Spacecraft Charge as a Source of Electrical Power for Spacecraft
Abstract
This thesis examines the suitability of spacecraft charge, collected at geosynchronous altitude, as a source of electrical power for spacecraft. An analytical plasma probe model is used to describe the flux of charged particle currents on two isolated (conductive) hemispheres of a spacecraft. Surface potentials are evaluated for both a body-stabilized and spin-stabilized spacecraft under average and worst case plasma conditions. A discharge current is simulated, between differentially charged surfaces, to examine the current flow required to balance the surface potentials. This current approximates the maximum current flow available from the spacecraft charge. The results show that surface potential differences can be large in in worst case plasma conditions, but the current available is too small to be useful as a power source. The discharge current does scale up in proportion to spacecraft surface area exposed to the plasma; however, the design of large conductive spacecraft surfaces is a problem in itself. Theses.
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 01, 1988
- Accession Number
- ADA202621
Entities
People
- Wayne Gale
Organizations
- Air Force Institute of Technology