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Establishment and Optimization of Ablation Surrogate Model for thermal protection material

Journal of Beijing Institute of Technology 2023年第4期32卷 477-493页

作者： Weizhen Pan Bo Gao Beijing Institute of Spacecraft System Engineering Beijing 100094China School of Astronautics Harbin Institute of TechnologyHarbin 150001China

The temperature response calculation of thermal protection materials,especially ablative thermal protection materials,usually adopts the ablation model,which is complicated in process and requires a large amount of calculation.Especially in the process of optimization calculation and parameter identification,the ablation model needs to be called many times,so it is necessary to construct an ablation surrogate model to improve the computational efficiency under the premise of ensuring the accuracy.In this paper,the Gaussian process model method is used to construct a thermal protection material ablation surrogate model,and the prediction accuracy of the surrogate model is improved through optimization.

关键词： ablation surrogate model thermal protection material

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Multi-phase flow effect on SRM nozzle flow field and thermal protection materials

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航空动力学报 2009年第10期24卷 2372-2378页

作者： SHAFQAT Wahab School of Astronautics Beijing University of Aeronautics and Astronautics

Multi-phase flow effect generated from the combustion of aluminum based composite propellant was performed on the thermal protection material of solid rocket motor(SRM) nozzle.Injection of alumina(Al2O3) particles from 5% to 10% was tried on SRM nozzle flow field to see the influence of multiphase flow on heat transfer computations.A coupled,time resolved CFD(computational fluid dynamics) approach was adopted to solve the conjugate problem of multi-phase fluid flow and heat transfer in the solid rocket motor nozzle.The governing equations are discretized by using the finite volume method.Spalart-Allmaras(S-A) turbulence model was employed.The computation was executed on the different models selected for the analysis to validate the temperature variation in the throat inserts and baking material of SRM nozzle.Comparison for temperatures variations were also carried out at different expansion ratios of nozzle.This paper also characterized the advanced SRM nozzle composites material for their high thermo stability and their high thermo mechanical capabilities to make it more reliable simpler and lighter.

关键词： solid rocket motor nozzle multiphase flow thermal protection material temperature distribution finite volume method

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维普期刊数据库

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thermal Investigation for Solid Rocket Motor Nozzle Inserts material

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Computer Aided Drafting,Design and Manufacturing 2009年第1期19卷 36-42页

作者： SHAFQAT Wahab School of Astronautics Beijing University of Aeronautics and Astronautics

A time-resolved numerical computational approach, involving the combustion of double-base propellant is performed on thermal protection material for SRM nozzle. An implicit Navier-Stokes Solver is selected to simulate two-dimensional axial-symmetric unsteady turbulent flow of compressible fluid. The governing equations are discredited by using the finite Volume method. S-A turbulence model is employed. CFD scheme is implemented to investigate the temperature distribution causes at nozzle throat inserts composite material. Different parameters have been selected for the analysis to validate the temperature variation in the throat inserts and baking material of SRM nozzle. The advanced SRM nozzle composite material is also characterized for the high thermo stability and high thermo mechanical capabilities to make it more reliable, simpler and lighter.

关键词： SRM nozzle thermal protection material temperature distribution finite volume method

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维普期刊数据库

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