Instantaneous Regression Rate Computation of Hybrid Rocket Motor Based on Fluid-Solid Coupling Technique

Yang, Yizhuo; Hu, Chunbo; Cai, Timin; Sun, Dechuan

doi:10.2514/6.2007-5350

Cited by 8 publications

(7 citation statements)

References 4 publications

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“…The advantages, such as safety, simplified throttling and shutdown, and low cost, make it suited for a broad range of application including sounding rocket, tactical rocket, space engines and launch vehicle. And over the past decade, the HRM has been widely investigated by experimental study, theoretical analysis and numerical simulation [2,13,19,20,23,24].…”

Section: Introductionmentioning

confidence: 99%

Regression rate and combustion performance investigation of aluminum metallized HTPB/98HP hybrid rocket motor with numerical simulation

Sun

Tian

et al. 2015

Aerospace Science and Technology

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Section: Introductionmentioning

confidence: 99%

Regression rate and combustion performance investigation of aluminum metallized HTPB/98HP hybrid rocket motor with numerical simulation

Sun

Tian

et al. 2015

Aerospace Science and Technology

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“…However, Liou and Lien [19] later noted that most of the previous numerical studies with existing turbulence models greatly overpredict turbulence levels. In an effort of obtaining more realistic results, several researchers have extended the previous methodology to the three-dimensional cases [20][21][22][23]. However, due to its complex physical nature of the problem, they still had to deal with the Reynolds-averaged Navier-Stokes equation (RANS)-type computations instead of seeking the direct solution of the unsteady NavierStokes equations.…”

mentioning

confidence: 99%

Large Eddy Simulation of Flow Development in Chamber with Surface Mass Injection

Lee

2009

Journal of Propulsion and Power

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Motivated by the recent experimental observation of noticeable features of dimplelike surface roughness patterns on the hybrid fuel grain, the authors investigated a cold flow in a porous chamber with surface mass injection through a large eddy simulation technique. The main purpose is to understand the role of turbulent structures in generating those irregular, isolated roughness patterns found on the fuel surface. It was noted that the structural feature of nearwall coherent vortices has been considerably altered by the application of wall injection, resulting in isolated cell-like contours of streamwise velocity distributed all over the horizontal planes close to the wall. This sudden change of contour shape is reminiscent of the roughness patterns observed in the accompanying experiment. The rapid evolution of the kinematical configuration of near-wall turbulence structures is believed to be caused by the effect of vertical momentum given at the wall as in the regression process. NomenclatureC S = model coefficient for velocity field C T = model coefficient for passive scalar h = half-channel height L x = domain size in streamwise direction L y = domain size in wall-normal direction, 2h L z = domain size in spanwise direction Pr = molecular Prandtl number p = pressure q j = residual scalar flux vector R uu = two point or autocorrelation of streamwise velocity Re h = Reynolds number based on inlet bulk velocity and half-channel height S ij = strain rate tensor, u i;j u j;i =2 T = temperature (passive scalar) T w = wall temperature t = time U b = inlet bulk velocity u = velocity component in x direction v = velocity component in y direction w = velocity component in z direction x = Cartesian coordinate in streamwise direction y = Cartesian coordinate in wall-normal direction z = Cartesian coordinate in spanwise direction t = turbulent diffusivity = filter width ij = Kronecker delta function t = turbulent viscosity ij = residual stress tensor Subscripts b = bulk mean quantity mean = averaged quantity over time and spanwise direction Superscripts h i = grid filter h i t = test filter = fluctuating component due to turbulence

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“…A convective heat feedback modelling approach was applied and results compared well with the experimental storable system, and under the usual ordnance restrictions, a design of this type can provide specific impulses of 20 s to 40 s above those of conventional solids 44 . Hybrid motors can be used exclusively or in combination with solid motors for missiles systems.…”

Section: Theoretical Modellingmentioning

confidence: 99%

“…A preliminary step towards computational fluid dynamics studies were undertaken for the 24" JIRAD hybrid rocket motor to understand flow field characteristics by applying multi-phase, multi-species combustion modelling 43 . Yang 44 , et. al.…”

Section: Combustion Instabilities In Hybrid Rocketsmentioning

confidence: 99%

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Hybrid Rocket Technology

Venugopal¹,

Rajesh²,

Ramanujachari³

2011

DSJ

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With their unique operational characteristics, hybrid rockets can potentially provide safer, lower-cost avenues for spacecraft and missiles than the current solid propellant and liquid propellant systems. Classical hybrids can be throttled for thrust tailoring, perform in-flight motor shutdown and restart. In classical hybrids, the fuel is stored in the form of a solid grain, requiring only half the feed system hardware of liquid bipropellant engines. The commonly used fuels are benign, nontoxic, and not hazardous to store and transport. Solid fuel grains are not highly susceptible to cracks, imperfections, and environmental temperature and are therefore safer to manufacture, store, transport, and use for launch. The status of development based on the experience of the last few decades indicating the maturity of the hybrid rocket technology is given in brief.

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Instantaneous Regression Rate Computation of Hybrid Rocket Motor Based on Fluid-Solid Coupling Technique

Cited by 8 publications

References 4 publications

Regression rate and combustion performance investigation of aluminum metallized HTPB/98HP hybrid rocket motor with numerical simulation

Regression rate and combustion performance investigation of aluminum metallized HTPB/98HP hybrid rocket motor with numerical simulation

Large Eddy Simulation of Flow Development in Chamber with Surface Mass Injection

Hybrid Rocket Technology

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