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 language | English |
|---|---|
| Title of host publication | Proceedings of the International Astronautical Congress, IAC |
| Publisher | International Astronautical Federation, IAF |
| Pages | 7529-7534 |
| Number of pages | 6 |
| Volume | 10 |
| ISBN (Print) | 9781634399869 |
| Publication status | Published - 2014 |
| Event | 65th International Astronautical Congress 2014: Our World Needs Space, IAC 2014 - Toronto, Canada Duration: 2014 Sep 29 → 2014 Oct 3 |
Other
| Other | 65th International Astronautical Congress 2014: Our World Needs Space, IAC 2014 |
|---|---|
| Country | Canada |
| City | Toronto |
| Period | 14/9/29 → 14/10/3 |
Fingerprint
ASJC Scopus subject areas
- Space and Planetary Science
- Aerospace Engineering
- Astronomy and Astrophysics
Cite this
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 proceeding › Conference contribution
}
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 -