@inproceedings{oai:jaxa.repo.nii.ac.jp:00016164,
 author = {藤川, 貴弘 and 土屋, 武司 and 田口, 秀之 and Fujikawa, Takahiro and Tsuchiya, Takeshi and Taguchi, Hideyuki},
 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, The trajectory research is conducted on experimental hypersonic vehicles launched by S-520 sounding rockets. Direct trajectory optimization techniques are applied to obtain the trajectory which maximizes the duration of the requested experimental conditions, i.e., a Mach number no less than 4 and dynamic pressure between 45 and 55 kPa. It is demonstrated that the experimental conditions can be achieved for more than 1 minute if the initial mass and launch angle of the sounding rocket are designed properly., 形態: PDF, Physical characteristics: PDF, 資料番号: AA0061856028, レポート番号: STCP-2012-028},
 pages = {1--4},
 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 = {観測ロケットを利用した極超音速飛行試験: 2軌道検討},
 year = {2013}
}