Finite Element Analysis of Short-edge Distance of Fastener Holes in Composite Laminates

Abstract

In the production process of aircraft structures, due to design defects or the accumulation of tolerances in part manufacturing and assembly, structural short margins appear at the mechanical joints of composite laminates. In this paper, the analytical method is used to analyze the hole edge stress of the composite material fastener, and the finite element analysis of the short edge distance of the fastener hole of the composite laminate structure is carried out. The hole edge stress and residual net of the structure after the short edge distance. The stress distribution of the cross-section is analyzed to discuss the changes of the stress and strain at the edge of the hole after the short margin of the composite laminate to determine the effect on the strength of the aircraft.