日本航空宇宙学会論文集
Online ISSN : 2432-3691
Print ISSN : 1344-6460
ISSN-L : 1344-6460
論文
観測ロケット利用による極超音速飛行実験に向けた実験機形状・飛行軌道の複合領域最適設計
藤川 貴弘土屋 武司田口 秀之
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2016 年 64 巻 3 号 p. 182-188

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A hypersonic flight experiment using an S-520 sounding rocket as a launch vehicle is planned in order to demonstrate integrated control technologies for vehicle attitude and propulsion. Its primary mission requirement is to achieve experimental conditions for the installed ramjet engines (constant 50kPa dynamic pressure at not less than Mach 4.0) for a sufficient duration. In this paper, a feasibility study of the flight experiment is conducted using a multidisciplinary design optimization technique. The experimental vehicle shape and the flight trajectory are simultaneously optimized so that the duration of the required experimental conditions is maximized. In particular, consideration is given to the trade-off between a longitudinal static margin and trimming capability since it is a major concern for flight control of winged suborbital re-entry vehicles. Gross mass and launch angle of the sounding rocket are varied to obtain vehicle shapes and associated trajectories that successfully satisfy the mission requirement.

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© 2016 The Japan Society for Aeronautical and Space Sciences
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