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针对高超声速飞行器气动热分析中采用CFD仿真计算耗费大,不符合概念设计阶段要求进行大量方案评估的问题,采取径向基近似模型代替高精度的CFD仿真模型,大大减少了高超声速飞行器气动热分析时的计算量。提出了一种新的序贯加点策略,将其应用于径向基近似建模过程中,提高了径向基近似模型的精度。将该近似模型应用于高超声速飞行器驻点气动热分析中,和普通径向基近似模型对比可知,本文提出的序贯径向基近似模型能够以较小的代价得到较高的精度,具有推广的价值。
In order to solve the problem that aerodynamic thermal analysis of hypersonic vehicles is costly and does not meet the requirement of conceptual design, a radial basis approximation model is used to replace the high-precision CFD simulation model, which greatly reduces the aerodynamic heat of hypersonic vehicle Analysis of the amount of computation. A new sequential strategy is proposed, which is applied to approximate modeling of radial basis to improve the accuracy of radial basis approximation model. The approximation model is applied to aerodynamic thermal analysis of stagnation point of hypersonic vehicles. Compared with the conventional radial base approximation model, it can be seen that the proposed sequential radial basis approximation model can obtain higher accuracy with less cost and has the advantages of popularization the value of.