高超声速导弹流场与结构温度场耦合数值分析

Coupling Numerical Simulation of Flow Field and Structure-thermal Field on Hypersonic Missile

为实现高超声速导弹平飞状态热力环境预示,采用分区求解方法,建立气动/热/结构多场耦合仿真计算模型,并对其流场和结构温度场进行了数值模拟。结果表明:弹体结构发生轴向拉伸和径向膨胀,且结构变形主要由气动加热引起;导弹头部气动热力环境较为严酷;结构变形对温度和压力仿真计算结果影响较小。在导弹平飞时,可忽略耦合效应,以提高流场与结构温度场数值仿真计算效率,对导弹设计具有指导意义。

A hypersonic missile of aerodynamic/thermal/structural multi-field coupling numerical simulation model is established to predict its thermodynamic environment on the condition of horizontal flight, which is implemented by using partition algorithm, and its flow field and structure-thermal field are analyzed. Results show that: missile body is stretched and expanded on axial direction and on radial direction, respectively, and structural deformation is mainly caused by aerodynamic heating;the thermodynamic environment is severe in missile head;structural deformation has little influence on the distribution of temperature and pressure. Coupling factors could be neglected to enhance numerical simulation efficiency of flow field and structure-thermal field on the condition of horizontal flight, which is meaningful for missile design.