摘要：AbstractThe Electro-Pneumatic Actuators (EPAs) using ON/OFF type solenoid valves are very popular in aerospace applications due to their robustness, simplicity, high Torque/Weight ratio, fast speed of response, etc. This paper deals with the modeling, simulation, plant characterization, design of a Pulse Width Modulation (PWM) Controller and model validation of an EPA used in missile applications. The EPA used in this work consists of 3-way, 2-position, ON-OFF type solenoid valves. A non-linear mathematical model of the EPA has been developed and implemented in the MATLAB/SIMULINK environment to carry out the simulation studies. The plant model is characterized in the experiment using Frequency Response Analysis (FRA). A Single Sided Pulse Width Modulation (SSPWM) Controller with phase lead-lag compensators and a proportional gain has been designed for the closed loop position control of the missile fin servo. The model is validated by comparing the experimental closed loop time responses with the simulation.
