著者
森 大吉郎 小野田 淳次郎 橋元 保雄 村上 卓司 白銀 博 小野島 昇
出版者
宇宙航空研究開発機構
雑誌
東京大学宇宙航空研究所報告 (ISSN:05638100)
巻号頁・発行日
vol.16, no.4, pp.1207-1221, 1980-11

To meet the severe structural requirements imposed on the tail fin of the newly developed S-520 type sounding rocket, two new concepts are adopted. The one is an aluminium honeycomb sandwich plate with carbon fibre reinforeced plastic (CFRP) facing as the structural member, and the other is a glass fibre reinforced plastic (GFRP) cover ablation plate with titanium leading edge to resist the aerodynamic heating. In this paper, research and developmental studies concerning this fin, including the design concept, model tests, aerodynamic heating tests using small solid rocket motor, and statical loading test to failure of the actual fin are presented.