An alternative three-node triangular composite shell element in terms of Reddy-type higher-order theory

Abstract

Composite curved shells are widely utilized as structural components in aerospace engineering. To inspire the potentiality of such structure, it is very necessary to well understand mechanical behaviors of composite curved shells. Compared to the composite plates, it is more difficult to predict accurately interlaminar stresses of composite curved shells. Therefore, this paper attempts to propose an alternative triangular composite shell element in terms of the Reddy-type global–local higher-order theory. In the present model, the continuity conditions of transverse shear stresses are enforced in advance to fulfill compatibility of transverse shear stresses at adjacent layers, which can improve precision of interlaminar stresses. In order to evaluate performance of the proposed shell element, several typical examples have been analyzed. Moreover, the results acquired from the present model are compared with the three-dimensional elasticity solutions and other published results. At the same time, a compression experiment of the thin-walled cylindrical grid structure is carried out to further verify the capability of the present model. These examples show that the proposed composite shell element can be used as an alternative method for static analysis of multi-layer thin and thick shell structures.