The Effects of Space Debris on Solar Propulsion

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.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1991
Accession Number
ADA235257

Entities

People

  • Mark Skibinski

Tags

Communities of Interest

  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Apogees
  • Artificial Satellites
  • Astronautics
  • Attitude Control Systems
  • Computer Programs
  • Computer Simulations
  • Computers
  • Low Earth Orbits
  • Mathematical Models
  • Payload
  • Propulsion Systems
  • Solar Propulsion
  • Space Debris
  • Space Objects
  • Spacecraft
  • Spacecraft Orbits
  • Thrusters

Readers

  • Space Exploration and Orbital Mechanics.
  • Systems Analysis and Design

Technology Areas

  • Space
  • Space - Orbital Debris