the 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
2
号
2_B
ページ
831 - 837
発行年
1966-06
抄録（英）
In this report, the dispersion of flight path of SSR Rocket due to the thrust malalignment and the stabilizing effects of spinning motion during burning are analysed. The calculational results show that the fin canting method, to set the fin blades at an angle to the axis of symmetry intead of parallel with it, is of limited usefulness because it does not give the rocket spin during the early part of burning, where it is most important, and that the method of canting vane in nozzle which gives the rocket an angular acceleration about its axis of symmetry, is more useful method than that of fin canting, because it gives the rocket spin during the early part of burning.
II.5.3 分散におよぼす旋転速度の影響(5 性能および気道)(II.関連研究)
SA0124902.pdf
(351.92KB)
