Kakuda Branch Office, National Aerospace Laboratory(NAL)
Kakuda Branch Office, National Aerospace Laboratory(NAL)
Kakuda Branch Office, National Aerospace Laboratory(NAL)
Kakuda Branch Office, National Aerospace Laboratory(NAL)
出版者
航空宇宙技術研究所
出版者（英）
National Aerospace Laboratory(NAL)
雑誌名
航空宇宙技術研究所報告
雑誌名(英)
Technical Report of National Aerospace Laboratory TR-530
巻
530
ページ
13
発行年
1978-03
抄録（英）
Spinning combustion tests for a 200mm-dia. class solid propellant rocket were conducted and compared with numerical results. The combustion surface obtained by the extinction test shows that the acceleration-produced burning effect is limited to the region having the angle 85.5 deg to 90 deg between the combustion surface and the acceleration vector. This angle extent was independent of the burning time and the grain configuration. The aspects of the combustion surface, together with the transient burning-rate augmentation data given by the strand experiment, were included in a model for computer programming of the predicted pressure-time diagram. The predicted pressure history and the variation of grain configuration with time show a qualitatively good comparison.
200mm径固体ロケットのスピン燃焼実験
naltr00530.pdf
(1.36MB)
