Patent ID: 8698444
Filing Date: 2014-04-15
Classification: F16H,H02J,Y02T

Abstract:
1. An aircraft electrical actuator arrangement comprising a plurality of electrical actuators coupled to an electrical power distribution network, the electrical power distribution network having at least one master power converter to convert electrical power from the electrical power distribution network for supply to each electrical actuator, the electrical actuators comprising at least one environmental control system actuator, at least one aileron actuator, at least one flap actuator, at least one slat actuator, at least one landing gear actuator, at least one thrust reverser actuator, at least one brake actuator and at least one taxiing actuator, a controller being coupled to the master power converter coupled, the controller being arranged to allow the supply of electrical power from the master power converter to the at least one environmental control system actuator during a first mode of operation of the aircraft, the controller being arranged to allow the supply of electrical power from the master power converter to at least one of the at least one aileron actuator, the at least one flap actuator, the at least one slat actuator, the at least one landing gear actuator, the at least one thrust reverser actuator, the at least one brake actuator or the at least one taxiing actuator during a second mode of operation of the aircraft.