Secondary electron generation, emission and transport: Effects on spacecraft charging and NASCAP models

Katz, Ira; Mandell, M. J.; Roche, J. C.; Purvis, C. K.

doi:10.1016/0304-3886(87)90089-1

Cited by 5 publications

(1 citation statement)

References 18 publications

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“…In a dense plasma such as in LEO, I se is not significant because these current densities are relatively small [16,17] with comparison to the ambient plasma current density, so the currentbalance equation can be written as:…”

Section: Surface Potentialmentioning

confidence: 99%

Study of Lorentz Force on Debris with High Area-to-Mass Ratios

Serra

Hoshi

Vasile

et al. 2018

Journal of Guidance, Control, and Dynamics

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The presence of plasma in Low Earth Orbit and above can be the cause of electrostatic charging on space objects with a conductive surface, which then become subject to the Lorentz force induced by the magnetic field. This paper investigates it effects on the trajectory of orbital debris with a high area-to-mass ratio, as their course is particularly influenced by non-gravitational perturbations such as atmospheric drag or solar radiation pressure. Depending on the altitude (low or medium) and the available data, different charging models have been coupled with an orbit propagator, featuring a range of non-Keplerian accelerations and both three and six degrees-of-freedom dynamics. In particular, there has been a focus on long-term effects by simulating charged versus non-charged objects over the time span of years or decades.

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Section: Surface Potentialmentioning

confidence: 99%

Study of Lorentz Force on Debris with High Area-to-Mass Ratios

Serra

Hoshi

Vasile

et al. 2018

Journal of Guidance, Control, and Dynamics

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show abstract

ISWAT spacecraft surface charging review

Minow,

Jordanova,

Pitchford

et al. 2024

Advances in Space Research

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A study of SCATHA eclipse charging

Whipple²

1988

J. Geophys. Res.

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We study eclipse charging events on the SCATHA spacecraft in a plasma environment which produced large vehicle potentials. We derive a simple relation which relates the spacecraft potential to spacecraft surface‐averaged and angle‐averaged fluxes and yields without assuming Maxwellian velocity distributions for the environment: . The potential varies with the ion mean energy Ei and with the net high‐energy electron current Ies above a critical energy Ec. Below Ec the incoming electrons are balanced by their own secondaries. Above Ec the incoming electrons are balanced by incoming ions and both electron‐produced and ion‐produced secondaries. The potential also depends on the ion thermal current Iio and the average ion yield . Data from five events show that the spacecraft potential correlates well with Ies when the ion properties stay relatively constant. Data from other events show that the potential varies with the ion mean energy. The magnitude of Ec is on the order of 20 to 30 keV. Quantitative prediction of the spacecraft potential depends sensitively on the secondary yield due to electrons.

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Secondary electron generation, emission and transport: Effects on spacecraft charging and NASCAP models

Cited by 5 publications

References 18 publications

Study of Lorentz Force on Debris with High Area-to-Mass Ratios

Study of Lorentz Force on Debris with High Area-to-Mass Ratios

ISWAT spacecraft surface charging review

A study of SCATHA eclipse charging

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