@techreport{oai:jaxa.repo.nii.ac.jp:00006008,
 author = {竹腰, 正雄 and 富岡, 定毅 and 植田, 修一 and 齋藤, 俊仁 and 泉川, 宗男 and Takegoshi, Masao and Tomioka, Sadatake and Ueda, Shuichi and Saito, Toshihito and Izumikawa, Muneo},
 month = {Nov},
 note = {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},
 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},
 year = {2006}
}