複合エンジン用エジェクターロケットの研究開発:複合エンジン組み込み用2連装ロケット燃焼器の設計・製作

• Material Type: 文書・図像類
• Title: 複合エンジン用エジェクターロケットの研究開発:複合エンジン組み込み用2連装ロケット燃焼器の設計・製作
• Author/Editor: 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
• Author Heading: 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
• Publication, Distribution, etc.: 宇宙航空研究開発機構
• Publication Date: 2006-11-01
• Publication Date (W3CDTF): 2006-11-01
• Alternative Title: Research and development of ejector rocket for combined cycle engine: Design and production of clustered rocket chamber for combined cycle engine
• Periodical title: 宇宙航空研究開発機構特別資料: 平成18年度 宇宙航空研究開発機構 総合技術研究本部 宇宙科学研究本部 研究成果報告書 = JAXA Special Publication: Report on Research Achievements for FY2006 Institute of Space and Astronautical Science, Institute of Aerospace Technology, Japan Aerospace Exploration Agency
• No. or year of volume/issue: JAXA-SP-06-006
• Volume: JAXA-SP-06-006
• Pages: 111-116
• ISSN (Periodical Title): ISSN : 1349-113X
• Text Language Code: jpn
• Subject Heading: ロケットラムジェット複合エンジン; エジェクタロケット; 燃焼室; インジェクタ; スクラムジェットエンジン; 性能試験; 燃焼試験; 酸素; 水素; rocket-ramjet combined-cycle engine; ejector rocket; combustion chamber; injectors; scramjet engine; performance test; combustion test; oxygen; hydrogen
• Target Audience: 一般
• Note (General): A gaseous hydrogen/gaseous oxygen rocket chamber was designed to fit in a rocket-ramjet combined cycle engine model, and its performance was evaluated experimentally. Such a rocket chamber is required to operate in a very wide operation range in terms of chamber pressure (P(sub c)) and mixture ratio (O/F). For stable operation, the injector has a choking point and a diffuser in the downstream portion. The design point of the injector is P(sub c) = 5.0 MPa, O/F = 7 when the supplying pressure of fuel and oxidizer is 7 MPa. The stable operation and 0.91 of the C* efficiency was attained in the ejector-jet/rocket mode operation at O/F = 6.5-7.5 and P(sub c) = 3-5 MPa. A stable operation and 0.93 of the C* efficiency was attained in the ramjet mode operation at O/F = 4.5-7 and P(sub c) = 0.6 MPa. The number of oxygen injectors used was variable, and stable operation was attained by supplying oxygen from two, three and four of eight injectors in the scramjet mode operation. The C* efficiency was 0.94 with four oxygen injector elements at O/F = 0.89, and 0.92 with three oxygen injector elements at O/F = 0.49. No thermal damage was observed in the all operating mode with a flush face injector. Since it was confirmed that the rocket chamber and the injector was able to be operated with stability in the all operating mode, a clustered rocket chamber to embed to the combined cycle engine was fabricated in FY2005.; 資料番号: AA0049500024; レポート番号: JAXA-SP-06-006
• Source: https://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=6008&item_no=1&attribute_id=31&file_no=1
• Access Restrictions: 限定公開
• Data Provider (Database): 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
• Original Data Provider (Database): 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