Static aeroelastic analysis of very flexible wings based on non-planar vortex lattice method

作     者：Xie Changchuan Wang Libo Yang Chao Liu Yi 

作者机构：School of Aeronautic Science and Engineering Beihang University 

出 版 物：《Chinese Journal of Aeronautics》 (中国航空学报（英文版）)

年 卷 期：2013年第26卷第3期

页      面：514-521页

核心收录：

学科分类：08[工学] 080103[工学-流体力学] 0802[工学-机械工程] 0825[工学-航空宇航科学与技术] 0801[工学-力学（可授工学、理学学位）] 

基　　金：National Natural Science Foundation of China(Nos.11172025,91116005) Research Fund for the Doctoral Program of Higher Education of China(No.20091102110015) 

主　　题：Aeroelasticity Geometric nonlinearity Non-planar aerodynamics Static aeroelasticity Vortex lattice method 

摘      要：A rapid and efficient method for static aeroelastic analysis of a flexible slender wing when considering the structural geometric nonlinearity has been developed in this paper. A non-planar vortex lattice method herein is used to compute the non-planar aerodynamics of flexible wings with large deformation. The finite element method is introduced for structural nonlinear statics analysis. The surface spline method is used for structure/aerodynamics coupling. The static aeroelastic characteristics of the wind tunnel model of a flexible wing are studied by the nonlinear method presented, and the nonlinear method is also evaluated by comparing the results with those obtained from two other methods and the wind tunnel test. The results indicate that the traditional linear method of static aeroelastic analysis is not applicable for cases with large deformation because it produces results that are not realistic. However, the nonlinear methodology, which involves combining the structure finite element method with the non-planar vortex lattice method, could be used to solve the aeroelastic deformation with considerable accuracy, which is in fair agreement with the test results. Moreover, the nonlinear finite element method could consider complex structures. The non-planar vortex lattice method has advantages in both the computational accuracy and efficiency. Consequently, the nonlinear method presented is suitable for the rapid and efficient analysis requirements of engineering practice. It could be used in the preliminary stage and also in the detailed stage of aircraft design.