the Institute of Space and Aeronautical Science University of Tokyo
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
826 - 830
発行年
1966-06
抄録（英）
In this report, the effects of cross wind on the dispersion of trajectory of SSR Rocket during burning are analysed. The analytical procedure is as follows; (a) Calculate the flight path angles at the end of burning for various launching angles in the case of no cross wind, (b) Calculate the flight path angles at the end of burning for various values of cross winds, (c) Comparing the results of (a) and (b), determine the effective launching angle under cross wind, which gives same flight path angle at the end of burning in the case of (a). The calculational results show that the corrective angles of launching are approximately + 0.6° for 1m/sec of head wind and -0.6°for 1Im/sec of tail wind.
II.5.2 横風による分散について(5 性能および気道)(II.関連研究)
SA0124901.pdf
(252.33KB)
