Computational Study of Fatigue Fracture in Rivet Housing of an Aeronautical Aluminum Alloy 7075-T6

This article describes computerized traction testing through the ANSYS software in aircraft materials, aluminum 7075-T6, which leads to variations of the strength limits with the stress concentration factor in the rivet cavity. However, was performed with a change in the radius of transition from the head to the body of the rivet in order to alleviate the stress concentrations within the rivet bore and improve the strength of the part by 5.25% with no relevant change in part displacement. The fatigue strength limit was higher in the samples without of the burr operation, observing that the geometric trunk of the section generated a decrease of 18.27% in the maximum plate stresses, with better uniformity in the tension distribution of the rivets, with a displacement of 3.125% and a minimum equivalent stress of 2.39% and a maximum of 24%, justifying the cause of the fracture in the riveting region.