Tokai University School of Engineering
Tokai University School of Engineering
Tokai University School of Engineering
出版者
宇宙航空研究開発機構宇宙科学研究本部
出版者（英）
Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA/ISAS)
雑誌名
第23回宇宙エネルギーシンポジウム 平成15年度
雑誌名(英)
The 23rd ISAS Space Energy Symposium March 9, 2004
ページ
50 - 54
発行年
2004-06
抄録（英）
In general, a space system is charged negatively due to an action of space plasma. A number of works for charging and discharging phenomena of the solar cell array surface in the space system under LEO (Low Earth Orbit) have been carried out. In the future, it is expected that various structures composed of metal and insulator are installed in the surface of the space system which has various functions. It is important to work out what phenomena occur in the system. In this work, experiments are carried out to clarify charging and discharging phenomena under LEO plasma environment using some samples that composed of metal and insulator. When negative voltage is applied to the metal of the sample, micro discharges are observed in oscillating wave-form pulse current at all samples. When the applied voltage is increased, single polarity pulse discharges are observed. The single polarity pulse discharging occurs only on the metal surface and the charges of discharging from the metal are much less than the total charges of charging to the surface of the insulator. This discharging is taken place between the charges on the insulator surface and ion sheath forming near the metal. If minute projection parts exist on the metal surface, the discharging voltage lowers. In these cases, the charges of the single polarity discharging do not depend on the area of the metal and the existence of the insulator.
低地球軌道宇宙プラズマ環境下における導体・絶縁体表面の帯電・放電特性の研究
