高超声速流场与结构温度场一体化计算方法  

Algorithms for hypersonic fluid-structural-thermal integrated

作　　者：季卫栋 王江峰[1] 樊孝峰[1] 赵法明 

机构地区：[1]南京航空航天大学航空宇航学院,南京210016

出　　处：《航空动力学报》2016年第1期153-160,共8页Journal of Aerospace Power

基　　金：国家高技术研究发展计划

摘　　要：在对国内外流场与结构温度场一体化计算方法的不足进行细致讨论的基础上,提出了一种高超声速流场与结构温度场一体化计算方法.采用统一的积分方程组作为气动加热和结构传热物理过程的控制方程,对整个物理场进行统一的迎风格式有限体积方法离散,给出了流场与结构交界面上温度、温度梯度及导热系数等参数的计算方法.在时间推进方面,定常状态采用多步龙格库塔迭代格式,非定常状态则采用双时间步长方法.采用发展的一体化算法对二维圆管模型的气动加热和结构传热问题进行了数值模拟.结果表明:2s时驻点物面温度为390K,与其他文献的误差在3.1K范围内;稳定时驻点物面温度为647K.An fluid-structural-thermal integrated algorithm was presented based on detailed discussion about the deficiency in domestic and foreign study on algorithm of fluid- structural-thermal integrated. A unified integral equation system was developed as the con- trol equation for physical process of aero-heating and structural heat transfer. The whole physical field was discretized by using an up-wind finite volume method. The corresponding algorithm were given to work out the value of the temperature, the temperature gradient and the heat transfer coefficient on the boundary between fluid and structure. In terms of time step, a multi-step Runge-Kutta iteration scheme was used in steady states while a dual-time step method was adopted in unsteady states. Numerical simulation of the aero-heating and structural heat transfer problem on a two-dimensional circular tube model was performed. Results show that the 2 s stagnation surface temperature is 390 K. Compared with other pa- pers, the maximum absolute error is 3.1K. The steady state stagnation surface temperature is 647 K.

关 键 词：流场与结构温度场一体化 气动加热 有限体积法 一体化算法 高超声速 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]