@inproceedings{oai:jaxa.repo.nii.ac.jp:00016454,
 author = {富岡, 定毅 and 平岩, 徹夫 and 齋藤, 俊仁 and 加藤, 周徳 and 小寺, 正敏 and 長谷川, 進 and Tomioka, Sadatake and Hiraiwa, Tetsuo and Saito, Toshihito and Kato, Kanenori and Kodera, Masatoshi and Hasegawa, Susumu},
 book = {平成22年度宇宙輸送シンポジウム: 講演集録, Proceedings of Space Transportation Symposium: FY2010},
 month = {},
 note = {平成22年度宇宙輸送シンポジウム(2011年1月20-21日. 宇宙航空研究開発機構宇宙科学研究所), 相模原市, 神奈川県, Space Transportation FY2010 (January 20-21, 2011. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency(JAXA)(ISAS)), Sagamihara, Kanagawa Japan, System analysis upon a TSTO launch vehicle equipping a Rocket-Based Combined Cycle Engine was conducted, to evaluate the benefits of hypersonic air-breathing technology upon the performance of the launch vehicle. Upon the results of aerodynamic performance prediction, structure analysis as well as the supply system analysis was conducted. Though a high Isp performance of the engine system was predicted, the resulting payload capability of the launch system was found to depend highly on the airframe weight including the engine weight, and ranged from less than 1% to 4% of the take-off weight. The analysis method and primary results are herein reported, 形態: カラー図版あり, 形態: CD-ROM1枚, Physical characteristics: Original contains color illustrations, Note: One CD-ROM, 資料番号: AA0065073007},
 publisher = {宇宙航空研究開発機構宇宙科学研究所, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)},
 title = {RBCC エンジンのシステム解析の現状について},
 year = {2011}
}