Affiliations: [a] School of Mechanical and Electronical Engineering, Central South University, Changsha, China
| [b]
School of Mechanical Engineering of North University of China, Taiyuan, China
| [c]
Xi’an Aerospace Precision Electromechanical Research Institute, Xi’an, China
Correspondence:
[*]
Corresponding author. Haoxin Zheng, School of Mechanical and Electronical Engineering, Central South University, Changsha 410083, China. E-mail: [email protected].
Abstract: The actuator is an important component of missiles and other aircraft to maintain the flight attitude. A method to calculate the power of the electric servo motor was proposed according to the load characteristics’ of both the servo motor and actuator. An optimization method for the transmission reduction ratio was obtained by considering the load torque equation. Dynamics simulations of the actuator were conducted under a variety of conditions. The simulation results show that the clearance and the friction between the ball screw and the fork, which consist of the transmission mechanism, induce the torque fluctuations, as a source of noise in the motor load. According to the optimization design of the Electric, the Actuator prototype has passed the test, the performance meets the design requirements.
