Performance Validation of a Single-Tube Pulse Detonation Rocket System

Kasahara, Jiro; Hasegawa, Akira; Nemoto, Toyoshi; Yamaguchi, Hiroyuki; Yajima, Takashi

doi:10.2514/1.37924

Cited by 55 publications

(30 citation statements)

References 32 publications

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“…For this advantage, their application as an alternative combustor in conventional rockets and air-breathing and gas turbine engines has been investigated experimentally, numerically, and theoretically (Kasahara et al [3][4][5], Sato et al. [6], Endo et al [7,8]).…”

Section: Introductionmentioning

confidence: 99%

Visualization of the non-steady state oblique detonation wave phenomena around hypersonic spherical projectile

Maeda¹,

Inada²,

Kasahara³

et al. 2011

Proceedings of the Combustion Institute

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Colloquium that describes the research topic:DETONATIONS, EXPLOSIONS AND SUPERSONIC COMBUSITON including pulse-detonation and scramjet engines. Total length of paper and method of determination:5811 words (method 1) 6. List word equivalent lengths for main text, nomenclature, references, each figure with caption, and each AbstractWe studied experimentally the shock waves and combustion waves generated by a hypersonic spherical projectile in an explosive mixture. An acetylene / oxygen mixture diluted with argon (2C 2 H 2 + 5O 2 + 7Ar) was used with various initial pressures (detonation cell sizes) to observe optically with a shadowgraph imaging system a shock-induced combustion (SIC), a stable oblique detonation wave (ODW), and a wave called a Straw Hat type consisting of a strong SIC and ODW. The criticality of stabilizing an ODW around a projectile is expressed by the ratio of the projectile diameter, d, to the cell size, λ, as d / λ = 3.63～4.84. Although the Straw Hat type wave in the vicinity of criticality is an unstable phenomena, it has been mainly observed by a single frame picture to date, so that it is difficult to discuss the time history of its wave structure. In this study, it was remarkable to directly carry out continuous optical observations using a high speed video camera which can continuously film 100 pictures with a 1 μs frame speed so as to allow an investigation of the sustaining mechanism of the unstable wave structure.Our results allowed the identification of an increase in unsteadiness in the relative distance between the projectile fronts and the transition points to an ODW as the time increased. They also showed local explosions in the SIC region near transition point transformed the ODW front upstream.(239 words)

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Section: Introductionmentioning

confidence: 99%

Visualization of the non-steady state oblique detonation wave phenomena around hypersonic spherical projectile

Maeda¹,

Inada²,

Kasahara³

et al. 2011

Proceedings of the Combustion Institute

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“…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]. With a simplified PDE setup, that is, when viscosity and heat conduction are neglected and a tube-geometry combustor is fully filled with propellant at ambient pressure and a detonation wave is initiated instantaneously, a PDRE using H 2 -O 2 propellant can achieve a specific impulse of 190 sec and an air-breathing PDE using hydrogen fuel can achieve a specific impulse of 4200 sec, as achieved in experiments by Schuer et al [26], Cooper et al [27] and…”

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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“…Many experimental, computational, and analytical works have focused on PDEs. Kasahara et al [5] fabricated and tested a pulse detonation rocket and also validated their model which predicts the thrust generated. Endo and Fujiwara [6] analyzed the performance of a straight-tube PDE fully filled with propellant, and formulated the pressure history at the thrust wall of the closed end of the PDE tube with no empirical parameters.…”

Section: Introductionmentioning

confidence: 99%

Propagation characteristics of shock waves driven by gaseous detonation waves

et al. 2010

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We experimentally investigated propagation characteristics of the shock wave driven by a gaseous detonation wave emerging from the open end of a cylindrical detonation tube. In the present study, we visualized the shock wave and exhaust flowfields using a shadowgraph optical system and we obtained peak overpressure in the tube axial direction and the continuous shape propagates with approximately sound characteristic so that the peak overpressure decreases proportional to 1/r. Eventually, the shock wave begins to attenuate more rapidly than ideal sound attenuation, which may be due to the viscous effect.

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Performance Validation of a Single-Tube Pulse Detonation Rocket System

Cited by 55 publications

References 32 publications

Visualization of the non-steady state oblique detonation wave phenomena around hypersonic spherical projectile

Visualization of the non-steady state oblique detonation wave phenomena around hypersonic spherical projectile

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

Propagation characteristics of shock waves driven by gaseous detonation waves

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