OPTIMIZATION AND CHARACTERISATION BY FINITE ELEMENT METHOD OF AN ELECTROMECHANICAL ACTAUTOR FOR MORE ELECTRIC AIRCRAFT APPLICATIONS

The future More Electric Aircraft (MEA) technology focus on increasing the use of electrical equipment to a larger extent, e.g. replacing conventional hydraulic and pneumatic actuators with electromechanical or electro hydrostatic actuators to reduce weight, cost and maintenance. Advances in enabling technologies of electric power generation, distribution, and utility equipment have made the use of electric actuators more competitive. Electric actuation can be based on Electro Hydrostatic (EHA), ElectroMechanical (EMA), or Magnetostrictive Actuator (MA) concepts. In this paper the experiences from a performed electromechanical actuator demonstrator program are presented together with a motor optimization method intended for future programs. The described actuator demonstrator is designed for an Unmanned Aerial Vehicle (UAV) application. The important key design criteria’s for the demonstrator have been reliability, redundancy, torque density, and reduced maintenance