Abstract
Cyclic loads have a significant impact on the fatigue life of aircraft lugs. To evaluate fatigue life of aircraft lugs, an accurate calculation of fatigue life is essential. Therefore, thermal stress and loading angle are introduced to establish the numerical model. Based on Manson–Coffin and Paris formulas, an approach is developed to predict failure of aircraft lugs under thermal stress and oblique loading angle. The numerical results show reasonable agreement with available data for a straight lug with an aligned load and a tapered lug with oblique loads. The results indicate that the fatigue life of aircraft lugs decreases as the surrounding temperature or loading angle increases. The feasibility of the numerical method is verified by the oblique load case.
Published Version
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