@inproceedings{oai:jaxa.repo.nii.ac.jp:00014431,
 author = {木村, 裕介 and 山田, 和彦 and 秋田, 大輔 and 安部, 隆士 and 小山, 将史 and 鈴木, 宏二郎 and 林, 光一 and 牧野, 仁 and Kimura, Yusuke and Yamada, Kazuhiko and Akita, Daisuke and Abe, Takashi and Koyama, Masashi and Suzuki, Kojiro and Hayashi, A. Koichi and Makino, Hitoshi},
 book = {宇宙航行の力学シンポジウム, Symposium on Flight Mechanics and Astrodynamics},
 month = {Dec},
 note = {宇宙航行の力学シンポジウム(平成20年度)(2008年12月4～5日、宇宙航空研究開発機構宇宙科学研究本部), Symposium on Flight Mechanics and Astrodynamics 2008 (December 4-5, 2008. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)), Sagamihara, Kanagawa Japan, A vehicle with a flexible aeroshell is promising for the innovative re-entry system because the aerodynamic heating during re-entry can be reduced dramatically due to its low-ballistic-coefficient.The key technologlies of this concept are the large, low-mass and flexible aeroshell. One of the solutions that satisfy these requirements is a flare-type flexible aeroshell sustain by an inflatable torus frame. Our group has researched various important subjects in order to apply the flexible aeroshell to actual atmospheric-entry missions. One topic of them is reported in this paper. The topic is a structural test of the flare-type inflatable aeroshell. The relation between the diferential pressure of inflatable torus and the maximum compressive force which inflatable torus is able to keep the configuration was obtained by the structural tests using two kinds of support rings. Furthermore, a low-speed wind tunnel test was carried out to investigate the configuration of inflatable aeroshell and its structural strength against anaerodynamic force during the night., 資料番号: AA0064729008},
 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)},
 title = {柔構造大気突入機用インフレータブルフレームの開発試験},
 volume = {平成20年度},
 year = {2009}
}