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)
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)
National Space Development Agency of Japan(NASDA)
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-696
巻
696
ページ
50
発行年
1982-01
抄録（英）
The development of a H-1 Rocket was started by the National Space Development Agency of Japan (NASDA) in 1981. The second stage of the launch vehicle uses a 10 ton thrust(in vacuum) liquid oxygen (LOX) and liquid hydrogen (LH2) pump-fed propulsion system, which has a gas generator cycle engine (LE-5). Since 1977, the National Aerospace Laboratory (NAL) and NASDA have been developing a turbopump system for the rocket engine. The turbopump system consists of a LOX turbopump, a LH2 turbopump, a gas generator and so on. In June 1980, the first turbopump system testing was conducted. Full power closed-loop operations of the turbopump system were successfully performed. The major problem in the testing was gas generator ignition troubles due to insufficient preconditioning of liquid oxygen feed lines. The present report describes the results of the turbopump system testing.
The Development and Study of the Turbopump System for LOX and LH2 Rocket Engine
naltr00696.pdf
(4.03MB)
