宇宙飛翔工学研究系

船木 一幸

フナキ イッコウ  (Ikkoh Funaki)

基本情報

所属
国立研究開発法人宇宙航空研究開発機構 宇宙科学研究所 宇宙飛翔工学研究系 教授
総合研究大学院大学 先端学術院 宇宙科学コース 教授
学位
博士(工学)(1995年3月 東京大学)

J-GLOBAL ID
200901056190267532
researchmap会員ID
1000253787

外部リンク

論文

 272
  • Yuki Murayama, Ryota Hara, Yoshiki Yamagiwa, Yuya Oshio, Hiroyuki Nishida, Ikkoh Funaki
    Journal of Evolving Space Activities 71(2) 67-77 2024年3月  査読有り
  • Yoshiki Matsunaga, Toru Takahashi, Hiroki Watanabe, Shinatora Cho, Hiroaki Kusawake, Kazuhiro Kajiwara, Fujio Kurokawa, Ikkoh Funaki
    Acta Astronautica 213 645-656 2023年10月  査読有り
  • Frank Jansen, Tommaso Andreussi, Giovanni Cesarretti, Manfred Ehresmann, Julia Grill, Georg Herdrich, Ikkoh Funaki, Nathalie Girard, Jan Thimo Grundmann, David Krejci, Hans Leiter, Frederic Masson, Volker Maiwald, Tommaso Misuri, Stephane Oriol, Antonio Piragino, Alexander Reissner, Lars Schanz
    10(1) 2023年4月17日  査読有り
  • 村山裕輝, 原亮太, 山極芳樹, 大塩裕哉, 西田浩之, 船木一幸
    日本航空宇宙学会論文集 2023年4月  査読有り
  • Kazuki Ishihara, Kentaro Yoneyama, Hiroaki Watanabe, Noboru Itouyama, Akira Kawasaki, Ken Matsuoka, Jiro Kasahara, Akiko Matsuo, Ikkoh Funaki, Kazuyuki Higashino
    Journal of Propulsion and Power 1-11 2023年2月21日  査読有り
    Rotating detonation engines (RDEs) have been actively researched around the world for application to next-generation aerospace propulsion systems because detonation combustion has theoretically higher thermal efficiency than conventional combustion. Moreover, because cylindrical RDEs have simpler combustors, further miniaturization of conventional combustors is expected. Therefore, in this study, with the aim of applying RDEs to space propulsion systems, a cylindrical RDE with a converging–diverging nozzle was manufactured; the combustor length [Formula: see text] was changed to 0, 10, 30, 50, and 200 mm; and the thrust performance and combustion mode with the different combustor lengths were compared. As a result, four combustion modes were confirmed. Detonation combustion occurred with a combustor length of [Formula: see text]: that is, a converging rotating detonation engine. The thrust performance of this engine was 94 to 100% of the theoretical rocket thrust performance, which is equivalent to the thrust performance of conventional rocket combustion generated at [Formula: see text]. This study shows that detonation combustion can significantly reduce engine weight while maintaining thrust performance.

MISC

 206

主要な書籍等出版物

 6
  • 船木 一幸, 山川 宏
    In-Tech 2012年3月 (ISBN: 9789535103394)

講演・口頭発表等

 561

共同研究・競争的資金等の研究課題

 28

産業財産権

 4