Abstract: A rotating machine assembly includes a rotating machine that has a cover that defines an outer surface of the rotating machine and a stator disposed within the cover. The stator is stationary with respect to the cover. The rotating machine also includes a shaft rotatably disposed at least partially within the cover so as to define a rotation axis. The shaft Includes a first end that is connectable to an aircraft engine and a second end that is opposite the first end. The rotating machine also includes a rotor attached to the shaft, the rotor being movable with respect to the stator and a power module including at least one MOSFET that periodically reverses an electrical current direction of the rotor. The power module includes the at least one MOSFET Is disposed within the cover.

Abstract: An aircraft electrical supply circuit including: a power distribution network, onboard the aircraft, for electrical devices located in an engine of the aircraft or near the engine; and a power supply generator built into the engine of the aircraft to supply AC voltage power to a deicing or anti-icing system. The power supply generator is connected to a thrust reverser electromechanical actuator by a rectifier for supplying DC voltage power to the actuator.

Abstract: A control system for controlling a plurality of distinct functions of a turbojet engine, each function being associated with a respective actuation device. The system includes: an electric motor adapted to supply mechanical energy to each of the actuation devices; an electronic control unit for the electric motor; and at least one switching device interposed between the motor and the actuation devices, the switching device(s) serving to distribute the mechanical energy supplied by the electric motor selectively to one of the actuation devices.

Abstract: An aircraft electrical supply circuit including: a power distribution network, onboard the aircraft, for electrical devices located in an engine of the aircraft or near the engine; and a power supply generator built into the engine of the aircraft to supply AC voltage power to a deicing or anti-icing system. The power supply generator is connected to a thrust reverser electromechanical actuator by a rectifier for supplying DC voltage power to the actuator.

Abstract: The invention relates to a device for regulating the flow rate of fuel taken from a fuel circuit of an aircraft propelled by an engine. The device comprises: a positive displacement pump receiving fuel from a fuel circuit of the aircraft and delivering fuel at a flow rate that is proportional to its speed of rotation; a differential gear having a predefined transmission ratio, a first inlet mechanically coupled to the aircraft engine, a second inlet mechanically coupled to an electric motor/generator, and an outlet mechanically coupled to the positive displacement pump to drive it in rotation; and an electronic control system for regulating the speed of rotation of the electric motor/generator as a function of a setpoint value for the flow rate of fuel to be injected.

Abstract: An electrical power supply circuit in an aircraft is disclosed. The circuit includes an electricity distribution network on board the aircraft for powering electrical equipment situated in an engine of the aircraft or in the surroundings of the engine, and a power supply generator integrated in the engine of the aircraft for powering a de-icing circuit. The electrical equipment includes nacelle loads connected to a DC voltage distribution bus which is connected to a voltage converter circuit powered by the distribution network. The de-icing circuit includes at least one electrical resistance for dissipating electricity returned to the DC voltage distribution bus by at least some of the nacelle loads.

Abstract: A control system for controlling a plurality of distinct functions of a turbojet engine, each function being associated with a respective actuation device. The system includes: an electric motor adapted to supply mechanical energy to each of the actuation devices; an electronic control unit for the electric motor; and at least one switching device interposed between the motor and the actuation devices, the switching device(s) serving to distribute the mechanical energy supplied by the electric motor selectively to one of the actuation devices.

Abstract: The invention relates to an electrical power supply circuit in an aircraft, the circuit comprising an electricity distribution network 17 on board the aircraft for powering electrical equipment 5b situated in an engine of the aircraft or in the surroundings of said engine and a power supply generator 27 integrated in the engine of the aircraft for powering a de-icing circuit 5a. The electrical equipment comprises nacelle loads (5b) connected to a DC voltage distribution bus (35), itself being connected to a voltage converter circuit (34) powered by the distribution network (17). The de-icing circuit (5a) comprises at least one electrical resistance (61) for dissipating electricity possibly returned to the DC voltage distribution bus (35) by at least some of the nacelle loads.

Abstract: The invention relates to a device for regulating the flow rate of fuel taken from a fuel circuit of an aircraft propelled by an engine. The device comprises: a positive displacement pump receiving fuel from a fuel circuit of the aircraft and delivering fuel at a flow rate that is proportional to its speed of rotation; a differential gear having a predefined transmission ratio, a first inlet mechanically coupled to the aircraft engine, a second inlet mechanically coupled to an electric motor/generator, and an outlet mechanically coupled to the positive displacement pump to drive it in rotation; and an electronic control system for regulating the speed of rotation of the electric motor/generator as a function of a setpoint value for the flow rate of fuel to be injected.