@inproceedings{oai:jaxa.repo.nii.ac.jp:00014462,
 author = {下田代, 優 and 福田, 航 and 野中, 聡 and 稲谷, 芳文 and Shimotashiro, Suguru and Fukuda, Akira and Nonaka, Satoshi and Inatani, Yoshifumi},
 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, For achieving fully reusable rocket vehicle, low speed aerodynamic studies are made on vertical landing vehicle. There is entry flight concept named nose-entry when vertical landing. Nose-entry needs turn-over maneuver in landing phase. In this paper, the method of turn-over maneuver is discussed. In order to obtain some suitable pitching moment characteristics for turnover maneuver, trade-off studies of vehicle shapes were conducted by using the DATCOM. Wind tunnel tests were conducted to evaluate the aerodynamic characteristics of the selected vehicle shape. By using the obtained aerodynamic characteristics from the wind tunnel tests, the turnover maneuver was numerically calculated. The advantageous turn-over maneuver was considered by varying the center of gravity and vehicle shapes. A flight demonstration was preliminarily conducted by a small scale model. In order to understand the flow field around a vehicle at high angle of attack, flow visualization over a vehicle model was also conducted in wind tunnel by oil flow method., 資料番号: AA0064729039},
 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 = {再使用ロケットの帰還飛行における機体転回運動},
 volume = {平成20年度},
 year = {2009}
}