TY - GEN
T1 - Study on a long-time operation towards rotating detonation rocket engine flight demonstration
AU - Ishihara, Kazuki
AU - Nishimura, Junpei
AU - Goto, Keisuke
AU - Nakagami, Soma
AU - Matsuoka, Ken
AU - Kasahara, Jiro
AU - Matsuo, Akiko
AU - Funaki, Ikkoh
AU - Moriai, Hideki
AU - Mukae, Hiroto
AU - Yasuda, Kazuki
AU - Nakata, Daisuke
AU - Higashino, Kazuyuki
N1 - Funding Information:
This study was subsidized by“ Study on Innovative Detonation Propulsion Mechanism,” Research-and Development Grant Program (Engineering) form the Institute of Space and Astronatuitical Science, the Japan Aerospace Exploration Agency, a Grant-in-Aid for Scientific Research (A), No. 24246137. and the Advanced Research Program for Energy and Environmental Technologies of the New Energy and Industrial Technology Development Organization (NEDO) of Japan. The test piece and test chamber were manufactured by YASUDA-KOKI co., ltd, NAKAMURA CONSTRUCTION co., ltd and MASHINAX co., ltd.
Publisher Copyright:
© 2017 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
PY - 2017
Y1 - 2017
N2 - Study of a Rotating Detonation Engine (RDE) has been carried out in many research institutions. The RDE has the advantage of high efficiency, simple structure and short combustor length. Toward the practical use for rocket engines, the evaluation of thrust efficiency at vacuum condition is necessary. In addition, it’s necessary to find a cooling method to endure the high heat load by detonation combustion. In this study, ethylene - oxygen mixtures are used as propellant, and we applied C/C composite, which is a heat resistant material, to a RDE and carried out a long-duration combustion test at sea level. As a result, we succeeded in the long-duration rotating detonation engine combustion demonstration of 6- 10 s at sea level for the first time in the world as rocket engine use, and the maximum thrust and the maximum specific impulse were achieved 301 N and 144 s.
AB - Study of a Rotating Detonation Engine (RDE) has been carried out in many research institutions. The RDE has the advantage of high efficiency, simple structure and short combustor length. Toward the practical use for rocket engines, the evaluation of thrust efficiency at vacuum condition is necessary. In addition, it’s necessary to find a cooling method to endure the high heat load by detonation combustion. In this study, ethylene - oxygen mixtures are used as propellant, and we applied C/C composite, which is a heat resistant material, to a RDE and carried out a long-duration combustion test at sea level. As a result, we succeeded in the long-duration rotating detonation engine combustion demonstration of 6- 10 s at sea level for the first time in the world as rocket engine use, and the maximum thrust and the maximum specific impulse were achieved 301 N and 144 s.
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U2 - 10.2514/6.2017-1062
DO - 10.2514/6.2017-1062
M3 - Conference contribution
AN - SCOPUS:85017269462
T3 - AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting
BT - AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting
PB - American Institute of Aeronautics and Astronautics Inc.
T2 - 55th AIAA Aerospace Sciences Meeting
Y2 - 9 January 2017 through 13 January 2017
ER -