飞行器热防护结构粗糙界面热阻预测及仿真分析  

Prediction and simulation of interfacial heat resistance for the rough interface of a thermal protection structure of aircraft

作　　者：李斌[1] 戴婷 LI Bin;DAI Ting(Research Institute of Aerospace Technology,Central South University,410083 Changsha,China)

机构地区：[1]中南大学航空航天技术研究院,长沙410083

出　　处：《应用力学学报》2025年第2期286-297,共12页Chinese Journal of Applied Mechanics

基　　金：国家自然科学基金资助项目(No.12102486);湖南省研究生科研创新资助项目(No.CX20220307)。

摘　　要：高超声速飞行器热防护结构通常由性能差异较大的材料构成,粗糙界面接触热阻对结构整体传热特性和防热效果的影响不可忽视。利用理论预测和数值仿真方法对热防护结构中隔热材料与金属材料的界面接触热阻问题进行研究,针对常用CMY(Cooper-Mikic-Yovanovich)接触热阻模型计算困难、不易描述粗糙界面复杂显微形貌等问题提出了改进方法,借助有限元软件对接触的力学过程与传热过程进行了仿真计算。在数值算例中,通过与文献实验数据的对比验证了方法的准确性,探讨了界面温度、接触压力和粗糙度对热阻的影响规律,并讨论了接触热阻在结构整体温度分布中的作用。结果表明接触压力和表面粗糙度均通过影响实际接触面积进而影响接触热阻,界面温度则主要通过影响材料物性参数从而改变接触热阻。高温条件下接触界面间辐射传热增强,引入接触热阻对热防护结构隔热层的影响较为显著。The thermal protection structures of hypersonic vehicles are usually composed of materials with significant performance differences,and the thermal contact resistance of rough interface plays an important role in the overall heat transfer characteristics and performance.The research on accurate prediction of thermal contact resistance under complex flight conditions and special thermal protection materials for hypersonic vehicles needs to be improved.The thermal contact resistance between thermal insulation material and metal material in thermal protection structures is investigated by theoretical prediction and numerical simulation.The advanced method is presented in view of the disadvantages in Cooper-Mikic-Yovanovich(CMY)model which is difficult to calculate and describe complex microscopic morphology of rough interfaces.The mechanics and heat transfer process of contact interface are analyzed by numerical simulation.In the numerical examples,accuracy of the method is verified by comparison with the experiment results in literature.The influences of interface temperature,contact pressure,and roughness on thermal resistance are explored,and the role of contact thermal resistance in the overall temperature distribution of the thermal protection structures is discussed.The results indicate that both contact pressure and surface roughness affect contact thermal resistance by affecting the actual contact area,while interface temperature mainly changes contact thermal resistance by affecting material physical parameters.Heat radiation between contact interfaces is enhanced at high temperature.The introduction of thermal contact resistance has a significant impact on the temperature field of insulation layer.

关 键 词：高超声速飞行器 热防护结构 接触热阻 理论预测 数值模拟 

分 类 号：V414.9[航空宇航科学与技术—航空宇航推进理论与工程]