Journal of Aerospace Engineering, 2015, Vol.28(4)
The present study deals with the dynamic stability behavior of laminated composite and sandwich plates subjected to in-plane static and periodic compressive loads based on a recently developed inverse hyperbolic zigzag theory by the authors. The present model satisfies the traction-free boundary conditions on the surfaces of the plate and interlaminar continuity conditions at the layer interfaces, thus obviating the need for a shear correction factor. An efficient C0 continuous isoparametric serendipity element with seven field variables is employed for the usual discretization of the plate structure. The effect of span-thickness ratio, modular ratio, boundary conditions, static load factor, and thickness ratios are examined by solving a variety of numerical problems on laminated composite and sandwich structures. The principal instability regions of plate structures are obtained using BolotinEs approach and are represented either in the nondimensional load amplitude-excitation frequency plane or load amplitude-load frequency plane. The evaluated results are compared with the available published results based on various deformation theories. The prediction of accurate results at the cost of less computational effort ensures the efficiency of the present models for a wide range of applications.
Laminates – Properties ; Dynamics (Mechanics) – Analysis ; Finite Element Method – Usage
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