@inproceedings{oai:jaxa.repo.nii.ac.jp:00017236,
 author = {藤田, 和央 and 小林, 清和 and 長谷川, 克也 and 長谷川, 宏 and 野中, 聡 and Fujita, Kazuhisa and Kobayashi, Kiyokazu and Hasegawa, Katsuya and Hasegawa, Hiroshi and Nonaka, Satoshi},
 book = {宇宙輸送シンポジウム　平成15年度, Proceedings of Space Transportation Symposium FY2003},
 month = {Apr},
 note = {The staged-combustion hybrid rocket (SCHR) engine is a new type of hybrid rocket engine, in which the primary combustion gas generated in the first-stage chamber with low oxidant/fuel ratio is perfectly burned in the second-stage chamber to achieve a high combustion efficiency. In order to actualize the SCHR engine for practical applications, it is necessary to understand the heat cycle and the combustion mechanisms, especially in the first-stage combustion chamber. From this viewpoint, the primary combustion test of the SCHR engine was conducted in the Noshiro Test Center (NTC) in December 2003. This article is a quick report of the experimental results., 資料番号: AA0047118006},
 pages = {21--24},
 publisher = {宇宙航空研究開発機構宇宙科学研究本部, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA/ISAS)},
 title = {2段燃焼型ハイブリッドロケットの燃焼特性},
 year = {2004}
}