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Active spacecraft potential control system selection for the Jupiter orbiter with probe missionIt is shown that the high flux of energetic plasma electrons and the reduced photoemission rate in the Jovian environment can result in the spacecraft developing a large negative potential. The effects of the electric fields produced by this charging phenomenon are discussed in terms of spacecraft integrity as well as charged particle and fields measurements. The primary area of concern is shown to be the interaction of the electric fields with the measuring devices on the spacecraft. The need for controlling the potential of the spacecraft is identified, and a system capable of active control of the spacecraft potential in the Jupiter environment is proposed. The desirability of using this system to vary the spacecraft potential relative to the ambient plasma potential is also discussed. Various charged particle release devices are identified as potential candidates for use with the spacecraft potential control system. These devices are evaluated and compared on the basis of system mass, power consumption, and system complexity and reliability.
Document ID
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Beattie, J. R.
(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Goldstein, R.
(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Date Acquired
August 9, 2013
Publication Date
February 24, 1977
Publication Information
Publication: Proc. of the Spacecraft Charging Technol. Conf.
Subject Category
Launch Vehicles And Space Vehicles
Accession Number
Funding Number(s)
Distribution Limits
Work of the US Gov. Public Use Permitted.
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