基于本征正交分解和代理模型的高超声速气动热模型降阶研究

doi:10.7527/S1000-6893.2014.0079

流体力学与飞行力学

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基于本征正交分解和代理模型的高超声速气动热模型降阶研究

陈鑫^1,2, 刘莉^1,2, 岳振江^1,2

1. 北京理工大学宇航学院, 北京 100081;
2. 北京理工大学飞行器动力学与控制教育部重点实验室, 北京 100081

收稿日期:2014-03-12 修回日期:2014-04-24 出版日期:2015-02-15 发布日期:2014-05-15
通讯作者: 刘莉 Tel.: 010-68914534 E-mail: liuli@bit.edu.cn E-mail:liuli@bit.edu.cn
作者简介:陈鑫男,博士研究生。主要研究方向:高超声速气动热弹性分析、高超声速气动热弹性建模及优化设计。Tel:010-68913290 E-mail:blingkx@hotmail.com;刘莉女,博士,教授,博士生导师。主要研究方向:飞行器总体设计、飞行器结构分析与设计、飞行动力学与控制。Tel:010-68914534 E-mail:liuli@bit.edu.cn;岳振江男,博士研究生。主要研究方向:飞行器总体设计、高超声速气动-热-结构分析及优化。Tel:010-68913290 E-mail:yuezj910420@gmail.com
基金资助:
国家自然科学基金(11372036)

Reduced order aerothermodynamic modeling research for hypersonic vehicles based on proper orthogonal decomposition and surrogate method

CHEN Xin^1,2, LIU Li^1,2, YUE Zhenjiang^1,2

1. School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China;
2. Key Laboratory of Dynamics and Control of Flight Vehicle, Ministry of Education, Beijing Institute of Technology, Beijing 100081, China

Received:2014-03-12 Revised:2014-04-24 Online:2015-02-15 Published:2014-05-15
Supported by:
National Natural Science Foundation of China (11372036)

摘要/Abstract

摘要：

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,POD-Kriging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。

关键词: 高超声速, 气动热, 本征正交分解, 代理模型, 降阶模型

Abstract:

Aerothermoelasticity is one of the key technologies for hypersonic vehicles. Accurate and efficient estimation of aerodynamic heating is the basis of the aerothermoelasticity. Aimed at solving the shortcomings of engineering calculation and computational fluid dynamics, a novel estimation method based on proper orthogonal decomposition (POD) and surrogate(POD-Surrogate) method is proposed. Furthermore, a reduced order modeling framework for aerothermodynamic is developed. Test results for the three-dimensional aerothermodynamic over a hypersonic control surface indicate that the average L_∞ errors for POD-Kriging method and POD-RBF (Radial Basis Function) method can reach 6% and 14%, and the average normalized root mean square error (NRMSE) errors can reach 4% and 12%. Using more POD basis modes would not obviously improve the estimation precision when the basis modes reach 20. Reduced order models for the three-dimensional aerothermodynamics over a hypersonic control surface indicate that the precision of POD-Kriging method is better than that of POD-RBF method. In a word, the reduced order modeling for three-dimensional aerothermodynamics has good precision and efficiency.

Key words: hypersonic, aerothermodynamic, proper orthogonal decomposition, surrogate model, reduced order model

中图分类号:

陈鑫, 刘莉, 岳振江. 基于本征正交分解和代理模型的高超声速气动热模型降阶研究[J]. 航空学报, 2015, 36(2): 462-472.

CHEN Xin, LIU Li, YUE Zhenjiang. Reduced order aerothermodynamic modeling research for hypersonic vehicles based on proper orthogonal decomposition and surrogate method[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(2): 462-472.

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E-mail：hkxb@buaa.edu.cn

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

基于本征正交分解和代理模型的高超声速气动热模型降阶研究

Reduced order aerothermodynamic modeling research for hypersonic vehicles based on proper orthogonal decomposition and surrogate method

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