Abstract
The effects of hole reaming (HR) after pre-fatigue damage on fatigue performance of AA2198-T8 were studied by using the digital image correlation (DIC) technique. The influences of stress distribution of the rivet hole on fatigue life were studied. When maximum axial strain is equal to 0.0005, the number of fatigue cycles is suggested as the fatigue crack initiation life. The prediction of fatigue lives by the calculation method combining Paris law and ABAQUS, and the experimental results are within a factor of 1.2-scatter band. This work provides a reference for the maintenance of fatigue damaged rivet holes in aircraft structure.
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