laser Interferometer Space Antenna (LISA). The orbits of these extreme-mass-ratio inspirals (EMRIs) are highly relativistic, displaying extreme versions of both perihelion precession and Lense-Thirring precession of the orbital plane. We investigate the question of whether the emitted waveforms can be used to strongly constrain the geometry of the central massive object, and in essence check that it corresponds to a Kerr black hole (BH). For a Kerr BH, all multipole moments of the spacetime have a simple, unique relation to M and S, the BH mass, and spin; in particular, the spacetime's mass quadrupole moment Q is given by Q=-S-2/M. Here we treat Q as an additional parameter, independent of S and M, and ask how well observation can constrain its difference from the Kerr value. This was already estimated by Ryan, but for the simplified case of circular, equatorial orbits, and Ryan also neglected the signal modulations arising from the motion of the LISA satellites. We consider generic orbits and include the modulations due to the satellite motions. For this analysis, we use a family of approximate (basically post-Newtonian) waveforms, which represent the full parameter space of EMRI sources, and which exhibit the main qualitative features of true, general relativistic waveforms. We extend this parameter space to include (in an approximate manner) an arbitrary value of Q, and then construct the Fisher information matrix for the extended parameter space. By inverting the Fisher matrix, we estimate how accurately Q could be extracted from LISA observations of EMRIs. For 1 yr of coherent data from the inspiral of a 10M black hole into rotating black holes of masses 10(5.5)M, 10(6)M, or 10(6.5)M, we find Delta(Q/M-3)similar to 10(-4), 10(-3), or 10(-2), respectively (assuming total signal-to-noise ratio of 100, typical of the brightest detectable EMRIs). These results depend only weakly on the eccentricity of the inspiral orbit or the spin of the central object. C1 Univ Southampton, Sch Math, Southampton SO17 1BJ, Hants, England. CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Barack, L (reprint author), Univ Southampton, Sch Math, Southampton SO17 1BJ, Hants, England. NR 29 TC 90 Z9 92 U1 0 U2 0 PU AMERICAN PHYSICAL SOC PI COLLEGE PK PA ONE PHYSICS ELLIPSE, COLLEGE PK, MD 20740-3844 USA SN 1550-7998 J9 PHYS REV D JI Phys. Rev. D PD FEB PY 2007 VL 75 IS 4 AR 042003 DI 10.1103/PhysRevD.75.042003 PG 11 WC Astronomy & Astrophysics; Physics, Particles & Fields SC Astronomy & Astrophysics; Physics GA 140VQ UT WOS:000244535200004 ER PT J AU Crowder, J Cornish, NJ AF Crowder, Jeff Cornish, Neil J. TI Solution to the galactic foreground problem for LISA SO PHYSICAL REVIEW D LA English DT Article ID ADAPTIVE MCMC METHOD; GRAVITATIONAL-RADIATION; METROPOLIS-HASTINGS; BINARIES; WAVES; STRATEGIES; PARAMETERS; INSPIRALS; SYSTEMS AB Low frequency gravitational wave detectors, such as the Laser Interferometer Space Antenna (LISA), will have to contend with large foregrounds produced by millions of compact galactic binaries in our galaxy. While these galactic signals are interesting in their own right, the unresolved component can obscure other sources. The science yield for the LISA mission can be improved if the brighter and more isolated foreground sources can be identified and regressed from the data. Since the signals overlap with one another, we are faced with a "cocktail party" problem of picking out individual conversations in a crowded room. Here we present and implement an end-to-end solution to the galactic foreground problem that is able to resolve tens of thousands of sources from across the LISA band. Our algorithm employs a variant of the Markov chain Monte Carlo (MCMC) method, which we call the blocked annealed Metropolis-Hastings (BAM) algorithm. Following a description of the algorithm and its implementation, we give several examples ranging from searches for a single source to searches for hundreds of overlapping sources. Our examples include data sets from the first round of mock LISA data challenges. C1 Montana State Univ, Dept Phys, Bozeman, MT 59717 USA. CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Crowder, J (reprint author), Montana State Univ, Dept Phys, Bozeman, MT 59717 USA. NR 55 TC 32 Z9 32 U1 0 U2 0 PU AMERICAN PHYSICAL SOC PI COLLEGE PK PA ONE PHYSICS ELLIPSE, COLLEGE PK, MD 20740-3844 USA SN 1550-7998 J9 PHYS REV D JI Phys. Rev. D PD FEB PY 2007 VL 75 IS 4 AR 043008 DI 10.1103/PhysRevD.75.043008 PG 17 WC Astronomy & Astrophysics; Physics, Particles & Fields SC Astronomy & Astrophysics; Physics GA 140VQ UT WOS:000244535200013 ER PT J AU Akylas, E Kassinos, SC Langer, CA AF Akylas, E. Kassinos, S. C. Langer, C. A. TI Rapid shear of initially anisotropic turbulence in a rotating frame SO PHYSICS OF FLUIDS LA English DT Article ID DIRECT NUMERICAL-SIMULATION; DISTORTION THEORY; BOUNDARY-LAYER; LINEAR-THEORY; FLOW AB In the present study, we investigate, using inviscid rapid distortion theory, the evolution of sheared turbulence in a rotating frame as a function of the rotation rate (including stable, transitional, and unstable regimes), and examine the sensitivity of the results for various nonisotropic initial conditions. Analytical solutions are derived for the evolution of the stresses and the structure dimensionality tensor components for three one-dimensional and three two-dimensional initializations. From these solutions, we calculate the asymptotic states of the turbulence, which are compared to the exact numerical solution of the three-dimensional initially isotropic case. From the investigation it is shown that the qualitative characteristics of the isotropic solution in the unstable regime are represented quite accurately when the initial turbulence is dependent at least on the axis of the rotation of the frame. For the transitional and the stable regimes, though, the initial dependence of the turbulence on the axis of the mean flow is also crucial. (c) 2007 American Institute of Physics. C1 Univ Cyprus, Dept Mech & Mfg Engn, CY-1678 Nicosia, Cyprus. Natl Observ Athens, Inst Environm Res, Athens, Greece. Stanford Univ, Ctr Turbulence Res, NASA Ames, Stanford, CA 94305 USA. RP Akylas, E (reprint author), Univ Cyprus, Dept Mech & Mfg Engn, CY-1678 Nicosia, Cyprus. EM kassinos@ucy.ac.cy RI Kassinos, Stavros/B-6404-2016; Akylas, Evangelos/E-4418-2016 OI Kassinos, Stavros/0000-0002-3501-3851; Akylas, Evangelos/0000-0002-2731-657X NR 29 TC 4 Z9 4 U1 0 U2 1 PU AMER INST PHYSICS PI MELVILLE PA CIRCULATION & FULFILLMENT DIV, 2 HUNTINGTON QUADRANGLE, STE 1 N O 1, MELVILLE, NY 11747-4501 USA SN 1070-6631 EI 1089-7666 J9 PHYS FLUIDS JI Phys. Fluids PD FEB PY 2007 VL 19 IS 2 AR 025102 DI 10.1063/1.2675939 PG 18 WC Mechanics; Physics, Fluids & Plasmas SC Mechanics; Physics GA 140UC UT WOS:000244531200015 ER PT J AU Hudy, LM Naguib, A Humphreys, WM AF Hudy, Laura M. Naguib, Ahmed Humphreys, William M. TI Stochastic estimation of a separated-flow field using wall-pressure-array measurements SO PHYSICS OF FLUIDS LA English DT Article ID SELF-SUSTAINED OSCILLATIONS; LINEAR INSTABILITY ANALYSIS; REATTACHING SHEAR-LAYER; TURBULENT-FLOW; OPEN CAVITY; SIMULATION; REGION AB Concurrent, surface-pressure and planar, particle image velocimetry (PIV) measurements were obtained in the separating/reattaching flow region downstream of an axisymmetric, backward-facing step at a Reynolds number of 8081, based on step height. The surface-pressure and PIV measurements were used to investigate the evolution of coherent structures in the flow field by employing proper orthogonal decomposition (POD) and multipoint, linear, stochastic estimation (mLSE) analysis techniques. POD was used to determine the dominant modes in the pressure signature, while mLSE was used to estimate the dominant flow structures above the wall from the wall-pressure POD modes over a series of time steps. It was found that a large-scale, coherent structure develops in place (i.e., temporally) at approximately half the reattachment distance. Once this structure reaches a height equivalent to the step, it sheds and accelerates downstream. This growth in place, and then shedding, resembles the evolution of the flow structure in the wake of bluff bodies. Such a "wake mode" has been observed in numerical-simulation studies of long cavities and backward-facing steps, where flow two dimensionality is controllable. The present study shows for the first time evidence for the existence of a wake mode in an experimental study of a backward-facing step. This is believed to relate to the quality of the two dimensionality (i.e., axisymmetry) of the test geometry and the ability to track the temporal evolution of structural features through mLSE. (c) 2007 American Institute of Physics. C1 Michigan State Univ, E Lansing, MI 48824 USA. NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Naguib, A (reprint author), Michigan State Univ, E Lansing, MI 48824 USA. EM naguib@egr.msu.edu NR 45 TC 31 Z9 32 U1 1 U2 6 PU AMER INST PHYSICS PI MELVILLE PA CIRCULATION & FULFILLMENT DIV, 2 HUNTINGTON QUADRANGLE, STE 1 N O 1, MELVILLE, NY 11747-4501 USA SN 1070-6631 J9 PHYS FLUIDS JI Phys. Fluids PD FEB PY 2007 VL 19 IS 2 AR 024103 DI 10.1063/1.2472507 PG 18 WC Mechanics; Physics, Fluids & Plasmas SC Mechanics; Physics GA 140UC UT WOS:000244531200011 ER PT J AU Kassinos, SC Akylas, E Langer, CA AF Kassinos, S. C. Akylas, E. Langer, C. A. TI Rapidly sheared homogeneous stratified turbulence in a rotating frame SO PHYSICS OF FLUIDS LA English DT Article ID LINEAR-THEORY; FLOW; INSTABILITY AB Rapid distortion theory is applied to stratified homogeneous turbulence that is sheared in a rotating frame. Insight into the stabilizing and destabilizing effects of the combined stratification and frame rotation is gained by considering initial fields that are two-dimensional, with the axis of independence aligned with the flow direction. For these conditions, we derive solutions for the Fourier components of the flow variables, and for one-point statistics in physical space. The analytical results are in qualitative agreement with the exact numerical solution for initially isotropic homogeneous turbulence, and they could be a reference point for the development of turbulence models. (c) 2007 American Institute of Physics. C1 Univ Cyprus, Dept Mech & Mfg Engn, CY-1678 Nicosia, Cyprus. Stanford Univ, Ctr Turbulence Res, NASA Ames, Stanford, CA 94305 USA. Natl Observ Athens, Inst Environm Res, Athens, Greece. RP Kassinos, SC (reprint author), Univ Cyprus, Dept Mech & Mfg Engn, 75 Kallipoleos, CY-1678 Nicosia, Cyprus. EM kassinos@ucy.ac.cy RI Kassinos, Stavros/B-6404-2016; Akylas, Evangelos/E-4418-2016 OI Kassinos, Stavros/0000-0002-3501-3851; Akylas, Evangelos/0000-0002-2731-657X NR 12 TC 4 Z9 4 U1 0 U2 1 PU AMER INST PHYSICS PI MELVILLE PA CIRCULATION & FULFILLMENT DIV, 2 HUNTINGTON QUADRANGLE, STE 1 N O 1, MELVILLE, NY 11747-4501 USA SN 1070-6631 EI 1089-7666 J9 PHYS FLUIDS JI Phys. Fluids PD FEB PY 2007 VL 19 IS 2 AR 021701 DI 10.1063/1.2710291 PG 4 WC Mechanics; Physics, Fluids & Plasmas SC Mechanics; Physics GA 140UC UT WOS:000244531200001 ER PT J AU Lofthouse, AJ Boyd, ID Wright, MJ AF Lofthouse, Andrew J. Boyd, Iain D. Wright, Michael J. TI Effects of continuum breakdown on hypersonic aerothermodynamics SO PHYSICS OF FLUIDS LA English DT Article ID SIMULATION MONTE-CARLO; EQUATIONS; BOLTZMANN; FLOWS AB Hypersonic vehicles experience different flow regimes during flight due to changes in atmospheric density. Hybrid continuum-particle methods, based on computational fluid dynamics (CFD) and direct simulation Monte Carlo (DSMC) methods, are being developed to simulate the flow in different hypersonic regimes. These methods use a breakdown parameter to determine regions of the flow where the CFD physics are no longer valid. The current study investigates the effect of continuum breakdown on surface aerothermodynamic properties (pressure, shear stress, and heat transfer rate) of a cylinder in a Mach 10 flow of argon gas for several different flow regimes, from the continuum to a rarefied gas. CFD and DSMC solutions are obtained at each flow condition. Total drag predictions differ by less than 1% for a continuum flow while CFD predicts a 26% higher drag than DSMC for a rarefied flow. Peak heat transfer rate differences range from less than 1% for a continuum flow to more than 32% for a rarefied flow, again with CFD predicting the higher value. Differences in drag and heat transfer are expected to decrease with the use of velocity slip and temperature jump boundary conditions with the CFD method. (c) 2007 American Institute of Physics. C1 Univ Michigan, Dept Aerosp Engn, Ann Arbor, MI 48109 USA. NASA, Ames Res Ctr, Reacting Flow Environm Branch, Moffett Field, CA 94035 USA. RP Lofthouse, AJ (reprint author), Univ Michigan, Dept Aerosp Engn, Ann Arbor, MI 48109 USA. EM ajloft@umich.edu NR 24 TC 18 Z9 18 U1 2 U2 9 PU AMER INST PHYSICS PI MELVILLE PA CIRCULATION & FULFILLMENT DIV, 2 HUNTINGTON QUADRANGLE, STE 1 N O 1, MELVILLE, NY 11747-4501 USA SN 1070-6631 J9 PHYS FLUIDS JI Phys. Fluids PD FEB PY 2007 VL 19 IS 2 AR 027105 DI 10.1063/1.2710289 PG 12 WC Mechanics; Physics, Fluids & Plasmas SC Mechanics; Physics GA 140UC UT WOS:000244531200023 ER PT J AU Choueiri, EY Randolph, TM AF Choueiri, Edgar Y. Randolph, Thomas M. TI Ionization front in a high-current gas discharge SO PHYSICS OF PLASMAS LA English DT Article ID MPD THRUSTERS; MAGNETOPLASMADYNAMIC THRUSTER; MAGNETIC-FIELD; PLASMA; ACCELERATION; ARGON; MODEL AB Spectroscopic measurements of ion/neutral density ratio profiles are made inside the high-current, low-pressure discharge of a coaxial magnetoplasmadynamic thruster and show the existence of a thin ionization front, upstream in the discharge, that effectively ionizes the incoming gas to ionization levels above 50%. The measurements allow an estimate of the width of this ionization front to be on the order of a few millimeters. Due to the known existence of microturbulence in the plasma, which can produce suprathermal electrons, an explanation of the measurements based on the existence of a suprathermal tail in the electron energy distribution function is sought. A theoretical model for the width of the ionization front is combined with a multilevel excitation model for argon and shows that a Maxwellian electron distribution function cannot account for the small length scale of the ionization front, and that the latter is more consistent with an electron distribution function having a suprathermal population, the magnitude of which is estimated by comparing the model to the experiments. (c) 2007 American Institute of Physics. C1 Princeton Univ, Elect Prop & Plasma Dynam Lab, Princeton, NJ 08544 USA. NASA, Jet Prop Lab, Pasadena, CA 91109 USA. RP Choueiri, EY (reprint author), Princeton Univ, Elect Prop & Plasma Dynam Lab, Princeton, NJ 08544 USA. NR 40 TC 0 Z9 0 U1 0 U2 2 PU AMER INST PHYSICS PI MELVILLE PA CIRCULATION & FULFILLMENT DIV, 2 HUNTINGTON QUADRANGLE, STE 1 N O 1, MELVILLE, NY 11747-4501 USA SN 1070-664X J9 PHYS PLASMAS JI Phys. Plasmas PD FEB PY 2007 VL 14 IS 2 AR 023506 DI 10.1063/1.2646365 PG 11 WC Physics, Fluids & Plasmas SC Physics GA 140UD UT WOS:000244531300044 ER PT J AU Kuo, SP Bivolaru, D AF Kuo, Spencer P. Bivolaru, Daniel TI The similarity of shock waves generated by a cone-shaped plasma and by a solid cone in a supersonic airflow SO PHYSICS OF PLASMAS LA English DT Article ID MITIGATION AB A truncated 60 degrees cone with a slender central spike, which protrudes to the tip location of a perfect cone, is designed as a wind tunnel model. It generates a bow shock in a supersonic airflow. This model is featured with an on-board discharge arrangement with the central spike and the truncated cone as two electrodes. When the central electrode is designated as the cathode, a dc pulsed discharge produces a hollow cone-shaped plasma that envelops the spike. The results show that this plasma has changed the original bow shock to a conical shock, equivalent to reinstating the model into a perfect cone and to generate a 70% increase in the body aspect ratio. A significant drag reduction in each discharge is inferred from the pressure measurements; at the discharge maximum, the pressure on the frontal surface of the body decreases by more than 30%, the pressure on the cone surface increases by about 5%, while the pressure on the cylinder surface remains unchanged. The energy loss due to wave drag is reduced to make up for the two-thirds of the energy consumed in the electric discharge for plasma generation. The measurements also show that the plasma effect on shock structure lasts much longer than the discharge period. (c) 2007 American Institute of Physics. C1 Polytech Univ, Dept Elect & Comp Engn, Brooklyn, NY 11201 USA. RP Kuo, SP (reprint author), NASA, Langley Res Ctr, Hampton, VA 23681 USA. NR 18 TC 6 Z9 7 U1 0 U2 8 PU AMER INST PHYSICS PI MELVILLE PA CIRCULATION & FULFILLMENT DIV, 2 HUNTINGTON QUADRANGLE, STE 1 N O 1, MELVILLE, NY 11747-4501 USA SN 1070-664X J9 PHYS PLASMAS JI Phys. Plasmas PD FEB PY 2007 VL 14 IS 2 AR 023503 DI 10.1063/1.2437747 PG 5 WC Physics, Fluids & Plasmas SC Physics GA 140UD UT WOS:000244531300041 ER PT J AU Morrison, D AF Morrison, David TI Debate about science and religion continues SO PHYSICS TODAY LA English DT Letter C1 NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Morrison, D (reprint author), NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. EM dmorrison@arc.nasa.gov NR 0 TC 0 Z9 0 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA CIRCULATION & FULFILLMENT DIV, 2 HUNTINGTON QUADRANGLE, STE 1 N O 1, MELVILLE, NY 11747-4501 USA SN 0031-9228 J9 PHYS TODAY JI Phys. Today PD FEB PY 2007 VL 60 IS 2 BP 10 EP 10 PG 1 WC Physics, Multidisciplinary SC Physics GA 133ZB UT WOS:000244051300003 ER PT J AU Encrenaz, T Sotin, C McCleese, D Head, J AF Encrenaz, Th. Sotin, C. McCleese, D. Head, J. TI Special issue of planetary of space science planet Mars II: A new image of planet Mars - Preface SO PLANETARY AND SPACE SCIENCE LA English DT Editorial Material ID ICE; EVOLUTION; ATMOSPHERE; OBLIQUITY; DEPOSITS; GLACIERS; METHANE; CLIMATE C1 Observ Paris, LESIA, F-92195 Meudon, France. Univ Nantes, Lab Planetol & Geodynam, F-44072 Nantes 3, France. Jet Propuls Lab, Pasadena, CA 91109 USA. Brown Univ, Dept Geol Sci, Providence, RI 02912 USA. RP Encrenaz, T (reprint author), Observ Paris, LESIA, F-92195 Meudon, France. EM therese.encrenaz@obspm.fr NR 27 TC 0 Z9 0 U1 0 U2 1 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 FEB PY 2007 VL 55 IS 3 SI SI BP 255 EP 257 DI 10.1016/j.pss.2006.06.017 PG 3 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 143BR UT WOS:000244695500001 ER PT J AU Langlais, B Purucker, M AF Langlais, Benoit Purucker, Michael TI A polar magnetic paleopole associated with Apollinaris Patera, Mars SO PLANETARY AND SPACE SCIENCE LA English DT Article; Proceedings Paper CT International Workshop on Planet Mars II CY MAY 23-JUN 01, 2005 CL Les Houches, FRANCE DE mars; magnetic fields; paleopoles; apollinaris patera ID GLOBAL SURVEYOR; INVERSE-THEORY; CRUST; POSITIONS AB A Martian paleomagnetic pole is calculated from a magnetic anomaly associated with the late Noachian age (and older) volcano Apollinaris Patera. This isolated volcano, located near the crustal dichotomy boundary at the Martian equator, has a correlative gravity anomaly, and was likely active for more than 107 years. It is one of the only volcanoes on Mars known to have a substantial magnetic anomaly associated with it, and one of the only examples of correlative magnetic and gravity sources. Magnetic directions calculated using either low- or high-altitude data, and single or multiple equivalent source dipoles, are nearly horizontal and southward directed. Assuming a single dipolar source magnetization, the preferred paleopole is at 65 degrees S, 59 degrees E. Assuming a larger magnetized area leads to a cluster of paleopoles near 88 degrees S, 99 degrees E. This paleopole is very close to the current rotation pole, and very different from previously calculated paleopoles. Our preferred interpretation is that the Apollinaris Patera magnetization was acquired near the end of the life of the Martian dynamo, and that subsequent polar wander was minimal. (c) 2006 Elsevier Ltd. All rights reserved. C1 Univ Nantes, Nantes Atlantic Univ, Lab Planetol & Geodynam, CNRS,UMR 6112, F-44000 Nantes, France. NASA, NAS, NRC, Planetary Geodynam Branch,GSFC, Greenbelt, MD 20771 USA. NASA, GSFC, Raytheon, Planetary Geodynam Branch, Greenbelt, MD 20771 USA. RP Langlais, B (reprint author), Univ Nantes, Nantes Atlantic Univ, Lab Planetol & Geodynam, CNRS,UMR 6112, 2 Rue Houssiniere, F-44000 Nantes, France. EM benoit.langlais@univ-nantes.fr; purucker@geomag.gsfc.nasa.gov RI Langlais, Benoit/K-5366-2012 OI Langlais, Benoit/0000-0001-5207-304X NR 37 TC 33 Z9 33 U1 0 U2 3 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 FEB PY 2007 VL 55 IS 3 SI SI BP 270 EP 279 DI 10.1016/j.pss.2006.03.008 PG 10 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 143BR UT WOS:000244695500003 ER PT J AU Milbury, CAE Smrekar, SE Raymond, CA Schubert, G AF Milbury, Colleen A. E. Smrekar, Suzanne E. Raymond, Carol A. Schubert, Gerald TI Lithospheric structure in the eastern region of Mars' dichotomy boundary SO PLANETARY AND SPACE SCIENCE LA English DT Article; Proceedings Paper CT International Workshop on Planet Mars II CY MAY 23-JUN 01, 2005 CL Les Houches, FRANCE DE mars; dichotomy; gravity; isostasy; crustal magnetism ID EFFECTIVE ELASTIC THICKNESS; MARTIAN HEMISPHERIC DICHOTOMY; CONTINENTAL LITHOSPHERE; ISOSTATIC COMPENSATION; CRUSTAL DICHOTOMY; PHASE-TRANSITIONS; MANTLE CONVECTION; SPECTRAL-ANALYSIS; MAGNETIC-FIELD; EVOLUTION AB We examine gravity, topography, and magnetic field data along the well-preserved Martian dichotomy boundary between 105 and 180 degrees E to better understand the origin and modification of the dichotomy boundary. Admittance modeling indicates bottom-loading for the Amenthes region (105-135 degrees E) with crustal and elastic thickness estimates of 15-40 km, and 15-35 km and top-loading for the Aeolis region (145-180 degrees E) with crustal and elastic thickness estimates of 10-20 km and 10-15 km, respectively. There is a general trend from bottom-loading in the west, to top-loading in the east. The bottom-loading signature near Amenthes may reflect its proximity to the Isidis basin or a broad valley southeast of Isidis. Surface volcanic deposits may produce the top-loading seen at Aeolis. Additional processes such as erosion and faulting have clearly affected the dichotomy and may contribute to the loading signature. Low elastic thickness estimates are consistent with loading in the Noachian, when heat flow was high. Significant Bouguer and isostatic gravity anomalies in these areas indicate substantial variations in the crustal density structure. Crater age dating indicates that major surface modification occurred early in the Noachian, and the small elastic thickness estimates also suggest that subsurface modification occurred in the Noachian. Magnetic and gravity anomalies show comparable spatial scales (several hundred kilometers). The similarity in scale and the constant ratio of the amplitudes of the isostatic and Bouguer gravity to the magnetic anomalies along the dichotomy suggest a common origin for the anomalies. Igneous intrusion and/or local thinning or thickening of the crust, possibly with a contribution from hydrothermal alteration, are the most likely mechanisms to create the observed anomalies. (c) 2006 Elsevier Ltd. All rights reserved. C1 Univ Calif Los Angeles, Dept Earth & Space Sci, Los Angeles, CA 90024 USA. CALTECH, Jet Propuls Lab, Pasadena, CA 91125 USA. Univ Calif Los Angeles, Inst Geophys & Planetary Phys, Los Angeles, CA 90024 USA. RP Milbury, CAE (reprint author), Univ Calif Los Angeles, Dept Earth & Space Sci, Los Angeles, CA 90024 USA. EM emilbury@ess.ucla.edu NR 49 TC 7 Z9 7 U1 0 U2 1 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 FEB PY 2007 VL 55 IS 3 SI SI BP 280 EP 288 DI 10.1016/j.pss.2006.03.009 PG 9 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 143BR UT WOS:000244695500004 ER PT J AU Atreya, SK Mahaffy, PR Wong, AS AF Atreya, Sushil K. Mahaffy, Paul R. Wong, Ah-San TI Methane and related trace species on Mars: Origin, loss, implications for life, and habitability SO PLANETARY AND SPACE SCIENCE LA English DT Article; Proceedings Paper CT International Workshop on Planet Mars II CY MAY 23-JUN 01, 2005 CL Les Houches, FRANCE DE mars; methane; life; habitability; oxidants; hydrogen peroxide; electrochemistry; triboelectricity; dust devils; serpentinization; mars; science laboratory; sample analysis at mars ID MARTIAN SURFACE-CHEMISTRY; OXIDANT ENHANCEMENT; HYDROGEN-PEROXIDE; DUST DEVILS; HOT-SPOTS; ATMOSPHERE; PHOTOCHEMISTRY; STABILITY; COMETS; MODEL AB One of the most puzzling aspects of Mars is that organics have not yet been found on the surface. The simplest of organic molecules, methane, was detected in the Martian atmosphere for the first time in 2003. The existence and behavior of methane on Mars is of great significance, as methane is a potential biomarker. In this paper we review our current understanding of possible sources and sinks of methane on Mars. We also investigate the role of other trace species in the maintenance and removal of methane from the atmosphere, as well as of other organic material from the surface. In particular, we examine the exogenous, hydrogeochemical-especially serpentinization-and biological sources, for supplying methane to Mars. We suggest that comets and meteorites are the least likely, whereas low-temperature serpentinization is the most plausible of all candidates to explain the methane observations. Nevertheless, it is premature to rule out the role of biology in producing methane on Mars, in view of available data. It is important to note that the loss of methane to surface must also be factored into any "source" scenarios for methane. Ordinary heterogeneous loss process to surface tends to be very slow. On the other hand, a reactive surface could potentially accelerate the destruction of methane. If correct, it would imply that a larger source of methane is present than currently estimated on the basis of photochemical loss alone. A reactive surface can also explain why no organic material has ever been detected on the Martian surface. The surface could become reactive if some oxidizer were present. We suggest that vast quantities of a powerful oxidant, hydrogen peroxide, can be produced in electrochemistry triggered by electrostatic fields generated in the Martian dust devils and dust storms, and in normal saltation process close to the surface. Finally, current observations are inadequate to prove or disprove the existence of life on Mars, now or in the past. The question of extraterrestrial life is a fundamental one, and it should be addressed meticulously on future missions to Mars. Measurements planned on the Mars Science Laboratory (MSL), especially carbon isotopes and chirality, will go a long way in meeting this goal. A brief overview of the MSL Mission and measurements relevant to the question of life and habitability of Mars is also presented in this paper. (c) 2006 Elsevier Ltd. All rights reserved. C1 Univ Michigan, Dept Atmospher Ocean & Space Sci, Ann Arbor, MI 48109 USA. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Atreya, SK (reprint author), Univ Michigan, Dept Atmospher Ocean & Space Sci, Space Res Bldg, Ann Arbor, MI 48109 USA. EM atreya@umich.edu RI Mahaffy, Paul/E-4609-2012 NR 65 TC 122 Z9 123 U1 23 U2 76 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 FEB PY 2007 VL 55 IS 3 SI SI BP 358 EP 369 DI 10.1016/j.pss.2006.02.005 PG 12 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 143BR UT WOS:000244695500009 ER PT J AU Walborn, NR Smith, N Howarth, ID Kober, GV Gull, TR Morse, JA AF Walborn, Nolan R. Smith, Nathan Howarth, Ian D. Kober, Gladys Vieira Gull, Theodore R. Morse, Jon A. TI Interstellar absorption-line evidence for high-velocity expanding structures in the Carina Nebula foreground SO PUBLICATIONS OF THE ASTRONOMICAL SOCIETY OF THE PACIFIC LA English DT Article ID ETA-CARINAE; SPECTROGRAPH; PROFILES; EJECTA; STARS AB The extreme, high-velocity interstellar absorption-line profiles toward h Carinae and 16 neighboring stars in Trumpler 16 are examined, including several new sight lines observed in the ultraviolet with the Hubble Space Telescope or in the optical from the Magellan and European Southern Observatories. No two sight lines are identical, but many velocity components are in common. When the velocity scale is shifted to a standard of rest defined by the Carina Nebula emission lines, the symmetries between negative and positive velocities are striking; at least 15 distinct "shells" can be recognized. This circumstance suggests that the complex expanding structures are predominantly in front of the ionizing cluster. There may be a relationship to indications of a supernova remnant in this direction, including a recent Chandra X-Ray Observatory image. Interpretations in terms of high-energy phenomena generated by ongoing star formation possibly on the near side of the giant H II region are also discussed. C1 Space Telescope Sci Inst, Baltimore, MD 21218 USA. Univ Colorado, Ctr Astrophys & Space Astron, Boulder, CO 80309 USA. UCL, Dept Phys & Astron, London, England. NASA, Goddard Space Flight Ctr, Lab Extraterr Planets & Stellar Astrophys, Greenbelt, MD 20771 USA. Sci Syst & Applicat Inc, Lanham, MD USA. Arizona State Univ, Dept Phys & Astron, Tempe, AZ 85287 USA. RP Walborn, NR (reprint author), Space Telescope Sci Inst, Baltimore, MD 21218 USA. EM walborn@stsci.edu; nathans@astro.berkeley.edu; idh@star.ucl.ac.uk; gvieira@dusty.gsfc.nasa.gov; gull@milkyway.gsfc.nasa.gov; jmorse@milkyway.gsfc.nasa.gov RI Gull, Theodore/D-2753-2012 OI Gull, Theodore/0000-0002-6851-5380 NR 33 TC 10 Z9 10 U1 0 U2 0 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 FEB PY 2007 VL 119 IS 852 BP 156 EP 169 DI 10.1086/511756 PG 14 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 138TS UT WOS:000244386200004 ER PT J AU Bailey, J Simpson, A Crisp, D AF Bailey, Jeremy Simpson, Andrew Crisp, David TI Correcting infrared spectra for atmospheric transmission SO PUBLICATIONS OF THE ASTRONOMICAL SOCIETY OF THE PACIFIC LA English DT Article ID MOLECULAR SPECTROSCOPIC DATABASE; MULTIPLE-SCATTERING; VENUS NIGHTSIDE; ABSORPTION; OXYGEN; RADIATION; ABUNDANCE; EMISSION; AIRGLOW; MODEL AB Astronomical spectra taken with ground-based telescopes in the near-IR spectral region are affected by strong absorptions due to molecules in the Earth's atmosphere, particularly CO2 and H2O. These features need to be removed in order to reveal the true spectrum of the object being observed. The traditional technique for doing this is to observe a standard star with a relatively featureless spectrum (a smooth spectrum standard) and divide the observed spectrum of the object by that of the standard. This technique has a number of practical difficulties but is also fundamentally flawed. Even with a perfectly smooth spectrum standard observed at an identical air mass to the object, this technique does not, in general, reproduce the spectrum of the object that would have been observed in the absence of the Earth's atmosphere. The problem arises because of the presence of high-resolution structure in the molecular absorption features, generally on a finer scale than the resolution of the observed spectrum. The transmission of the Earth's atmosphere for any spectral bin then depends on the unresolved spectral structure of the light being transmitted and cannot be represented by a unique value derived from the standard star, as the traditional technique assumes. We use high-resolution line-by-line radiative transfer models to quantify these effects for two cases: observations of a solar-type star, and observations of the planet Mars. For a solar-type star, application of the traditional technique causes errors of a few percent in the vicinity of strong atmospheric absorption features. The case of the planet Mars is an extreme case, since Mars has the same CO2 absorption features as the Earth's atmosphere. Our simulations show that applying the traditional astronomical technique to ground-based spectra of the planet Mars leads to systematic errors of up to similar to 50% in the vicinity of the strong CO2 absorption features. High-quality IR spectroscopy with ground-based telescopes requires an improved technique to handle the absorption in the Earth's atmosphere. We outline a possible approach based on the use of radiative transfer models for the Earth's atmosphere. We note that in general it is not possible to correct observed spectra for atmospheric absorption. However, a forward-modeling approach can be used in which a model spectrum for the object is generated, atmospheric transmission effects added, and the result compared with the observed spectrum. We present a demonstration of the ability of a model to accurately represent the Earth atmosphere transmission in the J band. C1 Macquarie Univ, Australian Ctr Astrobiol, Sydney, NSW 2109, Australia. CALTECH, Jet Prop Lab, Pasadena, CA USA. RP Bailey, J (reprint author), Macquarie Univ, Australian Ctr Astrobiol, Sydney, NSW 2109, Australia. EM jbailey@els.mq.edu.au NR 21 TC 24 Z9 24 U1 0 U2 4 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 FEB PY 2007 VL 119 IS 852 BP 228 EP 236 DI 10.1086/512824 PG 9 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 138TS UT WOS:000244386200009 ER PT J AU Idris, AH Convertino, VA Ratliff, DA Doerr, DF Lurie, KG Gabrielli, A Banner, MJ AF Idris, Aharned H. Convertino, Victor A. Ratliff, Duane A. Doerr, Donald F. Lurie, Keith G. Gabrielli, Andrea Banner, Michael J. TI Imposed power of breathing associated with use of an impedance threshold device SO RESPIRATORY CARE LA English DT Article; Proceedings Paper CT 34th Critical Care Congress of the Society-of-Critical-Care-Medicine CY 2005 CL Phoenix, AZ SP Soc Crit Care Med DE respiration; power of breathing; minute ventilation; inspiratory pressure; hypotension ID DECOMPRESSION CARDIOPULMONARY-RESUSCITATION; INSPIRATORY IMPEDANCE; CARDIAC-ARREST; HEMODYNAMIC-RESPONSES; HEMORRHAGIC-SHOCK; MECHANICAL WORK; PORCINE MODEL; VALVE; SPACEFLIGHT; HYPOTENSION AB OBJECTIVE: To measure the imposed power of breathing (imposed work of breathing per minute) associated with spontaneous breathing through an active impedance threshold device and a sham impedance threshold device. DESIGN: Prospective randomized blinded protocol. SETTING: University medical center. PATIENTS: Nineteen healthy, normotensive volunteers (10 males, 9 females, age range 20-56 y, mean +/- SD weight 54.8 +/- 7.7 kg for females, 84 +/- 8 kg for males). METHODS: The volunteers completed 2 trials of breathing through a face mask fitted with an active impedance threshold device set to open at -7 cm H(2)O pressure, or with a sham impedance threshold device, which was identical to the active device except that it did not contain an inspiratory threshold pressure valve diaphragm. Spontaneous breathing frequency (f), tidal volume (V(T)), exhaled minute ventilation, inspiratory pressure, and inspiratory time were measured with a respiratory monitor, and the data were directed to a laptop computer for real-time calculation of the imposed power of breathing. RESULTS: There were no significant differences in heart rate, respiratory rate, tidal volume, and minute ventilation, with and without inspiratory impedance. For the sham and active impedance threshold device groups, respectively, the mean +/- SD imposed power of breathing values were 0.92 +/- 0.63 J/min and 8.18 +/- 4.52 J/min (p < 0.001), the mean +/- SD inspiratory times were 1.98 +/- 0.86 s and 2.97 +/- 1.1 s (p = 0.001), and the mean +/- SD inspiratory airway/mouth pressures were -1.1 +/- 0.6 cm H(2)O and -11.7 +/- 2.4 cm H(2)O (p < 0.001). CONCLUSIONS: Breathing through an active impedance threshold device requires significantly more power than breathing through a sham device. All subjects tolerated the respiratory work load and were able to complete the study protocol. C1 Univ Florida, Coll Med, Dept Anesthesiol, Gainesville, FL 32610 USA. Univ Texas, SW Med Ctr, Dept Surg, Dallas, TX 75235 USA. Univ Texas, SW Med Ctr, Dept Emergency Med, Dallas, TX 75235 USA. USA, Inst Surg Res, Ft Sam Houston, TX 78234 USA. NASA, Bionet Corp, Kennedy Space Ctr, FL USA. NASA, Biol & Chem Labs Branch, Kennedy Space Ctr, FL USA. Adv Circulatory Syst, Eden Prairie, MN USA. Univ Minnesota, Dept Emergency Med, Minneapolis, MN USA. Univ Florida, Coll Med, Dept Physiol, Gainesville, FL 32610 USA. Univ Florida, Coll Med, Dept Surg, Gainesville, FL 32610 USA. RP Banner, MJ (reprint author), Univ Florida, Coll Med, Dept Anesthesiol, POB 100254, Gainesville, FL 32610 USA. FU NHLBI NIH HHS [HL077887] NR 26 TC 16 Z9 16 U1 0 U2 3 PU DAEDALUS ENTERPRISES INC PI IRVING PA 9425 N MAC ARTHUR BLVD, STE 100, IRVING, TX 75063-4706 USA SN 0020-1324 J9 RESP CARE JI Respir. Care PD FEB PY 2007 VL 52 IS 2 BP 177 EP 183 PG 7 WC Critical Care Medicine; Respiratory System SC General & Internal Medicine; Respiratory System GA 133XN UT WOS:000244047300006 PM 17261206 ER PT J AU Lester, ED Satomi, M Ponce, A AF Lester, Elizabeth D. Satomi, Masataka Ponce, Adrian TI Microflora of extreme arid Atacama Desert soils SO SOIL BIOLOGY & BIOCHEMISTRY LA English DT Article DE Atacama desert; Chile; extreme and desert; anhydrobiology; life in extreme environments ID MICROBIAL LIFE; MARS; CHILE AB Surface and subsurface soil samples from the most and region within the Atacama Desert, Chile, were analyzed for total organic carbon (TOC), phospholipid fatty acids (PLFA) and culturable bacteria. TOC content was determined to range between 560 and 765 mu g/g. PLFA analysis indicated 2.0 x 10(6)-1.0 x 10(7) cell equivalents/g. Culturing of soil extracts on R2A and TSA media yielded 1.6 x 10(3)-4.6 x 10(3) CFU/g, and 200-300 CFU/g heat shock survivors. Twenty isolated strains were identified based on analysis of 16S rRNA gene sequences, and divided into eight phylogenetic groups, including Rhodopseudomonas, Sphingomonas sp., Mesorhizohium sp., Asticcacaulis sp., Bradyrhizobium sp., Bacillus subtilis, Bacillus pumilus, and Burkholderia sp. (c) 2006 Elsevier Ltd. All rights reserved. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Ponce, A (reprint author), CALTECH, Jet Prop Lab, MS 300-123,4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Adrian.Ponce@jpl.nasa.gov NR 22 TC 73 Z9 77 U1 3 U2 31 PU PERGAMON-ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0038-0717 J9 SOIL BIOL BIOCHEM JI Soil Biol. Biochem. PD FEB PY 2007 VL 39 IS 2 BP 704 EP 708 DI 10.1016/j.soilbio.2006.09.020 PG 5 WC Soil Science SC Agriculture GA 122ES UT WOS:000243209100036 ER PT J AU Schmahl, EJ Pernak, RL Hurford, GJ Lee, J Bong, S AF Schmahl, E. J. Pernak, R. L. Hurford, G. J. Lee, J. Bong, S. TI Analysis of RHESSI flares using a radio astronomical technique SO SOLAR PHYSICS LA English DT Article DE Sun : X-rays; Sun : flares; instruments; image processing; numerical methods AB We have used Ramaty High Energy Solar Spectroscopic Imager (RHESSI) modulation profiles in the 25-300 keV range to construct high-fidelity visibilities of 25 flares having at least two components. These hard X-ray visibilities, which are mathematically identical to the visibilities of radio imaging, were input to software developed for mapping solar flares in the microwave domain using the Maximum Entropy Method (MEM). We compared and contrasted the MEM maps with Clean and Pixon maps made with RHESSI software. In particular, we assessed the reliability of the maps and their morphologies for future investigations of the symmetry of bipolar electron beaming in the sample set. C1 NASA, Goddard Space Flight Ctr, Lab Solar & Space Phys, Greenbelt, MD 20771 USA. Univ Maryland, Dept Astron, College Pk, MD 20742 USA. Catholic Univ Amer, Inst Astrophys & Computat Sci, Washington, DC 20064 USA. Univ Calif Berkeley, Space Sci Lab, Berkeley, CA 94720 USA. New Jersey Inst Technol, Ctr Solar & Terr Res, Newark, NJ 07102 USA. Korean Astron & Space Sci Inst, Taejon 305348, South Korea. RP Pernak, RL (reprint author), NASA, Goddard Space Flight Ctr, Lab Solar & Space Phys, Greenbelt, MD 20771 USA. EM pernak@lssp-mail.gsfc.nasa.gov NR 12 TC 39 Z9 39 U1 0 U2 4 PU SPRINGER PI DORDRECHT PA VAN GODEWIJCKSTRAAT 30, 3311 GZ DORDRECHT, NETHERLANDS SN 0038-0938 J9 SOL PHYS JI Sol. Phys. PD FEB PY 2007 VL 240 IS 2 BP 241 EP 252 DI 10.1007/s11207-007-0263-1 PG 12 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 152LM UT WOS:000245363500004 ER PT J AU Zhong, ZM AF Zhong, Zhimin TI Stability and conductivity study of the BaCe0.9-xZrxY0.1O2.95 systems SO SOLID STATE IONICS LA English DT Article DE proton conduction; stoichiometry; chemical stability; SOFC electrolyte; BaCeO3; BaZrO3 ID WATER-CONTAINING ATMOSPHERES; PROTON CONDUCTORS; COMBUSTION SYNTHESIS; SOLID ELECTROLYTES; CHEMICAL-STABILITY; NEUTRON-SCATTERING; BACEO3; PEROVSKITE; CERAMICS; NANOPARTICLES AB Solid oxide components such as protonic separation membranes for the hydrogen purification and electrolyte for solid oxide fuel cell require thermo-chemical stability and high conductance. The perovskite BaCe0.9Y0.1O2.95 exhibits good proton conduction at high temperatures, but shows poor thermo-chemical stability. Substituting Zr for Cc in BaCe0.9Y0.1O2.95 improves the thermo-chemical stability but reduces proton conduction. The objective of this work was to study the optimization of protonic conductance and thermo-chemical stability by changing the ratio of Ce to Zr in BaCe0.9-xZrxY0.1O2.95. To elucidate the dopant effect, a coprecipitation and freeze drying method has been developed to produce single phase perovskites of BaCe0.9-xZrxY0.1O2.95 (0 <= x <= 0.9). The method has been optimized to yield high purity and homogeneous powders with a particle size of 50-100 nm in diameter. The sintering characteristics were studied in the temperature range of 1400-1650 degrees C. BaCe0.9Y0.1O2.95, BaCe0.7Zr0.2Y0.1O2.95 and BaCe0.5Zr0.4Y0.1O2.95 can be sintered to high density at 1650 degrees C. Sintered BaCe0.5Zr0.4Y0.1O2.95 and BaCe0.3Zr0.6Y0.1O2.95 show good chemical stability against water and carbon dioxide. Electric conductivities of sintered samples, which have been measured by impedance spectroscopy, decrease with their Zr content. (c) 2006 Elsevier B.V. All rights reserved. C1 NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Zhong, ZM (reprint author), NexTech Mat Ltd, 404 Enterprise Dr, Lewis Ctr, OH 43035 USA. EM zhong11135@yahoo.com NR 42 TC 156 Z9 159 U1 5 U2 61 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS SN 0167-2738 J9 SOLID STATE IONICS JI Solid State Ion. PD FEB PY 2007 VL 178 IS 3-4 BP 213 EP 220 DI 10.1016/j.ssi.2006.12.007 PG 8 WC Chemistry, Physical; Physics, Condensed Matter SC Chemistry; Physics GA 155YZ UT WOS:000245616100007 ER PT J AU Dick, SJ AF Dick, Steven J. TI Assessing the impact of space on society SO SPACE POLICY LA English DT Article AB There have been surprisingly few studies of the societal impact of space exploration, yet the impact has been considerable, and wide ranging. After briefly reviewing what has been published, the author reports on activities by NASA to improve our understanding of this issue. In accordance with the National Aeronautics and Space Act of 1958, the NASA History Division has initiated a series of special studies and conferences on the societal impact of spaceflight. The first conference, held 19-21 September 2006 in Washington, DC and co-sponsored by the National Air and Space Museum, included some 35 speakers who addressed six main categories, spanning international, commercial, cultural, environmental and national security impacts. For both the conferences and the special studies, the goal is to examine the multifaceted impacts of spaceflight with rigorous historical research. (C) 2006 Elsevier Ltd. All rights reserved. C1 NASA HQ, Washington, DC 20546 USA. RP Dick, SJ (reprint author), NASA HQ, Washington, DC 20546 USA. EM steven.j.dick@nasa.gov NR 7 TC 2 Z9 2 U1 0 U2 0 PU ELSEVIER SCI LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD OX5 1GB, OXON, ENGLAND SN 0265-9646 J9 SPACE POLICY JI Space Policy PD FEB PY 2007 VL 23 IS 1 BP 29 EP 32 DI 10.1016/j.spacepol.2006.11.004 PG 4 WC International Relations; Social Sciences, Interdisciplinary SC International Relations; Social Sciences - Other Topics GA 141LC UT WOS:000244579000007 ER PT J AU Parker, PA Kowalski, SM Vining, GG AF Parker, Peter A. Kowalski, Scott M. Vining, G. Geoffrey TI Construction of balanced equivalent estimation second-order split-plot designs SO TECHNOMETRICS LA English DT Article DE central composite design; equivalent estimation design; restricted randomization; split-plot design ID RESPONSE-SURFACE DESIGNS AB Practical restrictions on randomization are commonplace in industrial experiments due to the presence of hard-to-change or costly-to-change factors. Using a split-plot design (SPD) structure reduces the number of times that these hard-to-change factors are reset during the experiment. A class of second-order response surface SPDs has been proposed in which the ordinary least squares estimates of the model are equivalent to the generalized least squares estimates. Equivalent estimation designs provide best linear unbiased estimates that are independent of the variance components and can be obtained with standard statistical software. Moreover, design selection is robust to model m is specification and does not require previous knowledge of the variance components. This article expands the conditions to obtain equivalent estimation designs and outlines two systematic design construction techniques for building balanced versions of the central composite design. In addition, it presents an approach to generating equivalent estimation D-optimal designs. By applying these design construction techniques, a catalog of designs is generated. These methods provide practitioners with the necessary tools to build equivalent estimation SPDs for a wide variety of applications. C1 NASA, Hampton, VA 23681 USA. Minitab Inc, State Coll, PA 16801 USA. Virginia Polytech Inst & State Univ, Dept Stat, Blacksburg, VA 24061 USA. RP Parker, PA (reprint author), NASA, Hampton, VA 23681 USA. EM peter.a.parker@nasa.gov; Skowalski@minitab.com; vining@vt.edu NR 22 TC 26 Z9 27 U1 0 U2 4 PU AMER STATISTICAL ASSOC PI ALEXANDRIA PA 1429 DUKE ST, ALEXANDRIA, VA 22314 USA SN 0040-1706 J9 TECHNOMETRICS JI Technometrics PD FEB PY 2007 VL 49 IS 1 BP 56 EP 65 DI 10.1198/004017006000000462 PG 10 WC Statistics & Probability SC Mathematics GA 132PK UT WOS:000243954500006 ER PT J AU Myhre, G Bellouin, N Berglen, TF Berntsen, TK Boucher, O Grini, A Isaksen, ISA Johnsrud, M Mishchenko, MI Stordal, F Tanre, D AF Myhre, Gunnar Bellouin, Nicolas Berglen, Tore F. Berntsen, Terje K. Boucher, Olivier Grini, Alf Isaksen, Ivar S. A. Johnsrud, Mona Mishchenko, Michael I. Stordal, Frode Tanre, Didier TI Comparison of the radiative properties and direct radiative effect of aerosols from a global aerosol model and remote sensing data over ocean SO TELLUS SERIES B-CHEMICAL AND PHYSICAL METEOROLOGY LA English DT Article ID BLACK CARBON AEROSOLS; TROPOSPHERIC AEROSOLS; SULFATE AEROSOLS; SATELLITE MEASUREMENTS; ANTHROPOGENIC SULFATE; OPTICAL-PROPERTIES; C-130 AIRCRAFT; SOOT AEROSOLS; AIR-POLLUTION; OZONE CHANGES AB A global aerosol transport model (Oslo CTM2) with main aerosol components included is compared to five satellite retrievals of aerosol optical depth (AOD) and one data set of the satellite-derived radiative effect of aerosols. The model is driven with meteorological data for the period November 1996 to June 1997 which is the time period investigated in this study. The modelled AOD is within the range of the AOD from the various satellite retrievals over oceanic regions. The direct radiative effect of the aerosols as well as the atmospheric absorption by aerosols are in both cases found to be of the order of 20 Wm(-2) in certain regions in both the satellite-derived and the modelled estimates as a mean over the period studied. Satellite and model data exhibit similar patterns of aerosol optical depth, radiative effect of aerosols, and atmospheric absorption of the aerosols. Recently published results show that global aerosol models have a tendency to underestimate the magnitude of the clear-sky direct radiative effect of aerosols over ocean compared to satellite-derived estimates. However, this is only to a small extent the case with the Oslo CTM2. The global mean direct radiative effect of aerosols over ocean is modelled with the Oslo CTM2 to be -5.5 Wm(-2) and the atmospheric aerosol absorption 1.5 Wm(-2). C1 Univ Oslo, Dept Geosci, N-0315 Oslo, Norway. Ctr Int Climate & Environm Res, Oslo, Norway. Norwegian Inst Air Res, Kjeller, Norway. Met Off, Exeter, Devon, England. Meteo France, CNRM, GMEI, Toulouse, France. NASA, Goddard Inst Space Studies, New York, NY 10025 USA. Univ Sci & Tech Lille Flandres Artois, CNRS, Opt Atmospher Lab, Villeneuve Dascq, France. RP Myhre, G (reprint author), Univ Oslo, Dept Geosci, POB 1022, N-0315 Oslo, Norway. EM gunnar.myhre@geo.uio.no RI Myhre, Gunnar/A-3598-2008; Boucher, Olivier/J-5810-2012; Boucher, Olivier/K-7483-2012; Mishchenko, Michael/D-4426-2012; OI Myhre, Gunnar/0000-0002-4309-476X; Boucher, Olivier/0000-0003-2328-5769; Boucher, Olivier/0000-0003-2328-5769; Stordal, Frode/0000-0002-5190-6473; Bellouin, Nicolas/0000-0003-2109-9559 NR 83 TC 53 Z9 54 U1 1 U2 16 PU BLACKWELL PUBLISHING PI OXFORD PA 9600 GARSINGTON RD, OXFORD OX4 2DQ, OXON, ENGLAND SN 0280-6509 J9 TELLUS B JI Tellus Ser. B-Chem. Phys. Meteorol. PD FEB PY 2007 VL 59 IS 1 BP 115 EP 129 DI 10.1111/j.1600-0889.2006.00226.x PG 15 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA 128TH UT WOS:000243681100010 ER PT J AU DellaCorte, C AF DellaCorte, Christopher TI Like pennies from heaven 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 0 PU SOC TRIBOLOGISTS & LUBRICATION ENGINEERS PI PARK RIDGE PA 840 BUSSE HIGHWAY, PARK RIDGE, IL 60068 USA SN 1545-858X J9 TRIBOL LUBR TECHNOL JI Tribol. Lubr. Technol. PD FEB PY 2007 VL 63 IS 2 BP 6 EP 6 PG 1 WC Engineering, Mechanical SC Engineering GA 135BG UT WOS:000244128200002 ER PT J AU Wilson, RJ Neumann, GA Smith, MD AF Wilson, R. John Neumann, Gregory A. Smith, Michael D. TI Diurnal variation and radiative influence of Martian water ice clouds SO GEOPHYSICAL RESEARCH LETTERS LA English DT Article ID THERMAL EMISSION SPECTROMETER; GENERAL-CIRCULATION MODEL; MARS; ATMOSPHERE; TIDES; CYCLE AB We have identified regions in the Martian tropics with anomalously warm nighttime surface temperatures. The seasonal evolution of these anomalies is strongly correlated with the waxing and waning of the tropical cloud belt that is most prominent during Northern Hemisphere summer. We attribute the anomalies to enhanced downward infrared radiation from water ice clouds. The close agreement with spatial maps of atmospheric extinction derived from Mars Orbiter Laser Altimeter radiometry strongly supports this interpretation. We show that a Mars general circulation model simulation with radiatively active water ice clouds is able to reasonably match the observed spatial pattern and amplitude of the surface temperature anomaly. The nighttime clouds are most prominent in the Tharsis and Arabia regions and are thicker ( optical depth similar to 1) and more extensive than daytime clouds. Our cloud retrievals are the first to spatially map the nighttime clouds and provide an estimate of their thermal influence. C1 NOAA, Geophys Fluid Dynam Lab, Princeton, NJ 08542 USA. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Wilson, RJ (reprint author), NOAA, Geophys Fluid Dynam Lab, POB 308, Princeton, NJ 08542 USA. EM john.wilson@noaa.gov RI Smith, Michael/C-8875-2012; Neumann, Gregory/I-5591-2013 OI Neumann, Gregory/0000-0003-0644-9944 NR 17 TC 39 Z9 39 U1 0 U2 2 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 JAN 31 PY 2007 VL 34 IS 2 AR L02710 DI 10.1029/2006GL027976 PG 4 WC Geosciences, Multidisciplinary SC Geology GA 133VB UT WOS:000244040900002 ER PT J AU Holladay, JD Brooks, KP Wegeng, R Hu, J Sanders, J Baird, S AF Holladay, J. D. Brooks, K. P. Wegeng, R. Hu, J. Sanders, J. Baird, S. TI Microreactor development for Martian in situ propellant production SO CATALYSIS TODAY LA English DT Article; Proceedings Paper CT 19th Meeting of the North-American-Catalysis-Society (NAM) CY MAY 22-27, 2005 CL Philadelphia, PA SP N Amer Catalysis Soc DE in situ resource utilization; Sabatier reactor; reverse water-gas-shift reactor; microchannel reactors AB A process is presented for in situ resource utilization of indigenous resources on Mars to produce hydrocarbon propellants using microchannel reactors. The proposed system utilizes CO2 from the atmosphere on Mars and hydrogen brought from Earth. The CO2 is reacted in a Sabatier reactor (SR) to produce methane (propellant) and water. The water generated is electrolyzed to produce oxygen (oxidant). The hydrogen is recycled. The microchannel SR used in this study consisted of integrated cooling and reaction channels, was < 100 cm(3) in volume and 175 g in mass, and used a proprietary catalyst. When operated at 400 degrees C, 70-80% CO2 conversion was achieved, which enabled similar to 0.0125 kg CH4/h production or one-eighth the target mission-required throughput. The modular design of microchannel reactors would enable simple scale-up to full-scale production for the proposed mission. To produce the desired oxygen-to-methane ratio (3.8 by mass), a reverse water-gas-shift reactor (RWGS) converts CO2 and hydrogen to water and CO. Again, the water is electrolyzed and the hydrogen recycled; the CO is discarded. The RWGS system contained 30 microchannels in a four-reactor monolith (70 cm(3)). When operated at 700 degrees C and at a contact time of 36 ms, 0.09 kg/h O-2 generation (half-scale production for a sample Direct Robotic Earth Return Mission) was achieved, and 0.18 kg/h (full-scale production) was accomplished when operated at 18 ms. (c) 2006 Elsevier B.V. All rights reserved. C1 Pacific NW Natl Lab, Richland, WA 99354 USA. NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. RP Holladay, JD (reprint author), Pacific NW Natl Lab, POB 999, Richland, WA 99354 USA. EM JD.Holladay@pnl.gov NR 7 TC 6 Z9 6 U1 7 U2 19 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS SN 0920-5861 J9 CATAL TODAY JI Catal. Today PD JAN 30 PY 2007 VL 120 IS 1 BP 35 EP 44 DI 10.1016/j.cattod.2006.07.019 PG 10 WC Chemistry, Applied; Chemistry, Physical; Engineering, Chemical SC Chemistry; Engineering GA 110KX UT WOS:000242378900005 ER PT J AU Osinski, GR Schwarcz, HP Smith, JR Kleindienst, MR Haldemann, AFC Churcher, CS AF Osinski, Gordon R. Schwarcz, Henry P. Smith, Jennifer R. Kleindienst, Maxine R. Haldemann, Albert F. C. Churcher, Charles S. TI Evidence for a similar to 200-100 ka meteorite impact in the Western Desert of Egypt SO EARTH AND PLANETARY SCIENCE LETTERS LA English DT Article DE impact cratering; impact glass; sedimentary target rock; skeletal crystallites; impact melting ID SHOCK METAMORPHISM; SEDIMENTARY-ROCKS; MELT ROCKS; CRATER; MARS; MORPHOLOGY; VOLATILES; LITHOLOGY; OASIS; GLASS AB In this study, we present evidence, in the form of unusual silicate glasses, for a meteorite impact event similar to 200- 100 ka in the Dakhleh Oasis, Western Desert, Egypt. These glasses, known locally as Dakhlch Glass, were derived from the shock melting of a series of unconsolidated sediments underlain by interbedded carbonates, sandstones and phosphate-fich lithologies. Hypervelocity impact in to a volatile-rich target resulted in the production of impact glasses with CaO and Al2O3 contents of up to similar to 25 and 18 wt.%, respectively. Other notable properties include the presence of globules of immiscible calcite and pyrrhotite melt phases, shattered quartz grains, and fragments of silicified plant matter. Dating of geoarchaeological artefacts associated with the Dakhleh Glass support preliminary Ar-40/Ar-39 data, indicating a similar to 200- 100 ka age for the impact event. Geoarchaeological evidence indicates that archaic Homo sapiens and early modem humans continually inhabited this region of the Western Desert during this period. While it is unclear at present whether the Dakhleh Glass was formed during a cratering event or a large aerial burst, the effect on the environment and inhabitants of Dakhleh would have been catastrophic. (c) 2006 Elsevier B.V. All rights reserved. C1 Canadian Space Agcy, St Hubert, PQ J3Y 8Y9, Canada. McMaster Univ, Sch Geog & Earth Sci, Hamilton, ON L8S 4K1, Canada. Washington Univ, St Louis, MO 63130 USA. Univ Toronto, Dept Anthropol, Mississauga, ON L5L 1C6, Canada. CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. Univ Toronto, Dept Zool, Toronto, ON M5S 3G5, Canada. RP Osinski, GR (reprint author), Canadian Space Agcy, 6767 Route Aeroport, St Hubert, PQ J3Y 8Y9, Canada. EM gordon.osinski@space.gc.ca NR 36 TC 17 Z9 17 U1 0 U2 1 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS SN 0012-821X J9 EARTH PLANET SC LETT JI Earth Planet. Sci. Lett. PD JAN 30 PY 2007 VL 253 IS 3-4 BP 378 EP 388 DI 10.1016/j.epsl.2006.10.039 PG 11 WC Geochemistry & Geophysics SC Geochemistry & Geophysics GA 138SZ UT WOS:000244384100006 ER PT J AU Halekas, JS Delory, GT Brain, DA Lin, RP Fillingim, MO Lee, CO Mewaldt, RA Stubbs, TJ Farrell, WM Hudson, MK AF Halekas, J. S. Delory, G. T. Brain, D. A. Lin, R. P. Fillingim, M. O. Lee, C. O. Mewaldt, R. A. Stubbs, T. J. Farrell, W. M. Hudson, M. K. TI Extreme lunar surface charging during solar energetic particle events SO GEOPHYSICAL RESEARCH LETTERS LA English DT Article ID ADVANCED COMPOSITION EXPLORER; ACE OBSERVATIONS; SPACECRAFT AB We analyzed a series of solar energetic particle events in late April and early May of 1998, during which lunar surface potentials reached values as large as similar to -4.5 kV ( the largest recorded by Lunar Prospector). The two largest surface charging events during this time period correspond to energetic particle injections, when the electron flux between 50 keV and 5 MeV exceeded the proton flux over the same energy range. We searched the entire Lunar Prospector data set for other large negative surface charging events, and found that they occur almost exclusively during magnetotail crossings ( when the Moon encounters the plasmasheet) and solar energetic particle events. Lunar surface charging ( and its effect on the lunar dust environment) during inherently unpredictable space weather events represents a significant hazard for exploration. C1 Univ Calif Berkeley, Space Sci Lab, Berkeley, CA 94720 USA. Univ Calif Berkeley, Dept Phys, Berkeley, CA 94720 USA. CALTECH, Pasadena, CA 91125 USA. Univ Maryland Baltimore Cty, Goddard Earth Sci & Technol Ctr, Baltimore, MD 21228 USA. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Dartmouth Coll, Dept Phys & Astron, Hanover, NH 03755 USA. RP Halekas, JS (reprint author), Univ Calif Berkeley, Space Sci Lab, Berkeley, CA 94720 USA. EM jazzman@ssl.berkeley.edu RI Stubbs, Timothy/I-5139-2013; Farrell, William/I-4865-2013; OI Stubbs, Timothy/0000-0002-5524-645X; Halekas, Jasper/0000-0001-5258-6128 NR 14 TC 33 Z9 35 U1 0 U2 2 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 JAN 30 PY 2007 VL 34 IS 2 AR L02111 DI 10.1029/2006GL028517 PG 5 WC Geosciences, Multidisciplinary SC Geology GA 133VA UT WOS:000244040800005 ER PT J AU Fujimoto, R Mitsuda, K McCammon, D Takei, Y Bauer, M Ishisaki, Y Porter, FS Yamaguchi, H Hayashida, K Yamasaki, NY AF Fujimoto, Ryuichi Mitsuda, Kazuhisa McCammon, Dan Takei, Yoh Bauer, Michael Ishisaki, Yoshitaka Porter, F. Scott Yamaguchi, Hiroya Hayashida, Kiyoshi Yamasaki, Noriko Y. TI Evidence for solar-wind charge-exchange X-ray emission from the Earth's magnetosheath SO PUBLICATIONS OF THE ASTRONOMICAL SOCIETY OF JAPAN LA English DT Article DE atomic processes; Earth; interplanetary medium; Sun : solar wind; X-rays : diffuse background ID INTERSTELLAR NEUTRALS; XMM-NEWTON; COMETS; SPECTRA; ABUNDANCES; PLASMAS; IONS; GAS; SKY AB We report an apparent detection of the C VI 4p to 1s transition line at 459 eV, during a long-term enhancement (LTE) in the Suzaku north ecliptic pole observation of 2005 September 2. The observed line intensity is comparable to that of the C VI 2p to 1s line at 367 eV. This is strong evidence for the charge-exchange process. In addition, O VII, O VIII, Ne X, and Mg XI lines showed clear enhancements. There are also features in the 750-900 eV range that could be due to some combination of Fe L lines, higher order transitions of O VIII (3p to 1s and 6p to 1s), and a Ne IX line. From the correlation of the X-ray intensity with the solar-wind flux on time scales of about half a day, and from the short-term (similar to 10 minutes) variations of the X-ray intensity, these lines most likely arise from solar-wind heavy ions interacting with neutral material in the Earth's magnetosheath. A hard power-law component is also necessary to explain the LTE spectrum. Its origin is not yet known. Our results indicate that solar activity can significantly contaminate Suzaku cosmic X-ray spectra below similar to 1 keV. Recommendations are provided for recognizing such contamination in observations of extended sources. C1 JAXA, Inst Space & Astronaut Sci, Sagamihara, Kanagawa 2298510, Japan. Univ Wisconsin, Dept Phys, Madison, WI 53706 USA. Max Planck Inst Extraterr Phys, D-85740 Garching, Germany. Tokyo Metropolitan Univ, Dept Phys, Hachioji, Tokyo 1920397, Japan. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Kyoto Univ, Fac Sci, Dept Phys, Sakyo Ku, Kyoto 6068502, Japan. Osaka Univ, Fac Sci, Dept Astrophys, Toyonaka, Osaka 5600043, Japan. RP Fujimoto, R (reprint author), JAXA, Inst Space & Astronaut Sci, 3-1-1 Yoshinodai, Sagamihara, Kanagawa 2298510, Japan. EM fujimoto@astro.isas.jaxa.jp RI Yamasaki, Noriko/C-2252-2008; Mitsuda, Kazuhisa/C-2649-2008; Porter, Frederick/D-3501-2012 OI Porter, Frederick/0000-0002-6374-1119 NR 32 TC 128 Z9 128 U1 0 U2 1 PU OXFORD UNIV PRESS PI OXFORD PA GREAT CLARENDON ST, OXFORD OX2 6DP, ENGLAND SN 0004-6264 EI 2053-051X J9 PUBL ASTRON SOC JPN JI Publ. Astron. Soc. Jpn. PD JAN 30 PY 2007 VL 59 SI 1 BP S133 EP S140 DI 10.1093/pasj/59.sp1.S133 PG 8 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 139ON UT WOS:000244441700008 ER PT J AU Hamaguchi, K Petre, R Matsumoto, H Tsujimoto, M Holt, SS Ezoe, Y Ozawa, H Tsuboi, Y Soong, Y Kitamoto, S Sekiguchi, A Kokubun, M AF Hamaguchi, Kenji Petre, Robert Matsumoto, Hironori Tsujimoto, Masahiro Holt, Stephen S. Ezoe, Yuichiro Ozawa, Hideki Tsuboi, Yohko Soong, Yang Kitamoto, Shunji Sekiguchi, Akiko Kokubun, Motohide TI Suzaku observation of diffuse X-ray emission from the Carina Nebula SO PUBLICATIONS OF THE ASTRONOMICAL SOCIETY OF JAPAN LA English DT Article DE ISM : abundances; ISM : individual (Carina nebula); supernova remnants; X-rays : ISM ID ETA-CARINAE; PULSAR 1E-1048.1-5937; CHANDRA OBSERVATIONS; DUST GRAINS; REGION; DISCOVERY; SPECTRUM; STARS; GAS; SPECTROSCOPY AB We studied extended X-ray emission from the Carina Nebula taken with the Suzaku CCD camera XIS on 2005 August 29. The X-ray morphology, plasma temperature, and absorption to the plasma are consistent with the earlier Einstein results. The Suzaku spectra newly revealed emission lines from various species, including oxygen, but not from nitrogen. This result restricts the N/O ratio to be significantly low, compared with evolved massive stellar winds, suggesting that the diffuse emission originated in an old supernova remnant or a super shell produced by multiple supernova remnants. The X-ray spectra from the north and south of eta Car showed distinct differences between 0.3-2 keV. The south spectrum shows strong L-shell lines of iron ions and K-shell lines of silicon ions, while the north spectrum shows them weak in intensity. This means that the silicon and iron abundances are a factor of 2-4 higher in the south region than in the north region. The abundance variation may be produced by an SNR ejecta, or related to dust formation around the star-forming core. C1 NASA, Goddard Space Flight Ctr, Astrophys Sci Div, Greenbelt, MD 20771 USA. Univ Space Res Assoc, Columbia, MD 21044 USA. Kyoto Univ, Grad Sch Sci, Dept Phys, Sakyo Ku, Kyoto 6068502, Japan. Rikkyo Univ, Fac Sci, Dept Phys, Toshima Ku, Tokyo 1718501, Japan. Franklin W Olin Coll Engn, Needham, MA 02492 USA. Inst Space & Astronaut Sci, Sagamihara, Kanagawa 2298510, Japan. Osaka Univ, Grad Sch Sci Earth & Space Sci, Toyonaka, Osaka 5600043, Japan. Chuo Univ, Fac Sci & Engn, Dept Phys, Bunkyo Ku, Tokyo 1128551, Japan. Univ Tokyo, Dept Phys, Bunkyo Ku, Tokyo 1130011, Japan. RP Hamaguchi, K (reprint author), NASA, Goddard Space Flight Ctr, Astrophys Sci Div, Greenbelt, MD 20771 USA. EM kenji@milkyway.gsfc.nasa.gov RI XRAY, SUZAKU/A-1808-2009 NR 51 TC 26 Z9 26 U1 0 U2 1 PU OXFORD UNIV PRESS PI OXFORD PA GREAT CLARENDON ST, OXFORD OX2 6DP, ENGLAND SN 0004-6264 EI 2053-051X J9 PUBL ASTRON SOC JPN JI Publ. Astron. Soc. Jpn. PD JAN 30 PY 2007 VL 59 SI 1 BP S151 EP S161 DI 10.1093/pasj/59.sp1.S151 PG 11 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 139ON UT WOS:000244441700010 ER PT J AU Ishisaki, Y Maeda, Y Fujimoto, R Ozaki, M Ebisawa, K Takahashi, T Ueda, Y Ogasaka, Y Ptak, A Mukai, K Hamaguchi, K Hirayama, M Kotani, T Kubo, H Shibata, R Ebara, M Furuzawa, A Iizuka, R Inoue, H Mori, H Okada, S Yokoyama, Y Matsumoto, H Nakajima, H Yamaguchi, H Anabuki, N Tawa, N Nagai, M Katsuda, S Hayashida, K Bamba, A Miller, ED Sato, K Yamasaki, NY AF Ishisaki, Yoshitaka Maeda, Yoshitomo Fujimoto, Ryuichi Ozaki, Masanobu Ebisawa, Ken Takahashi, Tadayuki Ueda, Yoshihiro Ogasaka, Yasushi Ptak, Andrew Mukai, Koji Hamaguchi, Kenji Hirayama, Masaharu Kotani, Taro Kubo, Hidetoshi Shibata, Ryo Ebara, Masatoshi Furuzawa, Akihiro Iizuka, Ryo Inoue, Hirohiko Mori, Hideyuki Okada, Shunsaku Yokoyama, Yushi Matsumoto, Hironori Nakajima, Hiroshi Yamaguchi, Hiroya Anabuki, Naohisa Tawa, Noriaki Nagai, Masaaki Katsuda, Satoru Hayashida, Kiyoshi Bamba, Aya Miller, Eric D. Sato, Kosuke Yamasaki, Noriko Y. TI Monte Carlo simulator and ancillary response generator of Suzaku XRT/XIS system for spatially extended source analysis SO PUBLICATIONS OF THE ASTRONOMICAL SOCIETY OF JAPAN LA English DT Article DE instrumentation : detectors; methods : data analysis; telescopes; X-rays : general ID GAS IMAGING SPECTROMETER; ONBOARD ASTRO-E; CRAB-NEBULA; RAY; GALAXIES; ASCA; CLUSTER; ABELL-1060; REPRESENTATIONS; PERFORMANCE AB We have developed a framework for the Monte Carlo simulations of X-Ray Telescope (XRT) and X-ray Imaging Spectrometer (XIS) on board Suzaku, mainly for the scientific analysis of spatially and spectroscopically complex celestial sources. A photon-by-photon instrumental simulator is built on the ANL platform, which has been successfully used in ASCA data analysis. The simulator has a modular structure, in which the XRT simulation is based on a ray-tracing library, while the XIS simulation utilizes a spectral "Redistribution Matrix File" (RMF), generated separately by other tools. Instrumental characteristics and calibration results [e.g., XRT geometry, reflectivity, mutual alignments, thermal shield transmission, build-up of the contamination on the XIS optical blocking filters (OBF)] are incorporated as completely as possible. Most of this information is available in the form of FITS (Flexible Image Transport System) files in the standard calibration database (CALDB). This simulator can also be utilized to generate an "Ancillary Response File" (ARF), which describes the XRT response and the amount of OBF contamination. An ARF is dependent on the spatial distribution of the celestial target and the photon accumulation region on the detector, as well as the observing conditions, such as the observation date and satellite attitude. We describe the principles of the simulator and the ARF generator, and demonstrate their performance compared with in-flight data. C1 Tokyo Metropolitan Univ, Dept Phys, Tokyo 1920397, Japan. Japan Aerosp Explorat Agcy, ISAS, Sagamihara, Kanagawa 2298510, Japan. Kyoto Univ, Dept Astron, Sakyo Ku, Kyoto 6068502, Japan. Nagoya Univ, Dept Particle & Astrophys, Chikusa Ku, Nagoya, Aichi 4648602, Japan. Johns Hopkins Univ, Dept Phys & Astron, Baltimore, MD 21218 USA. NASA, Goddard Space Flight Ctr, Astrophys Sci Div, Greenbelt, MD 20771 USA. Univ Space Res Assoc, Columbia, MD 21044 USA. Univ Maryland, Dept Phys, Koint Ctr Astrophys, Baltimore, MD USA. Tokyo Inst Technol, Dept Phys, Meguro Ku, Tokyo 1528551, Japan. Kyoto Univ, Dept Phys, Sakyo Ku, Kyoto 6068502, Japan. Nishi Harima Astron Observ, Sayo Cho, Hyogo 6795313, Japan. Osaka Univ, Dept Earth & Space Sci, Toyonaka, Osaka 5600043, Japan. RIKEN, Inst Phys & Chem Res, Wako, Saitama 3510198, Japan. MIT, Kavli Inst Astrophys & Space Res, Cambridge, MA 02139 USA. RP Ishisaki, Y (reprint author), Tokyo Metropolitan Univ, Dept Phys, 1-1 Minami Osawa, Tokyo 1920397, Japan. EM ishisaki@phys.metro-u.ac.jp RI Yamasaki, Noriko/C-2252-2008; Ozaki, Masanobu/K-1165-2013; XRAY, SUZAKU/A-1808-2009 NR 42 TC 308 Z9 308 U1 0 U2 5 PU OXFORD UNIV PRESS PI OXFORD PA GREAT CLARENDON ST, OXFORD OX2 6DP, ENGLAND SN 0004-6264 EI 2053-051X J9 PUBL ASTRON SOC JPN JI Publ. Astron. Soc. Jpn. PD JAN 30 PY 2007 VL 59 SI 1 BP S113 EP S132 DI 10.1093/pasj/59.sp1.S113 PG 20 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 139ON UT WOS:000244441700007 ER PT J AU Kelley, RL Mitsuda, K Allen, CA Arsenovic, P Audley, MD Bialas, TG Boyce, KR Boyle, RF Breon, SR Brown, GV Cottam, J DiPirro, MJ Fujmoto, R Furusho, T Gendreau, KC Gochar, GG Gonzalez, O Hirabayashi, M Holt, SS Inoue, H Ishida, M Ishisaki, Y Jones, CS Keski-Kuha, R Kilbourne, CA McCammon, D Morita, U Moseley, SH Mott, B Narasaki, K Ogawara, Y Ohashl, T Ota, N Panek, JS Porter, FS Serlemitsos, A Shirron, PJ Sneiderman, GA Szymkowiak, AE Takei, Y Tveekrem, JL Volz, SM Yamamoto, M Yamasaki, NY AF Kelley, Richard L. Mitsuda, Kazuhisa Allen, Christine A. Arsenovic, Petar Audley, Michael D. Bialas, Thomas G. Boyce, Kevin R. Boyle, Robert F. Breon, Susan R. Brown, Gregory V. Cottam, Jean DiPirro, Michael J. Fujmoto, Ryuichi Furusho, Tae Gendreau, Keith C. Gochar, Gene G. Gonzalez, Oscar Hirabayashi, Masayuki Holt, Stephen S. Inoue, Hajime Ishida, Manabu Ishisaki, Yoshitaka Jones, Carol S. Keski-Kuha, Ritva Kilbourne, Caroline A. McCammon, Dan Morita, Umeyo Moseley, S. Harvey Mott, Brent Narasaki, Katsuhiro Ogawara, Yoshiaki Ohashl, Takaya Ota, Naomi Panek, John S. Porter, F. Scott Serlemitsos, Aristides Shirron, Peter J. Sneiderman, Gary A. Szymkowiak, Andrew E. Takei, Yoh Tveekrem, June L. Volz, Stephen M. Yamamoto, Mikio Yamasaki, Noriko Y. TI The Suzaku high resolution X-ray Spectrometer SO PUBLICATIONS OF THE ASTRONOMICAL SOCIETY OF JAPAN LA English DT Article DE instrumentation : detectors; X-rays : general ID TRANSMISSION GRATING SPECTROMETER; ASTRO-E; MICROCALORIMETER ARRAYS; XRS MICROCALORIMETER; THERMAL DETECTORS; ONBOARD SUZAKU; XMM-NEWTON; PERFORMANCE; ASTROPHYSICS; SYSTEM AB The X-Ray Spectrometer (XRS) has been designed to provide the Suzaku Observatory with non-dispersive, high-resolution X-ray spectroscopy. As designed, the instrument covers the energy range 0.3 to 12 keV, which encompasses the most diagnostically rich part of the X-ray band. The sensor consists of a 32-channel array of X-ray microcalorimeters, each with an energy resolution of about 6 eV. The very low temperature required for operation of the array (60 mK) is provided by a four-stage cooling system containing a single-stage adiabatic demagnetization refrigerator, a superfluid-helium cryostat, a solid-neon dewar, and a single-stage, Stirling-cycle cooler. The Suzaku/XRS is the first orbiting X-ray microcalorimeter spectrometer and was designed to last more than three years in orbit. The early verification phase of the mission demonstrated that the instrument worked properly and that the cryogen consumption rate was low enough to ensure a mission lifetime exceeding 3 years. However, the liquid-He cryogen was completely vaporized two weeks after opening the dewar guard vacuum vent. The problem has been traced to inadequate venting of the dewar He and Ne gases out of the spacecraft and into space. In this paper we present the design and ground testing of the XRS instrument, and then describe the in-flight performance. An energy resolution of 6 eV was achieved during pre-launch tests and a resolution of 7 eV was obtained in orbit. The slight degradation is due to the effects of cosmic rays. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. JAXA, ISAS, Kanagawa 2298510, Japan. Univ Cambridge, Cavendish Lab, Cambridge CB3 OHE, England. Lawrence Livermore Natl Lab, Livermore, CA 94550 USA. Sumitomo Heavy Ind Ltd, Quantum Equipment Div, Niihama, Ehime 7920001, Japan. Olin Coll Engn, Needham, MA 02492 USA. Tokyo Metropolitan Univ, Dept Phys, Tokyo 1920397, Japan. Univ Wisconsin, Dept Phys, Madison, WI 53706 USA. RIKEN, Wako, Saitama 3510198, Japan. Yale Univ, Dept Phys, New Haven, CT 06511 USA. NASA, Washington, DC 20546 USA. Miyazaki Univ, Miyazaki 8892192, Japan. RP Kelley, RL (reprint author), NASA, Goddard Space Flight Ctr, Code 661, Greenbelt, MD 20771 USA. EM Richard.L.Kelley@gsfc.nasa.gov RI Yamasaki, Noriko/C-2252-2008; Mitsuda, Kazuhisa/C-2649-2008; Porter, Frederick/D-3501-2012; Kelley, Richard/K-4474-2012; XRAY, SUZAKU/A-1808-2009 OI Porter, Frederick/0000-0002-6374-1119; NR 65 TC 92 Z9 93 U1 0 U2 2 PU OXFORD UNIV PRESS PI OXFORD PA GREAT CLARENDON ST, OXFORD OX2 6DP, ENGLAND SN 0004-6264 EI 2053-051X J9 PUBL ASTRON SOC JPN JI Publ. Astron. Soc. Jpn. PD JAN 30 PY 2007 VL 59 SI 1 BP S77 EP S112 DI 10.1093/pasj/59.sp1.S77 PG 36 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 139ON UT WOS:000244441700006 ER PT J AU Koyama, K Inui, T Hyodo, Y Matsumoto, H Tsuru, TG Maeda, Y Murakami, H Yamauchi, S Kissel, SE Chan, KW Soong, Y AF Koyama, Katsuji Inui, Tatsuya Hyodo, Yoshiaki Matsumoto, Hironori Tsuru, Takeshi Go Maeda, Yoshitomo Murakami, Hiroshi Yamauchi, Shigeo Kissel, Steven E. Chan, Kai-Wing Soong, Yang TI Discoveries of diffuse iron line sources from the Sgr B region SO PUBLICATIONS OF THE ASTRONOMICAL SOCIETY OF JAPAN LA English DT Article DE ISM : clouds; ISM : HII regions; ISM : supernova remnants ID GALACTIC-CENTER REGION; SAGITTARIUS-A-EAST; X-RAY SOURCE; CHANDRA; EMISSION; CATALOG; CLOUD AB The radio complex Sgr B region was observed with the X-ray Imaging Spectrometer (XIS) on board Suzaku. This region exhibits diffuse iron lines at 6.4, 6.7, and 6.9 keV, which are K alpha lines of Fe I (neutral iron), Fe XXV (He-like iron), and Fe XXVI (H-like iron), respectively. The high energy resolving power of the XIS provided separate maps of the K-shell transition lines from Fe 1 (6.4 keV) and Fe XXV (6.7 keV). Although the 6.7 keV line is smoothly distributed over the Sgr B region, a local excess is found near (l, b) = (0.degrees 61, 0.degrees 01), possibly due to a new SNR. The plasma temperature is kT similar to 3 keV and the age is estimated to be younger than 7 x 10(3) yr. The 6.4 keV image is clumpy with local excesses near Sgr B2 and at (l, b) = (0.degrees 74, -0.degrees 09). Like Sgr B2, this excess may be another candidate of an X-ray reflection nebula. C1 Kyoto Univ, Dept Phys, Grad Sch Sci, Sakyo Ku, Kyoto 6068502, Japan. JAXA, Inst Space & Astronaut Sci, Plain Ctr, Sagamihara, Kanagawa 2298510, Japan. Iwate Univ, Fac Humanities & Social Sci, Morioka, Iwate 0208550, Japan. MIT, Kavli Inst Astrophys & Space Res, Cambridge, MA 02139 USA. NASA, Goddard Space Flight Ctr, Xray Astrophys Lab, Greenbelt, MD 20771 USA. RP Koyama, K (reprint author), Kyoto Univ, Dept Phys, Grad Sch Sci, Sakyo Ku, Kyoto 6068502, Japan. EM koyama@cr.scphys.kyoto-u.ac.jp; inuit@cr.scphys.kyoto-u.ac.jp RI XRAY, SUZAKU/A-1808-2009 NR 22 TC 44 Z9 44 U1 0 U2 0 PU OXFORD UNIV PRESS PI OXFORD PA GREAT CLARENDON ST, OXFORD OX2 6DP, ENGLAND SN 0004-6264 EI 2053-051X J9 PUBL ASTRON SOC JPN JI Publ. Astron. Soc. Jpn. PD JAN 30 PY 2007 VL 59 SI 1 BP S221 EP S227 DI 10.1093/pasj/59.sp1.S221 PG 7 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 139ON UT WOS:000244441700018 ER PT J AU Kubota, A Dotani, T Cottam, J Kotani, T Done, C Ueda, Y Fabian, AC Yasuda, T Takahashi, H Fukazawa, Y Yamaoka, K Makishima, K Yamada, S Kohmura, T Angelini, L AF Kubota, Aya Dotani, Tadayasu Cottam, Jean Kotani, Taro Done, Chris Ueda, Yoshihiro Fabian, Andrew C. Yasuda, Tomonori Takahashi, Hiromitsu Fukazawa, Yasushi Yamaoka, Kazutaka Makishima, Kazuo Yamada, Shinya Kohmura, Takayoshi Angelini, Lorella TI Suzaku discovery of iron absorption lines in outburst spectra of the X-ray transient 4U 1630-472 SO PUBLICATIONS OF THE ASTRONOMICAL SOCIETY OF JAPAN LA English DT Article DE accretion, accretion disks; X-rays : individual (4U 1630-472) ID HOLE CANDIDATE 4U-1630-47; SOURCE GRO J1655-40; ACCRETION DISKS; XMM-NEWTON; BINARY GX-13+1; BOARD SUZAKU; CRAB-NEBULA; BLACK-HOLES; HIGH-STATE; FEATURES AB We present the results of six Suzaku observations of the recurrent black hole transient 4U 1630-472 during its decline from outburst from February 8 to March 23 in 2006. All observations show the typical high/soft state spectral shape in the 2-50keV band, roughly described by an optically thick-disk spectrum in the soft energy band plus a weak power-law tail that becomes dominant only above similar to 20 keV. The disk temperature decreases from 1.4 keV to 1.2 keV as the flux decreases by a factor of 2, consistent with a constant radius, as expected for disk-dominated spectra. All of the observations reveal significant absorption lines from highly ionized (H-like and He-like) iron K alpha's at 7.0 keV and 6.7 keV. The energies of these absorption lines suggest a blue shift with an outflow velocity of similar to 1000 km s(-1). The H-like iron K alpha equivalent width remains approximately constant at similar to 30 eV over all of the observations, while that of the He-like Ka line increases from 7 eV to 20 eV. Thus, the ionization state of the material decreases, as expected from the decline in flux. By fitting the profile with Voigt functions (curve of growth) together with detailed photo-ionization calculations, the total absorbing column, and the ionization parameter were estimated to be (1.0-0.7) x 10(23) cm(-2) and (6-4) x 10(4), respectively, for a velocity dispersion of 500 km s(-1). This in turn constrains the size of the plasma to be similar to 10(10) cm, assuming a source distance of 10 kpc. C1 RIKEN, Inst Phys & Chem Res, Wako, Saitama 3510198, Japan. Japan Aerosp Explorat Agcy, Inst Space & Astronaut Sci, Sagamihara, Kanagawa 2298510, Japan. NASA, Goddard Space Flight Ctr, Explorat Universe Div, Greenbelt, MD 20771 USA. Tokyo Tech, Dept Phys, Tokyo 1528551, Japan. Univ Durham, Dept Phys, Durham DH1 3LE, England. Kyoto Univ, Dept Astron, Sakyo Ku, Kyoto 6068502, Japan. Inst Astron, Cambridge CB3 0HA, England. Hiroshima Univ, Dept Phys Sci, Hiroshima 7398526, Japan. Aoyama Gakuin Univ, Dept Phys, Sagamihara, Kanagawa 2298558, Japan. Univ Tokyo, Dept Phys, Bunkyo Ku, Tokyo 1130033, Japan. Kogakuin Univ, Dept Phys, Hachioji, Tokyo 1920015, Japan. RP Kubota, A (reprint author), RIKEN, Inst Phys & Chem Res, 2-1 Hirosawa, Wako, Saitama 3510198, Japan. EM aya@crab.riken.jp RI XRAY, SUZAKU/A-1808-2009; done, chris/D-4605-2016 OI done, chris/0000-0002-1065-7239 NR 61 TC 54 Z9 54 U1 0 U2 0 PU OXFORD UNIV PRESS PI OXFORD PA GREAT CLARENDON ST, OXFORD OX2 6DP, ENGLAND SN 0004-6264 EI 2053-051X J9 PUBL ASTRON SOC JPN JI Publ. Astron. Soc. Jpn. PD JAN 30 PY 2007 VL 59 SI 1 BP S185 EP S198 DI 10.1093/pasj/59.sp1.S185 PG 14 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 139ON UT WOS:000244441700014 ER PT J AU Matsumoto, H Ueno, M Bamba, A Hyodo, Y Mori, H Uchiyama, H Tsuru, TG Koyama, K Kataoka, J Katagiri, H Takahashi, T Hiraga, J Yamauchi, S Hughes, JP Senda, A Kokubun, M Kohmura, T Porter, FS AF Matsumoto, Hironori Ueno, Masaru Bamba, Aya Hyodo, Yoshiaki Mori, Hideyuki Uchiyama, Hideki Tsuru, Takeshi Go Koyama, Katsuji Kataoka, Jun Katagiri, Hideaki Takahashi, Tadayuki Hiraga, Junko Yamauchi, Shigeo Hughes, John P. Senda, Atsushi Kokubun, Motohide Kohmura, Takayoshi Porter, Frederick S. TI Suzaku observations of HESS J1616-508: Evidence for a dark particle accelerator SO PUBLICATIONS OF THE ASTRONOMICAL SOCIETY OF JAPAN LA English DT Article DE acceleration of particles; X-rays : individual (HESS J1616-508); X-rays : ISM ID X-RAY-EMISSION; SUPERNOVA REMNANT G347.3-0.5; GALACTIC PLANE SURVEY; TEV SOURCE; FOLLOW-UP; HESS J1813-178; GAMMA-RAYS; IRON LINE; CHANDRA; SHELL AB We observed the bright unidentified TeV gamma-ray source HESS J1616-508 with the X-ray Imaging Spectrometers onboard the Suzaku satellite. No X-ray counterpart was found to a limiting flux of 3.1 x 10(-13) erg s(-1) cm(-2) in the 2-10 keV band, which is some 60-times below the gamma-ray flux in the 1-10 TeV band. This object is bright in TeV gamma-rays, but very dim in the X-ray band, and thus is one of the best examples in the Galaxy of a "dark particle accelerator." We also detected soft thermal emission with kT similar to 0.3-0.6 keV near the location of HESS J1616-508. This may be due to a dust-grain scattering halo from the nearby bright supernova remnant RCW 103. C1 Kyoto Univ, Dept Phys, Grad Sch Sci, Sakyo Ku, Kyoto 6068502, Japan. Tokyo Inst Technol, Dept Phys, Fac Sci, Meguro Ku, Tokyo 1528551, Japan. RIKEN, Cosm Radiat Grp, Wako, Saitama 3510198, Japan. Hiroshima Univ, Dept Phys, Grad Sch Sci, Hiroshima 7398526, Japan. Japan Aerosp Explorat Agcy, Inst Space & Astronaut Sci, Sagamihara, Kanagawa 2298510, Japan. Iwate Univ, Fac Humanities & Social Sci, Morioka, Iwate 0208550, Japan. Rutgers State Univ, Dept Phys & Astron, Piscataway, NJ 08854 USA. Univ Tokyo, Dept Phys, Bunkyo Ku, Tokyo 1130033, Japan. Kogakuin Univ, Dept Gen Educ, Hachioji, Tokyo 1920015, Japan. NASA, Goddard Space Flight Ctr, Lab High Energy Astrophys, Greenbelt, MD 20771 USA. RP Matsumoto, H (reprint author), Kyoto Univ, Dept Phys, Grad Sch Sci, Sakyo Ku, Kyoto 6068502, Japan. EM matumoto@cr.scphys.kyoto-u.ac.jp RI Porter, Frederick/D-3501-2012; XRAY, SUZAKU/A-1808-2009 OI Porter, Frederick/0000-0002-6374-1119; NR 55 TC 29 Z9 29 U1 0 U2 2 PU OXFORD UNIV PRESS PI OXFORD PA GREAT CLARENDON ST, OXFORD OX2 6DP, ENGLAND SN 0004-6264 EI 2053-051X J9 PUBL ASTRON SOC JPN JI Publ. Astron. Soc. Jpn. PD JAN 30 PY 2007 VL 59 SI 1 BP S199 EP S208 DI 10.1093/pasj/59.sp1.S199 PG 10 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 139ON UT WOS:000244441700015 ER PT J AU Miniutti, G Fabian, AC Anabuki, N Crummy, J Fukazawa, Y Gallo, L Haba, Y Hayashida, K Holt, S Kunieda, H Larsson, J Markowitz, A Matsumoto, C Ohno, M Reeves, JN Takahash, T Tanaka, Y Terashima, Y Torii, K Ueda, Y Ushio, M Watanabe, S Yamauchi, M Yaqoob, T AF Miniutti, Giovanni Fabian, Andrew C. Anabuki, Naohisa Crummy, Jamie Fukazawa, Yasushi Gallo, Luigi Haba, Yoshito Hayashida, Kiyoshi Holt, Steve Kunieda, Hideyo Larsson, Josefin Markowitz, Alex Matsumoto, Chiho Ohno, Masanori Reeves, James N. Takahash, Tadayuki Tanaka, Yasuo Terashima, Yuichi Torii, Ken'ichi Ueda, Yoshihiro Ushio, Masayoshi Watanabe, Shin Yamauchi, Makoto Yaqoob, Tahir TI Suzaku observations of the hard X-ray variability of MCG-6-30-15: the effects of strong gravity around a Kerr black hole SO PUBLICATIONS OF THE ASTRONOMICAL SOCIETY OF JAPAN LA English DT Article DE galaxies : active; galaxies : individual (MCG-6-30-15); galaxies : Seyfert; X-rays : galaxies ID ACTIVE GALACTIC NUCLEI; K-ALPHA LINE; SEYFERT-1 GALAXY MCG-6-30-15; XMM-NEWTON; EMISSION-LINE; BOARD SUZAKU; WARM ABSORBER; COLD MATTER; IRON LINES; CYGNUS X-1 AB Suzaku has, for the first time, enabled the hard X-ray variability of the Seyfert 1 galaxy MCG -6-30-15 to be measured. The variability in the 14-45 keV band, which is dominated by a strong reflection hump, is quenched relative to that at a few keV. This directly demonstrates that the whole reflection spectrum is much less variable than the power-law continuum. The broadband spectral variability can be decomposed into two components - a highly variable power-law and constant reflection - as previously inferred from other observations in the 2-10 keV band. The strong reflection and high iron abundance give rise to a strong broad iron line, which requires the inner disc radius to be at about 2 gravitational radii. Our results are consistent with the predictions of the light bending model which invokes the very strong gravitational effects expected very close to a rapidly spinning black hole. C1 Univ Cambridge, Inst Astron, Cambridge CB3 0HA, England. Osaka Univ, Dept Earth & Space Sci, Toyonaka, Osaka 5600043, Japan. Hiroshima Univ, Dept Phys Sci, Sch Sci, Hiroshima 7398526, Japan. Max Planck Inst Extraterr Phys, D-37075 Garching, Germany. Inst Space & Astronaut Sci, Japan Aerosp Explorat Agcy, Kanagawa 2298510, Japan. Nagoya Univ, Dept Astrophys, Chikusa Ku, Nagoya, Aichi 4648602, Japan. FW Olin Coll Engn, Needham, MA 02492 USA. Nagoya Univ, Dept Phys, Chikusa Ku, Nagoya, Aichi 4648602, Japan. NASA, Goddard Space Flight Ctr, Astrophys Sci Div, Greenbelt, MD 20771 USA. Johns Hopkins Univ, Dept Phys & Astron, Baltimore, MD 21218 USA. Ehime Univ, Dept Phys, Matsuyama, Ehime 7908577, Japan. Kyoto Univ, Dept Astron, Sakyo Ku, Kyoto 606, Japan. Miyazaki Univ, Fac Engn, Dept Appl Phys, Miyazaki 8892192, Japan. RP Miniutti, G (reprint author), Univ Cambridge, Inst Astron, Madingley Rd, Cambridge CB3 0HA, England. EM miniutti@ast.cam.ac.uk RI Miniutti, Giovanni/L-2721-2014; XRAY, SUZAKU/A-1808-2009 OI Miniutti, Giovanni/0000-0003-0707-4531; NR 48 TC 129 Z9 129 U1 2 U2 3 PU OXFORD UNIV PRESS PI OXFORD PA GREAT CLARENDON ST, OXFORD OX2 6DP, ENGLAND SN 0004-6264 EI 2053-051X J9 PUBL ASTRON SOC JPN JI Publ. Astron. Soc. Jpn. PD JAN 30 PY 2007 VL 59 SI 1 BP S315 EP S325 DI 10.1093/pasj/59.sp1.S315 PG 11 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 139ON UT WOS:000244441700026 ER PT J AU Mitsuda, K Bautz, M Inoue, H Kelley, RL Koyama, K Kunieda, H Makshima, K Ogawara, Y Petre, R Takahashi, T Tsunemi, H White, NE Anabuki, N Angelini, L Arnaud, K Awaki, H Bamba, A Boyce, K Brown, GV Chan, KW Cottam, J Dotanli, T Doty, J Ebisawa, K Ezoe, Y Fabian, AC Figueroa, E Fujimoto, R Fukazawa, Y Furusho, T Furuzawa, A Gendreau, K Griffiths, RE Haba, Y Hamaguchi, K Harrus, I Hasinger, G Hatsukade, I Hayashida, K Henry, PJ Hiraga, JS Holt, SS Hornschemeier, A Hughes, JP Hwang, U Ishida, M Ishisaki, Y Isobe, N Itoh, M Iyomoto, N Kahn, SM Kamae, T Katagiri, H Kataoka, J Katayama, H Kawai, N Kilbourne, C Kinugasa, K Kissel, S Kitamoto, S Kohama, M Kohmura, T Kokubun, M Kotani, T Kotoku, J Kubota, A Madejski, GM Maeda, Y Makino, F Markowitz, A Matsumoto, C Matsumoto, H Matsuoka, M Matsushita, K McCammon, D Mihara, T Misaki, K Miyata, E Mizuno, T Mori, K Mori, H Morii, M Moseley, H Mukai, K Murakami, H Murakami, T Mushotzky, R Nagase, F Namiki, M Negoro, H Nakazawa, K Nousek, JA Okajima, T Ogasaka, Y Ohashi, T Oshima, T Ota, N Ozaki, M Ozawa, H Parmar, AN Pence, WD Porter, FS Reeves, JN Ricker, GR Sakurai, I Sanders, WT Senda, A Serlemitsos, P Shibata, R Soong, Y Smith, R Suzuki, M Szymkowiak, AE Takahashi, H Tamagawa, T Tamura, K Tamura, T Tanaka, Y Tashiro, M Tawara, Y Terada, Y Terashima, Y Tomida, H Torii, K Tsuboi, Y Tsujimoto, M Tsuru, TG Turner, MJL Ueda, Y Ueno, S Ueno, M Uno, S Urata, Y Watanabe, S Yamamoto, N Yamaoka, K Yamasaki, NY Yamashita, K Yamauchi, M Yamauchi, S Yaqoob, T Yonetoku, D Yoshida, A AF Mitsuda, Kazuhisa Bautz, Mark Inoue, Hajime Kelley, Richard L. Koyama, Katsuji Kunieda, Hideyo Makshima, Kazuo Ogawara, Yoshiaki Petre, Robert Takahashi, Tadayuki Tsunemi, Hiroshi White, Nicholas E. Anabuki, Naohisa Angelini, Lorella Arnaud, Keith Awaki, Hisamitsu Bamba, Aya Boyce, Kevin Brown, Gregory V. Chan, Kai-Wing Cottam, Jean Dotanli, Tadayasu Doty, John Ebisawa, Ken Ezoe, Yuichiro Fabian, Andrew C. Figueroa, Enectali Fujimoto, Ryuichi Fukazawa, Yasushi Furusho, Tae Furuzawa, Akihiro Gendreau, Keith Griffiths, Richard E. Haba, Yoshito Hamaguchi, Kenji Harrus, Ilana Hasinger, Gunther Hatsukade, Isamu Hayashida, Kiyoshi Henry, Patrick J. Hiraga, Junko S. Holt, Stephen S. Hornschemeier, Ann Hughes, John P. Hwang, Una Ishida, Manabu Ishisaki, Yoshitaka Isobe, Naoki Itoh, Masayuki Iyomoto, Naoko Kahn, Steven M. Kamae, Tuneyoshi Katagiri, Hideaki Kataoka, Jun Katayama, Haruyoshi Kawai, Nobuyuki Kilbourne, Caroline Kinugasa, Kenzo Kissel, Steve Kitamoto, Shunji Kohama, Mitsuhiro Kohmura, Takayoshi Kokubun, Motohide Kotani, Taro Kotoku, Jun'ichi Kubota, Aya Madejski, Greg M. Maeda, Yoshitomo Makino, Fumiyoshi Markowitz, Alex Matsumoto, Chiho Matsumoto, Hironori Matsuoka, Masaru Matsushita, Kyoko McCammon, Dan Mihara, Tatehiko Misaki, Kazutami Miyata, Emi Mizuno, Tsunefumi Mori, Koji Mori, Hideyuki Morii, Mikio Moseley, Harvey Mukai, Koji Murakami, Hiroshi Murakami, Toshio Mushotzky, Richard Nagase, Fumiaki Namiki, Masaaki Negoro, Hitoshi Nakazawa, Kazubiro Nousek, John A. Okajima, Takashi Ogasaka, Yasushi Ohashi, Takaya Oshima, Tai Ota, Naomi Ozaki, Masanobu Ozawa, Hideki Parmar, Arvind N. Pence, William D. Porter, F. Scott Reeves, James N. Ricker, George R. Sakurai, Ikuya Sanders, Wilton T. Senda, Atsushi Serlemitsos, Peter Shibata, Ryo Soong, Yang Smith, Randall Suzuki, Motoko Szymkowiak, Andrew E. Takahashi, Hiromitsu Tamagawa, Torn Tamura, Keisuke Tamura, Takayuki Tanaka, Yasuo Tashiro, Makoto Tawara, Yuzuru Terada, Yukikatsu Terashima, Yuichi Tomida, Hiroshi Torii, Ken'ichi Tsuboi, Yohko Tsujimoto, Masahiro Tsuru, Takeshi Go Turner, Martin J. L. Ueda, Yoshihiro Ueno, Shiro Ueno, Masaru Uno, Shin'ichiro Urata, Yuji Watanabe, Shin Yamamoto, Norimasa Yamaoka, Kazutaka Yamasaki, Noriko Y. Yamashita, Koujun Yamauchi, Makoto Yamauchi, Shigeo Yaqoob, Tahir Yonetoku, Daisuke Yoshida, Atsumasa TI The X-ray observatory Suzaku SO PUBLICATIONS OF THE ASTRONOMICAL SOCIETY OF JAPAN LA English DT Article DE instrumentation; space vehicles; space vehicles : instruments; X-rays : general ID IMAGING SPECTROMETER; XMM-NEWTON AB High-sensitivity wide-band X-ray spectroscopy is the key feature of the Suzaku X-ray observatory, launched on 2005 July 10. This paper summarizes the spacecraft, in-orbit performance, operations, and data processing that are related to observations. The scientific instruments, the high-throughput X-ray telescopes, X-ray CCD cameras, non-imaging hard X-ray detector are also described. C1 Japan Aerosp Explorat Agcy, Inst Space & Astronaut Sci, Dept High Energy Astrophys, Kanagawa 2298510, Japan. NASA, Goddard Space Flight Ctr, Explorat Universe Div, Greenbelt, MD 20771 USA. Aoyama Gakuin Univ, Dept Math & Phys, Kanagawa 2298558, Japan. Univ Cambridge, Inst Astron, Cambridge CB3 0HA, England. Carnegie Mellon Univ, Dept Phys, Pittsburgh, PA 15213 USA. Chuo Univ, Dept Phys, Tokyo 1128551, Japan. Ehime Univ, Dept Phys, Matsuyama, Ehime 7908577, Japan. ESTEC, Dept Space Sci, NL-2200 AG Noordwijk, Netherlands. Gunma Astron Observ, Gunma 3770702, Japan. Univ Hawaii, Astron Inst, Honolulu, HI 96822 USA. Hiroshima Univ, Dept Phys Sci, Higashihiroshima 7398526, Japan. Japan Aerosp Explorat Agcy, Inst Space & Astronaut Sci, ISS Sci Project Off, Tsukuba, Ibaraki 3058505, Japan. Iwate Med Univ, Fac Humanities & Social Sci, Morioka, Iwate 02085509, Japan. Kanazawa Univ, Dept Phys, Kanazawa, Ishikawa 9201192, Japan. Kobe Univ, Fac Human Dev, Kobe, Hyogo 6578501, Japan. Kougakuin Univ, Dept Phys, Tokyo 1920015, Japan. Kyoto Univ, Dept Astron, Sakyo Ku, Kyoto 6068502, Japan. Kyoto Univ, Dept Phys, Sakyo Ku, Kyoto 6068502, Japan. Univ Leicester, Leicester LE1 7RH, Leics, England. MIT, Kavli Inst Astrophys & Psace Res, Cambridge, MA 02139 USA. Max Planck Inst Extraterrestr, Garching, Germany. Miyazaki Univ, Dept Appl Phys, Miyazaki 8892192, Japan. Nagoya Univ, EcoTopia Sci Inst, Nagoya, Aichi 4648603, Japan. Nagoya Univ, Dept Astrophys, Nagoya, Aichi 4648602, Japan. NASA Head Quarter, Washington, DC USA. Nihon Fukushi Univ, Fac Social & Informat Sci, Aichi 4750012, Japan. Nihon Univ, Dept Phys, Tokyo 1018308, Japan. Noqsi Aerosp Ltd, Pine, CO 80470 USA. FW Olin Coll Engn, Needham, MA 02492 USA. Osaka Univ, Dept Earth & Space Sci, Osaka 5600043, Japan. Penn State Univ, University Pk, PA 16802 USA. RIKEN, Cosm Radiat Lab, Wako, Saitama 3510198, Japan. Rikkyo Univ, Dept Phys, Tokyo 1718501, Japan. Rutgers State Univ, Dept Phys, Piscataway, NJ 08854 USA. Rutgers State Univ, Dept Phys & Astron, Piscataway, NJ 08854 USA. Stanford Linear Accelerator Ctr, Menlo Pk, CA 94025 USA. Univ Tokyo, Dept Phys, Tokyo 1130033, Japan. Tokyo Inst Technol, Dept Phys, Meguro Ku, Tokyo 1528551, Japan. Tokyo Metropolitan Univ, Dept Phys, Tokyo 1920397, Japan. Tokyo Metropolitan Univ, Dept Phys, Tokyo 1920397, Japan. Tokyo Univ Sci, Dept Phys, Tokyo 1628601, Japan. Univ Wisconsin, Dept Phys, Madison, WI 53706 USA. Yale Univ, Dept Phys, New Haven, CT 06520 USA. RP Mitsuda, K (reprint author), Japan Aerosp Explorat Agcy, Inst Space & Astronaut Sci, Dept High Energy Astrophys, 3-1-1 Yoshinodai, Kanagawa 2298510, Japan. RI Yamasaki, Noriko/C-2252-2008; Mitsuda, Kazuhisa/C-2649-2008; White, Nicholas/B-6428-2012; Porter, Frederick/D-3501-2012; Tashiro, Makoto/J-4562-2012; Kelley, Richard/K-4474-2012; Terada, Yukikatsu/A-5879-2013; Ozaki, Masanobu/K-1165-2013; XRAY, SUZAKU/A-1808-2009; Mihara, Tatehiro/C-5536-2017; OI White, Nicholas/0000-0003-3853-3462; Porter, Frederick/0000-0002-6374-1119; Terada, Yukikatsu/0000-0002-2359-1857; Mihara, Tatehiro/0000-0002-6337-7943; Parmar, Arvind/0000-0002-3307-6517 NR 15 TC 677 Z9 678 U1 2 U2 25 PU OXFORD UNIV PRESS PI OXFORD PA GREAT CLARENDON ST, OXFORD OX2 6DP, ENGLAND SN 0004-6264 EI 2053-051X J9 PUBL ASTRON SOC JPN JI Publ. Astron. Soc. Jpn. PD JAN 30 PY 2007 VL 59 SI 1 BP S1 EP S7 DI 10.1093/pasj/59.sp1.S1 PG 7 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 139ON UT WOS:000244441700001 ER PT J AU Miyata, E Katsuda, S Tsunemi, H Hughes, JP Kokubun, M Porter, FS AF Miyata, Emi Katsuda, Satoru Tsunemi, Hiroshi Hughes, John P. Kokubun, Motohide Porter, F. Scott TI Detection of highly-ionized carbon and nitrogen emission lines from the Cygnus Loop supernova remnant with the Suzaku observatory SO PUBLICATIONS OF THE ASTRONOMICAL SOCIETY OF JAPAN LA English DT Article DE ISM : abundances; ISM : individual (Cygnus loop); ISM : supernova remnants; X-rays : ISM ID PLASMA AB We present the results of a Suzaku observation at the northeastern limb of the Cygnus Loop supernova remnant. The high detection efficiency together with the high spectral resolution of the Suzaku X-ray CCD cameras enables us to detect highly-ionized C and N emission lines from the Cygnus Loop for the first time. We performed an annular spectral analysis to our data set and investigated the plasma structure along the radial direction. Our data are well characterized by a two-component non-equilibrium ionization model with different values of electron temperature. Abundances of C to Fe are all depleted to typically 0.1 solar, even for Ne. Relative abundances to O are roughly consistent with solar values. C1 Osaka Univ, Grad Sch Sci, Dept Earth & Space Sci, Toyonaka, Osaka 5600043, Japan. Rutgers State Univ, Dept Phys & Astron, Piscataway, NJ 08854 USA. Univ Tokyo, Dept Phys, Bunkyo Ku, Tokyo 1130033, Japan. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Miyata, E (reprint author), Osaka Univ, Grad Sch Sci, Dept Earth & Space Sci, 1-1 Machikaneyama, Toyonaka, Osaka 5600043, Japan. EM miyata@ess.sci.osaka-u.ac.jp; katsuda@ess.sci.osaka-u.ac.jp; tsunemi@ess.sci.osaka-u.ac.jp; jackph@physics.rutgers.edu; kokubun@phys.s.u-tokyo.ac.jp; Frederick.S.Porter@gsfc.nasa.gov RI Porter, Frederick/D-3501-2012; XRAY, SUZAKU/A-1808-2009 OI Porter, Frederick/0000-0002-6374-1119; NR 11 TC 31 Z9 31 U1 0 U2 0 PU OXFORD UNIV PRESS PI OXFORD PA GREAT CLARENDON ST, OXFORD OX2 6DP, ENGLAND SN 0004-6264 EI 2053-051X J9 PUBL ASTRON SOC JPN JI Publ. Astron. Soc. Jpn. PD JAN 30 PY 2007 VL 59 SI 1 BP S163 EP S170 DI 10.1093/pasj/59.sp1.S163 PG 8 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 139ON UT WOS:000244441700011 ER PT J AU Mizuno, T Miyawaki, R Ebisawa, K Kubota, A Miyamoto, M Winter, LM Ueda, Y Isobe, N Dewangan, GC Done, C Griffiths, RE Haba, Y Kokubun, M Kotoku, J Makishima, K Matsushita, K Mushotzky, RF Namiki, M Petre, R Takahashi, H Tamagawa, T Terashima, Y AF Mizuno, Tsunefumi Miyawaki, Ryohei Ebisawa, Ken Kubota, Aya Miyamoto, Masao Winter, Lisa M. Ueda, Yoshihiro Isobe, Naoki Dewangan, Gulab C. Done, Chris Griffiths, Richard E. Haba, Yoshito Kokubun, Motohide Kotoku, Jun'ichi Makishima, Kazuo Matsushita, Kyoko Mushotzky, Ricard F. Namiki, Masaaki Petre, Robert Takahashi, Hiromitsu Tamagawa, Toru Terashima, Yuichi TI Suzaku observation of two ultraluminous X-ray sources in NGC 1313 SO PUBLICATIONS OF THE ASTRONOMICAL SOCIETY OF JAPAN LA English DT Article DE accretion, accretion disks; black hole physics; X-rays : individual (NGC 1313 X-1, NGC 1313 X-2) ID XMM-NEWTON OBSERVATIONS; NEARBY SPIRAL GALAXIES; BLACK-HOLE CANDIDATES; SLIM ACCRETION DISKS; HIGH STATE; BOARD SUZAKU; VARIABILITY; ABSORPTION; X-2; TRANSITIONS AB Two ultraluminous X-ray sources (ULXs) in the nearby Sb galaxy NGC 1313, named X-1 and X-2, were observed with Suzaku on 2005 September 15. During the observation for a net exposure of 28 ks (but over a gross time span of 90 ks), both objects varied in intensity by about 50%. The 0.4-10 keV X-ray luminosities of X-1 and X-2 were measured as 2.5 x 10(40) erg s(-1) and 5.8 x 10(39) erg s(-1), respectively, with the former exhibiting the highest ever reported for this ULX. The spectrum of X-1 can be explained by the sum of a strong and variable powerlaw component with a high-energy cutoff, and a stable multicolor blackbody with an innermost disk temperature of similar to 0.2 keV. These results suggest that X-1 was in a "very high" state, where disk emission is strongly Comptonized. The absorber within NGC 1313 toward X-1 is suggested to have a subsolar oxygen abundance. The spectrum of X-2 is best represented, in its fainter phase, by a multicolor blackbody model with an innermost disk temperature of 1.2-1.3 keV, and becomes flatter as the source becomes brighter. Hence, X-2 is interpreted to be in a slim-disk state. These results suggest that the two ULXs have black hole masses of some dozens to a few hundred of solar masses. C1 Hiroshima Univ, Dept Phys, Hiroshima 7398526, Japan. Univ Tokyo, Dept Phys, Bunkyo Ku, Tokyo 1130033, Japan. Japan Aerosp Explorat Agcy, Inst Space & Astronaut Sci, Sagamihara, Kanagawa 2298510, Japan. RIKEN, Inst Phys & Chem Res, Wako, Saitama 3510198, Japan. Tokyo Univ Sci, Dept Phys, Shinjuku Ku, Tokyo 1628601, Japan. NASA, Goddard Space Flight Ctr, Explorat Universe Div, Greenbelt, MD 20771 USA. Kyoto Univ, Dept Phys, Sakyo Ku, Kyoto 6068502, Japan. Carnegie Mellon Univ, Dept Phys, Pittsburgh, PA 15213 USA. Univ Durham, Dept Phys, Durham DH1 3LE, England. Nagoya Univ, Dept Phys, Chikusa Ku, Nagoya, Aichi 4648602, Japan. Tokyo Inst Technol, Dept Phys, Meguro Ku, Tokyo 1528551, Japan. Osaka Univ, Dept Earth & Space Sci, Toyonaka, Osaka 5600043, Japan. RP Mizuno, T (reprint author), Ehime Univ, Dept Phys, Matsuyama, Ehime 7908577, Japan. EM mizuno@hepl.hiroshima-u.ac.jp RI XRAY, SUZAKU/A-1808-2009; done, chris/D-4605-2016 OI done, chris/0000-0002-1065-7239 NR 56 TC 30 Z9 30 U1 0 U2 0 PU OXFORD UNIV PRESS PI OXFORD PA GREAT CLARENDON ST, OXFORD OX2 6DP, ENGLAND SN 0004-6264 EI 2053-051X J9 PUBL ASTRON SOC JPN JI Publ. Astron. Soc. Jpn. PD JAN 30 PY 2007 VL 59 SI 1 BP S257 EP S267 DI 10.1093/pasj/59.sp1.S257 PG 11 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 139ON UT WOS:000244441700022 ER PT J AU Mukai, K Ishida, M Kilbourne, C Mori, H Terada, Y Chan, KW Soong, Y AF Mukai, Koji Ishida, Manabu Kilbourne, Caroline Mori, Hideyuki Terada, Yukikatsu Chan, Kai-Wing Soong, Yang TI An apparent hard X-ray decline of CH Cygni SO PUBLICATIONS OF THE ASTRONOMICAL SOCIETY OF JAPAN LA English DT Article DE accretion, accretion disk; stars : binaries : symbiotic; stars : individual (CH Cyg); X-rays : stars ID SYMBIOTIC STARS; JET AB CH Cygni is a symbiotic star consisting of an M giant and an accreting white dwarf, which is known to be a highly variable X-ray source with a complex, two-component, spectra. Here, we report on two Suzaku observations of CH Cyg, taken in 2006 January and May, during which the system was seen to be in a soft X-ray bright, hard X-ray faint state. Based on the extraordinary strength of the 6.4 keV fluorescent Fe K alpha line, we show that the hard X-rays observed with Suzaku are dominated by scattering. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Univ Space Res Assoc, Columbia, MD USA. Tokyo Metropolitan Univ, Dept Phys, Hachioji, Tokyo 1920397, Japan. Kyoto Univ, Grad Sch Sci, Dept Phys, Sakyo Ku, Kyoto 6068502, Japan. RIKEN, Cosm Radiat Lab, Wako, Saitama 3510198, Japan. RP Mukai, K (reprint author), NASA, Goddard Space Flight Ctr, Code 662, Greenbelt, MD 20771 USA. EM mukai@milkyway.gsfc.nasa.gov; ishida@mpuax.phys.metro-u.ac.jp; cak@lheapop.gsfc.nasa.gov; mori@cr.scphys.kyoto-u.ac.jp; terada@riken.jp; kwchan@milkyway.gsfc.nasa.gov; soong@milkyway.gsfc.nasa.gov RI Terada, Yukikatsu/A-5879-2013; XRAY, SUZAKU/A-1808-2009 OI Terada, Yukikatsu/0000-0002-2359-1857; NR 23 TC 16 Z9 16 U1 0 U2 0 PU OXFORD UNIV PRESS PI OXFORD PA GREAT CLARENDON ST, OXFORD OX2 6DP, ENGLAND SN 0004-6264 EI 2053-051X J9 PUBL ASTRON SOC JPN JI Publ. Astron. Soc. Jpn. PD JAN 30 PY 2007 VL 59 SI 1 BP S177 EP S183 DI 10.1093/pasj/59.sp1.S177 PG 7 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 139ON UT WOS:000244441700013 ER PT J AU Ota, N Fukazawa, Y Fabian, AC Kanemaru, T Kawaharada, M Kawano, N Kelley, RL Kitaguchi, T Makishima, K Matsushita, K Murase, K Nakazawa, K Ohashi, T Sanders, JS Tamura, T Urata, Y AF Ota, Naomi Fukazawa, Yasushi Fabian, Andrew C. Kanemaru, Takehiro Kawaharada, Madoka Kawano, Naomi Kelley, Richard L. Kitaguchi, Takao Makishima, Kazuo Matsushita, Kyoko Murase, Kouichi Nakazawa, Kazuhiro Ohashi, Takaya Sanders, Jeremy S. Tamura, Takayuki Urata, Yuji TI Suzaku observations of the Centaurus cluster: Absence of bulk motions in the intracluster medium SO PUBLICATIONS OF THE ASTRONOMICAL SOCIETY OF JAPAN LA English DT Article DE galaxies : clusters : individual (Centaurus cluster); X-rays : galaxies : clusters; X-rays : ISM ID GALAXIES; TURBULENCE; FLOWS; ASCA AB The Centaurus cluster (z = 0.0104) was observed with the X-ray Imaging Spectrometer (XIS) onboard the Suzaku X-ray satellite in three pointings, one centered on the cluster core and the other two offset by +/- 8' in declination. To search for possible bulk motions of the intracluster medium, the central energy of a He-like Fe K line (at a rest-frame energy of 6.7 keV) was examined to look for a positional dependence. Over spatial scales of 50 kpc to 140 kpc around the cluster core, the central line energy was found to be constant within a calibration error of 15 eV. The 90% upper limit on the line-of-sight velocity difference is vertical bar Delta upsilon vertical bar < 1400km s(-1) giving a tighter constraint than previous measurements. The significant velocity gradients inferred from a previous Chandra study were not detected between two pairs of rectangular regions near the cluster core. These results suggest that the bulk velocity does not largely exceed the thermal velocity of the gas in the central region of the Centaurus cluster. The mean redshift of the intracluster medium was determined to be 0.0097, in agreement with the optical redshift of the cluster within the calibration uncertainty. Implications of the present results for estimating the cluster mass are briefly discussed. C1 RIKEN, Cosm Radiat Lab, Wako, Saitama 3510198, Japan. Hiroshima Univ, Dept Phys Sci, Sch Sci, Hiroshima 7398526, Japan. Univ Cambridge, Inst Astron, Cambridge CB3 0HA, England. Tokyo Univ Sci, Fac Sci, Dept Phys, Shinjuku Ku, Tokyo 1628601, Japan. Univ Tokyo, Dept Phys, Bunkyo Ku, Tokyo 1130033, Japan. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Saitama Univ, Dept Phys, Urawa, Saitama 3388570, Japan. Inst Space & Astronaut Sci, JAXA, Sagamihara, Kanagawa 2298510, Japan. Tokyo Metropolitan Univ, Dept Phys, Hachioji, Tokyo 1920397, Japan. RP Ota, N (reprint author), RIKEN, Cosm Radiat Lab, Wako, Saitama 3510198, Japan. EM ota@crab.riken.jp RI Kelley, Richard/K-4474-2012; Tamura, Takayuki/K-8236-2012; XRAY, SUZAKU/A-1808-2009; OI Sanders, Jeremy/0000-0003-2189-4501 NR 28 TC 32 Z9 32 U1 0 U2 0 PU OXFORD UNIV PRESS PI OXFORD PA GREAT CLARENDON ST, OXFORD OX2 6DP, ENGLAND SN 0004-6264 EI 2053-051X J9 PUBL ASTRON SOC JPN JI Publ. Astron. Soc. Jpn. PD JAN 30 PY 2007 VL 59 SI 1 BP S351 EP S359 DI 10.1093/pasj/59.sp1.S351 PG 9 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 139ON UT WOS:000244441700029 ER PT J AU Reeves, JN Awaki, H Dewangan, GC Fabian, AC Fukazawa, Y Gallo, L Griffiths, R Inoue, H Kunieda, H Markowitz, A Miniutti, G Mizuno, T Mushotzky, R Okajima, T Ptak, A Takahashi, T Terashima, Y Ushio, M Watanabe, S Yamasaki, T Yamauchi, M Yaqoob, T AF Reeves, James N. Awaki, Hisamitsu Dewangan, Gulab C. Fabian, Andy C. Fukazawa, Yasushi Gallo, Luigi Griffiths, Richard Inoue, Hajime Kunieda, Hideyo Markowitz, Alex Miniutti, Giovanni Mizuno, Tsunefumi Mushotzky, Richard Okajima, Takashi Ptak, Andy Takahashi, Tadayuki Terashima, Yuichi Ushio, Masayoshi Watanabe, Shin Yamasaki, Tomonori Yamauchi, Makoto Yaqoob, Tabir TI Revealing the high energy emission from the obscured Seyfert galaxy MCG-5-23-16 with Suzaku SO PUBLICATIONS OF THE ASTRONOMICAL SOCIETY OF JAPAN LA English DT Article DE galaxies : active; galaxies : individual (MCG-5-23-16); galaxies : Seyfert; X-rays : galaxies ID ACTIVE GALACTIC NUCLEI; X-RAY REFLECTION; K-ALPHA-EMISSION; XMM-NEWTON; BOARD SUZAKU; COLD MATTER; BLACK-HOLE; BEPPOSAX OBSERVATIONS; COMPTON REFLECTION; UNIFICATION MODEL AB We report on a 100 ks Suzaku observation of the bright, nearby (z = 0.008486) Seyfert 1.9 galaxy MCG -5-23-16. The broad-band (0.4-100keV) X-ray spectrum allows us to determine the nature of the high energy emission with little ambiguity. The X-ray continuum consists of a cutoff power-law of photon index r = 1.9, absorbed through Compton-thin matter of column density N-H = 1.6 x 10(22) cm(-2). A soft excess is observed below 1 keV and is likely a combination of emission from scattered continuum photons and distant photoionized gas. The iron K line profile is complex, showing narrow neutral iron K alpha and K beta emission, as well as a broad line which can be modeled by a moderately inclined accretion disk. The line profile shows either the disk is truncated at a few tens of gravitational radii, or the disk emissivity profile is relatively flat. A strong Compton reflection component is detected above 10 keV, which is best modeled by a combination of reflection off distant matter and the accretion disk. The reflection component does not appear to vary. The overall picture is that this Seyfert 1.9 galaxy is viewed at moderate (similar to 50 degrees) inclination through Compton-thin matter at the edge of a Compton-thick torus covering similar to 2 pi steradians, consistent with unified models. C1 NASA, Goddard Space Flight Ctr, Explorat Universe Div, Greenbelt, MD 20771 USA. Johns Hopkins Univ, Dept Phys & Astron, Baltimore, MD 21218 USA. Ehime Univ, Dept Phys, Matsuyama, Ehime 7908577, Japan. Carnegie Mellon Univ, Dept Phys, Pittsburgh, PA 15213 USA. Univ Cambridge, Inst Astron, Cambridge CB3 0HA, England. Hiroshima Univ, Dept Phys Sci, Hiroshima 7398526, Japan. Max Planck Inst Extraterr Phys, D-37075 Garching, Germany. Japan Aerosp Explorat Agcy, Inst Space & Astronaut Sci, Sagamihara, Kanagawa 2298510, Japan. Nagoya Univ, Dept Phys, Chikusa Ku, Nagoya, Aichi 4648602, Japan. Miyazaki Univ, Dept Appl Phys, Miyazaki 8892192, Japan. RP Reeves, JN (reprint author), NASA, Goddard Space Flight Ctr, Explorat Universe Div, Code 662, Greenbelt, MD 20771 USA. EM jnr@milkyway.gsfc.nasa.gov RI Miniutti, Giovanni/L-2721-2014; XRAY, SUZAKU/A-1808-2009 OI Miniutti, Giovanni/0000-0003-0707-4531; NR 78 TC 60 Z9 60 U1 0 U2 1 PU OXFORD UNIV PRESS PI OXFORD PA GREAT CLARENDON ST, OXFORD OX2 6DP, ENGLAND SN 0004-6264 EI 2053-051X J9 PUBL ASTRON SOC JPN JI Publ. Astron. Soc. Jpn. PD JAN 30 PY 2007 VL 59 SI 1 BP S301 EP S314 DI 10.1093/pasj/59.sp1.S301 PG 14 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 139ON UT WOS:000244441700025 ER PT J AU Serlemitsos, PJ Soong, Y Chan, KW Okajima, T Lehan, JP Maeda, Y Itoh, K Mori, H Iizuka, R Itoh, A Inoue, H Okada, S Yokoyama, Y Itoh, Y Ebara, M Nakamura, R Suzuki, K Ishida, M Hayakawa, A Inoue, C Okuma, S Kubota, R Suzuki, M Osawa, T Yamashita, K Kunieda, H Tawara, Y Ogasaka, Y Furuzawa, A Tamura, K Shibata, R Haba, Y Naitou, M Misaki, K AF Serlemitsos, Peter J. Soong, Yang Chan, Kai-Wing Okajima, Takashi Lehan, John P. Maeda, Yoshitomo Itoh, Kei Mori, Hideyuki Iizuka, Ryo Itoh, Akiharu Inoue, Hirohiko Okada, Shunsaku Yokoyama, Yushi Itoh, Yurni Ebara, Masatoshi Nakamura, Ryoko Suzuki, Kensuke Ishida, Manabu Hayakawa, Akira Inoue, Chiaki Okuma, Satoshi Kubota, Ren Suzuki, Masaki Osawa, Takeyuki Yamashita, Koujun Kunieda, Hideyo Tawara, Yuzuru Ogasaka, Yasushi Furuzawa, Akihiro Tamura, Keisuke Shibata, Ryo Haba, Yoshito Naitou, Masataka Misaki, Kazutami TI The X-ray telescope onboard Suzaku SO PUBLICATIONS OF THE ASTRONOMICAL SOCIETY OF JAPAN LA English DT Article DE instruments : detectors; telescopes; X-rays : general ID IN-ORBIT PERFORMANCE; BOARD SUZAKU; ASTRO-E; MIRRORS; SPECTROMETER; DETECTOR; DESIGN; SOLAR AB We present the design parameters, production process, and in-flight performance of the X-ray telescope (XRT) onboard Suzaku. The imaging capability is significantly improved over the ASCA XRT, which had half-power diameters of 36, to 1'8-2'3 for all four XRT-I modules. The optical axes are found to be distributed within a radius of 1'3, which makes the observation efficiency of all the XRTs more than 97% at the XIS-default observing position. The vignetting over the XIS field of view predicted via ray-tracing coincides with that measured for observations of the Crab Nebula to within similar to 10%. Contemporaneous fits of a power law to all of the XIS spectra of the Crab Nebula taken at the two standard observing positions (XIS/HXD-default positions) gives a flux consistent with that obtained by Toor and Seward (1974, AJ, 79, 995) to within similar to 2%. The pre-collimator on the top of each XRT module successfully reduces the intensity of the stray light from the 20' and 50'-off directions down to the level of pre-flight expectations. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. JAXA, Inst Space & Astronaut Sci, Sagamihara, Kanagawa 2298510, Japan. Tokyo Metropolitan Univ, Dept Phys, Tokyo 1920397, Japan. Nagoya Univ, Dept Paraticle & Astrophys, Chikusa Ku, Nagoya, Aichi 4648602, Japan. Max Planck Inst Extraterr Phys, D-85741 Garching, Germany. RP Serlemitsos, PJ (reprint author), NASA, Goddard Space Flight Ctr, Code 662, Greenbelt, MD 20771 USA. EM ishida@phys.metro-u.ac.jp RI XRAY, SUZAKU/A-1808-2009 NR 29 TC 342 Z9 343 U1 1 U2 6 PU OXFORD UNIV PRESS PI OXFORD PA GREAT CLARENDON ST, OXFORD OX2 6DP, ENGLAND SN 0004-6264 EI 2053-051X J9 PUBL ASTRON SOC JPN JI Publ. Astron. Soc. Jpn. PD JAN 30 PY 2007 VL 59 SI 1 BP S9 EP S21 DI 10.1093/pasj/59.sp1.S9 PG 13 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 139ON UT WOS:000244441700002 ER PT J AU Smith, RK Bautz, MW Edgar, RJ Fujimoto, R Hamaguchi, K Hughes, JR Ishida, M Kelley, R Kilbourne, CA Kuntz, KD McCammon, D Miller, E Mitsuda, K Mukai, K Plucinsky, PP Porter, FS Snowden, SL Takei, Y Terada, Y Tsuboi, Y Yamasaki, NY AF Smith, Randall K. Bautz, Mark W. Edgar, Richard J. Fujimoto, Ryuichi Hamaguchi, Kenji Hughes, John R. Ishida, Manabu Kelley, Richard Kilbourne, Caroline A. Kuntz, K. D. McCammon, Dan Miller, Eric Mitsuda, Kazuhisa Mukai, Koji Plucinsky, Paul P. Porter, F. Scott Snowden, Steve L. Takei, Yoh Terada, Yukikatsu Tsuboi, Yohko Yamasaki, Noriko Y. TI Suzaku observations of the local and distant hot ISM SO PUBLICATIONS OF THE ASTRONOMICAL SOCIETY OF JAPAN LA English DT Article DE ISM : bubbles; plasmas; X-rays : ISM ID INTERSTELLAR-MEDIUM; RAY; EMISSION; SPECTRUM; CHANDRA; PLASMA; BUBBLE; HALO; SKY AB Suzaku observed the molecular cloud MBM 12 and a blank field less than 3 degrees away to separate the local and distant components of the diffuse soft X-ray background. Towards MBM 12, a local (D less than or similar to 275 pc) O VII emission line was clearly detected with an intensity of 3.5 photons cm(-2) s(-1) sr(-1) (or line units, LU), and the O VIII flux was < 0.34 LU. The origin of this O VII emission could be hot gas in the Local Hot Bubble (LHB), charge exchange within the heliosphere with oxygen ions from the solar wind (SWCX), or both. If entirely from the LHB, the emission could be explained by a region with emission measure of 0.0075 cm(-6) pc and a temperature of 1.2 x 10(6) K. However, this temperature and emission measure implies 1/4 keV emission in excess of observations. There is no evidence in the X-ray light curve or solar wind data for a significant contribution from geocoronal SWCX, although interplanetary SWCX is still possible. In any case, the observed O VII flux represents an upper limit to both the LHB emission and interplanetary SWCX in this direction. The blank field was observed immediately afterwards. The net off-cloud O VII and O VIII intensities were (respectively) 2.34 +/- 0.33 and 0.77 +/- 0.16 LU, after subtracting the on-cloud foreground emission. If this more distant O VII and O VIII emission is from a thermal plasma in collisional equilibrium beyond the Galactic disk, we infer it has a temperature of (2.1 +/- 0.1) x 10(6) K with an emission measure of (4 +/- 0.6) x 10(-3) cm(-6) pc. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Johns Hopkins Univ, Dept Phys & Astron, Baltimore, MD 21218 USA. MIT, Kavli Inst Astrophys & Space Res, Cambridge, MA 02139 USA. Harvard Smithsonian Ctr Astrophys, High Energy Astrophys Div, Cambridge, MA 02138 USA. Rutgers State Univ, Piscataway, NJ 08854 USA. Univ Wisconsin, Dept Phys, Madison, WI 53706 USA. Tokyo Metropolitan Univ, Dept Phys, Hachioji, Tokyo 1920397, Japan. Japan Aerosp Explorat Agcy, JAXA, ISAS, Dept High Energy Astrophys, Sagamihara, Kanagawa 2298510, Japan. RIKEN, Cosm Radiat Lab, Wako, Saitama 3510198, Japan. Chuo Univ, Fac Sci & Engn, Dept Phys, Bunkyo Ku, Tokyo 1128551, Japan. RP Smith, RK (reprint author), NASA, Goddard Space Flight Ctr, Code 662, Greenbelt, MD 20771 USA. EM rsmith@milkyway.gsfc.nasa.gov RI Yamasaki, Noriko/C-2252-2008; Mitsuda, Kazuhisa/C-2649-2008; Porter, Frederick/D-3501-2012; Kelley, Richard/K-4474-2012; Terada, Yukikatsu/A-5879-2013; XRAY, SUZAKU/A-1808-2009 OI Porter, Frederick/0000-0002-6374-1119; Terada, Yukikatsu/0000-0002-2359-1857; NR 35 TC 70 Z9 70 U1 0 U2 0 PU OXFORD UNIV PRESS PI OXFORD PA GREAT CLARENDON ST, OXFORD OX2 6DP, ENGLAND SN 0004-6264 EI 2053-051X J9 PUBL ASTRON SOC JPN JI Publ. Astron. Soc. Jpn. PD JAN 30 PY 2007 VL 59 SI 1 BP S141 EP S150 DI 10.1093/pasj/59.sp1.S141 PG 10 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 139ON UT WOS:000244441700009 ER PT J AU Takei, Y Ohashi, T Henry, JP Mitsuda, K Fujimoto, R Tamura, T Yamasaki, NY Hayashida, K Tawa, N Matsushita, K Bautz, MW Hughes, JP Madejski, GM Kelley, RL Arnaud, KA AF Takei, Yoh Ohashi, Takaya Henry, J. Patrick Mitsuda, Kazuhisa Fujimoto, Ryuichi Tamura, Takayuki Yamasaki, Noriko Y. Hayashida, Kiyoshi Tawa, Noriaki Matsushita, Kyoko Bautz, Mark W. Hughes, John P. Madejski, Grzegorz M. Kelley, Richard L. Arnaud, Keith A. TI Search for oxygen emission from warm-hot intergalactic medium around a 2218 with Suzaku SO PUBLICATIONS OF THE ASTRONOMICAL SOCIETY OF JAPAN LA English DT Article DE cosmology : large-scale structure; galaxies : clusters : individual (A 2218); galaxies : intergalactic medium; X-rays : diffuse background ID EXTREME-ULTRAVIOLET EMISSION; X-RAY FOREST; XMM-NEWTON; EXCESS EMISSION; GALAXY CLUSTERS; COMA CLUSTER; CHANDRA; MARKARIAN-421; ABUNDANCES; DISCOVERY AB We searched for redshifted O emission lines from a possible warm-hot intergalactic medium (WHIM) surrounding the cluster of galaxies A 2218 at z = 0.1756 using the X-ray Imaging Spectrometer (XIS) instrument on Suzaku. This cluster is thought to have an elongated structure along the line of sight based on previous studies. We studied systematic uncertainties in the spectrum of the Galactic emission and in the soft X-ray response of the detectors due to the contamination building up on the XIS filters. We detected no significant redshifted O lines, and set a tight constraint on the intensity with upper 2 limits for the surface brightness of O VII and O VIII lines of 1.1 x 10(-7) and 3.0 x 10(-7) photons cm(-2) s(-1) arcmin(-2), respectively. These upper limits are significantly lower than the previously reported fluxes from the WHIM around other clusters of galaxies. We also discuss the prospect for detecting the WHIM lines with the Suzaku XIS in the future. C1 Inst Space & Astronaut Sci, Japan Aerosp Explorat Agcy, Sagamihara, Kanagawa 2298510, Japan. Tokyo Metropolitan Univ, Dept Phys, Hachioji, Tokyo 1920397, Japan. Univ Hawaii, Inst Astron, Honolulu, HI 96822 USA. Osaka Univ, Fac Sci, Dept Astrophys, Toyonaka, Osaka 5600043, Japan. Tokyo Univ Sci, Fac Sci, Dept Phys, Shinjuku Ku, Tokyo 1628601, Japan. MIT, Kavli Inst Astrophys & Space Res, Cambridge, MA 02139 USA. Rutgers State Univ, Dept Phys & Astron, Piscataway, NJ 08854 USA. Stanford Linear Accelerator Ctr, Menlo Pk, CA 94025 USA. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Takei, Y (reprint author), Inst Space & Astronaut Sci, Japan Aerosp Explorat Agcy, 3-1-1 Yoshinodai, Sagamihara, Kanagawa 2298510, Japan. EM takei@astro.isas.jaxa.jp RI Yamasaki, Noriko/C-2252-2008; Mitsuda, Kazuhisa/C-2649-2008; Kelley, Richard/K-4474-2012; Tamura, Takayuki/K-8236-2012; XRAY, SUZAKU/A-1808-2009 NR 40 TC 13 Z9 13 U1 0 U2 0 PU OXFORD UNIV PRESS PI OXFORD PA GREAT CLARENDON ST, OXFORD OX2 6DP, ENGLAND SN 0004-6264 EI 2053-051X J9 PUBL ASTRON SOC JPN JI Publ. Astron. Soc. Jpn. PD JAN 30 PY 2007 VL 59 SI 1 BP S339 EP S349 DI 10.1093/pasj/59.sp1.S339 PG 11 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 139ON UT WOS:000244441700028 ER PT J AU Tashiro, MS Abe, K Angelini, L Barthelmy, S Gehrels, N Ishikawa, N Kaluzienski, LJ Kawai, N Kelley, RL Kinugasa, K Kodaira, H Kohmura, T Kubota, K Maeda, Y Maeno, S Murakami, H Murakami, T Nakagawa, YE Nakazawa, K Nousek, J Okuno, S Onda, K Reeves, JN Ricker, G Sato, G Sonoda, E Suzuki, M Takahashi, T Tamagawa, T Torii, K Ueda, Y Urata, Y Yamaoka, K Yamauchi, M Yonetoku, D Yoshida, A Yoshinari, S AF Tashiro, Makoto S. Abe, Keiichi Angelini, Lorella Barthelmy, Scott Gehrels, Neil Ishikawa, Nobuyuki Kaluzienski, Louis J. Kawai, Nobuyuki Kelley, Richard L. Kinugasa, Kenzo Kodaira, Hironobu Kohmura, Takayoshi Kubota, Kaori Maeda, Yoshitomo Maeno, Shouta Murakami, Hiroshi Murakami, Toshio Nakagawa, Yujin E. Nakazawa, Kazuhiro Nousek, John Okuno, Shin'ya Onda, Kaori Reeves, James N. Ricker, George Sato, Goro Sonoda, Eri Suzuki, Motoko Takahashi, Tadayuki Tamagawa, Toru Torii, Ken'ichi Ueda, Yoshihiro Urata, Yuji Yamaoka, Kazutaka Yamauchi, Makoto Yonetoku, Daisuke Yoshida, Atsumasa Yoshinari, Satoru TI Swift and Suzaku observations of the X-ray afterglow from the GRB 060105 SO PUBLICATIONS OF THE ASTRONOMICAL SOCIETY OF JAPAN LA English DT Article DE gamma rays : burst; radiation mechanisms : non-thermal; relativistic jet; X-rays : individual (GRB 060105); X-rays : stars acceleration of particles ID BURST AFTERGLOWS; LIGHT CURVES; BOARD SUZAKU; TELESCOPE; VARIABILITY; DETECTOR; MISSION AB Results are presented of early X-ray afterglow observations of GRB 060105 by Swift and Suzaku. The bright, long gamma-ray burst GRB; 060105 triggered the Swift Burst Alert Telescope at 06:49:28 on 2006 January 5 (T-0). The Suzaku team commenced a pre-planned target of opportunity observation at 19 ks (5.3 hr) after the Swift trigger. The X-ray flux faded during observations from 6.8 x 10(-9) ergs(-1) cm(-2) (at T-0 + 87 s with the Swift/XRT) to 1.5 x 10(-13) erg s(-1) cm(-2) [at T-0 + 94-101 ks with the Suzaku X-ray Imaging Spectrometer (XIS)] in the 2-10 keV energy band. Following prompt emission and successive very steep decay, a shallow decay was observed from To + 187 s to T-0 + 1287 s. After an observation gap during T-0 + (1.5-3) ks, an extremely early steep decay was observed in T-0 + (4-30) ks. The lightcurve flattened again at T-0 + 30ks, and another steep decay followed from T-0 + 50ks to the end of observations. Both steep decays exhibited decay indices of 2.3-2.4. This very early break, if it is a jet break, is the earliest case among X-ray afterglow observations, suggesting a very narrow jet whose opening angle is well below 1 degrees. The unique Suzaku/XIS data allow us to set very tight upper limits on line emission or absorption in this GRB. For the reported pseudo-redshift of z = 4.0 +/- 1.3 the upper limit on the iron line equivalent width is 50 eV. C1 Saitama Univ, Dept Phys, Urawa, Saitama 3388570, Japan. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Aoyama Gakuin Univ, Dept Math & Phys, Sagamihara, Kanagawa 2298558, Japan. Tokyo Inst Technol, Dept Phys, Meguro Ku, Tokyo 1528551, Japan. Gunma Astron Observ, Gunma 3770702, Japan. Kanazawa Univ, Dept Phys, Kanazawa, Ishikawa 9201192, Japan. Kogakuin Univ, Dept Phys, Hachioji, Tokyo 1920015, Japan. Kyoto Univ, Fac Sci, Dept Astron, Sakyo Ku, Kyoto 6068502, Japan. Inst Space & Astronaut Sci, JAXA, Sagamihara, Kanagawa 2298510, Japan. Miyazaki Univ, Fac Engn, Miyazaki 8892192, Japan. Penn State Univ, Dept Astron & Astrophys, University Pk, PA 16802 USA. MIT, Ctr Space Res, Cambridge, MA 02139 USA. RIKEN, Wako, Saitama 3510198, Japan. Osaka Univ, Dept Earth & Space Sci, Toyonaka, Osaka 5600043, Japan. RP Tashiro, MS (reprint author), Saitama Univ, Dept Phys, Urawa, Saitama 3388570, Japan. EM tashiro@phy.saitama-u.ac.jp RI Barthelmy, Scott/D-2943-2012; Gehrels, Neil/D-2971-2012; Tashiro, Makoto/J-4562-2012; Kelley, Richard/K-4474-2012; XRAY, SUZAKU/A-1808-2009 NR 44 TC 7 Z9 7 U1 0 U2 0 PU OXFORD UNIV PRESS PI OXFORD PA GREAT CLARENDON ST, OXFORD OX2 6DP, ENGLAND SN 0004-6264 EI 2053-051X J9 PUBL ASTRON SOC JPN JI Publ. Astron. Soc. Jpn. PD JAN 30 PY 2007 VL 59 SI 1 BP S361 EP S367 DI 10.1093/pasj/59.sp1.S361 PG 7 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 139ON UT WOS:000244441700030 ER PT J AU Tsuru, TG Ozawa, M Hyodo, Y Matsumoto, H Koyama, K Awaki, H Fujimoto, R Griffiths, R Kilbourne, C Matsushita, K Mitsuda, K Ptak, A Ranalli, P Yamasaki, NY AF Tsuru, Takeshi Go Ozawa, Midori Hyodo, Yoshiaki Matsumoto, Hironori Koyama, Katsuji Awaki, Hisamitsu Fujimoto, Ryuichi Griffiths, Richard Kilbourne, Caroline Matsushita, Kyoko Mitsuda, Kazuhisa Ptak, Andrew Ranalli, Piero Yamasaki, Noriko Y. TI X-ray spectral study of the extended emission, 'the Cap' located 11.6 kpc above the disk of M 82 SO PUBLICATIONS OF THE ASTRONOMICAL SOCIETY OF JAPAN LA English DT Article DE galaxies : abundances; galaxies : individual (M 82); galaxies : jets; galaxies : starburst; X-rays : galaxies ID STARBURST GALAXY M82; HIGH-RESOLUTION CAMERA; H-ALPHA EMISSION; XMM-NEWTON; I SUPERNOVAE; NGC 253; ABUNDANCES; CLUSTERS; ASCA; MODELS AB The extended X-ray emission from 'the Cap' region, located 11' (11.6 kpc) above the disk of the starburst galaxy M 82, has been observed with Suzaku and XMM-Newton. Owing to the good energy resolution and the large collecting area of the XIS on Suzaku, combined with similar properties of the EPIC instrument on XMM-Newton, we have clearly detected K-shell emission lines from O VII, O VIII, Ne X, Mg XI, Mg XII, Sr XIII, and the Fe L complex. Two optically thin thermal plasma components are required to fit the observed X-ray spectra. We have determined the metal abundances of O, Ne, Mg, Si, and Fe in this region for the first time. Their metal abundance ratios agree well with those of metal-poor stars and the model prediction of metals synthesized by type-II supernovae, but they are not consistent with the metallicities of type-la supernovae. This result is support for the idea that the origin of the metals in the Cap is type-II supernova explosions occurring in the starburst regions in the M 82 galaxy. We discuss the possible contribution from sputtered dust grains to the metals in the Cap. An emission line consistent with the C VI transition of n = 4 to 1 at 0.459 keV has been marginally detected, although it is not statistically significant at the 99% confidence level; the presence of this line would suggest charge-exchange processes in the Cap. C1 Kyoto Univ, Dept Phys, Sakyo Ku, Kyoto 6068502, Japan. Ehime Univ, Dept Phys, Matsuyama, Ehime 7908577, Japan. JAXA, ISAS, Sagamihara, Kanagawa 2298510, Japan. Carnegie Mellon Univ, Dept Phys, Pittsburgh, PA 15213 USA. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Tokyo Univ Sci, Dept Phys, Shinjuku Ku, Tokyo 1628601, Japan. Johns Hopkins Univ, Dept Phys & Astron, Baltimore, MD 21218 USA. RIKEN, Cosm Radiat Lab, Wako, Saitama 3510198, Japan. RP Tsuru, TG (reprint author), Kyoto Univ, Dept Phys, Sakyo Ku, Kyoto 6068502, Japan. EM tsuru@cr.scphys.kyoto-u.ac.jp; midori@cr.scphys.kyoto-u.ac.jp RI Yamasaki, Noriko/C-2252-2008; Mitsuda, Kazuhisa/C-2649-2008; Ranalli, Piero/K-6363-2013; XRAY, SUZAKU/A-1808-2009 OI Ranalli, Piero/0000-0003-3956-755X; NR 62 TC 30 Z9 30 U1 0 U2 2 PU OXFORD UNIV PRESS PI OXFORD PA GREAT CLARENDON ST, OXFORD OX2 6DP, ENGLAND SN 0004-6264 EI 2053-051X J9 PUBL ASTRON SOC JPN JI Publ. Astron. Soc. Jpn. PD JAN 30 PY 2007 VL 59 SI 1 BP S269 EP S282 DI 10.1093/pasj/59.sp1.S269 PG 14 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 139ON UT WOS:000244441700023 ER PT J AU Ueno, M Sato, R Kataoka, J Bamba, A Harrus, I Hiraga, J Hughes, JP Kilbourne, CA Koyama, K Kokubun, M Nakajima, H Ozaki, M Petre, R Takahashi, T Tanaka, T Tomida, H Yaniaguchi, H AF Ueno, Masaru Sato, Rie Kataoka, Jun Bamba, Aya Harrus, Ilana Hiraga, Junko Hughes, John P. Kilbourne, Caroline A. Koyama, Katsuji Kokubun, Motohide Nakajima, Hiroshi Ozaki, Masanobu Petre, Robert Takahashi, Tadayuki Tanaka, Takaaki Tomida, Hiroshi Yaniaguchi, Hiroya TI A Suzaku observation of the low-ionization Fe-Line emission from RCW 86 SO PUBLICATIONS OF THE ASTRONOMICAL SOCIETY OF JAPAN LA English DT Article DE ISM : individual (RCW 86); ISM : supernova remnants; shock waves; X-rays : ISM ID SUPERNOVA REMNANT RCW-86; X-RAY-EMISSION; ACCELERATED ELECTRONS; VORONOI TESSELLATIONS; SHOCK ACCELERATION; SHELL; CASSIOPEIA; TAIL AB The newly operational X-ray satellite Suzaku observed the southwestern quadrant of the supernova remnant RCW 86 in 2006 February to study the nature of the 6.4 keV emission line first detected with the Advanced Satellite for Cosmology and Astronomy (ASCA). The new data confirm the existence of the line, localizing it for the first time; most of the line emission is adjacent and interior to the forward shock, and not at the locus of the continuum hard emission. We also report the first detection of a 7.1 keV line, which we interpret as K beta emission from low-ionization iron. The Fe K line features are consistent with a non-equilibrium plasma of Fe-rich ejecta with n(e)t less than or similar to 10(9) cm(-3) s and kT(e) similar to 5 keV. This combination of low n(e)t and high kT(e) suggests collisionless electron heating in an SNR shock. The Fe K alpha line shows evidence for intrinsic broadening, with a width of 47 (34-59) eV (99% error region). The difference in the spatial distributions of the hard continuum above 3 keV and the Fe K line emission supports a synchrotron origin for the hard continuum. C1 Tokyo Inst Technol, Fac Sci, Dept Phys, Meguro Ku, Tokyo 1528551, Japan. RIKEN, Inst Phys & Chem Res, Wako, Saitama 3510198, Japan. Johns Hopkins Univ, Dept Phys & Astron, Baltimore, MD 21218 USA. NASA, Goddard Space Flight Ctr, Xray Astrophys Lab, Greenbelt, MD 20771 USA. Rutgers State Univ, Dept Phys & Astron, Piscataway, NJ 08854 USA. Kyoto Univ, Grad Sch Sci, Dept Phys, Kyoto 6068502, Japan. Univ Tokyo, Dept Phys, Bunkyo Ku, Tokyo 1130033, Japan. Japan Aerosp Explorat Agcy, Inst Space & Astronaut Sci, Sagamihara, Kanagawa 2298510, Japan. Japan Aerosp Explorat Agcy, Inst Space & Astronaut Sci, ISS Sci Project Team, Tsukuba, Ibaraki 3058505, Japan. RP Ueno, M (reprint author), Tokyo Inst Technol, Fac Sci, Dept Phys, Meguro Ku, 2-12-1,Ohokayama, Tokyo 1528551, Japan. EM masaru@hp.phys.titech.ac.jp RI Ozaki, Masanobu/K-1165-2013; XRAY, SUZAKU/A-1808-2009 NR 30 TC 13 Z9 13 U1 0 U2 0 PU OXFORD UNIV PRESS PI OXFORD PA GREAT CLARENDON ST, OXFORD OX2 6DP, ENGLAND SN 0004-6264 EI 2053-051X J9 PUBL ASTRON SOC JPN JI Publ. Astron. Soc. Jpn. PD JAN 30 PY 2007 VL 59 SI 1 BP S171 EP S176 DI 10.1093/pasj/59.sp1.S171 PG 6 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 139ON UT WOS:000244441700012 ER PT J AU Yaqoob, T Murphy, KD Griffiths, RE Haba, Y Inoue, H Itoh, T Kelley, R Kokubun, M Markowitz, A Mushotzky, R Okajima, T Ptak, A Reeves, J Serlemitsos, PJ Takahashi, T Terashima, Y AF Yaqoob, Tahir Murphy, Kendrah D. Griffiths, Richard E. Haba, Yoshito Inoue, Hajime Itoh, Takeshi Kelley, Richard Kokubun, Motohide Markowitz, Alex Mushotzky, Richard Okajima, Takashi Ptak, Andrew Reeves, James Serlemitsos, Peter J. Takahashi, Tadayuki Terashima, Yuichi TI Precision FeK alpha and FeK beta line spectroscopy of the Seyfert 1.9 galaxy NGC 2992 with Suzaku SO PUBLICATIONS OF THE ASTRONOMICAL SOCIETY OF JAPAN LA English DT Article DE galaxies : active; galaxies : Seyfert; line : profiles; X-rays : galaxies; X-rays : individual (NGC 2992) ID ACTIVE GALACTIC NUCLEI; X-RAY-EMISSION; ABSORPTION CROSS-SECTIONS; K-VACANCY STATES; BLACK-HOLE; NGC 2992; ASCA OBSERVATIONS; OBSCURING TORUS; ACCRETION DISK; H I AB We present detailed time-averaged X-ray spectroscopy in the 0.5-10 keV band of the Seyfert 1.9 galaxy NGC 2992 with the Suzaku X-ray Imaging Spectrometer (XIS). There is an Fe K line emission complex that we model with broad and narrow lines and we show that the intensities of the two components are decoupled at a confidence level > 3 sigma. The broad line (EW = 118(-61)(+32) eV) could originate in an accretion disk (inclined at > 30 degrees). The narrow Fe K alpha line (EW = 163,47 eV) is unresolved by the XIS at 99% confidence and likely originates in distant matter. A significant (narrow) Fe K alpha line is also detected and we describe a new robust method to constrain the ionization state of Fe in the distant line emitter (e.g. the putative obscuring torus). The method does not require any knowledge of possible gravitational and Doppler energy shifts and we deduce that the predominant ionization state of Fe in the distant matter is lower than Fe VIII (at 99% confidence), conservatively taking into account residual calibration uncertainties and theoretical and experimental uncertainties in the Fe K fluorescent line energies. We argue that the narrow Fe K alpha and Fe K beta lines likely originate in a Compton-thin structure. C1 Johns Hopkins Univ, Dept Phys & Astron, Baltimore, MD 21218 USA. NASA, Goddard Space Flight Ctr, Div Atmospher Sci, Greenbelt, MD 20771 USA. Carnegie Mellon Univ, Dept Phys, Pittsburgh, PA 15213 USA. Nagoya Univ, Sch Sci, Dept Astrophys, Chikusa Ku, Nagoya, Aichi 4648601, Japan. Japan Aerosp Explorat Agcy, Inst Space & Astronaut Sci, Sagamihara, Kanagawa 2298510, Japan. Univ Tokyo, Dept Phys, Bunkyo Ku, Tokyo 1310033, Japan. RP Yaqoob, T (reprint author), Ehime Univ, Dept Phys, Matsuyama, Ehime 7908577, Japan. RI Kelley, Richard/K-4474-2012; XRAY, SUZAKU/A-1808-2009 NR 76 TC 38 Z9 38 U1 0 U2 1 PU OXFORD UNIV PRESS PI OXFORD PA GREAT CLARENDON ST, OXFORD OX2 6DP, ENGLAND SN 0004-6264 EI 2053-051X J9 PUBL ASTRON SOC JPN JI Publ. Astron. Soc. Jpn. PD JAN 30 PY 2007 VL 59 SI 1 BP S283 EP S299 DI 10.1093/pasj/59.sp1.S283 PG 17 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 139ON UT WOS:000244441700024 ER PT J AU Tedesco, M AF Tedesco, Marco TI Snowmelt detection over the Greenland ice sheet from SSM/I brightness temperature daily variations SO GEOPHYSICAL RESEARCH LETTERS LA English DT Article ID SOUTHEAST-ALASKAN ICEFIELDS; REGIONS AB We propose a technique for monitoring snowmelt over the Greenland ice sheet between 1992 and 2005 based on the difference between ascending and descending brightness temperatures (DAV) measured either at 19.35- or 37- GHz by the Special Sensor Microwave Imager (SSM/I). Wet snow is detected when both brightness temperatures and DAV values exceed fixed thresholds. Differently from existing techniques, a multi-frequency approach allows detection of wet snow at different depths and intensities, providing a tool for improving climatological and hydrological applications. Air temperature values either recorded by ground based stations or derived from model are used for calibrating and validating the technique. Results are compared with those obtained using backscattering coefficients recorded by the NASA's Quick Scatterometer (QuikSCAT) during an extreme melting event occurring on June 2002. Long-term results show that snowmelt extent has been increasing at a rate of similar to 40,000 Km(2) per year for the past 14 years. C1 Univ Maryland Baltimore Cty, Goddard Earth Sci & Technol Ctr, Baltimore, MD 21228 USA. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Tedesco, M (reprint author), Univ Maryland Baltimore Cty, Goddard Earth Sci & Technol Ctr, 5523 Res Pk Dr,Suite 320, Baltimore, MD 21228 USA. EM mtedesco@umbc.edu RI Tedesco, Marco/F-7986-2015 NR 15 TC 67 Z9 71 U1 0 U2 15 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 JAN 27 PY 2007 VL 34 IS 2 AR L02504 DI 10.1029/2006GL028466 PG 6 WC Geosciences, Multidisciplinary SC Geology GA 131NH UT WOS:000243875500005 ER PT J AU Jiang, X Ku, WL Shia, RL Li, QB Elkins, JW Prinn, RG Yung, YL AF Jiang, Xun Ku, Wai Lim Shia, Run-Lie Li, Qinbin Elkins, James W. Prinn, Ronald G. Yung, Yuk L. TI Seasonal cycle of N2O: Analysis of data SO GLOBAL BIOGEOCHEMICAL CYCLES LA English DT Article ID NITROUS-OXIDE; ATMOSPHERIC N2O; LIFETIMES; AIR; O3 AB [1] We carried out a systematic study of the seasonal cycle and its latitudinal variation in the nitrous oxide (N2O) data collected by National Oceanic and Atmospheric Administration - Global Monitoring Division (NOAA-GMD) and the Advanced Global Atmospheric Gases Experiment (AGAGE). In order to confirm the weak seasonal signal in the observations, we applied the multitaper method for the spectrum analysis and studied the stations with significant seasonal cycle. In addition, the measurement errors must be small compared with the seasonal cycle. The N2O seasonal cycles from seven stations satisfied these criteria and were analyzed in detail. The stations are Alert (82 degrees N, 62 degrees W), Barrow (71 degrees N, 157 degrees W), Mace Head (53 degrees N, 10 degrees W), Cape Kumukahi (19 degrees N, 155 degrees W), Cape Matatula (14 degrees S, 171 degrees W), Cape Grim (41 degrees S, 145 degrees E) and South Pole (90 degrees S, 102 degrees W). The amplitude ( peak to peak) of the seasonal cycle of N2O varies from 0.29 ppb (parts-per-billion by mole fraction in dry air) at the South Pole to 1.15 ppb at Alert. The month at which the seasonal cycle is at a minimum varies monotonically from April ( South Pole) to September ( Alert). The seasonal cycle in the Northern Hemisphere shows the influence of the stratosphere; the seasonal cycle of N2O in the Southern Hemisphere suggests greater influence from surface sources. Preliminary estimates are obtained for the magnitude of the seasonally varying sources needed to account for the observations. C1 CALTECH, Div Geol & Planetary Sci, Pasadena, CA 91125 USA. CALTECH, Jet Prop Lab, Pasadena, CA USA. NOAA, Global Monitoring Div, Earth Syst Res Lab, Boulder, CO USA. MIT, Dept Earth Atmospher & Planetary Sci, Ctr Global Change Sci, Cambridge, MA USA. RP Jiang, X (reprint author), CALTECH, Div Geol & Planetary Sci, Pasadena, CA 91125 USA. EM xun@gps.caltech.edu; kwl@gps.caltech.edu; rls@gps.caltech.edu; qinbin.li@jpl.nasa.gov; james.w.elkins@noaa.gov; rprinn@mit.edu; yly@gps.caltech.edu RI Ku, Wai Lim/R-7170-2016 OI Ku, Wai Lim/0000-0002-8859-6771 NR 18 TC 25 Z9 26 U1 2 U2 12 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 0886-6236 J9 GLOBAL BIOGEOCHEM CY JI Glob. Biogeochem. Cycle PD JAN 26 PY 2007 VL 21 IS 1 AR GB1006 DI 10.1029/2006GB002691 PG 12 WC Environmental Sciences; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Environmental Sciences & Ecology; Geology; Meteorology & Atmospheric Sciences GA 131NI UT WOS:000243875600001 ER PT J AU Hughes, CW Stepanov, VN Fu, LL Barnier, B Hargreaves, GW AF Hughes, C. W. Stepanov, V. N. Fu, L. -L. Barnier, B. Hargreaves, G. W. TI Three forms of variability in Argentine Basin ocean bottom pressure SO JOURNAL OF GEOPHYSICAL RESEARCH-OCEANS LA English DT Article ID LARGE-SCALE OSCILLATIONS; SEA-LEVEL VARIABILITY; TOPEX/POSEIDON; CIRCULATION; RESONANCE; ATLANTIC; DYNAMICS; WAVES AB [ 1] Ocean bottom pressure data are examined from a year-long deployment of two bottom pressure recorders, separated by 417 km, in the Argentine Basin. Three forms of variability are found. At high frequencies ( periods shorter than 2 hours) the signal appears to be due to gravity wave propagation with the waves preferentially coming from the west. At intermediate frequencies ( periods between 2 hours and 12 days), the two records are highly coherent and in phase, reflecting large-scale coherent fluctuations which are well reproduced in a barotropic ocean model. However, the dominant mode is at a period of 20 days, with a phase lag of about 90 - 100 degrees between the two records, consistent with the a mode of variability previously inferred from satellite altimetry and current meters, although the slightly shorter period is consistent with the suggestion that more than one mode contributes to the altimeter observations. Comparison with altimetry demonstrates that aliasing of higher-frequency signals is not a significant source of error and confirms that a previously used altimetry mapping technique reduces the apparent amplitude of the mode. The pressure records show a transport change of about 280 Sv over one 12-day period, and altimetry suggests that regions of higher variability exist. The mode is only weakly excited in barotropic models but is strongly excited in a baroclinic model with a realistic eddy field, suggesting that it is intrinsically linked to interactions between eddies, mean flow, and topography. C1 Proudman Oceanog Lab, Liverpool L3 5DA, Merseyside, England. Jet Prop Lab, Pasadena, CA USA. Inst Mecan Grenoble, Lab Ecoulements Geophys & Ind, F-38041 Grenoble, France. RP Hughes, CW (reprint author), Proudman Oceanog Lab, Joseph Proudman Bldg,6 Brownlow St, Liverpool L3 5DA, Merseyside, England. EM cwh@pol.ac.uk; vst@pol.ac.uk; llf@pacific.jpl.nasa.gov; bernard.barnier@hmg.inpg.fr; gwh@pol.ac.uk RI Hughes, Chris/A-3791-2010; Barnier, Bernard/F-2400-2016; OI Barnier, Bernard/0000-0002-7539-2542; Hughes, Chris/0000-0002-9355-0233 NR 22 TC 13 Z9 13 U1 0 U2 3 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 0148-0227 J9 J GEOPHYS RES-OCEANS JI J. Geophys. Res.-Oceans PD JAN 26 PY 2007 VL 112 IS C1 AR C01011 DI 10.1029/2006JC003679 PG 17 WC Oceanography SC Oceanography GA 131NU UT WOS:000243876900001 ER PT J AU Gobbi, GP Kaufman, YJ Koren, I Eck, TF AF Gobbi, G. P. Kaufman, Y. J. Koren, I. Eck, T. F. TI Classification of aerosol properties derived from AERONET direct sun data SO ATMOSPHERIC CHEMISTRY AND PHYSICS LA English DT Article ID OPTICAL DEPTH; SOLAR-RADIATION; VARIABILITY; INVERSION; THICKNESS; RADIANCE AB Aerosol spectral measurements by sunphotometers can be characterized by three independent pieces of information: 1) the optical thickness (AOT), a measure of the column aerosol concentration, 2) the optical thickness average spectral dependence, given by the Angstrom exponent (alpha), and 3) the spectral curvature of alpha (delta alpha). We propose a simple graphical method to visually convert (alpha, delta alpha) to the contribution of fine aerosol to the AOT and the size of the fine aerosols. This information can be used to track mixtures of pollution aerosol with dust, to distinguish aerosol growth from cloud contamination and to observe aerosol humidification. The graphical method is applied to the analysis of yearly records at 8 sites in 3 continents, characterized by different levels of pollution, biomass burning and mineral dust concentrations. Results depict the dominance of fine mode aerosols in driving the AOT at polluted sites. In stable meteorological conditions, we see an increase in the size of the fine aerosol as the pollution stagnates and increases in optical thickness. Coexistence of coarse and fine particles is evidenced at the polluted sites downwind of arid regions. C1 Univ Maryland, GEST, Baltimore, MD 21201 USA. Weizmann Inst Sci, Dept Environm Sci, IL-76100 Rehovot, Israel. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. CNR, Inst Sci Atmosfera & Clima, Rome, Italy. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Gobbi, GP (reprint author), Univ Maryland, GEST, Baltimore, MD 21201 USA. EM g.gobbi@isac.cnr.it RI ECK, THOMAS/D-7407-2012; Koren, Ilan/K-1417-2012 OI Koren, Ilan/0000-0001-6759-6265 NR 21 TC 113 Z9 117 U1 1 U2 18 PU COPERNICUS GESELLSCHAFT MBH PI GOTTINGEN PA BAHNHOFSALLEE 1E, GOTTINGEN, 37081, GERMANY SN 1680-7316 EI 1680-7324 J9 ATMOS CHEM PHYS JI Atmos. Chem. Phys. PD JAN 25 PY 2007 VL 7 BP 453 EP 458 PG 6 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA 129RT UT WOS:000243748100002 ER PT J AU Ruzmaikin, A Santee, ML Schwartz, MJ Froidevaux, L Pickett, HM AF Ruzmaikin, A. Santee, M. L. Schwartz, M. J. Froidevaux, L. Pickett, H. M. TI The 27-day variations in stratospheric ozone and temperature: New MLS data SO GEOPHYSICAL RESEARCH LETTERS LA English DT Article ID EMPIRICAL MODE DECOMPOSITION; AURA SATELLITE; EOS MLS; SOLAR; VARIABILITY AB We use new data obtained by the Microwave Limb Sounder (MLS) onboard of Aura spacecraft to investigate variations in stratospheric ozone and temperature concurrent with the 27-day variations of solar UV irradiance, measured simultaneously by the Solar Radiation and Climate Experiment (SORCE) during the declining phase of solar activity. Using Empirical Mode Decomposition we determine the latitudinal and height distributions of the 27-day modes for ozone and temperature and find that these modes are enhanced in the lower tropical stratosphere, and at high latitudes in winter. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Ruzmaikin, A (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM alexander.ruzmaikin@jpl.nasa.gov; mls@mls.jpl.nasa.gov RI Schwartz, Michael/F-5172-2016 OI Schwartz, Michael/0000-0001-6169-5094 NR 14 TC 20 Z9 20 U1 0 U2 0 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 JAN 25 PY 2007 VL 34 IS 2 AR L02819 DI 10.1029/2006GL028419 PG 4 WC Geosciences, Multidisciplinary SC Geology GA 131NE UT WOS:000243875200003 ER PT J AU Hahn, BC McLennan, SM Taylor, GJ Boynton, WV Dohm, JM Finch, MJ Hamara, DK Janes, DM Karunatillake, S Keller, JM Kerry, KE Metzger, AE Williams, RMS AF Hahn, Brian C. McLennan, Scott M. Taylor, G. Jeffrey Boynton, William V. Dohm, James M. Finch, Mike J. Hamara, David K. Janes, Daniel M. Karunatillake, Suniti Keller, John M. Kerry, Kristopher E. Metzger, Albert E. Williams, Remo M. S. TI Mars Odyssey Gamma Ray Spectrometer elemental abundances and apparent relative surface age: Implications for Martian crustal evolution SO JOURNAL OF GEOPHYSICAL RESEARCH-PLANETS LA English DT Article ID MERIDIANI-PLANUM; CHEMICAL-COMPOSITION; TERRESTRIAL PLANETS; ACCRETION HISTORY; NORTHERN PLAINS; IMPACT CRATERS; GUSEV CRATER; CHEMISTRY; SOILS; ROCKS AB [ 1] Quantifying secular variations in the chemical composition of the Martian crust provides unique insights into the processes that have guided the evolution of the Martian crust-mantle system. Using global abundances for a suite of elements determined by the Gamma Ray Spectrometer (GRS) on board the Mars Odyssey spacecraft and global mapping of apparent surface age adapted from existing geologic maps in the USGS Martian Geologic Investigation series, we report the average abundance of K, Th, Fe, Cl, H, and Si for the major Martian geologic epochs (Noachian, Hesperian, and Amazonian). Average GRS-determined K and Th abundances generally decrease by 9% and 7%, respectively, between the Hesperian and the Amazonian, possibly implying evolving magma chemistry throughout major resurfacing events ( although the effects of surficial alteration processes cannot be entirely discounted). GRS-determined Fe and Cl averages increase by 12% and 19%, respectively, with younger apparent relative surface age, suggesting the possible mobilization and transport of these elements through aqueous processes ( although an igneous origin for the variation in Fe also cannot be excluded). While H abundance does vary with surface age, the relationship is likely not governed by geologic processes. No statistically reliable apparent surface age relation was found for Si. C1 SUNY Stony Brook, Dept Geosci, Stony Brook, NY 11794 USA. Hawaii Inst Geophys & Planetol, Honolulu, HI USA. Univ Arizona, Lunar & Planetary Lab, Tucson, AZ 85721 USA. Univ Arizona, Dept Hydrol & Water Resources, Tucson, AZ 85721 USA. Cornell Univ, Dept Astron, Ithaca, NY 14853 USA. CALTECH, Jet Prop Lab, Pasadena, CA USA. RP Hahn, BC (reprint author), SUNY Stony Brook, Dept Geosci, 255 Earth & Space Sci Bldg, Stony Brook, NY 11794 USA. EM bhahn@mantle.geo.sunysb.edu RI Karunatillake, Suniti/A-5934-2009; Dohm, James/A-3831-2014 OI Karunatillake, Suniti/0000-0001-9891-1432; NR 73 TC 20 Z9 20 U1 1 U2 9 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 JAN 25 PY 2007 VL 112 IS E3 AR E03S11 DI 10.1029/2006JE002821 PG 13 WC Geochemistry & Geophysics SC Geochemistry & Geophysics GA 131NW UT WOS:000243877100001 ER PT J AU Koch, D Bond, TC Streets, D Unger, N van der Werf, GR AF Koch, Dorothy Bond, Tami C. Streets, David Unger, Nadine van der Werf, Guido R. TI Global impacts of aerosols from particular source regions and sectors SO JOURNAL OF GEOPHYSICAL RESEARCH-ATMOSPHERES LA English DT Article ID GENERAL-CIRCULATION MODEL; BLACK CARBON AEROSOL; ORGANIC-CARBON; 3-DIMENSIONAL MODEL; CLIMATE SENSITIVITY; GODDARD INSTITUTE; LIGHT-ABSORPTION; FUEL COMBUSTION; SULFUR CYCLE; ART. AB [1] We study the impacts of present-day aerosols emitted from particular regions and from particular sectors, as predicted by the Goddard Institute for Space Studies GCM. We track the distribution and direct radiative forcing of aerosols, including sulfate and black and organic carbon, emitted from major source regions (North America, Europe, south Asia, Southeast Asia, South America, and Africa). We also partition the emissions by sector, including industrial, power, residential, transport, biomass burning, and natural. Southeast Asia produces 15% and 10% of the world's black carbon and sulfate and exports over 2/ 3 of this burden over the Northern Hemisphere. About 1/ 2 of the SO2 emitted by Southeast Asia and Europe is not converted to sulfate because of oxidant limitation. Although Africa has the largest biomass burning emissions, South America generates a larger (about 20% of the global carbonaceous) aerosol burden; about 1/ 2 of this burden is exported and dominates the carbonaceous aerosol load in the Southern Hemisphere. Calculated direct anthropogenic radiative forcings are -0.29, -0.06, and 0.24 W m(-2) for sulfate, organic, and black carbon, respectively. The largest BC radiative forcings are from residential (0.09 W m(-2)) and transport (0.06 W m(-2)) sectors, making these potential targets to counter global warming. However, scattering components within these sectors reduce these to 0.04 and 0.03 W m(-2), respectively. Most anthropogenic sulfate comes from power and industry sectors, and these sectors are responsible for the large negative aerosol forcings over the central Northern Hemisphere. C1 Columbia Univ, NASA, Goddard Inst Space Studies, New York, NY 10025 USA. Univ Illinois, Dept Civil & Environm Engn, Urbana, IL 61801 USA. Argonne Natl Lab, Argonne, IL 60439 USA. Vrije Univ Amsterdam, Dept Hydrol & Geoenvironm Sci, Amsterdam, Netherlands. RP Koch, D (reprint author), Columbia Univ, NASA, Goddard Inst Space Studies, 2880 Broadway, New York, NY 10025 USA. EM dkoch@giss.nasa.gov RI Bond, Tami/A-1317-2013; Unger, Nadine/M-9360-2015; van der Werf, Guido/M-8260-2016; OI Bond, Tami/0000-0001-5968-8928; van der Werf, Guido/0000-0001-9042-8630; Streets, David/0000-0002-0223-1350 NR 49 TC 124 Z9 127 U1 5 U2 27 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 JAN 24 PY 2007 VL 112 IS D2 AR D02205 DI 10.1029/2005JD007024 PG 24 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA 131NJ UT WOS:000243875800001 ER PT J AU Nicholas, JB Purucker, ME Sabaka, TJ AF Nicholas, Joseph B. Purucker, Michael E. Sabaka, Terence J. TI Age spot or youthful marking: Origin of Reiner Gamma SO GEOPHYSICAL RESEARCH LETTERS LA English DT Article ID CRUSTAL MAGNETIC-ANOMALIES; LUNAR; MOON; MERCURY AB The highly magnetic ( field magnitudes of 50 nT at 18 km altitude) Reiner Gamma albedo feature on the near side of the moon has been explained in terms of differential space weathering of an old feature, or a recent cometary impact. We investigated this feature using magnetometer data from Lunar Prospector. The minimum magnetization necessary to explain the magnetic field observations varies from 100 A/m for a 10 m thick layer, to 1 A/m for a 1 km thick layer. Magnetic sources appear to lie within a few km of the surface, and be magnetized in a north-south direction. The strength of the magnetization appears spatially related to the albedo of the feature. These constraints point towards an ancient origin for the magnetic field signal ( possibly due to basin impact ejecta), and the origin of the albedo feature as a consequence of retarded ageing under the umbrella of the Reiner Gamma mini-magnetosphere. C1 Washington Int Sch, Washington, DC 20008 USA. NASA, Goddard Space Flight Ctr, Planetary Geodynam Lab, Raytheon, Greenbelt, MD 20771 USA. RP Nicholas, JB (reprint author), Washington Int Sch, Washington, DC 20008 USA. RI Sabaka, Terence/D-5618-2012 NR 15 TC 24 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 JAN 23 PY 2007 VL 34 IS 2 AR L02205 DI 10.1029/2006GL027794 PG 4 WC Geosciences, Multidisciplinary SC Geology GA 131NA UT WOS:000243874800005 ER PT J AU Riddle, MJ Craven, M Goldsworthy, PM Carsey, F AF Riddle, M. J. Craven, M. Goldsworthy, P. M. Carsey, F. TI A diverse benthic assemblage 100 km from open water under the Amery Ice Shelf, Antarctica SO PALEOCEANOGRAPHY LA English DT Article ID EAST ANTARCTICA; MCMURDO SOUND; WHITE-ISLAND; HOLOCENE RETREAT; MARINE SNOW; BEAVER LAKE; WEDDELL SEA; PRYDZ BAY; ROSS SEA; BENEATH AB [1] A hot water drill was used to penetrate 480 m of ice to reveal a diverse benthic assemblage, dominated by suspension-feeding invertebrates, under the Amery Ice Shelf ( East Antarctica) at a location 100 km from open water and at a depth of 775 m below sea level ( 840 m below the ice shelf surface). This is the first record of a benthic assemblage of this type found at this distance under an ice shelf. The few previous reports of life under ice shelves describe assemblages with very different trophic strategies ( e. g., sparse assemblages of mobile scavengers or chemotrophs) or are in circumstances in which in situ photosynthesis at tide cracks or through the ice cannot be ruled out as a potential source of primary production. The physical characteristics of the Amery Ice Shelf and the feeding strategies represented together indicate that the only likely source of primary production to sustain the benthic assemblage is material advected from open water. This suggestion is supported by observed current speeds in the vicinity and reported rates of particle settling. The observation under an ice shelf of a benthic assemblage that is very similar to those found elsewhere in Antarctica, in locations dominated by annual sea ice or at depths below the photic zone, has implications for the interpretation of sediment paleorecords to represent the history of ice shelf advance and retreat. Without observations of this living assemblage in situ, the remnants of its component species in the sediment record, such as sponge spicules, echinoderm ossicles, and bryozoan fragments, could be interpreted reasonably, but erroneously, to represent open water conditions. C1 Australian Govt Antarctic Div, Kingston, Tas 7050, Australia. Australian Govt Antarctic Div, Hobart, Tas, Australia. Antarctic Climate & Ecosyst Cooperat Res Ctr, Hobart, Tas, Australia. CALTECH, Jet Prop Lab, Pasadena, CA USA. RP Riddle, MJ (reprint author), Australian Govt Antarctic Div, Channel Highway, Kingston, Tas 7050, Australia. EM martin.riddle@aad.gov.au NR 53 TC 27 Z9 27 U1 0 U2 6 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 0883-8305 J9 PALEOCEANOGRAPHY JI Paleoceanography PD JAN 23 PY 2007 VL 22 IS 1 AR PA1204 DI 10.1029/2006PA001327 PG 8 WC Geosciences, Multidisciplinary; Oceanography; Paleontology SC Geology; Oceanography; Paleontology GA 131OE UT WOS:000243878100002 ER PT J AU Pounds, KA Reeves, JN AF Pounds, K. A. Reeves, J. N. TI Is the X-ray spectrum of the narrow emission line QSO PG1211+143 defined by its energetic outflow ? SO MONTHLY NOTICES OF THE ROYAL ASTRONOMICAL SOCIETY LA English DT Article DE galaxies : active; galaxies : individual : PG1211+143; quasars : general; galaxies : Seyfert; X-rays : galaxies ID ACTIVE GALACTIC NUCLEI; XMM-NEWTON; REFLECTION; EXCESS; MCG-6-30-15; ABSORPTION; GALAXIES; QUASARS; WINDS; AGN AB An XMM-Newton observation of the bright QSO PG1211+143 in 2001 revealed a blueshifted absorption line spectrum indicative of a high-velocity radial outflow of highly ionized gas. Unless highly collimated, the outflow mass rate was shown to be comparable to the accretion rate, with mechanical energy a significant fraction of the bolometric luminosity. Analysis of the full XMM-Newton data set now allows the wider effects of that energetic outflow to be explored. We find that absorption and re-emission of the primary continuum flux in the ionized outflow, together with a second, less strongly absorbed, continuum component can explain the strong 'soft excess' in PG1211+143 without the extreme velocity 'smearing' in conflict with observed absorption line widths. Previously unpublished data from a second XMM-Newton observation of PG1211+143 is shown to be consistent with the new spectral model, finding that the additional continuum component dominates the spectral variability. We speculate that this variable continuum component is powered by the high-velocity outflow. C1 Univ Leicester, Dept Phys & Astron, Leicester LE1 7RH, Leics, England. NASA, Goddard Space Flight Ctr, High Energy Astrophys Lab, Greenbelt, MD 20771 USA. RP Pounds, KA (reprint author), Univ Leicester, Dept Phys & Astron, Leicester LE1 7RH, Leics, England. EM kap@star.le.ac.uk NR 29 TC 18 Z9 18 U1 0 U2 0 PU BLACKWELL PUBLISHING PI OXFORD PA 9600 GARSINGTON RD, OXFORD OX4 2DQ, OXON, ENGLAND SN 0035-8711 J9 MON NOT R ASTRON SOC JI Mon. Not. Roy. Astron. Soc. PD JAN 21 PY 2007 VL 374 IS 3 BP 823 EP 831 DI 10.1111/j.1365-2966.2006.11170.x PG 9 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 124XI UT WOS:000243405300006 ER PT J AU Baykal, A Inam, SC Stark, MJ Heffner, CM Erkoca, AE Swank, JH AF Baykal, A. Inam, S. C. Stark, M. J. Heffner, C. M. Erkoca, A. E. Swank, J. H. TI Timing studies on RXTE observations of SAX J2103.5+4545 SO MONTHLY NOTICES OF THE ROYAL ASTRONOMICAL SOCIETY LA English DT Article DE accretion, accretion discs; stars : neutron; pulsars : individual : SAX J2103.5+4545; X-rays : binaries ID X-RAY SOURCES; MAGNETIZED NEUTRON-STARS; PULSAR SAX-J2103.5+4545; LUMINOSITY DEPENDENCE; ACCRETING PULSARS; DISCOVERY; TORQUE; ORBIT; EXO-2030+375; SPECTRA AB SAX J2103.5+4545 has been continuously monitored for similar to 900 d by the Rossi X-ray Timing Explorer (RXTE) since its outburst in 2002 July. Using these observations and previous archival RXTE observations of SAX J2103.5+4545, we refined the binary orbital parameters and find the new orbital period as P = (12.665 36 +/- 0.000 88) d and the eccentricity as 0.4055 +/- 0.0032. With these new orbital parameters, we constructed the pulse frequency and pulse frequency derivative histories of the pulsar and confirmed the correlation between X-ray flux and pulse frequency derivative presented by Baykal, Stark & Swank. We constructed the power spectra for the fluctuations of pulse frequency derivatives and found that the power-law index of the noise spectra is 2.13 +/- 0.6. The power-law index is consistent with random walk in pulse frequency derivative and is the steepest among the HMXRBs. X-ray spectra analysis confirmed the inverse correlation trend between power-law index and X-ray flux found by Baykal et al. C1 Middle E Tech Univ, Dept Phys, TR-06531 Ankara, Turkey. Baskent Univ, Dept Elect & Elect Engn, TR-06530 Ankara, Turkey. Lafayette Coll, Easton, PA 18042 USA. Univ Calif Riverside, Dept Phys, Riverside, CA 92521 USA. Univ Arizona, Dept Phys, Tucson, AZ 85721 USA. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Baykal, A (reprint author), Middle E Tech Univ, Dept Phys, TR-06531 Ankara, Turkey. EM altan@astroa.physics.metu.edu.tr; inam@baskent.edu.tr; starkm@lafayette.edu; carolyn.heffner@email.ucr.edu; aerkoca@physics.arizona.edu; swank@milkyway.gsfc.nasa.gov RI Swank, Jean/F-2693-2012 NR 44 TC 18 Z9 18 U1 0 U2 2 PU OXFORD UNIV PRESS PI OXFORD PA GREAT CLARENDON ST, OXFORD OX2 6DP, ENGLAND SN 0035-8711 EI 1365-2966 J9 MON NOT R ASTRON SOC JI Mon. Not. Roy. Astron. Soc. PD JAN 21 PY 2007 VL 374 IS 3 BP 1108 EP 1114 DI 10.1111/j.1365-2966.2006.11231.x PG 7 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 124XI UT WOS:000243405300031 ER PT J AU Yoo, B Xiao, F Bozhilov, KN Herman, J Ryan, MA Myung, NV AF Yoo, Bongyoung Xiao, Feng Bozhilov, Krassimir N. Herman, Jennifer Ryan, Margaret A. Myung, Nosang V. TI Electrodeposition of thermoelectric superlattice nanowires SO ADVANCED MATERIALS LA English DT Article ID ANODIC ALUMINA TEMPLATES; HIGH-DENSITY; ARRAYS; FABRICATION; BISMUTH; BI2TE3; TEMPERATURE; GROWTH; MERIT AB Bi2Te3/(Bi0.3Sb0.7)(2)Te-3 superlattice thermoelectric nanowires are synthesized by using a template-directed electrodeposition method. Adjustment of the deposition times and potentials enables precise control over the composition and length of each segment of the nanowires. Characterization of the superlattice nanowires by, amongst others, energy dispersive X-ray analysis (see figure) reveals their periodically varying structure. C1 Univ Calif Riverside, Dept Chem & Environm Engn, Riverside, CA 92521 USA. Univ Calif Riverside, Ctr Nanoscale Sci & Engn, Riverside, CA 92521 USA. Univ Calif Riverside, Ctr Facil Adv Microscopy & Microanal, Riverside, CA 92521 USA. CALTECH, Jet Prop Lab, Electrochem Technol Grp, Pasadena, CA 91109 USA. CALTECH, Jet Prop Lab, Mat & Device Technol Grp, Pasadena, CA 91109 USA. RP Myung, NV (reprint author), Univ Calif Riverside, Dept Chem & Environm Engn, Riverside, CA 92521 USA. EM myung@engr.ucr.edu NR 22 TC 86 Z9 90 U1 0 U2 27 PU WILEY-V C H VERLAG GMBH PI WEINHEIM PA BOSCHSTRASSE 12, D-69469 WEINHEIM, GERMANY SN 0935-9648 J9 ADV MATER JI Adv. Mater. PD JAN 20 PY 2007 VL 19 IS 2 BP 296 EP + DI 10.1002/adma.200600606 PG 5 WC Chemistry, Multidisciplinary; Chemistry, Physical; Nanoscience & Nanotechnology; Materials Science, Multidisciplinary; Physics, Applied; Physics, Condensed Matter SC Chemistry; Science & Technology - Other Topics; Materials Science; Physics GA 131WJ UT WOS:000243901600024 ER PT J AU Winter, LM Mushotzky, RF Reynolds, CS AF Winter, Lisa M. Mushotzky, Richard F. Reynolds, Christopher S. TI Elemental abundances of nearby galaxies through high signal-to-noise ratio XMM-Newton observations of ultraluminous X-ray sources SO ASTROPHYSICAL JOURNAL LA English DT Article DE ISM : abundances; ISM : general; X-rays : ISM ID MASS BLACK-HOLES; INTERSTELLAR-MEDIUM; METALLICITY RELATION; IRREGULAR GALAXIES; ACCRETION DISKS; SPIRAL GALAXIES; CROSS-SECTIONS; ABSORPTION; EMISSION; OXYGEN AB In this paper we examined XMM-Newton EPIC spectra of 14 ultraluminous X-ray sources ( ULXs) in addition to the XMM- Newton RGS spectra of two sources ( Holmberg II X-1 and Holmberg IX X-1). We determined oxygen and iron abundances of the host galaxy's ISMusing K- shell ( O) and L- shell ( Fe) X- ray photoionization edges toward these ULXs. We found that the oxygen abundances closely matched recent solar abundances for all of our sources, implying that ULXs live in similar local environments despite the wide range of galaxy host properties. Also, we compare the X- ray hydrogen column densities ( n(H)) for eight ULXs with column densities obtained from radio H I observations. The X- ray model nH values are in good agreement with the HI n(H) values, implying that the hydrogen absorption toward the ULXs is not local to the source ( with the exception of the source M81 XMM1). In order to obtain the column density and abundance values, we fitted the X- ray spectra of the ULXs with a combined power law and one of several accretion disk models. We tested the abundances obtained from the XSPEC models bbody, diskbb, grad, and diskpn along with a power law, finding that the abundances were independent of the thermal model used. We comment on the physical implications of these different model fits. We also note that very deep observations allow a breaking of the degeneracy noted by Stobbart and coworkers favoring a high-mass solution for the absorbed grad+power-law model. C1 Univ Maryland, Dept Astron, College Pk, MD 20742 USA. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Winter, LM (reprint author), Univ Maryland, Dept Astron, College Pk, MD 20742 USA. EM lwinter@astro.umd.edu; richard@milkyway.gsfc.nasa.gov; chris@astro.umd.edu OI Winter, Lisa/0000-0002-3983-020X NR 40 TC 23 Z9 23 U1 0 U2 4 PU UNIV CHICAGO PRESS PI CHICAGO PA 1427 E 60TH ST, CHICAGO, IL 60637-2954 USA SN 0004-637X J9 ASTROPHYS J JI Astrophys. J. PD JAN 20 PY 2007 VL 655 IS 1 BP 163 EP 178 DI 10.1086/510200 PN 1 PG 16 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 129JN UT WOS:000243725400014 ER PT J AU An, D Terndrup, DM Pinsonneault, MH Paulson, DB Hanson, RB Stauffer, JR AF An, Deokkeun Terndrup, Donald M. Pinsonneault, Marc H. Paulson, Diane B. Hanson, Robert B. Stauffer, John R. TI The distances to open clusters from main-sequence fitting. III. Improved accuracy with empirically calibrated isochrones SO ASTROPHYSICAL JOURNAL LA English DT Review DE Hertzsprung-Russell diagram; open clusters and associations : individual (M67, NGC 2516, Pleiades, Praesepe); stars : abundances; stars : activity; stars : distances; stars : evolution ID LOW-MASS STARS; PROPER-MOTION MEMBERSHIP; STANDARD STELLAR LIBRARY; COLOR-MAGNITUDE DIAGRAM; NEARBY FIELD STARS; SOLAR-TYPE STARS; PLEIADES CLUSTER; NGC 2516; HIPPARCOS-PARALLAXES; CHEMICAL-COMPOSITION AB We continue our series of papers on open cluster distances with a critical assessment of the accuracy of main-sequence fitting using isochrones that employ empirical corrections to the color- temperature relations. We use four nearby open clusters with multicolor photometry and accurate metallicities and present a new metallicity for Praesepe ([Fe/H]=+0.11 +/- 0.03) from high-resolution spectra. The internal precision of distance estimates is about a factor of 5 better than the case without the color calibrations. After taking into account all major systematic errors, we obtain distances accurate to about 2%-3% when there exists a good metallicity estimate. Metallicities accurate to better than 0.1 dex may be obtained from BVI(C)K(s) photometry alone. We also derive a helium abundance for the Pleiades of Y=0.279 +/- 0.015, which is equal within the errors to the Sun's initial helium abundance and that of the Hyades. Our best estimates of distances are ( m - M)(0)=6.33 +/- 0: 04, 8.03 +/- 0.04, and 9.61 +/- 0.03 to Praesepe, NGC 2516, and M67, respectively. Our Pleiades distance at the spectroscopic metallicity, ( m-M)(0)=5.66 +/- 0. 01( internal) +/- 0: 05( systematic), is in excellent agreement with several geometric distance measurements. We have made calibrated isochrones for -0.3 <=[Fe/H]<=+0.2 available online. C1 Ohio State Univ, Dept Astron, Columbus, OH 43210 USA. NASA, Goddard Space Flight Ctr, Planet Syst Branch, Greenbelt, MD 20771 USA. Univ Calif Observ, Lick Observ, Santa Cruz, CA USA. CALTECH, Infrared Proc & Anal Ctr, Pasadena, CA 91125 USA. RP An, D (reprint author), Ohio State Univ, Dept Astron, Columbus, OH 43210 USA. EM deokkeun@astronomy.ohio-state.edu; terndrup@astronomy.ohio-state.edu; pinsono@astronomy.ohio-state.edu; diane.b.paulson@gsfc.nasa.gov; hanson@ucolick.org; stauffer@ipac.caltech.edu NR 158 TC 107 Z9 109 U1 0 U2 2 PU IOP PUBLISHING LTD PI BRISTOL PA TEMPLE CIRCUS, TEMPLE WAY, BRISTOL BS1 6BE, ENGLAND SN 0004-637X J9 ASTROPHYS J JI Astrophys. J. PD JAN 20 PY 2007 VL 655 IS 1 BP 233 EP 260 DI 10.1086/509653 PN 1 PG 28 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 129JN UT WOS:000243725400017 ER PT J AU Blagrave, KPM Martin, PG Rubin, RH Dufour, RJ Baldwin, JA Hester, JJ Walter, DK AF Blagrave, K. P. M. Martin, P. G. Rubin, R. H. Dufour, R. J. Baldwin, J. A. Hester, J. J. Walter, D. K. TI Deviations from HeI case B recombination theory and extinction corrections in the Orion Nebula SO ASTROPHYSICAL JOURNAL LA English DT Article DE dust, extinction; HII regions; ISM : abundances; ISM : individual (Orion Nebula) ID FAINT EMISSION-LINES; CHEMICAL-COMPOSITION; PHYSICAL CONDITIONS; ECHELLE SPECTROPHOTOMETRY; TEMPERATURE-VARIATIONS; GASEOUS NEBULAE; DUST; MODEL; SPECTROSCOPY; DIAGNOSTICS AB We are engaged in a comprehensive program to find reliable elemental abundances in and probe the physical structure of the Orion Nebula, the brightest and best-resolved H II region. In the course of developing a robust extinction correction covering our optical and UV FOS and STIS observations, we examined the decrement within various series of He I lines. The decrements of the 2(3)S- n(3)P, 2(3)P- n(3)S, and 3(3)S- n(3)P series are not in accord with case B recombination theory. None of these anomalous He I decrements can be explained by extinction, indicating the presence of additional radiative transfer effects in He I lines ranging from the near-IR to the near-UV. CLOUDY photoionization equilibrium models including radiative transfer are developed to predict the observed He I decrements, and the quantitative agreement is quite remarkable. Following from these results, select He I lines are combined with H I and [ O II] lines and stellar extinction data to validate a new normalizable analytic expression for the wavelength dependence of the extinction. In so doing, the He+/ H+ abundance is also derived. C1 Univ Toronto, Canadian Inst Theoret Astrophys, Toronto, ON M4X 1K9, Canada. NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. Rice Univ, Houston, TX 77251 USA. Michigan State Univ, E Lansing, MI 48824 USA. Arizona State Univ, Tempe, AZ 85287 USA. S Carolina State Univ, Orangeburg, SC USA. RP Blagrave, KPM (reprint author), Univ Toronto, Canadian Inst Theoret Astrophys, 100 Coll St, Toronto, ON M4X 1K9, Canada. NR 44 TC 24 Z9 24 U1 0 U2 2 PU UNIV CHICAGO PRESS PI CHICAGO PA 1427 E 60TH ST, CHICAGO, IL 60637-2954 USA SN 0004-637X J9 ASTROPHYS J JI Astrophys. J. PD JAN 20 PY 2007 VL 655 IS 1 BP 299 EP 315 DI 10.1086/510151 PN 1 PG 17 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 129JN UT WOS:000243725400022 ER PT J AU Li, D Velusamy, T Goldsmith, PF Langer, WD AF Li, D. Velusamy, T. Goldsmith, P. F. Langer, William D. TI Massive quiescent cores in Orion. II. Core mass function SO ASTROPHYSICAL JOURNAL LA English DT Article DE ISM : clouds; methods : data analysis; stars : formation; stars : individual (Orion); submillimeter ID STAR-FORMING REGIONS; MOLECULAR CLOUD; INTERSTELLAR GRAINS; INITIAL CONDITIONS; STELLAR CLUSTERS; DUST; EMISSION; TURBULENCE; COLLAPSE; GAS AB We have surveyed submillimeter continuum emission from relatively quiescent regions in the Orion molecular cloud to determine how the core mass function in a high-mass star-forming region compares to the stellar initial mass function. Such studies are important for understanding the evolution of cores to stars, and for comparison to formation processes in high-and low-mass star-forming regions. We used the SHARC II camera on the Caltech Submillimeter Observatory telescope to obtain 350 mu m data having angular resolution of about 900, which corresponds to 0.02 pc at the distance of Orion. Further data processing using a deconvolution routine enhances the resolution to about 3". Such high angular resolution allows a rare look into individually resolved dense structures in a massive star-forming region. Our analysis combining dust continuum and spectral line data defines a sample of 51 Orion molecular cores with masses ranging from 0.1 to 46 M-circle dot and a meanmass of 9.8 M-circle dot, which is 1 order of magnitude higher than the value found in typical low-mass star-forming regions, such as Taurus. The majority of these cores cannot be supported by thermal pressure or turbulence, and are probably supercritical. They are thus likely precursors of protostars. The core mass function for the Orion quiescent cores can be fitted by a power law with an index equal to -0:85 +/- 0:21. This is significantly flatter than the Salpeter initial mass function and is also flatter than the core mass function found in low and intermediate star-forming regions. When compared with other massive star-forming regions such as NGC 7538, this slope is flatter than the index derived for samples of cores with masses up to thousands of M-circle dot. Closer inspection, however, indicates slopes in those regions similar to our result if only cores in a similar mass range are considered. Based on the comparison between the mass function of the Orion quiescent cores and those of cores in other regions, we find that the core mass function is flatter in an environment affected by ongoing high-mass star formation. Thus, it is likely that environmental processes play a role in shaping the stellar IMF later in the evolution of dense cores and the formation of stars in such regions. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. RP Li, D (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. EM dili@jpl.nasa.gov RI Goldsmith, Paul/H-3159-2016 NR 58 TC 25 Z9 26 U1 0 U2 2 PU UNIV CHICAGO PRESS PI CHICAGO PA 1427 E 60TH ST, CHICAGO, IL 60637-2954 USA SN 0004-637X J9 ASTROPHYS J JI Astrophys. J. PD JAN 20 PY 2007 VL 655 IS 1 BP 351 EP 363 DI 10.1086/509736 PN 1 PG 13 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 129JN UT WOS:000243725400027 ER PT J AU Brooke, TY Huard, TL Bourke, TL Boogert, ACA Allen, LE Blake, GA Evans, NJ Harvey, PM Koerner, DW Mundy, LG Myers, PC Padgett, DL Sargent, AI Stapelfeldt, KR van Dishoeck, EF Chapman, N Cieza, L Dunham, MM Lai, SP Porras, A Spiesman, W Teuben, PJ Young, CH Wahhaj, Z Lee, CW AF Brooke, Timothy Y. Huard, Tracy L. Bourke, Tyler L. Boogert, A. C. Adwin Allen, Lori E. Blake, Geoffrey A. Evans, Neal J., II Harvey, Paul M. Koerner, David W. Mundy, Lee G. Myers, Philip C. Padgett, Deborah L. Sargent, Anneila I. Stapelfeldt, Karl R. van Dishoeck, Ewine F. Chapman, Nicholas Cieza, Lucas Dunham, Michael M. Lai, Shih-Ping Porras, Alicia Spiesman, William Teuben, Peter J. Young, Chadwick H. Wahhaj, Zahed Lee, Chang Won TI The Spitzer c2d survey of nearby dense cores. IV. Revealing the embedded cluster in B59 SO ASTROPHYSICAL JOURNAL LA English DT Article DE infrared : ISM; infrared : stars; ISM : clouds; stars : pre-main sequence ID MAIN-SEQUENCE STARS; YOUNG STELLAR POPULATION; AURIGA MOLECULAR CLOUD; SPACE-TELESCOPE; DARK CLOUD; INTERSTELLAR EXTINCTION; SOURCE COUNTS; PIPE NEBULA; EVOLUTION; OPHIUCHI AB Infrared images of the dark cloud core B59 were obtained with the Spitzer Space Telescope as part of the "Cores to Disks'' Legacy Science project. Photometry from 3.6Y70 mu m indicates at least 20 candidate low-mass young stars near the core, more than doubling the previously known population. Out of this group, 13 are located within similar to 0.1 pc in projection of the molecular gas peak, where a new embedded source is detected. Spectral energy distributions span the range from small excesses above photospheric levels to rising in the mid-infrared. One other embedded object, probably associated with the millimeter source B59-MMS1, with a bolometric luminosity L-bol similar to 2L(circle dot), has extended structure at 3.6 and 4.5 mu m, possibly tracing the edges of an outflow cavity. The measured extinction through the central part of the core is A(V) greater than or similar to 45 mag. The B59 core is producing young stars with a high efficiency. C1 CALTECH, Dept Astron, Pasadena, CA 91125 USA. Smithsonian Astrophys Observ, Cambridge, MA USA. NOAO Gemini Sci Ctr, La Serena, Chile. CALTECH, Dept Geol & Planetary Sci, Pasadena, CA 91125 USA. Univ Texas, Dept Astron, Austin, TX 78712 USA. No Arizona Univ, Dept Phys & Astron, Flagstaff, AZ 86011 USA. Univ Maryland, Dept Astron, College Pk, MD 20742 USA. CALTECH, Spitzer Sci Ctr, Pasadena, CA 91125 USA. CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. Leiden Univ, Leiden, Netherlands. Natl Tsing Hua Univ, Inst Astron, Hsinchu, Taiwan. Natl Tsing Hua Univ, Dept Phys, Hsinchu, Taiwan. Acad Sinica, Inst Astron & Astrophys, Taipei 115, Taiwan. Nicholls State Univ, Dept Phys Sci, Thibodaux, LA 70310 USA. Korea Astron & Space Sci Inst, Taejon, South Korea. RP Brooke, TY (reprint author), CALTECH, Dept Astron, Pasadena, CA 91125 USA. EM tyb@astro.caltech.edu RI Stapelfeldt, Karl/D-2721-2012 NR 66 TC 43 Z9 43 U1 0 U2 2 PU UNIV CHICAGO PRESS PI CHICAGO PA 1427 E 60TH ST, CHICAGO, IL 60637-2954 USA SN 0004-637X J9 ASTROPHYS J JI Astrophys. J. PD JAN 20 PY 2007 VL 655 IS 1 BP 364 EP 374 DI 10.1086/510115 PN 1 PG 11 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 129JN UT WOS:000243725400028 ER PT J AU Horan, D Atkins, RW Badran, HM Blaylock, G Bradbury, SM Buckley, JH Byrum, KL Celik, O Chow, YCK Cogan, P Cui, W Daniel, MK Perez, ID Dowdall, C Falcone, AD Fegan, DJ Fegan, SJ Finley, JP Fortin, P Fortson, LF Gillanders, GH Grube, J Gutierrez, KJ Hall, J Hanna, D Holder, J Hughes, SB Humensky, TB Kenny, GE Kertzman, M Kieda, DB Kildea, J Krawczynski, H Krennrich, F Lang, MJ LeBohec, S Maier, G Moriarty, P Nagal, T Ong, RA Perkins, JS Petry, D Quinn, J Quinn, M Ragan, K Reynolds, PT Rose, HJ Schroedter, M Sembroski, GH Steele, D Swordy, SP Toner, JA Valcarcel, L Vassiliev, VV Wagner, RG Wakely, SP Weekes, TC White, RJ Williams, DA AF Horan, D. Atkins, R. W. Badran, H. M. Blaylock, G. Bradbury, S. M. Buckley, J. H. Byrum, K. L. Celik, O. Chow, Y. C. K. Cogan, P. Cui, W. Daniel, M. K. Perez, I. de la Calle Dowdall, C. Falcone, A. D. Fegan, D. J. Fegan, S. J. Finley, J. P. Fortin, P. Fortson, L. F. Gillanders, G. H. Grube, J. Gutierrez, K. J. Hall, J. Hanna, D. Holder, J. Hughes, S. B. Humensky, T. B. Kenny, G. E. Kertzman, M. Kieda, D. B. Kildea, J. Krawczynski, H. Krennrich, F. Lang, M. J. LeBohec, S. Maier, G. Moriarty, P. Nagal, T. Ong, R. A. Perkins, J. S. Petry, D. Quinn, J. Quinn, M. Ragan, K. Reynolds, P. T. Rose, H. J. Schroedter, M. Sembroski, G. H. Steele, D. Swordy, S. P. Toner, J. A. Valcarcel, L. Vassiliev, V. V. Wagner, R. G. Wakely, S. P. Weekes, T. C. White, R. J. Williams, D. A. TI Very high energy observations of gamma-ray burst locations with the whipple telescope SO ASTROPHYSICAL JOURNAL LA English DT Review DE gamma rays : bursts; gamma rays : observations ID COMPTON EMISSION; REFRESHED SHOCKS; EXTERNAL MATTER; LIGHT-CURVE; AFTERGLOWS; TEV; MODELS; FLARES; DISCOVERY; SEARCH AB Gamma-ray burst (GRB) observations at very high energies (VHE; E > 100 GeV) can impose tight constraints on some GRB emission models. Many GRB afterglow models predict a VHE component similar to that seen in blazars and plerions, in which the GRB spectral energy distribution has a double-peaked shape extending into the VHE regime. VHE emission coincident with delayed X-ray flare emission has also been predicted. GRB follow-up observations have had high priority in the observing program at the Whipple 10 m gamma-ray telescope, and GRBs will continue to be high-priority targets as the next-generation observatory, VERITAS, comes online. Upper limits on the VHE emission at late times (> similar to 4 hr) from seven GRBs observed with the Whipple Telescope are reported here. C1 Harvard Smithsonian Ctr Astrophys, Fred Lawrence Whipple Observ, Amado, AZ USA. Univ Utah, Dept Phys, Salt Lake City, UT USA. Tanta Univ, Dept Phys, Tanta, Egypt. Univ Massachusetts, Dept Phys, Amherst, MA 01003 USA. Univ Leeds, Sch Phys & Astron, Leeds, W Yorkshire, England. Washington Univ, Dept Phys, St Louis, MO 63130 USA. Argonne Natl Lab, Argonne, IL 60439 USA. Univ Calif Los Angeles, Dept Phys & Astron, Los Angeles, CA USA. Univ Coll Dublin, Sch Phys, Dublin 2, Ireland. Purdue Univ, Dept Phys, W Lafayette, IN 47907 USA. Univ Oxford, Dept Phys, Oxford, England. Penn State Univ, Dept Astron & Astrophys, University Pk, PA 16802 USA. Columbia Univ Barnard Coll, Dept Phys & Astron, New York, NY 10027 USA. Adler Planetarium & Astron Museum, Dept Astron, Chicago, IL USA. Natl Univ Ireland Univ Coll Galway, Dept Phys, Galway, Ireland. McGill Univ, Dept Phys, Montreal, PQ H3A 2T5, Canada. Univ Chicago, Enrico Fermi Inst, Chicago, IL 60637 USA. Depauw Univ, Dept Phys & Astron, Greencastle, IN 46135 USA. Iowa State Univ, Dept Phys & Astron, Ames, IA USA. Galway Mayo Inst Technol, Dept Phys & Life Sci, Galway, Ireland. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Cork Inst Technol, Dept Appl Phys & Instrumentat, Cork, Ireland. Univ Calif Santa Cruz, Santa Cruz Inst Particle Phys, Santa Cruz, CA 95064 USA. Univ Calif Santa Cruz, Dept Phys, Santa Cruz, CA 95064 USA. RP Horan, D (reprint author), Argonne Natl Lab, 9700 S Cass Ave, Argonne, IL 60439 USA. RI Hall, Jeter/E-9294-2015; Daniel, Michael/A-2903-2010; OI Daniel, Michael/0000-0002-8053-7910; Cui, Wei/0000-0002-6324-5772; Lang, Mark/0000-0003-4641-4201 NR 110 TC 18 Z9 18 U1 0 U2 4 PU UNIV CHICAGO PRESS PI CHICAGO PA 1427 E 60TH ST, CHICAGO, IL 60637-2954 USA SN 0004-637X J9 ASTROPHYS J JI Astrophys. J. PD JAN 20 PY 2007 VL 655 IS 1 BP 396 EP 405 DI 10.1086/509567 PN 1 PG 10 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 129JN UT WOS:000243725400031 ER PT J AU Shaposhnikov, N Swank, J Shrader, CR Rupen, M Beckmann, V Markwardt, CB Smith, DA AF Shaposhnikov, N. Swank, J. Shrader, C. R. Rupen, M. Beckmann, V. Markwardt, C. B. Smith, D. A. TI GRO J1655-40: Early stages of the 2005 outburst SO ASTROPHYSICAL JOURNAL LA English DT Article DE accretion; accretion disks; black hole physics; gamma rays : observations; stars : individual ( GRO J1655-40) ID X-RAY BINARIES; KERR BLACK-HOLE; ACCRETION DISK; LIGHT CURVES; STATE TRANSITIONS; LOW/HARD STATE; ENERGY-SPECTRA; JETS; COMPTONIZATION; EJECTIONS AB The black hole X-ray binary transient GRO J1655-40 underwent an outburst beginning in early 2005. We present the results of our multiwavelength observational campaign to study the early outburst spectral and temporal evolution, which combines data from X-ray (RXTE and INTEGRAL), radio (VLA), and optical (ROTSE and SMARTS) instruments. During the reported period, the source left quiescence and went through four major accreting black hole states: low-hard, hard intermediate, soft intermediate, and high-soft. We investigated dipping behavior in the RXTE band and compare our results to the 1996-1997 case, when the source was predominantly in the high-soft state, finding significant differences. We consider the evolution of the low-frequency quasi-periodic oscillations and find that the frequency strongly correlates with the spectral characteristics, before shutting off prior to the transition to the high-soft state. We model the broadband high-energy spectrum in the context of empirical models, as well as more physically motivated thermal and bulk motion Comptonization and Compton reflection models. RXTE and INTEGRAL data together support a statistically significant high-energy cutoff in the energy spectrum at approximate to 100-200 keV during the low-hard state. The RXTE data alone also show it very significantly during the transition, but not in the high-soft state spectra. We consider radio, optical, and X-ray connections in the context of possible synchrotron and synchrotron self-Compton origins of X-ray emission in low-hard and intermediate states. In this outburst of GRO J1655-40, the radio flux does not rise strongly with the X-ray flux. C1 NASA, Goddard Space Flight Ctr, Astrophys Sci Div, Greenbelt, MD USA. Univ Space Res Assoc, Ctr Res & Explorat Space Sci & Technol, Columbia, MD USA. Natl Opt Astron Observ, Tucson, AZ 85726 USA. Univ Maryland Baltimore Cty, Dept Phys, Joint Ctr Astrophys, Baltimore, MD 21228 USA. Univ Maryland, Dept Astron, College Pk, MD 20742 USA. Guilford Coll, Dept Phys, Greensboro, NC 27410 USA. RP Shaposhnikov, N (reprint author), NASA, Goddard Space Flight Ctr, Astrophys Sci Div, Greenbelt, MD USA. EM nikolai@milkyway.gsfc.nasa.gov RI Swank, Jean/F-2693-2012 NR 64 TC 37 Z9 37 U1 0 U2 1 PU UNIV CHICAGO PRESS PI CHICAGO PA 1427 E 60TH ST, CHICAGO, IL 60637-2954 USA SN 0004-637X J9 ASTROPHYS J JI Astrophys. J. PD JAN 20 PY 2007 VL 655 IS 1 BP 434 EP 446 DI 10.1086/509755 PN 1 PG 13 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 129JN UT WOS:000243725400034 ER PT J AU Corbet, RHD Markwardt, CB Tueller, J AF Corbet, R. H. D. Markwardt, C. B. Tueller, J. TI Swift bat and RXTE observations of the peculiar X-ray binary 4U 2206+54: Disappearance of the 9.6 day modulation SO ASTROPHYSICAL JOURNAL LA English DT Article DE stars : individual ( 4U 2206+54); stars : neutron; X rays : stars ID TIMING EXPLORER; NEUTRON-STAR; GRO J2058+42; 4U 2206+54; DISCOVERY; PULSAR; ACCRETION; PULSATIONS; ORBIT; MULTIWAVELENGTH AB Observations of the high-mass X-ray binary 4U 2206+54 with the Swift Burst Alert Telescope (BAT) do not show modulation at the previously reported period of 9.6 days found from observations made with the Rossi X-Ray Timing Explorer (RXTE) All-Sky Monitor (ASM). Instead, the strongest peak in the power spectrum of the BAT light curve occurs at a period of 19: 25 +/- 0: 08 days, twice the period found with the RXTE ASM. The maximum of the folded BAT light curve is also delayed compared to the maximum of the folded ASM light curve. The most recent ASM data folded on twice the 9.6 day period show similar morphology to the folded BAT light curve. This suggests that the apparent period doubling is a recent secular change rather than an energy-dependent effect. The 9.6 day period is thus not a permanent strong feature of the light curve. We suggest that the orbital period of 4U 2206+54 may be twice the previously proposed value. C1 Univ Space Res Assoc, NASA, Goddard Space Flight Ctr, XRay Astrophys Lab, Greenbelt, MD USA. Univ Maryland, Dept Astron, College Pk, MD 20742 USA. NASA, Goddard Space Flight Ctr, Astrophys Phys Lab, Greenbelt, MD 20771 USA. RP Corbet, RHD (reprint author), Univ Space Res Assoc, NASA, Goddard Space Flight Ctr, XRay Astrophys Lab, Greenbelt, MD USA. EM corbet@milkyway.gsfc.nasa.gov RI Tueller, Jack/D-5334-2012 NR 42 TC 24 Z9 24 U1 0 U2 1 PU IOP PUBLISHING LTD PI BRISTOL PA TEMPLE CIRCUS, TEMPLE WAY, BRISTOL BS1 6BE, ENGLAND SN 0004-637X EI 1538-4357 J9 ASTROPHYS J JI Astrophys. J. PD JAN 20 PY 2007 VL 655 IS 1 BP 458 EP 465 DI 10.1086/509319 PN 1 PG 8 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 129JN UT WOS:000243725400036 ER PT J AU Marley, MS Fortney, JJ Hubickyj, O Bodenheimer, P Lissauer, JJ AF Marley, Mark S. Fortney, Jonathan J. Hubickyj, Olenka Bodenheimer, Peter Lissauer, Jack J. TI On the luminosity of young jupiters SO ASTROPHYSICAL JOURNAL LA English DT Article DE planetary systems : formation; planets and satellites : formation ID EXTRASOLAR GIANT PLANETS; MASS DWARF STARS; BROWN DWARFS; EARLY EVOLUTION; ATMOSPHERIC CHEMISTRY; THERMAL STRUCTURE; PHASE-SEPARATION; SOLAR-SYSTEM; MODELS; ACCRETION AB Traditional thermal evolution models of giant planets employ arbitrary initial conditions selected more for computational expediency than physical accuracy. Since the initial conditions are eventually forgotten by the evolving planet, this approach is valid for mature planets, if not young ones. To explore the evolution at young ages of jovian mass planets, we have employed model planets created by one implementation of the core-accretion mechanism as initial conditions for evolutionary calculations. The luminosities and early cooling rates of young planets are highly sensitive to their internal entropies, which depend on the formation mechanism and are highly model dependent. As a result of the accretion shock through which most of the planetary mass is processed, we find lower initial internal entropies than commonly assumed in published evolution tracks. Consequently, young Jovian planets are smaller, cooler, and several to 100 times less luminous than predicted by earlier models. Furthermore, the time interval during which the young Jupiters are fainter than expected depends on the mass of planet. Jupiter mass planets (1M(J)) align with the conventional model luminosity in as little at 20 million years, but 10M(J) planets can take up to 1 billion years to match commonly cited luminosities, given our implementation of the core-accretion mechanism. If our assumptions, especially including our treatment of the accretion shock, are correct and if extrasolar Jovian planets indeed form with low entropy, then young Jovian planets are substantially fainter at young ages than currently believed. Furthermore, early evolution tracks should be regarded as uncertain for much longer than the commonly quoted 10(6) yr. These results have important consequences both for detection strategies and for assigning masses to young Jovian planets based on observed luminosities. C1 NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. Univ Calif Santa Cruz, UCO Lick Observ, Santa Cruz, CA 95064 USA. RP Marley, MS (reprint author), NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. EM Mark.S.Marley@NASA.gov; jfortney@mail.arc.nasa.gov RI Marley, Mark/I-4704-2013; OI Fortney, Jonathan/0000-0002-9843-4354 NR 62 TC 203 Z9 203 U1 1 U2 3 PU UNIV CHICAGO PRESS PI CHICAGO PA 1427 E 60TH ST, CHICAGO, IL 60637-2954 USA SN 0004-637X J9 ASTROPHYS J JI Astrophys. J. PD JAN 20 PY 2007 VL 655 IS 1 BP 541 EP 549 DI 10.1086/509759 PN 1 PG 9 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 129JN UT WOS:000243725400043 ER PT J AU Stothers, RB AF Stothers, Richard B. TI A virial theorem investigation of magnetic variations in the sun (vol 653, pg 73, 2006) SO ASTROPHYSICAL JOURNAL LA English DT Correction C1 NASA, Goddard Inst Space Studies, New York, NY 10025 USA. RP Stothers, RB (reprint author), NASA, Goddard Inst Space Studies, New York, NY 10025 USA. NR 1 TC 0 Z9 0 U1 0 U2 2 PU UNIV CHICAGO PRESS PI CHICAGO PA 1427 E 60TH ST, CHICAGO, IL 60637-2954 USA SN 0004-637X J9 ASTROPHYS J JI Astrophys. J. PD JAN 20 PY 2007 VL 655 IS 1 BP L63 EP L63 DI 10.1086/511752 PN 2 PG 1 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 129JO UT WOS:000243725500017 ER PT J AU Woods, PM Willacy, K AF Woods, Paul M. Willacy, Karen TI Benzene formation in the inner regions of protostellar disks SO ASTROPHYSICAL JOURNAL LA English DT Article DE astrochemistry; planetary systems : protoplanetary disks ID POLYCYCLIC AROMATIC-HYDROCARBONS; DENSE INTERSTELLAR CLOUDS; HERBIG AE/BE STARS; PROTOPLANETARY DISKS; CIRCUMSTELLAR DISKS; GAS TEMPERATURE; CHEMISTRY; PAHS; ADSORPTION; ATMOSPHERE AB Benzene (c-C6H6) formation in the inner 3 AU of a protostellar disk can be efficient, resulting in high abundances of benzene in the midplane region. The formation mechanism is different to that found in interstellar clouds and in protoplanetary nebulae, and proceeds mainly through the reaction between allene (C3H4) and its ion. This has implications for PAH formation, in that some fraction of PAHs seen in the solar system could be native rather than inherited from the interstellar medium. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. RP Woods, PM (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. EM paul.m.woods@jpl.nasa.gov RI Woods, Paul/E-6926-2011 OI Woods, Paul/0000-0003-4340-3590 NR 31 TC 22 Z9 22 U1 1 U2 5 PU UNIV CHICAGO PRESS PI CHICAGO PA 1427 E 60TH ST, CHICAGO, IL 60637-2954 USA SN 0004-637X J9 ASTROPHYS J JI Astrophys. J. PD JAN 20 PY 2007 VL 655 IS 1 BP L49 EP L52 DI 10.1086/511680 PN 2 PG 4 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 129JO UT WOS:000243725500013 ER PT J AU Zhang, B Zhang, BB Liang, EW Gehrels, N Burrows, DN Meszaros, P AF Zhang, Bing Zhang, Bin-Bin Liang, En-Wei Gehrels, Neil Burrows, David N. Meszaros, Peter TI Making a short gamma-ray burst from a long one: Implications for the nature of GRB 060614 SO ASTROPHYSICAL JOURNAL LA English DT Article DE gamma rays : bursts ID HOST GALAXY; AFTERGLOW; SUPERNOVA; MODELS; GRB-050709; EMISSION; FLARES; ORIGIN; SPECTROSCOPY; TELESCOPE AB The absence of a supernova accompanying the nearby long GRB 060614 poses a great puzzle about the progenitor of this event and challenges the current GRB classification scheme. This burst displays a short-hard emission episode followed by extended soft emission with strong spectral evolution. Noticing that this burst has an isotropic gamma-ray energy only similar to 8 times that of GRB 050724, a good candidate of merger-type short GRBs, we generate a "pseudo" burst that is similar to 8 times less energetic than GRB 060614 based on the spectral properties of GRB 060614 and the E(p) proportional to E(iso)(1/2) (Amati) relation. We find that this pseudoburst would have been detected by BATSE as a marginal short-duration GRB and would have properties in the Swift BAT and XRT bands similar to GRB 050724. This suggests that GRB 060614 is likely a more intense event in the traditional short-hard GRB category. Events like GRB 060614 that seem to defy the traditional short versus long classification of GRBs may require modification of our classification terminology for GRBs. By analogy with supernova classifications, we suggest that GRBs be classified into Type I ( typically short and associated with old populations) and Type II ( typically long and associated with young populations). We propose that GRB 060614 belongs to Type I and predict that similar events will be detected in elliptical galaxies. C1 Univ Nevada, Dept Phys & Astron, Las Vegas, NV 89154 USA. CAS, Yunnan Observ, Natl Astron Observ, Kunming, Peoples R China. Chinese Acad Sci, Grad Sch, Beijing, Peoples R China. Guangxi Univ, Dept Phys, Nanning 530004, Peoples R China. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Penn State Univ, Dept Astron & Astrophys, University Pk, PA 16802 USA. Penn State Univ, Dept Phys, University Pk, PA 16802 USA. RP Zhang, B (reprint author), Univ Nevada, Dept Phys & Astron, Las Vegas, NV 89154 USA. EM bzhang@physics.unlv.edu RI Gehrels, Neil/D-2971-2012; Zhang, Binbin/C-9035-2013 OI Zhang, Binbin/0000-0003-2002-116X NR 64 TC 124 Z9 129 U1 0 U2 13 PU IOP PUBLISHING LTD PI BRISTOL PA TEMPLE CIRCUS, TEMPLE WAY, BRISTOL BS1 6BE, ENGLAND SN 0004-637X J9 ASTROPHYS J JI Astrophys. J. PD JAN 20 PY 2007 VL 655 IS 1 BP L25 EP L28 DI 10.1086/511781 PN 2 PG 4 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 129JO UT WOS:000243725500007 ER PT J AU Sergeev, V Semenov, V Kubyshkina, M Ivanova, V Baumjohann, W Nakamura, R Penz, T Runov, A Zhang, TL Glassmeier, KH Angelopoulos, V Frey, H Sauvaud, JA Daly, P Cao, JB Singer, H Lucek, E AF Sergeev, V. Semenov, V. Kubyshkina, M. Ivanova, V. Baumjohann, W. Nakamura, R. Penz, T. Runov, A. Zhang, T. L. Glassmeier, K. -H. Angelopoulos, V. Frey, H. Sauvaud, J. -A. Daly, P. Cao, J. B. Singer, H. Lucek, E. TI Observation of repeated intense near-Earth reconnection on closed field lines with Cluster, Double Star, and other spacecraft SO GEOPHYSICAL RESEARCH LETTERS LA English DT Article ID SOLAR-WIND CONTROL; MAGNETIC RECONNECTION; CURRENT DISRUPTION; SUBSTORM; ONSET; MAGNETOTAIL; DYNAMICS; LOCATION; EVENT AB [1] We report strong repeated magnetic reconnection pulses that occurred deep inside closed plasma sheet flux tubes at r <= 14Re. They have been observed with a fortuitous spacecraft constellation during three consecutive turbulent magnetic dipolarizations, accompanied by localized auroral brightenings near the equatorward edge of a wide auroral oval. The reconnection separatrix was mapped to similar to 64 degrees CGLat in the ionosphere, where a very energetic and narrow energy-dispersed ion injection with unusually steep dispersion slope was observed. Reconstruction of the reconnection rate from magnetic waveforms at Cluster provided a reconnection pulse duration (similar to 1 min) and peak strength (E(R) similar to 8 mV/m) consistent with direct observations in the reconnection outflow region. The magnetic activity was rather weak, although the concurrent solar wind flow pressure was above the norm. We suggest that near-Earth reconnection events may be a phenomenon more frequent than generally thought. We also confirm that reconnection and the growth of strong turbulence in the near tail are strongly coupled together in near-Earth reconnection events. C1 St Petersburg State Univ, Inst Phys, St Petersburg 198504, Russia. Austrian Acad Sci, Space Res Inst, A-8042 Graz, Austria. Inst Geophys & Extraterrr Phys, D-38106 Braunschweig, Germany. Univ Calif Berkeley, Space Sci Lab, Berkeley, CA 94720 USA. Jet Prop Lab, Pasadena, CA USA. CNRS, Ctr Etud Spatiale Rayonnements, F-31028 Toulouse, France. Max Planck Inst Sonnensyst Forsch, D-37191 Katlenburg Lindau, Germany. Chinese Acad Sci, Ctr Space Sci & Appl Res, Beijing 100080, Peoples R China. NOAA, Boulder, CO 80303 USA. Univ London Imperial Coll Sci Technol & Med, Blackett Lab, London SW7 2BW, England. RP Sergeev, V (reprint author), St Petersburg State Univ, Inst Phys, St Petersburg 198504, Russia. EM victor@geo.phys.spbu.ru RI Baumjohann, Wolfgang/A-1012-2010; Semenov, Vladimir/A-5530-2013; Kubyshkina, Marina/G-9436-2013; Nakamura, Rumi/I-7712-2013; Sergeev, Victor/H-1173-2013; OI Baumjohann, Wolfgang/0000-0001-6271-0110; Semenov, Vladimir/0000-0001-6592-056X; Kubyshkina, Marina/0000-0001-5897-9547; Nakamura, Rumi/0000-0002-2620-9211; Sergeev, Victor/0000-0002-4569-9631; Frey, Harald/0000-0001-8955-3282 NR 20 TC 26 Z9 26 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 JAN 20 PY 2007 VL 34 IS 2 AR L02103 DI 10.1029/2006GL028452 PG 6 WC Geosciences, Multidisciplinary SC Geology GA 131DR UT WOS:000243848900006 ER PT J AU Hu, RM Martin, RV Fairlie, TD AF Hu, R. -M. Martin, R. V. Fairlie, T. D. TI Global retrieval of columnar aerosol single scattering albedo from space-based observations SO JOURNAL OF GEOPHYSICAL RESEARCH-ATMOSPHERES LA English DT Article ID RESOLUTION IMAGING SPECTRORADIOMETER; SEA-SALT AEROSOLS; OPTICAL-PROPERTIES; BLACK CARBON; TROPOSPHERIC AEROSOLS; SULFATE AEROSOLS; MODEL GOCART; ART.; CLIMATE; ABSORPTION AB We retrieve the global distribution of columnar single scattering albedo (omega(0)) by taking advantage of the high sensitivity of satellite measurements at ultraviolet channels by the Total Ozone Mapping Spectrometer (TOMS) to both aerosol optical depth and omega(0) and the high sensitivity of satellite measurements at visible channels by the Moderate Resolution Imaging Spectroradiometer (MODIS) to aerosol optical depth. A radiative transfer model (LIDORT) is used to calculate the local omega(0) that reproduces the TOMS aerosol index, when constrained by MODIS aerosol optical depth and by relative vertical profiles from a global chemical transport model (GEOS-CHEM). The simulated aerosol profiles are evaluated with lidar measurements of aerosol extinction. The retrieved omega(0) at 360 nm is near 1 over the remote ocean, in contrast with values of 0.75 to 0.9 over regions dominated by biomass burning and mineral dust aerosol. The retrieval uncertainty is 15%. We validate our retrieval with measurements from the Aerosol Robotic Network (AERONET); the correlation coefficient, slope, and intercept are 0.75, 0.99, and 0.02 respectively. C1 Dalhousie Univ, Dept Phys & Astmospher Sci, Halifax, NS, Canada. Harvard Univ, Harvard Smithsonian Ctr Astrophys, Cambridge, MA USA. NASA Langley Res Ctr, Hampton, VA USA. Harvard Univ, Dept Earth & Planetary Sci, Cambridge, MA 02138 USA. Harvard Univ, Dept Engn, Cambridge, MA 02138 USA. RP Hu, RM (reprint author), Dalhousie Univ, Dept Phys & Astmospher Sci, Halifax, NS, Canada. EM hu@fizz.phys.dal.ca RI Martin, Randall/A-2051-2008; Martin, Randall/C-1205-2014; Chem, GEOS/C-5595-2014 OI Martin, Randall/0000-0003-2632-8402; NR 73 TC 14 Z9 15 U1 0 U2 4 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 JAN 20 PY 2007 VL 112 IS D2 AR D02204 DI 10.1029/2005JD006832 PG 9 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA 131DY UT WOS:000243849600001 ER PT J AU Kapale, KT AF Kapale, K. T. TI Polarization preserving quantum nondemolition photodetector SO JOURNAL OF MODERN OPTICS LA English DT Article AB A polarization preserving quantum nondemolition photodetector is proposed based on nonlinearities obtainable through quantum coherence effects. An atomic level scheme is devised such that in the presence of strong linearly polarized drive field a coherent weak probe field acquires a phase proportional to the number of photons in the signal mode immaterial of its polarization state. It is also shown that the unavoidable phase-kicks resulting due to the measurement process are insensitive to the polarization state of the incoming signal photon. It is envisioned that such a device would have tremendous applicability in photonic quantum information proposals where quantum information in the polarization qubit is to be protected. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. Louisiana State Univ, Dept Phys & Astron, Hearne Inst Theoret Phys, Baton Rouge, LA 70803 USA. RP Kapale, KT (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,Mail Stop 126-347, Pasadena, CA 91109 USA. EM Kishor.T.Kapale@jpl.nasa.gov NR 8 TC 2 Z9 2 U1 0 U2 1 PU TAYLOR & FRANCIS LTD PI ABINGDON PA 4 PARK SQUARE, MILTON PARK, ABINGDON OX14 4RN, OXON, ENGLAND SN 0950-0340 J9 J MOD OPTIC JI J. Mod. Opt. PD JAN 20 PY 2007 VL 54 IS 2-3 BP 327 EP 335 DI 10.1080/09500340600753822 PG 9 WC Optics SC Optics GA 138UD UT WOS:000244387900013 ER PT J AU LeGrande, AN Lynch-Stieglitz, J AF LeGrande, Allegra N. Lynch-Stieglitz, Jean TI Surface currents in the western North Atlantic during the Last Glacial Maximum SO GEOCHEMISTRY GEOPHYSICS GEOSYSTEMS LA English DT Article DE Gulf Stream; Last Glacial Maximum; oceanography : physical : western boundary currents; paleoceanography : general or miscellaneous; paleoceanography : glacial ID FLORIDA CURRENT; PLANKTONIC-FORAMINIFERA; TRANSPORT; SEA; CYCLE AB [1] During the last ice age, the density gradient across the Florida Current was reduced, implying a reduction in the flow of the Gulf Stream through the Florida Straits. Here we investigate the possibility that a significant portion of this wind-driven western boundary flow bypassed the Florida Straits during glacial times due to either changes in bathymetry induced by the sea level drop or changes in wind patterns. Down core records of the oxygen isotope ratios of the planktonic foraminifer Globorotalia truncatulinoides are used to locate the density gradients and thus the locations of upper ocean currents in the western North Atlantic. We find that western boundary flow was largely confined within the Florida Straits during the Last Glacial Maximum as it is today. This finding supports the idea that the reduced density gradient across the Florida Current represents a reduction in the surface branch of the surface to deep meridional overturning circulation in the Atlantic rather than a reduction in the proportion of the wind-driven flow carried by the Florida Current. C1 NASA, Goddard Inst Space Studies, New York, NY 10025 USA. Columbia Univ, Ctr Climate Syst Res, New York, NY 10025 USA. Georgia Inst Technol, Sch Earth & Atmospher Sci, Atlanta, GA 30332 USA. RP LeGrande, AN (reprint author), NASA, Goddard Inst Space Studies, 2880 Broadway, New York, NY 10025 USA. EM legrande@giss.nasa.gov RI LeGrande, Allegra/D-8920-2012; OI LeGrande, Allegra/0000-0002-5295-0062; Lynch-Stieglitz, Jean/0000-0002-9353-1972 NR 16 TC 2 Z9 2 U1 3 U2 4 PU AMER GEOPHYSICAL UNION PI WASHINGTON PA 2000 FLORIDA AVE NW, WASHINGTON, DC 20009 USA SN 1525-2027 J9 GEOCHEM GEOPHY GEOSY JI Geochem. Geophys. Geosyst. PD JAN 19 PY 2007 VL 8 AR Q01N09 DI 10.1029/2006GC001371 PG 8 WC Geochemistry & Geophysics SC Geochemistry & Geophysics GA 131DJ UT WOS:000243848100002 ER PT J AU Hopfner, M von Clarmann, T Fischer, H Funke, B Glatthor, N Grabowski, U Kellmann, S Kiefer, M Linden, A Milz, M Steck, T Stiller, GP Bernath, P Blom, CE Blumenstock, T Boone, C Chance, K Coffey, MT Friedl-Vallon, F Griffith, D Hannigan, JW Hase, F Jones, N Jucks, KW Keim, C Kleinert, A Kouker, W Liu, GY Mahieu, E Mellqvist, J Mikuteit, S Notholt, J Oelhaf, H Piesch, C Reddmann, T Ruhnke, R Schneider, M Strandberg, A Toon, G Walker, KA Warneke, T Wetzel, G Wood, S Zander, R AF Hoepfner, M. von Clarmann, T. Fischer, H. Funke, B. Glatthor, N. Grabowski, U. Kellmann, S. Kiefer, M. Linden, A. Milz, M. Steck, T. Stiller, G. P. Bernath, P. Blom, C. E. Blumenstock, Th. Boone, C. Chance, K. Coffey, M. T. Friedl-Vallon, F. Griffith, D. Hannigan, J. W. Hase, F. Jones, N. Jucks, K. W. Keim, C. Kleinert, A. Kouker, W. Liu, G. Y. Mahieu, E. Mellqvist, J. Mikuteit, S. Notholt, J. Oelhaf, H. Piesch, C. Reddmann, T. Ruhnke, R. Schneider, M. Strandberg, A. Toon, G. Walker, K. A. Warneke, T. Wetzel, G. Wood, S. Zander, R. TI Validation of MIPAS ClONO2 measurements SO ATMOSPHERIC CHEMISTRY AND PHYSICS LA English DT Article ID LIMB EMISSION-SPECTRA; SOLAR OCCULTATION SPECTRA; CHLORINE NITRATE CLONO2; STRATOSPHERIC CHLORINE; MICHELSON INTERFEROMETER; REACTIVE NITROGEN; ANTARCTIC VORTEX; HIGH-RESOLUTION; APRIL 1993; Q-BRANCH AB Altitude profiles of ClONO2 retrieved with the IMK (Institut fur Meteorologie und Klimaforschung) science-oriented data processor from MIPAS/Envisat (Michelson Interferometer for Passive Atmospheric Sounding on Envisat) mid-infrared limb emission measurements between July 2002 and March 2004 have been validated by comparison with balloon-borne (Mark IV, FIRS2, MIPAS-B), airborne (MIPAS-STR), ground-based (Spitsbergen, Thule, Kiruna, Harestua, Jungfraujoch, Izana, Wollongong, Lauder), and spaceborne (ACE-FTS) observations. With few exceptions we found very good agreement between these instruments and MIPAS with no evidence for any bias in most cases and altitude regions. For balloon-borne measurements typical absolute mean differences are below 0.05 ppbv over the whole altitude range from 10 to 39 km. In case of ACE-FTS observations mean differences are below 0.03 ppbv for observations below 26 km. Above this altitude the comparison with ACE-FTS is affected by the photochemically induced diurnal variation of ClONO2. Correction for this by use of a chemical transport model led to an overcompensation of the photochemical effect by up to 0.1 ppbv at altitudes of 30-35 km in case of MIPAS-ACE-FTS comparisons while for the balloon-borne observations no such inconsistency has been detected. The comparison of MIPAS derived total column amounts with ground-based observations revealed no significant bias in the MIPAS data. Mean differences between MIPAS and FTIR column abundances are 0.11 +/- 0.12 x 10(14) cm(-2) (1.0 +/- 1.1%) and -0.09 +/- 0.19 x 10(14) cm(-2) (-0.8 +/- 1.7%), depending on the coincidence criterion applied. chi(2) tests have been performed to assess the combined precision estimates of MIPAS and the related instruments. When no exact coincidences were available as in case of MIPAS-FTIR or MIPAS-ACE-FTS comparisons it has been necessary to take into consideration a coincidence error term to account for chi(2) deviations. From the resulting chi(2) profiles there is no evidence for a systematic over/underestimation of the MIPAS random error analysis. C1 Forschungszentrum Karlsruhe, Inst Meteorol & Klimaforsch, Karlsruhe, Germany. Inst Astrofis Andalucia, E-18080 Granada, Spain. Univ Waterloo, Dept Chem, Waterloo, ON N2L 3G1, Canada. Harvard Smithsonian Ctr Astrophys, Atom & Mol Phys Div, Cambridge, MA 02138 USA. Natl Ctr Atmospher Res, Div Atmospher Chem, Boulder, CO 80307 USA. Univ Wollongong, Dept Chem, Wollongong, NSW, Australia. Harvard Smithsonian Ctr Astrophys, Opt & Infrared Astron Div, Cambridge, MA 02138 USA. Univ Liege, Inst Astrophys & Geophys, B-4000 Liege, Belgium. Chalmers, Dept Radio & Space Sci, S-41296 Gothenburg, Sweden. Univ Bremen, Inst Umweltphys, D-2800 Bremen 33, Germany. CALTECH, Jet Prop Lab, Pasadena, CA USA. Natl Inst Water & Atmospher Res, Lauder, New Zealand. RP Hopfner, M (reprint author), Forschungszentrum Karlsruhe, Inst Meteorol & Klimaforsch, Karlsruhe, Germany. EM michael.hoepfner@imk.fzk.de RI Milz, Mathias/C-9899-2011; Bernath, Peter/B-6567-2012; Ruhnke, Roland/J-8800-2012; Blumenstock, Thomas/K-2263-2012; Kleinert, Anne/A-7048-2013; Wetzel, Gerald/A-7065-2013; Hopfner, Michael/A-7255-2013; Stiller, Gabriele/A-7340-2013; Hase, Frank/A-7497-2013; Felix Friedl-Vallon, Felix/A-7741-2013; Oelhaf, Hermann/A-7895-2013; von Clarmann, Thomas/A-7287-2013; Reddmann, Thomas/A-7681-2013; Glatthor, Norbert/B-2141-2013; Kiefer, Michael/A-7254-2013; Schneider, Matthias/B-1441-2013; Funke, Bernd/C-2162-2008; Barthlott, Sabine/B-1439-2013; Jones, Nicholas/G-5575-2011; Notholt, Justus/P-4520-2016; OI Bernath, Peter/0000-0002-1255-396X; Hopfner, Michael/0000-0002-4174-9531; Stiller, Gabriele/0000-0003-2883-6873; von Clarmann, Thomas/0000-0003-2219-3379; Reddmann, Thomas/0000-0003-1733-7016; Funke, Bernd/0000-0003-0462-4702; Barthlott, Sabine/0000-0003-0258-9421; Jones, Nicholas/0000-0002-0111-2368; Notholt, Justus/0000-0002-3324-885X; Chance, Kelly/0000-0002-7339-7577; Mahieu, Emmanuel/0000-0002-5251-0286 NR 54 TC 32 Z9 33 U1 1 U2 4 PU COPERNICUS GESELLSCHAFT MBH PI GOTTINGEN PA BAHNHOFSALLEE 1E, GOTTINGEN, 37081, GERMANY SN 1680-7316 EI 1680-7324 J9 ATMOS CHEM PHYS JI Atmos. Chem. Phys. PD JAN 18 PY 2007 VL 7 BP 257 EP 281 DI 10.5194/acp-7-257-2007 PG 25 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA 129RN UT WOS:000243747400002 ER PT J AU Novakov, T Menon, S Kirchstetter, TW Koch, D Hansen, JE AF Novakov, T. Menon, S. Kirchstetter, T. W. Koch, D. Hansen, J. E. TI Reply to comment by R. L. Tanner and D. J. Eatough on "Aerosol organic carbon to black carbon ratios: Analysis of published data and implication for climate forcing'' SO JOURNAL OF GEOPHYSICAL RESEARCH-ATMOSPHERES LA English DT Editorial Material C1 Lawrence Berkeley Natl Lab, Environm Energy Technol Div, Berkeley, CA 94720 USA. NASA, Goddard Inst Space Studies, New York, NY 10025 USA. Columbia Univ, Earth Inst, New York, NY 10025 USA. Columbia Univ, Ctr Climate Syst Res, New York, NY 10025 USA. RP Novakov, T (reprint author), Lawrence Berkeley Natl Lab, Environm Energy Technol Div, Berkeley, CA 94720 USA. NR 2 TC 0 Z9 0 U1 0 U2 2 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 JAN 18 PY 2007 VL 112 IS D2 AR D02203 DI 10.1029/2006JD007941 PG 1 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA 131DW UT WOS:000243849400005 ER PT J AU Massey, R Rhodes, J Ellis, R Scoville, N Leauthaud, A Finoguenov, A Capak, P Bacon, D Aussel, H Kneib, JP Koekemoer, A McCracken, H Mobasher, B Pires, S Refregier, A Sasaki, S Starck, JL Taniguchi, Y Taylor, A Taylor, J AF Massey, Richard Rhodes, Jason Ellis, Richard Scoville, Nick Leauthaud, Alexie Finoguenov, Alexis Capak, Peter Bacon, David Aussel, Herve Kneib, Jean-Paul Koekemoer, Anton McCracken, Henry Mobasher, Bahram Pires, Sandrine Refregier, Alexandre Sasaki, Shunji Starck, Jean-Luc Taniguchi, Yoshi Taylor, Andy Taylor, James TI Dark matter maps reveal cosmic scaffolding SO NATURE LA English DT Article ID LARGE-SCALE STRUCTURE; WEAK; GALAXIES; EVOLUTION; IMAGES; SPACE; SHEAR AB Ordinary baryonic particles ( such as protons and neutrons) account for only one-sixth of the total matter in the Universe(1-3). The remainder is a mysterious 'dark matter' component, which does not interact via electromagnetism and thus neither emits nor reflects light. As dark matter cannot be seen directly using traditional observations, very little is currently known about its properties. It does interact via gravity, and is most effectively probed through gravitational lensing: the deflection of light from distant galaxies by the gravitational attraction of foreground mass concentrations(4,5). This is a purely geometrical effect that is free of astrophysical assumptions and sensitive to all matter - whether baryonic or dark(6,7). Here we show high-fidelity maps of the large-scale distribution of dark matter, resolved in both angle and depth. We find a loose network of filaments, growing over time, which intersect in massive structures at the locations of clusters of galaxies. Our results are consistent with predictions of gravitationally induced structure formation(8,9), in which the initial, smooth distribution of dark matter collapses into filaments then into clusters, forming a gravitational scaffold into which gas can accumulate, and stars can be built(10). C1 CALTECH, Pasadena, CA 91125 USA. CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. Lab Astrophys Marseille, F-13376 Marseille, France. Max Planck Inst Extraterr Phys, D-85748 Garching, Germany. Inst Astron, Edinburgh EH9 3HJ, Midlothian, Scotland. CNRS, CEA, Unite Mixte Rech, AIM, F-91191 Gif Sur Yvette, France. Univ Paris 07, CE Saclay, UMR 7158, F-91191 Gif Sur Yvette, France. Space Telescope Sci Inst, Baltimore, MD 21218 USA. Univ Paris 06, Inst Astrophys Paris, F-75014 Paris, France. Ctr Etud Saclay, CEA, DSM, DAPNIA,SEDI, F-91191 Gif Sur Yvette, France. Ehime Univ, Dept Phys, Matsuyama, Ehime 7908577, Japan. Univ Waterloo, Dept Phys & Astron, Waterloo, ON N2L 3G1, Canada. RP Massey, R (reprint author), CALTECH, MC105-24,1200 E Calif Blvd, Pasadena, CA 91125 USA. EM rjm@astro.caltech.edu RI Starck, Jean-Luc/D-9467-2011; Kneib, Jean-Paul/A-7919-2015; OI Starck, Jean-Luc/0000-0003-2177-7794; Kneib, Jean-Paul/0000-0002-4616-4989; Taylor, James/0000-0002-6639-4183; Koekemoer, Anton/0000-0002-6610-2048 NR 30 TC 198 Z9 203 U1 1 U2 16 PU NATURE PUBLISHING GROUP PI LONDON PA MACMILLAN BUILDING, 4 CRINAN ST, LONDON N1 9XW, ENGLAND SN 0028-0836 J9 NATURE JI Nature PD JAN 18 PY 2007 VL 445 IS 7125 BP 286 EP 290 DI 10.1038/nature05497 PG 5 WC Multidisciplinary Sciences SC Science & Technology - Other Topics GA 126HT UT WOS:000243504700038 PM 17206154 ER PT J AU von Savigny, C Sinnhuber, M Bovensmann, H Burrows, JP Kallenrode, MB Schwartz, M AF von Savigny, C. Sinnhuber, M. Bovensmann, H. Burrows, J. P. Kallenrode, M. -B. Schwartz, M. TI On the disappearance of noctilucent clouds during the January 2005 solar proton events SO GEOPHYSICAL RESEARCH LETTERS LA English DT Article ID POLAR MESOSPHERIC CLOUDS; AURA SATELLITE; EOS MLS; JULY 13; THERMOSPHERE; SCIAMACHY; EXPLORER; METHANE; OZONE; NLC AB [1] A possible connection between the January 2005 solar proton events (SPEs) and the partial disappearance of Noctilucent clouds (NLCs) in the southern polar mesopause region is studied. Space-borne measurements of the NLC occurrence rate made with SCIAMACHY on Envisat as well as temperature measurements with MLS on Aura are employed. Immediately after the onset of the enhanced solar particle precipitation on January 16, 2005, we observe a severe decrease in the NLC occurrence rate. Between 70 degrees S-80 degrees S the NLC occurrence rate drops from about 80% to less than 20% within the period of enhanced solar proton fluxes. Throughout this period an anti-correlation between NLC occurrence rate and temperatures at NLC altitude is found, and the disappearance of NLCs is apparently caused by increasing temperatures. Potential mechanisms leading to the warming are discussed. C1 Univ Bremen, Inst Environm Phys, Bremen, Germany. Univ Osnabruck, Dept Phys, D-46069 Osnabruck, Germany. CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP von Savigny, C (reprint author), Univ Bremen, Inst Environm Phys & Remote Sensing, Otto Hahn Allee 1, D-28334 Bremen, Germany. EM csavigny@iup.physik.uni-bremen.de RI Sinnhuber, Miriam/A-7252-2013; von Savigny, Christian/B-3910-2014; Schwartz, Michael/F-5172-2016; Bovensmann, Heinrich/P-4135-2016; Burrows, John/B-6199-2014 OI Schwartz, Michael/0000-0001-6169-5094; Bovensmann, Heinrich/0000-0001-8882-4108; Burrows, John/0000-0002-6821-5580 NR 17 TC 26 Z9 26 U1 1 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 JAN 17 PY 2007 VL 34 IS 2 AR L02805 DI 10.1029/2006GL028106 PG 4 WC Geosciences, Multidisciplinary SC Geology GA 131DM UT WOS:000243848400003 ER PT J AU Gascoin, F Rasmussen, J Snyder, GJ AF Gascoin, Franck Rasmussen, Julia Snyder, G. Jeffrey TI High temperature thermoelectric properties of Mo3Sb7-xTex for x=1.6 and 1.5 SO JOURNAL OF ALLOYS AND COMPOUNDS LA English DT Article DE intermetallics; antimonides; thermoelectric ID PHASES AB We have prepared and measured the electrical resistivity, Seebeck coefficient and thermal conductivity of the titled compounds in the 300-1050 K temperature range. The results show that both members of the solid solution are heavily doped semiconductor with a figure of merit zT reaching 0.80 at 1050 K for x = 1.6. Higher values of x resulted in multi phase samples. The heavily doped semiconducting nature of the materials is consistent with theoretical predictions based on valence-electron count (VEC). The flexible nature of the crystalline structure, range of VEC attainable, and existence of intercalation sites are discussed as a way to enhance the thermoelectric properties of materials of this particular structure type. (c) 2006 Elsevier B.V. All rights reserved. C1 Univ Montpellier 2, CNRS, UMR 5617, Lab Phys Chim Mat Condensee, F-34095 Montpellier 5, France. CALTECH, Jet Propuls Lab, Pasadena, CA 91109 USA. RP Gascoin, F (reprint author), Univ Montpellier 2, CNRS, UMR 5617, Lab Phys Chim Mat Condensee, Pl Eugene Bataillon, F-34095 Montpellier 5, France. EM franck.gascoin@lpmc.univ-montp2.fr RI Snyder, G. Jeffrey/E-4453-2011; Snyder, G/I-2263-2015 OI Snyder, G. Jeffrey/0000-0003-1414-8682; NR 19 TC 35 Z9 37 U1 0 U2 14 PU ELSEVIER SCIENCE SA PI LAUSANNE PA PO BOX 564, 1001 LAUSANNE, SWITZERLAND SN 0925-8388 EI 1873-4669 J9 J ALLOY COMPD JI J. Alloy. Compd. PD JAN 16 PY 2007 VL 427 IS 1-2 BP 324 EP 329 DI 10.1016/j.jallcom.2006.03.030 PG 6 WC Chemistry, Physical; Materials Science, Multidisciplinary; Metallurgy & Metallurgical Engineering SC Chemistry; Materials Science; Metallurgy & Metallurgical Engineering GA 129NI UT WOS:000243735800060 ER PT J AU Lamsal, LN Weber, M Labow, G Burrows, JP AF Lamsal, L. N. Weber, M. Labow, G. Burrows, J. P. TI Influence of ozone and temperature climatology on the accuracy of satellite total ozone retrieval SO JOURNAL OF GEOPHYSICAL RESEARCH-ATMOSPHERES LA English DT Article ID RADIATIVE-TRANSFER MODEL; NM SPECTRAL REGION; ATMOSPHERIC CONSTITUENTS; GEOPHYSICAL APPLICATIONS; MONITORING EXPERIMENT; GOME; TRENDS; SPECTROPHOTOMETER; VALIDATION; LATITUDES AB [1] Deviation of assumed ozone profile shape from true profile in the radiative transfer calculation affects the accuracy of total ozone (TOZ) retrieval. Earlier studies have identified high profile shape sensitivity of retrieved TOZ in polar latitudes, in particular at high solar zenith angles (SZA). This paper is devoted to the question of how TOZ retrievals are influenced by the choice of ozone and temperature profiles from various currently available climatologies. Ozone and temperature profiles from those climatologies are applied in the Weighting Function Differential Optical Absorption Spectroscopy (WFDOAS) algorithm to retrieve TOZ from GOME spectral measurements. Comparison of the retrieved TOZ with ground based measurements from selected stations in the polar, middle-, and low-latitude regions indicate both systematic error and random errors associated with the profile shapes. Those errors become prominent at SZA more than 70 degrees. The systematic error might be caused by the differences in the ozone number density peak altitude between the climatological profile and the actual profile. Biases in true temperature with respect to the climatological temperature profile contribute to the TOZ error by their impact on the ozone absorption coefficient and molecular scattering. Our studies based on GOME spectral measurements and synthetic radiance show that at high SZA, more than 10% systematic error in the retrieved TOZ can be easily introduced by the choice of climatological profiles. The random error is of the same order of magnitude, and it can be related to day-to-day variability of ozone and temperature profiles. In this paper we show that an improved and updated ozone and temperature climatological profiles can reduce the systematic errors in the retrieved TOZ from satellite spectral measurements. C1 Univ Bremen, Inst Environm Phys & Remote Sensing, D-2800 Bremen 33, Germany. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Lamsal, LN (reprint author), Dalhousie Univ, Dept Phys & Atmospher Sci, Sir James Dunn Bldg,Room 129, Halifax, NS B3H 3J5, Canada. EM lamsal@iup.physik.uni-bremen.de RI Lamsal, Lok/G-4781-2012; Weber, Mark/F-1409-2011; Burrows, John/B-6199-2014 OI Weber, Mark/0000-0001-8217-5450; Burrows, John/0000-0002-6821-5580 NR 48 TC 11 Z9 11 U1 0 U2 0 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 JAN 16 PY 2007 VL 112 IS D2 AR D02302 DI 10.1029/2005JD006865 PG 16 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA 131DV UT WOS:000243849300001 ER PT J AU Furukawa, Y O'Reilly, SE AF Furukawa, Yoko O'Reilly, S. E. TI Rapid precipitation of amorphous silica in experimental systems with nontronite (NAu-1) and Shewanella oneidensis MR-1 SO GEOCHIMICA ET COSMOCHIMICA ACTA LA English DT Article ID ANALYTICAL ELECTRON-MICROSCOPY; X-RAY-MICROANALYSIS; BACILLUS-SUBTILIS; CLAY-MINERALS; EXPERIMENTAL SILICIFICATION; TRANSMISSION ELECTRON; NANOSPHERE FORMATION; STRUCTURAL FE(III); PHOSPHORUS CYCLE; BIOGENIC SILICA AB Nanometer-size (< 50 nm) precipitates of amorphous silica globules were observed in laboratory systems containing nontronite NAu1. Shewanella oneidensis strain MR-1, and lean aqueous media. Their formation was attributed to the release of polysilicic acids at the expense of dissolving NAu-1, and subsequent polymerization and stabilization mediated by biomolecules. Rapid (< 24 h) silica globule formation was confirmed in the immediate vicinity of bacterial cells and extracellular polymeric substances in all experimental systems that contained bacteria, whether the bacteria were respiring dissolved O-2 or Fe(III) originating from NAu-1, and whether the bacteria were viable or heat-killed. Silica globules were not observed in bacteria- and biomolecule-free systems. Thermodynamic calculations using disilicic acid, rather than monomeric silica, as the primary aqueous silica species suggest that the systems may have been supersaturated with respect to amorphous silica even though they appeared to be undersaturated if all aqueous silica was assumed to be monomeric H4SiO4. The predominant aqueous silica species in the experimental systems was likely polysilicic acids because aqueous silica was continuously supplied from the concurrent dissolution of aluminosilicate. Further polymerization and globule formation may have been driven by the presence of polyamines, a group of biologically produced compounds that are known to drive amorphous silica precipitation in diatom frustules. Globules were likely to be positively charged in our systems due to chemisorption of organic polycations onto silica surfaces that would have been otherwise negatively charged. We propose the following steps for the formation of nanometer-size silica globules in our experimental systems: (i) continuous supply of polysilicic acids due to NAu-1 dissolution; (ii) polysilicic acid polymerization to form < 50 nm silica globules and subsequent stabilization mediated by microbially produced polyamines; (iii) charge reversal due to chemisorption of organic polycations; and (iv) electrostatic attraction of positively charged silica globules to net negatively charged bacterial cells. Rapid, biogenic precipitation of silica may be common in soil and sediment systems that appear to be undersaturated with respect to amorphous Si. Published by Elsevier Inc. C1 USN, Res Lab, Seafloor Sci Brance, Stennis Space Ctr, Stennis Space Ctr, MS 39529 USA. RP Furukawa, Y (reprint author), USN, Res Lab, Seafloor Sci Brance, Stennis Space Ctr, Stennis Space Ctr, MS 39529 USA. EM yoko.furukawa@nrlssc.navy.mil RI Furukawa, Yoko/B-3099-2013 NR 88 TC 19 Z9 19 U1 2 U2 9 PU PERGAMON-ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0016-7037 EI 1872-9533 J9 GEOCHIM COSMOCHIM AC JI Geochim. Cosmochim. Acta PD JAN 15 PY 2007 VL 71 IS 2 BP 363 EP 377 DI 10.1016/j.gca.2006.09.006 PG 15 WC Geochemistry & Geophysics SC Geochemistry & Geophysics GA 125XQ UT WOS:000243477200007 ER PT J AU Seol, JH Moore, AL Saha, SK Zhou, F Shi, L Ye, QL Scheffler, R Mingo, N Yamada, T AF Seol, Jae Hun Moore, Arden L. Saha, Sanjoy K. Zhou, Feng Shi, Li Ye, Qi Laura Scheffler, Raymond Mingo, Natalio Yamada, Toshishige TI Measurement and analysis of thermopower and electrical conductivity of an indium antimonide nanowire from a vapor-liquid-solid method SO JOURNAL OF APPLIED PHYSICS LA English DT Article ID TRANSPORT-PROPERTIES; BI NANOWIRES; INSB; PASSIVATION; POWER AB It has been suggested by theoretical calculation that indium antimonide (InSb) nanowires can possess improved thermoelectric properties compared to the corresponding bulk crystal. Here we fabricated a device using electron beam lithography to measure the thermopower and electrical conductivity of an individual InSb nanowire grown using a vapor-liquid-solid method. The comparison between the measurement results and transport simulations reveals that the nanowire was unintentionally degenerately doped with donors. Better control of the impurity doping concentration can improve the thermoelectric properties. (c) 2007 American Institute of Physics. C1 Univ Texas, Dept Mech Engn, Austin, TX 78712 USA. Univ Texas, Ctr Nano & Mol Sci & Technol, Texas Mat Inst, Austin, TX 78712 USA. NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. ELORET, Sunnyvale, CA 94086 USA. RP Shi, L (reprint author), Univ Texas, Dept Mech Engn, Austin, TX 78712 USA. EM lishi@mail.utexas.edu RI Yamada, Toshishige/E-7834-2012; Shi, Li/C-8123-2013; Moore, Arden/G-9227-2014 OI Yamada, Toshishige/0000-0001-7145-9212; Shi, Li/0000-0002-5401-6839; Moore, Arden/0000-0002-9217-7510 NR 26 TC 62 Z9 62 U1 2 U2 41 PU AMER INST PHYSICS PI MELVILLE PA 1305 WALT WHITMAN RD, STE 300, MELVILLE, NY 11747-4501 USA SN 0021-8979 EI 1089-7550 J9 J APPL PHYS JI J. Appl. Phys. PD JAN 15 PY 2007 VL 101 IS 2 AR 023706 DI 10.1063/1.2430508 PG 6 WC Physics, Applied SC Physics GA 131SS UT WOS:000243890800064 ER PT J AU Wikelski, M Kays, RW Kasdin, NJ Thorup, K Smith, JA Swenson, GW AF Wikelski, Martin Kays, Roland W. Kasdin, N. Jeremy Thorup, Kasper Smith, James A. Swenson, George W., Jr. TI Going wild: what a global small-animal tracking system could do for experimental biologists SO JOURNAL OF EXPERIMENTAL BIOLOGY LA English DT Editorial Material DE small animal; ICARUS initiative; migration pattern; migratory bird orientation; satellite; field experiments; tracking technology; telemetry; songbird; bat; insect ID QUELEA QUELEA-QUELEA; WEST-NILE-VIRUS; MIGRATORY BIRDS; HIPPOCAMPAL-FORMATION; EQUATORIAL BIRD; STABLE-ISOTOPES; ORIENTATION; PIGEONS; SONGBIRDS; TELEMETRY AB Tracking animals over large temporal and spatial scales has revealed invaluable and spectacular biological information, particularly when the paths and fates of individuals can be monitored on a global scale. However, only large animals (greater than similar to 300 g) currently can be followed globally because of power and size constraints on the tracking devices. And yet the vast majority of animals is small. Tracking small animals is important because they are often part of evolutionary and ecological experiments, they provide important ecosystem services and they are of conservation concern or pose harm to human health. Here, we propose a small-animal satellite tracking system that would enable the global monitoring of animals down to the size of the smallest birds, mammals (bats), marine life and eventually large insects. To create the scientific framework necessary for such a global project, we formed the ICARUS initiative (www.IcarusInitiative.org), the International Cooperation for Animal Research Using Space. ICARUS also highlights how small-animal tracking could address some of the 'Grand Challenges in Environmental Sciences' identified by the US National Academy of Sciences, such as the spread of infectious diseases or the relationship between biological diversity and ecosystem functioning. Small-animal tracking would allow the quantitative assessment of dispersal and migration in natural populations and thus help solve enigmas regarding population dynamics, extinctions and invasions. Experimental biologists may find a global small-animal tracking system helpful in testing, validating and expanding laboratory-derived discoveries in wild, natural populations. We suggest that the relatively modest investment into a global small-animal tracking system will pay off by providing unprecedented insights into both basic and applied nature. Tracking small animals over large spatial and temporal scales could prove to be one of the most powerful techniques of the early 21st century, offering potential solutions to a wide range of biological and societal questions that date back two millennia to the Greek philosopher Aristotle's enigma about songbird migration. Several of the more recent Grand Challenges in Environmental Sciences, such as the regulation and functional consequences of biological diversity or the surveillance of the population ecology of zoonotic hosts, pathogens or vectors, could also be addressed by a global small-animal tracking system. Our discussion is intended to contribute to an emerging groundswell of scientific support to make such a new technological system happen. C1 Princeton Univ, Dept Ecol & Evolutionary Biol, Princeton, NJ 08544 USA. New York State Museum & Sci Serv, Mammal Lab, Albany, NY 12230 USA. Princeton Univ, Dept Mech & Aerosp Engn, Princeton, NJ 08544 USA. Univ Copenhagen, Zool Museum, Bird Ringing Ctr, DK-2100 Copenhagen, Denmark. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. Univ Illinois, Dept Elect & Comp Engn, Urbana, IL 61801 USA. Univ Illinois, Dept Astron, Urbana, IL 61801 USA. RP Wikelski, M (reprint author), Princeton Univ, Dept Ecol & Evolutionary Biol, Princeton, NJ 08544 USA. EM wikelski@princeton.edu RI Thorup, Kasper/A-4835-2013; publist, CMEC/C-3010-2012; publicationpage, cmec/B-4405-2017 OI Thorup, Kasper/0000-0002-0320-0601; NR 65 TC 117 Z9 120 U1 9 U2 88 PU COMPANY OF BIOLOGISTS LTD PI CAMBRIDGE PA BIDDER BUILDING CAMBRIDGE COMMERCIAL PARK COWLEY RD, CAMBRIDGE CB4 4DL, CAMBS, ENGLAND SN 0022-0949 EI 1477-9145 J9 J EXP BIOL JI J. Exp. Biol. PD JAN 15 PY 2007 VL 210 IS 2 BP 181 EP 186 DI 10.1242/jeb.02629 PG 6 WC Biology SC Life Sciences & Biomedicine - Other Topics GA 134KX UT WOS:000244083000006 PM 17210955 ER PT J AU Savchenkov, AA Matsko, AB Mohageg, M Strekalov, DV Maleki, L AF Savchenkov, A. A. Matsko, A. B. Mohageg, M. Strekalov, D. V. Maleki, L. TI Parametric oscillations in a whispering gallery resonator SO OPTICS LETTERS LA English DT Article ID LINBO3 AB We demonstrate strongly nondegenerate optical continuous-wave parametric oscillations in crystalline whispering gallery mode resonators fabricated from LiNbO3. The required phase matching is achieved by geometrical confinement of the modes in the resonator. (c) 2006 Optical Society of America. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Savchenkov, AA (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RI Matsko, Andrey/A-1272-2007 NR 10 TC 44 Z9 44 U1 4 U2 10 PU OPTICAL SOC AMER PI WASHINGTON PA 2010 MASSACHUSETTS AVE NW, WASHINGTON, DC 20036 USA SN 0146-9592 J9 OPT LETT JI Opt. Lett. PD JAN 15 PY 2007 VL 32 IS 2 BP 157 EP 159 DI 10.1364/OL.32.000157 PG 3 WC Optics SC Optics GA 123LZ UT WOS:000243298700017 PM 17186049 ER PT J AU Grudinin, IS Maleki, L AF Grudinin, Ivan S. Maleki, Lute TI Ultralow-threshold Raman lasing with CaF2 resonators SO OPTICS LETTERS LA English DT Article ID SCATTERING; LASER; MICROCAVITIES AB We demonstrate efficient Raman lasing with CaF2 Whispering-gallery-mode resonators. Continuous-wave emission threshold is shown to be possible below 1 mu W with a 5 mm cavity, which is to our knowledge orders of magnitude lower than in any other Raman source. Low-threshold lasing is made possible by the ultrahigh optical quality factor of the cavity, of the order of Q = 5 x 10(10). Stokes components of up to the fifth order were observed at a pump power of 160 mu W, and up to the eighth order at 1 mW. A lasing threshold of 15 mu W was also observed in a 100 mu m CaF2 microcavity. Potential applications are discussed. (c) 2006 Optical Society of America. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Grudinin, IS (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 13 TC 39 Z9 39 U1 2 U2 8 PU OPTICAL SOC AMER PI WASHINGTON PA 2010 MASSACHUSETTS AVE NW, WASHINGTON, DC 20036 USA SN 0146-9592 J9 OPT LETT JI Opt. Lett. PD JAN 15 PY 2007 VL 32 IS 2 BP 166 EP 168 DI 10.1364/OL.32.000166 PG 3 WC Optics SC Optics GA 123LZ UT WOS:000243298700020 PM 17186052 ER PT J AU Hyde, P Nelson, R Kimes, D Levine, E AF Hyde, Peter Nelson, Ross Kimes, Dan Levine, Elissa TI Exploring LIDAR-RaDAR synergy - predicting aboveground biomass in a southwestern ponderosa pine forest using LiDAR, SAR and InSAR SO REMOTE SENSING OF ENVIRONMENT LA English DT Article DE LiDAR; RaDAR; SAR; canopy height; biomass ID REMOTELY-SENSED DATA; BOREAL FOREST; ECOSYSTEM CHARACTERIZATION; POLARIMETRIC RADAR; CANOPY STRUCTURE; RAIN-FOREST; BACKSCATTER; VEGETATION; INVENTORY; LASER AB Scanning Light Detecting and Ranging (LiDAR), Synthetic Aperture Radar (SAR) and Interferometric SAR (InSAR) were analyzed to determine (1) which of the three sensor systems most accurately predicted forest biomass, and (2) if LiDAR and SAR/InSAR data sets, jointly considered, produced more accurate, precise results relative to those same data sets considered separately. LiDAR ranging measurements, VHF-SAR cross-sectional returns, and X- and P-band cross-sectional returns and interferometric ranges were regressed with ground-estimated (from dbh) forest biomass in ponderosa, pine forests in the southwestern United States. All models were cross-validated. Results indicated that the average canopy height measured by the scanning LiDAR produced the best predictive equation. The simple linear LiDAR equation explained 83% of the biomass variability (n = 52 plots) with a cross-validated root mean square error of 26.0 t/ha. Additional LiDAR metrics were not significant to the model. The GeoSAR P-band (lambda=86 cm) cross-sectional return and the GeoSAR/InSAR canopy height (X-P) captured 30% of the forest biomass variation with an average predictive error of 52.5 t/ha. A second RaDAR-FOPEN collected VHF (lambda similar to 7.8 m) and cross-polarized P-band (lambda = 88 cm) cross-sectional returns, none of which proved useful for forest biomass estimation (cross-validated R-2 =0.09, RMSE=63.7 t/ha). Joint consideration of LiDAR and RaDAR measurements produced a statistically significant, albeit small improvement in biomass estimation precision. The cross-validated R-2 increased from 83% to 84% and the prediction error decreased from 26.0 t/ha to 24.9 t/ha when the GeoSAR X-P interferometric height is considered along with the average LiDAR canopy height. Inclusion of a third LiDAR metric, the 60th decile height, further increased the R-2 to 85% and decreased the RMSE to 24.1 t/ha. On this I I km(2) ponderosa pine study area, LiDAR data proved most useful for predicting forest biomass. RaDAR ranging measurements did not improve the LiDAR estimates. (c) 2006 Elsevier Inc. All rights reserved. C1 Sci Syst & Applicat, Lanham, MD USA. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Hyde, P (reprint author), Sci Syst & Applicat, Lanham, MD USA. EM peter_hyde@ssaihq.com RI Nelson, Ross/H-8266-2014 NR 41 TC 68 Z9 77 U1 5 U2 25 PU ELSEVIER SCIENCE INC PI NEW YORK PA 360 PARK AVE SOUTH, NEW YORK, NY 10010-1710 USA SN 0034-4257 J9 REMOTE SENS ENVIRON JI Remote Sens. Environ. PD JAN 15 PY 2007 VL 106 IS 1 BP 28 EP 38 DI 10.1016/j.rse.2006.07.017 PG 11 WC Environmental Sciences; Remote Sensing; Imaging Science & Photographic Technology SC Environmental Sciences & Ecology; Remote Sensing; Imaging Science & Photographic Technology GA 129AQ UT WOS:000243701200003 ER PT J AU Huang, D Knyazikhin, Y Dickinson, RE Rautiainen, M Stenberg, P Disney, M Lewis, P Cescatti, A Tian, YH Verhoef, W Martonchik, JV Myneni, RB AF Huang, Dong Knyazikhin, Yuri Dickinson, Robert E. Rautiainen, Miina Stenberg, Pauline Disney, Mathias Lewis, Philip Cescatti, Alessandro Tian, Yuhong Verhoef, Wout Martonchik, John V. Myneni, Ranga B. TI Canopy spectral invariants for remote sensing and model applications SO REMOTE SENSING OF ENVIRONMENT LA English DT Article DE spectral invariants; recollision probability; escape probability; radiative transfer ID COMMUNITY CLIMATE MODEL; VEGETATION LEAF-AREA; RADIATIVE-TRANSFER; CONIFER NEEDLES; SOLAR-RADIATION; SIMULATIONS; MODIS; SATELLITE; ALGORITHM; FRACTION AB The concept of canopy spectral invariants expresses the observation that simple algebraic combinations of leaf and canopy spectral transmittance and reflectance become wavelength independent and determine a small set of canopy structure specific variables. This set includes the canopy interceptance, the recollision and the escape probabilities. These variables specify an accurate relationship between the spectral response of a vegetation canopy to the incident solar radiation at the leaf and the canopy scale and allow for a simple and accurate parameterization for the partitioning of the incoming radiation into canopy transmission, reflection and absorption at any wavelength in the solar spectrum. This paper presents a solid theoretical basis for spectral invariant relationships reported in literature with an emphasis on their accuracies in describing the shortwave radiative properties of the three-dimensional vegetation canopies. The analysis of data on leaf and canopy spectral transmittance and reflectance collected during the international field campaign in Flakaliden, Sweden, June 25-July 4, 2002 supports the proposed theory. The results presented here are essential to both modeling and remote sensing communities because they allow the separation of the structural and radiometric components of the measured/modeled signal. The canopy spectral invariants offer a simple and accurate parameterization for the shortwave radiation block in many global models of climate, hydrology, biogeochemistry, and ecology. In remote sensing applications, the information content of hyperspectral data can be fully exploited if the wavelength-independent variables can be retrieved, for they can be more directly related to structural characteristics of the three-dimensional vegetation canopy. (c) 2006 Elsevier Inc. All rights reserved. C1 Boston Univ, Dept Geog, Boston, MA 02215 USA. Georgia Inst Technol, Sch Earth & Atmospher Sci, Atlanta, GA 30332 USA. Univ Helsinki, Dept Forest Ecol, Helsinki, Finland. UCL, NERC, Ctr Terr Carbon Dynam, London, England. UCL, Dept Geog, London, England. Ctr Ecol Alpina, I-38100 Trento, Italy. Commiss European Communities, Joint Res Ctr, Inst Environm & Sustainabil, Climate Change Unit, I-21020 Ispra, Italy. Natl Aerosp Lab, NLR, Amsterdam, Netherlands. CALTECH, Jet Prop Lab, Pasadena, CA USA. RP Huang, D (reprint author), Boston Univ, Dept Geog, 675 Commonwealth Ave, Boston, MA 02215 USA. EM dh@bu.edu RI Rautiainen, Miina/A-4208-2009; Verhoef, Wouter/D-4399-2009; Lewis, Philip/C-1588-2008; Disney, Mathias/C-1889-2008; Huang, Dong/H-7318-2014; Myneni, Ranga/F-5129-2012 OI Rautiainen, Miina/0000-0002-6568-3258; Lewis, Philip/0000-0002-8562-0633; Huang, Dong/0000-0001-9715-6922; NR 39 TC 64 Z9 64 U1 3 U2 17 PU ELSEVIER SCIENCE INC PI NEW YORK PA 360 PARK AVE SOUTH, NEW YORK, NY 10010-1710 USA SN 0034-4257 J9 REMOTE SENS ENVIRON JI Remote Sens. Environ. PD JAN 15 PY 2007 VL 106 IS 1 BP 106 EP 122 DI 10.1016/j.rse.2006.08.001 PG 17 WC Environmental Sciences; Remote Sensing; Imaging Science & Photographic Technology SC Environmental Sciences & Ecology; Remote Sensing; Imaging Science & Photographic Technology GA 129AQ UT WOS:000243701200009 ER PT J AU Wiesli, RA Beard, BL Braterman, PS Johnson, CM Saha, SK Sinha, MP AF Wiesli, Rene A. Beard, Brian L. Braterman, Paul S. Johnson, Clark M. Saha, Susanta K. Sinha, Mahadeva P. TI Iron isotope fractionation between liquid and vapor phases of iron pentacarbonyl SO TALANTA LA English DT Article DE Fe isotopes; iron pentacarbonyl; isotope fractionation; electron impact ionization mass spectrometry ID MASS-SPECTROMETRY; ELECTRON-IMPACT; METAL-CARBONYLS; FE; TETRACARBONYL; DECOMPOSITION; DEPOSITION AB Iron isotope fractionation between liquid and vapor iron pentacarbonyl was measured in a closed system at similar to 0 and similar to 21 degrees C to determine if Fe isotope analysis of iron pentacarbonyl vapor is viable using electron-impact, gas-source mass spectrometry. At the 2cr level, there is no significant Fe isotope fractionation between vapor and liquid underconditions thoughtto reflect equilibrium. Experiments at similar to 0 degrees C indicate iron pentacarbonyl vapor is similar to 0.05 per mil (parts per thousand) greater in (56)Fe/(54)Fe than liquid iron pentacarbonyl, which is just resolvable at the 1 sigma level. Partial decomposition of iron pentacarbonyl vapor or liquid to an iron oxide or iron metal shows that significant isotopic fractionation occurs, where the decomposed product has a lower 56Fe/54Fe ratio as compared to the starting iron pentacarbonyl. It follows that methods to decompose iron pentacarbonyl must be quantitative to obtain accurate isotope values. (c) 2006 Elsevier B.V. All rights reserved. C1 Univ Wisconsin, Dept Geol & Geophys, Madison, WI 53706 USA. Univ N Texas, Dept Chem, Denton, TX 76203 USA. CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Beard, BL (reprint author), Univ Wisconsin, Dept Geol & Geophys, Lewis G Weeks Hall,1215 W Dayton St, Madison, WI 53706 USA. EM beardb@geology.wisc.edu NR 33 TC 3 Z9 3 U1 0 U2 4 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS SN 0039-9140 J9 TALANTA JI Talanta PD JAN 15 PY 2007 VL 71 IS 1 BP 90 EP 96 DI 10.1016/j.talanta.2006.03.026 PG 7 WC Chemistry, Analytical SC Chemistry GA 134CG UT WOS:000244059600014 PM 19071272 ER PT J AU Gao, ST Li, XF Tao, WK Shie, CL Lang, S AF Gao, Shouting Li, Xiaofan Tao, Wei-Kuo Shie, Chung-Lin Lang, Steve TI Convective and moist vorticity vectors associated with tropical oceanic convection: A three-dimensional cloud-resolving model simulation SO JOURNAL OF GEOPHYSICAL RESEARCH-ATMOSPHERES LA English DT Article ID POTENTIAL VORTICITY; FRONTAL RAINBANDS; EXTRATROPICAL CYCLONES; MICROSCALE STRUCTURE; MESOSCALE PROCESSES; SYSTEMS; PRECIPITATION; ORGANIZATION; INSTABILITY; GENERATION AB [1] The relationships between cloud hydrometeors and convective/moist vorticity vectors are investigated using hourly data from a three-dimensional, 5-day cloud-resolving model (CRM) simulation during the Tropical Rainfall Measuring Mission (TRMM) Kwajalein Experiment (KWAJEX). Vertical components of convective and moist vorticity vectors are highly correlated with cloud hydrometeors. The vertical components represent the interaction between horizontal vorticity and horizontal moist potential temperature/specific humidity gradient. The vertical components of convective and moist vorticity vectors can be used to study tropical oceanic convection in both two-dimensional and three-dimensional frameworks. C1 Chinese Acad Sci, Inst Atmospher Phys, Lab Cloud Precipitat Phys & Severe Storms, Beijing 100029, Peoples R China. Sci Syst & Applicat Inc, Lanham, MD 20706 USA. NOAA, Natl Environm Satellite Data & Informat Serv, Joint Ctr Satellite Data Assimilat, Camp Springs, MD 20746 USA. NOAA, Natl Environm Satellite Data & Informat Serv, Ctr Satellite Applicat & Res, Camp Springs, MD 20746 USA. Univ Maryland Baltimore Cty, Goddard Earht Sci & Technol Ctr, Baltimore, MD 21250 USA. NASA, Goddard Space Flight Ctr, Atmospheres Lab, Greenbelt, MD 20771 USA. RP Gao, ST (reprint author), Chinese Acad Sci, Inst Atmospher Phys, Lab Cloud Precipitat Phys & Severe Storms, Beijing 100029, Peoples R China. EM gst@lasg.iap.ac.cn RI Li, Xiaofan/F-5605-2010; Li, Xiaofan/G-2094-2014 NR 28 TC 37 Z9 55 U1 0 U2 5 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 JAN 13 PY 2007 VL 112 IS D1 AR D01105 DI 10.1029/2006JD007179 PG 9 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA 126QT UT WOS:000243530400002 ER PT J AU Scott, CD Ugarov, M Hauge, RH Sosa, ED Arepalli, S Schultz, JA Yowell, L AF Scott, Carl D. Ugarov, Michael Hauge, Robert H. Sosa, Edward D. Arepalli, Sivaram Schultz, J. Albert Yowell, Leonard TI Characterization of large fullerenes in single-wall carbon nanotube production by ion mobility mass spectrometry SO JOURNAL OF PHYSICAL CHEMISTRY C LA English DT Article ID THIN-FILMS; GROWTH; MECHANISM; CLUSTERS; PURITY; ATOMS; C-60 AB Samples from nanotubes produced by various methods are analyzed by laser desorption-ionization ion mobility time-of-flight mass spectrometry (LDI-IM-TOF-MS). The measurements find mostly positive fullerene ions in the mass range from 240 to 10000 Da. These principal contaminants are produced along with single-wall carbon nanotubes, which are too large to be detected in the mass spectra. Large fullerenes in the spectra are identified by their regular pattern of two carbon atom intervals and agreement of their mobility with theory. The distribution of large fullerenes varies among the samples depending on the type of production technique. Large numbers of fullerenes are seen in samples produced by the arc process and by the laser ablation process, whereas relatively few fullerenes are seen in samples produced by CVD processes. Measured drift times are in good agreement with those calculated based on a rigid sphere model. From close examination of the drift time distributions, there appears to be isomers of lower mobility. Agreement of measured with calculated drift times suggest that these isomers may be elongated structures. To assess possible limiting shapes of isomers seen in the mobility spectra, it appears that the shapes of the large fullerenes of a given mass vary from spherical to possibly short cylinders. C1 NASA, Lyndon B Johnson Space Ctr, ES4, Houston, TX 77058 USA. Ionwerks Inc, Houston, TX 77005 USA. Rice Univ, Dept Chem, Carbon Nanotechnol Lab, Houston, TX 77005 USA. NASA, Lyndon B Johnson Space Ctr, ERC Inc, Houston, TX 77058 USA. RP Scott, CD (reprint author), NASA, Lyndon B Johnson Space Ctr, ES4, Houston, TX 77058 USA. RI Hauge, Robert/A-7008-2011; Arepalli, Sivaram/A-5372-2010 OI Hauge, Robert/0000-0002-3656-0152; NR 32 TC 6 Z9 6 U1 0 U2 4 PU AMER CHEMICAL SOC PI WASHINGTON PA 1155 16TH ST, NW, WASHINGTON, DC 20036 USA SN 1932-7447 J9 J PHYS CHEM C JI J. Phys. Chem. C PD JAN 11 PY 2007 VL 111 IS 1 BP 36 EP 44 DI 10.1021/jp063649k PG 9 WC Chemistry, Physical; Nanoscience & Nanotechnology; Materials Science, Multidisciplinary SC Chemistry; Science & Technology - Other Topics; Materials Science GA 147HK UT WOS:000244993800010 ER PT J AU Seiffert, M Borys, C Scott, D Halpern, M AF Seiffert, Michael Borys, Colin Scott, Douglas Halpern, Mark TI An upper limit to polarized submillimetre emission in Arp 220 SO MONTHLY NOTICES OF THE ROYAL ASTRONOMICAL SOCIETY LA English DT Article DE galaxies : individual : Arp 220; galaxies : magnetic fields; cosmic microwave background ID MICROWAVE BACKGROUND ANISOTROPIES; CLERK MAXWELL TELESCOPE; PROBE WMAP OBSERVATIONS; MEXICAN HAT WAVELET; MAGNETIC-FIELD; INFRARED POLARIMETRY; LINEAR-POLARIZATION; SCUBA OBSERVATIONS; MOLECULAR CLOUDS; 1ST MEASUREMENTS AB We report the results of pointed observations of the prototypical ultraluminous infrared galaxy (ULIRG) Arp 220 at 850 mu m using the polarimeter on the Submillimetre Common User Bolometer Array instrument on the James Clerk Maxwell Telescope. We find a Bayesian 99 per cent confidence upper limit on the polarized emission for Arp 220 of 1.54 per cent, averaged over the 15-arcsec beam-size. Arp 220 can serve as a proxy for other, more distant such galaxies. This upper limit constrains the magnetic field geometry in Arp 220 and also provides evidence that polarized ULIRGs will not be a major contaminant for next-generation cosmic microwave background polarization measurements. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. CALTECH, Pasadena, CA 91125 USA. Univ Toronto, Dept Astron & Astrophys, Toronto, ON M5S 3H4, Canada. Univ British Columbia, Dept Phys & Astron, Vancouver, BC V6T 1Z1, Canada. RP Seiffert, M (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM michael.seiffert@jpl.nasa.gov OI Scott, Douglas/0000-0002-6878-9840 NR 64 TC 15 Z9 15 U1 0 U2 0 PU OXFORD UNIV PRESS PI OXFORD PA GREAT CLARENDON ST, OXFORD OX2 6DP, ENGLAND SN 0035-8711 J9 MON NOT R ASTRON SOC JI Mon. Not. Roy. Astron. Soc. PD JAN 11 PY 2007 VL 374 IS 2 BP 409 EP 414 DI 10.1111/j.1365-2966.2006.11186.x PG 6 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 130IA UT WOS:000243792100003 ER PT J AU Rivera, E Haghighipour, N AF Rivera, E. Haghighipour, N. TI On the stability of test particles in extrasolar multiple planet systems SO MONTHLY NOTICES OF THE ROYAL ASTRONOMICAL SOCIETY LA English DT Article DE celestial mechanics; stars : individual : upsilon Andromedae; stars : individual : GJ 876; stars : individual : 47 UMa; stars : individual : 55 Cancri; planetary systems ID 47 URSAE-MAJORIS; HABITABLE ZONES; TERRESTRIAL PLANETS; EXOPLANETARY SYSTEMS; UPSILON-ANDROMEDAE; PREDICTING PLANETS; V-ANDROMEDAE; SOLAR-SYSTEM; APSIDAL RESONANCE; MASS PLANETS AB We have studied the dynamical evolution of test particles in the planetary systems of upsilon Andromedae, GJ 876, 47 UMa and 55 Cnc. Using recent radial velocity data of these stars and also utilizing a relatively new radial velocity fitting routine, we have obtained the orbital parameters of the giant planets of these systems, and studied the possibility of their harbouring of terrestrial-class planets and smaller objects. Our results indicate that, unlike the stable orbit of the newly discovered Earth-like planet of GJ 876, the orbit of the recently announced planet of 55 Cnc is unstable. Our simulations also show that the outer planet of 47 UMa may contain Trojan-type asteroids. We present the results of our detailed study of the orbital stability and dynamical behaviour of test particles throughout these systems, and investigate the possibility of stable orbits in their habitable zones. Within the context of the latter, it seems that the two systems of 47 UMa and 55 Cnc are still the only ones with the capability of harbouring habitable planets, although the new influence zones of their giant planets have caused their habitable regions to be different from the ones reported in the literature. C1 Univ Calif Santa Cruz, Lick Observ, Santa Cruz, CA 95064 USA. NASA, Ames Res Ctr, Space Sci & Astrobiol Div, Moffett Field, CA 94035 USA. Univ Hawaii Manoa, Inst Astron, Honolulu, HI USA. Univ Hawaii Manoa, NASA, Astrobiol Inst, Honolulu, HI USA. RP Rivera, E (reprint author), Univ Calif Santa Cruz, Lick Observ, 373 Interdisciplinary Sci, Santa Cruz, CA 95064 USA. EM rivera@ucolick.org; nader@ifa.hawaii.edu NR 73 TC 27 Z9 27 U1 0 U2 0 PU BLACKWELL PUBLISHING PI OXFORD PA 9600 GARSINGTON RD, OXFORD OX4 2DQ, OXON, ENGLAND SN 0035-8711 J9 MON NOT R ASTRON SOC JI Mon. Not. Roy. Astron. Soc. PD JAN 11 PY 2007 VL 374 IS 2 BP 599 EP 613 DI 10.1111/j.1365-2966.2006.11172.x PG 15 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 130IA UT WOS:000243792100020 ER PT J AU Brown, MJI Dey, A Jannuzi, BT Brand, K Benson, AJ Brodwin, M Croton, DJ Eisenhardt, PR AF Brown, Michael J. I. Dey, Arjun Jannuzi, Buell T. Brand, Kate Benson, Andrew J. Brodwin, Mark Croton, Darren J. Eisenhardt, Peter R. TI The evolving luminosity function of red galaxies SO ASTROPHYSICAL JOURNAL LA English DT Article DE galaxies : elliptical and lenticular, cD; galaxies : evolution; galaxies : luminosity function, mass function ID COLOR-MAGNITUDE RELATION; INFRARED ARRAY CAMERA; ESTIMATING PHOTOMETRIC REDSHIFTS; ARTIFICIAL NEURAL-NETWORKS; IRAC SHALLOW SURVEY; WIDE-FIELD SURVEY; TO-LIGHT RATIOS; X-RAY SURVEY; SPACE-TELESCOPE; ELLIPTIC GALAXIES AB We trace the assembly history of red galaxies since z = 1 by measuring their evolving space density with the B-band luminosity function. Our sample of 39,599 red galaxies, selected from 6.96 deg(2) of imaging from the NOAO Deep Wide-Field Survey and the Spitzer IRAC Shallow Survey, is an order of magnitude larger, in size and volume, than comparable samples in the literature. We measure a higher space density of z similar to 0.9 red galaxies than some of the recent literature, in part because we account for the faint yet significant galaxy flux that falls outside of our photometric aperture. The B-band luminosity density of red galaxies, which effectively measures the evolution of similar to L* galaxies, increases by only 36% +/- 13% from z = 0 to z = 1. If red galaxy stellar populations have faded by similar or equal to 1.24 B-band magnitudes since z = 1, the stellar mass contained within the red galaxy population has roughly doubled over the past 8 Gyr. This is consistent with star-forming galaxies being transformed into less than or similar to L* red galaxies after a decline in their star formation rates. In contrast, the evolution of similar or equal to 4L* red galaxies differs only slightly from a model with negligible z < 1 star formation and no galaxy mergers. If this model approximates the luminosity evolution of red galaxy stellar populations, then similar or equal to 80% of the stellar mass contained within today's 4L* red galaxies was already in place at z = 0.7. While red galaxy mergers have been observed, such mergers do not produce rapid growth of 4L* red galaxy stellar masses between z = 1 and the present day. C1 Princeton Univ Observ, Princeton, NJ 08544 USA. Monash Univ, Sch Phys, Clayton, Vic 3168, Australia. Natl Opt Astron Observ, Tucson, AZ 85726 USA. Univ Oxford, Dept Phys, Oxford OX1 2JD, England. CALTECH, Jet Prop Lab, Pasadena, CA USA. Univ Calif Berkeley, Dept Astron, Berkeley, CA 94720 USA. RP Brown, MJI (reprint author), Princeton Univ Observ, Peyton Hall, Princeton, NJ 08544 USA. EM mbrown@astro.princeton.edu RI Brown, Michael/B-1181-2015 OI Brown, Michael/0000-0002-1207-9137 NR 78 TC 232 Z9 232 U1 0 U2 4 PU UNIV CHICAGO PRESS PI CHICAGO PA 1427 E 60TH ST, CHICAGO, IL 60637-2954 USA SN 0004-637X J9 ASTROPHYS J JI Astrophys. J. PD JAN 10 PY 2007 VL 654 IS 2 BP 858 EP 877 DI 10.1086/509652 PN 1 PG 20 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 124PU UT WOS:000243382900013 ER PT J AU Osten, RA Drake, S Tueller, J Cummings, J Perri, M Moretti, A Covino, S AF Osten, Rachel A. Drake, Stephen Tueller, Jack Cummings, Jay Perri, Matteo Moretti, Alberto Covino, Stefano TI Nonthermal hard X-ray emission and iron K alpha emission from a superflare on II Pegasi SO ASTROPHYSICAL JOURNAL LA English DT Article DE stars : activity; stars : coronae; stars : flare; stars : individual (II Pegasi); stars : late-type; X-rays : stars ID EXTREME-ULTRAVIOLET-EXPLORER; CANUM-VENATICORUM SYSTEMS; LATE-TYPE STARS; SOLAR-FLARES; CHROMOSPHERIC EVAPORATION; PHOTOSPHERIC IRON; IMPULSIVE PHASE; STELLAR CORONAE; LINE EMISSION; UX-ARIETIS AB We report on an X-ray flare detected on the active binary system II Pegasi with the Swift telescope. The event triggered the Burst Alert Telescope ( BAT) in the hard X-ray band on 2005 December 16 at 11: 21: 52 UT with a 10-200 keV luminosity of 2.2 x 10(32) ergs s(-1) - a superflare, by comparison with energies of typical stellar flares on active binary systems. The trigger spectrum indicates a hot thermal plasma with T similar to 180 x 10(6) K. X-ray spectral analysis from 0.8 to 200 keV with the X-Ray Telescope and BAT in the next two orbits reveals evidence for a thermal component ( T > 80 x 10(6) K) and Fe K 6.4 keV emission. A tail of emission out to 200 keV can be fit with either an extremely high temperature thermal plasma ( T similar to 3 x 10(8) K) or power-law emission. Based on analogies with solar flares, we attribute the excess continuum emission to nonthermal thick-target bremsstrahlung emission from a population of accelerated electrons. We estimate the radiated energy from 0.01 to 200 keVto be similar to 6 x 10(36) ergs, the total radiated energy over all wavelengths similar to 10(38) ergs, the energy in nonthermal electrons above 20 keV similar to 3 x 10(40) ergs, and conducted energy < 5 x 10(43) ergs. The nonthermal interpretation gives a reasonable value for the total energy in electrons > 20 keV when compared to the upper and lower bounds on the thermal energy content of the flare. This marks the first occasion in which evidence exists for nonthermal hard X-ray emission from a stellar flare. We investigate the emission mechanism responsible for producing the 6.4 keV feature, and find that collisional ionization from nonthermal electrons appears to be more plausible than the photoionization mechanism usually invoked on the Sun and pre-main-sequence stars. C1 Univ Maryland, Dept Astron, College Pk, MD 20742 USA. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. ASI Sci Data Ctr, Frascati, Italy. INAF Osserv Astron Brera, Merate, Italy. Univ Space Res Assoc, Columbia, MD 21044 USA. RP Osten, RA (reprint author), Univ Maryland, Dept Astron, College Pk, MD 20742 USA. EM rosten@astro.umd.edu RI Tueller, Jack/D-5334-2012 NR 71 TC 52 Z9 52 U1 0 U2 1 PU IOP PUBLISHING LTD PI BRISTOL PA TEMPLE CIRCUS, TEMPLE WAY, BRISTOL BS1 6BE, ENGLAND SN 0004-637X EI 1538-4357 J9 ASTROPHYS J JI Astrophys. J. PD JAN 10 PY 2007 VL 654 IS 2 BP 1052 EP 1067 DI 10.1086/509252 PN 1 PG 16 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 124PU UT WOS:000243382900030 ER PT J AU Cohen, O Sokolov, IV Roussev, II Arge, CN Manchester, WB Gombosi, TI Frazin, RA Park, H Butala, MD Kamalabadi, F Velli, M AF Cohen, O. Sokolov, I. V. Roussev, I. I. Arge, C. N. Manchester, W. B. Gombosi, T. I. Frazin, R. A. Park, H. Butala, M. D. Kamalabadi, F. Velli, M. TI A semiempirical magnetohydrodynamical model of the solar wind SO ASTROPHYSICAL JOURNAL LA English DT Article DE interplanetary medium; methods : numerical; MHD; solar wind; Sun : evolution; Sun : magnetic fields ID MAGNETIC-FIELD; ALFVEN WAVES; MHD MODEL; CORONA; FLUX; SIMULATION; EVENT; SPEED; CME; SUN AB We present a new MHD model for simulating the large-scale structure of the solar corona and solar wind under "steady state" conditions stemming from the Wang-Sheeley-Arge empirical model. The processes of turbulent heating in the solar wind are parameterized using a phenomenological, thermodynamical model with a varied polytropic index. We employ the Bernoulli integral to bridge the asymptotic solar wind speed with the assumed distribution of the polytropic index on the solar surface. We successfully reproduce the mass flux from Sun to Earth, the temperature structure, and the large-scale structure of the magnetic field. We reproduce the solar wind speed bimodal structure in the inner heliosphere. However, the solar wind speed is in a quantitative agreement with observations at 1 AU for solar maximum conditions only. The magnetic field comparison demonstrates that the input magnetogram needs to be multiplied by a scaling factor in order to obtain the correct magnitude at 1 AU. C1 Univ Michigan, Dept Atmospher Ocean & Space Sci, Ann Arbor, MI 48109 USA. Univ Hawaii, Inst Astron, Honolulu, HI 96822 USA. USAF, Res Lab, Space Vehicles Directorate, Hanscom AFB, MA USA. Univ Illinois, Dept Elect & Comp Engn, Urbana, IL 61801 USA. CALTECH, Jet Prop Lab, Pasadena, CA USA. RP Cohen, O (reprint author), Univ Michigan, Dept Atmospher Ocean & Space Sci, Ann Arbor, MI 48109 USA. EM oferc@umich.edu; iroussev@ifa.hawaii.edu; nick.arge@hanscom.af.mil; frazin@uiuc.edu; mvelli@jpl.nasa.gov RI Roussev, Ilia/E-9141-2011; Gombosi, Tamas/G-4238-2011; Manchester, Ward/I-9422-2012; Frazin, Richard/J-2625-2012; Sokolov, Igor/H-9860-2013 OI Cohen, Ofer/0000-0003-3721-0215; Gombosi, Tamas/0000-0001-9360-4951; Sokolov, Igor/0000-0002-6118-0469 NR 27 TC 101 Z9 102 U1 0 U2 3 PU UNIV CHICAGO PRESS PI CHICAGO PA 1427 E 60TH ST, CHICAGO, IL 60637-2954 USA SN 0004-637X J9 ASTROPHYS J JI Astrophys. J. PD JAN 10 PY 2007 VL 654 IS 2 BP L163 EP L166 DI 10.1086/511154 PN 2 PG 4 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 124PV UT WOS:000243383000015 ER PT J AU Worden, J Liu, X Bowman, K Chance, K Beer, R Eldering, A Gunson, M Worden, H AF Worden, John Liu, Xiong Bowman, Kevin Chance, Kelly Beer, Reinhard Eldering, Annmarie Gunson, Michael Worden, Helen TI Improved tropospheric ozone profile retrievals using OMI and TES radiances SO GEOPHYSICAL RESEARCH LETTERS LA English DT Article ID EMISSION SPECTROMETER; MODEL; SATELLITE AB We perform a study for characterizing the vertical resolution of tropospheric ozone profile retrievals from the combination of simulated ultraviolet (UV) and thermal infrared (TIR) observations that are representative of the EOS Aura Ozone Monitoring Instrument (OMI) and the Tropospheric Emission Spectrometer (TES). Under the low thermal contrast conditions used for this simulation, we find that estimating ozone profiles by combining UV and TIR radiances results in a factor of two or more improvement in the ability to resolve boundary layer ozone, as compared with either instrument alone. In addition, there is a substantial improvement in the vertical resolution of ozone in the free troposphere (between 20% and 60%) as compared to the TES vertical resolution. This study points towards the importance of combining multiple spectral regions for dramatically improving the sounding of tropospheric trace gases. C1 CALTECH, Jet Prop Lab, Div Earth & Space Sci, Pasadena, CA 91109 USA. Harvard Smithsonian Ctr Astrophys, Atom & Mol Phys Div, Cambridge, MA 02138 USA. RP Worden, J (reprint author), CALTECH, Jet Prop Lab, Div Earth & Space Sci, 4800 OAk Grove Dr,MS 183-301, Pasadena, CA 91109 USA. EM john.worden@jpl.nasa.gov RI Liu, Xiong/P-7186-2014; OI Liu, Xiong/0000-0003-2939-574X; Chance, Kelly/0000-0002-7339-7577 NR 21 TC 41 Z9 41 U1 2 U2 5 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 JAN 10 PY 2007 VL 34 IS 1 AR L01809 DI 10.1029/2006GL027806 PG 5 WC Geosciences, Multidisciplinary SC Geology GA 126QG UT WOS:000243528900003 ER PT J AU McKendry, IG Strawbridge, KB O'Neill, NT Macdonald, AM Liu, PSK Leaitch, WR Anlauf, KG Jaegle, L Fairlie, TD Westphal, DL AF McKendry, Ian G. Strawbridge, Kevin B. O'Neill, Norman T. Macdonald, Anne Marie Liu, Peter S. K. Leaitch, W. Richard Anlauf, Kurt G. Jaegle, Lyatt Fairlie, T. Duncan Westphal, Douglas L. TI Trans-Pacific transport of Saharan dust to western North America: A case study SO JOURNAL OF GEOPHYSICAL RESEARCH-ATMOSPHERES LA English DT Article ID ASIAN DUST; OPTICAL-PROPERTIES; GOCART MODEL; APRIL 1998; AEROSOL; DEPOSITION; TRAJECTORIES; CLIMATOLOGY; SIMULATION; CANADA AB The first documented case of long-range transport of Saharan dust over a pathway spanning Asia and the Pacific to western North America is described. Crustal material generated by North African dust storms during the period 28 February to 3 March 2005 reached western Canada on 13-14 March 2005 and was observed by lidar and sunphotometer in the Vancouver region and by high-altitude aerosol instrumentation at Whistler Peak. Global chemical models (GEOS-Chem and NRL NAAPS) confirm the transport pathway and suggest source attribution was simplified in this case by the distinct, and somewhat unusual, lack of dust activity over Eurasia (Gobi and Takla Makan deserts) at this time. Over western North America the dust layer, although subsiding close to the boundary layer, did not appear to contribute to boundary layer particulate matter concentrations. Furthermore, sunphotometer observations (and associated inversion products) suggest that the dust layer had only subtle optical impact (aerosol optical thickness (tau(a500)) and Angstrom exponent (alpha(440-870)) were 0.1 and 1.2, respectively) and was dominated by fine particulate matter (modes in aerodynamic diameter at 0.3 and 2.5 mu m). High-altitude observations at Whistler, British Columbia, confirm the crustal origin of the layer (rich in Ca++ ions) and the bimodal size distribution. Although a weak event compared to the Asian trans-Pacific dust events of 1998 and 2001, this novel case highlights the possibility that Saharan sources may contribute episodically to the aerosol burden in western North America. C1 Univ British Columbia, Dept Geog, Atmospher Sci Program, Vancouver, BC V5Z 1M9, Canada. Environm Canada, Ctr Atmospher Res Expt, Sci & Technol Branch, Egberg, ON, Canada. Univ Sherbrooke, Dept Geomat Appl, CARTEL, Sherbrooke, PQ, Canada. Environm Canada, Sci & Technol Branch, Toronto, ON, Canada. Univ Washington, Dept Atmospher Sci, Seattle, WA 98195 USA. NASA Langley Res Ctr, Hampton, VA USA. Harvard Univ, Dept Earth & Planetary Sci, Cambridge, MA USA. USN, Res Lab, Marine Meteorol Div, Monterey, CA USA. RP McKendry, IG (reprint author), Univ British Columbia, Dept Geog, Atmospher Sci Program, Vancouver, BC V5Z 1M9, Canada. EM ian@geog.ubc.ca; kstrawbridge@dow.on.doe.ca; noneill@courrier.usherb.ca; annemarie.macdonald@ec.gc.ca; peter.liu@ec.gc.ca; richard.leaitch@ec.gc.ca; kurt.anlauf@ec.gc.ca; jaegle@atmos.washington.edu; t.d.fairlie@larc.nasa.gov; westphal@nrlmry.navy.mil RI Chem, GEOS/C-5595-2014 NR 38 TC 41 Z9 42 U1 1 U2 12 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 JAN 10 PY 2007 VL 112 IS D1 AR D01103 DI 10.1029/2006JD007129 PG 13 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA 126QQ UT WOS:000243530100002 ER PT J AU Zhang, YC Rossow, WB Stackhouse, PW AF Zhang, Yuanchong Rossow, William B. Stackhouse, Paul W., Jr. TI Comparison of different global information sources used in surface radiative flux calculation: Radiative properties of the surface SO JOURNAL OF GEOPHYSICAL RESEARCH-ATMOSPHERES LA English DT Article ID REFLECTANCE DISTRIBUTION FUNCTION; ISCCP DATA SETS; SATELLITE-OBSERVATIONS; ALBEDO RETRIEVALS; INPUT DATA; VALIDATION; MICROWAVE; CLIMATE; CLOUD; MODEL AB Direct estimates of surface radiative fluxes that resolve regional and weather-scale variability over the whole globe with reasonable accuracy have only become possible with the advent of extensive global, mostly satellite, data sets within the past couple of decades. The accuracy of these fluxes, estimated to be about 10-15 W/m(2), is largely limited by the accuracy of the input data sets. The leading uncertainties in the surface fluxes are no longer predominantly induced by clouds but are now as much associated with uncertainties in the surface and near-surface atmospheric properties. This study presents a fuller, more quantitative evaluation of the uncertainties for the surface albedo and emissivity and surface skin temperatures by comparing the main available global data sets from the Moderate-Resolution Imaging Spectroradiometer product, the NASA Global Energy and Water Cycle Experiment Surface Radiation Budget project, the European Centre for Medium-Range Weather Forecasts, the National Aeronautics and Space Administration, the National Centers for Environmental Prediction, the International Satellite Cloud Climatology Project (ISCCP), the Laboratoire de Meteorologie Dynamique, NOAA/NASA Pathfinder Advanced Very High Resolution Radiometer project, and the NOAA Optimum Interpolation Sea Surface Temperature Analysis and the Tropical Rainfall Measuring Mission (TRMM) Microwave Image project. The data sets are, in practice, treated as an ensemble of realizations of the actual climate such that their differences represent an estimate of the uncertainty in their measurements because we do not possess global "truth'' data sets for these quantities. The results are globally representative and may be taken as a generalization of our previous ISCCP-based uncertainty estimates for the input data sets. Surface properties have the primary role in determining the surface upward shortwave (SW) and longwave (LW) flux. From this study the following conclusions are obtained. Although land surface albedos in the near-infrared remain poorly constrained (highly uncertain), they do not cause too much error in total surface SW fluxes; the more subtle regional and seasonal variations associated with vegetation and snow are still in doubt. The uncertainty of the broadband black-sky SW albedo for land surface from this study is about 7%, which can easily induce 5-10 W/m(2) uncertainty in (upwelling) surface SW flux estimates. Even though available surface (broadband) LW emissivity data sets differ significantly (3-5% uncertainty), this disagreement is confined to wavelengths > 20 mu m so that there is little practical effect (1-3 W/m(2)) on the surface upwelling LW fluxes. The surface skin temperature is one of two leading factors that cause problems with surface LW fluxes. Even though the differences among the various data sets are generally only 2-4 K, this can easily cause 10-15 W/m(2) uncertainty in calculated surface (upwelling) LW fluxes. Significant improvements could be obtained for surface LW flux calculations by improving the retrievals of (in order of decreasing importance): (1) surface skin temperature, (2) surface air and near-surface-layer temperature, (3) column precipitable water amount, and 4) broadband emissivity. In addition, for surface SW fluxes, improvements could be obtained (excluding improved cloud treatment) by improving the retrievals of (1) aerosols (from our sensitivity studies but not discussed in this work) and (2) surface (black-sky) albedo, of which the NIR part of the spectrum has mch larger uncertainty. C1 Columbia Univ, NASA Goddard Inst Space Studies, Dept Appl Phys & Appl Math, New York, NY USA. Columbia Univ, NASA Goddard Inst Space Studies, New York, NY USA. NASA Langley Res Ctr, Hampton, VA USA. RP Zhang, YC (reprint author), Columbia Univ, NASA Goddard Inst Space Studies, Dept Appl Phys & Appl Math, New York, NY USA. EM yzhang@giss.nasa.gov RI Rossow, William/F-3138-2015 NR 60 TC 40 Z9 40 U1 1 U2 12 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 JAN 10 PY 2007 VL 112 IS D1 AR D01102 DI 10.1029/2005JD007008 PG 20 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA 126QQ UT WOS:000243530100001 ER PT J AU Shukla, S Zhang, P Cho, HJ Seal, S Ludwig, L AF Shukla, Satyajit Zhang, Peng Cho, Hyoung J. Seal, Sudipta Ludwig, Lawrence TI Room temperature hydrogen response kinetics of nano-micro-integrated doped tin oxide sensor SO SENSORS AND ACTUATORS B-CHEMICAL LA English DT Article DE hydrogen; response kinetics; MEMS; sensor; tin oxide ID SOL-GEL NANOCRYSTALS; GAS SENSORS; THIN-FILMS; SNO2; MICROSENSORS; IMPREGNATION; SENSITIVITY; CO AB The nano-micro-integrated sensor has been fabricated by sol-gel depositing the nanocrystalline indium oxide (In2O3)-doped tin oxide (SnO2) thin film on microelectromechanical systems (MEMS) device having interdigitated electrode configurations with two different electrode spacing (10 mu m and 20 mu m) and two different number of fingers (8 and 20). The present nano-micro-integrated sensor exhibits high H-2 sensitivity range (S = 3-10(5)) for the H-2 concentration within the range of 100-15,000 ppm at room temperature. It has been demonstrated that, the room temperature response kinetics of the present nano-micro-integrated sensor is a function of finger spacing, H-2 concentration and air-pressure, but independent of number of fingers. Such dependence has been explained on the basis of Le Chatelier's principle applied to the associated H-2 sensing mechanism and the role of above parameters in shifting the dynamic equilibrium of the involved surface reactions under the described test conditions. A new definition of the response time has been proposed, which is not only suitable for the theoretical analysis but also for the practical applications, where a gas-leak detection alarm is required to be triggered. (c) 2006 Published by Elsevier B.V. C1 Univ Cent Florida, Surface Engn & Nanotechnol Facil, AMPAC, Orlando, FL 32816 USA. Univ Cent Florida, Mech Mat Aerosp Engn Dept, Orlando, FL 32816 USA. NASA, KSC, Elect & Data Acquisit Lab, Kennedy Space Ctr, FL 32899 USA. RP Seal, S (reprint author), Univ Cent Florida, Surface Engn & Nanotechnol Facil, AMPAC, 4000 Cent Florida Blvd, Orlando, FL 32816 USA. EM sshukla@ucf.edu; sseal@mail.ucf.edu OI Shukla, Satyajit/0000-0002-7947-8095 NR 19 TC 38 Z9 39 U1 4 U2 23 PU ELSEVIER SCIENCE SA PI LAUSANNE PA PO BOX 564, 1001 LAUSANNE, SWITZERLAND SN 0925-4005 J9 SENSOR ACTUAT B-CHEM JI Sens. Actuator B-Chem. PD JAN 10 PY 2007 VL 120 IS 2 BP 573 EP 583 DI 10.1016/j.snb.2006.03.010 PG 11 WC Chemistry, Analytical; Electrochemistry; Instruments & Instrumentation SC Chemistry; Electrochemistry; Instruments & Instrumentation GA 134HH UT WOS:000244073600032 ER PT J AU Kulkarni, P Chellam, S Mittlefehldt, DW AF Kulkarni, Pranav Chellam, Shankararaman Mittlefehldt, David W. TI Microwave-assisted extraction of rare earth elements from petroleum refining catalysts and ambient fine aerosols prior to inductively coupled plasma-mass spectrometry SO ANALYTICA CHIMICA ACTA LA English DT Article DE microwave digestion; fluidized-bed catalytic cracking (FCC) catalysts; inductively coupled plasma-mass spectrometry (ICP-MS); instrumental neutron activation analysis (INAA); rare earth elements; lanthanides; particulate matter (PM2.5) ID ATOMIC EMISSION-SPECTROMETRY; NEUTRON-ACTIVATION ANALYSIS; AIRBORNE PARTICLES; PARTICULATE MATTER; GEOLOGICAL SAMPLES; TRACE-ELEMENTS; ICP-MS; LANTHANIDES; APPORTIONMENT; DIGESTION AB A robust microwave-assisted acid digestion procedure followed by inductively coupled plasma-mass spectrometry (ICP-MS) was developed to quantify rare earth elements (REEs) in fluidized-bed catalytic cracking (FCC) catalysts and atmospheric fine particulate matter (PM2.5). High temperature (200 degrees C), high pressure (200 psig), acid digestion (HNO3, HF and H3BO3) with 20 min dwell time effectively solubilized REEs from six fresh catalysts, a spent catalyst and PM2.5. This method was also employed to measure 27 non-REEs including Na, Mg, Al, Si, K, Sc, Ti, V, Cr, Mn, Fe, Co, Ni, Cu, Zn, Ga, As, Se, Rb, Sr, Zr, Mo, Cd, Cs, Ba, Pb and U. Complete extraction of several REEs (Y, La, Ce, Pr, Nd, Tb, Dy and Er) required HF indicating that they were closely associated with the aluminosilicate structure of the zeolite FCC catalysts. Internal standardization using In-115 quantitatively corrected non-spectral interferences in the catalyst digestate matrix. Inter-laboratory comparison using ICP-optical emission spectroscopy (ICP-OES) and instrumental neutron activation analysis (INAA) demonstrated the applicability of the newly developed analytical method for accurate analysis of REEs in FCC catalysts. The method developed for FCC catalysts was also successfully implemented to measure trace to ultra-trace concentrations of La, Ce, Pr, Nd, Sm, Gd, Eu and Dy in ambient PM2.5 in an industrial area of Houston, TX. (c) 2006 Elsevier B.V. All rights reserved. C1 Univ Houston, Dept Civil & Environm Engn, Houston, TX 77204 USA. Univ Houston, Dept Chem Engn, Houston, TX 77204 USA. NASA, Lyndon B Johnson Space Ctr, Astromat Res & Explorat Sci Off, Houston, TX 77058 USA. RP Chellam, S (reprint author), Univ Houston, Dept Civil & Environm Engn, 4800 Calhoun Rd, Houston, TX 77204 USA. EM chellam@uh.edu NR 38 TC 39 Z9 41 U1 2 U2 42 PU ELSEVIER SCIENCE BV PI AMSTERDAM PA PO BOX 211, 1000 AE AMSTERDAM, NETHERLANDS SN 0003-2670 J9 ANAL CHIM ACTA JI Anal. Chim. Acta PD JAN 9 PY 2007 VL 581 IS 2 BP 247 EP 259 DI 10.1016/j.aca.2006.08.035 PG 13 WC Chemistry, Analytical SC Chemistry GA 128NS UT WOS:000243665200008 PM 17386451 ER PT J AU Horvath, A Davies, R AF Horvath, Akos Davies, Roger TI Comparison of microwave and optical cloud water path estimates from TMI, MODIS, and MISR SO JOURNAL OF GEOPHYSICAL RESEARCH-ATMOSPHERES LA English DT Article ID LIQUID WATER; PASSIVE MICROWAVE; SATELLITE MEASUREMENTS; TROPICAL OCEANS; ALGORITHM; PRECIPITATION; IMAGER; SSM/I; RETRIEVALS; PRODUCTS AB [1] This study investigated the consistency between microwave and optical water path estimates of oceanic clouds from Tropical Rainfall Measurement Mission (TRMM) Microwave Imager (TMI), Moderate Resolution Imaging Spectroradiometer ( MODIS), and Multiangle Imaging Spectroradiometer (MISR). We used microwave estimates from the Wentz algorithm for warm, nonprecipitating clouds and both Wentz retrievals and standard TMI profiles for cold, precipitating clouds. Optical estimates were derived from cloud optical thickness and particle effective radius. For warm, nonprecipitating clouds the two methods showed good agreement at the 25-km resolution of the microwave measurements, with liquid water path means being within 5-10%, an overall correlation of 0.85, and RMS difference of similar to 25 g m(-2). Multiangle optical retrievals showed only weak variations with view zenith angle, building further confidence in the results. An error analysis suggested that optical estimates were more certain than microwave ones, primarily because 1-D plane-parallel radiative transfer seemed to apply well at the coarser comparison scales. However, there appeared to be a slight but systematic dependence on cloud amount as microwave retrievals increasingly overestimated optical ones at cloud fractions below similar to 65%. For cold, precipitating clouds we tested three common interpretations of optical retrievals: liquid water path, ice water path, and total water path. The relationship between microwave and optical estimates was weak in all cases, with correlations no more than 0.5, and RMS differences at least an order of magnitude larger than for warm clouds. The weakest correlation (0.37) was found when optical retrievals were interpreted as ice water paths. If anything, optical estimates appeared best correlated with microwave cloud liquid water paths. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. RP Horvath, A (reprint author), Univ Miami, Rosenstiel Sch Marine & Atmospher Sci, 4600 Rickenbacker Causeway, Miami, FL 33149 USA. EM ahorvath@rsmas.miami.edu RI Horvath, Akos/A-2453-2008; Davies, Roger/D-4296-2009 OI Horvath, Akos/0000-0002-5860-2368; Davies, Roger/0000-0002-2991-0409 NR 31 TC 31 Z9 32 U1 0 U2 4 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 JAN 9 PY 2007 VL 112 IS D1 AR D01202 DI 10.1029/2006JD007101 PG 12 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA 126QP UT WOS:000243530000002 ER PT J AU Mitchell, DL Lillis, RJ Lin, RP Connerney, JEP Acuna, MH AF Mitchell, D. L. Lillis, R. J. Lin, R. P. Connerney, J. E. P. Acuna, M. H. TI A global map of Mars' crustal magnetic field based on electron reflectometry SO JOURNAL OF GEOPHYSICAL RESEARCH-PLANETS LA English DT Article ID SOLAR-CYCLE VARIATION; IMPACT BASINS; TOPOGRAPHY; EVOLUTION; LOWLANDS; WINDS AB We present a global map of the amplitude of Mars' crustal magnetic field at 170-km altitude based on electron reflectometry, using data from the Magnetometer/Electron Reflectometer (MAG/ER) experiment on board Mars Global Surveyor. This new map contains features that are about seven times weaker than those in previously published maps obtained with the MAG alone from the 400-km-altitude mapping orbit. The increased sensitivity and nearly complete sampling reveal numerous weak magnetic sources in the northern lowlands. A group of these sources forms a nearly complete ring surrounding the Utopia basin, coinciding with a ridge of thickened crust. A larger 5800-km-diameter ring is defined by a similar to 120 degrees arc of magnetic sources that extend to the north pole, supporting the hypothesis that part of the dichotomy boundary was established or modified by the Utopia impact. We also map the magnetic signatures of the Hellas, Argyre, and Isidis impact basins with increased dynamic range, confirming the large contrast in magnetic field strength between the basin interior and surroundings. Magnetic sources surround most of the Tharsis rise, except in the north, suggesting that the construction of Tharsis thermally demagnetized a large region of the northern lowlands. Thermal demagnetization is also suggested in the Elysium region, which intersects the inner Utopia magnetic ring, and south of the Hellas basin in the vicinity of Peneus Patera and Amphitrites Patera. C1 Univ Calif Berkeley, Space Sci Lab, Berkeley, CA 94720 USA. NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Mitchell, DL (reprint author), Univ Calif Berkeley, Space Sci Lab, 7 Gauss Way, Berkeley, CA 94720 USA. EM mitchell@ssl.berkeley.edu RI connerney, john/I-5127-2013; Lillis, Robert/A-3281-2008; OI Lillis, Robert/0000-0003-0578-517X; connerney, jack/0000-0001-7478-6462 NR 37 TC 33 Z9 34 U1 0 U2 6 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 JAN 9 PY 2007 VL 112 IS E1 AR E01002 DI 10.1029/2005JE002564 PG 9 WC Geochemistry & Geophysics SC Geochemistry & Geophysics GA 126QY UT WOS:000243531100001 ER PT J AU Sprague, AL Boynton, WV Kerry, KE Janes, DM Kelly, NJ Crombie, MK Nelli, SM Murphy, JR Reedy, RC Metzger, AE AF Sprague, Ann L. Boynton, William V. Kerry, Kris E. Janes, Daniel M. Kelly, Nora J. Crombie, M. Katherine Nelli, Steven M. Murphy, James R. Reedy, Robert C. Metzger, Albert E. TI Mars' atmospheric argon: Tracer for understanding Martian atmospheric circulation and dynamics SO JOURNAL OF GEOPHYSICAL RESEARCH-PLANETS LA English DT Article ID STATIONARY PLANETARY-WAVES; TES NADIR DATA; GENERAL-CIRCULATION; POLAR CAPS; MGS TES; NUMERICAL-SIMULATION; MODEL SIMULATIONS; TRAVELING-WAVES; NEAR-SURFACE; ODYSSEY AB One and one half Mars years, from 8 June 2002 to 2 April 2005, of atmospheric argon (Ar) measurements are described and studied in the context of understanding how Ar, a minor constituent of the Martian atmosphere that does not condense at temperatures found on Mars, can be used to study Martian circulation and dynamics. The Ar data are from the gamma subsystem of the gamma ray spectrometer currently operating on the Mars Odyssey spacecraft in orbit around Mars. A comprehensive data analysis including g ray production and attenuation by the atmosphere is presented. Four discoveries are discussed. (1) There is a factor of 6 enhancement of Ar measured over south polar latitudes (75 degrees S to 90 degrees S) for 2 consecutive Mars years occurring near the onset of southern winter. (2) There is no similar strong enhancement of Ar over north polar regions during northern winter. Part of this difference is explained by the global topographic dichotomy and the fact that the duration of northern autumn and winter is only similar to 80% as long as that of southern autumn and winter. (3) Rapid seasonal fluctuations in Ar abundance from 60 degrees S to 90 degrees S may be evidence for wave activity at the perimeter of the southern seasonal polar cap. (4) The magnitude of the Ar enhancement over the south polar region lacks spatial coincidence with either the relatively dark "cryptic terrain'' or the relatively bright albedo regions; however, a divergence in Ar abundance near L-s=267.5 degrees may be an expression of later CO2 sublimation in the bright terrain rather than in the cryptic region. C1 Univ Arizona, Lunar & Planetary Lab, Tucson, AZ 85721 USA. New Mexico State Univ, Dept Astron, Las Cruces, NM 88003 USA. Univ New Mexico, Inst Meteorit, Albuquerque, NM 87131 USA. CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Sprague, AL (reprint author), Univ Arizona, Lunar & Planetary Lab, Tucson, AZ 85721 USA. EM sprague@lpl.arizona.edu; wboynton@lpl.arizona.edu; krisk@lpl.arizona.edu; buck@lpl.arizona; nkelly@lpl.arizona.edu; mkcrombie@lpl.arizona.edu; snelli@nmsu.edu; murphy@nmsu.edu; rreedy@unm.edu; albert.e.metzger@jpl.nasa.gov NR 52 TC 13 Z9 13 U1 0 U2 3 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 JAN 9 PY 2007 VL 112 IS E3 AR E03S02 DI 10.1029/2005JE002597 PG 15 WC Geochemistry & Geophysics SC Geochemistry & Geophysics GA 126RB UT WOS:000243531400001 ER PT J AU Omidi, N Sibeck, DG AF Omidi, N. Sibeck, D. G. TI Formation of hot flow anomalies and solitary shocks SO JOURNAL OF GEOPHYSICAL RESEARCH-SPACE PHYSICS LA English DT Article ID EARTHS BOW SHOCK; DIAMAGNETIC CAVITIES UPSTREAM; PERPENDICULAR SHOCKS; OBSERVATIONAL TEST; COLLISIONLESS; SIMULATIONS; DISCONTINUITY; REFORMATION; WIND AB Interaction of a tangential discontinuity (TD) with the bow shock is investigated by using electromagnetic, global hybrid simulations in which ions are treated kinetically via particle-in-cell methods and electrons form a massless fluid. On the basis of previous studies, it was expected that the interaction would result in the formation of a hot flow anomaly (HFA) propagating along the curved bow shock surface. The results are unexpected in two major ways. First, the hot flow anomaly is only formed during the interaction of the TD with the quasi-parallel side of the bow shock. The lack of a HFA on the perpendicular side is due to the inability of a large fraction of ions to escape into the solar wind, as is required for an HFA to form. Second, the interaction of the TD with the quasi-perpendicular portion of the bow shock results in a previously unknown, shock structure which we name the "solitary shock." The solitary shock consists of a finite width (a few ion inertial length), fast magnetosonic shock-like structure followed by a relatively less compressed, more turbulent plasma with complex and spatially varying properties in the downstream region. We have determined that the formation of the solitary shock after the passage of the TD is due to the new direction of the interplanetary magnetic field. Further, this is not a transitory phenomena and when the interplanetary magnetic field cone angle is large (similar to > 50 degrees) a significant portion of the bow shock surface is affected. Solitary shocks form in the regions where the motional electric field in the magnetosheath points away from the shock. We demonstrate that solitary shocks differ from regular quasi-perpendicular shocks due to differences in ion dissipation processes. We also present the results of a detailed survey of the effects of simulation parameters such as cell size, resistivity, system size, and 2.5-dimensional versus three-dimensional domains on the solitary shock solutions. C1 Solana Sci Inc, Solana Beach, CA 82075 USA. NASA Goddard Space Flight Ctr, Greenbelt, MA USA. RP Omidi, N (reprint author), Solana Sci Inc, 777 S Pacific Coast Highway,Suite 208B, Solana Beach, CA 82075 USA. EM omidi@solanasci.com RI Sibeck, David/D-4424-2012 NR 31 TC 46 Z9 47 U1 1 U2 3 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 JAN 6 PY 2007 VL 112 IS A1 AR A01203 DI 10.1029/2006JA011663 PG 15 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA 124FJ UT WOS:000243352700001 ER PT J AU Crippen, RE Hook, SJ Fielding, EJ AF Crippen, Robert E. Hook, Simon J. Fielding, Eric J. TI Nighttime ASTER thermal imagery as an elevation surrogate for filling SRTM DEM voids SO GEOPHYSICAL RESEARCH LETTERS LA English DT Article ID REFLECTION RADIOMETER ASTER; EMISSION AB The Shuttle Radar Topographic Mission (SRTM) produced digital elevation models (DEMs) of most of Earth's land surface, but the radar observational geometry resulted in data voids in areas of high relief. Here we test the derivation of elevation from Advanced Spaceborne Thermal Emission and Reflection Radiometer ( ASTER) nighttime thermal data for the purpose of filling these voids. The method uses the general linear relationship between temperature and altitude as described by the environmental lapse rate. The results for the test area are generally superior to void filling by interpolation, particularly where voids cross ridges or canyons. Errors associated with the approach are identified along with potential improvements. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Crippen, RE (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM robert.e.crippen@jpl.nasa.gov RI Fielding, Eric/A-1288-2007 OI Fielding, Eric/0000-0002-6648-8067 NR 7 TC 7 Z9 7 U1 0 U2 0 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 JAN 4 PY 2007 VL 34 IS 1 AR L01302 DI 10.1029/2006GL028496 PG 5 WC Geosciences, Multidisciplinary SC Geology GA 124ET UT WOS:000243351000008 ER PT J AU Yu, Z Shen, S McCreary, JP Yaremchuk, M Furue, R AF Yu, Z. Shen, S. McCreary, J. P. Yaremchuk, M. Furue, R. TI South China Sea throughflow as evidenced by satellite images and numerical experiments SO GEOPHYSICAL RESEARCH LETTERS LA English DT Article ID WINTER PHYTOPLANKTON BLOOMS; LUZON STRAIT; INTERANNUAL VARIABILITY; INDIAN-OCEAN; MIXED-LAYER; KUROSHIO; PACIFIC; CIRCULATION; PHILIPPINE; INTRUSION AB The South China Sea throughflow begins at the Luzon Strait, as an intrusion of the Kuroshio. At the present time, there are insufficient in situ measurements either to estimate accurately the transport loss or to provide a clear picture of the Kuroshio pathway at the Luzon Strait. In this study, we use newly available, multi-year, high-resolution satellite images and a numerical model to track the warm, relatively low-biomass, Pacific water carried by the Kuroshio. A suite of numerical experiments are carried out to identify key factors that influence Kuroshio paths at the Luzon Strait. The model can reproduce the satellite-inferred Kuroshio paths across the Luzon Strait only when a significant amount of the Kuroshio water is allowed to enter the Luzon Strait during December - February, therefore providing strong evidence for the existence of the South China Sea throughflow. C1 Univ Hawaii, Sch Ocean & Earth Sci & Technol, Int Pacific Res Ctr, Honolulu, HI 96822 USA. George Mason Univ, Greenbelt, MD 20771 USA. NASA, Goddard Earth Sci Data & Informat Serv Ctr, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Yu, Z (reprint author), Univ Hawaii, Sch Ocean & Earth Sci & Technol, Int Pacific Res Ctr, 1680 East West Rd, Honolulu, HI 96822 USA. EM zuojun@hawaii.edu NR 36 TC 35 Z9 38 U1 1 U2 8 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 JAN 4 PY 2007 VL 34 IS 1 AR L01601 DI 10.1029/2006GL028103 PG 6 WC Geosciences, Multidisciplinary SC Geology GA 124ET UT WOS:000243351000002 ER PT J AU Felder, M Poli, P Joiner, J AF Felder, Martin Poli, Paul Joiner, Joanna TI Errors induced by ozone field horizontal inhomogeneities into simulated nadir-viewing orbital backscatter UV measurements SO JOURNAL OF GEOPHYSICAL RESEARCH-ATMOSPHERES LA English DT Article ID OCCULTATION OBSERVATION OPERATORS; DATA ASSIMILATION SYSTEM; GRADIENTS AB Radiative transfer calculations for nadir-viewing satellites normally assume the atmosphere to be horizontally homogeneous. Yet it has been shown recently that horizontal gradients can lead to significant errors in satellite infrared and microwave soundings. We extend the methodology to nadir backscatter ultraviolet forward modeling and present a first estimate of the effect's magnitude. The Solar Backscatter Ultraviolet/2 (SBUV/2) instrument, a nadir sounder, serves as our test bed. We find that the RMS error in calculated SBUV radiance induced by ozone inhomogeneities ranges between 0.05 and 0.3% (0.1 - 0.5%) for the 318 nm (306 and 313 nm) channel. The lower (higher) estimate corresponds to soundings with small (high) solar zenith angle. Occurrence of higher errors, particularly at wavelengths longer than 300 nm, coincides with some of the most interesting atmospheric phenomena like tropopause folds and the south polar ozone hole. This leads to a seasonal variation of the magnitude of the effect. Because of the mostly zonal variability of the ozone distribution, there is also the possibility that biases may be introduced, which is particularly critical if the data are to be assimilated or used to determine trends. The results presented are tested for robustness using different model atmospheres. C1 NASA, Goddard Space Flight Ctr, Atmospheres Lab, Greenbelt, MD 20771 USA. Ctr Natl Rech Meteorol, Toulouse, France. RP Felder, M (reprint author), Leibniz Comp Ctr, Garching, Germany. EM felder@lrz.de; paul.poli@meteo.fr; joanna.joiner@nasa.gov RI Joiner, Joanna/D-6264-2012; OI Poli, Paul/0000-0002-8392-6524 NR 18 TC 0 Z9 0 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 JAN 4 PY 2007 VL 112 IS D1 AR D01303 DI 10.1029/2005JD006769 PG 10 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA 124FE UT WOS:000243352100001 ER PT J AU Saunders, R Rayer, P Brunel, P von Engeln, A Bormann, N Strow, L Hannon, S Heilliette, S Liu, X Miskolczi, F Han, Y Masiello, G Moncet, JL Uymin, G Sherlock, V Turner, DS AF Saunders, R. Rayer, P. Brunel, P. von Engeln, A. Bormann, N. Strow, L. Hannon, S. Heilliette, S. Liu, Xu Miskolczi, F. Han, Y. Masiello, G. Moncet, J. -L. Uymin, Gennady Sherlock, V. Turner, D. S. TI A comparison of radiative transfer models for simulating Atmospheric Infrared Sounder (AIRS) radiances SO JOURNAL OF GEOPHYSICAL RESEARCH-ATMOSPHERES LA English DT Article ID ASSIMILATION; TRANSMITTANCES; COMPUTATION AB A comparison of radiative transfer models for simulating radiances from the Atmospheric Infrared Sounder (AIRS), has been undertaken. Results from 14 line-by-line and fast parameterized infrared models were submitted. Several aspects of the models were compared. First, the forward model calculations for all 2378 AIRS channels for 52 diverse atmospheric profiles and one tropical Pacific profile coincident with AIRS data were performed for three local zenith viewing angles: nadir, 45, and 60 degrees. Second, for a subset of the models and only 20 AIRS channels the transmittances from each layer to space were provided. Finally, for some models the Jacobians with respect to temperature, water vapor, and ozone were also computed. For the forward model calculations, most models agree to within 0.02 K when compared to a reference line-by-line model averaged over a subset of profiles, with the exception of a few spectral regions. When compared with AIRS observations, however, the mean differences increase to 0.2 K, and for a few models even greater differences are seen. The transmittance differences highlighted regions of the spectrum where the spectroscopy of the models differs, particularly in the carbon dioxide absorption bands at 667 cm(-1) and 2386 cm(-1). For the Jacobians all models have some profiles/channels that do not fit the reference well, and the main problems are documented here. The model differences only increase slightly for off-nadir viewing angles for both forward and Jacobian calculations. C1 Met Off, Exeter EX1 3PB, Devon, England. CMS, MeteoFrance, F-22302 Lannion, France. Univ Bremen, Inst Environm Phys, D-28334 Bremen, Germany. European Ctr Medium Range Weather Forecasts, Reading RG2 9AX, Berks, England. Univ Maryland Baltimore Cty, Dept Phys, Baltimore, MD 21250 USA. CNRS, Meteorol Dynam Lab, F-91128 Palaiseau, France. NASA, Langley Res Ctr, Hampton, VA 23681 USA. NESDIS, NOAA, Camp Springs, MD 20746 USA. CNR, IMAA, I-85050 Potenza, Italy. Atmospher & Environm Res Inc, Lexington, MA 02421 USA. Natl Inst Water & Atmospher Res, Wellington, New Zealand. Met Serv Canada, Downsview, ON, Canada. RP Saunders, R (reprint author), Met Off, Exeter EX1 3PB, Devon, England. RI Han, Yong/F-5590-2010; Masiello, Guido/I-6459-2015 OI Han, Yong/0000-0002-0183-7270; Masiello, Guido/0000-0002-7986-8296 NR 27 TC 35 Z9 36 U1 1 U2 8 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 JAN 4 PY 2007 VL 112 IS D1 AR D01S90 DI 10.1029/2006JD007088 PG 17 WC Meteorology & Atmospheric Sciences SC Meteorology & Atmospheric Sciences GA 124FE UT WOS:000243352100002 ER PT J AU Sotin, C AF Sotin, Christophe TI Planetary science - Titan's lost seas found SO NATURE LA English DT Editorial Material ID SURFACE C1 Univ Nantes, Lab Planetol & Geodynam, F-44322 Nantes 3, France. RP Sotin, C (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. EM christophe.sotin@univ-nantes.fr NR 6 TC 8 Z9 9 U1 0 U2 1 PU NATURE PUBLISHING GROUP PI LONDON PA MACMILLAN BUILDING, 4 CRINAN ST, LONDON N1 9XW, ENGLAND SN 0028-0836 J9 NATURE JI Nature PD JAN 4 PY 2007 VL 445 IS 7123 BP 29 EP 30 DI 10.1038/445029a PG 2 WC Multidisciplinary Sciences SC Science & Technology - Other Topics GA 122KG UT WOS:000243225100021 PM 17203046 ER PT J AU Stofan, ER Elachi, C Lunine, JI Lorenz, RD Stiles, B Mitchell, KL Ostro, S Soderblom, L Wood, C Zebker, H Wall, S Janssen, M Kirk, R Lopes, R Paganelli, F Radebaugh, J Wye, L Anderson, Y Allison, M Boehmer, R Callahan, P Encrenaz, P Flamini, E Francescetti, G Gim, Y Hamilton, G Hensley, S Johnson, WTK Kelleher, K Muhleman, D Paillou, P Picardi, G Posa, F Roth, L Seu, R Shaffer, S Vetrella, S West, R AF Stofan, E. R. Elachi, C. Lunine, J. I. Lorenz, R. D. Stiles, B. Mitchell, K. L. Ostro, S. Soderblom, L. Wood, C. Zebker, H. Wall, S. Janssen, M. Kirk, R. Lopes, R. Paganelli, F. Radebaugh, J. Wye, L. Anderson, Y. Allison, M. Boehmer, R. Callahan, P. Encrenaz, P. Flamini, E. Francescetti, G. Gim, Y. Hamilton, G. Hensley, S. Johnson, W. T. K. Kelleher, K. Muhleman, D. Paillou, P. Picardi, G. Posa, F. Roth, L. Seu, R. Shaffer, S. Vetrella, S. West, R. TI The lakes of Titan SO NATURE LA English DT Article ID RADAR MAPPER; METHANE; SURFACE; CLOUDS AB The surface of Saturn's haze-shrouded moon Titan has long been proposed to have oceans or lakes, on the basis of the stability of liquid methane at the surface(1,2). Initial visible(3) and radar(4,5) imaging failed to find any evidence of an ocean, although abundant evidence was found that flowing liquids have existed on the surface(5,6). Here we provide definitive evidence for the presence of lakes on the surface of Titan, obtained during the Cassini Radar flyby of Titan on 22 July 2006 (T-16). The radar imaging polewards of 70 degrees north shows more than 75 circular to irregular radar-dark patches, in a region where liquid methane and ethane are expected to be abundant and stable on the surface(2,7). The radar-dark patches are interpreted as lakes on the basis of their very low radar reflectivity and morphological similarities to lakes, including associated channels and location in topographic depressions. Some of the lakes do not completely fill the depressions in which they lie, and apparently dry depressions are present. We interpret this to indicate that lakes are present in a number of states, including partly dry and liquid-filled. These northern-hemisphere lakes constitute the strongest evidence yet that a condensable-liquid hydrological cycle is active in Titan's surface and atmosphere, in which the lakes are filled through rainfall and/or intersection with the subsurface 'liquid methane' table. C1 Proxemy Res, Rectortown, VA 20140 USA. UCL, Dept Earth Sci, London WC1E 6BT, England. CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. Univ Arizona, Lunar & Planetary Lab, Tucson, AZ 85721 USA. Johns Hopkins Univ, Appl Phys Lab, Space Dept, Laurel, MD 20723 USA. US Geol Survey, Flagstaff, AZ 86001 USA. Wheeling Jesuit Univ, Tucson, AZ 85719 USA. Planetary Sci Inst, Tucson, AZ 85719 USA. Stanford Univ, Stanford, CA 94305 USA. NASA, Goddard Inst Space Studies, New York, NY 10025 USA. Observ Paris, F-92195 Meudon, France. Alenia Aerospazio, I-00131 Rome, Italy. Fac Ingn, I-80125 Naples, Italy. CALTECH, Div Geol & Planetary Sci, Pasadena, CA 91125 USA. Observ Aquitain Sci Univers UMR 5804, F-33270 Floirac, France. Univ Roma La Sapienza, I-00184 Rome, Italy. Politecn Bari, Dipartimento Interateneo Fis, I-70126 Bari, Italy. RP Stofan, ER (reprint author), Proxemy Res, Rectortown, VA 20140 USA. EM estofan@proxemy.com RI Lorenz, Ralph/B-8759-2016; Lopes, Rosaly/D-1608-2016 OI Lorenz, Ralph/0000-0001-8528-4644; Lopes, Rosaly/0000-0002-7928-3167 NR 27 TC 279 Z9 286 U1 7 U2 56 PU NATURE PUBLISHING GROUP PI LONDON PA MACMILLAN BUILDING, 4 CRINAN ST, LONDON N1 9XW, ENGLAND SN 0028-0836 EI 1476-4687 J9 NATURE JI Nature PD JAN 4 PY 2007 VL 445 IS 7123 BP 61 EP 64 DI 10.1038/nature05438 PG 4 WC Multidisciplinary Sciences SC Science & Technology - Other Topics GA 122KG UT WOS:000243225100035 PM 17203056 ER PT J AU Gasso, S Stein, AF AF Gasso, Santiago Stein, Ariel F. TI Does dust from Patagonia reach the sub-Antarctic Atlantic ocean? SO GEOPHYSICAL RESEARCH LETTERS LA English DT Article ID SOUTHERN-OCEAN; IRON; ARGENTINA; AEROSOLS; CLIMATE; CYCLES; SYSTEM; MODIS AB Although emission of dust from the Patagonia desert is shown by global aerosol models, there is conflicting observational evidence of dust activity in the region. Because dust from Patagonia into the Southern Ocean ( SO) may play a role in regulating phytoplankton activity, it is necessary to confirm whether there is dust activity and if so, how far the dust travels into the SO. We used a combination of surface visibility, satellite measurements ( MODIS and OMI) and transport model (HYSPLIT) to track and report for the first time a dust event originating in Patagonia. We show that the dust reached the free troposphere in the Sub-Antarctic Atlantic Ocean. Although the dust emission was significant, cloudiness and dilution of the plume resulted in difficult conditions to track dust in the SW Atlantic. We show that the use of any single tool (i.e., MODIS or OMI) is not enough to track the dust and only an integrated approach of satellite and modeling tools can achieve a consistent description. As a result, current platforms used for dust detection are probably underestimating aerosol loading in the area. C1 Univ Maryland Baltimore Cty, Goddard Earth Sci & Technol Ctr, Baltimore, MD 21228 USA. Earth Resources & Technol, Jessup, MD USA. RP Gasso, S (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. EM santiago@climate.gsfc.nasa.gov RI Stein, Ariel/G-1330-2012; Stein, Ariel F/L-9724-2014; Gasso, Santiago/H-9571-2014 OI Stein, Ariel F/0000-0002-9560-9198; Gasso, Santiago/0000-0002-6872-0018 NR 21 TC 58 Z9 58 U1 0 U2 11 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 JAN 3 PY 2007 VL 34 IS 1 AR L01801 DI 10.1029/2006GL027693 PG 5 WC Geosciences, Multidisciplinary SC Geology GA 124ER UT WOS:000243350800003 ER PT S AU Eberspeaker, PJ Gregory, DD AF Eberspeaker, P. J. Gregory, D. D. GP ESA BE Conroy, L TI An overview of the NASA Sounding Rockets and Balloon Programs SO 18TH ESA SYMPOSIUM ON EUROPEAN ROCKET AND BALLOON PROGRAMMES AND RELATED RESEARCH SE ESA Special Publications LA English DT Proceedings Paper CT 18th ESA Symposium on European Rocket and Balloon Programmes and Related Research CY JUN 03-07, 2007 CL Visby, SWEDEN SP European Space Agcy AB The U. S. National Aeronautics and Space Administration (NASA) Sounding Rockets and Balloon Programs conduct a total of 40 to 50 missions per year in support of the NASA scientific community and other users. The NASA Sounding Rockets Program supports the science community by integrating their experiments into the sounding rocket payload, and providing both the rocket vehicle and launch operations services. Activities since 2005 have included operations from White Sands Missile Range and a major campaign from Poker Flat Research Range in Alaska. Technology efforts have included enhancement of the SAAB S-19 Boost Guidance System, development of new inertial and celestial attitude control systems, and the development of new vehicle systems to support the evolving requirements of the user community. The NASA Balloon Program supported multi-disciplinary space science missions in 2006 with flights from the U.S., Sweden, and Antarctica. A record setting number of heavy-lift Long Duration Balloon (LDB) missions were flown with two flights from Sweden to Canada and three LDB missions launched in Antarctica. NASA exercised a test flight of the Ultra Long Duration Balloon (ULDB) launched from Esrange in June 2006. NASA continues with enhancements for balloon missions with development of the ULDB for 60-100 day missions as well as development of enhanced flight support systems. An overview of the various aspects of the NASA Sounding Rocket and Balloon Programs will be presented as well as the outlook for the future. C1 [Eberspeaker, P. J.; Gregory, D. D.] NASA, Goddard Space Flight Ctr, Wallops Flight Facil, Wallops Isl, VA 23337 USA. RP Eberspeaker, PJ (reprint author), NASA, Goddard Space Flight Ctr, Wallops Flight Facil, Wallops Isl, VA 23337 USA. NR 1 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 J9 ESA SPEC PUBL PY 2007 VL 647 BP 25 EP 32 PG 8 WC Engineering, Aerospace; Astronomy & Astrophysics; Remote Sensing SC Engineering; Astronomy & Astrophysics; Remote Sensing GA BHP94 UT WOS:000255234200005 ER PT S AU Jones, WV AF Jones, W. Vernon GP ESA BE Conroy, L TI Long-duration balloon experiments - An approach to solve future challenges with respect to astronomy and astrophysics SO 18TH ESA SYMPOSIUM ON EUROPEAN ROCKET AND BALLOON PROGRAMMES AND RELATED RESEARCH SE ESA Special Publications LA English DT Proceedings Paper CT 18th ESA Symposium on European Rocket and Balloon Programmes and Related Research CY JUN 03-07, 2007 CL Visby, SWEDEN SP European Space Agcy AB Scientific ballooning has enabled significant investigations from modest investments for several decades. Increasingly more sophisticated instruments have been used as longer flights became available. Some investigations have been competitive with space missions, while others have enabled orbital missions. In 2004 NASA chartered a Scientific Ballooning Planning Team to identify science objectives that have the greatest potential to contribute to NASA's strategic goals. The astronomy and astrophysics goals are driven primarily by a series of decadal surveys conducted with oversight by the National Academy of Sciences. This report focuses on those challenges that can be met at least in part by ballooning. C1 NASA, Headquarters Sci Mission Directorate, Div Astrophys, Washington, DC 20546 USA. RP Jones, WV (reprint author), NASA, Headquarters Sci Mission Directorate, Div Astrophys, Washington, DC 20546 USA. EM w.vernon.jones@nasa.gov 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 J9 ESA SPEC PUBL PY 2007 VL 647 BP 73 EP 80 PG 8 WC Engineering, Aerospace; Astronomy & Astrophysics; Remote Sensing SC Engineering; Astronomy & Astrophysics; Remote Sensing GA BHP94 UT WOS:000255234200011 ER PT S AU Schmidlin, FJ Morrison, B Baldwin, T Moore, P Northam, ET AF Schmidlin, F. J. Morrison, B. Baldwin, T. Moore, P. Northam, E. T. GP ESA BE Conroy, L TI The NASA African Monsoon Multidisciplinary Analyses mission: Balloon-borne radiosonde results from Cape Verde SO 18TH ESA SYMPOSIUM ON EUROPEAN ROCKET AND BALLOON PROGRAMMES AND RELATED RESEARCH SE ESA Special Publications LA English DT Proceedings Paper CT 18th ESA Symposium on European Rocket and Balloon Programmes and Related Research CY JUN 03-07, 2007 CL Visby, SWEDEN SP European Space Agcy ID DISTURBANCES AB Easterly waves that may develop into damaging hurricanes as they move westward over the southern Atlantic Ocean was the subject of the research mission that occurred between 15 August 2006 and 14 September 2006. Easterly wave and tropical convective activity interacting near the Intertropical Convergence Zone (ITCZ) can trigger the formation of damaging tropical cyclones. Balloon-borne radiosondes were released as part of the NASA African Monsoon Multidisciplinary Analyses (NAMMA) mission, a component of the multi-national mission, to study West African-originating easterly wave activity. Balloon-borne radiosondes with Global Positioning System (GPS) capability were released every 4 hours from Praia, Cape Verde Islands to obtain 4-D position information (time, altitude, latitude, and longitude). High-resolution measurements of temperature, relative humidity, and wind at a vertical resolution of 4-6 meters effectively captured significant temporal features of convective and easterly wave activity. We present time series of selected meteorological parameters covering the 30-day campaign period. Interaction of the Saharan Aerosol Layer (SAL), the mid-level easterly jet, and at least seven easterly wave passages at Praia is discussed. These data are an important part of the overall measurement mission and contribute to understanding the morphology of easterly wave development, movement, and their sustainment. C1 [Schmidlin, F. J.; Morrison, B.; Baldwin, T.; Moore, P.; Northam, E. T.] NASA, Goddard Space Flight Ctr, Wallops Isl, VA 23337 USA. RP Schmidlin, FJ (reprint author), NASA, Goddard Space Flight Ctr, Wallops Isl, VA 23337 USA. EM fjs@osb.wff.nasa.gov 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 J9 ESA SPEC PUBL PY 2007 VL 647 BP 161 EP 162 PG 2 WC Engineering, Aerospace; Astronomy & Astrophysics; Remote Sensing SC Engineering; Astronomy & Astrophysics; Remote Sensing GA BHP94 UT WOS:000255234200024 ER PT S AU Goldberg, RA Feofilov, AG Kutepov, AA Pesnell, WD Schmidlin, FJ AF Goldberg, Richard A. Feofilov, Artem G. Kutepov, Alexander A. Pesnell, W. Dean Schmidlin, F. J. GP ESA BE Conroy, L TI Re-evaluation of SABER temperatures triggered by comparison with MaCWAVE MET rocket measurements SO 18TH ESA SYMPOSIUM ON EUROPEAN ROCKET AND BALLOON PROGRAMMES AND RELATED RESEARCH SE ESA Special Publications LA English DT Proceedings Paper CT 18th ESA Symposium on European Rocket and Balloon Programmes and Related Research CY JUN 03-07, 2007 CL Visby, SWEDEN SP European Space Agcy ID MESOSPHERE AB Sequences of MET rockets launched from Andoya Rocket Range during the MaCWAVE/MIDAS Program in July 2002 were used to evaluate the meteorology of the mesosphere/lower thermosphere (MLT) region (5590 km). Two of the failing sphere flights were coordinated with TIMED Satellite overflights, particularly when the SABER IR radiometer tangent point was near 85 km, to help validate SABER temperatures. The observed discrepancies between the temperature profiles produced by each technique indicated a need to refine the SABER algorithms used to derive temperature, mainly in the polar summer mesosphere. Further study of this discrepancy has established the importance of the large non-local thermal equilibrium effects (NLTE) affecting this region, primarily because of its cold temperatures and large temperature gradients. Finally, after also accounting for the redistribution of v(2) quanta among various CO(2) isotopes, the retrieved summer polar mesopause altitudes moved upward by 2 - 4 km, in better agreement with both the falling sphere measurements and climatological models of this region. Review of these measurements and results is used to demonstrate the high value of inter-comparisons between satellite remote sensing measurements and ground truth provided by various techniques including coordinated rocket underflights. C1 [Goldberg, Richard A.; Kutepov, Alexander A.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Goldberg, RA (reprint author), NASA, Goddard Space Flight Ctr, Code 674, Greenbelt, MD 20771 USA. EM richard.a.goldberg@nasa.gov RI Pesnell, William/D-1062-2012; Goldberg, Richard /E-1881-2012; Feofilov, Artem/A-2271-2015 OI Pesnell, William/0000-0002-8306-2500; Feofilov, Artem/0000-0001-9924-4846 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 J9 ESA SPEC PUBL PY 2007 VL 647 BP 297 EP 300 PG 4 WC Engineering, Aerospace; Astronomy & Astrophysics; Remote Sensing SC Engineering; Astronomy & Astrophysics; Remote Sensing GA BHP94 UT WOS:000255234200047 ER PT S AU Jones, WV Pierce, D Gregory, D Said, M Fairbrother, D Stuchlik, D Thompson, L Estep, R Merritt, B Cathey, H Garde, G Young, L AF Jones, W. V. Pierce, D. Gregory, D. Said, M. Fairbrother, D. Stuchlik, D. Thompson, L. Estep, R. Merritt, B. Cathey, H. Garde, G. Young, L. GP ESA BE Conroy, L TI An overview of the capabilities of the NASA balloon program in support of earth and space science investigations SO 18TH ESA SYMPOSIUM ON EUROPEAN ROCKET AND BALLOON PROGRAMMES AND RELATED RESEARCH SE ESA Special Publications LA English DT Proceedings Paper CT 18th ESA Symposium on European Rocket and Balloon Programmes and Related Research CY JUN 03-07, 2007 CL Visby, SWEDEN SP European Space Agcy AB The NASA Balloon Program is committed to meeting the challenges of the science community to enable extended duration and global scientific investigations based on the development of advanced balloon vehicles and support systems. Recently, the Swedish Space Corporation/Esrange and the National Aeronautics and Space Administration (NASA) have inaugurated a joint European / U.S. capability for medium-duration heavyload scientific balloon flights from Sweden to Canada or Alaska. This new capability complements the NASA / U.S. National Science Foundation Office of Polar Programs achievement of more than a decade of successful long-duration flights around Antarctica. This paper will highlight the recent campaigns conducted from Sweden and Antarctica as well as recent technology efforts in support of terrestrial and planetary missions. C1 [Jones, W. V.] NASA Headquarters, Sci Miss Directorate, Washington, DC 20546 USA. RP Jones, WV (reprint author), NASA Headquarters, Sci Miss Directorate, Washington, DC 20546 USA. EM w.vernon.jones@nasa.gov; David.L.Pierce@nasa.gov; Henry.M.Cathey.1@gsfc.nasa.gov NR 6 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 J9 ESA SPEC PUBL PY 2007 VL 647 BP 553 EP 556 PG 4 WC Engineering, Aerospace; Astronomy & Astrophysics; Remote Sensing SC Engineering; Astronomy & Astrophysics; Remote Sensing GA BHP94 UT WOS:000255234200093 ER PT S AU Swain, M AF Swain, M. BE Epchtein, N Candidi, M TI Modeling results and implications for astronomy at Dome C SO 1st ARENA Conference on Large Astronomical Infrastructures at CONCORDIA, Prospects and Constraints for Antarctic Optical/IR Astronomy SE EAS PUBLICATIONS SERIES LA English DT Proceedings Paper CT 1st ARENA Conference on Large Astronomical Infrastructures at CONCORDIA, Prospects and Constraints for Antarctic Optical/ IR Astronomy CY OCT 16-19, 2006 CL Roscoff, FRANCE SP ARENA Coodinated Action European Commiss ID ANTARCTIC PLATEAU; SOUTH-POLE AB Modeling of astronomically important atmospheric parameters, and the impact these parameters have on instrument performance, is a powerful tool for assessing the astronomical potential of Antarctic sites. This paper summarizes some of the significant findings from a combination of regional climate modeling and adaptive optics simulations. Together with estimates of the sky background, this work strongly implies that the unique astronomical potential of Dome C work that can be done at no other location - is high angular resolution science. In particular, the simulations show that diffraction limited resolution in the optical is possible with a modest AO system deployed on a telescope mounted above the Antarctic boundary layer. This potential strongly differentiates Dome C from other sites and suggests a tower-mounted, AO equipped, similar to 2.5 m class telescope, located at Dome C, could be the premier visible imaging observatory in the post-HST era. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Swain, M (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 17 TC 0 Z9 0 U1 0 U2 0 PU E D P SCIENCES PI CEDEX A PA 17 AVE DU HOGGAR PARC D ACTIVITES COUTABOEUF BP 112, F-91944 CEDEX A, FRANCE SN 1633-4760 BN 978-2-7598-0017-9 J9 EAS PUBLICATIONS PY 2007 VL 25 BP 43 EP 48 DI 10.1051/eas:2007070 PG 6 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BGN51 UT WOS:000248621600008 ER PT B AU Schairer, ET Heineck, JT AF Schairer, E. T. Heineck, J. T. GP IEEE TI Photogrammetric Recession Measurements of ablative materials in the NASA Ames sixty-megawatt arcjet SO 2007 22ND INTERNATIONAL CONGRESS ON INSTRUMENTATION IN AEROSPACE SIMULATION FACILITIES LA English DT Proceedings Paper CT 22nd International Congress on Instrumentation in Aerospace Simulation Facilities CY JUN 10-14, 2007 CL Pacific Grove, CA SP IEEE Aerosp, Elec Syst Soc, AIAA AB The Photogrammetric Recession Measurement (PRM) technique has been applied in several tests of ablative thermal-protection system materials in the 60-MW arcjet at NASA Ames Research Center. This paper presents selected results from those tests to illustrate the capabilities and limitations of the technique. C1 [Schairer, E. T.; Heineck, J. T.] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Schairer, ET (reprint author), NASA, Ames Res Ctr, Mail Stop 260-1, Moffett Field, CA 94035 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 978-1-4244-1599-1 PY 2007 BP 15 EP 24 PG 10 WC Engineering, Aerospace; Engineering, Electrical & Electronic; Instruments & Instrumentation SC Engineering; Instruments & Instrumentation GA BHD70 UT WOS:000252358500003 ER PT B AU Wernet, MP AF Wernet, Mark P. GP IEEE TI Time-resolved PIV for space-time correlations in hot jets SO 2007 22ND INTERNATIONAL CONGRESS ON INSTRUMENTATION IN AEROSPACE SIMULATION FACILITIES LA English DT Proceedings Paper CT 22nd International Congress on Instrumentation in Aerospace Simulation Facilities CY JUN 10-14, 2007 CL Pacific Grove, CA SP IEEE Aerosp, Elec Syst Soc, AIAA ID PARTICLE IMAGE VELOCIMETRY AB Temporally Resolved Particle Image Velocimetry (TR-PIV) is being used to characterize the decay of turbulence in jet flows - a critical element for understanding the acoustic properties of the flow. A TR-PIV system, developed in-house at the NASA Glenn Research Center, is capable of acquiring planar PIV image frame pairs at up to 10 kHz. The data reported here were collected at Mach numbers of 0.5 and 0.9 and at temperature ratios of 0.89 and 1.76. The field of view of the TR-PIV system covered 6 nozzle diameters along the lip line of the 50.8 mm diameter jet. The cold flow data at Mach 0.5 were compared with hotwire anemometry measurements in order to validate the new TR-PIV technique. The axial turbulence profiles measured across the shear layer using TR-PIV were thinner than those measured using hotwire anemometry and remained centered along the nozzle lip line. The collected TR-PIV data illustrate the differences in the single point statistical flow properties of cold and hot jet flows. The planar, time-resolved velocity records were then used to compute two-point space-time correlations of the flow at the Mach 0.9 flow condition. The TR-PIV results show that there are differences in the convective velocity and growth rate of the turbulent structures between cold and hot flows at the same Mach number. C1 NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Wernet, MP (reprint author), NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. NR 16 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-1599-1 PY 2007 BP 77 EP 87 PG 11 WC Engineering, Aerospace; Engineering, Electrical & Electronic; Instruments & Instrumentation SC Engineering; Instruments & Instrumentation GA BHD70 UT WOS:000252358500010 ER PT B AU Watkins, AN Leighty, BD Lipford, WE Wong, OD Oglesby, DM Ingram, JL AF Watkins, A. Neal Leighty, Bradley D. Lipford, William E. Wong, Oliver D. Oglesby, Donald M. Ingram, JoAnne L. GP IEEE TI Development of a Pressure Sensitive Paint system for measuring global surface pressures on rotorcraft blades SO 2007 22ND INTERNATIONAL CONGRESS ON INSTRUMENTATION IN AEROSPACE SIMULATION FACILITIES LA English DT Proceedings Paper CT 22nd International Congress on Instrumentation in Aerospace Simulation Facilities CY JUN 10-14, 2007 CL Pacific Grove, CA SP IEEE Aerosp, Elec Syst Soc, AIAA AB This paper will describe the results from a proof of concept test to examine the feasibility of using Pressure Sensitive Paint (PSP) to measure global surface pressures on rotorcraft blades in hover. The test was performed using the U.S. Army 2-meter Rotor Test Stand (2MRTS) and 15% scale swept rotor blades. Data were collected from five blades using both the intensity- and lifetime-based approaches. This paper will also outline several modifications and improvements that are underway to develop a system capable of measuring pressure distributions on up to four blades simultaneously at hover and forward flight conditions. C1 [Watkins, A. Neal; Leighty, Bradley D.; Lipford, William E.] NASA, Langley Res Ctr, Adv Sensing & Opt Measurement Branch, Hampton, VA 23681 USA. [Wong, Oliver D.] US Army, RDECOM, AMRDEC, Aeroflight Dynam Directorate, Hampton, VA 23681 USA. [Oglesby, Donald M.; Ingram, JoAnne L.] Swales Aerosp Inc, Hampton, VA 23681 USA. RP Watkins, AN (reprint author), NASA, Langley Res Ctr, Adv Sensing & Opt Measurement Branch, Hampton, VA 23681 USA. NR 17 TC 0 Z9 0 U1 1 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-1599-1 PY 2007 BP 134 EP + PG 4 WC Engineering, Aerospace; Engineering, Electrical & Electronic; Instruments & Instrumentation SC Engineering; Instruments & Instrumentation GA BHD70 UT WOS:000252358500016 ER PT B AU Bivolaru, D Lee, JW Jones, SB Tedder, S Danehy, PM Weikl, MC Magnotti, G Cutler, AD AF Bivolaru, D. Lee, J. W. Jones, S. B. Tedder, S. Danehy, P. M. Weikl, M. C. Magnotti, G. Cutler, A. D. GP IEEE TI Mobile CARS-IRS instrument for simultaneous spectroscopic measurement of multiple properties in gaseous flows SO 2007 22ND INTERNATIONAL CONGRESS ON INSTRUMENTATION IN AEROSPACE SIMULATION FACILITIES LA English DT Proceedings Paper CT 22nd International Congress on Instrumentation in Aerospace Simulation Facilities CY JUN 10-14, 2007 CL Pacific Grove, CA SP IEEE Aerosp, Elec Syst Soc, AIAA ID SUPERSONIC COMBUSTOR; LASER; MODELESS AB This paper describes a measurement system based on the dual-pump coherent anti-Stokes Raman spectroscopy (CARS) and interferometric Rayleigh scattering (IRS) methods. The IRS measurement is performed simultaneously with the CARS measurement using a common green laser beam as a narrow-band light source. The mobile CARS-IRS instrument is designed for the use both in laboratories as well as in ground-based combustion test facilities. Furthermore, it is designed to be easily transported between laboratory and test facility. It performs single-point spatially and temporally resolved simultaneous measurements of temperature, species mole fraction of N-2, O-2, and H-2, and two-components of velocity. A mobile laser system can be placed inside or outside the test facility, while a beam receiving and monitoring system is placed near the measurement location. Measurements in a laboratory small-scale Mach 1.6 H-2-air combustion-heated supersonic jet were performed to test the capability of the system. Final setup and pretests of a larger scale reacting jet are onaoing at NASA Langley Research Center's Direct Connect Supersonic Combustor Test Facility (DCSCTF). C1 [Bivolaru, D.; Lee, J. W.; Jones, S. B.; Tedder, S.; Danehy, P. M.] NASA, Langley Res Ctr, Hampton, VA 23681 USA. [Weikl, M. C.] Univ Erlangen Nurnberg, Erlangen, Germany. [Magnotti, G.; Cutler, A. D.] George Washington Univ, Newport News, VA 23602 USA. RP Bivolaru, D (reprint author), NASA, Langley Res Ctr, Hampton, VA 23681 USA. EM Daniel.Bivolaru-1@nasa.gov RI Weikl, Markus/C-6277-2008 FU NASA Fundamental Aeronautics Program - Hypersonics Project; Erlangen Graduate School in Advanced Optical Technologies (SAOT) FX This work was supported by the NASA Fundamental Aeronautics Program - Hypersonics Project, Experimental Capabilities and Propulsion Disciplines and Mr. George Rumford, program manager of the Defense Test Resource Management Center (DTRMC) Test and Evaluation/Science and Technology (T&E/S&T) program, under the Hypersonic Test focus area. Markus C. Weikl would like to thank the Erlangen Graduate School in Advanced Optical Technologies (SAOT) for financial support. NR 14 TC 0 Z9 0 U1 0 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-1599-1 PY 2007 BP 154 EP + PG 2 WC Engineering, Aerospace; Engineering, Electrical & Electronic; Instruments & Instrumentation SC Engineering; Instruments & Instrumentation GA BHD70 UT WOS:000252358500019 ER PT B AU Mielke, AF Elam, KA Sung, CJ AF Mielke, A. F. Elam, K. A. Sung, C. J. GP IEEE TI Development of a Rayleigh scattering diagnostic for time-resolved gas flow velocity, temperature, and density measurements in aerodynamic test facilities SO 2007 22ND INTERNATIONAL CONGRESS ON INSTRUMENTATION IN AEROSPACE SIMULATION FACILITIES LA English DT Proceedings Paper CT 22nd International Congress on Instrumentation in Aerospace Simulation Facilities CY JUN 10-14, 2007 CL Pacific Grove, CA SP IEEE Aerosp, Elec Syst Soc, AIAA ID BRILLOUIN-SCATTERING; LASER VELOCIMETER; SPECTRA AB A molecular Rayleigh scattering technique is developed to measure time-resolved gas velocity, temperature, and density in unseeded turbulent flows at sampling rates up to 32 kHz. A high power continuous-wave laser beam is focused at a point in an air flow field and Rayleigh scattered light is collected and fiber-optically transmitted to the spectral analysis and detection equipment. The spectrum of the light, which contains information about the temperature and velocity of the flow, is analyzed using a Fabry-Perot interferometer. Photomultipler tubes operated in the photon counting mode allow high frequency sampling of the circular interference pattern to provide time-resolved flow property measurements. An acoustically driven nozzle flow is studied to validate velocity fluctuation measurements, and an asymmetric oscillating counterflow with unequal enthalpies is studied to validate the measurement of temperature fluctuations. Velocity fluctuations are compared with constant temperature anemometry measurements and temperature fluctuations are compared with constant current anemometry measurements at the same locations. Time-series and power spectra of the temperature and velocity measurements are presented. A numerical simulation of the light scattering and detection process was developed and compared with experimental data for future use as an experiment design tool. C1 [Mielke, A. F.] NASA, Glenn Res Ctr, 21000 Brookpk Rd,MS 77-1, Cleveland, OH 44135 USA. [Elam, K. A.] Jacobs Sverdrup, Cleveland, OH 44135 USA. [Sung, C. J.] Case Western Reserve Univ, Cleveland, OH 44106 USA. RP Mielke, AF (reprint author), NASA, Glenn Res Ctr, 21000 Brookpk Rd,MS 77-1, Cleveland, OH 44135 USA. NR 28 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-1599-1 PY 2007 BP 163 EP + PG 2 WC Engineering, Aerospace; Engineering, Electrical & Electronic; Instruments & Instrumentation SC Engineering; Instruments & Instrumentation GA BHD70 UT WOS:000252358500020 ER PT B AU Schwartz, RJ Fleming, GA AF Schwartz, Richard J. Fleming, Gary A. GP IEEE TI Virtual diagnostics interface:Real time comparison of experimental data and CFD predictions for a NASA Ares I-Like vehicle SO 2007 22ND INTERNATIONAL CONGRESS ON INSTRUMENTATION IN AEROSPACE SIMULATION FACILITIES LA English DT Proceedings Paper CT 22nd International Congress on Instrumentation in Aerospace Simulation Facilities CY JUN 10-14, 2007 CL Pacific Grove, CA SP IEEE Aerosp, Elec Syst Soc, AIAA DE Virtual Diagnostics Interface; ViDI; real time data acquisition; data comparison AB Virtual Diagnostics Interface technology, or ViDI, is a suite of techniques utilizing image processing, data handling and three-dimensional computer graphics. These techniques aid in the design, implementation, and analysis of complex aerospace experiments. LiveView3D is a software application component of ViDI used to display experimental wind tunnel data in real-time within an interactive, three-dimensional virtual environment. The LiveView3D software application was under development at NASA Langley Research Center (LaRC) for nearly three years. LiveView3D recently was upgraded to perform real-time (as well as post-test) comparisons of experimental data with pre-computed Computational Fluid Dynamics (CFD) predictions. This capability was utilized to compare experimental measurements with CFD predictions of the surface pressure distribution of the NASA Ares I Crew Launch Vehicle (CLV) - like vehicle when tested in the NASA LaRC Unitary Plan Wind Tunnel (UPWT) in December 2006 - January 2007 timeframe. The wind tunnel tests were conducted to develop a database of experimentally-measured aerodynamic performance of the CLV-Iike configuration for validation of CFD predictive codes. C1 [Schwartz, Richard J.] NASA, Langley Res Ctr, Swales Aerosp, Adv Sensing & Opt Mesurement Branch, Hampton, VA 23665 USA. [Fleming, Gary A.] NASA, Langley Res Ctr, Adv Sensing & Opt Meausurement Branch, Hampton, VA USA. RP Schwartz, RJ (reprint author), NASA, Langley Res Ctr, Swales Aerosp, Adv Sensing & Opt Mesurement Branch, Hampton, VA 23665 USA. EM Richard.J.Schwartz@nasa.gov; Galy.A.Fleming@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 BN 978-1-4244-1599-1 PY 2007 BP 265 EP + PG 3 WC Engineering, Aerospace; Engineering, Electrical & Electronic; Instruments & Instrumentation SC Engineering; Instruments & Instrumentation GA BHD70 UT WOS:000252358500029 ER PT B AU Bell, JH Hand, LA AF Bell, James H. Hand, Lawrence A. GP IEEE TI Calculation of mass transfer coefficients in a crystal growth chamber through heat transfer measurements SO 2007 22ND INTERNATIONAL CONGRESS ON INSTRUMENTATION IN AEROSPACE SIMULATION FACILITIES LA English DT Proceedings Paper CT 22nd International Congress on Instrumentation in Aerospace Simulation Facilities CY JUN 10-14, 2007 CL Pacific Grove, CA SP IEEE Aerosp, Elec Syst Soc, AIAA AB The growth rate of a crystal in a supersaturated solution is limited by both reaction kinetics and the local concentration of solute. If the local mass transfer coefficient is too low, concentration of solute at the crystal-solution interface will drop below saturation, leading to a defect in the growing crystal. Here, mass transfer coefficients are calculated for a rotating crystal growing in a supersaturated solution of potassium di-hydrogen phosphate (KDP) in water. Since mass transfer is difficult to measure directly, the instantaneous distribution of the heat transfer coefficient on a heated scale model crystal in water is measured using temperature-sensitive paint (TSP). To the authors' knowledge this is the first use of TSP to measure temperature distributions in water. The corresponding mass transfer coefficient is then calculated using the Chilton-Colburn analogy. Measurements were made for three crystal sizes at two running conditions each. Running conditions include periodic reversals of rotation direction. Heat transfer coefficients were found to vary significantly both across the crystal faces and over the course of a rotation cycle, but not from one face to another. Mean heat transfer coefficients increased with both crystal size and rotation rate. Additional experiments show that continuous rotation of the crystal results in about a 40% lower heat transfer compared to rotation with periodic reversals. The continuous rotation case also shows a cyclic variation in heat transfer coefficient of about 15%, with a period of about 72 times the rotation period. Calculated mass transfer coefficients were broadly in line with expectations from the full-scale crystal growth experiments. C1 [Bell, James H.; Hand, Lawrence A.] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Bell, JH (reprint author), NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. NR 6 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-1599-1 PY 2007 BP 283 EP 303 PG 21 WC Engineering, Aerospace; Engineering, Electrical & Electronic; Instruments & Instrumentation SC Engineering; Instruments & Instrumentation GA BHD70 UT WOS:000252358500031 ER PT S AU Dabipi, IK Dingwall, BJ Arumala, JO AF Dabipi, I. K. Dingwall, B. J. Arumala, J. O. GP IEEE TI Creating collaborative developmental communities: A pipeline to Science, Technology, Engineering and Mathematics (STEM) education SO 2007 37TH ANNUAL FRONTIERS IN EDUCATION CONFERENCE, GLOBAL ENGINEERING : KNOWLEDGE WITHOUT BORDERS - OPPORTUNITIES WITHOUT PASSPORTS, VOLS 1- 4 SE Frontiers in Education Conference LA English DT Proceedings Paper CT 37th Annual Frontiers in Education Conference CY OCT 10-13, 2007 CL Milwaukee, WI AB Creating real change in the number and demographic proportions of students pursuing careers in Science, Technology, Engineering & Mathematics (STEM) careers is a task that requires a community effort It requires the active support and involvement of school systems, industries, governmental agencies like NASA, local communities, institutions of higher education as well as potential employers to create an environment that welcomes the best and the brightest students, regardless of gender, ethnicity, religion, or disability. By joining forces with local schools, communities, and institutions of higher education, we can develop and maintain effective and seamless pipelines through which students who wish to pursue careers in STEM fields can have a clearly defined and well supported path to success. We can become the support network that students from populations that do not traditionally pursue these careers lack. In short, we are combining forces to collectively 'inspire the next generation's This paper presents the early partnership results between NASA-UMES Summer Internship Program (NUSIP), a University Program and the Science Technical and Engineering Pipeline for Underserved Populations (STEP UP), a High School Program. It presents the highlights of the interaction and collaborative efforts of the programs. C1 [Dabipi, I. K.] Univ Maryland Eastern Shore, Princess Anne, MD 21853 USA. [Dingwall, B. J.] NASA, Goddard Space Flight Ctr, Wallops Flight Facil, Wallops Isl, VA 23337 USA. [Arumala, J. O.] Univ Maryland Eastern Shore, Dept Technol, Princess Anne, MD 21853 USA. EM ikdabipi@umes.edu; Brenda.J.Dingwall@nasa.gov; joarumala@umes.edu FU NASA FX The authors wish to offer their sincere gratitude to NASA for sponsoring the internship program and the continuous funding that has made the process possible. NR 6 TC 0 Z9 0 U1 0 U2 3 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 0190-5848 BN 978-1-4244-1083-5 J9 PROC FRONT EDUC CONF PY 2007 BP 574 EP + PG 2 WC Education & Educational Research; Education, Scientific Disciplines SC Education & Educational Research GA BHV02 UT WOS:000256621900129 ER PT B AU Kibler, AB Jamieson, BG Durand, DM AF Kibler, Andrew B. Jamieson, Brian G. Durand, Dominique M. GP IEEE TI A transparent penetrating Microelectrode array for in-vitro hippocampus recording SO 2007 3RD INTERNATIONAL IEEE/EMBS CONFERENCE ON NEURAL ENGINEERING, VOLS 1 AND 2 LA English DT Proceedings Paper CT 3rd International IEEE/EMBS Conference on Neural Engineering CY MAY 02-05, 2007 CL Kohala Coast, HI SP IEEE, EMBS ID BRAIN-SLICES AB A novel penetrating microelectrode array was designed and fabricated for the purpose of recording activity in the hippocampus of mice. The array allows two dimensional recording of 64 simultaneous sites of the hippocampus, in vitro. Traditional surface electrode arrays, although easy to fabricate, do not penetrate to the active tissue of hippocampus slices and thus theoretically have a lower signal/noise ratio and lower selectivity than a penetrating array. Furthermore, the structure of the hippocampus slice preparation results in dead tissue in closest proximity to these traditional electrodes and the cell bodies of the CA1 region are obscured by them, degrading activity-based optical imaging techniques as wen. An array of 64 electrode posts was fabricated in silicon and bonded to a clear glass substrate. The impedance of the electrodes was measured to be approximately 1.5M Ohms +- 500Ohms. The signal to noise ratio was measured and found to be 19.4 +/- 3 dB compared to 3.9 +/- 0.8 dB S/N for signals obtained with voltage sensitive dye RH414. These data suggest that the penetrating electrode array is superior to that of the voltage sensitive dye technique for two-dimensional recording. C1 [Kibler, Andrew B.; Durand, Dominique M.] Case Western Reserve Univ, Ctr Neural Engn, Dept Biomed Engn, Cleveland, OH 44106 USA. [Jamieson, Brian G.] NASA, Goddard Space Flight Ctr, Greenbelt, MD USA. RP Kibler, AB (reprint author), Case Western Reserve Univ, Ctr Neural Engn, Dept Biomed Engn, Cleveland, OH 44106 USA. FU NIH [R01NS4075] FX Financial support for this proposal was provided by NIH grant R01NS4075. 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 978-1-4244-0791-0 PY 2007 BP 276 EP + DI 10.1109/CNE.2007.369664 PG 2 WC Engineering, Electrical & Electronic; Nanoscience & Nanotechnology; Neurosciences SC Engineering; Science & Technology - Other Topics; Neurosciences & Neurology GA BGM68 UT WOS:000248513500069 ER PT B AU Burleigh, S AF Burleigh, Scott GP IEEE TI Interplanetary Overlay Network SO 2007 4TH IEEE CONSUMER COMMUNICATIONS AND NETWORKING CONFERENCE, VOLS 1-3 SE IEEE Consumer Communications and Networking Conference LA English DT Proceedings Paper CT 4th IEEE Consumer Communications and Networking Conference CY JAN 11-13, 2007 CL Las Vegas, NV SP IEEE DE DTN; bundle protocol; space flight; RTOS AB Interplanetary Overlay Network (ION) is an implementation of the DTN Bundle Protocol that is intended to be usable for interplanetary communications. The space flight-specific constraints on this implementation are discussed, as are the architecture of ION-based DTN nodes and the results of some initial performance benchmarking. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. RP Burleigh, S (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. EM Scott.Burleigh@jpl.nasa.gov NR 6 TC 21 Z9 21 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-0666-1 J9 CONSUM COMM NETWORK PY 2007 BP 222 EP 226 DI 10.1109/CCNC.2007.51 PG 5 WC Computer Science, Hardware & Architecture; Engineering, Electrical & Electronic; Telecommunications SC Computer Science; Engineering; Telecommunications GA BIF54 UT WOS:000259117100044 ER PT B AU Kitsuki, H Suzuki, M Ngo, Q Gleason, K Wilhite, P Cassell, AM Li, J Yang, CY AF Kitsuki, Hirohiko Suzuki, Makoto Ngo, Quoc Gleason, Kristofer Wilhite, Patrick Cassell, Alan M. Li, Jun Yang, Cary Y. GP IEEE TI Current-induced Breakdown of Carbon Nanofibers for Interconnect Applications SO 2007 7TH IEEE CONFERENCE ON NANOTECHNOLOGY, VOL 1-3 LA English DT Proceedings Paper CT 7th IEEE Conference on Nanotechnology CY AUG 02-05, 2007 CL Hong Kong, PEOPLES R CHINA SP IEEE, IEEE Nanotechnol Council, IEEE Electron Devices Soc, Chinese Univ Hong Kong, Ctr Micro & Nano Syst, ETH, Inst Robot & Intelligent Syst, GETI, KC Wong Educ Fdn, US Army Int Technol Ctr, ACS NANO, CRC Press, Taylor & Francis Grp, intel DE carbon nanofibers; current-induced breakdown; scanning electron microscopy (STEM); thermal transport ID NANOTUBES; GROWTH; ARRAYS AB Current-induced breakdown phenomena of carbon nanofibers (CNFs) for future on-chip interconnect applications are presented. Scanning transmission electron microscopy (STEM) techniques are developed to study the structural damage by current stress, including in situ electrical measurement with STEM, and sample-preparation-free STEM imaging. The analysis shows that the breakdown occurs along graphitic layers comprising the CNF and that the maximum current density has strong correlation with electrical resistivity. The effect of heat dissipation into the underlying substrate is also studied using different experimental configurations. C1 [Kitsuki, Hirohiko; Suzuki, Makoto; Ngo, Quoc; Gleason, Kristofer; Wilhite, Patrick; Yang, Cary Y.] Santa Clara Univ, Ctr Nanostruct, Santa Clara, CA 95053 USA. [Ngo, Quoc; Cassell, Alan M.; Li, Jun] NASA, Ames Res Ctr, Ctr Adv Aerosp Mat & Devices, Moffett Field, CA 94035 USA. RP Kitsuki, H (reprint author), Santa Clara Univ, Ctr Nanostruct, Santa Clara, CA 95053 USA. NR 23 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-0607-4 PY 2007 BP 342 EP + PG 2 WC Engineering, Electrical & Electronic; Nanoscience & Nanotechnology SC Engineering; Science & Technology - Other Topics GA BIO98 UT WOS:000261434900077 ER PT B AU Kobayashi, NP Logeeswaran, VJ Li, XM Islam, MS Straznicky, J Wang, SY Li, ZY Williams, RS AF Kobayashi, Nobuhiko P. Logeeswaran, V. J. Li, Xuema Islam, M. Saif Straznicky, Joseph Wang, Shih-Yuan Li, Zhiyong Williams, R. Stanley GP IEEE TI Indium Phosphide Nanowire Photoconductors on Non-single Crystalline Silicon-based Platform SO 2007 7TH IEEE CONFERENCE ON NANOTECHNOLOGY, VOL 1-3 LA English DT Proceedings Paper CT 7th IEEE Conference on Nanotechnology CY AUG 02-05, 2007 CL Hong Kong, PEOPLES R CHINA SP IEEE, IEEE Nanotechnol Council, IEEE Electron Devices Soc, Chinese Univ Hong Kong, Ctr Micro & Nano Syst, ETH, Inst Robot & Intelligent Syst, GETI, KC Wong Educ Fdn, US Army Int Technol Ctr, ACS NANO, CRC Press, Taylor & Francis Grp, intel DE indium phosphide; nanowire; photoconductor; silicon; monolithic integration ID PHOTODETECTORS; GROWTH AB We describe the fabrication and characterization of photoconductors in which an ensemble of indium phosphide nanoneedles was utilized. DC electrical transport properties of the fabricated photoconductors were characterized under illumination with monochromatic light at 633 nm. This is the first demonstration of III-V compound semiconductor nanometer-scale structures monolithically integrated on non-single crystalline silicon-based materials as an optoelectronic device that can be fabricated by a simple and flexible process not limited by single crystal substrates. C1 [Kobayashi, Nobuhiko P.] Univ Calif Santa Cruz, Baskin Sch Engn, Santa Cruz, CA 95064 USA. [Kobayashi, Nobuhiko P.] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Kobayashi, Nobuhiko P.] Univ Calif, NECTAR, Adv Studies Lab, Moffett Field, CA 94035 USA. [Li, Xuema; Straznicky, Joseph; Wang, Shih-Yuan; Williams, R. Stanley] Hewlett Packard Corp, Informat & Quantum Syst Lab, Palo Alto, CA 94304 USA. [Logeeswaran, V. J.; Islam, M. Saif] Univ Calif Davis, Dept Elect & Comp Engn, Davis, CA 95616 USA. RP Kobayashi, NP (reprint author), Univ Calif Santa Cruz, Baskin Sch Engn, Santa Cruz, CA 95064 USA. EM nobby@soe.ucsc.edu RI Kobayashi, Nobuhiko/E-3834-2012; Williams, R. Stanley/A-8281-2009 OI Williams, R. Stanley/0000-0003-0213-4259 NR 17 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-0607-4 PY 2007 BP 469 EP + PG 2 WC Engineering, Electrical & Electronic; Nanoscience & Nanotechnology SC Engineering; Science & Technology - Other Topics GA BIO98 UT WOS:000261434900106 ER PT B AU Sun, XH Ju, SH Janes, D Yu, B AF Sun, Xuhui Ju, Sanghyun Janes, David Yu, Bin GP IEEE TI Self-Assembly of Low-Dimensional Phase-Change Nanomaterials For Information Storage SO 2007 7TH IEEE CONFERENCE ON NANOTECHNOLOGY, VOL 1-3 LA English DT Proceedings Paper CT 7th IEEE Conference on Nanotechnology CY AUG 02-05, 2007 CL Hong Kong, PEOPLES R CHINA SP IEEE, IEEE Nanotechnol Council, IEEE Electron Devices Soc, Chinese Univ Hong Kong, Ctr Micro & Nano Syst, ETH, Inst Robot & Intelligent Syst, GETI, KC Wong Educ Fdn, US Army Int Technol Ctr, ACS NANO, CRC Press, Taylor & Francis Grp, intel DE phase change; PRAM; nanowire ID OPTICAL-DATA STORAGE; THIN-FILMS; GERMANIUM TELLURIDE; MEMORY; NANOWIRES; BEHAVIOR; GETE AB Low-dimensional phase-change nanomaterials offer advantages over their bulk counterpart in data storage due to reduced threshold energies for phase transition. These features contribute to low power, scalability, and fast write/erase. We reported synthesis approach and material studies of 1-D chalcogenide materials including GeTe, In2Se3, and Ge2Sb2Te5 nanowires targeted for nonvolatile memories. The phase-change nanowires were synthesized via thermal evaporation under VLS mechanism. The crystal structure, morphology, and composition of the synthesized nanowires were investigated by SEM, EDX, HR-TEM and XPS. The nanowires are structurally uniform with single crystalline structures. Chalcogenide nanowires exhibit significantly reduced melting points, low activation energy and excellent morphology, making them promising nano media for data storage with low energy consumption and excellent scalability. C1 [Sun, Xuhui; Yu, Bin] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Ju, Sanghyun; Janes, David] Purdue Univ, Birck Nanotechnol Ctr, W Lafayette, IN 47907 USA. RP Sun, XH (reprint author), NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. FU NASA contract to UARC FX B.Yu and X. Sun are with the University Affiliated Research Center (UARC)at NASA Ames Research Center and their work was supported by a NASA contract to UARC NR 16 TC 0 Z9 0 U1 0 U2 4 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-0607-4 PY 2007 BP 1075 EP + PG 2 WC Engineering, Electrical & Electronic; Nanoscience & Nanotechnology SC Engineering; Science & Technology - Other Topics GA BIO98 UT WOS:000261434900241 ER PT S AU Aldrich, JB de Oliveira, MC AF Aldrich, J. B. de Oliveira, M. C. GP IEEE TI Convex subspaces for time-optimal control of robotic systems on prescribed paths SO 2007 AMERICAN CONTROL CONFERENCE, VOLS 1-13 SE Proceedings of the American Control Conference LA English DT Proceedings Paper CT 26th American Control Conference CY JUL 09-13, 2007 CL New York, NY AB For robotic manipulators designed to follow a prescribed maneuver, this paper solves the classic time-optimal control problem using a convex optimization approach. By assuming a Bernstein polynomial basis for the path velocity, and enforcing torque constraints at discrete points along the path, the time-optimal control problem becomes a finite-dimensional optimization problem with non-convex equality constraints. However, a rank 2 spectral decomposition of the torque constraints yields equivalent semi-definite quadratic constraints which allow us to solve the problem as a sequence of convex subproblems guaranteed to converge to the global minimum. An advantage of this approach is that bang-bang control solutions are replaced by smooth motor commands, even though the higher-order derivatives of the system are not explicitly constrained. Numerical examples illustrate the algorithm. C1 [Aldrich, J. B.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [de Oliveira, M. C.] Univ Calif San Diego, Dept Mech & Aerosp Engn, La Jolla, CA 92093 USA. RP Aldrich, JB (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM jaldrich@jpl.nasa.gov; mauricio@ucsd.edu NR 7 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 0743-1619 BN 978-1-4244-0988-4 J9 P AMER CONTR CONF PY 2007 BP 6035 EP + PG 2 WC Automation & Control Systems; Engineering, Electrical & Electronic; Engineering, Mechanical SC Automation & Control Systems; Engineering GA BHD12 UT WOS:000252258804138 ER PT B AU Yang, RQ AF Yang, Rui Q. GP IEEE TI Interband Cascade Lasers: from concept to devices and applications SO 2007 CONFERENCE ON LASERS & ELECTRO-OPTICS/QUANTUM ELECTRONICS AND LASER SCIENCE CONFERENCE (CLEO/QELS 2007), VOLS 1-5 LA English DT Proceedings Paper CT Conference on Lasers and Electro-Optics/Quantum Electronics and Laser Science Conference CY MAY 06-11, 2007 CL Baltimore, MD AB The development of mid-infrared interband cascade lasers from concept to devices and applications will be reviewed. Their current status and future prospects will be discussed. 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. EM Rui.Q.Yang@jpl.nasa.gov NR 9 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-3590-6 PY 2007 BP 371 EP 371 PG 1 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BKO20 UT WOS:000268751000187 ER PT B AU Wu, X Gu, Y Yan, F Choa, FS Shu, P AF Wu, X. Gu, Y. Yan, F. Choa, F. S. Shu, P. GP IEEE TI High Uniformity, Stability, and Reliability Large-Format InGaAs APD Arrays SO 2007 CONFERENCE ON LASERS & ELECTRO-OPTICS/QUANTUM ELECTRONICS AND LASER SCIENCE CONFERENCE (CLEO/QELS 2007), VOLS 1-5 LA English DT Proceedings Paper CT Conference on Lasers and Electro-Optics/Quantum Electronics and Laser Science Conference CY MAY 06-11, 2007 CL Baltimore, MD AB The characteristics of both etched mesa and guard ring type of InGaAs APD arrays were compared. High uniformity, high stability, and high reliability guard-ring type of arrays with a size up to 64x64 were fabricated. (C)2007 Optical Society of America C1 [Wu, X.] Adtech Opt, City Of Industry, CA 91748 USA. [Shu, P.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Wu, X (reprint author), Adtech Opt, City Of Industry, CA 91748 USA. EM choa@umbc.edu FU NASA STTR FX This work is supported by NASA STTR NR 1 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-3590-6 PY 2007 BP 408 EP + PG 2 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BKO20 UT WOS:000268751000206 ER PT B AU Itzler, MA Jiang, XD Ben-Michael, R Slomkowski, K Krainak, MA Wu, S Sun, XL AF Itzler, Mark A. Jiang, Xudong Ben-Michael, Rafael Slomkowski, Krystyna Krainak, Michael A. Wu, Stewart Sun, Xiaoli GP IEEE TI InGaAsP/InP Single Photon Avalanche Photodetectors For 1.06 mu m Free-Running Photon Counting SO 2007 CONFERENCE ON LASERS & ELECTRO-OPTICS/QUANTUM ELECTRONICS AND LASER SCIENCE CONFERENCE (CLEO/QELS 2007), VOLS 1-5 LA English DT Proceedings Paper CT Conference on Lasers and Electro-Optics/Quantum Electronics and Laser Science Conference CY MAY 06-11, 2007 CL Baltimore, MD ID PHOTODIODES AB We demonstrate large area InP-based single photon avalanche diodes capable of free-running operation at 1.06 mu m with dark count rates below 1000 Hz, detection efficiencies greater than 10%, and single photon count rates exceeding 1 MHz. (C)2007 Optical Society of America C1 [Itzler, Mark A.; Jiang, Xudong; Ben-Michael, Rafael; Slomkowski, Krystyna] Princeton Lightwave Inc, 2555 US Route 130, Cranbury, NJ 08512 USA. [Krainak, Michael A.; Wu, Stewart; Sun, Xiaoli] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Itzler, MA (reprint author), Princeton Lightwave Inc, 2555 US Route 130, Cranbury, NJ 08512 USA. EM mitzler@princetonlightwave.com RI Sun, Xiaoli/B-5120-2013 FU NASA [NNG06LA04C] FX This work was supported by NASA under grant NNG06LA04C. NR 6 TC 0 Z9 0 U1 0 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-3590-6 PY 2007 BP 410 EP + PG 2 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BKO20 UT WOS:000268751000207 ER PT B AU Barnes, NP Walsh, BM Reichle, DJ AF Barnes, Norman P. Walsh, Brian M. Reichle, Donald J. GP IEEE TI Asymmetric Time Constants SO 2007 CONFERENCE ON LASERS & ELECTRO-OPTICS/QUANTUM ELECTRONICS AND LASER SCIENCE CONFERENCE (CLEO/QELS 2007), VOLS 1-5 LA English DT Proceedings Paper CT Conference on Lasers and Electro-Optics/Quantum Electronics and Laser Science Conference CY MAY 06-11, 2007 CL Baltimore, MD AB Time constants for population density rise and decay are often unequal. Asymmetric time constants result from: ground state depletion, up conversion, and amplified spontaneous emission. All these effects were modeled and Tm:germanate experiments support model. (C) 2007 Optical Society of America C1 [Barnes, Norman P.; Walsh, Brian M.; Reichle, Donald J.] NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Barnes, NP (reprint author), NASA, Langley Res Ctr, Hampton, VA 23681 USA. EM n.p.barnes@larc.nasa.gov NR 1 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-3590-6 PY 2007 BP 594 EP 595 PG 2 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BKO20 UT WOS:000268751000299 ER PT B AU Bai, YX Yu, JR Petros, M Petzar, P Trieu, B Lee, H Singh, U AF Bai, Yingxin Yu, Jirong Petros, M. Petzar, Paul Trieu, Bo Lee, Hyung Singh, U. GP IEEE TI Highly efficient Q-switched Ho:YLF laser pumped by Tm:fiber laser SO 2007 CONFERENCE ON LASERS & ELECTRO-OPTICS/QUANTUM ELECTRONICS AND LASER SCIENCE CONFERENCE (CLEO/QELS 2007), VOLS 1-5 LA English DT Proceedings Paper CT Conference on Lasers and Electro-Optics/Quantum Electronics and Laser Science Conference CY MAY 06-11, 2007 CL Baltimore, MD AB A highly efficient Q-switched Ho:YLF laser pumped by a Tm:fiber laser has been designed and demonstrated. When the pump power is 30 W, the pulse energy is 30mJ at the repetition rate of 100Hz. (C) 2007 Optical Society of America C1 [Bai, Yingxin] Sci Syst & Applicat Inc, 1 Enterprise Pkwy, Hampton, VA 23666 USA. [Yu, Jirong; Trieu, Bo; Singh, U.] NASA, Langley Res Ctr, Hampton, VA 23681 USA. [Petros, M.] Sci & Technol Corp, Hampton, VA 23666 USA. [Petzar, Paul; Lee, Hyung] Natl Inst Aerosp, Hampton, VA 23668 USA. RP Bai, YX (reprint author), Sci Syst & Applicat Inc, 1 Enterprise Pkwy, Hampton, VA 23666 USA. EM Ybai@larc.nasa.gov NR 5 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-3590-6 PY 2007 BP 596 EP + PG 2 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BKO20 UT WOS:000268751000300 ER PT B AU Wang, CC Trivedi, S Jin, F Chen, ZY Khurgin, J Rodriguez, P Prasad, NS AF Wang, Chen-Chia Trivedi, Sudhir Jin, Feng Chen, Zhongyang Khurgin, Jacob Rodriguez, Ponciano Prasad, Narasimha S. GP IEEE TI Biological Life Signs Detection Using High Sensitivity Pulsed Laser Vibrometer SO 2007 CONFERENCE ON LASERS & ELECTRO-OPTICS/QUANTUM ELECTRONICS AND LASER SCIENCE CONFERENCE (CLEO/QELS 2007), VOLS 1-5 LA English DT Proceedings Paper CT Conference on Lasers and Electro-Optics/Quantum Electronics and Laser Science Conference CY MAY 06-11, 2007 CL Baltimore, MD AB We present experimentally the remote detection of biological life signs, including heartbeat, breathing, gross physical movement, and blood circulation conditions using a highly sensitive, speckle-tolerant pulsed laser vibrometer that allows interrogation from essentially any part of the subject's body. (C) 2007 Optical Society of America C1 [Wang, Chen-Chia; Trivedi, Sudhir; Jin, Feng] Brimrose Corp Amer, 7720 Belair Rd, Baltimore, MD 21236 USA. [Chen, Zhongyang; Khurgin, Jacob] Johns Hopkins Univ, Dept Elect & Comp Engn, Baltimore, MD 21218 USA. [Rodriguez, Ponciano] INAOE, Puebla 7200, Mexico. [Prasad, Narasimha S.] NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Wang, CC (reprint author), Brimrose Corp Amer, 7720 Belair Rd, Baltimore, MD 21236 USA. EM ccwang@Brimrose.com RI khurgin, Jacob/A-3278-2010 FU US Army through a SBIR Phase II Army through a SBIR Phase II contract to Brimrose Corp . of America [W15P7T-O6-C-F004] FX The authors acknowledge the partial financial support by US Army through a SBIR Phase II contract to Brimrose Corp . of America, contract # W15P7T-O6-C-F004 NR 2 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-3590-6 PY 2007 BP 997 EP + PG 2 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BKO20 UT WOS:000268751000501 ER PT B AU Lewis, JR DeYoung, RJ Severance, K AF Lewis, Jasper R. DeYoung, Russell J. Severance, Kurt GP IEEE TI Regional Aerosol Transport Study Using a Compact Aircraft Lidar SO 2007 CONFERENCE ON LASERS & ELECTRO-OPTICS/QUANTUM ELECTRONICS AND LASER SCIENCE CONFERENCE (CLEO/QELS 2007), VOLS 1-5 LA English DT Proceedings Paper CT Conference on Lasers and Electro-Optics/Quantum Electronics and Laser Science Conference CY MAY 06-11, 2007 CL Baltimore, MD AB A compact aircraft lidar using a Nd:YAG pulsed laser, fiber coupled telescope, and three-channel receiver was flown in the Norfolk-Virginia Beach and California Central Valley regions to show lidar can reveal complex regional aerosol distributions. (C)2007 Optical Society of America C1 [Lewis, Jasper R.] Hampton Univ, Hampton, VA 23668 USA. [DeYoung, Russell J.; Severance, Kurt] NASA, Langley Res Ctr, Hampto, VA USA. RP Lewis, JR (reprint author), Hampton Univ, Hampton, VA 23668 USA. EM J.R.Lewis@larc.nasa.gov; Russell.J.DeYoung@nasa.gov; Kurt.Severance@nasa.gov NR 2 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-3590-6 PY 2007 BP 1351 EP + PG 2 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BKO20 UT WOS:000268751001116 ER PT B AU Abshire, JB Harding, DJ Sun, XL Krainak, MA Seas, T Dabney, PW AF Abshire, James B. Harding, David J. Sun, Xiaoli Krainak, Michael A. Seas, Tony Dabney, Phillip W. GP IEEE TI Pushbroom Laser Altimetry using Fiber Lasers and Photon Counting Detectors SO 2007 CONFERENCE ON LASERS & ELECTRO-OPTICS/QUANTUM ELECTRONICS AND LASER SCIENCE CONFERENCE (CLEO/QELS 2007), VOLS 1-5 LA English DT Proceedings Paper CT Conference on Lasers and Electro-Optics/Quantum Electronics and Laser Science Conference CY MAY 06-11, 2007 CL Baltimore, MD AB We report on progress in developing a new swath mapping laser altimeter measurement approach using multiple laser measurement beams, modulated fiber lasers, photon counting detectors, and event timers for future space missions. (C)2007 Optical Society of America C1 [Abshire, James B.; Harding, David J.; Sun, Xiaoli; Krainak, Michael A.; Seas, Tony; Dabney, Phillip W.] NASA, Goddard Space Flight Ctr, Terr Phys Lab, Greenbelt, MD 20771 USA. RP Abshire, JB (reprint author), NASA, Goddard Space Flight Ctr, Terr Phys Lab, Mail Code 920, Greenbelt, MD 20771 USA. EM James.Abshire@gsfc.nasa.gov RI Sun, Xiaoli/B-5120-2013; Dabney, Philip/C-9976-2013; Abshire, James/I-2800-2013; Harding, David/F-5913-2012 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 978-1-4244-3590-6 PY 2007 BP 1467 EP 1468 PG 2 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BKO20 UT WOS:000268751001174 ER PT B AU Sun, XL Riris, H Cavanaugh, JF McGarry, JF Jackson, GB Zellar, RS Smith, DE Zuber, MT AF Sun, Xiaoli Riris, Haris Cavanaugh, John F. McGarry, Jan F. Jackson, Glenn B. Zellar, Ronald S. Smith, David E. Zuber, Maria T. GP IEEE TI The Lunar Orbiter Laser Altimter and the Laser Ranging System on the Lunar Reconnaissance Orbiter SO 2007 CONFERENCE ON LASERS & ELECTRO-OPTICS/QUANTUM ELECTRONICS AND LASER SCIENCE CONFERENCE (CLEO/QELS 2007), VOLS 1-5 LA English DT Proceedings Paper CT Conference on Lasers and Electro-Optics/Quantum Electronics and Laser Science Conference CY MAY 06-11, 2007 CL Baltimore, MD AB The design of Lunar Orbiter Laser Altimeter oil the Lunar Reconnaissance Orbiter is presented. The one-way laser ranging system that provides precision tracking of the spacecraft position from Earth is also described. (C)2007 Optical Society of America C1 [Sun, Xiaoli; Riris, Haris; Cavanaugh, John F.; McGarry, Jan F.; Jackson, Glenn B.; Zellar, Ronald S.; Smith, David E.] NASA, Goddard Space Flight Ctr, Code 690, Greenbelt, MD 20771 USA. [Zuber, Maria T.] MIT, Dept Earth Atmospher & Planetary Sci, Cambridge, MA 02139 USA. RP Sun, XL (reprint author), NASA, Goddard Space Flight Ctr, Code 690, Greenbelt, MD 20771 USA. EM xiaoli.sun-1@nasa.gov RI Sun, Xiaoli/B-5120-2013; McGarry, Jan/C-4109-2013; Riris, Haris/D-1004-2013 NR 0 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-3590-6 PY 2007 BP 1469 EP + PG 2 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BKO20 UT WOS:000268751001175 ER PT B AU Abshire, JB Riris, H Sun, XL Krainak, MA Kawa, R Mao, JP Jian, PS Burris, JF AF Abshire, James B. Riris, Haris Sun, Xiaoli Krainak, Michael A. Kawa, Randy Mao, Jian-Ping Jian, Pey-Schuan Burris, John F. GP IEEE TI Lidar Approach for Measuring the CO2 Concentrations in the Troposphere from Space SO 2007 CONFERENCE ON LASERS & ELECTRO-OPTICS/QUANTUM ELECTRONICS AND LASER SCIENCE CONFERENCE (CLEO/QELS 2007), VOLS 1-5 LA English DT Proceedings Paper CT Conference on Lasers and Electro-Optics/Quantum Electronics and Laser Science Conference CY MAY 06-11, 2007 CL Baltimore, MD ID SPECTROSCOPY; LASER AB We report progress in assessing the feasibility of a new satellite-based laser-sounding instrument to measure CO2 concentrations in the lower troposphere from space. (c) 2007 Optical Society of America C1 [Abshire, James B.; Riris, Haris; Sun, Xiaoli; Kawa, Randy; Burris, John F.] NASA, Goddard Space Flight Ctr, Sci & Explorat Directorate, Codes 690 & 610, Greenbelt, MD 20771 USA. [Krainak, Michael A.] NASA, Goddard Space Flight Ctr, Appl Engn & Technol, Greenbelt, MD 20771 USA. [Mao, Jian-Ping; Jian, Pey-Schuan] Sci Syst & Applicat Inc, Greenbelt, MD 20771 USA. RP Abshire, JB (reprint author), NASA, Goddard Space Flight Ctr, Sci & Explorat Directorate, Codes 690 & 610, Greenbelt, MD 20771 USA. EM James.Abshire@gsfc.nasa.gov RI Kawa, Stephan/E-9040-2012; Sun, Xiaoli/B-5120-2013; Riris, Haris/D-1004-2013; Abshire, James/I-2800-2013 NR 6 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-3590-6 PY 2007 BP 1474 EP + PG 2 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BKO20 UT WOS:000268751001178 ER PT B AU Seas, A Li, S Stephen, M Novo-Gradac, AMD Kashem, N Vasilyev, A Troupaki, E Chen, SS Rosanova, A AF Seas, Antonios Li, Steve Stephen, Mark Novo-Gradac, Anne-Marie D. Kashem, Nasir Vasilyev, Aleksey Troupaki, Elisavet Chen, Songsheng Rosanova, Alberto GP IEEE TI Development and Vacuum Life Test of a Diode-Pumped Cr:Nd:YAG Laser (Heritage Laser) for Space Applications SO 2007 CONFERENCE ON LASERS & ELECTRO-OPTICS/QUANTUM ELECTRONICS AND LASER SCIENCE CONFERENCE (CLEO/QELS 2007), VOLS 1-5 LA English DT Proceedings Paper CT Conference on Lasers and Electro-Optics/Quantum Electronics and Laser Science Conference CY MAY 06-11, 2007 CL Baltimore, MD AB The development and vacuum life-testing of a diode pumped Cr:Nd:YAG laser for space applications is presented. Furthermore results from long life-testing of 808-nm laser diode arrays in air and vacuum are discussed. C1 [Seas, Antonios; Li, Steve; Stephen, Mark; Novo-Gradac, Anne-Marie D.; Kashem, Nasir] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Vasilyev, Aleksey; Troupaki, Elisavet; Chen, Songsheng; Rosanova, Alberto] Sci Syst & Appl, Lanham, MD USA. RP Seas, A (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. EM Antonios.A.Seas@nasa.gov NR 1 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-3590-6 PY 2007 BP 1532 EP + PG 2 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BKO20 UT WOS:000268751001207 ER PT B AU Stephen, M Krainak, M Riris, H Allan, G AF Stephen, Mark Krainak, Michael Riris, Haris Allan, Graham GP IEEE TI Single-Frequency, Frequency-Doubled, Erbium-Doped, Fiber-Amplified Transmitter for Oxygen A-Band Spectroscopy SO 2007 CONFERENCE ON LASERS & ELECTRO-OPTICS/QUANTUM ELECTRONICS AND LASER SCIENCE CONFERENCE (CLEO/QELS 2007), VOLS 1-5 LA English DT Proceedings Paper CT Conference on Lasers and Electro-Optics/Quantum Electronics and Laser Science Conference CY MAY 06-11, 2007 CL Baltimore, MD ID DIFFERENTIAL ABSORPTION LIDAR; ATMOSPHERIC-PRESSURE AB We developed a frequency-doubled, DFB-seeded EDFA. 8 Walls of frequency-doubled power was achieved in a single-frequency, wavelength tunable, power scalable laser transmitter used for spectroscopic remote sensing of the oxygen A-band. (C) 2007 Optical Society of America C1 [Stephen, Mark; Krainak, Michael; Riris, Haris] NASA, Goddard Space Flight Ctr, Code 554, Greenbelt, MD 20771 USA. [Allan, Graham] Sigma Space Corp, Lanham, MD 20706 USA. RP Stephen, M (reprint author), NASA, Goddard Space Flight Ctr, Code 554, Greenbelt, MD 20771 USA. EM mark.a.stephen@nasa.gov RI Riris, Haris/D-1004-2013; Allan, Graham/D-3905-2013 NR 10 TC 0 Z9 0 U1 0 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-3590-6 PY 2007 BP 1537 EP + PG 2 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BKO20 UT WOS:000268751001210 ER PT B AU Bakhikrin, YA Wysocki, G Fraser, MP Yang, RQ Tittel, FK AF Bakhikrin, Yury A. Wysocki, Gerard Fraser, Matthew P. Yang, Rui Q. Tittel, Frank K. GP IEEE TI Sensitive, Real-Time Interband Cascade Laser Based Sensor for Ethane Monitoring SO 2007 CONFERENCE ON LASERS & ELECTRO-OPTICS/QUANTUM ELECTRONICS AND LASER SCIENCE CONFERENCE (CLEO/QELS 2007), VOLS 1-5 LA English DT Proceedings Paper CT Conference on Lasers and Electro-Optics/Quantum Electronics and Laser Science Conference CY MAY 06-11, 2007 CL Baltimore, MD ID EXHALED ETHANE; LIPID-PEROXIDATION; CARBON-MONOXIDE AB A gas sensor based on a CW mid-infrared interband cascade laser and wavelength modulation spectroscopy capable of measuring ethane concentrations with a detection sensitivity of 0.15ppbv/root Hz is reported. (C) 2006 Optical Society of America C1 [Bakhikrin, Yury A.; Wysocki, Gerard; Fraser, Matthew P.; Tittel, Frank K.] Rice Univ, Rice Quantum Inst, Houston, TX 77251 USA. [Yang, Rui Q.] Jet Prop Lab, Oakland 91209, CA USA. RP Bakhikrin, YA (reprint author), Rice Univ, Rice Quantum Inst, Houston, TX 77251 USA. EM yubakh@rice.edu FU NSF ERC MIRTHE project FX Partial financial support of the work was provided by NSF ERC MIRTHE project. NR 10 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-3590-6 PY 2007 BP 1599 EP + PG 2 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BKO20 UT WOS:000268751001241 ER PT B AU Malkova, N Ning, CZ AF Malkova, N. Ning, C. Z. GP IEEE TI Transformation of Surface States from Shockley-like to Tamm-like in Photonic Crystals SO 2007 CONFERENCE ON LASERS & ELECTRO-OPTICS/QUANTUM ELECTRONICS AND LASER SCIENCE CONFERENCE (CLEO/QELS 2007), VOLS 1-5 LA English DT Proceedings Paper CT Conference on Lasers and Electro-Optics/Quantum Electronics and Laser Science Conference CY MAY 06-11, 2007 CL Baltimore, MD AB We investigate how the asymmetry of surface potential affects the Shockley surface states in photonic crystals and demonstrate the transformation of the Shockley surface states into the Tamm states for the first time. (C) 2000 Optical Society of America C1 [Malkova, N.] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Ning, C. Z.] Arizona State Univ, Dept Elect Engn, Ctr Nanoohoton, Tempe, AZ 85287 USA. RP Malkova, N (reprint author), NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. EM umalkova@mail.arc.nasa.gov; cning@asu.edu NR 1 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-3590-6 PY 2007 BP 2111 EP + PG 2 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BKO20 UT WOS:000268751001500 ER PT B AU Piredda, G Smith, DD Yoon, Y Boyd, RW Xiao, RF Wendling, B AF Piredda, Giovanni Smith, David D. Yoon, Youngkwon Boyd, Robert W. Xiao, Rongfu Wendling, Bettina GP IEEE TI Saturable Absorption in Nanocomposite Gold-Silica Materials with high Gold Fill Fraction SO 2007 CONFERENCE ON LASERS & ELECTRO-OPTICS/QUANTUM ELECTRONICS AND LASER SCIENCE CONFERENCE (CLEO/QELS 2007), VOLS 1-5 LA English DT Proceedings Paper CT Conference on Lasers and Electro-Optics/Quantum Electronics and Laser Science Conference CY MAY 06-11, 2007 CL Baltimore, MD AB We present frequency-resolved measurements of the nonlinear absorption coefficient in gold-silica nanocomposite materials with high gold fill fraction. (C) 2007 Optical Society of America C1 [Piredda, Giovanni; Yoon, Youngkwon; Boyd, Robert W.] Univ Rochester, Inst Opt, Rochester, NY 14627 USA. [Smith, David D.] Nasa Marshall Space Flight Ctr, Huntsville, AL 35811 USA. [Xiao, Rongfu] Hong Kong Univ Sci & Technol, Dept Phys, Kowloon, Peoples R China. [Wendling, Bettina] Hong Kong Univ Sci & Technol, Dept Phys, Kowloon, Peoples R China. RP Piredda, G (reprint author), Univ Rochester, Inst Opt, Rochester, NY 14627 USA. EM piredda@optics.rochester.edu NR 6 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-3590-6 PY 2007 BP 2127 EP + PG 2 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BKO20 UT WOS:000268751001508 ER PT B AU Fromzel, VA Prasad, CR Petrosyan, KB Liaw, Y Shi, WH Yakshin, M DeYoung, R AF Fromzel, Viktor A. Prasad, Coorg R. Petrosyan, Karina B. Liaw, Yishinn Shi Wenhui Yakshin, Mikhail DeYoung, Russell GP IEEE TI Rapidly Tunable, Narrow Linewidth, 1W, 1 kHz Ce:LiCAF Laser Pumped by the Fourth Harmonic of a Diode-Pumped Nd:YLF Laser for Ozone DIAL Measurements SO 2007 CONFERENCE ON LASERS & ELECTRO-OPTICS/QUANTUM ELECTRONICS AND LASER SCIENCE CONFERENCE (CLEO/QELS 2007), VOLS 1-5 LA English DT Proceedings Paper CT Conference on Lasers and Electro-Optics/Quantum Electronics and Laser Science Conference CY MAY 06-11, 2007 CL Baltimore, MD AB A compact, rapidly tunable (282-315 nm), narrow line-width (0.2 nm) Ce:LiCAF laser pumped by the fourth harmonic of a diode-pumped Nd:YLF laser is capable of delivering 1mJ/pulse at a pulse repetition frequency of 1 kHz. C1 [Fromzel, Viktor A.; Prasad, Coorg R.; Petrosyan, Karina B.; Liaw, Yishinn; Shi Wenhui; Yakshin, Mikhail] Sci & Engn Serv Inc, Columbia, MD 21046 USA. [DeYoung, Russell] NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Fromzel, VA (reprint author), Sci & Engn Serv Inc, Columbia, MD 21046 USA. EM vfromzel@sesi-md.com NR 1 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-3590-6 PY 2007 BP 2254 EP + PG 2 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BKO20 UT WOS:000268751001572 ER PT B AU Petros, M Yu, JR Trieu, B Bai, YX Petzar, P Singh, UN Reithmaier, K AF Petros, Mulugeta Yu, Jirong Trieu, Bo Bai, Yingxin Petzar, Paul Singh, Upendra N. Reithmaier, Karl GP IEEE TI 2.5 MHz Line-Width High-energy, 2 mu m Coherent Wind Lidar Transmitter SO 2007 CONFERENCE ON LASERS & ELECTRO-OPTICS/QUANTUM ELECTRONICS AND LASER SCIENCE CONFERENCE (CLEO/QELS 2007), VOLS 1-5 LA English DT Proceedings Paper CT Conference on Lasers and Electro-Optics/Quantum Electronics and Laser Science Conference CY MAY 06-11, 2007 CL Baltimore, MD AB The design of a diode pumped, injection seeded MOPA with a transform limited line width and diffraction limited beam quality is presented. This lidar transmitter produces over 300mJ energy at 10 Hz repetition rate. (C) 2007 Optical Society of America C1 [Petros, Mulugeta] Sci & Technol Corp, 10 Basil Sawyer Dr, Hampton, VA 23666 USA. [Yu, Jirong; Trieu, Bo; Singh, Upendra N.] NASA, Langley Res Ctr, Hampton, VA 23681 USA. [Bai, Yingxin; Petzar, Paul; Reithmaier, Karl] SAIC, Hampton, VA 23666 USA. RP Petros, M (reprint author), Sci & Technol Corp, 10 Basil Sawyer Dr, Hampton, VA 23666 USA. EM m.petros@larc.nasa.gov NR 2 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-3590-6 PY 2007 BP 2258 EP + PG 2 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BKO20 UT WOS:000268751001574 ER PT B AU Poulios, D Stysley, PR Kay, RB Coyle, B AF Poulios, Demetrios Stysley, Paul R. Kay, Richard B. Coyle, Barry GP IEEE TI 100 mJ Q-Switched, High Efficiency, High Brightness Nd:YAG Oscillator: Wavefront Analysis SO 2007 CONFERENCE ON LASERS & ELECTRO-OPTICS/QUANTUM ELECTRONICS AND LASER SCIENCE CONFERENCE (CLEO/QELS 2007), VOLS 1-5 LA English DT Proceedings Paper CT Conference on Lasers and Electro-Optics/Quantum Electronics and Laser Science Conference CY MAY 06-11, 2007 CL Baltimore, MD ID ND-YAG AB A diode-pumped, 100 mJ/pulse, Nd:YAG oscillator employing a dual pump head design aligned orthogonally in an unstable resonator configuration producing aperture-free TEM00 beams is presented. (c)2007 Optical Society of America C1 [Poulios, Demetrios; Stysley, Paul R.; Kay, Richard B.] American Univ, Dept Phys, Washington, DC 20016 USA. [Coyle, Barry] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Poulios, D (reprint author), American Univ, Dept Phys, Washington, DC 20016 USA. EM barry@cornfed.gsfc.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 BN 978-1-4244-3590-6 PY 2007 BP 2262 EP + PG 2 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BKO20 UT WOS:000268751001576 ER PT B AU Bakunov, MI Bodrov, SB Maslov, AV AF Bakunov, M. I. Bodrov, S. B. Maslov, A. V. GP IEEE TI Temporal Dynamics of Optical-to-Terahertz Conversion in Electro-Optic Crystal SO 2007 CONFERENCE ON LASERS & ELECTRO-OPTICS/QUANTUM ELECTRONICS AND LASER SCIENCE CONFERENCE (CLEO/QELS 2007), VOLS 1-5 LA English DT Proceedings Paper CT Conference on Lasers and Electro-Optics/Quantum Electronics and Laser Science Conference CY MAY 06-11, 2007 CL Baltimore, MD ID RADIATION; RECTIFICATION AB We developed a theory of the optical-to-terahertz conversion of a femtosecond laser pulse with finite width in a slab of nonlinear crystal. This theory explains previous experiments and reveals new schemes for terahertz generation. (C) 2007 Optical Society of America C1 [Bakunov, M. I.; Bodrov, S. B.] Univ Nizhny Novgorod, Dept Radiophys, Nizhnii Novgorod 603950, Russia. [Bakunov, M. I.; Bodrov, S. B.] Russian Acad Sci, Inst Appl Sci, Nizhnii Novgorod 117901, Russia. [Maslov, A. V.] NASA, Ames Res Ctr, Ctr Nanotechnol, Moffett Field, CA 94035 USA. RP Bakunov, MI (reprint author), Univ Nizhny Novgorod, Dept Radiophys, Nizhnii Novgorod 603950, Russia. EM bakunov@rf.unn.ru; bosbor@ufp.appl.sci-nnov.ru RI Bodrov, Sergey/D-1962-2012; Bakunov, Michael/E-2875-2017 OI Bakunov, Michael/0000-0002-4209-1372 FU RFBR [05-02-39022, 06-02-17495] FX M.I.B. and S.B.B. were supported in part by RFBR Grant Nos. 05-02-39022 and 06-02-17495. NR 4 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-3590-6 PY 2007 BP 2272 EP + PG 2 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BKO20 UT WOS:000268751001581 ER PT B AU Maslov, AV Ning, CZ AF Maslov, A. V. Ning, C. Z. GP IEEE TI Metal-encased semiconductor nanowires as waveguides for ultrasmall lasers SO 2007 CONFERENCE ON LASERS & ELECTRO-OPTICS/QUANTUM ELECTRONICS AND LASER SCIENCE CONFERENCE (CLEO/QELS 2007), VOLS 1-5 LA English DT Proceedings Paper CT Conference on Lasers and Electro-Optics/Quantum Electronics and Laser Science Conference CY MAY 06-11, 2007 CL Baltimore, MD AB We show that a semiconductor nanowire encased by a metal offers the smallest laser waveguide, despite the large Joule loss. The TM(01) mode immediately above its cut-off is most advantageous for making sub-wavelength lasers. (C) 2006 Optical Society of America C1 [Maslov, A. V.; Ning, C. Z.] NASA, Ames Res Ctr, Ctr Nanotechnol, Moffett Field, CA 94035 USA. RP Maslov, AV (reprint author), NASA, Ames Res Ctr, Ctr Nanotechnol, MS 229-1, Moffett Field, CA 94035 USA. EM amaslov@mail.arc.nasa.gov; cning@mail.arc.nasa.gov NR 7 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-3590-6 PY 2007 BP 2326 EP 2327 PG 2 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BKO20 UT WOS:000268751001608 ER PT B AU Harry, GM Folkner, W Fritschel, P Phinney, ES Shaddock, DA AF Harry, Gregory M. Folkner, William Fritschel, Peter Phinney, E. Sterl Shaddock, Daniel A. GP IEEE TI The Big Bang Observer: High Laser Power for Gravitational Wave Astrophysics SO 2007 CONFERENCE ON LASERS & ELECTRO-OPTICS/QUANTUM ELECTRONICS AND LASER SCIENCE CONFERENCE (CLEO/QELS 2007), VOLS 1-5 LA English DT Proceedings Paper CT Conference on Lasers and Electro-Optics/Quantum Electronics and Laser Science Conference CY MAY 06-11, 2007 CL Baltimore, MD AB The Big Bang Observer(BBO) is a proposed space-based gravitational wave detector which will look for the stochastic background of gravitational waves from the early universe. The positions of three free test masses, 50,000 km apart, will be monitored by laser interferometry. To reduce noise, 300 W of 355 urn light obtained from frequency-tripling the output of Nd:YAG lasers will be used. These lasers and other technology necessary for BBO will require significant research before a potential launch date of 2025. C1 [Harry, Gregory M.; Fritschel, Peter] MIT, LIGO Lab, 77 Massachusetts Ave, Cambridge, MA 02139 USA. [Folkner, William; Shaddock, Daniel A.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Phinney, E. Sterl] CALTECH, Pasadena, CA 91125 USA. RP Harry, GM (reprint author), MIT, LIGO Lab, 77 Massachusetts Ave, Cambridge, MA 02139 USA. EM gharry@ligo.mit.edi RI Shaddock, Daniel/A-7534-2011 OI Shaddock, Daniel/0000-0002-6885-3494 NR 6 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-3590-6 PY 2007 BP 2792 EP 2792 PG 1 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BKO20 UT WOS:000268751001857 ER PT B AU Shmerko, VP Yanushkevich, SN Moon, H Stoica, A Yager, RR AF Shmerko, V. P. Yanushkevich, S. N. Moon, H. Stoica, A. Yager, R. R. BE Stoica, A Arslan, T Howard, D Kim, TH ElRayis, A TI Accelerating decision making support in biometric assistant for remote temperature measures SO 2007 ECSIS SYMPOSIUM ON BIO-INSPIRED, LEARNING, AND INTELLIGENT SYSTEMS FOR SECURITY, PROCEEDINGS LA English DT Proceedings Paper CT ECSIS Symposium on Bio-Inspired, Learning and Intelligent Systems for Security (BLISS 2007) CY AUG 09-SEP 10, 2007 CL Univ Edinburgh, Edinburgh, SCOTLAND SP EU, European Ctr Secure Informat & Syst HO Univ Edinburgh AB This paper aims to contribute to the practice of biometrics-based physical access control system design. Such a system is the distributed network of biometric-based assistants. Assistants are considered to be decision making support components in a system. In this paper the techniques for accelerating decision making support for remote temperature measures are proposed. These techniques are based on semantic interpretation of biometric data, in particular, infrared images, implemented as accelerators using field-programmable gate arrays (FPGAs). Semantics are based on the theory of belief functions, concerned with the problem of representing and manipulating uncertain information. C1 [Shmerko, V. P.; Yanushkevich, S. N.; Moon, H.] Univ Calgary, ECE Dept, Calgary, AB, Canada. [Stoica, A.] NASA, Calif Inst Technol, Jet Propuls Lab, Humanoid Robot Lab, Pasadena, CA USA. [Yager, R. R.] Iona Coll, Inst Machine Intelligence, New Rochelle, NY 10801 USA. RP Shmerko, VP (reprint author), Univ Calgary, ECE Dept, Calgary, AB, Canada. EM syanshk@ucalgary.ca; hmoon@ucalgary.ca; Adrian.Stoica@jpl.nasa.gov; yager@panix.com RI Yager, Ronald/A-2960-2013 FU Natural Sciences and Engineering Research Council of Canada (NSERC); Canadian Foundation for Innovations (CFI); Government of the Province of Alberta; Alberta Informatics Circle of Excellence (iCore) FX This Project was partially supported by the Natural Sciences and Engineering Research Council of Canada (NSERC), the Canadian Foundation for Innovations (CFI), the Government of the Province of Alberta, and the Alberta Informatics Circle of Excellence (iCore). A part of the Project has been implemented as an initiative within the JPLs Humanoid Robotics Laboratory and Machine Intelligence Institute, Iona College, New Rochelle, NY. 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 978-0-7695-2919-6 PY 2007 BP 11 EP + DI 10.1109/BLISS.2007.38 PG 2 WC Automation & Control Systems; Computer Science, Artificial Intelligence; Computer Science, Interdisciplinary Applications; Computer Science, Theory & Methods; Mathematical & Computational Biology SC Automation & Control Systems; Computer Science; Mathematical & Computational Biology GA BGP99 UT WOS:000249653000002 ER PT B AU Ponchak, GE Jordan, JL Scardelletti, M Stalker, AR AF Ponchak, George E. Jordan, Jennifer L. Scardelletti, Maximilian Stalker, Amy R. GP IEEE TI Characteristics of coplanar waveguide on sapphire for high temperature applications (25 to 4000 degrees C) SO 2007 EUROPEAN MICROWAVE CONFERENCE, VOLS 1-4 LA English DT Proceedings Paper CT 37th European Microwave Conference CY OCT 08-12, 2007 CL Munich, GERMANY AB This paper presents the characteristics of coplanar waveguide transmission lines fabricated on R-plane sapphire substrates as a function of temperature across the temperature range of 25 to 400 degrees C. Effective permittivity and attenuation are measured on a high temperature probe station. Two techniques are used to obtain the transmission line characteristics, a Thru-Reflect-Line calibration technique that yields the propagation coefficient and resonant stubs. To a first order fit of the data, the effective permittivity and the attenuation increase linearly with temperature. C1 [Ponchak, George E.; Jordan, Jennifer L.; Scardelletti, Maximilian; Stalker, Amy R.] NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Ponchak, GE (reprint author), NASA, Glenn Res Ctr, 21000 Brook Pk Rd, Cleveland, OH 44135 USA. NR 16 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-2-87487-001-9 PY 2007 BP 925 EP 928 DI 10.1109/EUMC.2007.4405345 PG 4 WC Engineering, Electrical & Electronic; Optics; Telecommunications SC Engineering; Optics; Telecommunications GA BHS15 UT WOS:000255921400236 ER PT S AU Moghaddam, B Weiss, Y Avidan, S AF Moghaddam, Baback Weiss, Yair Avidan, Shai GP IEEE TI Fast pixel/part selection with sparse eigenvectors SO 2007 IEEE 11TH INTERNATIONAL CONFERENCE ON COMPUTER VISION, VOLS 1-6 SE IEEE International Conference on Computer Vision LA English DT Proceedings Paper CT 11th IEEE International Conference on Computer Vision CY OCT 14-21, 2007 CL Rio de Janeiro, BRAZIL SP IEEE AB We extend the "Sparse LDA" algorithm of [7] with new sparsity bounds on 2-class separability and efficient partitioned matrix inverse techniques leading to 1000-fold speed-ups. This mitigates the O(n(4)) scaling that has limited this algorithm's applicability to vision problems and also prioritizes the less-myopic backward elimination stage by making it faster than forward selection. Experiments include "sparse eigenfaces" and gender classification on FERET data as well as pixel/part selection for OCR on MNIST data using Bayesian (GP) classification. Sparse-LDA is an attractive alternative to the more demanding Automatic Relevance Determination. State-of-the-art recognition is obtained while discarding the majority of pixels in all experiments. Our sparse models also show a better fit to data in terms of the "evidence" or marginal likelihood. C1 [Moghaddam, Baback] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91125 USA. [Weiss, Yair] Hebrew Univ Jerusalem, Jerusalem, Israel. [Avidan, Shai] Adobe Syst Inc, Boston, MA USA. RP Moghaddam, B (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91125 USA. EM baback@jpl.nasa.gov; yweiss@cs.huji.ac.il; avidan@adobe.com 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 1550-5499 BN 978-1-4244-1630-1 J9 IEEE I CONF COMP VIS PY 2007 BP 2073 EP + PG 2 WC Computer Science, Artificial Intelligence; Engineering, Electrical & Electronic; Imaging Science & Photographic Technology SC Computer Science; Engineering; Imaging Science & Photographic Technology GA BHP11 UT WOS:000255099302007 ER PT B AU Chung, DJ Anagnostou, D Ponchak, G Tentzeris, MM Papapolymerou, J AF Chung, D. J. Anagnostou, D. Ponchak, G. Tentzeris, M. M. Papapolymerou, J. GP IEEE TI Light weight MIMO phased arrays with beam steering capabilities using RF MEMS SO 2007 IEEE 18TH INTERNATIONAL SYMPOSIUM ON PERSONAL, INDOOR AND MOBILE RADIO COMMUNICATIONS, VOLS 1-9 LA English DT Proceedings Paper CT 18th IEEE International Symposium on Personal, Indoor and Mobile Radio Communication CY SEP 03-07, 2007 CL Athens, GREECE SP IEEE Commun Soc, Univ Athens, Natl Tech AB A conceptual design of a MIMO Phased antenna array on Liquid Crystal Polymer (LCP) is introduced. Because of the properties of the substrate, the overall design is comparably light weight and semi-flexible to previous MIMO designs. Each input output unit array is capable of steering the beam +/- 6 degrees in a 1-D space. This beam steer is enabled with the use of a 2-bit reconfigurable phase shifter using RF MEMS. The building blocks of a single input and output has been simulated to prove the concept. In addition, the array can be expanded to beam steer in a 2-D space for each individual unit. Overall, the entire system Will be capable of having the beam steering function in multiple directions. C1 [Chung, D. J.; Tentzeris, M. M.; Papapolymerou, J.] Georgia Inst Technol, Atlanta, GA 30332 USA. [Anagnostou, D.] SD Sch Mines & Technol, Rapid City, SD USA. [Ponchak, G.] NASA, Glenn Res Ctr, Cleveland, OH USA. RP Chung, DJ (reprint author), Georgia Inst Technol, Atlanta, GA 30332 USA. RI Anagnostou, Dimitris/A-3124-2009 OI Anagnostou, Dimitris/0000-0003-4266-0309 NR 5 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-1143-6 PY 2007 BP 1902 EP + PG 2 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BHI16 UT WOS:000253402501088 ER PT S AU Muir, J Xia, Y Holguin, N Judex, S Qin, YX Jeka, J Evans, H Lang, T Rubin, C AF Muir, J. Xia, Y. Holguin, N. Judex, S. Qin, Y-X Jeka, J. Evans, H. Lang, T. Rubin, C. GP IEEE TI Retention of bone density and postural status with a non-invasive extremely low level mechanical signal: A ground based evaluation of efficacy SO 2007 IEEE 33RD ANNUAL NORTHEAST BIOENGINEERING CONFERENCE SE Annual IEEE Northeast Bioengineering Conference LA English DT Proceedings Paper CT IEEE 33rd Annual Northeast Bioengineering Conference CY MAR 10-11, 2007 CL Long Isl, NY SP IEEE, EMB, AIChE ID LOW-MAGNITUDE AB In space, rapid losses in bone mineral density (BMD) leave astronauts at an increased risk of bone fracture. Longer microgravity missions combined with the lack of efficacy of current exercise regimes in reducing this loss leads to the need of a new treatment. This study has the goal of testing a treatment in the form of a low magnitude mechanical vibration. As an analog of space flight, 18 subjects spent 90 days in continuous 6 degree head down tilt, eight of which received 10 minutes of vibration treatment a day. Measurements of bone density and balance found that there was a 30-50% nonsignificant reduction in BMD loss in the hip, as well as a significant decrease in the loss of postural control. The combined factors of stronger bones and increased balance greatly reduce the risk of bone fracture. With a proposed multi-year planetary mission to Mars being planned by NASA, the need for improved musculoskeletal health is of increasing importance, and this device may provide the needed mode of increasing astronaut safety. C1 [Muir, J.; Xia, Y.; Holguin, N.; Judex, S.; Qin, Y-X; Rubin, C.] SUNY Stony Brook, Stony Brook, NY 11794 USA. [Jeka, J.] Univ Maryland, College Pk, MD 21228 USA. [Evans, H.] NASA, Johnson Space Ctr, Houston, TX USA. [Lang, T.] Univ Calif San Francisco, San Francisco, CA 94143 USA. RP Muir, J (reprint author), SUNY Stony Brook, Stony Brook, NY 11794 USA. RI Lang, Thomas/B-2685-2012 OI Lang, Thomas/0000-0002-3720-8038 FU NASA [NRA-03-OBRP-06] FX We are grateful for the financial support provided by NASA NRA-03-OBRP-06, and to the entire bed rest team led by Dr. Jan Meck. 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 0277-1063 BN 978-1-4244-1032-3 J9 NORTHEAST BIOENGIN C PY 2007 BP 1 EP + DI 10.1109/NEBC.2007.4413250 PG 2 WC Engineering, Biomedical; Engineering, Electrical & Electronic; Materials Science, Biomaterials; Radiology, Nuclear Medicine & Medical Imaging SC Engineering; Materials Science; Radiology, Nuclear Medicine & Medical Imaging GA BHP13 UT WOS:000255100600001 ER PT S AU Holguin, N Muir, J Evans, HJ Qin, YX Rubin, C Wagshul, M Judex, S AF Holguin, Nilsson Muir, Jesse Evans, Harlan J. Qin, Yi-Xian Rubin, Clinton Wagshul, Mark Judex, Stefan GP IEEE TI Mechanical vibrations reduce the intervertebral disc swelling and muscle atrophy from bed rest SO 2007 IEEE 33RD ANNUAL NORTHEAST BIOENGINEERING CONFERENCE SE Annual IEEE Northeast Bioengineering Conference LA English DT Proceedings Paper CT IEEE 33rd Annual Northeast Bioengineering Conference CY MAR 10-11, 2007 CL Long Isl, NY SP IEEE, EMB, AIChE ID IN-VIVO; VOLUME; MOTION; MRI AB Loss of functional weight bearing, such as experienced during space flight or bedrest, causes detrimental morphological volume changes to the intervertebral. disc (IVD) beyond the normal diurnal cycle (10-13%), and muscle. Bed rest (BR) was used to test the hypothesis that, short-duration, low-magnitude, high-frequency mechanical vibrations will attenuate the IVD swelling and intrinsic back muscle atrophy induced by long-term bedrest. Control and experimental subjects underwent BR for up to 90d and were scanned by CT at 0d and 90d, and by MRI at 0d, 60d, 90d and 8d after completion of BR. In addition, experimental subjects received vibrations at 0.3g and 30Hz for 10min/day. Muscle volume was measured by CT scans and IVD volume was measured by MRI scans. During BR, mechanical vibrations abated the IVD swelling at 60d by 150% and 90d by 65%. Eight days after bed rest, the control group showed a plasticity of 9%, while the experimental group showed no residual change (p>0.05). Mechanical vibrations reduced the intrinsic back muscle atrophy from long-term bed rest by 33% (p>0.05). These data demonstrate the rapid deterioration of the musculoskeletal system with BR but present vibrations as a promising non-pharmacologic countermeasure to disc degeneration and muscle atrophy. C1 [Holguin, Nilsson; Muir, Jesse; Qin, Yi-Xian; Rubin, Clinton; Wagshul, Mark; Judex, Stefan] SUNY Stony Brook, Dept Biomed Engn, Stony Brook, NY 11794 USA. [Evans, Harlan J.] NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. RP Holguin, N (reprint author), SUNY Stony Brook, Dept Biomed Engn, Stony Brook, NY 11794 USA. FU National Space Biomedical Research Institute; NASA FX This research opportunity was funded by the National Space Biomedical Research Institute and NASA. NR 8 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 0277-1063 BN 978-1-4244-1032-3 J9 NORTHEAST BIOENGIN C PY 2007 BP 25 EP + DI 10.1109/NEBC.2007.4413262 PG 2 WC Engineering, Biomedical; Engineering, Electrical & Electronic; Materials Science, Biomaterials; Radiology, Nuclear Medicine & Medical Imaging SC Engineering; Materials Science; Radiology, Nuclear Medicine & Medical Imaging GA BHP13 UT WOS:000255100600013 ER PT S AU Carsten, J Rankin, A Ferguson, D Stentz, A AF Carsten, Joseph Rankin, Arturo Ferguson, Dave Stentz, Anthony GP IEEE TI Global path planning on board the mars exploration rovers SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES DE MER; robotics; Mars rover; flight software; autonomous; navigation; path planning; Field D* AB In January 2004, NASN's twin Mars Exploration Rovers (MERs), Spirit and Opportunity, began searching the surface of Mars for evidence of past water activity. In order to localize and approach scientifically interesting targets, the rovers employ an on-board navigation system. Given the latency in sending commands from Earth to the Martian rovers (and in receiving return data), a high level of navigational autonomy is desirable. Autonomous navigation with hazard avoidance (AutoNav) is currently performed using a local path planner called GESTALT (Grid-based Estimation of Surface Traversability Applied to Local Terrain). GESTALT uses stereo cameras to evaluate terrain safety and avoid obstacles. GESTALT works well to guide the rovers around narrow and isolated hazards, however, it is susceptible to failure when clusters of closely spaced, non-traversable rocks form extended obstacles. In May 2005, a new technology task was initiated at the Jet Propulsion Laboratory to address this limitation. A version of the Carnegie Mellon University Field D* global path planner has been integrated into MER flight software, enabling simultaneous local and global planning during AutoNav. A revised version of AutoNav was uploaded to the rovers during the summer of 2006. This paper describes how global planning was integrated into the MER flight software, and presents results of testing the improved AutoNav system using the MER Surface System TestBed rover. C1 [Carsten, Joseph; Rankin, Arturo] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Ferguson, Dave; Stentz, Anthony] Carnegie Mellon Univ, Inst Robot, Pittsburgh, PA 15213 USA. RP Carsten, J (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM joseph.carsten@jpl.nasa.gov; arturo.rankin@jpl.nasa.gov; dif@cmu.edu; tony@cmu.edu NR 10 TC 0 Z9 0 U1 3 U2 3 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 9 EP + PG 2 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235300002 ER PT S AU Helmick, DM Angelova, A Livianu, M Matthies, LH AF Helmick, Daniel M. Angelova, Anelia Livianu, Matthew Matthies, Larry H. GP IEEE TI Terrain adaptive navigation for Mars rovers SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB A navigation system for Mars rovers in very rough terrain has been designed, implemented, and tested on a research rover in Mars analog terrain. This navigation system consists of several technologies that are integrated to increase the capabilities compared to current rover navigation algorithms. These technologies include: goodness maps and terrain triage, terrain classification, remote slip prediction, path planning, high-fidelity traversability analysis (HFTA), and slip-compensated path following. The focus of this paper is not on the component technologies, but rather on the integration of these components. Results from the onboard integration of several of the key technologies described here are shown. Additionally, the results from independent demonstrations of several of these technologies are shown. Future work will include the demonstration of the entire integrated system described here. C1 [Helmick, Daniel M.; Angelova, Anelia; Livianu, Matthew; Matthies, Larry H.] Jet Prop Lab, Pasadena, CA 91106 USA. RP Helmick, DM (reprint author), Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91106 USA. NR 24 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 20 EP 30 PG 11 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235300003 ER PT S AU DiCicco, M Bajracharya, M Nickels, K Backes, P AF DiCicco, Matthew Bajracharya, Max Nickels, Kevin Backes, Paul GP IEEE TI The EPEC algorithm for vision guided manipulation: Analysis and validation SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB This paper describes the simulated performance and experimental validation of a computationally efficient algorithm for improving positioning accuracy of robot arms using low speed feedback from fixed stereo cameras. The algorithm, called End-Effector Position Error Compensation (EPEC) is robust to visual occlusion of the end-effector and does not require high fidelity calibration of either the arm or stereo camera. The algorithm works by calculating an error vector between the locations of a fiducial on the arm's end-effector as predicted by arm kinematics and detected by a stereo camera triangulation. With this knowledge, the commanded target pose is adjusted to compensate for positioning errors. A simulation environment where arbitrary error can be introduced into arm-camera systems is introduced and used to provide an assessment of the performance of the algorithm under both ideal and degraded conditions. Experimental results in the laboratory and on Mars are presented to validate the simulated performance estimates. C1 [DiCicco, Matthew; Bajracharya, Max; Nickels, Kevin; Backes, Paul] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP DiCicco, M (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 16 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 31 EP 41 PG 11 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235300004 ER PT S AU Nickels, K Bajracharya, M Trebi-Ollennu, A Liebersbach, R AF Nickels, Kevin Bajracharya, Max Trebi-Ollennu, Ashitey Liebersbach, Robert GP IEEE TI Kinematic-vision residuals analysis SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES ID MARS EXPLORATION ROVER AB This paper describes the design, validation, and integration of a tool to locate a portion of the Instrument Deployment Device (IDD) on the Mars Exploration Rover (MER) vehicles on Mars in imagery from the front Hazard avoidance cameras, and to track the differences between the predicted and detected position of the manipulator over time. The analysis of Kinematic-Vision Residuals, or the difference between where a manipulator is expected to appear in onboard imagery and where it actually appears in the imagery, yields insight into several aspects of an operational robotic system. The fidelity of the IDD and camera models is evaluated. Systematic changes in the performance over time can give insight to rover degradation or other changes. Finally, new models can be proposed and evaluated on the basis of trended data over time. C1 [Nickels, Kevin] Trinity Univ, Dept Engn Sci, 1 Trinity Pl, San Antonio, TX 78259 USA. [Bajracharya, Max; Trebi-Ollennu, Ashitey; Liebersbach, Robert] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Nickels, K (reprint author), Trinity Univ, Dept Engn Sci, 1 Trinity Pl, San Antonio, TX 78259 USA. EM knickels@trinity.edu; maxb@robotics.jpl.nasa.gov; ashitey@jpl.nasa.gov; Robert.R.Liebersbach-121188@jpl.nasa.gov NR 10 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 42 EP + PG 2 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235300005 ER PT S AU Mungas, C Fisher, D Mungas, GS Apostolopoulos, D Wagner, M AF Mungas, Christopher Fisher, David Mungas, Greg S. Apostolopoulos, Dimi Wagner, Michael GP IEEE TI SILVRCLAW III - Advanced wheel design and testing SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB Enhancing robotic(1,2) surface mobility systems are a fundamental Mars Exploration Program goal because many surface-investigation goals require traversing significant distances in widely varying terrain conditions. SILVRCLAW (Stowable, Inflatable, Large, Vectran, Rigidizable, Cold-resistant, Lightweight, All-terrain Wheel) is an inflatable, rigidizable wheel technology that enables compact robotic vehicles to be deployed with significant ground clearance. Such a vehicle could traverse aggressive rocky terrains with a resultant low obstacle density (less than one obstacle per similar to 100m), travel over chasms with >1m separation, and offer the mission operator the ability to navigate with orbital-imaging resolution (i.e. with Mars Reconnaissance Orbiter's Highrise telescope). Because of its high intrinsic mobility, SILVRCLAW can negotiate substantial obstacles, thus allowing a robotic rover to climb over obstacles as opposed to driving around them. Such capability could dramatically increase terrain access and rover range for a given weight class. In previous work, we reported on the development and initial testing of a SILVRCLAW exoskeleton wheel shell for purposes of understanding mobility performance and wear in Mars-like simulants. In this work we discuss environmental testbed results of a new cleated SILVRCLAW exoskeleton shell and the current development of a prototype deployable SILVRCLAW. C1 [Mungas, Christopher; Fisher, David] Firestar Engn LLC, 557 Burbank St, Broomfield, CO 80020 USA. [Mungas, Greg S.] Jet Prop Lab, Pasadena, CA 91109 USA. [Apostolopoulos, Dimi; Wagner, Michael] Protolnnovat LLC, Pittsburgh, PA 15224 USA. RP Mungas, C (reprint author), Firestar Engn LLC, 557 Burbank St, Broomfield, CO 80020 USA. EM chris@firestar-engineering.com; david@firestar-engineering.com; greg.mungas@jpl.nasa.gov; dalv@protoinnovations.com; mwagner@protoinnovations.com FU NASA's Mars Technology Program/Base Technology/Rover Technology [MT03- 0000-0167]; Mars Technology Program's staff FX The SILVRCLAW team gratefully acknowledges the support of NASA's Mars Technology Program/Base Technology/Rover Technology through Contract# MT03- 0000-0167, the Mars Technology Program's staff, and the large number of technology program review committee members who have contributed to make this work possible. NR 5 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 53 EP + PG 3 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235300006 ER PT S AU Backes, P Collins, C AF Backes, Paul Collins, Curtis GP IEEE TI A sample caching concept for planetary missions SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB A Sample Caching Subsystem (SCS) concept that provides transfer and storage of core and soil samples for planetary missions has been developed. The SCS could be carried on a rover and a rover arm-mounted coring tool could acquire samples and deposit the samples in the SCS. The SCS would transfer the samples into a sample container, with each sample in a separate sleeve. Important to the SCS design is the ability to seal each sleeve, and the sample with it, to isolate it from other samples and from the external environment. Sealing of the samples will allow for maintaining the integrity of organic materials over many years thereby allowing the samples to be analyzed in later missions or after a return trip to Earth. C1 [Backes, Paul; Collins, Curtis] CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. RP Backes, P (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. NR 12 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 63 EP 68 PG 6 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235300007 ER PT S AU Curtis, S Brandt, M Bowers, G Brown, G Cheung, C Cooperider, C Desch, M Desch, N Dorband, J Gregory, K Lee, K Lunsford, A Minetto, F Truszkowski, W Wesenberg, R Vranish, J Abrahantes, M Clark, P Capon, T Weaker, M Watson, R Olivier, P Rilee, ML AF Curtis, Steven Brandt, Matthew Bowers, Greg Brown, Gary Cheung, Cynthia Cooperider, Caner Desch, Mike Desch, Noah Dorband, John Gregory, Kyle Lee, Ken Lunsford, Allan Minetto, Fred Truszkowski, Walt Wesenberg, Richard Vranish, John Abrahantes, Miguel Clark, Pamela Capon, Tom Weaker, Michael Watson, Richard Olivier, Philip Rilee, Michael L. GP IEEE TI Tetrahedral robotics for space exploration SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB A reconfigurable space filling robotic architecture has a wide range of possible applications. One of the more intriguing possibilities is mobility in very irregular and otherwise impassable terrain. NASA Goddard Space Flight Center is developing the third generation of its Addressable Reconfigurable Technology (ART) Tetrahedral Robotics Architecture. An ART-based variable geometry truss consisting of 12 tetrahedral elements made from 26 smart struts on a wireless network has been developed. The primary goal of this development is the demonstration of a new kind of robotic mobility that can provide access and articulation that complement existing capabilities. An initial set of gaits and other behaviors are being tested, and accommodations for payloads such as sensor and telemetry packages are being studied. In this paper, we describe our experience with the ART Tetrahedral Robotics Architecture and the improvements implemented in the third generation of this technology. Applications of these robots to space use the 12-TET as a vehicle to carry science instruments in crewed or un-crewed mission contexts. Even our current 3(rd)-generation 12-TET points out the possibility of providing mobile payload capacity at either central or corner nodes. The ART/TR architecture provides a unique capability to construct a wide variety of reconfigurable truss structures all constructed from the same fundamental strut and node elements, providing the possibility of a great deal of flexibility and functionality in an undifferentiated system. C1 [Curtis, Steven; Brandt, Matthew; Bowers, Greg; Brown, Gary; Cheung, Cynthia; Cooperider, Caner; Desch, Mike; Desch, Noah; Dorband, John; Gregory, Kyle; Lee, Ken; Lunsford, Allan; Minetto, Fred; Truszkowski, Walt; Wesenberg, Richard; Vranish, John] NASA, Goddard Space Flight Ctr, Lab Planetary Magnetospheres, Code 695, Greenbelt, MD 20771 USA. [Abrahantes, Miguel] Hope Coll, Holland, MI USA. [Clark, Pamela; Capon, Tom; Weaker, Michael; Watson, Richard] Catholic Univ Amer, Washington, DC 20064 USA. [Olivier, Philip] Mercer Univ, Macon, GA USA. [Rilee, Michael L.] Comp Sci Corp, Cincinnati, OH 45202 USA. RP Curtis, S (reprint author), NASA, Goddard Space Flight Ctr, Lab Planetary Magnetospheres, Code 695, Greenbelt, MD 20771 USA. EM Steven.A.Curtis@nasa.gov; abrahantes@hope.edu; Pamela.E.Clark.1@gsfc.nasa.gov; olivier_pd@mercer.edu; Michael.Rilee@csc.com NR 9 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 69 EP + PG 2 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235300008 ER PT S AU Nickels, K Huber, E DiCicco, M AF Nickels, Kevin Huber, Eric DiCicco, Matthew GP IEEE TI Hand-eye calibration using active vision SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES ID CAMERAS AB The project described in this paper designed and implemented a hand-eye calibration method for manipulators under observation by stereo cameras. This method has been utilized on Johnson Space Center's Robonaut, and on a planetary manipulator mock-up at the Jet Propulsion Laboratory. The intent of this calibration is to improve the manipulator's hand-eye coordination. The approach uses kinematic and stereo vision measurements, namely the joint angles self-reported by the arm and 3-D positions of a calibration fixture as measured by vision, to estimate the transformation from the arm's base coordinate system to its hand coordinate system and to its vision coordinate system. In this formulation, the stereo measurements are assumed to be accurate, and any mismatches are absorbed in a modified model of the arm. These methods have shown to reduce mismatch between kinematically derived positions and visually derived positions on Robonaut Unit A from a mean of 13.75cm to a mean of 1.85cm. Improved performance in semi-autonomous tasks is also described. On JPL's manipulator, with kinematics similar to that of the Mars Exploration Rover, the calibration reduced the mismatch from 15.26mm to between 3mm and 5.5mm. C1 [Nickels, Kevin] Trinity Univ, Dept Engn Sci, 1 Trinity Pl, San Antonio, TX 78259 USA. [Huber, Eric] NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. [DiCicco, Matthew] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Nickels, K (reprint author), Trinity Univ, Dept Engn Sci, 1 Trinity Pl, San Antonio, TX 78259 USA. EM knickels@trinity.edu; eric@roboteyes.com; Matthew.A.Dicicco@jpl.nasa.gov NR 26 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 78 EP + PG 3 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235300009 ER PT S AU Graham, JB AF Graham, Jerry B. GP IEEE TI Prospecting rovers for Lunar exploration SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB A study of rover options for exploring the permanently shadowed regions of the lunar environment is presented. The potential for nearly continuous solar illumination and the possible existence of substantial water ice deposits focus the exploration planner's attention on the polar regions of the Moon. These regions feature permanently shadowed craters that, remote sensing data suggest, may contain water ice. This water ice, if present, can be converted to fuel cell reactants, breathing oxygen, potable water, and rocket propellant, all vital resources for the ultimate exploration of the moon and the solar system. To provide early ground truth on the existence and abundance of this water ice for subsequent mission planning purposes, the NASA Lunar Precursor Robotics Program (LPRP) sponsored a study of potential prospecting rover concepts as one part of the LPRP-2 Pre-Phase A studies. Numerous vehicle configurations were conceptualized to support a suite of prospecting and scientific measurement equipment for sustained operations in a permanently shadowed crater. Trades and analyses were performed for key functions including mobility, power, and thermal management. Rover options in the 400 to 530 kg class are developed which are capable of either confirming the presence of water ice at the poles or conclusively demonstrating its absence. C1 [Graham, Jerry B.] NASA, George C Marshall Space Flight Ctr, Huntsville, AL 35812 USA. RP Graham, JB (reprint author), NASA, George C Marshall Space Flight Ctr, Huntsville, AL 35812 USA. NR 4 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 88 EP 98 PG 11 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235300010 ER PT S AU Diner, DJ Boland, SW Davis, ES Kahn, RA Hostetler, CA Ferrare, RA Hair, JW Cairns, B Torres, O AF Diner, David J. Boland, Stacey W. Davis, Edgar S. Kahn, Ralph A. Hostetler, Chris A. Ferrare, Richard A. Hair, John W. Cairns, Brian Torres, Omar GP IEEE TI Future mission concept for 3-d remote sensing of aerosols from low earth Orbit SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES ID MULTIWAVELENGTH LIDAR; PARAGON FRAMEWORK; SATELLITE DATA; AIR-POLLUTION; AMAZON SMOKE; CLOUD; RETRIEVAL; PARAMETERS; PROFILES; CLIMATE AB Aerosols are generated and transformed by myriad processes, affecting Earth's climate, hydrological cycle, air quality, and human health. In this paper, we describe the scientific rationale and mission architecture for a future aerosol mission concept, the Aerosol Global Interactions Satellite (AEGIS). Its payload is designed to eliminate ambiguities in aerosol microphysical retrievals and contribute to the next generation of atmospheric models. By combining several satellite-based approaches aimed at observing the 3-D distribution of aerosol abundances, sizes, shapes, and absorption, AEGIS represents a major advance in our ability to monitor and characterize particulate matter from space, and comprises a logical next step beyond the Earth Observing System, the "A-train," and Glory. C1 [Diner, David J.; Boland, Stacey W.; Davis, Edgar S.; Kahn, Ralph A.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Hostetler, Chris A.; Ferrare, Richard A.; Hair, John W.] NASA Langley Res Ctr, Hampton 23681, VA USA. [Cairns, Brian] Columbia Univ, Goddard Inst Space Studies, New York, NY 10025 USA. [Torres, Omar] NASA, Goddard Space Flight Ctr, Univ Maryland Baltimore Cty, Greenbelt, MD 20771 USA. RP Diner, DJ (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM David.J.Diner@jpl.nasa.gov; Chris.A.Hostetler@nasa.gov; bcairns@giss.nasa.gov; torres@qhearts.gsfc.nasa.gov RI Kahn, Ralph/D-5371-2012; Torres, Omar/G-4929-2013 OI Kahn, Ralph/0000-0002-5234-6359; NR 50 TC 0 Z9 0 U1 0 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 119 EP + PG 4 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235300013 ER PT S AU Clark, KB AF Clark, Karla B. GP IEEE TI Europa explorer - An exceptional mission using existing technology SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB A mission to Europa has been identified as a high priority by the science community for several years. The difficulty of an orbital mission-due primarily to the propulsive requirements and Jupiter's trapped radiation-led to many studies that investigated various approaches to meeting the science goals. The Europa Orbiter Mission studied in the late 1990s only met the most fundamental science objectives. The science objectives have evolved with the discoveries from the Galileo mission. JPL studied one concept-Europa Explorer-for a Europa orbiting mission that could meet a much-expanded set of science objectives. A study science group was formed to verify that the science objectives and goals were being adequately met by the resulting mission design concept. The Europa Explorer design emerged primarily from two key self-imposed constraints: 1) Meet the full set of identified non-lander science objectives. 2) Use only existing technology. Though other design concepts are viable for alternate program constraint sets, this paper will only discuss the results of this concept study. C1 [Clark, Karla B.] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Clark, KB (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,Mail Stop 301-360, 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 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 139 EP 158 PG 20 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235300015 ER PT S AU Diner, DJ Booth, JT Davis, ES Jovanovic, V Macenka, SA Moroney, C Davies, R AF Diner, David J. Booth, Jeffrey T. Davis, Edgar S. Jovanovic, Veljko Macenka, Steven A. Moroney, Catherine Davies, Roger GP IEEE TI Future mission concept for operational retrieval of cloud-top heights and cloud motion wind vectors SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES ID MISR AB To meet operational demands for vertically-resolved atmospheric winds, we propose a wide-swath multiangle stereo imaging system that could be easily integrated into future satellite platforms. The concept uses techniques proven with the Multi-angle Imaging SpectroRadiometer (MISR) instrument, currently flying in polar low-Earth orbit (LEO) on NASA's Terra satellite. MISR has demonstrated the feasibility of obtaining accurate stereophotogrammetric retrievals of cloud and aerosol plume heights and height-resolved cloud-tracked wind vectors. MISR obtains multiangle imagery with along-track pointing angles ranging from nadir to 70 degrees forward and backward of nadir and makes use of the several-minute time delay among a triplet of multiangle views to separate the effects of wind displacement from height-induced stereoscopic parallax. Careful attention to multiangle image co-registration (crucial for obtaining accurate wind retrievals) has led to wind estimates that exhibit negligible bias relative to reanalysis data. The root-mean-square uncertainty in speed is estimated to be in the 1-3 m/sec range, depending on whether the wind component is parallel or perpendicular to the flight direction and on the degree of quality control applied. The uncertainty in height assignment is on the order of 300 m. Comparison of results from a forward-viewing angle triplet with independent retrievals from a backward-viewing triplet provides an important control on retrieval quality. A key attribute of the stereophotogrammetric approach to retrieving cloud heights (and winds) is that the technique is purely geometric. Accurate radiometric calibration is not required, thereby enabling significant simplification of a future instrument dedicated to stereo height and wind retrievals. Furthermore, the approach is insensitive to atmospheric temperature profiles and cloud emissivities, and provides data of consistent quality at all latitudes from polar orbit. It is also purely passive, so sensor lifetime is not a major issue. Since the technique relies on pattern matching, only a single mid-visible spectral band is required (a separate thermal infrared band, e.g., at 3.7 mu m, would be needed in order to acquire measurements at night). Future improvements in computer capability will enable improved pattern-matching algorithms that could be implemented operationally. This simple, compact, and relatively inexpensive concept would assist numerical weather prediction models by retrieving cloud-motion vector winds in traditionally data-sparse areas (mid-oceans and high latitudes), would continue the unique data record begun with MISR by establishing long-term cloud-top height and cloud-motion wind monitoring with sensitivities capable of detecting atmospheric response to climate forcings, and would provide global measurements of the injection and transport heights of distinct aerosol plumes from wildfires, dust storms, and volcanic eruptions. C1 [Diner, David J.; Booth, Jeffrey T.; Davis, Edgar S.; Jovanovic, Veljko; Macenka, Steven A.; Moroney, Catherine] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Davies, Roger] Univ Auckland, Dept Phys, Auckland 92019, New Zealand. RP Diner, DJ (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM David.J.Diner@jpl.nasa.gov; r.davies@auckland.ac.nz RI Davies, Roger/D-4296-2009 OI Davies, Roger/0000-0002-2991-0409 NR 13 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 159 EP + PG 3 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235300016 ER PT S AU Elliott, JO Reh, K Spilker, T AF Elliott, John O. Reh, Kim Spilker, Tom GP IEEE TI Concept for titan exploration using a radioisotopically heated montgolfiere SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB This paper describes the results of a recent Titan exploration mission study aimed at investigating optimal methods for scientific observation of the atmosphere and surface of this veiled moon. During the course of this study a mission design concept was evolved which involves sending a two element mission to Titan, consisting of an orbiter for global observations and data relay, and an aerial vehicle which would drift in the atmosphere for more detailed surface study. The type of aerial vehicle proposed is a hot air balloon, or montgolfiere, which would use the Titan atmosphere, heated using the waste heat from its radioisotope power system to provide long term buoyancy. Once deployed, the montgolfiere would ride with the easterly winds, occasionally changing altitude to take advantage of possible reverse wind directions and even descending to the surface to physically sample sites of interest as they come up. Seasonal and tidal north-south winds would allow the mission to explore different latitudes, which Cassini data have shown to be amazingly diverse in geologic nature. Communication from the montgolfiere would be relayed through the accompanying orbiter spacecraft, as well as directly to Earth, providing the potential for data return from Titan's surface equivalent to that provided by many comparable orbiter missions at much closer destinations. C1 [Elliott, John O.; Reh, Kim; Spilker, Tom] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Elliott, JO (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 2 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 218 EP 228 PG 11 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235300021 ER PT S AU Cutts, JA Balint, TS Belz, AP Peterson, CE AF Cutts, James A. Balint, Tibor S. Belz, Andrea P. Peterson, Craig E. GP IEEE TI Overview of NASA's 2006 SSE strategic Roadmap SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB 2003 Solar System Exploration (SSE) Decadal Survey, the National Research Council (NRC) prioritized scientific targets and recommended missions to explore them. Taking these into account, NASA's 2006 Solar System Exploration (SSE) Strategic Roadmap (SRM) identified a set of large Flagship, medium New Frontiers (NF) and small Discovery class missions, addressing key exploration objectives. Discovery and NF missions are competed, and due to their lower cost caps, address fewer science objectives than the large missions, while mostly utilizing existing technologies. Directed Flagship class missions are considered necessary to answer some of the most important questions on Solar System formation and habitability. They also provide drivers for technology development, which in turn would benefit all mission classes. Additionally, this SSE SRM offers a comprehensive discussion on science objectives for Solar System exploration, and technologies enabling these missions. It outlines Research and Analysis (R&A), which is required to maintain the proposed program, and to post process scientific data. Education and Public Outreach (E/PO) communicates NASA's activities to the public of all ages, and as discussed, is considered an important part of the Agency's programs. These elements are connected through interdependencies and links to other programmatic activities, including the Mars and New Millennium Programs. The Roadmap also explores potential implementation trades, suggesting multiple ways to execute a balanced program that consist of all mission classes and supported by technology development, R&A, and E/PO, while staying within a projected budget allocation for SSE. In this paper we outline this proposed SSE Strategic Roadmap, representing NASA's exploration plans for the next three decades. C1 [Cutts, James A.; Balint, Tibor S.; Belz, Andrea P.; Peterson, Craig E.] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Cutts, JA (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,M-S 301-345, Pasadena, CA 91109 USA. NR 6 TC 0 Z9 0 U1 0 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 229 EP 238 PG 10 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235300022 ER PT S AU Urgiles, E Wilcox, J Montes, O Osman, S Venkateswaran, K Cepeda, M Maxim, J Braby, L Pillai, SD AF Urgiles, Eduardo Wilcox, Jaroslava Montes, Oliver Osman, Shariff Venkateswaran, Kasthuri Cepeda, Martha Maxim, Joseph Braby, Les Pillai, Suresh D. GP IEEE TI Electron beam irradiation for microbial reduction on spacecraft components SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES ID ASSEMBLY FACILITY; SPORES; RESISTANT; QUALITY; MEAT AB The highest degree of Planetary Protection (PP) applies to landed planetary missions and sample return missions. To date, Dry Heat Microbial Reduction (DHMR) treatment is the only NASA approved PP technique for meeting the stringent sterility requirements for life detection missions and to prevent forward contamination. However, spacecraft (s/c) and payloads are made up of a diverse set of man-made materials and components, some of which are incompatible with DHMR. NASA has therefore begun investigating several complementary sterilization techniques to DHMR. Here, we report on our progress in the investigation of the effectiveness of electron beam (e-beam) irradiation technique funded by a NASA Mars Exploration Program (MEP'03) award. E-beam irradiation using deep penetrating (several centimeters) high-energy (10 MeV) electrons is a well-developed method used for sterilization of food products in bulk quantities using linear accelerators. In contrast, low-energy (100keV) electrons deposit their energy into about 50 micrometers, comparable to the scale of bacterial spores (typically several micrometers). The match between the depth of the penetration and spore size makes the "low-energy" electron irradiation extremely efficient for surface sterilization. E-beam irradiation is non-contact, leaves no residues, and as our preliminary results indicate is compatible with many s/c materials. Secondary contamination is often unavoidable since pre-sterilized s/c parts are used again for functional testing and re-assembly, necessitating reapplication of sterilization treatment. The 100 keV electron source is sufficiently small so that it could be made portable, which would make it suited for treatment localized, previously sterilized parts and subsystems. C1 [Urgiles, Eduardo; Wilcox, Jaroslava; Montes, Oliver; Osman, Shariff; Venkateswaran, Kasthuri] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Cepeda, Martha; Maxim, Joseph; Braby, Les; Pillai, Suresh D.] Texas A&M Univ, Natl Ctr E beam Res, College Stn, TX 77843 USA. RP Urgiles, E (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Eduardo.Urgiles@jpl.nasa.gov; Jaroslava.Z.Wilcox@jpl.nasa.gov; sosman@jpl.nasa.gov; kjvenkat@jpl.nasa.gov FU NASA's MEP PP program FX This work has been supported by NASAs MEP PP03 program. NR 24 TC 0 Z9 0 U1 3 U2 6 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 239 EP + PG 4 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235300023 ER PT S AU Salinas, Y Zimmerman, W Kulczycki, E Chung, S Cholakian, T AF Salinas, Yuki Zimmerman, Wayne Kulczycki, Eric Chung, Shirley Cholakian, Tanya GP IEEE TI Bio-barriers: Preventing forward contamination and protecting planetary astrobiology instruments SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB A small team of engineers at the Jet Propulsion Laboratory (JPL), California Institute of Technology have developed a unique capability for protecting planetary environments that might harbor bio-signatures, as well as protecting the instruments looking for trace organic signatures of past and/or extant life. Bio-barrier materials, designs of bio-barrier structures for flight applications, and actual flight test results for missions such as the upcoming Mars Scout, Phoenix, 07 launch are discussed in this indepth examination of both the process and steps taken to develop effective bio-barrier mechanisms for planetary environments. C1 [Salinas, Yuki; Zimmerman, Wayne; Kulczycki, Eric; Chung, Shirley; Cholakian, Tanya] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Salinas, Y (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 6 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 254 EP 271 PG 18 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235300024 ER PT S AU Kerzhanovich, VV Hall, JL Faibrother, D Said, M AF Kerzhanovich, Viktor V. Hall, Jeffery L. Faibrother, Debora Said, Magdi GP IEEE TI Major progress in planetary aerobot technologies SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB Aerobots (robotic balloons) may significantly change the future of in situ planetary exploration. On Ve(1)nus, aerobots may serve as the scientific platforms for the in situ measurement of atmospheric gases and for the study of atmospheric circulation. They can be used to drop imaging and deep sounding probes at sites of interest and to acquire and relay high-rate imaging data. Balloon technology is enabling for any Venus surface sample return mission because of the need to lift the sample above most of the atmosphere for rocket return to Earth or Venus orbit. On Mars, aerobots can fill the gap in imaging resolution/coverage between the orbiters and rovers, and perform investigation involving atmospheric sampling, atmospheric circulation, magnetic field mapping and subsurface radar sounding. Solar-heated balloons could be used as low atmospheric decelerators for low-speed landing. On Titan, powered aerobots or even passive balloons can perform long duration low-altitude flight for surface mapping, in situ atmospheric measurements, periodic in situ 2 surface sampling and deployment of surface packages.(2) Progressively successful flight tests of different aerobots in the past several years signify major progress in the development of planetary aerobot technology. Two types of full scale Mars balloon prototypes were successfully deployed and inflated in the Mars-like environment of the Earth's stratosphere. A one-third scale prototype of the Titan airship made of cryogenic flexible material was built and tested at the Titan surface temperature of 93 K. A full-size mockup of Titan airship was aerially deployed and inflated during a helicopter drop test. A robust leak-free and sulfuric acid tolerating superpressure balloon capable for multi-day flight in Venus atmosphere has been designed, built and tested. Collectively, these results constitute an experience, knowledge and technology basis from which can be implemented low-risk element in the planetary missions. C1 [Kerzhanovich, Viktor V.; Hall, Jeffery L.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Faibrother, Debora; Said, Magdi] Goddard Space Flight Ctr, Wallops Flight Facil, Wallops Island, MD USA. RP Kerzhanovich, VV (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Viktor.V.Kerzhanovich@jpl.nasa.gov; Jeffery.L.Hall@jpl.nasa.gov NR 12 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 292 EP + PG 3 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235300026 ER PT S AU Kastner, J Beaudet, RA Dunphy, J Lin, Y Newlin, L Peterson, C Spry, A AF Kastner, Jason Beaudet, Robert A. Dunphy, Julia Lin, Ying Newlin, Laura Peterson, Craig Spry, Andy GP IEEE TI Tools for assessing planetary protection implementation strategies SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES ID AIRBORNE BACTERIAL-SPORES; MARS 1969 SPACECRAFT; MICROBIOLOGICAL PROFILES; THERMAL-RESISTANCE AB When spacecraft go to Mars, Europa, Enceladus or other solar system bodies which might be of interest relative to the process of chemical evolution and/or the origin of life, measures will be employed to ensure the missions meet strict biological contamination requirements. These measures, generically referred to as "Planetary Protection" (PP) are designed to preserve our ability to study other worlds as they exist in their natural states and help ensure that the scientific investigations (or the interpretation of scientific measurements) aren't confounded by Earth life that might have been inadvertently transferred to the body of interest. To be implemented most effectively, PP strategies should be fully integrated with the mission's schedule and cost profile, but in the early mission design stages the number of open options can make it difficult to perform planetary protection trade studies. This issue is being addressed at NASA's Jet Propulsion Laboratory (JPL) with the development of design tools that will permit the assessment of both the effectiveness and cost of alternative PP approaches in the mission design process. By applying these tools during the mission design process, project designers and program managers will be able to adopt the PP approach best suited to the mission architecture as well as estimate its cost in terms of dollars, schedule impact, and biological contamination risk.(1,2). C1 [Kastner, Jason; Beaudet, Robert A.; Dunphy, Julia; Lin, Ying; Newlin, Laura; Peterson, Craig; Spry, Andy] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Kastner, J (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 14 TC 0 Z9 0 U1 0 U2 4 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 303 EP 310 PG 8 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235300027 ER PT S AU Levin, GV Miller, JD Straat, PA Lodder, RA Hoover, RB AF Levin, Gilbert V. Miller, Joseph D. Straat, Patricia A. Lodder, Robert A. Hoover, Richard B. GP IEEE TI Detecting life and biology-related parameters on mars SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES DE words-life on Mars; Viking LR experiment; laser diode analyses; SSSI; life detection experiments; chiral metabolism; photosynthesis; circadian rhythm; water on Mars; Mars soil properties; robotic instruments; spacecraft sterilization ID LABELED RELEASE EXPERIMENT; FACULTATIVE ANAEROBE; SP-NOV.; PERMAFROST; ICE; MICROORGANISMS; HYDROGEN; GLACIER; ODYSSEY; BRINES AB An integrated, miniaturized, low-power instrument capable of the detection and early characterization of microbial life in the soil of Mars is proposed. Based on the detection and monitoring of ongoing metabolism as being the surest evidence for extant life, the experiments will probe for chirality in metabolism, for circadian rhythmicity, and for photosynthesis. However, the instrument package will also be able to detect biosignatures and a variety of other physical and chemical parameters of the Martian surface that have significance for life. These include the presence and the physical state of water, the existence of an oxidant, the pH and the penetrability of the soil. Using the legacy of the 1976 Viking Labeled Release (LR) life detection experiment in conjunction with state-of-the-art laser diode spectral analysis, the instrument can be flown stand-alone, with or without a rover, or as part of a Mars Science Laboratory (MSL)-type mission. Sterility for experiment integrity and for planetary protection is provided. C1 [Levin, Gilbert V.] Spherix Inc, 12051 Indian Creek Court, Beltsville, MD 20705 USA. [Miller, Joseph D.] Univ Southern Calif, Dept Cell & Neurobiol, Los Angeles, CA USA. [Straat, Patricia A.] 830 Windy Knoll, Sykesville, MD USA. [Lodder, Robert A.] Univ Kentucky, Lexington, KY 40506 USA. [Hoover, Richard B.] NASA, NSSTC, Marshall Space Flight Ctr, Huntsville 35805, AL USA. RP Levin, GV (reprint author), Spherix Inc, 12051 Indian Creek Court, Beltsville, MD 20705 USA. EM glevin@spherix.com; jdm@usc.edu; pstraat@comeast.net; lodder@uky.edu; richard.hoover@nasa.gov NR 45 TC 0 Z9 0 U1 0 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 311 EP + PG 5 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235300028 ER PT S AU Kaiser, ML Adams, WJ AF Kaiser, Michael L. Adams, W. James GP IEEE TI STEREO mission overview SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB NASA's Solar TErrestrial RElations Observatory (STEREO) mission began as a concept study in 1997 and was confirmed as a follow on to NASA's highly successful line of Solar observing missions. Launched on October 25, 2006 (Figure 1) the twin observatories will take unprecedented images of the sun from a unique off the sun-earth axis angle in 3-D. Along with the suite of ultraviolet and visible light imagers the mission also carries an array of state of the art energetic particle detectors and electromagnetic sensors to enable better understanding of the dynamics of the sun's coronal mass ejections and solar wind.1(2). C1 [Kaiser, Michael L.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Adams, W. James] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Kaiser, ML (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. EM michael.kaiser@nasa.gov; jim.adams@nasa.gov NR 0 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 326 EP + PG 2 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235300029 ER PT S AU Johnston, MD Graf, JE Zurek, RW Eisen, HJ Jai, BH AF Johnston, M. D. (Dan) Graf, James E. Zurek, Richard W. Eisen, Howard J. Jai, Benhan GP IEEE TI The Mars Reconnaissance Orbiter mission: From launch to the primary science orbit SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB The Mars Reconnaissance Orbiter (MRO) was launched from Cape Canaveral Air Force Station, Florida, USA, aboard an Atlas V-401 launch vehicle on August 12, 2005. The MRO spacecraft carries a very sophisticated scientific payload. Its primary science mission is to to provide global, regional survey, and targeted observations from a low-altitude orbit for one Martian year (687 Earth days). After a seven-month interplanetary transit, the spacecraft fired its six main engines and established a highly elliptical capture orbit at Mars. During the post Mars Orbit Insertion (MOD early check-out period, four instruments acquired engineering-quality data. This was followed by five months of aerobraking operations. After aerobraking was terminated, a series of propulsive maneuvers were used to establish the desired low-altitude science orbit. As the spacecraft is readied for its primary science mission, spacecraft and instrument checkout and deployment activities have continued. After the science phase is completed, the orbiter will provide telecommunications support for future Mars missions. This paper provides a status of the actual mission to date (through October 2006) and briefly describes the planned operations for the upcoming science mission. (1) (2). C1 [Johnston, M. D. (Dan); Graf, James E.; Zurek, Richard W.; Eisen, Howard J.; Jai, Benhan] CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. RP Johnston, MD (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. NR 5 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 334 EP 352 PG 19 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235300030 ER PT S AU Wilcox, JZ Urgiles, E Toda, R Crisp, J AF Wilcox, Jaroslava Z. Urgiles, Eduardo Toda, Risaku Crisp, Joy GP IEEE TI Atmospheric Electron induced X-ray Spectrometer (AEXS) development SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB The progress in the development of the Atmospheric Electron X-ray Spectrometer (AEXS) is described. The AEXS is a surface analysis tool based on excitation of characteristic x-ray fluorescence (XRF) spectra from samples in ambient atmospheres using a focused electron beam. Operation in ambient atmospheres with moderate-to-high spatial resolution in comparison to similar instruments is obtained through the use of a thin electron transmissive membrane to isolate the vacuum of the electron probe, obviating the need for the samples to be drawn into the probe vacuum. Our initial setup consisted of an actively pumped chamber from within which the electrons were transmitted - not a portable instrument. The instrument that has been assembled and used to acquire XRF spectra in our laboratory during the past two years consists of a 20keV electron tube sealed with a SiN membrane and requires no active pumping - a big step towards the development of a stand-alone instrument. The microprobe was used to perform elemental analysis of NIST and USGS standards, with good agreement with the certified composition for samples in up to about 90 Torr-cm thick atmosphere, and for resolving the composition of mm-sized mineral grains in inhomogeneous samples, a big improvement over the several cm-scale spatial resolution of the APXS instrument that flew on NASA's MER mission. (12). C1 [Wilcox, Jaroslava Z.; Urgiles, Eduardo; Toda, Risaku; Crisp, Joy] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Wilcox, JZ (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 11 TC 0 Z9 0 U1 0 U2 3 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 426 EP 436 PG 11 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235300038 ER PT S AU Buhler, CR Calle, CI Clements, JS Mantovani, JG Ritz, ML AF Buhler, Charles R. Calle, Carlos I. Clements, J. Sid Mantovani, James G. Ritz, Mindy L. GP IEEE TI Test method for In situ electrostatic characterization of lunar dust SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES ID PHOTOELECTRON SHEATH; LEVITATION; SPACE AB The unmanageable effects of the dust on the surface of the moon made lunar traverses for the Apollo astronauts nearly impossible after three days exposure. These effects, governed by electrostatic properties, are responsible for their behavior and, to this date, are largely unclassified. Although many of the electrostatic characteristics of lunar soil have been measured, there are other electrostatic properties yet to be determined, such as chargeability (or charge-to-mass ratio), charge decay characteristics, and triboelectric properties. The purpose of this paper is to present a future in situ instrument capable of simultaneously measuring four important electrostatic properties: dielectric permittivity, volume resistivity, charge decay, and the chargeability of triboelectrically charged soil. This paper serves to illustrate the testing methods necessary to classify the electrostatic properties of lunar dust using in situ instrumentation and the required techniques therein. A review of electrostatic classification of lunar simulant materials is provided as is its relevance to the success of future human lunar missions. (12). C1 [Buhler, Charles R.; Ritz, Mindy L.] ASRC Aerosp, Kennedy Space Ctr, FL 32899 USA. [Calle, Carlos I.; Mantovani, James G.] NASA, Kennedy Space Ctr, FL 32899 USA. [Clements, J. Sid] Appalachian State Univ, Dept Phys & Astronomy, Boone, NC 28608 USA. RP Buhler, CR (reprint author), ASRC Aerosp, Kennedy Space Ctr, FL 32899 USA. EM Charles.Buhler-1@ksc.nasa.gov NR 23 TC 0 Z9 0 U1 1 U2 4 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 437 EP + PG 2 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235300039 ER PT S AU Mungas, G Sepulveda, C Johnson, K Pelletier, M La Baw, C Boynton, J Anderson, M AF Mungas, Greg Sepulveda, Cesar Johnson, Kenneth Pelletier, Michael La Baw, Clayton Boynton, John Anderson, Mark GP IEEE TI Raman/CHAMP instrument for lunar in-situ resource prospecting I - Imager design SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB Lunar ISRU precursor prospecting missions are being considered in order to characterize the lunar surface environment and to determine volatile and mineral content as well as mechanical and thermal properties of the lunar regolith for purposes of designing future excavation and In-Situ Resource Utilization (ISRU) processing equipment. The Raman/CHAMP instrument (RCI) is being developed as part of an instrument/experiment suite development project known as Regolith and Environment Science and Oxygen and Lunar Volatile Extraction (RESOLVE) being developed and sponsored under the NASA ISRU Project. The RCI supports the lunar surface characterization measurements by providing crucial field macroscopic and microscopic images coupled with Raman spectroscopy. The RCI provides the ability to collect high resolution, hand lens to field microscopy images and spectroscopic measurements from a robotic arm with the ability to resolve, characterize, and chemically differentiate >90% of lunar Apollo fines. The entire measurement process is highly adaptive and does not necessarily require any type of active sampling. In this paper we provide an overview of the RCI. We discuss the optical design optimization and analysis process for this particular type of instrument. We discuss recent results of integration tests of the Mars Microbeam Raman Spectrometer (MMRS) with the MIDP CHAMP instrument, fluorescence analysis, and individual glass fluorescence tests. Finally, we conclude with a summary of anticipated instrument measurement performance based on Zemax optical modeling of an RCI engineering model that is currently in development.(1 2). C1 [Mungas, Greg; Sepulveda, Cesar; Johnson, Kenneth; Pelletier, Michael; La Baw, Clayton; Boynton, John; Anderson, Mark] CALTECH, Jet Prop Lab, Pasadena, CA 91006 USA. RP Mungas, G (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91006 USA. NR 3 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 456 EP 463 PG 8 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235300040 ER PT S AU Buehler, MG Chin, KB Seshadri, S Keymeulen, D Anderson, RC McCann, TA AF Buehler, M. G. Chin, K. B. Seshadri, S. Keymeulen, D. Anderson, R. C. McCann, T. A. GP IEEE TI Electrical properties probe measures water/ice content of martian soils using impedance spectroscopy SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB We are developing a simple apparatus to quickly determine the amount of water/ice using two probes that contact the regolith. Using impedance spectroscopy, we describe how conductivity measurements were used to determine the amount of water/ice in simulated martian soils. We measured silica sand samples containing 0.05% to 10% water doped with KCI and MgSO4 between -65 degrees C and 25 degrees C. Results indicate that we are able to measure the water/ice content of coarse silica sand with > 0.05% water and > 0.5% ice. For a concentration, C*, of ions or defects, water/ice gravimetric content, theta(g), and equivalent conductivity, A, the conductivity is a = 2.5x10(-7) Lambda.C*.theta(1.8)(g). C1 [Buehler, M. G.; Chin, K. B.; Seshadri, S.; Keymeulen, D.; Anderson, R. C.; McCann, T. A.] CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. RP Buehler, MG (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. NR 15 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 464 EP 482 PG 19 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235300041 ER PT S AU Mantovani, JG Calle, CI AF Mantovani, J. G. Calle, C. I. GP IEEE TI Controllable transport of particulate materials for in-situ characterization SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB A non-mechanical technique is presented for transporting micron-sized lunar or Martian soil simulant particles in a controllable manner to an instrument for subsequent analysis. The particles move across a surface in response to multi-phase, high-voltage waveforms that are applied to sets of line-electrodes of constant spacing, which are embedded under an insulating surface. The direction of particle motion is found to be perpendicular to the electrode axis. As a simple demonstration of the technique, results of net charge measurements are presented for particles in the lunar soil simulant JSC-1a (<25 mu m), and the Martian soil simulant JSC Mars-1 (20-25 mu m) that were transported into a Faraday cup under ambient conditions. The results are presented using three-phase Moesner-Higuchi waveforms and for several line-electrode spacings. The results indicate that the technique is a potentially viable, non-mechanical method of collecting and transporting regolith particles for in-situ characterization during robotic planetary missions. (1,2). C1 [Mantovani, J. G.; Calle, C. I.] NASA, Electrostat & Surface Phys Lab, Kennedy Space Ctr, FL 32899 USA. RP Mantovani, JG (reprint author), NASA, Electrostat & Surface Phys Lab, Mailcode KT-E-3, Kennedy Space Ctr, FL 32899 USA. EM james.g.mantovani@nasa.gov NR 16 TC 0 Z9 0 U1 0 U2 3 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 483 EP 491 PG 9 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235300042 ER PT S AU Tripathi, RK Wilson, JW AF Tripathi, Ram K. Wilson, John W. GP IEEE TI Radiation risk issues for long-term exposure to ionizing space radiation SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES ID ABSORPTION CROSS-SECTIONS; ACCURATE UNIVERSAL PARAMETERIZATION; TRANSPORT AB NASA is focused on the agency's vision for space exploration encompassing a broad range of human and robotic missions including missions to Moon, Mars and beyond. As a result, there is a focus on long duration human space missions. Exposure from the hazards of severe space radiation in deep space and/or long duration missions is 'the show stopper.' Thus, protection from the hazards of severe space radiation is of paramount importance to the new vision. NASA is committed to the safety of the missions and the crew, and there is an overwhelming emphasis on the reliability issues for space missions and the habitat. It is envisioned to have long duration human presence on the Moon for deep space exploration. As NASA is looking forward to exploration in deep space, there is a need to go beyond current technology to the technology of the future. Faced with a limited budget and an expanding space exploration program, the old way of doing business is inadequate, and NASA requires revolutionary technologies to make advances. The technology of today is adequate for short-term human exposure to space radiation in low earth orbit (LEO) missions. We have developed methodology and concomitant technology for probabilistic reliability based risk assessment from exposure from space radiation for long duration and/or deep space missions. Risk issues for long-term exposure to ionizing space radiation are highlighted. C1 [Tripathi, Ram K.; Wilson, John W.] NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Tripathi, RK (reprint author), NASA, Langley Res Ctr, Hampton, VA 23681 USA. EM ram.k.tripathi@larc.nasa.gov; john.w.wilson@nasa.gov NR 28 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 492 EP + PG 4 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235300043 ER PT S AU Schwadron, N Goodrich, C Spence, H Townsend, L Cucinotta, F Kim, MHY Weyland, M Golightly, MJ Desai, M Posner, A Hassler, D Krauss-Varban, D Luhmann, J Miller, J Heber, B Onsager, T AF Schwadron, Nathan Goodrich, Chuck Spence, Harlan Townsend, Larry Cucinotta, Frank Kim, Myung-Hee Y. Weyland, Mark Golightly, Michael J. Desai, Mihir Posner, Arik Hassler, Don Krauss-Varban, Dietmar Luhmann, Janet Miller, Jack Heber, Bemd Onsager, Terry GP IEEE TI Earth-Moon-Mars Radiation Environment Module (EMMREM) SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES ID SOLAR PARTICLE EVENTS; ISOTOPE SPECTROMETER; WIND SPACECRAFT; COSMIC-RAYS; SPECTRA; ABERRATIONS; DEPENDENCE; EXPOSURE; AUGUST; MODEL AB We are preparing to return humans to the Moon and setting the stage for exploration to Mars and beyond. However, it is unclear if long missions outside of Low-Earth Orbit (LEO) can be accomplished with acceptable risk. The central objective of our project, the Earth-Moon-Mars Radiation Exposure Module (EMMREM), is to develop and validate a numerical module for completely characterizing time-dependent radiation exposure in the Earth-Moon-Mars and Interplanetary space environments. EMMREM will provide the ability to predict radiation exposure on the surface or atmosphere of Earth, on the Moon, Mars, and in interplanetary space between Earth and Mars. EMMREM is being designed for broad use by researchers to predict radiation exposure by integrating over almost any incident particle distribution from interplanetary space. EMMREM is being developed using contemporary state-of-the-art particle radiation models. Beyond this, it will have the capability to incorporate new and improving models, as they become available, to give continually improved estimates of radiation hazards and effects. EMMREM will be comprehensively validated using direct and contemporaneous measurements near Earth, at the Moon and Mars to significantly reduce uncertainties in radiation exposure predictions. EMMREM will characterize the extremes, statistics, and variations over time of radiation exposure caused by solar energetic particles and cosmic rays. The results of EMMREM will improve risk assessment models so that future human exploration missions can be adequately planned for. This makes EMMREM highly relevant to NASA's Vision for Space Exploration and the Living With a Star Programs. (1 2). C1 [Schwadron, Nathan; Goodrich, Chuck; Spence, Harlan] Boston Univ, 725 Commonwealth, Boston, MA 02215 USA. [Townsend, Larry] Univ Tennessee, Knoxville, TN 37996 USA. [Cucinotta, Frank; Kim, Myung-Hee Y.; Weyland, Mark] NASA, Houston, TX 77058 USA. [Golightly, Michael J.] AFRL VSBXR, Hanscom AFB, MA 07131 USA. [Desai, Mihir; Posner, Arik] Southwest Res Inst, San Antonio, TX USA. [Hassler, Don] Southwest Res Inst, Boulder, CO 80302 USA. [Krauss-Varban, Dietmar; Luhmann, Janet] Univ Calif Berkeley, Berkeley, CA 94720 USA. [Miller, Jack] Lawrence Berkeley Natl lab, Berkeley, CA 94720 USA. [Heber, Bemd] Univ Kiel, D-24098 Kiel, Germany. [Onsager, Terry] NOAA, Space Environm Ctr, Boulder, CO 80303 USA. RP Schwadron, N (reprint author), Boston Univ, 725 Commonwealth, Boston, MA 02215 USA. EM nathanas@bu.edu; ccg@bu.edu; spence@bu.edu; ltownsen@tennessee.edu; francis.a.cucinotta1@jsc.nasa.gov; myung-hee.y.kim1@jsc.nasa.gov; Michael.Golightly@hanscom.af.mil; mdesai@swri.edu; aposner@swri.edu; hassler@boulder.swri.edu; varban@ssl.berkeley.edu; jgluhman@ssl.berkeley.edu; miller@lbl.gov; b.heber@physik.uni-stuttgart.de; terry.onsager@noaa.gov NR 53 TC 0 Z9 0 U1 0 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 520 EP + PG 5 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235300046 ER PT S AU Carmain, A Dunn, C Ziemer, J Hruby, V Spence, D Demmons, N Roy, T McCormick, R Ehrbar, E Zwahlen, J Connolly, W O'Donnell, J Markley, F Maghami, P Hsu, O AF Carmain, A. Dunn, C. Ziemer, J. Hruby, V. Spence, D. Demmons, N. Roy, T. McCormick, R. Ehrbar, E. Zwahlen, J. Connolly, W. O'Donnell, J. Markley, F. Maghami, P. Hsu, O. GP IEEE TI Space technology 7-Micropropulsion and mass distribution SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES ID MISSION; LISA AB The NASA New Millennium Program Space Technology 7 (ST7) project will validate technology for precision spacecraft control. The ST7 Distrubance Reduction System (DRS) will contain new micropulsion technology to be flown as part of the European Space Agency's LISA (Laser Interferometer Space Antenna) Pathfinder project. After launch into a low Earth orbit in early 2010, the LISA Pathfinder spacecraft will be maneuered to a halo orbit about the Earth-Sun L1 Lagrange point for operations. The DRS will control the position of the spacecraft relative to a reference to an accuracy of one nanometer over time scales of several thousand seconds. To perform the control the spacecraft will use a new colloid thruster technology. The thrusters will operate over the range of 5 to 30 micro-Newtons with precision of 0.1 micro-Newton. The thrust will be generated by using a high electric field to extract charged droplets of a conducting colloid fluid and accelerating them with a precisely adjustable voltage. The control position reference will be provided by the European LISA Technology Package, which will include two nearly free-floating test masses. The test mass position and attitude will be sensed and adjusted using electrostatic capacitance bridges. The DRS will control the spacecraft position with respect to one test mass while minimizing disturbances on the second test mass. The dynamic control system will cover eighteen degrees of freedom, six for each of the test masses and six for the spacecraft. In the absence of other disturbances, the test masses will slowly gravitate toward local concentrations of spacecraft mass. The test mass acceleration must be minimized to maintain the acceleration of the enclosing dragfree spacecraft within the control authority of the micropropulsion system. Therefore, test mass acceleration must be predicted by accurate measurement of mass distribution, then offset by the placement of specially shaped balance masses near each test mass. The acceleration is characterized by calculating the gravitational effect of over ten million modeled points of a nearly 500-kg spacecraft. and the process of precision mass modeling of the DRS equipment.(1 2). C1 [Carmain, A.; Dunn, C.; Ziemer, J.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Hruby, V.; Spence, D.; Demmons, N.; Roy, T.; McCormick, R.; Ehrbar, E.; Zwahlen, J.; Connolly, W.] Busek Co Inc, Natick, MA 07160 USA. [O'Donnell, J.; Markley, F.; Maghami, P.; Hsu, O.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Carmain, A (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM andrew.carmain@jpl.nasa.gov; vhruby@busek.com; james.r.odonnell@nasa.gov NR 11 TC 0 Z9 0 U1 0 U2 3 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 530 EP + PG 2 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235300047 ER PT S AU Rossoni, P AF Rossoni, Peter GP IEEE TI Structural bus and release mechanisms on the ST5 satellites - Summary and status SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB The Space Technology 5 Mechanical System met the challenge of packaging a fully functional science and technology satellite system with its Deployer mechanism into a compact 0.07 m(3) volume. Three 25 kg satellites were orbited in constellation in March, 2006. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Rossoni, P (reprint author), NASA, Goddard Space Flight Ctr, Mail Code 544, Greenbelt, MD 20771 USA. NR 4 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 540 EP 553 PG 14 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235300048 ER PT S AU Samson, J Gardner, G Lupia, D Patel, M Davis, P Aggarwal, V George, A Kalbarcyzk, Z AF Samson, John Gardner, Gary Lupia, David Patel, Minesh Davis, Paul Aggarwal, Vikas George, Alan Kalbarcyzk, Zbigniew GP IEEE TI Technology validation: NMP ST8 dependable multiprocessor project II SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB With the ever-increasing demand for higher bandwidth and processing capacity of today's space exploration, space science, and defense missions, the ability to efficiently apply Commercial-Off-The-Shelf (COTS) processors for on-board computing has become a critical need. In response to this need, NASA's New Millennium Program (NMP) commissioned the development of Dependable Multiprocessor (DM) technology for use in science and autonomy missions, but the technology is also applicable to a wide variety of DoD missions. The goal of the DM project is to provide spacecraft/payload processing capability 10x - 100x what is available today, enabling heretofore unrealizable levels of science and autonomy. DM technology is being developed as part of the NMP ST8 (Space Technology 8) project. The objective of this NMP ST8 effort is to combine high-performance, fault tolerant, COTS-based cluster processing and fault tolerant middleware in an architecture and software framework capable of supporting a wide variety of mission applications. Dependable Multiprocessor development is continuing as one of the four selected ST8 flight experiments planned to be flown in 2009. (1,2,3) There are three key problems that need to be overcome in order to fly COTS in space: 1) an effective approach for handling SEUs (Single Event Upsets) in high performance cluster processors, 2) handling thermal issues associated with state-of-the-art COTS components, and 3) achieving high power efficiency (throughput per watt). DM technology solves all three problems. DM solves the SEU problem by combining cluster management software withSEU tolerance-enhancing software in a flexible, efficient, integrated DM middleware suite. DM solves the thermal issue by mining the ruggedized, conductive-cooled, COTS airborne embedded processing domain. DM solves the power efficiency problem by mining the high performance, low power mobile computing processing domain. Recently, the DM project successfully passed several key NMP ST8 project milestones: the TRL5 (Technology Readiness Level 5) technology validation demonstration, the Experiment Preliminary Design Review, and the NASA Non Advocate Review. Passing the TRL5 milestone qualified the DM project for advancement to flight system development status. The ST8 Project passed its Preliminary Design and Confirmation Review and is now in its Implementation Phase. This paper describes the status of the project, the technology validation experiments and demonstrations achieved to date, the plans for the TRL6 technology validation effort, and the plans for the TRL7 flight validation. C1 [Samson, John; Gardner, Gary; Lupia, David] Honeywell Inc, Aerosp Syst, Minneapolis, MN 55408 USA. [Patel, Minesh; Davis, Paul; Aggarwal, Vikas] Tandel Syst LLC, Oldsmar, FL USA. [George, Alan] Univ Florida, Gainesville, FL 32611 USA. [Kalbarcyzk, Zbigniew] Univ Illinois, Chicago, IL 60680 USA. [Kalbarcyzk, Zbigniew] CALTECH, Jet Propuls Lab, Pasadena, CA 91125 USA. RP Samson, J (reprint author), Honeywell Inc, Aerosp Syst, Minneapolis, MN 55408 USA. EM john.r.samson@honeywell.com; mpatel@tandelsystems.com; george@hcs.ufl.edu; kalbar@crhc.uiuc.edu FU The Dependable Multiprocessor effort is under NASA NMP ST-8 [NMO-710209] FX The Dependable Multiprocessor effort is funded under NASA NMP ST-8 contract NMO-710209. NR 16 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 554 EP + PG 4 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235300049 ER PT S AU Herrell, LM AF Herrell, Linda M. GP IEEE TI Access to space for technology validation missions: A practical guide SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB Space technology experiments and validation missions share a common dilemma with the aerospace industry in general: the high cost of access to space. Whether the experiment is a so-called university cubesat, a university measurement experiment, or a NASA New Millennium Program (NMP) technology validation mission, the access to space option can be scaled appropriately for the particular constraints. A cubesat might fly as one of a number of cubesats that negotiate a flight on an experimental vehicle. A university experiment might do the same. A NASA flight validation might partner with an Air Force experimental mission.(1,2) But what is the range of options, and what are the benefits of one approach over another? What are the limitations of one approach over another? How can one assess the viability for implementing a particular experiment? How does one go about acquiring such a space access? A methodology is presented which identifies the approach used by the New Millennium Program to understand what access-to-space options are available. A range of spacecraft, adaptors and launch vehicles are available for any particular mission. But which combination is the most cost effective? Which has the least technical risk? Which has the least programmatic risk? All of these elements play into the final choice for access to space. The approach for a cubesat or small flight experiment will certainly be different than the approach for NUT. But what are the common elements, fundamentally, in 'finding a ride to space'? And what information is useful to a flight experiment that does not yet know the method that will be used for launch? These issues are addressed and guidelines are suggested for the reader. No single reference exists to address these questions so the guidelines present a summary meant to point the reader to further information. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Herrell, LM (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 1 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 591 EP 598 PG 8 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235300052 ER PT S AU Kim, SC Shepperd, SW Norris, HL Goldberg, HR Wallace, MS AF Kim, Susan C. Shepperd, Stanley W. Norris, H. Lee, III Goldberg, Hannah R. Wallace, Mark S. GP IEEE TI Mission design and trajectory analysis for inspection of a host spacecraft by a microsatellite SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB The trajectory analysis and mission design for inspection of a host spacecraft by a microsatellite is motivated by the current developments in designing and building prototypes of a microsatellite inspector vehicle. A mission in which a host spacecraft is in orbit about Earth is covered in this paper. A toolset has been created, composed of both natural and forced motion trajectories. The toolset evaluates an inspection mission concept based on figures of merit over four primary operational modes: deployment mode, global inspection mode, point inspection mode, and disposal mode. Merit figures investigated include the quality of inspection through resolution, lighting conditions, viewing angles, total inspection coverage, tracking spacecraft constraints and consumables regarding telecommunications, spacecraft power, and fuel expenditure. This paper presents the design of the inspection mission design toolset and summarizes the performance of a baseline inspection mission concept of a host in Earth orbit. C1 [Kim, Susan C.] Unmanned Syst, Northrop Grumman Integrated Syst, 17066 Goldentop Rd, San Diego, CA 92127 USA. [Shepperd, Stanley W.; Norris, H. Lee, III] Charles Stark Draper Lab Inc, Technol Square 555, Cambridge, MA 02139 USA. [Goldberg, Hannah R.; Wallace, Mark S.] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Kim, SC (reprint author), Unmanned Syst, Northrop Grumman Integrated Syst, 17066 Goldentop Rd, San Diego, CA 92127 USA. NR 8 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 640 EP + PG 3 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235300057 ER PT S AU Fontaine, KS AF Fontaine, Kathleen S. GP IEEE TI Architecture and data management challenges in GEOSS and IEOS SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB The international Group on Earth Observations (GEO) was initiated in 2003 to engage all the nations of the Earth in building a coordinated, comprehensive, and sustained Earth observation capability, known as the Global Earth Observation System of Systems (GEOSS). The GEO website describes GEOSS this way: "GEOSS will build on and add value to existing Earth-observation systems by coordinating their efforts, addressing critical gaps, supporting their interoperability, sharing information, reaching a common understanding of user requirements, and improving delivery of information to users." Each member nation has responded to GEO by establishing some sort of coordinating body; within the United States, that is the United States Group on Earth Observations (USGEO). This paper will describe the establishment of GEO and USGEO, will provide an overview of the activities and challenges in the area of architecture and data management, and will highlight some of the major efforts underway within USGEO today. C1 NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Fontaine, KS (reprint author), NASA, Goddard Space Flight Ctr, Code 610-2, Greenbelt, MD 20771 USA. EM kathy.fontaine@nasa.gov NR 4 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 673 EP 682 PG 10 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235300059 ER PT S AU Samadi, S Gerard, R Hunter, M Marshall, JJ Schweiss, RJ Wolfe, RE Masuoka, EJ AF Samadi, Shahin Gerard, Ryan Hunter, Mary Marshall, James J. Schweiss, Robert J. Wolfe, Robert E. Masuoka, Edward J. GP IEEE TI Reusing software to build data processing systems: NPP Science Data Segment case study SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB Over the years, numerous large and complex information systems have been created to store, process, and disseminate vast volumes of remotely-sensed Earth science data. These systems have the potential to be reused to process similar data from other missions or instruments, reducing risk, schedule, and associated development cost for future projects.(12) One example of this kind of reuse is found in the Science Data Segment (SDS) of the National Polar-orbiting Operational Environmental Satellite System (NPOESS) Preparatory Project (NPP). This project provides remotely-sensed atmosphere, land, ocean, ozone, and sounder data that will serve the meteorological and global climate change to scientific communities while also providing risk reduction for NPOESS, the U.S. Government's future low-Earth orbiting weather and environmental satellite system. NPP serves as a bridge between current and future missions by providing pre-operational on-orbit test and risk reduction for key NPOESS instruments and ground-based data processing capabilities, while maintaining continuity of environmental data used for long-term climate change research. The role of the SDS is to independently assess the quality of NPP data products for accomplishing climate research. The NPP Science Data Segment achieves its goals by leveraging off of existing processing centers. NPP SDS will perform the evaluation and analysis of atmosphere, land, ocean, ozone, and sounder data products. This paper will focus on the software reuse aspects of the SDS, and in particular, reuse of the Moderate Resolution Imaging Spectroradiometer (MODIS) Adaptive Processing System (MODAPS) in the development of the Land Product Evaluation and Algorithm Test Environment (PEATE) and Science Data Depository and Distribution Element (SWE). Additional pieces of the SDS also reuse other existing Earth science data systems such as the Sea-viewing Wide Field-of-view Sensor (SeaWiFS) Ocean Data Processing System (ODPS) and the Ozone Monitoring Instrument (OMI) Data Processing System (OMIDAPS). Due to space constraints and to avoid duplication of content, this paper focuses on how the reuse of the existing MODAPS software system assists the NPP SDS project in meeting its requirements and goals. C1 [Samadi, Shahin; Gerard, Ryan; Hunter, Mary; Marshall, James J.] NASA, Goddard Space Flight Ctr, Innovim, Mail Stop 614-5, Greenbelt, MD 20771 USA. [Schweiss, Robert J.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Wolfe, Robert E.; Masuoka, Edward J.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Samadi, S (reprint author), NASA, Goddard Space Flight Ctr, Innovim, Mail Stop 614-5, Greenbelt, MD 20771 USA. EM shahin.samadi@gsfc.nasa.gov; ryan.gerard@gsfc.nasa.gov; mary.hunter@gsfc.nasa.gov; james.marshall@gsfc.nasa.gov; robert.j.schweiss@nasa.gov; robert.e.wolfe@nasa.gov; edward.j.masuoka@nasa.gov RI Wolfe, Robert/E-1485-2012; Marshall, James/A-9611-2009 OI Wolfe, Robert/0000-0002-0915-1855; Marshall, James/0000-0002-6867-5616 NR 9 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 683 EP + PG 3 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235300060 ER PT S AU Singh, G SanMartin, AM Wong, EC AF Singh, Gurkirpal SanMartin, Alejandro M. Wong, Edward C. GP IEEE TI Guidance and control design for powered descent and landing on Mars SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB Future Mars landing missions must be capable of autonomously delivering highly capable and mobile rovers safely and gently in an upright orientation. The airbag landing system used to deliver earlier rovers (Mars Pathfinder and the two Mars Exploration vehicles) is incapable of landing the Mars Science Laboratory (MSL)-class rover. The design of a novel Sky-Crane landing concept to land the proposed Mars Science Laboratory rover is presented here. The descent is guided and actively controlled in six degrees of freedom. Terminal guidance is robust to terrain variations-induced altimeter noise. A Terminal Descent Sensor provides surface relative velocity and altitude measurements, the Inertial Measurement Unit measurements help propagate the vehicle attitude and positions. Guidance and control system commands eight throttle-able Mars Lander Engines to actively control the vehicle attitude and translations. Computer simulations demonstrate the viability of this concept in the presence of various environmental, configuration, and hardware imperfections.(12). C1 [Singh, Gurkirpal; SanMartin, Alejandro M.; Wong, Edward C.] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Singh, G (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 4 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 726 EP 733 PG 8 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235300064 ER PT S AU Vaughn, JAS Singh, G Prakash, R Frisbee, RH Corliss, JM Tutterow, RD AF Vaughn, Joshua A. St. Singh, Gurkirpal Prakash, Ravi Frisbee, Robert H. Corliss, James M. Tutterow, Robin D. GP IEEE TI Design of a retro rocket Earth landing system for the Orion spacecraft SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB The Orion spacecraft is tasked with taking humans to space and returning them safely to Earth at a site in the continental United States. To ensure that the crew returns safely to Earth, a landing system must be designed to reduce the terminal velocity so that, upon landing, the impact loads are minimal and the capsule does not roll over. The retro rocket landing system presented here has been currently baselined because of its performance capabilities over other landing attenuation options such as airbags and landing struts. Preliminary fault analysis and mass and volume sizing led to a down-select of various rocket configurations to base mounted vertical rockets that would be exposed when the heatshield separated. Additionally, the design contains horizontal rockets through the backshell that would be exposed by blowout ports. The trades performed for the retro rocket system led to a design consisting of four 7000 lbf vertical rockets sized to reduce the vertical velocity from 25 ft/s to 5 ft/s. Additionally, four 9400-lbf horizontal rockets were sized to reduce horizontal velocities ranging from 0 to 58 ft/s to less than 20 ft/s. This paper summarizes the analysis that led to the selection of this concept as a preliminary design. This design will change as the Orion spacecraft design and landing system requirements are modified.(1,2) . C1 [Vaughn, Joshua A. St.; Singh, Gurkirpal; Prakash, Ravi; Frisbee, Robert H.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Corliss, James M.; Tutterow, Robin D.] NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Vaughn, JAS (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Joshua.St.Vaughn@jpl.nasa.gov; James.M.Corliss@nasa.gov NR 3 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 734 EP + PG 3 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235300065 ER PT S AU Way, DW Powell, RW Chen, A Steltzner, AD Martin, AMS Burkhart, PD Mendeck, GF AF Way, David W. Powell, Richard W. Chen, Allen Steltzner, Adam D. Martin, A. Miguel San Burkhart, P. Daniel Mendeck, Gavin F. GP IEEE TI Mars Science Laboratory: Entry, descent, and landing system performance SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB In 2010, the Mars Science Laboratory (MSL) mission will pioneer the next generation of robotic Entry, Descent, and Landing (EDL) systems, by delivering the largest and most capable rover to date to the surface of Mars. To do so, MSL will fly a guided lifting entry at a lift-to-drag ratio in excess of that ever flown at Mars, deploy the largest parachute ever at Mars, and perform a novel Sky Crane maneuver. Through improved altitude capability, increased latitude coverage, and more accurate payload delivery, MSL is allowing the science community to consider the exploration of previously inaccessible regions of the planet.(12) The MSL EDL system is a new EDL architecture based on Viking heritage technologies and designed to meet the challenges of landing increasingly massive payloads on Mars. In accordance with Level-1 requirements, the MSL EDL system is being designed to land an 850 kg rover to altitudes as high as 1 km above the Mars Orbiter Laser Altimeter defined areoid within 10 km of the desired landing site. Accordingly, MSL will enter the largest entry mass, fly the largest 70 degree sphere-cone aeroshell, generate the largest hypersonic lift-to-drag ratio, and deploy the largest Disk-Gap-Band supersonic parachute of any previous mission to Mars. Major EDL events include a hypersonic guided entry, supersonic parachute deploy and inflation, subsonic heatshield jettison, terminal descent sensor acquisition, powered descent initiation, sky crane terminal descent, rover touchdown detection, and descent stage flyaway. In order to conservatively assess the EDL system performance against the +1.0 km altitude requirement, the EDL design team has identified a system design stress case that results in lower altitude performance and reduced timeline margins. Key performance metrics, derived from Level-1 requirements and tracked by the EDL design team to indicate performance capability and timeline margins, include altitude and range at parachute deploy, time on radar, and propellant use. The current system-level performance assessment shows that MSL is capable of meeting all Level-1 requirements with sufficient timeline margins. However, as entry ballistic coefficient continues to increase, system design trade-studies continue to focus on techniques to increase altitude performance while balancing entry guidance precision and entry environmental requirements. The MSL EDL system, which will continue to develop over the next three years, will enable a notable extension in the advancement of Mars surface science. This paper describes the current MSL EDL system performance as predicted by end-to-end EDL simulations, highlights the sensitivity of this baseline performance to several key environmental assumptions, and discusses some of the challenges faced in delivering such an unprecedented rover payload to the surface of Mars. C1 [Way, David W.; Powell, Richard W.] NASA, Langley Res Ctr, Hampton, VA 23665 USA. [Chen, Allen; Steltzner, Adam D.; Martin, A. Miguel San; Burkhart, P. Daniel] NASA, Jet Prop Lab, Pasadena, CA USA. [Mendeck, Gavin F.] NASA, Johnson Space Flight Ctr, Houston, TX USA. RP Way, DW (reprint author), NASA, Langley Res Ctr, Hampton, VA 23665 USA. EM David.W.Way@larc.nasa.gov NR 10 TC 0 Z9 0 U1 1 U2 3 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 758 EP + PG 3 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235300067 ER PT S AU Lorenzoni, LV SanMartin, M Steltzner, A Chen, A AF Lorenzoni, Leila V. SanMartin, Miguel Steltzner, Adam Chen, Allen GP IEEE TI Preliminary assessment of MSL EDL sensitivity to Martian Environments SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB The Mars Science Laboratory Mission (MSL) will be launched during fall 2009 and will reach Mars at its northern summer season. The MSL entry, descent, and landing system is designed to land the heaviest rover, with the best landing precision, and highest elevation capability to date on Mars. The challenging ellipse size and high elevation sites are achieved by use of a guided lifting entry vehicle. The final landing site will be selected one year before launch and therefore the system's performance is to be evaluated for all possible environments in all possible landing sites. This paper discusses EDL sensitivities to support landing site safety preliminary assessment; it illustrates the sensitivities to Martian features identified as relevant to the EDL design. The Martian environmental parameters to which the EDL system is evaluating its sensitivities are atmospheric density and pressure, wind characteristics, speed of sound and terrain characteristics of slope distribution, rock abundance, and radio frequency backscatter. This paper briefly describes the EDL timeline and illustrates the EDL system features critical to understanding EDL performance in the Martian Environment. A preliminary assessment of EDL performance used to support characterization of landing site safety guidelines is presented. Critical sensitivities to atmospheric density, wind speed, local speed of sound and terrain slopes uncertainties have been preliminarily identified and discussed within. C1 [Lorenzoni, Leila V.; SanMartin, Miguel; Steltzner, Adam; Chen, Allen] Jet Propuls Lab, Pasadena, CA USA. RP Lorenzoni, LV (reprint author), Jet Propuls Lab, Pasadena, CA USA. NR 4 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 777 EP 784 PG 8 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235300068 ER PT S AU Edquist, KT Hollis, BR Dyakonov, AA Laub, B Wright, MJ Rivellini, TP Slimko, EM Willcockson, WH AF Edquist, Karl T. Hollis, Brian R. Dyakonov, Artem A. Laub, Bernard Wright, Michael J. Rivellini, Tomasso P. Slimko, Eric M. Willcockson, William H. GP IEEE TI em Mars Science Laboratory entry capsule aerothermodynamics and thermal protection system SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES ID SMART-LANDER; CAVITIES AB The Mars Science Laboratory (MSL) spacecraft is being designed to carry a large rover (> 800 kg) to the surface of Mars using a blunt-body entry capsule as the primary decelerator. The spacecraft is being designed for launch in 2009 and arrival at Mars in 2010. The combination of large mass and diameter with non-zero angle-of-attack for MSL will result in unprecedented convective heating environments caused by turbulence prior to peak heating. Navier-Stokes computations predict a large turbulent heating augmentation for which there are no supporting flight data(1) and little ground data for validation. Consequently, an extensive experimental program has been established specifically for MSL to understand the level of turbulent augmentation expected in flight. The experimental data support the prediction of turbulent transition and have also uncovered phenomena that cannot be replicated with available computational methods. The result is that the flight aeroheating environments predictions must include larger uncertainties than are typically used(2) for a Mars entry capsule. Finally, the thermal protection system (TPS) being used for MSL has not been flown at the heat flux, pressure, and shear stress combinations expected in flight, so a test program has been established to obtain conditions relevant to flight. This paper summarizes the aerothermodynamic defmition analysis and TPS development, focusing on the challenges that are unique to MSL. C1 [Edquist, Karl T.; Hollis, Brian R.] NASA, Langley Res Ctr, Hampton, VA 23681 USA. [Dyakonov, Artem A.] Natl Inst Aerosp, Hampton, VA 23666 USA. [Laub, Bernard; Wright, Michael J.] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Rivellini, Tomasso P.; Slimko, Eric M.] Jet Prop Lab, Pasadena, CA 91109 USA. [Willcockson, William H.] Lock Martin Space Syst Co, Littleton, CO 80125 USA. RP Edquist, KT (reprint author), NASA, Langley Res Ctr, Hampton, VA 23681 USA. EM Karl.T.Edquist@nasa.gov; Brian.R.Hollis@nasa.gov; a.a.dyakonov@larc.nasa.gov; Bernard.Laub@nasa.gov; Michael.J.Wright@nasa.gov; Tommaso.P.Rivellini@jpl.nasa.gov; Eric.M.Slimko@jpl.nasa.gov; william.h.willcockson@lmco.com NR 19 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 785 EP + PG 3 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235300069 ER PT S AU Brugarolas, PB San Martin, AM Wong, EC AF Brugarolas, Paul B. San Martin, A. Miguel Wong, Edward C. GP IEEE TI Entry attitude controller for the Mars Science Laboratory SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB This paper describes the preliminary concept for the RCS 3-axis attitude controller for the exoatmospheric and guided entry phases of the Mars Science Laboratory Entry, Descend and Landing. The entry controller is formulated as three independent channels in the control frame, which is nominally aligned with the stability frame. Each channel has a feedfoward and a feedback. The feedforward path enables fast response to large bank commands. The feedback path stabilizes the vehicle angle of attack and sideslip around its trim position, and tracks bank commands. The feedback path has a PD/D structure with deadbands that minimizes fuel usage. The performance of this design is demonstrated via simulation. C1 [Brugarolas, Paul B.; San Martin, A. Miguel; Wong, Edward C.] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Brugarolas, PB (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, M-S 198-326, 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 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 798 EP 803 PG 6 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235300070 ER PT S AU Kipp, D Martin, MS Essmiller, J Way, D AF Kipp, Devin Martin, Miguel San Essmiller, John Way, David GP IEEE TI Mars Science Laboratory entry, descent, and landing triggers SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB In 2010, plans call for the Mars Science Laboratory (MSL) mission to pioneer the next generation of robotic Entry, Descent, and Landing (EDL) systems by delivering the. largest and most capable rover to date to the surface of Mars. Improved altitude performance, coupled with latitude limits as large as 45 degrees off the equator and a precise delivery to within 10 km of a surface target, will allow the science community to select the MSL landing site from thousands of scientifically interesting and previously inaccessible locations. Realizing these impressive performance metrics requires proper execution of a complex sequence of time-critical flight system reconfiguration events. This sequence, which begins approximately 15 minutes prior to touchdown, includes cruise stage separation, cruise balance mass jettison, entry balance mass jettison, parachute deployment, heatshield separation, backshell separation, rover separation, and flyaway start. Each of these events must occur within a narrow operational envelope and must be triggered autonomously based on estimates of the spacecraft state. Triggers are either 'timed', whereby the spacecraft state estimate is reliant upon pre-flight predictions, or 'sensed', whereby the spacecraft state estimates are constructed in real-time using data from the on-board sensor suite. Regardless of method, all triggers must execute properly in the presence of potentially significant variability in Martian winds, atmospheric properties, and surface topography. Careful budgeting is necessary to manage uncertainties and impacts on EDL performance. This paper discusses the design of trigger algorithms that control event execution during the EDL sequence and highlights some of the related challenges faced by the MSL design team. (1,2). C1 [Kipp, Devin; Martin, Miguel San; Essmiller, John] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Way, David] NASA, Langley Res Ctr, Hampton, VA USA. RP Kipp, D (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Devin.M.Kipp@jpl.nasa.gov FU National Aeronautics and Space Administration FX The research described in this paper was carried out at the Jet Propulsion Laboratory, California Institute of Technology, under a contract with the National Aeronautics and Space Administration. This paper has been cleared for public U.S. and foreign release by JPL document review services under clearance number CL#07-0263. NR 3 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 804 EP + PG 2 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235300071 ER PT S AU Hoffman, P Rivillini, T Slimko, E Dahya, N Agajanian, A Knight, J Sengupta, A Thoma, B Webster, R Gallon, J Gradziel, M AF Hoffman, Pamela Rivillini, Tomasso Slimko, Eric Dahya, Neilesh Agajanian, Anthony Knight, Jennifer Sengupta, Anita Thoma, Benjamin Webster, Richard Gallon, John Gradziel, Michael GP IEEE TI Preliminary design of the cruise, entry, descent, and landing mechanical subsystem for MSL SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB Mars Science Laboratory is a scientific mission to the surface of Mars that would include a rover with 10 science instruments. In order to accomplish this mission, the rover must be transported from Earth to the Martian surface. The mechanical hardware that transports the rover is developed by the Cruise, Entry, Descent, and Landing (CEDL) Mechanical Subsystem Team. This mechanical hardware includes the Cruise Stage Structure, the Aeroshell Subsystem, the Parachute Deceleration Subsystem, the Descent Stage Structure, the Bridle & Umbilical Device, and the pyro and separation devices that allow for the numerous separation events that occur in the EDL sequence. The key challenges for this system lie in the complex configuration (both geometric and subsystem accommodations), multiple unique load cases, and numerous separation events. This paper will describe the preliminary design and key challenges of each of these mechanical assemblies that comprise the CEDL Mechanical Subsystem.(12). C1 [Hoffman, Pamela; Rivillini, Tomasso; Slimko, Eric; Dahya, Neilesh; Agajanian, Anthony; Knight, Jennifer; Sengupta, Anita; Thoma, Benjamin; Webster, Richard; Gallon, John; Gradziel, Michael] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Hoffman, P (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 9 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 814 EP 831 PG 18 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235300072 ER PT S AU Sengupta, A Steltzner, A Witkowski, A Rowan, J AF Sengupta, Anita Steltzner, Adam Witkowski, Al Rowan, Jerry GP IEEE TI An overview of the Mars Science Laboratory Parachute Decelerator System SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB In 2010 the Mars Science Laboratory (MSL) mission will deliver NASA's largest and most capable rover to the surface of Mars. MSL will explore previously unattainable landing sites due to the implementation of a high precision Entry, Descent, and Landing (EDL) system. The Parachute Decelerator System (PDS) is an integral part of the EDL system, providing a mass and volume efficient source of aerodynamic drag to decelerate the entry vehicle from Mach 2 to subsonic speeds, prior to final propulsive descent to the surface. The PDS for MSL is a mortardeployed 19.7m Viking type Disk-Gap-Band (DGB) parachute, chosen to meet the EDL timeline requirements and to utilize the heritage parachute systems from Viking, Mars Pathfinder, Mars Exploration Rover, and Phoenix NASA Mars Lander Programs. The preliminary design of the parachute soft goods, including materials selection, stress analysis, fabrication approach and development testing, will be discussed. The preliminary design of the mortar deployment system, including mortar system sizing and performance predictions, gas generator design, and development mortar testing, will also be presented.(12). C1 [Sengupta, Anita; Steltzner, Adam] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Witkowski, Al; Rowan, Jerry] Pionner Aerosp Corp, South Winder 06074, CT USA. RP Sengupta, A (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Anita.sengupta@jpl.nasa.gov; Adam.Steltzner@jpl.nasa.gov; Awitkowski@pioneer.zodiac.com; Jrowan@pioneer.zodiac.com NR 8 TC 0 Z9 0 U1 0 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 832 EP + PG 3 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235300073 ER PT S AU Peng, CY Ortiz, G Rivellini, T Lee, D Lih, SS Waydo, J White, C Haggart, S Voorhees, C Rainen, R AF Peng, Chia-Yen Ortiz, Gary Rivellini, Tommaso Lee, Darlene Lih, Shyh-Shiuh Waydo, Jaime White, Chris Haggart, Sean Voorhees, Chris Rainen, Richard GP IEEE TI Dynamic simulations of Mars Science Laboratory EDL landing loads and stability SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB The Mars Science Laboratory is being planned to launch in 2009 to deliver the third generation rover safely to the surface of Mars and conduct comprehensive in situ investigations. To deliver the rover for precision touchdown landing, it requires a new Entry, Descent, and Landing (EDL) approach using hypersonic aeromaneuver guided entry and skycrane-based powered descent and landing. The skycrane system is capable of efficiently and safely landing a large payload on Mars using a propulsion system configured into a descent stage. The rover will be released from the descent stage via descent-rate-limiter umbilical device and then placed directly onto the surface of Mars. As required by the skycrane landing architecture, the MSL rover is designed as a "lander" to survive touchdown as well as traverse environments. Since it is difficult, costly and, in many cases, impossible to test the skycrane descent and landing system in Mars-like environments, the MSL project relies heavily on dynamic simulations to validate the skycrane landing concept and predict the landing loads and stability of the rover. As a result, a multi-year extensive Loads and Stability Analysis Program has been conducted to develop seamless and robust simulations of the complicated skycrane landing dynamics with a large set of environmental parameters. This paper describes the overall approaches to the MSL touchdown simulation effort, landing loads and stability analysis, rover developmental test program, and applications of both the analysis and testing results to a mass-efficient and landing-capable rover structure design. (1). C1 [Peng, Chia-Yen; Ortiz, Gary; Rivellini, Tommaso; Lee, Darlene; Lih, Shyh-Shiuh; Waydo, Jaime; White, Chris; Haggart, Sean; Voorhees, Chris; Rainen, Richard] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Peng, CY (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 6 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 840 EP 849 PG 10 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235300074 ER PT S AU Jonsson, AK Morris, RA Pedersen, L AF Jonsson, Ari K. Morris, Robert A. Pedersen, Liam GP IEEE TI Autonomy in space exploration: Current capabilities and future challenges SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB Deep space exploration requires vehicles with appropriate autonomous capabilities. In order to accomplish their missions, spacecraft need to respond to potential hazards while seeking to expand human knowledge of deep space. (1) (2). This paper provides an overview of the role of autonomy for space exploration. First, we explore the range of autonomous behavior that is useful in space exploration. Second, three core requirements are defined for autonomous space systems. Fourth, we identify the decision-making capabilities that will ensure the effectiveness and safety of autonomous systems. Fifth, we describe architectures for integrating capabilities into an autonomous system. Finally, we discuss the challenges that are faced currently in developing and deploying autonomy technologies for space. C1 [Jonsson, Ari K.; Morris, Robert A.; Pedersen, Liam] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Jonsson, AK (reprint author), NASA, Ames Res Ctr, MS 269-1, Moffett Field, CA 94035 USA. NR 25 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 883 EP 894 PG 12 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235300078 ER PT S AU Imbriale, WA Weinreb, S Mani, H AF Imbriale, William A. Weinreb, Sander Mani, Handi GP IEEE TI Design of a wideband Radio Telescope SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB A wideband Radio Telescope is being designed for use in the Goldstone Apple Valley Radio Telescope program. It uses an existing 34-meter antenna retrofitted with a tertiary offset mirror placed at the apex of the main reflector. It can be rotated to use two feeds that cover the 1.2 to 14 GHz band. The feed for 4.0 to 14.0 GHz is a cryogenically cooled commercially available open boundary quadridge horn from ETS-Lindgren. Coverage from 1.2 to 4.0 GHz is provided by an un-cooled scaled version of the same feed. The performance is greater than 40% over most of the band and greater than 55%from 6 to 13.5 GHz. (1) (2). C1 [Imbriale, William A.] Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Weinreb, Sander; Mani, Handi] CALTECH, Pasadena, CA USA. RP Imbriale, WA (reprint author), Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM William.A.Imbriale@jpl.nasa.gov; Sander.Weinreb@jpl.nasa.gov FU National Aeronautics and Space Administration FX The research was carried out at the Jet Propulsion Laboratory, California Institute of Technology, under a contract with the National Aeronautics and Space Administration. NR 5 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 934 EP + PG 2 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235300084 ER PT S AU Silva, A Conroy, B Losh, DL Vodonos, Y AF Silva, Arnold Conroy, Bruce Losh, David L. Vodonos, Yakov GP IEEE TI Development and implementation experience of 20kW CW transmitters at the DSN 34-m BWG antennas SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB New 20kW S- and X-Band transmitters were developed by JPL for the six 34-m Beam Waveguide Antennas of the Deep Space Network (DSN) to support NASA Mars missions starting in 2003. These transmitters were based upon design concepts published previously in the Proceedings of the 2003 IEEE Aerospace Conference. They provide a 7dB improvement in uplink power at X-Band, coverage of both deep space and near-earth uplink bands, simplified control for operations, increased modularity of electronics for better maintainability, and built-in performance logging to assist in troubleshooting and to support future product improvements. Despite the similarity of design to the previous 20kW transmitters on the 70-m DSN antennas, several problems were discovered during the initial months of operation. Problems included secondary effects due to introduction of unsatisfactory cooling water quality, poor station grounding process, flaws in the manufacturing of high-voltage transformers, unreliable commercial and Mil-Spec screened parts, as well as some errors in design and hardware specification. Some problems with custom-made high-power microwave components have been overcome; however, obtaining similar parts in the future may be difficult. Addressing the transmitter problems has been an ongomig task over the past four years, but the result has been significant improvement in overall transmitter reliability as the issues of design and component engineering, maintenance support, and Earth station logistics, were resolved. (1,2). C1 [Silva, Arnold; Conroy, Bruce; Losh, David L.; Vodonos, Yakov] Jet Prop Lab, Pasadena, CA 91109 USA. RP Silva, A (reprint author), 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 SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 946 EP 954 PG 9 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235300085 ER PT S AU Cwik, T Agnes, G Moussessian, A Norton, C Zhao, F AF Cwik, Tom Agnes, Greg Moussessian, Alina Norton, Charles Zhao, Feng GP IEEE TI A precision deployable aperture system facility SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB Precision deployment is an enabling technology for future NASA large aperture missions. Possible concept missions include optical, infrared, sub-millimeter, or microwave apertures too large to fit unfolded in a launch shroud. Dimensional stability is the overriding structural design driver for these large deployable apertures. The stability is driven by constraints derived from the system's mass and structural stability and to thermal and dynamical loads. As the aperture size increases, and the systems mass density is correspondingly decreased, the ability to test the performance of these apertures in a 1-g environment requires both a unique facility and special testing methodologies. (1) (2). This talk will describe a facility under development that includes an enclosure with extreme environmental control, a metrology systems for measuring deployment precision and aspects of an integrated modeling system that will be validated in the facility. Though built to the demanding specifications of deployed optical systems, this talk will focus on components of the facility specific to space-based microwave and millimeter wave antenna systems. The first component of the facility is an enclosure with 10m x 5m x 3m (L x W x H) usable volume that is controlled under ambient temperature to thermal stability of < 0.01 C degrees/Hr, acoustic control of < 35 dBA and seismic control of < 10 mu gs. The enclosure includes a gravity offload system and allows development of single and multi-petal test articles. Instrumentation in the facility includes three-dimensional videogrammetry system capable of absolute measurement accuracy less than 1 millimeter, and a laser vibrometer system for modal testing. The second component of the facility is the development of an optical metrology system for aligning and monitoring large, deployable structures and telescopes to a fraction of a wavelength. A six beam 'optical hexapod' metrology gauge is being built that will measure to 1 micron absolute accuracy with 1 nanometer relative accuracy over a 10m range. The final component of the facility is comprised of system architecture and modeling components using integrated modeling tools for predictive simulations of aperture systems under orbital loads. These models are being compared to controlled experiments completed in the facility. C1 [Cwik, Tom; Agnes, Greg; Moussessian, Alina; Norton, Charles; Zhao, Feng] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Cwik, T (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 2 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 978 EP 984 PG 7 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235300088 ER PT S AU Moghaddam, M Rahmat-Samii, Y Partridge, P Van Nieuwstadt, L Vitaz, J Haynes, M Huang, J Cable, V AF Moghaddam, Mahta Rahmat-Samii, Yahya Partridge, Preston Van Nieuwstadt, Line Vitaz, Jackie Haynes, Mark Huang, John Cable, Vaughn GP IEEE TI Dual polarized UHF/VHF honeycomb stacked-patch feed array for a large-aperture space-borne radar antenna SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB As penetration depth through vegetation and ground becomes more important in active remote sensing applications, there is a shift toward using lower frequencies. To facilitate imaging of ground water, soil moisture and composition, and penetrating through forest canopies, a dual-band synthetic aperture radar (SAR) has been proposed to operate at VHF and UHF frequencies. To accommodate weekly repeat observations from LEO, a swath of roughly 350 Km is needed, requiring a 30-m long antenna aperture from the SAR design point of view. The beams of the UHF and the VHF antennas must coincide in the cross-track direction, resulting in antenna widths of 3m and 11m, respectively. A stacked, linearly dual-polarized patch array feeding a 30 meter diameter parabolic reflector is proposed for this application, which synthesizes near-rectangular effective apertures on the reflector. Using a mesh reflector technology, the mass of such an antenna configuration is about ten times smaller than a corresponding phased-array antenna. A scaled-frequency version of the feed array was initially designed, built, and tested. It was also integrated with a scaled reflector antenna to verify the performance of the overall system. The actual frequency version was then designed, built, and tested. The design of the dual-band stacked array and the power dividers will be discussed, the fabrication process explained, and the approaches used for optimizing the performance characteristics will be presented. The measurement results for return loss on both transmit and receive, isolation, and radiation pattern will be presented and shown to be in good agreement with the simulated results. (12). C1 [Moghaddam, Mahta; Van Nieuwstadt, Line; Vitaz, Jackie; Haynes, Mark] Univ Michigan, Ann Arbor, MI 48109 USA. [Rahmat-Samii, Yahya] Univ California, Los Angeles, CA USA. [Partridge, Preston] Aerosp Corp, El Segundo, CA USA. [Huang, John; Cable, Vaughn] Jet Prop Lab, Pasadena, CA USA. RP Moghaddam, M (reprint author), Univ Michigan, Ann Arbor, MI 48109 USA. EM mmoghadd@umich.edu NR 6 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 985 EP + PG 3 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235300089 ER PT S AU MacNeal, BE Abraham, DS Cesarone, RJ AF MacNeal, Bruce E. Abraham, Douglas S. Cesarone, Robert J. GP IEEE TI DSN antenna array architectures based on future NASA mission needs SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB A flexible method of parametric, full life-cycle cost analysis has been combined with data on NASA's future communication needs to estimate the required number and operational dates of new antennas for the Deep Space Network (DSN). The requirements were derived from a subset of missions in the Integrated Mission Set database of NASA's Space Communications Architecture Working Group. Assuming that no new antennas are "constructed", the simulation shows that the DSN is unlikely to meet more than 20% of mission requirements by 2030. Minimum full life-cycle costs result when antennas in the diameter range, 18m-34m, are constructed. Architectures using a mixture of antenna diameters produce a slightly lower full life-cycle cost. C1 [MacNeal, Bruce E.; Abraham, Douglas S.; Cesarone, Robert J.] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP MacNeal, BE (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 SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 1066 EP 1073 PG 8 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235301002 ER PT S AU Shambayati, S AF Shambayati, Shervin GP IEEE TI The struggle for Ka-band: NASA's gradual move towards using 32-GHz Ka-band for Deep Space Missions SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB 32-GHz Ka-band was first considered for deep-space use in 1976. In 1979, 1 GHz of spectrum at 32GHz Ka-band was allocated for Deep Space use. Since then NASA's Jet Propulsion Laboratory (JPL) has been developing technologies and architectures necessary to support Ka-band planetary missions. This paper is a survey of JPL's effort. This survey includes a summary of early paper studies done in the 1980's and 1990's, development of the 34-m beam waveguide (BWG) antennas at the Deep Space Network (DSN), and Ka-band experiments on Mars Observer, Mars Global Surveyor, Deep Space 1, Cassini and Mars Reconnaissance Orbiter spacecraft. The focus of this paper is on the technological and architectural challenges that 32-GHz Ka-band operations have presented throughout this long history. These include challenges presented by the weather and tighter pointing requirements for the spacecraft as well as the need to use multiple data rates during a pass. C1 [Shambayati, Shervin] 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. NR 105 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 1074 EP 1094 PG 21 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235301003 ER PT S AU Shambayati, S Border, JS Morabito, DD Mendoza, R AF Shambayati, Shervin Border, James S. Morabito, David D. Mendoza, Ricardo GP IEEE TI MRO Ka-band demonstration: Cruise phase lessons learned SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB NASA's Mars Reconnaissance Orbiter (MRO) was launched on August 12, 2005 and was inserted into Mars orbit successfully on March 10, 2006. From September 2005 through January 2006, the Ka-band signal from the spacecraft was tracked several times by NASA's Deep Space Network (DSN). During these tracks a number of Ka-band functions for both the spacecraft and the ground systems were tested. These tests were performed to assess the readiness of the ground system and spacecraft to support Ka-band demonstration activities during MRO's primary science phase (PSP). As a result of these tests a number of important lessons were learned regarding the performance of the Ka-band link and the performance of the ground equipment. This paper presents the performance of the ground antenna pointing, Delta Differential One-Way Ranging (Delta DOR) performance and the telemetry performance of the Ka-band link. These results indicate that the extra effort for pointing calibration of the ground antennas at Ka-band is extremely useful; Ka-band shows potential for improved Delta DOR performance and the models for Ka-band performance of the ground station microwave noise temperature are very accurate. C1 [Shambayati, Shervin; Border, James S.; Morabito, David D.; Mendoza, Ricardo] 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. NR 14 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 1095 EP 1111 PG 17 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235301004 ER PT S AU Sanders, FA Jones, G Levesque, M AF Sanders, Felicia A. Jones, Grailing, Jr. Levesque, Michael GP IEEE TI Transfer of files between the Deep Impact spacecrafts and the ground data system using CFDP: a case study SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB The CCSDS File Delivery Protocol (CFDP) Standard could reshape ground support architectures by enabling applications to communicate over the space link using reliable-symmetric transport services. JPL utilized the CFDP standard to support the Deep Impact Mission. The architecture was based on layering the CFDP applications on top of the CCSDS Space Link Extension Services for data transport from the mission control centers to the ground stations. On July 4, 2005 at 1:52 A.M. EDT, the Deep Impact impactor successfully collided with comet Tempel 1. During the final 48 hours prior to impact, over 300 files were uplinked to the spacecraft, while over 10 thousand files were downlinked from the spacecraft using the CFDP during the encounter timeframe. This paper uses the Deep Impact Mission as a case study in a discussion of the CFDP architecture, Deep Impact Mission requirements, and design for integrating the CFDP into the JPL deep space support services. Issues and recommendations for future missions using CFDP are also provided. C1 [Sanders, Felicia A.; Jones, Grailing, Jr.; Levesque, Michael] Jet Prop Lab, Pasadena, CA 91107 USA. RP Sanders, FA (reprint author), Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91107 USA. NR 1 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 1112 EP 1116 PG 5 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235301005 ER PT S AU Gao, JL Leang, D AF Gao, Jay L. Leang, Dee GP IEEE TI A demand access protocol for space applications SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB This paper describes a demand access protocol for space communications, which is a messaging procedure that facilitates the exchange of resource requests and grants between users and service providers. A minimal set of operational and environmental needs and constraints are assumed since the intent is to keep the protocol flexible and efficient for a wide-range of envisioned NASA robotic and human exploration missions. The protocol described in this document defines the message format and procedures used to ensure proper and correct functioning of a demand access communications system, which must operate under customized resource management policies applied by the users and service providers. This protocol also assumes a minimal set of capabilities from the underlying communications system so that no unique requirements are imposed on the communications sub-systems.(1) (2). C1 [Gao, Jay L.; Leang, Dee] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Gao, JL (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 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 1139 EP 1145 PG 7 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235301008 ER PT S AU Guillaume, A Lee, S Wang, YF Zheng, H Hovden, R Chau, S Tung, YW Terrile, RJ AF Guillaume, Alexandre Lee, Seugnwon Wang, Yeou-Fang Zheng, Hua Hovden, Robert Chau, Savio Tung, Yu-Wen Terrile, Richard J. GP IEEE TI Deep Space Network scheduling using evolutionary computational methods SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB The Deep Space Network (DSN) is an international network of antennas that supports all of NASA's deep space missions. With the increasing demand of tracking time, DSN is highly over-subscribed. Therefore, the allocation of the DSN resources should be optimally scheduled to satisfy the requirements of as many missions as possible. Currently, the DSN schedules are manually and iteratively generated through several meetings to resolve conflicts. In an attempt to ease the burden of the DSN scheduling task, we have applied evolutionary computational techniques to the DSN scheduling problem. These methods provide a decision support system by automatically generating a population of optimized schedules under varying conflict conditions. These schedules are used to decide the simplest path to resolve conflicts as new scheduled items are added or changed along the scheduled 26 weeks.(1 2). This paper presents the specific approach taken to formulate the problem in terms of gene encoding, fitness function, and genetic operations. The genome is encoded such that a subset of the scheduling constraints is automatically satisfied. Several fitness functions are formulated to emphasize different aspects of the scheduling problem. The optimal solutions of the different fitness functions demonstrate the trade-off of the scheduling problem and provide insight into a conflict resolution process. C1 [Guillaume, Alexandre; Lee, Seugnwon; Wang, Yeou-Fang; Zheng, Hua; Hovden, Robert; Chau, Savio; Tung, Yu-Wen; Terrile, Richard J.] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Guillaume, A (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 2 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 1146 EP 1151 PG 6 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235301009 ER PT S AU Tsao, P Okino, C Clare, LP AF Tsao, Philip Okino, Clayton Clare, Loren P. GP IEEE TI Performance evaluation of video codecs in the space environment SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB In human missions to other planets and natural satellites (e.g., return to the Moon and future missions to Mars), there will be a need to provide video services for such functions as monitoring analysis, personal private video conversations and general public outreach. There is a desire to provide these services by leveraging terrestrial Internet concepts and technology. In this work we focus on the video performance mechanisms as they are impacted in a space environment, where long range latencies and bit errors arise in the wireless/RF links. We provide results from experiments using open source implementations of commercial video standards. Both Peak Signal-to-Noise Ratio (PSNR) and Structural Similarity (SSIM) are used as a performance metrics.(1) (2). C1 [Tsao, Philip; Okino, Clayton; Clare, Loren P.] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Tsao, P (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 19 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 1152 EP 1160 PG 9 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235301010 ER PT S AU Schumann, J Denney, E AF Schumann, Johann Denney, Ewen GP IEEE TI Automatic generation of certifiable space communication software SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB Reliable, secure and effective communication between a spacecraft and the ground station, or between multiple spacecraft is central to all space missions. Smooth control of spacecraft and the downlink of mission and science data rely heavily on reliable means of communication. Moreover, heightened needs for operations security in recent years add complexity to communication system requirements. The communication system, therefore, is a highly safety and mission critical component. A single successful malicious attack or a flaw in the code can have serious consequences that put the mission or even human life at risk. We are integrating and adapting a set of existing tools in order to provide a unified end-to-end approach to the design, analysis, implementation, and certification of space communication software. Our tools are based upon rigorous logical and mathematical foundations, and are capable of automatically generating high-quality communication software from a high-level model. Automatic, tamper-proof formal certification techniques are used to provide explicit guarantees about important reliability and security properties and the absence of implementation errors. C1 [Schumann, Johann; Denney, Ewen] NASA, Ames Res Ctr, RIACS, Moffett Field, CA 94035 USA. RP Schumann, J (reprint author), NASA, Ames Res Ctr, RIACS, Moffett Field, CA 94035 USA. NR 23 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 1171 EP 1178 PG 8 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235301012 ER PT S AU Nguyen, S Okino, C Clare, L Walsh, W AF Nguyen, Sam Okino, Clayton Clare, Loren Walsh, William GP IEEE TI Space-based Voice over IP networks SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES ID SPEECH AB In human space exploration missions, there will be a need to provide voice communications services. In this work we focus on the performance of Voice over IP (VoIP) techniques applied to space networks, where long range latencies, simplex links, and significant bit error rates occur. Link layer and network layer overhead issues are examined. We posit that imposing additional speech processing latencies in the form of multiple frames per packet is tolerable in the space regime, and show resulting performance overhead improvements. Furthermore, we find that even with channel bit error rates of 10(-5) and 10(-4), the frame size does not severely degrade the original speech.(1) (2). C1 [Nguyen, Sam; Okino, Clayton; Clare, Loren] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Walsh, William] LinQuest Corp, Orange, CA 92868 USA. RP Nguyen, S (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Sam.P.Nguyen@jpl.nasa.gov; Clayton.M.Okino@jpl.nasa.gov; Loren.P.Clare@jpl.nasa.gov; William.Walsh@LinQuest.com NR 8 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 1179 EP 1189 PG 11 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235301013 ER PT S AU Alemany, K Morse, EL Easter, RW AF Alemany, Kristina Morse, Elisabeth L. Easter, Robert W. GP IEEE TI Control authority network analysis applied to lunar outpost deployment SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB In order to return humans to the Moon, the Constellation Program will be required to operate a complex network of humans and spacecraft in several locations. This requires an early look at how decision-making authority will be allocated and transferred between humans and computers, for each of the many decision steps required for the various mission phases. This paper presents an overview of such a control authority analysis, along with an example based upon a lunar outpost deployment scenario. The results illustrate how choosing an optimal control authority architecture can serve to significantly reduce overall mission risk, when applied early in the design process.*. C1 [Alemany, Kristina] Georgia Inst Technol, Atlanta, GA 30332 USA. [Morse, Elisabeth L.; Easter, Robert W.] NASA, Jet Prop Lab, Pasadena, CA 91109 USA. RP Alemany, K (reprint author), Georgia Inst Technol, Atlanta, GA 30332 USA. EM kristina_alemany@ae.gatech.edu NR 7 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 1199 EP 1211 PG 13 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235301015 ER PT S AU Gal-Edd, J Fatig, CC AF Gal-Edd, Jonathan Fatig, Curtis C. GP IEEE TI Lunar robotic relay the first phase of building the lunar ground networks SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB As part of the National Aeronautics and Space Administration (NASA) mission, the lunar exploration team has identified the Moon's South Pole as a target for a robotics mission due the possibility of existence of water in the craters. The role of lunar relay satellites is to provide coverage for areas that do not have a direct view of the Earth. The lunar relay satellites and the Earth ground network supporting them are key for the many robotic and manned missions. In this type of mission, though similar to the Mars relay system, the design of the ground network in support of the lunar relay system requires attention to ground network infrastructure, spectrum, and tracking requirements. This paper will address the evolution of Exploration Ground stations and ground options to support the early Lunar Relay Satellite (LRS-1) for robotics mission and its relation to manned relay (LRS-2 and LRS-3). C1 [Gal-Edd, Jonathan; Fatig, Curtis C.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Gal-Edd, J (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. EM Jonathan.S.Gal-Edd@nasa.gov; curtis.fatig@gsfc.nasa.gov NR 3 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 1217 EP 1223 PG 7 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235301017 ER PT S AU Majid, WA Bagri, DS AF Majid, Walid A. Bagri, Durgadas S. GP IEEE TI Availability of calibration sources for measuring spacecraft angular position with sub-nanoradian accuracy SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES ID RADIO-SOURCES; SKY; GHZ AB Precision measurements are now capable of determining the angular position of spacecrafts with accuracies of 2-5 nanoradians. To achieve this level of precision, compact radio sources with flux density of at least a few hundred milli-Jansky (at 8.4 GHz) are used for calibration purposes. Further improvements in position measurement accuracy may be possible with use of appropriate calibrators near the direction of the spacecrafts even if the calibrators are much weaker (a few milli-Jansky) in flux density. In this paper we discuss the calibrator flux density required to achieve sub-nanoradian astrometric accuracy and attempt to estimate the density of suitable calibrators, using existing source count surveys. We point out, however, that the fraction of these sources that are suitable for use as calibrators is not well understood and requires further study. C1 [Majid, Walid A.; Bagri, Durgadas S.] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Majid, WA (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 14 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 1243 EP 1248 PG 6 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235301020 ER PT S AU Hashmi, AJ Eftekhar, AA Adibi, A Amoozegar, F AF Hashmi, Ali Javed Eftekhar, Ali Asghar Adibi, Ali Amoozegar, Farid GP IEEE TI Effect of tracking errors on performance of telescope arrays receiver for deep space optical communication SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB On earth, a large aperture telescope is required to achieve the substantial data rates needed for a deep space optical communication link. However, not only are large telescopes very costly but, it is also very difficult to attain near diffraction limited performance with large apertures. An array of relatively smaller sized telescopes combined to form a larger synthesized aperture is a viable and efficient alternative to a large monolithic telescope. However, the performance of telescope arrays needs to be investigated under certain limiting factors such as turbulence, tracking errors etc. In this paper, we analyze the impact of tracking errors on the performance of telescope arrays. A deep space optical communication link between Mars and a telescope array receiver on earth is simulated. A closed loop tracking system is employed at the receiver end to cater for the random tracking errors. Monte Carlo Simulation results show that, under tracking errors the performance of telescope arrays can reach very close to that of a large monolithic telescope with the same total photon collecting area. Hence, telescope arrays are a cost-effective alternative for deep space optical communication. (12). C1 [Hashmi, Ali Javed; Eftekhar, Ali Asghar; Adibi, Ali] Georgia Inst Technol, 777 Atlantic Dr, Atlanta, GA 30332 USA. [Amoozegar, Farid] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Hashmi, AJ (reprint author), Georgia Inst Technol, 777 Atlantic Dr, Atlanta, GA 30332 USA. EM adibi@ece.gatech.edu; Farid.Amoozegar@jpl.nasa.gov NR 13 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 1249 EP 1256 PG 8 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235301021 ER PT S AU Akkawi, F Bader, A Fletcher, D Akkawi, K Ayyash, M Alzoubi, K AF Akkawi, Faisal Bader, Atef Fletcher, Daryl Akkawi, Kayed Ayyash, Moussa Alzoubi, Khaled GP IEEE TI Software adaptation: A conscious design for oblivious programmers SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB Agility, mobility, evolvability, and reconfigure-ability are the main characteristics for the next generation software systems. Software adaptation can be seen as the ability to reconfigure the software system by the software engineer, hence the term software adaptability, or the ability of the software to reconfigure itself, hence the term software adaptiveness. Software adaptability and adaptiveness are complementary for building conscious design that can accommodate cohesive components built by programmers that are oblivious to the nature of future changes. The intent of software adaptability is to evolve and reuse the software components in future contexts, whereas the intent of software adaptiveness is to enable the software system to alter its behavior at runtime in order to avoid performance degradation and resource contention. In this paper we present a unified approach that deploys aspect-oriented technology in order to engineer adaptability into the software system and data-mining techniques in order to engineer adaptiveness into the software system. The approach utilizes aspect-orientation and deploys intelligent agents in the design and development of software systems. The intelligent agents in our approach utilize the Q-learning technique in order to discover patterns of performance degradation and reliability violation. The paper articulates the benefits of aspect-oriented methodology and data-mining techniques in building software systems that can cope gracefully with the unanticipated environment changes and requirement changes.(1,2). C1 [Akkawi, Faisal] Northwestern Univ, Chicago, IL 60616 USA. [Bader, Atef] Lucent Technol, Naperville, IL 60655 USA. [Fletcher, Daryl] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Akkawi, Kayed] Robert Morris Coll, Chicago, IL 60616 USA. [Ayyash, Moussa] IIT, Chicago, IL 60616 USA. [Alzoubi, Khaled] Saint Xavier Univ, Chicago, IL 60655 USA. RP Akkawi, F (reprint author), Northwestern Univ, Chicago, IL 60616 USA. EM f-akkawi@northwestern.edu; abader@lucent.com; ayyamou@iit.edu; alzoubi@sxu.edu NR 38 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 1433 EP 1444 PG 12 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235301039 ER PT S AU Kerczewski, RJ Dyer, G AF Kerczewski, Robert J. Dyer, Glen GP IEEE TI Eurocontrol/FAA future communications study - Phase II technology assessments SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB As a result of International Civil Aviation Organization (ICAO) Air Navigation Commission (ANC) meeting 11 in 2003, a need emerged to identify a future air-ground communications system for air traffic management (ATM) communications on which different regions of the world could eventually converge. This need results from the extreme difficulties in having divergent communications systems to meet identical ATM communications requirements in different regions of the world. The US Federal Aviation Administration (FAA) and Eurocontrol initiated a joint activity called the Future Communications Study (FCS) to develop solutions to the need identified by the ANC. The FCS includes operational concepts and communications requirements development, analysis of business and institutional elements, and identification and assessment of technology alternatives. Two of three phases of the FCS technology identification and assessment have been completed. The first phase identified all relevant communications technologies that could be applied to the aeronautical safety communications requirements and screened those technologies against a set of evaluation criteria to determine the best candidates. The second phase performed detailed technical evaluations of a subset of those candidates to determine their potential performance under the expected conditions and operational scenarios envisioned under the FCS. This paper provides background on the FCS and presents an overview of the approach and results of the FCS technology assessment to date. C1 [Kerczewski, Robert J.] NASA, Glenn Res Ctr, 21000 Brookpk Rd, Cleveland, OH 44135 USA. [Dyer, Glen] IIT Corp, Herndon, VA USA. RP Kerczewski, RJ (reprint author), NASA, Glenn Res Ctr, 21000 Brookpk Rd, Cleveland, OH 44135 USA. EM rkerczewski@nasa.gov; glen.dyer@itt.com NR 3 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 1473 EP 1480 PG 8 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235301042 ER PT S AU Sabelhaus, P Geithner, P Diaz, C AF Sabelhaus, Phil Geithner, Paul Diaz, Charles GP IEEE TI Cryogenic optical thermal-vacuum testing of the James Webb Space Telescope (JWST) SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES DE Cryogenic optical testing and verification the; James Webb Space Telescope is one of the biggest; challenges in the I&T program. JWST has constructed an; incremental verification program for the Optical Telescope; and the Integrated Science Instrument Module to ensure; compliance and to mitigate the severity of problems on; flight hardware.(12.) C1 [Sabelhaus, Phil; Geithner, Paul; Diaz, Charles] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Sabelhaus, P (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. EM Phillip.A.Sabelhaus@nasa.gov; cdiaz@hst.nasa.gov NR 13 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 1602 EP 1607 PG 6 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235301053 ER PT S AU Hagopian, JG Ohl, R Bos, B Davila, P Eichhorn, W Hylan, J Hill, M Nowak, M Pasquale, B Sampler, H Wilson, M Gallagher, B Hardaway, J Sullivan, J Young, P Keepers, T Quigley, R AF Hagopian, John G. Ohl, Raymond Bos, Brent Davila, Pamela Eichhorn, William Hylan, Jason Hill, Michael Nowak, Maria Pasquale, Bert Sampler, Henry Wilson, Mark Gallagher, Benjamin Hardaway, James Sullivan, Joseph Young, Philip Keepers, Timothy Quigley, Robert GP IEEE TI Optical alignment and test of the James Webb Space Telescope Integrated Science Instrument Module SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB The James Webb Space Telescope (JWST) is a 6.6m diameter, segmented, deployable telescope for cryogenic IR space astronomy (similar to 40K). The JWST Observatory architecture includes the Optical Telescope Element (OTE) and the Integrated Science Instrument Module (ISIM) element that contains four science instruments (SI) including a Guider. The SI's and Guider are mounted to a composite metering structure with outer dimensions of 2.1x2.2x1.9m. The SI and Guider units are integrated to the ISIM structure and optically tested at NASA/Goddard Space Flight Center as an instrument suite using an OTE SIMulator (OSIM). OSIM is a high-fidelity, cryogenic JWST telescope simulator that features a 1.5m diameter powered mirror. The SIs are aligned to the structure's coordinate system under ambient, clean room conditions using laser tracker and theodolite metrology. Temperature-induced mechanical SI alignment and structural changes are measured using a photogrammetric measurement system at ambient and cryogenic temperatures. OSIM is aligned to the ISIM mechanical coordinate system at the cryogenic operating temperature via internal mechanisms and feedback from alignment sensors in six degrees of freedom. SI performance, including focus, pupil shear and wavefront error, is evaluated at the operating temperature using OSIM. We describe the ambient and cryogenic optical alignment, test and verification plan for the ISIM element. C1 [Hagopian, John G.; Ohl, Raymond; Bos, Brent; Davila, Pamela; Eichhorn, William; Hylan, Jason; Hill, Michael; Nowak, Maria; Pasquale, Bert; Sampler, Henry; Wilson, Mark] NASA, Goddard Space Flight Ctr, Code 551,8800 Greenbelt Rd, Greenbelt, MD 20771 USA. [Gallagher, Benjamin; Hardaway, James; Sullivan, Joseph] Ball Aerosp Tech Corp, Boulder, CO 80301 USA. [Young, Philip] Young Engineer Serv, Albuquerque, NM USA. [Keepers, Timothy; Quigley, Robert] Swales Aerosp Inc, Beltsville, MD 20705 USA. RP Hagopian, JG (reprint author), NASA, Goddard Space Flight Ctr, Code 551,8800 Greenbelt Rd, Greenbelt, MD 20771 USA. EM john.g.hagopian@nasa.gov NR 7 TC 1 Z9 1 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 1608 EP 1620 PG 13 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235301054 ER PT S AU Howard, JM Hayden, B Keski-Kuha, R Feinberg, L AF Howard, Joseph M. Hayden, Bill Keski-Kuha, Ritva Feinberg, Lee GP IEEE TI Optical modeling of the alignment and test of the NASA James Webb Space Telescope SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB Optical modeling challenges of the ground alignment plan and optical test and verification of the NASA James Webb Space Telescope are discussed. Issues such as back-out of the gravity sag of light-weighted mirrors, as well as the use of a sparse-aperture auto-collimating flat system are discussed. A walk-through of the interferometer based alignment procedure is summarized, and sensitivities from the sparse aperture wavefront test are included as examples.(12). C1 [Howard, Joseph M.; Hayden, Bill; Keski-Kuha, Ritva; Feinberg, Lee] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Howard, JM (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. NR 4 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 1621 EP 1626 PG 6 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235301055 ER PT S AU Dean, BH AF Dean, Bruce H. GP IEEE TI Looking at Hubble through the eyes of JWST SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES ID PHASE-RETRIEVAL ALGORITHMS; DIFFRACTION PLANE PICTURES; IMAGE-RECONSTRUCTION; ADAPTIVE OPTICS; TELESCOPE; DIVERSITY; MODULUS; OBJECT AB The phase retrieval algorithm developed for the James Webb Space Telescope (JWST) is applied to archival image data that was originally used to characterize the Hubble Space Telescope (HST) primary mirror edge defect. The value obtained for the spherical aberration is compared with earlier values reported by several teams comprising the Hubble Aberration Recovery Project (HARP). Several lessons learned from the Hubble phase retrieval problem are described and a discussion is given on how these have been incorporated into the JWST Observatory design.(1,2). C1 [Dean, Bruce H.] NASA, Goddard Space Flight Ctr, Opt Branch, Greenbelt, MD 20771 USA. RP Dean, BH (reprint author), NASA, Goddard Space Flight Ctr, Opt Branch, Mailstop 551, Greenbelt, MD 20771 USA. NR 37 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 1627 EP 1636 PG 10 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235301056 ER PT S AU Stahl, HP AF Stahl, H. Philip GP IEEE TI JWST lightweight mirror TRL-6 results SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES ID GENERATION SPACE TELESCOPE; TECHNOLOGY DEVELOPMENT AB Mirror technology for a Primary Mirror Segment Assembly (PMSA) is a system of components: reflective coating; polished optical surface; mirror substrate; actuators, mechanisms and flexures; and reaction structure. The functional purpose of a PMSA is to survive launch, deploy and align itself to form a 25 square meter collecting area 6.5 meter diameter primary mirror with a 131 nm rms wavefront error at temperatures < 50K and provide stable optical performance for the anticipated thermal environment. At the inception of JWST in 1996, such a capability was at a Technology Readiness Level (TRL) of 3. A highly successful technology development program was initiated including the Sub-scale Beryllium Mirror Demonstrator (SBMD) and Advanced Mirror System Demonstrator (AMSD) projects. These projects along with flight program activities have matured mirror technology for JWST to TRL-6. A directly traceable prototype (and in some cases the flight hardware itself) has been built, tested and operated in a relevant environment.(12). C1 [Stahl, H. Philip] NASA, George C Marshall Space Flight Ctr, Huntsville, AL 35812 USA. RP Stahl, HP (reprint author), NASA, George C Marshall Space Flight Ctr, XD-30, Huntsville, AL 35812 USA. NR 18 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 1637 EP 1648 PG 12 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235301057 ER PT S AU Saif, B Bluth, M Eegholm, B Zukowski, B Keski-Kuha, R Blake, P AF Saif, Babak Bluth, Marcel Eegholm, Bente Zukowski, Barbara Keski-Kuha, Ritva Blake, Peter GP IEEE TI Electronic speckle pattern interferometry for JWST SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB Development of many new technologies is required to successfully produce the large, lightweight, deployable, cryogenic telescope with segmented primary mirror for the James Webb Space Telescope (JWST) mission. One of the technologies is interferometry to verify structural deformations in large, deployable, lightweight, cryogenic, precision structures to nanometer level accuracy. An instantaneous acquisition phase shifting speckle interferometer was designed and built to support the development of JWST Optical Telescope Element (OTE) primary mirror backplane. This paper discusses characterization of the Electronic Speckle Pattern Interferometer (SPS-DSPI) developed for JWST to verify its capability to measure structural deformations in large composite structures at cryogenic temperature.(1). C1 [Saif, Babak] Space Telescope Sci Inst, 3700 San Martin Dr, Baltimore, MD 21218 USA. [Bluth, Marcel; Eegholm, Bente; Zukowski, Barbara] Swales Aerospace, Beltsville, MD 20705 USA. [Keski-Kuha, Ritva; Blake, Peter] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Saif, B (reprint author), Space Telescope Sci Inst, 3700 San Martin Dr, Baltimore, MD 21218 USA. EM saif@stsci.edu; beegholm@swales.com; ritva.keski-kuha@nasa.gov NR 12 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 1649 EP 1658 PG 10 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235301058 ER PT S AU Stahl, HP Feinberg, L AF Stahl, H. Philip Feinberg, Lee GP IEEE TI Summary of NASA Advanced Telescope and Observatory Capability Roadmap SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB The NASA Advanced Telescope and Observatory (ATO) Capability Roadmap addresses technologies necessary for NASA to enable future space telescopes and observatories operating in all electromagnetic bands, from x-rays to millimeter waves, and including gravity-waves. It lists capability priorities derived from current and developing Space Missions Directorate (SMD) strategic roadmaps. Technology topics include optics; waveftont sensing and control and interferometry; distributed and advanced spacecraft systems; cryogenic and thermal control systems; large precision structure for observatories; and the infrastructure essential to future space telescopes and observatories.(1 2). C1 [Stahl, H. Philip] NASA, George C Marshall Space Flight Ctr, XD-30, Huntsville, AL 35812 USA. [Feinberg, Lee] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Stahl, HP (reprint author), NASA, George C Marshall Space Flight Ctr, XD-30, Huntsville, AL 35812 USA. EM h.philip.stahl@nasa.gov; LFeinberg@hst.nasa.gov NR 9 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 1659 EP 1669 PG 11 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235301059 ER PT S AU Chao, TH AF Chao, Tien-Hsin GP IEEE TI Electro-optic imaging Fourier transform spectrometer SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB JPL is developing an innovative compact, low mass, Electro-Optic Imaging Fourier Transform Spectrometer (E-O IFTS) for hyperspectral. imaging applications. The spectral region of this spectrometer will be 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 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 experimental progress will be presented.(12). C1 [Chao, Tien-Hsin] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Chao, TH (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 3 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 1694 EP 1699 PG 6 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235301062 ER PT S AU Liebe, CC Alexander, J Aung, M Goldberg, H Johnson, A Lam, R Maize, E Meras, P Montgomery, J Palacios, P Spiers, G Wilson, M AF Liebe, Carl Christian Alexander, James Aung, Mimi Goldberg, Hannah Johnson, Andrew Lam, Raymond Maize, Earl Meras, Patrick Montgomery, James Palacios, Peter Spiers, Gary Wilson, Michael GP IEEE TI Field testing of Lunar Access and Navigation Device (LAND) SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB A laser radar system has been constructed. It is based on a commercial PC with digitizer, pulse delay instrument, National Instruments 10 card and an optical head from a previous laser radar program. The laser radar was mounted on a gyro stabilized gimbal on the nose of a helicopter and flown in the Mojave Desert in September 2006. The collected data will be used to test algorithms for future precision lunar landers, which may be utilizing a laser radar as the primary landing sensor. This paper will describe the laser radar and PC based acquisition system used for the data collection, and provide an overview of the supporting test sensors and architecture. Preliminary data collected during the helicopter field testing will also be presented. C1 [Liebe, Carl Christian; Alexander, James; Aung, Mimi; Goldberg, Hannah; Johnson, Andrew; Lam, Raymond; Maize, Earl; Meras, Patrick; Montgomery, James; Palacios, Peter; Spiers, Gary; Wilson, Michael] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Liebe, CC (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 IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 1755 EP 1766 PG 12 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235301069 ER PT S AU Liebe, CC Dubovitsky, S Peters, R AF Liebe, Carl Christian Dubovitsky, Serge Peters, Robert GP IEEE TI 3D metrology camera SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB We describe a concept for a metrology system that can simultaneously determine the Cartesian coordinates of thousands of targets and has no moving parts. The system is called the MSTAR(3D) system and is based on two color interferometry where the conventional photodiode has been replaced with an extremely fast focal plane array. It permits the measurement of the three-dimensional position of multiple targets with a fraction of a millimeter accuracy. In this paper, the concept will be described in detail. Proof of concept measurements have been performed on a candidate camera. The measured parameters have been used in error budgets for performance validation of the concept. It will be shown that a metrology system like MSTAR(3D) can determine the xyz position with sub-millimeter accuracy. This is sufficient accuracy for most large structure metrology systems and wave front corrections for large radar antennas. C1 [Liebe, Carl Christian; Dubovitsky, Serge; Peters, Robert] CALTECH, Jet Prop Lab, Pasadena, CA 91101 USA. RP Liebe, CC (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91101 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 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 1767 EP 1774 PG 8 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235301070 ER PT S AU Bagri, DS AF Bagri, Durgadas. S. GP IEEE TI Frequency synthesis approach to determine spacecraft angular position with sub-nanoradian accuracy SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB This paper describes a possible approach to measuring angular position of a spacecraft with reference to a nearby calibration source (quasar) with an accuracy of a few tenths of a nanoradian using a very long baseline interferometer that measures the interferometer phase with a modest accuracy. It employs (1) radio frequency (RF) phase delay to determine the spacecraft position with a high precision, and (2) multiple group delay measurements using either frequency tones or telemetry signals at different frequency spacing to resolve ambiguity of the fringe (cycle) containing the direction of the spacecraft. C1 [Bagri, Durgadas. S.] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Bagri, DS (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 4 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 1834 EP 1838 PG 5 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235301078 ER PT S AU Sadowy, G Heavey, B Moller, D Rignot, E Zawadzd, M Rengarajan, S AF Sadowy, Gregory Heavey, Brandon Moller, Delwyn Rignot, Eric Zawadzd, Mark Rengarajan, Sembiam GP IEEE TI Technology demonstration of Ka-band digitally-beamformed radar for ice topography mapping SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES ID SHUNT SLOTS; ARRAYS; DESIGN AB GLISTIN (Glacier and Land Ice Surface Topography Interferometer) is a spaceborne interferometric synthetic aperture radar for topographic mapping of ice sheets and glaciers. GLISTIN will collect ice topography measurements over a wide swath with sub-seasonal repeat intervals using a Ka-Band digitally-beamformed antenna. This paper will give an overview of the system design and key technology demonstrations including a 1m x 1m digitally-beamformed Ka-band waveguide slot antenna with integrated digital receivers. We will also detail the experimental scenario that we will use to demonstrate both the beamforming and interferometric performance of this system.(1 2). C1 [Sadowy, Gregory; Heavey, Brandon; Moller, Delwyn; Rignot, Eric; Zawadzd, Mark] Jet Prop Lab, 4800 Oak Grove Drve, Pasadena, CA 91109 USA. [Rengarajan, Sembiam] Calif State Univ Northridge, Northridge, CA USA. RP Sadowy, G (reprint author), Jet Prop Lab, 4800 Oak Grove Drve, Pasadena, CA 91109 USA. EM sadowy@jpl.nasa.gov RI Rignot, Eric/A-4560-2014 OI Rignot, Eric/0000-0002-3366-0481 NR 5 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 2222 EP + PG 3 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235302013 ER PT S AU Martin, S AF Martin, Stefan GP IEEE TI Starlight nulling technology at the Jet Propulsion Laboratory SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB The current interests in extra-solar planet detection and space-based and ground-based interferometry for astronomical observations have led to the development of a number of nulling instruments at the Jet Propulsion Laboratory (JPL) and elsewhere. This paper(1 2) summarizes briefly JPL's efforts in nulling interferometry to date and consists of illustrations of some key nulling technologies. The basic optical layouts of instruments demonstrating three different nulling techniques are shown. In an effort to narrow the area of discussion, some notable nulling efforts made elsewhere will not be included. C1 [Martin, Stefan] Jet Prop Lab, Pasadena, CA 91101 USA. RP Martin, S (reprint author), Jet Prop Lab, Pasadena, CA 91101 USA. NR 25 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 2242 EP 2250 PG 9 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235302015 ER PT S AU Sainuele, R Wallace, JK Schmidtlin, E Shao, M Levine, BM Fregoso, S AF Sainuele, Rocco Wallace, J. Kent Schmidtlin, Edouard Shao, Michael Levine, B. Martin Fregoso, Santos GP IEEE TI Experimental progress and results of a visible nulling coronagraph SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB The crux of visible exoplanet detection is overcoming significant star-planet contrast ratios on the order of 10(-7) to 10(-10)-at very small angular separations. We are developing a nulling interferometer coronagraph designed to achieve a 10(-6) contrast ratio at a working science bandpass of 20% visible light using a pseudo-achromatic phase flip. Recent results yield contrast ratios at the 10(-6) level with a 15% visible bandpass averaged over three seconds. Further broadening of the bandpass will require hardware modifications, although the argument is made that broadening the bandpass should not adversely affect the null depth until beyond 20% visible light. The current testbed configuration has reached monochromatic null depths of 1.11 x 10(-7) (lambda = 638 nm) averaged over three seconds. This paper will describe the experimental approach for achieving broadband nulls, as well as error considerations and limitations, and the most recent results of the nulling interferometer testbed. C1 [Sainuele, Rocco] Northop Grumman Corp, 1 Space Pk Dr, Redondo Beach, CA 90278 USA. [Wallace, J. Kent; Schmidtlin, Edouard; Shao, Michael; Levine, B. Martin; Fregoso, Santos] Jet Prop Lab, Pasadena, CA 91109 USA. RP Sainuele, R (reprint author), Northop Grumman Corp, 1 Space Pk Dr, Redondo Beach, CA 90278 USA. EM rocco.samuele@ngc.com FU Terrestrial Planet Finder Program FX This work was carried out by Northrop Grumman Internal Resources and the Jet Propulsion Laboratory, California Institute of Technology, under contract with the National Aeronautics and Space Administration and supported by the Terrestrial Planet Finder Program. NR 6 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 2251 EP + PG 2 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235302016 ER PT S AU Wallace, JK Macintosh, B Shao, M Bartos, R Dumont, P Levine, BM Rao, S Samuele, R Shelton, C AF Wallace, J. Kent Macintosh, Bruce Shao, Michael Bartos, Randall Dumont, Phil Levine, B. Martin Rao, Shanti Samuele, Rocco Shelton, Chris GP IEEE TI An interferometric wave front sensor for measuring post-coronagraph errors on large optical telescopes SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB The Gemini Planet Imager (GPI) [1], now in the early stages of development, is a ground-based extreme adaptive optics system with an advanced coronagraphic system and integral-field spectrometer. At commissioning in early 2011, it will be deployed on one of the twin eight meter Gemini Telescopes. This powerful instrument, which works at a science wavelength in the near-infrared, will enable the direct detection and characterization of self-luminous Jupiter-class planets from the ground. Semi-static and non-common path wave front errors that are not sensed by the active wave front sensor in the adaptive optics system will lead to a focal plane speckle pattern that will mask exo-planets. The GPI Instrument will incorporate an interferometric wave front sensor, designed and developed at JPL, which will measure these errors. This talk will emphasis this novel sensor and describes how it is used to measure the non-common path amplitude and phase errors in the system that would otherwise limit the achievable contrast. We will describe the system error budget as well as simulations that model the system performance. Finally, we will also discuss the status of our laboratory testbed that is designed to test the fundamental principles of post-coronagraph wave front sensing. This system promises a rich combination of interferometry and large optical systems in support of cutting edge science research. C1 [Wallace, J. Kent; Shao, Michael; Bartos, Randall; Dumont, Phil; Levine, B. Martin; Rao, Shanti; Shelton, Chris] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Macintosh, Bruce] Lawrence Livermore Natl Lab, Livermore, CA 94550 USA. [Samuele, Rocco] Northrop Grumman, Redondo Beach, CA 90278 USA. RP Wallace, JK (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM James.K.Wallace@jpl.nasa.gov FU National Science Foundation Science and Technology Center for Adaptive Optics; [AST-9876783] FX This work has been supported in part or full by the National Science Foundation Science and Technology Center for Adaptive Optics, managed by the University of California at Santa Cruz under cooperative agreement No. AST-9876783 NR 5 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 2258 EP + PG 2 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235302017 ER PT S AU Serabyn, G AF Serabyn, Gene GP IEEE TI High-contrast, narrow-field imaging with a multi-aperture telescope SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES ID BEAM COMBINER; FIBERS AB The direct detection of faint planetary companions to bright nearby stars calls for the development of high-contrast narrow-field detection techniques. A number of novel coronagraphic approaches aimed at filling this niche have recently been proposed, but this challenging observational goal may also call for the development of novel types of telescope architecture. As discussed here, one approach to high-contrast narrow field imaging involves replacing the monolithic telescope assembly by an array of small "sub-aperture" telescopes, with the final pupil being assembled by means of a single-mode fiber array. Such an approach can potentially greatly relax the volume, mass and cost constraints thought to apply to large and accurately-figured monolithic telescopes. However, the suggested approach relies on the use of a well-matched, low-dispersion, single-mode fiber array. Classical single mode fibers would require dispersion correction to match pathlengths, but the new generation of photonic fibers, with design-selectable parameters, may ease this issue.(1,2). C1 [Serabyn, Gene] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Serabyn, G (reprint author), CALTECH, Jet Prop Lab, MS 171-113, Pasadena, CA 91109 USA. NR 11 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 2265 EP 2271 PG 7 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235302018 ER PT S AU Morris, R Dungan, J AF Morris, Robert Dungan, Jennifer GP IEEE TI Harnessing the sensor web through model-based observation SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB ,This paper introduces the notion of model-based observing. a process of coordinating resources in a sensor web based on goals generated from Earth science or other investigations. Model-based observing will transform a sensor web into a cognitive web, a distributed, goal-directed sensing system. For a collection of remote sensors to be a cognitive web, an information infrastructure with the following features must be developed. First, there needs to be a representation of current observation goals and the tasks being performing to accomplish these goals. Second, there must be a means to recognize when changes to the sensing environment threaten to prevent the accomplishment of those goals. Third, a cognitive web must adapt to changes in its own configuration; it must be able to recognize opportunities for modifying its data acquisition plans in order to improve overall performance. It must act as a coordinator of resources, an optimizer of tasks, and a broker for data products. An architecture for a cognitive web is proposed that would utilize continuous planning and scheduling, plan execution and monitoring, and model-based goal generation. Portions of this architecture exist in extant systems.(1 2). C1 [Morris, Robert; Dungan, Jennifer] NASA, Ames Res Ctr, MS 269-1 Moffett Field, Moffett Field, CA 94035 USA. RP Morris, R (reprint author), NASA, Ames Res Ctr, MS 269-1 Moffett Field, Moffett Field, CA 94035 USA. EM morris@email.arc.nasa.gov; Jennifer.L.Dungan@nasa.gov NR 19 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 2300 EP + PG 3 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235302022 ER PT S AU Kizhner, S Patel, UD Vootukuru, M AF Kizhner, Semion Patel, Umeshkurnar D. Vootukuru, Meg GP IEEE TI On representative spaceflight instrument and associated instrument Sensor Web framework SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB Sensor Web-based adaptation and sharing of space flight mission resources, including those of the Space-Ground and Control-User communication segments, could greatly benefit from utilization of heritage Internet Protocols and devices applied for Spaceflight (SpaceIP). This had been successfully demonstrated by a few recent spaceflight experiments. However, while terrestrial applications of Internet protocols are well developed and understood (mostly due to billions of dollars in investments by the military and industry), the spaceflight application of Internet protocols is still in its infancy. Progress in the developments of SpaceIP-enabled instrument components will largely determine the SpaceIP utilization of those investments and acceptance in years to come. Likewise SpaceIP, the development of commercial real-time and instrument co-located computational resources, data compression and storage, can be enabled on-board a spacecraft instrument and, in turn, support a powerful application to Sensor Web-based design of a spaceflight instrument. These are presently only co-located with the spacecraft Command and Data Handling System (C&DH). Sensor Web-enabled re-configuration and adaptation of structures for hardware resources and information systems on instrument level will commence application of Field Programmable Gate Arrays (FPGA) and other aerospace programmable logic devices for what this technology was intended. These are a few obvious potential benefits of Sensor Web technologies for spaceflight applications on instrument level. However, they are still waiting to be explored. This is because there is a need for a new approach to spaceflight instrumentation in order to make these mature sensor web technologies applicable for spaceflight. In this paper we present an approach in developing related and enabling spaceflight instrument-level technologies based on the new concept of a representative Instrument Sensor Web (ISW). This concept widens the scope of heritage sensor webs and facilitates the application of sensor web technologies to complex representative instruments on-board future spacecrafts. C1 [Kizhner, Semion; Patel, Umeshkurnar D.] NASA, Goddard Space Flight Ctr, Greenbelt Rd, Greenbelt, MD 20771 USA. [Vootukuru, Meg] Syneren Technolo Corp, Arlington, VA 22201 USA. RP Kizhner, S (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt Rd, Greenbelt, MD 20771 USA. EM Semion.Kizhner-1@nasa.gov NR 8 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 2308 EP + PG 3 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235302023 ER PT S AU Ivancic, WD AF Ivancic, William D. GP IEEE TI Secure, Autonomous, Intelligent Controller for integrating distributed sensor webs SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB This paper describes the infrastructure and protocols necessary to enable near-real-time commanding, access to space-based assets, and the secure interoperation between sensor webs owned and controlled by various entities. Select terrestrial and aeronautics-base sensor webs will be used to demonstrate time-critical interoperability between integrated, intelligent sensor webs both terrestrial and between terrestrial and space-based assets. For this work, a Secure, Autonomous, Intelligent Controller and knowledge generation unit is implemented using Virtual Mission Operation Center technology. C1 [Ivancic, William D.] NASA, Glenn Res Ctr, Cleveland, OH 44145 USA. RP Ivancic, WD (reprint author), NASA, Glenn Res Ctr, Cleveland, OH 44145 USA. NR 3 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 2318 EP 2323 PG 6 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235302024 ER PT S AU Donnellan, A Parker, J Norton, C Lyzenga, G Glasscoe, M Fox, G Pierce, M Rundle, J McLeod, D Grant, L Brooks, W Tullis, T AF Donnellan, Andrea Parker, Jay Norton, Charles Lyzenga, Gregory Glasscoe, Margaret Fox, Geoffrey Pierce, Marlon Rundle, John McLeod, Dennis Grant, Lisa Brooks, Walter Tullis, Terry GP IEEE TI QuakeSim: Enabling model interactions in solid earth science sensor webs SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB QuakeSim is problem-solving environment for understanding earthquake processes through the integration of multiscale models and data. The goal of QuakeSim is to substantially improve earthquake forecasts, which will ultimately lead to mitigation of damage from this natural hazard. Irnproved earthquake forecasting is dependent on measurement of surface deformation as well as analysis of geological and seismological data. Space-borne technologies, in the form of continuous GPS networks and InSAR satellites, are the key contributors to measuring surface deformation. We are expanding our QuakeSim Web Services environment to integrate, via Ontolody-based Federation, both real-time and archival sensor data with high-performance computing applications for data mining and assimilation. We are federating sensor data sources, with a focus on InSAR and GPS data, for an improved modeling environment for forecasting earthquakes. These disparate measurements form a complex sensor web in which data must be integrated into comprehensive multiscale models. In order to account for the complexity of modeled fault systems, investigations must be carried out on high-performance computers. We are building upon our "Grid of Grids" approach, which included the development of extensive Geographical Information System-based "Data Grid" services. We are extending our earlier approach to integrate the Data Grid components with improved "Execution Grid" services that are suitable for interacting with high-end computing resources. These services are being deployed on the Columbia computer at NASA Ames and the Cosmos computer cluster at JPL.(1 2). C1 [Donnellan, Andrea; Parker, Jay; Norton, Charles; Lyzenga, Gregory; Glasscoe, Margaret] CALTECH, Jet Prop Lab, INSAR, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Fox, Geoffrey; Pierce, Marlon] Indiana Univ, Commun Grids Lab, Bloomington, IN 47404 USA. [Rundle, John] Univ Calif Davis, Dept Phys, Davis, CA 95616 USA. [McLeod, Dennis] Univ Southern Calif, Los Angeles, CA 90089 USA. [Grant, Lisa] Univ Calif Irvine, Irvine, CA 92697 USA. [Brooks, Walter] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Tullis, Terry] Brown Univ, Dept Geol Sci, Providence, RI 02912 USA. RP Donnellan, A (reprint author), CALTECH, Jet Prop Lab, INSAR, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Andrea.Donnellan@jpl.nasa.gov NR 19 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 2330 EP + PG 3 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235302026 ER PT S AU Pingree, PJ Blavier, JFL Toon, GC Bekker, DL AF Pingree, Paula J. Blavier, Jean-Francois L. Toon, Geoffrey C. Bekker, Dmitriy L. GP IEEE TI An FPGA/SoC approach to on-board data processing enabling new mars science with smart payloads SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES ID SPECTROSCOPY; DESIGN AB A proposed Mars Scout Mission known as MARVEL is vying for the 2011 launch opportunity. One of its primary instruments, MATMOS, will produce large volumes of data in short, 3-minute bursts during its on-orbit observation of sunrise and sunset. The remaining orbit time of 112 minutes is available for on-board data processing to reduce data volume prior to downlink. This data processing relies heavily on floating-point FFTs. The Xilinx Virtex-II Pro FPGA was evaluated in a previous research task, but could not meet the performance requirements, even with an integrated soft-core floating-point unit (FPU). The next-generation Virtex-4 FPGA contains an auxiliary processor unit (APU) that provides a flexible high bandwidth interface for fabric co-processor modules (FCM) to the PowerPC405 core. In this paper we show that coupling the FPU FCM with the APU provides sufficient computation power to meet MATMOS's data processing requirements when implemented in a multi-processor, dual-FPGA system.(1,2). C1 [Pingree, Paula J.; Blavier, Jean-Francois L.; Toon, Geoffrey C.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Bekker, Dmitriy L.] Rochester Inst Technol, Dept Comp Engn, Rochester, NY 14623 USA. RP Pingree, PJ (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Paula.J.Pingree@jpl.nasa.gov; Jeanfrancois.L.Blavier@jpl.nasa.gov; Geoffrey.C.Toon@jpl.nasa.gov; Dmitriy.Bekker@gmail.com NR 18 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 2357 EP + PG 3 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235302030 ER PT S AU Jacobson, CA AF Jacobson, Craig A. GP IEEE TI International Space Station remote sensing pointing analysis SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB This paper(1 2) analyzes the geometric and disturbance aspects of utilizing the International Space Station for remote sensing of earth targets. The proposed instrument (in prototype development) is SHORE (Station High-Performance Ocean Research Experiment), a multi-band optical spectrometer with 15 in pixel resolution. The analysis investigates the contribution of the error effects to the quality of data collected by the instrument. This analysis supported the preliminary studies to determine feasibility of utilizing the International Space Station as an observing platform for a SHORE type of instrument. Rigorous analyses will be performed if a SHORE flight program is initiated. The analysis begins with the discussion of the coordinate systems involved and then conversion from the target coordinate system to the instrument coordinate system. Next the geometry of remote observations from the Space Station is investigated including the effects of the instrument location in Space Station and the effects of the line of sight to the target. The disturbance and error environment on Space Station is discussed covering factors contributing to drift and jitter, accuracy of pointing data and target and instrument accuracies. C1 [Jacobson, Craig A.] NASA, UB E, Kennedy Space Ctr, FL 32899 USA. NR 6 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 2369 EP 2381 PG 13 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235302031 ER PT S AU Rakow, G McGuirk, P Kimmery, C Jaffe, P AF Rakow, Glenn McGuirk, Patrick Kimmery, Clifford Jaffe, Paul GP IEEE TI SpaceWire Plug 'n' Play SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB The ability to rapidly deploy inexpensive satellites to meet tactical goals has become an important goal for military space systems. In fact, Operationally Responsive Space (ORS) has been in the spotlight at the highest levels. The Office of the Secretary of Defense (OSD) has identified that the critical next step is developing the bus standards and modular interfaces. Historically, satellite components have been constructed based on bus standards and standardized interfaces. However, this has not been done to a degree, which would allow the rapid deployment of a satellite [3]. Advancements in plug-and-play (PnP) technologies for terrestrial applications can serve as a baseline model for a PnP approach for satellite applications. Since SpaceWire (SpW) has become a de facto standard for satellite high-speed (>200Mbp) on-board communications, it has become important for SpW to adapt to this Plug and Play (PnP) environment. Because SpW is simply a bulk transport protocol and lacks built-in PnP features, several changes are required to facilitate PnP with SpW. The first is for Host(s) to figure out what the network looks like, i.e., how pieces of the network, routers and nodes, are connected together; network mapping, and to receive notice of changes to the network. The second is for the components connected to the network to be understood so that they can communicate. The first element, network topology mapping & change of status indication, is being defined (topic of this paper). The second element describing how components are to communicate has been defined by ARFL with the electronic data sheets known as XTEDS. The first element, network mapping, is recent activities performed by Air Force Research Lab (ARFL), Naval Research Lab (NRL), NASA and US industry (Honeywell, Clearwater, FL, and others). This work has resulted in the development of a protocol that will perform the lower level functions of network mapping and Change Of Status (COS) indication required by Plug 'n' Play over SpaceWire. This work will be presented to the SpaceWire working group for standardization under European Cooperation for Space Standardization (ECSS) and to obtain a permanent Protocol ID [2]. The portion of the Plug 'n' Play protocol that will be described in this paper is how the Host(s) of a SpaceWire network map the network and detect additions and deletions of devices on a SpaceWire network.(1 2). C1 [Rakow, Glenn] NASA, GSFC, Code 561, Greenbelt, MD USA. [McGuirk, Patrick] Micro RDC, Albuquerque, NM USA. [Kimmery, Clifford] Honeywell Inc, Cleawater, FL USA. [Jaffe, Paul] NRL, Washington, DC USA. RP Rakow, G (reprint author), NASA, GSFC, Code 561, Greenbelt, MD USA. EM Glenn.P.Rakow@nasa.gov; Patrick.McGuirk@micro-rdc.com; clifford.kimmery@honeywell.com; paul.jaffe@nrl.navy.mil NR 3 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 2415 EP + PG 2 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235302036 ER PT S AU Alena, RL Ossenfort, JP Laws, KI Goforth, A Figueroa, F AF Alena, Richard L. Ossenfort, John P. Laws, Kenneth I. Goforth, Andre Figueroa, Fernando GP IEEE TI Communications for Integrated Modular Avionics SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB The aerospace industry has been adopting avionics architectures to take advantage of advances in computer engineering. Integrated Modular Avionics (IMA), as described in ARINC 653, distributes functional modules into a robust configuration interconnected with a "virtual backplane" data communications network. Each avionics module's function is defined in software compliant with the APEX Application Program Interface. The Avionics Full-Duplex Ethernet (AFDX) network replaces the point-to-point connections used in previous distributed systems with "virtual links". This network creates a command and data path between avionics modules with the software and network defining the active virtual links over an integrated physical network. In the event of failures, the software and network can perform complex reconfigurations very quickly, resulting in a very robust system. In this paper, suitable architectures, standards and conceptual designs for IMA computational modules and the virtual backplane are defined and analyzed for applicability to spacecraft. The AFDX network standard is examined in detail and compared with IEEE 802.3 Ethernet. A reference design for the "Ancillary Sensor Network" (ASN) is outlined based on the IEEE 1451 "Standard for a Smart Transducer Interface for Sensors and Actuators" using real-time operating systems, time deterministic AFDX and wireless LAN technology. Strategies for flight test and operational data collection related to Systems Health Management are developed, facilitating vehicle ground processing. Finally, a laboratory evaluation defines performance metrics and test protocols and summarizes the results of AFDX network tests, allowing identification of design issues and determination of ASN subsystem scalability, from a few to potentially thousands of smart and legacy sensors.(12). C1 [Alena, Richard L.; Ossenfort, John P.; Laws, Kenneth I.; Goforth, Andre; Figueroa, Fernando] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Alena, RL (reprint author), NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. NR 13 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 2498 EP 2515 PG 18 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235302046 ER PT S AU Schatzel, DV AF Schatzel, Donald V. GP IEEE TI Multi-functional spacecraft structures integrating electrical and mechanical functions SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB Future earth orbiting, solar system and celestial body autonomous missions can benefit from spacecraft systems and instruments that have significantly lower weight and volume over current state of the art designs. Incorporating electronic traces or signal paths directly into the spacecraft or instrument structure can provide a significant savings in weight and volume. In addition, local computer processing power, increased operational speed and larger memory storage are achievable by using embedded or direct chip attach design methods.(12) The objective of this technology development is to demonstrate the feasibility of electronic circuit boards that function as structural members within a subsystem. This dual functionality will be achieved by utilizing printed circuit board materials that demonstrate structural properties of strength and stiffness that can compete with current spacecraft structural applications that require the use of aluminum and titanium. Recent developments in printed circuit board fabrication processes has given printed circuit boards increased strength and stiffness by incorporating single or multiple graphite weave layers within the printed circuit board structure during the lamination fabrication process. In addition to potential reductions in mass through the elimination of metal spars, circuit card chassis', panels, backplanes and cabling this technology development will provide the ability to implement high density local data processing capability directly at or near instruments such as cameras or sensors. This technology development will test the strength, stiffness and reliability of custom sample multi-functional structural box beams utilizing layers of graphite weave within the printed circuit board. The mechanical strength test results of the carbon graphite weave constructed box beams will be compared to the strength test results of similar geometry mechanical members constructed of extruded aluminum. This research may lead to planar geometry configurations that are applicable to building more complex spacecraft elements using a multi-functional structure approach. Connecting these different planar geometries requires innovative methods that can use structural adhesive and fasteners to achieve effective structural members that can compete with metallic structures. C1 [Schatzel, Donald V.] Jet Propuls Lab, Pasadena, CA 91109 USA. RP Schatzel, DV (reprint author), Jet Propuls Lab, 4800 Oak Groove Dr, Pasadena, CA 91109 USA. NR 3 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 2549 EP 2554 PG 6 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235302051 ER PT S AU Sacco, GF Ferraro, RD von Allmen, P Rennels, DA AF Sacco, Gian Franco Ferraro, Robert D. von Allmen, Paul Rennels, Dave A. GP IEEE TI Fault injection campaign for a fault tolerant duplex framework SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB Software based Fault Tolerance may allow the use of COTS digital electronics in building a highly reliable computing system for spacecraft. In this work we present the results of a fault injection campaign we conducted on the Duplex Framework(DF). The DF is a software developed by the UCLA group [1], [2] that allows to run two copies (or replicas) of the same program on two different nodes of a commercial off-the-shelf (COTS) computer cluster. By the means of a third process (comparator) running on a different node that constantly monitors the results computed by the two replicas, the DF is able to restart the two replica processes if an inconsistency in their computation is detected. In order to test the reliability of the DF we wrote a simple fault injector that injects faults in the virtual memory of one of the replica process to simulate the effects of radiation in space. These faults occasionally cause the process to crash or produce erroneous outputs. For this study we used two different applications, one that computes an encryption of a input file using the RSA algorithm, and another that optimizes the trade-off between time spent and the fuel consumption for a low-thrust orbit transfer. But the DF is generic enough that any application written in C or Fortran could be used with little or no modification of the original source code. Our results show the potential of such approach in detecting and recovering from radiation induced random errors. This approach is very cost efficient compared to hardware implemented duplex operations and can be adopted to control processes on spacecrafts where the fault rate produced by cosmic rays is not very high. C1 [Sacco, Gian Franco; Ferraro, Robert D.; von Allmen, Paul; Rennels, Dave A.] Jet Propuls Lab, 4800 Oak Grove Dr, Pasadena, CA 91125 USA. [Rennels, Dave A.] Univ Calif Los Angeles, Los Angeles, CA 90095 USA. RP Sacco, GF (reprint author), Jet Propuls Lab, 4800 Oak Grove Dr, Pasadena, CA 91125 USA. NR 5 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 2582 EP + PG 3 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235302055 ER PT S AU Patrick, MC Thaler, SL Stevenson-Chavis, K AF Patrick, M. Clinton Thaler, Stephen L. Stevenson-Chavis, Katherine GP IEEE TI Demonstration of self-training autonomous neural networks in space vehicle docking simulations SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB Neural Networks have been under examination for decades in many areas of research, with varying degrees of success and acceptance. Key goals of computer learning, rapid problem solution, and automatic adaptation have been elusive at best. This paper(1,2) summarizes efforts at NASA's Marshall Space Flight Center harnessing such technology to autonomous space vehicle docking for the purpose of evaluating applicability to future missions. C1 [Patrick, M. Clinton] NASA, George C Marshall Space Flight Ctr, MSFC EV43, Huntsville, AL 35812 USA. [Thaler, Stephen L.] Imaginat Engn Inc, St Louis, MO 63146 USA. [Stevenson-Chavis, Katherine] NASA, George C Marshall Space Flight Ctr, MSFC EV21, Huntsville, AL 35812 USA. RP Patrick, MC (reprint author), NASA, George C Marshall Space Flight Ctr, MSFC EV43, Huntsville, AL 35812 USA. EM clint.patrick@nasa.gov; sthaler@imagination-engines.com; katherine.m.chavis@nasa.gov NR 14 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 2591 EP + PG 2 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235302056 ER PT S AU Stoica, A Zebulum, R Keymeulen, D Ramesham, R Neff, J Katkoori, S AF Stoica, Adrian Zebulum, Ricardo Keymeulen, Didier Ramesham, Rajeshuni Neff, Joseph Katkoori, Srinivas GP IEEE TI Temperature-adaptive circuits on reconfigurable analog arrays SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB This paper describes a new reconfigurable analog array (RAA) architecture and an integrated circuit (IC), and its use to map analog circuits that adapt to extreme temperatures. Evolution-driven adaptation takes place on the RAA IC, guided by algorithms implemented in a Field Programmable Gate Array (FPGA) collocated with the RAA in the extreme temperature environment. The experiments demonstrate circuit adaptation over a wide temperature range, from extremely low of -180 degrees C to high of 120 degrees C.(12). C1 [Stoica, Adrian; Zebulum, Ricardo; Keymeulen, Didier; Ramesham, Rajeshuni] CALTECH, Jet Propuls Lab, Pasadena, CA 91109 USA. [Neff, Joseph] SPAWAR, San Diego, CA USA. [Katkoori, Srinivas] Univ S Florida, Tampa, FL 33620 USA. RP Stoica, A (reprint author), CALTECH, Jet Propuls Lab, Pasadena, CA 91109 USA. EM adrian.stoica@jpl.nasa.gov FU National Aeronautics and Space Administration (NASA) FX The work described in this paper was performed at the Jet Propulsion Laboratory, California Institute of Technology and was sponsored by the National Aeronautics and Space Administration (NASA). We are grateful for encouragement and support from Project Manager Dr Michael Watson from NASA Marshall Space Flight Center, and NASA Program Managers Dr Mita Desai and Dr. Chris Moore. NR 9 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 2608 EP + PG 4 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235302058 ER PT S AU Keymeulen, D Zebulum, R Rajeshuni, R Stoica, A Katkoori, S Graves, S Novak, F Antill, C AF Keymeulen, Didier Zebulum, Ricardo Rajeshuni, Ramesham Stoica, Adrian Katkoori, Srinivas Graves, Sharon Novak, Frank Antill, Charles GP IEEE TI Extreme temperature electronics based on self-adaptive system using field programmable gate array SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB (12) Space missions often require radiation and extreme-temperature hardened electronics to survive the harsh environments beyond earth's atmosphere. Traditional approaches to preserve electronics incorporate radiation shielding, insulation and redundancy at the expense. of power and weight. In this work, we report the implementation of a self-adaptive system using a field programmable gate array (FPGA) and data converters. The self-adaptive system can autonomously recover the lost functionality of a reconfigurable analog array (RAA) integrated circuit (IC) [3]. Both the RAA IC and the self-adaptive system are operating in extreme temperatures (from 120 degrees C down to -180 degrees C). The RAA IC consists of reconfigurable analog blocks interconnected by several switches and programmable by bias voltages. It implements filters/amplifiers with bandwidth up to 20 MHz. The self-adaptive system controls the RAA IC and is realized on Commercial-Off-The-Shelf (COTS) parts. It implements a basic compensation algorithm that corrects a RAA IC in less than a few milliseconds. Experimental results for the cold temperature environment (down to -180 degrees C) show the change over temperature of the response of the RAA for all possible bias voltage and demonstrate the feasibility of this approach. C1 [Keymeulen, Didier; Zebulum, Ricardo; Rajeshuni, Ramesham; Stoica, Adrian] CALTECH, Jet Prop Lab, MS 303-300,4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Katkoori, Srinivas] Univ S Florida, CSE Dept, Tampa, FL 33620 USA. [Graves, Sharon; Novak, Frank; Antill, Charles] NASA LaRC, Hampton, VA 23681 USA. RP Keymeulen, D (reprint author), CALTECH, Jet Prop Lab, MS 303-300,4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM didier.keymeulen@jpl.nasa.gov FU National Aeronautics and Space Administration (NASA) FX The work described in this paper was performed at the Jet Propulsion Laboratory, California Institute of Technology, and NASA Langley Research Center and was sponsored by the National Aeronautics and Space Administration (NASA). We are grateful for encouragement and support from Project Manager Dr. Michael Watson from NASA Marshall Space Flight Center, and NASA Program Managers Dr. Mita Desai and Dr. Chris Moore. NR 7 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 2614 EP + PG 3 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235302059 ER PT S AU Shield, J Goldberg, H Kiem, J Morales, M Scharf, D AF Shield, Joel Goldberg, Hannah Kiem, Jason Morales, Mauricio Scharf, Dan GP IEEE TI Terrestrial attitude estimation for the Formation Control Testbed (FCT) SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB In this paper we look at the problem of terrestrial (earth based) attitude estimation of a unique robotic vehicle using full three axis attitude measurements and three axis inertial rate sensors (gyros). The vehicle is completely autonomous and uses air bearings to simulate the drag free dynamic environment of space. An onboard infrared camera system is used to provide quaternion measurements representing the attitude of the robot relative to the room frame of the test facility. Fiber optic gyros are used to sense the inertial angular rates. To simulate the performance of the system, a stochastic model of the gyros was developed based on long term rate table data. The angle random walk, bias, and bias stability were determined to agree with the data provided in the manufactures specification sheet. We show that a 3X reduction in the standard deviation of the attitude estimates can be achieved by proper mixing of the two sensor measurements. The attitude estimation algorithm used in this paper also provides bias free estimates of the angular rate which can be used for control or other purposes. These results are established in both high fidelity simulations and experimentally using data taken during real time operation of the robot. C1 [Shield, Joel; Goldberg, Hannah; Kiem, Jason; Morales, Mauricio; Scharf, Dan] CALTECH, Jet Prop Lab, Guuidance & Control Anal Grp, Pasadena, CA 91109 USA. RP Shield, J (reprint author), CALTECH, Jet Prop Lab, Guuidance & Control Anal Grp, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 8 TC 0 Z9 0 U1 1 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 2686 EP 2695 PG 10 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235302065 ER PT S AU Jerebets, SA AF Jerebets, Sergei A. GP IEEE TI Gyro evaluation for the mission to Jupiter SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES ID HEMISPHERICAL-RESONATOR GYRO AB As an important component in NASA's New Frontiers Program, the Jupiter Polar Orbiter (Juno) mission is designed to investigate in-depth physical properties of Jupiter. It will include the giant planet's ice-rock core and atmospheric studies as well as exploration of its polar magnetosphere. It will also provide the opportunity to understand the origin of the Jovian magnetic field. Due to severe radiation environment of the Jovian system, this mission inherently presents a significant technical challenge to Attitude Control System (ACS) design since the ACS sensors must survive and function properly to reliably maneuver the spacecraft throughout the mission. Different gyro technologies and their critical performance characteristics are discussed, compared and evaluated to facilitate a choice of appropriate gyro-based inertial measurement unit to operate in a harsh Jovian environment to assure mission success.(12). C1 [Jerebets, Sergei A.] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Jerebets, SA (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 18 TC 0 Z9 0 U1 1 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 2702 EP 2710 PG 9 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235302067 ER PT S AU Carrington, C Howell, J AF Carrington, Connie Howell, Joe GP IEEE TI Modular, reconfigurable, high-energy technology development SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB The Modular, Reconfigurable High-Energy (MRHE) Technology Demonstrator project was to have been a series of ground-based demonstrations to mature critical technologies needed for in-space assembly of a high-power high-voltage modular spacecraft in low Earth orbit, enabling the development of future modular solar-powered exploration cargo-transport vehicles and infrastructure. 1 2 MRHE was a project in the High Energy Space Systems (HESS) Program, within NASA's Exploration Systems Research and Technology (ESR&T) Program. NASA participants included Marshall Space Flight Center (MSFC), the Jet Propulsion Laboratory (JPL), and Glenn Research Center (GRC). Contractor participants were the Boeing Phantom Works in Huntsville, AL, Lockheed Martin Advanced Technology Center in Palo Alto, CA, ENTECH, Inc. in Keller, TX, and the University of AL Huntsville (UAH). MRHE's technical objectives were to mature: (a) lightweight, efficient, high-voltage, radiation-resistant solar power generation (SPG) technologies; (b) innovative, lightweight, efficient thermal management systems; (c) efficient, 100kW-class, high-voltage power delivery systems from an SPG to an electric thruster system; (d) autonomous rendezvous and docking technology for in-space assembly of modular, reconfigurable spacecraft; (e) robotic assembly of modular space systems; and (f) modular, reconfigurable distributed avionics technologies. Maturation of these technologies was to be implemented through a series of increasingly-inclusive laboratory demonstrations that would have integrated and demonstrated two systems-of-systems: (a) the autonomous rendezvous and docking of modular spacecraft with deployable structures, robotic assembly, reconfiguration both during assembly and in the event of module failure, and the use of reconfigurable distributed avionics systems to perform these functions; and (b) the development and integration of an advanced thermal heat pipe and a high-voltage power delivery system with a representative lightweight high-voltage SPG array. In addition, an integrated simulation testbed would have been developed containing software models representing the technologies being matured in the laboratory demos. The testbed would have also included models for non-MRHE-developed subsystems such as electric propulsion, so that end-to-end performance could have been assessed. This paper presents an overview of the MRHE Phase I activities at MSFC and its contractor partners. The assembly demonstration in the Lockheed Martin Advanced Technology Center (LMATC) Robot-Satellite facility was a major Phase I accomplishment. Three robot-satellites successfully demonstrated rendezvous & docking, self-assembly, reconfiguration, adaptable GN&C, deployment, and interfaces between modules. ENTECH's Phase I technology maturation accomplishments include material recommendations for radiation-hardened Stretched Lens Array (SLA) concentrator lenses, and a design concept and test results for a hi-voltage PV receiver. UAH's accomplishments include Supertube heat-pipe test results, which support estimates of thermal conductivities at 30,000 times that of an equivalent silver rod. MSFC performed systems trades and developed a preliminary concept design for a 100kW-class modular reconfigurable solar electric propulsion transport vehicle. Boeing Phantom Works in Huntsville performed assembly and rendezvous and docking trades and launch vehicles and orbit analysis. A concept animation video was produced by SAIC, which showed rendezvous and docking and SLA-square-rigger (SLASR) deployment in LEO. C1 [Carrington, Connie; Howell, Joe] NASA, George C Marshall Space Flight Ctr, Autonomous Rendezvous & Docking Grp, EV21, Huntsville, AL 35812 USA. RP Carrington, C (reprint author), NASA, George C Marshall Space Flight Ctr, Autonomous Rendezvous & Docking Grp, EV21, Huntsville, AL 35812 USA. EM connie.carrington@nasa.gov; joe.howell@nasa.gov NR 13 TC 0 Z9 0 U1 0 U2 3 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 2731 EP + PG 2 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235302070 ER PT S AU Roe, F Betts, K Carrington, C AF Roe, Fred Betts, Kevin Carrington, Connie GP IEEE TI Hydra rendezvous and docking sensor system SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB U.S. technology to support the Crew Exploration Vehicle (CEV) rendezvous and docking operations was developed by NASA and supporting industry during an extensive research and development program conducted during the 1990's and early 2000 time frame at the Marshall Space Flight Center. Development and demonstration of a rendezvous/docking sensor was identified early in NASA's AR&D Program as the critical enabling technology that allows automated proximity operations and docking. A first generation rendezvous/docking sensor, the Video Guidance Sensor (VGS), was developed and successfully flown on STS 87 and again on STS 95, proving the concept of a video-based sensor. Advances in both video and signal processing technologies and the lessons learned from the two successful flight experiments provided a baseline for the development of a new generation of video based rendezvous/docking sensors. The Advanced Video Guidance Sensor (AVGS) has greatly increased performance and additional capability for longer-range operation. A Demonstration Automatic Rendezvous Technology (DART) flight experiment was flown in April 2005 using AVGS as the primary proximity operations sensor. Because of the,absence of a docking mechanism on the target satellite, this mission did not demonstrate the ability of the sensor to control docking. Mission results indicate that the rendezvous sensor operated successfully in "spot mode" (2 km acquisition of the target, bearing data only) but was never commanded to "acquire and track" the docking target.(12). Parts obsolescence issues prevent the construction of current AVGS designs to support the NASA Exploration initiative. This flight-proven AR&D technology is being modularized and upgraded with additional capabilities through the Hydra project at the Marshall Space Flight Center. Hydra brings a unique engineering approach and sensor architecture to the table, to address the continuing issues of parts obsolescence and multiple sensor integration. This paper presents an approach to sensor hardware trades, to address the needs of future vehicles that may rendezvous and dock with the International Space Station (ISS). It will also discuss approaches for upgrading AVGS to address parts obsolescence, and concepts for modularizing the sensor to provide configuration flexibility for multiple vehicle applications. Options for complementary sensors to be integrated into the multi-head Hydra system will also be presented. Complementary sensor options include ULTO (R), a digital image correlator system that could provide relative six-degree-of-freedom information independently from AVGS, and range-finding sensors. System trades for common targets, integrated targets, and independent targets, suitable for use with the multi-sensor options in Hydra, will be discussed. C1 [Roe, Fred] Adv Opt Syst Inc, 6767 Old Madison Pike,Suite 410, Huntsville, AL 35806 USA. [Betts, Kevin] Bd Syst Inc, Huntsville, AL 35802 USA. [Carrington, Connie] NASA Marshall Space Flight Ctr, EV21, Huntsville, AL 35812 USA. RP Roe, F (reprint author), Adv Opt Syst Inc, 6767 Old Madison Pike,Suite 410, Huntsville, AL 35806 USA. EM roe@aos-inc.com; kbetts@cdy.bdsys.com; connie.carrington@nasa.gov NR 8 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 2796 EP + PG 3 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235302074 ER PT S AU Smith, RS Subbotin, MV Hadaegh, FY AF Smith, Roy S. Subbotin, Maksim V. Hadaegh, Fred Y. GP IEEE TI Decentralized estimation and control in high precision spacecraft formations: Comparison studies SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES ID MULTIPLE; INTERFEROMETRY; SYSTEMS AB High-precision formation flying missions can implement very large science instruments, but require a very high level of coordination and control. Two coordination and control architectures are described and evaluated on two small prototypical formation flying missions. The first architecture is based on a decentralized, parallel estimation approach with every spacecraft in the formation maintaining an estimate of the entire formation state. Each spacecraft updates its estimator on the basis of local measurements and communicated information from other spacecraft. The second architecture uses a central spacecraft to maintain the formation estimate and calculate the required control actions for all other spacecraft. Communication is required to convey the measurements and actuation commands between the central spacecraft and the rest of the formation. These case studies illustrate that in the presence of small communication delays and communication channel noise, the decentralized architecture outperforms the centralized one, even in the case where it has fewer communication links. C1 [Smith, Roy S.; Subbotin, Maksim V.] Univ Calif Santa Barbara, Dept Elect & Comp Engn, Santa Barbara, CA 93106 USA. [Hadaegh, Fred Y.] CALTECH, Jet Propuls Lab, Pasadena, CA 91109 USA. RP Smith, RS (reprint author), Univ Calif Santa Barbara, Dept Elect & Comp Engn, Santa Barbara, CA 93106 USA. EM roy@ece.ucsb.edu; subbotin@engineering.ucsb.edu; Fred.Y.Hadaegh@jpl.nasa.gov RI Smith, Roy/C-7340-2009 OI Smith, Roy/0000-0002-8139-4683 NR 36 TC 0 Z9 0 U1 1 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 2812 EP + PG 4 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235302076 ER PT S AU Tralli, DM Foxall, W Schultz, C AF Tralli, David M. Foxall, William Schultz, Craig GP IEEE TI Concept for a high MEO InSAR seismic monitoring system SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB Demonstration of a spaceborne system to image seismic surface waves dynamically (i.e. coseismically) would be the early steps of a future operational capability for monitoring earthquakes and discriminating clandestine underground nuclear tests. Complementing the global network of seismic instruments, such system would enable unprecedented global mapping of the velocity structure of the Earth's crust, thereby improving hypocentral. location, understanding of rupture dynamics and wave propagation effects, and source characterization. Seismic wave measurement requirements include lower bounds on delectability of events and wave amplitude accuracy for different levels of analysis, such as source characterization and crustal tomography, with 10-100 mu m wave amplitude resolution for waves nominally traveling 5 km/s, an upper frequency bound based on earthquake surface displacement spectra, and minimum horizontal resolution (1-5 km) and areal coverage. Advanced radar technologies are keys to demonstrating a pre-operational system leading to a high MEO (10,400 km orbit altitude) constellation for continuous surveillance. (123). C1 [Tralli, David M.] NASA, Jet Prop Lab, CALTECH, Natl Space Technol Applicat Off, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Foxall, William; Schultz, Craig] Lawrence Livermore Natl Lab, Livermore, CA 94550 USA. RP Tralli, DM (reprint author), NASA, Jet Prop Lab, CALTECH, Natl Space Technol Applicat Off, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM tralli@jpl.nasa.gov; bfoxall@llnl.gov NR 11 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 2869 EP + PG 2 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235302082 ER PT S AU Lambrigtsen, B Tanner, A Gaier, T Kangaslahti, P Brown, S AF Lambrigtsen, Bjorn Tanner, Alan Gaier, Todd Kangaslahti, Pekka Brown, Shannon GP IEEE TI Prototyping a new Earth observing sensor - GeoSTAR SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB The Geostationary Synthetic Thinned Aperture Radiometer (GeoSTAR) was conceived to fill a gap in our Earth remote sensing capabilities - the lack of a microwave atmospheric sounder in geostationary orbit. This capability is highly desired because of the advantageous observing point GEO offers, with continuous views of the entire visible Earth disc - crucial for observation of hurricanes and other rapidly evolving atmospheric phenomena. The GeoSTAR concept is a radical departure from the conventional way of constructing a microwave sounding radiometer, which typically uses a scanning parabolic reflector that focuses a narrow receiving "beam" into a single receiver. Instead, the STAR approach is to use a 2-D array of a large number of receivers to synthesize a large aperture and operate the system as a spatial interferometer that images the scene in two dimensions without requiring scanning. Such systems have been investigated before, and the European Space Agency is developing a soil moisture satellite mission based on this concept, but none had been adequately demonstrated either on the ground or in space. This is a perfect case for a prototyping effort. An effort has been under way at the Jet Propulsion Laboratory for the last 3-4 years to build a GeoSTAR prototype and demonstrate that the 2-D STAR approach works. The prototype, which is a moderate-aperture implementation of a fully functional temperature sounder, was completed in early 2005 and has since undergone a number of tests. This prototyping effort, which involved both technology and system development as well as development of new testing methodologies, has been very successful. The GeoSTAR concept, even though it has not been tested in a space environment and therefore is not formally at TRL 6 (i.e. per NASA's definition), is now ready to be considered for space mission opportunities. A companion effort to assess the expected impact on weather forecast accuracy through a so-called Observational System Simulation Experiment (OSSE) is also under way. Together, the prototyping and the OSSE constitute crucial steps on the road to a space mission. C1 [Lambrigtsen, Bjorn; Tanner, Alan; Gaier, Todd; Kangaslahti, Pekka; Brown, Shannon] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Lambrigtsen, B (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Bjorn.Lambrigtsen@jpl.nasa.gov NR 8 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 2876 EP 2884 PG 9 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235302083 ER PT S AU Baron, RL Gerber, AJ Tralli, D Pagano, T Aumann, G Rogez, F Sobel, H Sepulveda, C Carnright, R Dittberner, G Bajpai, S AF Baron, Richard L. Gerber, Andrew J. Tralli, Dave Pagano, Tom Aumann, George Rogez, Francois Sobel, Hal Sepulveda, Cesar Carnright, Rob Dittberner, Gerald Bajpai, Shyam GP IEEE TI Broadband Imager-Sounder for Terrestrial Remote Observations (BISTRO) SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB BISTRO a Broadband Imager-Sounder for Terrestrial Remote Observations is designed as an integral instrument for an envisioned future NOAA National Global Operational Environmental Satellite System (NGOESS) architecture. This ultra-spectral imager/sounder provides for greater than 4000 spectral channels covering a band from 0.4 to 16.5 microns. The instantaneous footprint on the ground has 4000 spatial elements ranging from 0.25 to 1 km depending on the channel wavelength. Each S/C in the NGOESS constellation is proposed to carry an identical copy of the instrument supporting complete global coverage. The overall system, using BISTRO as a core observing instrument, is designed to meet or exceed current (e.g. POEs and GOEs) and planned (eg. GOES-R, and NPOESS) EDRs, CDRs, and other anticipated "user" requirements in the optical and infrared areas of the electromagnetic spectrum for sounding and imaging. Anticipated future "science" requirements for short- and or long-term (climate) observations have been explored with the science and operations community and are tentatively provided for in the overall system design. C1 [Baron, Richard L.; Gerber, Andrew J.; Tralli, Dave; Pagano, Tom; Aumann, George; Rogez, Francois; Sobel, Hal; Sepulveda, Cesar; Carnright, Rob] CALTECH, Jet Prop Lab, Natl Space Technol Applicat Off, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Dittberner, Gerald; Bajpai, Shyam] NOAA NESDIS, Annapolis, MD USA. RP Baron, RL (reprint author), CALTECH, Jet Prop Lab, Natl Space Technol Applicat Off, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Richard.L.Baron@jpl.nasa.gov NR 8 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 2885 EP + PG 2 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235302084 ER PT S AU Jaap, J Meyer, P Davis, E Richardson, L AF Jaap, John Meyer, Patrick Davis, Elizabeth Richardson, Lea GP IEEE TI Remote collaboration on task scheduling for humans at Mars SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB As humans venture farther from Earth for longer durations, it will become essential for those on the journey to have significant control over the scheduling of their own activities as well as the activities of their companion systems and robots. However, the crew will not do all the scheduling; timelines will be the result of collaboration with ground personnel. Emerging technologies such as in-space message buses, delay-tolerant networks, and in-space internet will be the carriers on which the collaboration rides. Advances in scheduling technology, in the areas of task modeling, scheduling engines, and user interfaces will allow the crew to become virtual scheduling experts. New concepts of operations for producing the timeline will allow the crew and the ground support to collaborate while providing safeguards to ensure that the mission will be effectively accomplished without endangering the systems or personnel.(12). C1 [Jaap, John; Meyer, Patrick; Davis, Elizabeth; Richardson, Lea] NASA, George C Marshall Space Flight Ctr, Huntsville, AL 35812 USA. RP Jaap, J (reprint author), NASA, George C Marshall Space Flight Ctr, Huntsville, AL 35812 USA. NR 6 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 2911 EP 2920 PG 10 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235302087 ER PT S AU Peterson, C Balint, T Belz, A Cutts, J AF Peterson, Craig Balint, Tibor Belz, Andrea Cutts, James GP IEEE TI Overview of high priority technologies for Solar System exploration SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB During the past two years, a new Solar System Exploration Roadmap has been developed, supplanting the previous 2003 version. This roadmap identifies a number of high priority technology developments that will be essential to the success of several of the roadmap missions. These technologies include advanced Radioisotope Power Systems (RPS), aerocapture systems and advanced propulsion, numerous technologies capable of surviving the extreme environments encountered in many of these missions, and improved capabilities for both forward and back planetary protection. These key technologies and the missions that require them are described, along with the estimated timeline for their development as laid out in the exploration roadmap.(12). C1 [Peterson, Craig; Balint, Tibor; Belz, Andrea; Cutts, James] NASA, Jet Prop Lab, CALTECH, Pasadena, CA 91109 USA. RP Peterson, C (reprint author), NASA, Jet Prop Lab, CALTECH, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 5 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 2921 EP 2933 PG 13 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235302088 ER PT S AU Anderson, DJ Sankovic, J Wilt, D Abelson, RD Fleuria, JP AF Anderson, David J. Sankovic, John Wilt, David Abelson, Robert D. Fleuria, Jean-Pierre GP IEEE TI NASA's advanced Radioisotope Power Conversion Technology development status SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES ID THERMAL-CONDUCTIVITY AB NASA's Advanced Radioisotope Power Systems (ARPS) project is developing the next generation of radioisotope power conversion technologies that will enable future missions that have requirements that cannot be met by either photovoltaic systems or by current radioisotope power systems (RPSs). Requirements of advanced RPSs include high efficiency and high specific power (watts/kilogram) in order to meet future mission requirements with less radioisotope fuel and lower mass so that these systems can meet requirements for a variety of future space applications, including continual operation surface missions, outer-planetary missions, and solar probe. These advances would enable a factor of 2 to 4 decrease in the amount of fuel required to generate electrical power. Advanced RPS development goals also include long-life, reliability, and scalability. This paper provides an update on the contractual efforts under the Radioisotope Power Conversion Technology (RPCT) NASA Research Announcement (NRA) for research and development of Stirling, thermoelectric, and thermophotovoltaic power conversion technologies. The paper summarizes the current RPCT NRA efforts with a brief description of the effort, a status and/or summary of the contractor's key accomplishments, a discussion of upcoming plans, and a discussion of relevant system-level benefits and implications. The paper also provides a general discussion of the benefits from the development of these advanced power conversion technologies and the eventual payoffs to future missions (discussing system benefits due to overall improvements in efficiency, specific power, etc.).(1,2). C1 [Anderson, David J.; Sankovic, John; Wilt, David] NASA, Glenn Res Ctr, Div Sci, Cleveland, OH 44135 USA. [Abelson, Robert D.; Fleuria, Jean-Pierre] CALTECH, NASA, Jet Prop Lab, Power Syst Sect,Photovolta Applicat Grp, Pasadena, CA USA. RP Anderson, DJ (reprint author), MIT, Cambridge, MA 02139 USA. NR 29 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 2934 EP 2953 PG 20 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235302089 ER PT S AU Balint, TS AF Balint, Tibor S. GP IEEE TI Design reference mission set for RPS enabled missions in support of NASA's SSE roadmap SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB NASA's 2006 Solar System Exploration (SSE) Strategic Roadmap identified a set of small, medium and large missions, to address exploration targets, set out by the National Research Council (NRC) in the SSE Decadal Survey. Large size Flagship class missions are proposed to target Europa, Titan / Enceladus, Venus, and the Neptune system. Under the current candidate architectures, all of these Flagship class missions would require Radioisotope Power Systems (RPSs), as enabling technologies. Medium size New Frontiers (NF) class missions could also consider RPSs, although the ones targeting the 3rd NF opportunity would not likely utilize them. To constrain costs, small size Discovery class missions are not allowed to use RPSs. The proposed SSE Roadmap missions represent the highest priority subset of a broader collection of mission concepts, called NASA's SSE Design Reference Mission (DRM) set. In line with the SSE DRM set, the RPS DRM set includes a collection of potential future missions, which could be enabled or enhanced by the use of RPS technologies. Currently, NASA has proposed the development of the Multi-Mission Radioisotope Thermoelectric Generator (MMRTG), with static power conversion; and the Stirling Radioisotope Generator (SRG), with dynamic conversion. Advanced RPSs under consideration for possible development target increased specific power levels, consequently increasing electric power generation for the same amount of fuel, or reducing fuel requirements for the same power output, compared to the proposed MMRTG or SRG. It is expected that the RPSs will need modifications to operate in the extreme environments of Titan or Venus. An RPS on the proposed Titan Explorer would use smaller fins to minimize heat rejection in the extreme cold environment; while the Venus Mobile Explorer long-lived in situ mission would require the development of a new RPS, in order to tolerate the extreme hot environment, and to provide active cooling to the payload and other electric components. This paper discusses NASA's SSE RPS DRM set in line with the SSE DRM set, and gives a qualitative assessment of the impact of various RPS options on the potential mission architectures. The assessment could aid NASA with RPS technology development planning, and with the understanding of fuel needs over the next three decades.(1 2). C1 [Balint, Tibor S.] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Balint, TS (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,M-S 301-170U, Pasadena, CA 91109 USA. NR 12 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 2954 EP 2962 PG 9 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235302090 ER PT S AU Haldemann, AFC McHenry, M Petras, R Bornstein, B Castano, R Cameron, J Estlin, T Farr, TG Gaines, D Jain, A Leff, C Lim, C Nesnas, I Pomerantz, M Powell, M Shu, IH Volpe, R AF Haldemann, Albert F. C. McHenry, Michael Petras, Richard Bornstein, Benjamin Castano, Rebecca Cameron, Johnathan Estlin, Tara Farr, Tom G. Gaines, Daniel Jain, Abhinandan Leff, Craig Lim, Christopher Nesnas, Issa Pomerantz, Mark Powell, Mark Shu, I-Hsiang Volpe, Richard GP IEEE TI Simulation to evaluate autonomous behaviors for mobile planetary surface science missions SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB Ahstract-The Science Operations On Planetary Surfaces (SOOPS) task was created with the goal of evaluating, developing and validating methods for increasing the productivity of science operations on planetary surfaces. The highly integrated spacecraft-instrument payload systems of planetary surface missions create operational constraints (e.g. power, data volume, number of ground control interactions) that can reduce the effective science capabilities. Technological solutions have been proposed to mitigate the impact of those constraints on science return. For example, enhanced mobility autonomy, robotic arm autonomous deployment, and on-board image analysis have been implemented on the Mars Exploration Rovers. Next generation improvements involve on-board science-driven decision-making and data collection. SOOPS takes a systems level approach to science operations and thus to evaluating and demonstrating the potential benefits of technologies that are already in development at the 'component level'. (1 2) A simulation environment- "Field Test in a Box" or SOOPS-FTB-has been developed with realistic terrains and scientifically pertinent information content. The terrain can be explored with a simulated spacecraft and instruments that are operated using an activity planning software interface which closely resembles that used for actual surface spacecraft missions. The simulation environment provides flexibility and control over experiments that help answer "what if" questions about the performance of proposed autonomous technologies. The experiments also help evaluate operator interaction with the autonomous system, and improve the designs of the control tools. We will report the recent results of SOOPS-FTB experiments with an on-board rock feature mapping capability, which is effectively a data compression scheme. This experiment illustrates SOOPS ability to explore the use of a new software componenent within a fixed hardware configuration. It is also conceivable that SOOPS-FTB could be put to use with simulations of new payload elements to test and evaluate more advanced integrated operations. C1 [Haldemann, Albert F. C.; McHenry, Michael; Petras, Richard; Bornstein, Benjamin; Castano, Rebecca; Cameron, Johnathan; Estlin, Tara; Farr, Tom G.; Gaines, Daniel; Jain, Abhinandan; Leff, Craig; Lim, Christopher; Nesnas, Issa; Pomerantz, Mark; Powell, Mark; Shu, I-Hsiang; Volpe, Richard] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Haldemann, AFC (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 14 TC 0 Z9 0 U1 0 U2 3 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 2963 EP 2971 PG 9 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235302091 ER PT S AU Thompson, DR Castano, R AF Thompson, David R. Castano, Rebecca GP IEEE TI Performance comparison of rock detection algorithms for autonomous planetary geology SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB Detecting rocks in images is a valuable capability for autonomous planetary science. Rock detection facilitates selective data collection and return. It also assists with image analysis on Earth. This work reviews seven rock detection algorithms from the autonomous science literature. We evaluate each algorithm with respect to several autonomous geology applications. Tests show the algorithms' performance on Mars Exploration Rover imagery, terrestrial images from analog environments, and synthetic images from a Mars terrain simulator. This provides insight into the detectors' performance under different imaging conditions. C1 [Thompson, David R.] Carnegie Mellon Univ, Inst Robot, Pittsburgh, PA 15206 USA. [Castano, Rebecca] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Thompson, DR (reprint author), Carnegie Mellon Univ, Inst Robot, Pittsburgh, PA 15206 USA. NR 15 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 2972 EP 2980 PG 9 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235302092 ER PT S AU Castano, R Estlin, T Gaines, D Chouinard, C Bornstein, B Anderson, RC Burl, M Thompson, D Castano, A Judd, M AF Castano, Rebecca Estlin, Tara Gaines, Dan Chouinard, Caroline Bornstein, Ben Anderson, Robert C. Burl, Michael Thompson, David Castano, Andres Judd, Michele GP IEEE TI Onboard autonomous rover science SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES ID MARS AB The Onboard Autonomous Science Investigation System (OASIS) was used in the first formal demonstration of closed loop opportunistic detection and reaction during a rover traverse on the FIDO rover at NASA's Jet Propulsion Laboratory. In addition to hardware demonstrations, the system has been demonstrated and exercised in simulation using the Rover Analysis, Modeling, and Simulation (ROAMS) planetary rover simulator [I]. We discuss several system enhancements including new planning and scheduling capabilities and image prioritization. We also describe the new end-of-traverse capability that includes taking a partial panorama of images, assessing these for targets of interest, and collecting narrow angle images of selected targets. Finally, we present several methods for estimating properties of rocks and provide a comparative assessment. Understanding the relationship of these methods is important to correctly interpret autonomous rock analyses performed during a traverse.(1 2). C1 [Castano, Rebecca; Estlin, Tara; Gaines, Dan; Chouinard, Caroline; Bornstein, Ben; Anderson, Robert C.; Burl, Michael; Thompson, David; Castano, Andres; Judd, Michele] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Castano, R (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 30 TC 0 Z9 0 U1 0 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 2981 EP 2993 PG 13 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235302093 ER PT S AU Roush, TL Hogan, R AF Roush, Ted L. Hogan, Robert GP IEEE TI Automated classification of visible and near-infrared spectra using self-organizing maps SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES ID NEURAL-NETWORKS; FEATURES; INDUSTRY; MARS AB Existing and planned space missions to planetary and satellite surfaces produce increasing volumes of spectral data. Understanding the scientific content in this large data volume is a daunting task. Various statistical approaches are available to assess such data sets. We apply an automated classification scheme based on Kohonen Self-Organizing maps (SOM) developed originally for the thermal infrared (TIR) and extended here to the visible and near-infrared (VNIR). Available data from spectral libraries are used to train and test the classification in the VNIR. The library spectra are labeled in a hierarchical scheme with class, sub-class, and mineral group names. After training, the test spectra are presented to the SOM output layer and assigned membership to the appropriate cluster. These assignments are then evaluated to assess the robustness, scientific meaning and accuracy of the derived SOM classes as they relate to the spectral labels. We investigate the influence of particle size on our results by training and classifying three particle size separates. We find the SOM results are robust based upon the number of clusters determined from ten independent training/testing efforts. We find the SOM results are most scientifically meaningful for the grossest differences between materials, although some individual groups retain high accuracy even when the overall accuracy of the SOM is low.(1 2). C1 [Roush, Ted L.] NASA, Ames Res Ctr, MS 245-3, Moffett Field, CA 94035 USA. [Hogan, Robert] Bay Area Environm Res Inst, Moffett Field, CA 94035 USA. RP Roush, TL (reprint author), NASA, Ames Res Ctr, MS 245-3, Moffett Field, CA 94035 USA. EM troush@mail.arc.nasa.gov; hogan@cosmic.arc.nasa.gov NR 23 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 2994 EP + PG 3 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235302094 ER PT S AU Shapiro, AA Schone, H Brinza, DE Garrett, HB Feather, MS AF Shapiro, Andrew A. Schone, Harald Brinza, David E. Garrett, Henry B. Feather, Martin S. GP IEEE TI A fast technology infusion model for aerospace organizations SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB A multi-year, Fast Technology Infusion initiative is presented which seeks to develop a model for aerospace organizations to improve the cost-effectiveness by which they mature new, in-house developed software and hardware technologies for space mission use. The first year task under the umbrella of this initiative will provide the framework to demonstrate and document the fast infusion process. The viability of this approach will be demonstrated on two technologies developed in prior years with internal Jet Propulsion Laboratory (JPL) funding. One hardware technology and one software technology were selected for maturation within one calendar year or less. The overall objective is to achieve cost and time savings in the qualification of technologies for space use. At the end of the recommended three-year effort, we will have demonstrated for six or more in-house developed technologies a clear path to insertion using a documented process that permits adaptation to a broad range of hardware and software projects.(1,2). C1 [Shapiro, Andrew A.; Schone, Harald; Brinza, David E.; Garrett, Henry B.; Feather, Martin S.] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Shapiro, AA (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 9 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 3004 EP 3014 PG 11 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235302095 ER PT S AU Chambliss, J AF Chambliss, Joe GP IEEE TI Exploration life support overview and benefits SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB NASA's Exploration Life Support (ELS) Project is providing technology development to address air, water and waste product handling for future exploration vehicles. Existing life support technology and processes need to improve to enable exploration vehicles to meet mission goals. The weight, volume, power and thermal control required, reliability, crew time and life cycle cost are the primary targets for ELS technology development improvements. An overview of the ELS technologies being developed leads into an evaluation of the benefits the ELS technology developments offer. C1 [Chambliss, Joe] NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. RP Chambliss, J (reprint author), NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. NR 8 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 3032 EP 3042 PG 11 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235302097 ER PT S AU Jan, DL AF Jan, Darrell L. GP IEEE TI Environmental monitoring instruments: Using ISS as a testbed for exploration SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB NASA began the Advanced Environmental Monitoring and Control (AEMC) program in 1996. Its mission is to "provide future spacecraft with advanced, microminiaturized networks of integrated sensors to monitor environmental health and accurately determine and control the physical, chemical and biological environment of the crew living areas and their environmental control systems. In earlier years, AEMC focused on fundamental technology development, frequently performed by academia. Following the Vision for Space Exploration announcement in 2004, AEMC moved its focus to developing technologies for flight. Under a Memorandum of Agreement between the Exploration Systems Mission Directorate and the Space Operations Mission Directorate, AEMC is developing three instruments that will be tested on the International Space Station (ISS). Flight experience gained from utilization of the devices on-board ISS will help validate the technologies for Exploration class missions. These instruments are: a miniature gas chromatograph/mass spectrometer called VCAM (Vehicle Cabin Atmosphere Monitor) for trace contaminant monitoring; an atmospheric event monitor (Electronic Nose or ENose) to detect inadvertent release of specific chemicals; and a Colorimetric Solid Phase Extraction (CSPE) method for determination of biocides and other constituents in water systems. An additional instrument, the Lab-on-a-Chip Portable Test System (LOCAD PTS) has been launched to ISS, and will demonstrate sensitive microbial detection. This paper describes the status of development of each of these instruments.(1). C1 [Jan, Darrell L.] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Jan, DL (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 3 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 3043 EP 3049 PG 7 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235302098 ER PT S AU Mitchell, JD Cryan, SP Strack, D Brewster, LL Williamson, MJ Howard, RT Johnston, AS AF Mitchell, Jennifer D. Cryan, Scott P. Strack, David Brewster, Linda L. Williamson, Marlin J. Howard, Richard T. Johnston, A. S. (Nick) GP IEEE TI Automated Rendezvous and Docking sensor testing at the Flight Robotics Laboratory SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB The Exploration Systems Architecture defines missions that require rendezvous, proximity operations, and docking (RPOD) of two spacecraft both in Low Earth Orbit (LEO) and in Low Lunar Orbit (LLO). Uncrewed spacecraft must perform automated and/or autonomous rendezvous, proximity operations and docking operations (commonly known as Automated Rendezvous and Docking, AR&D). The crewed versions may also perform AR&D, possibly with a different level of automation and/or autonomy, and must also provide the crew with relative navigation information for manual piloting. The capabilities of the RPOD sensors are critical to the success of the Exploration Program. NASA has the responsibility to determine whether the Crew Exploration Vehicle (CEV) contractor-proposed relative navigation sensor suite will meet the CEV requirements. The relatively low technology readiness of relative navigation sensors for AR&D has been carried as one of the CEV Projects top risks. The AR&D Sensor Technology Project seeks to reduce this risk by increasing technology maturation of selected relative navigation sensor technologies through testing and simulation, and to allow the CEV Project to assess the relative navigation sensors.(12). C1 [Mitchell, Jennifer D.; Cryan, Scott P.] NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. RP Mitchell, JD (reprint author), NASA, Lyndon B Johnson Space Ctr, 2101 NASA Parkway,MC EG6, Houston, TX 77058 USA. NR 1 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 3050 EP 3065 PG 16 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235302099 ER PT S AU Epp, CD Smith, TB AF Epp, Chirold D. Smith, Thomas B. GP IEEE TI Autonomous Precision Landing and Hazard Detection and Avoidance Technology (ALHAT) SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB As NASA plans to send humans back to the Moon and develop a lunar outpost, technologies must be developed to place humans and cargo safely, precisely, repeatedly, on the lunar surface with the capability to avoid surface hazards. Exploration Space Architecture Study requirements include the need for global lunar surface access with safe, precise landing without lighting constraints on terrain that may have landing hazards for human scale landing vehicles. Landing accuracies of perhaps 100's of meters for sortie crew missions to 10's of meters for Outpost class missions are required. The Autonomous precision Landing Hazard Avoidance Technology (ALHAT) project will develop the new and unique descent and landing Guidance, Navigation and Control (GNC) hardware and software technologies necessary for these capabilities. The ALHAT project will qualify a lunar descent and landing GNC system to a Technology Readiness Level (TRL) of 6 capable of supporting lunar crewed, cargo, and robotic missions. The (ALHAT) development project was chartered by NASA Headquarters in October 2005. This paper describes the project development, research, analysis and concept evolution that has occurred since the assignment of the project. This includes the areas of systems engineering, GNC, sensors, sensor algorithms, simulations, fielding testing, laboratory testing, Hardware-In-The-Loop testing, system avionics and system certification concepts. This paper provides a high level overview of the background, the program management plan, and the current status of the ALHAT project.(12). C1 [Epp, Chirold D.; Smith, Thomas B.] NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. RP Epp, CD (reprint author), NASA, Lyndon B Johnson Space Ctr, 2101 NASA Parkway, Houston, TX 77058 USA. NR 1 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 3066 EP 3072 PG 7 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235302100 ER PT S AU Wilcox, BH AF Wilcox, Brian H. GP IEEE TI ATHLETE: A mobility and manipulation system for the moon SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB A robotic vehicle called ATHLETE - the All-Terrain, Hex-Limbed, Extra-Terrestrial Explorer is described, along with initial results of field tests of two prototype vehicles. 1 2 This vehicle concept is capable of efficient rolling mobility on moderate terrain and walking mobility on extreme terrain. Each limb has a quick-disconnect tool adapter so that it can perform general-purpose handling, assembly, maintenance, and servicing tasks using any or all of the limbs. C1 [Wilcox, Brian H.] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Wilcox, BH (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM brian.h.wilcox@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 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 3086 EP 3095 PG 10 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235302102 ER PT S AU Pettegrew, R Easton, J Struk, P Anderson, E AF Pettegrew, Richard Easton, John Struk, Peter Anderson, Eric GP IEEE TI In-flight manual electronics repair for deep-space missions SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB Severe limitations on mass and volume available for spares on long-duration spaceflight missions will require electronics repair to be conducted at the component level, rather than at the sub-assembly level (referred to as Orbital Replacement Unit, or 'ORU'), as is currently the case aboard the International Space Station. Performing reliable component-level repairs in a reduced gravity environment by crew members will require careful planning, and some specialty tools and systems. Additionally, spacecraft systems must be designed to enable such repairs. This paper is an overview of a NASA project which examines all of these aspects of component level electronic repair. Results of case studies that detail how NASA, the U.S. Navy, and a commercial company currently approach electronics repair are presented, along with results of a trade study examining commercial technologies and solutions which may be used in future applications. Initial design recommendations resulting from these studies are also presented.(1,2) C1 [Pettegrew, Richard; Easton, John] NASA Glenn Res Ctr, Natl Ctr Space Explorat Res, Cleveland, OH 44135 USA. RP Pettegrew, R (reprint author), NASA Glenn Res Ctr, Natl Ctr Space Explorat Res, 21000 Brookpk Rd,MS 110-3, Cleveland, OH 44135 USA. 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 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 3096 EP 3111 PG 16 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235302103 ER PT S AU Bugga, R Smart, M Whitacre, J West, W AF Bugga, Ratnakumar Smart, Marshall Whitacre, Jay West, William GP IEEE TI Lithium ion batteries for space applications SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB Interplanetary missions require rechargeable batteries with unique performance characteristics: high specific energy, wide operating temperatures, demonstrated reliability, and safety. Li-ion batteries are fast becoming the most common energy storage solution for these missions, as they are able to meet the more demanding technical specifications without being excessively massive. At JPL, we have undertaken materials development studies on both cathodes and electrolytes with the goal of further enhancing battery specific energy, discharge and charge capability, and functional temperature range. Results of these studies are described below. C1 [Bugga, Ratnakumar; Smart, Marshall; Whitacre, Jay; West, William] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Bugga, R (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM ratnakumar.v.bugga@jpl.nasa.gov NR 7 TC 0 Z9 0 U1 0 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 3112 EP + PG 3 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235302104 ER PT S AU Beals, DC AF Beals, David C. GP IEEE TI Technology infusion planning within the exploration technology development program SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES C1 [Beals, David C.] NASA, Langley Res Ctr, Explorat Technol Dev Program, Hampton, VA 23681 USA. RP Beals, DC (reprint author), NASA, Langley Res Ctr, Explorat Technol Dev Program, MS 178, Hampton, VA 23681 USA. NR 0 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 3119 EP 3125 PG 7 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235302105 ER PT S AU Schumann, J Liu, Y AF Schumann, Johann Liu, Yan GP IEEE TI Tools and methods for the verification and validation of adaptive aircraft control systems SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB The appeal of adaptive control to the aerospace domain should be attributed to the neural network models adopted in online adaptive systems for their ability to cope with the demands of a changing environment. However, continual changes induce uncertainty that limits the applicability of conventional validation techniques to assure the reliable performance of such systems. In this paper, we present several advanced methods proposed for verification and validation (V&V) of adaptive control systems, including Lyapunov analysis, statistical inference, and compaxison to the well-known Kalman filters. We also discuss two monitoring tools for two types of neural networks employed in the NASA F-15 flight control system as adaptive learners: the confidence tool for the outputs of a Sigma-Pi network, and the validity index for the output of a Dynamic Cell Structure (DCS) network. C1 [Schumann, Johann] NASA Ames, RIACS, Moffett Field, CA 94035 USA. [Liu, Yan] Motorola Labs, Schaumburg, IL 60193 USA. RP Schumann, J (reprint author), NASA Ames, RIACS, Moffett Field, CA 94035 USA. EM schumann@email.arc.nasa.gov; yanliu@motorola.com NR 26 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 3320 EP + PG 2 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235303018 ER PT S AU Markosian, LZ Mansouri-Samani, M Mehlitz, PC Pressburger, T AF Markosian, Lawrence Z. Mansouri-Samani, Masoud Mehlitz, Peter C. Pressburger, Tom GP IEEE TI Program model checking using Design-for-Verification: NASA flight software case study SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB Model checking is a verification technique developed in the 1980s that has a history of industrial application in hardware verification and verification of communications protocol specifications. Program model checking is a technique for model checking software in which the program itself is the model to be checked. Program model checking has shown potential for detecting software defects that are extremely difficult to detect through traditional testing. The technique has been the subject of research and relatively small-scale applications but faces several barriers to wider deployment. This paper is a report on continuing work applying Java PathFinder (JPF), a program model checker developed at NASA Ames Research Center, to the Shuttle Abort Flight Management system, a situational awareness application originally developed for the Space Shuttle. The paper provides background on the model checking tools that were used and the target application, and then focuses on the application of a "Design for Verification" (D4V) principle and its effect on model checking. The case study helps validate the applicability of program model checking technology to real NASA flight software. A related conclusion is that application of D4V principles can increase the efficiency of model checking in detecting subtle software defects. The paper is oriented toward software engineering technology transfer personnel and software practitioners considering introducing program model checking technology into their organizations. C1 [Markosian, Lawrence Z.; Mansouri-Samani, Masoud; Mehlitz, Peter C.; Pressburger, Tom] NASA, Ames Res Ctr, QSS Grp Inc, Moffett Field, CA 94035 USA. RP Markosian, LZ (reprint author), NASA, Ames Res Ctr, QSS Grp Inc, Moffett Field, CA 94035 USA. EM lzmarkosian@email.arc.nasa.gov; masoud@email.arc.nasa.gov; pcmehlitz@email.arc.nasa.gov; Tom.Pressburger@nasa.gov FU NASA Office of Safety and Mission Assurances Software Assurance Research Program; NASA Engineering for Complex Systems Program FX The research reported in this paper was funded by the NASA Office of Safety and Mission Assurance's Software Assurance Research Program. The development of the Propel toolset, which was used in this research, was funded by the NASA Engineering for Complex Systems Program. NR 2 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 3328 EP + PG 2 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235303019 ER PT S AU Maluf, DA McDermott, WJ Knight, CD Smith, EE Gurram, M AF Maluf, David A. McDermott, William J. Knight, Christopher D. Smith, Ernest E. Gurram, Mohana GP IEEE TI Searching across the international space station databases SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES DE intelligent information systems; netmark; NX-Search; context search; semantic interoperation; heterogeneous systems; integration AB Data access in the enterprise requires us to combine data from different sources and different formats. It is advantageous to focus on the intersection of the knowledge across sources and domains; identifying appropriately related knowledge and ignoring irrelevant knowledge, which distracts and serves to make the integration unwieldy and more complicated than necessary. A contextualized search over multiple domains is proposed in this paper-using context-sensitive queries to support disciplined manipulation of domain knowledge resources. The objective of a context search is to provide the capability to interrogate many largely semantically disjoint domain knowledge resources in an automated and intelligent fashion. The intelligent search system detailed supports formally the tasks of selecting, combining, extending, specializing, and modifying components from a diverse set of domains. This paper demonstrates a new paradigm in composition of information for enterprise applications. In particular, it discusses an approach to achieve data integration across multiple sources in a manner that does not require heavy investment in application, database, and middleware maintenance. This lean approach to integration leads to cost-effective and scalable data integration with an underlying schema-less object-relational database management system. This highly scalable information on demand system framework, called NX-Search, is an implementation of an information system built on NETMARK. NETMARK is a flexible, high-throughput open database integration framework for managing, storing, and searching unstructured or semi-structured arbitrary XML and HTML used widely at the National Aeronautics Space Administration (NASA) and industry. C1 [Maluf, David A.; McDermott, William J.; Knight, Christopher D.] NASA, Code TI,Mail Stop 269-4, Moffett Field, CA 94035 USA. [Smith, Ernest E.] NASA, Houston, TX 77058 USA. [Gurram, Mohana] Adv Comp Sci Res Inst, Moffett Field, CA 94035 USA. RP Maluf, DA (reprint author), NASA, Code TI,Mail Stop 269-4, Moffett Field, CA 94035 USA. EM David.A.Maluf@nasa.gov; William.J.McDermott@nasa.gov; Christopher.D.Knight@nasa.gov; Emest.E.Smith@nasa.gov; mgurram@riacs.edu NR 8 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 3386 EP + PG 3 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235303025 ER PT S AU Pan, L AF Pan, Lei GP IEEE TI NavP: Structured and multithreaded distributed parallel programming SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES ID AUTOMATIC DATA; HARMFUL AB We present Navigational Programming (NavP) - a distributed parallel programming methodology based on the principles of migrating computations and multithreading. The four major steps of NavP are: (1) Distribute the data using the data communication pattern in a given algorithm; (2) Insert navigational commands for the computation to migrate and follow large-sized distributed data; (3) Cut the sequential migrating thread and construct a mobile pipeline; and (4) Loop back for refinement. NavP is significantly different from the current prevailing Message Passing (MP) approach. The advantages of NavP include: (1) NavP is structured distributed programming and it does not change the code structure of an original algorithm. This is in sharp contrast to MP as MP implementations in general do not resemble the original sequential code; (2) NavP implementations are always competitive with the best MPI implementations in terms of performance. Approaches such as DSM or HPF have failed to deliver satisfying performance as of today in contrast, even if they are relatively easy to use compared to MP; (3) NavP provides incremental parallelization, which is beyond the reach of MP; and (4) NavP is a unifying approach that allows us to exploit both fine- (multithreading on shared memory) and coarse- (pipelined tasks on distributed memory) grained parallelism. This is in contrast to the currently popular hybrid use of MP+OpenMP, which is known to be complex to use. We present experimental results that demonstrate the effectiveness of NavP. C1 [Pan, Lei] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Pan, L (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM lei.pan@jpl.nasa.gov NR 41 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 3524 EP 3534 PG 11 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235303038 ER PT S AU Lee, S Hua, H Carnright, R Coggi, J Stodden, D AF Lee, Seungwon Hua, Hook Carnright, Robert Coggi, John Stodden, David GP IEEE TI Lessons learned from adapting aerospace engineering tools to the parallel and grid computing environment SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB Many widely-used aerospace data visualization tools are interactive in nature and are programmed to run on a single processor. While such tools support real-time manipulation of simulation environments, the computations that generate the data are often batch oriented and computation intensive. In many cases, the data generation software is too tuned to a single-processor infrastructure to be readily adapted for emerging parallel and grid computing environments. This paper presents several lessons learned from adapting an aerospace engineering tool to the parallel and grid computing architecture. The architecture provides the ability to perform high-power computing by distributing process execution across many computers connected by a dedicated network or the internet. Some of the challenging tasks involved in the adaptation are (1) to decouple the user interface and display functions from the computational functions, since interaction and graphics are usually unnecessary expenses in parallel and grid computing, (2) to identify and parallelize computationally expensive functions without the drastic modification of the code and data structures, (3) to find a lightweight, yet versatile software solution for a client-server machine interface for remote job execution. The solutions we found for these elaborate tasks are presented and their pros and cons are discussed. (1) (2). C1 [Lee, Seungwon; Hua, Hook; Carnright, Robert] Jet Propuls Lab, 4800 Oak Grove Dr, Pasadena, CA 91202 USA. [Coggi, John; Stodden, David] Aerosp Corp, El Segundo, CA 90245 USA. RP Lee, S (reprint author), Jet Propuls Lab, 4800 Oak Grove Dr, Pasadena, CA 91202 USA. EM Seungwon.Lee@jpl.nasa.gov NR 1 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 3535 EP + PG 3 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235303039 ER PT S AU Gal-Edd, J Detter, R Jones, R Fatig, CC AF Gal-Edd, Jonathan Detter, Ryan Jones, Ron Fatig, Curtis C. GP IEEE TI Standardization of XML database exchanges and the James Webb Space Telescope experience SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB The National Aeronautics and Space Administration (NASA) James Webb Space Telescope (JWST) has been working with various standard communities such the Object Management Group (OMG) and the Consultative Committee for Space Data Systems (CCSDS) to assist in the definition of a common eXtensible Markup Language (XML) for database exchange format. The CCSDS and OMG standards are intended for the exchange of core command and telemetry information, not for all database information needed to exercise a NASA space mission. The mission-specific database, containing all the information needed for a space mission, is translated from/to the standard using a translator. The standard is meant to provide a system that encompasses 90% of the information needed for command and telemetry processing. This paper will discuss standardization of the XML database exchange format, tools used, and the JWST experience, as well as future work with XML standard groups both commercial and government. C1 [Gal-Edd, Jonathan; Detter, Ryan] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Jones, Ron] ARTS Corp, NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Fatig, Curtis C.] SAIC, NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Gal-Edd, J (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. EM Edd@nasa.gov; Ryan.D.Detter@nasa.gov; ronald.jones@asrcrts.com; curtis.fatig@gsfc.nasa.gov NR 2 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 3540 EP + PG 3 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235303040 ER PT S AU Malin, JT Throop, DR AF Malin, Jane T. Throop, David R. GP IEEE TI Basic concepts and distinctions for an aerospace ontology of functions, entities and problems SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB Aerospace problems and corrective actions involve hardware, software, processes, operations, humans and organizations. This paper describes a set of taxonomies for interpreting descriptions of aerospace entities, functions, properties and problems. Each category expresses a class concept. Categories have associated 'mapping' words and phrases (synonyms or names) that express these concepts. The taxonomies and mapping words are designed to support ontology development and aid text analysis. The text analysis has been used to semi-automatically generate system functional models from requirements. Text analysis can also be used to find trends and recurrences in problem reports and change requests. The paper describes an Upper Ontology that provides top-level distinctions for classifying objects, occurrences, properties and mathematical abstractions. Additional taxonomies partition Descriptions, Concepts, Entities, Functions/Actions, Problems, and Refining Properties. The paper describes a use case, semantic extraction and classification of key concepts in free text in the Space Shuttle problem reporting database. (1) (2). C1 [Malin, Jane T.] NASA, Lyndon B Johnson Space Ctr, 2101 NASA Rd 1, Houston, TX 77058 USA. [Throop, David R.] Boeing Co, Houston, TX 77058 USA. RP Malin, JT (reprint author), NASA, Lyndon B Johnson Space Ctr, 2101 NASA Rd 1, Houston, TX 77058 USA. EM jane.t.malin@nasa.gov; david.r.throop@boeing.com NR 35 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 3546 EP + PG 4 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235303041 ER PT S AU Weiss, KA AF Weiss, Kathryn Anne GP IEEE TI Reviewing aerospace proposals with respect to software architecture SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB One of the most difficult aspects of evaluating competing software architectures is the lack of a basis of comparison. More often than not, software architecture document formats, modeling techniques, and descriptions are so different from one supplier to the next that a direct comparison is virtually impossible. Furthermore, these architecture descriptions may have varying degrees of completeness, making it even more difficult to select the best alternative. However, reviewers are given insight into the stage of development and maturity of the software architecture based on the specificity of the documentation as well as the level of abstraction of the design artifacts that comprise each supplier's architecture. By organizing the information contained within the architecture documentation into a standard form, reviewers are enabled to compare seemingly disparate architectures. This paper outlines a method for organizing and then evaluating the information contained within competing software architecture descriptions that helps alleviate some of these difficulties. The information organization technique and subsequent analysis are demonstrated on the 4D/RCS reference architecture for intelligent control systems. C1 [Weiss, Kathryn Anne] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Weiss, KA (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 13 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 3564 EP 3583 PG 20 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235303042 ER PT S AU Goebel, K Qiu, H Eklund, N Yan, WZ AF Goebel, Kai Qiu, Hai Eklund, Neil Yan, Weizhong GP IEEE TI Modeling propagation of gas path damage SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB This paper describes how damage propagation can be tracked and modeled for a range of fault modes in some modules of commercial high bypass aircraft engines. To that end, response surfaces of all sensors are generated via a thermo-dynamical simulation model for the engine (cycle deck) as a function of variations of flow and efficiency of the modules of interest. These surfaces are normalized and superimposed. Next, sensor readings are matched to those surfaces and - using an optimization approach - the corresponding flow and efficiency pair is found that best explains the sensor data. This flow and efficiency pair is then compared to previous pairs and the direction of the change as well as the rate of change is determined. The whole trajectory is then projected into the time domain. An extrapolation of the curve to the limit (which is established via operational margins) yields the remaining life. In a backward mode, the extrapolated curve is discretized and estimated future flow and efficiency pairs are retrieved. These pairs are then input to the cycle deck to produce future anticipated sensor readings as well as confirmatory trips of operational margins. Changes of the future sensor readings with real readings are used to adjust the remaining life calculations. The method is demonstrated on time series of historical engine faults. C1 [Goebel, Kai] NASA, Ames Res Ctr, Prognost Ctr Excellence, RIACS, MS 269-4, Moffett Field, CA 94035 USA. [Qiu, Hai; Eklund, Neil; Yan, Weizhong] GE Global Res, Niskayuna, NY 12309 USA. RP Goebel, K (reprint author), NASA, Ames Res Ctr, Prognost Ctr Excellence, RIACS, MS 269-4, Moffett Field, CA 94035 USA. EM goebel@email.arc.nasa.gov; qiu@research.ge.com; eklund@research.ge.com; yan@research.ge.com NR 3 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 3683 EP + PG 3 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235303052 ER PT S AU Tang, L Saxena, A Orchard, ME Kacprzynski, GJ Vachtsevanos, G Patterson-Hine, A AF Tang, Liang Saxena, Abhinav Orchard, Marcos E. Kacprzynski, Gregory J. Vachtsevanos, George Patterson-Hine, Ann GP IEEE TI Simulation-based design and validation of Automated Contingency Management for propulsion systems SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB Automated Contingency Management (ACM), or the ability to confidently and autonomously adapt to fault and/or contingency conditions with the goal of still achieving mission objectives, can be considered the ultimate technological goal of a health management system. To establish confidence on the ACM system, objective performance evaluations should be executed. The need for verification and validation (V&V) techniques for ACM has also been specifically identified by DOD agencies and within the NASA community recently. This paper presents a general process and related techniques for developing and validating ACM systems for advanced propulsion systems. A novel ACM modeling paradigm, optimization-based ACM strategies, V&V approaches and performance metrics are developed. While some well-established formal methods such as model checking techniques are applicable to some sub-problems, this research has been more focused on innovative informal methods that attempt to address ACM performance requirements, optimality, robustness, etc. A pressure fed, monopropellant propulsion system for a small space flight vehicle is utilized as initial proof-of-concept implementation for the proposed techniques and preliminary simulation results are presented. C1 [Tang, Liang; Kacprzynski, Gregory J.] Impact Technol, LLC Canal View Blvd, Rochester, NY 14623 USA. [Saxena, Abhinav; Orchard, Marcos E.; Vachtsevanos, George] Georgia Inst Technol, Sch Elect & Comp Engn, Atlanta, GA 30332 USA. [Patterson-Hine, Ann] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Tang, L (reprint author), Impact Technol, LLC Canal View Blvd, Rochester, NY 14623 USA. EM Greg.Kacprzynski@impact-tek.com FU NASA Ames Research Center in Moffett Field, CA, under STTR [NNA05AC53C] FX This work was supported by the NASA Ames Research Center in Moffett Field, CA, under STTR contract No. NNA05AC53C. We would also like to recognize the contributions of Dr. Irtaza Barl as, Dr. Michael Roemer from Impact Technologies, LLC, and Dr. Biqing Wu, Mr. Bhaskar Saha, Mr. Johan Reim ann, Dr. Bin Zhang and Dr. Young Jin Lee from Georgia Institute of Technology. NR 23 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 3708 EP + PG 3 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235303055 ER PT S AU Dempsey, PJ Lewicki, DG Le, DD AF Dempsey, Paula J. Lewicki, David G. Le, Dy D. GP IEEE TI Investigation of current methods to identify helicopter gear health SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB This paper provides an overview of current vibration methods used to identify the health of helicopter transmission gears. The gears are critical to the transmission system that provides propulsion, lift and maneuvering of the helicopter. This paper reviews techniques used to process vibration data to calculate conditions indicators (CI's), guidelines used by the government aviation authorities in developing and certifying the Health and Usage Monitoring System (HUMS), condition and health indicators used in commercial HUMS, and different methods used to set thresholds to detect damage. Initial assessment of a method to set thresholds for vibration based condition indicators applied to flight and test rig data by evaluating differences in distributions between comparable transmissions are also discussed. Gear condition indicator FM4 values are compared on an OH58 helicopter during 14 maneuvers and an OH58 transmission test stand during crack propagation tests. Preliminary results show the distributions between healthy helicopter and rig data are comparable and distributions between healthy and damaged gears show significant differences.(1,2). C1 [Dempsey, Paula J.] NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. [Lewicki, David G.] U S Army Res Lab, Cleveland, OH 44135 USA. [Le, Dy D.] FAA, William J Hughes Tech Ctr, Atlantic, NJ 08405 USA. RP Dempsey, PJ (reprint author), NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. EM paula.j.dempsey@nasa.gov; david.g.lewicki@grc.nasa.gov; dy.le@faa.gov NR 40 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 3768 EP + PG 4 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235303061 ER PT S AU Hu, X Eklund, N Goebel, K Cheetham, W AF Hu, Xiao Eklund, Neil Goebel, Kai Cheetham, William GP IEEE TI Hybrid change detection for aircraft engine fault diagnostics SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES ID TIME-SERIES; INFERENCE AB Change detection is an important task for remote monitoring, fault diagnostics and system prognostics. When a fault occurs, it will often times cause changes in measurable quantities of the system. Early detection of changes in system measurements that indicate abnormal conditions helps the diagnostics of the fault so that appropriate maintenance action can be taken before the fault progresses, causes secondary damage to the system and the equipment experiences downtime. In this paper, we investigate the performance of a suite of change detection algorithms. A set of synthetic time series data with different change patterns are generated based on the empirical distribution of real engine performance data so that the individual change detection algorithm can be evaluated and compared against each other. At last, the results from the individual change detection algorithms are fused together to demonstrate that the ensemble of the change detection algorithms generates better performance than any individual detection algorithm. C1 [Hu, Xiao; Eklund, Neil; Cheetham, William] GE Global Res, 1 Res Circle, Schenectady, NY 12309 USA. [Goebel, Kai] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Hu, X (reprint author), GE Global Res, 1 Res Circle, Schenectady, NY 12309 USA. EM hux@research.ge.com; eklund@research.ge.com; goebel@email.arc.nasa.gov; cheetham@research.ge.com NR 27 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 3805 EP + PG 4 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235303065 ER PT S AU Lee, C AF Lee, Charles GP IEEE TI Prior training of data mining system for fault detection SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB Many approaches have been used to fault discovery in complex systems. Model based reasoning; data mining analysis; rule base methods are the few among those approaches. To be successfully applied, these approaches all have to have some knowledge about the system prior to faults detection during the system run. 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 prior knowledge and use them to set the initial state of the decision trees.(12). C1 [Lee, Charles] 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 IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 3837 EP 3842 PG 6 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235303068 ER PT S AU Das, S Srivastava, AN Chattopadhyay, A AF Das, Santanu Srivastava, Ashok N. Chattopadhyay, Aditi GP IEEE TI Classification of damage signatures in composite plates using one-class SVMs SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES ID ROLLING-ELEMENT BEARINGS; FREQUENCY RESONANCE TECHNIQUE AB Damage characterization through wave propagation and scattering is of considerable interest to many non-destructive evaluation techniques. For fiber-reinforced composites, complex waves can be generated during the tests due to the non-homogeneous and anisotropic nature of the material when compared to isotropic materials. Additional complexities are introduced due to the presence of the damage and thus results in difficulty to characterize these defects. The inability to detect damage in composite structures limits their use in practice. A major task of structural health monitoring is to identify and characterize the existing defects or defect evolution through the interactions between structural features and multidisciplinary physical phenomena. In a wave-based approach to addressing this problem, the presence of damage is characterized by the changes in the signature of the resultant wave that propagates through the structure. In order to measure and characterize the wave propagation, we use the response of the surface-mounted piezoelectric transducers as input to an advanced machine-leaming based classifier known as a Support Vector Machine.(123). C1 [Das, Santanu; Chattopadhyay, Aditi] Arizona State Univ, Dept Mech & Aerosp Engn, Tempe, AZ 85287 USA. [Srivastava, Ashok N.] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Das, S (reprint author), Arizona State Univ, Dept Mech & Aerosp Engn, Tempe, AZ 85287 USA. EM santanu.das@asu.edu; ashok@email.arc.nasa.gov; aditi@asu.edu FU Air Force Office of Scientific Research [F496200310174] FX The research is supported by Air Force Office of Scientific Research, grant number: F496200310174, technical monitor Dr. Clark Allred and NASA Ames Research Center, technical monitor Dr. A. N. Srivastava. Their support is gratefully acknowledged. NR 30 TC 0 Z9 0 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 4060 EP + PG 4 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235303091 ER PT S AU Hoyle, C Mehr, A Tumer, I Chen, W AF Hoyle, C. Mehr, A. Tumer, I. Chen, W. GP IEEE TI On quantifying cost-benefit of ISHM in aerospace systems SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES ID DESIGN AB Integrated Systems Health Management (ISHM) is a desired system engineering capability to detect, assess, and isolate faults in complex aerospace systems to improve safety and reliability. At the conceptual design level, system-level engineers must make decisions regarding the extent of vehicle fault coverage using on-board sensors and the data collection, processing, interpretation, display, and action capabilities for the various subsystems, all considered essential parts of ISHM. In this paper, we propose a Cost-Benefit Analysis approach to initiate the ISHM design process. The key to this analysis is the formulation of an objective function that explicitly quantifies the cost-benefit factors involved with using ISHM technology in various subsystems. In the end, to determine the best ISHM system configuration, an objective is formulated, referred to as Profit, which is expressed as the product of system Availability (A) and Revenue per unit Availability (R), minus the sum of Cost of Detection (CD) and Cost of Risk (C-R). Cost of Detection includes the cost of periodic inspection/maintenance and the cost of including ISHM; Cost of Risk quantifies risk in financial terms as a function of the consequential cost of a fault and the probabilities of occurrence and detection. Increasing the ISHM footprint will generally lower Cost of Risk while raising Cost of Detection, while Availability will increase or decrease based upon the balance of the reliability and detectability of the sensors added, versus their ability to reduce total maintenance time. The analysis is conducted at the system functional level, with ISHM allocated to functional blocks in the optimization analysis. The proposed method is demonstrated using a simplified aerospace system design problem resulting in a configuration of sensors which optimizes the cost-benefit of the ISHM system for the given input parameters. In this problem, profit was increased by 11%, inspection interval increased by a factor of 1.5, and cost of risk reduced by a factor of 2.4.(1 2). C1 [Hoyle, C.; Chen, W.] Northwestern Univ, Evanston, IL 60208 USA. [Mehr, A.] NASA, Ames Res Ctr, QSS Grp, Moffett Field, CA 94035 USA. [Tumer, I.] Oregon State Univ, Corvallis, OR 97331 USA. RP Hoyle, C (reprint author), Northwestern Univ, Evanston, IL 60208 USA. EM cj-hoyle@northwestern.edu; amehr@email.arc.nasa.gov; irem.tumer@oregonstate.edu; weichen@northwestern.edu RI Chen, Wei/B-7574-2009 NR 17 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 4209 EP + PG 2 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235304003 ER PT S AU Goldberg, A Horvath, G AF Goldberg, Allen Horvath, Greg GP IEEE TI Software fault protection with ARINC 653 SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB With flight software becoming ever more complex, assuming that it behaves perfectly is no longer realistic. At the same time Verification and Validation (V&V) is consuming up to 50% of flight software development costs. The adaptation of fault protection concepts to flight software is attractive, particularly in the context of the fault containment and health management capabilities of ARINC 653. We propose a proactive, unified, model-based approach in which the behavior of the software is monitored against a model of its expected behavior. We describe how that may be incorporated into the ARINC 653 health management architecture. We describe software capabilities that facilitate software fault protection. These capabilities include enhancements to the ARINC 653 application executive, tools for software instrumentation, and a temporal logic runtime monitoring framework for high-level specification and monitoring. We analyze the aspects of the software that should be modeled and the types of failure responses. We show how these concepts may be applied to the Mission Data System (MDS) flight software framework. C1 [Goldberg, Allen] Kestrel Technol, 4984 El Camino Real,Suite 320, Los Altos, CA 94022 USA. [Horvath, Greg] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Goldberg, A (reprint author), Kestrel Technol, 4984 El Camino Real,Suite 320, Los Altos, CA 94022 USA. EM goldberg@kestreltechnology.com; Gregory.A.Horvath@jpl.nasa.gov FU NASA's [A06AA24C] FX We gratefully acknowledge support by NASA's Exploration System Mission Directorate under contract A06AA24C. Portions of the research described in this paper were carried out at the Jet Propulsion Laboratory, California Institute of Technology, under a contract with the National Aeronautics and Space Administration. NR 17 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 4216 EP + PG 3 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235304004 ER PT S AU Balaban, E Narasimhan, S Cannon, HN Brownston, LS AF Balaban, Edward Narasimhan, Sriram Cannon, Howard N. Brownston, Lee S. GP IEEE TI Model-based fault detection and diagnosis system for NASA Mars subsurface drill prototype SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB The Drilling Automation for Mars Environment (DAME) project, led by NASA Ames Research Center, is aimed at developing a lightweight, low-power drill prototype that can be mounted on a Mars lander and be capable of drilling down several meters below the Mars surface for conducting geology and astrobiology research. The DAME drill system incorporates a large degree of autonomy - from quick diagnosis of system state and fault conditions to taking the appropriate recovery actions - while also striving to achieve as many of the operational objectives as possible. This paper outlines, on a general level, the overall DAME architecture, equipment, and autonomy package. The main focus, however, is on describing the model-based fault detection and diagnosis system, including the modeling approach, the fault modes handled, and the diagnostic algorithms. The results of the latest field tests, conducted in 2006 in Haughton Crater on Devon Island (a Mars analogue site in Canadian Arctic), are also discussed.(12). C1 [Balaban, Edward; Cannon, Howard N.; Brownston, Lee S.] NASA, Ames Res Ctr, QSS, Moffett Field, CA 94035 USA. [Narasimhan, Sriram] NASA, Ames Res Ctr, USRA, Moffett Field, CA 94035 USA. RP Balaban, E (reprint author), NASA, Ames Res Ctr, QSS, Moffett Field, CA 94035 USA. EM balaban@email.arc.nasa.gov 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 SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 4227 EP + PG 4 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235304005 ER PT S AU Watson, MD Johnson, SB AF Watson, Michael D. Johnson, Stephen B. GP IEEE TI Theory of vehicle management systems SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB With the increasing capability of computers, engineers have designed vehicles to perform ever more complex tasks. Whether fully automated, as with robotic space probes, or partially automated in conjunction with a crew, vehicles have become both more complex and more capable. To manage this complexity, designers have developed increasingly sophisticated vehicle management systems (VMS) to manage vehicle internal states, and to operate in its external environment. While often effective, design of VMSs has often been on an ad hoc basis. Using insights from information theory, complexity theory, and artificial intelligence, this paper develops a theoretical framework in which to understand the nature of VMSs. The theory defines the interaction of VMS functions and provides a mathematical formulation to assess the complexity of different VMS configurations.(12) C1 [Watson, Michael D.; Johnson, Stephen B.] NASA, George C Marshall Space Flight Ctr, EV43 Adv Sensors & Syst Hlth Management Branch, Huntsville, AL 35812 USA. RP Watson, MD (reprint author), NASA, George C Marshall Space Flight Ctr, EV43 Adv Sensors & Syst Hlth Management Branch, Huntsville, AL 35812 USA. NR 2 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 4240 EP 4247 PG 8 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235304006 ER PT S AU Martin, RA AF Martin, Rodney A. GP IEEE TI Unsupervised anomaly detection and diagnosis for liquid rocket engine propulsion SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB The results of a comprehensive array of unsupervised anomaly detection algorithms applied to Space Shuttle Main Engine (SSME) data are presented. Most of the algorithms are based upon variants of the well-known unconditional Gaussian mixture model (GMM). One goal of the paper is to demonstrate the maximum utility of these algorithms by the exhaustive development of a very simple GMM. Selected variants will provide us with the added benefit of diagnostic capability. Another algorithm that shares a common technique for detection with the GMM is presented, but instead uses a different modeling paradigm. The model provides a more rich description of the dynamics of the data, however the data requirements are quite modest. We will show that this very simple and straightforward method finds an event that characterizes a departure from nominal operation. We show that further diagnostic investigation with the GMM-based method can be used as a means to gain insight into operational idiosyncrasies for this nominally categorized test. Therefore, by using both modeling paradigms we can corroborate planned operational commands or provide warnings for unexpected operational commands. C1 [Martin, Rodney A.] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Martin, RA (reprint author), NASA, Ames Res Ctr, Mail Stop 269-1, Moffett Field, CA 94035 USA. NR 26 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 4248 EP 4262 PG 15 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235304007 ER PT S AU Osipov, SV Luchinskyl, DG Smelyanskiy, VN Lee, SH Kiris, C Timucin, DA AF Osipov, Slava V. Luchinskyl, Dmitry G. Smelyanskiy, Vadim N. Lee, Sun Hwan Kiris, Cetin Timucin, Dogan A. GP IEEE TI Bayesian framework for in-flight SRM data management and decision support SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB We report progress in the development of a novel Bayesian framework for an in-flight Failure Decision and Prognostic (FD&P) system for Solid Rocket Boosters (SRBs) based on a combination of low-dimensional performance models and a Bayesian framework for diagnostics and prognostics of the parameters of nonlinear flow of combustion products in the combustion chamber. To simulate faults we introduce high-fidelity models of these faults based on stochastic partial differential equations (SPDE). To infer parameters of the model, the SPDE is reduced to a low dimensional performance model (LDPM). It is shown by example of the nozzle blocking fault that using a novel Bayesian framework, it becomes possible both to infer the variations of SRB parameters stimulated by the fault and to predict values of the pressure and time of the overpressure fault even in the case of highly nonlinear fault dynamics. The extension of the method to the diagnostic and prognostic of the case burning fault is discussed. C1 [Osipov, Slava V.; Luchinskyl, Dmitry G.; Smelyanskiy, Vadim N.; Kiris, Cetin; Timucin, Dogan A.] NASA, Ames Res Ctr, Mail Stop 269-2, Moffett Field, CA 94035 USA. [Osipov, Slava V.; Luchinskyl, Dmitry G.; Smelyanskiy, Vadim N.] Miss Crit Technol Inc, El Segundo, CA 90245 USA. [Lee, Sun Hwan] Stanford Univ, Dept Aeronaut & Astronaut, Stanford, CA 94305 USA. RP Smelyanskiy, VN (reprint author), NASA, Ames Res Ctr, Mail Stop 269-2, Moffett Field, CA 94035 USA. EM osipov@email.arc.nasa.gov; luchinsk@email.arc.nasa.gov; vadim@email.arc.nasa.gov; sunhlee@stanford.edu; ckiris@mail.arc.nasa.gov; timucin@email.arc.nasa.gov NR 25 TC 0 Z9 0 U1 0 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 4263 EP + PG 4 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235304008 ER PT S AU Fox, JM McCurdy, M AF Fox, Jason M. McCurdy, Michael GP IEEE TI Activity planning for the Phoenix Mars lander mission SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB The Phoenix Mars Mission is the first mission in the NASA Scout Program. As a Scout Mission, Phoenix must be relatively low-cost and yet highly innovative. Likewise, the Ground Data System (GDS) is under similar constraints. Key to the GDS tool development has been the utilization of the Ensemble framework - an open architecture for the development, integration, and deployment of mission operations software. Ensemble has enabled the production of a low-cost, feature-rich tool to support tactical mission activity planning called The Phoenix Science Interface (PSI). We will explain how PSI has broken new ground on several different fronts. First, PSI is among the pioneers in mission-ready tools built on the Ensemble framework. The promise of Ensemble is that it will enable NASA missions to derive greater results from their investment in mission operations software. PSI serves as a prime example of that promise. PSI is also revolutionary due to its ownership and manner of development. The development process is truly a collaborative effort between multiple groups at both The Jet Propulsion Laboratory and The Ames Research Center. No single team and no single NASA center "owns" the entire PSI tool. Rather, several teams contribute components to a tightly integrated system held together via the Ensemble framework. The end result is a feature rich tool with a consistent look-and-feel that allows the mission operators to achieve their objectives. Another advancement in PSI is the novel use of servers for performing difficult tasks such as detailed resource modeling, flight rule violation checks, and constraint network management. PSI connects to the server version of APGEN (Activity Plan Generator), a well-established multimission activity planning tool. This server, renamed APcore, is capable of handling resource modeling and flight rule enforcement requests. PSI also leverages Europa, a planning and scheduling server capable of constraint network management. Together with APcore and Europa, PSI is an example of the tight integration between data analysis and scheduling that has never before been achieved on a flight mission. Further, we will describe the overall functionality that PSI brings to the GDS and how it fits into the GDS design. PSI fills the role of a downlink image browser enabling tactical operators to gain quick access to newly acquired images as well as an uplink activity planning tool supporting the development of the day-to-day activity plans for the lander.(1 2). C1 [Fox, Jason M.] CALTECH, Jet Prop Lab, M-S 310-250D,4800 Oak Grove Dr, Pasadena, CA 91109 USA. [McCurdy, Michael] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Fox, JM (reprint author), CALTECH, Jet Prop Lab, M-S 310-250D,4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Jason.M.Fox@jpl.nasa.gov; michael.mccurdy@nasa.gov NR 4 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 4279 EP + PG 3 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235304009 ER PT S AU Bell, DG Kuehnel, F Maxwell, C Kim, R Kasraie, K Gaskins, T Hogan, P Coughlan, J AF Bell, David G. Kuehnel, Frank Maxwell, Chris Kim, Randy Kasraie, Kushyar Gaskins, Tom Hogan, Patrick Coughlan, Joe GP IEEE TI NASA World Wind: Opensource GIS for mission operations SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES ID MODIS AB This paper describes NASA World Wind, its technical architecture and performance, and its emerging use for mission operations. World Wind is a geographic information system that provides graphical access to terabytes of imagery and elevation models for planets and other celestial objects including satellite and other data of the Earth, Moon, Mars, Venus, and Jupiter; as well as astronomical data made available through the Sloan Digital Sky Survey. World Wind is also a customizable system that can be integrated as part of other applications. World Wind is not only an application in which add-ons can be integrated, but is also being developed as a plugin that can be integrated with other applications. This paper also describes the significant contributions of the international opensource community in making World Wind what it is today. Contributions have involved the following: 1) lead development of add-ons, several of which have been integrated as part of the core system available for direct download via sourceforge, 2) lead provider of high-resolution data sets, 3) lead help desk support through internet relay chat for end-users and developers, and 4) significant technical contributions to the core system including bug identification, tracking and resolution as well as ideas for new features and source code modifications.(1 2). C1 [Bell, David G.; Kuehnel, Frank; Maxwell, Chris; Kim, Randy; Kasraie, Kushyar] NASA, Ames Res Ctr, Adv Comp Sci Res Inst, Univ Space Res Assoc, MS 269-4, Moffett Field, CA 94035 USA. [Gaskins, Tom] LLC, Redmond, WA 98052 USA. [Hogan, Patrick; Coughlan, Joe] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Bell, DG (reprint author), NASA, Ames Res Ctr, Adv Comp Sci Res Inst, Univ Space Res Assoc, MS 269-4, Moffett Field, CA 94035 USA. EM dbell@riacs.edu; kuehnel@email.arc.nasa.gov; cmaxwell@arc.nasa.gov; rkim@arc.nasa.gov; kkasraie@arc.nasa.gov; tom@tomgaskins.com; phogan@mail.arc.nasa.gov; jcoughlan@mail.arc.nasa.gov FU Microsoft Corporation; Sun Microsystems FX Thanks to Microsoft Corporation for providing the hardware and software for the servers that deliver the geographic information to World Wind browsers, to Sun Microsystems for their support increating a Java versionof World Wind, and to Google for supporting the opensource community by funding several students working on World Wind. Thanks also to the individuals in the opensource communitywho have helped make World Wind what it is today. NR 10 TC 1 Z9 1 U1 0 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 4317 EP + PG 2 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235304012 ER PT S AU Allard, D AF Allard, Dan GP IEEE TI Development of a ground data messaging infrastructure for the Mars Science Laboratory and beyond SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB (12)The Mission Data Processing and Control Subsystem (MPCS) under development for the Mars Science Laboratory (MSL) incorporates a messaging-based architecture to support event-driven flight operations. MPCS (otherwise known as "Chill") applications communicate over a Java Messaging Service (JMS) compliant messaging bus using messages defined by common Extensible Markup Language (XML) data schemas. This communications approach provides a system-wide "information bus". that functions as a "blackboard" of flight and ground activity information available to interested clients. While messaging over JMS offers important connectivity benefits such as ease-of-integration, significant questions and challenges lie ahead. Primary concerns include the ability of clients to keep up with high rates of published messages during system tests as well as real-time operations and how to best mitigate information bus traffic problems through file system data storage and database management. This paper will discuss the issues and lessons learned by the Chill team from the development, integration and early stages of deployment of a ground data system (GDS) architecture built on a messaging infrastructure. C1 [Allard, Dan] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Allard, D (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 0 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 4340 EP 4347 PG 8 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235304014 ER PT S AU Sturdevant, KF AF Sturdevant, Kathryn F. GP IEEE TI Cruisin' and Chillin': Testing the Java-based distributed ground data system "Chill" with CruiseControl SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB This paper describes the design of the development test environment for the Mission Data Processing and Control Subsystem (MPCS), code-named "Chill." MPCS Chill is currently in development to support the Mars Science Laboratory (MSL), scheduled for launch in 2009. Chill is a Linux-based ground data system which includes both telemetry and command functions. The development test configuration consists of five levels: unit testing, end-to-end testing, user interface testing, external interface testing, and installation/deployment testing. This paper will focus primarily on the automation of the lowest two levels, unit and end-to-end testing.(12) MPCS Chill's continuous integration process is provided by its adaptation of CruiseControl, which is an open source framework for a continuous build process. CruiseControl is configured on the dedicated build machine, a Linux workstation, which is the target platform. Chill has configured CruiseControl into two project loops: the first fetches the latest version of software from a central repository, builds it, and performs unit tests (JUnit). The second loop runs scripted end-to-end tests, which are performed on the results of the first build. Results are reported via email notification and a web interface provides the details of the current and previous builds for each loop. The evolution of test definition is: requirements feed into design, design leads to use cases, and tests are derived from use cases, thus leading to the mapping of tests to requirements. Unit tests operate on internal components, while end-to-end tests operate at a higher level of abstraction and therefore can be traced to requirements. The evolutionary process ensures that we are testing to requirements. MPCS Chill presents a model for testing Java-based distributed ground systems in a semi-automated manner. The MPCS model is highly applicable to other projects looking to automate their testing in addition to achieving continuous integration. C1 [Sturdevant, Kathryn F.] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Sturdevant, KF (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 IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 4348 EP 4355 PG 8 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235304015 ER PT S AU Mishkin, A Lee, Y Korth, D LeBlanc, T AF Mishkin, Andrew Lee, Young Korth, David LeBlanc, Troy GP IEEE TI Human-robotic missions to the Moon and Mars: Operations design implications SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB For most of the history of space exploration, human and robotic programs have been independent, and have responded to distinct requirements. The NASA Vision for Space Exploration calls for the return of humans to the Moon, and the eventual human exploration of Mars; the complexity of this range of missions will require an unprecedented use of automation and robotics in support of human crews. The challenges of human Mars missions, including roundtrip communications time delays of 6 to 40 minutes, interplanetary transit times of many months, and the need to manage lifecycle costs, will require the evolution of a new mission operations paradigm far less dependent on real-time monitoring and response by an Earthbound operations team. Robotic systems and automation will augment human capability, increase human safety by providing means to perform many tasks without requiring immediate human presence, and enable the transfer of traditional mission control tasks from the ground to crews. Developing and validating the new paradigm and its associated infrastructure may place requirements on operations design for nearer-term lunar missions. The authors, representing both the human and robotic mission operations communities, assess human lunar and Mars mission challenges, and consider how human-robot operations may be integrated to enable efficient joint operations, with the eventual emergence of a unified exploration operations culture.(1 2). C1 [Mishkin, Andrew; Lee, Young] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Korth, David; LeBlanc, Troy] Johnson Space Ctr, Houston, TX 77058 USA. RP Mishkin, A (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM andrew.h.mishkin@jpl.nasa.gov; young.h.lee@jpl.nasa.gov; david.h.korth@nasa.gov; troy.p.leblanc@nasa.gov FU Jet Propulsion Laboratory, California Institute of Technology; National Aeronautics and Space Administration FX This work was performed at the Jet Propulsion Laboratory, California Institute of Technology, under contract with the National Aeronautics and Space Administration. NR 2 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 4375 EP + PG 3 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235304018 ER PT S AU Olson, JM AF Olson, John M. GP IEEE TI Tactile display technologies as an enabler for space exploration operations SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES ID SAFETY-CENTER DATA; NAVAL AVIATION; HUMAN ERROR; SYSTEM; HEAD AB Tactile displays have demonstrated improved situational awareness (SA) in aerospace research with the potential to improve safety and mission success for space exploration operations. Tactile Situation Awareness System (TSAS) studies have demonstrated improved pilot and operator SA and performance in both simulated and actual flight-testing, including a study of simulated Space Shuttle guided precision approaches and landings (A/Ls) where 12 US Air Force test pilot subjects each performed 24 precision A/Ls from 50,000 ft Mean Sea Level (MSL) in a realistic medium fidelity, fixed-based Shuttle simulator with partial instrument failures, secondary visual, and arithmetic tasks to increase cognitive workload. A tactile display belt using 24 electro-mechanical tactile transducers (tactors) was worn by all subjects. The control group (n=6) used visual-only information for 16 of 24 trials; the test group (n=6) received tactile guidance cues for all 24 trials. The study results from six objective and subjective measures plus pre- and post-flight surveys showed that tactile displays decreased overall workload, improved SA, counteracted fatigue, and provided superior warning and monitoring capacity for this dynamic, complex spaceflight related task. Performance improvement results were statistically inconclusive, although operator feedback revealed that sensory input was generally intuitive and improved task learning despite degraded system, and environmental conditions. The results implied improvements in overall safety, consistency, reliability, and ease of training and operations for both this specific task and broader general applications. Further, the results suggest that Tactile Display technologies may be a key integrated systems solution to bolstering the success, reliability, and sustained performance of the critical human element of our national space exploration operations.(12). C1 [Olson, John M.] NASA Headquarters, Explorat Syst Mission Directorate, Washington, DC 20546 USA. RP Olson, JM (reprint author), NASA Headquarters, Explorat Syst Mission Directorate, 300 E St SW,Suite 2P86, Washington, DC 20546 USA. NR 24 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 4385 EP 4396 PG 12 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235304019 ER PT S AU Guy, P Barrett, L Fatig, C AF Guy, Paul Barrett, Larry Fatig, Curtis GP IEEE TI The James Webb Space Telescope experience: A lifecycle approach to ground support equipment SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES DE ground system; JWST; development; I&T AB The James Webb Space Telescope (JWST) developed by the National Aeronautics and Space Administration (NASA), represents a significant undertaking in the study of the early formation of galaxies. Dubbed "NASA's Cosmology Time Machine", JWST is scheduled to launch in 2013. One area Goddard Space Flight Center (GSFC) has responsibility for is the Integrated Science Instrument Module (ISM element of JWST, which will integrate the four infrared Science Instruments (SIs) that are currently under development. This represents a considerable challenge, since the various Instrument Development Teams (IDTs) are geographically located in various facilities across the United States, in Europe, and in Canada. A fundamental issue is to manage the risk associated with coordinating the development of the SIs and their associated engineering products with the eventual integration of these independently developed components into ISIM. To this end, the ISIM Team at GSFC has developed a strategy for providing the IDTs with a common set of Ground Support Equipment (GSE) to facilitate their development efforts. This commonality enables the various IDTs to effortlessly share engineering products within the limits imposed by non-technical (i.e., security) constraints. C1 [Guy, Paul] Goddard Space Flight Ctr, Code 565, Greenbelt, MD 20771 USA. [Barrett, Larry] Orbital Sci Corp, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Fatig, Curtis] SAIC, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Guy, P (reprint author), Goddard Space Flight Ctr, Code 565, Greenbelt, MD 20771 USA. EM pguy@hst.nasa.gov; Ibarrett@hst.nasa.gov; cfatig@hst.nasa.gov NR 0 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 4397 EP + PG 2 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235304020 ER PT S AU Stetson, HK Deitsch, DK Cruzen, CA Haddock, AT AF Stetson, Howard K. Deitsch, David K. Cruzen, Craig A. Haddock, Angie T. GP IEEE TI Autonomous payload operations onboard the International Space Station SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB Operating the International Space Station (ISS) involves many complex crew tended, ground operated and combined systems. Over the life of the ISS program, it has become evident that by having automated and autonomous systems onboard, more can be accomplished and at the same time reducing the workload of the crew and ground operators. Engineers at the National Aeronautics and Space Administration's (NASA) Marshall Space Flight Center in Huntsville Alabama, working in collaboration with The Charles Stark Draper Laboratory, have developed an autonomous software system that uses the Timeliner User Interface Language and expert logic to continuously monitor ISS payload systems, issue commands and signal ground operators as required. This paper describes the development history of the system, its concept of operation and components. The paper also discusses the testing process as well as the facilities used to develop the system. The paper concludes with a description of future enhancement plans for use on the ISS as well as potential applications to Lunar and Mars exploration systems.(1 2). C1 [Stetson, Howard K.; Deitsch, David K.] Teledyne Brown Engn Inc, Huntsville, AL 35812 USA. [Cruzen, Craig A.; Haddock, Angie T.] NASA Marshall Space Flight Ctr, Huntsville, AL 35812 USA. RP Stetson, HK (reprint author), Teledyne Brown Engn Inc, Huntsville, AL 35812 USA. EM howard.k.stetson@msfc.nasa.gov; david.k.deitsch@msfc.nasa.gov; craig.crazen@nasa.gov; angie.haddock@nasa.gov NR 6 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 4413 EP + PG 3 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235304022 ER PT S AU Badaruddin, KS Hernandez, JC Brown, JM AF Badaruddin, Kareem S. Hernandez, Juan C. Brown, Jay M. GP IEEE TI The importance of hardware-in-the-loop testing to the Cassini mission to Saturn SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB The Cassini-Huygens Program is a joint effort between European Space Agency (ESA), which delivered the Huygens probe, and the National Aeronautics and Space Administration (NASA), which delivered the Cassini spacecraft. The Jet Propulsion Laboratory (JPL) manages the Cassini spacecraft for NASA. Cassini's primary mission is to survey the complex Saturnian system and release the ESA-Huygens probe at Titan. The Cassini Integrated Test Lab (ITL) at JPL is a high-fidelity hardware-in-the-loop testbed. It uses Attitude and Articulation Control Subsystem (AACS) and Command and Data Subsystem (CDS) flight hardware (H/W), as well as high-fidelity simulations of the other spacecraft subsystems and signals. The ITL's primary objective is to validate and verify sequences, Flight Software, and mission critical events, and it serves other purposes such as training the flight crew. This paper examines some of the AACS and CDS H/W and their peripheral devices used in the ITL. It examines the unique advantages gained by using H/W in the Cassini ITL, as well as the tradeoffs of using H/W versus simulations of these devices. Of late, consideration has been given in developing test plans for future flight projects to using purely software simulation testbeds: this paper offers evidence of the value of hardware-in-the-loop testbeds, demonstrating that hardware-in-the-loop testbeds should continue to have an important role in assuring the success of flight projects.(1, 2). C1 [Badaruddin, Kareem S.; Hernandez, Juan C.; Brown, Jay M.] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Badaruddin, KS (reprint author), CALTECH, Jet Prop Lab, MS 230-104,4800 Oak Grove Dr, 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 SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 4425 EP 4433 PG 9 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235304023 ER PT S AU Lee, M Miller, C Eldering, A Qu, Z AF Lee, Meemong Miller, Charles Eldering, Annmarie Qu, Zheng GP IEEE TI Earth science mission concept design system SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB Knowledge about the Earth system (i.e., the physical-chemical processes that describe its evolution) is generated from global measurements of geophysical parameters taken at appropriate mission observation scenarios.. Any given instrument transforms the incoming signal into an instrument-dependent output, from which the scientific observable of interest, say a chemical constituent, is eventually retrieved. The ability to simulate high-fidelity incoming geophysical signals, instrument transformations, and retrievals is currently project specific, and this ability is developed after a particular instrument design has been chosen. This seriously limits the process of conceiving the next-generation missions starting from the science questions to be answered, and choosing the appropriate measurement strategy based on the expected accuracy and precision. To enable science-driven mission concept formulation and design validation, the atmospheric scientists at JPL developed a set of parameters for defining the measurement requirements that are verifiable and traceable and a set of metrics for evaluating the mission concepts that are quantifiable and tradable. This paper presents a global atmospheric science mission concept design system that allows scientists to explore a large range of mission concepts integrating the measurement requirement parameters and evaluation metrics. C1 [Lee, Meemong; Miller, Charles; Eldering, Annmarie; Qu, Zheng] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Lee, M (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove, Pasadena, CA 91109 USA. NR 7 TC 1 Z9 1 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 4448 EP 4461 PG 14 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235304025 ER PT S AU Terrile, RJ Kordon, M Postma, M Salcedo, J Hanks, D Wood, E AF Terrile, Richard J. Kordon, Mark Postma, Mona Salcedo, Jose Hanks, David Wood, Eric GP IEEE TI Automated design of spacecraft telecommunication subsystems using evolutionary computational techniques SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB This paper(1,2) discusses the application of evolutionary computing to a dynamic space vehicle telecommunication subsystem resource and performance simulation in a parallel processing environment. Our objective is to demonstrate the feasibility, application and advantage of using evolutionary computation techniques for the early design search and optimization of space systems. With this approach, engineers specify several sets of conditional subsystem performance criteria to trade off subsystem goals of mass, cost, performance and risk. Once specified, the integrated evolutionary/simulation software will then automatically generate a design option for each criteria, selecting and sizing telecom elements based on the space system's anticipated performance in the simulated environment. Initial activity plans from an actual JPL mission, Deep Impact (DI) are used to test the software. Our results have shown human-competitive advantages by generating credible design concepts much faster than humans are able to and without the need for expert initial designs. C1 [Terrile, Richard J.; Kordon, Mark; Postma, Mona; Salcedo, Jose; Hanks, David; Wood, Eric] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Terrile, RJ (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 9 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 4487 EP 4495 PG 9 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235304029 ER PT S AU Jansma, PA Derro, ME AF Jansma, P. A. Trisha Derro, Mary Ellen GP IEEE TI If you want good systems engineers, sometimes you have to grow your own! SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB Given the ever increasing number, scope and complexity of systems today, it is vital to have a cadre of highly trained and skilled systems engineers to ensure that those systems are developed and operated successfully. But from where will those systems engineers come? The Jet Propulsion Laboratory (JPL) has come to the conclusion that if you want them, sometimes you have to grow your own. The JPL Systems Engineering Advancement (SEA) project was launched in FY2004 to advance the practice of systems engineering at JPL, and to address the three key aspects of change: people, process and technology. A significant major portion of the People component of the SEA Project is devoted to a systems engineering on-the-job training (OJT) program. The SEA OJT program will train 50 systems engineers over a five year period according to a three-pronged systems engineering competency model. This competency model includes technical domain knowledge, understanding of systems engineering standards, processes and practices, and highly valued behavioral attributes. The behavioral attributes fall into four broad categories: leadership, communication, problem solving and systems thinking, and attitudes and attributes. The SEA Project wrestled with determining the best way to train potential systems engineers along each axis of the competency model, especially how best to inculcate the behavioral attributes. Ultimately, they determined a range of activities that would accomplish their objectives. This mix includes classroom training, hands-on project experience, mentoring and coaching, shadowing, 360 degree feedback, and attending conferences and workshops. This paper(1, 2) provides an overview of the JPL SEA OJT Program including the candidate selection criteria, selection process, training approach and activities, and lessons learned. C1 [Jansma, P. A. Trisha; Derro, Mary Ellen] CALTECH, Jet Prop Lab, SEA Project, Pasadena, CA 91109 USA. RP CALTECH, Jet Prop Lab, SEA Project, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 26 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 4501 EP 4515 PG 15 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235304031 ER PT S AU Webster, J Corcoran, P AF Webster, Jeffery Corcoran, Patricia GP IEEE TI NPR 7120.5 and NASA's program/project on-line library and resource information system (POLARIS) SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB NASA's POLARIS information system provides rapid access to key program and project management requirements, guidance, and tools needed for planning and implementing NASA flight, technology, and infrastructure projects. Developed under leadership of the Office of the Chief Engineer, NASA's POLARIS provides an agency-wide, web-based information system that greatly enhances the support provided to program & project managers and their teams. POLARIS provides improved access to the agency's requirements, guidelines, and tools for program and project management. Instead of searching through long documents to find needed information, POLARIS enables users within the NASA intranet domain to access user-friendly interactive summaries and charts, dynamically search and display requirements, and access tools and other pertinent information needed to manage and implement NASA programs and projects. This paper presents a detailed description of the POLARIS website, an overview of the POLARIS design and development process, and the lessons learned in developing a system of this type. C1 [Webster, Jeffery; Corcoran, Patricia] CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. RP Webster, J (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. NR 2 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 4516 EP 4528 PG 13 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235304032 ER PT S AU Taylor, RL AF Taylor, Randall L. GP IEEE TI Ten years after: Enduring lessons learned from mars pathfinder SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB On July 4, 1997, the eyes of the world were focused on the high-risk entry, descent, and landing (EDL) of Mars Pathfmder (MPF). The mission employed a system of aeroshell, parachute, altimeter, retrorockets, and airbags in an audacious attempt to emplace a small science station on Mars and deploy a microrover for short-scale exploration. The project was implemented under NASA's new "faster-better-cheaper" (FBC) paradigm, which included a short development cycle and a hard cost cap. MPF and Sojourner, "the little rover that could," proved to be highly successful and received much press at the time.(1 2) The Mars Pathfinder team had produced a set of lessons learned presentations following launch. This material captured what were believed to be the key lessons, both positive and negative, from 5 years of difficult and dynamic work, and was intended to offer guidance to future NASA projects. Over time, however, what had been considered to be "lessons" in 1997 would be questioned by future FBC and non-FBC projects. Looking back from a vantage point 10 years after MPF launch in December 1996, it is possible to more objectively separate out the enduring lessons from ones that did not remain valid, represented one-time-only occurrences, or carried unintended adverse consequences. Today's assessment encompasses what worked, what did not work, and what could have been done better, from a 2006 perspective. This paper gives a brief overview of the Mars Pathfinder project, its requirements, and its management approach; identifies the principal lessons learned as understood at the time; provides examples of lessons that did not stand the test of time; and describes what are considered to be the lasting messages of a successful and exciting endeavor. C1 CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Taylor, RL (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Randall.L.Taylor@jpl.nasa.gov NR 8 TC 0 Z9 0 U1 0 U2 4 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 4529 EP 4535 PG 7 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235304033 ER PT S AU Rogers, EW Dillon, RL Tinsley, CH AF Rogers, Edward W. Dillon, Robin L. Tinsley, Catherine H. GP IEEE TI Avoiding common pitfalls in lessons learned processes that support decisions with significant risks SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB Since the Columbia accident, the National Aeronautics and Space Administration (NASA) has worked extensively to improve its "Lessons Learned" processes so that NASA can avoid repeating past decision making errors. This paper identifies the most serious pitfalls in lessons learned processes that support decisions that must be made in situations with significant risks. We focus on three steps in the lessons learned process: collecting lessons learned, managing lessons learned systems, and applying lessons learned appropriately to future missions. By identifying the pitfalls in each of these three processes, we hope to improve lessons learned systems to support current and future missions. Also, we describe steps taken at Goddard Space Flight Center (GSFC) and for the Exploration Systems Mission Directorate (ESMD) to improve the lessons learned process and to support the development of a learning organization.(12). C1 [Rogers, Edward W.] NASA, Goddard Space Flight Ctr, Code 170, Greenbelt, MD 20771 USA. [Dillon, Robin L.; Tinsley, Catherine H.] Georgetown Univ, McDonough Sch Business, Washington, DC 20057 USA. RP Rogers, EW (reprint author), NASA, Goddard Space Flight Ctr, Code 170, Greenbelt, MD 20771 USA. EM edward.w.rogers@nasa.gov; rld9@georgetown.edu; tinsleyc@georgetown.edu FU NASA/USRA; NASA Goddard Space Flight Center FX The participation of Georgetown University faculty has been funded in part by the NASA/USRA Center for Program/Project Management Research and by NASA Goddard Space Flight Center whose support is gratefully acknowledged. We also would like to thank David Lengyel, Exploration Systems Mission Directorate Risk Manager and David Oberhettinger, Office of the Chief Engineer, NASA/Caltach Jet Propulsion Laboratory for their help and feedback on this paper NR 9 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 4536 EP + PG 4 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235304034 ER PT S AU Meshkat, L AF Meshkat, Leila GP IEEE TI A holistic approach for risk management during design SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB In this paper, an approach for the identification, assessment, mitigation and continuous management of risks during the process of designing a space mission is presented. This approach has been developed by observing the risk patterns that occur at the Project Design Center of the Jet Propulsion Laboratory (TeamX) which develops conceptual, concurrent design of Space Missions. TeamX develops an end-to-end conceptual design of a Space Mission in a matter of one or two weeks. As the creator and operator of the risk chair in TeamX, the author has had the opportunity to observe the risk patterns that occur during design over the course of many design sessions. This paper introduces an abstraction and generalization of those patterns. Risk is defined as anything that can go wrong, along with its approximate likelihood and consequence. The indicators, and causes, and effects of these risks are cross cutting across the multiple levels of people and processes involved in the design, and the actual design product itself.(12). C1 CALTECH, Jet Prop Lab, Pasadena, CA 91101 USA. RP Meshkat, L (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91101 USA. NR 8 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 4564 EP 4568 PG 5 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235304037 ER PT S AU Kordon, M Wall, S Stone, H Blume, W Skipper, J Ingham, M Neelon, J Chase, J Baalke, R Hanks, D Salcedo, J Solish, B Postma, M Machuzak, R AF Kordon, Mark Wall, Steve Stone, Henry Blume, William Skipper, Joseph Ingham, Mitch Neelon, Joe Chase, James Baalke, Ron Hanks, David Salcedo, Jose Solish, Benjamin Postma, Mona Machuzak, Richard GP IEEE TI Model-based engineering design pilots at JPL SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB This paper discusses two recent formulation phase Model-Based Engineering Design pilot projects at the Jet Propulsion Laboratory. It describes how model-based functional and state analyses were synthesized and integrated with system performance simulation and mission planning then piloted in the formulation phase of two deep space missions. C1 [Kordon, Mark; Wall, Steve; Stone, Henry; Blume, William; Skipper, Joseph; Ingham, Mitch; Neelon, Joe; Chase, James; Baalke, Ron; Hanks, David; Salcedo, Jose; Solish, Benjamin; Postma, Mona; Machuzak, Richard] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Kordon, M (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 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 4605 EP 4624 PG 20 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235304042 ER PT S AU Putz, P Maluf, DA Bell, DG Gurram, MM Hsu, J Patel, HN Swanson, KJ AF Putz, Peter Maluf, David A. Bell, David G. Gurram, Mohana M. Hsu, Jennifer Patel, Hemil N. Swanson, Keith J. GP IEEE TI Earned value management at NASA: An integrated, lightweight solution SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB This paper describes a fresh approach to Earned Value Management (EVM) at the U.S. National Aeronautics and Space Administration (NASA). The goal of this approach is to provide a lightweight tool that allows project managers to apply earned value performance measurements with minimal effort in terms of data entry, and without the need to learn the highly specialized jargon that mystifies many EVM solutions. The presented technical and managerial solution addresses the practical challenges of applying EVM in the messy realm of project management. An empirical case study involving five projects at the NASA Ames Research Center illustrates the challenges of creating a consistent performance measurement baseline under the constraints of schedule, budget, and labor requirements, and of matching actual costs with budgeted costs on the level of granularity needed. The case study also highlights the benefits of using the implemented EVM solution in terms of data quality and time savings. The paper concludes with general recommendations for the design and application of EVM tools with the focus on ease of use. C1 [Putz, Peter; Bell, David G.; Gurram, Mohana M.] NASA, Ames Res Ctr, Univ Space Res Assoc, Moffett Field, CA 94035 USA. [Maluf, David A.; Swanson, Keith J.] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Hsu, Jennifer; Patel, Hemil N.] NASA, Ames Res Ctr, QSS Grp Inc, Moffett Field, CA 94035 USA. RP Putz, P (reprint author), NASA, Ames Res Ctr, Univ Space Res Assoc, Moffett Field, CA 94035 USA. EM pputz@riacs.edu; david.a.maluf@nasa.gov; dbell@riacs.edu; mgurram@riacs.edu; jennifer@email.arc.nasa.gov; patel@email.arc.nasa.gov; keith.j.swanson@nasa.gov NR 3 TC 0 Z9 0 U1 1 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 4655 EP + PG 3 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235304046 ER PT S AU Graham, DR AF Graham, David R. GP IEEE TI Using cost-risk to connect cost estimating and earned value management (EVM) SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE AEROSPACE CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB NASA space vehicle acquisition cost management has come under close scrutiny in the past three years due to perceived and actual cost overruns. As a result of two reports, the 2004 GAO report entitled, "Lack of Disciplined Cost-Estimating Processes Hinders NASA's Ability to Effectively Manage Its Programs" and the 2004 "President's Commission on Implementation of United States Space Exploration Policy", NASA reengineered its cost management with an emphasis on risk and cost-risk management. The new cost management process involves the identification, assessment and quantification of risky WBS elements in the cost estimating process for reporting feedback using Earned Value Management (EVM). The project manager will be able to use the resulting performance measurement metrics from the EVM system to track high-risk element actual cost-risk behavior. Thus, through the synergy between the cost estimating and EVM processes the project manager will have the benefit of the highest quality cost information with which to manage his/her effort.(12). C1 NASA, HQ PA&E, Cost Anal Div, Washington, DC 20546 USA. RP Graham, DR (reprint author), NASA, HQ PA&E, Cost Anal Div, 300 E St SW, Washington, DC 20546 USA. RI Caposaldo, Marica/I-8659-2014 NR 1 TC 0 Z9 0 U1 0 U2 4 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 4663 EP 4671 PG 9 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235304047 ER PT S AU Emmons, DL Bitten, RE Freaner, CW AF Emmons, Debra L. Bitten, Robert E. Freaner, Claude W. GP IEEE TI Using historical NASA cost and schedule growth to set future program and project reserve guidelines SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES AB By looking at historical schedule and cost growth, the past can be used to established reserve guidelines for future missions. This paper looks at recent NASA cost and schedule growth history, categorizes the reasons for growth, isolates growth due to external programmatic reasons versus internal technical reasons, assesses relationships for causality and provides guidance for the proper cost and schedule reserves to be carried at both the Program and Project levels. Mission cost and schedule growth history from both planetary and Earth-orbiting programs, such as Mars Exploration, Discovery, Medium and Small Explorer, Earth System Science Pathfinder, New Millennium and others, are investigated. The reserve guidelines developed are compared to industry standard guidelines and rules of thumb to determine if these standard practices continue to be valid. C1 [Emmons, Debra L.; Bitten, Robert E.] Grumman Aerosp Corp, 200 S Los Robles Ave,Suite 150, Pasadena, CA 91101 USA. [Freaner, Claude W.] NASA, Washington, DC 20546 USA. RP Emmons, DL (reprint author), Grumman Aerosp Corp, 200 S Los Robles Ave,Suite 150, Pasadena, CA 91101 USA. EM debra.l.emmons@aero.org; robert.e.bitten@aero.org; claude.freaner@nasa.gov NR 25 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 4672 EP + PG 4 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235304048 ER PT S AU Montemerlo, M Sloboda, S AF Montemerlo, Mel Sloboda, Steve GP IEEE TI Track 14 PANELS government plans, policies, and education SO 2007 IEEE AEROSPACE CONFERENCE, VOLS 1-9 SE IEEE Aerospace Conference Proceedings LA English DT Proceedings Paper CT 2007 IEEE Aerospace Conference CY MAR 03-10, 2007 CL Big Sky, MT SP IEEE, Panasonic, Aerosp Corp, IET, dSPACE, CALTECH, Amer Inst Aeronaut & Astronaut, ASES C1 [Montemerlo, Mel] NASA Headquarters, Washington, DC 20006 USA. RP Montemerlo, M (reprint author), NASA Headquarters, Washington, DC 20006 USA. NR 0 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1095-323X BN 978-1-4244-0524-4 J9 AEROSP CONF PROC PY 2007 BP 4688 EP + PG 2 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Robotics SC Engineering; Computer Science; Robotics GA BGY10 UT WOS:000251235304049 ER PT S AU Sweriduk, GD Cheng, VHL Andre, AD Foyle, DC AF Sweriduk, G. D. Cheng, V. H. L. Andre, A. D. Foyle, D. C. GP IEEE TI Automation tools for high-precision taxiing SO 2007 IEEE/AIAA 26TH DIGITAL AVIONICS SYSTEMS CONFERENCE, VOLS 1-3 SE IEEE-AIAA Digital Avionics Systems Conference LA English DT Proceedings Paper CT 26th Digital Avionics Systems Conference CY OCT 21-25, 2007 CL Dallas, TX SP IEEE, AIAA AB Airport congestion is a growing problem, as most air travelers can attest. Efforts are now under way to reduce congestion by increasing the traffic flow rate at airports through the use of automation tools. Which runway and taxiways an aircraft occupies, and when, must be precisely scheduled and executed. Presented herein are results on developing a system which can generate a 4-D trajectory and follow the trajectory accurately. C1 [Sweriduk, G. D.; Cheng, V. H. L.] Optimal Synthesis Inc, Palo Alto, CA 94022 USA. [Andre, A. D.] Interface Analysis Associates, Gilroy, CA 95020 USA. [Foyle, D. C.] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Sweriduk, GD (reprint author), Optimal Synthesis Inc, Palo Alto, CA 94022 USA. FU NASA under the Small Business Innovations Research program [NNA06AA06C] FX This work was supported by NASA under the Small Business Innovations Research program, contract no. NNA06AA06C 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 2155-7195 BN 978-1-4244-1107-8 J9 IEEEAAIA DIGIT AVION PY 2007 BP 1 EP + PG 3 WC Engineering, Aerospace; Computer Science, Information Systems; Engineering, Electrical & Electronic; Transportation Science & Technology SC Engineering; Computer Science; Transportation GA BHM72 UT WOS:000254342600001 ER PT S AU Idris, H Vivona, R Garcia-Chico, JL Wing, D AF Idris, Husni Vivona, Robert Garcia-Chico, Jose-Luis Wing, David GP IEEE TI Distributed traffic complexity management by preserving trajectory flexibility SO 2007 IEEE/AIAA 26TH DIGITAL AVIONICS SYSTEMS CONFERENCE, VOLS 1-3 SE IEEE-AIAA Digital Avionics Systems Conference LA English DT Proceedings Paper CT 26th Digital Avionics Systems Conference CY OCT 21-25, 2007 CL Dallas, TX SP IEEE, AIAA AB In order to handle the expected increase in air traffic volume, the next generation air transportation system is moving towards a distributed control architecture, in which ground-based service providers such as controllers and traffic managers and air-based users such as pilots share responsibility for aircraft trajectory generation and management. This paper presents preliminary research investigating a distributed trajectory-oriented approach to manage traffic complexity, based on preserving trajectory flexibility. The underlying hypotheses are that preserving trajectory flexibility autonomously by aircraft naturally achieves the aggregate objective of avoiding excessive traffic complexity, and that trajectory flexibility is increased by collaboratively minimizing trajectory constraints without jeopardizing the intended air traffic management objectives. This paper presents an analytical framework in which flexibility is defined in terms of robustness and adaptability to disturbances and preliminary metrics are proposed that can be used to preserve trajectory flexibility. The hypothesized impacts are illustrated through analyzing a trajectory solution space in a simple scenario with only speed as a degree of freedom, and in constraint situations involving meeting multiple times of arrival and resolving conflicts. C1 [Idris, Husni; Vivona, Robert; Garcia-Chico, Jose-Luis] L 3 Communicat, Billerica, MA USA. [Wing, David] NASA Langley Res Ctr, Hampton, VA USA. RP Idris, H (reprint author), L 3 Communicat, Billerica, MA USA. EM Husni.idris@L-3com.com; David.wi.ng@nasa.gov FU NASA [NNA07BA86C] FX This research was funded by NASA under contract NNA07BA86C. NR 19 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2155-7195 BN 978-1-4244-1107-8 J9 IEEEAAIA DIGIT AVION PY 2007 BP 506 EP + PG 3 WC Engineering, Aerospace; Computer Science, Information Systems; Engineering, Electrical & Electronic; Transportation Science & Technology SC Engineering; Computer Science; Transportation GA BHM72 UT WOS:000254342600048 ER PT B AU Callantine, TJ AF Callantine, Todd J. GP IEEE TI Tradeoffs in high density trajectory-based operations SO 2007 IEEE/AIAA 26TH DIGITAL AVIONICS SYSTEMS CONFERENCE, VOLS 1-3 SE Digital Avionics Systems Conference LA English DT Proceedings Paper CT 26th Digital Avionics Systems Conference CY OCT 21-25, 2007 CL Dallas, TX SP IEEE, AIAA AB Alleviating Air Traffic Management (ATM) system capacity barriers and environmental impacts around major metropolitan areas is critical for the Next Generation Air Transportation System. This paper presents initial research toward applying fast-time simulation methods to evaluate system-level tradeoffs in high-density trajectory-based operations in order to identify suitable roles for humans in the future system. A mid-term concept of operations in which aircraft are scheduled to arrive at the runway on optimized descent profiles ("CDAs") along Area Navigation/Required Navigation Performance (RNAV/RNP) routes separated from other RNAV/RNP arrival. and departure routings serves as the core concept for discussion. The paper discusses tradeoffs between RNAV/RNP route designs, airspace configuration, aircraft and Flight Management System (FMS) performance, pilot procedures, scheduling automation, and the control methods to be applied. Initial efforts to simulate the core concept have concentrated on developing RNAV/RNP CDAs and departure routes; the paper presents example route designs and discusses tradeoffs arising from them. An important challenge lies in verifying an ATM concept's robustness. This entails demonstrating that a concept provides reasonable means to cope with uncertainties. The paper discusses the application of fast-time simulation methods to an iterative concept development process in which effectiveness in coping with uncertainty is the primary driver for evaluating design tradeoffs and refining the concept. C1 San Jose State Univ, NASA, Ames Res Ctr, Moffett Field, CA USA. RP Callantine, TJ (reprint author), San Jose State Univ, NASA, Ames Res Ctr, Moffett Field, CA USA. EM tcallantine@mail.arc.nasa.gov NR 16 TC 0 Z9 0 U1 1 U2 3 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-1107-8 J9 DIGIT AVION SYST CON PY 2007 BP 519 EP 530 PG 12 WC Engineering, Aerospace; Computer Science, Information Systems; Engineering, Electrical & Electronic; Transportation Science & Technology SC Engineering; Computer Science; Transportation GA BHM72 UT WOS:000254342600049 ER PT S AU Hall, D Budinger, J AF Hall, Dana Budinger, James GP IEEE TI Nextgen ats conmunications, navigation, and surveiellance test bed SO 2007 IEEE/AIAA 26TH DIGITAL AVIONICS SYSTEMS CONFERENCE, VOLS 1-3 SE IEEE-AIAA Digital Avionics Systems Conference LA English DT Proceedings Paper CT 26th Digital Avionics Systems Conference CY OCT 21-25, 2007 CL Dallas, TX SP IEEE, AIAA AB Following an approximate 12 month planning and definition period, implementation of the Next Generation Air Transportation System (NextGen) Communication, Navigation and Surveillance (CNS) Test Bed began in earnest during mid-year 2006. This Test Bed, focused on the evaluation of promising CNS technologies and systems, presently encompasses three airports in the Cleveland, Ohio region and a Test and Demonstration Center located at NASA Glenn Research Center (GRC). The Test Bed coverage will be extended before the end of 2007 to include a 200 mile radius around the Cleveland metropolitan area thus creating a wide area air-ground test and demonstration capability. The three included airports (Hopkins International, Burke Lakefront, and Lorain County Regional) are representative of various classes of airports across the country close to population centers that will be central to accommodating forecasted air travel growth over the next 20 years. Sensis, in partnership with the Cleveland Airport System, the Lorain County Regional Airport Authority, and the FAA, has installed an advanced version multilateration surveillance system and wireless communications infrastructure at each of these airports. Implemented as well is a prototype of a Remote Tower System (a.k.a., a Staffed Virtual Tower) that "shadow controls" operations at Burke Lakefront Airport from the Test and Demonstration Center some 13 miles away. The Test Bed is integrated as a system via a prototype of a regional information sharing and management system. Sensis Corporation, GRC, and their Test Bed partners are collaborating to define and test possible solutions for some of the most significant challenges to the success of NextGen. In addition to remote monitoring and control of airports, the issues under investigation by this team include validating the promised efficiencies of negotiated 4-D arrival and departure trajectories, assessing advanced integrated surveillance capabilities, helping solve the continuing safety problem of runway incursions, and improving the efficiency of airport and airline surface operations. GRC is planning to explore the potential for an IEEE 802.16e standard-based wireless airport surface communications network operating in the 5.1 GHz band, soon to be allocated for safety critical airground communications services. This paper summarizes the mid-2007 status of this Test Bed and shares plans for the next twelve months. C1 [Hall, Dana] Sensis Corp, E Syracuse, NY USA. [Budinger, James] NASA Glenn Res Ctr, Cleveland, OH USA. RP Hall, D (reprint author), Sensis Corp, E Syracuse, NY USA. NR 2 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2155-7195 BN 978-1-4244-1107-8 J9 IEEEAAIA DIGIT AVION PY 2007 BP 653 EP + PG 2 WC Engineering, Aerospace; Computer Science, Information Systems; Engineering, Electrical & Electronic; Transportation Science & Technology SC Engineering; Computer Science; Transportation GA BHM72 UT WOS:000254342600062 ER PT S AU Verma, S Kozon, T Cheng, V Ballinger, D AF Verma, Savita Kozon, Thomas Cheng, Victor Ballinger, Deborah GP IEEE TI Changes in roles/responsibilities of air traffic control under precision taxiing SO 2007 IEEE/AIAA 26TH DIGITAL AVIONICS SYSTEMS CONFERENCE, VOLS 1-3 SE IEEE-AIAA Digital Avionics Systems Conference LA English DT Proceedings Paper CT 26th Digital Avionics Systems Conference CY OCT 21-25, 2007 CL Dallas, TX SP IEEE, AIAA AB In support of the NASA NGATS (Next Generation Air Transportation System) ATM (Air Traffic Management) Airportal Program, a realtime simulation study investigated the changes in roles and responsibilities for tower controllers brought about by the introduction of a new automation tool to achieve precision taxiing. The prototype tool, GoSAFE (Ground Operation, Situation Awareness and Efficiency Flow), is part of a future surface concept. This future surface concept envisages that future surface operations will involve taxi clearances containing precisely timed taxi routes. The study was conducted in two parts: (1) the first phase was used to identify issues with the original control jurisdiction that arose due to the introduction of increased surface traffic and automation in the tower, and (2) the second phase was used to design new areas of jurisdiction in coordination with the introduction of the automation technology and to test this new partnership. Four retired controllers participated in a Human-in-the-Loop real-time simulation study based on the Dallas/Fort Worth (DFW) International Airport (East side only). The controllers interacted with the tool under two conditions - one using datalink and another using voice to issue and deliver clearances to the pilots. Phase-1 data analysis results showed a significant difference in the average workload reported at different controller positions, with the local east controller being particularly busy. Phase-2 data analysis results indicated a more balanced redistribution of workload and communications among the controller positions. Comparison of the two phases has been described in the results section, which includes an analysis of the dependent measures of workload, situation awareness, and nature of communications. Comparison of the two conditions was also done for phase-2, for some of the dependent measures. The results suggested that changes in roles of new automation and human operators will need to be considered when designing procedures. C1 [Verma, Savita] San Jose State Univ, Res Fdn, NASA, San Jose, CA 95192 USA. [Kozon, Thomas] Raytheon, NASA, Moffett Field, CA USA. [Cheng, Victor] Optimal Synth Inc, Palo Alto, CA USA. [Ballinger, Deborah] NASA, Ames Res Ctr, Moffett Field, CA USA. RP Verma, S (reprint author), San Jose State Univ, Res Fdn, NASA, San Jose, CA 95192 USA. EM saverma@mail.arc.nasa.gov; tkozon@mail.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 2155-7195 BN 978-1-4244-1107-8 J9 IEEEAAIA DIGIT AVION PY 2007 BP 1077 EP + PG 2 WC Engineering, Aerospace; Computer Science, Information Systems; Engineering, Electrical & Electronic; Transportation Science & Technology SC Engineering; Computer Science; Transportation GA BHM72 UT WOS:000254342600105 ER PT S AU Han, C Hsu, S Chang, K Huang, J AF Han, C. Hsu, S. Chang, K. Huang, J. GP IEEE TI A Ku/Ka-dual band reflectarray to emulate a cylindrical reflector for titan cloud precipitation radar and altimeter SO 2007 IEEE ANTENNAS AND PROPAGATION SOCIETY INTERNATIONAL SYMPOSIUM, VOLS 1-12 SE IEEE Antennas and Propagation Society International Symposium LA English DT Proceedings Paper CT IEEE Antennas-and-Propagation-Society International Symposium CY JUN 09-15, 2007 CL Honolulu, HI SP IEEE, Antennas & Propagat Soc AB A Ku/Ka dual-band reflectarray* has been developed as a demonstration model for the next generation of Titan Cloud Precipitation Radar and Altimeter (TCPRA). The reflectarray developed is a substitute of a parabolic cylindrical reflector and it is offset-fed by two linear arrays. The antenna has a 50-cm-square aperture and uses two 2-mil thick membranes for both bands enabling transformation into a future larger deployable structure. To show the scanning capability in the cross-track plane, the antenna utilizes the phased array feeds with one for broadside beam and the other for 200 tilted beam along the focal line. Measurement results performed in the indoor anechoic chamber at Texas A&M University will be presented in this paper. C1 [Han, C.; Hsu, S.; Chang, K.] Texas A&M Univ, Dept Elect & Comp Engn, College Stn, TX 77843 USA. [Huang, J.] Jet Prop Lab, Pasadena, CA 91109 USA. RP Han, C (reprint author), Texas A&M Univ, Dept Elect & Comp Engn, College Stn, TX 77843 USA. NR 5 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1522-3965 BN 978-1-4244-0877-1 J9 IEEE ANTENNAS PROP PY 2007 BP 1326 EP + PG 3 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BHS60 UT WOS:000255973400323 ER PT S AU Pogorzelski, RJ Stride, S Venkatesan, J Zawadzki, M AF Pogorzelski, R. J. Stride, S. Venkatesan, J. Zawadzki, M. GP IEEE TI A seven element X-band agile beam receiver SO 2007 IEEE ANTENNAS AND PROPAGATION SOCIETY INTERNATIONAL SYMPOSIUM, VOLS 1-12 SE IEEE Antennas and Propagation Society International Symposium LA English DT Proceedings Paper CT IEEE Antennas-and-Propagation-Society International Symposium CY JUN 09-15, 2007 CL Honolulu, HI SP IEEE, Antennas & Propagat Soc AB We describe the design, fabrication, and testing of a seven element X-band coup. led oscillator based phased array receiver. An array of seven mutually injection locked S-band voltage controlled oscillators provides seven local oscillator signals that are mixed with the signals received by each of seven microstrip patch elements in the aperture. Beam-steering of the receive array is accomplished by inducing the required phase shift in the local oscillator signal associated with each array element. The downconverted in-phase intermediate frequency signals are then summed in a UHF combining network. Frequency doubling of the oscillator signals is employed to extend the scan range. C1 [Pogorzelski, R. J.; Stride, S.; Venkatesan, J.; Zawadzki, M.] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Pogorzelski, RJ (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 5 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1522-3965 BN 978-1-4244-0877-1 J9 IEEE ANTENNAS PROP PY 2007 BP 1767 EP 1770 PG 4 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BHS60 UT WOS:000255973401094 ER PT S AU Lee, RQ Popovic, Z Rondineau, S Miranda, FA AF Lee, Richard Q. Popovic, Zoya Rondineau, Sebastien Miranda, Felix A. GP IEEE TI Steerable space fed lens array for low-cost adaptive ground station applications SO 2007 IEEE ANTENNAS AND PROPAGATION SOCIETY INTERNATIONAL SYMPOSIUM, VOLS 1-12 SE IEEE Antennas and Propagation Society International Symposium LA English DT Proceedings Paper CT IEEE Antennas-and-Propagation-Society International Symposium CY JUN 09-15, 2007 CL Honolulu, HI SP IEEE, Antennas & Propagat Soc C1 [Lee, Richard Q.; Miranda, Felix A.] NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. [Popovic, Zoya; Rondineau, Sebastien] Univ Colorado, Boulder, CO 80309 USA. RP Lee, RQ (reprint author), NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. NR 2 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1522-3965 BN 978-1-4244-0877-1 J9 IEEE ANTENNAS PROP PY 2007 BP 1953 EP 1956 PG 4 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BHS60 UT WOS:000255973401139 ER PT S AU Nessel, JA Simons, RN Miranda, FA AF Nessel, James A. Simons, Rainee N. Miranda, Felix A. GP IEEE TI Near field radiation characteristics of implantable square spiral chip inductor antennas for bio-sensors SO 2007 IEEE ANTENNAS AND PROPAGATION SOCIETY INTERNATIONAL SYMPOSIUM, VOLS 1-12 SE IEEE Antennas and Propagation Society International Symposium LA English DT Proceedings Paper CT IEEE Antennas-and-Propagation-Society International Symposium CY JUN 09-15, 2007 CL Honolulu, HI SP IEEE, Antennas & Propagat Soc C1 [Nessel, James A.; Simons, Rainee N.; Miranda, Felix A.] NASA, GRC, Cleveland, OH 44135 USA. RP Nessel, JA (reprint author), NASA, GRC, Cleveland, OH 44135 USA. NR 9 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1522-3965 BN 978-1-4244-0877-1 J9 IEEE ANTENNAS PROP PY 2007 BP 2940 EP 2943 PG 4 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BHS60 UT WOS:000255973401380 ER PT S AU Johnson, WA Basilio, LI Kotulski, JD Jorgenson, RE Warne, LK Coats, RS Wilton, DR Champagne, NJ Capolino, F Grant, JB Khayat, MA AF Johnson, William A. Basilio, Lorena I. Kotulski, Joseph D. Jorgenson, Roy E. Warne, Larry K. Coats, Rebecca S. Wilton, Donald R. Champagne, Nathan J. Capolino, Filippo Grant, J. Brian Khayat, Michael A. GP IEEE TI EIGER (TM): An open-source frequency-domain electromagnetics code SO 2007 IEEE ANTENNAS AND PROPAGATION SOCIETY INTERNATIONAL SYMPOSIUM, VOLS 1-12 SE IEEE Antennas and Propagation Society International Symposium LA English DT Proceedings Paper CT IEEE Antennas-and-Propagation-Society International Symposium CY JUN 09-15, 2007 CL Honolulu, HI SP IEEE, Antennas & Propagat Soc ID INTEGRALS; AIR C1 [Johnson, William A.; Basilio, Lorena I.; Kotulski, Joseph D.; Jorgenson, Roy E.; Warne, Larry K.; Coats, Rebecca S.] Sandia Natl Labs, Albuquerque, NM 87118 USA. [Wilton, Donald R.] Univ Houston, Houston, TX 77204 USA. [Champagne, Nathan J.] ERC Inc, ESCG JE02, Houston, TX 77258 USA. [Capolino, Filippo] Univ Siena, I-53100 Siena, Italy. [Grant, J. Brian] ANT S, Livermore, CA 94550 USA. [Khayat, Michael A.] NASA, Johnson Space Ctr, Houston, TX 77058 USA. RP Johnson, WA (reprint author), Sandia Natl Labs, Albuquerque, NM 87118 USA. EM wajohns@sandia.gov FU Sandia Corporation, a Lockheed Martin Company, for the United States Department of Energy [DE-AC04-94AL85000] FX Sandia is a multiprogram laboratory operated by Sandia Corporation, a Lockheed Martin Company, for the United States Department of Energy under contract DE-AC04-94AL85000. NR 7 TC 0 Z9 0 U1 0 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1522-3965 BN 978-1-4244-0877-1 J9 IEEE ANTENNAS PROP PY 2007 BP 3065 EP + PG 2 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BHS60 UT WOS:000255973401411 ER PT S AU Scardelletti, MC Jordan, JL Stalker, AR Ponchak, GE AF Scardelletti, Maximilian C. Jordan, Jennifer L. Stalker, Amy R. Ponchak, George E. GP IEEE TI High temperature characterization of alumina substrates and folded slot antenna SO 2007 IEEE ANTENNAS AND PROPAGATION SOCIETY INTERNATIONAL SYMPOSIUM, VOLS 1-12 SE IEEE Antennas and Propagation Society International Symposium LA English DT Proceedings Paper CT IEEE Antennas-and-Propagation-Society International Symposium CY JUN 09-15, 2007 CL Honolulu, HI SP IEEE, Antennas & Propagat Soc C1 [Scardelletti, Maximilian C.; Jordan, Jennifer L.; Stalker, Amy R.; Ponchak, George E.] NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Scardelletti, MC (reprint author), NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. EM Maximilian.C.Scardelletti@nasa.gov NR 5 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1522-3965 BN 978-1-4244-0877-1 J9 IEEE ANTENNAS PROP PY 2007 BP 3480 EP 3483 PG 4 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BHS60 UT WOS:000255973402060 ER PT S AU Jordan, JL Ponchak, GE Tavassolian, N Tentzeris, MM AF Jordan, Jennifer L. Ponchak, George E. Tavassolian, Negar Tentzeris, Manos M. GP IEEE TI Characteristics of a linearly tapered slot antenna (LTSA) conformed longitudinally around a cylinder SO 2007 IEEE ANTENNAS AND PROPAGATION SOCIETY INTERNATIONAL SYMPOSIUM, VOLS 1-12 SE IEEE Antennas and Propagation Society International Symposium LA English DT Proceedings Paper CT IEEE Antennas-and-Propagation-Society International Symposium CY JUN 09-15, 2007 CL Honolulu, HI SP IEEE, Antennas & Propagat Soc C1 [Jordan, Jennifer L.; Ponchak, George E.] NASA, Glenn Res Ctr, Cleveland, OH 44136 USA. [Tavassolian, Negar; Tentzeris, Manos M.] Georgia Inst Technol, Atlanta, GA 30332 USA. RP Jordan, JL (reprint author), NASA, Glenn Res Ctr, Cleveland, OH 44136 USA. EM Jennifer.L.Jordan@nasa.gov NR 3 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1522-3965 BN 978-1-4244-0877-1 J9 IEEE ANTENNAS PROP PY 2007 BP 3516 EP + PG 3 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BHS60 UT WOS:000255973402068 ER PT S AU Chen, C Prather, DW Siegel, PH AF Chen, Caihua Prather, Dennis W. Siegel, Peter H. GP IEEE TI Design of a 600 GHz Fresnel lens antenna for passive and active imaging SO 2007 IEEE ANTENNAS AND PROPAGATION SOCIETY INTERNATIONAL SYMPOSIUM, VOLS 1-12 SE IEEE Antennas and Propagation Society International Symposium LA English DT Proceedings Paper CT IEEE Antennas-and-Propagation-Society International Symposium CY JUN 09-15, 2007 CL Honolulu, HI SP IEEE, Antennas & Propagat Soc AB This paper presents design information and methodology for a high frequency (600 GHZ) Fresnel lens that can significantly reduce the thickness and weight of dielectric based lenses for imaging and spectroscopy applications in the submillimeter wave bands. C1 [Chen, Caihua; Prather, Dennis W.] Univ Delaware, Dept Elect & Comp Engn, Newark, DE 19716 USA. [Siegel, Peter H.] CALTECH, Pasadena, CA 91125 USA. [Siegel, Peter H.] Jet Prop Lab, Pasadena, CA 91125 USA. RP Chen, C (reprint author), Univ Delaware, Dept Elect & Comp Engn, Newark, DE 19716 USA. NR 5 TC 1 Z9 1 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1522-3965 BN 978-1-4244-0877-1 J9 IEEE ANTENNAS PROP PY 2007 BP 3972 EP + PG 2 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BHS60 UT WOS:000255973402176 ER PT S AU Rengarajan, SR Zawadzki, MS Hodges, RE AF Rengarajan, Sembiam R. Zawadzki, Mark S. Hodges, Richard E. GP IEEE TI Bandwidth enhancement of large planar slot arrays SO 2007 IEEE ANTENNAS AND PROPAGATION SOCIETY INTERNATIONAL SYMPOSIUM, VOLS 1-12 SE IEEE Antennas and Propagation Society International Symposium LA English DT Proceedings Paper CT IEEE Antennas-and-Propagation-Society International Symposium CY JUN 09-15, 2007 CL Honolulu, HI SP IEEE, Antennas & Propagat Soc ID SHUNT SLOTS; DESIGN C1 [Rengarajan, Sembiam R.; Zawadzki, Mark S.; Hodges, Richard E.] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Rengarajan, SR (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 8 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1522-3965 BN 978-1-4244-0877-1 J9 IEEE ANTENNAS PROP PY 2007 BP 3992 EP 3995 PG 4 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BHS60 UT WOS:000255973402181 ER PT S AU Nikolaou, S Ponchak, GE Tentzeris, MM Papapolymerou, J AF Nikolaou, Symeon Ponchak, George E. Tentzeris, Manos M. Papapolymerou, John GP IEEE TI Compact cactus-shaped ultra wide-band (UWB) monopole on organic substrate SO 2007 IEEE ANTENNAS AND PROPAGATION SOCIETY INTERNATIONAL SYMPOSIUM, VOLS 1-12 SE IEEE Antennas and Propagation Society International Symposium LA English DT Proceedings Paper CT IEEE Antennas-and-Propagation-Society International Symposium CY JUN 09-15, 2007 CL Honolulu, HI SP IEEE, Antennas & Propagat Soc ID ANTENNA AB The implementation of a novel cactus-shaped monopole antenna that demonstrates an easily controllable return loss and omni-directional radiation patterns in frequency range from 2.9 GHz up to 12 GHz that exceeds the designated ultra wide band (UWB) range is discussed in this paper. The effect of the geometry characteristics on the return loss behavior is briefly explained. The proposed prototype antenna is fabricated on 225 pm thick Liquid Crystal Polymer (LCP) with overall board dimensions of 28 mm x 32mm. C1 [Nikolaou, Symeon; Tentzeris, Manos M.; Papapolymerou, John] Georgia Inst Technol, Sch ECE, Atlanta, GA 30332 USA. [Ponchak, George E.] NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Nikolaou, S (reprint author), Georgia Inst Technol, Sch ECE, Atlanta, GA 30332 USA. EM simos@ece.gatech.edu NR 6 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1522-3965 BN 978-1-4244-0877-1 J9 IEEE ANTENNAS PROP PY 2007 BP 4206 EP + PG 3 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BHS60 UT WOS:000255973402233 ER PT S AU Khayat, MA Wilton, DR Fink, PW AF Khayat, Michael A. Wilton, Donald R. Fink, Patrick W. GP IEEE TI An improved transformation and optimized sampling scheme for the numerical evaluation of singular and near-singular potentials SO 2007 IEEE ANTENNAS AND PROPAGATION SOCIETY INTERNATIONAL SYMPOSIUM, VOLS 1-12 SE IEEE Antennas and Propagation Society International Symposium LA English DT Proceedings Paper CT IEEE Antennas-and-Propagation-Society International Symposium CY JUN 09-15, 2007 CL Honolulu, HI SP IEEE, Antennas & Propagat Soc C1 [Khayat, Michael A.; Fink, Patrick W.] NASA, Johnson Space Ctr, Houston, TX 77058 USA. [Wilton, Donald R.] Univ Houston, Dept Elect & Comp Engn, Houston, TX 77204 USA. RP Khayat, MA (reprint author), NASA, Johnson Space Ctr, Houston, TX 77058 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 1522-3965 BN 978-1-4244-0877-1 J9 IEEE ANTENNAS PROP PY 2007 BP 4405 EP + PG 2 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BHS60 UT WOS:000255973402282 ER PT S AU Fink, PW Wilton, DR Khayat, MA AF Fink, Patrick W. Wilton, Donald R. Khayat, Michael A. GP IEEE TI Simple and efficient numerical evaluation of near-hypersingular integrals SO 2007 IEEE ANTENNAS AND PROPAGATION SOCIETY INTERNATIONAL SYMPOSIUM, VOLS 1-12 SE IEEE Antennas and Propagation Society International Symposium LA English DT Proceedings Paper CT IEEE Antennas-and-Propagation-Society International Symposium CY JUN 09-15, 2007 CL Honolulu, HI SP IEEE, Antennas & Propagat Soc C1 [Fink, Patrick W.; Khayat, Michael A.] NASA, Lyndon B Johnson Space Ctr, Electromagnet Syst Branch, Houston, TX 77058 USA. [Wilton, Donald R.] Univ Houston, Dept Elect & Comp Engn, Houston, TX 77204 USA. RP Fink, PW (reprint author), NASA, Lyndon B Johnson Space Ctr, Electromagnet Syst Branch, Houston, TX 77058 USA. NR 5 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1522-3965 BN 978-1-4244-0877-1 J9 IEEE ANTENNAS PROP PY 2007 BP 4409 EP + PG 2 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BHS60 UT WOS:000255973402283 ER PT S AU Rajagopalan, H Rahmat-Samii, Y Imbriale, WA AF Rajagopalan, Harish Rahmat-Samii, Yahya Imbriale, William A. GP IEEE TI Reconfigurable patch-slot reflectarray elements using RE MEMS switches: A subreflector wavefront controller SO 2007 IEEE ANTENNAS AND PROPAGATION SOCIETY INTERNATIONAL SYMPOSIUM, VOLS 1-12 SE IEEE Antennas and Propagation Society International Symposium LA English DT Proceedings Paper CT IEEE Antennas-and-Propagation-Society International Symposium CY JUN 09-15, 2007 CL Honolulu, HI SP IEEE, Antennas & Propagat Soc C1 [Rajagopalan, Harish; Rahmat-Samii, Yahya] Univ Calif Los Angeles, Dept Elect Engn, Los Angeles, CA 90095 USA. [Imbriale, William A.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Rajagopalan, H (reprint author), Univ Calif Los Angeles, Dept Elect Engn, Los Angeles, CA 90095 USA. EM harish@ee.ucla.edu; rahmat@ee.ucla.edu; imbriale@jpl.nasa.gov FU Jet Propulsion Laboratory; California Institute of Technology; National Aeronautics and Space Administration FX This work was supported in part by the Jet Propulsion Laboratory, California Institute of Technology, under a contract with the National Aeronautics and Space Administration. 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 1522-3965 BN 978-1-4244-0877-1 J9 IEEE ANTENNAS PROP PY 2007 BP 4736 EP 4739 PG 4 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BHS60 UT WOS:000255973403034 ER PT S AU Yang, F Kirn, Y Huang, J Elsherbeni, A AF Yang, Fan Kirn, Yanghyo Huang, John Elsherbeni, Atef GP IEEE TI A single-layer tri-band reflectarray antenna design SO 2007 IEEE ANTENNAS AND PROPAGATION SOCIETY INTERNATIONAL SYMPOSIUM, VOLS 1-12 SE IEEE Antennas and Propagation Society International Symposium LA English DT Proceedings Paper CT IEEE Antennas-and-Propagation-Society International Symposium CY JUN 09-15, 2007 CL Honolulu, HI SP IEEE, Antennas & Propagat Soc ID VARIABLE ROTATION ANGLES; ELEMENTS; PATCHES C1 [Yang, Fan; Kirn, Yanghyo; Elsherbeni, Atef] Univ Mississippi, Dept Elect Engn, University, MS 38677 USA. [Huang, John] CALTECH, Jet Propulsion Lab, Pasadena, CA 91109 USA. RP Yang, F (reprint author), Univ Mississippi, Dept Elect Engn, University, MS 38677 USA. EM fyang@olemiss.edu; yhkim@olemiss.edu; john.huang@ipl.nasa.gov; atef@olemiss.edu NR 7 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1522-3965 BN 978-1-4244-0877-1 J9 IEEE ANTENNAS PROP PY 2007 BP 4837 EP + PG 3 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BHS60 UT WOS:000255973403059 ER PT S AU Xu, SH Rajagopalan, H Rahmat-Samii, Y Imbriale, WA AF Xu, Shenheng Rajagopalan, Harish Rahmat-Samii, Yahya Imbriale, William A. GP IEEE TI A novel reflector surface distortion compensating technique using a sub-reflectarray SO 2007 IEEE ANTENNAS AND PROPAGATION SOCIETY INTERNATIONAL SYMPOSIUM, VOLS 1-12 SE IEEE Antennas and Propagation Society International Symposium LA English DT Proceedings Paper CT IEEE Antennas-and-Propagation-Society International Symposium CY JUN 09-15, 2007 CL Honolulu, HI SP IEEE, Antennas & Propagat Soc C1 [Xu, Shenheng; Rajagopalan, Harish; Rahmat-Samii, Yahya] Univ Calif Los Angeles, Dept Elect Engn, Los Angeles, CA 90095 USA. [Imbriale, William A.] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Xu, SH (reprint author), Univ Calif Los Angeles, Dept Elect Engn, Los Angeles, CA 90095 USA. EM shxu@ee.ucla.edu; rharish@ucla.edu; rahmat@ee.ucla.edu; imbriale@jpl.nasa.gov FU Jet Propulsion Laboratory, California Institute of Technology; National Aeronautics and Space Administration FX This work was supported in part by the Jet Propulsion Laboratory, California Institute of Technology, under a contract with the National Aeronautics and Space Administration. NR 6 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1522-3965 BN 978-1-4244-0877-1 J9 IEEE ANTENNAS PROP PY 2007 BP 4845 EP + PG 3 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BHS60 UT WOS:000255973403061 ER PT S AU Cable, VP AF Cable, Vaughn P. GP IEEE TI Subarray aperture focusing for power beaming SO 2007 IEEE ANTENNAS AND PROPAGATION SOCIETY INTERNATIONAL SYMPOSIUM, VOLS 1-12 SE IEEE Antennas and Propagation Society International Symposium LA English DT Proceedings Paper CT IEEE Antennas-and-Propagation-Society International Symposium CY JUN 09-15, 2007 CL Honolulu, HI SP IEEE, Antennas & Propagat Soc C1 [Cable, Vaughn P.] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Cable, VP (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 5 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1522-3965 BN 978-1-4244-0877-1 J9 IEEE ANTENNAS PROP PY 2007 BP 5369 EP 5372 PG 4 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BHS60 UT WOS:000255973403189 ER PT S AU Saha, B Goebel, K Poll, S Christophersen, J AF Saha, Bhaskar Goebel, Kai Poll, Scott Christophersen, Jon GP IEEE TI An integrated approach to battery health monitoring using Bayesian regression and state estimation SO 2007 IEEE AUTOTESTCON, VOLS 1 AND 2 SE IEEE Autotestcon LA English DT Proceedings Paper CT 42nd Annual AUTOTESTCON Conference CY SEP 17-20, 2007 CL Baltimore, MD SP IEEE Aerosp & Elect Syst Soc, IEEE Instrumentat & Measurement Soc ID HYBRID-ELECTRIC VEHICLES; LEAD-ACID-BATTERIES; OF-CHARGE AB The application of the Bayesilan theory of managing uncertainty and complexity to regression and classification in the form of Relevance Vector Machine (RVM), and to state estimation via Particle Filters (PF), proves to be a powerful tool to integrate the diagnosis and prognosis of battery health. Accurate estimates of the state-of-charge (OC), the state-of-health (SOH) and state-of-life(SOL) for batteries provide a significant value addition to the management of any operation involving electrical systems. This is especially true for aerospace systems, where unanticipated battery performance may lead to catastrophic failures. Batteries, composed of multiple electrochemical cells, are complex systems whose internal state variables are either inaccessible to sensors or hard to measure under operational conditions. In addition, battery performance is strongly influenced by ambient environmental and load conditions. Consequently, inference and estimation techniques need to be applied on indirect measurements, anticipated operational conditions and historical data, for which a Bayeslan statistical approach is suitable. Accurate models of electro-chemical processes in the form of equivalent electric circuit parameters need to be combined with statistical models of state transitions, aging processes and measurement fidelity, need to be combined in a formal framework to make the approach viable. The RVM, which is a Bayesian treatment of the Support Vector Machine (SVM), is used for diagnosis as well as for model development. The PF framework uses this model and statistical estimates of the noise in the system and anticipated operational conditions to provide estimates of SOC, SOH and SOL. Validation of this approach on experimental data from Li-ion batteries is presented. C1 [Saha, Bhaskar] Georgia Inst Technol, 777 Atlant Dr, Atlanta, GA 30332 USA. [Goebel, Kai; Poll, Scott] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Christophersen, Jon] Idaho Natl Lab, Idaho Falls, ID 83415 USA. RP Saha, B (reprint author), Georgia Inst Technol, 777 Atlant Dr, Atlanta, GA 30332 USA. EM bsaha@ece.gatech.edu; goebel@email.arc.ness.gov; spoll@email.arc.nasa.gov; Jon.Christophersen@inl.gov NR 15 TC 40 Z9 44 U1 4 U2 24 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1088-7725 BN 978-1-4244-1238-9 J9 IEEE AUTOTESTCON PY 2007 BP 646 EP + DI 10.1109/AUTEST.2007.4374280 PG 3 WC Automation & Control Systems; Computer Science, Software Engineering; Computer Science, Theory & Methods; Engineering, Electrical & Electronic SC Automation & Control Systems; Computer Science; Engineering GA BHI79 UT WOS:000253448600087 ER PT S AU Angelova, A Matthies, L Helmick, D Perona, P AF Angelova, Anelia Matthies, Larry Helmick, Daniel Perona, Pietro GP IEEE TI Fast terrain classification using variable-length representation for autonomous navigation SO 2007 IEEE CONFERENCE ON COMPUTER VISION AND PATTERN RECOGNITION, VOLS 1-8 SE IEEE Conference on Computer Vision and Pattern Recognition LA English DT Proceedings Paper CT IEEE Conference on Computer Vision and Pattern Recognition CY JUN 17-22, 2007 CL Minneapolis, MN SP IEEE, hp invent, INI-GraphicsNet, VIOSO AB We propose a method for learning using a set of feature representations which retrieve different amounts of information at different costs. The goal is to create a more efficient terrain classification algorithm which can be used in real-time, onboard an autonomous vehicle. Instead of building a monolithic classifier with uniformly complex representation for each class, the main idea here is to actively consider the labels or misclassification cost while constructing the classifier For example, some terrain classes might be easily separable from the rest, so very simple representation will be sufficient to learn and detect these classes. This is taken advantage of during learning, so the algorithm automatically builds a variable-length visual representation which varies according to the complexity of the classification task This enables fast recognition of different terrain types during testing. We also show how to select a set of feature representations so that the desired terrain classification task is accomplished with high accuracy and is at the same time efficient. The proposed approach achieves a good trade-off between recognition performance and speedup on data collected by an autonomous robot. C1 [Angelova, Anelia; Perona, Pietro] CALTECH, Dept Comp Sci, Pasadena, CA 91125 USA. [Matthies, Larry; Helmick, Daniel] CALTECH, Jet Propuls Lab, Pasadena, CA 91125 USA. RP Angelova, A (reprint author), CALTECH, Dept Comp Sci, Pasadena, CA 91125 USA. EM anelia@caltech.edu; perona@caltech.edu; lhm@jpl.nasa.gov; dhelmick@jpl.nasa.gov FU NASA's Mars Technology Program FX This research was carried out by the Jet Propulsion Laboratory, California Institute of Technology with funding from the NASA's Mars Technology Program. We thank Max Bajracharya and the anonymous reviewers for providing very useful comments on the paper. NR 18 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1063-6919 BN 978-1-4244-1179-5 J9 PROC CVPR IEEE PY 2007 BP 414 EP + PG 2 WC Computer Science, Software Engineering; Mathematical & Computational Biology; Remote Sensing; Imaging Science & Photographic Technology SC Computer Science; Mathematical & Computational Biology; Remote Sensing; Imaging Science & Photographic Technology GA BGT02 UT WOS:000250382800056 ER PT S AU Eastman, RD Le Moigne, J Netanyahu, NS AF Eastman, Roger D. Le Moigne, Jacqueline Netanyahu, Nathan S. GP IEEE TI Research issues in image registration for remote sensing SO 2007 IEEE CONFERENCE ON COMPUTER VISION AND PATTERN RECOGNITION, VOLS 1-8 SE IEEE Conference on Computer Vision and Pattern Recognition LA English DT Proceedings Paper CT IEEE Conference on Computer Vision and Pattern Recognition CY JUN 17-22, 2007 CL Minneapolis, MN SP IEEE, hp invent, INI-GraphicsNet, VIOSO ID SUBPIXEL REGISTRATION; SENSED IMAGERY; PERFORMANCE; MISREGISTRATION; CALIBRATION; ACCURACY AB Image registration is an important element in data processing for remote sensing with many applications and a wide range of solutions. Despite considerable investigation the field has not settled on a definitive solution for most applications and a number of questions remain open. This article looks at selected research issues by surveying the experience of operational satellite teams, application-specific requirements for Earth science, and our experiments in the evaluation of image registration algorithms with emphasis on the comparison of algorithms for subpixel accuracy. We conclude that remote sensing applications put particular demands on image registration algorithms to take into account domain-specific knowledge of geometric transformations and image content. C1 [Eastman, Roger D.] Loyola Coll, Baltimore, MD 21210 USA. [Le Moigne, Jacqueline] NASA, Goddard Space Flight Ctr, Greenbelt, MD USA. [Netanyahu, Nathan S.] Bar Ilan Univ, Ramat Gan, Israel. [Netanyahu, Nathan S.] Univ Maryland, College Pk, MD USA. RP Eastman, RD (reprint author), Loyola Coll, Baltimore, MD 21210 USA. EM reastman@loyola.edu; Jacqueline.LeMoigne@nasa.gov; nathan@cfar.umd.edu NR 35 TC 2 Z9 2 U1 0 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1063-6919 BN 978-1-4244-1179-5 J9 PROC CVPR IEEE PY 2007 BP 3233 EP + PG 3 WC Computer Science, Software Engineering; Mathematical & Computational Biology; Remote Sensing; Imaging Science & Photographic Technology SC Computer Science; Mathematical & Computational Biology; Remote Sensing; Imaging Science & Photographic Technology GA BGT02 UT WOS:000250382806048 ER PT B AU Lohn, JD Kraus, WF Hornby, GS AF Lohn, Jason D. Kraus, William F. Hornby, Gregory S. GP IEEE TI Automated design of a MEMS resonator SO 2007 IEEE CONGRESS ON EVOLUTIONARY COMPUTATION, VOLS 1-10, PROCEEDINGS SE IEEE Congress on Evolutionary Computation LA English DT Proceedings Paper CT IEEE Congress on Evolutionary Computation CY SEP 25-28, 2007 CL Singapore, SINGAPORE SP IEEE AB As the application and complexity of microelectromechanical (MEMS) devices increases, there is a corresponding need for automated design and optimization tools to augment engineers' design skills. Evolutionary computation provides a set of tools that may prove very effective in this application domain. Here we present a novel evolutionary computation encoding scheme for specifying MEMS designs, and use this scheme to evolve a MEMS meandering resonator. Using fewer evaluations, we are able to evolve designs that perform as well as those previous reported. C1 [Lohn, Jason D.] Carnegie Mellon Univ, W Campus Bldg 23,5000 Forbes Ave, Pittsburgh, PA 15213 USA. [Kraus, William F.; Hornby, Gregory S.] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Kraus, William F.; Hornby, Gregory S.] Univ Calif Santa Cruz, Moffett Field, CA 94035 USA. RP Lohn, JD (reprint author), Carnegie Mellon Univ, W Campus Bldg 23,5000 Forbes Ave, Pittsburgh, PA 15213 USA. EM jlohn@west.cmu.edu; bkraus@email.aic.nasa.gov; homby@email.aic.nasa.gov FU NASA Ames Research Center [NNX07AE45A] FX This work was supported in part by NASA Ames Research Center grant NNX07AE45A NR 10 TC 5 Z9 5 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-1339-3 J9 IEEE C EVOL COMPUTAT PY 2007 BP 3486 EP + DI 10.1109/CEC.2007.4424924 PG 2 WC Computer Science, Artificial Intelligence; Computer Science, Theory & Methods SC Computer Science GA BHT10 UT WOS:000256053702081 ER PT B AU Hancher, MD Horriby, GS AF Hancher, Matthew D. Horriby, Gregory S. GP IEEE TI Evolving quadruped gaits with a heterogeneous modular robotic system SO 2007 IEEE CONGRESS ON EVOLUTIONARY COMPUTATION, VOLS 1-10, PROCEEDINGS SE IEEE Congress on Evolutionary Computation LA English DT Proceedings Paper CT IEEE Congress on Evolutionary Computation CY SEP 25-28, 2007 CL Singapore, SINGAPORE SP IEEE ID SELF-RECONFIGURATION; SPACE AB There has been much research into the development of robotic controllers in educational, industrial and government research labs, but limited hardware budgets constrain the types of morphologies in which researchers can experiment with. One option is to use LEGO components or other toy-grade kits, but these have well-known limitations. Here we present a heterogeneous modular robotic platform that can be reconfigured to a wide variety of robot morphologies, such as legged robots and manipulator arms. In addition, we have developed a simulation environment for our modules allowing for the artificial evolution, or learning, of behaviors to occur in simulation for transfer to reality. We demonstrate the effectiveness of our system by evolving a quadruped gait in simulation which successfully transfers to a hardware version of this robot. C1 [Hancher, Matthew D.] NASA, Ames Res Ctr, Intelligent Syst Div, Mail Stop 269-3, Moffett Field, CA 94035 USA. [Horriby, Gregory S.] Univ Calif Santa Cruz, Santa Cruz, CA USA. RP Hancher, MD (reprint author), NASA, Ames Res Ctr, Intelligent Syst Div, Mail Stop 269-3, Moffett Field, CA 94035 USA. EM mdh@email.arc.nasa.gov; hornby@email.arc.nasa.gov NR 35 TC 1 Z9 1 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-1339-3 J9 IEEE C EVOL COMPUTAT PY 2007 BP 3631 EP + DI 10.1109/CEC.2007.4424943 PG 2 WC Computer Science, Artificial Intelligence; Computer Science, Theory & Methods SC Computer Science GA BHT10 UT WOS:000256053702100 ER PT B AU Worth, R Pater, RH Islam, M Smith, C AF Worth, Richard Pater, Ruth H. Islam, Moni Smith, Charles GP IEEE TI Insulated bus pipe (IBP) for shipboard applications SO 2007 IEEE ELECTRIC SHIP TECHNOLOGIES SYMPOSIUM LA English DT Proceedings Paper CT IEEE Electric Ship Technologies Symposium (ESTS 2007) CY MAY 21-23, 2007 CL Arlington, VA SP Power Engn Soc, Power Elect Soc, Ind Applicat Soc, Ocean Engn Soc, Dielect & Elect Insulat Soc, Vehicular Technol Soc, Inst Marine Engn Sci & Technol, Amer Assoc Naval Engineers AB The commercial shipbuilding industry and the U.S. Navy have decreed that the aim of the "All Electric Ship" power system design will be for survivability and continuity of electrical power supply. In general, ship service electric power and electric propulsion power requirements are approaching hundreds of megawatts. There are major challenges to the use of standard cable at medium voltage levels onboard due to cable stiffness, and cable bend radius requirements for distributing very high current around the ship. This paper examines the practical design and installation benefits associated with IBP as a possible alternative to shipboard electric power cable. Although IBP? is widely used in the utility industry, the shipboard use of IBP is limited to several passenger cruise ships. IBP is considered a more efficient medium & high voltage transmission line over cable for Integrated Power System (IPS) ships due to cable size, quantity, and installation time. There are technical issues that must be resolved before advocating the use of IBP onboard Navy ships. This paper presents an overview of IBP technology, examines IBP technical issues and presents probable solutions for Navy and commercial shipboard applications. One of the probable solutions that are discussed is a new type of insulating material for IBP that should significantly enhance the Navy 3 hour gas flame circuit integrity flame test withstand capability. This paper recommends that the proven IBP prototypes and their models be the procurement specifications. The paper also recommends: Inclusion of IBP application recommended practices in shipbuilding standards such as IEEE-45 and IEEE-1580 Inclusion of IBP in ABS rules for commercial ships, ABS NVR for naval vessels, and other national and international shipbuilding rules and regulations. C1 [Worth, Richard] NSWCCD NAVSEA, Philadelphia, PA 19112 USA. [Islam, Moni] Northrop Grumman Ship Syst, Avondale, PA 70094 USA. [Smith, Charles] Northrop Grumman Newport News, Newport News, VA 92886 USA. [Pater, Ruth H.] NASA Langley Res Ctr, Hampton, VA 23666 USA. RP Worth, R (reprint author), NSWCCD NAVSEA, Philadelphia, PA 19112 USA. EM Richard.worth@navy.mil; Ruth.H.Pater@NASA.GOV; Moni.islam@ngc.com; Charies.smith@ngc.com NR 5 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-0946-4 PY 2007 BP 122 EP + DI 10.1109/ESTS.2007.372074 PG 3 WC Engineering, Ocean; Engineering, Electrical & Electronic SC Engineering GA BGQ89 UT WOS:000249858800019 ER PT B AU Barsoum, MF Moision, B Fitz, M Divsalar, D Hamkins, J AF Barsoum, Maged F. Moision, Bruce Fitz, Michael Divsalar, Dariush Hamkins, Jon GP IEEE TI Iterative coded pulse-position-modulation for deep-space optical communications SO 2007 IEEE INFORMATION THEORY WORKSHOP, VOLS 1 AND 2 LA English DT Proceedings Paper CT IEEE Information Theory Workshop CY SEP 02-06, 2007 CL Tahoe City, CA SP IEEE ID PARITY-CHECK CODES; CHANNEL; CONVERGENCE; CAPACITY; DESIGN AB This paper presents and compares two iterative coded modulation techniques for deep-space optical communications using pulse-position modulation (PPM). The first code, denoted by SCPPM, consists of the serial concatenation of an outer convolutional code, an interleaver, a bit accumulator, and PPM. The second code, denoted by LDPC-PPM, consists of the serial concatenation of an LDPC code and PPM. We employ Extrinsic Information Transfer (EXIT) charts for their analysis and design. Under conditions typical of a communications link from Mars to Earth, SCPPM is 1 dB away from capacity, while LDPC-PPM is 1.4 dB away from capacity, at a Bit Error Rate (BER) of approximately 10(-5). However, LDPC-PPM lends itself naturally to low latency parallel processing in contrast to SCPPM. C1 [Barsoum, Maged F.; Moision, Bruce; Divsalar, Dariush; Hamkins, Jon] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Fitz, Michael] Univ Calif Los Angeles, Dept Elect Engn, Los Angeles, CA 90095 USA. RP Barsoum, MF (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM mbarsoum@jpl.nasa.gov; bmoision@jpl.nasa.gov; fitz@ee.ucla.edu; Dariush.Divsalar@jpl.nasa.gov; jon.hamkins@jpl.nasa.gov NR 20 TC 2 Z9 2 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-1563-2 PY 2007 BP 66 EP + DI 10.1109/ITW.2007.4313051 PG 2 WC Computer Science, Information Systems; Computer Science, Theory & Methods; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BHI73 UT WOS:000253441300012 ER PT B AU Song, SM Lin, S Abdel-Ghaffar, K Fong, WH AF Song, Shumei Lin, Shu Abdel-Ghaffar, Khaled Fong, Wai H. GP IEEE TI Erasure-burst and error-burst decoding of linear codes SO 2007 IEEE INFORMATION THEORY WORKSHOP, VOLS 1 AND 2 LA English DT Proceedings Paper CT IEEE Information Theory Workshop CY SEP 02-06, 2007 CL Tahoe City, CA SP IEEE ID PARITY-CHECK CODES; CHANNEL AB Iterative algorithms for decoding over erasure-burst channels have attracted much interest lately due to their simplicity. Although the performance of these techniques is typically good, it may not be optimal if the underlying matrix used for decoding is not properly chosen. In this paper, we construct matrices that lead to optimal performance when used with iterative decoding over erasure-burst channels. We also develop a simple decoding technique that makes use of these same matrices to decode any linear code over error-burst channels. For cyclic codes, this algorithm is optimal. C1 [Song, Shumei; Lin, Shu; Abdel-Ghaffar, Khaled] Univ Calif Davis, Dept Elect & Comp Engn, Davis, CA 95616 USA. [Fong, Wai H.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Song, SM (reprint author), Univ Calif Davis, Dept Elect & Comp Engn, Davis, CA 95616 USA. EM ssmsong@ece.ucdavis.edu; shulin@ece.ucdavis.edu; ghaffar@ece.ucdavis.edu; wai.fong@gsfc.nasa.gov FU NASA [NNG05GD13G]; Northrop Grumman Space Technology FX This work was supported by NASA under Grant NNG05GD13G and a gift from Northrop Grumman Space Technology. NR 10 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-1563-2 PY 2007 BP 132 EP + DI 10.1109/ITW.2007.4313062 PG 2 WC Computer Science, Information Systems; Computer Science, Theory & Methods; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BHI73 UT WOS:000253441300023 ER PT B AU Jones, C Dolinar, S Andrews, K Divsalar, D Zhang, Y Ryan, W AF Jones, C. Dolinar, S. Andrews, K. Divsalar, D. Zhang, Y. Ryan, W. GP IEEE TI Functions and architectures for LDPC decoding SO 2007 IEEE INFORMATION THEORY WORKSHOP, VOLS 1 AND 2 LA English DT Proceedings Paper CT IEEE Information Theory Workshop CY SEP 02-06, 2007 CL Tahoe City, CA SP IEEE ID PARITY-CHECK CODES AB Implementation of belief propagation for low-density parity-check codes involves selection of functions possessing manageable dynamic range, topologic considerations for aggregation of these functions such that nodes of varying degree can be efficiently realized, and message passing architectures that offer various alternatives for flexibility and throughput. This paper discusses each of these topics and contrasts optimal and sub-optimal techniques where appropriate. In particular, optimal functions for producing extrinsic messages in the absence of an inverse function are described and compared to sub-optimal approaches that do not compute a full set of extrinsic messages. In addition we describe structured and universal message passing architectures and discuss scenarios where application of each may be appropriate. C1 [Jones, C.; Dolinar, S.; Andrews, K.; Divsalar, D.] Jet Propuls Lab, Pasadena, CA 91109 USA. [Zhang, Y.; Ryan, W.] Univ Arizona, Elect & Comp Engn, Tucson, AZ 85721 USA. RP Jones, C (reprint author), Jet Propuls Lab, Pasadena, CA 91109 USA. EM crjones@jpl.nasa.gov; sdolinar@jpl.nasa.gov; andrews@jpl.nasa.gov; dariush@jpl.nasa.gov; yifei@ece.arizona.edu; ryan@ece.arizona.edu NR 19 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-1563-2 PY 2007 BP 577 EP + DI 10.1109/ITW.2007.4313138 PG 2 WC Computer Science, Information Systems; Computer Science, Theory & Methods; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BHI73 UT WOS:000253441300099 ER PT S AU Angrisani, L D'Arco, M Greenhall, C Lo Moriello, RS AF Angrisani, Leopoldo D'Arco, Mauro Greenhall, Charles Lo Moriello, Rosario Schiano GP IEEE TI Enlarging the input frequency range of a phase noise meter through bandpass sampling strategies SO 2007 IEEE INSTRUMENTATION & MEASUREMENT TECHNOLOGY CONFERENCE, VOLS 1-5 SE IEEE Instrumentation and Measurement Technology Conference LA English DT Proceedings Paper CT 24th IEEE Instrumentation and Measurement Technology Conference CY MAY 01-03, 2007 CL Warsaw, POLAND SP IEEE DE phase noise measurement; phase noise meter; quadrature demodulation; bandpass sampling; bandwidth enlargement AB Measurement of phase noise affecting oscillators or clocks is a fundamental practice whenever the need of a reliable time-base is of primary concern. In spite of the number of methods or techniques either available in literature or implemented as personalities in general purpose equipment, very accurate measurement results can be gained only from expensive, dedicated instruments. To offer a cost-effective alternative to dedicated instruments, the authors have already realized a DSP-based phase noise meter, capable of assuring high performance and real-time operation. The meter, however, suffers from a reduced analysis bandwidth (about 250 kHz) and needs an external time-base for input signal digitization. To overcome these drawbacks, the authors propose hereinafter the adoption both of bandpass sampling strategies and internal time-base. After some remarks on the previous version of the meter, key features of the adopted time-base and proposed sampling strategy are described in detail. Results of experimental tests, carried out on sinusoidal signals provided both by function and arbitrary waveform generators, are presented and discussed; evidence of the meter's reliability and efficacy is finally given. C1 [Angrisani, Leopoldo; Lo Moriello, Rosario Schiano] Univ Naples Federico II, Dipartimento Informat & Sistemist, Via Claudio 21, I-80125 Naples, Italy. [D'Arco, Mauro] Univ Naples Federico II, Dipartimento Ingn Elettr, I-80125 Naples, Italy. [Greenhall, Charles] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Angrisani, L (reprint author), Univ Naples Federico II, Dipartimento Informat & Sistemist, Via Claudio 21, I-80125 Naples, Italy. EM angrisan@unina.it; darco@unina.it; rschiano@unina.it; cgreenhall@jpl.nasa.gov NR 13 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1091-5281 BN 978-1-4244-0588-6 J9 IEEE IMTC P PY 2007 BP 2351 EP + PG 2 WC Automation & Control Systems; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Nanoscience & Nanotechnology; Instruments & Instrumentation; Robotics; Remote Sensing SC Automation & Control Systems; Computer Science; Engineering; Science & Technology - Other Topics; Instruments & Instrumentation; Robotics; Remote Sensing GA BGY21 UT WOS:000251296802076 ER PT S AU Case, JT Kharkovsky, S Zoughi, R Hepburn, F AF Case, J. T. Kharkovsky, S. Zoughi, R. Hepburn, F. GP IEEE TI High resolution millimeter wave inspecting of the Orbiter acreage heat tiles of the Space Shuttle SO 2007 IEEE INSTRUMENTATION & MEASUREMENT TECHNOLOGY CONFERENCE, VOLS 1-5 SE IEEE Instrumentation and Measurement Technology Conference LA English DT Proceedings Paper CT 24th IEEE Instrumentation and Measurement Technology Conference CY MAY 01-03, 2007 CL Warsaw, POLAND SP IEEE DE millimeter waves; high resolution; nondestructive inspecting; space shuttle; heat tiles AB The physical cause of Space Shuttle Columbia's catastrophic failure was a breach in its thermal protection system, caused by a piece of External Tank insulating foam (SOFI) separating from the External Tank and striking the leading edge of the left wing of the Orbiter. Consequently, there is an urgent need for a rapid, robust and life-circle oriented nondestructive testing (NDT) technique capable of inspecting the SOFI as well as the Orbiter's protective heat tiles and its fuselage prior and subsequent to a launch. Microwave and millimeter wave NDT methods have shown great potential to achieve these goals using real focused reflectometer techniques and synthetic aperture focused techniques. This paper presents recent results of an investigation for the purpose of detecting anomalies such as debonds and corrosion in the structurally complex multi-sectioned protective heat tiles using a real focused 150 GHz (D-band) reflectometer and wide-band millimeter wave holography at 18-26.5 GHz (K-band) and 33-50 GHz (Q-band). The results of these investigations clearly show the utility of millimeter wave NDT methods for detecting such anomalies. Both methods provide a significant amount of information about the nature of an anomaly including size and location. C1 [Case, J. T.; Kharkovsky, S.; Zoughi, R.] Univ Missouri, Dept Elect & Comp Engn, Appl Microwave Nondestruct Testing Lab, Rolla, MO 65409 USA. [Hepburn, F.] NASA, George C Marshall Space Flight Ctr, Huntsville, AL 35812 USA. RP Case, JT (reprint author), Univ Missouri, Dept Elect & Comp Engn, Appl Microwave Nondestruct Testing Lab, Rolla, MO 65409 USA. FU NASA; Marshall Space Flight Center (MSFC); Huntsville, Alabama, USA FX Funding for this work has been provided through a cooperative agreement with the NASA Marshall Space Flight Center (MSFC), Huntsville, Alabama, USA. NR 6 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1091-5281 BN 978-1-4244-0588-6 J9 IEEE IMTC P PY 2007 BP 2437 EP + PG 2 WC Automation & Control Systems; Computer Science, Interdisciplinary Applications; Engineering, Electrical & Electronic; Nanoscience & Nanotechnology; Instruments & Instrumentation; Robotics; Remote Sensing SC Automation & Control Systems; Computer Science; Engineering; Science & Technology - Other Topics; Instruments & Instrumentation; Robotics; Remote Sensing GA BGY21 UT WOS:000251296802093 ER PT S AU Chowdhury, PK Reaz, AS Atiquzzaman, M Ivancic, W AF Chowdhury, Pulak K. Reaz, Abu S. Atiquzzaman, Mohammed Ivancic, William GP IEEE TI Performance analysis of SINEMO: Seamless IP-diversity based NEtwork MObility SO 2007 IEEE INTERNATIONAL CONFERENCE ON COMMUNICATIONS, VOLS 1-14 SE IEEE International Conference on Communications LA English DT Proceedings Paper CT IEEE International Conference on Communications (ICC 2007) CY JUN 24-28, 2007 CL Glasgow, SCOTLAND SP IEEE ID ROUTE OPTIMIZATION; NEMO AB IETF has proposed Mobile IPv6-based Network Mobility (NEMO) basic support protocol (BSP) to support network mobility. NEMO BSP inherits all the drawbacks of Mobile IPv6, such as inefficient routing path, single point of failure, high handover latency and packet loss, and high packet overhead. To address these drawbacks, we proposed an IP diversity-based network mobility management scheme called Seamless IP-diversity based NEtwork MObility (SINEMO). In this paper, we develop analytical models to analyze and compare the performance of SINEMO and NEMO BSP. Our analysis shows that SINEMO enhances the performance of network mobililty compared to NEMO BSP. We have implemented a testbed for SINEMO to support our claim of SINEMO's high performance. C1 [Chowdhury, Pulak K.; Reaz, Abu S.; Atiquzzaman, Mohammed] Univ Oklahoma, Sch Comp Sci, Norman, OK 73019 USA. [Ivancic, William] NASA, Glenn Res Ctr, Satellite Networks & Architectures Branch, Cleveland, OH 44135 USA. RP Chowdhury, PK (reprint author), Univ Oklahoma, Sch Comp Sci, Norman, OK 73019 USA. EM pulak@ou.edu; sayeem_reaz@ou.edu; atiq@ou.edu; wivancic@grc.nasa.gov FU NASA [NAG3-2922] FX The research reported in this paper was funded by NASA Grant NAG3-2922. NR 11 TC 5 Z9 5 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1550-3607 BN 978-1-4244-0352-3 J9 IEEE ICC PY 2007 BP 6032 EP + DI 10.1109/ICC.2007.999 PG 2 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BIA16 UT WOS:000257882504059 ER PT S AU Lei, SL Palazzolo, A Kascak, A AF Lei, Shuliang Palazzolo, Alan Kascak, Albert GP IEEE TI Fuzzy logic intelligent control system of magnetic bearings SO 2007 IEEE INTERNATIONAL CONFERENCE ON FUZZY SYSTEMS, VOLS 1-4 SE IEEE International Conference on Fuzzy Systems LA English DT Proceedings Paper CT IEEE International Conference on Fuzzy Systems CY JUL 23-26, 2007 CL London, ENGLAND SP IEEE AB This paper presents a fuzzy logic based intelligent control system applied to magnetic bearings. The core in the expert system is fuzzy logic controllers with Mamdani architecture. The fuzzy logic controllers for rub detection and automatic gain scheduling were implemented. The expert system not only provides a means to capture the run time data of the magnetic bearings, to process and monitor the parameters, and to diagnose malfunctions, but also protects the magnetic bearings from rub anomaly and implements the control on a real time basis. C1 [Lei, Shuliang; Kascak, Albert] NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. [Palazzolo, Alan] Texas A&M Univ, Dept Engn Mech, College Stn, TX 77843 USA. RP Lei, SL (reprint author), NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. EM slei@neo.tamu.edu NR 8 TC 0 Z9 0 U1 0 U2 1 PU IEEE, ELECTRON DEVICES SOC & RELIABILITY GROUP PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1098-7584 BN 978-1-4244-1209-9 J9 IEEE INT CONF FUZZY PY 2007 BP 570 EP + PG 2 WC Computer Science, Artificial Intelligence; Computer Science, Theory & Methods; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BHD83 UT WOS:000252371500100 ER PT S AU Berenji, HR Wang, Y Vachtsevanos, G AF Berenji, Hamid R. Wang, Yan Vachtsevanos, George GP IEEE TI Case based reasoning for monopropellant propulsion SO 2007 IEEE INTERNATIONAL CONFERENCE ON FUZZY SYSTEMS, VOLS 1-4 SE IEEE International Conference on Fuzzy Systems LA English DT Proceedings Paper CT IEEE International Conference on Fuzzy Systems CY JUL 23-26, 2007 CL London, ENGLAND SP IEEE AB Multi-agent Prognostic Health and Usage Monitoring (Multi-PHUM) is proposed in the paper for use in fault diagnosis and prognosis. Georgia Tech has developed a Matlab simulation model of monopropellant propulsion for studying fault diagnosis. Here we apply Multi-PHUM to the fault diagnosis of the monopropellant propulsion system. In particular, regulator failure is discussed here. C1 [Berenji, Hamid R.; Wang, Yan] NASA, Intelligent Inference Syst Grp, Res Pk Moffett Field, Moffett Field, CA 94035 USA. [Vachtsevanos, George] Georgia Inst Technol, Sch Elect Engn, Atlanta, GA 30332 USA. RP Berenji, HR (reprint author), NASA, Intelligent Inference Syst Grp, Res Pk Moffett Field, Moffett Field, CA 94035 USA. EM berenji@iiscorp.com; ywang@iiscorp.com FU NASA Ames Research Center [NNA05sBE71C] FX This work is supported by the NASA Ames Research Center under Grant NNA05sBE71C. NR 4 TC 0 Z9 0 U1 0 U2 0 PU IEEE, ELECTRON DEVICES SOC & RELIABILITY GROUP PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1098-7584 BN 978-1-4244-1209-9 J9 IEEE INT CONF FUZZY PY 2007 BP 2005 EP + PG 2 WC Computer Science, Artificial Intelligence; Computer Science, Theory & Methods; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BHD83 UT WOS:000252371500343 ER PT B AU Bhasin, KB Putt, C Hayden, J Tseng, S Miller, R Hudiburg, J Miller, D Jeffries, A Sartwell, T Biswas, A Kennedy, B Jennings, E AF Bhasin, Kul B. Putt, Chuck Hayden, Jeffrey Tseng, Shirley Miller, Ron Hudiburg, John Miller, Dave Jeffries, Alan Sartwell, Tom Biswas, Abi Kennedy, Brian Jennings, Esther GP IEEE TI Architecting the communication and navigation networks for NASA's space exploration systems SO 2007 IEEE INTERNATIONAL CONFERENCE ON SYSTEM OF SYSTEMS ENGINEERING, VOLS 1 AND 2 LA English DT Proceedings Paper CT IEEE International Conference on System of Systems Engineering CY APR 16-18, 2007 CL San Antonio, TX SP IEEE DE system architecting; architecting process; communication; navigation; tracking; space exploration; space network; ground network; space systems AB NASA is planning a series of short and long duration human and robotic missions to explore the Moon and then Mars. A key objective of the missions is to grow, through a series of launches, a system of systems communication, navigation, and timing infrastructure at minimum cost while providing a network-centric infrastructure that maximizes the exploration capabilities and science return. There is a strong need to use architecting processes in the mission pre-formulation stage to describe the systems, interfaces, and interoperability needed to implement multiple space communication systems that are deployed over time, yet support interoperability with each deployment phase and with 20 years of legacy systems. In this paper we present a process for defining the architecture of the communications, navigation, and networks needed to support future space explorers with the best adaptable and evolable network-centric space exploration infrastructure. The process steps presented are: 1) Architecture decomposition, 2) Defining mission systems and their interfaces, 3) Developing the communication, navigation, networking architecture, and 4) Integrating systems, operational and technical views and viewpoints. We demonstrate the process through the architecture development of the communication network for upcoming NASA space exploration missions. C1 [Bhasin, Kul B.; Putt, Chuck; Hayden, Jeffrey; Tseng, Shirley] NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. [Miller, Ron; Hudiburg, John; Miller, Dave; Jeffries, Alan; Sartwell, Tom] Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Biswas, Abi; Kennedy, Brian; Jennings, Esther] Jet Prop Lab, Pasadena, CA 91109 USA. RP Bhasin, KB (reprint author), NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. EM Kul.B.Bhasin@nasa.gov; jlhayden@earthlink.net; shirleytseng@earthlink.net; Ron.A.Miller@nasa.gov; John.J.Hudiburg@nasa.gov; David.Miller@itt.com; Alan@JeTSI.com; Tom.Sartwell@gdc4s.com; Abhijit.Biswas@jpl.nasa.gov; Brian.Kennedy@jpl.nasa.gov; Esther.H.Jennings@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 BN 978-1-4244-1159-7 PY 2007 BP 217 EP + PG 2 WC Computer Science, Hardware & Architecture; Computer Science, Information Systems; Computer Science, Theory & Methods; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BHH57 UT WOS:000253304300037 ER PT B AU Weisbin, CR Moeller, R Zimmerman, W Smythe, W Van Houten, T Lincoln, W Smith, JH Elfes, A Adumitroaie, V AF Weisbin, Charles R. Moeller, R. Zimmerman, W. Smythe, W. Van Houten, T. Lincoln, W. Smith, J. H. Elfes, A. Adumitroaie, V. GP IEEE TI Analysis of concepts for large-scale robotic lunar precursor missions SO 2007 IEEE INTERNATIONAL CONFERENCE ON SYSTEM OF SYSTEMS ENGINEERING, VOLS 1 AND 2 LA English DT Proceedings Paper CT IEEE International Conference on System of Systems Engineering CY APR 16-18, 2007 CL San Antonio, TX SP IEEE DE productivity; decision-making; return on investment; value; optimization; analysis software; NASA lunar missions; exploration; technology development AB Two concepts for large-scale, complex, robotic missions to search for frozen water at the lunar South Pole are systematically analyzed to determine their relative productivity and investment requirements. The Strategic Assessment of Risk and Technology (START) methodology and tool are utilized to determine temporal R&D-investment recommendations to optimize mission performance goals subject to budget, workforce, and other non-technical constraints. Explicit distinction is made between enabling and enhancing technologies. Uncertainties and dependencies are included within the optimization framework. This study determined that given the constraints used in this analysis, the longer mission would return 12 times the value of the shorter mission for roughly an 11% increase in cost, and would be enabled with the recommended temporal technology portfolio. C1 [Weisbin, Charles R.; Moeller, R.; Zimmerman, W.; Smythe, W.; Van Houten, T.; Lincoln, W.; Smith, J. H.; Elfes, A.; Adumitroaie, V.] Jet Propuls Lab, Syst Modeling & Anal Program Off, Pasadena, CA 91109 USA. RP Weisbin, CR (reprint author), Jet Propuls Lab, Syst Modeling & Anal Program Off, Pasadena, CA 91109 USA. EM Charles.R.Weisbin@jpl.nasa.gov RI Elfes, Alberto/E-2463-2011 OI Elfes, Alberto/0000-0003-2433-995X 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 978-1-4244-1159-7 PY 2007 BP 587 EP 592 PG 6 WC Computer Science, Hardware & Architecture; Computer Science, Information Systems; Computer Science, Theory & Methods; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BHH57 UT WOS:000253304300099 ER PT S AU Horan, B Nahavandi, S Creighton, D Tunstel, E AF Horan, B. Nahavandi, S. Creighton, D. Tunstel, E. GP IEEE TI Fuzzy haptic augmentation for telerobotic stair climbing SO 2007 IEEE INTERNATIONAL CONFERENCE ON SYSTEMS, MAN AND CYBERNETICS, VOLS 1-8 SE IEEE International Conference on Systems Man and Cybernetics Conference Proceedings LA English DT Proceedings Paper CT IEEE International Conference on Systems, Man and Cybernetics CY OCT 07-10, 2007 CL Montreal, COOK ISLANDS SP IEEE AB Teleoperated robotic systems provide a valuable solution for the exploration of hazardous environments. The ability to explore dangerous environments from the safety of a remote location represents an important progression towards the preservation of human safety in the inevitable response to such a threat. While the benefits of removing physical human presence are clear, challenges associated with remote operation of a robotic system need to be addressed. Removing direct human presence from the robot's operating environment introduces telepresence as an important consideration in achieving the desired objective. The introduction of the haptic modality represents one approach towards improving operator performance subject to reduced telepresence. When operating in an urban environment, teleoperative stair climbing is not an uncommon scenario. This work investigates the operation of an articulated track mobile robot designed for ascending stairs under teleoperative control. In order to assist the teleoperator in improved navigational capabilities, a fuzzy expert system is utilised to provide the teleoperator with intelligent haptic augmentation with the aim of improving task performance. C1 [Horan, B.; Nahavandi, S.; Creighton, D.] Deakin Univ, Intelligent Syst Res Lab, Geelong, Vic 3217, Australia. [Tunstel, E.] Jet Prop Lab, Pasadena, CA 91109 USA. RP Horan, B (reprint author), Deakin Univ, Intelligent Syst Res Lab, Geelong, Vic 3217, Australia. EM benpatri@deakin.edu.au; nahavand@deakin.edu.au; dougc@deakin.edu.au; tunstel@ieee.org FU ISR Lab: Intelligent Systems Research Laboratory, at Deakin University, Australia FX This work was supported by the ISR Lab: Intelligent Systems Research Laboratory, at Deakin University, Australia. NR 12 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1062-922X BN 978-1-4244-0990-7 J9 IEEE SYS MAN CYBERN PY 2007 BP 1280 EP + PG 2 WC Automation & Control Systems; Computer Science, Artificial Intelligence; Computer Science, Cybernetics; Engineering, Electrical & Electronic SC Automation & Control Systems; Computer Science; Engineering GA BHP06 UT WOS:000255016301043 ER PT S AU Ravinder, U McCann, RS Beutter, B Stone, L Huemer, V AF Ravinder, Ujwala McCann, Robert S. Beutter, Brent Stone, Leland Huemer, Valerie GP IEEE TI Development of a human performance modeling tool for user interface evaluation in next generation spacecraft: An empirical approach SO 2007 IEEE INTERNATIONAL CONFERENCE ON SYSTEMS, MAN AND CYBERNETICS, VOLS 1-8 SE IEEE International Conference on Systems Man and Cybernetics Conference Proceedings LA English DT Proceedings Paper CT IEEE International Conference on Systems, Man and Cybernetics CY OCT 07-10, 2007 CL Montreal, COOK ISLANDS SP IEEE AB Computational models of human performance hold considerable promise for streamlining design/test/redesign cycles for crew interfaces on next-generation space vehicles. To fulfill that promise, however, the models will have to be able to simulate and predict human performance in a highly complex operational environment. We describe an empirical approach to aid model development, which is based on analyses of the oculomotor behavior of human operators during a fault management task in a part-task shuttle cockpit simulator. For each operator, each of the eye fixations involved in the fault management task was classified as belonging to one of nine information acquisition categories (e.g. reading text, checking systems parameters, monitoring an action). For each category, we combined the fixation data across the operators and two levels of automation to produce a well populated distribution of fixation latencies, each of which was well fit by a gamma function. We then performed simulations in which, for each operator, the duration of each fixation involved in the fault management task was repeatedly stochastically sampled from the appropriate gamma distribution. The average of these samples was then substituted for the actual duration of each fixation, and the sum of the model-based fixation durations was then compared to the actual fault management completion time obtained from each observer. The model-derived task completion times were highly predictive of both the mean and variance in operators' actual finishing times. The next steps in generating model-based behavior are discussed. C1 [Ravinder, Ujwala; Huemer, Valerie] NASA, Ames Res Ctr, San Jose State Univ Fdn & Working, Moffett Field, CA 94035 USA. [McCann, Robert S.; Beutter, Brent; Stone, Leland] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Ravinder, U (reprint author), NASA, Ames Res Ctr, San Jose State Univ Fdn & Working, Moffett Field, CA 94035 USA. EM uravinder@mail.arc.nasa.gov; rmccann@mail.arc.nasa.gov; bbeutter@mail.arc.nasa.gov; lstone@mail.arc.nasa.gov; vhuemer@mail.arc.nasa.gov 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 SN 1062-922X BN 978-1-4244-0990-7 J9 IEEE SYS MAN CYBERN PY 2007 BP 3167 EP + PG 2 WC Automation & Control Systems; Computer Science, Artificial Intelligence; Computer Science, Cybernetics; Engineering, Electrical & Electronic SC Automation & Control Systems; Computer Science; Engineering GA BHP06 UT WOS:000255016303019 ER PT S AU Tunstel, E Anderson, GT Wilson, EW AF Tunstel, Edward Anderson, Gary T. Wilson, Edtnond W. GP IEEE TI Autonomous mobile surveying for science rovers using in situ distributed remote sensing SO 2007 IEEE INTERNATIONAL CONFERENCE ON SYSTEMS, MAN AND CYBERNETICS, VOLS 1-8 SE IEEE International Conference on Systems Man and Cybernetics Conference Proceedings LA English DT Proceedings Paper CT IEEE International Conference on Systems, Man and Cybernetics CY OCT 07-10, 2007 CL Montreal, COOK ISLANDS SP IEEE ID ROBOTS AB The search for signs of past or present life on planetary surfaces such as Mars is a high priority objective of international space agencies. At present and in the near future, the most promising means to conduct such searches employ robotic systems that operate from planetary orbits or on planetary surfaces. This paper presents a robotic system concept for mobile search and surveying on planetary surfaces. It employs an open-path absorption spectrometer with components distributed on a rover and terrain to measure biogenic gases in the near-surface atmosphere. Rover motion control algorithms are presented and demonstrated in simulation for surveying wide areas autonomously using the distributed spectrometer for in situ remote sensing. C1 [Tunstel, Edward] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Anderson, Gary T.] Univ Arkansas, Dept Appl Sci, Little Rock, AR 72204 USA. [Wilson, Edtnond W.] Harding Univ, Dept Chem, Searcy, AR 72149 USA. RP Tunstel, E (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM tunstel@ieee.org; gtanderson@ualr.edu; wilson@harding.edu FU NASA ASTID Program, Science Mission Director FX The research described in this paper was performed in part at the Jet Propulsion Laboratory, California Institute of Technology, under contract with the National Aeronautics and Space Administration, and at Harding University and the University of Arkansas at Little Rock with sponsorship of the NASA ASTID Program, Science Mission Director NR 13 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1062-922X BN 978-1-4244-0990-7 J9 IEEE SYS MAN CYBERN PY 2007 BP 3215 EP + PG 2 WC Automation & Control Systems; Computer Science, Artificial Intelligence; Computer Science, Cybernetics; Engineering, Electrical & Electronic SC Automation & Control Systems; Computer Science; Engineering GA BHP06 UT WOS:000255016303027 ER PT B AU Lai, R Mei, XB Deal, WR Yoshida, W Kim, YM Liu, PH Lee, J Uyeda, J Radisic, V Lange, M Gaier, T Samoska, L Fung, A AF Lai, R. Mei, X. B. Deal, W. R. Yoshida, W. Kim, Y. M. Liu, P. H. Lee, J. Uyeda, J. Radisic, V. Lange, M. Gaier, T. Samoska, L. Fung, A. GP IEEE TI Sub 50 nm InPHEMT device with Fmax greater than 1 THz SO 2007 IEEE INTERNATIONAL ELECTRON DEVICES MEETING, VOLS 1 AND 2 SE International Electron Devices Meeting LA English DT Proceedings Paper CT IEEE International Electron Devices Meeting CY DEC 10-12, 2007 CL Washington, DC SP IEEE AB In this paper, we present the latest advancements of sub 50 nm InGaAs/InAlAs/InP High Electron Mobility Transistor (InP HEMT) devices that have achieved extrapolated Fmax above 1 THz. This extrapolation is both based on unilateral gain (1.2 THz) and maximum stable gain/maximum available gain (1.1 THz) extrapolations, with an associated fT of 385 GHz. This extrapolation is validated by the demonstration of a 3-stage common source low noise MMIC amplifier which exhibits greater than 18 dB gain at 300 GHz and 15 dB gain at 340 GHz. C1 [Lai, R.; Mei, X. B.; Deal, W. R.; Yoshida, W.; Kim, Y. M.; Liu, P. H.; Lee, J.; Uyeda, J.; Radisic, V.; Lange, M.] Northrop Grumman Space Technol, 1 Space Pk, Redondo Beach, CA 90278 USA. [Gaier, T.; Samoska, L.; Fung, A.] Jet Prop Lab, Pasadena, CA 91109 USA. RP Lai, R (reprint author), Northrop Grumman Space Technol, 1 Space Pk, Redondo Beach, CA 90278 USA. FU DARPA SWIFT; Army Research Laboratory under the ARL [W91 1QX-06-C-0050] FX This work was supported by DARPA SWIFT Program (Dr. Mark Rosker) and Army Research Laboratory (Dr. H. Alfred Hung) under the ARL Contract No:W91 1QX-06-C-0050. The authors would like to thank Lynn Danh, Jennifer Wang, Richard To, Stella Makishi, Jeff Baky, Weang Coakley, Kho, Patti Oliver, Tim Naeole, Mike Keang Barsky, Liu and members of NGST microelectronics laboratory and RF design team for their support in MMIC layout, on-wafer DC and RF testing data summary, and wafer fabrication support. The authors would also like to thank Ron Grundbacher, Aaron Oki, Reynold Kagiwada, Dwight Streit and Dave Farkas for their support and advice. This research was carried out in part at the Jet Propulsion Laboratory, California Institute of Technology, under a contract with the National|Aeronautics and Space Administration. NR 5 TC 123 Z9 129 U1 0 U2 24 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-1507-6 J9 INT EL DEVICES MEET PY 2007 BP 609 EP + DI 10.1109/IEDM.2007.4419013 PG 2 WC Engineering, Multidisciplinary; Engineering, Electrical & Electronic SC Engineering GA BIG52 UT WOS:000259347800138 ER PT B AU Joy, T Pyo, S Park, S Choi, C Palsule, C Han, H Feng, C Lee, S Mckee, J Altice, P Hong, C Boemler, C Hynecek, J Louie, M Lee, J Kim, D Haddad, H Pain, B AF Joy, Tom Pyo, Sunggyu Park, Sunghyung Choi, Changhoon Palsule, Chintamani Han, Hyungjun Feng, Chen Lee, Sangjoo McKee, Jeff Altice, Parker Hong, Chris Boemler, Christian Hynecek, Jerry Louie, Michael Lee, Juil Kim, Daebyung Haddad, Homayoon Pain, Bedabrata GP IEEE TI Development of a production-ready, back-illuminated CMOS image sensor with small pixels SO 2007 IEEE INTERNATIONAL ELECTRON DEVICES MEETING, VOLS 1 AND 2 SE International Electron Devices Meeting LA English DT Proceedings Paper CT IEEE International Electron Devices Meeting CY DEC 10-12, 2007 CL Washington, DC SP IEEE AB A back-illuminated 2 megapixel CMOS sensor utilizing mature wafer manufacturing operations is described. Sensitivity, dark current and other key pixel performance measures are compared against an equivalent conventional sensor. Aspects of the process integration that make the technology manufacturable are described. Simulations that predict the performance of a full color sensor are discussed. C1 [Joy, Tom; Choi, Changhoon; Palsule, Chintamani; Feng, Chen; McKee, Jeff; Altice, Parker; Hong, Chris; Boemler, Christian; Hynecek, Jerry; Louie, Michael; Haddad, Homayoon] Magnachip Semicond Amer, Adv Pixel Res Ctr, Lake Oswego, OR 97034 USA. [Pyo, Sunggyu; Park, Sunghyung; Han, Hyungjun; Lee, Sangjoo; Lee, Juil; Kim, Daebyung; Pain, Bedabrata] Magnachip Corp, Seoul, South Korea. [Pain, Bedabrata] CALTECH, Jet Prop Lab, Pasadena, CA USA. RP Joy, T (reprint author), Magnachip Semicond Amer, Adv Pixel Res Ctr, Lake Oswego, OR 97034 USA. EM tom.joy@magnachip.com NR 6 TC 8 Z9 8 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-1507-6 J9 INT EL DEVICES MEET PY 2007 BP 1007 EP + DI 10.1109/IEDM.2007.4419125 PG 3 WC Engineering, Multidisciplinary; Engineering, Electrical & Electronic SC Engineering GA BIG52 UT WOS:000259347800231 ER PT S AU Chen, Y Westergard, L Billman, C Leon, R Vo, T White, M Mojarradi, M Kolawa, E AF Chen, Yuan Westergard, Lynett Billman, Curtis Leon, Rosa Vo, Tuan White, Mark Mojarradi, Mohammad Kolawa, Elizabeth GP IEEE TI Cryogenic reliability impact on analog circuits at extreme low temperatures SO 2007 IEEE INTERNATIONAL RELIABILITY PHYSICS SYMPOSIUM PROCEEDINGS - 45TH ANNUAL SE International Reliability Physics Symposium LA English DT Proceedings Paper CT 45th Annual IEEE International Reliability Physics Symposium CY APR 15-19, 2007 CL Phoenix, AZ SP IEEE DE low temperature electronics; hot carrier aging; analog circuit reliability ID DEGRADATION AB Cryogenic temperatures have a greater impact on analog circuit reliability than on digital circuit reliability. Analog gain tolerance may provide a more relaxed criterion while the offset voltage criterion has more bias dependence. For a pre-determined analog circuit offset failure criterion and circuit operating temperature profile, either design rules can be generated for the balanced and unbalanced matching transistor pairs in the circuit for certain hot carrier aging life requirement, or the hot carrier aging life time can be estimated for a certain unbalanced matching transistor pairs/chains. C1 [Chen, Yuan; Leon, Rosa; Vo, Tuan; White, Mark; Mojarradi, Mohammad; Kolawa, Elizabeth] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Westergard, Lynett; Billman, Curtis] AMI Semicond, Pocatello, ID USA. RP Chen, Y (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM yuan.chen@jpl.nasa.gov NR 13 TC 1 Z9 1 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1541-7026 BN 978-1-4244-0918-1 J9 INT RELIAB PHY SYM PY 2007 BP 156 EP + PG 3 WC Computer Science, Hardware & Architecture; Engineering, Electrical & Electronic; Physics, Condensed Matter SC Computer Science; Engineering; Physics GA BGH49 UT WOS:000246989600026 ER PT S AU Okojie, RS Nguyen, P Nguyen, V Savrun, E Lukco, D Buehler, J Mccue, T AF Okojie, R. S. Nguyen, P. Nguyen, V. Savrun, E. Lukco, D. Buehler, J. McCue, T. GP IEEE TI Failure mechanisms in MEMS based silicon carbide high temperature pressure sensors SO 2007 IEEE INTERNATIONAL RELIABILITY PHYSICS SYMPOSIUM PROCEEDINGS - 45TH ANNUAL SE International Reliability Physics Symposium LA English DT Proceedings Paper CT 45th Annual IEEE International Reliability Physics Symposium CY APR 15-19, 2007 CL Phoenix, AZ SP IEEE DE silicon carbide; pressure sensors; high temperature; reliability AB We report recent results of the long term reliability evaluation of single crystal silicon carbide (SiC) piezoresistive pressure sensors operated up to 500 degrees C. In-depth failure analysis was performed to identify the mechanisms responsible for their failures. Accelerated Stress Test (AST) that was developed specifically for high temperature operating devices was initially performed to extract the stable operating parameters of the transducers, which allowed for extracting the operating parameters. After the AST that included several hours of cyclic pressure and temperature excursions, the recorded maximum drift of the zero pressure offset voltage at room temperature, V-oz(25 degrees C), was 1.9 mV, while the maximum drift at 500 degrees C was 2.0 mV. The maximum recorded drift of the full-scale pressure sensitivity after ten hours of thermal cycling at 500 degrees C was +/- 1 mu V/V/psi. In all cases, the observed failures during field validation were associated with the detachment of the Au die-attach from the sensor bondpads. C1 [Okojie, R. S.] NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. [Nguyen, P.; Nguyen, V.; Savrun, E.] Sienna Technol Inc, Woodingville, WA 98072 USA. [Lukco, D.; Buehler, J.; McCue, T.] ASRC Aerosp, Cleveland, OH 44135 USA. RP Okojie, RS (reprint author), NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. NR 6 TC 3 Z9 3 U1 1 U2 5 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1541-7026 BN 978-1-4244-0918-1 J9 INT RELIAB PHY SYM PY 2007 BP 429 EP + DI 10.1109/RELPHY.2007.369928 PG 2 WC Computer Science, Hardware & Architecture; Engineering, Electrical & Electronic; Physics, Condensed Matter SC Computer Science; Engineering; Physics GA BGH49 UT WOS:000246989600069 ER PT S AU Wang, GG Qin, GX Ma, ZQ Ma, PX Racanelli, M Ponchak, GE AF Wang, Guogong Qin, Guoxuan Ma, Zhenqiang Ma, Pingxi Racanelli, Marco Ponchak, George E. GP IEEE TI Power performance characteristics of SiGe power HBTs at extreme temperatures SO 2007 IEEE INTERNATIONAL RELIABILITY PHYSICS SYMPOSIUM PROCEEDINGS - 45TH ANNUAL SE International Reliability Physics Symposium LA English DT Proceedings Paper CT 45th Annual IEEE International Reliability Physics Symposium CY APR 15-19, 2007 CL Phoenix, AZ SP IEEE ID HETEROJUNCTION BIPOLAR-TRANSISTORS; OPERATION AB This paper presents the RF (6 GHz) power performance characteristics of SiGe power HBTs at cryogenic (77K) and high operation temperature (chuck temperature 120 degrees C, junction temperature up to 160 degrees C). It shows that, without specific device optimizations for cryogenic operation, the power SiGe HBTs exhibit excellent large-signal characteristics at 77K. Comparing with room-temperature operation, similar power gain, output power and PAE were obtained when the devices were operated at the cryogenic temperature. The SiGe power HBTs also operate well at high junction temperature with reasonable power gain and output power degradations. The modeling of the SiGe power HBTs under high operation temperature indicates significant increase of base resistance (RB) and emitter resistance (RE) that account for the degradation of power performance of these devices. C1 [Wang, Guogong; Qin, Guoxuan; Ma, Zhenqiang] Univ Wisconsin, Dept Elect & Comp Engn, 1415 Engn Dr, Madison, WI 53706 USA. [Ma, Pingxi; Racanelli, Marco] Jazz Semiconductor, Newport Beach, CA USA. [Ponchak, George E.] NASA, Glenn Res Ctr, Cleveland, OH USA. RP Wang, GG (reprint author), Univ Wisconsin, Dept Elect & Comp Engn, 1415 Engn Dr, Madison, WI 53706 USA. EM mazq@engr.wisc.edu FU NSF [ECS 0323717] FX This work was supported by NSF under grant ECS 0323717. NR 9 TC 1 Z9 1 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1541-7026 BN 978-1-4244-0918-1 J9 INT RELIAB PHY SYM PY 2007 BP 584 EP + DI 10.1109/RELPHY.2007.369962 PG 2 WC Computer Science, Hardware & Architecture; Engineering, Electrical & Electronic; Physics, Condensed Matter SC Computer Science; Engineering; Physics GA BGH49 UT WOS:000246989600103 ER PT S AU Narasimham, B Shuler, RL Black, JD Bhuva, BL Schrimpf, RD Witulski, AF Holman, WT Massengill, LW AF Narasimham, B. Shuler, R. L. Black, J. D. Bhuva, B. L. Schrimpf, R. D. Witulski, A. F. Holman, W. T. Massengill, L. W. GP IEEE TI Quantifying the effectiveness of guard bands in reducing the collected charge leading to soft errors SO 2007 IEEE INTERNATIONAL RELIABILITY PHYSICS SYMPOSIUM PROCEEDINGS - 45TH ANNUAL SE International Reliability Physics Symposium LA English DT Proceedings Paper CT 45th Annual IEEE International Reliability Physics Symposium CY APR 15-19, 2007 CL Phoenix, AZ SP IEEE DE single event; SET; soft error; SER; RHBD; guard bands; pulse-width AB Soft errors pose a major reliability threat to advanced electronic components and systems. Novel techniques are needed to mitigate the soft error rate (SER) of integrated circuits (ICs) and in some cases a combination of different mitigation techniques may be required for significant performance improvements. In this work, an autonomous single event transient (SET) pulse-width characterization technique is used to quantify the effect of guard bands in reducing the collected charge and SER of integrated circuits. Inclusion of guard bands is a simple approach for Radiation Hardening by Design (RHBD). Experiment results on a 0.35-mu m technology show reduced SET pulse-width for devices with guard bands; the corresponding reduction in SER was estimated to be greater than 55% for technologies ranging from 0.35-mu m to 0.07-mu m. C1 [Narasimham, B.; Bhuva, B. L.; Schrimpf, R. D.; Witulski, A. F.; Holman, W. T.; Massengill, L. W.] Vanderbilt Univ, Dept EECS, 221 Kirkland Hall, Nashville, TN 37235 USA. [Shuler, R. L.; Black, J. D.] NASA, Johnson Space Ctr, Avionic Syst Div, Houston, TX 77058 USA. RP Narasimham, B (reprint author), Vanderbilt Univ, Dept EECS, 221 Kirkland Hall, Nashville, TN 37235 USA. EM balaji.narasimham@vanderbilt.edu NR 6 TC 2 Z9 3 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1541-7026 BN 978-1-4244-0918-1 J9 INT RELIAB PHY SYM PY 2007 BP 676 EP + DI 10.1109/RELPHY.2007.369565 PG 2 WC Computer Science, Hardware & Architecture; Engineering, Electrical & Electronic; Physics, Condensed Matter SC Computer Science; Engineering; Physics GA BGH49 UT WOS:000246989600149 ER PT B AU Kulkarni, NV Phan, MQ AF Kulkarni, Nilesh V. Phan, Minh Q. GP IEEE TI Reinforcement-learning-based magneto-hydrodynamic control of hypersonic flows SO 2007 IEEE INTERNATIONAL SYMPOSIUM ON APPROXIMATE DYNAMIC PROGRAMMING AND REINFORCEMENT LEARNING LA English DT Proceedings Paper CT IEEE International Symposium on Approximate Dynamic Programming and Reinforcement Learning CY APR 01-05, 2007 CL Honolulu, HI AB In this work, we design a policy-iteration-based Q-learning approach for on-line optimal control of ionized hypersonic flow at the inlet of a scramjet engine. Magneto-hydrodynamics (MHD) has been recently proposed as a means for flow control in various aerospace problems. This mechanism corresponds to applying external magnetic fields to ionized flows towards achieving desired flow behavior. The applications range from external flow control for producing forces and moments on the air-vehicle to internal flow control designs, which compress and extract electrical energy from the flow. The current work looks at the later problem of internal flow control. The baseline controller and Q-function parameterizations are derived from an off-line mixed predictive-control and dynamic-programming-based design. The nominal optimal neural network Q-function and controller are updated on-line to handle modeling errors in the off-line design. The on-line implementation investigates key concerns regarding the conservativeness of the update methods. Value-iteration-based update methods have been shown to converge in a probabilistic sense. However, simulations results illustrate that realistic implementations of these methods face significant training difficulties, often failing in learning the optimal controller on-line. The present approach, therefore, uses a policyiteration-based update, which has time-based convergence guarantees. Given the special finite-horizon nature of the problem, three novel on-line update algorithms are proposed. These algorithms incorporate different mix of concepts, which include bootstrapping, and forward and backward dynamic programming update rules. Simulation results illustrate success of the proposed update algorithms in re-optimizing the performance of the MHD generator during system operation. C1 [Kulkarni, Nilesh V.] NASA, Ames Res Ctr, QSS Grp Inc, Moffett Field, CA 94035 USA. [Phan, Minh Q.] Dartmouth Coll, Thayer Sch Engn, Hanover, NH 03755 USA. RP Kulkarni, NV (reprint author), NASA, Ames Res Ctr, QSS Grp Inc, Moffett Field, CA 94035 USA. FU ANSER Corporation through from the National Science Foundation FX This work was funded by ANSER Corporation through a grant from the National Science Foundation. The authors wish to thank Ray Chase and Paul Werbos for this funding support. Prof. Richard Miles at Princeton University and his applied physics group, especially Mikhail Shneyder, provided the MHD modeling support. The authors also wish to thank Prof. Robert Stengel at Princeton University and Kalmanje Krishnakumar at NASA Ames Research Center for their support. NR 25 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-0706-4 PY 2007 BP 9 EP + DI 10.1109/ADPRL.2007.368163 PG 2 WC Computer Science, Artificial Intelligence SC Computer Science GA BGM94 UT WOS:000248536200002 ER PT S AU Fang, WC Kedar, S AF Fang, Wai-Chi Kedar, Sharon GP IEEE TI Gigascale system design of sensor networks for active volcanoes SO 2007 IEEE INTERNATIONAL SYMPOSIUM ON CIRCUITS AND SYSTEMS, VOLS 1-11 SE IEEE International Symposium on Circuits and Systems LA English DT Proceedings Paper CT IEEE International Symposium on Circuits and Systems CY MAY 27-30, 2007 CL New Orleans, LA SP IEEE AB In this paper, an intelligent surveillance system using sensor networks for monitoring active volcanoes has been presented. We combine sensor network system engineering with systems-on-chip implementation to develop a gigascale integrated surveillance system called Sensor Networks for Active Volcanoes (SNAV). We report SNAV specific science-related requirements and system-level operations for this surveillance system. We also present the SNAV system-on-chip implementation. The success of this work enables low-power, low-cost sensor networks for the intelligent surveillance systems. C1 [Fang, Wai-Chi; Kedar, Sharon] CALTECH, Jet Prop Lab, NASA, Pasadena, CA 91109 USA. RP Fang, WC (reprint author), CALTECH, Jet Prop Lab, NASA, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 5 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 0271-4302 BN 978-1-4244-0920-4 J9 IEEE INT SYMP CIRC S PY 2007 BP 373 EP 376 DI 10.1109/ISCAS.2007.378467 PG 4 WC Computer Science, Artificial Intelligence; Computer Science, Software Engineering; Engineering, Biomedical; Engineering, Electrical & Electronic; Mathematical & Computational Biology; Nanoscience & Nanotechnology; Imaging Science & Photographic Technology; Telecommunications SC Computer Science; Engineering; Mathematical & Computational Biology; Science & Technology - Other Topics; Imaging Science & Photographic Technology; Telecommunications GA BGZ68 UT WOS:000251608400094 ER PT B AU Koppen, SV Ely, JJ Smith, LJ Jones, RA Fleck, VJ Salud, MT Mielnik, J AF Koppen, Sandra V. Ely, Jay J. Smith, Laura J. Jones, Richard A. Fleck, Vincent J. Salud, Maria Theresa Mielnik, John GP IEEE TI Airborne RF measurement system and analysis of representative flight RF environment SO 2007 IEEE INTERNATIONAL SYMPOSIUM ON ELECTROMAGNETIC COMPATIBILITY: WORKSHOP AND TUTORIAL NOTES, VOLS 1-3 LA English DT Proceedings Paper CT IEEE Symposium on Electromagnetic Compatibility CY JUL 08-13, 2007 CL Honolulu, HI SP IEEE, EMC Soc DE aircraft; EMC; EMI; CNS; RF; radio; measurement; ILS AB Environmental radio frequency (RF) data over a broad band of frequencies were needed to evaluate the airspace around several airports. An RF signal measurement system was designed using a spectrum analyzer connected to an aircraft VHF/UHF navigation antenna installed on a small aircraft. This paper presents an overview of the RF measurement system and provides analysis of a sample of RF signal measurement data over a frequency range of 30 MHz to 1000 MHz. C1 [Koppen, Sandra V.; Ely, Jay J.; Smith, Laura J.; Jones, Richard A.; Fleck, Vincent J.] NASA, Langley Res Ctr, Hampton, VA 23665 USA. [Salud, Maria Theresa; Mielnik, John] Lockheed Martin Corp, Hampton, VA USA. RP Koppen, SV (reprint author), NASA, Langley Res Ctr, Hampton, VA 23665 USA. NR 6 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-1349-2 PY 2007 BP 99 EP + PG 2 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BHL51 UT WOS:000254096000019 ER PT B AU Nguyen, TX Koppen, SV Ely, JJ Szatkowski, GN Mielnik, JJ Salud, MTP AF Nguyen, Truong X. Koppen, Sandra V. Ely, Jay J. Szatkowski, George N. Mielnik, John J. Salud, Maria Theresa P. GP IEEE TI Small aircraft RF interference path loss SO 2007 IEEE INTERNATIONAL SYMPOSIUM ON ELECTROMAGNETIC COMPATIBILITY: WORKSHOP AND TUTORIAL NOTES, VOLS 1-3 LA English DT Proceedings Paper CT IEEE Symposium on Electromagnetic Compatibility CY JUL 08-13, 2007 CL Honolulu, HI SP IEEE, EMC Soc DE interference path loss; portable electronic devices; aircraft; radio; communication; navigation; front-door coupling; PEDs; IPL; IPC AB Interference to aircraft radio receivers is an increasing concern as more portable electronic devices are allowed onboard. Interference signals are attenuated as they propagate from inside the cabin to aircraft radio antennas mounted on the outside of the aircraft. The attenuation level is referred to as the interference path loss (IPL) value. Significant published IPL data exists for transport and regional category airplanes. This report fills a void by providing data for small business/corporate and general aviation aircraft. In this effort, IPL measurements are performed on ten small aircraft of different designs and manufacturers. Multiple radio systems are addressed. Along with the typical worst-case coupling values, statistical distributions are also reported that could lead to better interference risk assessment. C1 [Nguyen, Truong X.; Koppen, Sandra V.; Ely, Jay J.; Szatkowski, George N.] NASA, Langley Res Ctr, Hampton, VA 23665 USA. RP Nguyen, TX (reprint author), NASA, Langley Res Ctr, Hampton, VA 23665 USA. NR 8 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-1349-2 PY 2007 BP 105 EP 110 PG 6 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BHL51 UT WOS:000254096000020 ER PT B AU Johnk, RT Novotny, DR Grosvenor, CA Canales, N Camell, DG Koepke, GH Scully, RC AF Johnk, Robert T. Novotny, David R. Grosvenor, Chriss A. Canales, Nino Camell, Dennis G. Koepke, Galen H. Scully, Robert C. GP IEEE TI RF electromagnetic penetration of the NASA space shuttle Endeavour performed with an ultra-wideband system SO 2007 IEEE INTERNATIONAL SYMPOSIUM ON ELECTROMAGNETIC COMPATIBILITY: WORKSHOP AND TUTORIAL NOTES, VOLS 1-3 LA English DT Proceedings Paper CT IEEE Symposium on Electromagnetic Compatibility CY JUL 08-13, 2007 CL Honolulu, HI SP IEEE, EMC Soc DE Fourier Transform, hangar, Kennedy Space Center; orbiter; penetration measurement reverberation chamber; shuttle; time-domain, time-gating ultra-wideband AB This paper summarizes a joint NIST-NASA measurement effort to thoroughly evaluate the electromagnetic penetration of the shuttle Endeavour. NASA is concerned about the effects that microwave imaging radar systems might have on critical avionics systems on its fleet of space shuttles. As part of a multifaceted effort, a portable, NIST-developed ultra-wideband measurement system was deployed at the Kennedy Space Center to evaluate electromagnetic penetration over the frequency range of 30 MHZ - 6 GHz at selected locations inside Endeavour. The measurements were performed inside a large metal hangar, which exhibited robust reverberant behavior. A combination of reverb chamber techniques and time/frequency signal processing permitted the evaluation of electromagnetic penetration at six different locations inside the orbiter. C1 [Johnk, Robert T.; Novotny, David R.; Grosvenor, Chriss A.; Canales, Nino; Camell, Dennis G.; Koepke, Galen H.] Natl Inst Stand & Technol, Electromagnet Div, Time Domain Fields Project, Boulder, CO 80303 USA. [Scully, Robert C.] NASA Johnson Space Ctr, Avion Syst Div, Houston, TX USA. RP Johnk, RT (reprint author), Natl Inst Stand & Technol, Electromagnet Div, Time Domain Fields Project, Boulder, CO 80303 USA. NR 6 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-1349-2 PY 2007 BP 605 EP + PG 2 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BHL51 UT WOS:000254096000112 ER PT B AU Barsoum, MR Jones, C Fitz, M AF Barsoum, Maged R. Jones, Christopher Fitz, Michael GP IEEE TI Constellation design via capacity maximization SO 2007 IEEE INTERNATIONAL SYMPOSIUM ON INFORMATION THEORY PROCEEDINGS, VOLS 1-7 LA English DT Proceedings Paper CT IEEE International Symposium on Information Theory CY JUN 24-29, 2007 CL Nice, FRANCE SP IEEE ID MULTIDIMENSIONAL CONSTELLATIONS; GAUSSIAN-CHANNEL AB Traditional constellations are uniformally spaced. By giving up uniform spacing, constellations can be designed to have larger joint (i.e. overall) capacity or parallel decoding capacity. In this paper non-uniformally spaced (i.e. 'geometrically' shaped) constellations are designed to maximize either of these quantities. By way of numerical capacity computations we show that except in special cases, there are no universally optimal geometrically shaped constellations across all code rates, and that the optimization of a constellation has to target a specific code rate. Unlike joint capacity, optimizing for parallel decoding capacity is label dependent. For PAM and PSK constellations, we found the maximum parallel decoding capacity to be achieved using gray (not necessarfly binary reflective gray) labels. However, for PAM constellations, not all gray labels can yield the highest parallel decoding capacity. Besides the conventional use of a (log(2)(M)-1)/log(2) (M) code rate with an M-point constellation for bandwidth efficient communications, the optimized constellations could offer further non-trivial gains at lower code rates (unlike traditional constellations). An optimized constellation is used with a state-of-the-art LDPC code and simulation results are presented. This paper also draws a distinction between probabilistic shaping and geometric shaping and in fact proves under broad conditions, that any gain in capacity which can be found via probabilistic shaping can also be achieved or exceeded solely through geometric shaping. C1 [Barsoum, Maged R.; Jones, Christopher] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Fitz, Michael] Univ Calif Los Angeles, Dept Elect Engn, Los Angeles, CA 90095 USA. RP Barsoum, MR (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM mbarsoum@jpl.nasa.gov; crjones@jpl.nasa.gov; fitz@ee.ucla.edu NR 15 TC 10 Z9 10 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-1397-3 PY 2007 BP 1821 EP + DI 10.1109/ISIT.2007.4557486 PG 2 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BHW32 UT WOS:000257010202026 ER PT B AU Agarwal, A El-Ghazawi, T El-Askary, H Le-Moigne, J AF Agarwal, Abhishek El-Ghazawi, Tarek El-Askary, Hesham Le-Moigne, Jacquline GP IEEE TI Efficient hierarchical-PCA dimension reduction for hyperspectral imagery SO 2007 IEEE INTERNATIONAL SYMPOSIUM ON SIGNAL PROCESSING AND INFORMATION TECHNOLOGY, VOLS 1-3 LA English DT Proceedings Paper CT 7th IEEE International Symposium on Signal Processing and Information Technology CY DEC 15-18, 2007 CL Cairo, EGYPT SP IEEE, IEEE Signal Proc Soc, IEEE Comp Soc DE PCA; dimension reduction; hyperspectral AB Hyperspectral systems have improved significantly through recent advancements in sensor technology, which have made possible to acquire data with several hundred channels. These advances provide the possible benefit of not only collecting more detailed information than previously possible, but also of producing more accurate data. Some of the major challenges in handling such large data sets are removing redundant information and assuring the continued relevance of vital information to the application at hand. For example, conventional methods for land use and land cover classifications may not be applicable, due to the large data volumes used to characterize hyperspectral cubes. Therefore, these conventional methods may require a preprocessing step, namely dimension reduction. Dimension reduction can be seen as a transformation from a high order dimension to a low order dimension in order to conquer the so-called "curse of the dimensionality," which eliminates data redundancy. Principal Component Analysis (PCA) is one such data reduction technique, which is often used when analyzing remotely sensed data. In computing the principal components, the eigenvalues of the covariance matrix of the 3-D image must be computed. Since this is a global operation it requires high computational resources and requires whole image to be stored which increases memory requirements. This paper reports an hierarchical algorithm, which can effectively reduce the hyperspectral data to intrinsic dimensionality. In the hierarchical PCA, we break the image into various parts and then perform PCA on each part separately and then combine the results. The classification results over the original and the resulting reduced data have been compared. The results show that reduced data obtained by hierarchical PCA can compare favorably to the results obtained from original data. C1 [Agarwal, Abhishek; El-Ghazawi, Tarek] George Washington Univ, Dept Elect & Comp Engn, Washington, DC 20052 USA. [El-Askary, Hesham] Univ Alexandria, Fac Sci, Dept Environm Sci, Alexandria, Egypt. [Le-Moigne, Jacquline] NASA Goddard Space Flight Ctr, Greenbelt, MD USA. RP Agarwal, A (reprint author), George Washington Univ, Dept Elect & Comp Engn, Washington, DC 20052 USA. EM agarwala@gwu.edu; tarek@gwu.edu; helaskar@gmu.edu; lemoigne@cesdis.gsfc.nasa.gov RI El-Askary, Hesham/B-7762-2010 NR 5 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-1834-3 PY 2007 BP 1077 EP + PG 3 WC Computer Science, Information Systems; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BHT87 UT WOS:000256344200198 ER PT S AU Zhao, K Zhang, A Farr, W Yu-Hwa, L AF Zhao, Kai Zhang, Arthur Farr, William Yu-Hwa, Lo GP IEEE TI Ultra low noise InGaAs single photon detector with transient carrier buffere SO 2007 IEEE LEOS ANNUAL MEETING CONFERENCE PROCEEDINGS, VOLS 1 AND 2 SE IEEE Lasers and Electro-Optics Society (LEOS) Annual Meeting LA English DT Proceedings Paper CT 20th Annual Meeting of the IEEE-Lasers-and-Electro-Optics-Society CY OCT 21-25, 2007 CL Lake Buena Vista, FL AB Sub-Geiger mode single photon detection with ultra low excess noise is demonstrated on an InGaAs based avalanche detector with transient carrier buffer. C1 [Zhao, Kai] Univ Calif San Diego, Dept Phys, La Jolla, CA 92093 USA. [Zhang, Arthur; Yu-Hwa, Lo] Univ Calif San Diego, Jacobs Sch Engn, Dept Phys, La Jolla, CA 92093 USA. [Farr, William] Jet Prop Lab, Pasadena, CA USA. RP Zhao, K (reprint author), Univ Calif San Diego, Dept Phys, La Jolla, CA 92093 USA. EM kzhao@physics.ucsd.edu 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 1092-8081 BN 978-1-4244-0924-2 J9 IEEE LEOS ANN MTG PY 2007 BP 447 EP + PG 2 WC Engineering, Electrical & Electronic; Nanoscience & Nanotechnology; Optics SC Engineering; Science & Technology - Other Topics; Optics GA BIG51 UT WOS:000259345200222 ER PT S AU Gu, YL Choa, FS Wu, S Wu, XC Yan, F Su, P Krainak, MA AF Gu, Yonglin Choa, Fow-Sen Wu, Stewart Wu, Xiucheng Yan, Feng Su, Peter Krainak, Michael A. GP IEEE TI Current bias mode - An innovative scheme for photon counting avalanche photodiodes (APD) array operations SO 2007 IEEE LEOS ANNUAL MEETING CONFERENCE PROCEEDINGS, VOLS 1 AND 2 SE IEEE Lasers and Electro-Optics Society (LEOS) Annual Meeting LA English DT Proceedings Paper CT 20th Annual Meeting of the IEEE-Lasers-and-Electro-Optics-Society CY OCT 21-25, 2007 CL Lake Buena Vista, FL AB We report an innovative scheme that use DC-current bias plus gated-voltage pulses to operate APDs. Such an operation can simplify the problem of breakdown-voltage nonuniformity in large-format APD arrays with excellent single photon detection efficiency. C1 [Gu, Yonglin; Choa, Fow-Sen; Yan, Feng] Univ Maryland Baltimore Cty, Dept CSEE, Baltimore, MD 21250 USA. [Wu, Stewart; Su, Peter; Krainak, Michael A.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Wu, Xiucheng] Adtech Opt, City of Industry, CA 91748 USA. RP Gu, YL (reprint author), Univ Maryland Baltimore Cty, Dept CSEE, Baltimore, MD 21250 USA. EM choa@umbc.edu NR 5 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1092-8081 BN 978-1-4244-0924-2 J9 IEEE LEOS ANN MTG PY 2007 BP 453 EP + PG 2 WC Engineering, Electrical & Electronic; Nanoscience & Nanotechnology; Optics SC Engineering; Science & Technology - Other Topics; Optics GA BIG51 UT WOS:000259345200225 ER PT S AU Poberezhskiy, IY Meras, P Chang, DH Spiers, GD AF Poberezhskiy, Ilya Y. Meras, Patrick Chang, Daniel H. Spiers, Gary D. GP IEEE TI Compact and robust refilling and connectorization of hollow core photonic crystal fiber gas reference cells SO 2007 IEEE LEOS ANNUAL MEETING CONFERENCE PROCEEDINGS, VOLS 1 AND 2 SE IEEE Lasers and Electro-Optics Society (LEOS) Annual Meeting LA English DT Proceedings Paper CT 20th Annual Meeting of the IEEE-Lasers-and-Electro-Optics-Society CY OCT 21-25, 2007 CL Lake Buena Vista, FL ID BANDGAP FIBERS AB A simple method for evacuating, refilling and connectorizing hollow-core photonic crystal fiber for use as gas reference cell is proposed and demonstrated. It relies on torch-sealing a quartz filling tube connected to a mechanical splice between regular and hollow-core fibers. C1 [Poberezhskiy, Ilya Y.; Meras, Patrick; Chang, Daniel H.; Spiers, Gary D.] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Poberezhskiy, IY (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. EM ilya@jpl.nasa.gov NR 5 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1092-8081 BN 978-1-4244-0924-2 J9 IEEE LEOS ANN MTG PY 2007 BP 568 EP 569 DI 10.1109/LEOS.2007.4382533 PG 2 WC Engineering, Electrical & Electronic; Nanoscience & Nanotechnology; Optics SC Engineering; Science & Technology - Other Topics; Optics GA BIG51 UT WOS:000259345200283 ER PT S AU Oldham, DR Scardelletti, MC AF Oldham, Daniel R. Scardelletti, Maximilian C. GP IEEE TI JTRS/SCA and Custom/SDR waveform comparision SO 2007 IEEE MILITARY COMMUNICATIONS CONFERENCE, VOLS 1-8 SE IEEE Military Communications Conference LA English DT Proceedings Paper CT IEEE Military Communications Conference (MILCOM 2007) CY OCT 29-31, 2007 CL Orlando, FL SP IEEE AB This paper compares two waveform implementations generating the same RF signal using the same SDR development system. Both waveforms implement a satellite modem using QPSK modulation at 1M BPS data rates with one half rate convolutional encoding. Both waveforms are partitioned the same across the general purpose processor (GPP) and the field programmable gate array (FPGA). Both waveforms implement the same equivalent set of radio functions on the GPP and FPGA. The GPP implements the majority of the radio functions and the FPGA implements the final digital RF modulator stage. One waveform is implemented directly on the SDR development system and the second waveform is implemented using the JTRS/SCA model. This paper contrasts the amount Of resources to implement both waveforms and demonstrates the importance of waveform partitioning across the SDR development system. C1 [Oldham, Daniel R.; Scardelletti, Maximilian C.] NASA, Glenn Res Ctr, Brookpark, OH USA. RP Oldham, DR (reprint author), NASA, Glenn Res Ctr, Brookpark, OH USA. NR 8 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2155-7578 BN 978-1-4244-1512-0 J9 IEEE MILIT COMMUN C PY 2007 BP 400 EP 404 PG 5 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BHL80 UT WOS:000254160000065 ER PT S AU Divsalar, D Dolinar, S Jones, C AF Divsalar, Dariush Dolinar, Sam Jones, Christopher GP IEEE TI Short protograph-based LDPC codes SO 2007 IEEE MILITARY COMMUNICATIONS CONFERENCE, VOLS 1-8 SE IEEE Military Communications Conference LA English DT Proceedings Paper CT IEEE Military Communications Conference (MILCOM 2007) CY OCT 29-31, 2007 CL Orlando, FL SP IEEE ID PARITY-CHECK CODES; CONSTRUCTION; CAPACITY AB In this paper we design protograph-based LDPC codes with short block sizes. Mainly we consider rate 1/2 codes with input block sizes 64, 128, and 256 bits. To simplify the encoder and decoder implementations for high data rate transmission, the structure of the codes is based on protographs and circulants. These codes are designed for short block sizes based on maximizing the minimum distance and stopping set size subject to a constraint on the maximum variable node degree. In particular, we consider codes with variable node degrees between 3 and 5. Increasing the node degree leads to larger minimum distances, at the expense of smaller girth. Therefore, there is a trade-off between undetected error rate performance (improved by increasing minimum distance) and the degree of sub-optimality of the iterative decoders typically used (which are adversely affected by graph loops). Various LDPC codes are compared and simulation results are provided. C1 [Divsalar, Dariush; Dolinar, Sam; Jones, Christopher] 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; sam@shannon.jpl.nasa.gov; christop@jpl.nasa.gov NR 22 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 2155-7578 BN 978-1-4244-1512-0 J9 IEEE MILIT COMMUN C PY 2007 BP 1994 EP 1999 PG 6 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BHL80 UT WOS:000254160001079 ER PT S AU U-Yen, K Wollack, EJ Moseley, SH Papapolymerou, J Laskar, J AF U-Yen, Kongpop Wollack, Edward J. Moseley, Samuel H. Papapolymerou, John Laskar, Joy GP IEEE TI A compact low-loss magic-T using microstrip-slotline transitions SO 2007 IEEE/MTT-S INTERNATIONAL MICROWAVE SYMPOSIUM DIGEST, VOLS 1-6 SE IEEE MTT-S International Microwave Symposium LA English DT Proceedings Paper CT IEEE/MTT-S International Microwave Symposium CY JUN 03-08, 2007 CL Honolulu, HI SP IEEE MTTS DE microstrip circuits; passive circuits; power combiners; power dividers; slotline transitions ID LINES AB The design of a compact low-loss magic-T is proposed. The planar magic-T incorporates the compact microstrip-slotline tee junction and small microstrip-slotline transition area to reduce slotline radiation. The experimental results show that the magic-T produces broadband in-phase and out-of-phase power combiner/divider responses, has an average in-band insertion loss of 0.3 dB and small in-band phase and amplitude imbalance of less than +/- 1.6 degrees and +/- 0.3 dB, respectively. C1 [U-Yen, Kongpop; Wollack, Edward J.; Moseley, Samuel H.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Papapolymerou, John; Laskar, Joy] Georgia Inst Technol, Atlanta, GA 30332 USA. RP U-Yen, K (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RI Wollack, Edward/D-4467-2012 OI Wollack, Edward/0000-0002-7567-4451 NR 6 TC 3 Z9 3 U1 1 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 0149-645X BN 978-1-4244-0687-6 J9 IEEE MTT S INT MICR PY 2007 BP 37 EP + DI 10.1109/MWSYM.2007.380212 PG 2 WC Engineering, Electrical & Electronic; Optics; Telecommunications SC Engineering; Optics; Telecommunications GA BGV76 UT WOS:000250827400009 ER PT S AU Deal, WR Mei, XB Radisic, V Yoshida, W Liu, PH Uyeda, J Barsky, M Gaier, T Fung, A Samoska, L Lai, R AF Deal, W. R. Mei, X. B. Radisic, V. Yoshida, W. Liu, P. H. Uyeda, J. Barsky, M. Gaier, T. Fung, A. Samoska, L. Lai, R. GP IEEE TI A 245-GHz MMIC: Amplifier with 80-mu m output periphery and 12-dB gain SO 2007 IEEE/MTT-S INTERNATIONAL MICROWAVE SYMPOSIUM DIGEST, VOLS 1-6 SE IEEE MTT-S International Microwave Symposium LA English DT Proceedings Paper CT IEEE/MTT-S International Microwave Symposium CY JUN 03-08, 2007 CL Honolulu, HI SP IEEE MTTS DE MMIC; millimeter wave; HEMT; coplanar waveguide; power amplifier ID G-BAND; GHZ AB In this paper we present a MMIC amplifier which demonstrates similar to 12-dB gain at a center frequency of 245-GHz The MMIC is intended to demonstrate the potential of power amplification at short-millimeter wave frequencies. Each stage of the three stage amplifier utilizes a 1:2 output split to reach a total output periphery of 80-mu m. The combination of high realized gain per stage and output periphery indicate the potential generating output powers on the order of several mW at short mm-wave frequencies using MMIC amplifiers for the first time. The amplifier is implemented in coplanar waveguide and uses an InP HEMT process with a 35-nm gate. C1 [Deal, W. R.; Mei, X. B.; Radisic, V.; Yoshida, W.; Liu, P. H.; Uyeda, J.; Barsky, M.; Lai, R.] Northrop Grumman Corp, Redondo Beach, CA 90278 USA. [Gaier, T.; Fung, A.; Samoska, L.] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Deal, WR (reprint author), Northrop Grumman Corp, Redondo Beach, CA 90278 USA. FU DARPA SWIFT Program; Army Research Laboratory under ARL [W911QX-06-C-0050] FX This work was supported by the DARPA SWIFT Program and Army Research Laboratory under the ARL Contract no. W911QX-06-C-0050 and the authors would like to thank Dr. Mark Rosker (DARPA) and Dr. Alfred Hung (ARL). The authors would like to thank members of the Northrop Grumman laboratories from MMIC layout support with Jeff Coakley and Stella Makishi, MBE material growth lead by Patrick Chin and Mike Lange, MMIC wafer fabrication with Young-Min Kim, Dave Farkas, Jane Lee, Danny Li, Linh )C Dang, Jennifer Wang, Keang Kho, Pat Oliver, John Kane and Tim Naeole. The authors would also like to thank Aaron Oki, Reynold Kagiwada and Cheng-Chih Yang for their support. This research was carried out in part at the Jet Propulsion Laboratory, California Institute of Technology, under a contract with the National Aeronautics and Space Administration. NR 7 TC 8 Z9 8 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 0149-645X BN 978-1-4244-0687-6 J9 IEEE MTT S INT MICR PY 2007 BP 329 EP + DI 10.1109/MWSYM.2007.380419 PG 2 WC Engineering, Electrical & Electronic; Optics; Telecommunications SC Engineering; Optics; Telecommunications GA BGV76 UT WOS:000250827400076 ER PT S AU Geldzahler, BJ Rush, JJ Deutsch, LJ Statman, JI AF Geldzahler, B. J. Rush, J. J. Deutsch, L. J. Statman, J. I. GP IEEE TI Engineering the next generation deep space network SO 2007 IEEE/MTT-S INTERNATIONAL MICROWAVE SYMPOSIUM DIGEST, VOLS 1-6 SE IEEE MTT-S International Microwave Symposium LA English DT Proceedings Paper CT IEEE/MTT-S International Microwave Symposium CY JUN 03-08, 2007 CL Honolulu, HI SP IEEE MTTS DE antenna arrays; satellite communication; satellite tracking AB A NASA-wide Space Communications Architecture Working Group has recommended that the Apollo-era Deep Space Network large antennas be replaced with arrays of small antennas. We view the DSN antennas as nodes of an emerging end-to-end networking structure. In this note, we discuss plans and implementation status of ground and spacecraft components of the next generation DSN. C1 [Geldzahler, B. J.; Rush, J. J.] NASA, Washington, DC 20546 USA. [Deutsch, L. J.; Statman, J. I.] CALTECH, Jet Prop Lab, Pasadena 91109, CA USA. RP Geldzahler, BJ (reprint author), NASA, Washington, DC 20546 USA. NR 5 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 0149-645X BN 978-1-4244-0687-6 J9 IEEE MTT S INT MICR PY 2007 BP 930 EP 933 PG 4 WC Engineering, Electrical & Electronic; Optics; Telecommunications SC Engineering; Optics; Telecommunications GA BGV76 UT WOS:000250827402043 ER PT S AU Pham, T Deboy, C AF Pham, Timothy Deboy, Christopher GP IEEE TI Polarization combining in the DSN - Recent results SO 2007 IEEE/MTT-S INTERNATIONAL MICROWAVE SYMPOSIUM DIGEST, VOLS 1-6 SE IEEE MTT-S International Microwave Symposium LA English DT Proceedings Paper CT IEEE/MTT-S International Microwave Symposium CY JUN 03-08, 2007 CL Honolulu, HI SP IEEE MTTS DE satellite communication; Earth terminals; radio receivers; diversity methods; polarization combining; arraying AB Communications with satellites exploring other planets and objects far from Earth is provided by NASA's Deep Space Network (DSN). Deep space by its nature places a limit on return data rates. This adds to mission cost through extended contact time. Methods that increase mission data rates can substantially reduce the number of required ground contacts and overall cost; or, alternatively, they can increase science data return for a fixed amount of contact time. This paper reports on the first in-flight results of using polarization diversity combining in deep space communications to, nearly double the downlink data rate. The DSN and the satellite microwave telecommunications systems are detailed, along with a model of the DSN combining gain. Test results from Mars Odyssey and the New Horizons Mission to Pluto are described, including operational constraints and potential improvements. The significant impact and benefits of this new capability are discussed. C1 [Pham, Timothy] Jet Prop Lab, Pasadena, CA 91109 USA. [Deboy, Christopher] Johns Hopkins Univ, Appl Phys Lab, Laurel, MD USA. RP Pham, T (reprint author), Jet Prop Lab, Pasadena, CA 91109 USA. NR 2 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 0149-645X BN 978-1-4244-0687-6 J9 IEEE MTT S INT MICR PY 2007 BP 942 EP 945 PG 4 WC Engineering, Electrical & Electronic; Optics; Telecommunications SC Engineering; Optics; Telecommunications GA BGV76 UT WOS:000250827402046 ER PT S AU Dengler, RJ Cooper, KB Chattopadhyay, G Mehdi, I Schlecht, E Skalare, A Chen, C Siegel, PH AF Dengler, R. J. Cooper, K. B. Chattopadhyay, G. Mehdi, I. Schlecht, E. Skalare, A. Chen, C. Siegel, P. H. GP IEEE TI 600 GHz Imaging radar with 2 cm range resolution SO 2007 IEEE/MTT-S INTERNATIONAL MICROWAVE SYMPOSIUM DIGEST, VOLS 1-6 SE IEEE MTT-S International Microwave Symposium LA English DT Proceedings Paper CT IEEE/MTT-S International Microwave Symposium CY JUN 03-08, 2007 CL Honolulu, HI SP IEEE MTTS DE submillimeter wave imaging; FMCW chirp radar; submillimeter wave radar; radar imaging; THz radar AB We report the first submillimeter-wave imaging system that has radar ranging capabilities. By frequency-modulating the K-band synthesizers of a single-pixel 630 GHz scanning vector imager and applying a distortion compensation technique in software, we have achieved a range resolution of approximately 2 cm for targets at a range of several meters. Relief images of test objects obtained with our system demonstrate that three-dimensional THz imaging of scanned targets is feasible using a room temperature, all solid-state approach. C1 [Dengler, R. J.; Cooper, K. B.; Chattopadhyay, G.; Mehdi, I.; Schlecht, E.; Skalare, A.; Siegel, P. H.] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Chen, C.] Univ Delaware, EE Dept, Newark, DE 19716 USA. [Siegel, P. H.] CALTECH, Dept Biol, Pasadena, CA 91125 USA. RP Dengler, RJ (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 9 TC 1 Z9 1 U1 2 U2 10 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 0149-645X BN 978-1-4244-0687-6 J9 IEEE MTT S INT MICR PY 2007 BP 1367 EP + PG 2 WC Engineering, Electrical & Electronic; Optics; Telecommunications SC Engineering; Optics; Telecommunications GA BGV76 UT WOS:000250827403061 ER PT S AU Wollack, EJ Vanin, FM AF Wollack, Edward J. Vanin, Felice Maria GP IEEE TI Broadband transitions for micro-machined waveguides SO 2007 IEEE/MTT-S INTERNATIONAL MICROWAVE SYMPOSIUM DIGEST, VOLS 1-6 SE IEEE MTT-S International Microwave Symposium LA English DT Proceedings Paper CT IEEE/MTT-S International Microwave Symposium CY JUN 03-08, 2007 CL Honolulu, HI SP IEEE MTTS DE waveguides; waveguide transitions; waveguide discontinuities ID HORN; ANTENNA AB When chemically micromachining silicon wafers by wet etching, the naturally occurring shapes are trapezoidal or hexagonal instead of rectangular. Practical applications require interfacing these common crossections with standard rectangular waveguides; therefore, efficient transitions with broadband characteristics are necessary for enhancing reliability, simplicity, and cost-effectiveness. This paper presents a straightforward design approach and measurements for convenient broadband transitions. The uses of such interfaces improve compatibility with existing precision waveguide measurement capabilities and facilitate the realization of broadband transitions. C1 [Wollack, Edward J.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Vanin, Felice Maria] Univ Maryland, Dept Elect Engn, College Pk, MD 20740 USA. RP Wollack, EJ (reprint author), NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RI Wollack, Edward/D-4467-2012 OI Wollack, Edward/0000-0002-7567-4451 NR 13 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 0149-645X BN 978-1-4244-0687-6 J9 IEEE MTT S INT MICR PY 2007 BP 1742 EP + PG 2 WC Engineering, Electrical & Electronic; Optics; Telecommunications SC Engineering; Optics; Telecommunications GA BGV76 UT WOS:000250827404060 ER PT S AU Goldsmith, PF AF Goldsmith, Paul F. GP IEEE TI Submillimeter astronomy and Mauna Kea - An overview SO 2007 IEEE/MTT-S INTERNATIONAL MICROWAVE SYMPOSIUM DIGEST, VOLS 1-6 SE IEEE MTT-S INTERNATIONAL MICROWAVE SYMPOSIUM DIGEST LA English DT Proceedings Paper CT IEEE/MTT-S International Microwave Symposium CY JUN 03-08, 2007 CL Honolulu, HI SP IEEE MTTS DE submillimeter wave propagation; submillimeter wave antennas; submillimeter wave spectroscopy AB Astronomy in the submillimeter region of the electromagnetic spectrum, covering wavelengths between 1mm and 0.1 mm, is now just past its 306 anniversary. During this period there has been enormous progress in technology for detecting and analyzing signals. This has led to discovery of astronomical sources not even considered when observations in this wavelength range began. A critical aspect of progress has been the increase in the capability of telescopes. Submillimeter astronomers have changed from "borrowing" optical telescopes to having dedicated telescopes with far greater sensitivity (single antennas) and angular resolution (interferometers). In this paper we review the development of submillimeter telescopes, noting the special role played by instruments located on Mauna Kea. C1 [Goldsmith, Paul F.] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Goldsmith, PF (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 0 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 0149-645X BN 978-1-4244-0687-6 J9 IEEE MTT-S PY 2007 BP 1837 EP 1840 PG 4 WC Engineering, Electrical & Electronic; Optics; Telecommunications SC Engineering; Optics; Telecommunications GA BGV76 UT WOS:000250827404082 ER PT S AU De Geronimo, G Chen, W Fried, J Li, Z Pinelli, DA Rehak, P Vernon, E Gaskin, JA Ramsey, BD Anelli, G AF De Geronimo, Gianluigi Chen, Wei Fried, Jack Li, Zheng Pinelli, Donald A. Rehak, Pavel Vernon, Emerson Gaskin, Jessica A. Ramsey, Brian D. Anelli, Giovanni GP IEEE TI Front-end ASIC for high resolution x-ray spectrometers SO 2007 IEEE NUCLEAR SCIENCE SYMPOSIUM CONFERENCE RECORD, VOLS 1-11 SE IEEE Nuclear Science Symposium Conference Record LA English DT Proceedings Paper CT IEEE Nuclear Science Symposium/Medical Imaging Conference CY OCT 26-NOV 03, 2007 CL Honolulu, HI SP IEEE ID SILICON DRIFT DETECTORS; CHARGE-SENSITIVE PREAMPLIFIER; CONTINUOUS RESET; READOUT CIRCUIT; JFET; CHAMBER AB We present an application specific integrated circuit (ASIC) for high-resolution x-ray spectrometers. The ASIC is designed to read out signals from a pixelated silicon drift detector (SDD). Each hexagonal pixel has an area of 15 mm(2) and an anode capacitance of less than 100 IF. There is no integrated Field Effect transistor (FET) in the pixel, rather, the readout is done by wire-bonding the anodes to the inputs of the ASIC. The ASIC provides 14 channels of low-noise charge amplification, high-order shaping with baseline stabilization, and peak detection with analog memory. The readout is sparse and based on low voltage differential signaling. An interposer provides all the interconnections required to bias and operate the system. The channel dissipates 1.6 mW. The complete 14-pixel unit covers an area of 210 mm2, dissipates 12 mW cm(-2), and can be tiled to cover an arbitrarily large detection area. We measured a preliminary resolution of 172 eV at -35 C on the 6 keV peak of a Fe-55 source. C1 [De Geronimo, Gianluigi; Chen, Wei; Fried, Jack; Li, Zheng; Pinelli, Donald A.; Rehak, Pavel; Vernon, Emerson] Brookhaven Natl Lab, Instrumentat Div, Upton, NY 11973 USA. [Gaskin, Jessica A.; Ramsey, Brian D.] NASA, George C Marshall Space Flight Ctr, Huntsville, AL 35812 USA. [Anelli, Giovanni] CERN, Geneva, Switzerland. RP De Geronimo, G (reprint author), Brookhaven Natl Lab, Instrumentat Div, Upton, NY 11973 USA. NR 28 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1082-3654 BN 978-1-4244-0922-8 J9 IEEE NUCL SCI CONF R PY 2007 BP 26 EP 31 DI 10.1109/NSSMIC.2007.4436283 PG 6 WC Physics, Applied; Imaging Science & Photographic Technology; Physics, Nuclear; Physics, Particles & Fields; Radiology, Nuclear Medicine & Medical Imaging; Spectroscopy SC Physics; Imaging Science & Photographic Technology; Radiology, Nuclear Medicine & Medical Imaging; Spectroscopy GA BHY13 UT WOS:000257380400005 ER PT S AU Hoover, AS Bacrania, MK Dry, D Hastings, EP Lamont, SP Rim, JH Rabin, MW Rudy, CR Vo, DT Beall, JA Doriese, WB Hilton, GC Horansky, RD Irwin, KD Ullom, JN Vale, LR Kilbourne, CA King, J Porter, FS AF Hoover, A. S. Bacrania, M. K. Dry, D. Hastings, E. P. Lamont, S. P. Rim, J. H. Rabin, M. W. Rudy, C. R. Vo, D. T. Beall, J. A. Doriese, W. B. Hilton, G. C. Horansky, R. D. Irwin, K. D. Ullom, J. N. Vale, L. R. Kilbourne, C. A. King, J. Porter, F. S. GP IEEE TI Simulating the response of ultra-high energy resolution X- and gamma-ray microcalorimeter detectors SO 2007 IEEE NUCLEAR SCIENCE SYMPOSIUM CONFERENCE RECORD, VOLS 1-11 SE IEEE Nuclear Science Symposium Conference Record LA English DT Proceedings Paper CT IEEE Nuclear Science Symposium/Medical Imaging Conference CY OCT 26-NOV 03, 2007 CL Honolulu, HI SP IEEE AB Microcalorimeter detectors based on transition-edge sensors coupled to a bulk absorber are an emerging technology for hard X-ray and soft gamma-ray measurements. Monte Carlo simulations codes, like GEANT4, can be a valuable tool for evaluating detector design ideas, interpreting measured data, and predicting detector performance. We report on initial attempts to reproduce measured microcalorimeter data with GEANT4 simulations. C1 [Hoover, A. S.; Bacrania, M. K.; Dry, D.; Hastings, E. P.; Lamont, S. P.; Rim, J. H.; Rabin, M. W.; Rudy, C. R.; Vo, D. T.] Los Alamos Natl Lab, POB 1663, Los Alamos, NM 87545 USA. [Doriese, W. B.; Hilton, G. C.; Horansky, R. D.; Irwin, K. D.; Ullom, J. N.; Vale, L. R.] Natl Inst Stand & Technol, Boulder, CO 80303 USA. [Kilbourne, C. A.; King, J.; Porter, F. S.] NASA, Greenbelt, MD 20771 USA. RP Hoover, AS (reprint author), Los Alamos Natl Lab, POB 1663, Los Alamos, NM 87545 USA. RI Porter, Frederick/D-3501-2012; Rim, Jung/J-5150-2015 OI Porter, Frederick/0000-0002-6374-1119; Rim, Jung/0000-0002-9081-0917 NR 2 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1082-3654 BN 978-1-4244-0922-8 J9 IEEE NUCL SCI CONF R PY 2007 BP 847 EP 849 DI 10.1109/NSSMIC.2007.4436461 PG 3 WC Physics, Applied; Imaging Science & Photographic Technology; Physics, Nuclear; Physics, Particles & Fields; Radiology, Nuclear Medicine & Medical Imaging; Spectroscopy SC Physics; Imaging Science & Photographic Technology; Radiology, Nuclear Medicine & Medical Imaging; Spectroscopy GA BHY13 UT WOS:000257380400183 ER PT S AU Hartsough, NE Iwanczyk, JS Barber, WC Namkung, M Trombka, JI AF Hartsough, Neal E. Iwanczyk, Jan S. Barber, William C. Namkung, Min Trombka, Jacob I. GP IEEE TI Polycrystalline mercuric iodide films for novel detector applications SO 2007 IEEE NUCLEAR SCIENCE SYMPOSIUM CONFERENCE RECORD, VOLS 1-11 SE IEEE Nuclear Science Symposium Conference Record LA English DT Proceedings Paper CT IEEE Nuclear Science Symposium/Medical Imaging Conference CY OCT 26-NOV 03, 2007 CL Honolulu, HI SP IEEE ID RADIATION DETECTORS AB Polycrystalline mercuric iodide (HgI2) films have been in use as direct-conversion detectors for a number of applications including x-ray, gamma-ray, and charged-particle detectors. One application for particle detectors is as an anticoincidence detector used in conjunction with a large-volume scintillator employed as gamma-ray spectrometer. For space-based applications, background high-energy protons interact with the scintillator to produce spurious signals which interfere with the primary gamma-ray data. The shield detector produces a veto signal so that those detection events in the spectrometer which are due to high-energy charged particle interactions can be ignored, improving the quality of the gamma-ray spectrum collected. We are optimizing a sublimation-based film growth process to grow large-area HgI2 active anticoincidence shield detectors directly on planar substrates. The growth process is quick and relatively inexpensive, and results in a shield detector that is just a few hundred microns in thickness, thus saving cost and valuable space and weight for the total instrument package. We present recent results from polycrystalline HgI2 films used for charged-particle detection. These results demonstrate that a novel active anticoincidence shield based on polycrystalline mercuric iodide can act as an alternative to a scintillator/PMT design. C1 [Hartsough, Neal E.; Iwanczyk, Jan S.; Barber, William C.] DxRay Inc, Northridge, CA 91324 USA. [Namkung, Min; Trombka, Jacob I.] NASA, Goddard Space Flight Ctr, Code 661, Greenbelt, MD 20771 USA. RP Hartsough, NE (reprint author), DxRay Inc, Northridge, CA 91324 USA. EM neal.hartsough@dxray.com RI Namkung, Min/E-1533-2012 FU U.S. National Aeronautics and Space Administration [NNG05CA15C] FX This work was supported in part by the U.S. National Aeronautics and Space Administration under Grant No. NNG05CA15C. NR 8 TC 1 Z9 1 U1 0 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1082-3654 BN 978-1-4244-0922-8 J9 IEEE NUCL SCI CONF R PY 2007 BP 1541 EP + DI 10.1109/NSSMIC.2007.4437292 PG 2 WC Physics, Applied; Imaging Science & Photographic Technology; Physics, Nuclear; Physics, Particles & Fields; Radiology, Nuclear Medicine & Medical Imaging; Spectroscopy SC Physics; Imaging Science & Photographic Technology; Radiology, Nuclear Medicine & Medical Imaging; Spectroscopy GA BHY13 UT WOS:000257380401058 ER PT S AU Adams, JH Christl, MJ Kuznetsov, E Parnell, TA Pendleton, GN Watts, JW AF Adams, J. H. Christl, M. J. Kuznetsov, E. Parnell, T. A. Pendleton, G. N. Watts, J. W. GP IEEE TI A radiation dosimeter concept for the lunar surface environment SO 2007 IEEE NUCLEAR SCIENCE SYMPOSIUM CONFERENCE RECORD, VOLS 1-11 SE IEEE Nuclear Science Symposium Conference Record LA English DT Proceedings Paper CT IEEE Nuclear Science Symposium/Medical Imaging Conference CY OCT 26-NOV 03, 2007 CL Honolulu, HI SP IEEE AB A novel silicon detector configuration for radiation dose measurements in an environment where solar energetic particles are of most concern is described. The dosimeter would also measure the dose from galactic cosmic rays. In the lunar environment a large range in particle flux and ionization density must be measured and converted to dose equivalent This could be accomplished with a thick (e.g. 2mm) silicon detector segmented into cubic volume elements "voxels" followed by a second, thin monolithic silicon detector. The electronics needed to implement this detector concept include analog signal processors (ASIC) and a field programmable gate array (FPGA) for data accumulation and conversion to linear energy transfer (LET) spectra and to dose-equivalent (Sievert). Currently available commercial ASIC's and FPGA's are suitable for implementing the analog and digital systems. C1 [Adams, J. H.; Christl, M. J.; Kuznetsov, E.; Parnell, T. A.; Pendleton, G. N.; Watts, J. W.] NASA, George C Marshall Space Flight Ctr, Space Sci Off VP62, Huntsville, AL 35812 USA. RP Adams, JH (reprint author), NASA, George C Marshall Space Flight Ctr, Space Sci Off VP62, Huntsville, AL 35812 USA. EM James.H.Adams@NASA.GOV; Mark.Christl@NASA.GOV; Evgeny.N.Kuznetsov@NASA.GOV; Thomas.A.Parnell@NASA.GOV; Geoff.Pendlton@Dynetics.Com; John.Watts@NASA.GOV FU National Aeronautics and Space Administration FX This work was supported by the National Aeronautics and Space Administration. 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 1082-3654 BN 978-1-4244-0922-8 J9 IEEE NUCL SCI CONF R PY 2007 BP 2074 EP + DI 10.1109/NSSMIC.2007.4436561 PG 2 WC Physics, Applied; Imaging Science & Photographic Technology; Physics, Nuclear; Physics, Particles & Fields; Radiology, Nuclear Medicine & Medical Imaging; Spectroscopy SC Physics; Imaging Science & Photographic Technology; Radiology, Nuclear Medicine & Medical Imaging; Spectroscopy GA BHY13 UT WOS:000257380401167 ER PT S AU Kim, MHY Nikjoo, H Dicello, JF Pisacane, VL Cucinotta, FA AF Kim, Myung-Hee Y. Nikjoo, Hooshang Dicello, John F. Pisacane, Vincent L. Cucinotta, Francis A. GP IEEE TI Comparison of integrated radiation transport models with TEPC measurements for the average quality factors in space flights SO 2007 IEEE NUCLEAR SCIENCE SYMPOSIUM CONFERENCE RECORD, VOLS 1-11 SE IEEE Nuclear Science Symposium Conference Record LA English DT Proceedings Paper CT IEEE Nuclear Science Symposium/Medical Imaging Conference CY OCT 26-NOV 03, 2007 CL Honolulu, HI SP IEEE ID IONS AB The purpose of this work was to test our theoretical model for the interpretation of radiation data measured in space. During the space missions astronauts are exposed to the complex field of radiation type and kinetic energies from galactic cosmic rays (GCRs), trapped protons, and sometimes solar particle events (SPEs). The tissue equivalent proportional counter (TEPC) is a simple, time-dependent approach to radiation monitoring for astronauts on board the International Space Station. Another and a newer approach to microdosimetry is the use of silicon-on-insulator (SOI) technology launched on the MidSTAR-1 mission in low Earth orbit (LEO). In the radiation protection practice, the average quality factor of a radiation field is defined as a function of linear energy transfer (LET), Q(avg)(LET). However, TEPC measures the average quality factor as a function of the lineal energy y, Q(avg)(y), defined as the average energy deposition in a volume divided by the average chord length of the volume. Lineal energy, y, deviates from LET due to energy straggling, delta-ray escape or entry, and nuclear fragments produced in the detector volume. Using an integrated space radiation model (which includes the transport codes BRYNTRN and HZETRN, and the quantum nuclear interaction model QMSFRG) and the response distribution functions of the walled-TEPC, we compared model calculations with the walled-TEPC measurements from NASA missions in LEO in order to develop a method of accurate exposure predictions for the lunar and the Mars missions. Good agreement was found for Q(avg)(y) between the model and measured spectra from past NASA missions. The Q(avg)(y) values for the trapped or the solar protons over-estimate the Q(avg)(LET) values, and the quantities increase with shield thickness due to nuclear fragmentation. The Q(avg)(v) for the complete GCR spectra measured from flight TEPCs under-estimate the Q(avg)(LET). The values for the GCR decrease with the shield thickness. Our analysis for a proper interpretation of observed data supports the use of TEPCs for monitoring the space radiation environment. C1 [Kim, Myung-Hee Y.; Nikjoo, Hooshang] Univ Space Res Assoc, Houston, TX 77058 USA. [Dicello, John F.; Pisacane, Vincent L.] US Naval Acad, Annapolis, MD 21402 USA. [Cucinotta, Francis A.] NASA, Johnson Space Ctr, Houston, TX 77058 USA. RP Kim, MHY (reprint author), Univ Space Res Assoc, Houston, TX 77058 USA. EM myung-hee.y.kim@nasa.gov FU National Space Biomedical Research Institute [NASA NCC 9-58] FX This work was supported in part by the NASA Space Radiation Risk Project and the National Space Biomedical Research Institute under Grant No. NASA NCC 9-58. NR 10 TC 1 Z9 1 U1 0 U2 3 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1082-3654 BN 978-1-4244-0922-8 J9 IEEE NUCL SCI CONF R PY 2007 BP 2362 EP + PG 3 WC Physics, Applied; Imaging Science & Photographic Technology; Physics, Nuclear; Physics, Particles & Fields; Radiology, Nuclear Medicine & Medical Imaging; Spectroscopy SC Physics; Imaging Science & Photographic Technology; Radiology, Nuclear Medicine & Medical Imaging; Spectroscopy GA BHY13 UT WOS:000257380401225 ER PT B AU Rosenzweig, JB Cook, AM Dunning, M England, RJ Musumeci, P Bellaveglia, M Boscolo, M Catani, L Cianchi, A Di Pirro, G Ferrario, M Filippetto, D Gatti, G Palumbo, L Vicario, C Jones, S AF Rosenzweig, J. B. Cook, A. M. Dunning, M. England, R. J. Musumeci, P. Bellaveglia, M. Boscolo, M. Catani, L. Cianchi, A. Di Pirro, G. Ferrario, M. Filippetto, D. Gatti, G. Palumbo, L. Vicario, C. Jones, S. GP IEEE TI Optimum electron bunch creation in a photoinjector using space-charge expansion SO 2007 IEEE PARTICLE ACCELERATOR CONFERENCE, VOLS 1-11 SE IEEE Particle Accelerator Conference LA English DT Proceedings Paper CT IEEE Particle Accelerator Conference CY JUN 25-29, 2007 CL Albuquerque, NM SP IEEE AB Recent studies have shown that by illuminating a photocathode with an ultra-short laser pulse of appropriate transverse profile, a uniform density, ellipsoidally shaped electron bunch can be dynamically formed. Linear space-charge fields then exist in all dimensions inside of the bunch, which minimizes emittance growth. Here we study this process, and its marriage to the standard emittance compensation scenario that is implemented in most modem photoinjectors. We show that the two processes are compatible, with simulations indicating that a very high brightness beam can be obtained. An initial time-resolved expenment has been performed at the SPARC injector in Frascati, involving Cerenkov radiation produced at an aerogel. We discuss the results of this preliminary experiment, as well as plans for future experiments at the UCLA Pegasus laboratory to resolve the ellipsoidal bunch shape at low energy. Future measurements at high energy based on fs resolution RF sweepers are discussed. C1 [Rosenzweig, J. B.; Cook, A. M.; Dunning, M.; England, R. J.; Musumeci, P.] Univ Calif Los Angeles, Particle Beam Phys Lab, Dept Phys & Astron, Los Angeles, CA 90095 USA. [Bellaveglia, M.; Boscolo, M.; Catani, L.; Cianchi, A.; Di Pirro, G.; Ferrario, M.; Filippetto, D.; Gatti, G.; Palumbo, L.; Vicario, C.] Ist Nazl Fis Nucl, Nazl Frascati Lab, Rome, Italy. [Jones, S.] CALTECH, Jet Prop Lab, Pasadena, CA 91101 USA. RP Rosenzweig, JB (reprint author), Univ Calif Los Angeles, Particle Beam Phys Lab, Dept Phys & Astron, Los Angeles, CA 90095 USA. RI Cook, Alan/D-2557-2013; Gatti, Giancarlo/K-3345-2013 OI Gatti, Giancarlo/0000-0001-7730-7893 NR 10 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-0916-7 J9 IEEE PART ACC CONF PY 2007 BP 2288 EP + PG 2 WC Engineering, Electrical & Electronic; Physics, Particles & Fields SC Engineering; Physics GA BHP10 UT WOS:000255096302232 ER PT B AU MacDougall, F Ennis, J Yang, XH Schneider, M MacDonald, JR Fox, P Hopkins, T Jow, TR Ho, J Yen, SPS AF MacDougall, Fred Ennis, Joel Yang, Xiao Hui Schneider, Mark MacDonald, J. Ross Fox, Phil Hopkins, Tom Jow, T. Richard Ho, Janet Yen, S. P. S. GP IEEE TI The development and performance of high energy density capacitors SO 2007 IEEE PULSED POWER CONFERENCE, VOLS 1-4 LA English DT Proceedings Paper CT 16th IEEE International Pulsed Power Conference CY JUN 17-22, 2007 CL Albuquerque, NM SP IEEE, Sandia Natl Labs, Natl Secur Technologies, ICAR, Gen Atom Fus Energy Res, Ktech Corp, Gen Atom Elect Syst, HVR, Lawrence Livermore Natl Lab, Los Alamos Natl Lab, Tera Anal Ltd, Tech X, Ultravolt, Major Tool & Machine, Voss Sci, BAE Syst, Saft, Diversified Technologies Inc, ABB, Axsys Technologies, Agilent Technologies, Appl Technologies Pulse Sci, TSP, Pulse Power Solut, LLC, e2v, Barth Elect Inc, Novacap, Lambda, Powerex, Strangenes Ind Inc, SBE, HV Component Associates, Field Precis AB The US Army Research Laboratory has sponsored a capacitor development program for film dielectric capacitors that has yielded both superior capacitor performance and the ability to evaluate new polymers on a fast track. The performance of recently developed capacitors, projections for pulse power capacitors in the near term, and the development track for new polymers will be discussed as well as the ability to support efforts by both industry and academic researchers to bring new polymers to a finished film capacitor product quickly. C1 [MacDougall, Fred; Ennis, Joel; Yang, Xiao Hui; Schneider, Mark; MacDonald, J. Ross; Fox, Phil; Hopkins, Tom] Gen Atom Elect Syst Inc, 4949 Greencraig Lane, San Diego, CA 92123 USA. [Jow, T. Richard; Ho, Janet] Army Res Lab, Adelphi, MD 20783 USA. [Yen, S. P. S.] Jet Prop Lab, Pasadena, CA 91109 USA. RP MacDougall, F (reprint author), Gen Atom Elect Syst Inc, 4949 Greencraig Lane, San Diego, CA 92123 USA. FU U.S. Army Research Laboratory [W911QX-04-D-0003] FX Portions of the research reported in this document/presentation was performed in connection with contract W911QX-04-D-0003 with the U.S. Army Research Laboratory. The views and conclusions contained in this document/presentation are those o f the authors and should not be interpreted as presenting the official policies or position, either expressed or implied, of the U.S. Army Research Laboratory or the U.S. Government unless so designated by other authorized documents. Citation of manufacturers or trade names does not constitute an official endorsement or appr oval of the use there of. The U.S. Government is authorized to reproduce and distribute reprints for Government purposes not with standing any copyright notation here on. NR 2 TC 0 Z9 0 U1 0 U2 3 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-0913-6 PY 2007 BP 278 EP + DI 10.1109/PPPS.2007.4651838 PG 2 WC Engineering, Electrical & Electronic; Physics, Applied; Physics, Nuclear SC Engineering; Physics GA BHJ74 UT WOS:000253619300060 ER PT S AU Thrivikraman, TK Kuo, WML Comeau, JP Sutton, AK Cressler, JD Marshall, PW Mitchell, MA AF Thrivikraman, Tushar K. Kuo, Wei-Min Lance Comeau, Jonathan P. Sutton, Akil K. Cressler, John D. Marshall, Paul W. Mitchell, Mark A. BE Kushner, L TI A 2 mW, sub-2 dB noise figure, SiGe low-noise amplifier for X-band high-altitude or space-based radar applications SO 2007 IEEE RADIO FREQUENCY INTEGRATED CIRCUITS (RFIC) SYMPOSIUM, DIGEST OF PAPERS SE IEEE Radio Frequency Integrated Circuits Symposium LA English DT Proceedings Paper CT IEEE Radio Frequency Integrated Circuits Symposium (RFIC) CY JUN 03-05, 2007 CL Honolulu, HI SP IEEE Microwave Theory & Tech Soc, IEEE Elect Devices Soc, IEEE Solid State Circuits Soc ID GHZ AB This paper presents a low-power X-band low-noise amplifier (LNA) implemented in silicon-germanium (SiGe) technology targeting high-altitude or space-based low-power density phased-array radar systems. To our knowledge, this X-band LNA is the first in a Si-based technology to achieve less than 2 dB mean noise figure while dissipating only 2 mW from a 1.5 V power supply. The gain of the circuit is 10 dB at 10 GHz with an IIP3 of 0 dBm. In addition to standard amplifier characterization, the LNA's total dose radiation response has been evaluated. C1 [Thrivikraman, Tushar K.; Kuo, Wei-Min Lance; Comeau, Jonathan P.; Sutton, Akil K.; Cressler, John D.] Georgia Inst Technol, Sch Elect & Comp Engn, 777 Atlantic Dr NW, Atlanta, GA 30332 USA. [Marshall, Paul W.] NASA, Brookneal, VA 24528 USA. [Mitchell, Mark A.] Georgia Tech Res Inst, Atlanta, GA 30332 USA. RP Thrivikraman, TK (reprint author), Georgia Inst Technol, Sch Elect & Comp Engn, 777 Atlantic Dr NW, Atlanta, GA 30332 USA. EM uhrivi@ece.gatech.edu FU Georgia Tech Research Institute Fellows Council; NASA-NEPP; DTRA; SiGe Devices and Circuits Group; Georgia Electronic Design Center at Georiga Tech FX The authors are grateful for the support of the Georgia Tech Research Institute Fellows Council and Dr. D. Parekh for IRAD project support; NASA-NEPP and DTRA for radiation testing support; B. Jun, A. Sutton, R. Diestelhorst and the members of the SiGe Devices and Circuits Group; and Georgia Electronic Design Center at Georiga Tech. NR 13 TC 17 Z9 17 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1529-2517 BN 978-1-4244-0530-5 J9 IEEE RAD FREQ INTEGR PY 2007 BP 629 EP + DI 10.1109/RFIC.2007.380962 PG 2 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BGL30 UT WOS:000248148800142 ER PT B AU Diaz-Calderon, A Backes, PG Bonitz, RG AF Diaz-Calderon, Antonio Backes, Paul G. Bonitz, Robert G. GP IEEE TI An autonomous robotic scooping approach for planetary sample acquisition SO 2007 IEEE/RSJ INTERNATIONAL CONFERENCE ON INTELLIGENT ROBOTS AND SYSTEMS, VOLS 1-9 LA English DT Proceedings Paper CT IEEE/RSJ International Conference on Intelligent Robots and Systems CY OCT 29-NOV 02, 2007 CL San Diego, CA SP IEEE, RSJ AB This paper describes a system design concept to enable automated sample acquisition on planetary surfaces without the use of additional sensor information such as cameras and force/torque sensors. A simple and robust solution is presented to the unique problems encountered in in situ science applications with its tight constraints on mass, power, computing resources and lack of flight-qualified hardware. Problems addressed include end-effector contact detection, trajectory generation, hardware fault monitoring and autonomous determination of terrain profile. C1 [Diaz-Calderon, Antonio; Backes, Paul G.; Bonitz, Robert G.] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Diaz-Calderon, A (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 9 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-0912-9 PY 2007 BP 827 EP 832 PG 6 WC Automation & Control Systems; Computer Science, Artificial Intelligence; Engineering, Manufacturing; Engineering, Electrical & Electronic; Robotics SC Automation & Control Systems; Computer Science; Engineering; Robotics GA BHL44 UT WOS:000254073200130 ER PT B AU Nayar, HD Nesnas, IAD AF Nayar, Hari D. Nesnas, Issa A. D. GP IEEE TI Re-usable kinematic models and algorithms for manipulators and vehicles SO 2007 IEEE/RSJ INTERNATIONAL CONFERENCE ON INTELLIGENT ROBOTS AND SYSTEMS, VOLS 1-9 LA English DT Proceedings Paper CT IEEE/RSJ International Conference on Intelligent Robots and Systems CY OCT 29-NOV 02, 2007 CL San Diego, CA SP IEEE, RSJ AB A generalized kinematic modeling framework, called Mechanism-Model, has been developed for use in the CLARAty robotic reusable software. Mechanism-Model supports a wide range of systems - from manipulator arms to legged and wheeled rovers. It also enables the development of generalized kinematics, dynamics and collision detection algorithms. In this paper, we describe the unified modeling approach used in Mechanism-Model and provide details of its object-oriented implementation in C++. We also present an example application illustrating use of Mechanism-Model. C1 [Nayar, Hari D.; Nesnas, Issa A. D.] CALTECH, Jet Prop Lab, Pasadena, CA 91001 USA. RP Nayar, HD (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr,MS 82-105, Pasadena, CA 91001 USA. EM Hari.D.Nayar@jpl.nasa.gov; Issa.A.Nesnas@jpl.nasa.gov NR 11 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-0912-9 PY 2007 BP 839 EP 844 PG 6 WC Automation & Control Systems; Computer Science, Artificial Intelligence; Engineering, Manufacturing; Engineering, Electrical & Electronic; Robotics SC Automation & Control Systems; Computer Science; Engineering; Robotics GA BHL44 UT WOS:000254073200132 ER PT B AU Meyer, C Deans, M AF Meyer, C. Deans, M. GP IEEE TI Content based retrieval of images for planetary exploration SO 2007 IEEE/RSJ INTERNATIONAL CONFERENCE ON INTELLIGENT ROBOTS AND SYSTEMS, VOLS 1-9 LA English DT Proceedings Paper CT IEEE/RSJ International Conference on Intelligent Robots and Systems CY OCT 29-NOV 02, 2007 CL San Diego, CA SP IEEE, RSJ ID SEGMENTATION AB Planetary missions generate a large quantity of image data. In flight operations or on servers such as Planetary Data Systems (PDS) these data products are only searchable by keys such as the Sol, spacecraft clock, or rover motion counter index, with little connection to the semantic content of the images. During mission science operations the science team typically pores over each and every data product returned, which may not require more sophisticated organization and search tools. However, for analyzing existing image databases with thousands or millions of images, manual searching, matching, or classification is intractable. In this paper, we present a method for matching images based on similarities in visual texture. For every image in a database, a series of filters are used to compute the response to localized frequencies and orientations. Filter responses are turned into a low dimensional descriptor vector, generating a 37 dimensional fingerprint. At query time, fingerprints are quickly matched to find images with similar appearance. Image databases containing several thousand images are pre-processed offline in a matter of hours. Image matches from the database are found in a matter of seconds. We have demonstrated this image matching technique using three sources of data and carried out user tests to evaluate matching performance by hand labeling results. User tests verify approximately 40% false positive rate within the top 14 matches. This represents a powerful search tool for databases of thousands of images where the a priori match probability for an image might be less than 1%. C1 [Meyer, C.; Deans, M.] NASA, Ames Res Ctr, IRG Intelligent Robot Lab, Moffett Field, CA 94035 USA. RP Meyer, C (reprint author), CSEM Swiss Ctr Elect & Microtechnol, CH-6055 Alpnach Dorf, Switzerland. EM celine.meyer@csem.ch; mdeans@arc.nasa.gov NR 22 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-0912-9 PY 2007 BP 1383 EP 1388 PG 6 WC Automation & Control Systems; Computer Science, Artificial Intelligence; Engineering, Manufacturing; Engineering, Electrical & Electronic; Robotics SC Automation & Control Systems; Computer Science; Engineering; Robotics GA BHL44 UT WOS:000254073200219 ER PT B AU Kozma, R Hunstberger, T Aghazarian, H Freeman, WJ AF Kozma, Robert Hunstberger, Terry Aghazarian, Hrand Freeman, Walter J. GP IEEE TI Implementing intentional robotics principles using SSR2K platform SO 2007 IEEE/RSJ INTERNATIONAL CONFERENCE ON INTELLIGENT ROBOTS AND SYSTEMS, VOLS 1-9 LA English DT Proceedings Paper CT IEEE/RSJ International Conference on Intelligent Robots and Systems CY OCT 29-NOV 02, 2007 CL San Diego, CA SP IEEE, RSJ ID MODEL; NAVIGATION; ARCHITECTURE; BEHAVIOR; SYSTEMS AB We demonstrate the operation of the SODAS approach (Self-organized Ontogenetic Development of Autonomous Systems) for on-line processing of sensory inputs and onboard dynamic behavior tasking using SRR2K (Sample Return Rover) platform at the Planetary Robotics indoor facility of HE SODAS employs a biologically inspired dynamic neural network architecture operating on the principle of chaotic neural dynamics manifesting intentionality in the style of brains. Intentional behavior includes the cyclic operation of prediction, testing by action, sensing, perceiving, and assimilating the learned features. The experiments illustrate robust obstacle avoidance combined with goal-oriented navigation by the SRR2K robot. C1 [Kozma, Robert] Univ Memphis, 373 Dunn Hall, Memphis, TN 38152 USA. [Kozma, Robert] Air Force Res Lab, Bedford, MA 01731 USA. [Hunstberger, Terry; Aghazarian, Hrand] CALTECH, Jet Prop Lab, Planetary Robot Lab, Pasadena, CA 91109 USA. [Freeman, Walter J.] Univ Calif Berkeley, Grad Sch, MCB, Div Neurobiol, Berkeley, CA 94720 USA. RP Kozma, R (reprint author), Univ Memphis, 373 Dunn Hall, Memphis, TN 38152 USA. EM rkozma@memphis.edu; Terry.Huntsberger@jpl.nasa.gov; Hrand.Aghazarian@jpl.nasa.gov; dfreeman@berkeley.edu RI Kozma, Robert/C-6365-2013 FU National Aeronautics and Space Administration; Neville Marzwell of the Advanced Concepts Office at JPL; Computing, Information and Communications Technology (CICT) Program under NASA HQ; Mars Technology Program Office at JPL FX The research described in this paper was carried out at the Jet Propulsion Laboratory, California Institute of Technology, under a contract with the National Aeronautics and Space Administration. The first author (RK) would like to thank Neville Marzwell of the Advanced Concepts Office at JPL for his financial support of this project. The additional authors (TH, HA) would like to thank the Computing, Information and Communications Technology (CICT) Program under NASA HQ and the Mars Technology Program Office at JPL for their financial support of this project. The authors would also like to thank the members of the Planetary Robotics Laboratory at JPL for their technical support. The help by Roman Ilin, U of Memphis is greatly appreciated. NR 44 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-0912-9 PY 2007 BP 2268 EP + PG 2 WC Automation & Control Systems; Computer Science, Artificial Intelligence; Engineering, Manufacturing; Engineering, Electrical & Electronic; Robotics SC Automation & Control Systems; Computer Science; Engineering; Robotics GA BHL44 UT WOS:000254073201137 ER PT B AU Sigel, DA Wettergreen, D AF Sigel, Deborah A. Wettergreen, David GP IEEE TI Star tracker celestial localization system for a lunar rover SO 2007 IEEE/RSJ INTERNATIONAL CONFERENCE ON INTELLIGENT ROBOTS AND SYSTEMS, VOLS 1-9 LA English DT Proceedings Paper CT IEEE/RSJ International Conference on Intelligent Robots and Systems CY OCT 29-NOV 02, 2007 CL San Diego, CA SP IEEE, RSJ AB An artificial satellite independent localization system for a lunar rover using the stars for navigation is described. The system uses a wide field-of-view star tracker and wide range high precision inclinometers to determine location on the Moon using quaternion output from the star tracker along with pitch and roll data from the inclinometer. C1 [Sigel, Deborah A.] NASA, Jet Prop Lab, Pasadena, CA 91109 USA. [Wettergreen, David] Carnegie Mellon Univ, Inst Robot, Pittsburgh, PA 15213 USA. RP Sigel, DA (reprint author), NASA, Jet Prop Lab, Pasadena, CA 91109 USA. EM dsigel@alumni.cmu.edu; dsw@ri.cmu.edu FU National Science Foundation Graduate Research Fellowship, utilized at Carnegie Mellon University FX This work was supported in part by the National Science Foundation Graduate Research Fellowship, utilized at Carnegie Mellon University. NR 13 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-0912-9 PY 2007 BP 2857 EP + PG 2 WC Automation & Control Systems; Computer Science, Artificial Intelligence; Engineering, Manufacturing; Engineering, Electrical & Electronic; Robotics SC Automation & Control Systems; Computer Science; Engineering; Robotics GA BHL44 UT WOS:000254073201239 ER PT B AU Gurkan, D Yuan, X Benhaddou, D Figueroa, F Morris, J AF Gurkan, D. Yuan, X. Benhaddou, D. Figueroa, F. Morris, J. GP IEEE TI Sensor networking testbed with IEEE 1451 compatibility and network performance monitoring SO 2007 IEEE SENSORS APPLICATIONS SYMPOSIUM LA English DT Proceedings Paper CT 2nd IEEE Sensors Applications Symposium CY FEB 06-08, 2007 CL San Diego, CA ID DISTRIBUTED DECISION FUSION AB Design and implementation of a testbed for testing and verifying IEEE 1451-eonipatible sensor systems with network performance monitoring is Of significant importance. The performance parameters measurement as well as decision support systems implementation will enhance the understanding of sensor systems with plug-and-play capabilities. The paper will present the design aspects for such a testbed enviroment under development at University of Houston in collaboration with NASA Stennis Space Center SSST (Smart Sensor System Testbed). C1 [Gurkan, D.; Yuan, X.; Benhaddou, D.; Figueroa, F.; Morris, J.] Univ Houston, Dept Engn Technol, Houston, TX 77004 USA. [Figueroa, F.; Morris, J.] NASA, Stennis Space Ctr, Mississippi State, MS USA. RP Gurkan, D (reprint author), Univ Houston, Dept Engn Technol, Houston, TX 77004 USA. EM dgurkan@uh.edu FU NASA [NNS06 ZBAOOJC] FX The authors would like to thank NASA for funding this work under CAN agreement no.NNS06 ZBAOOJC. 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 BN 978-1-4244-0677-7 PY 2007 BP 1 EP + PG 2 WC Engineering, Electrical & Electronic; Remote Sensing SC Engineering; Remote Sensing GA BGR17 UT WOS:000250041200001 ER PT B AU Knuth, KH Tse, MK Choinsky, J Maunu, HA Carbon, DF AF Knuth, Kevin H. Tse, Man Kit Choinsky, Joshua Maunu, Haley A. Carbon, Duane F. GP IEEE TI Bayesian source separation applied to identiefying complex organic molecules in space SO 2007 IEEE/SP 14TH WORKSHOP ON STATISTICAL SIGNAL PROCESSING, VOLS 1 AND 2 LA English DT Proceedings Paper CT 14th IEEE/SP Workshop on Statistical Signal Processing CY AUG 26-29, 2007 CL Madison, WI SP IEEE, SP DE source separation; Bayesian; spectral estimation; astrophysics; biochemistry ID POLYCYCLIC AROMATIC-HYDROCARBONS; UNIDENTIFIED INFRARED-EMISSION AB Emission from a class of benzene-based molecules known as Polycyclic Aromatic Hydrocarbons (PAHs) dominates the infrared spectrum of star-forming regions. The observed emission appears to arise from the combined emission of numerous PAH species, each with its unique spectrum. Linear superposition of the PAH spectra identifies this problem as a source separation problem. It is, however, of a formidable class of source separation problems given that different PAH sources potentially number in the hundreds, even thousands, and there is only one measured spectral signal for a given astrophysical site. Fortunately, the source spectra of the PAHs are known, but the signal is also contaminated by other spectral sources. We describe our ongoing work in developing Bayesian source separation techniques relying on nested sampling in conjunction with an ON/OFF mechanism enabling simultaneous estimation of the probability that a particular PAH species is present and its contribution to the spectrum. C1 [Knuth, Kevin H.; Tse, Man Kit; Choinsky, Joshua; Maunu, Haley A.] SUNY Albany, Dept Phys, Albany, NY 12222 USA. [Carbon, Duane F.] NASA, Ames Res Ctr, Adv Supercomp Div, Moffett Field, CA USA. RP Knuth, KH (reprint author), SUNY Albany, Dept Phys, Albany, NY 12222 USA. FU NASA AISRP [NNH05ZDA001] FX Supported by NASA AISRP NNH05ZDA001 NR 6 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-1197-9 PY 2007 BP 346 EP + DI 10.1109/SSP.2007.4301277 PG 2 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BHI51 UT WOS:000253416000072 ER PT B AU Lopes, CG Satorius, E Estabrook, P Sayed, AH AF Lopes, C. G. Satorius, E. Estabrook, P. Sayed, A. H. GP IEEE TI Efficient adaptive carrier tracking for Mars to Earth communications during entry, descent and landing SO 2007 IEEE/SP 14TH WORKSHOP ON STATISTICAL SIGNAL PROCESSING, VOLS 1 AND 2 LA English DT Proceedings Paper CT 14th IEEE/SP Workshop on Statistical Signal Processing CY AUG 26-29, 2007 CL Madison, WI SP IEEE, SP DE adaptive filters; frequency estimation; combination of filters; Mars exploration ID MULTIPLE SINUSOIDS; MAXIMUM-LIKELIHOOD; FREQUENCY; FILTERS AB In the Mars rover missions the signals transmitted back to Earth travel under low SNR conditions in highly non-stationary channels [1, 2]. During the entry, descent and landing phase (EDL), the spacecraft high dynamics yields severe Doppler effects. We propose a robust and low complexity scheme to estimate and track carrier frequency from the received signals at the Earth end. The method employs a hierarchical arrangement of convex linear prediction cells that is dynamically adapted to respond to the channel conditions. The adaptive combination is able to outperform the best individual estimator in the set, leading to a universal scheme for frequency estimation and tracking. In order to compensate the lag error effect, we explore an efficient forward and backward aggregation scheme that improves considerably the frequency RMS error as compared to the original method [3]. C1 [Lopes, C. G.; Sayed, A. H.] Univ Calif Los Angeles, Dept Elect Engn, Los Angeles, CA 90095 USA. [Satorius, E.; Estabrook, P.] Jet Prop Lab, Pasadena, CA 91109 USA. RP Lopes, CG (reprint author), Univ Calif Los Angeles, Dept Elect Engn, Los Angeles, CA 90095 USA. EM Edgar.H.Satorius@jpl.nasa.gov; Polly.Estabrook@jpl.nasa.gov FU Jet Propulsion Laboratory [1276256]; NSF [ECS-0601266]; CAPES, Brazil [1168/01-0] FX This material was supported by the Jet Propulsion Laboratory under award 1276256 and by NSF award ECS-0601266. The first author was also supported by a fellowship from CAPES, Brazil, under award 1168/01-0. NR 14 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-1197-9 PY 2007 BP 517 EP + DI 10.1109/SSP.2007.4301312 PG 2 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BHI51 UT WOS:000253416000107 ER PT B AU Frank, J AF Frank, Jeremy GP IEEE TI Using data mining to enhance automated planning and scheduling SO 2007 IEEE Symposium on Computational Intelligence and Data Mining, Vols 1 and 2 LA English DT Proceedings Paper CT IEEE Symposium on Computational Intelligence and Data Mining CY APR 01-05, 2007 CL Honolulu, HI SP IEEE ID SEARCH; FF AB Automated planning is a combinatorial problem that is important to many NASA endeavors, including ground operations and control applications for unmanned and manned space flight. There is significant value to integrating planning and data mining to create better planners. We describe current work in this area, covering uses of data mining to speed up planners, improve the quality of plans returned by planners, and learn domain models for automated planners. The central contribution of this paper is a snap shot of the state of the art in integrating these technologies and a summary of challenges and open research issues. C1 NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Frank, J (reprint author), NASA, Ames Res Ctr, Mail Stop N269-3, Moffett Field, CA 94035 USA. NR 22 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-0705-7 PY 2007 BP 251 EP 260 DI 10.1109/CIDM.2007.368881 PG 10 WC Computer Science, Artificial Intelligence SC Computer Science GA BGO89 UT WOS:000249119800038 ER PT B AU Granat, R Aydin, G Pierce, M Qi, ZG Bock, Y AF Granat, Robert Aydin, Galip Pierce, Marlon Qi, Zhigang Bock, Yehuda GP IEEE TI Analysis of streaming GPS measurements of surface displacement through a web services environment SO 2007 IEEE SYMPOSIUM ON COMPUTATIONAL INTELLIGENCE AND DATA MINING, VOLS 1 AND 2 LA English DT Proceedings Paper CT IEEE Symposium on Computational Intelligence and Data Mining CY APR 01-05, 2007 CL Honolulu, HI SP IEEE ID HIDDEN MARKOV MODEL; CASCADIA SUBDUCTION ZONE; SPEECH RECOGNITION; SLIP; SILENT; SLOW; EARTHQUAKES; JAPAN AB We present a method for performing mode classification of real-time streams of GPS surface position data. Our approach has two parts: an algorithm for robust, unconstrained fitting of hidden Markov models (HMMs) to continuous-valued time series, and SensorGrid technology that manages data streams through a series of filters coupled with a publish/subscribe messaging system. The SensorGrid framework enables strong connections between data sources, the HMM time series analysis software, and users. We demonstrate our approach through a web portal environment through which users can easily access data from the SCIGN and SOPAC GPS networks in Southern California, apply the analysis method, and view results. Ongoing real-time mode classifications of streaming GPS data are displayed in a map-based visualization interface. C1 [Granat, Robert] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Aydin, Galip; Qi, Zhigang] Indiana Univ, Dept Comp Sci, Bloomington, IN 47404 USA. [Aydin, Galip; Pierce, Marlon; Qi, Zhigang] Indiana Univ, Commun Grids Lab, Bloomington, IN 47404 USA. [Bock, Yehuda] Univ Calif San Diego, Scrips Inst Oceanog, La Jolla, CA 92093 USA. RP Granat, R (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM granat@jpl.nasa.gov; gaydin@cs.indiana.edu; mpierce@cs.indiana.edu; zqi@cs.indiana.edu; ybock@ucsd.edu OI Pierce, Marlon/0000-0002-9582-5712 FU dvanced Information Systems Technology Program of NASAs Earth Sun System Technology Office; NASA SENH [NAG5-13269]; NASA ACCESS [NNG06GG94A] FX This work was supported by the Advanced Information Systems Technology Program of NASA's Earth-Sun System Technology Office and by NASA SENH grant NAG5-13269 and NASA ACCESS grant NNG06GG94A. Use of the Geodetics, Inc. RTD software was provided by UCSD. NR 28 TC 3 Z9 3 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-0705-7 PY 2007 BP 750 EP 757 DI 10.1109/CIDM.2007.368951 PG 8 WC Computer Science, Artificial Intelligence SC Computer Science GA BGO89 UT WOS:000249119800108 ER PT B AU Veeramachaneni, K Yan, WZ Goebel, K Osadciw, L AF Veeramachaneni, Kalyan Yan, Weizhong Goebel, Kai Osadciw, Lisa GP IEEE TI Improving classifier fusion using particle swarm optimization SO 2007 IEEE SYMPOSIUM ON COMPUTATIONAL INTELLIGENCE IN MULTI-CRITERIA DECISION MAKING LA English DT Proceedings Paper CT 1st IEEE Symposium of Computational Intelligence in Multicriteria Decision Making CY APR 01-05, 2007 CL Honolulu, HI SP IEEE DE decision level fusion; multiple classifiers fusion; particle swarm optimization ID SENSOR DETECTION SYSTEMS AB Both experimental and theoretical studies have proved that classifier fusion can be effective in improving overall classification performance. Classifier fusion can be performed on either score (raw classifier outputs) level or decision level. While tremendous research interests have been on score-level fusion, research work for decision-level fusion is sparse. This paper presents a particle swarm optimization based decision-level fusion scheme for optimizing classifier fusion performance. Multiple classifiers are fused at the decision level, and the particle swarm optimization algorithm finds optimal decision threshold for each classifier and the optimal fusion rule. Specifically, we present an optimal fusion strategy for fusing multiple classifiers to satisfy accuracy performance requirements, as applied to a real-world classification problem. The optimal decision fusion technique is found to perform significantly better than the conventional classifier fusion methods, i.e., traditional decision level fusion and averaged sum rule. C1 [Veeramachaneni, Kalyan; Osadciw, Lisa] Syracuse Univ, Dept EECS, Syracuse, NY 13210 USA. [Yan, Weizhong] GE Global Change Ctr, Niskayuna, NY USA. [Goebel, Kai] NASA, Ames Res Ctr, Moffett Field, CA USA. RP Veeramachaneni, K (reprint author), Syracuse Univ, Dept EECS, Syracuse, NY 13210 USA. EM kveerama@syr.edu; yan@crd.ge.com; goebel@email.arc.nasa.com; laosadci@syr.edu 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 BN 978-1-4244-0702-6 PY 2007 BP 128 EP + DI 10.1109/MCDM.2007.369427 PG 2 WC Computer Science, Artificial Intelligence SC Computer Science GA BGM53 UT WOS:000248485300020 ER PT S AU Brown, P Hartmann, P Schellhase, A Powers, A Brown, T Hartmann, C Gaines, D AF Brown, Paul Hartmann, Paul Schellhase, Amy Powers, Annie Brown, Tim Hartmann, Clinton Gaines, Darryl GP IEEE TI Asset tracking on the International Space Station using global SAW tag RFID technology SO 2007 IEEE ULTRASONICS SYMPOSIUM PROCEEDINGS, VOLS 1-6 SE Ultrasonics Symposium LA English DT Proceedings Paper CT IEEE Ultrasonics Symposium CY OCT 28-31, 2007 CL New York, NY SP IEEE DE SAW RFID; global SAW tag; GST; International Space Station; asset tracking AB Final preparations are underway to test Global SAW Tag (GST) RFID technology [1, 2] for tracking assets aboard the International Space Station (ISS) [3]. This will be the first test of RFID technology on ISS. It is planned for early 2008 by the Expedition 16 crew. It will evaluate the ability of SAW RFID to track consumable items while packed in standard crew bags. The GST system was selected based on its signal penetration ability and its anti-collision capabilities that allow reliable detection of tags even when placed on, behind, and between items with high liquid and metal content in randomly packed crew bags. Substantial savings of highly-valuable crew time is projected with corresponding improvements in ISS crew productivity. C1 [Brown, Paul; Hartmann, Paul; Hartmann, Clinton] RF SAW Inc, Richardson, TX USA. [Schellhase, Amy] Johnson Space Ctr, Barrios Technol, Houston, TX USA. [Powers, Annie; Brown, Tim; Gaines, Darryl] Johnson Space Ctr, NASA, Houston, TX USA. RP Brown, P (reprint author), RF SAW Inc, Richardson, TX USA. NR 2 TC 8 Z9 8 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1051-0117 BN 978-1-4244-1383-6 J9 ULTRASON PY 2007 BP 72 EP + DI 10.1109/ULTSYM.2007.31 PG 2 WC Acoustics; Biophysics; Engineering, Electrical & Electronic; Physics, Applied; Imaging Science & Photographic Technology SC Acoustics; Biophysics; Engineering; Physics; Imaging Science & Photographic Technology GA BHM55 UT WOS:000254281800016 ER PT B AU Costello, DJ Pusane, AE Jones, CR Divsalar, D AF Costello, Daniel J., Jr. Pusane, Ali Ernre Jones, Christopher R. Divsalar, Dariush GP IEEE TI A comparison of ARA- and protograph-based LDPC block and convolutional codes SO 2007 INFORMATION THEORY AND APPLICATIONS WORKSHOP LA English DT Proceedings Paper CT IEEE Information Theory and Applications Workshop CY FEB, 2006 CL Univ Calif San Diego, La Jolla, CA HO Univ Calif San Diego AB ARA- and protograph-based LDPC codes are capable of achieving error performance similar to randomly constructed codes while enjoying several implementation advantages as a result of their structure. LDPC convolutional codes can be derived from these codes through an unwrapping process. In this paper, we review the unwrapping process as well as the pipeline decoder that allows continuous decoding of LDPC convolutional codes. Computer simulations are then used to demonstrate that the unwrapped convolutional codes achieve a "convolutional gain" in error performance. We conjecture that this is due to the concatenation of many constraint lengths worth of received symbols in the pipeline decoding process. The consequences of this improved performance are examined in terms of factors related to decoder implementation: processor size, memory requirements, and decoding delay (latency). Finally, given identical protograph kernels, we compare derived block and convolutional codes based on the above measures. C1 [Costello, Daniel J., Jr.; Pusane, Ali Ernre] Univ Notre Dame, Dept Elect Engn, Notre Dame, IN 46556 USA. [Jones, Christopher R.; Divsalar, Dariush] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Costello, DJ (reprint author), Univ Notre Dame, Dept Elect Engn, Notre Dame, IN 46556 USA. EM Costello.2@nd.edu; Pusane.1@nd.edu; crjones@jpl.nasa.gov; dariush.divsalar@jpl.nasa.gov RI Pusane, Ali/A-2648-2016 OI Pusane, Ali/0000-0002-8412-6684 FU NSF [CCR02-05310, CCF05-15012]; NASA [NNG05GH73G]; Jet Propulsion Laboratory/California Institute of Technology FX This work was supported in part by NSF Grants CCR02-05310, CCF05-15012, NASA Grant NNG05GH73G, and at the Jet Propulsion Laboratory/California Institute of Technology under a contract with NASA. 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 978-0-615-15314-8 PY 2007 BP 109 EP + PG 3 WC Computer Science, Information Systems; Computer Science, Interdisciplinary Applications; Computer Science, Theory & Methods; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BGV69 UT WOS:000250812500017 ER PT B AU Simon, M Divsalar, D AF Simon, Marvin Divsalar, Dariush GP IEEE TI When is differential detection optimum for ideal and partially coherent reception/demodulation of M-PSK? SO 2007 INFORMATION THEORY AND APPLICATIONS WORKSHOP LA English DT Proceedings Paper CT IEEE Information Theory and Applications Workshop CY FEB, 2006 CL Univ Calif San Diego, La Jolla, CA HO Univ Calif San Diego ID ENCODED M-PSK; RECEIVERS; MPSK AB We investigate the low SNR behavior of the optimum MAP sequence (blockwise) detection metric for ideal and partially coherent detection of differentially encoded MPSK modulation. In particular, we show that based on an observation of N >= 2 symbols in the presence of a phase ambiguity introduced by the carrier tracking loop and assumed to be constant over the observation, this optimum coherent metric approaches that of multiple symbol differential detection (MSDD) asymptotically as the SNR approaches zero. More importantly, we show that for practical low SNR applications (e.g., error-correction coded systems), the region of SNR where the optimum coherent metric becomes synonymous with MSDD grows with the modulation order M. Finally, we consider the MSDD metric itself modified for symbol-by-symbol detection and demonstrate that for sufficiently low SNR (asymptotically as the SNR approaches zero), its behavior is equivalent to conventional (N = 2) differential detection, i.e., no gain to be had be extending the observation interval beyond two symbols. Unfortunately, unlike the sequence detection case, here the SNR region of validity of the low SNR approximation does not increase with increasing modulation order M. C1 [Simon, Marvin; Divsalar, Dariush] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, 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 FU National Aeronautics and Space Administration FX The research in this paper was performed at the Jet Propulsion Laboratory, California Institute of Technology under a contract with the National Aeronautics and Space Administration. NR 6 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-0-615-15314-8 PY 2007 BP 130 EP + PG 2 WC Computer Science, Information Systems; Computer Science, Interdisciplinary Applications; Computer Science, Theory & Methods; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BGV69 UT WOS:000250812500020 ER PT B AU Gilbert, T Dyer, G Budinger, J AF Gilbert, Tricia Dyer, Glen Budinger, James GP IEEE TI Future communication study technology investigations SO 2007 INTEGRATED COMMUNICATIONS, NAVIGATION AND SURVEILLANCE CONFERENCE LA English DT Proceedings Paper CT Conference on Integrated Communications, Navigation and Surveillance CY MAY 01-03, 2007 CL Herndon, VA AB One goal of the Future Communication Study (FCS) cooperative research program is the investigation of candidate communications technologies to identify those that can support the long-term aeronautical mobile air-ground communication operating concept. The FCS was initiated by the Federal Aviation Administration (FAA) and EUROCONTROL to support the International Civil Aviation Organization (ICAO) Aeronautical Communication Panel (ACP) Working Group C (WG-C) (for aeronautical communications) activities to investigate technologies to meet emerging concepts of operation and communication requirements for the future [air/ground] radio system (FRS). The study is in its third and final year (due to complete later in 2007). The FAA requested NASA Glenn Research Center (GRC) to conduct the FCS technology investigation task for the U.S. GRC has contracted with ITT Corporation to perform the task which includes the development of evaluation criteria derived from requirements, screening of candidate technologies, in-depth technology studies and evaluation to identify most promising technology candidates for all airspace domains. This paper provides and overview of the FCS technology investigation progress, providing results and status on the topic areas noted above. The paper concludes a description of on-going and future work that will be conducted to conclude the FCS and support development of technology recommendations. C1 [Gilbert, Tricia; Dyer, Glen] ITT Corp, Herndon, VA 20171 USA. [Budinger, James] NASA Glenn Res Ctr, Cleveland, OH USA. RP Gilbert, T (reprint author), ITT Corp, Herndon, VA 20171 USA. EM tricia.gilbert@itt.com; glen.dyer@itt.com; James.M.Budinger@nasa.gov NR 0 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-1215-0 PY 2007 BP 83 EP + PG 2 WC Engineering, Aerospace; Computer Science, Interdisciplinary Applications; Telecommunications SC Engineering; Computer Science; Telecommunications GA BGW87 UT WOS:000251015600010 ER PT J AU Nguyen, LH Ramakrishnan, J Granda, JJ AF Nguyen, Louis H. Ramakrishnan, Jayant Granda, Jose J. BE Granda, J Cellier, F TI International Space Station Centrifuge Rotor Models A Comparison of the Euler-Lagrange and the Bond Graph Modeling Approach SO 2007 INTERNATIONAL CONFERENCE ON BOND GRAPH MODELING AND SIMULATION (ICBGM '07) LA English DT Proceedings Paper CT 8th International Conference on Bond Graph Modeling and Simulation (ICBGM)/Western Simulation MultiConference CY JAN 14-17, 2007 CL San Diego, CA SP Soc Modeling & Simulat Int (SCS), Amer Inst Aeronaut & Astronaut (AIAA) DE Bond Graph; International Space Station; Controller Interactions; Centrifuge; Multi-body System AB The assembly and operation of the International Space Station (ISS) require extensive testing and engineering analysis to verify that the Space Station system of systems would work together without any adverse interactions. Since the dynamic behavior of an entire Space Station cannot be tested on earth, math models of the Space Station structures and mechanical systems have to be built and integrated in computer simulations and analysis tools to analyze and predict what will happen in space. The ISS Centrifuge Rotor (CR) is one of many mechanical systems that need to be modeled and analyzed to verify the ISS integrated system performance on-orbit. This study investigates using Bond Graph modeling techniques as quick and simplified ways to generate models of the ISS Centrifuge Rotor. This paper outlines the steps used to generate simple and more complex models of the CR using Bond Graph Computer Aided Modeling Program with Graphical Input (CAMP-G). Comparisons of the Bond Graph CR models with those derived from Euler-Lagrange equations in MATLAB and those developed using multibody dynamic simulation at the National Aeronautics and Space Administration (NASA) Johnson Space Center (JSC) are presented to demonstrate the usefulness of the Bond Graph modeling approach for aeronautics and space applications. C1 [Nguyen, Louis H.] NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. RP Nguyen, LH (reprint author), NASA, Lyndon B Johnson Space Ctr, 2101 NASA Pkwy, Houston, TX 77058 USA. EM louis.h.nguyen@nasa.gov; jayant@arescorporation.com; grandajj@gaia.ecs.csus.edu NR 4 TC 0 Z9 0 U1 0 U2 1 PU SOC MODELING SIMULATION INT-SCS PI SAN DIEGO PA PO BOX 17900, SAN DIEGO, CA 92177 USA BN 978-1-56555-310-1 PY 2007 BP 56 EP 63 PG 8 WC Automation & Control Systems; Computer Science, Interdisciplinary Applications; Engineering, Multidisciplinary SC Automation & Control Systems; Computer Science; Engineering GA BAF75 UT WOS:000304037300007 ER PT S AU Mei, XB Yoshida, W Deal, W Liu, PH Lee, J Uyeda, J Dang, L Wang, J Liu, W Li, D Barsky, M Kim, YM Lange, M Chin, TP Radisic, V Gaier, T Fung, A Lai, R AF Mei, X. B. Yoshida, W. Deal, W. Liu, P. H. Lee, J. Uyeda, J. Dang, L. Wang, J. Liu, W. Li, D. Barsky, M. Kim, Y. M. Lange, M. Chin, T. P. Radisic, V. Gaier, T. Fung, A. Lai, R. GP IEEE TI 35nm InPHEMT for millimeter and sub-millimeter wave applications SO 2007 INTERNATIONAL CONFERENCE ON INDIUM PHOSPHIDE AND RELATED MATERIALS, CONFERENCE PROCEEDINGS SE International Conference on Indium Phosphide and Related Materials LA English DT Proceedings Paper CT 19th International Conference on Indium Phosphide and Related Materials CY MAY 14-18, 2007 CL Matsue, JAPAN SP Japan Soc Appl Phys, IEEE Lasers & Electro Opt Soc, IEEE Electron Devices Soc AB A new InP HEMT process has been developed with 35nm gate length and improved Ohmic contact. A gate-source capacitance of 0.4pF/mm is achieved with the reduced gate length, a 30% improvement over our baseline 70nm device. The contact resistance is successfully reduced to 0.07 with the newly designed contact layer combined with an alloyed Au/Ge/NUAu Ohmic metal. Good device characteristics has been demonstrated with a transconductance as high as 2 S/mm and a cutoff frequency f(T) of 420GHz. A single-stage common-source amplifier was fabricated with this new process. A peak gain of 5dB is measured at 265GHz. A MAG/MSG of 3dB at 300GHz was achieved, making the device suitable for applications at frequencies well into the millimeter-wave and even sub-millimeterwave band. C1 [Mei, X. B.; Yoshida, W.; Deal, W.; Liu, P. H.; Lee, J.; Uyeda, J.; Dang, L.; Wang, J.; Liu, W.; Li, D.; Barsky, M.; Kim, Y. M.; Lange, M.; Chin, T. P.; Radisic, V.; Lai, R.] Northrop Grumman Space Technol, 1 Space Pk, Redondo Beach, CA 90278 USA. [Gaier, T.; Fung, A.] Jet Prop Lab, Pasadena, CA 91109 USA. RP Mei, XB (reprint author), Northrop Grumman Space Technol, 1 Space Pk, Redondo Beach, CA 90278 USA. FU DARPA SWIFT program (DR.Mark Rosker); Army Research Laboratory (Dr.H.Alfred Hung) under the ARL [W911QX-06-C-0050] FX This work was supported by DARPA SWIFT program (DR.Mark Rosker) and Army Research Laboratory (Dr.H.Alfred Hung) under the ARL Contract No.W911QX-06-C-0050. NR 5 TC 1 Z9 1 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1092-8669 BN 978-1-4244-0874-0 J9 CONF P INDIUM PHOSPH PY 2007 BP 59 EP 62 DI 10.1109/ICIPRM.2007.381122 PG 4 WC Engineering, Electrical & Electronic; Optics SC Engineering; Optics GA BGM76 UT WOS:000248523100016 ER PT S AU Pan, L Xue, JL Lai, MK Dillencourt, MB Bic, LF AF Pan, Lei Xue, Jingling Lai, Ming Kin Dillencourt, Michael B. Bic, Lubomir F. GP IEEE TI Toward Automatic Data Distribution for Migrating Computations SO 2007 INTERNATIONAL CONFERENCE ON PARALLEL PROCESSING WORKSHOPS (ICPP) SE International Conference on Parallel Processing Workshops LA English DT Proceedings Paper CT 36th Annual International Conference on Parallel Processing (ICPP 2007) CY JUL 10-SEP 14, 2007 CL Xian, PEOPLES R CHINA DE data distribution; navigational trace graph (NTG); graph partitioning; navigational programming ID MEMORY MACHINES; DATA ALIGNMENT; REDISTRIBUTION AB Program parallelization requires mapping computation and data to processing elements. Navigational programming (NavP), based on the principle of migrating computations, offers a different approach than the conventional solutions that use a SPMD model. This paper focuses on data distribution for NavP. We introduce the Navigational Trace Graph (NTG), a mathematical structure that captures the alignment and distribution preferences of a sequential program. Graph partitioning is applied to NTGs to obtain data distribution solutions. The major advantage is that our methodology can focus exclusively on reducing communication overhead first and later determine the actual computation partition and parallelization, because NavP computations migrate freely across partitions. This is in stark contrast to SPMD, where the data partitioning imposes hard constraints on the threads because they are stationary We present experimental results to demonstrate the effectiveness of our approach. C1 [Pan, Lei] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. [Xue, Jingling] Univ New South Wales, Sch Comp Sci & Engn, Sydney, NSW 2052, Australia. [Lai, Ming Kin; Dillencourt, Michael B.; Bic, Lubomir F.] Univ Calif Irvine, Dept Comp Sci, Irvine, CA 92697 USA. RP Pan, L (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM lei.pan@jpl.nasa.gov; jingling@cse.unsw.edu.au; mingl@ics.uci.edu; dillenco@ics.uci.edu; bic@ics.uci.edu NR 13 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 1530-2016 BN 978-1-4244-3165-6 J9 INT CONF PARA PROC PY 2007 BP 225 EP + PG 2 WC Computer Science, Hardware & Architecture; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BKB61 UT WOS:000267695300027 ER PT B AU Jun, B Merrett, N Phillips, S Sutton, AK Cressler, JD Williams, J Ahyi, C Marshall, PW AF Jun, Bongim Merrett, Neil Phillips, Stan Sutton, Akil K. Cressler, John D. Williams, John Ahyi, Claude Marshall, Paul W. GP IEEE TI Comparison of 63 MeV proton and 10 keV X-ray radiation effects in 4H-SiC depletion-mode vertical trench JFETs SO 2007 INTERNATIONAL SEMICONDUCTOR DEVICE RESEARCH SYMPOSIUM, VOLS 1 AND 2 LA English DT Proceedings Paper CT International Semiconductor Device Research Symposium CY DEC 12-14, 2007 CL College Pk, MD C1 [Jun, Bongim; Phillips, Stan; Sutton, Akil K.; Cressler, John D.] Georgia Inst Technol, Sch Elect & Comp Engn, Atlanta, GA 30332 USA. [Merrett, Neil] Semisouth, Starkville, MS USA. [Williams, John; Ahyi, Claude] Auburn Univ, Dept Phys, Auburn, AL 36849 USA. [Marshall, Paul W.] NASA, GSFC, Washington, DC USA. RP Jun, B (reprint author), Georgia Inst Technol, Sch Elect & Comp Engn, Atlanta, GA 30332 USA. EM stan.phillips@gatech.edu NR 5 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-1891-6 PY 2007 BP 58 EP + PG 2 WC Engineering, Electrical & Electronic; Nanoscience & Nanotechnology; Physics, Applied SC Engineering; Science & Technology - Other Topics; Physics GA BHR89 UT WOS:000255857100030 ER PT B AU Sutton, AK Cressler, JD Carts, MA Marshall, PW Pellish, JA Reed, RA Alles, ML Niu, GF AF Sutton, Akil. K. Cressler, John D. Carts, Martin A. Marshall, Paul W. Pellish, Jonathan A. Reed, Robert A. Alles, Michael L. Niu, Guofu GP IEEE TI Proton-induced SEU in SiGe digital logic at cryogenic temperatures SO 2007 INTERNATIONAL SEMICONDUCTOR DEVICE RESEARCH SYMPOSIUM, VOLS 1 AND 2 LA English DT Proceedings Paper CT International Semiconductor Device Research Symposium CY DEC 12-14, 2007 CL College Pk, MD C1 [Sutton, Akil. K.; Cressler, John D.] Georgia Inst Technol, Sch Elect & Comp Engn, Atlanta, GA 30332 USA. [Carts, Martin A.] Muniz Engn, Houston, TX USA. [Marshall, Paul W.] NASA, GSFC, Washington, DC USA. [Pellish, Jonathan A.; Reed, Robert A.; Alles, Michael L.] Vanderbilt Univ, Dept Elect Engn & Comp Sci, Nashville, TN USA. [Niu, Guofu] Auburn Univ, Dept Elect & Comp Engn, Auburn, AL 36849 USA. RP Sutton, AK (reprint author), Georgia Inst Technol, Sch Elect & Comp Engn, Atlanta, GA 30332 USA. EM asutton@ece.gatech.edu NR 5 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-1891-6 PY 2007 BP 64 EP + PG 2 WC Engineering, Electrical & Electronic; Nanoscience & Nanotechnology; Physics, Applied SC Engineering; Science & Technology - Other Topics; Physics GA BHR89 UT WOS:000255857100033 ER PT B AU Aslam, S Franz, D Stahle, C Miko, L Pugel, D Zhang, JP Gaska, R AF Aslam, Shahid Franz, Dave Stahle, Carl Miko, Laddawan Pugel, Diane Zhang, Jianping Gaska, Remis GP IEEE TI Dual band ultraviolet AlGaN photodetectors for space applications SO 2007 INTERNATIONAL SEMICONDUCTOR DEVICE RESEARCH SYMPOSIUM, VOLS 1 AND 2 LA English DT Proceedings Paper CT International Semiconductor Device Research Symposium CY DEC 12-14, 2007 CL College Pk, MD C1 [Aslam, Shahid; Franz, Dave; Stahle, Carl; Miko, Laddawan; Pugel, Diane] NASA, Goddard Space Flight Ctr, Detector Syst Branch, Code 553, Greenbelt, MD 20771 USA. [Zhang, Jianping; Gaska, Remis] Sensor Elect Technol Inc, Columbia, SC 29209 USA. RP Aslam, S (reprint author), NASA, Goddard Space Flight Ctr, Detector Syst Branch, Code 553, Greenbelt, MD 20771 USA. RI Aslam, Shahid/D-1099-2012 NR 0 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-1891-6 PY 2007 BP 225 EP 225 PG 1 WC Engineering, Electrical & Electronic; Nanoscience & Nanotechnology; Physics, Applied SC Engineering; Science & Technology - Other Topics; Physics GA BHR89 UT WOS:000255857100115 ER PT B AU Pugel, DE Dhar, S Huflavarad, SS Vispute, RD Varughese, B Takeuchi, I Venkatesan, T AF Pugel, D. E. Dhar, S. Huflavarad, S. S. Vispute, R. D. Varughese, B. Takeuchi, I. Venkatesan, T. GP IEEE TI Evolution of annealed undoped single crystal ZnO surfaces and implications for Schottky barrier height SO 2007 INTERNATIONAL SEMICONDUCTOR DEVICE RESEARCH SYMPOSIUM, VOLS 1 AND 2 LA English DT Proceedings Paper CT International Semiconductor Device Research Symposium CY DEC 12-14, 2007 CL College Pk, MD C1 [Pugel, D. E.] NASA, Goddard Space Flight Ctr, Detector Syst Branch, Greenbelt, MD 20771 USA. [Dhar, S.; Vispute, R. D.; Venkatesan, T.] Univ Maryland, Dept Phys, Ctr Nanophys & Adv Mat, College Pk, MD USA. [Huflavarad, S. S.] Univ Alaska Fairbanks, Off Elect Miniaturizat, Fairbanks, AK USA. [Vispute, R. D.] UMBC Technol Ctr, Blue Wave Semicond Inc, Baltimore, MD 21227 USA. [Varughese, B.] Univ Maryland, Mat Res Sci & Engn Ctr, College Pk, MD 20742 USA. [Takeuchi, I.] Univ Maryland, Dept Mat Sci & Engn, College Pk, MD USA. RP Pugel, DE (reprint author), NASA, Goddard Space Flight Ctr, Detector Syst Branch, Greenbelt, MD 20771 USA. EM Betsy.Pugel@nasa.gov RI Venkatesan, Thirumalai/E-1667-2013 NR 6 TC 0 Z9 0 U1 0 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-1891-6 PY 2007 BP 296 EP 296 PG 1 WC Engineering, Electrical & Electronic; Nanoscience & Nanotechnology; Physics, Applied SC Engineering; Science & Technology - Other Topics; Physics GA BHR89 UT WOS:000255857100151 ER PT B AU Brown, AD Chervenak, J Chuss, D Henry, R Wollack, E Mikula, V AF Brown, Ari-David Chervenak, James Chuss, David Henry, Ross Wollack, Edward Mikula, Vilem GP IEEE TI Auxiliary resistive components for millimeter to sub-mm astronomical observatories SO 2007 INTERNATIONAL SEMICONDUCTOR DEVICE RESEARCH SYMPOSIUM, VOLS 1 AND 2 LA English DT Proceedings Paper CT International Semiconductor Device Research Symposium CY DEC 12-14, 2007 CL College Pk, MD C1 [Brown, Ari-David; Chervenak, James; Chuss, David; Henry, Ross; Wollack, Edward; Mikula, Vilem] NASA, Goddard Space Flight Ctr, Code 553, Greenbelt, MD 20771 USA. RP Brown, AD (reprint author), NASA, Goddard Space Flight Ctr, Code 553, Greenbelt, MD 20771 USA. EM abrown@pop500.gfc.nasa.gov RI Wollack, Edward/D-4467-2012 OI Wollack, Edward/0000-0002-7567-4451 NR 1 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-1891-6 PY 2007 BP 326 EP 326 PG 1 WC Engineering, Electrical & Electronic; Nanoscience & Nanotechnology; Physics, Applied SC Engineering; Science & Technology - Other Topics; Physics GA BHR89 UT WOS:000255857100167 ER PT B AU Ribaya, BP Niemann, DL Makarewicz, J Gunther, NG Nguyen, CV Rahman, M AF Ribaya, Bryan P. Niemann, Darrell L. Makarewicz, Joseph Gunther, Norman G. Nguyen, Cattien V. Rahman, Mahmud GP IEEE TI An empirical study of dynamic properties of an individual carbon nanotube electron source system SO 2007 INTERNATIONAL SEMICONDUCTOR DEVICE RESEARCH SYMPOSIUM, VOLS 1 AND 2 LA English DT Proceedings Paper CT International Semiconductor Device Research Symposium CY DEC 12-14, 2007 CL College Pk, MD C1 [Ribaya, Bryan P.; Niemann, Darrell L.; Gunther, Norman G.; Rahman, Mahmud] Santa Clara Univ, Dept Elect Engn, Electron Devices Lab, Santa Clara, CA 95053 USA. [Nguyen, Cattien V.] ELORET Corp, Sunnyvale, CA USA. [Ribaya, Bryan P.; Niemann, Darrell L.; Makarewicz, Joseph; Nguyen, Cattien V.] NASA, Ames Res Ctr, Moffett Field, CA USA. RP Rahman, M (reprint author), Santa Clara Univ, Dept Elect Engn, Electron Devices Lab, Santa Clara, CA 95053 USA. EM mrahman@scu.edu NR 5 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-1891-6 PY 2007 BP 381 EP + PG 2 WC Engineering, Electrical & Electronic; Nanoscience & Nanotechnology; Physics, Applied SC Engineering; Science & Technology - Other Topics; Physics GA BHR89 UT WOS:000255857100195 ER PT B AU Scardelletti, MC Parro, RJ Varaljay, N Zimmerman, S Zorman, CA AF Scardelletti, M. C. Parro, R. J. Varaljay, N. Zimmerman, S. Zorman, C. A. GP IEEE TI Amorphous SiC as a structural layer in microbridge-based RF MEMS switches for use in software-defined radio SO 2007 INTERNATIONAL SEMICONDUCTOR DEVICE RESEARCH SYMPOSIUM, VOLS 1 AND 2 LA English DT Proceedings Paper CT International Semiconductor Device Research Symposium CY DEC 12-14, 2007 CL College Pk, MD C1 [Scardelletti, M. C.; Varaljay, N.] NASA, Glenn Res Ctr, Washington, DC 20546 USA. [Parro, R. J.; Zimmerman, S.; Zorman, C. A.] Casr Western Reserve Univ, Dept Elect Engn & Comp Sci, Cleveland, OH 10900 USA. RP Scardelletti, MC (reprint author), NASA, Glenn Res Ctr, Washington, DC 20546 USA. EM Maximilian.C.Scardelletti@grc.nasa.gov NR 3 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-1891-6 PY 2007 BP 477 EP + PG 2 WC Engineering, Electrical & Electronic; Nanoscience & Nanotechnology; Physics, Applied SC Engineering; Science & Technology - Other Topics; Physics GA BHR89 UT WOS:000255857100245 ER PT B AU Picard, YN Caldwell, JD Twigg, ME Eddy, CR Mastro, MA Henry, RL Holm, RT Neudeck, PG Trunek, AJ Powell, JA AF Picard, Yoosuf N. Caldwell, Joshua D. Twigg, Mark E. Eddy, Chip R., Jr. Mastro, Michael A. Henry, Richard L. Holm, Ronald T. Neudeck, Philip G. Trunek, Andrew J. Powell, J. Anthony GP IEEE TI The influence of substrate atomic step morphology on threading dislocation distributions in III-nitride films SO 2007 INTERNATIONAL SEMICONDUCTOR DEVICE RESEARCH SYMPOSIUM, VOLS 1 AND 2 LA English DT Proceedings Paper CT International Semiconductor Device Research Symposium CY DEC 12-14, 2007 CL College Pk, MD C1 [Picard, Yoosuf N.; Caldwell, Joshua D.; Twigg, Mark E.; Eddy, Chip R., Jr.; Mastro, Michael A.; Henry, Richard L.; Holm, Ronald T.] USN, Res Lab, Washington, DC 20375 USA. [Neudeck, Philip G.] NASA, Glenn Res Ctr, Washington, DC 20375 USA. [Trunek, Andrew J.] OAI, Washington, DC 20375 USA. [Powell, J. Anthony] Sest Inc, Washington, DC 20375 USA. RP Picard, YN (reprint author), USN, Res Lab, Washington, DC 20375 USA. EM yoosuf.picard@nrl.navy.mil RI Caldwell, Joshua/B-3253-2008 OI Caldwell, Joshua/0000-0003-0374-2168 NR 4 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-1891-6 PY 2007 BP 537 EP + PG 2 WC Engineering, Electrical & Electronic; Nanoscience & Nanotechnology; Physics, Applied SC Engineering; Science & Technology - Other Topics; Physics GA BHR89 UT WOS:000255857100277 ER PT B AU Hensley, S Madsen, SN AF Hensley, Scott Madsen, Soren N. GP IEEE TI Interferometric radar waveform design and the effective interferometric wavelength SO 2007 INTERNATIONAL WAVEFORM DIVERSITY & DESIGN CONFERENCE LA English DT Proceedings Paper CT International Waveform Diversity and Design Conference CY JUN 04-08, 2007 CL Pisa, ITALY SP IEEE AB Interferometric radar systems are used by the research, commercial and military communities for applications ranging from topographic mapping to measuring subtle deformations of the Earth's surface for geophysical processes such as earthquakes, volcanoes and ice motion. These systems operate at a variety of wavelengths from 1 cm to 1 m depending on the application. As the number of users of the spectrum increases it is becoming increasingly necessary for these systems to alter their waveforms to have the necessary interoperable compatibility. In particular, notching of certain spectral bands within the radar transmit band may be required to avoid interference with critical users operating in the same band. For high accuracy applications it is necessary to account for how these waveform differences affect the interferometric phase and correlation. We have developed a formula for the effective interferometric wavelength that accounts for the effect of the transmitted waveform on the effective interferometric wavelength and the way the data is processed. C1 [Hensley, Scott; Madsen, Soren N.] Jet Prop Lab, Pasadena, CA 91109 USA. RP Hensley, S (reprint author), Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 2 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-1275-4 PY 2007 BP 287 EP 291 DI 10.1109/WDDC.2007.4339428 PG 5 WC Computer Science, Theory & Methods; Engineering, Electrical & Electronic; Optics; Imaging Science & Photographic Technology; Telecommunications SC Computer Science; Engineering; Optics; Imaging Science & Photographic Technology; Telecommunications GA BHG48 UT WOS:000252960900061 ER PT B AU Wood, L Eddy, WM Ivancic, W Mckim, J Jackson, C AF Wood, Lloyd Eddy, Wesley M. Ivancic, Will Mckim, Jim Jackson, Chris GP IEEE TI Saratoga: a Delay-Tolerant Networking convergence layer with efficient link utilization SO 2007 INTERNATIONAL WORKSHOP ON SATELLITE AND SPACE COMMUNICATIONS, IWSSC '07, CONFERENCE PROCEEDINGS LA English DT Proceedings Paper CT International Workshop on Satellite and Space Communications CY SEP 12-14, 2007 CL Univ Salzburg, Salzburg, AUSTRIA SP IEEE, SATNEX, IEEE Commun Soc HO Univ Salzburg DE UDP; Saratoga; Delay Tolerant Networking; DTN AB Saratoga is a lightweight transport protocol based on the User Datagram Protocol (UDP/IP). Saratoga was developed by Surrey Satellite Technology Ltd (SSTL) for file transfers of imaging data recorded onboard the Internet-Protocol-based Disaster Monitoring Constellation (DMC) satellites, and has been in operational use from low Earth orbit since 2004. Saratoga focuses only on efficient communication to the next hop when link connectivity is available, by filling the link with packets sent at line rate. This ensures that as much data as possible is transferred to the peering node during a twelve-minutes-or-less pass over a satellite ground station. Saratoga uses a minimal bandwidth-efficient negative acknowledgement mechanism to ensure reliable data transfer. We examine how Saratoga can be adapted to serve as an efficient convergence layer for Delay-Tolerant Networking (DTN), by transferring DTN bundles as well as riles. This will allow DTN networks to increase efficiency of communication across briefly-available disrupted links - for long-distance deep space links as well as for short-distance terrestrial mobile ad-hoc networks. C1 [Wood, Lloyd] Cisco Syst, Global Govt Solut grp, Feltham, Middx, England. [Eddy, Wesley M.] Verizon Fed Network Syst, Arlington, VA USA. [Eddy, Wesley M.; Ivancic, Will; Mckim, Jim] NASA, Glenn Res Ctr, Cleveland, OH USA. [Mckim, Jim] RS Informat Syst, Mclean, VA USA. [Jackson, Chris] Univ Surrey Res Pk, Surrey Satellite Technol Ltd, Guildford, Surrey, England. RP Wood, L (reprint author), Cisco Syst, Global Govt Solut grp, Feltham, Middx, England. EM lwood@cisco.com; weddy@grc.nasa.gov; William.D.Ivancic@grc.nasa.gov; James.H.McKim@gre.nasa.gov; C.Jackson@sstl.co.uk FU NASA's Earth Science Technology Office (ESTO) FX Work on this document at NASA's Glenn Research Center was funded by NASA's Earth Science Technology Office (ESTO). NR 15 TC 17 Z9 17 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-0938-9 PY 2007 BP 168 EP + DI 10.1109/IWSSC.2007.4409410 PG 2 WC Engineering, Electrical & Electronic; Telecommunications SC Engineering; Telecommunications GA BHF67 UT WOS:000252738300031 ER PT B AU Luvall, JC Rickman, D Gonzalez, J AF Luvall, Jeffrey C. Rickman, Doug Gonzalez, Jorge GP IEEE TI The use of the Airborne Thermal/Visible Land Application Sensor (ATLAS) to determine the thermal response numbers for urban areas SO 2007 INTERNATIONAL WORKSHOP ON THE ANALYSIS OF MULTI-TEMPORAL REMOTE SENSING IMAGES LA English DT Proceedings Paper CT 4th International Workshop on the Analysis of Multi-Temporal Remote Sensing Images CY JUL 18-20, 2007 CL Louvain, BELGIUM AB The additional heating of the air over the city is the result of the replacement of naturally vegetated surfaces with those composed of asphalt, concrete, rooftops and other man-made materials. The temperatures of these artificial surfaces can be 20 to 40 degrees C higher than vegetated surfaces. This produces a dome of elevated air temperatures 5 to 8 degrees C greater over the city, compared to the air temperatures over adjacent rural areas. Urban landscapes are a complex mixture of vegetated and nonvegetated surfaces. It is difficult to take enough temperature measurements over a large city area to characterize the complexity of urban radiant surface temperature variability. The NASA Airborne Thermal and Land Applications Sensor (ATLAS) operates in the visual and IR bands was used in February 2004 to collect data from San Juan, Puerto Rico with the main objective of investigating the Urban Heat Island (UHI) in tropical cities. Ref. [1] developed the TRN (thermal response number) as a technique using aircraft remotely sensed surface temperatures to quantify the thermal response of urban surfaces. The TRN was used to quantify the thermal response of various urban surface types ranging from completely vegetated surfaces to asphalt pavements for San Juan, Puerto Rico. C1 [Luvall, Jeffrey C.; Rickman, Doug] NASA, Marshall Space Flight Ctr, NSSTC, 320 Sparkman Dr, Huntsville, AL 35805 USA. [Gonzalez, Jorge] Santa Clara Univ, Dept Engn Mech, Santa Clara, CA 95053 USA. RP Luvall, JC (reprint author), NASA, Marshall Space Flight Ctr, NSSTC, 320 Sparkman Dr, Huntsville, AL 35805 USA. EM jluvall@nasa.gov; jorge@ece.uprm.edu NR 8 TC 1 Z9 1 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-0845-0 PY 2007 BP 117 EP + PG 2 WC Engineering, Electrical & Electronic; Remote Sensing SC Engineering; Remote Sensing GA BHL36 UT WOS:000254030300023 ER PT B AU Chattopadhyay, G Kuo, CL Day, P Bock, JJ Zmuidzinas, J Lange, AE AF Chattopadhyay, Goutam Kuo, Chao-Lin Day, Peter Bock, James J. Zmuidzinas, Jonas Lange, Andrew E. GP IEEE TI Planar antenna arrays for CMB polarization detection SO 2007 JOINT 32ND INTERNATIONAL CONFERENCE ON INFRARED AND MILLIMETER WAVES AND 15TH INTERNATIONAL CONFERENCE ON TERAHERTZ ELECTRONICS, VOLS 1 AND 2 LA English DT Proceedings Paper CT Joint 32nd International Conference on Infrared and Millimeter Waves/15th International Conference on Terahertz Electronics CY SEP 03-09, 2007 CL Cardiff, ENGLAND SP IEEE, Inst Phys, Cardiff Univ, Sch Phys & Astron, IEEE MTTS ID MILLIMETER AB A novel slot antenna array architecture is presented for Cosmic Microwave Background (CMB) polarization detection. Future CMB polarization detection instruments will require large focal planes with thousand of detectors to have large throughput improving overall sensitivity of the instrument. Field of view of these detectors needs to be restricted to reduce stray radiation pickup. Current technology of using metal horn antennas are found impractical for very large arrays. Although planar antennas solve many of the problems of horn antenna, they require substrate lens to have a narrow beam required for CMB polarization detection. We have designed and developed dual-polarized antennas producing a narrow beam without any substrate lenses and is compatible with large focal plane architecture. The antenna array output for each polarization is combined in phase and detected using transition edge sensors (TES). These dualpolarized slot antennas provide approximately 20-25% fractional bandwidth with better than 20 dB cross polarization. C1 [Chattopadhyay, Goutam] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. CALTECH, Dept Phys, Pasadena, CA USA. RP Chattopadhyay, 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 IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-1438-3 PY 2007 BP 179 EP + PG 2 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BIA55 UT WOS:000257936900075 ER PT B AU Bakunov, MI Bodrov, SB Maslov, AV Tsarev, MV AF Bakunov, Michael I. Bodrov, Sergey B. Maslov, Alexey V. Tsarev, Maxim V. GP IEEE TI Theory of terahertz generation in a slab of electro-optic material with femtosecond laser pulse focused to a line SO 2007 JOINT 32ND INTERNATIONAL CONFERENCE ON INFRARED AND MILLIMETER WAVES AND 15TH INTERNATIONAL CONFERENCE ON TERAHERTZ ELECTRONICS, VOLS 1 AND 2 LA English DT Proceedings Paper CT Joint 32nd International Conference on Infrared and Millimeter Waves/15th International Conference on Terahertz Electronics CY SEP 03-09, 2007 CL Cardiff, ENGLAND SP IEEE, Inst Phys, Cardiff Univ, Sch Phys & Astron, IEEE MTTS ID OPTICAL RECTIFICATION; RADIATION AB A theory that describes the optical-to-terahertz conversion of femtosecond laser pulses via optical rectification in a slab of an electro-optic material is developed. Two typical experimental situations - phase-matched regime (ZnTe excited with 0.8 mu m optical pump) and nonphase-matched regime (GaAs excited with 1.56 mu m optical pump) - are considered. The theory accounts for the transverse size of the laser beam and allows us to explore the dependence of the conversion efficiency on laser focusing. We trace the temporal dynamics of the optical-to-terahertz conversion inside the slab and study the angular distribution of the terahertz emission from the slab. The optimal parameters (such as laser transverse size and crystal thickness) maximizing the terahertz; yield for ZnTe and GaAs are calculated. C1 [Bakunov, Michael I.; Bodrov, Sergey B.; Tsarev, Maxim V.] Univ Nizhny Novgorod, Dept Radiophys, Nizhnii Novgorod 603950, Russia. [Bakunov, Michael I.; Bodrov, Sergey B.; Tsarev, Maxim V.] Russian Acad Sci, Inst Phys Appl, Moscow 117901, Russia. [Maslov, Alexey V.] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Bakunov, MI (reprint author), Univ Nizhny Novgorod, Dept Radiophys, Nizhnii Novgorod 603950, Russia. EM bakunov@rf.unn.ru RI Bodrov, Sergey/D-1962-2012; Bakunov, Michael/E-2875-2017 OI Bakunov, Michael/0000-0002-4209-1372 FU RFBR [05-02-39022, 06-02-17495] FX Two of the authors (S.B.B. and M.I.B.) were supported in part by RFBR Grant Nos. 05-02-39022 and 06-02-17495. A. V. M. is now at Canon Development Americas, Inc. NR 6 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-1438-3 PY 2007 BP 187 EP + PG 2 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BIA55 UT WOS:000257936900079 ER PT B AU Bodrov, SB Bakunov, MI Maslov, AV Liu, S AF Bodrov, Sergey B. Bakunov, Michael I. Maslov, Alexey V. Liu, Shenggang GP IEEE TI Efficient Cherenkov emission of terahertz radiation from an ultrashort laser pulse propagating along a waveguiding structure with nonlinear core SO 2007 JOINT 32ND INTERNATIONAL CONFERENCE ON INFRARED AND MILLIMETER WAVES AND 15TH INTERNATIONAL CONFERENCE ON TERAHERTZ ELECTRONICS, VOLS 1 AND 2 LA English DT Proceedings Paper CT Joint 32nd International Conference on Infrared and Millimeter Waves/15th International Conference on Terahertz Electronics CY SEP 03-09, 2007 CL Cardiff, ENGLAND SP IEEE, Inst Phys, Cardiff Univ, Sch Phys & Astron, IEEE MTTS ID OPTICAL RECTIFICATION; LITHIUM-NIOBATE; GENERATION AB A scheme for efficient Cherenkov emission of terahertz radiation using nonlinear optical rectification of femtosecond laser pulses propagating in a sandwich-like structure is proposed and investigated. The structure consists of a thin nonlinear core covered by prisms with low terahertz absorption. We developed a theory of terahertz generation in such structures and calculated spatial distributions of the generated terahertz field, its energy spectrum and conversion efficiency. The developed theory predicts the optical-to-terahertz conversion efficiency of up to several percent in a 1 cm long and 1 cm wide Si-LiNbO3-Si sandwich structure with a 40 pm thick nonlinear layer pumped by 5 mu J Ti:sapphire laser with pulse duration of 100 fs. C1 [Bodrov, Sergey B.; Bakunov, Michael I.] Russian Acad Sci, Inst Appl Phys, Nizhnii Novgorod 603950, Russia. [Bodrov, Sergey B.; Bakunov, Michael I.] Univ Nizhny Novgorod, Dept Radiophys, Nizhnii Novgorod 603950, Russia. [Maslov, Alexey V.] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Liu, Shenggang] Univ Elect Sci & Technol China, Inst Appl Phys, Chengdu 610054, Peoples R China. RP Bodrov, SB (reprint author), Russian Acad Sci, Inst Appl Phys, Nizhnii Novgorod 603950, Russia. EM bosbor@ufp.appl.sci-nnov.ru; bakunov@rf.unn.ru RI Bodrov, Sergey/D-1962-2012; Bakunov, Michael/E-2875-2017 OI Bakunov, Michael/0000-0002-4209-1372 FU RFBR [05-02-39022, 06-02-17495]; "Dynasty"; NSFC [60611120128] FX Two of the authors (S. B. B. and M. I. B.) were supported in art by RFBR Grant Nos. 05-02-39022 and 06-02-17495. S. B. . also acknowledges partial support from the fund Dynasty.S. L. was supported in part by NSFC Grant No. 60611120128. . V. M. is now at Canon Development Americas, Inc. NR 6 TC 0 Z9 0 U1 0 U2 1 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-1438-3 PY 2007 BP 189 EP + PG 2 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BIA55 UT WOS:000257936900080 ER PT B AU Dicker, SR Mason, BS Korgut, PM Abrahams, JH Ade, PAR Aguirre, J Ames, TJ Benford, DJ Chen, TC Chervenak, JA Cotton, WD Devlin, MJ Figueroa-Feliciano, E Irwin, KD Maher, S Mello, M Moseley, SH Staguhn, J Norrod, RD Tally, DJ Tucker, C Werner, BA White, SD AF Dicker, S. R. Mason, B. S. Korgut, P. M. Abrahams, J. H. Ade, P. A. R. Aguirre, J. Ames, T. J. Benford, D. J. Chen, T. C. Chervenak, J. A. Cotton, W. D. Devlin, M. J. Figueroa-Feliciano, E. Irwin, K. D. Maher, S. Mello, M. Moseley, S. H. Staguhn, J. Norrod, R. D. Tally, D. J. Tucker, C. Werner, B. A. White, S. D. GP IEEE TI MUSTANG. First light and current status SO 2007 JOINT 32ND INTERNATIONAL CONFERENCE ON INFRARED AND MILLIMETER WAVES AND 15TH INTERNATIONAL CONFERENCE ON TERAHERTZ ELECTRONICS, VOLS 1 AND 2 LA English DT Proceedings Paper CT Joint 32nd International Conference on Infrared and Millimeter Waves/15th International Conference on Terahertz Electronics CY SEP 03-09, 2007 CL Cardiff, ENGLAND SP IEEE, Inst Phys, Cardiff Univ, Sch Phys & Astron, IEEE MTTS ID GREEN BANK TELESCOPE; SYSTEM AB MUSTANG is a 90 GHz bolometer camera built for use as a facility instrument on the 100 m Green Bank radio telescope (GBT). MUSTANG has an 8 by 8 focal plane array of transition edge sensor bolometers read out using time-multiplexed SQUID electronics. On the GBT each pixel has an 8" beam size. In one hour we expect to be able to map a 15' square of sky to 0.2 mJy/beam RMS making MUSTANG on the GBT a very competitive instrument capable of a wide range of galactic and extragalactic science. In September 2006 MUSTANG had first light and became the first instrument to use the GBT at 90 GHz. During two months of subsequent testing we showed that MUSTANG behaved as well on the telescope as it did in the lab. Observations were made of many astronomical sources including Saturn and the star forming region W3. We were able to confirm our beamshape and different observing strategies were tested. Procedures were put in place for pointing and focusing and a data analysis pipeline was set up. Several problems were identified during commissioning and are currently being addressed. One of these, excessive 1/f noise, has already been solved and we plan to take our first science observations in late 2007. C1 [Dicker, S. R.; Devlin, M. J.; Werner, B. A.] Univ Penn, Dept Phys & Astron, 209 S 33rd St, Philadelphia, PA 19104 USA. [Mason, B. S.; Korgut, P. M.; Aguirre, J.; Cotton, W. D.; Mello, M.; Norrod, R. D.; White, S. D.] Natl Radio Astron Observ, Green Bank, WV 24944 USA. [Abrahams, J. H.; Ames, T. J.; Benford, D. J.; Chen, T. C.; Chervenak, J. A.; Maher, S.; Moseley, S. H.; Staguhn, J.; Tally, D. J.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Ade, P. A. R.; Tucker, C.] Cardiff Univ, Sch Phys & Astron, Cardiff CF24 3AA, England. [Figueroa-Feliciano, E.] MIT, Dept Phys, Cambridge, MA 02139 USA. [Irwin, K. D.] Natl Inst Stand & Technol, 325 Broadway, Boulder, CO 80303 USA. RP Dicker, SR (reprint author), Univ Penn, Dept Phys & Astron, 209 S 33rd St, Philadelphia, PA 19104 USA. RI Benford, Dominic/D-4760-2012 OI Benford, Dominic/0000-0002-9884-4206 FU National RadioAstronomy Observatory through the NSF [AST-0607654] FX Funding for this project was provided by the National RadioAstronomy Observatory through the NSF and NSF award number AST-0607654 NR 6 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-1438-3 PY 2007 BP 325 EP + PG 2 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BIA55 UT WOS:000257936900144 ER PT B AU Hargrave, PC Ade, PAR Bock, JJ Chapin, EL Chung, J Devlin, MJ Dicker, S Griffin, M Gundersen, JO Halpern, M Hughes, DH Klein, J MacTavish, CJ Marsden, G Martin, PG Martin, TG Mauskopf, P Netterfield, CB Olmi, L Pascale, E Patanchon, G Rex, M Scott, D Semnisch, C Thomas, N Truch, MDP Tucker, C Tucker, GS Viero, MP Wiebe, DV AF Hargrave, P. C. Ade, P. A. R. Bock, J. J. Chapin, E. L. Chung, J. Devlin, M. J. Dicker, S. Griffin, M. Gundersen, J. O. Halpern, M. Hughes, D. H. Klein, J. MacTavish, C. J. Marsden, G. Martin, P. G. Martin, T. G. Mauskopf, P. Netterfield, C. B. Olmi, L. Pascale, E. Patanchon, G. Rex, M. Scott, D. Semnisch, C. Thomas, N. Truch, M. D. P. Tucker, C. Tucker, G. S. Viero, M. P. Wiebe, D. V. GP IEEE TI BLAST - The Balloon-borne Large Aperture Sub-millimeter Telescope SO 2007 JOINT 32ND INTERNATIONAL CONFERENCE ON INFRARED AND MILLIMETER WAVES AND 15TH INTERNATIONAL CONFERENCE ON TERAHERTZ ELECTRONICS, VOLS 1 AND 2 LA English DT Proceedings Paper CT Joint 32nd International Conference on Infrared and Millimeter Waves/15th International Conference on Terahertz Electronics CY SEP 03-09, 2007 CL Cardiff, ENGLAND SP IEEE, Inst Phys, Cardiff Univ, Sch Phys & Astron, IEEE MTTS DE array; balloon; bolometer; cryogenic; detector; sub-millimeter; telescope AB The Balloon-borne Large Aperture Sub-millimeter Telescope (BLAST) has recently completed a highly successful long duration balloon flight from Antarctica. The instrument design incorporates a 2m diameter primary mirror, with large format bolometer arrays operating at 250, 350 and 500 microns. By providing the first sensitive large-area (>>10 sq. degrees) surveys at these wavelengths, BLAST will address some of the most important galactic and cosmological questions regarding the formation and evolution of stars, galaxies and clusters. C1 [Hargrave, P. C.; Ade, P. A. R.; Chung, J.; Griffin, M.; Mauskopf, P.; Netterfield, C. B.] Cardiff Univ, Dept Phys & Astron, 5 Parade, Cardiff CF24 3AA, Wales. [Halpern, M.; MacTavish, C. J.; Martin, T. G.; Pascale, E.; Tucker, C.; Wiebe, D. V.] Univ Toronto, Dept Phys, Toronto, ON M5S1A7, Canada. [Bock, J. J.] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. [Bock, J. J.] CALTECH, Observ Cosmol, Pasadena, CA 91125 USA. [Chapin, E. L.; Chung, J.; Halpern, M.; Marsden, G.; Patanchon, G.; Scott, D.] Univ British Columbia, Dept Phys & Astronomy, Vancouver, BC V6T 1Z1, Canada. [Devlin, M. J.; Dicker, S.; Klein, J.; Rex, M.; Semnisch, C.] Univ Penn, Dept Phys & Astron, Philadelphia, PA 19104 USA. [Gundersen, J. O.; Thomas, N.] Miami Univ, Dept Phys, Miami, FL 33146 USA. [Martin, P. G.] Univ Toronto, Canadian Inst Theoret Astrophys, Toronto, ON M5S3H8, Canada. [Olmi, L.] Inst Radioastronomia, I-50125 Florence, Italy. [Olmi, L.] Univ Puerto Rico Rio Piedras, San Juan, PR USA. [Truch, M. D. P.; Tucker, G. S.] Brown Univ, Dept Phys, Providence, RI 02912 USA. [Hughes, D. H.] INAOE, Puebla 72000, Mexico. [Patanchon, G.] Lab APC, F-75205 Paris, France. [Martin, P. G.; Netterfield, C. B.; Viero, M. P.] Univ Toronto, Dept Astron & Astrophys, Toronto, ON M5S3H4, Canada. RP Hargrave, PC (reprint author), Cardiff Univ, Dept Phys & Astron, 5 Parade, Cardiff CF24 3AA, Wales. EM p.hargrave@astro.cf.ac.uk NR 5 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-1438-3 PY 2007 BP 586 EP + PG 2 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BIA55 UT WOS:000257936900267 ER PT B AU Mehdi, I Schlecht, E Maestrini, A Gill, J Lee, C Ward, J AF Mehdi, Imran Schlecht, Erich Maestrini, Alain Gill, John Lee, Choonsup Ward, John GP IEEE TI Submillimeter-wave Schottky diode receivers SO 2007 JOINT 32ND INTERNATIONAL CONFERENCE ON INFRARED AND MILLIMETER WAVES AND 15TH INTERNATIONAL CONFERENCE ON TERAHERTZ ELECTRONICS, VOLS 1 AND 2 LA English DT Proceedings Paper CT Joint 32nd International Conference on Infrared and Millimeter Waves/15th International Conference on Terahertz Electronics CY SEP 03-09, 2007 CL Cardiff, ENGLAND SP IEEE, Inst Phys, Cardiff Univ, Sch Phys & Astron, IEEE MTTS AB Compact and broadband room temperature receivers are a critical technology for future planetary missions. We report on a room temperature mixer covering the 520 to 600 GHz range with better than 5000 K DSB noise temperature. The receiver front end consists of a bias-able sub-harmonically pumped Schottky mixer and a balanced six anode tripler, both chips made on membrane substrates. This front end in combination with digital backends can provide a low-power, compact, and broadband receiver for future applications. C1 [Mehdi, Imran; Schlecht, Erich; Maestrini, Alain; Gill, John; Lee, Choonsup; Ward, John] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Mehdi, I (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 5 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-1438-3 PY 2007 BP 735 EP 736 PG 2 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BIA55 UT WOS:000257936900335 ER PT B AU Cooper, KB Dengler, RJ Chattopadhyay, G Schlecht, E Gill, J Skalare, A Mehdi, I Siegel, PH AF Cooper, K. B. Dengler, R. J. Chattopadhyay, G. Schlecht, E. Gill, J. Skalare, A. Mehdi, I. Siegel, P. H. GP IEEE TI Submillimeter-wave active radar imager SO 2007 JOINT 32ND INTERNATIONAL CONFERENCE ON INFRARED AND MILLIMETER WAVES AND 15TH INTERNATIONAL CONFERENCE ON TERAHERTZ ELECTRONICS, VOLS 1 AND 2 LA English DT Proceedings Paper CT Joint 32nd International Conference on Infrared and Millimeter Waves/15th International Conference on Terahertz Electronics CY SEP 03-09, 2007 CL Cardiff, ENGLAND SP IEEE, Inst Phys, Cardiff Univ, Sch Phys & Astron, IEEE MTTS ID TERAHERTZ TECHNOLOGY AB The authors have developed and demonstrated 3D imaging using a submillimeter-wave FMCW radar with a fast microwave chirp and phase coherent detection. The technique provides an important advantage over more traditional CW RF imaging in that time gating of the return signals allows optimization of the received scene illumination or specific depth reconstruction. This can be used to enhance (or hide) specific objects or greatly reduce background clutter. The system was initially prototyped with available RF components near 600 GHz and a 12.6 GHz chirp producing a 250 MHz/msec sweep yielding a range resolution of 1.2 cm. Lateral resolution on the scene is set by a 20cm diameter Teflon lens antenna producing approximately 2cm at 4m distance. The RF transmit power (generated by a W-band power amplifier and an in-house frequency multiplier chain) is less than 0.5 mW but when coupled with a heterodyne downconverter (in-house developed fundamental balanced Schottky diode mixer, 4000K DSB noise temperature) yields a measured dynamic range of more than 70dB. A more compact and higher resolution system is currently under construction and will employ an 18 GHz msec sweep rate microwave chirp for sub-cm range resolution, a 40cm reflector and a higher power transmitter, dramatically increasing resolution and dynamic range. The talk will cover the system design and some early results we have obtained on test targets at 4 m. C1 [Cooper, K. B.; Dengler, R. J.; Chattopadhyay, G.; Schlecht, E.; Gill, J.; Skalare, A.; Mehdi, I.; Siegel, P. H.] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Cooper, KB (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. NR 8 TC 0 Z9 0 U1 0 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-1438-3 PY 2007 BP 903 EP 904 PG 2 WC Engineering, Electrical & Electronic; Physics, Applied SC Engineering; Physics GA BIA55 UT WOS:000257936900414 ER PT S AU Li, C Inoue, M Crout, R Rouse, L Welsh, S Coor, J Weeks, E AF Li, C. Inoue, M. Crout, R. Rouse, L. Welsh, S. Coor, Jennifer Weeks, E. GP IEEE TI Comparison of non-hurricane and hurricane induced near inertial oscillations in deep water of Gulf of Mexico SO 2007 OCEANS, VOLS 1-5 SE OCEANS-IEEE LA English DT Proceedings Paper CT 2007 OCEANS Conference CY SEP 29-OCT 04, 2007 CL Vancouver, CANADA SP MTS, IEEE, Canada, Oceanworks, ISE Grp Co, Sun Star Elect L P, KONGSBERG, IMAGENEX TECHNOL CORP, ONR, OPSI ID CURRENTS AB By using oil platform based ADCPs on the continental slope, some time series and spectrum analyses are implemented to examine the general flow distributions including those of the near inertial oscillations and their temporal variations along the vertical water columns for the Gulf of Mexico during different time periods in the year of 2005 and 2006, particularly in 2005, when a few hurricanes struck the Gulf of Mexico coast of the US, causing tremendous amount of damages. Among these hurricanes are the infamous Hurricanes Katrina and Rita. However, during the Hurricanes Katrina and Rita, most of the acoustic Doppler current profilers from oil platforms and moorings were not functioning and only a couple of the deep water ADCPs were collecting data during the storms. This paper presents some preliminary studies analyzing the ADCP data using different methods, such as rotary spectra and wavelet analysis. The rotary spectra of the velocity showed interesting patterns of inertial oscillations before, during, and after the hurricanes. C1 [Li, C.; Inoue, M.; Rouse, L.; Welsh, S.; Coor, Jennifer; Weeks, E.] Louisiana State Univ, Inst Coastal Studies, Dept Oceanog & Coastal Sci, Baton Rouge, LA 70803 USA. [Crout, R.] Stennis Space Ctr, Stennis Space Ctr, MS 39529 USA. RP Li, C (reprint author), Louisiana State Univ, Inst Coastal Studies, Dept Oceanog & Coastal Sci, Baton Rouge, LA 70803 USA. FU Minerals Management Service (MMS) through Cooperative Agreement [0104CA32806]; Task Order [0106TO39901] FX This study was funded by the Minerals Management Service (MMS) through Cooperative Agreement 0104CA32806, Task Order 0106TO39901. NR 13 TC 0 Z9 0 U1 0 U2 3 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 0197-7385 BN 978-0-933957-37-4 J9 OCEANS-IEEE PY 2007 BP 944 EP + PG 2 WC Engineering, Marine; Oceanography; Remote Sensing; Telecommunications SC Engineering; Oceanography; Remote Sensing; Telecommunications GA BHU56 UT WOS:000256526300139 ER PT S AU Newcomb, JJ Snyder, MA Hillstrom, WR Goodman, R AF Newcomb, Joal J. Snyder, Mark A. Hillstrom, Wesley R. Goodman, Ralph GP IEEE TI Measurements of ambient noise during extreme wind conditions in the Gulf of Mexico SO 2007 OCEANS, VOLS 1-5 SE OCEANS-IEEE LA English DT Proceedings Paper CT 2007 OCEANS Conference CY SEP 29-OCT 04, 2007 CL Vancouver, CANADA SP MTS, IEEE, Canada, Oceanworks, ISE Grp Co, Sun Star Elect L P, KONGSBERG, IMAGENEX TECHNOL CORP, ONR, OPSI ID UNDERWATER AB The Littoral Acoustic Demonstration Center (LADC) deployed three Environmental Acoustic Recording System (EARS) buoys in the northern Gulf of Mexico during the summer of 2002 (LADC 02). The hydrophone of each buoy was approximately 50 m from the bottom in water depths of 645 m to 1034 m. During LADC 02 Tropical Storm Isidore and Hurricane Lili passed within approximately 73 nmi and 116 nmi, respectively, west of the EARS buoys. The proximity of these storm systems to the EARS buoys, in conjunction with wind speed data from three nearby National Data Buoy Center weather (NDBC) buoys, allows for the direct comparison of underwater ambient noise levels with high wind speeds. These results are compared to the G. M. Wenz spectra at frequencies from 1 kHz to 5.5 kHz. Anomalously high levels of ambient noise may be due to banding effects of the storms. Results of the ambient noise analysis will be presented. C1 [Newcomb, Joal J.] USN, Res Lab, Code 7185,Bldg 1005, Stennis Space Ctr, MS 39529 USA. [Snyder, Mark A.; Hillstrom, Wesley R.] Stennis Space Ctr, Naval Oceangraph Office, Stennis Space Ctr, MS 39529 USA. [Goodman, Ralph] Univ So Mississippi, Stennis Space Ctr, MS 39529 USA. RP Newcomb, JJ (reprint author), USN, Res Lab, Code 7185,Bldg 1005, Stennis Space Ctr, MS 39529 USA. FU ONR Program Element [62435N] FX This research was supported by ONR Program Element 62435N. NR 4 TC 0 Z9 0 U1 2 U2 2 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 0197-7385 BN 978-0-933957-37-4 J9 OCEANS-IEEE PY 2007 BP 958 EP + PG 2 WC Engineering, Marine; Oceanography; Remote Sensing; Telecommunications SC Engineering; Oceanography; Remote Sensing; Telecommunications GA BHU56 UT WOS:000256526300141 ER PT S AU Meeson, BW McDonnell, J Parsons, C AF Meeson, Blanche W. McDonnell, Janice Parsons, Chris GP IEEE TI More than one-way to catch a fish: Use of effective translation of ocean science to promote ocean literacy SO 2007 OCEANS, VOLS 1-5 SE OCEANS-IEEE LA English DT Proceedings Paper CT 2007 OCEANS Conference CY SEP 29-OCT 04, 2007 CL Vancouver, CANADA SP MTS, IEEE, Canada, Oceanworks, ISE Grp Co, Sun Star Elect L P, KONGSBERG, IMAGENEX TECHNOL CORP, ONR, OPSI AB An understanding and appreciation of the ocean, Great Lakes and coasts' role in our lives (from commerce to recreation to weather) and our interdependence upon them is a chief goal of the Ocean Literacy Initiative. Today most Americans undervalue the ocean because few know and value the vital functions the ocean performs in service to our society and to each of us individually. One requisite for ocean literacy is the promotion of effective life-long learning of these vital functions and services through sustained communication that captures both our hearts and minds. Story development and data translation address one aspect of lifelong learning, the sustained supply of compelling and accurate science and technology stories about the ocean, coasts, and Great Lakes. Stories that educators and communication professionals can incorporate into all types of learning materials. Here we continue our examination of two models (Government Research Enterprise and an Academic Research Organization) that are case studies in developing and identifying highly effective story development and data translation practices. C1 [Meeson, Blanche W.] NASA, Goddard Space Flight Ctr, Mailstop 610-2, Greenbelt, MD 20771 USA. [McDonnell, Janice] State Univ New Jersey, Marine & Coastal Sci Inst, New Brunswick, NJ 08901 USA. [Parsons, Chris] Word Craft, Monterey, CA 93942 USA. RP Meeson, BW (reprint author), NASA, Goddard Space Flight Ctr, Mailstop 610-2, Greenbelt, MD 20771 USA. FU NASA FX B.M. would like to gratefully acknowledge NASA's support for this work and the contribution of the entire Earth science story development and data translation team in the development of this case study. J.M, C.K. gratefully acknowledge NSF's support which has contributed to the development of the model outlined here. NR 9 TC 0 Z9 0 U1 1 U2 4 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 0197-7385 BN 978-0-933957-37-4 J9 OCEANS-IEEE PY 2007 BP 1556 EP + PG 2 WC Engineering, Marine; Oceanography; Remote Sensing; Telecommunications SC Engineering; Oceanography; Remote Sensing; Telecommunications GA BHU56 UT WOS:000256526301043 ER PT B AU Mochizuki, M Asada, A Ura, T Tanaka, T Zheng, H Ensign, T Kawai, K Colombo, OL Nagahashi, K AF Mochizuki, Masashi Asada, Akira Ura, Tamaki Tanaka, Teruki Zheng, Hong Ensign, Tom Kawai, Koji Colombo, Oscar L. Nagahashi, Kenji GP IEEE TI Development of seafloor geodetic observation system based on AUV technology SO 2007 SYMPOSIUM ON UNDERWATER TECHNOLOGY AND WORKSHOP ON SCIENTIFIC USE OF SUBMARINE CABLES AND RELATED TECHNOLOGIES, VOLS 1 AND 2 LA English DT Proceedings Paper CT 5th International Symposium on Underwater Technology/5th Workshop on Scientific Use of Submarine Cables and Related Technologies CY APR 17-20, 2007 CL Tokyo, JAPAN SP IEEE Ocean Engn Soc, IEEE OES, Japan Chapter, Univ Tokyo, Inst Ind Sci, US Off Naval Res Global Asia, Japan Agcy Marine Earth Sci & Technol AB Institute of Industrial Science, University of Tokyo has started a project to develop new-generation seafloor geodetic observation system in cooperation with Hydrographic and Oceanographic Department, Japan Coast Guard. Central idea of this new system is to utilize techniques underwater robot and seafloor platform to take measurements in place of using a research vessel. Combination of these two techniques make it possible to conduct the observation with selecting favorable condition of sea and GPS satellite distributions, to make much more frequent observations and to enable flexible planning of observation in response to sudden geodetic events. Trial model of the newly developing system was finished. The repetition of trial and error has begun through a number of the field experiments in order to bring the system to completion. C1 [Mochizuki, Masashi; Asada, Akira; Ura, Tamaki] Univ Tokyo, Inst Ind Sci, Tokyo, Japan. [Tanaka, Teruki; Zheng, Hong] SEA Corp, Tokyo, Japan. [Ensign, Tom] Engn Acoust Inc, Casselberry, FL USA. [Kawai, Koji] Japan Coast Guard, Hydrog & Ocenog Dept, Tokyo, Japan. [Colombo, Oscar L.] NASA, Goddard Space Flight Ctr, GEST, Greenbelt, MD USA. [Nagahashi, Kenji] Mitsui Engn & Shipbldg Co Ltd, Tokyo, Japan. RP Mochizuki, M (reprint author), Univ Tokyo, Inst Ind Sci, Tokyo, Japan. FU Ministry for Education, Culture, Sports, Science and Technology, Japan. FX We acknowledge the city of Ito, the Ito Sunrise Marina and the Ito fisheries cooperative association for providing their facilities for our conducting the observation. The authors thank to crew members on the JHOD R/V TENYO for their skillful support during the observation The GMT software [18] was used for preparing some of the figures in this paper. This research is supported by the Grant-in Aid for Scientific Research from the Ministry for Education, Culture, Sports, Science and Technology, Japan. NR 18 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA BN 978-1-4244-1207-5 PY 2007 BP 223 EP + DI 10.1109/UT.2007.370789 PG 3 WC Robotics; Oceanography; Remote Sensing SC Robotics; Oceanography; Remote Sensing GA BGM65 UT WOS:000248512300039 ER PT B AU Modarress, D Svitek, P Modarress, K Wilson, DW AF Modarress, D. Svitek, Pavel Modarress, Katy Wilson, Daniel W. GP IEEE TI Micro-optical sensors for underwater velocity measurement SO 2007 Symposium on Underwater Technology and Workshop on Scientific Use of Submarine Cables and Related Technologies, Vols 1 and 2 LA English DT Proceedings Paper CT 5th International Symposium on Underwater Technology/5th Workshop on Scientific Use of Submarine Cables and Related Technologies CY APR 17-20, 2007 CL Tokyo, JAPAN SP IEEE Ocean Engn Soc, IEEE OES, Japan Chapter, Univ Tokyo, Inst Ind Sci, US Off Naval Res Global Asia, Japan Agcy Marine Earth Sci & Technol AB This manuscript describes recent progress in the development and fielding of optical MEMS-based Mini- and Micro-sensors for surface and underwater applications. The non-intrusive sensors have been developed to measure vehicle speed, boundary layer velocity profile, and skin friction. The MiniLDV (TM) and Micro Velocimeters have been used as a speed sensor in torpedoes, scaled submarines, and surface vessels at sea and in tow tanks. The same instruments have also been used for boundary layer profilometry at variety of Reynolds numbers. MicroS (TM) shear stress sensors have been used for drag reduction studies in full-scale sea trials. The small size and integrated electronics of the micro-sensors make them especially appropriate for applications in UUV and AUV. In all cases, particles present in the ocean water were found to be adequate both in concentration and size as scattering sources for the measurement. The building blocks for MEMS-based optical sensors are described and examples of sea trials are presented. C1 MSE, Pasadena, CA USA. Jet Propuls Lab, Pasadena, CA USA. RP Modarress, D (reprint author), MSE, Pasadena, CA 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 978-1-4244-1207-5 PY 2007 BP 235 EP 239 DI 10.1109/UT.2007.370801 PG 5 WC Robotics; Oceanography; Remote Sensing SC Robotics; Oceanography; Remote Sensing GA BGM65 UT WOS:000248512300041 ER PT J AU Meuleau, N Brafman, RI AF Meuleau, Nicolas Brafman, Ronen I. BE Veloso, MM TI Hierarchical Heuristic Forward Search in Stochastic Domains SO 20TH INTERNATIONAL JOINT CONFERENCE ON ARTIFICIAL INTELLIGENCE LA English DT Proceedings Paper CT 20th International Joint Conference on Artificial Intelligence CY JAN 06-12, 2007 CL Hyderabad, INDIA AB Many MDPs exhibit an hierarchical structure where the agent needs to perform various subtasks that are coupled only by a small sub-set of variables containing, notably, shared resources. Previous work has shown how this hierarchical structure can be exploited by solving several sub-MDPs representing the different subtasks in different calling contexts, and a root MDP responsible for sequencing and synchronizing the subtasks, instead of a huge MDP representing the whole problem. Another important idea used by efficient algorithms for solving flat MDPs, such as (L)AO* and (L)RTDP, is to exploit reachability information and an admissible heuristics in order to accelerate the search by pruning states that cannot be reached from a given starting state under an optimal policy. In this paper, we combine both ideas and develop a variant of the AO* algorithm for performing forward heuristic search in hierarchical models. This algorithm shows great performance improvements over hierarchical approaches using standard MDP solvers such as Value Iteration, as well as with respect to AO* applied to a flat representation of the problem. Moreover, it presents a general new method for accelerating AO* and other forward search algorithms. Substantial performance gains may be obtained in these algorithms by partitioning the set of search nodes, and solving a subset of nodes completely before propagating the results to other subsets. C1 [Meuleau, Nicolas] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. RP Meuleau, N (reprint author), NASA, Ames Res Ctr, Mail Stop 269-3, Moffett Field, CA 94035 USA. EM nmeuleau@email.arc.nasa.gov; brafman@cs.bgu.ac.il NR 12 TC 1 Z9 1 U1 0 U2 0 PU IJCAI-INT JOINT CONF ARTIF INTELL PI FREIBURG PA ALBERT-LUDWIGS UNIV FREIBURG GEORGES-KOHLER-ALLEE, INST INFORMATIK, GEB 052, FREIBURG, D-79110, GERMANY PY 2007 BP 2542 EP 2549 PG 8 WC Computer Science, Artificial Intelligence; Computer Science, Theory & Methods SC Computer Science GA BRU54 UT WOS:000283721000408 ER PT B AU Hinchey, M Dai, YS Rouff, CA Rash, JL Qi, MR AF Hinchey, Michael Dai, Yuan-Shun Rouff, C. A. Rash, James L. Qi, Mingrui GP IEEE Computer Society TI Modeling for NASA autonomous nano-technology swarm missions and model-driven autonomic computing SO 21ST INTERNATIONAL CONFERENCE ON ADVANCED NETWORKING AND APPLICATIONS, PROCEEDINGS LA English DT Proceedings Paper CT 21st International Conference on Advanced Networking and Applications CY MAY 21-23, 2007 CL Niagara Falls, CANADA SP IEEE Comp Soc Tech Comm Distributed Proc, Nokia AB NASA ANTS (Autonomous Nano-Technology Swarm missions will be operating in the universe, and therefore rely much on high autonomy. This paper presents a novel technology for NASA's ANTS missions, named as Model-Driven Autonomic Computing. As the foundation for the technology, a new model is constructed for the ANTS system. Exceeding other existent models, the new hierarchical model overcomes the challenges of largeness, complexity, dynamicity and unexpectedness possessed by the ANTS system. Then, the paper exhibits the structure and functions of virtual neuron that is basic unit together with the model for the model-driven autonomic technology in ANTS missions. The paper also deploys self-configuration, self-healing, self-optimization and self-protection for ANTS. A case study, examples and simulations are illustrated C1 [Hinchey, Michael] Loyola Coll, Dept Comp Sci, Baltimore, MD 21210 USA. [Dai, Yuan-Shun; Qi, Mingrui] Purdue Univ, IUPUI, Dept Comp Sci, W Lafayette, IN USA. [Rouff, C. A.] SAIC, Mclean, VA USA. [Rash, James L.] NASA, Goddard Space Flight Ctr, Goddard, MD USA. RP Hinchey, M (reprint author), Loyola Coll, Dept Comp Sci, Baltimore, MD 21210 USA. EM mhinchey@loyola.edu; ydai@cs.iupui.edu; qim@cs.iupui.edu NR 13 TC 1 Z9 2 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 978-0-7695-2846-5 PY 2007 BP 250 EP + DI 10.1109/AINA.2007.93 PG 2 WC Computer Science, Theory & Methods; Telecommunications SC Computer Science; Telecommunications GA BGH66 UT WOS:000247030000035 ER PT B AU Kobler, B McCall, F Van Opstal, M Thompson, H Hunter, K AF Kobler, Ben McCall, Fritz Van Opstal, Mike Thompson, Hoot Hunter, Kirk TI Early experiences in managing inter-site storage area networks using secure web services SO 24TH IEEE CONFERENCE ON MASS STORAGE SYSTEMS AND TECHNOLOGIES, PROCEEDINGS LA English DT Proceedings Paper CT 24th IEEE Conference on Mass Storage Systems and Technologies CY SEP 24-27, 2007 CL San Diego, CA SP IEEE Comp Soc, MSSTC AB The NASA Goddard Space Flight Center and the University of Maryland Institute for Advanced Computer Studies have deployed a pilot system for managing distributed IP-Based Storage Area Networks of dynamically allocated SAN extensions in the Advanced Virtual Engine Test Cell (AVETEC) Data Intensive Computing Environment (DICE). The system implements the framework for managing inter-site storage area networks using Grid and Web Services technologies presented at MSST06. It includes several new components including a basic registry and a java-based command line interface. The test-bed provides some early experiences with the reliability, usability, and security of the system, as well as some performance testing of the web services. C1 [Kobler, Ben] NASA, Goddard Space Flight Ctr, Washington, DC 20006 USA. [McCall, Fritz; Van Opstal, Mike] Univ Maryland, Inst Adv Comp Studies, College Pk, MD USA. [Thompson, Hoot; Hunter, Kirk] Patuxent Technol, Jacksonville, FL USA. RP Kobler, B (reprint author), NASA, Goddard Space Flight Ctr, Washington, DC 20006 USA. EM ben.kobler@nasa.gov; fmccall@umiacs.umd.edu; mvanopst@umiacs.umd.edu; hoot@ptpnow.edu; khunter@ptpnow.edu NR 13 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 978-0-7695-3025-3 PY 2007 BP 293 EP + DI 10.1109/MSST.2007.4367988 PG 2 WC Computer Science, Hardware & Architecture; Computer Science, Information Systems; Computer Science, Theory & Methods; Engineering, Electrical & Electronic SC Computer Science; Engineering GA BGX98 UT WOS:000251201000029 ER PT S AU Lutz, R AF Lutz, Robyn TI Portraits in practice SO 29TH INTERNATIONAL CONFERENCE ON SOFTWARE ENGINEERING: ICSE 2007 COMPANION VOLUME, PROCEEDINGS SE International Conference on Software Engineering LA English DT Proceedings Paper CT 29th International Conference on Software Engineering (ICSE 2007) CY MAY 20-26, 2007 CL Minneapolis, MN SP IEEE Comp Soc, TCSE, ACM SIGSOFT AB Portraits in Practice invites companies with technically advanced software-engineering practices and intriguing research challenges to discuss them with the XSE 2007 participants. The sessions in this track let researchers hear industrial practitioners describe their projects and concerns in some detail, and they let other practitioners hear what technologies these companies recommend. The track provides an open discussion and blunt assessment of future needs with experts from these leading industries. The goal is to encourage and foment improved communication between leading companies and academic researchers. C1 [Lutz, Robyn] Iowa State Univ, Ames, IA 50011 USA. [Lutz, Robyn] Jet Prop Lab, Pasadena, CA USA. RP Lutz, R (reprint author), Iowa State Univ, Ames, IA 50011 USA. EM rlutz@cs.iastate.edu NR 0 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 SN 0270-5257 BN 978-0-7695-2892-2 J9 PROC INT CONF SOFTW PY 2007 BP 33 EP + DI 10.1109/ICSECOMPANION.2007.58 PG 2 WC Computer Science, Software Engineering SC Computer Science GA BGH68 UT WOS:000247030600010 ER PT S AU Dehlinger, J Humphrey, M Suvorov, L Padmanabhan, P Lutz, R AF Dehlinger, Josh Humphrey, Meredith Suvorov, Lada Padmanabhan, Prasanna Lutz, Robyn TI DECIMAL and PLFaultCAT: From product-line requirements to Product-Line member software fault trees SO 29TH INTERNATIONAL CONFERENCE ON SOFTWARE ENGINEERING: ICSE 2007 COMPANION VOLUME, PROCEEDINGS SE International Conference on Software Engineering LA English DT Proceedings Paper CT 29th International Conference on Software Engineering (ICSE 2007) CY MAY 20-26, 2007 CL Minneapolis, MN SP IEEE Comp Soc, TCSE, ACM SIGSOFT AB PLFaultCAT is a tool for software fault tree analysis (SFTA) during product-line engineering. When linked with DECIMAL, a product-line requirements verification tool, the enhanced version of PLFaultCAT provides traceability between product-line requirements and SFTA hazards as well as semi-automated derivation of the SFTA for each new product-line system previously verified by DECIMAL. The combined tool reduces the effort needed to safely reuse requirements and customize the product-line SFTA as each new system is constructed. C1 [Dehlinger, Josh; Humphrey, Meredith; Suvorov, Lada; Lutz, Robyn] Iowa State Univ, Ames, IA 50011 USA. [Padmanabhan, Prasanna] Citrix Syst Inc, Ft Lauderdale, FL 33309 USA. [Lutz, Robyn] CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. RP Dehlinger, J (reprint author), Iowa State Univ, Ames, IA 50011 USA. EM dehlinge@iastate.edu; mjh@iastate.edu; suvorov@iastate.edu; p.prasanna@mailcity.com; rlutz@cs.iastate.edu FU National Science Foundation [0204139, 0205588, 0541163] FX This research was supported by the National Science Foundation under grants 0204139, 0205588 and 0541163. NR 3 TC 3 Z9 3 U1 0 U2 3 PU IEEE COMPUTER SOC PI LOS ALAMITOS PA 10662 LOS VAQUEROS CIRCLE, PO BOX 3014, LOS ALAMITOS, CA 90720-1264 USA SN 0270-5257 BN 978-0-7695-2892-2 J9 PROC INT CONF SOFTW PY 2007 BP 49 EP + DI 10.1109/ICSECOMPANION.2007.29 PG 2 WC Computer Science, Software Engineering SC Computer Science GA BGH68 UT WOS:000247030600016 ER PT S AU Black, JK AF Black, J. K. BE Irastorza, IG Colas, P Gorodetzky, P TI TPCs in high-energy astronomical polarimetry - art. no. 012005 SO 3rd Symposium on Large TPCs for Low Energy Rare Event Detection SE JOURNAL OF PHYSICS CONFERENCE SERIES LA English DT Proceedings Paper CT 3rd Symposium on Large TPCs for Low Energy Rare Event Detection CY DEC 11-12, 2006 CL Paris, FRANCE ID X-RAY-POLARIZATION; ADVANCED COMPTON TELESCOPE; CRAB-NEBULA; PHOTON POLARIZATION; IMAGING DETECTOR; ASTROPHYSICS; SENSITIVITY; PERFORMANCE; CHAMBER; MISSION AB High-energy astrophysics has yet to exploit the unique and important information that polarimetry could provide, largely due to the limited sensitivity of previously available polarimeters. In recent years, numerous efforts have been initiated to develop instruments with the sensitivity required for astronomical polarimetry over the 100 eV to 10 GeV band. Time projection chambers (TPCs), with their high-resolution event imaging capability, are an integral part of some of these efforts. After a brief overview of current astronomical polarimeter development efforts, the role of TPCs will be described in more detail. These include TPCs as photoelectric X-ray polarimeters and TPCs as components of polarization-sensitive Compton and pair-production telescopes. C1 NASA, Goddard Space Flight Ctr, Silver Spring, MD 20910 USA. RP Black, JK (reprint author), NASA, Goddard Space Flight Ctr, Code 662, Silver Spring, MD 20910 USA. NR 46 TC 7 Z9 7 U1 0 U2 0 PU IOP PUBLISHING LTD PI BRISTOL PA DIRAC HOUSE, TEMPLE BACK, BRISTOL BS1 6BE, ENGLAND SN 1742-6588 J9 J PHYS CONF SER PY 2007 VL 65 BP 12005 EP 12005 AR 012005 DI 10.1088/1742-6596/65/1/012005 PG 10 WC Physics, Applied; Physics, Nuclear SC Physics GA BGU27 UT WOS:000250576600005 ER PT S AU Thompson, DJ AF Thompson, D. J. CA GLAST LAT Collaboration BE Bassa, CG Wang, Z Cumming, A Kaspi, VM TI Gamma-ray pulsar studies with GLAST SO 40 YEARS OF PULSARS: MILLISECOND PULSARS, MAGNETARS AND MORE SE AIP Conference Proceedings LA English DT Proceedings Paper CT AIP Conference: 40 Years of Pulsars CY AUG 12-17, 2007 CL Montreal, CANADA SP McGill Univ, Phys Dept, McGill Univ, Fac Sci, Canadian Inst Theoret Astrophys, Canadian Inst Adv Res DE pulsars; gamma rays, telescopes ID MILLISECOND PULSARS; X-RAY; EMISSION; DISCOVERY; RADIATION; RADIO; YOUNG; SEARCH AB Some pulsars have their maximum observable energy output in the gamma-ray band, offering the possibility of using these high-energy photons as probes of the particle acceleration and interaction processes in pulsar magnetospheres. After an extended hiatus between satellite missions, the recently-launched AGILE mission and the upcoming Gamma-ray Large Area Space Telescope (GLAST) Large Area Telescope (LAT) will allow gamma-ray tests of the theoretical models developed based on past discoveries. With its greatly improved sensitivity, better angular resolution, and larger energy reach than older instruments, GLAST LAT should detect dozens to hundreds of new gamma-ray pulsars and measure luminosities, light curves, and phase-resolved spectra with unprecedented resolution. It will also have the potential to find radio-quiet pulsars like Geminga, using blind search techniques. Cooperation with radio and X-ray pulsar astronomers is an important aspect of the LAT team's planning for pulsar studies. C1 [Thompson, D. J.; GLAST LAT Collaboration] NASA, Goddard Space Flight Ctr, Astrophys Sci Div, Greenbelt, MD 20771 USA. RP Thompson, DJ (reprint author), NASA, Goddard Space Flight Ctr, Astrophys Sci Div, Greenbelt, MD 20771 USA. RI Thompson, David/D-2939-2012 OI Thompson, David/0000-0001-5217-9135 NR 31 TC 0 Z9 0 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 978-0-7354-0502-8 J9 AIP CONF PROC PY 2007 VL 983 BP 56 EP 63 PG 8 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BHL21 UT WOS:000254022400009 ER PT S AU Gavriil, FP Dib, R Kaspi, VM AF Gavriil, Fotis P. Dib, Rim Kaspi, Victoria M. BE Bassa, CG Wang, Z Cumming, A Kaspi, VM TI Activity from magnetar candidate 4U 0142+61: Bursts and emission lines SO 40 YEARS OF PULSARS: MILLISECOND PULSARS, MAGNETARS AND MORE SE AIP Conference Proceedings LA English DT Proceedings Paper CT AIP Conference: 40 Years of Pulsars CY AUG 12-17, 2007 CL Montreal, CANADA SP McGill Univ, Phys Dept, McGill Univ, Fac Sci, Canadian Inst Theoret Astrophys, Canadian Inst Adv Res DE anomalous X-ray pulsar; magnetar; neutron star ID X-RAY PULSAR; SOFT GAMMA-REPEATERS; NEUTRON-STARS; 1E-1048.1-5937; 4U-0142+61; OUTBURST AB After 6 years of quiescence, Anomalous X-ray Pulsar (AXP) 4U 0142+61 entered an active phase in 2006 March that lasted several months. During the active phase, several bursts were detected, and many aspects of the X-ray emission changed. We report on the discovery of six X-ray bursts, the first ever seen from this AXP in similar to 10 years of Rossi X-ray Timing Explorer monitoring. All the bursts occurred in the interval between 2006 April 6 and 2007 February 7. The burst durations ranged from 8-3 x 10(3) s as characterized by T-90. These are very long durations even when compared to the broad T90 distributions of other bursts from AXPs and Soft Gamma Repeaters (SGRs). The first five burst spectra are well modeled by simple blackbodies, with temperature kT similar to 2-6 keV However, the sixth and most energetic burst had a complicated spectrum consisting of at least three emission lines with possible additional emission and absorption lines. The most significant feature was at similar to 14 keV. Similar 14-keV spectral features were seen in bursts from AXPs 1E 1048.1-5937 and XTE J1810-197. If this feature is interpreted as a proton cyclotron line, then it supports the existence of a magnetar-strength field for these AXPs. Several of the bursts were accompanied by a short-term pulsed flux enhancement. We discuss these events in the context of the magnetar model. C1 [Gavriil, Fotis P.] NASA, Goddard Space Flight Ctr, Astrophys Sci Div, Code 662, Greenbelt, MD 20771 USA. [Gavriil, Fotis P.] Univ Maryland Baltimore Cty, CRESST, Baltimore, MD 21250 USA. [Dib, Rim; Kaspi, Victoria M.] McGill Univ, Dept Phys, 3600 Univ St, Montreal, PQ H3A 2T8, Canada. RP Gavriil, FP (reprint author), NASA, Goddard Space Flight Ctr, Astrophys Sci Div, Code 662, Greenbelt, MD 20771 USA. NR 20 TC 0 Z9 0 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 978-0-7354-0502-8 J9 AIP CONF PROC PY 2007 VL 983 BP 234 EP + PG 2 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BHL21 UT WOS:000254022400054 ER PT S AU Dib, R Kaspi, VM Gavrii, FP AF Dib, Rim Kaspi, Victoria M. Gavrii, Fotis P. BE Bassa, CG Wang, Z Cumming, A Kaspi, VM TI Glitches in anomalous X-ray pulsars SO 40 YEARS OF PULSARS: MILLISECOND PULSARS, MAGNETARS AND MORE SE AIP Conference Proceedings LA English DT Proceedings Paper CT AIP Conference: 40 Years of Pulsars CY AUG 12-17, 2007 CL Montreal, CANADA SP McGill Univ, Phys Dept, McGill Univ, Fac Sci, Canadian Inst Theoret Astrophys, Canadian Inst Adv Res DE anomalous X-ray pulsar; magnetar; neutron star ID 1RXS J170849.0-400910; NEUTRON STARS; VORTEX CREEP; SUPERFLUIDITY; VARIABILITY; 4U-0142+61; EMISSION; OUTBURST AB After 10 years of RXTE monitoring of 5 Anomalous X-ray Pulsars, we report the detection of 10 glitches and 5 glitch candidates. Armed with sufficient data for a meaningful comparison of AXP and radio pulsar glitch properties, we show that in terms of fractional frequency change, AXPs are among the most actively glitching neutron stars, with glitch amplitudes in general larger than in radio pulsars. However, in terms of absolute glitch amplitude, AXP glitches are unremarkable. We show that three of the largest AXP glitches observed thus far have recoveries that are unusual among those of radio pulsar glitches, with the combination of recovery time scale and fraction yielding changes in spin-down rates following the glitch similar to, or larger than, the long-term average. We also observed a large long-term fractional increase in the magnitude of the spin-down rate of 1E 1841-045, following its largest glitch. These observations are challenging to interpret in standard glitch models, as is the frequent occurence of large glitches given AXPs' high measured temperatures. We speculate that the stellar core may be involved in the largest AXP glitches. Furthermore we show that unlike in radio pulsars, AXP glitches sometimes, but not necessarily always, involve major radiative events. C1 [Dib, Rim; Kaspi, Victoria M.] McGill Univ, Dept Phys, 3600 Univ St, Montreal, PQ H3A 2T8, Canada. [Gavrii, Fotis P.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Dib, R (reprint author), McGill Univ, Dept Phys, 3600 Univ St, Montreal, PQ H3A 2T8, Canada. NR 25 TC 0 Z9 0 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 978-0-7354-0502-8 J9 AIP CONF PROC PY 2007 VL 983 BP 239 EP + PG 2 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BHL21 UT WOS:000254022400055 ER PT S AU Dib, R Kaspi, VM Gavriil, FP AF Dib, Rim Kaspi, Victoria M. Gavriil, Fotis P. BE Bassa, CG Wang, Z Cumming, A Kaspi, VM TI 10 years of RXTE monitoring of five anomalous X-ray pulsars SO 40 YEARS OF PULSARS: MILLISECOND PULSARS, MAGNETARS AND MORE SE AIP Conference Proceedings LA English DT Proceedings Paper CT AIP Conference: 40 Years of Pulsars CY AUG 12-17, 2007 CL Montreal, CANADA SP McGill Univ, Phys Dept, McGill Univ, Fac Sci, Canadian Inst Theoret Astrophys, Canadian Inst Adv Res DE anomalous X-ray pulsar; magnetar; neutron star ID GLITCH; OUTBURST; BURSTS; 4U-0142+61; EMISSION AB Anomalous X-ray Pulsars are believed to be magnetars: young, isolated neutron stars powered by a large magnetic energy reservoir. Here, we review recent observational progress on five anomalous X-ray pulsars based on a 10-year long monitoring project done using the Rossi X-Ray Timing Explorer (RXTE). In particular, we discuss timing behavior including glitches, radiative variability including bursts, pulsed flux changes, and pulse profile changes. We compare the timing properties to those of regular rotation-powered pulsars, and we consider the observed radiative phenomena in the context of the magnetar model. C1 [Dib, Rim; Kaspi, Victoria M.] McGill Univ, Dept Phys, 3600 Univ St, Montreal, PQ H3A 2T8, Canada. [Gavriil, Fotis P.] NASA, Goddard Space Flight Ctr, Ctr Astrophys Sci, Code 661, Greenbelt, MD 20771 USA. RP Dib, R (reprint author), McGill Univ, Dept Phys, 3600 Univ St, Montreal, PQ H3A 2T8, Canada. NR 28 TC 0 Z9 0 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 978-0-7354-0502-8 J9 AIP CONF PROC PY 2007 VL 983 BP 262 EP + PG 2 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BHL21 UT WOS:000254022400060 ER PT S AU Tam, CR Gavriil, FP Dib, R Kaspi, VM Woods, PM Bassa, C AF Tam, Cindy R. Gavriil, Fotis P. Dib, Rim Kaspi, Victoria M. Woods, Peter M. Bassa, Cees BE Bassa, CG Wang, Z Cumming, A Kaspi, VM TI The variable X-ray and near-IR behavior of the particularly anomalous X-ray pulsar 1E 1048.1-5937 SO 40 YEARS OF PULSARS: MILLISECOND PULSARS, MAGNETARS AND MORE SE AIP Conference Proceedings LA English DT Proceedings Paper CT AIP Conference: 40 Years of Pulsars CY AUG 12-17, 2007 CL Montreal, CANADA SP McGill Univ, Phys Dept, McGill Univ, Fac Sci, Canadian Inst Theoret Astrophys, Canadian Inst Adv Res DE anomalous X-ray pulsar; magnetar; neutron star ID SOFT GAMMA-REPEATERS; MAGNETIZED NEUTRON-STARS; INFRARED COUNTERPART; VARIABILITY; 1E-1048.1-5937; MAGNETARS; EMISSION; SPECTRUM AB We present the results of X-ray and near-IR observations of the anomalous X-ray pulsar 1E 1048.1-5937, believed to be a magnetar. This AXP underwent a period of extreme variability during 2001-2004, but subsequently entered an extended and unexpected quiescence in 2004-2006, during which we monitored it with RXTE, CXO, and HST. Its timing properties were stable for >3 years throughout the quiescent period. 1E 1048.1-5937 again went into outburst in March 2007, which saw a factor of >7 total X-ray flux increase which was anti-correlated with a pulsed fraction decrease, and correlated with spectral hardening, among other effects. The near-IR counterpart also brightened following the 2007 event. We discuss our findings in the context of the magnetar and other models. C1 [Tam, Cindy R.; Dib, Rim; Kaspi, Victoria M.; Bassa, Cees] McGill Univ, Dept Phys, 3600 Univ St, Montreal, PQ H3A 2T8, Canada. [Gavriil, Fotis P.] NASA, Goddard Space Flight Ctr, Astrophys Sci Div, Greenbelt, MD 20771 USA. [Woods, Peter M.] Dynet Inc, Huntsville, AL 35806 USA. [Woods, Peter M.] NSSTC, Huntsville, AL 35805 USA. RP Tam, CR (reprint author), McGill Univ, Dept Phys, 3600 Univ St, Montreal, PQ H3A 2T8, Canada. NR 18 TC 0 Z9 0 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 978-0-7354-0502-8 J9 AIP CONF PROC PY 2007 VL 983 BP 271 EP + PG 2 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BHL21 UT WOS:000254022400063 ER PT S AU Zhu, WW Kaspi, VM Woods, PM Gavriil, FP Dib, R AF Zhu, Weiwei Kaspi, Victoria M. Woods, Peter M. Gavriil, Fotis P. Dib, Rim BE Bassa, CG Wang, Z Cumming, A Kaspi, VM TI The long-term radiative evolution of anomalous X-ray pulsar 1E 2259+586 after its 2002 outburst SO 40 YEARS OF PULSARS: MILLISECOND PULSARS, MAGNETARS AND MORE SE AIP Conference Proceedings LA English DT Proceedings Paper CT AIP Conference: 40 Years of Pulsars CY AUG 12-17, 2007 CL Montreal, CANADA SP McGill Univ, Phys Dept, McGill Univ, Fac Sci, Canadian Inst Theoret Astrophys, Canadian Inst Adv Res DE anomalous X-ray pulsar; magnetar; neutron star ID 1RXS J170849.0-400910; MAGNETAR; EMISSION; XTE-J1810-197; 1E-2259+586; BURSTS; GLITCH AB We present an analysis of five X-ray Multi-Mirror Mission (XMM) observations of the Anomalous X-ray Pulsar (AXP) 1E 2259+586 taken in 2004 and 2005 during its relaxation following its 2002 outburst. We compare these data with those of five previous XMM observations taken in 2002 and 2003, and find that the observed flux decay is well described by a power-law of index -0.69 +/- 0.03. As of mid-2005, the source may still have been brighter than pre-outburst, and was certainly hotter. We find a strong correlation between hardness and flux, as seen in other AXP outbursts. We discuss the implications of these results for the magnetar model. C1 [Zhu, Weiwei; Kaspi, Victoria M.; Dib, Rim] McGill Univ, Dept Phys, 3600 Univ St, Montreal, PQ H3A 2T8, Canada. [Woods, Peter M.] Dynet Inc, Huntsville, AL 35806 USA. [Woods, Peter M.] NSSTC, Huntsville, AL 35805 USA. [Gavriil, Fotis P.] NASA, Goddard Space Flight Ctr, Astrophys Sci Div, Greenbelt, MD 20771 USA. [Gavriil, Fotis P.] Univ Maryland Baltimore Cty, Ctr Res & Explorat Space Sci & Technol, Baltimore, MD 21250 USA. RP Zhu, WW (reprint author), McGill Univ, Dept Phys, 3600 Univ St, Montreal, PQ H3A 2T8, Canada. NR 24 TC 0 Z9 0 U1 0 U2 0 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 978-0-7354-0502-8 J9 AIP CONF PROC PY 2007 VL 983 BP 277 EP + PG 2 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BHL21 UT WOS:000254022400065 ER PT S AU Motch, C Pires, AM Haberl, F Schwope, A Zavlin, VE AF Motch, C. Pires, A. M. Haberl, F. Schwope, A. Zavlin, V. E. BE Bassa, CG Wang, Z Cumming, A Kaspi, VM TI Proper motions of ROSAT discovered isolated neutron stars measured with Chandra: First X-ray measurement of the large proper motion of RX J1308.6+2127/RBS 1223 SO 40 YEARS OF PULSARS: MILLISECOND PULSARS, MAGNETARS AND MORE SE AIP Conference Proceedings LA English DT Proceedings Paper CT AIP Conference: 40 Years of Pulsars CY AUG 12-17, 2007 CL Montreal, CANADA SP McGill Univ, Phys Dept, McGill Univ, Fac Sci, Canadian Inst Theoret Astrophys, Canadian Inst Adv Res DE isolated neutron stars; proper motions ID RBS1223; ABSORPTION; SPECTRUM AB The unprecedented spatial resolution of the Chandra observatory opens the possibility to detect with relatively high accuracy proper motions at X-ray wavelengths. We have conducted an astrometric study of three of the "Magnificent Seven", the thermally emitting radio quiet isolated neutron stars (INSs) discovered by ROSAT. These three INSs (RX J0420.0-5022, RX J0806.4-4123 and RX J1308.6+2127/RBS 1223) either lack an optical counterpart or have one too faint to be used for astrometric purposes. We obtained ACIS observations 3 to 5 years apart to constrain or measure the displacement of the sources on the X-ray sky using as reference the background of extragalactic or remote galactic X-ray sources. Upper limits of 138 mas/yr and 76 mas/yr on the proper motion of RX J0420.0-5022 and RX J0806.4-4123, respectively, have already been presented in [7]. Here we report the very significant measurement (similar to 10 sigma) of the proper motion of the third INS of our program, RX J1308.6+2127/RBS 1223. Comparing observations obtained in 2002 and 2007 reveals a displacement of 1.1 arcsec implying a yearly proper motion of 223 mas, the second fastest measured for the ROSAT discovered INSs. The source is rapidly moving away from the galactic plane at a speed which precludes any significant accretion of matter from the interstellar medium. Its transverse velocity of similar to 740 (d/700 pc) km/s might be the largest of the "Magnificent Seven" and among the fastest recorded for neutron stars. RX J1 308.6+2127/RBS 1223 is thus a young high velocity cooling neutron star. The source may have its origin in the closest part of the Scutum 0132 association about 0.8 Myr ago, an age consistent with that expected from cooling curves, but significantly younger than inferred from pulse timing measurements (1.5 Myr). C1 [Motch, C.; Pires, A. M.] CNRS, Observ Strasbourg, Strasbourg, France. [Pires, A. M.] Geofis Ciencia Atmosferica USP, Astron Inst, Sao Paulo, Brazil. [Haberl, F.] Max Planck Inst Extraterr Phys, Garching, Germany. [Schwope, A.] Astrophys Inst Potsdam, Potsdam, Germany. [Zavlin, V. E.] NASA, MSFC, Space Sci Lab, Huntsville, AL 35811 USA. RP Motch, C (reprint author), CNRS, Observ Strasbourg, Strasbourg, France. NR 12 TC 1 Z9 1 U1 1 U2 1 PU AMER INST PHYSICS PI MELVILLE PA 2 HUNTINGTON QUADRANGLE, STE 1NO1, MELVILLE, NY 11747-4501 USA SN 0094-243X BN 978-0-7354-0502-8 J9 AIP CONF PROC PY 2007 VL 983 BP 354 EP + PG 2 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BHL21 UT WOS:000254022400084 ER PT S AU Horst, S Anagnostou, DE Ponchak, GE Tentzeris, E Papapolymerou, J AF Horst, Stephen Anagnostou, Dimitrios E. Ponchak, George E. Tentzeris, Emmanouil Papapolymerou, John GP IEEE TI Beam-Shaping of Planar Array Antennas Using Integrated Attenuators SO 57TH ELECTRONIC COMPONENTS & TECHNOLOGY CONFERENCE, 2007 PROCEEDINGS SE Electronic Components and Technology Conference LA English DT Proceedings Paper CT 57th Electronic Components and Technology Conference CY 2007 CL Reno, NV SP Elect Components Assemblies & Mat Assoc, Elect Ind Alliance, IEEE, CPMT AB The use of planar integrated attenuators to shape the beam of a planar array antenna is investigated on a lightweight organic polymer ideal for satellite applications. The entire array is fabricated using a single type of liquid crystal polymer (LCP), reducing the cost of fabrication and simplifying the integration of the attenuators. A fabricated prototype was designed, fabricated, and measured revealing a sidelobe reduction of 12dB compared with a similar antenna using a uniform amplitude distribution, or an overall sidelobe level of -25dB. The 3dB beamwidth of the binomial array was measured to be 31 degrees, an increase of 3 degrees over the uniform amplitude case. C1 [Horst, Stephen; Tentzeris, Emmanouil; Papapolymerou, John] Georgia Inst Technol, 85 5th St NW, Atlanta, GA 30308 USA. [Anagnostou, Dimitrios E.] South Dakato Sch Mines & Technol, Rapid City, SD 57701 USA. [Ponchak, George E.] NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Horst, S (reprint author), Georgia Inst Technol, 85 5th St NW, Atlanta, GA 30308 USA. RI Anagnostou, Dimitris/A-3124-2009 OI Anagnostou, Dimitris/0000-0003-4266-0309 NR 5 TC 0 Z9 0 U1 0 U2 0 PU IEEE PI NEW YORK PA 345 E 47TH ST, NEW YORK, NY 10017 USA SN 0569-5503 BN 978-1-4244-0984-6 J9 ELEC COMP C PY 2007 BP 165 EP + DI 10.1109/ECTC.2007.373792 PG 2 WC Engineering, Electrical & Electronic; Materials Science, Multidisciplinary; Materials Science, Characterization & Testing SC Engineering; Materials Science GA BGJ78 UT WOS:000247705500025 ER PT S AU Beckmann, V Shrader, CR Gehrels, N Soldi, S Produit, N AF Beckmann, V. Shrader, C. R. Gehrels, N. Soldi, S. Produit, N. GP ESA BE Grebenev, S Sunyaev, R Winkler, C TI The hard X-ray luminosity function of integral detected AGN SO 6TH INTEGRAL WORKSHOP: THE OBSCURED UNIVERSE SE ESA SPECIAL PUBLICATIONS LA English DT Proceedings Paper CT 6th Integral Workshop on the Obscured Universe CY JUL 02-08, 2006 CL Space Res Inst, Moscow, RUSSIA SP Space Res Inst, European Space Agcy, Russian Acad Sci, Russian Basic Res Fdn HO Space Res Inst DE galaxies : active; X-rays : galaxies; surveys; galaxies : Seyfert ID ACTIVE GALACTIC NUCLEI; ROSAT DEEP SURVEY; ALL-SKY SURVEY; COSMOLOGICAL EVOLUTION; LOCKMAN FIELD; CATALOG; SPECTRUM; CHANDRA; VARIABILITY; QUASARS AB We have compiled a complete extragalactic sample based on similar to 25,000deg(2) to a limiting flux of 3 x 10(-11) ergs cm(-2) s(-1) (similar to 7,000deg(2) to a flux limit of 10(-11) ergs cm(-2) s(-1)) in the 20 - 40 keV band with INTEGRAL. We have constructed a detailed exposure map to compensate for effects of non-uniform exposure. The flux-number relation is best described by a power-law with a slope of alpha = 1.66 +/- 0.11. The integration of the cumulative flux per unit area leads to f(20-40) (keV) = 2.6 x 10(-10) ergs cm(-2) s(-1) sr(-1), which is about 1% of the known 20 - 40 keV X-ray background. We present the first luminosity function of AGN in the 20-40 keV energy range, based on 38 extragalactic objects detected by the imager IBIS/ISGRI on-board INTEGRAL. The luminosity function shows a smoothly connected two power-law form, with an index of gamma(1) = 0.8 below, and gamma(2) = 2.1 above the turn-over luminosity of L-* = 2.4 x 10(43) ergs s(-1). The emissivity of all INTEGRAL AGN per unit volume is W20-40 (keV) (> 10(41) ergs s(-1)) = 2.8 x 10(38) ergs s(-1) h(70)(3) Mpc(-3). These results are consistent with those derived in the 2 - 20 keV energy band and do not show a significant contribution by Compton-thick objects. Because the sample used in this study is truly local ((z) over bar = 0.022), only limited conclusions can be drawn for the evolution of AGN in this energy band. But the objects explaining the peak in the cosmic X-ray background are likely to be either low luminosity AGN (L-X < 10(41) ergs s(-1)) or of other type, such as intermediate mass black holes, clusters, and star forming regions, or they have to be at higher redshift. C1 [Beckmann, V.; Shrader, C. R.; Gehrels, N.] NASA, Goddard Space Flight Ctr, Astrophys Sci Div, Greenbelt, MD 20771 USA. RP Beckmann, V (reprint author), NASA, Goddard Space Flight Ctr, Astrophys Sci Div, Code 661, Greenbelt, MD 20771 USA. RI Gehrels, Neil/D-2971-2012; OI Produit, Nicolas/0000-0001-7138-7677 NR 35 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 2007 VL 622 BP 173 EP 180 PG 8 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BHK58 UT WOS:000253876500027 ER PT S AU Gehrels, N AF Gehrels, N. CA Swift Team GP ESA BE Grebenev, S Sunyaev, R Winkler, C TI Summary of Swift observations of gamma ray bursts SO 6TH INTEGRAL WORKSHOP: THE OBSCURED UNIVERSE SE ESA Special Publications LA English DT Proceedings Paper CT 6th Integral Workshop on the Obscured Universe CY JUL 02-08, 2006 CL Space Res Inst, Moscow, RUSSIA SP Space Res Inst, European Space Agcy, Russian Acad Sci, Russian Fdn Basic Res HO Space Res Inst DE gamma ray bursts ID 28 FEBRUARY 1997; HOST GALAXY; AFTERGLOW; REDSHIFT; TELESCOPE; GRB-050709; EMISSION; SUPERNOVAE; DISCOVERY; MISSION AB Swift is a NASA MIDEX mission with primary objective to study gamma-ray bursts (GRBs) and use them as probes of conditions in the high-redshift Universe. It is an international mission with hardware participation by the US, UK and Italy. The mission was launched on 20 November 2004 and is detecting similar to 100 gamma-ray bursts (GRBs) each year. For almost every burst there is a prompt (within similar to 90 s) spacecraft repointing to give Xray and UV/optical observations of the afterglow. Swift has already collected an impressive database including prompt emission to higher sensitivities than BATSE, uniform monitoring of afterglows, and rapid follow-up by other observatories notified through the GCN. Significant progress has been made in our understanding of short GRBs. The detection of X-ray afterglows has led to accurate localizations and the conclusion that short GRBs can occur in non-star forming galaxies or regions, whereas long GRBs are strongly concentrated within star forming regions. This is consistent with the NS merger model. Swift has greatly increased the redshift range of GRB detection. The highest redshift GRBs, at z similar to 5 - 6, are approaching the era of reionization. Ground-based deep optical spectroscopy of high redshift bursts is giving metallicity measurements and other information on the source environment to greater distances than other techniques. The localization of GRB 060218 to a nearby galaxy, and association with SN 2006aj, added a valuable member to the class of GRBs with detected supernova. The prospects for future progress are excellent given the > 10 year orbital lifetime of the Swift satellite. C1 [Gehrels, N.; Swift Team] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. RP Gehrels, N (reprint author), NASA, Goddard Space Flight Ctr, Code 661, Greenbelt, MD 20771 USA. EM gehrels@milkyway.gsfc.nasa.gov RI Gehrels, Neil/D-2971-2012 NR 41 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 SPEC PUBL PY 2007 VL 622 BP 527 EP 531 PG 5 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BHK58 UT WOS:000253876500100 ER PT S AU Kazanas, D Mastichiadis, A Georganopoulos, M AF Kazanas, Demosthenes Mastichiadis, Apostolos Georganopoulos, Markos GP ESA BE Grebenev, S Sunyaev, R Winkler, C TI The "supercritical pile" GRB model: Afterglows and GRB, XRR, XRF unification SO 6TH INTEGRAL WORKSHOP: THE OBSCURED UNIVERSE SE ESA SPECIAL PUBLICATIONS LA English DT Proceedings Paper CT 6th Integral Workshop on the Obscured Universe CY JUL 02-08, 2006 CL Space Res Inst, Moscow, RUSSIA SP Space Res Inst, European Space Agcy, Russian Acad Sci, Russian Basic Res Fdn HO Space Res Inst DE gamma ray bursts; afterglows ID GAMMA-RAY BURSTS; ACTIVE GALACTIC NUCLEI; F-NU PEAK; HIGH-ENERGY; LUMINOSITY; SPECTRA; FLARES; BATSE AB We present the general notions and observational consequences of the "Supercritical Pile" GRB model; the fundamental feature of this model is a detailed process for the conversion of the energy stored in relativistic protons in the GRB Relativistic Blast Waves (RBW) into relativistic electrons and then into radiation. The conversion is effected through the p gamma -> p e(+) e(-) reaction, whose kinematic threshold is imprinted on the GRB spectra to provide a peak of their emitted luminosity at energy E-P similar to 1 MeV in the lab frame. We extend this model to include, in addition to the (quasi-)thermal relativistic post-shock protons an accelerated component of power law form. This component guarantees the production of e(+)e(-)-pairs even after the RBW has slowed down to the point that its (quasi-)thermal protons cannot fulfill the threshold of the above reaction. We suggest that this last condition marks the transition from the prompt to the afterglow GRB phase. We also discuss conditions under which this transition is accompanied by a significant drop in the flux and could thus account for several puzzling, recent observations. Finally, we indicate that the same mechanism applied to the late stages of the GRB evolution leads to a decrease in E-p proportional to Gamma(2)(t) proportional to t(-3/4), a feature amenable to future observational tests. C1 [Kazanas, Demosthenes; Georganopoulos, Markos] NASA, Goddard Space Flight Ctr, Astrophys Sci Div, Greenbelt, MD 20771 USA. RP Kazanas, D (reprint author), NASA, Goddard Space Flight Ctr, Astrophys Sci Div, Greenbelt, MD 20771 USA. NR 20 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 2007 VL 622 BP 577 EP 584 PG 8 WC Astronomy & Astrophysics SC Astronomy & Astrophysics GA BHK58 UT WOS:000253876500107 ER PT J AU Ordway, FI Dahm, WK Dannenberg, K Haeussermann, W Reisig, G Stuhlinger, E von Tiesenhausen, G Willhite, I AF Ordway, Frederick I., III Dahm, Werner K. Dannenberg, Konrad Haeussermann, Walter Reisig, Gerhard Stuhlinger, Ernst von Tiesenhausen, Georg Willhite, Irene TI A memoir: From peenemunde to USA: A classic case of technology transfer SO ACTA ASTRONAUTICA LA English DT Article; Proceedings Paper CT 54th International-Astronautical-Federation Congress (IAF) CY SEP 29-OCT 03, 2003 CL Bremen, GERMANY SP Int Astronaut Federat AB This paper traces the development of rocket technology in Germany from the 1930s and 1940s that led to the massive, and historically unprecedented, transfer of rocket, missile, launch-vehicle and related technologies to the post-World-War-II United States. This achievement was made possible by an initial group of 118 German rocket specialists to which others were gradually added. The contributions to rocketry, upper atmosphere and space research, and eventually manned space travel provided by Germany's Wernher von Braun and his team of engineers, scientists, technicians and support personnel is, in particular, described, and the ongoing influence of the innovations they introduced is considered. (c) 2006 Elsevier Ltd. All rights reserved. C1 Marshall Univ Alabama, USA, Redstone Arsenal, Huntsville, AL USA. US Space & Rocket Ctr, Saturn V Restorat Comm, Huntsville, AL USA. NASA, Peenemunde USA Ft Bliss White Sands, Redstone Arsenal, Huntsville, AL USA. One Tranquil Base, Huntsville, AL 35805 USA. RP Ordway, FI (reprint author), Marshall Univ Alabama, USA, Redstone Arsenal, Huntsville, AL USA. EM ordmars@aol.com; irenew@spacecamp.com RI Yin, Yimei/G-7749-2012 NR 41 TC 1 Z9 1 U1 0 U2 2 PU PERGAMON-ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 0094-5765 J9 ACTA ASTRONAUT JI Acta Astronaut. PD JAN PY 2007 VL 60 IS 1 BP 24 EP 47 DI 10.1016/j.actaastro.2006.05.003 PG 24 WC Engineering, Aerospace SC Engineering GA 100YG UT WOS:000241705500004 ER PT J AU Sudbrack, CK Noebe, RD Seidman, DN AF Sudbrack, Chantal K. Noebe, Ronald D. Seidman, David N. TI Compositional pathways and capillary effects during isothermal precipitation in a nondilute Ni-Al-Cr alloy SO ACTA MATERIALIA LA English DT Article DE nanostructure; coarsening; Ni-Al-Cr alloys; atom-probe tomography; capillary phenomena ID 3-DIMENSIONAL ATOM-PROBE; TEMPORAL EVOLUTION; DIFFUSION; KINETICS; SYSTEM; PHASE; NANOSTRUCTURE; MICROSCOPY AB For a Ni-5.2A1-14.2Cr at.% alloy with moderate solute supersaturations, the compositional pathways, as measured with atom-probe tomography, during early to later stage gamma'(L1(2))-precipitation (R = 0.45-10 nm), aged at 873 K, are discussed in light of a multi-component coarsening model. Employing nondilute thermodynamics, detailed model analyses during quasi-stationary coarsening of the experimental data establish that the gamma/gamma' interfacial free-energy is 22-23 + 7 mJ m(-2). Additionally, solute diffusivities are significantly slower than model estimates. Strong quantitative evidence indicates that an observed gamma'-supersaturation of Al results from the Gibbs-Thomson effect, providing the first experimental verification of this phenomenon. The Gibbs-Thomson relationship for a ternary system, as well as differences in measured phase equilibria with CALPHAD assessments, are considered in great detail. (c) 2006 Acta Materialia Inc. Published by Elsevier Ltd. All rights reserved. C1 Northwestern Univ, Dept Mat Sci & Engn, Evanston, IL 60208 USA. Argonne Natl Lab, Div Mat Sci, Argonne, IL 60439 USA. NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Seidman, DN (reprint author), Northwestern Univ, Dept Mat Sci & Engn, 2220 Campus Dr, Evanston, IL 60208 USA. EM d-seidman@northwestern.edu RI Seidman, David/B-6697-2009 NR 40 TC 43 Z9 45 U1 1 U2 7 PU PERGAMON-ELSEVIER SCIENCE LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD OX5 1GB, ENGLAND SN 1359-6454 J9 ACTA MATER JI Acta Mater. PD JAN PY 2007 VL 55 IS 1 BP 119 EP 130 DI 10.1016/j.actamat.2006.08.009 PG 12 WC Materials Science, Multidisciplinary; Metallurgy & Metallurgical Engineering SC Materials Science; Metallurgy & Metallurgical Engineering GA 118FV UT WOS:000242928700010 ER PT J AU Cohen, HS Bloomberg, JJ AF Cohen, Helen S. Bloomberg, Jacob J. TI Modified dynamic visual acuity tests after acoustic neuroma resection SO ACTA OTO-LARYNGOLOGICA LA English DT Article DE vestibular; seating; positioning; functional vision; compensatory gaze mechanisms ID OCULAR REFLEX AB Conclusion. These data suggest that visual acuity during quiet sitting is dynamic, requiring full body interaction of vestibulo-ocular and postural responses. These findings may have practical implications for seating design and design of tasks requiring good visual acuity while seated. Objectives. Looking at something during quiet sitting is usually assumed to be a static activity. We tested the idea that visual acuity during quiet sitting is dynamic, requiring integration of whole body responses as well as intact vestibulo-ocular reflexes. Materials and methods. Normal subjects and patients scheduled for acoustic neuroma resection were tested preoperatively. Patients were then tested during the four in-patient postoperative days. Testing was done while seated, with or without head and back support, while reading numbers from slides on a laptop computer at eye level, in font sizes from 20 pt to 12 pt. The dependent measure was percent correct per font size. Results. In both groups scores while sitting unsupported were significantly higher than with full support or only back support. In patients, scores were significantly decreased on postoperative day I and gradually increased toward normal but maintained the pattern of better scores when sitting unsupported than with head or back support. C1 Baylor Coll Med, Dept Otolaryngol Head & Neck Surg, Houston, TX 77030 USA. NASA, Johnson Space Ctr, Neurosci Lab, Houston, TX 77058 USA. RP Cohen, HS (reprint author), Baylor Coll Med, Dept Otolaryngol Head & Neck Surg, 1 Baylor Plaza, Houston, TX 77030 USA. EM hcohen@bcm.tmc.edu NR 10 TC 3 Z9 3 U1 0 U2 2 PU TAYLOR & FRANCIS AS PI OSLO PA PO BOX 12 POSTHUSET, NO-0051 OSLO, NORWAY SN 0001-6489 J9 ACTA OTO-LARYNGOL JI Acta Oto-Laryngol. PY 2007 VL 127 IS 8 BP 825 EP 828 DI 10.1080/00016480601002047 PG 4 WC Otorhinolaryngology SC Otorhinolaryngology GA 202CR UT WOS:000248880100007 PM 17762992 ER PT S AU Turner, TL Cabell, RH Canot, RJ Silcox, RJ AF Turner, Travis L. Cabell, Randolph H. Canot, Roberto J. Silcox, Richard J. BE Matsuzaki, Y Ahmadian, M Leo, DJ TI Development of a SMA hybrid composite jet engine chevron concept - art. no. 65250J SO Active and Passive Smart Structures and Integrated Systems 2007 SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Active and Passive Smart Structures and Integrated Systems CY MAR 19-22, 2007 CL San Diego, CA SP SPIE, Amer Soc Mech Engineers DE jet engine chevrons; active/adaptive chevrons; shape control; deflection control; jet noise control; flow effectors; flow control; shape memory alloys; Nitinol; embedded actuators ID FABRICATION AB Control of jet noise continues to be an important research topic. Exhaust-nozzle chevrons have been shown to reduce jet noise, but parametric effects are not well understood. Additionally, thrust loss due to chevrons at cruise suggests significant benefit from active chevrons. The focus of this study is development of an active chevron concept for the primary purpose of parametric studies for jet noise reduction in the laboratory and technology development to leverage for full scale systems. The active chevron concept employed in this work consists of a laminated composite structure with embedded shape memory alloy (SMA) actuators, termed a SMA hybrid composite (SMAHC). SMA actuators are embedded on one side of the bending axis of the structure such that thermal excitation generates a moment and deflects the structure. Two active chevron concepts are demonstrated; one that is powered to immerse and one that is powered to retract. A brief description of the chevron designs is followed by details of the fabrication approach. Results from bench-top tests are presented and correlated with predictions from a numerical model. Very repeatable performance is achieved with excellent agreement between predicted and measured results. Although the deflection requirement is not achieved in the presented results, the approach to meeting the performance requirement is evident. C1 NASA, Langley Res Ctr, Hampton, VA 23681 USA. RP Turner, TL (reprint author), NASA, Langley Res Ctr, Hampton, VA 23681 USA. NR 27 TC 1 Z9 1 U1 0 U2 3 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-0-8194-6646-4 J9 P SOC PHOTO-OPT INS PY 2007 VL 6525 BP J5250 EP J5250 AR 65250J DI 10.1117/12.716023 PG 12 WC Energy & Fuels; Engineering, Mechanical; Optics SC Energy & Fuels; Engineering; Optics GA BGK75 UT WOS:000248047400015 ER PT S AU Spuckler, CM AF Spuckler, Charles M. BE Zhu, D Schulz, U TI COMPARISON OF THE RADIATIVE TWO-FLUX AND DIFFUSION APPROXIMATIONS SO ADVANCED CERAMIC COATINGS AND INTERFACES SE Ceramic Engineering and Science Proceedings LA English DT Proceedings Paper CT 30th International Conference and Exposition on Advanced Ceramics and Composites CY JAN 22-27, 2006 CL Cocoa Beach, FL ID DISCRETE ORDINATES METHOD; HEAT-TRANSFER; REFRACTIVE-INDEX AB Approximate solutions are sometimes used to determine the heat transfer and temperatures in a semitransparent material in which conduction and thermal radiation are acting. A comparison of the Milne-Eddington two-flux approximation and the diffusion approximation for combined conduction and radiation heat transfer in a ceramic material was preformed to determine the accuracy of the diffusion solution. A plane gray semitransparent layer without a substrate and a non-gray semitransparent plane layer on an opaque substrate were considered. For the plane gray layer the material is semitransparent for all wavelengths and the scattering and absorption coefficients do not vary with wavelength. For the non-gray plane layer the material is semitransparent with constant absorption and scattering coefficients up to a specified wavelength. At higher wavelengths the non-gray plane layer is assumed to be opaque. The layers are heated on one side and cooled on the other by diffuse radiation and convection. The scattering and absorption coefficients were varied. The error in the diffusion approximation compared to the Milne-Eddington two flux approximation was obtained as a function of scattering coefficient and absorption coefficient. The percent difference in interface temperatures and heat flux through the layer obtained using the Milne-Eddington two-flux and diffusion approximations are presented as a function of scattering coefficient and absorption coefficient. The largest errors occur for high scattering and low absorption except for the back surface temperature of the plane gray layer where the error is also larger at low scattering and low absorption. It is shown that the accuracy of the diffusion approximation can he improved for some scattering and absorption conditions if a reflectance obtained from a Kubelka-Munk type two flux theory is used instead of a reflection obtained from the Fresnel equation. The Kubelka-Munk reflectance accounts for surface reflection and radiation scattered back by internal scattering sites while the Fresnel reflection only accounts for surface reflections. C1 NASA, Glenn Res Ctr, Cleveland, OH 44145 USA. RP Spuckler, CM (reprint author), NASA, Glenn Res Ctr, 21000 Brookpk Rd, Cleveland, OH 44145 USA. NR 13 TC 0 Z9 0 U1 0 U2 0 PU AMER CERAMIC SOC PI WESTERVILLE PA 735 CERAMIC PLACE, WESTERVILLE, OH 43081-8720 USA SN 0196-6219 BN 978-0-470-08053-5 J9 CERAM ENG SCI PROC PY 2007 VL 27 IS 3 BP 127 EP 137 PG 11 WC Materials Science, Ceramics; Materials Science, Coatings & Films SC Materials Science GA BRG37 UT WOS:000282671600012 ER PT S AU Sun, X Abshire, JB Krainak, MA Hasselbrack, WB AF Sun, Xiaoli Abshire, James B. Krainak, Michael A. Hasselbrack, William B. BE Becker, W TI Photon counting pseudorandom noise code laser altimeters - art. no. 67710O SO ADVANCED PHOTON COUNTING TECHNIQUES II SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Advanced Photon Counting Techniques II CY SEP 09-11, 2007 CL Boston, MA SP SPIE DE single photon counting; PN Code; laser ranging; lidar ID MODULATION CW LIDAR AB We have characterized the performance of photon counting pseudorandom noise (PN) code laser ranging system at both 1064 and 1570 mn. The PN code modulation(1,2) is a binary signal which is widely used in telecommunications and RF ranging applications. When used in lidar(3-10) PN code modulation allows the transmitter to operate with a peak power, equal to only twice the average power which is compatible with the optical fiber communication technology. Our photon counting receiver approach accumulates the received photon stream into a histogram, then cross correlates the histogram with the original PN code sequence. The time of flight is given by the location of the peak in the correlation function. For multiple targets within the laser beam footprint, each target produce a peak in the correlation function at the delay corresponding to the target range. Our approach for altimetry also uses receiver range bin much shorter than the PN code bit period. This permits the correlation to be calculated with higher time resolution than the PN code bit period and substantially improves the time and range resolution. Our laboratory measurements with a breadboard receiver shows a greater than 90% probability of detection in a 0.5 msec integration time with 50 fW average received optical power at 1064 mn when using an InGaAsP hybrid photomultiplier tube detector. We have also achieved a less than 5cm rms ranging precision, when using a 250 psec range bin and at about 100 KHz detected signal photon C1 [Sun, Xiaoli] NASA, Goddard Space Flight Ctr, Code 694,690,554, Greenbelt, MD 20771 USA. RP Sun, X (reprint author), NASA, Goddard Space Flight Ctr, Code 694,690,554, Greenbelt, MD 20771 USA. RI Sun, Xiaoli/B-5120-2013; Abshire, James/I-2800-2013 NR 12 TC 6 Z9 6 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 978-0-8194-6931-1 J9 P SOC PHOTO-OPT INS PY 2007 VL 6771 BP O7710 EP O7710 DI 10.1117/12.735453 PG 9 WC Biophysics; Remote Sensing; Optics SC Biophysics; Remote Sensing; Optics GA BHJ08 UT WOS:000253477700013 ER PT S AU Morgan, RM Wilkie, K Bao, X Sidick, E AF Morgan, Rhonda M. Wilkie, Keats Bao, Xiaoqi Sidick, Erkin BE Carreras, RA Gonglewski, JD Rhoadarmer, TA TI Actuator fault detection via electrical impedance testing SO ADVANCED WAVEFRONT CONTROL: METHODS, DEVICES, AND APPLICATIONS V SE PROCEEDINGS OF THE SOCIETY OF PHOTO-OPTICAL INSTRUMENTATION ENGINEERS (SPIE) LA English DT Proceedings Paper CT Conference on Advanced Wavefront Control: Methods, Devices, and Applications V CY AUG 29-30, 2007 CL San Diego, CA SP SPIE DE PMN actuators; deformable mirrors; adaptive optics; wavefront sensing and control ID MULTILAYER ELECTROSTRICTIVE ACTUATORS AB Lead magnesium niobate (PMN) actuators are electrostrictive actuators with high dynamic range used in deformable mirrors. Actuator fault detection in deformable mirrors typically occurs through optical testing. We developed a non-optical method for detecting actuator faults via low electric field resonance testing. The low electric field resonance method is standard practice for characterizing piezoelectric materials. The piezoelectric/electrostrictive coefficient couples the electrical and mechanical impedance of the actuator; a change in the mechanical boundaries (force) on the actuator results in a shift of the impedance resonances. We demonstrate experimentally that a PMN actuator can fracture but retain functionality under compression and that the fracture can be detected by measuring the impedance resonances at various bias voltages (various values of tension and compression). A concurrent optical test using a displacement interferometer was used to corroborate the results. We propose the impedance resonance approach as a non-optical fault detection test for in-situ actuators. C1 [Morgan, Rhonda M.; Wilkie, Keats; Bao, Xiaoqi; Sidick, Erkin] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Morgan, RM (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM Rhonda.Morgan@jpl.nasa.gov NR 9 TC 0 Z9 0 U1 0 U2 0 PU SPIE-INT SOC OPTICAL ENGINEERING PI BELLINGHAM PA 1000 20TH ST, PO BOX 10, BELLINGHAM, WA 98227-0010 USA SN 0277-786X BN 978-0-8194-6859-8 J9 P SOC PHOTO-OPT INS PY 2007 VL 6711 AR 67110A DI 10.1117/12.734935 PG 11 WC Optics SC Optics GA BHH05 UT WOS:000253180500009 ER PT B AU Edwards, W Miles, RF von Winterfeldt, D AF Edwards, Ward Miles, Ralph F., Jr. von Winterfeldt, Detlof BE Edwards, W Miles, RF VonWinterfeldt, D TI Advances in Decision Analysis FROM FOUNDATIONS TO APPLICATIONS Introduction SO ADVANCES IN DECISION ANALYSIS: FROM FOUNDATIONS TO APPLICATIONS LA English DT Editorial Material; Book Chapter ID DYNAMIC COHERENCE; PROSPECT-THEORY; RISK C1 [Edwards, Ward] Univ So Calif, Dept Psychol, Los Angeles, CA 90089 USA. [Miles, Ralph F., Jr.] CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. [von Winterfeldt, Detlof] Univ So Calif, Viterbi Sch Engn, Los Angeles, CA 90089 USA. NR 125 TC 3 Z9 3 U1 0 U2 0 PU CAMBRIDGE UNIV PRESS PI CAMBRIDGE PA THE PITT BUILDING, TRUMPINGTON ST, CAMBRIDGE CB2 1RP, CAMBS, ENGLAND BN 978-0-52186-368-1; 978-0-521-68230-5 PY 2007 BP 1 EP 12 DI 10.1017/CBO9780511611308.002 D2 10.1017/CBO9780511611308 PG 12 WC Psychology, Applied SC Psychology GA BXL31 UT WOS:000296286100002 ER PT B AU Miles, RF Von Winterfeldt, D AF Miles, Ralph F., Jr. Von Winterfeldt, Detlof BE Edwards, W Miles, RF VonWinterfeldt, D TI Advances in Decision Analysis FROM FOUNDATIONS TO APPLICATIONS Preface SO ADVANCES IN DECISION ANALYSIS: FROM FOUNDATIONS TO APPLICATIONS LA English DT Editorial Material; Book Chapter C1 [Miles, Ralph F., Jr.] CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. [Von Winterfeldt, Detlof] Univ So Calif, Viterbi Sch Engn, Los Angeles, CA 90089 USA. RP Miles, RF (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. NR 30 TC 0 Z9 0 U1 0 U2 0 PU CAMBRIDGE UNIV PRESS PI CAMBRIDGE PA THE PITT BUILDING, TRUMPINGTON ST, CAMBRIDGE CB2 1RP, CAMBS, ENGLAND BN 978-0-52186-368-1 PY 2007 BP XI EP XV D2 10.1017/CBO9780511611308 PG 5 WC Psychology, Applied SC Psychology GA BXL31 UT WOS:000296286100001 ER PT B AU Miles, RF AF Miles, Ralph F., Jr. BE Edwards, W Miles, RF VonWinterfeldt, D TI The Emergence of Decision Analysis SO ADVANCES IN DECISION ANALYSIS: FROM FOUNDATIONS TO APPLICATIONS LA English DT Article; Book Chapter ID CONJOINT-MEASUREMENT; UTILITY; FOUNDATIONS; UNCERTAINTY; RISK AB Decision analysis emerged as a discipline separate from decision theory or operations research following World War II. It could not have emerged earlier. It required a stable society with the appropriate philosophy and culture, and a sufficiently rich mathematical language to think logically about decision making. It required the understanding of subjective probability of Ramsey (1926) and de Finetti (1931, 1937), and the appropriate measure of preference under uncertainty of von Neumann and Morgenstern (1947) and later of Savage (1954). It formally came into being with the naming by Howard and his merger of decision theory and systems analysis (1966). C1 CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. RP Miles, RF (reprint author), CALTECH, Jet Prop Lab, Pasadena, CA 91125 USA. NR 148 TC 4 Z9 4 U1 1 U2 3 PU CAMBRIDGE UNIV PRESS PI CAMBRIDGE PA THE PITT BUILDING, TRUMPINGTON ST, CAMBRIDGE CB2 1RP, CAMBS, ENGLAND BN 978-0-52186-368-1; 978-0-521-68230-5 PY 2007 BP 13 EP 31 DI 10.1017/CBO9780511611308.003 D2 10.1017/CBO9780511611308 PG 19 WC Psychology, Applied SC Psychology GA BXL31 UT WOS:000296286100003 ER PT S AU Lary, DJ Koratkar, A AF Lary, David J. Koratkar, Anuradha BE Sammonds, PR Thompson, JMT TI Data Assimilation and Objectively Optimised Earth Observation SO ADVANCES IN EARTH SCIENCE: FROM EARTHQUAKES TO GLOBAL WARMING SE Royal Society Series on Advances in Science LA English DT Article; Book Chapter ID MARINE BOUNDARY-LAYER; HALOGEN OCCULTATION EXPERIMENT; METHANE OXIDATION; AEROSOL; VALIDATION; OZONE; UARS; PROGRAM; MODEL; HNO3 AB This chapter describes a vision for a future objectively optimised earth observation system with integrated scientific analysis. The system envisioned will dynamically adapt the what, where, and when of the observations made in an online fashion to maximise information content, minimise uncertainty in characterising the systems state vector, and minimise both the required storage and data, processing time for a, given observation capability. Higher level goals could also be specified such is the remote identification of sites of likely malaria outbreaks. By facilitating the early identification of potential breeding sites of major vector species before a disease outbreak occurs and identifying the locations for larvicide and insecticide applications. This would reduce costs, lessen the chance of developing pesticide resistance, and minimise the damage to the environment. Here we describe a prototype system applied to atmospheric chemistry with two relatively mature symbiotic components that seeks to achieve this goal. One component is the science goal monitor (SGM), the other is an Automatic code generation System for chemical modeling and assimilation (AutoChem) described online at www.AutoChem.info/. The Science Coal Monitor (SGM.) is a prototype software tool to determine the best strategies for implementing science goal driven automation in missions. The tools being developed in SGM improve the ability to monitor and react to the changing status of scientific events. The SGM system enables scientists to specify what to look for and how to react in descriptive rather than technical terms. The system monitors streams of science data to identify occurrences of key events previously specified by the scientist. When an event Occurs, the system autonomously coordinates the execution of the scientist's desired goals. The data assimilation system can feed multivariate objective measures to the SGM such as information content and system uncertainty so that SGM can schedule suitable observations given the observing system constraints. The observing system may of course be a sensor web suite of assets including orbital and suborbital platforms. Once the observations are made an integrated scientific analysis is performed which automatically produces a cross-linked web site for easy dissemination and to facilitate investigation of the scientific issues. A prototype is available at www.CDACentral.info/. C1 [Lary, David J.] NASA, Goddard Space Flight Ctr, Global Modelling & Assimilat Off, Greenbelt, MD USA. Univ Maryland Baltimore Cty, GEST, Baltimore, MD 21228 USA. [Lary, David J.] Tel Aviv Univ, Tel Aviv, Israel. RP Lary, DJ (reprint author), NASA, Goddard Space Flight Ctr, Global Modelling & Assimilat Off, Greenbelt, MD USA. EM David.Lary@umbc.edu NR 42 TC 0 Z9 0 U1 0 U2 0 PU IMPERIAL COLLEGE PRESS PI COVENT GARDEN PA 57 SHELTON STREET, COVENT GARDEN WC2H 9HE, ENGLAND SN 1793-1827 BN 978-1-86094-761-2 J9 ROY SOC SER ADV SCI PY 2007 VL 2 BP 293 EP 309 PG 17 WC Environmental Sciences; Meteorology & Atmospheric Sciences; Multidisciplinary Sciences SC Environmental Sciences & Ecology; Meteorology & Atmospheric Sciences; Science & Technology - Other Topics GA BKV87 UT WOS:000269438100014 ER PT B AU Achar, BNN Lorenz, CF Hartley, TT AF Achar, B. N. Narahari Lorenz, Carl F. Hartley, Tom T. BE Sabatier, J Agrawal, OP Machado, JAT TI The Caputo fractional derivative: Initialization issues relative to fractional differential equations SO ADVANCES IN FRACTIONAL CALCULUS: THEORETICAL DEVELOPMENTS AND APPLICATIONS IN PHYSICS AND ENGINEERING LA English DT Proceedings Paper CT 2nd Symposium on Fractional Derivatives and Their Applications (FDTAs CY SEP, 2005 CL Long Beach, CA SP ASME DETC DE Caputo fractional derivatives; initialization issues AB Recognizing the importance of proper initialization of a system, which is evolving in time according to a differential equation of fractional order, Lorenzo and Hartley developed the method of properly incorporating the effect of the past (history) by means of an initialization function for the Riemann-Liouville and the Grunwald formulations of fractional calculus. The present work addresses this issue for the Caputo fractional derivative and cautions that the commonly held belief that the Caputo formulation of fractional derivatives properly accounts for the initialization effects is not generally true when applied to the solution of fractional differential equations. C1 [Achar, B. N. Narahari] Univ Memphis, Memphis, TN 38152 USA. [Lorenz, Carl F.] NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. [Hartley, Tom T.] Univ Akron, Cleveland, OH 44135 USA. RP Achar, BNN (reprint author), Univ Memphis, Memphis, TN 38152 USA. EM nachar@memphis.edu RI Tenreiro Machado, J. A./M-2173-2013 OI Tenreiro Machado, J. A./0000-0003-4274-4879 NR 12 TC 6 Z9 6 U1 0 U2 3 PU SPRINGER PI DORDRECHT PA PO BOX 17, 3300 AA DORDRECHT, NETHERLANDS BN 978-1-4020-6041-0 PY 2007 BP 27 EP + DI 10.1007/978-1-4020-6042-7_3 PG 2 WC Mathematics, Applied; Mathematics SC Mathematics GA BGW64 UT WOS:000250957200003 ER PT B AU Adams, JL Hartley, TT Lorenz, CF AF Adams, Jay L. Hartley, Tom T. Lorenz, Carl F. BE Sabatier, J Agrawal, OP Machado, JAT TI Complex order-distributions using conjugated order differintegrals SO ADVANCES IN FRACTIONAL CALCULUS: THEORETICAL DEVELOPMENTS AND APPLICATIONS IN PHYSICS AND ENGINEERING LA English DT Proceedings Paper CT 2nd Symposium on Fractional Derivatives and Their Applications (FDTAs CY SEP, 2005 CL Long Beach, CA SP ASME DETC DE fractional-order systems; fractional calculus; conjugated-order differintegrals; complex order-distributions; complex-order differintegrals AB This paper develops the concept of the complex order-distribution. This is a continuum of fractional differintegrals of complex order. Two types of complex order-distributions are considered, uniformly distributed and Gaussian distributed. It is shown that these basis distributions can be summed to approximate other complex order-distributions. Conjugated differintegrals, introduced in this paper, are an essential analytical tool applied in this development. Conjugated-order differintegrals are fractional derivatives whose orders are complex conjugates. These conjugate-order differintegrals allow the use of complex-order differintegrals while still resulting in real time-responses and real transfer-functions. An example is presented to demonstrate the complex order-distribution concept. This work enables the generalization of fractional system identification to allow the search for complex order-derivatives that may better describe realtime behaviors. C1 [Adams, Jay L.; Hartley, Tom T.] Univ Akron, Dept Elect & Comp Engn, Akron, OH 44325 USA. [Hartley, Tom T.] NASA, Glenn Res Ctr, Cleveland, OH 44135 USA. RP Adams, JL (reprint author), Univ Akron, Dept Elect & Comp Engn, Akron, OH 44325 USA. EM JLA36@uakron.edu; TomHartley@aol.com; Carl.F.Lorenzo@grc.nasa.gov RI Tenreiro Machado, J. A./M-2173-2013 OI Tenreiro Machado, J. A./0000-0003-4274-4879 FU NASA FX The authors gratefully acknowledge the support of the NASA Glenn Research Center. NR 9 TC 2 Z9 2 U1 0 U2 1 PU SPRINGER PI DORDRECHT PA PO BOX 17, 3300 AA DORDRECHT, NETHERLANDS BN 978-1-4020-6041-0 PY 2007 BP 347 EP + DI 10.1007/978-1-4020-6042-7_24 PG 2 WC Mathematics, Applied; Mathematics SC Mathematics GA BGW64 UT WOS:000250957200024 ER PT J AU Ipatov, SI A'Hearn, MF Klaasen, KP AF Ipatov, S. I. A'Hearn, M. F. Klaasen, K. P. TI Automatic removal of cosmic ray signatures in Deep Impact images SO ADVANCES IN SPACE RESEARCH LA English DT Article DE cosmic rays; visual and infrared images; Deep Impact mission AB The results of recognition of cosmic ray (CR) signatures on single images made during the Deep Impact mission were analyzed for several codes written by several authors. For automatic removal of CR signatures on many images, we suggest using the code imgclean (http://pdssbn.astro.umd.edu/volume/didoc_0001/document/calibration_software/dical_v5/) written by E. Deutsch as other codes considered do not work properly automatically with a large number of images and do not run to completion for some images; however, other codes can be better for analysis of certain specific images. Sometimes imgclean detects false CR signatures near the edge of a comet nucleus, and it often does not recognize all pixels of long CR signatures. Our code rmcr is the only code among those considered that allows one to work with raw images. For most visual images made during low solar activity at exposure time t > 4 s, the number of clusters of bright pixels on an image per second per sq. cm of CCD was about 2-4, both for dark and normal sky images. At high solar activity, it sometimes exceeded 10. The ratio of the number of CR signatures consisting of n pixels obtained at high solar activity to that at low solar activity was greater for greater n. The number of clusters detected as CR signatures on a single infrared image is by at least a factor of several greater than the actual number of CR signatures; the number of clusters based on analysis of two successive dark infrared frames is in agreement with an expected number of CR signatures. Some glitches of false CR signatures include bright pixels repeatedly present on different infrared images. Our interactive code imr allows a user to choose the regions on a considered image where glitches detected by imgclean as CR signatures are ignored. In other regions chosen by the user, the brightness of some pixels is replaced by the local median brightness if the brightness of these pixels is greater by some factor than the median brightness. The interactive code allows one to delete long CR signatures and prevents removal of false CR signatures near the edge of the nucleus of the comet. The interactive code can be applied to editing any digital images. Results obtained can be used for other missions to comets. (C) 2007 COSPAR. Published by Elsevier Ltd. All rights reserved. C1 [Ipatov, S. I.; A'Hearn, M. F.] Univ Maryland, College Pk, MD 20742 USA. [Klaasen, K. P.] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. RP Ipatov, SI (reprint author), Carnegie Inst Washington, Dept Terr Magnetism, 5241 Broad Branch Rd, Washington, DC 20015 USA. EM siipatov@hotmail.com RI Ipatov, Sergei/O-2302-2014 OI Ipatov, Sergei/0000-0002-1413-9180 NR 6 TC 5 Z9 5 U1 0 U2 2 PU ELSEVIER SCI LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD OX5 1GB, OXON, ENGLAND SN 0273-1177 J9 ADV SPACE RES JI Adv. Space Res. PY 2007 VL 40 IS 2 BP 160 EP 172 DI 10.1016/j.asr.2007.04.012 PG 13 WC Astronomy & Astrophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Astronomy & Astrophysics; Geology; Meteorology & Atmospheric Sciences GA 268OO UT WOS:000253589300002 ER PT J AU Mukai, T Abe, S Hirata, N Nakamura, R Barnouin-Jha, OS Cheng, AF Mizuno, T Hiraoka, K Honda, T Demura, H Gaskell, RM Hashimoto, T Kubota, T Matsuoka, M Scheeres, DJ Yoshikawa, M AF Mukai, T. Abe, S. Hirata, N. Nakamura, R. Barnouin-Jha, O. S. Cheng, A. F. Mizuno, T. Hiraoka, K. Honda, T. Demura, H. Gaskell, R. M. Hashimoto, T. Kubota, T. Matsuoka, M. Scheeres, D. J. Yoshikawa, M. TI An overview of the LIDAR observations of asteroid 25143 Itokawa SO ADVANCES IN SPACE RESEARCH LA English DT Article DE asteroids; Itokawa; LIDAR; mass; density ID HAYABUSA; 25143-ITOKAWA; SPACECRAFT; SHAPE; MASS AB We present an overview of the laser altimeter(LIDAR) results for asteroid 25143 Itokawa. The trace of a 7 x 12-m elliptical beam spot made it possible to determine the local surface topography with an accuracy of a few meters in altitude, from a home position roughly 7 km above the surface. Sequential detection of the altitude of the spacecraft during two orbital spans of descent for sampling allowed determination of the asteroid mass as 3.58 x 10(10) kg +/- 5% and 3.54 x 10(10) kg +/- 6%, which are consistent with the most probable mass estimate of 3.51 x 10(10) kg +/- 3% given by Fujiwara et al. [Fujiwara, A., Kawaguchi, J., Yeomans, D.K. et al., 2006. The rubble-pile asteroid Itokawa as observed by Hayabusa. Science 312, 1330-1334]. Together with the total volume of the asteroid deduced from a shape model (i.e., 1.84 x 10(7) m(3) +/- 3%), this estimate by LIDAR suggests that asteroid Itokawa has a low density of 1.9 g/cm(3) +/- 9% and a high bulk porosity of about 40%. (C) 2007 COSPAR. Published by Elsevier Ltd. All rights reserved. C1 [Mukai, T.; Abe, S.; Hiraoka, K.; Honda, T.] Kobe Univ, Grad Sch Sci & Technol, Kobe, Hyogo 6578501, Japan. [Nakamura, R.] Natl Inst Adv Ind Sci & Technol, Tsukuba, Ibaraki 3058568, Japan. [Barnouin-Jha, O. S.; Cheng, A. F.] Johns Hopkins Univ, Appl Phys Lab, Laurel, MD 20723 USA. [Mizuno, T.; Hashimoto, T.; Kubota, T.; Yoshikawa, M.] Japan Aerosp Explorat Agcy, Inst Space & Astronaut Sci, Kanagawa 2298510, Japan. [Hirata, N.; Demura, H.] Univ Aizu, Dept Comp Software, Fukushima 9658580, Japan. [Gaskell, R. M.] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. [Matsuoka, M.] NEC Aerosp Syst, Kanagawa 2240053, Japan. [Scheeres, D. J.] Univ Michigan, Dept Aerosp Engn, Ann Arbor, MI 48109 USA. RP Mukai, T (reprint author), Kobe Univ, Grad Sch Sci & Technol, Kobe, Hyogo 6578501, Japan. EM mukai@kobe-u.ac.jp RI Barnouin, Olivier/I-7475-2015 OI Barnouin, Olivier/0000-0002-3578-7750 NR 10 TC 8 Z9 8 U1 0 U2 0 PU ELSEVIER SCI LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD OX5 1GB, OXON, ENGLAND SN 0273-1177 J9 ADV SPACE RES JI Adv. Space Res. PY 2007 VL 40 IS 2 BP 187 EP 192 DI 10.1016/j.asr.2007.04.075 PG 6 WC Astronomy & Astrophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Astronomy & Astrophysics; Geology; Meteorology & Atmospheric Sciences GA 268OO UT WOS:000253589300005 ER PT J AU Russell, CT Barucci, MA Binzel, RP Capria, MT Christensen, U Coradini, A De Sanctis, MC Feldman, WC Jaumann, R Keller, HU Konopliv, AS McCord, TB McFadden, LA McKeegan, KD McSween, HY Mottola, S Nathues, A Neukum, G Pieters, CM Prettyman, TH Raymond, CA Sierks, H Smith, DE Spohn, T Sykes, MV Vilas, F Zuber, MT AF Russell, C. T. Barucci, M. A. Binzel, R. P. Capria, M. T. Christensen, U. Coradini, A. De Sanctis, M. C. Feldman, W. C. Jaumann, R. Keller, H. U. Konopliv, A. S. McCord, T. B. McFadden, L. A. McKeegan, K. D. McSween, H. Y. Mottola, S. Nathues, A. Neukum, G. Pieters, C. M. Prettyman, T. H. Raymond, C. A. Sierks, H. Smith, D. E. Spohn, T. Sykes, M. V. Vilas, F. Zuber, M. T. TI Exploring the asteroid belt with ion propulsion: Dawn mission history, status and plans SO ADVANCES IN SPACE RESEARCH LA English DT Article DE asteroids; Vesta; Ceres; hygeia; ion propulsion ID CERES AB In this report, we describe the journey Dawn has taken in the recent past, its present status, and its future mission. The overall objective of Dawn is to explore backward in time via its observations of the primitive bodies, Vesta and Ceres. Thus Dawn embarks on three journeys. The first is its tumultuous temporal terrestrial trek during development. The second is its soon-to-be voyage in space to 4 Vesta, the second most massive asteroid in the main belt, and to 1 Ceres, the most massive. The third is its journey backward in time to infer the conditions as the solar system was formed. Finally, we discuss how it is possible to go back even further in time, beyond the,horizon of the Dawn mission to obtain "pre Dawn" observations at 10 Hygiea, the fourth most massive asteroid, and one more primitive than Vesta and Ceres. (C) 2007 COSPAR. Published by Elsevier Ltd. All rights reserved. C1 [Russell, C. T.; McKeegan, K. D.] Univ Calif Los Angeles, JGPP, Los Angeles, CA 90095 USA. [Barucci, M. A.] Observ Paris, LESIA, Meudon, France. [Binzel, R. P.; Zuber, M. T.] Dept Earth Atmospher & Planetary Sci, Cambridge, MA 02139 USA. [Capria, M. T.; Coradini, A.; De Sanctis, M. C.] Area Ric Tor Vergata, IASF, I-00133 Rome, Italy. [Christensen, U.; Keller, H. U.; Nathues, A.; Sierks, H.] Max Planck Inst Solar Syst Res, D-37191 Katlenburg Lindau, Germany. [Feldman, W. C.; Sykes, M. V.] Plantary Sci Inst, Tucson, AZ 85719 USA. [Jaumann, R.; Mottola, S.] ISSS, DLR, German Aerosp Ctr, D-12489 Berlin, Germany. [Konopliv, A. S.; Raymond, C. A.] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. [McCord, T. B.] Space Sci Inst, Winthrop, WA USA. [McFadden, L. A.] Univ Maryland, Dept Astron, College Pk, MD 20742 USA. [McSween, H. Y.] Univ Tennessee, DEPS, Knoxville, TN 37996 USA. [Neukum, G.] Free Univ Berlin, IGGG, D-12249 Berlin, Germany. [Pieters, C. M.] Brown Univ, Dept Geol Sci, Providence, RI 02912 USA. [Prettyman, T. H.] LANL, MS D466, Los Alamos, NM 87545 USA. [Smith, D. E.] NASA, Goddard Space Flight Ctr, Greenbelt, MD 20771 USA. [Vilas, F.] MMT Observ, Tucson, AZ 85719 USA. RP Russell, CT (reprint author), Univ Calif Los Angeles, JGPP, Los Angeles, CA 90095 USA. EM ctrussel@igpp.ucla.edu RI McKeegan, Kevin/A-4107-2008; McFadden, Lucy-Ann/I-4902-2013; De Sanctis, Maria Cristina/G-5232-2013; UCLA, SIMS/A-1459-2011 OI McKeegan, Kevin/0000-0002-1827-729X; capria, maria teresa/0000-0002-9814-9588; Prettyman, Thomas/0000-0003-0072-2831; Russell, Christopher/0000-0003-1639-8298; McFadden, Lucy-Ann/0000-0002-0537-9975; De Sanctis, Maria Cristina/0000-0002-3463-4437; NR 14 TC 17 Z9 17 U1 1 U2 4 PU ELSEVIER SCI LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD OX5 1GB, OXON, ENGLAND SN 0273-1177 J9 ADV SPACE RES JI Adv. Space Res. PY 2007 VL 40 IS 2 BP 193 EP 201 DI 10.1016/j.asr.2007.05.083 PG 9 WC Astronomy & Astrophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Astronomy & Astrophysics; Geology; Meteorology & Atmospheric Sciences GA 268OO UT WOS:000253589300006 ER PT J AU Jun, I Swiram, RT Rumaikin, A Feyninan, J Tylka, AJ Dietrich, WF AF Jun, I. Swiram, R. T. Rumaikin, A. Feyninan, J. Tylka, A. J. Dietrich, W. F. TI Statistics of solar energetic particle events: Fluences, durations, and time intervals SO ADVANCES IN SPACE RESEARCH LA English DT Article DE solar energetic particle event; JPL solar proton model; solar Probe ID PROBABILITY MODEL; PROTON AB The high-energy solar proton data obtained from instruments onboard the IMP-8 spacecraft are used to investigate statistical distributions of event fluences, event durations, and time intervals between adjacent events. The results show that: (1) the event fluences can be approximately fit to a log-normal distribution and (2) the distributions of event durations and time intervals between the events can be represented by Poisson distributions. A virtual data set was generated using these distributions to extend the Solar Probe method [Feynman, J., Tylka, A.J., Reames, D.B., Gabriel, S.B. Near-sun energetic particle environment of Solar Probe-Phasel final report, JPL Report, 2000] of obtaining the mission-integrated fluences to longer missions. By using the virtual data set generated in this study, we are able to obtain the smooth distribution of mission fluences for missions of any duration, which is not possible when only the available data sets was used. (C) 2007 Published by Elsevier Ltd on behalf of COSPAR. C1 [Jun, I.; Rumaikin, A.; Feyninan, J.] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. [Swiram, R. T.] SRS Technol, Montrose, CA 91020 USA. [Tylka, A. J.; Dietrich, W. F.] USN, Res Lab, EO Hulburt Ctr Space Res, Washington, DC 20375 USA. RP Jun, I (reprint author), CALTECH, Jet Prop Lab, 4800 Oak Grove Dr, Pasadena, CA 91109 USA. EM insoojun@jpl.nasa.gov RI Tylka, Allan/G-9592-2014 NR 10 TC 10 Z9 10 U1 0 U2 0 PU ELSEVIER SCI LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD OX5 1GB, OXON, ENGLAND SN 0273-1177 J9 ADV SPACE RES JI Adv. Space Res. PY 2007 VL 40 IS 3 BP 304 EP 312 DI 10.1016/j.asr.2006.12.019 PG 9 WC Astronomy & Astrophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Astronomy & Astrophysics; Geology; Meteorology & Atmospheric Sciences GA 268OP UT WOS:000253589400003 ER PT J AU Adams, JH Bhattacharya, M Lin, ZW Pendleton, G Watts, JW AF Adams, J. H. Bhattacharya, M. Lin, Z. W. Pendleton, G. Watts, J. W. TI The ionizing radiation environment on the moon SO ADVANCES IN SPACE RESEARCH LA English DT Article DE lunar albedo neutrons; radiation environment on the moon ID DOSE CONVERSION COEFFICIENTS; MAN ANATOMICAL MODEL; MONOENERGETIC NEUTRONS; LUNAR PROSPECTOR; SPECTRA; HELIUM AB The ionizing radiation environment on the moon that contributes to the radiation hazard for astronauts consists of galactic cosmic rays, solar energetic particles and albedo particles (mainly neutrons), from the lunar surface. We present calculations of the effective dose rate due to lunar albedo neutrons. These calculations are based on GEANT4 Monte Carlo simulations of albedo neutron production on the moon. We compare our results with the Lunar Prospector (LP) fast neutron data. We also compare the effective dose rate from lunar albedo neutrons to that from galactic cosmic rays and solar energetic particles. (C) 2007 COSPAR. Published by Elsevier Ltd. All rights reserved. C1 [Bhattacharya, M.; Lin, Z. W.] Univ Alabama, Natl Space Sci & Technol Ctr, Huntsville, AL 35805 USA. [Adams, J. H.; Watts, J. W.] NASA, George C Marshall Space Flight Ctr, Huntsville, AL 35805 USA. [Pendleton, G.] Dynetics Inc, Huntsville, AL 35806 USA. RP Bhattacharya, M (reprint author), Assoc Univ Inc, Brookhaven Natl Lab, Natl Nucl Data Ctr, Bldg 197D, Upton, NY 11973 USA. EM mbhattac@bnl.gov NR 12 TC 16 Z9 17 U1 1 U2 3 PU ELSEVIER SCI LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD OX5 1GB, OXON, ENGLAND SN 0273-1177 J9 ADV SPACE RES JI Adv. Space Res. PY 2007 VL 40 IS 3 BP 338 EP 341 DI 10.1016/j.asr.2007.05.032 PG 4 WC Astronomy & Astrophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Astronomy & Astrophysics; Geology; Meteorology & Atmospheric Sciences GA 268OP UT WOS:000253589400008 ER PT J AU Donovan, E Trondsen, T Spann, J Liu, W Spanswick, E Lester, M Tu, CY Ridley, A Henderson, M Immel, T Mende, S Bonnell, J Syrjaesuo, M Sofko, G Cogger, L Murphree, J Jayachandran, PT Pulkkinen, T Rankin, R Sigwarth, J AF Donovan, E. Trondsen, T. Spann, J. Liu, W. Spanswick, E. Lester, M. Tu, C. -Y. Ridley, A. Henderson, M. Immel, T. Mende, S. Bonnell, J. Syrjaesuo, M. Sofko, G. Cogger, L. Murphree, J. Jayachandran, P. T. Pulkkinen, T. Rankin, R. Sigwarth, J. TI Global auroral imaging in the ILWS era SO ADVANCES IN SPACE RESEARCH LA English DT Article DE global auroral imaging; geospace; ILWS; system level science ID NEUTRAL ATMOSPHERE; POLAR SPACECRAFT; EMISSIONS; FUV; CONVECTION; DEPENDENCE; RESOLUTION; SUPERDARN; ELECTRON; IMAGER AB The overarching objective of the ILWS Geospace program is to facilitate system level science. This demands synoptic observations such as global auroral imaging. At present, there is no funded mission during ILWS that. incorporates a global auroral imager. The imaging community needs to move now to address this important gap. While doing so, it is interesting to take stock of global auroral observations that have not been achieved, or that have been achieved only to a limited extent. These include simultaneous imaging across all relevant scales, spectral resolution of sufficient quality to allow for global maps of characteristic energy and energy flux of precipitating electrons, continuous global auroral imaging for time periods spanning long-duration geomagnetic events, systematic interhemispheric conjugate observations, auroral observations magnetically conjugate to in situ measurements, and automatic classification of auroral images. These observations can be achieved within the next decade. If they are, then they will facilitate exciting new science. (C) 2007 Published by Elsevier Ltd on behalf of COSPAR. C1 [Donovan, E.; Trondsen, T.; Spanswick, E.; Syrjaesuo, M.; Cogger, L.; Murphree, J.] Univ Calgary, Dept Phys & Astron, Calgary, AB T2N 1N4, Canada. [Spann, J.] NASA, George C Marshall Space Flight Ctr, Space Sci Branch, Huntsville, AL 35812 USA. [Liu, W.] Canadian Space Agcy, Space Sci Program, St Hubert, PQ J3Y 8Y9, Canada. [Lester, M.] Univ Leicester, Dept Phys & Astron, Leicester LE1 7RH, Leics, England. [Tu, C. -Y.] Peking Univ, Dept Geophys, Beijing 100871, Peoples R China. [Ridley, A.] Univ Michigan, Ctr Space Environm Modeling, Ann Arbor, MI 48109 USA. [Henderson, M.] Los Alamos Natl Lab, Los Alamos, NM 87545 USA. [Immel, T.; Mende, S.; Bonnell, J.] Univ Calif Berkeley, Space Sci Lab, Berkeley, CA 94720 USA. [Sofko, G.] Univ Saskatchewan, Dept Phys & Engn Phys, Saskatoon, SK S7N 5E2, Canada. [Jayachandran, P. T.] Univ Western Ontario, Dept Phys & Astron, London, ON N6A 3K7, Canada. [Pulkkinen, T.] Finnish Meteorol Inst, FIN-00101 Helsinki, Finland. [Rankin, R.] Univ Alberta, Dept Phys, Edmonton, AB T6G 2J1, Canada. [Sigwarth, J.] Univ Alberta, Dept Phys, Edmonton, AB T6G 2J1, Canada. RP Donovan, E (reprint author), Univ Calgary, Dept Phys & Astron, Calgary, AB T2N 1N4, Canada. EM eric@phys.ucalgary.ca RI Ridley, Aaron/F-3943-2011; Pulkkinen, Tuija/D-8403-2012; Syrjasuo, Mikko/E-5088-2012; Trondsen, Trond/F-5751-2016; Henderson, Michael/A-3948-2011; OI Ridley, Aaron/0000-0001-6933-8534; Pulkkinen, Tuija/0000-0002-6317-381X; Trondsen, Trond/0000-0002-9538-1832; Henderson, Michael/0000-0003-4975-9029; Donovan, Eric/0000-0002-8557-4155 NR 36 TC 3 Z9 3 U1 0 U2 1 PU ELSEVIER SCI LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD OX5 1GB, OXON, ENGLAND SN 0273-1177 J9 ADV SPACE RES JI Adv. Space Res. PY 2007 VL 40 IS 3 BP 409 EP 418 DI 10.1016/j.asr.2006.09.028 PG 10 WC Astronomy & Astrophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Astronomy & Astrophysics; Geology; Meteorology & Atmospheric Sciences GA 268OP UT WOS:000253589400018 ER PT J AU George, K Durante, M Cucinotta, FA AF George, K. Durante, M. Cucinotta, F. A. TI Chromosome aberrations in astronauts SO ADVANCES IN SPACE RESEARCH LA English DT Article DE biodosimetry; High-LET; chromosome; FISH; space radiation ID RADIATION INTERACTION EXPERIMENT; BLOOD-LYMPHOCYTES; SPACE-FLIGHT; CANCER-RISKS; SHIELDING EFFECTIVENESS; HEAVY-IONS; IN-VIVO; SPACEFLIGHT; EXPOSURE; DAMAGE AB A review of currently available data on in vivo induced chromosome damage in the blood lymphocytes of astronauts proves that cytogenetic biodosimetry analyses on blood collected within, a week or two of return from space provides a reliable estimate of equivalent radiation dose and risk after protracted exposure to space radiation of a few months or more. Recent studies indicate that biodosimetry estimates from single spaceflights lie within the range expected from physical dosimetry and biophysical models, but very large uncertainties are associated with single individual measurements and the total sample population remains low. Retrospective doses may be more difficult to estimate because of the fairly rapid time-dependent loss of "stable" aberrations in blood lymphocytes. Also, biodosimetry estimates from individuals who participate in repeated missions, or very long (interplanetary) missions, may be complicated by an adaptive response to space radiation and/or changes in lymphocyte survival and repopulation. A discussion of published data is presented and specific issues related to space radiation biodosimetry protocols are discussed. (c) 2007 Published by Elsevier Ltd on behalf of COSPAR. C1 [George, K.] Wyle Labs, Houston, TX 77058 USA. [Durante, M.] Univ Naples Federico 2, Dept Phys, I-80126 Naples, Italy. [Cucinotta, F. A.] NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. RP George, K (reprint author), Wyle Labs, 1290 Hercules Dr, Houston, TX 77058 USA. EM Kerry.A.George@nasa.gov RI Durante, Marco/K-1315-2014; OI Durante, Marco/0000-0002-4615-553X NR 42 TC 3 Z9 4 U1 0 U2 7 PU ELSEVIER SCI LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD OX5 1GB, OXON, ENGLAND SN 0273-1177 J9 ADV SPACE RES JI Adv. Space Res. PY 2007 VL 40 IS 4 BP 483 EP 490 DI 10.1016/j.asr.2007.03.100 PG 8 WC Astronomy & Astrophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Astronomy & Astrophysics; Geology; Meteorology & Atmospheric Sciences GA 268OQ UT WOS:000253589500006 ER PT J AU Emami, K Hada, M Lacy, S Clement, J Rusek, A Cucinotta, FA Wu, H AF Emami, K. Hada, M. Lacy, S. Clement, J. Rusek, A. Cucinotta, F. A. Wu, H. TI Apoptosis and micronuclei induction in human epithelial cells exposed to energetic carbon ions in the Bragg peak region SO ADVANCES IN SPACE RESEARCH LA English DT Article DE space radiation; shielding; Bragg curve; apoptosis; micronuclei ID RELATIVE BIOLOGICAL EFFECTIVENESS; PROSTATE-CANCER; RADIATION; SPACE; RADIOTHERAPY; IRRADIATION; ENVIRONMENT; CURVE AB Space radiation is a complex mixture of charged particles from solar and galactic origins. Many of these high energy charged particles can penetrate current spacecraft shielding and produce secondary particles, creating significant health hazard. Therefore, understanding the biological effects of these particles along the particle traversal is critical in optimizing new shielding designs. Here, we studied DNA damage on monolayer culture of mammary epithelial cell line irradiated by 290 MeV/nucleon carbon ions. Frequencies of apoptosis and micronuclei (MN) induction were scored across the Bragg curve at entrance radiation doses of 0.5 and 2 Gy. The results for both doses show that the peak of apoptosis yield coincides with the physical Bragg peak. However, the peak location for the MN frequency appears to be dose dependent. We argue that the presence of a higher proportion of micronuclei prior to the Bragg peak at the higher radiation dose is the consequence of "overkill" at the physical Bragg peak location. Results of the carbon exposure were compared with the data for the same cell type exposed to gamma-rays. (c) 2007 Published by Elsevier Ltd on behalf of COSPAR. C1 [Emami, K.; Hada, M.; Cucinotta, F. A.] NASA, Lyndon B Johnson Space Ctr, Radiat Biophys Lab, Houston, TX 77058 USA. [Emami, K.] Wyle Lab, Houston, TX 77058 USA. [Hada, M.] Univ Space Res Assoc, Houston, TX 77058 USA. [Lacy, S.; Clement, J.] Texas So Univ, Dept Chem, Houston, TX 77004 USA. [Rusek, A.] Brookhaven Natl Lab, Upton, NY 11973 USA. RP Wu, H (reprint author), NASA, Lyndon B Johnson Space Ctr, Radiat Biophys Lab, Mail Code SK37, Houston, TX 77058 USA. EM honglu.wu-l@nasa.gov NR 19 TC 2 Z9 2 U1 0 U2 0 PU ELSEVIER SCI LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD OX5 1GB, OXON, ENGLAND SN 0273-1177 J9 ADV SPACE RES JI Adv. Space Res. PY 2007 VL 40 IS 4 BP 501 EP 505 DI 10.1016/j.asr.2007.04.101 PG 5 WC Astronomy & Astrophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Astronomy & Astrophysics; Geology; Meteorology & Atmospheric Sciences GA 268OQ UT WOS:000253589500008 ER PT J AU Leandro, LJ Szewczyk, NJ Benguria, A Herranz, R Lavan, D Medina, FJ Gasset, G van Loon, J Conley, CA Marco, R AF Leandro, L. J. Szewczyk, N. J. Benguria, A. Herranz, R. Lavan, D. Medina, F. J. Gasset, G. van Loon, J. Conley, C. A. Marco, R. TI Comparative analysis of Drosophila melanogaster and Caenorhabditis elegans gene expression experiments in the European Soyuz flights to the International Space Station SO ADVANCES IN SPACE RESEARCH LA English DT Article DE microarrays; gene expression patterns; microgravity; International Space Station; Drosophila melanogaster; Caenorhabditis elegans; European Soyuz missions; Spanish Cervantes mission; Dutch Delta mission AB The European Soyuz missions have been one of the main routes for conducting scientific experiments onboard the International Space Station, which is currently in the construction phase. A relatively large number of life and physical sciences experiments as well as technology demonstrations have been carried out during these missions. Included among these experiments are the Gene experiment during the Spanish "Cervantes" Soyuz mission and the ICE-1st experiment during the Dutch "Delta" mission. In both experiments, full genome microarray analyses were carried out on RNA extracted from whole animals recovered from the flight. These experiments indicated relatively large scale changes in gene expression levels in response to spaceflight for two popular model systems, Drosophila melanogaster (Gene) and Caenorabditis elegans (ICE-1st). Here we report a comparative analysis of results from these two experiments. Finding orthologous genes between the fruit fly and the nematode was far from straightforward, reducing the number of genes that we could compare to roughly 20% of the full comparative genome. Within this sub-set of the data (2286 genes), only six genes were found to display identical changes between species (decreased) while 1809 genes displayed no change in either species. Future experiments using ground simulation techniques will allow producing a better, more comprehensive picture of the putative set of genes affected in multicellular organisms by changes in gravity and getting a deeper understanding of how animals respond and adapt to spaceflight. (c) 2007 COSPAR. Published by Elsevier Ltd. All rights reserved. C1 [Leandro, L. J.; Herranz, R.; Marco, R.] UAM, CSIC, Dept Bioquim II Biomed Alberto Sols, Madrid, Spain. [Szewczyk, N. J.; Conley, C. A.] NASA, Ames Res Ctr, Moffett Field, CA 94035 USA. [Szewczyk, N. J.] Univ Pittsburgh, Dept Biol Sci, Pittsburgh, PA 15260 USA. [Benguria, A.] CSIC, Ctr Nacl Biotecnol, E-28041 Madrid, Spain. [Medina, F. J.] CSIC, Ctr Invest Biol, E-28040 Madrid, Spain. [Gasset, G.] Univ Toulouse 3, GSBMS, F-31062 Toulouse, France. [van Loon, J.] Vrije Univ Amsterdam, Dutch Expt Support Ctr, DESC OCB ACTA, Amsterdam, Netherlands. RP Marco, R (reprint author), UAM, CSIC, Dept Bioquim II Biomed Alberto Sols, Madrid, Spain. EM roberto.marco@uam.es RI van Loon, Jack/A-4250-2013; Herranz, Raul/A-6510-2010; Medina, F. Javier/M-2278-2014; OI Herranz, Raul/0000-0002-0246-9449; Medina, F. Javier/0000-0002-0866-7710; Szewczyk, Nathaniel/0000-0003-4425-9746 FU NIAMS NIH HHS [R01 AR054342-01A1] NR 11 TC 15 Z9 20 U1 0 U2 12 PU ELSEVIER SCI LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD OX5 1GB, OXON, ENGLAND SN 0273-1177 J9 ADV SPACE RES JI Adv. Space Res. PY 2007 VL 40 IS 4 BP 506 EP 512 DI 10.1016/j.asr.2007.05.070 PG 7 WC Astronomy & Astrophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Astronomy & Astrophysics; Geology; Meteorology & Atmospheric Sciences GA 268OQ UT WOS:000253589500009 PM 18084631 ER PT J AU Mancusi, D Beaucei, A Gialanella, G Grossi, G Manti, L Pugliese, M Rusek, A Scampoli, P Sihver, L Durante, M AF Mancusi, D. Beaucei, A. Gialanella, G. Grossi, G. Manti, L. Pugliese, M. Rusek, A. Scampoli, P. Sihver, L. Durante, M. TI Comparison of aluminum and lucite for shielding against 1 GeV protons SO ADVANCES IN SPACE RESEARCH LA English DT Article DE protons; shielding; chromosome aberrations; fragmentation ID ENERGY IRON IONS; PROTECTION AB Shielding is the only countermeasure currently available for exposure to cosmic radiation during space travel. We compared aluminum (Al) and polymethylmethacrylate (PMMA, or Incite) shields of 20 g/cm(2) thickness using 1 GeV protons accelerated at the NASA Space Radiation Laboratory. The dose rate increased after the shield, and the increase was more pronounced after the Al than the PMMA shield. No significant differences in the induction of chromosomal aberrations were observed in human lymphocytes exposed to the same dose with no shield or behind the Al and PMMA blocks. However, the biological effectiveness per incident proton was increased by the shields. Simulations using the General-Purpose Particle and Heavy-Ion Transport Code System (PHITS) show that the increase in dose is caused by target fragments, and aluminum produces more secondary protons than PMMA. Nevertheless, the spectrum of particles behind the shield is confined within the low-LET region, and the biological effectiveness is consequently similar. (c) 2007 COSPAR. Published by Elsevier Ltd. All rights reserved. C1 [Gialanella, G.; Grossi, G.; Manti, L.; Pugliese, M.; Scampoli, P.; Durante, M.] Univ Naples Federico 2, Dept Phys, Naples, Italy. [Gialanella, G.; Grossi, G.; Manti, L.; Pugliese, M.; Scampoli, P.; Durante, M.] Ist Nazl Fis Nucl, I-80125 Naples, Italy. [Mancusi, D.; Sihver, L.] Chalmers, S-41296 Gothenburg, Sweden. [Beaucei, A.] Univ Naples Federico 2, Dept Biol, Naples, Italy. [Rusek, A.] Brookhaven Natl Lab, NASA, Space Radiat Lab, Upton, NY 11973 USA. RP Durante, M (reprint author), Univ Naples Federico 2, Dept Phys, Naples, Italy. EM Marco.Durante@na.infn.it RI Durante, Marco/K-1315-2014; OI Mancusi, Davide/0000-0002-2518-8228; Durante, Marco/0000-0002-4615-553X NR 7 TC 6 Z9 6 U1 0 U2 1 PU ELSEVIER SCI LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD OX5 1GB, OXON, ENGLAND SN 0273-1177 J9 ADV SPACE RES JI Adv. Space Res. PY 2007 VL 40 IS 4 BP 581 EP 585 DI 10.1016/j.asr.2006.11.033 PG 5 WC Astronomy & Astrophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Astronomy & Astrophysics; Geology; Meteorology & Atmospheric Sciences GA 268OQ UT WOS:000253589500019 ER PT J AU Mahev, V Popov, D Jones, JA Casey, RC AF Mahev, Vladislav Popov, Draltri Jones, Jeffrey A. Casey, Rachael C. TI Mechanism of action for anti-radiation vaccine in reducing the biological impact of high-dose gamma irradiation SO ADVANCES IN SPACE RESEARCH LA English DT Article DE radiobiology; vaccine; acute radiation sickness; radiation countermeasures; immunotherapy ID ATOMIC-BOMB SURVIVORS; IONIZING-RADIATION; MAMMALIAN-CELLS; SPACE RADIATION; DNA-DAMAGE; CANCER; RADIOSENSITIVITY; MORTALITY; RISKS; PORE AB Ionizing radiation is a major health risk of long-term space travel, the biological consequences of which include genetic and oxidative damage. In this study, we propose an original mechanism by which high doses of ionizing radiation induce acute toxicity. We identified biological components that appear in the lymphatic vessels shortly after high-dose gamma irradiation. These radiation-induced toxins, which we have named specific radiation determinants (SRD), were generated in the irradiated tissues and then circulated throughout the body via the lymph circulation and bloodstream. Depending on the type of SRD elicited, different syndromes of acute radiation sickness (ARS) were expressed. The SRDs were developed into a vaccine used to confer active immunity against acute radiation toxicity in immunologically naive animals. Animals that were pretreated with SRDs exhibited resistance to lethal doses of gamma radiation, as measured by increased survival times and survival rates. In comparison, untreated animals that were exposed to similar large doses of gamma radiation developed acute radiation sickness and died within days. This phenomenon was observed in a number of mammalian species. Initial analysis of the biochemical characteristics indicated that the SRDs were large molecular weight (200-250 kDa) molecules that were comprised of a mixture of protein, lipid, carbohydrate, and mineral. Further analysis is required to further identify the SRD molecules and the biological mechanism by which they mediate the toxicity associated with acute radiation sickness. By doing so, we may develop an effective specific immunoprophylaxis as a countermeasure against the acute effects of ionizing radiation. (c) 2007 Published by Elsevier Ltd on behalf of COSPAR. C1 [Mahev, Vladislav] Russian Acad Sci, Vladicaucasian Sci Ctr, Vladicaucas 362008, N Ossetia Alani, Russia. [Popov, Draltri] Adv Med Technol & Syst, Richmond Hill, ON L4E 4W8, Canada. [Jones, Jeffrey A.] NASA, Lyndon B Johnson Space Ctr, Houston, TX 77058 USA. [Casey, Rachael C.] Univ Space Res Assoc, Houston, TX 77058 USA. RP Mahev, V (reprint author), Russian Acad Sci, Vladicaucasian Sci Ctr, 93 Pr Kosta Hetagyrova, Vladicaucas 362008, N Ossetia Alani, Russia. EM niobiot@mail.ru; dlpopov@fcibroad-band.com; jeffrey.ajones@nasa.gov; rachael.casev-l@nasa.gov NR 24 TC 3 Z9 5 U1 0 U2 2 PU ELSEVIER SCI LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD OX5 1GB, OXON, ENGLAND SN 0273-1177 J9 ADV SPACE RES JI Adv. Space Res. PY 2007 VL 40 IS 4 BP 586 EP 590 DI 10.1016/j.asr.2007.03.098 PG 5 WC Astronomy & Astrophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Astronomy & Astrophysics; Geology; Meteorology & Atmospheric Sciences GA 268OQ UT WOS:000253589500020 ER PT J AU Griffin, M Abergel, A Ade, P Andre, P Baluteau, JP Bock, J Franceschini, A Gear, W Glenn, J Griffin, D King, K Lellouch, E Madden, S Naylor, D Oliver, S Olofsson, G Page, M Perez-Fournon, I Rowan-Robinson, M Saraceno, P Sawyer, E Swinyard, B Vigroux, L Wright, G AF Griffin, Matthew Abergel, Alain Ade, Peter Andre, Philippe Baluteau, Jean-Paul Bock, James Franceschini, Alberto Gear, Walter Glenn, Jason Griffin, Douglas King, Ken Lellouch, Emmanuel Madden, Suzanne Naylor, David Oliver, Seb Olofsson, Goeran Page, Mat Perez-Fournon, Ismael Rowan-Robinson, Michael Saraceno, Paolo Sawyer, Eric Swinyard, Bruce Vigroux, Laurent Wright, Gillian CA Spire Consortium TI The Herschel-SPIRE instrument and its capabilities for extragalactic astronomy SO ADVANCES IN SPACE RESEARCH LA English DT Article DE Herschel; far-infrared; extragalactic surveys ID COUPLED BOLOMETER ARRAYS; STAR-FORMATION; DESIGN; PERFORMANCE; GALAXIES AB SPIRE, the Spectral and Photometric Imaging Receiver, is one of three instruments to fly on the European Space Agency's Herschel Space Observatory. It contains a three-band imaging photometer operating at 250, 350 and 500 mu m, and an imaging Fourier transform spectrometer covering 194-672 mu m. The SPIRE detectors are arrays of feedhorn-coupled bolometers cooled to 0.3 K. The photometer has a field of view of 4 x 8', observed simultaneously in the three spectral bands. The spectrometer has an approximately circular field of view with a diameter of 2.6' The spectral resolution can be adjusted between 0.04 and 2 cm(-1) (resolving power of 20-1000 at 250 mu m). SPIRE will be used for many galactic and extragalactic science programmes, a number of which will be implemented as Herschel Key Projects. The SPIRE consortium's Guaranteed Time (GT) programme will devote more than 1000 h to Key Projects covering the high-redshift universe and local galaxies, which will be carried out in coordination with other GT programmes, especially that of the PACs consortium. It is also expected that substantial amounts of Herschel Open Time will be used for further extragalactic investigations. The high-redshift part of the SPIRE GT programme will focus on blank-field surveys with a range of depths and areas optimised to sample the luminosity-red shift plane and characterize the bolometric luminosity density of the universe at high-redshift. Fields will be selected that are well covered by Spitzer, SCUBA-2, PACS-GT and near-IR surveys, to facilitate source identifications and enable detailed studies of the redshifts, spectral energy distributions, and other properties of detected galaxies. The local galaxies programme will include a detailed spectral and photometric study of a sample of well resolved nearby galaxies, a survey of more than 300 local galaxies designed to provide a statistical survey of dust in the nearby universe, and a study of the ISM in low-metallicity environments, bridging the gap between the local universe and primordial galaxies. (C) 2007 COSPAR. Published by Elsevier Ltd. All rights reserved. C1 [Griffin, Matthew; Ade, Peter; Gear, Walter] Cardiff Univ, Sch Phys & Astron, Cardiff CF24 3AA, Wales. [Abergel, Alain] Ctr Univ Orsay, Inst Astrophys Spatiale, F-91405 Orsay, France. [Andre, Philippe; Madden, Suzanne] CEA Saclay, Serv Astrophys, F-91191 Gif Sur Yvette, France. [Baluteau, Jean-Paul] Astrophys Lab, Marseille 12, France. [Bock, James] CALTECH, Jet Prop Lab, Pasadena, CA 91109 USA. [Franceschini, Alberto] Univ Padua, Dipartimento Astron, I-35122 Padua, Italy. [Glenn, Jason] Univ Colorado, Dept Astrophys & Planetary Sci, Boulder, CO 80309 USA. [Griffin, Douglas; King, Ken; Sawyer, Eric; Swinyard, Bruce] Rutherford Appleton Lab, Didcot OX11 0QX, Oxon, England. [Lellouch, Emmanuel] Observ Paris, F-92195 Meudon, France. [Naylor, David] Univ Lethbridge, Lethbridge, AB T1K 3M4, Canada. [Oliver, Seb] Univ Sussex, Dept Phys & Astron, Brighton BN1 9QH, E Sussex, England. [Olofsson, Goeran] Stockholm Observ, SE-10691 Stockholm, Sweden. [Page, Mat] UCL, Mullard Space Sci Lab, Dorking RH5 6NT, Surrey, England. [Perez-Fournon, Ismael] Inst Astrofis Canarias, E-38200 San Cristobal la Laguna, Spain. [Rowan-Robinson, Michael] Univ London Imperial Coll Sci Technol & Med, Blackett Lab, London SW7 2AZ, England. [Saraceno, Paolo] Ist Fis Spazio Interplanetario, I-00133 Rome, Italy. [Vigroux, Laurent] Inst Astrophys, F-75014 Paris, France. [Wright, Gillian] Royal Observ, UK Astron Technol Ctr, Edinburgh EH9 3HJ, Midlothian, Scotland. RP Griffin, M (reprint author), Cardiff Univ, Sch Phys & Astron, 5 Parade, Cardiff CF24 3AA, Wales. EM matt.griffin@astro.cf.ac.uk NR 21 TC 24 Z9 24 U1 0 U2 0 PU ELSEVIER SCI LTD PI OXFORD PA THE BOULEVARD, LANGFORD LANE, KIDLINGTON, OXFORD OX5 1GB, OXON, ENGLAND SN 0273-1177 J9 ADV SPACE RES JI Adv. Space Res. PY 2007 VL 40 IS 5 BP 612 EP 619 DI 10.1016/j.asr.2007.03.032 PG 8 WC Astronomy & Astrophysics; Geosciences, Multidisciplinary; Meteorology & Atmospheric Sciences SC Astronomy & Astrophysics; Geology; Meteorology & Atmospheric Sciences GA 268OR UT WOS:000253589600004 ER EF