JAXA Repository / AIREX 未来へ続く、宙(そら)への英知

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title低地球軌道プラズマ環境下における絶縁体表面の帯電-時間特性測定
Other TitleMeasurement of characteristics of insulator surface charging to time under low earth orbit plasma environment
Author(jpn)上坂 章人; 呉地 淳一; 岡部 昭三
Author(eng)Uesaka, Akihito; Kurechi, Junichi; Okabe, Shozo
Author Affiliation(jpn)東海大学 工学部; 東海大学 工学部; 東海大学 工学部
Author Affiliation(eng)Tokai University School of Engineering; Tokai University School of Engineering; Tokai University School of Engineering
Issue Date2004-06
PublisherInstitute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA/ISAS)
宇宙航空研究開発機構宇宙科学研究本部
Publication title第23回宇宙エネルギーシンポジウム 平成15年度
The 23rd ISAS Space Energy Symposium March 9, 2004
Start page55
End page59
Publication date2004-06
Languagejpn
AbstractIn recent years, as the solar power satellite, the spacecraft is enlarged and requires much higher voltage. However, there are some technical problems as using high voltage in the solar power system. In the space environment, electric discharges occur on the solar cell arrays and the discharges cause damage to the arrays and the efficiency falls. Therefore, it is important to work out to these problems for developing the application in the space. There are two causes in the electric discharges at the solar arrays. One is electric charging phenomenon at a coverglass surface of the solar cell by interaction between the solar cell and the space plasma. The other one is electric field emphasis at a triple junction point that consists of the coverglass and interconnector in the space plasma. In this paper, the charging phenomena of the coverglass on the solar cell under Low Earth Orbit space plasma environment is discussed. So, the charging experiments are carried out using a sample that consists of Acrylic insulator and Aluminum conductor in simulated LEO plasma environment. In the experiments, distributions of electric charges are measured to time on the insulator surface of the sample. As a result, it is clarified that the electric charging of the insulator surface is based on positive ions in the space, and the charging depends on the strength of the electric field on its surface. Therefore, electric discharges occur when the potential difference between the object of the solar system and plasma space increases.
Keywordssimulated space environment; spacecraft charging; space plasma; electric discharge; low Earth orbit; solar array; solar power satellite; insulator surface; 擬似宇宙環境; 宇宙機帯電; 宇宙プラズマ; 放電; 低地球軌道; 太陽電池アレイ; 太陽発電衛星; 絶縁体表面
Document TypeConference Paper
JAXA Categoryシンポジウム・研究会
SHI-NOAA0047275012
URIhttps://repository.exst.jaxa.jp/dspace/handle/a-is/51253


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