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 Jan 1
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

Access to Document

10.2514/6.2014-4034

Fingerprint Dive into the research topics of 'Thrust measurement of rotating detonation engine by sled test'. Together they form a unique fingerprint.

Cite this

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

@inproceedings{047b3bed172e42059081c22254ef61ee,

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",

year = "2014",

month = jan,

day = "1",

doi = "10.2514/6.2014-4034",

language = "English",

series = "50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014",

publisher = "American Institute of Aeronautics and Astronautics Inc.",

booktitle = "50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014",

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

}

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

PY - 2014/1/1

Y1 - 2014/1/1

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.

UR - http://www.scopus.com/inward/record.url?scp=84913529370&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=84913529370&partnerID=8YFLogxK

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 -