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

Abstract: A heater that inhibits the formation of ice in an air gap separating a stationary stator and a rotatable rotor of a rotating machine. The heater includes a plurality of stringers configured to be arranged in associated winding slots of the associated stator adjacent the air gap, and extending between two ends of the heater. Each of the stringers includes two electrical resistance heating traces arranged between two electrical insulation layers that are arranged between two thermal conduction layers. The traces extend along an entire length of each of the stringers between the two ends of the heater. The traces are electrically isolated from each other.

Abstract: An electrotechnical device for an aircraft includes a housing having a surface and a magnetic circuit formed by a stack of laminated sheets and composed of a yoke. The yoke is fixed on the surface of the housing by means of a thermal interface and has a surface. At least one low-frequency coil component is attached to at least part of the surface of the yoke by attachment means.

Abstract: A three-phase rotary transformer includes a first, a second and a third primary coil respectively associated with a first, a second and a third secondary coil. The second primary and secondary coils each include a first and a second sub-coil. Each of the first and third coils are housed with a respective sub-coil of the second coil respectively in a first and in a second housing of a slot of a magnetic body. For each slot, the housing corresponding to a sub-coil, has an axial dimension greater than an axial dimension of the housing corresponding to the corresponding coil.

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 method for detecting an electrical arc in an electrical system including analyzing a reflectogram representative of a spatial distribution of impedance in said electrical system and, when an electric arc is identified in the reflectogram, incrementing a detection counter by one unit.

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 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 system for generating air includes: an electromechanical device generating an airflow equipped with an air inlet opening and an outlet; a casing extending between a first end attached to the air inlet opening and a second end located opposite the first end, the casing including two parts together defining a closed recess, each part including a hollow wall defining a channel extending between the two ends of the casing, each channel opening in front of the air inlet opening so that the electromechanical device is supplied with air routed by the channels; and at least one electronic card for power supply or control of the electromechanical device located in the recess of the casing.

Abstract: Methods for determining a maximum duration of use of a battery, include: selecting a period of use of the battery; obtaining values of factors of degradation of the battery during the period of use of the battery selected during the selection step; determining at least one indicator of ageing of the battery on the basis of the degradation factor values obtained in the step of obtaining said values; and identifying intervals of variation of the degradation factors during said period of use, each ageing indicator being associated with actual variation intervals which each have a minimum value and a maximum value of said factors used during the determination step; and a step of predicting the maximum duration of use on the basis of the variation intervals obtained in the step of identification, the at least one ageing indicator and the operating limits of the battery.

Abstract: Aircraft comprising a primary propeller driven in rotation by a motor, the motor having a first assembly and a second assembly movable in rotation relative to each other along an axis of rotation, the primary propeller being secured in rotation to one of said first assembly and second assembly, the first assembly and the second assembly being movable in translation relative to each other along a direction of translation defined by the axis of rotation, between a rest position and a service position, characterized in that said aircraft comprises a locking system, comprising a housing and an indexing element, the housing being formed in one among the first assembly and the second assembly, the indexing element being secured to the other among the first assembly and the second assembly, the locking system having an engaged configuration in which the indexing element is at least partially inserted into the housing.

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 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 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 comprising a fuselage (1) subdivided by a floor (2) into a top volume (3) and a bottom value (4) in which girders (5) extend supporting the floor and co-operating with the fuselage and the floor to define two lateral housings (6) that are of substantially triangular cross-section and that extend parallel to a longitudinal axis of the fuselage. Calculation units (100) are arranged in the lateral housings and each comprises a box (101) defining a main compartment containing calculation modules (122) insertable into the main compartment along an insertion axis through an opening in the compartment and connectable to the connectors (115) carried by a back wall (116) of the compartment so as to extend into the main compartment opposite from the opening, the insertion axis being substantially parallel to the longitudinal axis of the fuselage.

Abstract: The invention concerns a helicopter ventilation architecture, said helicopter comprising at least two avionics bays (112a, 112b) comprising electronic equipment (116a, 116b) to be ventilated, said architecture comprising, for each avionics bay, an air inlet (120a, 120b) allowing outside air to enter the avionics bay in order to ventilate said avionics bay, and an air outlet (124a, 124b), allowing the air ventilating the avionics bay to exit the avionics bay, characterised in that the ventilation architecture further comprises a mixing chamber (134), connected to the air outlets, configured to receive the air originating from all the avionics bays, at least one air duct (138a, 138b), connected to the mixing chamber and to an outlet (130a, 130b) for discharging the air to the outside, and at least two fans (128a, 128b), arranged and distributed in the air duct or ducts.

Abstract: A generator for comprising a rotor, an inner shaft, an outer shaft, and an actuation means. The inner shaft is at least partially disposed inside the outer shaft. The inner shaft is coupled to the outer shaft by means of a translatable drive connection. The actuation means is configured to actuate the second shaft towards a retracted position. The translatable drive connection is configured to allow a transfer of torque between the first and second shafts, and enables movement of the second shaft, relative to the first shaft, along its axis of rotation from an extended position to a retracted position, such that an input portion of the second shaft can be at least partially retracted in a retraction direction towards the rotor upon activation of the actuation mechanism. A disconnect mechanism disposed on the second shaft can therefore be disconnected upon retraction of the second shaft.

Abstract: A power assembly that has at least two power modules that each have at least one component to be cooled, for example, an electronic chip mounted on a base from which cooling elements extend. Each power module also has a hollow body with a channel for flow of a coolant fluid Each power module is mounted on each respective body so that the cooling elements extend at least partially into said channel through an opening of the body. At least one deflector is mounted in the channel between the cooling elements of the two modules so as to force the coolant fluid to flow in the zone of the channel comprising the cooling elements.

Abstract: A propulsion unit for an aircraft, including an engine and a propeller shaft 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.

Abstract: The present invention relates to a device (1) for monitoring the degradation of rolling bearings (15a, 15b) in a rotating machine (10) comprising at least two rolling bearings (15a, 15b) each having two concentric rings (16-18) rotating relative to each other, at least one ring (17, 18) of each bearing (15a) being rotationally connected to a ring (17, 18) of another bearing (15b). The device (1) comprises a member (30) for measuring the speed of rotation (?1) of the rotationally connected rings (17, 18), and data processing means suitable for detecting a variation in the speed of rotation (?1) of the rotationally connected rings (17, 18), which variation is representative of degradation of a bearing (15).