Flight Validation of a Rotary-Valved Four-Cylinder Pulse Detonation Rocket

Matsuoka, K.; Morozumi, Tomohito; Takagi, Syunsuke; Kasahara, Jiro; Matsuo, Akiko; Funaki, Ikkoh

doi:10.2514/1.b35739

Cited by 26 publications

(4 citation statements)

References 18 publications

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“…The U.S. Air Force Research Laboratory conducted a flight test with a PDE by using a modified Long E-Z aircraft equipped with a PDE developed by them [1]. Kasahara's team at the University of Tsukuba (2009) and Nagoya University (2015) exhibited single and quad-tube rocket-type PDEs via ground and flight demonstrations [2,3]. In 2011, General Electric conducted a performance test of a gas turbine system based on a pulse detonation combustor [4].…”

Section: Introductionmentioning

confidence: 99%

Experimental Investigation of Detonation Propagation Modes and Thrust Performance in a Small Rotating Detonation Engine Using C2H4/O2 Propellant

2021

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A small rotating detonation engine (RDE) model and the corresponding experimental setup were constructed for the experimental investigation of the detonation propagation characteristics and thrust performance of a circular RDE. Experiments were conducted at a range of 0.3–2.5 equivalence ratio with a total mass flow rate of less than 180.0 g/s using a C2H4/O2 mixture. Irregularly unstable detonative combustion occurs immediately after the detonation initiation, which includes initiation, propagation, decaying, and the merging of detonation waves. Following this, periodically unsteady detonative combustion occurs in the circular channel, resulting in the stable operation of the RDE. During stable operation, two detonation waves are predominant, rotating along the wall at a speed lower than the Chapman–Jouguet (CJ) detonation speed. The characteristic velocity efficiency is approximately 73% on average. The low characteristic velocity efficiency is presumed to be caused by the unoptimized combustion channel and the poor mixing efficiency owing to the two-dimensional injector configuration. The effect of the RDE component design and the RDE flow field characteristics need to be further investigated for improving the performance of the RDE.

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Section: Introductionmentioning

confidence: 99%

Experimental Investigation of Detonation Propagation Modes and Thrust Performance in a Small Rotating Detonation Engine Using C2H4/O2 Propellant

2021

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“…The direct measurement of real moving motion of a RDEpowered system can evaluate the total system's acceleration that conventional stational load-cell measurements [13,15,16,18,19,21,22] did not capture. Although such a direct measurement of system's acceleration has been conducted in a pulse detonation engine (PDE) rocket system with a vertical flight test [23], RDE is at the stage of feasibility study of a RDE-powered small flight demonstrator [24]. Because there is no knowledge of any existing RDE system demonstration worldwide, it is important to evaluate steady RDE system operation and the system's acceleration from real moving motion to validate generated thrust performance in semipractical propulsion systems, based on the first principle that thrust can accelerate an object.…”

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confidence: 99%

Thrust Validation of Rotating Detonation Engine System by Moving Rocket Sled Test

Goto¹,

Kato²,

Ishihara³

et al. 2021

Journal of Propulsion and Power

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This Paper presents the results of a rotating detonation engine rocket sled test demonstration on a 127 mm gauge rail at 100 m long high-speed running track test equipment to evaluate the thrust performance of a stand-alone rotating detonation engine propulsion system. The developed sled test demonstrator contained all onboard subsystems, including engine, gas cylinders, valves, controller, and a data logger. The sled test demonstrator successfully generated thrust, and three or four detonation waves of 1460 to 1800 m∕s were observed during the 2.0 s burn time. The measured specific impulse in the sled test was 144 s as estimated from the acceleration of the demonstrator and the mass decrease in the onboard cylinders. The test results were compared with the data from a laboratory-stand firing test using a load cell, and the specific impulses of the sled test were found to be comparable to the results of the stand firing test.

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“…Kailasanath [1,2], Wolanski [3], and Li et al [4] widely reviewed applications and presented research developments in the area of detonative propulsion. System-level studies of a pulse detonation rocket conducted by Kasahara et al [6] and Matsuoka et al [7] validated detonative propulsion system performance with a sliding test [6] and vertical-flight test [7]. Compared to a pulse detonation engine (PDE), a rotating detonation engine (RDE) uses one or more detonation waves that continuously circle around its annular chamber to generate thrust.…”

mentioning

confidence: 99%

“…The propulsive performance of RDE and PDE have been widely investigated by many institutions [6,7,9,[12][13][14][15][16][17][18][19][20][21][22][23]29,30]. Kindracki et al [12] measured the thrust and specific impulse of RDE under 0.5 bar.…”

mentioning

confidence: 99%

Propulsive Performance and Heating Environment of Rotating Detonation Engine with Various Nozzles

Goto¹,

Nishimura²,

Kawasaki³

et al. 2019

Journal of Propulsion and Power

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Flight Validation of a Rotary-Valved Four-Cylinder Pulse Detonation Rocket

Cited by 26 publications

References 18 publications

Experimental Investigation of Detonation Propagation Modes and Thrust Performance in a Small Rotating Detonation Engine Using C2H4/O2 Propellant

Experimental Investigation of Detonation Propagation Modes and Thrust Performance in a Small Rotating Detonation Engine Using C2H4/O2 Propellant

Thrust Validation of Rotating Detonation Engine System by Moving Rocket Sled Test

Propulsive Performance and Heating Environment of Rotating Detonation Engine with Various Nozzles

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