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

Material type: 文書・図像類

Author: 竹腰, 正雄ほか

Publisher: 宇宙航空研究開発機構

Publication date: 2006-01-20

Material Format: Digital

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Note (General)：: A gaseous hydrogen/gaseous oxygen rocket chamber was designed to fit to a Rocket-Based-Combined-Cycle engine model, and its performances were evaluate...

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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:可変燃焼圧・可変混合比ロケットエンジンの研究
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: 2006-01-20
Publication Date (W3CDTF): 2006-01-20
Alternative Title: Research and development of ejector rocket for combined cycle engine: Research of rocket engine with variable combustion pressure and variable mixture ratio
Periodical title: 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
No. or year of volume/issue: JAXA-SP-05-010
Volume: JAXA-SP-05-010
Pages: 75-80
ISSN (Periodical Title): ISSN : 1349-113X
Text Language Code: jpn
Subject Heading: 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
Target Audience: 一般
Note (General): 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
Access Restrictions: 限定公開
Periodical Title (NCID): AA11984031
https://ci.nii.ac.jp/ncid/AA11984031
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