In order to study the fatigue gain of cold expansion-strengthening 7050 aluminum alloy hole components of aircraft fuselage， a combination of numerical simulation and experimental study is used to investigate the cold expansion strengthening process， fatigue loading process， fatigue crack initiation and crack propagation process of hole components. The stress distribution and corresponding fatigue behavior of hole components at different states of the dangerous cross-section are investigated by numerical simulation， the influence of the residual stress field on the fatigue performance is analyzed， the intrinsic connection between residual stress and fatigue crack initiation and crack propagation is explored， and a numerical prediction model of the fatigue life of cold expansion-strengthening hole components is established. The results show that the residual compressive stress introduced by hole cold expansion strengthening can reduce the maximum tensile stress in the hole wall when hole components are loaded， change the location of fatigue crack emergence， inhibit fatigue crack emergence and crack propagation， and improve the fatigue life of 7050 aluminum alloy hole components by nearly 2 times. And the error of the fatigue life numerical prediction model is within 12%.