This research sought to determine the impact of space debris on solar propulsion for orbital transfer missions from low Earth Orbit (LEO) to Geosynchronous Earth Orbit (GEO). Orbital debris is a major concern because the present solar propulsion development calls for two 40 X 30 meter inflatable concentrators which present a large area for space debris impact. The initial questions to be researched were: (1) How much extra inflationary gas will be required to make up for meteroid and artificial space debris leaks. and (2) What is the probability of a catastrophic collision with the concentrators. Numerous debris models and many assumptions were used to calculate answers for these questions, but overall the inflatable reflectors were judged to be a plausible concept. It is plausible in that the amount of helium inflatent needed to keep the concentrators rigid is an acceptable weight (12 lbm). Also the probability of a catastrophic collision for a 40 day mission is minimal (0.1%). Furth research and computer simulation is needed to better define the man-made debris distribution for elliptical (transfer) orbits due to their constant changing altitude.
Effects of Space Debris on Solar Propulsion
1991
37 pages
Report
Keine Angabe
Englisch
Electric & Ion Propulsion , Astronautics , Spacecraft Trajectories & Flight Mechanics , Catastrophic conditions , Collisions , Computerized simulation , Debris , Distribution , Earth orbits , Helium , Impact , Inflatable structures , Manmade , Missions , Models , Orbits , Reflectors , Space environments , Synchronous satellites , Transfer , Space debris , Solar propulsion , Transfer trajectories
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