Study on a rotary-valved four-cylinder pulse detonation rocket: Thrust measurement by ground test

Tomohito Morozumi, Ryuki Sakamoto, Takashi Kashiwazaki, Ken Matsuoka, Shunsuke Takagi, Jiro Kasahara, Akiko Matsuo, Ikkoh Funaki

研究成果: Conference contribution

抄録

Thrust measurement experiment was carried out using a four-cylinder pulse detonation rocket engine (PDRE) with a rotary valve. The PDRE uses three types of gases, oxidizer, fuel, and purge gas to generate detonation wave intermittently and produces thrust. A rotary valve attached coaxially to a motor for supplying these three gases intermittently was used. The mechanism of the rotary valve is very simple. It is built up with a top cover, a rotating disk, and a casing, and has advantage to enable high mass flow rate and high frequency operation. In this study, pulse detonation rocket (PDR) for flight tests was developed. Thrust measurement experiment by grand test was carried out to check the performance of the this PDR. The oxidizer was N<inf>2</inf>O, the fuel was C<inf>2</inf>H<inf>4</inf>, and the purge gas was He. In the operation time for 1500 msec with C<inf>2</inf>H<inf>4</inf>-N<inf>2</inf>O propellant, we achieved time-averaged thrust of 256 N and specific impulse of 130.8 sec.

本文言語English
ホスト出版物のタイトル52nd Aerospace Sciences Meeting
出版社American Institute of Aeronautics and Astronautics Inc.
ISBN(印刷版)9781624102561
出版ステータスPublished - 2014
イベント52nd Aerospace Sciences Meeting 2014 - National Harbor, United States
継続期間: 2014 1 132014 1 17

Other

Other52nd Aerospace Sciences Meeting 2014
国/地域United States
CityNational Harbor
Period14/1/1314/1/17

ASJC Scopus subject areas

  • 航空宇宙工学

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