Fatigue damage analysis of wing-fuselage attachment lug

Abstract

In the present paper, the fatigue behavior of failure critical pin-loaded lug with the through-the-thickness crack at a hole is analyzed. Such an investigation examines the stress analysis and the residual life estimation through a computational model here proposed in which suitable fracture mechanics concepts are employed. Hence, the stress ratio dependence crack growth model is taken into account to assess the fatigue strength of damaged lug. Further, in order to calculate the stress intensity factor, fracture mechanics based analytical and numerical approaches are applied. Finally, to demonstrate the compatibility of developed model, relevant experimental data are used. Such crack growth observations show a fairly good correlation with obtained failure assessments.