@inproceedings{oai:jaxa.repo.nii.ac.jp:00016203,
 author = {五十嵐, 真二 and 福地, 亜宝郎 and 山本, 研吾 and Igarashi, Shinji and Fukuchi, Aporo and Yamamoto, Kengo},
 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, A hybrid rocket engine is suitable for the reusable launch vehicle in low cost and safety. The authors study the hybrid rocket engine with a low cost fuel targeting the reusable launch vehicle like the Space Ship 2. For developing large-scale engines for the reusable launch vehicle, we conducted the hot firing tests of sub-scale hybrid rocket engines to obtain combustion characteristics of the low cost fuel. The fuel grains were multi-port type and wagon-wheel type, and the size of the grains was 160 mm in diameter and 350 mm in length, and the oxidizer was LOX. It was found that the ignition and combustion were very stable. We confirmed the burning time that more than 20-second duration was achieved., 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: AA0061856067, レポート番号: STCP-2012-067},
 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 = {低コスト燃料を用いたサブスケールハイブリッドロケットエンジンの燃焼特性},
 year = {2013}
}