Abstract
Based on the von Karman large deformation assumptions, a 72-degree-of-freedom high-precision higher order triangular plate element using a simplified higher order shear deformation plate theory is developed for the analysis of postbuckling behavior of a composite laminated plate subjected to edge shortening or in-plane compressive loading. By examining the local minimum of total potential energy of each mode, a clear picture of buckled pattern change is presented. Results show that the buckled pattern change may occur for plates with certain material properties and boundary conditions. The important transverse shear effect on the buckled pattern change is also presented. It shows that the buckling mode will shift from first to second mode shortly after buckling occurs if the transverse shear deformation is included.
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