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  • Other Sources  (22)
  • Spacecraft Design, Testing and Performance  (13)
  • Man/System Technology and Life Support  (5)
  • Crustal deformation (cf. Earthquake precursor: deformation or strain)  (4)
  • 2000-2004  (22)
Collection
  • Other Sources  (22)
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Keywords
Years
Year
  • 1
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    Continuous Global Positioning System measurements of postglacial adjustment in Fennoscandia: 2. Modeling results (2004)
    In:  J. Geophys. Res., Luxembourg, Conseil de l'Europe, vol. 109, no. B2, pp. 724-727, pp. B02412, (ISSN: 1340-4202)
    Details
    Publication Date: 2004
    Keywords: Crustal deformation (cf. Earthquake precursor: deformation or strain) ; uplift ; Geodesy ; Rheology ; Inelastic ; earth mantle ; Modelling ; JGR
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    BIBLIOGRAPHY SEISMOLOGY
  • 2
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    Kinematics of active deformation in the Sulaiman Lobe and Range, Pakistan (2000)
    In:  J. Geophys. Res., Paris, Pergamon, vol. 105, no. B6, pp. 13,253-13,279, pp. 1246
    Details
    Publication Date: 2000
    Keywords: Crustal deformation (cf. Earthquake precursor: deformation or strain) ; Plate tectonics ; India ; Fault plane solution, focal mechanism ; Waves ; form ; Inversion ; 7215 ; Seismology ; Earthquake ; parameters ; 7230 ; Seismicity ; and ; seismotectonics ; 8102 ; Tectonophysics ; Continental ; contractional ; orogenic ; belts ; 8107 ; Continental ; neotectonics ; JGR
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    BIBLIOGRAPHY SEISMOLOGY
  • 3
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    Vertical crustal motion observed in the BIFROST project (2003)
    In:  J. Geodynamics, Stuttgart, Ferdinand Enke Verlag, vol. 35, no. 4-5, pp. 425-441, pp. L07611, (ISSN: 1340-4202)
    Details
    Publication Date: 2003
    Keywords: Crustal deformation (cf. Earthquake precursor: deformation or strain) ; Scandinavia ; Sweden ; Dam ; JGD
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    BIBLIOGRAPHY SEISMOLOGY
  • 4
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    Comparison of geodetic and geologic data from the Wasatch region, Utah and implications for the spectral character of earth deformation at periods of 10 to 10 million years (2003)
    In:  J. Geophys. Res., Klagenfurt, Nuclear Technology Publ., vol. 108, no. B4, pp. ETG 7-1 to ETG 7-23, pp. 2199, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 2003
    Keywords: Fault zone ; Crustal deformation (cf. Earthquake precursor: deformation or strain) ; Geol. aspects ; JGR ; 1208 ; Geodesy ; and ; Gravity: ; Crustal ; movements--intraplate ; (8110) ; 1243 ; Space ; geodetic ; surveys ; 7209 ; Seismology: ; Earthquake ; dynamics ; and ; mechanics ; 8107 ; Tectonophysics: ; Continental ; neotectonics ; 8109 ; Continental ; tectonics--extensional ; (0905)
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    BIBLIOGRAPHY SEISMOLOGY
  • 5
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    Human and behavioral factors contributing to spine-based neurological cockpit injuries in pilots of high-performance aircraft: recommendations for management and prevention (2000)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: In high-performance aircraft, the need for total environmental awareness coupled with high-g loading (often with abrupt onset) creates a predilection for cervical spine injury while the pilot is performing routine movements within the cockpit. In this study, the prevalence and severity of cervical spine injury are assessed via a modified cross-sectional survey of pilots of multiple aircraft types (T-38 and F-14, F-16, and F/A-18 fighters). Ninety-five surveys were administered, with 58 full responses. Fifty percent of all pilots reported in-flight or immediate post-flight spine-based pain, and 90% of fighter pilots reported at least one event, most commonly (〉 90%) occurring during high-g (〉 5 g) turns of the aircraft with the head deviated from the anatomical neutral position. Pre-flight stretching was not associated with a statistically significant reduction in neck pain episodes in this evaluation, whereas a regular weight training program in the F/A-18 group approached a significant reduction (mean = 2.492; p 〈 0.064). Different cockpit ergonomics may vary the predisposition to cervical injury from airframe to airframe. Several strategies for prevention are possible from both an aircraft design and a preventive medicine standpoint. Countermeasure strategies against spine injury in pilots of high-performance aircraft require additional research, so that future aircraft will not be limited by the human in control.
    Keywords: Man/System Technology and Life Support
    Type: Military medicine (ISSN 0026-4075); Volume 165; 1; 6-12
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Representation of the Geosynchronous Plasma Environment for Spacecraft Charging Calculations (2004)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: Historically, our ability to predict and postdict surface charging has suffered from both a lack of reliable secondary emission and backscattered electron yields and poor characterization of the plasma environment. One difficulty lies in the common practice of fitting the plasma data to a Maxwellian or Double Maxwellian distribution function, which may not represent the data well for charging purposes. For 13 years Los Alamos National Laboratory (LANL) has been accumulating measurements of electron and proton spectra from Magnetospheric Plasma Analyzer (MPA) instruments aboard a series of geosynchronous satellites. These data provide both a plasma characterization and the potential of the instrument ground. We use electron and ion flux spectra measured by the LANL MPA to examine how the use of different spectral representations of the charged particle environment in computations of spacecraft potentials during magnetospheric substorms affects the accuracy of the results. We calculate the spacecraft potential using both the measured fluxes and several different fits to these fluxes. These flux measurements and fits have been corrected for the difference between the measured and calculated potential. The potentials computed using the measured fluxes, the best available material properties of graphite carbon, and a secondary electron escape fraction of 81%, are within a factor of three of the measured potential for nearly all the data. Using a Kappa fit to the electron distribution function and a Maxwellian fit to the ion distribution function gives agreement similar to the calculations using the actual data. Alternative spectral representations, including Maxwellian and double Maxwellian for both species, lead to less satisfactory agreement between predicted and measured potentials.
    Keywords: Spacecraft Design, Testing and Performance
    Type: 8th Spacecraft Charging Technology Conference; NASA/CP-2004-213091
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    NASCAP-2K: An Overview (2004)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: Nascap-2k is the modern replacement for the older 3-D charging codes NASCAP/GEO, NASCAP/LEO, POLAR, and DynaPAC. Built on the DynaPAC kernel and incorporating surface charging, environment and space potential models from the older codes, Nascap-2k performs charging calculations for a wide variety of space environments under control of a unified graphical interface. In this paper we illustrate the use of Nascap-2k for spacecraft charging calculations. We touch on some of the unique physical and mathematical models on which the code is based. Examples/demos include the use of Object Toolkit, charging calculations in geosynchronous substorm, solar wind, low earth orbit, and auroral environments, and display and analysis of surface potentials, space potentials and particle trajectories.
    Keywords: Spacecraft Design, Testing and Performance
    Type: 8th Spacecraft Charging Technology Conference; NASA/CP-2004-213091
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Comparison of the NASCAP/GEO, POLAR, SEE Charging Handbook, and NASCAP-2K.1 Spacecraft Charging Codes (2001)
    In:  Other Sources
    Details
    Publication Date: 2019-07-17
    Description: The NASA Charging Analyzer Program (NASCAP) spacecraft charging software developed by Maxwell Technologies has been widely used for the past fifteen to twenty years in satellite design and investigation of spacecraft charging related anomalies. Individual versions of the NASCAP software are available for use in low inclination, low Earth orbit environments (NASCAP[LEO) and geostationary orbit environments (NASCAP/GEO). In addition, the Potentials of Large objects in the Auroral Region (POLAR) code is available for use in LEO polar orbit environments. NASCAP/GEO and POLAR were both written in the 1980's using algorithms appropriate for the computers of the time. They solve the Poisson-Vlasov system for currents and densities assuming limited speed and memory of computer systems standard for the day. In addition, use of the charging models requires individual input files that are not readily transported into the various codes to facilitate comparison of results by the user.
    Keywords: Spacecraft Design, Testing and Performance
    Type: 7th Spacecraft Charging Technology Conference; Apr 23, 2001 - Apr 27, 2001; Noordwijk; Netherlands
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    The Microwave Anisotropy Probe (MAP): Guidance, Navigation, and Control Hardware Suite (2002)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Microwave Anisotropy Probe (MAP) was launched June 30, 2001 to create an all-sky map of the Cosmic Microwave Background. The mission's hardware suite included two Lockheed Martin AST-201 star trackers, two Kearfott Two-Axis Rate Assemblies (TARAs) mounted to provide X, Y and redundant Z-axis rates, two Adcole Digital Sun Sensor (DSS) heads sharing one set of electronics, twelve Adcole Coarse Sun Sensor (CSS) eyes, three Ithaco E-sized Reaction Wheel Assemblies (RWAs), and a Propulsion Subsystem that employed eight PRIMEX Rocket Engine Modules (REMs). This hardware has allowed MAP to meet its various Orbit and Attitude Control Requirements, including performing a complex zero-momentum scan, meeting its attitude determination requirements, and maintaining a trajectory that places MAP in a lissajous orbit around the second Sun-Earth Lagrange point (L2) via phasing loops and a lunar gravity assist. Details of MAP's attitude determination, attitude control, and trajectory design are presented separately. This paper will focus on the performance of the hardware components mentioned above, as well as the significant lessons learned through the use of these components. An emphasis will be placed on spacecraft design modifications that were needed to accommodate existing hardware designs into the MAP Observatory design.
    Keywords: Spacecraft Design, Testing and Performance
    Type: AIAA Guidance and Control Conference; Aug 01, 2002; Monterey, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Tool for Bending a Metal Tube Precisely in a Confined Space (2003)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: A relatively simple, manually operated tool enables precise bending (typically, within 1/2 of the specified bend angle) of a metal tube located in a confined space, with a minimum of flattening of the tube and without significant gouging of the tube surface. The tool is designed for use in a situation in which the tube cannot be removed from the confined space for placement in a conventional benchmounted tube bender. The tool is also designed for use in a situation in which previously available hand-held tube benders do not afford the required precision, do not support the tube wall sufficiently to prevent flattening or gouging, and/or do not fit within the confined space. The tool is designed and fabricated for the specific outer diameter and bend radius of the tube to be bent. The tool (see figure) includes a clamping/radius block and a top clamping block that contain mating straight channels of semicircular cross section that fit snugly around the tube. The mating portions of the clamping/radius block and the top clamping block are clamped around a length of the tube that is adjacent to the bend and that is intended to remain straight. The clamping/radius block is so named because beyond the straight clamping section, its semicircular channel extends to a non-clamping section that is curved at the specified bend radius. A pivot hole is located in the clamping/radius block at the center of the bend circle. The tool includes a bending block that, like the other blocks, contains a straight semicircular channel that fits around the outside of the tube. The bending block contains a pivot hole to be aligned with the pivot hole in the clamping/radius block. Once the tube has been clamped between the clamping/ radius and top clamping blocks, the bending block is placed around the tube, the pivot holes are aligned, and a pivot pin is inserted through the pivot holes.
    Keywords: Man/System Technology and Life Support
    Type: GSC-14412 , NASA Tech Briefs, April 2003; 5-6
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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