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

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

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

2 Citations (Scopus)

Abstract

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.

Original languageEnglish
Title of host publication50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014
PublisherAmerican Institute of Aeronautics and Astronautics Inc.
ISBN (Print)9781624103032
DOIs
Publication statusPublished - 2014
Event50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and exhibit 2014 - Cleveland, United States
Duration: 2014 Jul 282014 Jul 30

Other

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

Fingerprint

Pulse detonation engines
Rocket engines
Propellants
Detonation
Engine cylinders
Pipe
Recovery

ASJC Scopus subject areas

  • Energy Engineering and Power Technology
  • Aerospace Engineering
  • Control and Systems Engineering
  • Electrical and Electronic Engineering
  • Mechanical Engineering

Cite this

Takagi, S., Morozumi, T., Matsuoka, K., Kasahara, J., Matsuo, A., & Funaki, I. (2014). Study on Pulse Detonation Rocket Engine using flight test demonstrator “Todoroki II”. In 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014 American Institute of Aeronautics and Astronautics Inc.. https://doi.org/10.2514/6.2014-4033

Study on Pulse Detonation Rocket Engine using flight test demonstrator “Todoroki II”. / Takagi, Shunsuke; Morozumi, Tomohito; Matsuoka, Ken; Kasahara, Jiro; Matsuo, Akiko; Funaki, Ikkoh.

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014. American Institute of Aeronautics and Astronautics Inc., 2014.

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

Takagi, S, Morozumi, T, Matsuoka, K, Kasahara, J, Matsuo, A & Funaki, I 2014, Study on Pulse Detonation Rocket Engine using flight test demonstrator “Todoroki II”. in 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014. American Institute of Aeronautics and Astronautics Inc., 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and exhibit 2014, Cleveland, United States, 14/7/28. https://doi.org/10.2514/6.2014-4033
Takagi S, Morozumi T, Matsuoka K, Kasahara J, Matsuo A, Funaki I. Study on Pulse Detonation Rocket Engine using flight test demonstrator “Todoroki II”. In 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014. American Institute of Aeronautics and Astronautics Inc. 2014 https://doi.org/10.2514/6.2014-4033
Takagi, Shunsuke ; Morozumi, Tomohito ; Matsuoka, Ken ; Kasahara, Jiro ; Matsuo, Akiko ; Funaki, Ikkoh. / Study on Pulse Detonation Rocket Engine using flight test demonstrator “Todoroki II”. 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014. American Institute of Aeronautics and Astronautics Inc., 2014.
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