Study on a rotary-valved four-cylinder pulse detonation rocket: Six degree-of-freedom flight measurement

Ken Matsuoka, Shunsuke Takagi, Jiro Kasahara, Tomohito Morozumi, Takashi Kashiwazaki, Yutaka Fujiwara, Akiko Matsuo, Ikkoh Funaki

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

8 Citations (Scopus)


We constructed a rotary-valved four-cylinder PDR system (flight vehicle) for the flight demonstration. Total length and weight of the vehicle were 1910mm and approximately 33 kg with propellant and purge gas, respectively (detonation tube inner diameter and length: 37 mm and 800 mm, respectively). We investigated the thrust performance of the PDR system and the thrust-to-weight ratio on grand test. Propellant-based specific impulse of 131 s, time-averaged thrust of 256 N and thrust-to weight ratio of 0.8 were achieved [32]. The flight test using the newly-developed launch-recovery system was proposed and carried out. The system operated perfectly, and we successfully recovered the PDR without damage. It was confirmed that the rolling by rotating the rotary valve and significant vibration by pulse detonation had a low impact on the flight. The stable PDR operation and the detonation engine thrust in real flight condition (6-degree-of-freedom condition) were validated.

Original languageEnglish
Title of host publication52nd Aerospace Sciences Meeting
PublisherAmerican Institute of Aeronautics and Astronautics Inc.
ISBN (Electronic)9781624102561
Publication statusPublished - 2014
Event52nd Aerospace Sciences Meeting 2014 - National Harbor, United States
Duration: 2014 Jan 132014 Jan 17

Publication series

Name52nd Aerospace Sciences Meeting


Other52nd Aerospace Sciences Meeting 2014
Country/TerritoryUnited States
CityNational Harbor

ASJC Scopus subject areas

  • Aerospace Engineering


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