Pit is a kind of damage form that often occurs in the daily operation process of aircraft. It is formed by permanent plastic deformation due to the impact of foreign objects. In addition to the stress concentration caused by structural geometric changes, it will also produce local residual stress in the interior. Its impact on fatigue cannot be evaluated only through the stress concentration analysis of structural geometric changes. In this paper, the bearing capacity of the damaged metal skin dent is studied. By establishing the finite element model, the stress of the intact structure and the dent with different width depth ratio is compared and analysed.

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In the production process of aircraft structures, due to design defects or the accumulation of tolerances in part manufacturing and assembly, structural short margins appear at the mechanical joints of composite laminates. In this paper, the analytical method is used to analyze the hole edge stress of the composite material fastener, and the finite element analysis of the short edge distance of the fastener hole of the composite laminate structure is carried out. The hole edge stress and residual net of the structure after the short edge distance. The stress distribution of the cross-section is analyzed to discuss the changes of the stress and strain at the edge of the hole after the short margin of the composite laminate to determine the effect on the strength of the aircraft.