硅橡胶基防热涂层烧蚀和热响应特性预报方法

doi:10.7527/S1000-6893.2022.28141

Abstract

Abstract:

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.

Key words: thermal protection coatings, silicone rubber, ablation mechanism, thermal decomposition characteristic, coupling model of ablation and thermal response

CLC Number:

V259

Shengbo SHI, Bao LEI, Yuntian ZHANG, Li HU, Maoyuan LI, Jun LIANG. Prediction method of ablation and thermal response for a thermal protection coating with silicone rubber[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(23): 428141-428141.

Figures/Tables 13

Table 1

Basic material properties of innovative thermal protection coating with silicone rubber

变量	取值	变量	取值
原始材料密度 $ρ v$ /（kg·m^-3）	460	热解反应焓变 $Δ H g$ /（kJ·kg^-1）	1 000
炭化材料密度 $ρ c$ /（kg·m^-3）	285	碳的氧化反应焓变 $Δ H c$ /（kJ·kg^-1）	9 211
原始材料比热容 $C p v$ /（J·（g·K）^-1）	1.49	热分解反应表观活化能 $E ¯ a$ /（kJ·mol^-1）	100.8
炭化材料比热容 $C p c$ /（J·（g·K）^-1）	1.13	热分解反应指前因子 $A$ / s^-1	1.81×10⁴
原始材料热导率 $k v$ /（W·（m·K）^-1）	0.08	热分解反应反应级数 $n$	2.5
炭化材料热导率 $k c$ /（W·（m·K）^-1）	0.55	表面发射系数 $ε$	0.65~0.90
SiO₂蒸发压 $p v$ /10⁵Pa	exp（18.48-57 780/T_w）	热解气体比热容 $C p g$ /（J·（kg·K）^-1）	2.39+1.05×10^-3T
SiO₂蒸发过程焓变 $Δ H v$ /（kJ·kg^-1）	12 686

Table 1

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Table 2

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关键烧蚀性能	质量烧蚀量/g	平均质量烧蚀率/（g·s^-1）	背面温度/℃
实验值	3.03	0.028	70.8
模拟值	3.69	0.034	72.0

[1]	SHAO Meng, GU Yizhuo, CHENG Yong, SUN Jing, LI Min, ZHANG Zuoguang. Thermal Expansion Mold Design Using Silicone Rubber and Processing Quality Analysis of Bidirectional Stiffened Plates [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2012, (6): 1116-1124.
[2]	Hong Yanji;Wang Guangyu;Dou Zhiguo. State of Art of Laser Ablation Microthruster [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2009, 30(9): 1555-1565.

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

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