Performance evaluation of a rotating detonation engine with conical-shape tail

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

Research output: Chapter in Book/Report/Conference proceedingConference contribution

9 Citations (Scopus)

Abstract

A study on a rotating detonation engines (RDE) having the advantage of high frequency operation (1~100 kHz) and simple structure has been carried out in many research groups for the practical use toward a rocket engine. However, there are many unsolved parts about internal flow of a RDE, and the state of its channel exit has not been solved exactly. In this study, we used gas ethylene and gas oxygen as propellant. A slide mechanism for thrust measurement was developed. We will evaluate and the thrust performance and the state of channel exit of a RDE by the nozzle shape. We performed combustion test of a RDE with a conical-shape tail. As a results, thrust of a RDE with a conical-shape tail was achieved 101 ~ 308 N.

Original languageEnglish
Title of host publication53rd AIAA Aerospace Sciences Meeting
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624103438
DOIs
Publication statusPublished - 2015
Event53rd AIAA Aerospace Sciences Meeting, 2015 - Kissimmee, United States
Duration: 2015 Jan 52015 Jan 9

Other

Other53rd AIAA Aerospace Sciences Meeting, 2015
CountryUnited States
CityKissimmee
Period15/1/515/1/9

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ASJC Scopus subject areas

  • Aerospace Engineering

Cite this

Ishihara, K., Kato, Y., Matsuoka, K., Kasahara, J., Matsuo, A., & Funaki, I. (2015). Performance evaluation of a rotating detonation engine with conical-shape tail. In 53rd AIAA Aerospace Sciences Meeting [AIAA 2015-0630] American Institute of Aeronautics and Astronautics Inc, AIAA. https://doi.org/10.2514/6.2015-0630