Thermal buckling of composite plates with a strip delamination

Abstract

We consider strip delamination models with general anisotropic laminated configurations subjected to compression dominated in-plane mechanical loads and a temperature load that varies only in the thickness direction. On the basis of the laminated plate theory, the equations governing cylindrical postbuckling deformation are derived. These equations depend on the temperature load through the axial and shear components of the sublaminate thermal forces only (i.e., three parameters N,*, &* and N,,* as defined in Sec. 3). Close-form, exact solutions are obtained for the deformation of the disbonded and intact sublaminates. A simple expression is given for the energy release rate in terms of the midplane strains and curvature of the sublaminates near the delamination front. A moderate out-of-plane temperature gradient may severely aggravate the postbuckling deflection. The larger the existing in-plane mechanical loads, the more threatening is the effect of non-uniform temperature on the postbuckling deformation and the associated energy release rate.