Abstract: The flow field and thermal environment of gap in solid rocket nozzle were simulated by finite element method.A non structure,high resolution FE scheme was used to calculate the pressure distribution and aerodynamic heating of gap at different incidence angle and Mach number.The properties of the flow field and thermal environment of gap were analysed.The numerical results are agree well with the experimental results

Key words: Rocket engine nozzle;Crack;Flow distribution;Thermal environment;Finit element method;Numerical simulation

摘要： 用有限元素法数值模拟了固体火箭发动机喷管内缝隙的流场和热环境。采用非结构的高分辨率的有限元离散格式，计算了不同攻角和不同Ｍａ数的缝隙内压力分布和气动加热，分析了缝隙内流场和热环境特性，数值结果与风洞实验结果符合很好。

关键词: 火箭发动机喷管;裂纹;流动分布;热环境;有限元法;数值仿真