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

7 Citations (Scopus)

Abstract

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 (Print)9781624102561
Publication statusPublished - 2014
Event52nd Aerospace Sciences Meeting 2014 - National Harbor, United States
Duration: 2014 Jan 132014 Jan 17

Other

Other52nd Aerospace Sciences Meeting 2014
CountryUnited States
CityNational Harbor
Period14/1/1314/1/17

Fingerprint

Detonation
Engine cylinders
Rockets
Propellants
Demonstrations
Engines
Recovery
Gases

ASJC Scopus subject areas

  • Aerospace Engineering

Cite this

Matsuoka, K., Takagi, S., Kasahara, J., Morozumi, T., Kashiwazaki, T., Fujiwara, Y., ... Funaki, I. (2014). Study on a rotary-valved four-cylinder pulse detonation rocket: Six degree-of-freedom flight measurement. In 52nd Aerospace Sciences Meeting American Institute of Aeronautics and Astronautics Inc..

Study on a rotary-valved four-cylinder pulse detonation rocket : Six degree-of-freedom flight measurement. / Matsuoka, Ken; Takagi, Shunsuke; Kasahara, Jiro; Morozumi, Tomohito; Kashiwazaki, Takashi; Fujiwara, Yutaka; Matsuo, Akiko; Funaki, Ikkoh.

52nd Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics Inc., 2014.

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

Matsuoka, K, Takagi, S, Kasahara, J, Morozumi, T, Kashiwazaki, T, Fujiwara, Y, Matsuo, A & Funaki, I 2014, Study on a rotary-valved four-cylinder pulse detonation rocket: Six degree-of-freedom flight measurement. in 52nd Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics Inc., 52nd Aerospace Sciences Meeting 2014, National Harbor, United States, 14/1/13.
Matsuoka K, Takagi S, Kasahara J, Morozumi T, Kashiwazaki T, Fujiwara Y et al. Study on a rotary-valved four-cylinder pulse detonation rocket: Six degree-of-freedom flight measurement. In 52nd Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics Inc. 2014
Matsuoka, Ken ; Takagi, Shunsuke ; Kasahara, Jiro ; Morozumi, Tomohito ; Kashiwazaki, Takashi ; Fujiwara, Yutaka ; Matsuo, Akiko ; Funaki, Ikkoh. / Study on a rotary-valved four-cylinder pulse detonation rocket : Six degree-of-freedom flight measurement. 52nd Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics Inc., 2014.
@inproceedings{254639ddf66942469556eb3ab153c2fc,
title = "Study on a rotary-valved four-cylinder pulse detonation rocket: Six degree-of-freedom flight measurement",
abstract = "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.",
author = "Ken Matsuoka and Shunsuke Takagi and Jiro Kasahara and Tomohito Morozumi and Takashi Kashiwazaki and Yutaka Fujiwara and Akiko Matsuo and Ikkoh Funaki",
year = "2014",
language = "English",
isbn = "9781624102561",
booktitle = "52nd Aerospace Sciences Meeting",
publisher = "American Institute of Aeronautics and Astronautics Inc.",

}

TY - GEN

T1 - Study on a rotary-valved four-cylinder pulse detonation rocket

T2 - Six degree-of-freedom flight measurement

AU - Matsuoka, Ken

AU - Takagi, Shunsuke

AU - Kasahara, Jiro

AU - Morozumi, Tomohito

AU - Kashiwazaki, Takashi

AU - Fujiwara, Yutaka

AU - Matsuo, Akiko

AU - Funaki, Ikkoh

PY - 2014

Y1 - 2014

N2 - 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.

AB - 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.

UR - http://www.scopus.com/inward/record.url?scp=84938406335&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=84938406335&partnerID=8YFLogxK

M3 - Conference contribution

SN - 9781624102561

BT - 52nd Aerospace Sciences Meeting

PB - American Institute of Aeronautics and Astronautics Inc.

ER -