@techreport{oai:jaxa.repo.nii.ac.jp:00044953,
 author = {上絛, 謙二郎 and 志村, 隆 and 橋本, 亮平 and 山田, 仁 and 野坂, 正隆 and 鈴木, 峰男 and 渡辺, 光男 and 渡辺, 義明 and 長谷川, 敏 and 菊池, 正孝 and 十亀, 英司 and KAMIJO, Kenjiro and SHIMURA, Takashi and HASHIMOTO, Ryohei and YAMADA, Hitoshi and NOSAKA, Masataka and SUZUKI, Mineo and WATANABE, Mitsuo and WATANABE, Yoshiaki and HASEGAWA, Satoshi and KIKUCHI, Masataka and SOGAME, Eiji},
 month = {Jan},
 note = {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., 資料番号: NALTR0696000, レポート番号: NAL TR-696},
 title = {The Development and Study of the Turbopump System for LOX and LH2 Rocket Engine},
 year = {1982}
}