TY - GEN
T1 - Thrust measurement of rotating detonation engine by sled test
AU - Kato, Yuichi
AU - Ishihara, Kazuki
AU - Gawahara, Keita
AU - Matsuoka, Ken
AU - Kasahara, Jiro
AU - Matsuo, Akiko
AU - Funaki, Ikkoh
N1 - Funding Information:
The present RDE development 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.The fundamental device development was subsidized by a Grant-in-Aid for Scientific Research (A), No. 24246137.
Publisher Copyright:
© 2014 2014 by nagoya university. Published by the American Institute of Aeronautics and Astronautics, Inc.
PY - 2014
Y1 - 2014
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 only once ignition. Toward the practical use for rocket engine, the evaluation of thrust efficiency and the knowledge of combustion under high acceleration or multiple degrees of freedom are essential. In this study, C2H4 + O2 mixture was used as propellant. A Slide mechanism for thrust measyrement was developed, and the mechanism reduced noise and exhausted burned gas. So, the thrust history was acquired and the thrust performance was assessed.
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 only once ignition. Toward the practical use for rocket engine, the evaluation of thrust efficiency and the knowledge of combustion under high acceleration or multiple degrees of freedom are essential. In this study, C2H4 + O2 mixture was used as propellant. A Slide mechanism for thrust measyrement was developed, and the mechanism reduced noise and exhausted burned gas. So, the thrust history was acquired and the thrust performance was assessed.
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U2 - 10.2514/6.2014-4034
DO - 10.2514/6.2014-4034
M3 - Conference contribution
AN - SCOPUS:84913529370
T3 - 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014
BT - 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014
PB - American Institute of Aeronautics and Astronautics Inc.
T2 - 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and exhibit 2014
Y2 - 28 July 2014 through 30 July 2014
ER -