高超声速飞行器大面积热防护系统的传热数值分析  

Numerical analysis of thermal protection system heat transfer for hypersonic vehicle

作　　者：刘斌[1,2] 刘刚伟[1] 徐绯[1] 汤忠斌[1] 

机构地区：[1]西北工业大学航空学院,西安710072 [2]西北工业大学无人机所飞机室,西安710072

出　　处：《应用力学学报》2011年第3期294-298,328-329,共5页Chinese Journal of Applied Mechanics

基　　金：国家自然科学基金(90916027);教育部新世纪优秀人才支持计划(NCET080454)

摘　　要：隔热毡是高超声速飞行器防热系统中重要的组成部分。隔热毡内存在复杂的多种传热形式的耦合,本文详细地分析了隔热结构内导热与辐射的复合换热问题,用光学厚极限法分析了隔热层纤维席内辐射热流。建立了高温绝热毡有效热导率的数值计算模型,分析了温度和压力对传热机制的影响。该模型预测的有效导热系数与试验结果最大误差不超过6%。通过应用数值分析方法得到有效导热系数,建立了防热结构一维瞬态传热模型,该模型结果与瞬态实验结果最大误差为8%。最后还计算出不同厚度隔热毡蒙皮结构的温度响应,并分析讨论了隔热毡厚度对隔热效果的影响。本文研究表明:TPS隔热毡的厚度达到63.3mm后,继续增加尺寸,其隔热效率将明显降低。Insulation is an important part of hypersonic vehicle thermal protection system.The combined radiation/conduction heat transfer in high-porosity,high-temperature fibrous insulations is investigated numerically.A numerical model is established to solve the governing combined radiation and conduction heat transfer equations based on control volumes method.The radiation heat transfer is modeled by the optically thick approximation.The numerical model is validated by comparison with steady-state effective thermal conductivity measurements at different densities and pressure.The numerical model is also validated by comparison with a transient thermal test simulation under real reentry aerodynamic heating condition.Finally,a one-dimensional thermal model is established,which is used to calculate temperature response of thermal protection system infrastructure for variation of insulation thickness difference,and analyze thermal insulating efficiency with insulation thickness difference.

关 键 词：高超声速飞行器 防热系统 控制容积法 光学厚极限法 有效导热系数 

分 类 号：O343.6[理学—固体力学]