Abstract: A system for controlling electrical power supply of an aircraft includes at least two control boards and at least two switching members. Each switching member is connected to each control board. Each control board includes a processor. Each processor is configured to determine a command for switching states of switch contacts of each switching member and to determine information relating to validity of each switching command. Each switching member includes a transmitter to determine a command to be transmitted to a detector to detect parallelization, a power actuator configured to transmit a power signal to the switch contacts depending on the command received from the detector, and switch contacts configured to selectively open or close an electrical power supply line. The command is selected from the switching commands and the information relating to the validity of each switching command.

Abstract: Electrical distribution system for an aircraft comprising at least one computer communicating with the avionics (2), at least one computer (1) suitable for communicating with at least one computer communicating with the avionics (2), each computer containing stored data. The system comprises a context information storage device (4), suitable for storing a copy of the data stored in the different computers, and an updating device, suitable for determining that a computer has been replaced by determining that it does not hold the same data as the other computers of the distribution system and/or as the context information storage device (4), the updating device being suitable for controlling the downloading of the data from the context information storage device or from a computer communicating with the avionics, into the replaced computer.

Abstract: This beam shaper for an aircraft headlight comprises a light input surface (3) and a light output surface (6), the output surface comprises prism-shaped areas so as to deflect a light beam transmitted between the light input surface and output surface by guiding the beam in two directions (D1, D2) which are oblique relative to an optical axis (A) of the beam shaper.

Abstract: An aircraft landing light with static function switching for producing at least two beams having different characteristics, in particular different orientations and/or openings, comprises an array of light-emitting diode lighting modules (6) each comprising at least two sets of at least one light source (S1, S2), operable selectively and statically to provide at least one of the lighting functions. Each lighting module (6) comprises a common converging lens (L) for the light sources, the converging lens comprising a light input optical surface (Li) and a light output optical surface (L2), said light sources being positioned in relation to the light input optical surface.

Abstract: A device for detecting an electrical load connected to an electric power supply network. The device comprises means for injecting a test signal into the electrical network and means for identifying the presence and the nature of an electrical load connected to the electrical network on the basis of the test signal.

Abstract: A multicore data processing system includes a set of data processing cores. At least a part of each data processing core includes a set of local data input and output interfaces for access to peripheral devices dedicated to said cores. It further includes a set of global data input and output interfaces for access to peripheral devices shared between said cores.

Abstract: A control device for a human-machine interface includes a base and a moveable member in the form of a lever or a push element, which can be moved relative to the base. The control device further includes at least one electroactive element positioned between the moveable member and a fixed element of the base.

Abstract: This electromagnetic contactor comprises a set of controlled switches (C1, C2, C3), at least one electromagnetic field generator (L; L1, L2), for example a coil, associated with an adjustable core (P) controlling the state of the controlled switches and a unit (UC) controlling the power supply of the electromagnetic field generator. It comprises means for detecting the position of the adjustable core to detect the state of the controlled switches.

Abstract: A device for electrically connecting power distribution plates, comprises a connector fastened to one end of a first plate and comprising power contacts for a second plate. The connector comprises a pair of separate electrical connection parts which together electrically connect two power busbars of the first plate to two power busbars of the second plate and each includes a base for electrically connecting and mechanically fastening the part to a power busbar of the first plate and a power contact branch extending from the base and intended to interact with a power busbar of the second plate.

Abstract: A device for electrically connecting power distribution plates, comprises a connector fastened to one end of a first plate and comprising power contacts for a second plate. The connector comprises a pair of separate electrical connection parts which together electrically connect two power busbars of the first plate to two power busbars of the second plate and each includes a base for electrically connecting and mechanically fastening the part to a power busbar of the first plate and a power contact branch extending from the base and intended to interact with a power busbar of the second plate.

Abstract: The invention relates to a power communication architecture (100) for an aircraft comprising: a power electronics module management unit (103) that is capable of receiving input signals (104) and of delivering a current setpoint (106); at least one power electronics module (107) that is capable of receiving said current setpoint (106); at least one load (105) that is controlled by the at least one power electronics module (107); the power electronics module management unit (103) storing control laws (108) for controlling the one or more loads (105) allowing a current setpoint (106) to be transmitted according to the input signals (104) and said control laws (108). The invention also relates to an electrical distribution device for an aircraft comprising at least one such architecture.

Abstract: This switching element for an electrical energy distribution board comprises a distribution bar and a support plate on which the distribution bar is fixed. The switching element comprises a coil, a contact movable under the action of the coil, said contact being mounted movably in a chamber. Said chamber comprises two parts intended to be mounted on the distribution board (P) in such a way that the movable contact acts on said bar, said chamber being furnished with means of fixing to the distribution bar or to the plate, the switching element being non-removably fixed by said chamber onto the distribution board (P).

Abstract: Device for transforming and for rectifying polyphase, in particular three-phase, voltage comprising a polyphase transformer comprising a voided central zone, a voltage rectifier circuit that is connected to the transformer and a fan. The voltage rectifier circuit includes at least three heat dissipation units forming a right prism of regular polygonal section comprising a voided central zone, the transformer, the voltage rectifier circuit and the fan being positioned such that at least some of the airflow produced by the fan flows through the voided central zone of the rectifier so as to immerse the transformer.

Abstract: Connection system arranged in a rack, for connecting at least one protection board (13a, 13b) of an electrical distribution system of an aircraft with a primary power supply, to at least one powered device (8a, 8b) and to a motherboard arranged in the rack. The connection system includes at least one modular connector on each protection board and, for each protection board capable of being inserted in the rack, at least one additional modular connector attached at least partly on the rack and at least one additional connector connected to the motherboard.

Abstract: The invention relates to an electrically and thermally connecting device (3) for batteries and pieces of electrical distribution equipment of an aircraft, comprising a casing (5) containing a plurality of bare under-voltage parts (7), said connecting device (3) being intended to make contact with a portion of the casing (5) and at least one bare under-voltage part (7), said connecting device (3) furthermore comprising: at least one base (11) that is made from a thermally conductive material and that is intended to be fastened to the portion of the casing (5); at least one head (13) that comprises a springback connector and that is intended to make contact with the bare under-voltage parts (7) and the portion of the casing (5); and an intermediate element (15) that is intended to electrically connect the bare parts (7), said element (15) being clamped between a base (11) and a head (13). The invention also relates to a battery and to a piece of electrical distribution equipment for an aircraft.

Abstract: A battery cooling and heating device that includes an assembly of plates made from heat-conducting material that are configured to be positioned between the cells of the battery and a heating member in contact with said assembly of plates made from heat-conducting material.

Abstract: A data processing system for a graphical interface includes at least one graphics processing unit (GPU) and at least one central processing unit (CPU) which communicates with the graphics processing unit, said processing unit and said central processing unit each including a group of data processing cores (C1, . . . , C6, C?1, . . . C?6). The data processing cores of the graphics processing unit are each connected to a data processing core of the central processing unit via a single dedicated bus (B1, . . . , B6) in such a way as to carry out a data transfer in parallel between said graphics processing unit and said central processing unit.

Abstract: An optical lighting system for an aircraft includes an optical unit that can be configured according to the phases of flight or taxiing of the aircraft in order to emit a beam of light the spread and aim characteristics of which are dependent on the said phases of flight or of taxiing.

Abstract: Disclosed herein is an assembly for controlling solid-state switching elements in an aircraft having at least one power pathway comprising at least one power line supplying power to at least one item of equipment on board an aircraft from at least one electrical power source via a power switch, and at least one control member controlling at least one power switch according to control signals arising from a control means. The control assembly comprises a single power supply supplying power to the control members.

Abstract: This electric arc extinguishing device for a three-phase power distribution system comprises at least one metal strip (6) and at least one insulating support (7) on which the strip is mounted and comprising means for attaching the device between current distribution bars extending from side to side, the support comprising lateral faces (11) bearing against said bars, the strip being mounted on the support in such a way as to be internally offset relative to said lateral faces.