Abstract: In order to accurately obtain the fatigue performance parameters of the typical structural details of aircraft and verify the rationality of stress and durability life calculation method, two types of typical structural detail simulation specimens were designed with 7075-T7651 aluminum alloy and 05Cr13Ni8Mo2Al stainless steel as the research objects, and the fatigue test under the random spectrum was carried out. Based on the fracture surface observation results of scanning electron microscope, the fracture surface inversion model was established by combining Paris formula and trapezoidal method, and the inversion methods of crack initiation life, propagation life and stress amplitude were systematically studied, then the method effectiveness was verified by combining multiple engineering application cases. The results showed that the fracture surfaces of both types of material simulation specimens exhibited typical fatigue characteristics, and the crack sources were mostly located in the stress concentration area. Paris formula was suitable for life inversion in the stable propagation stage, and the trapezoidal method was more suitable for the calculation of full-cycle life under complex loads. The relative error absolute value between the fatigue life obtained by inversion and the measured value was less than 7%, and the stress amplitude calculation results matched well with the design load spectrum. This study provides reliable fracture surface inversion technical support for the fatigue performance evaluation of aircraft structural details.