Finite element estimation of interlaminar stresses in laminated composites

Abstract

A four noded, 36 degrees of freedom, rectangular laminated plate element based on the higher order shear deformation theory has been developed. Nodal degrees of freedom include two-in-plane displacements, the normal displacement, its two first derivatives and the second cross-derivative and three additional nodal displacement variables, representing the higher order shear deformation effects. The stiffness matrix corresponding to the classical laminated plate theory is available as a special case. Interlaminar stresses are estimated by integrating the local equilibrium equations. The performance of this element is illustrated with the aid of few numerical studies.