Dynamic performance of a matrix converter driven electro-mechanical actuator for an aircraft rudder

A dynamic model of a matrix converter driven electromechanical actuator for a civil aircraft rudder is developed. The model focuses on the dynamic system response and represents the matrix converter in all averaged manner without switching to achieve fast Simulation. Simulation results showing step response and frequency response of the actuator system are given. The dominant parameters that affect the speed of response in changing the position reference are, the maximum speed of the electrical machine, the inertia of its rotor, and the maximum current.