@inproceedings{oai:jaxa.repo.nii.ac.jp:00004019,
 author = {高橋, 裕介 and 河, 東顯 and 山田, 和彦 and 安部, 隆士 and 鈴木, 宏二郎 and Takahashi, Yusuke and Ha, Dongheun and Yamada, Kazuhiko and Abe, Takashi and Suzuki, Kojiro},
 book = {宇宙航空研究開発機構特別資料: 第45回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2013論文集, JAXA Special Publication},
 month = {Mar},
 note = {第45回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2013 (2013年7月4日-5日. タワーホール船堀), 東京, 45th Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2013 (July 4-5, 2013. Tower Hall Funabori), Tokyo, Japan, A reentry flight demonstration of an advanced reentry vehicle was carried out using JAXA S-310-41 sounding rocket. The vehicle was equipped with a flexible (membrane) aeroshell deployed by an inflatable torus structure and demonstrated deceleration at higher altitude. During the reentry flight, position, velocity and acceleration of the vehicle were measured by the global positioning system (GPS). Moreover, drag coefficient history was evaluated by the vehicle acceleration and the global reference atmospheric model (GRAM99). In the present study, flow field simulations around the reentry vehicle were conducted with numerical simulation methods. Aerodynamic force of the vehicle was investigated with the measured history through the supersonic and subsonic regions during the reentry. In the flow field simulation, it was found that the measured drag coefficient data shows a reasonable agreement with the predicted one in higher and lower altitudes. In addition, it was clarified that compressible effect in front of the vehicle appears in supersonic region, and a feature of vortex ring at the rear of the vehicle is formed in subsonic region., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA0062268019, レポート番号: JAXA-SP-13-011},
 pages = {103--108},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {観測ロケット実験における柔軟構造飛翔体の空力解析について},
 volume = {JAXA-SP-13-011},
 year = {2014}
}