基于Kriging代理模型的高升力构型优化设计  

Optimization Design of High-lift Configuration Using Kriging Model

作　　者：许瑞飞 段卓毅 钱瑞战 Xu Ruifei;Duan Zhuoyi;Qian Ruizhan(AVIC The First Aircraft Institute,Xi’an 710089,China)

机构地区：[1]航空工业第一飞机设计研究院,陕西西安710089

出　　处：《航空科学技术》2023年第3期58-63,共6页Aeronautical Science & Technology

摘　　要：本文发展了一种基于Kriging模型的高升力构型优化设计方法。采用分区对接网格技术求解N-S方程以及遗传算法,在着陆构型下使多段翼型升力系数最大。为了降低计算量和计算时间,在优化过程中采用Kriging模型代替复杂的流场计算。为了提高模型的精度,采用EI方法增加新的样本点。利用该方法完成了多段翼型缝道参数和外形优化设计。结果表明,在只优化襟翼缝道和襟翼缝道与外形同时优化两种情况下,该方法使得多段翼型最大升力系数分别提高7.55%和9.48%。The Kriging-based multi-objective optimization design method for high-lift configuration is developed in this paper. By introducing the Navier-Stocks solver with S-A turbulence model, the zonal patched grids and the genetic algorithm, the lift coefficient under the landing condition is maximized. In order to reduce the computational time and cost, Kriging model is applied to the process of the optimization design for replacing the complex computational program. EI method is introduced to give additional sample points in order to introduce the accuracy of the model. The optimization design for the position and configuration of multi-element airfoil are carried out. The results show that the lift coefficient of the multi-element airfoil can be increased by 7.55% under the condition that the position of the flap is optimized, and when the position and configuration of the flap are both optimized, the lift coefficient of the multielement airfoil can increase by 9.48%.

关 键 词：KRIGING模型 拉丁超立方抽样 增升装置 优化设计 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]