Study on a four-cylinder pulse detonation rocket engine with a coaxial high frequency rotary valve

Tomohito Morozumi, Ken Matsuoka, Ryuki Sakamoto, Yutaka Fujiwara, Jiro Kasahara, Akiko Matsuo, Ikkoh Funaki

研究成果: Conference contribution

3 被引用数 (Scopus)

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. We used a rotary valve attached coaxially to a motor for supplying these three gases intermittently. 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. The oxidizer was N2O, the fuel was ethylene, and the purge gas was He. In the operation time for 1000 msec with C2H4-N2O propellant, we achieved time-averaged thrust of 258.5 N and specific impulse of 138.7 sec.

本文言語English
ホスト出版物のタイトル51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013
出版ステータスPublished - 2013
イベント51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013 - Grapevine, TX, United States
継続期間: 2013 1 72013 1 10

出版物シリーズ

名前51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013

Other

Other51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013
CountryUnited States
CityGrapevine, TX
Period13/1/713/1/10

ASJC Scopus subject areas

  • Space and Planetary Science
  • Aerospace Engineering

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