@inproceedings{oai:jaxa.repo.nii.ac.jp:00017429,
 author = {藤田, 和央 and 野中, 聡 and 小川, 博之 and 中島, 俊 and 秋葉, 鐐二郎 and 山本, 洋一 and 山本, 研吾 and Fujita, Kazuhisa and Nonaka, Satoshi and Ogawa, Hiroyuki and Nakajima, Takashi and Akiba, Ryojiro and Yamamoto, Yoichi and Yamamoto, Kengo},
 book = {宇宙輸送シンポジウム　平成13年度, Proceedings of Space Transportation Symposium FY2001},
 month = {Apr},
 note = {Preliminary assessment of a staged-combustion hybrid rocket engine is done, and its application to a micro-satellite launching rocket is studied. The staged-combustion hybrid engine is based on a new concept of two-stage combustion, which has advantages of propellant flexibility, low cost, operation safety, high performance, and low environmental pollution. A case study has shown that an SS520-class sounding rocket equipped with the staged-combustion hybrid engine for the 1st stage is capable of launching a 10-kg-class satellite to LEO., 資料番号: AA0033392001},
 pages = {1--4},
 publisher = {宇宙科学研究所, The Institute of Space and Astronautical Science (ISAS)},
 title = {2段燃焼型ハイブリッドエンジンの検討},
 year = {2002}
}