针对大气环境内吸气式高超声速飞行器热防护要求,得出前缘、下表面和上表面的热防护结构应分别采用碳/碳(C/C)防热材料、刚性陶瓷防热瓦材料和柔性隔热毡材料。基于Abaqus分析软件建立以机身为主的热分析有限元模型,计算了高超声速飞行器在典型气动加热载荷情况下的温度场分布和在整个飞行过程中温度的变化情况。通过温度分布得到机身前缘的峰值温度达1637℃,上下表面峰值温度分别为635、805℃,验证了本研究提出的热防护结构形式的有效性。通过温度与时间曲线得出飞行500 s左右时,飞行器前缘及上下表面温度急剧增加、温度梯度大,500~1500 s期间持续高温,在1500 s后温度迅速降低。同时建立了C/C、陶瓷瓦及柔性隔热毡3种典型耐高温材料的传热模型,对其防热结构的防热效率进行评估,得到其最佳的防热材料厚度为57.6、52.9、53.3 mm,可为防热结构的设计提供参考。 According to the requirement of thermal protection of the aspirated hypersonic vehicle in the atmospheric environment, it is concluded that the thermal protection structure of the leading edge, the lower surface and the upper surface should adopt the C / C heat-resistant material, the rigid ceramic heat-shrink tile material and the flexible Insulation felt material. Based on the Abaqus analysis software, a finite element model of the body-based thermal analysis was established. The temperature field distribution and the temperature change of the hypersonic vehicle under typical aerodynamic heating loads were calculated. Through the temperature distribution, the peak temperature of the leading edge of the fuselage reaches 1637 ℃, and the peak temperature of the upper and lower surfaces are 635 and 805 ℃, respectively. The results show that the proposed structure is effective. When the flight temperature is about 500 s, the temperature rises sharply on the front and the upper and lower surfaces of the aircraft, the temperature gradient is large, and the temperature is high for 500-1500 s. The temperature is rapidly decreased after 1500 s. At the same time, the heat transfer models of three kinds of typical high temperature resistant materials, including C / C, ceramic tile and flexible insulation blanket, were established. The heat-protection efficiency of the heat-resistant structure was evaluated. The best heat-resistant material thickness was 57.6, 53.3 mm, which provides a reference for the design of heat-resistant structures.