Aircraft applications demand high reliability and high power density while aiming to achieve simplicity in operation, increased fuel efficiency and reduced costs of operation and environmental impact. Fighter aircraft especially, must have high manoeuvrability and must be able to handle huge thrust as compared to passenger aircrafts. This paper deals with the development of an all electric actuator with the view of replacing the existing electro hydraulic actuator which powers the control surface that controls pitching of the fighter aircraft and provides the same torque and displacement with better manoeuvrability. The rotary motion of electric actuator is translated to linear movement of ball screw which controls the angular motion of control surface. Development of electric actuator involves selection of a motor with high torque to provide electric actuation, and simulating it in Matlab with closed loop feedback control. Switched reluctance motor is considered for the application and it is simulated in closed loop with one common switch converter and C-dump converter so as to the best results. A comparative study of the output of the motor is carried out in using the two different converters.