硅 橡 胶 基 防 热 涂 层 烧 蚀 和 热 响 应 特 性 预 报 方 法

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.