@techreport{oai:jaxa.repo.nii.ac.jp:00044842,
 author = {上條, 謙二郎 and 橋本, 亮平 and 志村, 隆 and 山田, 仁 and 渡辺, 光男 and 渡辺, 義明 and 長谷川, 敏 and KAMIJO, Kenjiro and HASHIMOTO, Ryohei and SHIMURA, Takashi and YAMADA, Hitoshi and WATANABE, Mitsuo and WATANABE, Yoshiaki and HASEGAWA, Satoshi},
 month = {Oct},
 note = {The development of a 10 ton thrust liquid oxygen and liquid hydrogen(LOX and LH2)rocket engine is conducted by the National Space Development Agency. The LOX/LH2 engine uses the gas-generator cycle and has dual shaft turbopums with turbines in series. The National Aerospace Laboratory has carried out the development and study of the turbopumps for the engine in co-operation with the National Space Development Agency. The present report descibes the first development and study of the LOX turbopump, which was conducted chiefly by the National Aerospace Laboratory. The LOX turbopump consists of a single stage centrifugal pump with a cavitating inducer and a single-stage two-rotor velocity compounded impulse turbine. The performance of the test turbopump, including the pump pressure rise, the pump and turbine efficiency, turbine power, etc., showed good agreement with the predicted values. The turbopump assembly and most of the components, except the gas seals, also showed good performance through out all the tests. One problem experienced with regard to the gas seals was solved by the modification of the seals. The technical data obtained in this development and study are utilized in order to make the flight type LOX turbopump., 資料番号: NALTR0588000, レポート番号: NAL TR-588},
 title = {液酸・液水ロケットエンジン用液酸ターボポンプの試作研究},
 year = {1979}
}