Abstract: | Aiming at the flutter impact factors of the elastic large inertia electromechanical actuator system in an unmanned aerial vehicle (UAV), the influence of transmission stiffness, clearance, inertia, and damping on the actuator system is analyzed. Firstly, through the analysis of the flutter phenomenon, the cause of the flutter is located. Secondly, the factors affecting the flutter of the double inertia system are analyzed by simulation. Finally, through the experimental verification, it is considered that by properly increasing the damping of the actuator and modifying the control algorithm, the effects of elastic vibration of the connecting mechanism and large load inertia can be reduced. The input shaper is used in the control algorithm to effectively suppress the flutter caused by specific square wave command. Through experimental verification, the improved actuator reduces the flutter caused by elastic large inertia electric, and the residual flutter of the actuator surface is eliminated. |