关键词: 疲劳寿命, 局部应力应变, 机翼

Abstract: Finite Element Analyses are carried out for a complex aircraft wing structure and more detailed analyses are made by using refined three-dimensional mesh at the critical hole region.Several aircraft flight attitudes to account for the complicated load histories are analyzed. Neuber's formula is used to convert elastic stresses at critical point from FEM into elastoplastic stresses and strains. Different cyclic stress-strain curves of the relevant material are considered and results compared. The fatigue damage is accumulated cycle by cylcle and the structure life is reached when the damage reaches unity.The predicted life of the aircraft wing agrees well with the actual fatigue test.

Key words: fatigue life, local stress-strain, wing