Institute of Space and Aeronautical Science, University of Tokyo
Institute of Space and Aeronautical Science, University of Tokyo
Institute of Space and Aeronautical Science, University of Tokyo
出版者
東京大学宇宙航空研究所
雑誌名
東京大学宇宙航空研究所報告
巻
16
号
4_A
ページ
1207 - 1221
発行年
1980-11
抄録（英）
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.
<論文>S-520ロケット用尾翼の試作
SA0125912.pdf
(756.75KB)
