著者

庄山 直芳 藤本 浩司

出版者

一般社団法人 日本航空宇宙学会

雑誌

航空宇宙技術 (ISSN:18840477)

巻号頁・発行日

vol.19, pp.39-45, 2020 (Released:2020-01-31)

参考文献数

19

被引用文献数

1

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A concept study was performed on the spin-launch of a small orbital launch vehicle from a balloon. The small rocket is based on an existing sounding rocket SS-520, the smallest orbital rocket in the world. The increase in launch capacity was calculated by considering the velocity increment required to reach a low earth orbit. Three-dimensional trajectory analysis was performed to obtain the allowable elevation angle error to achieve an orbit insertion accuracy of 1 km in apogee altitude. A new attitude control system of the launcher hanging on a balloon, which uses a double gimbal control moment gyroscope (DCMG), was proposed to satisfy the launch safety requirement. The other issues to be addressed, including the combustion and dynamic behaviors of propellant at high altitude, the reusability of the launcher system, were also discussed.