TY - GEN
T1 - Preliminary experiments on rotating detonation rocket engine for flight demonstration using sounding rocket
AU - Goto, Keisuke
AU - Nishimura, Junpei
AU - Higashi, Junichi
AU - Taki, Haruna
AU - Ukai, Takato
AU - Hayamizu, Yuki
AU - Kikuchi, Koyo
AU - Yamada, Taihei
AU - Watanabe, Shun
AU - Hotta, Koutaro
AU - Inakawa, Tomoya
AU - Kubota, Akiya
AU - Yamaguchi, Masato
AU - Daicho, Toshiki
AU - Kawasaki, Akira
AU - Matsuoka, Ken
AU - Kasahara, Jiro
AU - Matsuo, Akiko
AU - Funaki, Ikkoh
AU - Yasuda, Kazuki
AU - Mori, Kenta
AU - Yagihashi, Hiromitsu
AU - Nakata, Daisuke
AU - Uchiumi, Masaharu
AU - Higashino, Kazuyuki
N1 - Funding Information:
The present RDE development was subsidized by a “Study on Innovative Detonation Propulsion Mechanism,” Research-and-Development Grant Program (Engineering) from the Institute of Space and Astronautical Science, the Japan Aerospace Exploration Agency, and a “Research and Development of an Ultra-High-Thermal-Efficiency Rotating Detonation Engine with Self-Compression Mechanism,” Advanced Research Program for Energy and Environmental Technologies, the New Energy and Industrial Technology Development Organization. The fundamental device development was subsidized by a Grant-in-Aid for Scientific Research (A), No. 24246137.
Publisher Copyright:
© 2018, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2018
Y1 - 2018
N2 - Rotating detonation engine (RDE) is a promising candidate for future upper stage motor because of its high theoretical efficiency and short combustor length. Technological demonstration in space will be necessary to evaluate the performance and flight dynamics of RDE as a space propulsion system. Toward a flight test, we built an open-structure, rocket RDE-powered vehicle to measure thrust to validate a feasibility of an onboard propulsion system. We carried out 4.4 s combustion test, and achieved over 73% of ideal specific impulse above 1.1 MPa of static pressure in the RDE combustor.
AB - Rotating detonation engine (RDE) is a promising candidate for future upper stage motor because of its high theoretical efficiency and short combustor length. Technological demonstration in space will be necessary to evaluate the performance and flight dynamics of RDE as a space propulsion system. Toward a flight test, we built an open-structure, rocket RDE-powered vehicle to measure thrust to validate a feasibility of an onboard propulsion system. We carried out 4.4 s combustion test, and achieved over 73% of ideal specific impulse above 1.1 MPa of static pressure in the RDE combustor.
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U2 - 10.2514/6.2018-0157
DO - 10.2514/6.2018-0157
M3 - Conference contribution
AN - SCOPUS:85141605505
SN - 9781624105241
T3 - AIAA Aerospace Sciences Meeting, 2018
BT - AIAA Aerospace Sciences Meeting
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Aerospace Sciences Meeting, 2018
Y2 - 8 January 2018 through 12 January 2018
ER -