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In spite of considerable importance in engineering practice, especially in aerospace structures, thermal postbuckling behavior of nanocomposite curved panels has received little attention. This article aims to analyze different situations of postbuckling response of carbon nanotube (CNT) reinforced composite flat and cylindrical panels exposed to uniform temperature rise. CNTs are embedded into isotropic matrix through functionally graded distributions. The properties of constitutive materials are assumed to be temperature dependent and effective properties of CNT-reinforced composite are estimated according to an extended rule of mixture. Governing equations of thick panels are established within the framework of higher order shear deformation theory taking into account geometrical nonlinearity, initial imperfection, panel-foundation interaction, and elasticity of tangential constraints of boundary edges. Analytical solutions for simply supported panels are assumed and Galerkin method is adopted to derive nonlinear load-deflection relations from which temperature-deflection equilibrium paths are traced through an iteration algorithm. The study reveals that combined effects of curvature of panel, tangential constraints of edges, and initial geometrical imperfection can lead to the change in type of buckling response. Numerical analyses also indicate different influences on the postbuckling behavior of thermally loaded nanocomposite panels.

mechanics based design of structures and machines

Thermally induced postbuckling of higher order shear deformable CNT-reinforced composite flat and cylindrical panels resting on elastic foundations with elastically restrained edges