Abstract: Said device (16) for controlling an electrical thrust reverser control system (1) for an aircraft comprises electrical supply means (9) and control means (19) which are configured to couple the electrical supply means (9) to the electrical control system (1) when the aircraft is on the ground and to uncouple the electrical supply means (9) from the electrical control system (1) when the aircraft is flying.

Abstract: A testability method for the in-flight testing of an operating state of an electronic power chain having at least one power converter intended for driving an electric motor that actuates at least one aircraft component includes controlling actuation of the converter, transmitting a test signal, collecting at least one measurement signal, and determining an operating state.

Abstract: An electrical control system intended for an aircraft turbojet engine nacelle includes two control modules of a single power module controlling an electric machine and an approval module linking each of the control modules to the single power module. The approval module selectively authorizes the control of the single power module by one of the control modules.

Abstract: A testability method for the in-flight testing of an operating state of an electronic power chain having at least one power converter intended for driving an electric motor that actuates at least one aircraft component includes controlling actuation of the converter, transmitting a test signal, collecting at least one measurement signal, and determining an operating state.

Abstract: A thrust reverser device for an aircraft includes at least two thrust reversers, and each of them includes a movable cowl movably actuated by an actuator driven by an electric motor. The electric motor is powered by a single power-conversion module including at least one autotransformer which is supplied with an alternating electric voltage and connected to at least one rectifier stage converting the alternating electric voltage into a direct voltage. The rectifier stage is connected to a current balancing stage and a current smoothing stage, supplying with the direct voltage the electric motor of the electric actuator of the movable cowl.

Abstract: A control system for a thrust reverser with a movable cowl includes an electromechanical actuator to actuate the movable cowl, an electric drive unit (M) driving the actuator, and a power control unit capable of controlling the electric drive unit (M). The power control unit moves the movable cowl to a closed position and/or to a deployed position. In particular, the control system includes an electronic circuit for electric braking capable of braking the electric drive unit (M), in case of overspeed of the drive unit when the movable cowl is moved to the closed position and/or to the deployed position.

Abstract: A thrust reverser device for an aircraft includes at least two thrust reversers, and each of them includes a movable cowl movably actuated by an actuator driven by an electric motor. The electric motor is powered by a single power-conversion module including at least one autotransformer which is supplied with an alternating electric voltage and connected to at least one rectifier stage converting the alternating electric voltage into a direct voltage. The rectifier stage is connected to a current balancing stage and a current smoothing stage, supplying with the direct voltage the electric motor of the electric actuator of the movable cowl.

Abstract: A control system for a thrust reverser with a movable cowl includes an electromechanical actuator to actuate the movable cowl, an electric drive unit (M) driving the actuator, and a power control unit capable of controlling the electric drive unit (M). The power control unit moves the movable cowl to a closed position and/or to a deployed position. In particular, the control system includes an electronic circuit for electric braking capable of braking the electric drive unit (M), in case of overspeed of the drive unit when the movable cowl is moved to the closed position and/or to the deployed position.

Abstract: The invention relates to a filtering device connected between a rectifier module of a variable speed drive and an alternating current power supply network, the filtering device comprising an EMC filter comprising a common-mode inductor having a winding on each phase of the power supply network, the windings being magnetically coupled together. The filtering device comprises a shunt circuit connected in parallel with at least one of the windings of the common-mode inductor, the shunt circuit comprising passive components and making it possible to shunt a common-mode current flowing in the common-mode inductor in a frequency zone about a resonance frequency of the EMC filter.

Abstract: The invention relates to a filtering device connected between a rectifier module of a variable speed drive and an alternating current power supply network, the filtering device comprising an EMC filter comprising a common-mode inductor having a winding on each phase of the power supply network, the windings being magnetically coupled together. The filtering device comprises a shunt circuit connected in parallel with at least one of the windings of the common-mode inductor, the shunt circuit comprising passive components and making it possible to shunt a common-mode current flowing in the common-mode inductor in a frequency zone about a resonance frequency of the EMC filter.