Author/Authors :
Mozaffari، A. نويسنده Department of Mechanical and Aerospace Engineering, K.N.T. University of Technology, Tehran, Iran Mozaffari, A. , Morovat، F. نويسنده Department of Mechanical and Aerospace Engineering, K.N.T. University of Technology, Tehran, Iran Morovat, F. , Zaare، H. نويسنده Department of Aerospace Engineering, Sharif University of Technology, Tehran, Iran Zaare, H.
Abstract :
The present study deals with the buckling analysis laminated composite truncated conical sandwich shells with flexible core subject to combined axial compressive load and external pressure. The higher order governing equations of motion are presented for conical composite sandwich shells. They are derived from the Hamilton principle. Then, by use of Improved Higher-order Sandwich Shell Theory, the base solutions of the governing equations are obtained in the form of power series via general recursive relations. The first order shear deformation theory is used for the face sheets and a 3D-elasticity solution of weak core is employed for the flexible core. By application of various boundary conditions such as clamped and simply-supported edges, the natural frequencies of the conical composite sandwich shell are obtained. The obtained results are compared with the numerical results from FEM analysis and good agreements are reached. An extensive parametric study is also conducted to investigate the effect of total thickness to radius ratio on the buckling load.
