Pulse detonation propulsion: challenges, current status, and future perspective

Roy, Gabriel D.; Frolov, S.M.; Борисов, А. А.; Netzer, David W.

doi:10.1016/j.pecs.2004.05.001

Cited by 762 publications

(292 citation statements)

References 59 publications

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“…Detonation waves have been studied for many years due to their potential applications in hypersonic propulsion systems, see Kailasanath (2003) and Roy et al (2004). Among the potential applications is the use of oblique detonation wave in continuous detonation wave engines and ram accelerators (Nettleton 2000).…”

Section: Introductionmentioning

confidence: 99%

Numerical study on unstable surfaces of oblique detonations

2014

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In this study, the onset of cellular structure on oblique detonation surfaces is investigated numerically using a one-step irreversible Arrhenius reaction kinetic model. Two types of oblique detonations are observed from the simulations. One is weakly unstable characterized by the existence of a planar surface, and the other is strongly unstable characterized by the immediate formation of the cellular structure. It is found that a high degree of overdrive suppresses the formation of cellular structures as confirmed by the results of many previous studies. However, the present investigation demonstrates that cellular structures also appear with degree of overdrive of 2.06 and 2.37, values much higher than ∼1.8 suggested previously in the literature for the critical value defining the instability boundary of oblique detonations. This contradiction could be explained by the use of differently shaped walls, a straight wall used in this study and a custom-designed curved wedge system so as to induce straight oblique detonations in previous studies. Another possible reason could be due to the low and possibly insufficient resolution used in previously published studies. Hence, simulations with different grid sizes are also performed to examine the effect of resolution on the numerical solutions. Using the present results, analysis also shows that although the characteristic lengths of unstable surfaces are different when the incident Mach number changes, these length scales are proportional to tangential velocities. Hence, the interior time determined by the overdrive degree is identified, and its limitation as the instability parameter is discussed.

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Section: Introductionmentioning

confidence: 99%

Numerical study on unstable surfaces of oblique detonations

2014

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“…In recent years, the potential application of detonation waves in hypersonic propulsion systems has been widely explored, see Kailasanath (2003) and Roy et al (2004). One kind of detonation propulsion utilizes the oblique detonation wave, which is the basis of oblique detonation wave engines (ODWE) and Ram Accelerators (Nettleton 2000).…”

Section: Introductionmentioning

confidence: 99%

On the transition pattern of the oblique detonation structure

2012

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Oblique detonation waves are simulated to study the evolution of their morphology as gasdynamic and chemical parameters are varied. Although two kinds of transition pattern have previously been observed, specifically an abrupt transition and a smooth one, the determining factors for the transition pattern are still unclear. Numerical results show that the transition pattern is influenced by the inflow Mach number, chemical activation energy and heat release. Despite the fact that these parameters were known to influence the detonation instability, the transition pattern variation cannot be predicted according to the instability criterion. In this study, the difference in the oblique shock and detonation angles is proposed as the criterion to determine the transition pattern with the aid of shock-polar analysis. It is found that the smooth transition will appear when the angle difference is small, while the abrupt transition will occur when the difference is large. The shift from the smooth transition to the abrupt transition occurs when the angle difference is about 15 • -18 • . The previously proposed criterion using the characteristic time ratio is also examined and compared with the present angle difference criterion, and the latter is proved to provide better results.

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“…A pulse detonation engine (PDE) is such a typical heat engine. A PDE can obtain nearly constant thrust and perform mechanical work by the generation of a high-frequency detonation wave [5][6][7][8][9][10][11][12][13][14][15][16][17][18]. The PDEs are classified as air-breathing PDEs [19][20][21][22] or pulse detonation rocket engines (PDREs) [23][24][25].…”

Section: Introductionmentioning

confidence: 99%

Optical and thrust measurement of a pulse detonation combustor with a coaxial rotary valve

Matsuoka

Esumi

Ikeguchi

et al. 2012

Combustion and Flame

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We developed a rotary valve for a pulse detonation engine (PDE), and confirmed its basic characteristics and performance. In a square cross-section combustor, we visualized a multi-shot of a pulse detonation rocket engine (PDRE) cycle at an operation frequency of 160 Hz by using a high-speed camera (time resolution: 3.33 μsec, space resolution: 0.4 mm) and a Schlieren method.The propellant filling process and the purge process were confirmed, and each process was modeled.Moreover, we confirmed the processes of detonation wave generation and burned gas blowdown. In addition, we investigated the impact of shortening the passage width of a combustor and negative-time ignition (ignition time is earlier than the end-time of the propellant filling process) on the deflagration-to-detonation transition (DDT) distance and time. The DDT distance did not depend on the passage width of a combustor and decreased under the negative-time ignition condition. With a passage width of 20 mm, the DDT distance decreased by 22% under the negative-time ignition condition to a minimum value (76 ± 8 mm). The DDT time from spark time reached a minimum value (69 ± 14 μsec) under the condition of a passage width of 10 mm and negative-time ignition.The detonation initiation time and the DDT distance were represented by the time until the flame expanded toward the tube-axis one-dimensionally from ignition (characteristic time). We also carried out thrust measurement using a PDRE system composed of a circular cross-section combustor and the newly developed valve. We obtained a stable time-averaged thrust in a wide range of operation frequency (40 Hz -160 Hz) and confirmed the increase of specific impulse due to a partial-fill effect.

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Pulse detonation propulsion: challenges, current status, and future perspective

Cited by 762 publications

References 59 publications

Numerical study on unstable surfaces of oblique detonations

Numerical study on unstable surfaces of oblique detonations

On the transition pattern of the oblique detonation structure

Optical and thrust measurement of a pulse detonation combustor with a coaxial rotary valve

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