@techreport{oai:jaxa.repo.nii.ac.jp:00006247,
 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 = {Jan},
 note = {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},
 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},
 year = {2006}
}