The aging aircraft fuselage skin contains multiple hole edge cracks

and the skin holes will change from circular holes to elliptical holes under loads.The calculation of stress intensity factors for multiple elliptical hole edge cracks is an important problem in a fracture mechanics analysis.An analytical calculation method based on a complex function theory and an approximate superposition method was used to solve the stress intensity factor of multiple elliptical hole edge cracks under the farfield stress

and the change rules of stress intensity factors under several modes of symmetric cracks at the edge of double elliptical holes

inner cracks at the edge of double elliptical holes

outer cracks at the edge of double elliptical holes and cracks on the same side of double elliptical holes were analyzed.The numerical examples show that the stress intensity factor of the crack at the edge of multiple elliptical holes is affected by the crack length

the half-axis ratio of elliptical holes and the spacing of holes.As the crack tip approaches gradually

the interference phenomenon between cracks tends to be significant.