Abstract: A device for actuating an aircraft undercarriage leg includes an electronic controller and an actuator. The actuator includes a three-phase electric motor connected to the electronic controller. The device is arranged to authorize gravity deployment of the aircraft undercarriage leg. The motor includes a stator having at least first and second star-coupled three-phase windings. The electronic controller includes a first control channel connected to the first three-phase winding, and a second control channel connected to the second three-phase winding. Each of the control channels includes a controller that generates a high-level control instruction, a driver that generates a low-level driver instruction from the high-level control instruction, and a braking circuit that brakes the motor during the gravity deployment of the leg by using energy produced by the motor. The device is arranged to use the control channels as a function of the availabilities of the components of each channel.

Abstract: A bistable linear electromagnet comprising a first housing (10) and a second housing (11) in alignment, a movable armature (18) comprising a rod (19) and a shuttle (20) that is slidably mounted, and a first coil (13) positioned in the first housing and a second coil (15) positioned in the second housing. A cavity (25) is made in a measurement wall (4) of one of the housings, and the electromagnet comprises a magnetic field sensor (26) positioned in the cavity and designed to measure a magnetic flux existing in a magnetic path formed by the walls of said housing and by the shuttle, in order to detect whether the shuttle has moved towards or away from the abutment wall of said first or second housing.

Abstract: Architecture of an aircraft braking system having a brake (20) comprising a plurality of electromechanical actuators (25), with each electromechanical actuator (25) comprising a power module and a digital communication module (26). The brake digital communication modules are interconnected to form a digital network (30). The system also has two control units (22a, 22b) adapted for generating digital signals for controlling electric motors and one network interconnection member (23) connected to two control units and incorporated in the digital network for distributing the digital control signals to the digital communication modules via the digital network.

Abstract: A bistable linear electromagnet comprising a first housing (10) and a second housing (11) in alignment, a movable armature (18) comprising a rod (19) and a shuttle (20) that is slidably mounted, and a first coil (13) positioned in the first housing and a second coil (15) positioned in the second housing. A cavity (25) is made in a measurement wall (4) of one of the housings, and the electromagnet comprises a magnetic field sensor (26) positioned in the cavity and designed to measure a magnetic flux existing in a magnetic path formed by the walls of said housing and by the shuttle, in order to detect whether the shuttle has moved towards or away from the abutment wall of said first or second housing.

Abstract: Architecture of an aircraft braking system comprising: a brake (20) comprising a plurality of electromechanical actuators (25), with each electromechanical actuator (25) comprising a power module and a digital communication module (26), with the brake digital communication modules being interconnected to form a digital network (30); two control units (22a, 22b) adapted for generating digital signals for controlling electric motors; one network interconnection member (23) connected to two control units and incorporated in the digital network for distributing the digital control signals to the digital communication modules via the digital network.