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Potential of Earth Orbiting Spacecraft Influenced by Meteoroid Hypervelocity Impacts
Umeå universitet, Teknisk-naturvetenskapliga fakulteten, Institutionen för fysik.ORCID-id: 0000-0003-2177-0955
Umeå universitet, Teknisk-naturvetenskapliga fakulteten, Institutionen för fysik. Swedish Institute of Space Physics, Kiruna, Sweden.
Umeå universitet, Teknisk-naturvetenskapliga fakulteten, Institutionen för fysik. Arctic University of Norway, Tromsø, Norway.
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2017 (Engelska)Ingår i: IEEE Transactions on Plasma Science, ISSN 0093-3813, E-ISSN 1939-9375, Vol. 45, nr 8, s. 2048-2055Artikel i tidskrift (Refereegranskat) Published
Abstract [en]

Detection of hypervelocity impacts on a spacecraft body using electric field instruments has been established as a new method for monitoring of dust grains in our solar system. Voyager, WIND, Cassini, and STEREO spacecraft have shown that this technique can be a complementary method to conventional dust detectors. This approach uses fast short time changes in the spacecraft potential generated by hypervelocity dust impacts, which can be detected by monopole electric field instruments as a pulse in the measured electric field. The shape and the duration of the pulse strongly depend on parameters of the ambient plasma environment. This fact is very important for Earth orbiting spacecraft crossing various regions of the Earth's magnetosphere where the concentration and the temperature of plasma particles change significantly. We present the numerical simulations of spacecraft charging focused on changes in the spacecraft potential generated by dust impacts in various locations of the Earth's magnetosphere. We show that identical dust impacts generate significantly larger pulses in regions with lower electron density. We discuss the influence of the photoelectron distribution for dust impact detections showing that a small amount of energetic photoelectrons significantly increases the potential of the spacecraft body and the pulse duration. We also show that the active spacecraft potential control (ASPOC) instrument onboard the cluster spacecraft strongly reduces the amplitude and the duration of the pulse resulting in difficulties of dust detection when ASPOC is ON. Simulation of dust impacts is compared with pulses detected by the Earth orbiting cluster spacecraft in the last part of Section III.

Ort, förlag, år, upplaga, sidor
2017. Vol. 45, nr 8, s. 2048-2055
Nyckelord [en]
Dust grains, hypervelocity impacts, meteoroids, spacecraft charging
Nationell ämneskategori
Fusion, plasma och rymdfysik
Identifikatorer
URN: urn:nbn:se:umu:diva-140978DOI: 10.1109/TPS.2017.2676984ISI: 000407374400031Scopus ID: 2-s2.0-85015612120OAI: oai:DiVA.org:umu-140978DiVA, id: diva2:1154130
Forskningsfinansiär
Rymdstyrelsen, 110/14Rymdstyrelsen, 77/14Tillgänglig från: 2017-11-01 Skapad: 2017-11-01 Senast uppdaterad: 2023-03-23Bibliografiskt granskad

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Vaverka, JakubPellinen-Wannberg, AstaMann, IngridDe Spiegeleer, AlexandreHamrin, MariaNorberg, CarolPitkänen, Timo

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Vaverka, JakubPellinen-Wannberg, AstaMann, IngridDe Spiegeleer, AlexandreHamrin, MariaNorberg, CarolPitkänen, Timo
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Institutionen för fysik
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IEEE Transactions on Plasma Science
Fusion, plasma och rymdfysik

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