Thermal Buckling of Laminated Composite Plates Using a Simple Four Variable Plate Theory

In this study, the thermal buckling behavior of composite laminate plates cross-ply and angle-ply all edged simply supported subjected to a uniform temperature field is investigated, using simple trigonometric shear deformation theory. Four unknown variables are involved in theory, satisfied zero traction boundary condition on surface without correction factors, Hamilton's principle used derive equations motion depending Simple Variable Plate Theory for angle-ply, then solved through Navier's double sequence, obtain critical laminated plates. Effect changing some design parameters such as, orthotropy ratio (E1/E2), aspect (a/b), thickness (a/h), expansion coefficient (α2/α1), which have same good agreement when compared with previously published results maximum discrepancy (0.5%).