並列タイトル等液酸・液水ロケットエンジンターボポンプシステムの研究
タイトル(掲載誌)航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-696
一般注記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
一次資料へのリンクURLhttps://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=44953&item_no=1&attribute_id=31&file_no=1
連携機関・データベース国立情報学研究所 : 学術機関リポジトリデータベース(IRDB)(機関リポジトリ)
提供元機関・データベース宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ