Study on a Rotary-Valved Four-Cylinder Pulse Detonation Rocket: Six Degree-of-Freedom Flight Measurement

Matsuoka, K.; Takagi, Shunsuke; Kasahara, Jiro; Morozumi, Tomohito; Kashiwazaki, Takashi; Fujiwara, Y.; Matsuo, Akiko; Funaki, Ikkoh

doi:10.2514/6.2014-1319

Cited by 6 publications

(3 citation statements)

References 22 publications

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“…Propellantbased specific impulse of 130.8 s, time-averaged thrust of 256 N and thrust-to weight ratio of 0.8 were achieved. Moreover, the flight test using the newly-developed launch-recovery system was carred out [24]. The newlydeveloped launch-recovery system operated perfectly, and we successfully recovered the PDR without damage.…”

Section: Discussionmentioning

confidence: 97%

“…Six degree-of-freedom flight measurement of the PDR was investigated by Matsuoka et al 24 . The newlydeveloped launch-recovery system operated perfectly, and the PDR was successfully recovered without damage.…”

Section: Flight Testmentioning

confidence: 99%

“…The rolling by rotation of the rotary valve and the significant vibration by intermittent detonation was not confirmed and the detonation engine thrust was validated in real flight condition (6-degree-of-freedom condition). The timeaveraged thrust was estimated at F exp = 237 N, and the propellant-based experimental specific impulse was estimated at 106 s [24](81% of the ground test). Fig.11 shows the PDR in flight.…”

Section: Flight Testmentioning

confidence: 99%

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Study on a Rotary-Valved Four-Cylinder Pulse Detonation Rocket : Thrust Measurement by Ground Test

Morozumi

Sakamoto

Kashiwazaki

et al. 2014

52nd Aerospace Sciences Meeting

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Thrust measurement experiment was carried out using a four-cylinder pulse detonation rocket engine (PDRE) with a rotary valve. The PDRE uses three types of gases, oxidizer, fuel, and purge gas to generate detonation wave intermittently and produces thrust. A rotary valve attached coaxially to a motor for supplying these three gases intermittently was used. The mechanism of the rotary valve is very simple. It is built up with a top cover, a rotating disk, and a casing, and has advantage to enable high mass flow rate and high frequency operation. In this study, pulse detonation rocket (PDR) for flight tests was developed. Thrust measurement experiment by grand test was carried out to check the performance of the this PDR. The oxidizer was N 2 O, the fuel was C 2 H 4 , and the purge gas was He. In the operation time for 1500 msec with C 2 H 4 -N 2 O propellant, we achieved time-averaged thrust of 256 N and specific impulse of 130.8 sec. Nomenclaturef D = detonation generating frequency f exp = experimental operation frequency f M = motor operation frequency f PDE = 1 PDE cycle frequency per tube I sp = propellant-based experimental specific impulse m i = purge gas mass flow rate m p = propellant mass flow rate P exp = oxidizer exhaust pressure (pressure between rotary valve and detonation tube) p i = purge gas supply pressure p p = propellant supply pressure R = gas constant T = temperature t ope = operation time V = volume  = equivalent ratio  p = propellant fill fraction

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Section: Discussionmentioning

confidence: 97%

Section: Flight Testmentioning

confidence: 99%

Section: Flight Testmentioning

confidence: 99%

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Study on a Rotary-Valved Four-Cylinder Pulse Detonation Rocket : Thrust Measurement by Ground Test

Morozumi

Sakamoto

Kashiwazaki

et al. 2014

52nd Aerospace Sciences Meeting

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The Experimental Study about the Effect of Operating Conditions on Multi-tube Pulse Detonation Engine Performance

Kim

Han

Choi

2018

JASS

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Investigation on the Time Error of Detonation Acoustic in Process of Formation and Propagation

Xu¹,

Wang²,

Hu³

et al. 2018

International Journal of Turbo &Amp; Jet-Engines

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The time error of detonation acoustic in process of detonation formation and propagation in a multi-cycle gas-liquid two-phase pulsed detonation engine is experimentally investigated. Results from the tests show that before the detonation wave escapes through the open-end of PDE tube, the maximum average arrival time error of detonation acoustic is achieved in the process of overdriven detonation. After detonation wave exists of PDE tube, arrival time error at 0 deg is greater than the other directivity angles in all distances and increases dramatically first and then almost stays at a certain value. The filling fraction has a major impact on the time error of detonation acoustic. With filling fraction increasing, there are increases in arrival time error and interval time error. Arrival time error with the highest filling fraction at 30 deg is much greater than other filling fraction. The convergent nozzle exhibits a marked suppression in the time error of detonation acoustic, where the maximum reductions of 62.02 percent and 56.13 percent are obtained in arrival time error and interval time error respectively.

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Study on a Rotary-Valved Four-Cylinder Pulse Detonation Rocket: Six Degree-of-Freedom Flight Measurement

Cited by 6 publications

References 22 publications

Study on a Rotary-Valved Four-Cylinder Pulse Detonation Rocket : Thrust Measurement by Ground Test

Study on a Rotary-Valved Four-Cylinder Pulse Detonation Rocket : Thrust Measurement by Ground Test

The Experimental Study about the Effect of Operating Conditions on Multi-tube Pulse Detonation Engine Performance

Investigation on the Time Error of Detonation Acoustic in Process of Formation and Propagation

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