Abstract
In order to study the multiple sites damage (MSD) under fatigue loading which was occurring in the airframe of aging aircraft, the digital image correlation (DIC) technique was used to evaluate MSD in the hollow pre-notched specimen with 2024-T4 aluminum alloy subjected to cyclic loading conditions. Fatigue lives and displacement fields obtained from digital images recorded during fatigue tests were used to analyze the crack initiation and propagation. The results show that the fatigue life increases with the increase of hole spacing and that the case of collinear cracks becomes more dangerous than that of non-collinear cracks for MSD specimens. The experiments and DIC analyses were carried out to validate the type of fatigue crack propagation, firstly by mode I, and then by the mode I and II with hybrid expansion. Based on the combination of ABAQUS and Paris formula, stress intensity factors (SIF) and fatigue lives were acquired, which provide the conservative estimation of fatigue life.
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