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1. An electric flight control system for an aircraft provided with flight control surfaces, said system comprising:
at least one local electro-hydraulic generator to supply, from within a fuselage of the aircraft, hydraulic servocontrols located outside the fuselage and connected to flight control surfaces; a trimmable horizontal stabilizer actuator (THSA) including at least one electric motor; and an electronic module that commonly supplies power to each of the at least one local electro-hydraulic generator and to each of the at least one electric motor, wherein each local electro-hydraulic generator is provided with a fixed frequency AC voltage with a constant rms, and comprises at least one electric motor which is an induction motor powered by said fixed frequency AC voltage with said constant rms value and configured to operate at a constant speed, and the hydraulic servocontrols powered by the at least one electro-hydraulic generator from within the fuselage of the aircraft are located on at least one of a wing, an elevator, or a rudder of the aircraft.
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