@inproceedings{oai:jaxa.repo.nii.ac.jp:00016305,
 author = {村中, 崇信 and 篠原, 育 and 高木, 亮治 and 森, 治 and 白澤, 洋次 and 船瀬, 龍 and 大野, 剛 and Muranaka, Takanobu and Shinohara, Iku and Takaki, Ryoji and Mori, Osamu and Shirasawa, Yoji and Funase, Ryu and Ono, Go},
 book = {平成24年度宇宙輸送シンポジウム: 講演集録, Proceedings of Space Transportation Symposium: FY2012},
 month = {Jan},
 note = {平成24年度宇宙輸送シンポジウム (2013年1月17日-1月18日. 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)), 相模原市, 神奈川県, Space Transportation FY2012 (January 17-18, 2013. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, Solar sail is a next-generation spacecraft that has a large-scale membrane to utilize the solar radiation pressure as its thrust. Hence, stable deployment of the membrane during a space flight is a critical issue to maintain the thrust performance of the spacecraft. In this paper, we have numerically estimated the electrostatic force on the membrane due to spacecraft charging as one of the possible factor to cause the deformation of the deployed membrane. We obtained spatial distribution of the electrostatic force and the maximum magnitude of the force on the membrane in solar wind plasma at 1.0 AU. We also made structural analysis for the deployed membrane with the electrostatic force. As a result, we can hardly recognize the deformation of the membrane due to the electrostatic force in this case., 形態: カラー図版あり, 形態: PDF, Physical characteristics: Original contains color illustrations, Physical characteristics: PDF, 資料番号: AA0061856169, レポート番号: STEP-2012-086},
 publisher = {宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS), Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)},
 title = {ソーラーセイル膜面の構造におよぼす宇宙機帯電による静電力の影響評価},
 year = {2013}
}