@inproceedings{oai:jaxa.repo.nii.ac.jp:00016198,
 author = {笠原, 次郎 and 坂本, 龍基 and 両角, 智人 and 柏崎, 貴司 and 藤原, 大 and 松岡, 健 and 松尾, 亜紀子 and 船木, 一幸 and Kasahara, Jiro and Sakamoto, Ryuki and Morozumi, Tomohito and Kashiwazaki, Takashi and Fujiwara, Yutaka and Matsuoka, Ken and Matsuo, Akiko and Funaki, Ikko},
 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, Thrust-measurement experiment was carried out using a four-cylinder pulse detonation rocket engine (PDRE) with a rotary valve. This PDRE used three types of gases, oxidizer (N2O), fuel (C2H4), and purge gas (He) to generate detonation wave intermittently. We used a rotary valve attached coaxially to a motor for supplying these three gases. We achieved time-averaged thrust of 258.5 N and specific impulse of 138.7 sec in the operation for 1000 msec., 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: AA0061856062, レポート番号: STCP-2012-062},
 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 = {回転バルブ式４気筒パルスデトネーションエンジン飛行試験機の研究開発},
 year = {2013}
}