高超声速飞行器多层复杂热防护结构气-固耦合快速热分析方法  

Fast Algorithm of Coupled Flow-Thermal for Multi-Layered Complex TPS of Hypersonic Aircraft

作　　者：刘健[1] 原志超[1] 杨恺[1] 高效伟[1,2] 

机构地区：[1]大连理工大学航空航天学院,辽宁大连116024 [2]高超声速冲压发动机技术重点实验室,北京100074

出　　处：《推进技术》2016年第2期227-234,共8页Journal of Propulsion Technology

摘　　要：为了实现高超声速飞行器多种复杂结构热防护系统的气-固耦合快速热分析,采用热网络法建立非稳态等效一维传热模型;对于具有弧度的热防护结构,提出了驻点和翼前缘热阻等效计算方法,并给出了修正计算公式;结合气动热环境工程算法,实现了对任意多层复杂防热结构外部气动加热与内部结构传热的快速耦合分析。分别对钝锥气动加热和高超声速二维圆管气-固耦合传热问题进行了模拟,得到了与实验符合较好的结果,且计算效率很高;并对Micro-X验证机的全过程进行了耦合热分析,结果表明多层防热结构具有很好的防热效果,显著降低了结构内部温度。和传统耦合算法相比,此算法可快速有效地分析模拟气-固耦合问题,满足高超声速飞行器热防护系统初始设计阶段的使用要求。To fast analyze the flow-thermal coupling problems for multi-layered complex TPS of hypersonic aircraft,an equivalent one-dimensional unsteady heat transfer model is established. For curved TPS,an equiva-lent computational method is proposed by forming the equivalent thermal resistance at the stagnation point and wing leading edge through using the correctional factor. For arbitrary multi-layered complex TPS,a fast coupling technique of aerodynamic heating of the outside air and the heat transfer in the structure is performed based on the use of the engineering algorithm for predicting aeroheating environment. Numerical examples for blunted cone and two-dimensional hypersonic fluid-solid thermally coupled flow around a cylinder are adopted for verifying the correctness of the aerodynamic heat and the coupling algorithm,and an example for the Micro-X vehicle is given to demonstrate the potential of the method in the coupling thermal analysis of a whole flying process. Com-pared to the traditional coupling algorithm, the approach can analyze the coupled flow-thermal problems effi-ciently,which could be applied to the initial design of the TPS of hypersonic aircraft.

关 键 词：高超声速飞行器 热防护系统 气动加热 耦合传热分析 快速算法 

分 类 号：V411.3[航空宇航科学与技术—航空宇航推进理论与工程]