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

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Other TitleValidation of Multi-Utility Spacecraft Charging Analysis Tool (MUSCAT) by laboratory plasma measurement
Author(jpn)倉原 直美; 細田 聡史; 村中 崇信; 八田 真児; Kim, Jeongho; Cho, Mengu
Author(eng)Kurahara, Naomi; Hosoda, Satoshi; Muranaka, Takanobu; Hatta, Shinji; Kim, Jeongho; Cho, Mengu
Author Affiliation(jpn)九州工業大学; 九州工業大学; 九州工業大学; 九州工業大学; 九州工業大学; 九州工業大学
Author Affiliation(eng)Kyushu Institute of Technology; Kyushu Institute of Technology; Kyushu Institute of Technology; Kyushu Institute of Technology; Kyushu Institute of Technology; Kyushu Institute of Technology
Issue Date2006-06
PublisherInstitute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA/ISAS)
Publication title第25回宇宙エネルギーシンポジウム 平成17年度
The Twenty-fifth Space Energy Symposium March 10, 2006
Start page36
End page40
Publication date2006-06
AbstractIn recent years, electric discharges on spacecraft become serious problem as spacecraft voltage increases. If electric discharges occur, catastrophic damage such as burning of power cable and solar array would be induced. Understanding the interaction between space environment and spacecraft has become an important issue for the safe operation of spacecraft since charging-arcing problem has caused loss of power. For that reason, quantitative analysis of spacecraft charging is necessary from the early stage of satellite design. MUSCAT is a spacecraft charging analysis tool, which can help satellite engineers to analyze spacecraft charging. The main purpose of this research is to validate the MUSCAT. In this paper, a current collection by a conductor and plasma space potential distribution around the fixed electrical potential are discussed. Validation tests were carried out in the following three steps. (1) 2-D distribution measurement of plasma parameters (temperature, density, and electrical potential) with a langmuir probe. (2) Current collection by a rectangular conductor. (3) Plasma space potential distribution around a body with a fixed electrical potential. From the 2-D distribution measurement, plasma temperature, density, and electrical potential were given to MUSCAT simulation as impute parameters. Next, the rectangular electrode was biased to measure the collected current-voltage profile. Finally, an emissive probe attached to traverse devices was moved. Inside the chamber to observe the sheath surrounding the rectangular electrode. The measurement values gave good agreement with the values of MUSCAT calculation. In conclusion, MUSCAT can simulate a phenomenon of current collection and plasma space potential around the fixed electrical potential very well.
Keywordscomputer program; spacecraft charging; plasma measurement; solar array; computerized simulation; satellite design; electric discharge; high voltage; surface potential; space potential; ion current; 計算機プログラム; 宇宙機帯電; プラズマ測定; 太陽電池アレイ; 計算機シミュレーション; 衛星設計; 放電; 高電圧; 表面電位; 空間電位; イオン電流
Document TypeConference Paper
JAXA Categoryシンポジウム・研究会

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