@inproceedings{oai:jaxa.repo.nii.ac.jp:00008024,
 author = {長崎, 俊和 and 福重, 進也 and 赤星, 保浩 and 渡辺, 圭子 and 菅原, 賢尚 and 高良, 隆男 and Cho, Mengu and 原田, 昭治 and Nagasaki, Toshikazu and Fukushige, Shinya and Akahoshi, Yasuhiro and Watanabe, Keiko and Sugahara, Kensho and Kora, Takao and Cho, Mengu and Harada, Shoji},
 book = {第27回宇宙エネルギーシンポジウム　平成19年度, The Twenty-seventh Space Energy Symposium},
 month = {May},
 note = {In recent years, space debris increases because many rockets and satellites have been launched. A solar array of a spacecraft has become larger with the higher voltage and electrical power. Therefore, the risk of debris impact and possibility of discharge on the solar array is increasing. If space debris impacts solar array, it electric power decreases or loses. When space debris impact on the solar array, high-density plasma is discharged. The arc that led may generate the plasma. This is Temporary Sustained Arc. This discharge can lead to carbonize the insulation layer of the solar array by Joule heat due to the large current through the plasma, and form permanent short-circuit. If this phenomenon continues, a permanent short circuit course will be formed between a solar cell and a substrate. This is Permanent Sustained Arc. It causes decrease or loss of generating capacity of a solar array coupon. In this study, the first purpose is verified that sustained arc is discharged or not by space debris impacts on solar array. The second purpose is elucidated the threshold of sustained arc. We want to reduce the influence affect the missions of a satellite by those results. Therefore, we took notice a density and electron temperature of the plasma which induce to discharge and clarified the threshold of sustained arc generating for hypervelocity impact test by two-stage light gas gun. The triple probe method was used plasma measurement test. The results show that electron temperature and electron density have correlation with impact speed, and the plasma density is higher than the plasma environment on low earth orbit. A possibility of TSA (Temporary Sustained Arc) generation is large over 80 [V], and generating of PSA (Permanent Sustained Arc) was confirmed over 183 [V]-2.4 [A] of power supply voltage. The generating conditions of PSA are sustaining voltage is 50 [V], current is 2.2 [A] and dissipation power of discharge circuit is 110 [W]. Therefore, it is desirable that dissipation power of the satellite is less than 110 [W] for preventing generating of PSA., 資料番号: AA0063965011},
 pages = {54--58},
 publisher = {宇宙航空研究開発機構宇宙科学研究本部, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA/ISAS)},
 title = {デブリ衝突により起こる太陽電池アレイの持続放電の閾値},
 year = {2008}
}