Graduate School of Engineering, The University of Tokyo
School of Engineering, The University of Tokyo
Aerospace Research and Development Directorate, Japan Aerospace Exploration Agency (JAXA)
出版者
宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)
出版者（英）
Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)
雑誌名
平成24年度宇宙輸送シンポジウム: 講演集録
雑誌名(英)
Proceedings of Space Transportation Symposium: FY2012
Space Transportation FY2012 (January 17-18, 2013. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan
抄録（英）
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.
観測ロケットを利用した極超音速飛行試験: 2軌道検討
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