TY - JOUR
T1 - Thrust performance of rotary-valved four-cylinder pulse detonation rocket engine
AU - Matsuoka, Ken
AU - Sakamoto, Ryuki
AU - Morozumi, Tomohito
AU - Kasahara, Jiro
AU - Matsuo, Akiko
AU - Funaki, Ikkoh
N1 - Publisher Copyright:
© 2015 The Japan Society for Aeronautical and Space Sciences.
PY - 2015
Y1 - 2015
N2 - We designed a rotary valve for a multi-cylinder pulse detonation rocket engine (PDRE), and constructed a greatly simplified rotary-valved four-cylinder PDRE (inner diameter and length of detonation tube: 37 mm and 1,600 mm, respectively). The partial-fill effect of a propellant in a multi-cylinder PDRE under high-frequency operation was investigated. The suctioned-air fill fraction was estimated using the model of Sato et al., which is a semiempirical formula for the partial-fill effect of a propellant based on two-dimensional numerical analysis [Sato et al., Journal of Propulsion and Power, Vol. 22, No. 1, 2006, pp. 64-69]. A maximum propellant-based specific impulse of 251 s and a time-averaged thrust of 242 N were achieved using C2H4-O2 as the propellant and an operation frequency of 129.6 Hz/tube (fill pressure: 1 atm). The maximum operation frequency was 160.3 Hz/tube (641.2 Hz/all tubes).
AB - We designed a rotary valve for a multi-cylinder pulse detonation rocket engine (PDRE), and constructed a greatly simplified rotary-valved four-cylinder PDRE (inner diameter and length of detonation tube: 37 mm and 1,600 mm, respectively). The partial-fill effect of a propellant in a multi-cylinder PDRE under high-frequency operation was investigated. The suctioned-air fill fraction was estimated using the model of Sato et al., which is a semiempirical formula for the partial-fill effect of a propellant based on two-dimensional numerical analysis [Sato et al., Journal of Propulsion and Power, Vol. 22, No. 1, 2006, pp. 64-69]. A maximum propellant-based specific impulse of 251 s and a time-averaged thrust of 242 N were achieved using C2H4-O2 as the propellant and an operation frequency of 129.6 Hz/tube (fill pressure: 1 atm). The maximum operation frequency was 160.3 Hz/tube (641.2 Hz/all tubes).
KW - Pulse detonation engine
KW - Pulse detonation rocket engine
KW - Rotary valve
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U2 - 10.2322/tjsass.58.193
DO - 10.2322/tjsass.58.193
M3 - Article
AN - SCOPUS:84932632682
SN - 0549-3811
VL - 58
SP - 193
EP - 203
JO - Transactions of the Japan Society for Aeronautical and Space Sciences
JF - Transactions of the Japan Society for Aeronautical and Space Sciences
IS - 4
ER -