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

14 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
Country/TerritoryUnited States
CityKissimmee
Period15/1/515/1/9

ASJC Scopus subject areas

  • Aerospace Engineering

Fingerprint

Dive into the research topics of 'Performance evaluation of a rotating detonation engine with conical-shape tail'. Together they form a unique fingerprint.

Cite this