考虑硅橡胶基防热涂层烧蚀和开裂的热/力耦合数值模型

卞晨杰; 孙得川; 冯昕; 李博乾; 高超

doi:10.7527/S1000-6893.2026.33595

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DOI: https://doi.org/10.7527/S1000-6893.2026.33595

考虑硅橡胶基防热涂层烧蚀和开裂的热/力耦合数值模型

卞晨杰 ,
孙得川 ,
冯昕 ,
李博乾 ,
高超

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1. 大连理工大学
2. 大连理工大学工业装备结构分析优化与CAE软件全国重点实验室
3. 大连理工大学航空航天学院
4. 航天材料及工艺研究所

收稿日期: 2026-03-20

修回日期: 2026-09-07

网络出版日期: 2026-09-10

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Thermal/mechanical coupling numerical model considering ablation and cracking of silicone rubber-based thermal protective coating

BIAN Chen-Jie ,
SUN De-Chuan ,
FENG Xin ,
LI Bo-Qian ,
GAO Chao

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Received date: 2026-03-20

Revised date: 2026-09-07

Online published: 2026-09-10

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摘要

硅橡胶基防热涂层在气动热/力环境中会发生烧蚀和开裂现象，影响其防热效果和力学性能。通过高温热膨胀仪和万能试验机研究了涂层在常温和高温下的力学特性，并通过高温燃气流实验研究了其动态烧蚀和开裂过程，建立了考虑上述现象的热/力耦合有限元模型，进行了裂纹扩展计算。变形量曲线表明材料在低温下(小于600 K)以线性热膨胀为主，高温下开始显著收缩。不同温度条件下，材料性能分别表现为“增强弹性体”、“有机软化聚合物”和“无机多孔脆性陶瓷体”。烧蚀实验表明涂层开裂几乎发生在炭化层，最大开裂深度约处在炭化层和热解层交界面附近。数值结果表明涂层早期变形倾向于表层和底部约束区，随着烧蚀和传热深入，变形收缩范围和量级逐渐增大，导致两侧膨胀。考虑开裂后，材料主应力和主应变有所增加，前期(0~12 s)表层的温度梯度和热应力均较高，裂纹在此处萌生，剧烈的热膨胀和收缩效应放大了裂纹扩展驱动力，使其快速发展；中后期(12~30 s)温度梯度减小，裂尖处能量平衡，裂纹扩展趋缓并停止。

关键词： 硅橡胶; 防热涂层; 烧蚀; 裂纹; 热/力耦合; 数值模型

本文引用格式

卞晨杰 , 孙得川 , 冯昕 , 李博乾 , 高超 . 考虑硅橡胶基防热涂层烧蚀和开裂的热/力耦合数值模型[J]. 航空学报, 0 : 1 -0 . DOI: 10.7527/S1000-6893.2026.33595

Abstract

The silicone rubber-based thermal protective coating may undergo ablation-coupled cracking in aerothermodynamic environments, which affects its thermal protection effectiveness and mechanical properties. The coatings’ mechanical properties at room and high temperatures were studied using a high-temperature thermomechanical analyzer and a universal testing machine. The dynamic ablation and cracking processes were investigated using high-temperature gas flow experiments. A thermo/mechanical coupling finite element model was established to consider the above phenomena, and crack propagation calculations were performed. The deformation curve shows that the material undergoes linear thermal expansion at low temperatures (below 600 K), before beginning to contract significantly at higher temperatures. The material properties show as “reinforced elastomer”, “organically softened polymer”, and “inorganic, porous and brittle ceramic” under different temperature conditions. Ablation experiment results indicate that cracks almost occur in the char layer, with the maximum crack depth being near the interface between the char and pyrolysis layers. The numerical results indicate that the early deformation of the coating occurs primarily in the surface layer and the bottom constrained region. As ablation and heat transfer progress deeper into the material, the range and magnitude of deformation and shrinkage gradually increase, resulting in expansion on both sides of the material. After considering the cracking effects, the principal stresses and strains of the material increase. During the initial stage (0~12 seconds), the temperature gradient and thermal stress on the surface layer are relatively high, resulting in crack initiation at these locations. The effects of intense thermal expansion and contraction amplify the driving force for crack propagation, causing rapid crack development. In the middle-to-late stage (12~30 seconds), the temperature gradient decreases, the energy at the crack tip reaches equilibrium, and the rate of crack propagation slows down and stops.

Key words： silicon rubber; thermal protection coating; ablation; cracking; thermal/mechanical coupling; numerical model

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