@inproceedings{oai:jaxa.repo.nii.ac.jp:00006508,
 author = {田原, 弘一 and 増山, 貴久 and Tahara, Hirokazu and Masuyama, Takahisa},
 book = {宇宙航空研究開発機構特別資料: 第1回宇宙環境シンポジウム報告書, JAXA Special Publication: Proceedings of the First Spacecraft Environment Symposium},
 month = {Mar},
 note = {In the future, LEO spacecraft will be larger and higher powered. Because of the balance of leakage currents through ambient space plasma, their main conductive body will have a higher negative potential without plasma contactor operation. When spacecraft operate with a higher voltage, more intensive arcing is suspected to occur on the surface. When an arc occurs on the spacecraft insulating surface, it causes some problems such as degradation of spacecraft surface material. Therefore it's important to know how much energy is supplied to an arcing and how much an arcing degrades spacecraft surface materials. In previous works, it was observed that arc spots diameter tended to enlarge with initial stored energy. Here, arc spots can signify the location on insulating material where an arc occurred. In this study, numerical simulation to verify the dependence of arc spot diameter on initial energy and to estimate how much energy is supplied to arc plasma were carried out. Calculated Results showed that arc spot diameter enlarged as initially stored energy increased. Furthermore, the plasma density near arc spot was much higher than that of ambient space plasma because of ablation of the insulator due to arcing., 資料番号: AA0048468016, レポート番号: JAXA-SP-04-010},
 pages = {78--83},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {宇宙機表面絶縁材料のアーキングによる破壊現象の数値計算},
 volume = {JAXA-SP-04-010},
 year = {2005}
}