In order to provide the calculation basis of the required power of the rudder surface, theoretical support is provided for the design of the engineering actuator, and a calculation method for the power required by the aircraft elevator is proposed, which is calculated by different types of aircraft examples. First, we explain the different kinds of working conditions, and elaborate the evaluation criteria used for rate calculation. Then, the calculation method of the average rate of load is proposed to analyze the characteristics of the hinge torque. Finally, the calculation of the no-load rate is used to analyze the rudder surface. The calculation results show that the required power calculated by this method not only guarantees the stability margin, but also has theoretical correlation with the rudder surface load. The design results are safe and reasonable, and have practical guiding significance for engineering design.