高超声速飞行器流-热-固耦合数值模拟

选用HiFire-1锥体部分作为研究对象, 采用顺序耦合方法, 对飞行器锥体的流-热-固耦合场进行了研究分析。在外流场的数值模拟中采用Transition k-kl-w湍流模型准确计算出了转捩位置和热流数值, 在温度场和应力场的数值模拟中计算了气动加热1 s时温度场和应力场的分布, 温度最高点和变形最大处均出现在头锥顶端, 温度在轴线方向上呈现环状的分布, 沿轴线逐渐降低, 整体结构的弹性变形和温度正相关, 且主要变形区域集中在前端高温区。

Hypersonic vehicle flow-heat-solid coupling simulation

Take the HiFire-1 cone as the research subject to analyze the aircraft flow-heat-solid coupling field by sequential coupling method. Transition k-kl-w turbulence model has been used to accurately calculate the position of the transition and flux values in the outside flow field numerical simulation which is basically consistent with the experimental data. In temperature field and stress field numerical simulation, the temperature field and stress field distribution of the HiFire-1 cone is calculated when aerodynamic heating time is 1 s. The results showed that the maximum temperature and deformation point occurred at the top of the cone. Cone temperature presented cyclic distribution in the axial direction, and decreased gradually along the axis. The top node temperature gradually rises over time and the change trend gradually slows down. The elastic deformation of the overall structure is positive correlation with the temperature, and the main deformation zone focus on the front area of high temperature.