An unusual charging event on ISEE 1

Olsen, R. C.; Whipple, E. C.

doi:10.1029/ja093ia06p05568

Cited by 9 publications

(6 citation statements)

References 29 publications

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“…Mass spectrometer analysis of the low-energy ions was not possible on SCATHA. Previously published ISEE 1 data indicated that the mass was greater than 16 amu [Olsen and Whipple, 1988]. These data would be consistent with mass 28, silicon.…”

Section: Discussionsupporting

confidence: 83%

“…Spacecraft generated ions have previously been identified in data from ATS-5 [Deforest, 1973], ATS-6 [Olsen et al, 1981], and ISEE-1 [Olsen and Whipple, 1988]. Data from the SCATHA satellite are shown here for 2 events, one during a naturally occurring, eclipse charging period, and one for a negative charging period induced by ion gun operations.…”

Section: Observationsmentioning

confidence: 99%

“…They have been termed "spacecraft generated ions", and have since been noted in observations from ATS 6 and ISEE 1. [Olsen et al, 1981;Olsen and Whipple, 1988]. At lower altitudes, sputtering by rammed, neutral N 2 and 0 2 was observed on Atmospheric Explorer [Hanson et al, 1981].…”

Section: Spacecraft Chargingmentioning

confidence: 99%

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Spacecraft‐generated ions

Olsen¹,

Norwood²

1991

J. Geophys. Res.

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Electrostatic analyzer measurements of ions on the SCATHA satellite show evidence of locally generated ions. These measurements come during periods of large negative charging (~-100 to -10,000 V) at or near geosynchronous altitude. Ions are observed at energies below the satellite potential, which, in the absence of scattering, must have been generated on or near the satellite surface. Differential charging measurements from the Surface Satellite Potential Monitor indicated that there were surfaces with the proper magnitude of differential charging to provide a source for the observed ions. Application of the Sigmund-Thompson theories on sputtering show that ambient 10-to100-keV O+ on glass should provide a yield of 0.5 to 1.0 particles per incident ion. Roughly 2-4% of this yield is ionized. This is sufficient to explain the flux levels observed. Particle tracking using the NASA Charging Analyzer Program (NASCAP) showed that the energies measured provided a sweep of trajectories along the satellite surface, but no specific source was identified.

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Section: Discussionsupporting

confidence: 83%

Section: Observationsmentioning

confidence: 99%

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Spacecraft‐generated ions

Olsen¹,

Norwood²

1991

J. Geophys. Res.

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“…We assume that the potential is known on the entire surface, which is reasonable only for highly conductive surfaces (such as were used on Cluster). Insulating materials, which can charge to very large potentials [ DeForest , 1972; Olsen and Whipple , 1988; Whipple , 1976], would require a different treatment.…”

Section: Numerical Modelmentioning

confidence: 99%

Electrostatic structure around spacecraft in tenuous plasmas

2007

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[1] Most satellite-based in situ plasma experiments are affected in some manner by the electrostatic structure surrounding the spacecraft. In order to better understand this structure, we have developed a fully three-dimensional self-consistent model that can accept realistic spacecraft geometry, including both thin ($10 À4 m) wires and long ($10 2 m) booms, with open boundary conditions. The model uses an integral formulation incorporating boundary element, multigrid and fast multipole methods to overcome problems associated with the large range in scale sizes and inherently three-dimensional structure. By applying the model to the Cluster spacecraft, we show that the electric potential structure is dominated by the charge on the wire booms, with the spacecraft body contributing at small distances. Consequently, the potential near the EFW (Electric Fields and Waves experiment) probes at the end of the wire booms is typically significantly above the true plasma potential. For the Cluster spacecraft, we show that this effect causes a 19% underestimation of the spacecraft potential and 13% underestimation of the ambient electric field. We further assess the electric field due to the sunward-oriented photoelectron cloud, showing that the cloud contributes little to the observed spurious sunward field in the EFW data.Citation: Cully, C. M., R. E. Ergun, and A. I. Eriksson (2007), Electrostatic structure around spacecraft in tenuous plasmas,

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“…The existence of potential barriers, though never explicitly measured, has been inferred from the electron energy spectra observed at a spot on the surface on the ATS‐5 satellite [ Olsen , 1980; Olsen et al , 1981] and on ISEE 1 [ Olsen and Whipple , 1988] previously. Potential barriers were also of concern for the Geotail and Cluster satellites [ Zhao et al , 1996; Thiebault et al , 2004].…”

Section: Introductionmentioning

confidence: 99%

Analytic models for a rapidly spinning spherical satellite charging in sunlight

Tautz¹

2005

J. Geophys. Res.

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[1] We present elementary analytic models for a fast-spinning, dielectric-coated, spherical spacecraft charging in sunlight. The models are based on a multipole expansion of Laplacian potentials external to the spacecraft surface. We assume azimuthal symmetry about the spin axis, and the spin period must be short compared with surface differential charging times. There are three parameters in the models: the monopole potential, the relative strength of the dipole/quadrupole components with respect to the monopole, and a mixing angle. The combination of monopole potentials along with the dipole or quadrupole contributions produce potential barriers which form at the satellite surface. These barriers can act to block escaping photoelectrons and lead to current balance, allowing sunlight charging to high negative levels. The sunlit side charges less (negatively) than the shade side and the ratio of Sun to shade potentials is near its threshold value for high-level charging. We have calculated more general cases with various values of Sun angle relative to the spin axis by combining the dipole and quadrupole components. The potential barrier shape and area vary for different cases and the maximum barrier approximately follows the Sun angle. We stress that for physical interpretation of data obtained on board, one should take into account the potential distribution and where the instrument is located.Citation: Tautz, M., and S. T. Lai (2005), Analytic models for a rapidly spinning spherical satellite charging in sunlight,

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An unusual charging event on ISEE 1

Cited by 9 publications

References 29 publications

Spacecraft‐generated ions

Spacecraft‐generated ions

Electrostatic structure around spacecraft in tenuous plasmas

Analytic models for a rapidly spinning spherical satellite charging in sunlight

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