Abstract: The additional loads generated when the aircraft carries out maneuvering flight make the main bearing stiffness of the aero-engine change, which affects the dynamic characteristics of the aero-engine rotor system. Considering the interaction and relative position relationship between rolling body and inner and outer rings, the quasi-static model of rolling bearing is established, and coupled with the rotor finite element model, the dynamic model of rolling bearing-rotor system is established to consider the role of typical hovering maneuvering load; the system dynamic equations are solved by using the Newmark-β integration method to reveal the changing law of the bearing stiffness characteristics under the action of maneuvering load; based on the results of bearing stiffness analysis, the dynamic characteristics of the rotor system under different maneuvering flight conditions are analyzed. The results show that: the maneuvering load will make the bearing stiffness change nonlinearly, and the bearing stiffness change trend is opposite under the action of additional centrifugal force and additional gyroscopic moment; under the maneuvering flight condition of different radii, the bearing stiffness change trend is dominated by the additional centrifugal force or the additional gyroscopic moment, respectively; the maneuvering load makes the first-order critical speed of rotor increase, and the stiffness enhancement effect is produced for the whole system; the additional centrifugal force and additional gyroscopic moment make the axis trajectory of the wheel center offset in different directions, and the nonlinear change of bearing stiffness under maneuvering load will change the offset.