For the long-serving aircraft, the holes in the overlap of the aircraft skin will change from circular holes to elliptical holes under the action of load. It is of great significance to calculate and analyse the stress intensity factor of the multi-elliptical hole-edge crack for the fracture mechanics analysis. This paper used the analytical calculation methods of finite truncation method and residue method. Both methods are based on the theory of complex function and combined with the approximate superposition method to calculate the stress intensity factors of cracks on the edge of multiple elliptical holes. Take the infinite plate with symmetrical cracks at the edge of two collinear elliptical holes as the research object. Calculate the stress intensity factors of the cracks at the edge of elliptical holes under different modes such as different semi-axial ratios and different hole spacings. The results show the residue method is more concise than the finite truncation method in calculating stress intensity factors for multiple elliptical holes, and the calculation error is smaller and the calculation efficiency is higher.
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