@inproceedings{oai:jaxa.repo.nii.ac.jp:00016612,
 author = {小室, 智幸 and 伊藤, 勝宏 and 佐藤, 和雄 and 丹野, 英幸 and 高橋, 政浩 and 重松, 一真 and 松尾, 亜紀子 and Komuro, Tomoyuki and Ito, Katsuhiro and Sato, Kazuo and Tanno, Hideyuki and Takahashi, Masahiro and Shigematsu, Kazuma and Matsuo, Akiko},
 book = {宇宙輸送シンポジウム: 講演集録, Proceedings of Space Transportation Symposium},
 month = {Jan},
 note = {平成21年度宇宙輸送シンポジウム(2010年1月14日-15日, 宇宙航空研究開発機構宇宙科学研究本部), Space Transportation Symposium (January 14-15, 2010. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency(JAXA)),  Sagamihara, Kanagawa Japan, The combustion gas jet device that used the detonation tube to simulate the rocket exhaust of the combined cycle engine was made, and the characteristic was examined. Shortening the examination time and the decrease in pressure were observed in the Injector though the Plateau area was obtained in the detonation tube exit. Still, a constant pressure is obtained of about 2msec. The combined cycle engine examination at the HIEST is scheduled to be executed with this device., 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: AA0064741042},
 publisher = {宇宙航空研究開発機構宇宙科学研究本部, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)},
 title = {高温衝撃風洞によるロケット複合エンジン実験手法の研究},
 volume = {平成21年度},
 year = {2010}
}