HISAKI Project Team

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

 312
  • Rinpei Sakata, Masahiro Inada, Noboru Itouyama, Ken Matsuoka, Jiro Kasahara, Akira Kawasaki, Akiko Matsuo, Ikkoh Funaki
    Journal of Propulsion and Power 1-10 2024年6月20日  査読有り
    A coupled cylindrical rotating detonation engine (RDE) with two cylindrical RDEs (both combustors had a combustor inner diameter of 23 mm and an axial length of 30 mm) placed next to each other was tested for rocket clustering application. The objective of the experiment was to achieve two-engine synchronized initiation with a single igniter. Experiments were conducted on the inner wall of the combustors with different connecting-hole diameters and wall heights to evaluate the ignition delay time, combustion mode, and propulsion performance. The propellants were gaseous ethylene and oxygen, and experiments were conducted under constant conditions of mass flow rate ([Formula: see text]), equivalence ratio ([Formula: see text]), and backpressure (approximately 10 kPa). When the two combustion chambers were completely separated by a wall, ignition occurred with a time delay of 260 ms in the chamber without an igniter. However, when a large hole ([Formula: see text] diameter) was placed in the wall separating the two combustion chambers, synchronous initiation was successful. Synchronous initiation was also successful when the wall height was lowered (7-mm height). Under both conditions, the same level of specific impulse was achieved as for RDEs operating at the same mass flux.
  • Tomoki Sato, Kotaro Nakata, Kazuki Ishihara, Noboru Itouyama, Ken Matsuoka, Jiro Kasahara, Akira Kawasaki, Daisuke Nakata, Hikaru Eguchi, Masaharu Uchiumi, Akiko Matsuo, Ikkoh Funaki
    Combustion and Flame 264 113443-113443 2024年6月  査読有り
  • Kazuki Ishihara, Tomoki Sato, Tomoaki Kimura, Kosuke Nakajima, Kotaro Nakata, Noboru Itouyama, Akira Kawasaki, Ken Matsuoka, Koichi Matsuyama, Jiro Kasahara, Hikaru Eguchi, Daisuke Nakata, Masaharu Uchiumi, Akiko Matsuo, Ikkoh Funaki
    Journal of Spacecraft and Rockets 1-11 2024年5月28日  査読有り
    There are few experimental studies on rotating detonation engines (RDEs) with liquid propellants. This study reveals the static thrust performance of a cylindrical RDE with ethanol and liquid nitrous oxide as propellants under atmospheric pressure. This RDE had an inner diameter of 40 mm, a maximum combustor length of 230 mm, a nozzle contraction ratio of 1.7, and a nozzle expansion ratio of 9.1. Nineteen experiments were conducted at total mass flow rates of [Formula: see text], mixture ratios of 3.6–5.9, and combustion pressures of 0.35–0.46 MPa, resulting in a maximum detonation velocity of [Formula: see text] (approximately 80% of the theoretical detonation velocity, [Formula: see text]), maximum thrust at sea level of 294 N, and maximum specific impulse at sea level of 148 s. In addition, the maximum characteristic exhaust velocity, [Formula: see text], was [Formula: see text], which was 99% of the theoretical value. The characteristic length of the combustion chamber at this time was 0.15 m. Since conventional rocket combustion requires 1.57 m to achieve the same [Formula: see text] efficiency, this study shows that detonation combustion can reduce the combustor size by 88%.
  • 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
  • Maximilien Berthe, James Schalkwyk, Onur Çelik, Debdut Sengupta, Ken Fujino, Andreas Makoto Hein, Luciana Tenorio, Josué Cardoso, dos Santos, S. Peter Worden, Philip D. Mauskopf, Yasuyuki Miyazaki, Ikkoh Funaki, Shinjiro Tsuji, Piotr Fil, Kojiro Suzuki
    Progress in Aerospace Sciences, 150 (1) 2024 2024年  査読有り

MISC

 426

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

 640

共同研究・競争的資金等の研究課題

 31

産業財産権

 4