Development Of Aerodynamic Coupling Calculation Module For Wing Structure Based On SiPESC Platform And Panel Method

Due to the influence of aeroelasticity on the safety and flight performance of aircraft,aeroelasticity has always been an important problem concerned by many scholars in the field of aircraft manufacture and design.Current research on aeroelasticity focuses on elastic structures in the air.The main factors of the study are: aerodynamic force,corresponding structural response and the interaction between the above two factors.In this paper,aerodynamic modeling and the fluid-solid coupling analysis of the wing is carried out by combining the structural mechanical response calculated by SiPESC of the independent CAE platform.The following work was completed:(1)The aerodynamic model is modeled by the surface vortex lattice method and the aerodynamic force is interpolated by the surface spline interpolation algorithm.Furthermore,the static aeroelastic analysis process of the wing is realized by calling the structural analysis module of sipesc.fems to calculate the structural response and update the configuration of the finite element structure and the aerodynamic structure.The results are compared with the general finite element software Nastran to verify the accuracy of the results.(2)After modal condensation of the aeroelastic equations of motion,the coefficient matrix of aerodynamic correlation is obtained by dipole lattice method,and the linear flutter analysis was carried out by the V-g method,and the flutter velocity and frequency were obtained.The results are compared with the general finite element software Nastran to verify the accuracy of the results.(3)Considering geometric nonlinearity of large deformation wing,a program framework for geometric nonlinear static aeroelastic analysis is established by combining nonlinear analysis module in SiPESC.fems.The geometric nonlinear equilibrium state of the airfoil is obtained after iterative calculation,and the solution flow of static aeroelastic deformation of nonlinear structure is completed(4)Through the nonlinear static aeroelastic analysis,the corresponding coefficient matrix of the dynamic linearization equation can be obtained after the final calculation convergence of the system.A program framework for geometric nonlinear flutter analysis is established,and according to the information of wing length and natural frequency,several converted frequency points are given and calculated at these converted frequency points.Given some inlet Mach number,the nonlinear damping and frequency corresponding to each velocity are obtained according to the nonlinear flutter analysis flow.Then a complete nonlinear flutter v-g diagram is obtained to find the exact flutter velocity...