WEKO3
アイテム
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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
https://jaxa.repo.nii.ac.jp/records/6247
https://jaxa.repo.nii.ac.jp/records/6247cbd95d66-474b-47fb-858c-d7feef8f6e0a
名前 / ファイル | ライセンス | アクション |
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49056016.pdf (2.8 MB)
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Item type | テクニカルレポート / Technical Report(1) | |||||
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公開日 | 2015-03-26 | |||||
タイトル | ||||||
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 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | スクラムジェットエンジン | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | エンジン試験 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | ロケットエンジン設計 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 複合サイクルエンジン | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 燃焼室 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 同軸ノズル | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 燃焼試験 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 燃焼効率 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 燃料噴射 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 噴射器 | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | scramjet engine | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | engine test | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | rocket engine design | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | combined cycle engine | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | combustion chamber | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | coaxial nozzle | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | firing test | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | combustion efficiency | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | fuel injection | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | injector | |||||
資源タイプ | ||||||
資源タイプ識別子 | http://purl.org/coar/resource_type/c_18gh | |||||
資源タイプ | technical report | |||||
その他のタイトル(英) | ||||||
その他のタイトル | Research and development of ejector rocket for combined cycle engine: Research of rocket engine with variable combustion pressure and variable mixture ratio | |||||
著者 |
竹腰, 正雄
× 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 |
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著者所属 | ||||||
宇宙航空研究開発機構 総合技術研究本部 | ||||||
著者所属 | ||||||
宇宙航空研究開発機構 総合技術研究本部 | ||||||
著者所属 | ||||||
宇宙航空研究開発機構 総合技術研究本部 | ||||||
著者所属 | ||||||
宇宙航空研究開発機構 総合技術研究本部 | ||||||
著者所属 | ||||||
宇宙航空研究開発機構 総合技術研究本部 | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency Institute of Space Technology and Aeronautics | ||||||
出版者 | ||||||
出版者 | 宇宙航空研究開発機構 | |||||
出版者(英) | ||||||
出版者 | Japan Aerospace Exploration Agency (JAXA) | |||||
書誌情報 |
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 en : 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 JAXA-SP-05-010, p. 75-80, 発行日 2006-01-20 |
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抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | 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. | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 1349-113X | |||||
書誌レコードID | ||||||
収録物識別子タイプ | NCID | |||||
収録物識別子 | AA11984031 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AA0049056016 | |||||
レポート番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | レポート番号: JAXA-SP-05-010 |