Prediction method of ablation and thermal response for a thermal protection coating with silicone rubber

被引：0
|
作者：
Shi S. [1 ,2 ]
Lei B. [3 ]
Zhang Y. [1 ]
Hu L. [2 ]
Li M. [4 ]
Liang J. [5 ]
机构：
[1] Shaanxi Aerospace Flight Vehicle Design Key Laboratory, School of Astronautics, Northwestern Polytechnical University, Xi’an
[2] Shanghai Key Laboratory of Spacecraft Mechanism, Shanghai
[3] China Aerospace Sanjiang Group Design Corporation, Wuhan
[4] Beijing System Design Institute of Electro⁃Mechanic Engineering, Beijing
[5] Institute of Advanced Structure Technology, Beijing Institute of Technology, Beijing
来源：
Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | 2023年 / 44卷 / 23期
基金：
中国国家自然科学基金;
关键词：
ablation mechanism; coupling model of ablation; silicone rubber; thermal decomposition characteristic; thermal protection coatings; thermal response;
D O I：
10.7527/S1000-6893.2022.28141
中图分类号：
学科分类号：
摘要：
The prediction method of both ablation mechanism and properties of light-weight，high-efficient thermal protection coatings for moderate thermal environment of high speed aerospace vehicles are systematically studied. The high-temperature thermal environment test of a thermal protection coating with silicone rubber was carried out using quartz lamp radiation heating equipment. The evolution law of microstructure for the material under high temperature was analyzed. The ablation and thermal protection mechanism were clarified. Based on the principles of mass and energy conservation，a coupled prediction model of ablation and thermal response for thermal protection coatings with silicone rubber was established by combining with aerodynamic relationship of boundary layer and heat conduction equation of internal materials. In the model，various heat absorption mechanisms caused by the process of ablation，phase transition and gas diffusion were considered. The surface ablation and heat transfer of the thermal protection coating with silicone rubber were simulated under a typical heat flux condition. The thermal responses of the material were obtained，and the thermal protection and insulation properties of the thermal protection coating with silicone rubber were analyzed. Both the mass loss rate and back temperature from the developed model were in good agreement with the experimental results，which validated the coupling prediction model. This model has the potential to the applications of elaborated design and property prediction of ablative thermal protection coatings. © 2023 AAAS Press of Chinese Society of Aeronautics and Astronautics. All rights reserved.
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