Experiments in charge control at geosynchronous orbit - ATS-5 and ATS-6

Olsen, R. C.

doi:10.2514/3.25742

Cited by 36 publications

(14 citation statements)

References 14 publications

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“…Two fundamental lessons were learned from these earlier experiences: (Olsen, 1981(Olsen, , 1985 has shown that spacecraft floating potential can be regulated at small values by means of the operation of a low-energy plasma source on the spacecraft.…”

mentioning

confidence: 99%

The Thermal Ion Dynamics Experiment and Plasma Source Instrument

et al. 1995

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confidence: 99%

The Thermal Ion Dynamics Experiment and Plasma Source Instrument

et al. 1995

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“…mitigation for lowering the charging level can be carried out by transporting electrons or ions from the surface concerned to the ambient plasma or to other surfaces. Emission of electron or ion beams can control the spacecraft potential, if the beam current exceeds the ambient current [16]- [21]. The potential can be clamped at a finite, positive, or negative, value which can be fairly constant temporarily, if the environment does not vary too much.…”

Section: Mitigation Methodsmentioning

confidence: 99%

“…The only exception is the auroral region (about 60°-70° latitudes) where high-energy electrons may come down from high altitudes. In general, charged beam emission [16]- [21] from a spacecraft can affect the spacecraft potential. The beam current should be included in the current balance equation.…”

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confidence: 99%

A critical overview on spacecraft charging mitigation methods

Lai

2003

IEEE Trans. Plasma Sci.

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The public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources gathering and maintaining the data needed, and completing and reviewing the collection of information. Send comments regarding this burden estimate or any other aspect of this collection Sl-.l?I°i'm',°";jr2'". '"i] Al SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES) PERFORMING ORGANIZATION REPORT NUMBER AFRL-VS-HA-TR-2004-1073 SPONSOR/MONITOR'S ACRONYM{S) DISTRIBUTION/AVAILABILITY STATEMENT ABSTRACTInteractions between hazardous space plasmas and spacecraft surfaces often result in spacecraft charging. Spacecraft charging may disturb the scientific measurements onboard, affect communications, control, and operations of spacecraft, and may be harmfiil to the health of the elecronics on the spacecraft. Several mitigation methods have been proposed or tested in recent years. This paper presents a critical overview on all of the mitigation methods known to date: 1) passive emthods usmg sharp spikes and high secondary emission coefficient surface materials and 2) active methods using controlled emissions of electrons, ions, plasmas, neutral gas, and polar molecules. Paradoxically, emission of low-energy positive ions from a highly negatively charged spacecraft can reduce the chargmg level, because the ions tend to return and may generate secondary electrons which then escape. We discuss the advantages and disadvantages of each of the methods and illustrate the ideas by means of examples of results obtained on SCATHA and DSCS satellites. Finally, mitigation of deep dielectric charging is briefly discussed. Abstract-Interactions between hazardous space plasmas and spacecraft surfaces often result in spacecraft charging. Spacecraft charging may disturb the scientific measurements onboard, affect communications, control, and operations of spacecraft, and may be harmful to the health of the electronics on the spacecraft. Several mitigation methods have been proposed or tested in recent years. This paper presents a critical overvievf on all of the mitigation methods known to date: 1) passive methods using sharp spikes and high secondary emission coefficient surface materials and 2) active methods using controlled emissions of electrons, ions, plasmas, neutral gas, and polar molecules. Paradoxically, emission of low-energy positive ions from a highly negatively charged spacecraft can reduce the charging level, because the ions tend to return and may generate secondary electrons which then escape. We discuss the advantages and disadvantages of each of the methods and illustrate the ideas by means of examples of results obtained on SCATHA and DSCS satellites. Finally, mitigation of deep dielectric charing is briefly discussed. SUBJECT TERMS

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“…The with partial successes [Cohen, etal., 1981; Cohen and transverse energy gained by a diverging beam Lai, 1982;Olsen, 1985;Werner, 1988]. When the electron in a supercharging situation can be of the beam current is lower than the ambient current, the order of the beam energy.…”

Section: In Polar Regionsmentioning

confidence: 99%

Recent advances in spacecraft charging

Lai¹

1994

32nd Aerospace Sciences Meeting and Exhibit

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Experiments in charge control at geosynchronous orbit - ATS-5 and ATS-6

Cited by 36 publications

References 14 publications

The Thermal Ion Dynamics Experiment and Plasma Source Instrument

The Thermal Ion Dynamics Experiment and Plasma Source Instrument

A critical overview on spacecraft charging mitigation methods

Recent advances in spacecraft charging

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