The Nonlinear Aeroelastic Analysis Of Wings Based On CFD/CSD

The thesis analysed the nonlinear aeroelastical problem of wings by CFD and CSD method.The thesis induced the formulations of Mindlin plate element and shear spatial beam element by T.L. format. The program of dynamic nonlinear finite element of wings was programmed. With this program, the statical and dynamic solutions of three structures were caculated. The results equal to the results of NASTRAN approximatively.The thesis found the physical matrix of composite plate with the layered modeling method. The mechanical behavior of composite structure could be approximatively analysed by substituting the physical matrix of composite for physical matrix of program. The geometric nonlinear characteristic and different layered angle of composite influenced the stiffness and frequence of structure. The results indicated that the wing's displacement would increase along with pressure of wing. The bending frequence would reduce and the 1st torsional frequence also reduced along with the displacement of wing. The different layered angle could change the distribution of stiffness and the frequence of structure.The fluid mesh could move along with the mesh of structure. The in-out datas were saved and read effectively. The program could actualize the CFD and CSD function with the program of dynamic nonlinear finite element and the interpolation between structure and fluid. The thesis analysed nonlinear aeroelastic behavior of two wings by coupling method and got the nonlinear aeroelastic response. The results of program approximated NASTRAN.The analytical method of this thesis could calculate nonlinear aeroelastical problems of complex structure by the powerful function of fluid calculation. This method had an important significance for engineering applications and provided effective instrument for analyzing nonlinear aeroelastical problems of complex structure in time domain.