@inproceedings{oai:jaxa.repo.nii.ac.jp:00006351,
 author = {細田, 聡史 and 奥村, 哲平 and Kim, Jeong-ho and Cho, Mengu and 豊田, 和弘 and Hosoda, Satoshi and Okumura, Teppei and Kim, Jeong-ho and Cho, Mengu and Toyoda, Kazuhiro},
 book = {宇宙航空研究開発機構特別資料, JAXA Special Publication: 9th Spacecraft Charging Technology Conference},
 month = {Aug},
 note = {In order to realize 400 volts operation in LEO, arcing caused by interaction between spacecraft and surrounding LEO plasma must be overcome. We have been investigating designs of high voltage solar array. This paper is the summary report for all the tests. The coupon with ion barrier film made from ETFE (called 'film coupon') never suffered any arc. We carried out the tests under realistic orbit environment for the film coupon. It was confirmed that the covered film performed successfully in all the situations. This coupon has never arced for more than 25 hours that was equivalent to 1 percent power degradation in 30 years operation. No film contamination and degradation were observed after 90 C baking. No primary arc occurred at all vacuum pressure and no frictional charging occurred by contact. With respect to debris impact, the covered film had little damage even if the film support was hit directly. Also, film attachments were well supported after the heat cycle of - 90 to + 90 C by reducing tension of film. Conductive substrate, however, suffered many arcs at - 400 V. Also, a sustained arc phenomenon between cells and substrate was induced by simulated debris impact. Therefore, use of flexible substrate is adequate for 400 V solar array in LEO environment., 資料番号: AA0049206036, レポート番号: JAXA-SP-05-001E},
 pages = {280--285},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {Development of 400 V solar array technology for LEO spacecraft},
 volume = {JAXA-SP-05-001E},
 year = {2005}
}