Coupled simulation of fluid flow and propellant burning surface regression in a solid rocket motor

Li, Qiang; He, Guoqiang; Liu, Peijin; Li, Jiang

doi:10.1016/j.compfluid.2014.01.028

Cited by 16 publications

(10 citation statements)

References 20 publications

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“…These results indicate that the relative errors of the interpolation scheme presented in this paper are allowable for engineering applications. The calculated relative error is comparable with that reported in [11] where the same interpolation scheme was employed for the three-dimensional volume mesh data interpolation. This finding indicates that the presented interpolation scheme is robust and adaptable, although it is quite simple.…”

Section: Numerical Simulationssupporting

confidence: 84%

“…Given that the interior nodes of fluid subdomain are intact, which may give rise to mesh skewness and distortion, fluid volume mesh smooth is necessary. In this study, the local volume mesh smoothing and the corresponding volume data interpolation scheme presented in [11] are used.…”

Section: Coupling Proceduresmentioning

confidence: 99%

“…The set of governing equations for the compressible viscous flow in the ALE formulation can be expressed as [8][9][10][11] ∂ ∂t…”

Section: Fluid Subdomainmentioning

confidence: 99%

See 2 more Smart Citations

Fluid–solid coupled simulation of the ignition transient of solid rocket motor

Liu

2015

Acta Astronautica

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Section: Numerical Simulationssupporting

confidence: 84%

Section: Coupling Proceduresmentioning

confidence: 99%

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Fluid–solid coupled simulation of the ignition transient of solid rocket motor

Liu

2015

Acta Astronautica

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“…The LSM processes geometry using implicit representation; that is, an ℝ-dimensional geometry is represented by an isosurface in ℝ + 1 dimensional space. Implicit representation provides the capability to handle complex topological changes but also requires a larger data structure and more computation [11]. Full three-dimensional (3D) LSM burnback simulation may consume hours of computation time.…”

Section: Introductionmentioning

confidence: 99%

Combined Acceleration Methods for Solid Rocket Motor Grain Burnback Simulation Based on the Level Set Method

Wei

Bao

Liu

et al. 2018

International Journal of Aerospace Engineering

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A detailed study of a set of combined acceleration methods is presented with the objective of accelerating the solid rocket motor grain burnback simulation based on the level set method. Relevant methods were improved by making use of unique characteristics of the grains, and graphical processing unit (GPU) parallelization is utilized to perform the computationally intensive operations. The presented flow traced the expansion of burning surfaces, and then Boolean operations were applied on the resulting surfaces to extract various geometric metrics. The initial signed distance field was built by an improved distance field generating method, and a highly optimized GPU kernel was used for estimating the gradient required by the level set method. An innovative Boolean operation method, thousands of times faster than ordinary ones, was ultimately proposed. Performance tests show that the overall speedup was close to 15 on desktop-class hardware, simulation results were proven to converge to analytical results, and the error boundary was 0.25%.

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“…The method for measuring the pressure coupled response of composite propellant is suggested in [5]. A numerical approach for simulating the fluid-solid interaction problems in the ignition transient is suggested by Li, Liu, He [6]. It is stressed [7], the dynamic behavior analysis of this thin-walled structure under the action of impact loads is performed.…”

Section: Introductionmentioning

confidence: 99%

Model of Segmentation of Rocket Fairings Due to the Action of a Cumulative Charge

et al. 2018

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Safe separation of the rocket payload fairing is one of the most important factors that affect the success of a flight mission. In recent years, composite materials instead of aluminum alloys are widely used in rocketry. Such materials must satisfy a number of requirements that include the certainty of a local failure due to the action of a cumulative charge of the given power. To analyze this process numerical research is an advisable approach. The model of a composite rocket fairing separating due to the action of a cumulative charge has been developed. The properties of the composite material have been modeled based on the averaged characteristics obtained experimentally. The cumulative charge has been modeled by impulse loading having parameters adequate to the charge type. The time of action of the impulse, maximum pressure and width of the loading area are determined from the charge properties and geometry. The rocket fairing is considered as a composite shell composed of conical and cylindrical parts. A technique for 3D numerical analysis of the dynamic strength and structural failure has been developed. The mathematical model of the structure deformation and failure takes into account the dynamical properties of the material. The maximum plastic deformation is used as a failure criterion. The results of numerical simulation for the typical rocket payload fairing are presented.

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Coupled simulation of fluid flow and propellant burning surface regression in a solid rocket motor

Cited by 16 publications

References 20 publications

Fluid–solid coupled simulation of the ignition transient of solid rocket motor

Fluid–solid coupled simulation of the ignition transient of solid rocket motor

Combined Acceleration Methods for Solid Rocket Motor Grain Burnback Simulation Based on the Level Set Method

Model of Segmentation of Rocket Fairings Due to the Action of a Cumulative Charge

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