Abstract: A propulsion and non-propulsive electrical generation system for an aircraft having at least one turbomachine and at least two pairs of rotors, the rotors of the same pair of rotors being symmetrically opposite on the aircraft with respect to the same center of symmetry, at least four motors each driving a rotor, at least one generator coupled to a turbomachine, an even number of power lines and at most equal to the number of rotors, each power line having at least one propulsion branch coupled to a motor, a battery coupled at the output to the propulsion branch, and an AC-DC converter coupled between an output of a generator and the propulsion branch.

Abstract: A method for starting a permanent magnet synchronous electric motor comprising a rotor and a stator comprising coils connected respectively to a plurality of phases and a conversion circuit connecting the plurality of phases to a power supply source in order to control the rotation of the rotor of the synchronous motor, the conversion circuit comprising a converter supplying power to a DC-AC converter comprising a plurality of controllable transistors for controlling the rotation of the rotor according to a plurality of successive control phases, the method comprising: ? a step of controlling the transistors of the DC-AC converter according to a control table associating each control phase with a configuration of the transistors so as to determine an acceleration ramp of the rotor of the motor, ? a step of determining an electrical angle A based on a predetermined acceleration ACC, and ? a step of determining a control phase change signal Q if the electrical angle A is greater than a predetermined threshold a

Abstract: An aircraft with hybrid thermal/electrical propulsion includes a turbomachine; a first electrical source; a second electrical source equipped with an electrical energy storage device; a non-propulsion electrical distribution network; a low-voltage electrical distribution network; and a propulsion electrical distribution network. The three electrical distribution networks are electrically supplied by the first and second electrical sources and electrically interconnected by static converters.

Abstract: The invention concerns a method for controlling an assembly of at least two inverters (1a, 1b) in an electricity generating system with parallel inverters. The method comprises the implementation by at least one data processing unit (2a, 2b) of the steps: (a) for each inverter (1a, 1b) of the assembly, obtaining an input duty factor (PWMi) of an input signal (Si) received by the inverter (1a, 1b), (b) calculating a mean duty factor (PWMm) from the input duty factors (PWMi), (c) modulating and synchronising the input signal (Si) received by each inverter (1a, 1b) into an output signal (So) having an output duty factor (PWMo) corresponding to the mean duty factor (PWMm).

Abstract: The invention relates to an architecture of a propulsion system of a multi-engine helicopter comprising turboshaft engines connected to a power transmission gearbox, characterised in that it comprises: at least one hybrid turboshaft engine (20) capable of operating in at least one standby mode during a stable cruise flight of the helicopter; at least two systems (30; 40) for controlling each hybrid turboshaft engine (20), each system (30; 40) comprising an electric machine (31; 41) connected to the hybrid turboshaft engine (20) and suitable for rotating the gas generator thereof, and at least one source (33; 43) of electrical power for said electric machine (31; 41), each reactivation system (30; 40) being configured such that it can drive said turboshaft engine (20) in at least one operating mode among a plurality of predetermined modes.

Abstract: A method for controlling a system for generating electric power for a power distribution network of an aircraft, the system for generating electric power comprising a generator, a rectifier, an inverter which produces a voltage according to several fixed-frequency phases, a DC voltage bus which connects the rectifier to the inverter, the control method comprising: —a correction step to determine at least one correction quantity GC, —a step of determining a signal SO for controlling the inverter from the determined correction quantity GC, —a step of determining a signal SG for controlling the generator from the determined correction quantity GC and —a step of transmitting the control signals SO, SG to the inverter and to the generator, respectively.

Abstract: A method for controlling an inverter configured to power electrically a motor including a stator and a rotor capable of being rotated relative to the stator when the motor is electrically powered, the inverter including a plurality of switches suitable for being controlled to open/close in order to regulate the power supply of the motor, each switch having a predetermined transition time from a closed state to an open state, and a predetermined transition time from the open state to the closed state, wherein the method includes the step of not generating the command to open and close the switches when this violates the predetermined transition times from a closed state to an open state, and the predetermined transition times from the open state to the closed state.

Abstract: An electrical control device including at least one power module which further includes at least one controlled power switch, at least one control card attached to the power module, and electrical connection which connect the control card to the control module. The electrical connection includes at least one pin which is electrically connected and extends from the power module, or, respectively, the control card, and at least one receptacle which is electrically connected and mounted on the control card, or, respectively, the power module, the pin being inserted, at least partially, into the receptacle. The pin and the receptacle is designed to provide an electrical connection between them whilst allowing the pin to be removed from the receptacle.

Abstract: A method for controlling a system for generating electric power for a power distribution network of an aircraft, the system for generating electric power comprising a generator, a rectifier, an inverter which produces a voltage according to several fixed-frequency phases, a DC voltage bus which connects the rectifier to the inverter, the control method comprising: —a correction step to determine at least one correction quantity GC, —a step of determining a signal SO for controlling the inverter from the determined correction quantity GC, —a step of determining a signal SG for controlling the generator from the determined correction quantity GC and —a step of transmitting the control signals SO, SG to the inverter and to the generator, respectively.

Abstract: Electronic module comprising a protective casing defining an internal volume and an electronic board placed in the internal volume, the electronic module comprising: means, for detecting a predetermined environmental condition of the internal volume, means for generating a cool zone inside the internal volume, which means are arranged such that the cool zone is separated from the electronic board; a control unit that is linked to the means for detecting an environmental condition and to the means for generating a cool zone and arranged to trigger the means for generating a cool zone when the means for detecting a predetermined environmental condition in the internal volume detect an environmental condition that is liable to result in the moisture in the air contained in the internal volume condensing on the electronic board.

Abstract: An electric circuit for a power converter having a substrate having a first face on which electronic components are mounted and a second face intended to cooperate with a cooling system, the substrate having a stack of conductive layers made of electrically and thermally conductive material and at least one insulating layer made of electrically insulating material, two successive conductive layers being separated by an insulating layer, and the conductive and insulating layers extending in parallel planes and being mechanically associated together. Each conductive layer has two opposite faces parallel to the plane in which the first face of the substrate extends and includes, on at least one of its two faces, at least one boss extending in a direction perpendicular to the plane, the at least one boss passing through at least one other conductive layer and opening out onto the first or the second face of the substrate.

Abstract: An assembly including an accessory gearbox mechanically connected to an electricity generator having a support shaft that includes a calibrated breakable section designed to disconnect the electricity generator physically from the accessory gearbox when an incident is detected on the electricity generator, the protection device including an unlocking mechanism provided with a lock that, under the action of an external control unit, releases a cutting tool so as to cut said calibrated breakable section.

Abstract: Air compressor comprising a centrifugal-type compression wheel defining an axial direction and a radial direction, an air intake opening extending circumferentially around the compression wheel and opening onto a compression part, the compression part comprising a first portion forming a volute for the ejection of compressed air which is mounted facing the compression wheel in the radial direction, and an at least partly annular second portion extending around the first portion, the second portion comprising a central orifice receiving at least part of the compression wheel and an air deflection torus, the volute being made of metallic material and the torus made of thermoplastic material filled with non-metallic elements, the thermoplastic material having a thermal expansion corresponding to that of the metallic material.

Abstract: The invention relates to a system for synchronising energy sources coupled to an electrical grid supplying at least one electrical load of an aircraft, said system comprising; a main source of electrical energy supplying said electrical load comprising a multi-stage generator, said multi-stage generator comprising; a primary stage comprising a generator with permanent magnets, a secondary stage comprising an excitation, and a tertiary stage comprising a main generator; an auxiliary source of electrical energy supplying said electrical load; and a device for synchronising the main source and the auxiliary source, designed to measure an electrical voltage at the outlet of the primary stage of the main source, and to control the supply of said electrical load by means of the auxiliary source of electrical energy at an electrical voltage slaved to the characteristics of frequency and phase of the electrical voltage of the primary stage.

Abstract: A helicopter turbomachine includes an electric starter motor configured to rotate a drive shaft, a heat sink for cooling the electric motor, and a reversible ventilation wheel driven by the electric motor. The turbomachine also includes an overrunning clutch that transmits the torque from the electric motor to the drive shaft. The electric motor is configured such that, in the first direction of rotation, the motor rotates the drive shaft and the ventilation wheel to generate an air flow through the heat sink in a direct direction, and, in the reverse direction of rotation, the motor rotates only the ventilation wheel to generate an air flow through the heat sink in a direction opposite the direct direction.

Abstract: The disclosure relates to a brushless and magnet-free synchronous electrical machine, wherein it comprises a stator (20) comprising a ring (22), a winding (28) and a tooth system (24) comprising teeth (26) extending parallel to the axis of rotation from the ring (22), said winding being wound around the tooth system (24), a rotor (10), comprising a first portion (12a) extending in p preferred directions (18a), a second portion (12b) extending in p preferred directions (18b) shifted by p with respect to the preferred directions of the first portion (18a), and an intermediate portion (14) linking the first portion (12a) to the second portion (12b), and a coil (40) for exciting the rotor, fixed with respect to the stator, supplied with a DC electric current, positioned around the intermediate portion (14) of the rotor and configured so as to generate an electric flux in the rotor (10) through magnetic induction.

Abstract: A system comprising a rack and at least one line replaceable module, the rack further comprising a primary transmission circuit comprising a primary antenna, primary emission components designed to generate an emitted power containing uplink data, and primary receiving components designed to receive downlink data, the line replaceable module comprising a secondary transmission circuit comprising a secondary antenna, secondary receiving components designed to receive the emitted power and the uplink data, and secondary emission components designed to generate the downlink data, the emitted power, the uplink data and the downlink data being transmitted via a shared coupling between the primary antenna and the secondary antenna.

Abstract: An electrical power distribution assembly for an airplane, the assembly including an electric switch device for placing in a Karman fairing of the airplane.

Abstract: A circular electric connector including a socket extending along an axis and provided at an axial end with cavities, and a sealing grommet provided on the axial end defining a front face through which electric elements may be inserted in the cavities and a circumferential wall, the connector additionally including a housing wherein the socket is housed, the housing including an attachment device for attachment with a backshell, the connector including a retaining ring around the circumferential wall of the grommet, the retaining ring being adapted to limit the expansion of the diameter of the grommet when the electric elements are inserted through the grommet. A connection may be made with such a connector and a known or modified backshell.

Abstract: A propulsion unit for an aircraft, including an engine and a propeller and further a propeller with airfoils which is coupled to the propeller shaft and having electrical members consuming electrical power, sealing between a case and the propeller shaft being ensured by a dynamic seal housed between a rotating dynamic seal support secured to the propeller shaft and a dynamic seal support flange secured to an end portion of the case, the rotating dynamic seal support being secured to the propeller shaft and abutted against a bearing for supporting this propeller shaft, it is provided that the propulsion unit, in order to deliver electrical power to the electrical members, having a rotating transformer rotated by the propeller shaft and including a stator, a casing of which is secured to the dynamic seal support flange and a rotor, a casing of which is secured to this propeller shaft.