Abstract: The periodic low-frequency vibration generated by the rotation of the blade of non-fixed-wing aircraft such as helicopters in flight will be transmitted to the cockpit，aero engines and landing gears through the rigid body，which will cause continuous vibration of the body and affect the driving safety of personnel in severe cases. Based on this，this paper proposes a rotating eccentric mass-type vibration damping electric actuator and carries out research on its control method. The output force model and load torque model of the rotating eccentric mass-type vibration damping electric actuator are theoretically derived. The power actuator output force servo control strategy based on the parallel independent control of dual motors is proposed，and the stability analysis is carried out in the complex frequency domain. Aiming at the torque ripple problem caused by sine wave nonlinear load disturbance，the dual-motor parallel independent control strategy is optimized. Through load feedforward control，the system has good robustness and anti-interference. An experimental prototype of a weight of 14 kg is developed and the steady-state and dynamic performance comparison and verification experiments of the electric actuator before and after the optimized control strategy are completed. The results show that the dynamic and steady-state performance of the actuator output force under the optimized control strategy meets the requirements of various technical indicators.