@inproceedings{oai:jaxa.repo.nii.ac.jp:00016190,
 author = {佐藤, 正喜 and 橋本, 知之 and 高田, 仁志 and 木村, 俊哉 and 小野寺, 卓郎 and 成尾, 芳博 and Sato, Masaki and Hashimoto, Tomoyuki and Takada, Satoshi and Kimura, Toshiya and Onodera, Takuo and Naruo, Yoshihiro},
 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, JAXA/ISAS has worked out a conceptual design of reusable launch vehicle for sub-orbital sounding missions, called Reusable Sounding Rocket (RSR). The RSR adopts a clustered propulsion system which is composed of 4 pump-fed rocket engines using LOX/LH2 as propellants. Each engine has the thrust of 40 kN at sea level and should have advanced features such as capability of continuous throttling from 40 % to 100 % thrust, reusability of more than 100 flights, easy inspection for short turnaround time within 24 hours and so on. In order to mitigate the risk of engine development, the technology demonstration has been initiated. The design concept of the RSR engine and the current status of technology demonstration are presented in this paper., 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: AA0061856054, レポート番号: STCP-2012-054},
 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 = {再使用観測ロケットエンジンの技術実証},
 year = {2013}
}