高速飞行条件下CMC材料细观热响应特性  

Mesoscopic thermal response characteristics of CMC materials under high-speed flight conditions

作　　者：王偲琛 张超 蔡兴考 杨肖峰 肖光明 杜雁霞[1,2] WANG Caichen;ZHANG Chao;CAI Xingkao;YANG Xiaofeng;XIAO Guangming;DU Yanxia(State Key Laboratory of Aerodynamics,Mianyang 621000,China;Institute of Computing for Aerodynamics Research,China Aerodynamics Research and Development Center,Mianyang 621000,China)

机构地区：[1]空天飞行空气动力科学与技术全国重点实验室,绵阳621000 [2]中国空气动力研究与发展中心计算空气动力研究所,绵阳621000

出　　处：《航空学报》2025年第3期269-280,共12页Acta Aeronautica et Astronautica Sinica

摘　　要：耐高温防热结构性能评估与设计是保障高速飞行器热安全的重要前提,精确预测真实飞行条件下防热结构非稳态热响应特性至关重要。以典型陶瓷基复合防热结构(CMC)为研究对象,分别基于有限体积法(FVM)和有限差分法(FDM)开展了飞行器前缘外流场计算以及对流辐射耦合条件下CMC材料代表单元体(REV)模型与等效模型热响应过程模拟,对比分析了瞬时气动热载荷条件下CMC材料非稳态热响应特性。研究表明:REV模型的热响应在流热耦合条件下反映出更为复杂的时空分布特性,在给定的高速飞行条件下,气动热载荷条件为150.34 kW/m2,相较于等效模型,其壁面最大温差可达21.78 K,且热流差极值延后温差极值2.39 s出现;结构内部温度分布与基体和纱线的空间分布及热物性强相关,沿厚度方向温度梯度呈逐渐衰减的“振荡”波形。相关研究结论可为飞行器热防护系统低冗余设计及热环境精确预测提供重要理论参考。The performance evaluation and design of high-temperature thermal protection structures are vital prerequi⁃sites for ensuring thermal safety in high-speed aircraft.Accurately predicting the non-steady-state thermal response characteristics of thermal protection structures under actual flight conditions is of utmost importance.This study investi⁃gates typical Ceramic Matrix Composite(CMC)thermal protection structures.The aerodynamic flow field around the leading edge of the aircraft was computed using both the Finite Volume Method(FVM)and Finite Difference Method(FDM).Additionally,simulations were conducted to model the thermal response process of Representative Volume(REV)and equivalent models of CMC materials under the coupling conditions of convection and radiation.A com⁃parative analysis was performed to investigate the non-steady-state thermal response characteristics of CMC materials under transient aerothermal loads.The research findings indicate that the thermal response of the REV model exhibits a more complex spatiotemporal distribution under the coupling conditions of fluid flow and heat transfer.Under the pre⁃scribed conditions,with an aerothermal load condition of 150.34 kW/m2,the REV model shows a maximum tempera⁃ture difference of 21.78 K on the wall,and the peak difference in heat flux occurs 2.39 s after the peak temperature difference.The internal temperature distribution of the structure is strongly influenced by the spatial distribution and thermal properties of the matrix and fiber yarn.Along the thickness direction,the temperature gradient exhibits an os⁃cillatory waveform with a gradual attenuation.The conclusions of this study can provide important theoretical refer⁃ences for the low redundancy design of aircraft thermal protection systems and the accurate prediction of thermal envi⁃ronments.These findings can contribute to the development of more efficient and reliable thermal protection systems for aircraft,ensuring their thermal safety under high-speed flight conditions.

关 键 词：高速飞行器 CMC材料 REV模型 有限体积法(FVM) 有限差分法(FDM) 对流辐射耦合 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]