Finite element analysis of composite sandwich structures by selective layerwise higher-order models

In this paper, displacement and stress analyses of composite sandwich laminates are presented by using two types of three layered sandwich elements, which are deduced from the authors' selective layerwise higher-order theory. The finite element models dealt with in the this study are [(110)(110)(110)] and [(332)(332)(332)] elements, where brackets stand for the entire sandwich and three parentheses in the brackets, respectively from the left-hand side to the right, denote the upper skin (U), the core (C) and the lower skin (L) layers. Three integers in each of the parentheses denote, respectively, the degrees of freedom in the two in-plane and the out-of-plane directions. For introducing the displacement continuities at the layer interfaces, the penalty method is employed. By using the present sandwich element models, a simply-supported square sandwich plate subjected to uniformly distributed lateral load is analyzed, and the accuracy and efficiency of the present sandwich elements are assessed. It is observed that [(332)(332)(332)] element is more accurate than [(110)(110)(110)] element.