高超声速飞行器前缘流-热-固一体化计算

针对高超声速流动气动加热与结构传热的复杂耦合问题，探索和研究基于有限体积法的高超声速流-热-固一体化求解方法，将流场与结构温度场进行统一建模与数值模拟。该方法避开了传统气动加热和结构传热耦合求解方法在时间域内进行流场与结构温度场耦合交替迭代计算所带来的大量数据交换与计算，将流场与结构温度场作为一个物理场，采用统一的控制方程进行求解。采用典型高超声速绕流二维圆管稳态或非稳态流-热-固耦合算例对该一体化方法进行验证，稳态时圆管驻点温度最高达到648 K，非稳态时的热流密度和结构温度与参考文献和实验值吻合较好，由此证明了该方法的可靠性和正确性。与耦合计算方法的对比分析结果表明：该一体化求解方法所得计算结果更接近实验值，并且计算量和网格依赖性都相对较小，具有更好的稳定性和计算精度，能为高超声速飞行器一体化热防护设计提供有效的理论和技术支撑。
A fluid-thermal-structural integrated method was presented based on finite volume method for hypersonic aeroheating-structural-thermal interaction. A system of unified integral equations was developed as the control equations for physical process of aero-heating and structural heat transfer. The whole physical field was discretized by using an up-wind finite volume method, which avoids the fussy data exchange and computational complexity in coupling method. To demonstrate its capability, applications for fluid-thermal-structural analysis of hypersonic ow over 2D stainless steel cylinder in steady and unsteady states, were performed and discussed. The numerical results show that the maximum temperature of about 648 K occurs at the stagnation point of stainless steel cylinder in a steady state and the objective physical processes in a good agreement with measured values in unsteady state. Compared with the coupling method, the integrated algorithm has shown a better stability with lesser grid dependence，which provides theoretical and technical support for the thermal protection system of hypersonic vehicles.