Fatigue Life Analysis of Aircraft Structural Components
Stevan Maksimović, PhD (Eng)[1])
This work defines an effective computation procedure that combines Neuber`s Rule and the finite element method with strain–life criterions in order to accurately predict fatigue crack initiation life and then establish an estimated schedule of fatigue life. The proposed procedure is applied to the representative aircraft structural components such as a plate with hole to obtain predicted lives. Computation results are compared with experimental results. Comparative results demonstrate that the fatigue life estimated by the novel procedure closely approximates the experimental results.
Key words: fatigue, aircraft, aircraft structures, scyclic loading, crack initiation, finite element method, numerical simulation.