Space Technology Research Group, National Aerospace Laboratory(NAL)
Space Technology Research Group, National Aerospace Laboratory(NAL)
Space Technology Research Group, National Aerospace Laboratory(NAL)
Space Technology Research Group, National Aerospace Laboratory(NAL)
Space Technology Research Group, 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)
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-637
300-mm-diameter thrust controllable solid rocket motors were successfully fired under atmospheric conditions. Thrust magnitude control was attained by changing the flow rate of the hydrogen peroxide decomposition gas injected into the solid rocket motor. Incomplete combustion termination that occurred earlier than expected was due to the excessive heat flux irradiated from the hot surfaces of the ablative insulation liner towards the extinguished propellant surface. More effective liner material was selected through additional tests for the advanced thrust controllable motor.
推力大きさ制御型固体ロケット・モータの燃焼実験(第1報 300φ端面燃焼方式)
naltr00637.pdf
(2.09MB)
