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  • Other Sources  (38)
  • SPACECRAFT DESIGN, TESTING AND PERFORMANCE  (38)
  • 1980-1984  (38)
  • 1940-1944
  • 1980  (38)
  • 1940
  • 1
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    P78-2 satellite and payload responses to electron beam operations on March 30, 1979 (1980)
    In:  Other Sources
    Details
    Publication Date: 2016-06-07
    Description: The operating modes of the SC4-1 payload, the resultant charging of the spacecraft frame and sample materials on the spacecraft exterior and recorded transient pulses are reported. Arcing was detected by pulse monitors in several electron beam modes of operation. The ejection of a beam of 6 mA of 3 keV electrons caused three distinct payload failures and created a transient problem in the telemetry system. The exact time, nature, and cause of these failures was determined and component failure and why they failed was identified. Analytical and modeling techniques are used to examine possible spacecraft and payload responses to the electron beam ejection which might have contributed to the arcing and payload failures.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Charging Technol., 1980; p 509-559
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Orbiter/shuttle carrier aircraft separation: Wind tunnel, simulation, and flight test overview and results (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A summary of the approach and landing test phase of the space shuttle program is given from the orbiter/shuttle carrier aircraft separation point of view. The data and analyses used during the wind tunnel testing, simulation, and flight test phases in preparation for the orbiter approach and landing tests are reported.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-58223
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Flight evidence of spacecraft surface contamination rate enhancement by spacecraft charging obtained with a quartz crystal microbalance (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The significance of the fraction of the mass outgassed by a negatively charged space vehicle which is ionized within the vehicle plasma sheath and electrostatically reattracted to the space vehicle was determined. The ML-12 retarding potential analyzer/temperature controlled quartz crystal microbalances (RPA/TQCMs) distinguishes between charged and neutral molecules and investigates contamination mass transport mechanism. Two long term, quick look flight data sets indicate that on the average a significant fraction of mass arriving at one RPA/TQCM is ionized. It is assumed that vehicle frame charging during these periods was approximately uniformly distributed in degree and frequency. It is shown that electrostatic reattraction of ionized molecules is an important contamination mechanism at and near geosynchronous altitudes.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Charging Technol., 1980; p 493-508
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    NASA TECHNICAL REPORTS
  • 4
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    Electron angular distributions during charging events (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The angular distribution of electrons and ions at times of spacecraft charging were examined for several charging events. Generally it was found that electrons measured perpendicular to the Earth's magnetic field are more intense and more energetic than those measured parallel to the magnetic field during charging events. During the substorm charging injection, the electron spectra harden at all angles to the magnetic field as the evolution of the charging spectra is monitored by the P78-2 satellites. An example of the onset of charging and the changes in the electron distributions is examined. The evolution of the electrons from a 'soft' plasma sheet distribution to a 'hard' charging distribution is compared with the charging of Kapton on the satellite and the spacecraft frame potential. The ions are used to determine the spacecraft potential. Evidence of periodic surface potential variations related to particle anisotropies are presented and discussed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Charging Technol., 1980; p 370-385
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    NASA TECHNICAL REPORTS
  • 5
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    Space radiator trade studies for the 25 kW Power System (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Advanced radiator designs which will survive the meteoroid hazard of near earth orbit for five years are evaluated for the 25 kW Power System. Weight comparisons of heat pipe radiators and pumped fluid radiators incorporating meteoroid bumpers are presented for the initial 25 kW Power System and growth versions to 250 kW. The heat pipe concept is enhanced by a new design of the thermal interface between the heat pipe and coolant loop. The results show small weight differences between the advanced heat pipe and pumped fluid concepts for heat loads up to about 50 kW. The heat pipe panels have a weight advantage for larger heat loads.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: ASME PAPER 80-ENAS-27 , Intersociety Environmental Systems Conference; Jul 14, 1980 - Jul 17, 1980; San Diego, CA
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    NASA TECHNICAL REPORTS
  • 6
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    Meteosat spacecraft charging investigation (1980)
    In:  Other Sources
    Details
    Publication Date: 2016-06-07
    Description: A number of phenomena observed on the first orbiting Meteosat satellite attributed to spacecraft charging effects are considered. Design analysis, correlation of anomalies with space environmental data, on ground tests with an engineering model spacecraft, tests on the validity of improvements, and installation of suitable monitors for the second improved flight satellite are discussed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Charging Technol., 1980; p 814-834
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    NASA TECHNICAL REPORTS
  • 7
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    P78-2 SCATHA environmental data atlas (1980)
    In:  Other Sources
    Details
    Publication Date: 2016-06-07
    Description: The 100 eV to approximately 1 MeV plasma environment encountered by the P78-2 Spacecraft Charging at High Altitudes (SCATHA) satellite during its initial operation period was studied. Forty-four days of 10 minute averages of the four moments of the electron and ion distribution functions calculated from the SC5 and SC9 energetic particle measurements were analyzed to determine occurrence frequency, local time variation, geomagnetic activity variation, and L shell variation. The single and double Maxwellian parameters derived from the four moments were similarly analyzed. The interrelationships between the moments and derived parameters were computed and the results compared with the ATS-5 and ATS-6 atlas. Results of this analysis establish a baseline range for the SCATHA plasma environment.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Charging Technol., 1980; p 802-813
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    NASA TECHNICAL REPORTS
  • 8
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    Military standards and SCATHA program update of MIL-STD-1541 (1980)
    In:  Other Sources
    Details
    Publication Date: 2016-06-07
    Description: The elctromagnetic compatability requirements for space systems, 15 October 1973, to be met by industry contractors for spacecraft launch vehicles and other special space systems, are considered. Deficiencies in the existing standard with respect to spacecraft charge and discharge phenomena, the technical ramifications for generating a new standard, and the upgrading of MIL-STD-1541 with requirements supplied as a result of the SCATHA program are discussed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Charging Technol., 1980; p 768-788
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    NASA TECHNICAL REPORTS
  • 9
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    Comparison of NASCAP modelling results with lumped circuit analysis (1980)
    In:  Other Sources
    Details
    Publication Date: 2016-06-07
    Description: Engineering design tools that can be used to predict the development of absolute and differential potentials by realistic spacecraft under geomagnetic substorm conditions are described. Two types of analyses are in use: (1) the NASCAP code, which computes quasistatic charging of geometrically complex objects with multiple surface materials in three dimensions; (2) lumped element equivalent circuit models that are used for analyses of particular spacecraft. The equivalent circuit models require very little computation time, however, they cannot account for effects, such as the formation of potential barriers, that are inherently multidimensional. Steady state potentials of structure and insulation are compared with those resulting from the equivalent circuit model.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Spacecraft Charging Technol., 1980; p 665-683
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    NASA TECHNICAL REPORTS
  • 10
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    Analysis of ambient and beam particle characteristics during the ejection of an electron beam from a satellite in near-geosynchronous orbit on March 30, 1979 (1980)
    In:  Other Sources
    Details
    Publication Date: 2016-06-07
    Description: An electron beam system was operated over a wide range of beam currents and energies for periods both in sunlight and in eclipse. Complex pitch angle modulations of the electron spectra are separately decomposed for each beam operation. When electrons are emitted perpendicular to the magnetic field with an energy of 3 keV and a current of 0.10 mA they return as a coherent beam only to the parallel detector. Throughout the beam operations the pitch angle distributions show electrons with energy less than beam energy streaming along the field line. Analytic expressions for the satellite electric field are constructed and particle trajectories are determined.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Charging Technol., 1980; p 642-664
    Format: text
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    NASA TECHNICAL REPORTS
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