A remark on the state-space concept applied to bending, buckling and free vibration of composite laminates

The present study shows that the state-space concept used to generate exact solutions for various boundary conditions for bending, buckling and free vibration of composite laminates, can be modified easily and exactly and has no drawback when the laminate thickness is reduced. Numerical results for central deflections, axial stresses, transverse shear stresses, critical buckling loads and natural frequencies of cross-ply laminated plates are obtained using the classical, first- and third-order theories for large side to thickness ratios. Copyright (C) 1996 Elsevier Science Ltd.