Effects of Space Debris on Solar Propulsion
Effects of Space Debris on Solar Propulsion
- Neue Suche nach: M. Skibinski
- Neue Suche nach: M. Skibinski
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.
Dokumentinformationen
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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