Abstract :
The concept of replacing the hydraulic system with electric actuation, coupled with changes to the electric generation technology and flight control systems, is commonly termed the all-electric-aircraft. Earlier studies have shown that the all electric aircraft can give the aircraft´s manufactures and operators considerable cost benefits, particularly due to reductions in system complexity and overall weight. The all-electric-aircraft concept can be subdivided into fly-by-wire, where the hydraulically or electrically powered flight actuators are electrically signalled, and power-by-wire, where the actuators are directly powered from the aircraft´s electrical system. The key to the implementation of the power-by-wire aircraft, is the development of compact, reliable, electrically powered actuators to replace the conventional hydraulic system. With recent developments in high performance motors and power electronics research is being undertake to develop suitable electrical actuators. Electrically powered flight actuators can take one of two principal configurations, the electromechanical actuator with mechanical gearing, and the electrohydrostatic actuator with, fluidic gearing, between the motor and the actuated surface
