基于动响应数据的大柔性机翼结构降阶方法  

Reduced order method for large flexible wing structure based on dynamic response data

作　　者：谢长川[1] 张铎耀 安朝 XIE Changchuan;ZHANG Duoyao;AN Chao(School of Aeronautic Science and Engineering,Beihang University,Beijing 100191,China)

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100191

出　　处：《北京航空航天大学学报》2023年第6期1319-1330,共12页Journal of Beijing University of Aeronautics and Astronautics

摘　　要：现代飞行器机翼柔性大,几何非线性问题不可忽略。基于动响应数据样本,基于谐波平衡和快速Fourier变换对结构动力学方程中的非线性刚度系数进行识别,建立非线性结构降阶模型。引入位移残量基模态,进行柔性机翼大变形的位移恢复。结合曲面涡格法和三维曲面插值方法搭建大柔性机翼几何非线性气动弹性分析框架。相比传统基于静力学数据回归分析的几何非线性结构降阶方法,该方法需要的载荷集数目小,提高了分析效率。计算结果表明:与非线性有限元方法相比,非线性结构降阶模型准确度高,能够有效应用于大柔性机翼几何非线性静气动弹性分析,而传统的线性计算方法与非线性方法相比结果差异较大。Due to the flexibility of modern aircraft wing,geometric nonlinearity cannot be neglected.Based on dynamic response data samples,non-linear stiffness coefficients in structural dynamics equation are identified based on harmonic balance and fast Fourier transform,and a non-linear structural order reduction model is established.The basic mode of displacement residue is introduced to recover the displacement of large flexible wings.A geometrically nonlinear aeroelastic analysis framework for large flexible wings is established by combining non-planar vortex lattice method and non-planar spline interpolation method.Compared with reduced order model for the traditional geometric nonlinear structure based on static data regression analysis,the proposed method requires a small number of load sets and improves analysis efficiency.Results show that compared with the nonlinear finite element method,the proposed model has high accuracy and can be effectively applied to the geometric nonlinear static aeroelastic analysis of large flexible wings.The result of traditional linear calculation method is significantly different from that of the nonlinear method.

关 键 词：几何非线性 快速傅里叶变换 参数识别 降阶模型 静气动弹性 

分 类 号：V211.47[航空宇航科学与技术—航空宇航推进理论与工程] V214.1