Abstract
Postbuckling behavior of a 3D braided composite cylindrical panel under axial compression is investigated. The material properties of epoxy are expressed as a linear function of temperature. The governing equations are based on Reddy's higher order shear deformation shell theory with a von Kármán-Donnell type of kinematic nonlinearity and including thermal effects. A boundary layer theory of shell buckling is utilized to study postbuckling of panels. The results reveal that the temperature changes, the fiber volume fraction, in-plane boundary conditions, as well as initial geometric imperfections have a significant effect on the buckling and postbuckling behavior of braided composite cylindrical panels.
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