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  • 1
    Publication Date: 2013-08-31
    Description: This report focuses on the data acquired by detailed examination of LDEF intercostals, 68 of which are now in possession of the Meteoroid and Debris Special Investigation Group (M&D SIG) at JSC. In addition, limited data will be presented for several small sections from the A0178 thermal control blankets that were examined/counted prior to being shipped to Principal Investigators (PI's) for scientific study. The data presented here are limited to measurements of crater and penetration-hole diameters and their frequency of occurrence which permits, yet also constrains, more model-dependent, interpretative efforts. Such efforts will focus on the conversion of crater and penetration-hole sizes to projectile diameters (and masses), on absolute particle fluxes, and on the distribution of particle-encounter velocities. These are all complex issues that presently cannot be pursued without making various assumptions which relate, in part, to crater-scaling relationships, and to assumed trajectories of natural and man-made particle populations in LEO that control the initial impact conditions.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Langley Research Center, LDEF: 69 Months in Space. Second Post-Retrieval Symposium, Part 2; p 313-324
    Format: application/pdf
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  • 2
    Publication Date: 2019-06-28
    Description: Meteoroid and space debris impact data obtained from space exposed spacecraft parts or meteoroid experiments is analyzed. The returned space exposed surfaces considered include spacecraft windows, meteoroid experiments exposed on space flights, and samples of opportunity such as foil wrapped around a cosmic ray package. The debris flux is found to exceed the meteoroid flux in creating impact craters smaller than 20 microns in diameter, and may again exceed it for impact structures larger than a few mm in diameter. For impact structures between 100 microns and 1 mm in diameter, the debris flux is found to be several times less than the meteoroid flux. Determining more accurately the meteoroid or orbital debris mass that makes a given crater or hole size remains is considered to be the main remaining problem.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 90-1349
    Format: text
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  • 3
    Publication Date: 2019-07-12
    Description: Data taken on the SCATHA satellite at geosynchronous altitudes during periods of electron beam ejection in sunlight showed that the potential difference between an electrically isolated boom and the satellite main body was a function of beam current, energy, and boom-sun angle. The potential difference decreased as the boom area illuminated by the sun increased; the maximum and minimum potential differences were measured when minimum and maximum boom areas, respectively, were exposed to the sun. It is shown that photoelectrons, created on the boom, could be engulfed in the electrostatic field of the highly charged satellite main body. Theoretical calculations made using a simple current balance model showed that these electrons could provide a substantial discharging current to the main body and cause the observed variations in the potential difference between the main body and the booms.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AD-A190390 , AFGL-TR-87-0336 , Journal of Geophysical Research (ISSN 0148-0227); 92; 12319-12
    Format: text
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