複合エンジン用エジェクターロケットの研究開発:可変燃焼圧・可変混合比ロケットエンジンの研究

• 資料種別: 文書・図像類
• タイトル: 複合エンジン用エジェクターロケットの研究開発:可変燃焼圧・可変混合比ロケットエンジンの研究
• 著者・編者: 竹腰, 正雄; 富岡, 定毅; 植田, 修一; 齋藤, 俊仁; 泉川, 宗男; Takegoshi, Masao; Tomioka, Sadatake; Ueda, Shuichi; Saito, Toshihito; Izumikawa, Muneo
• 著者標目: 竹腰, 正雄; 富岡, 定毅; 植田, 修一; 齋藤, 俊仁; 泉川, 宗男; Takegoshi, Masao; Tomioka, Sadatake; Ueda, Shuichi; Saito, Toshihito; Izumikawa, Muneo
• 出版事項: 宇宙航空研究開発機構
• 出版年月日等: 2006-01-20
• 出版年（W3CDTF）: 2006-01-20
• 並列タイトル等: Research and development of ejector rocket for combined cycle engine: Research of rocket engine with variable combustion pressure and variable mixture ratio
• タイトル（掲載誌）: 宇宙航空研究開発機構特別資料: 平成16年度総合技術研究本部宇宙領域宇宙科学研究本部合同研究成果報告書:宇宙輸送系基盤技術 = JAXA Special Publication: FY2004 Report of Joint Research Achievements of the Space Division of Institute of Aerospace Technology and Institute of Space and Astronautical Science: Basic Technologies of Space Transportation Systems
• 巻号年月日等（掲載誌）: JAXA-SP-05-010
• 掲載巻: JAXA-SP-05-010
• 掲載ページ: 75-80
• ISSN（掲載誌）: ISSN : 1349-113X
• 本文の言語コード: jpn
• 件名標目: スクラムジェットエンジン; エンジン試験; ロケットエンジン設計; 複合サイクルエンジン; 燃焼室; 同軸ノズル; 燃焼試験; 燃焼効率; 燃料噴射; 噴射器; scramjet engine; engine test; rocket engine design; combined cycle engine; combustion chamber; coaxial nozzle; firing test; combustion efficiency; fuel injection; injector
• 対象利用者: 一般
• 一般注記: A gaseous hydrogen/gaseous oxygen rocket chamber was designed to fit to a Rocket-Based-Combined-Cycle engine model, and its performances were evaluated experimentally. The rocket chamber was required to operate at a very wide operation range in terms of chamber pressure (P(sub c)) and mixture ratio (O/F); P(sub c) = 0.6 MPa & O/F = 6 for 'ramjet-mode' operation, P(sub c) = 0.6 MPa & O/F = 0.5 for a typical 'scramjet-mode' operation, and P(sub c) = 5 MPa & O/F = 7 for 'ejector-rocket-mode' operation. For stable operation, both gaseous hydrogen injectors and gaseous oxygen injectors, which were aligned co-axially, had choking point and diffuser at downstream portion. The number of the oxygen injector in use could be selected. The outer hydrogen injector showed lower discharge coefficient and lower durability against back-pressure than the inner oxygen injector. The hot-firing tests with a heat-sink type combustion chamber showed stable operation with the C* efficiency of 87 percent for the ramjet-mode operation and 83 percent for the scramjet-mode operation. The hot-firing tests with a water-cooled combustion chamber also showed stable operation with the C* efficiency of 95 percent for the ejector-rocket-mode operation.; 資料番号: AA0049056016; レポート番号: JAXA-SP-05-010
• オンライン閲覧公開範囲: 限定公開
• 掲載誌（NCID）: AA11984031; https://ci.nii.ac.jp/ncid/AA11984031
• 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）; https://irdb.nii.ac.jp
• 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