Prediction of Fatigue Crack Growth Rates under Variable Loading Using a Simple Crack Closure Model

摘要

A model which predicts fatigue crack growth rates in aluminum alloys subjected to flight service loading is presented. The model is based on an approximate description of the crack opening behavior and was applied successfully in an analysis of effects of crack growth acceleration and retardation observed experimentally under variable amplitude loading. The model describes effects of the plane strain to plane stress transition and of relatively high overloads on crack growth rate of the crack.