Modeling of Heat Transfer in Decomposable Materials of Thermal Protection Coating of Reentry Vehicle
Authors: Barinov D.Ya., Prosuntsov P.V. | Published: 06.12.2016 |
Published in issue: #6(111)/2016 | |
Category: Aviation and Rocket-Space Engineering | Chapter: Aerodynamics and Heat Transfer Processes in Aircrafts | |
Keywords: mathematical model, reentry, vehicle, thermal protection, decomposable material, ablation |
In this research we carried out mathematical modeling of the heat transfer in the element of thermal protection system (TPS) of the space reentry vehicle. One-dimensional formulation of the problem has been considered. The TPS element consists of three layers: a decomposable material, fibrous insulating material and a metal power structure. We developed physical and mathematical models of heat and mass transfer in the element of thermal protection. Furthermore, by means of the finite-element method in the software package Marc. Software Marc, we calculated the temperature fields during the descent to the Earth. We also obtained the carbonized layer depth and the temperature of the beginning of pyrolysis. Finally, we examined the influence of such parameters as emissivity of the TPS surface, thermal conductivity of a decomposable material in the area of medium and high temperatures, the activation energy of the material on the thermal state of the coating and the temperature of the power structure. Findings of the research show, that the biggest effect on the temperature of metal construction is provided by the activation energy and thermal conductivity in the area of medium temperatures, while the surface temperature is determined by emissivity of the surface. Thermal conductivity of a decomposable material in the area of high temperatures does not influence the temperature field of the TPS element.
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