Effect of Holes on the Damage Propagation of Composite Plate Using Peridynamic Method

Abstract

The ultimate goal of this research is to investigate the effect of whole orientations on the crack propagation in unidirectional composite materials under a uniform velocity. The composite materials have been extensively utilized in the aerospace industry. To assemble one part of the fuselage to another one, the composite panels should be fastened to each other. Fastening the composite panels can be possible with joint which is necessary to make holes on the panels. The number of holes and their orientations may affect the strength of composite panels. It seems necessary to quantify the strength of composite structures with different number of holes and orientations. It is substantial to obtain the load when crack starts initiating in the composite plates. To fulfill the requirement, the nonlocal theory which is called peridynamic method is employed to study the crack propagation. In this paper, crack initiations, crack propagation, and failure mode is studied using the peridynamic method. The effect of hole and number of orientations is investigated on the strength and ultimate failure of composite plates. The PD simulation results are compared to experimental study for plate with two holes for validation.