Flight demonstration of a pulse detonation rocket system todoroki II

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

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

Abstract

We constructed a rotary-valved four-cylinder pulse detonation rocket system (Todoroki II) for the flight demonstration. The total length and weight of the vehicle were 1910 mm and approximately 32.5 kg with propellant and purge gas, respectively (detonation tube inner diameter and length: 36 mm and 805 mm, respectively). We investigated the thrust performance of Todoroki II and the thrust-to-weight ratio on grand test. A propellant-based specific impulse of 131 s, a time-averaged thrust of 256 N and a thrust-to weight ratio of 0.8 were achieved. The flight test using the newly-developed launch-recovery system was carried out. The system operated perfectly, and we successfully recovered the Todoroki II 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 pulse detonation operation and the detonation engine thrust in real flight condition (6-degree-of-freedom condition) were validated.

Original languageEnglish
Title of host publicationProceedings of the International Astronautical Congress, IAC
PublisherInternational Astronautical Federation, IAF
Pages7529-7534
Number of pages6
Volume10
ISBN (Print)9781634399869
Publication statusPublished - 2014
Event65th International Astronautical Congress 2014: Our World Needs Space, IAC 2014 - Toronto, Canada
Duration: 2014 Sep 292014 Oct 3

Other

Other65th International Astronautical Congress 2014: Our World Needs Space, IAC 2014
CountryCanada
CityToronto
Period14/9/2914/10/3

Fingerprint

Detonation
Rockets
detonation
rockets
thrust
Demonstrations
flight
pulses
propellants
Propellants
flight conditions
specific impulse
flight tests
Engine cylinders
engines
vibration
engine
vehicles
degrees of freedom
recovery

ASJC Scopus subject areas

  • Space and Planetary Science
  • Aerospace Engineering
  • Astronomy and Astrophysics

Cite this

Matsuoka, K., Takagi, S., Kasahara, J., Morozumi, T., Matsuo, A., & Funaki, I. (2014). Flight demonstration of a pulse detonation rocket system todoroki II. In Proceedings of the International Astronautical Congress, IAC (Vol. 10, pp. 7529-7534). International Astronautical Federation, IAF.

Flight demonstration of a pulse detonation rocket system todoroki II. / Matsuoka, Ken; Takagi, Shunsuke; Kasahara, Jiro; Morozumi, Tomohito; Matsuo, Akiko; Funaki, Ikkoh.

Proceedings of the International Astronautical Congress, IAC. Vol. 10 International Astronautical Federation, IAF, 2014. p. 7529-7534.

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

Matsuoka, K, Takagi, S, Kasahara, J, Morozumi, T, Matsuo, A & Funaki, I 2014, Flight demonstration of a pulse detonation rocket system todoroki II. in Proceedings of the International Astronautical Congress, IAC. vol. 10, International Astronautical Federation, IAF, pp. 7529-7534, 65th International Astronautical Congress 2014: Our World Needs Space, IAC 2014, Toronto, Canada, 14/9/29.
Matsuoka K, Takagi S, Kasahara J, Morozumi T, Matsuo A, Funaki I. Flight demonstration of a pulse detonation rocket system todoroki II. In Proceedings of the International Astronautical Congress, IAC. Vol. 10. International Astronautical Federation, IAF. 2014. p. 7529-7534
Matsuoka, Ken ; Takagi, Shunsuke ; Kasahara, Jiro ; Morozumi, Tomohito ; Matsuo, Akiko ; Funaki, Ikkoh. / Flight demonstration of a pulse detonation rocket system todoroki II. Proceedings of the International Astronautical Congress, IAC. Vol. 10 International Astronautical Federation, IAF, 2014. pp. 7529-7534
@inproceedings{548a05c33ee348a080d8a651b02bcef6,
title = "Flight demonstration of a pulse detonation rocket system todoroki II",
abstract = "We constructed a rotary-valved four-cylinder pulse detonation rocket system (Todoroki II) for the flight demonstration. The total length and weight of the vehicle were 1910 mm and approximately 32.5 kg with propellant and purge gas, respectively (detonation tube inner diameter and length: 36 mm and 805 mm, respectively). We investigated the thrust performance of Todoroki II and the thrust-to-weight ratio on grand test. A propellant-based specific impulse of 131 s, a time-averaged thrust of 256 N and a thrust-to weight ratio of 0.8 were achieved. The flight test using the newly-developed launch-recovery system was carried out. The system operated perfectly, and we successfully recovered the Todoroki II 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 pulse detonation 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 Akiko Matsuo and Ikkoh Funaki",
year = "2014",
language = "English",
isbn = "9781634399869",
volume = "10",
pages = "7529--7534",
booktitle = "Proceedings of the International Astronautical Congress, IAC",
publisher = "International Astronautical Federation, IAF",

}

TY - GEN

T1 - Flight demonstration of a pulse detonation rocket system todoroki II

AU - Matsuoka, Ken

AU - Takagi, Shunsuke

AU - Kasahara, Jiro

AU - Morozumi, Tomohito

AU - Matsuo, Akiko

AU - Funaki, Ikkoh

PY - 2014

Y1 - 2014

N2 - We constructed a rotary-valved four-cylinder pulse detonation rocket system (Todoroki II) for the flight demonstration. The total length and weight of the vehicle were 1910 mm and approximately 32.5 kg with propellant and purge gas, respectively (detonation tube inner diameter and length: 36 mm and 805 mm, respectively). We investigated the thrust performance of Todoroki II and the thrust-to-weight ratio on grand test. A propellant-based specific impulse of 131 s, a time-averaged thrust of 256 N and a thrust-to weight ratio of 0.8 were achieved. The flight test using the newly-developed launch-recovery system was carried out. The system operated perfectly, and we successfully recovered the Todoroki II 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 pulse detonation 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 pulse detonation rocket system (Todoroki II) for the flight demonstration. The total length and weight of the vehicle were 1910 mm and approximately 32.5 kg with propellant and purge gas, respectively (detonation tube inner diameter and length: 36 mm and 805 mm, respectively). We investigated the thrust performance of Todoroki II and the thrust-to-weight ratio on grand test. A propellant-based specific impulse of 131 s, a time-averaged thrust of 256 N and a thrust-to weight ratio of 0.8 were achieved. The flight test using the newly-developed launch-recovery system was carried out. The system operated perfectly, and we successfully recovered the Todoroki II 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 pulse detonation 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=84938283304&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=84938283304&partnerID=8YFLogxK

M3 - Conference contribution

SN - 9781634399869

VL - 10

SP - 7529

EP - 7534

BT - Proceedings of the International Astronautical Congress, IAC

PB - International Astronautical Federation, IAF

ER -