Experimental and numerical flutter analysis of a folding fin with multiple asymmetric free-plays

作     者：Chenyu LIU Chao AN Changchuan XIE Xin ZHANG Lan YANG Chenyu LIU;Chao AN;Changchuan XIE;Xin ZHANG;Lan YANG

作者机构：School of Aeronautic Science and EngineeringBeihang UniversityBeijing 100191China Beijing Institute of Electronic System EngineeringBeijing 100854China Beijing Institute of Astronautical Systems EngineeringBeijing 100076China 

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

年 卷 期：2024年第37卷第5期

页      面：332-348页

核心收录：

学科分类：080103[工学-流体力学] 08[工学] 080104[工学-工程力学] 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：This study was supported by the National Natural Science Foundation of China(No.12102027) 

主　　题：Free-play Limit cycle oscillation Flutter Component mode synthesis Vortex-lattice method 

摘      要：Experimental folding fin models with an adjustable free-play are tested in a wind *** fin structure is modeled using the free-interface component mode synthesis method,and its free-play is modeled as four independent nonlinear springs with asymmetric stiffness.A nonplanar unsteady vortex-lattice method considering compressibility is employed to address nonlinear deformation and high subsonic *** spline interpolation is improved through projection and *** aeroelastic characteristics of folding fins with different free-play magnitudes,initial conditions and elastic-axis positions are analyzed using an established time-marching method because of its relatively small computation scale and high *** results show good consistency among the presented method,the wind tunnel test and the harmonic balance *** is a negative correlation between the critical speed of divergent motion and the ratio of the initial condition to the free-play *** either the free-play magnitude or the initial condition is extreme(tiny or vast),the system nonlinearity degenerates to ***,the flutter prevention design of a linear model can be applied to a nonlinear model,such as moving the elastic-axis position *** presented fin configuration exhibits an unstable limit cycle oscillation because the orders of coupled flutter modes do not change with variations in equivalent linear stiffness.