论文部分内容阅读
气动热弹性分析是高超声速飞行器设计的关键技术之一。高超声速飞行器气动热的准确快速预测是气动热弹性分析的重要前提。针对当前气动加热工程计算、数值计算和实验研究均不能很好满足设计要求的问题,采用本征正交分解(POD)与代理模型(Surrogate)技术结合的模型降阶(POD-Surrogate)方法,建立了一种快速高效的高超声速气动热降阶模型框架。针对典型高超声速三维翼面气动热预测研究结果表明:当保留的POD基模态个数大于20时,PODKriging方法和POD-RBF(Radial Basis Function)方法的降阶模型得到的翼面温度分布与计算流体力学(CFD)计算温度L∞平均误差分别达到6%和14%,相对均方根误差(NRMSE)平均误差分别达到4%和12%,继续增加POD的基模态并不能提高降阶模型的预测精度;针对高超声速机翼气动热计算,POD-Kriging方法比POD-RBF方法具有更高的精度;针对典型的高超声速三维翼面气动热预测表明:基于POD-Surrogate方法的气动热降阶模型具有较高的精度和效率。
Pneumatic thermoelastic analysis is one of the key technologies in hypersonic aircraft design. The accurate and rapid prediction of aerodynamic heat of hypersonic vehicles is an important prerequisite for aerodynamic thermoelastic analysis. In view of the current aerodynamic heating engineering calculation, numerical calculation and experimental research can not meet the design requirements well, the POD-Surrogate method is combined with the POD and Surrogate techniques, A fast and efficient hypersonic aerodynamic reduction model framework was established. According to the aerodynamic thermal prediction of a typical hypersonic three-dimensional airfoil, the results show that the airfoil temperature distribution obtained by the reduced-order model of the PODKriging method and the POD-RBF (Radial Basis Function) method, when the number of POD base modes remaining is greater than 20, Computational fluid dynamics (CFD) calculation of temperature L∞ average error of 6% and 14%, respectively, and the average error of relative root mean square error (NRMSE) of 4% and 12%, respectively, continue to increase the base mode of POD does not improve the order POD-Kriging method is more accurate than POD-RBF method for aerodynamic heat calculation of hypersonic wing. The aerodynamic heat prediction of a typical hypersonic three-dimensional airfoil shows that aerodynamic heat based on the POD-Surrogate method Reduced order model has high accuracy and efficiency.