Accession Number:

ADA235257

Title:

The Effects of Space Debris on Solar Propulsion

Descriptive Note:

Final rept. Jun-Jul 1990

Corporate Author:

PHILLIPS LAB EDWARDS AFB CA

Personal Author(s):

• Skibinski, Mark

Report Date:

1991-03-01

Pagination or Media Count:

37.0

Abstract:

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 meteoroid 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. Further research and computer simulation is needed to better define the man-made debris distribution for elliptical transfer orbits due to their constant changing altitude.

Descriptors:

• *SPACECRAFT DEBRIS
• *SOLAR COLLECTORS
• DEBRIS
• EARTH ORBITS
• SPACE ENVIRONMENTS
• MODELS
• DISTRIBUTION
• MISSIONS
• MANMADE
• HELIUM
• CATASTROPHIC CONDITIONS
• INFLATABLE STRUCTURES
• SPACE MISSIONS
• REFLECTORS
• COLLISIONS
• SYNCHRONOUS SATELLITES
• TRANSFER TRAJECTORIES
• SPACE PROPULSION
• IMPACT
• COMPUTERIZED SIMULATION
• ORBITS

Subject Categories:

• Unmanned Spacecraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE