Study on Pulse Detonation Rocket Engine using flight test demonstrator “Todoroki II”

Shunsuke Takagi, Tomohito Morozumi, Ken Matsuoka, Jiro Kasahara, Akiko Matsuo, Ikkoh Funaki

研究成果: Conference contribution

4 被引用数 (Scopus)

抄録

A pulse detonation engine (Pulse Detonation Engine, PDE) generates a detonation wave intermittently, and obtains a thrust and work. In this research, the four cylinder pulse detonation rocket engine system “Todoroki II” was developed. The total weight of the flight test demonstrator is 32.5 kg. Moreover, the length is 1910 mm and the diameter of a combustion tube of a pipe in 800 mm is 37 mm. The launch and the recovery system for a flight test were also developed. The flight vehicle is recoveried without damage by winding system. It was proved that the flight test can be done repeatedly. In this flight test, the propellant mass flow estimated is mp=229 g/s. A time average thrust is Fave=254 N, the specific impulse of a propellant base is estimated to be Isp, PF =113 s, this specific impulse is 86 % of a ground test. The attitude of Todoroki incline to the positive direction of pitch up. The some factors of the inclination of Todoroki II are that the number of iginition different in each combustion tube and the attitude of Todoroki II launched is tilted. Considering these factors calculation results agree with experimental results in the attitude of Todoroki II.

本文言語English
ホスト出版物のタイトル50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014
出版社American Institute of Aeronautics and Astronautics Inc.
ISBN(電子版)9781624103032
DOI
出版ステータスPublished - 2014
イベント50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and exhibit 2014 - Cleveland, United States
継続期間: 2014 7月 282014 7月 30

出版物シリーズ

名前50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014

Other

Other50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and exhibit 2014
国/地域United States
CityCleveland
Period14/7/2814/7/30

ASJC Scopus subject areas

  • エネルギー工学および電力技術
  • 航空宇宙工学
  • 制御およびシステム工学
  • 電子工学および電気工学
  • 機械工学

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