Design of Eccentric Mass-Type Vibration-Damping Electric Actuator Control System for Non-Fixed-Wing Aircraft

The main spiral blade of non-fixed wing aircraft will produce periodic vibration force when rotating, which will not only reduce the service life of airborne equipment, but also greatly affect the working state of pilots. Due to the narrow damping band of passive damping device, it is difficult to meet the vibration reduction requirements of modern aircraft. Therefore, this article proposes an eccentric mass block type electrical control system based on active vibration control Force actuator system and a prototype is developed. In this article, the output force model of eccentric wheel type anti vibration actuator, the periodic fluctuating load model of motor side, the linearization model of gear clearance and the dynamic model of the whole electric actuator are established. Secondly, according to the system stability control requirements, the controller parameters of the electric actuator are designed. The maximum value of the gear clearance dimension is introduced into the control system to correct the controller parameters, and provide theoretical design basis for the actuator gear clearance size. Finally, the sensitivity function from the disturbance side to the control error side is calculated. The effectiveness of the parameters and the robustness of the control system are verified by the sensitivity
$H_{\infty }$
control theory. The results show that the prototype has good dynamic and steady-state performance and meets the vibration control requirements of the main spiral blade of the non-fixed wing aircraft.