@inproceedings{oai:jaxa.repo.nii.ac.jp:00016448,
 author = {笠原, 次郎 and 松岡, 健 and 江角, 元貴 and 松尾, 亜紀子 and 船木, 一幸 and Kasahara, Jiro and Matsuoka, Ken and Esumi, Motoki and Matsuo, Akiko and Funaki, Ikko},
 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, We proposed a novel rotary valve system for a pulse detonation rocket engine (PDRE). Since this valve can supply three gases (oxidizer, fuel, purge gas) into a pulse detonation tube (combustor) by using a single rotary disk, the total weight of this valve is very low. We carried out the optical and thrust measurements by using the PDRE system with the rotary valve and ethylene-oxygen propellant in order to confirm the thrust performance of the system. As a result, we confirmed the stable operation of the system over a wide range of operation frequency (40-160 Hz) and measured the time-averaged thrust. The maximum time-averaged thrust of 71.4 N and the maximum specific impulse of 232 sec were achieved at operation frequency of 160 Hz., 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: AA0065073001},
 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 = {回転バルブを用いた高周波数作動 パルスデトネーションエンジンに関する研究},
 year = {2011}
}