Thrust measurement of rotating detonation engine by sled test

Yuichi Kato; Kazuki Ishihara; Keita Gawahara; Ken Matsuoka; Jiro Kasahara; Akiko Matsuo; Ikkoh Funaki

doi:10.2514/6.2014-4034

Thrust measurement of rotating detonation engine by sled test

Yuichi Kato, Kazuki Ishihara, Keita Gawahara, Ken Matsuoka, Jiro Kasahara, Akiko Matsuo, Ikkoh Funaki

Department of Mechanical Engineering

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

5 Citations (Scopus)

Abstract

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.

Original language	English
Title of host publication	50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014
Publisher	American Institute of Aeronautics and Astronautics Inc.
ISBN (Electronic)	9781624103032
DOIs	https://doi.org/10.2514/6.2014-4034
Publication status	Published - 2014
Event	50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and exhibit 2014 - Cleveland, United States Duration: 2014 Jul 28 → 2014 Jul 30

Publication series

Name	50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014

Other

Other	50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and exhibit 2014
Country	United States
City	Cleveland
Period	14/7/28 → 14/7/30

ASJC Scopus subject areas

Energy Engineering and Power Technology
Aerospace Engineering
Control and Systems Engineering
Electrical and Electronic Engineering
Mechanical Engineering

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Kato, Y., Ishihara, K., Gawahara, K., Matsuoka, K., Kasahara, J., Matsuo, A., & Funaki, I. (2014). Thrust measurement of rotating detonation engine by sled test. In 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014 (50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014). American Institute of Aeronautics and Astronautics Inc.. https://doi.org/10.2514/6.2014-4034

Thrust measurement of rotating detonation engine by sled test. / Kato, Yuichi; Ishihara, Kazuki; Gawahara, Keita; Matsuoka, Ken; Kasahara, Jiro; Matsuo, Akiko; Funaki, Ikkoh.

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014. American Institute of Aeronautics and Astronautics Inc., 2014. (50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014).

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

Kato, Y, Ishihara, K, Gawahara, K, Matsuoka, K, Kasahara, J, Matsuo, A & Funaki, I 2014, Thrust measurement of rotating detonation engine by sled test. in 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014. 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014, American Institute of Aeronautics and Astronautics Inc., 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and exhibit 2014, Cleveland, United States, 14/7/28. https://doi.org/10.2514/6.2014-4034

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title = "Thrust measurement of rotating detonation engine by sled test",

abstract = "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.",

author = "Yuichi Kato and Kazuki Ishihara and Keita Gawahara and Ken Matsuoka and Jiro Kasahara and Akiko Matsuo and Ikkoh Funaki",

note = "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.; 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and exhibit 2014 ; Conference date: 28-07-2014 Through 30-07-2014",

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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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