著者

冠 昭夫 若松 義男 志村 隆 都木 恭一郎 鳥井 義弘 KANMURI Akio WAKAMATSU Yoshio SHIMURA Takashi TOKI Kyoichiro TORII Yoshihiro

出版者

航空宇宙技術研究所

雑誌

航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-868 (ISSN:03894010)

巻号頁・発行日

vol.868, pp.33, 1985-07

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The first Japanese LOX/LH2 rocket engine (LE-5) employs a turbopump-fed gas generator cycle system. The LE-5 engine starts up in such an unique method that the power of the turbopump system is at first built up by a coolant bleed cycle followed by a gas generator cycle. A computer program for the start transient simulation has been developed and it has been utilized for analysing start-up characteristics of the LE-5 engine. The outline of the computer program and the analytical results are discussed here. The results of the analysis have been effectively used for the setting of the firing test condition and for the determination of the engine start sequence in each phases of the development. The results of the simulation are also compared with the experimental results.