| 摘要 |
An aircraft (40) electrical actuator arrangement comprises a plurality of electrical actuators (11) coupled to an electrical power distribution network, the electrical power distribution network has a master power converter (1) to convert electrical power from the electrical power distribution network for supply to each electrical actuator (11). The electrical actuators (11) comprise an environmental control system actuator (68), an aileron actuator (78), a flap actuator (70), a slat actuator (72), a landing gear actuator (76), a thrust reverser actuator (74), a brake actuator (80) and a taxiing actuator (82). A controller is coupled to the master power converter (1). The controller is arranged to allow the supply of electrical power from the master power converter (1) to the environmental control system actuator (68) during a first mode of operation of the aircraft (40). The controller is arranged to allow the supply of electrical power from the master power converter (1) to at least one of the aileron, the flap, the slat, the landing gear, the thrust reverser, the brake actuator or the taxiing actuator (78, 70,72, 76, 74, 80, 82) during a second mode of operation of the aircraft (40).
|
