摘要
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。
The traditional CFD simulation of aerodynamic heating analysis of hypersonic vehicle confronts the difficulty of large calculation scale and is not applicable for conceptual design.This paper substitute radial basis function surrogate model for CFD simulation model for the objective of reducing the calculation scale of aerodynamic heating analysis.A new strategy of adding points sequentially is proposed,and is applied to the process of surrogate modeling.And the precision of surrogate model is improved.Compared with traditional radial basis function surrogate model,the new surrogate model proposed in this paper is more accurate and more efficient,and deserves to be promoted.
出处
《工程热物理学报》
EI
CAS
CSCD
北大核心
2015年第8期1804-1808,共5页
Journal of Engineering Thermophysics
基金
国家自然科学基金资助项目(No.11404405)
关键词
径向基模型
高超声速飞行器
气动热
序贯加点
radial basis function
hypersonic vehicle
aerodynamic heating
add points sequentially
