@inproceedings{oai:jaxa.repo.nii.ac.jp:00016176,
 author = {小室, 智幸 and 高木, 翔平 and 高橋, 政浩 and 富岡, 定毅 and 佐藤, 和雄 and 伊藤, 勝宏 and Komuro, Tomoyuki and Takagi, Shohei and Takahashi, Masahiro and Tomioka, Sadatake and Sato, Kazuo and Ito, Katsuhiro},
 book = {平成24年度宇宙輸送シンポジウム: 講演集録, Proceedings of Space Transportation Symposium: FY2012},
 month = {Jan},
 note = {平成24年度宇宙輸送シンポジウム (2013年1月17日-1月18日. 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)), 相模原市, 神奈川県, Space Transportation FY2012 (January 17-18, 2013. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, The purpose of this study is to accomplish combustion in RBCC engine operating in hypersonic flow at Mach 11 flight condition. Auxiliary injection for combustion enhancement in RBCC engine was tested experimental at JAXA-Kakuda Space Center using high enthalpy shock tunnel (HIEST). By injecting a portion of fuel besides in residual fuel in the rocket exhaust, combustion of residual hydrogen in the rocket exhaust was attained., 形態: カラー図版あり, 形態: PDF, Physical characteristics: Original contains color illustrations, Physical characteristics: PDF, 資料番号: AA0061856040, レポート番号: STCP-2012-040},
 publisher = {宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS), Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)},
 title = {ロケット-ラムジェット複合サイクルエンジンの極超音速でのスクラムモード試験},
 year = {2013}
}