Active control of electric potential of spacecraftTechniques are discussed for controlling the potential of a spacecraft by means of devices which release appropriate charged particles from the spacecraft to the environment. Attention is given to electron emitters, ion emitters, a basic electron emitter arrangement, techniques for sensing electric field or potential, and flight experiments on active potential control. It is recommended to avoid differential charging on spacecraft surfaces because it can severely affect the efficacy of emitters. Discharging the frame of a spacecraft with dielectric surfaces involves the risk of stressing the dielectric material excessively. The spacecraft should, therefore, be provided with grounded conductive surfaces. It is pointed out that particles released by control systems can return to the spacecraft.
Document ID
19780063216
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Goldstein, R. (California Institute of Technology, Jet Propulsion Laboratory, Pasadena Calif., United States)
Date Acquired
August 9, 2013
Publication Date
January 1, 1977
Subject Category
Spacecraft Design, Testing And Performance
Meeting Information
Meeting: International Symposium on Space Technology and Science