The invention relates to a method for controlling a power converter connected to a DC voltage network and comprising a rotary electric machine, the converter comprising parallel electrical arms, each provided with at least two MOSFETs, and a control circuit comprising a protection module configured to prevent the simultaneous conduction of the MOSFETs in the same arm. The method comprises: - detecting (410) a short circuit in the network; then - deactivating (420) the protection module; and - controlling (430) the MOSFETs in an ideal diode mode, wherein each MOSFET conducts as soon as the voltage at its terminals is negative, thereby causing simultaneous conduction of the MOSFETs in the same arm when the current flowing through the filter inductor exceeds the current supplied by the electric machine, and in a synchronous rectification mode once the current is lower.
H02P 29/024 - Détection d’un défaut, p. ex. court circuit, rotor bloqué, circuit ouvert ou perte de charge
H02M 1/32 - Moyens pour protéger les convertisseurs autrement que par mise hors circuit automatique
H02M 7/5387 - Transformation d'une puissance d'entrée en courant continu en une puissance de sortie en courant alternatif sans possibilité de réversibilité par convertisseurs statiques utilisant des tubes à décharge avec électrode de commande ou des dispositifs à semi-conducteurs avec électrode de commande utilisant des dispositifs du type triode ou transistor exigeant l'application continue d'un signal de commande utilisant uniquement des dispositifs à semi-conducteurs, p. ex. onduleurs à impulsions à un seul commutateur dans une configuration en pont
One aspect of the invention relates to a method (4) for transmitting data between a first electronic device (30) with a discrete output (OUT_mult) and a second device (20) connected to the first device (30) via the discrete output (OUT_mult), comprising: the first device (30) defining (41) an expected output voltage level (Vcmd) from among the plurality of predefined voltage levels, a voltage regulation loop of the first device (30) regulating (42) the output voltage level, the regulation loop controlling (43) an output transistor (Q1) of the first device (30) so as to have the expected output voltage level (OUT_mult), the output of the output transistor being the discrete output (D, OUT_mult) connected to the second device (20), and the second device (20) reading (44) the voltage level of the discrete output.
An integrated unit for de-icing the propeller blades and the nose of a turbomachine including: a rotary transformer including a static part and a rotary part; a DC-to-AC voltage converter connected at its output to the static part of the rotary transformer and intended to be connected at its input to a DC electrical power supply, and a power switch connected to the rotary transformer and configured to transmit electrical power to at least one pair of propeller blades and to the nose cone of the turbomachine.
The invention relates to a method (100) for controlling an electrical distribution system (1) that comprises a data concentrator (2) connected to a plurality of sensors (6), wherein sensor (6) is associated with a protection and communication device (4) connected between the sensor (6) and the concentrator (2), and wherein the concentrator (2) and each protection and communication device (4) each comprises electronic circuitry for implementing the management method (100). The control method comprises at least the following steps: - configuring (101) a list of data items and a transmission frequency for each protection and communication device (4) according to the sensor (6) and an electrical load that are associated therewith; - acquiring (102) a signal from a sensor (6) and transmitting it to the corresponding protection and communication device (4); - transmitting (103) a predefined data item or a calculation corresponding to the acquired signal, wherein the transmission is sent by the corresponding protection and communication device (4) to the concentrator (2), and wherein the transmission is sent at the configured transmission frequency.
H02J 13/00 - Circuits pour pourvoir à l'indication à distance des conditions d'un réseau, p. ex. un enregistrement instantané des conditions d'ouverture ou de fermeture de chaque sectionneur du réseauCircuits pour pourvoir à la commande à distance des moyens de commutation dans un réseau de distribution d'énergie, p. ex. mise en ou hors circuit de consommateurs de courant par l'utilisation de signaux d'impulsion codés transmis par le réseau
H02H 7/26 - Protection sectionnelle de systèmes de câbles ou de lignes, p. ex. pour déconnecter une section dans laquelle un court-circuit, un défaut à la terre, ou une décharge d'arc se sont produits
H02H 1/00 - Détails de circuits de protection de sécurité
5.
ELECTRICAL GENERATION SYSTEM AND METHOD, FOR SUPPLYING POWER TO AT LEAST ONE ELECTRICAL NETWORK OF AN AIRCRAFT
BP*DC*DCBP*BP*BP*), and resetting the integral corrector (CI) of the regulation unit (21a) of the power supply path depending on the divergence indicator (M3).
H02J 1/10 - Fonctionnement de sources à courant continu en parallèle
B64D 41/00 - Installations génératrices de puissance pour servitudes auxiliaires
G05B 5/00 - Dispositions pour éliminer l'instabilité
G05B 11/36 - Commandes automatiques électriques avec les dispositions nécessaires pour obtenir des caractéristiques particulières, p. ex. proportionnelles, intégrales, différentielles
6.
DEVICE AND METHOD FOR CONTROLLING A SYNCHRONOUS MACHINE AND FOR ESTIMATING ROTOR POSITION, FROM START-UP TO A PREDETERMINED LOW SPEED
One aspect of the invention relates to a control device (2) for starting up a synchronous electric motor (1) up to a predetermined threshold speed, comprising: a current regulator (4) that delivers a voltage setpoint (V #dq) in accordance with a regulation current setpoint (l #dq′), a computing unit (5) for computing a current feedback. (Idq) in accordance with measurements of the phase currents (lu, Iv, Iw), an estimator (6) for estimating an angular position of the rotor (θelec), in accordance with a difference between a reference stator flux vector (λq) that depends on the feedback currents (Iq) and an adaptive stator flux vector (λqv) that depends on the voltage setpoint (V#dq), on the feedback currents (Iq, Id), and on an estimated electrical speed (ωelec), a setpoint current modifier (7) that computes, when the estimated electrical speed (ωelec) is lower than the predetermined threshold speed, a regulator setpoint DC current (l#d) having a non-zero value.
The invention relates to a housing (1) for an electric energy storage battery, which includes a platform (2) configured so that power elements (3) of the battery attach thereto, a protective cover (5) covering the platform (2), and means for mechanically attaching the protective cover (5) to the platform, the platform (2) comprising means for electrical connection of the battery and means (6) for thermal management of the power elements (3). The platform and the protective cover form a structure for containing any thermal runaway of the power elements (3), the housing comprising a battery management system (16) of which at least one portion (16a) is mounted outside the containment structure and is in a heat-exchange relationship with the thermal control means (6) of the power elements (3).
H01M 10/42 - Procédés ou dispositions pour assurer le fonctionnement ou l'entretien des éléments secondaires ou des demi-éléments secondaires
H01M 10/48 - Accumulateurs combinés à des dispositions pour mesurer, tester ou indiquer l'état des éléments, p. ex. le niveau ou la densité de l'électrolyte
H01M 10/613 - Refroidissement ou maintien du froid
H01M 10/6556 - Composants solides comprenant des canaux d'écoulement ou des tubes pour un échange de chaleur
H01M 50/207 - Bâtis, modules ou blocs de multiples batteries ou de multiples cellules caractérisés par leur forme
H01M 50/24 - MonturesBoîtiers secondaires ou cadresBâtis, modules ou blocsDispositifs de suspensionAmortisseursDispositifs de transport ou de manutentionSupports caractérisés par les propriétés physiques des boîtiers ou des bâtis, p. ex. dimensions adaptés pour protéger les batteries de leur environnement, p. ex. de la corrosion
H01M 50/249 - MonturesBoîtiers secondaires ou cadresBâtis, modules ou blocsDispositifs de suspensionAmortisseursDispositifs de transport ou de manutentionSupports spécialement adaptés aux aéronefs ou aux véhicules, p. ex. aux automobiles ou aux trains
H01M 50/271 - Couvercles des boîtiers secondaires, des bâtis ou des blocs
H01M 50/284 - MonturesBoîtiers secondaires ou cadresBâtis, modules ou blocsDispositifs de suspensionAmortisseursDispositifs de transport ou de manutentionSupports comprenant l’insertion de cartes de circuits, p. ex. de cartes de circuits imprimés
H01M 10/667 - Relations d'échange de chaleur entre les éléments et d'autres systèmes, p. ex. chauffage central ou piles à combustibles le système étant un composant électronique, p. ex. un UCT, un inverseur ou un condensateur
A battery power supply device of an electrical energy supply system for aircraft includes at least two battery modules connected to a DC power network through a positive line, a negative line, and power switching elements, wherein each module includes at least one switching device for isolating said module from said network or for connecting said module to the network.
H02J 7/00 - Circuits pour la charge ou la dépolarisation des batteries ou pour alimenter des charges par des batteries
B60L 58/19 - Commutation entre la connexion en série et la connexion en parallèle des modules de batterie
B60L 58/21 - Procédés ou agencements de circuits pour surveiller ou commander des batteries ou des piles à combustible, spécialement adaptés pour des véhicules électriques pour la surveillance et la commande des batteries de plusieurs modules de batterie ayant la même tension nominale
The present invention relates to a system (0) for controlling the short-circuit current of an electrical network (3) comprising a power converter (2) controlled by a control system (4) and configured to rectify and regulate the voltage of the electric machine (1), the control system (4) comprising: - a synchronization unit (41); - a control unit (42) for controlling: - in an active short-circuit mode, - in free-wheeling mode, - by asynchronous pulse width modulation, - a regulation unit (43); such that, in the event of a short circuit, the control system (4) controls the power converter (2) in order to deliver to the electrical network (3) a direct current equal to the predetermined value.
The invention relates to a rotating machine comprising a coaxial rotor (20) and a stator (30), the rotor (20) being rotatable about an axis of rotation, the machine comprising a bearing (10) for guiding the rotation of the rotor (20), the bearing (10) being in contact with a surface (200) of the rotor (20), the bearing (10) comprising a rolling device (100) around the rotor (20) and a detection device (110), the detection device (110) comprising a first element (110') and a second element (110''), the first element (110') extending around the rotor (20), the second element (110'') being rigidly attached to the stator (30), the detection device (110) being configured to switch from a rest configuration, wherein the first element (110') is at a distance from the rotor (20) and the second element (110''), to a braking configuration, wherein the first element (110') is rotated by the rotor (20) and wherein the second element (110'') exerts a reaction opposite to the rotation on the first element (110'), the detection device (110) being configured to switch from the rest configuration to the braking configuration when the rotation of the rotor (20) is eccentric with respect to the axis of rotation.
H02K 49/10 - Embrayages dynamo-électriquesFreins dynamo-électriques du type à aimant permanent
H02K 7/00 - Dispositions pour la mise en œuvre d'énergie mécanique associées structurellement aux machines dynamo-électriques, p. ex. association structurelle avec des moteurs mécaniques d'entraînement ou des machines dynamo-électriques auxiliaires
H02K 7/08 - Association structurelle avec des paliers
H02K 7/10 - Association structurelle avec des embrayages, des freins, des engrenages, des poulies ou des démarreurs mécaniques
F16C 19/52 - Paliers à contact de roulement pour mouvement de rotation exclusivement avec dispositifs affectés par des conditions anormales ou indésirables
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (CNRS) (France)
ECOLE SUPERIEURE DE PHYSIQUE ET DE CHIMIE INDUSTRIELLES DE LA VILLE DE PARIS (France)
SORBONNE UNIVERSITE (France)
Inventeur(s)
Carreira Rufato, Raul
Guerin, Fabrice
Lebey, Thierry Michel André
Abrégé
The invention relates to a method for detecting electric arcs in an electrical circuit of an aeronautical system, which method comprises a first phase (P1) of identifying recurring patterns in the behaviour of the electric current, on an electric line of the electrical circuit, and storing the recurring patterns in a pattern database, and a second diagnostic phase (P2) which involves comparing the behaviour of the electric current on the electric line with recurring patterns stored in the pattern database, and detecting an electric arc when the behaviour does not correspond to a recurring pattern stored in the pattern database.
G01R 31/00 - Dispositions pour tester les propriétés électriquesDispositions pour la localisation des pannes électriquesDispositions pour tests électriques caractérisées par ce qui est testé, non prévues ailleurs
G01R 31/12 - Test de la rigidité diélectrique ou de la tension disruptive
12.
TURBINE ENGINE COMPRISING A MODULE FOR CORRECTING A TORSIONAL MODE OF A TRANSMISSION LINE CONNECTED TO AN ELECTRIC MACHINE AND ASSOCIATED METHOD
The invention relates to an aircraft turbine engine (T) comprising an electric machine (1) connected to a transmission line (2) and a control device (3) configured to determine the currents flowing through the electric machine (1) so that it provides an electric machine torque in accordance with a control torque, wherein the control device (3) comprises a correction module (4) configured to correct the torsional mode (Mt) of the transmission line (2), wherein the correction module (4) is configured to determine a time measurement of a torque parameter of the rotor (12) of the electric machine (1) over a monitoring range, calculate a correction torque from the time measurement over the monitoring range, and calculate the control torque from a reference torque (TRQcons) and the correction torque.
H02P 6/10 - Dispositions pour commander l'ondulation du couple, p. ex. en assurant une ondulation réduite du couple
H02P 9/02 - Dispositions pour la commande de génératrices électriques de façon à obtenir les caractéristiques désirées à la sortie Détails
H02P 21/05 - Dispositions ou procédés pour la commande de machines électriques par commande par vecteur, p. ex. par commande de l’orientation du champ spécialement adaptés pour amortir les oscillations des moteurs, p. ex. pour la réduction du pompage
13.
TURBOMACHINE PROPELLER COMPRISING A HIGH-POWER DE-ICING SYSTEM
An aircraft turbomachine propeller comprising a propeller cone and blades, the propeller cone and the blades comprising a plurality of heating members (220), and a system (222) for supplying electrical power to said plurality of heating members, mounted in the propeller cone and configured to generate electrical energy autonomously from the rotation of a main shaft of the turbomachine (216) driving the propeller in rotation, the electrical power supply system comprising an electric machine (290) comprising a rotating stator (230B) fulfilling an armature function and constrained to rotate with the main shaft of the turbomachine, and a rotor (230A) performing an inductor function and constrained to rotate with a high-speed auxiliary shaft (232) rotating at a rotational speed greater than the rotational speed of the main shaft of the turbomachine.
The invention relates to a contactor (1) comprising two pairs (C1, C2) of adjacent arc chambers (2), arranged in a rectangle and each divided into two electric arc extinguishing areas (8). Within each pair, each arc chamber comprises: a movable terminal (4) provided with a first and a second movable contact (5a, 5b), a first fixed terminal (6a) provided with a first fixed contact (7a) located facing the first movable contact (5a), a second fixed terminal (6b) common to the two arc chambers (2) and provided with a second fixed contact (7b) located facing the second movable contact (5b), - two electric arc extinguishing devices (17) each located in an extinguishing area (8). The contactor further comprises an actuator (18) connected to the four movable terminals, actuation of the actuator causing the four movable terminals to move simultaneously between a closed state and an open state.
The present disclosure proposes a device (110) for powering an electrical network (120) of an aeronautical propulsion system (100), the device (110) comprising: an electrical generator (112), preferably a permanent-magnet synchronous electrical machine, comprising a rotor and a stator, the rotor being configured to be driven by a turbine engine (111), the stator being configured to generate a first AC voltage (V1); an AC/DC converter (114) configured to rectify the first voltage (V1) delivered by the electrical generator (112) so as to obtain a second voltage (V2); and a DC/DC converter (116) configured to chop the second voltage (V2) delivered by the AC/DC converter (114) so as to obtain a third voltage (V3), the DC/DC converter (116) being downstream of the AC/DC converter (114) with reference to current flow from the AC/DC converter (114) to the DC/DC converter (116).
H02P 9/48 - Dispositions pour obtenir des caractéristiques constantes à la sortie, la génératrice étant à vitesse variable, p. ex. sur un véhicule
H02M 7/12 - Transformation d'une puissance d'entrée en courant alternatif en une puissance de sortie en courant continu sans possibilité de réversibilité par convertisseurs statiques utilisant des tubes à décharge avec électrode de commande ou des dispositifs à semi-conducteurs avec électrode de commande
H02J 4/00 - Circuits pour réseaux principaux ou de distribution, la nature alternative ou continue du courant n'étant pas précisée
H02M 1/00 - Détails d'appareils pour transformation
H02M 1/12 - Dispositions de réduction des harmoniques d'une entrée ou d'une sortie en courant alternatif
H02M 1/42 - Circuits ou dispositions pour corriger ou ajuster le facteur de puissance dans les convertisseurs ou les onduleurs
H02M 3/158 - Transformation d'une puissance d'entrée en courant continu en une puissance de sortie en courant continu sans transformation intermédiaire en courant alternatif par convertisseurs statiques utilisant des tubes à décharge avec électrode de commande ou des dispositifs à semi-conducteurs avec électrode de commande utilisant des dispositifs du type triode ou transistor exigeant l'application continue d'un signal de commande utilisant uniquement des dispositifs à semi-conducteurs avec commande automatique de la tension ou du courant de sortie, p. ex. régulateurs à commutation comprenant plusieurs dispositifs à semi-conducteurs comme dispositifs de commande finale pour une charge unique
H02M 7/23 - Transformation d'une puissance d'entrée en courant alternatif en une puissance de sortie en courant continu sans possibilité de réversibilité par convertisseurs statiques utilisant des tubes à décharge avec électrode de commande ou des dispositifs à semi-conducteurs avec électrode de commande utilisant des dispositifs du type triode ou transistor exigeant l'application continue d'un signal de commande utilisant uniquement des dispositifs à semi-conducteurs agencés pour la marche en parallèle
H02M 7/217 - Transformation d'une puissance d'entrée en courant alternatif en une puissance de sortie en courant continu sans possibilité de réversibilité par convertisseurs statiques utilisant des tubes à décharge avec électrode de commande ou des dispositifs à semi-conducteurs avec électrode de commande utilisant des dispositifs du type triode ou transistor exigeant l'application continue d'un signal de commande utilisant uniquement des dispositifs à semi-conducteurs
A power contactor including: a fixed part including two fixed elements; a moveable part able to come into contact with the fixed part and to move between an open position and closed position of the contactor, the moveable part including two switching elements and two conducting elements, and the distance between the fixed part and the two conducting elements being greater than the distance between the fixed part and the two switching elements in open position of the contactor, such that the switching elements come into contact with the fixed part before the conducting elements when the contactor changes from open position to closed position; and a motor configured to actuate and place the moveable part in contact with the fixed part.
An electrical propulsion system for an aircraft includes a central bus and a plurality of branches, each branch having at least one electrical power source, at least one electric propulsion device, and a branch bus, connected to each source and to each propulsion device of the branch. Each branch includes a DC/DC voltage converter connecting the branch bus to the central bus, said DC/DC voltage converter being configured to galvanically isolate said branch bus from the central bus.
H02H 7/12 - Circuits de protection de sécurité spécialement adaptés aux machines ou aux appareils électriques de types particuliers ou pour la protection sectionnelle de systèmes de câble ou de ligne, et effectuant une commutation automatique dans le cas d'un changement indésirable des conditions normales de travail pour convertisseursCircuits de protection de sécurité spécialement adaptés aux machines ou aux appareils électriques de types particuliers ou pour la protection sectionnelle de systèmes de câble ou de ligne, et effectuant une commutation automatique dans le cas d'un changement indésirable des conditions normales de travail pour redresseurs pour convertisseurs ou redresseurs statiques
B64D 27/35 - Aménagements pour la production, la distribution, la récupération ou le stockage d'énergie électrique à bord
A power contactor including: a fixed part; a movable part able to come into contact with the fixed part and to move between an open position and a closed position of the contactor, the movable part including at least one power contact; an auxiliary contact and a pyrotechnic actuator, the auxiliary contact and the pyrotechnic actuator being placed in parallel with the power contact, and the pyrotechnic actuator being configured to be triggered during a levitation of the contactor in such a way as to move the contactor into the open position; and a motor configured to actuate the movable part and to put it in contact with the fixed part characterized in that the power contact and the auxiliary contact are desynchronized in such a way that when the contactor is closed, the power contact comes into contact with the fixed part before the auxiliary contact.
H01H 39/00 - Dispositifs de commutation actionnés par une explosion produite à l'intérieur du dispositif et amorcée par un courant électrique
H01H 3/26 - Dispositions comportant une énergie à l'intérieur de l'interrupteur pour actionner le mécanisme d'entraînement utilisant un moteur dynamo-électrique
H02K 1/2796 - Rotors faisant face axialement à des stators le rotor étant formé de plusieurs aimants disposés sur la circonférence dans lesquels les deux faces axiales du rotor font face à un stator
H02K 1/2798 - Rotors faisant face axialement à des stators le rotor étant formé de plusieurs aimants disposés sur la circonférence dans lesquels les deux faces axiales du stator font face à un rotor
H02K 21/24 - Moteurs synchrones à aimants permanentsGénératrices synchrones à aimants permanents avec des induits fixes et des aimants tournants avec des aimants disposés axialement en face des induits, p. ex. dynamos de bicyclette du type moyeu
The invention relates to a power contactor comprising a fixed part and a mobile part able to move in translation relative to the fixed part under the activation of a linear actuator (12) and in a direction of displacement, between a contact position and a breaking position, the contact position forming a normally closed rest position of the contactor, the displacement of the mobile part carrying along a mobile contact (24) so as to separate it from a fixed contact (26) facing it in an extinguishing chamber (22), by compressing a contact compression spring (28) and a core return spring (30), characterized in that, in order to avoid any rebounding of the mobile part when the linear actuator returns to its rest position, a magnetic holding member fixes this mobile part in the contact position before it rebounds due to the springs.
The invention relates to a nacelle system for an electric machine (2) provided with cooling fins (6), the nacelle system comprising a fairing (40) configured to conform to the outer shape of the electric machine provided with cooling fins, the fairing (40) comprising at least one firewall (44), the fairing (50) comprising a fairing wall (52) having an inner surface (52a) intended to be oriented facing the electric machine (2) and an opposite outer surface (52b) intended to be oriented away from the electric machine (2), the at least one firewall (54) being arranged between the inner surface (52a) and the outer surface (52b) of the fairing wall.
B64D 27/30 - Aéronefs caractérisés par des groupes moteurs électriques
B64D 29/00 - Nacelles, carénages ou capotages des groupes moteurs
B64D 35/026 - Transmission de la puissance des groupes moteurs aux hélices ou aux rotorsAménagements des transmissions spécialement adaptés à des groupes moteurs spécifiques aux groupes moteurs électriques le groupe moteur électrique faisant corps avec l’hélice ou le rotor
B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
F02C 7/25 - Prévention ou protection contre l'incendie
22.
METHOD FOR MONITORING THE STATE OF HEALTH OF AN EXPLOSIVE CELL BATTERY AND DEVICE IMPLEMENTING THIS METHOD
A method for monitoring the state of health of a battery with explosive cells including a plurality of internal components that are distributed throughout a plurality of regions (region 1, region 2), each region of the battery including at least one explosive cell, each internal component being associated with a device for checking the coherence of the internal component, the method including a first check for checking the coherence of the data of a first internal component in a region of the battery; a second check for checking the coherence of the data of a second internal component in the same region of the battery, the first and second checks being spaced apart by a predefined period of time.
G01R 31/392 - Détermination du vieillissement ou de la dégradation de la batterie, p. ex. état de santé
H01M 10/42 - Procédés ou dispositions pour assurer le fonctionnement ou l'entretien des éléments secondaires ou des demi-éléments secondaires
H01M 10/48 - Accumulateurs combinés à des dispositions pour mesurer, tester ou indiquer l'état des éléments, p. ex. le niveau ou la densité de l'électrolyte
23.
ELECTRICAL POWER CONTACTOR PROVIDED WITH AN OPTICAL PROTECTION DEVICE
The invention relates to an electrical power contactor (13) comprising: - a quenching chamber (15), - at least one fixed contact (16.1, 16.2) placed inside the quenching chamber (15), and - a movable contact (17) able to move between: - a closed position in which the movable contact (17) makes contact with the fixed contact (16.1, 16.2), - an open position in which the movable contact (17) is moved away from the fixed contact (16.1, 16.2), - an optical detector (20) placed inside or near the quenching chamber (15), - an electrical quenching member (21), and - a control device (25) configured to activate the electrical quenching member (21) when a duration of an electric arc detected by the optical detector (20) is greater than a response time to nominal opening of the electrical power contactor (13).
A filter includes a positive busbar and a negative busbar that have a positive terminal and a negative terminal, respectively; at least one positive output terminal and at least one negative output terminal, respectively; and two portions, respectively, each portion having parallel folds to define planes which succeed one another. Each plane is inclined relative to the next plane. One of the portions is an internal portion that is fitted inside the other portion, which is an external portion. Each plane of one portion extends in parallel with and facing an associated plane of the other portion. Differential mode capacitors connected between the two portions.
B60L 50/51 - Propulsion électrique par source d'énergie intérieure au véhicule utilisant de la puissance de propulsion fournie par des batteries ou des piles à combustible caractérisée par des moteurs à courant alternatif
H02M 1/14 - Dispositions de réduction des ondulations d'une entrée ou d'une sortie en courant continu
A double-throw power switch (200) comprising: - a fixed part (210); - a mobile part able to come into contact with the fixed part and to move between a position in which the switch is open and a position in which the switch is closed, the mobile part comprising a switching contact (240) and at least one passing contact (230, 231, 232); - springs configured to apply a pressing force to the mobile part, pressing it towards the fixed part; - a pair of magnets (250) for generating a constant-direction magnetic field; - an interrupter chamber; characterized in that the distance (d1) between the fixed part and the switching contact is less than the distance (d2) between the fixed part and the passing contacts and in that the switching contact comprises a first portion (241) placed at a first end of the passing contacts, a second portion (242) placed at a second end of the passing contacts and a third portion (243) comprising one branch when there is one passing contact or (n-1) branches, where n is the number of passing contacts and n is strictly greater than 2, the passing contacts being parallel to one another and placed on either side of the branches of the third portion of the switching contact.
A motor with integrated control, includes an electric machine equipped with a rotating portion, which is mounted on a rotary shaft; an electronic control unit for controlling the electric machine; a casing including a first cavity in which the electric machine is accommodated and a second cavity, adjacent to the first cavity, in which the electronic control unit is accommodated, the rotary shaft passing through both the first cavity and the second cavity; a thermal partition mounted at a junction between the first cavity and the second cavity; and a centrifugal pump, which is mounted on the rotary shaft at the junction between the first cavity and the second cavity of the casing and generates an airflow from the second cavity to the first cavity.
H02K 9/06 - Dispositions de refroidissement ou de ventilation par l'air ambiant s'écoulant à travers la machine comportant des moyens pour établir la circulation d'un agent de refroidissement avec des ventilateurs ou des dispositifs d'entraînement mûs par l'arbre de la machine
H02K 5/20 - Enveloppes ou enceintes caractérisées par leur configuration, leur forme ou leur construction avec des canaux ou des conduits pour la circulation d'un agent de refroidissement
H02K 11/33 - Circuits d’entraînement, p. ex. circuits électroniques de puissance
27.
ELECTRICAL CONVERTER CONFIGURED TO SUPPLY AN ELECTRIC MACHINE WITH POWER, ELECTRICAL MODULE COMPRISING SUCH A CONVERTER, AND METHOD FOR USING SUCH AN ELECTRICAL MODULE
An electrical converter configured to supply an electric machine, in particular for an aircraft, with power, comprising an annular stator and a rotor. The electrical converter comprising a plurality of power inverters, each comprising a plurality of power devices that are configured to be connected to the annular stator so as to supply the electric machine with power, a casing comprising a plurality of inner baths and outer baths, a coolant circuit configured to supply each inner bath and each outer bath with coolant. The power devices being mounted in the inner baths and the outer baths so as to allow all of the power devices to be cooled.
H05K 7/20 - Modifications en vue de faciliter la réfrigération, l'aération ou le chauffage
H02M 1/32 - Moyens pour protéger les convertisseurs autrement que par mise hors circuit automatique
H02M 7/00 - Transformation d'une puissance d'entrée en courant alternatif en une puissance de sortie en courant continuTransformation d'une puissance d'entrée en courant continu en une puissance de sortie en courant alternatif
A quenching chamber includes, for each zone of contact between a mobile contact and two fixed contacts, respectively, two pairs of guides that extend from the mobile contact and the contact zone in question, respectively, so as to guide, under the action of a magnetic field of constant direction, an electric arc. The pairs of guides follow one after the other in the direction of the magnetic field, and each pair of guides delineates between them a guiding zone. The guiding zones overlap at least partially in the direction of the magnetic field.
The present invention relates to a system for converting and transporting electrical energy in a turbomachine-propelled aircraft, said system including:
at least a first rotary electric machine connected mechanically to the low-pressure shaft by means of a coupling device,
a second rotary electric machine connected mechanically to the high-pressure shaft by means of an accessory gearbox, and
said first electric power module and said second electric power module being connected electrically to an internal electrical network of the turbomachine,
a generator coupled to the accessory gearbox and intended to supply an electrical network of the aircraft with electricity, and
a control device for controlling start-up of the turbomachine by at least one rotary electric machine, for compensating for power consumed by the generator, and for implementing distribution between the power absorbed by the high-pressure shaft and the power absorbed by the low-pressure shaft.
A device for connection to an on-board multiplexed network of communication by multi-mode optical fibers for an aircraft, the device comprising a first optical component for modifying the spatial profile of a light beam, comprising a multi-mode optical input terminal configured to be connected to a first multi-mode optical fiber and single-mode optical output terminals, and a second optical component for modifying the spatial profile of a light beam, comprising single-mode optical input terminals and a multi-mode optical output terminal configured to be connected to a second multi-mode optical fiber. It further comprises an optical harness for switching and reassigning a transmission channel including single-mode optical inputs coupled to the single-mode optical output terminals of the first component, single-mode optical outputs coupled to the single-mode optical input terminals of the second optical component, and single-mode waveguides.
G02B 6/28 - Moyens de couplage optique ayant des bus de données, c.-à-d. plusieurs guides d'ondes interconnectés et assurant un système bidirectionnel par nature en mélangeant et divisant les signaux
The invention relates to a power contactor (100) comprising: - a fixed part (120); - a movable part (110) able to come into contact with the fixed part and to move between an open position and a closed position of the contactor, the movable part comprising two contact points (111, 112) for contact with the fixed part; - a first spring (141) placed on the movable part and configured to apply a pressing force on the movable part towards the fixed part; - an actuator (150) configured to actuate the movable part and bring it into contact with the fixed part; - an insulating support (101) containing the fixed part, the movable part and the first spring, characterized in that the power contactor also comprises: - a magnetic circuit (103) surrounding at least one portion of the movable part; and - a plate (102) fastened to the movable part and configured to come into contact with the magnetic circuit so as to form a closed magnetic circuit surrounding the movable part when the contactor is in the closed position, the insulating support also containing the plate and the magnetic circuit, and the distance (d1) between the plate and the magnetic circuit being strictly greater than the distance (d2) between the two contact points and the fixed part.
H01H 1/54 - Moyens pour accroître la pression de contact, empêcher la vibration des contacts, maintenir ensemble les contacts après l'entrée en contact, ou pour ramener les contacts à la position d'ouverture par force magnétique
H01H 50/42 - Circuits magnétiques auxiliaires, p. ex. pour le maintien de l'armature en position de repos ou de retour de l'armature à la position de repos, pour l'amortissement ou l'accélération du mouvement
32.
METHOD FOR REGULATING AN ELECTRIC MACHINE IN MOTOR MODE BY PARALLEL HYBRIDISATION OF AN AUXILIARY ELECTRICAL NETWORK
The invention relates to an electrical system for an aircraft, comprising a main network (110) and an auxiliary network (120) connected to the main network (110) and a device for regulating the rotary electric machine (111), the regulating device comprising: - a first regulating member (131) for regulating the voltage of the main network (110) connected to the control unit (113), the first regulating member (131) being configured to regulate the induction current of the rotor of the rotary electric machine (111); - a second member (132) for regulating the current at the terminals of the rotary electric machine (111) connected to the control module (123), the second regulating member (132) being configured to control the current generated by the converter (122), the electrical system being configured to adopt: - a generator configuration in which the rotary electric machine (111) transmits an electric current to the at least one electric component (200); and - a motor configuration in which the value of the current at the output of the converter (122) is greater than the value of the current of the at least one electric component (200), the electrical system switching from the generator configuration to the motor configuration, and vice versa, by controlling the regulating device (123).
H02P 9/14 - Dispositions pour la commande de génératrices électriques de façon à obtenir les caractéristiques désirées à la sortie par variation du champ
Disclosed is a rotary transformer that has a radial air gap and is intended to be installed around a rotatable shaft, the rotary transformer consisting of a plurality of annular stator sectors (22) and of a plurality of annular rotor sectors (24), the juxtaposition of said annular sectors forming a stator ring and a rotor ring which consist of elementary magnetic stator and rotor circuits comprising outer (30) and inner (34) magnetic cores as well as a first electrical winding (32) and a second electrical winding (36) to allow electrical energy to be transferred by electromagnetic induction between the stator and rotor rings, wherein the inner (34) and outer (30) magnetic cores, which each have a standard C-or I-shape, are axially mounted and separated by a radial air gap e_, and the outer magnetic cores and/or the inner magnetic cores have, at each of their two ends, annular flared portions (30A, 30B; 34A, 34B) that are produced by cutting into adjacent sectors a magnetic circular ring formed of an axial stack of circular metal sheets advantageously provided with notches to facilitate their assembly on the outer and inner magnetic cores.
Disclosed is a rotary transformer intended to be installed around a rotatable shaft, the rotary transformer consisting of a plurality of annular stator sectors (22) and of a plurality of annular rotor sectors (24), the juxtaposition of said annular sectors forming a stator ring and a rotor ring which consist of elementary magnetic stator and rotor circuits comprising outer (40) and inner (48) magnetic cores as well as a first electrical winding (50) and a second electrical winding (52) to allow electrical energy to be transferred by electromagnetic induction between the stator and rotor rings, the inner and outer magnetic cores being separated by two air gaps e1 and e2 located on either side of the inner magnetic core, wherein the outer magnetic cores (40) are each in the form of a C-shaped claw and the inner magnetic cores (48) are each in the form of an I-shaped bar, and the outer magnetic cores (40) and/or the inner magnetic cores (48) have, at each of the air gaps, annular flared portions (44) produced by cutting into adjacent sectors a magnetic circular ring (46) formed of a radial stack of circular metal sheets advantageously provided with notches to facilitate their assembly on the outer and inner magnetic cores.
The invention relates to a device (1) for supplying electrical power, comprising: —a power source, —a system to be supplied with power, —a first busbar (2) connected to the system to be supplied with power, —a second busbar (3) connected to the CN power source, —an elastic element (13), —a heat-sensitive element (6) configured to melt at a predefined temperature, and—a holding system (7,8,9) allowing the two busbars (2,3) and the heat-sensitive element (6) to be held in contact, —the two busbars (2,3) making p electrical contact, —the elastic element (13) being configured to move the two busbars (2,3) away from each other and to break the M electrical contact, when the heat-sensitive element (6) melts.
H01H 37/76 - Élément de contact actionné par fusion d'une matière fusible, actionné par combustion d'une matière combustible ou par explosion d'une matière explosive
The invention relates to an inductive filtering device comprising a closed magnetic core (12) formed around a central recess (14) and at least one electrical conductor (16) wound around the magnetic core (12) so as to pass through the central recess (14), the electrical conductor (16) extending along a curved main axis (20) suitable for the winding, wherein the electrical conductor (16) has a first portion (16a) arranged in the central recess (14) and a second portion (16b) arranged outside the central recess (14), wherein a section of the first portion (16a) is defined perpendicularly to the main axis in the portion in question and a section of the second portion (16b) is defined perpendicularly to the main axis in the portion in question, and wherein a surface area of the first section is smaller than a surface area of the second section.
The invention relates to a winding configured to ensure the passage of an electric current between two main connection points, the device comprising: - a magnetic core (12); - a main electrical conductor (14) in the form of a first flat strip extending between two ends each provided with one of the main connection points (14c, 14d), and being wound around the magnetic core (12) in order to form an inductor; - an auxiliary electrical conductor (20) in the form of a second strip wound together with the main electrical conductor, and provided with an auxiliary connection point (20c); and - an electrical insulator (22) separating the main electrical conductor from the auxiliary electrical conductor in order to form a capacitor between the two electrical conductors.
The invention relates to an adapted power line and to an energy converter comprising at least one power line. The power line comprises at least one linear electrical conductor (40) and at least one resistive component (42), separate from the conductor and connected in parallel with the conductor over a portion of the linear electrical conductor (40), a value of the resistance of the resistive component being at least equal to ten times a resistance value of the linear electrical conductor (40) over the portion in question.
A method for automatically setting an angular position sensor of a magnet rotor in relation to a stator of a synchronous machine, including an angle error compensator which adjusts the angles measured by the angular position sensor by an angular difference calculated by imposing a direct setpoint current equal to zero and by comparing a setpoint voltage with a quadrature return current, a direct return current resulting from a direct Park transform of current measured at the stator phase outputs and a rotor electrical speed, a predetermined value corresponding to the rotor magnet flux, and a quadrature inductance.
Electrical cut-off device including a fuse used to open a power line in which a direct current circulates, a movable drawer connected to the fuse and capable, once the fuse is broken, of moving in a fixed chamber under the action of a compression spring mounted between the fixed chamber and the movable drawer, and an auxiliary contact whose fixed contact part is secured to the fixed chamber and movable contact part is secured to the movable drawer whose movement will cause the opening of the normally closed auxiliary contact.
An electrical system includes an electrical power module with a heat sink provided with heat-dissipating projections. The system further includes a cold plate of a heat-transfer fluid box. The cold plate has cavities which are complementary to the projections so as to receive said projections. Liquid metal is inserted between the heat sink and the cold plate, at least between the projections and the cavities.
limLoadLoadLoadlimLoadsuppLoadlimLoadsuppsuppsupp from the auxiliary grid into the main grid, - otherwise, not carrying out injection from the auxiliary grid into the main grid.
H02J 3/38 - Dispositions pour l’alimentation en parallèle d’un seul réseau, par plusieurs générateurs, convertisseurs ou transformateurs
H02J 3/48 - Dispositions pour l’alimentation en parallèle d’un seul réseau, par plusieurs générateurs, convertisseurs ou transformateurs contrôlant la répartition de puissance entre les générateurs, convertisseurs ou transformateurs contrôlant la répartition de la composante en phase
H02J 3/50 - Dispositions pour l’alimentation en parallèle d’un seul réseau, par plusieurs générateurs, convertisseurs ou transformateurs contrôlant la répartition de puissance entre les générateurs, convertisseurs ou transformateurs contrôlant la répartition de la composante déphasée
43.
GENERATOR WITH HYBRID EXCITATION FOR A HYBRID ELECTRIC PROPULSION SYSTEM
The invention relates to a hybrid electric propulsion system (200) for a turbojet engine, comprising: - a first permanent magnet synchronous machine (230) connected to an AC-DC converter (231) and intended to be connected to a high-pressure shaft (222) of the turbojet engine; - a hybrid excitation generator (240) comprising a brushless synchronous machine (242), a second permanent magnet synchronous machine (241) connected in series with the brushless synchronous machine, and a bridge rectifier (243) connected to the brushless synchronous machine, the hybrid excitation generator being intended to be connected to a low-pressure shaft (212) of the turbojet engine and the brushless synchronous machine comprising a generator (3421), an exciter (3422), rotating diodes placed between the generator and the exciter, and a DC-DC converter (244) connected to the exciter; - an energy storage system (250); and - a DC power supply network connected to the AC-DC converter and to the bridge rectifier.
H02P 9/10 - Commande s'exerçant sur le circuit d'excitation de la génératrice afin de réduire les effets nuisibles de surcharges ou de phénomènes transitoires, p. ex. application, suppression ou changement brutal de la charge
B64D 27/02 - Aéronefs caractérisés par le type ou la position des groupes moteurs
B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur ou l'énergie de ressorts
A method and a system for determining control parameters of a rotating electric machine, including: a two-phase imaginary reference frame module configured to construct two imaginary two-phase signals (xα, xβ) based on a measurement of the mechanical position θmeca of the axis of a rotor of the rotating machine received from a position sensor, an open-loop module configured to determine in open loop an estimate of the electrical speed, so-called the open-loop estimated electrical speed ωestflt, using the imaginary two-phase signals, a phase-locked loop module configured to generate the actual electrical position θ of the rotating machine from the two imaginary two-phase signals (xα, xβ) and using the open-loop estimated electrical speed ωestflt received from the open-loop module.
Two electric poles are controlled in one and the same circuit breaker by an undivided opening mechanism controlled by a pyrotechnic actuator. The opening of the circuit that is brought about by this actuator, which is fast for a large opening travel of the mobile contacts, makes it possible to extinguish electric arcs under good conditions. The poles may be placed in series on one and the same electrical circuit in order to reduce the potential difference across the terminals of each of them, thereby further increasing the effectiveness of the circuit breaker in terms of arc extinguishing.
The invention relates to an electrical energy storage battery (1) comprising at least one stack (7) of electrical cells (6), a housing comprising a base (3) to which the stack (7) of the battery (1) is attached and a shell covering the base (3). The battery (1) comprises at least two compression plates (8) arranged on either side of the stack (7), means (10) for attaching the plates (8) to the base (3) and at least one tie rod (12) capable of compressing the compression plates against the cells of the stack (7). The base (3) comprises means (13) for the thermal management of the electrical cells (6).
H01M 10/60 - Chauffage ou refroidissementCommande de la température
H01M 50/204 - Bâtis, modules ou blocs de multiples batteries ou de multiples cellules
H01M 50/264 - MonturesBoîtiers secondaires ou cadresBâtis, modules ou blocsDispositifs de suspensionAmortisseursDispositifs de transport ou de manutentionSupports avec des moyens de fixation, p. ex. des serrures pour des cellules ou des batteries, p. ex. cadres périphériques, courroies ou tiges
H01M 50/293 - MonturesBoîtiers secondaires ou cadresBâtis, modules ou blocsDispositifs de suspensionAmortisseursDispositifs de transport ou de manutentionSupports caractérisés par des éléments d’espacement ou des moyens de positionnement dans les racks, les cadres ou les blocs caractérisés par le matériau
47.
MODULE FOR DETECTING A BATTERY LEVEL OF CHARGE, ASSEMBLY COMPRISING THE MODULE, AND AIRCRAFT COMPRISING THE ASSEMBLY
The invention relates to a module (1) for detecting a battery level of charge, comprising: an ammeter (10) comprising a magnetometer (15) and a current-measuring device (18), a voltmeter (20) comprising a first contact terminal (22), a second contact terminal (24) and a voltage-measuring device (28), a temperature sensor (30), a housing (50) intended to be attached to a first interconnection bar (82) and a second interconnection bar (84), the housing (50) having a receptacle (58) in which the magnetometer (15) is received, the receptacle (52) being intended to be received in a measuring hole (83) of the first interconnection bar (82), a first attachment member (52) for attaching the housing (50) to the first interconnection bar (82) and a second attachment member (54) for attaching the housing (50) to the second interconnection bar (84).
G01R 31/364 - Connexions pour bornes de batteries, munies de dispositions de mesure intégrées
H01M 10/48 - Accumulateurs combinés à des dispositions pour mesurer, tester ou indiquer l'état des éléments, p. ex. le niveau ou la densité de l'électrolyte
H01M 10/42 - Procédés ou dispositions pour assurer le fonctionnement ou l'entretien des éléments secondaires ou des demi-éléments secondaires
48.
LC INTERFACING FILTER INCORPORATING A DAMPING CIRCUIT
The invention relates to an LC interfacing filter comprising a parallel capacitor and a series inductor having eddy-current magnetic losses, the inductor (10) being configured so that the eddy-current magnetic losses are predominant with respect to the hysteresis losses, the inductor consisting of a tube (12) made of magnetic material and around which an electrical conductor (14) is wound, with an insulating sheet (16) separating the tube of magnetic material from the electrical conductor.
H01F 27/34 - Moyens particuliers pour éviter ou réduire les effets électriques ou magnétiques indésirables, p. ex. pertes à vide, courants réactifs, harmoniques, oscillations, champs de fuite
H01F 17/04 - Inductances fixes du type pour signaux avec noyau magnétique
H01F 27/32 - Isolation des bobines, des enroulements, ou de leurs éléments
H01F 17/06 - Inductances fixes du type pour signaux avec noyau magnétique avec noyau refermé sur lui-même, p. ex. tore
H01F 27/22 - Refroidissement par conduction de chaleur à travers des éléments de remplissage solides ou en poudre
A contactor includes a bridge which is movable between a closed state and an open state, including movable contacts; two fixed contacts facing the movable contacts, wherein in the closed state the movable contacts are in contact with the fixed contacts and in the open state the movable contacts are spaced apart from the fixed contacts; two magnets generating a magnetic field and generating a magnetic force in order to move an arc appearing between the fixed contacts and the movable contacts passing from a closed state to an open state; two fin blocks; and two pairs of arc guides, each being directed from the movable contacts to each of the two fin blocks, wherein at least fin slots forming a groove of the fin blocks face each guide of a pair of arc guides.
A method including calculating a total electrical charge accumulated in a battery at the current time by Coulomb counting on the basis of a total electrical charge accumulated in the battery at a previous time and on the basis of a current supplied by the battery, calculating a stored charge state, equal to the total accumulated electrical charge divided by a maximum total charge, calculating an available electrical charge on the basis of a difference between the total electrical charge and a non-extractible electrical charge which cannot be extracted from the battery because of its temperature, calculating an available charge state, equal to the available electrical charge divided by a maximum available charge.
G01R 31/367 - Logiciels à cet effet, p. ex. pour le test des batteries en utilisant une modélisation ou des tables de correspondance
G01R 31/36 - Dispositions pour le test, la mesure ou la surveillance de l’état électrique d’accumulateurs ou de batteries, p. ex. de la capacité ou de l’état de charge
G01R 31/3832 - Dispositions pour la surveillance de variables des batteries ou des accumulateurs, p. ex. état de charge utilisant l’intégration du courant sans mesurer la tension de la batterie
51.
ELECTRICAL GENERATION ARCHITECTURE FOR HYBRIDISED TURBOMACHINE
Electrical architecture for an aircraft with thermal/electrical hybrid propulsion, comprising, for each turbine engine:
an aeroplane AC electrical network,
at least one first electrical machine mechanically coupled to a high-pressure shaft of the turbine engine;
at least one second electrical machine mechanically coupled to a low-pressure shaft of the turbine engine;
a reversible AC/AC electrical energy conversion module;
switch elements; and
an electronic system for controlling the conversion module and the switch elements, configured to put the architecture;
in at least one so-called “power distribution hybridisation” operating mode corresponding to a first configuration of the switch elements in which the at least one second machine is coupled to the aeroplane network and at least one first machine is coupled to the aeroplane network via the electrical energy conversion module.
B60L 50/10 - Propulsion électrique par source d'énergie intérieure au véhicule utilisant la puissance de propulsion fournie par des générateurs entraînés par le moteur, p. ex. des générateurs entraînés par des moteurs à combustion
B64D 27/02 - Aéronefs caractérisés par le type ou la position des groupes moteurs
B64D 27/10 - Aéronefs caractérisés par le type ou la position des groupes moteurs du type à turbine à gaz
B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur ou l'énergie de ressorts
H02J 3/46 - Dispositions pour l’alimentation en parallèle d’un seul réseau, par plusieurs générateurs, convertisseurs ou transformateurs contrôlant la répartition de puissance entre les générateurs, convertisseurs ou transformateurs
An electrical converter includes an inverter configured to provide at least one input AC voltage from an input DC voltage (VE). The electrical converter further includes an AC-to-AC voltage converter configured to provide an output AC voltage from the at least one input AC voltage such that the output AC voltage has an amplitude that depends on a frequency of the at least one input AC voltage. A rectifier is configured to provide an output DC voltage from the output AC voltage.
H02M 5/293 - Transformation d'une puissance d'entrée en courant alternatif en une puissance de sortie en courant alternatif, p. ex. pour changement de la tension, pour changement de la fréquence, pour changement du nombre de phases sans transformation intermédiaire en courant continu par convertisseurs statiques utilisant des tubes à décharge avec électrode de commande ou des dispositifs à semi-conducteurs avec électrode de commande utilisant des dispositifs du type triode ou transistor exigeant l'application continue d'un signal de commande utilisant uniquement des dispositifs à semi-conducteurs
H02M 7/06 - Transformation d'une puissance d'entrée en courant alternatif en une puissance de sortie en courant continu sans possibilité de réversibilité par convertisseurs statiques utilisant des tubes à décharge sans électrode de commande ou des dispositifs à semi-conducteurs sans éléctrode de commande
H02M 7/539 - Transformation d'une puissance d'entrée en courant continu en une puissance de sortie en courant alternatif sans possibilité de réversibilité par convertisseurs statiques utilisant des tubes à décharge avec électrode de commande ou des dispositifs à semi-conducteurs avec électrode de commande utilisant des dispositifs du type triode ou transistor exigeant l'application continue d'un signal de commande utilisant uniquement des dispositifs à semi-conducteurs, p. ex. onduleurs à impulsions à un seul commutateur avec commande automatique de la forme d'onde ou de la fréquence de sortie
09 - Appareils et instruments scientifiques et électriques
37 - Services de construction; extraction minière; installation et réparation
42 - Services scientifiques, technologiques et industriels, recherche et conception
Produits et services
Apparatus and instruments for conducting, switching,
transforming, accumulating, regulating or controlling
electric current; electric harnesses; electric cables;
fiber-optic cables; optical fibers; connection equipment for
electric and optical cables; electric converters; protective
sheaths for electric cables and electric harnesses;
electrical equipment management systems (apparatus,
instruments and software); computer hardware and software in
the field of electricity distribution; software applied to
the protection, control, management, monitoring and
supervision of electrical installations and equipment. Repair, overhaul, reconditioning, adaptation, modification,
servicing and maintenance of electric and electronic
apparatus, instruments, systems, material and equipment for
use in the aeronautical and defense fields; repair,
overhaul, reconditioning, adaptation, modification,
servicing and maintenance of electrical installations and
electrical wiring for use in the aeronautical and defense
fields. Engineering and design office services (engineers'
services); research and development of new products;
professional consultancy and advisory service relating to
engineering; all these services relating to electrical
installations, equipment, apparatus, instruments and wiring
used in the aeronautical and defense fields.
The present invention relates to a power module (10) comprising: - a substrate (11), - electronic components (13) transferred onto the substrate (11), - a stiffening frame (25) assembled, in particular soldered, onto the substrate (11) and extending at least partially around the electronic components (13) so as to delimit an encapsulation space (26), and - an encapsulation material (20) arranged inside the encapsulation space (26), for coating the electronic components (13).
H01L 23/04 - ConteneursScellements caractérisés par la forme
H01L 23/24 - Matériaux de remplissage caractérisés par le matériau ou par ses propriétes physiques ou chimiques, ou par sa disposition à l'intérieur du dispositif complet solide ou à l'état de gel, à la température normale de fonctionnement du dispositif
55.
ACCUMULATOR BATTERY WITH ACTIVE THERMAL MANAGEMENT
Battery comprising an accumulator in contact via one of its ends with a heat pipe via the stack of a strip, of a thermal pad and of a thermal-interface plate, the strip allowing electrical connection of the accumulator, the thermal pad being positioned between the strip and the thermal-interface plate so as to improve the area of contact and thermal conduction, the thermal-interface plate being thermally connected to the heat pipe, the heat pipe comprising a heat-transport fluid which transports heat energy and being connected to a heat exchanger allowing the heat-transport fluid to be heated or cooled.
The invention relates to an electrical circuit (200) comprising at least one electrical converter stage and at least one capacitor (106) arranged upstream of said at least one electrical converter stage, the electrical circuit furthermore comprising a high-voltage source (102) and a contactor (104) arranged in series between the high-voltage source and the electrical converter, the electrical circuit comprising a pre-charging circuit (208) for pre-charging said capacitor, the pre-charging circuit being arranged in parallel with said contactor, wherein the pre-charging circuit comprises the following, in series in order from the high-voltage source to the capacitor: a fuse (214), a low-voltage relay (216) housed in a metal housing (217), a transistor (218) and a pre-charging resistor (212), the housing of the low-voltage relay being connected to a terminal of the high-voltage source (102).
An electrical architecture for an aircraft includes a first propulsion power distribution system distributing a high DC voltage, a second propulsion power distribution system distributing a high DC voltage, a first AC power distribution system distributing a three-phase AC voltage, a second AC power distribution system distributing a three-phase AC voltage, a first inverter connected between the first propulsion power distribution system and the first AC power distribution system, a second inverter connected between the second propulsion power distribution system and the second AC power distribution system, and an electronics module connected to the first inverter and to the second inverter in order to control the frequency of the three-phase AC voltage generated by the first inverter and the frequency of the three-phase AC voltage generated by the second inverter.
H02J 3/38 - Dispositions pour l’alimentation en parallèle d’un seul réseau, par plusieurs générateurs, convertisseurs ou transformateurs
H02J 3/42 - Synchronisation d'un générateur pour sa connexion à un réseau ou à un autre générateur avec connexion automatique en parallèle quand le synchronisme est obtenu
H02M 7/797 - Transformation d'une puissance d'entrée en courant alternatif en une puissance de sortie en courant continuTransformation d'une puissance d'entrée en courant continu en une puissance de sortie en courant alternatif avec possibilité de réversibilité par convertisseurs statiques utilisant des tubes à décharge avec électrode de commande ou des dispositifs à semi-conducteurs avec électrode de commande utilisant des dispositifs du type triode ou transistor exigeant l'application continue d'un signal de commande utilisant uniquement des dispositifs à semi-conducteurs
58.
BATTERY PROVIDED WITH A COOLING DEVICE COMPRISING AT LEAST ONE HEAT PIPE
The invention relates to an electric battery (10) comprising a plurality of electrochemical cells (11) arranged inside a containment structure (12). The battery (10) is provided with a cooling device comprising at least one heat pipe (1) configured to contain a heat-transfer fluid that is intended to undergo an evaporation and condensation cycle, wherein calories are drawn from an evaporation end (4) of the heat pipe (1) arranged in contact with the cells (11) and delivered to a condensation end (5) of the heat pipe (1) to a cold source (F) located outside the confinement structure (12), the at least one heat pipe (1) being overmoulded onto a base (13) of the confinement structure (12).
The invention relates to a method for evaluating the lifespan of an electrical connection between connectors each comprising at least one electrical contact housed in a housing, the housings being configured to be mechanically coupled to each other, comprising the following steps: - measuring the variation in the electrical contact resistance between the electrical contacts alone, as a function of a number of movements of the electrical contacts against each other and for a number of values of movement amplitude; - determining, from the preceding measurements, a function defining a maximum number of movements beyond which the electrical contact resistance exceeds a predefined maximum value representative of a degraded state of the connection, as a function of movement amplitude; - measuring movement amplitudes of each of the cavities of the housings in which the electrical contacts are intended to be placed, by subjecting the housings to mechanical stresses of amplitude and frequency of different values; - determining, from the measurements of amplitude, dynamic transfer functions of the housings defining the movement amplitude of the electrical contacts as a function of the amplitude and frequency of the mechanical stresses applied to the housings; - determining, for given amplitude and frequency values of the mechanical stresses applied to the connectors and using the functions determined beforehand, the lifespan of the connection between the connectors.
The invention relates to a method for monitoring and protecting an electrical hybridisation system against the risk of fire, the electrical hybridisation system comprising two rotary machines, each having at least one stator winding, each stator winding being associated with an AC-to-DC converter and a distribution box for delivering, on the basis of the DC voltages delivered by the AC-to-DC converters, a high DC voltage, on the one hand, for local loads and, on the other hand, for the electrical network of an aircraft, in which method current and voltage measurements are carried out in the distribution box, the converters and the stator windings of the rotary machines and if, once these measurements are consolidated together in a control card, the risk of fire is determined, the contactors of the distribution box and/or of the converters are selectively opened and the rotary machines are mechanically disconnected.
H02H 7/06 - Circuits de protection de sécurité spécialement adaptés aux machines ou aux appareils électriques de types particuliers ou pour la protection sectionnelle de systèmes de câble ou de ligne, et effectuant une commutation automatique dans le cas d'un changement indésirable des conditions normales de travail pour génératrices dynamo-électriquesCircuits de protection de sécurité spécialement adaptés aux machines ou aux appareils électriques de types particuliers ou pour la protection sectionnelle de systèmes de câble ou de ligne, et effectuant une commutation automatique dans le cas d'un changement indésirable des conditions normales de travail pour compensateurs synchrones
H02H 7/085 - Circuits de protection de sécurité spécialement adaptés aux machines ou aux appareils électriques de types particuliers ou pour la protection sectionnelle de systèmes de câble ou de ligne, et effectuant une commutation automatique dans le cas d'un changement indésirable des conditions normales de travail pour moteurs dynamo-électriques contre une charge excessive
H02P 29/02 - Protection contre les surcharges sans interruption automatique de l’alimentation
H02P 5/74 - Dispositions spécialement adaptées à la régulation ou la commande de la vitesse ou du couple d’au moins deux moteurs électriques pour commander au moins deux moteurs dynamo-électriques à courant alternatif
H02P 29/64 - Commande ou détermination de la température de l’enroulement
61.
AIRCRAFT TURBOMACHINE PROPELLER COMPRISING A SYSTEM FOR AUTONOMOUS SUPPLY OF HEATING MEMBERS FOR DE-ICING AND ASSOCIATED METHOD
The invention relates to an aircraft turbomachine propeller comprising a cone extending axially along an axis (X) and blades, the propeller being configured to be rotated by a shaft of the turbomachine (A), the propeller comprising a plurality of heating members (2) and a power supply system (3) for supplying power to the heating members (2), the power supply system (3) being mounted in the cone and configured to autonomously generate electrical power from the rotation of the shaft of the turbomachine (A).
B64D 15/12 - Dégivrage ou antigivre des surfaces externes des aéronefs par chauffage électrique
B64D 41/00 - Installations génératrices de puissance pour servitudes auxiliaires
F01D 25/02 - Dispositifs de dégivrage pour machines motrices dans lesquelles se produisent des phénomènes de givrage
H02K 7/18 - Association structurelle de génératrices électriques à des moteurs mécaniques d'entraînement, p. ex. à des turbines
F02C 7/00 - Caractéristiques, parties constitutives, détails ou accessoires non couverts dans, ou d'un intérêt plus général que, les groupes Entrées d'air pour ensembles fonctionnels de propulsion par réaction
62.
ELECTRICAL DISTRIBUTION SYSTEM FOR AN AIRCRAFT AND ASSOCIATED METHOD
The invention relates to an electrical distribution system (1) for an aircraft, comprising at least a first electrical distribution module (HV1) configured to supply at least two electrical loads (M1-1, M1-2) with power from at least a first electrical source (B1), a second electrical distribution module (HV2) configured to supply at least two electrical loads (M2-1, M2-2) with power from at least a second electrical source (B2), each electrical distribution module (HV1, HV2) comprising a first path (HV1-, HV2-) and a second path (HV1+, HV2+), each second path (HV1+, HV2+) of an electrical distribution module (HV1, HV2) being connected to the same equaliser busbar (2) by a second transfer line (LT1+, LT2+, LTi+) comprising a transfer contactor (GT1, GT2, GTi).
H02J 1/08 - Systèmes à trois filsSystèmes ayant plus de trois fils
B60L 3/00 - Dispositifs électriques de sécurité sur véhicules propulsés électriquementContrôle des paramètres de fonctionnement, p. ex. de la vitesse, de la décélération ou de la consommation d’énergie
H02J 9/06 - Circuits pour alimentation de puissance de secours ou de réserve, p. ex. pour éclairage de secours dans lesquels le système de distribution est déconnecté de la source normale et connecté à une source de réserve avec commutation automatique
63.
POWER SHARING IN AN AIRCRAFT USING DISTRIBUTED CONTROL
The invention relates to a system (100) for exchanging power in an aircraft, the system comprising: - a voltage bus (160); - a low-pressure electromechanical converter (150 BP); - a high-pressure electromechanical converter (150 HP); and - for each electromechanical converter (150 BP, 150 HP), a voltage control module (125 BP, 125 HP). The system (100) further comprises: - a computer (106) designed to provide a sharing setpoint (S) between the exchanged powers (PHP, PBP), this sharing setpoint (S) varying over time; and - for at least one of the electromechanical converters (150 BP, 150 HP): a module (120 BP, 120 HP) for ensuring that the sharing setpoint (S) is observed, which module is designed to adjust the power (PHP, PBP) that is exchanged by the relevant electromechanical converter (150 BP, 150 HP) in order to observe the received sharing setpoint (S), taking into account a received evaluation (PBP°, PHP°) of the power (PBP, PHP) exchanged by the other of the electromechanical converters (150 BP, 150 HP).
B64D 31/00 - Systèmes de commande des groupes moteursAménagement de systèmes de commande des groupes moteurs sur aéronefs
B64D 41/00 - Installations génératrices de puissance pour servitudes auxiliaires
F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
F02C 7/36 - Transmission de puissance entre les différents arbres de l'ensemble fonctionnel de turbine à gaz, ou entre ce dernier et l'utilisateur de puissance
F02C 9/00 - Commande des ensembles fonctionnels de turbines à gazCommande de l'alimentation en combustible dans les ensembles fonctionnels de propulsion par réaction alimentés en air ambiant
H02J 1/10 - Fonctionnement de sources à courant continu en parallèle
H02J 1/12 - Fonctionnement de générateurs à courant continu en parallèle avec des convertisseurs, p. ex. avec un redresseur à arc de mercure
H02J 3/46 - Dispositions pour l’alimentation en parallèle d’un seul réseau, par plusieurs générateurs, convertisseurs ou transformateurs contrôlant la répartition de puissance entre les générateurs, convertisseurs ou transformateurs
H02J 4/00 - Circuits pour réseaux principaux ou de distribution, la nature alternative ou continue du courant n'étant pas précisée
H02J 13/00 - Circuits pour pourvoir à l'indication à distance des conditions d'un réseau, p. ex. un enregistrement instantané des conditions d'ouverture ou de fermeture de chaque sectionneur du réseauCircuits pour pourvoir à la commande à distance des moyens de commutation dans un réseau de distribution d'énergie, p. ex. mise en ou hors circuit de consommateurs de courant par l'utilisation de signaux d'impulsion codés transmis par le réseau
64.
POWER SHARING IN AN AIRCRAFT USING CENTRALISED CONTROL
The invention relates to a system (100) for exchanging power in an aircraft, the system comprising: - a voltage bus (160); - a low-pressure electromechanical converter (150BP); - a high-pressure electromechanical converter (150HP); and - for each electromechanical converter (150BP, 150HP): a voltage control module (130BP, 130HP) and a control module (140BP, 140HP) for ensuring that the exchange setpoint (GBP*, GHP*) is observed. The system (100) further comprises a power adjustment module (106) configured, for at least one of the electromechanical converters (150BP, 150HP): to determine a voltage correction (δVBP, δVHP); and to apply, in the voltage control module (130BP, 130HP) associated with the relevant electromechanical converter (150BP, 150HP), the voltage correction (δVBP, δVHP) to a voltage setpoint (VDC*) so that the voltage control module (130BP, 130HP) adjusts the bus voltage (VDC) to the corrected voltage setpoint (VDC*).
B64D 41/00 - Installations génératrices de puissance pour servitudes auxiliaires
F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
F02C 7/36 - Transmission de puissance entre les différents arbres de l'ensemble fonctionnel de turbine à gaz, ou entre ce dernier et l'utilisateur de puissance
F02C 9/00 - Commande des ensembles fonctionnels de turbines à gazCommande de l'alimentation en combustible dans les ensembles fonctionnels de propulsion par réaction alimentés en air ambiant
H02J 1/10 - Fonctionnement de sources à courant continu en parallèle
H02J 1/12 - Fonctionnement de générateurs à courant continu en parallèle avec des convertisseurs, p. ex. avec un redresseur à arc de mercure
H02J 3/46 - Dispositions pour l’alimentation en parallèle d’un seul réseau, par plusieurs générateurs, convertisseurs ou transformateurs contrôlant la répartition de puissance entre les générateurs, convertisseurs ou transformateurs
H02J 4/00 - Circuits pour réseaux principaux ou de distribution, la nature alternative ou continue du courant n'étant pas précisée
H02J 13/00 - Circuits pour pourvoir à l'indication à distance des conditions d'un réseau, p. ex. un enregistrement instantané des conditions d'ouverture ou de fermeture de chaque sectionneur du réseauCircuits pour pourvoir à la commande à distance des moyens de commutation dans un réseau de distribution d'énergie, p. ex. mise en ou hors circuit de consommateurs de courant par l'utilisation de signaux d'impulsion codés transmis par le réseau
B64D 31/00 - Systèmes de commande des groupes moteursAménagement de systèmes de commande des groupes moteurs sur aéronefs
09 - Appareils et instruments scientifiques et électriques
37 - Services de construction; extraction minière; installation et réparation
42 - Services scientifiques, technologiques et industriels, recherche et conception
Produits et services
(1) Appareils et instruments pour la conduite, la distribution, la transformation, l'accumulation, le réglage ou la commande du courant électrique; harnais électriques; câbles électriques; câbles à fibres optiques; fibres optiques; matériels de raccordement pour câbles électriques et optiques; convertisseurs électriques; gaines de protection pour câbles électriques et harnais électriques; systèmes (appareils, instruments et logiciels) de gestion des équipements électriques; matériel informatique et logiciels dans le domaine de la distribution d'électricité; logiciels appliqués à la protection, au contrôle, à la gestion, à la surveillance et à la supervision d'installations et équipements électriques. (1) Réparation, révision, remise en état, adaptation, modification, entretien et maintenance d'appareils, d'instruments, de systèmes, de matériel et d'équipements électriques et électroniques utilisés dans les domaines aéronautique et de la défense; réparation, révision, remise en état, adaptation, modification, entretien et maintenance des installations électriques et des câblages électriques utilisés dans les domaines aéronautique et de la défense.
(2) Service d'ingénierie et de bureau d'études (travaux d'ingénieurs); recherche et développement de nouveaux produits; service de conseils et consultations professionnels relatifs à l'ingénierie; tous ces services étant relatifs aux installations, équipements, appareils, instruments et câblages électriques utilisés dans les domaines aéronautique et de la défense.
09 - Appareils et instruments scientifiques et électriques
37 - Services de construction; extraction minière; installation et réparation
42 - Services scientifiques, technologiques et industriels, recherche et conception
Produits et services
Apparatus and instruments for conducting, switching, transforming, accumulating, regulating or controlling electric current; electric harnesses; electric cables; fiber-optic cables; optical fibers; connection equipment for electric and optical cables; electric converters; protective sheaths for electric cables and electric harnesses; electrical equipment management systems (apparatus, instruments and software); computer hardware and software in the field of electricity distribution; software applied to the protection, control, management, monitoring and supervision of electrical installations and equipment. Repair, overhaul, reconditioning, adaptation, modification, servicing and maintenance of electric and electronic apparatus, instruments, systems, material and equipment for use in the aeronautical and defense fields; repair, overhaul, reconditioning, adaptation, modification, servicing and maintenance of electrical installations and electrical wiring for use in the aeronautical and defense fields. Engineering and design office services (engineers' services); research and development of new products; professional consultancy and advisory service relating to engineering; all these services relating to electrical installations, equipment, apparatus, instruments and wiring used in the aeronautical and defense fields.
Aircraft electric propulsion system including: a motor including a hollow rotor, and a power and control electronics device, in which the power and control electronics device includes at least two ring-shaped electrical tracks each including at least two inverters, the inverters being connected to each other in parallel, wherein the electrical tracks delimit a hollow circular part of the power and control electronics device, the hollow circular part being placed in the axis of the hollow rotor of the motor.
H02K 11/33 - Circuits d’entraînement, p. ex. circuits électroniques de puissance
B64C 29/00 - Aéronefs capables d'atterrir ou de décoller à la verticale, p. ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL]
B64D 27/30 - Aéronefs caractérisés par des groupes moteurs électriques
H02K 9/19 - Dispositions de refroidissement ou de ventilation pour machines avec enveloppe fermée et circuit fermé de refroidissement utilisant un agent de refroidissement liquide, p. ex. de l'huile
H02K 21/16 - Moteurs synchrones à aimants permanentsGénératrices synchrones à aimants permanents avec des induits fixes et des aimants tournants avec des aimants tournant à l'intérieur des induits avec des noyaux d'induits annulaires à pôles saillants
The invention relates to a power electronic module (23) comprising a housing (29), a substrate (31), at least one electronic component (33) transferred onto the substrate (31), a gel (35) encapsulating the electronic component (33) on the substrate (31) and in the housing (29), the power electronic module comprising a tapped nut (37) held in a wall (39) of the housing (29), a threaded rod (41) extending through the nut (37) inside and outside the housing (29), and a base (43) transferred onto the substrate (31) and aligned with the longitudinal axis of the rod (41).
H01L 23/373 - Refroidissement facilité par l'emploi de matériaux particuliers pour le dispositif
H01L 23/053 - ConteneursScellements caractérisés par la forme le conteneur étant une structure creuse ayant une base isolante qui sert de support pour le corps semi-conducteur
H01L 23/24 - Matériaux de remplissage caractérisés par le matériau ou par ses propriétes physiques ou chimiques, ou par sa disposition à l'intérieur du dispositif complet solide ou à l'état de gel, à la température normale de fonctionnement du dispositif
H01L 25/07 - Ensembles consistant en une pluralité de dispositifs à semi-conducteurs ou d'autres dispositifs à l'état solide les dispositifs étant tous d'un type prévu dans une seule des sous-classes , , , , ou , p. ex. ensembles de diodes redresseuses les dispositifs n'ayant pas de conteneurs séparés les dispositifs étant d'un type prévu dans la sous-classe
69.
MODULAR INTERCONNECTIONS FOR A MOTOR AND A POWER ELECTRONIC UNIT
An assembly made up of power electronics unit including three-phase outputs and a three-phase motor including three-phase inputs, wherein the assembly includes N three-phase outputs and N three-phase inputs with N>1, the three-phase inputs of the three-phase motor are opposite the three-phase outputs of the power electronic unit, the three-phase outputs and the three-phase inputs are located at the outer periphery of the power electronic unit and at the outer periphery of the three-phase motor, respectively, and the shape and the perimeter of the outer periphery of the three-phase motor are identical to those of the outer periphery of the power electronic unit.
H02K 11/33 - Circuits d’entraînement, p. ex. circuits électroniques de puissance
H02K 3/28 - Schémas d'enroulements ou de connexions entre enroulements
H02K 11/00 - Association structurelle de machines dynamo-électriques à des organes électriques ou à des dispositifs de blindage, de surveillance ou de protection
70.
ELECTRICAL CONTACTOR WITH AN INTEGRATED BREAKING DEVICE
The invention relates to an electrical contactor (10, 10') with an integrated breaking device comprising at least one arc-breaking device (20) having a first guide (21), a second guide (22), which is connected to the contact (12), and a finned breaking module (23), which comprises a series of conductive fins (24) extending between the first guide (21) and the second guide (22). The arc-breaking device (20) comprises a controlled switch (26) connected between two conductive fins (24) of the finned breaking module (23) and controlled by an electronic control unit (27).
Embodiments of the disclosure relate to a power electronics apparatus. The power electronics apparatus includes at least a first electrically conductive element and a second electrically conductive element. The elements are intended to be at a first electrical potential and at a second electrical potential, respectively. At least a first and second power electronics components are mounted on the first and second elements, respectively, a first portion and a second portion of a sink are mounted on the first conductive element and on the second conductive element, respectively, so as to permit the transfer of heat from each power component to the corresponding portion of the sink through the corresponding conductive element. An electrical insulator is present between each portion of the sink so as to prevent the risk of flashover between the two portions.
H01L 23/367 - Refroidissement facilité par la forme du dispositif
H01L 23/00 - Détails de dispositifs à semi-conducteurs ou d'autres dispositifs à l'état solide
H01L 23/14 - Supports, p. ex. substrats isolants non amovibles caractérisés par le matériau ou par ses propriétés électriques
H01L 23/373 - Refroidissement facilité par l'emploi de matériaux particuliers pour le dispositif
H01L 25/07 - Ensembles consistant en une pluralité de dispositifs à semi-conducteurs ou d'autres dispositifs à l'état solide les dispositifs étant tous d'un type prévu dans une seule des sous-classes , , , , ou , p. ex. ensembles de diodes redresseuses les dispositifs n'ayant pas de conteneurs séparés les dispositifs étant d'un type prévu dans la sous-classe
H05K 7/20 - Modifications en vue de faciliter la réfrigération, l'aération ou le chauffage
72.
POWER MODULE, AIRCRAFT COMPRISING SUCH A POWER MODULE, AND METHOD FOR MANUFACTURING THE POWER MODULE
The power module (100) comprises: - a substrate with an electrically insulating board (204) and electrically conductive tracks; - an electrical component (106) secured against at least one of the electrically conductive tracks; - a resistor (114) secured against at least one of the electrically conductive tracks; - a capacitor (116) connected in series with the resistor (114); and - an encapsulation (302). It furthermore comprises: - two pins (218, 220) having bases secured to two of the conductive tracks, these bases being covered by the encapsulation (302), and free ends projecting outside the encapsulation (302); and the capacitor (116) is placed outside the encapsulation (302) and connected to the free ends of the pins (218, 220).
H01L 23/498 - Connexions électriques sur des substrats isolants
H01L 23/367 - Refroidissement facilité par la forme du dispositif
H01L 23/538 - Dispositions pour conduire le courant électrique à l'intérieur du dispositif pendant son fonctionnement, d'un composant à un autre la structure d'interconnexion entre une pluralité de puces semi-conductrices se trouvant au-dessus ou à l'intérieur de substrats isolants
The invention relates to a normally closed contactor (21) which comprises a fixed contact (22) and a movable contact (23) facing each other in a housing (25), the movable contact (23) being movable between a closed position and an open position. A contact pressure spring (26) pushes the movable contact towards the fixed contact. An actuator (27) comprises a movable portion (29) rigidly connected to the movable contact (23) which moves it from the closed position to the open position. A return spring (33) pushes the movable portion (29) into its closed position. The mechanical anti-rebound device (34) comprises a first locking part (35) rigidly connected to the housing and a second locking part (36) opposite the first and rigidly connected to the movable portion (29), these locking parts (35, 36) being engaged in mutual locking when the movable contact (23) is in its closed position.
The invention relates to a system comprising one of the battery modules (2) coupled to at least one control device and formed of battery cells arranged in parallel coherent chains of battery cells, the battery modules (2) being distributed in two independent networks including a high-voltage network (3) and a low-voltage network (4) coupled in series, the low-voltage network (4) including a battery module (2) including a first sub-network (4A) and a second sub-network (4B) electrically separated from the first sub-network (4A) by a physical separation element (8) arranged on the battery module (2) of the low-voltage network (4), characterised in that each battery module (2) of the high-voltage network (3) includes a number of parallel coherent chains of battery cells equal to the number of parallel coherent chains of battery cells of each battery module (2) of the first sub-network (4A).
H01M 50/249 - MonturesBoîtiers secondaires ou cadresBâtis, modules ou blocsDispositifs de suspensionAmortisseursDispositifs de transport ou de manutentionSupports spécialement adaptés aux aéronefs ou aux véhicules, p. ex. aux automobiles ou aux trains
The invention relates to a high-voltage interrupter chamber (10) having a vertical main axis A and comprising two fixed contacts (18), offset with respect to each other in a transverse direction perpendicular to the main axis A, and a movable contact (20), wherein the movable contact (20) is mounted so as to be translatably movable with respect to the fixed contacts (18) between a closed position and an open position, the interrupter chamber (10) further comprising permanent magnets (28, 30) that are distributed on either side of the fixed contacts (18) and the movable contact (20), characterised in that it comprises a screen (34) made of an electrically insulating material, which is arranged between the fixed contacts (18).
The electrical installation (100) for an aircraft comprises: - a power source (102); - an electrical load (104); - first and second power supply lines (114, 116) connecting the electrical load (104) to the power source (102) in order to supply electric power to the electrical load (104); and - a double-break power contactor (118) located on the first power supply line (114), the power contactor (118) comprising two fixed contacts (118F) and one movable contact (118M). It furthermore comprises: - a branch (130) in parallel with the first power supply line (114), connected between the movable contact (118M) and a point (B) of the first power supply line (114); and - a device for opening one of the power supply lines (114, 116) on the basis of a current flowing in the branch (130).
H01H 9/38 - Contacts auxiliaires sur lesquels l'arc est transféré des contacts principaux
B60L 3/04 - Coupure de l'alimentation en énergie en cas de fausse manœuvre
H01H 9/54 - Circuits non adaptés à une application particulière du dispositif de commutation non prévus ailleurs
H01H 33/59 - Circuits non adaptés à une application particulière de l'interrupteur et non prévus ailleurs, p. ex. pour assurer le fonctionnement de l'interrupteur en un point déterminé de la période du courant alternatif
H01H 39/00 - Dispositifs de commutation actionnés par une explosion produite à l'intérieur du dispositif et amorcée par un courant électrique
H01H 85/02 - Dispositifs de protection dans lesquels le courant circule à travers un organe en matière fusible et est interrompu par déplacement de la matière fusible lorsqu'il devient excessif Détails
77.
ELECTRICAL MODULE CONFIGURED TO BE CONNECTED TO A POWER SHAFT OF A TURBINE ENGINE FOR AIRCRAFT AND METHOD FOR ASSEMBLING SUCH A MODULE
An electrical module configured to be connected to a power shaft of a turbine engine of an aircraft. The electrical module being configured to draw off power from/inject power into the power shaft. The electrical module comprising an electric machine comprising a machine housing in which a stator and a rotor is mounted, configured to be mechanically connected to the power shaft, the machine housing having a cylindrical shape extending along a cylinder axis, a first electric converter mounted in a first housing, a second electric converter mounted in a second housing, the second converter being independent of the first converter, the first housing and the second housing each being in the shape of a half-cylinder extending along the cylinder axis so as to form a cylindrical assembly that is mounted as an extension of the machine housing of the electric machine to limit the size of the electrical module.
H02M 7/00 - Transformation d'une puissance d'entrée en courant alternatif en une puissance de sortie en courant continuTransformation d'une puissance d'entrée en courant continu en une puissance de sortie en courant alternatif
B64D 27/35 - Aménagements pour la production, la distribution, la récupération ou le stockage d'énergie électrique à bord
H02K 11/00 - Association structurelle de machines dynamo-électriques à des organes électriques ou à des dispositifs de blindage, de surveillance ou de protection
78.
ARRANGEMENT OF CELLS OF AN ENERGY STORAGE ELEMENT AND METHOD FOR ASSEMBLING THIS ARRANGEMENT
The invention relates to an arrangement (10) of cells (11, 12) of an energy storage element comprising at least a first and a second adjacent cell (11, 12) each comprising two electrical connection tabs (13, 14) of positive polarity and negative polarity, respectively. Each of the tabs (13) of the first cell (11) comprises a folded portion (13b) extending from this first cell (11) to the second cell (12) and each of the tabs (14) of the second cell (12) comprises a folded portion (14b) extending from this second cell (12) to the first cell (11). The assembly (10) comprises a consecutive stack comprising a support (15), a first conductive bar (16), the folded portion (13b) of the connection tab (13) of the first cell (11), a second conductive bar (17), the folded portion (14b) of the connection tab (14) of the second cell (12), and a third conductive bar (18), the assembly (10) comprising means (19, 22) for the reversible fastening of this stack which are configured to apply a clamping force to the stack.
H01M 50/517 - Procédés pour interconnecter les batteries ou cellules adjacentes par des moyens de fixation, p. ex. vis, rivets ou boulons
H01M 50/503 - Interconnecteurs pour connecter les bornes des batteries adjacentesInterconnecteurs pour connecter les cellules en dehors d'un boîtier de batterie caractérisées par la forme des interconnecteurs
H01M 50/55 - Bornes caractérisées par la position des terminaux sur les cellules sur le même côté de la cellule
Aircraft electrical propulsion system comprising at least one electric motor (10) of which a setpoint is calculated according to a first channel (ISA) comprising a first control unit (20A) and according to a second channel (18B) comprising a second control unit (20B), the at least one electric motor comprising a rotor (12) and two star-wound stators (14A, 14B) and the first control unit of the first channel is connected to one of the two star-wound stators via a first power converter (22A) and the second control unit of the second channel is connected to the other of the two star-wound stators via a second power converter (22B), each of the first and second channels being rated for half the total power of the at least one electric motor.
H02P 29/028 - Détection d’un défaut, p. ex. court circuit, rotor bloqué, circuit ouvert ou perte de charge le moteur continuant de fonctionner malgré le défaut, p. ex. élimination, compensation ou résolution du défaut
H02P 6/00 - Dispositions pour commander les moteurs synchrones ou les autres moteurs dynamo-électriques utilisant des commutateurs électroniques en fonction de la position du rotorCommutateurs électroniques à cet effet
H02P 25/22 - Enroulements multiplesEnroulements pour plus de trois phases
80.
MOTOR WITH INTEGRATED CONTROL WITH AIR CIRCULATION IN THE ELECTRONIC CONTROL UNIT
The invention relates to a motor (10) with integrated control, comprising: - an electric machine (11) provided with at least one rotating part mounted on a drive shaft (40); - an electronic control unit (12) for controlling the electric machine; - a casing comprising a first cavity (21) in which the electric machine (11) is housed and a second cavity (22) in which the electronic control unit (12) is housed, the drive shaft passing through both the first and second cavities (21, 22), the second cavity being closed by at least one wall (23) close to the first cavity; and - an air-mixing device (50, 60), housed in the second cavity (22) and generating an air circulation within the second cavity so as to homogenise an air temperature within the second cavity.
H02K 11/33 - Circuits d’entraînement, p. ex. circuits électroniques de puissance
H02K 9/06 - Dispositions de refroidissement ou de ventilation par l'air ambiant s'écoulant à travers la machine comportant des moyens pour établir la circulation d'un agent de refroidissement avec des ventilateurs ou des dispositifs d'entraînement mûs par l'arbre de la machine
H02K 9/08 - Dispositions de refroidissement ou de ventilation par un agent de refroidissement gazeux circulant entièrement à l'intérieur de l'enveloppe de la machine
81.
POWER MODULE FOR SUPPLYING POWER TO AN ELECTRICAL LOAD OF AN AIRCRAFT, POWER SUPPLY SYSTEM AND ASSOCIATED METHOD
The invention relates to a power module (M) for supplying power to an electrical load (L) of an aircraft, the power module (M) comprising a plurality of power electronic components (2) mounted on a support substrate (1), at least one encapsulation layer (5) for encapsulating the plurality of power electronic components (2) in order to protect them, at least one power electrical connection (4) connected to at least one power electronic component (2), at least one fusible protection layer (6) in which at least one portion (40) of the power electrical connection (4) extends, the fusible protection layer (6) being configured to change state when a current greater than an allowable threshold flows in the portion (40) of the power electrical connection (4) so as to permanently stop the flow of current in the portion (40).
The invention relates to an electric contactor (10, 10') with integrated breaking device, comprising at least one arc-breaking device (20) having a first guide (21), a second guide (22), which is connected to the contact (12), and a finned breaking module (23), which is arranged between the first guide (21) and the second guide (22). Each arc-breaking device (20) has a fuse (25), which is arranged between the first arc guide (21) and the second arc guide (22), and an insulating enclosure (29), inside which the finned breaking module (23) and the fuse (25) are arranged, the fuse (25) being separated from at least one of the arc guides (21, 22) by a physical space (30).
H01H 73/18 - Moyens pour éteindre ou supprimer un arc
H01H 9/10 - Adaptation pour coupe-circuit incorporé
H01H 85/02 - Dispositifs de protection dans lesquels le courant circule à travers un organe en matière fusible et est interrompu par déplacement de la matière fusible lorsqu'il devient excessif Détails
83.
DEVICE FOR CONTROLLING A LEAST ONE ELECTRIC MOTOR FOR AN AIRCRAFT-PROPELLING ASSEMBLY
The present invention relates to a device (1) for controlling an electric aircraft-propelling assembly, said propelling assembly comprising a propeller (3) and at least one electric motor (4) that is powered by an electric supply voltage and that delivers a torque and a rotation speed to drive the propeller (3). The control device (1) comprises at least a unit (11) for measuring an electric supply voltage, and a control unit (12) suitable for making a signal delivered to the electric motor vary as a function of said electric supply voltage, with a view to making the rotation speed of the propeller vary.
The power contactor (100) comprises: - a fixed contact (102A); - a movable contact (104A); and - an electric insulating screen (112) designed to move between a spaced position and a position interposed between the fixed contact (102A) and the movable contact (104A) in the remote position of the latter. It furthermore comprises: - a return device (116) designed to push the screen (112) from its spaced position to its interposed position; and - a fuse (118) forming a mechanical stop that prevents the screen (112) from leaving its spaced position, the fuse (118) being designed to trip in order to allow the screen (112) to leave its spaced position so as to reach its interposed position under the effect of the return device (116), under the effect of heat released by an electric arc that occurs between the contact.
The apparatus (100) comprises: - a power source (102); - an electrical load (104); - first and second supply lines (114, 116) connecting the electrical load (104) to the power source (102), with a view to supplying electrical power to the electrical load (104); and - a power contactor (118) located on the first supply line (114). The apparatus (100) further comprises: - a branch (130) parallel to the first supply line (114), connected between two points (A, B) of the first supply line (114), these two points (A, B) surrounding the power contactor (118); - on this branch (130), an auxiliary contact (132) connected to the power contactor (118) and intended to open before and close after the power contactor (118); and - a device for opening, depending on a current flowing through the branch (130), one of the supply lines (114, 116).
H01H 9/38 - Contacts auxiliaires sur lesquels l'arc est transféré des contacts principaux
B60L 3/04 - Coupure de l'alimentation en énergie en cas de fausse manœuvre
H01H 9/54 - Circuits non adaptés à une application particulière du dispositif de commutation non prévus ailleurs
H01H 33/59 - Circuits non adaptés à une application particulière de l'interrupteur et non prévus ailleurs, p. ex. pour assurer le fonctionnement de l'interrupteur en un point déterminé de la période du courant alternatif
The invention relates to an electrical device (100) for protecting an electrical installation intended to be placed between a power supply (101) and an electrical load (102), the device comprising: - a power contactor (120) comprising two contacts (121, 122) that are intended to be connected to the power supply; - at least two Hall sensors (161, 162) configured to measure the electric currents at the input of the power contactor; - an electrical precharging circuit (150) intended to be placed between the power supply and the power contactor and connected to the electrical load; - a relay (140) configured to connect or disconnect the electrical precharging circuit; - a pyrotechnic electrical cutoff device (130) intended to be connected to the power supply and to the power contactor, and - a controller (110) configured to receive the measurements from the Hall sensors and to open or close the power contactor and the relay.
H02H 3/02 - Circuits de protection de sécurité pour déconnexion automatique due directement à un changement indésirable des conditions électriques normales de travail avec ou sans reconnexion Détails
H02H 3/087 - Circuits de protection de sécurité pour déconnexion automatique due directement à un changement indésirable des conditions électriques normales de travail avec ou sans reconnexion sensibles à une surcharge pour des systèmes à courant continu
87.
ELECTRICAL GENERATION SYSTEM FOR AIRCRAFT, AND ASSOCIATED METHOD
The invention relates to a contactor (1) comprising one or two electric arc extinguishing zones (5a) each comprising a magnetic blowout device which moves the electric arc (8a) – arising between a fixed contact (4a) and a movable contact (3a) of a movable bridge (2) switching to the open state – toward an electric arc extinguishing block (9a, 9b) comprising a plurality of stacked parallel fins (10). Each extinguishing zone is bounded in particular by two side walls (12a, 12b) each located at a distance from the fins of an electric arc extinguishing block, an upper wall (13) and a lower wall (14) which is located at a distance from the fins of the electric arc extinguishing blocks and is connected to each side wall by a concave connection (15a, 15b) of curved cross-section. The fins of each electric arc extinguishing block are inclined by an angle α of between 30 and 85 degrees with respect to the inner surface (20a, 20b) of the closest side wall.
The invention relates to a battery support comprising a base (1) and a heat transfer circuit (2), the heat transfer circuit (2) comprising a first duct and a second duct, wherein a first end of the first duct allows a heat transfer liquid to be received and a first end of the second duct allows the heat transfer liquid to be discharged, the first duct and the second duct being connected together by the second end thereof, the first duct and the second duct being delimited, on the one hand, by the base (1) and, on the other hand, by a set of walls, the first duct and the second duct sharing a common wall. The cross-section of the walls of the heat transfer circuit (2) is W-shaped and the heat transfer circuit is produced by additive manufacturing.
Assembly comprising a wall (14) and a wall feed-through system (10) configured to allow an electrical conductor (12) to be fed through the wall (14) and comprising an electrical conductor (12) intended to be mounted in a first through-hole (14a) passing through a wall (14) and comprising a shoulder (12a) and a threaded portion (17), on the opposite side to the shoulder (12a). The wall feed-through system (10) comprises a sealing member (18) configured to isolate the electrical conductor (12) from the wall (14) and configured to allow the electrical conductor (12) to be centred in the through-hole (14a) passing through the wall (14), said sealing member (18) being mounted between the shoulder (12a) of the electrical conductor (12) and a first surface (14b) of the wall (14), and a fastening member (22) configured to fasten the electrical conductor (12) and the sealing member (18) to the wall (14), and an insulating member (24, 30) partially surrounding at least the electrical conductor (12) and bearing axially between a second surface (14c) of the wall (14), the opposite surface from the first surface (14b) of the wall (14), and the fastening member (22).
The invention relates to a smart motor (10) including an electromechanical converter (12), electrical filtering means (14), an electronic control unit (16), two independent housings (18, 20) having a hollow cylindrical shape and being separated in an axial direction DA and a cooling device (24), a first housing (18) comprising a first end (180) and enclosing the electromechanical converter and a second housing (20) comprising a first end (200) and enclosing the electrical filtering means and the electronic control unit and the cooling device surrounding the first and second housings, the motor further comprising a first cover (182) enclosing a second end of the first housing (18) and a second cover (202) enclosing a second end of the second housing (20), the first and second covers facing each other and having ready-to-use connectors (40, 50), at least one of the first and second covers being made of a thermally insulating material.
H02K 11/33 - Circuits d’entraînement, p. ex. circuits électroniques de puissance
H02K 5/22 - Parties auxiliaires des enveloppes non couvertes par les groupes , p. ex. façonnées pour former des boîtes à connexions ou à bornes
H02K 7/08 - Association structurelle avec des paliers
H02K 5/20 - Enveloppes ou enceintes caractérisées par leur configuration, leur forme ou leur construction avec des canaux ou des conduits pour la circulation d'un agent de refroidissement
93.
AXIAL FAN FOR AIR COOLED ELECTRICAL AIRCRAFT MOTOR
Described is a fan assembly for an electrical aircraft motor having an axial fan with an inner hub of a first diameter and an outer hub of a second diameter. The outer hub may be concentrically aligned with the inner hub. A plurality of blades may extend between the inner hub and the outer hub. The fan assembly may also have a mounting plate connected to the inner hub. The mounting plate may attach to a component of the electrical aircraft motor.
F02K 5/00 - Ensembles fonctionnels comportant un moteur, autre qu'une turbine à gaz, entraînant un compresseur ou un ventilateur soufflant
B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur ou l'énergie de ressorts
B64D 33/08 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des systèmes de refroidissement des ensembles fonctionnels de propulsion
94.
AXIAL FAN FOR AIR COOLED ELECTRICAL AIRCRAFT MOTOR
Described is a fan assembly for an electrical aircraft motor having an axial fan with an inner hub of a first diameter and an outer hub of a second diameter. The outer hub may be concentrically aligned with the inner hub. A plurality of blades may extend between the inner hub and the outer hub. The fan assembly may also have a mounting plate connected to the inner hub. The mounting plate may attach to a component of the electrical aircraft motor.
H02K 5/18 - Enveloppes ou enceintes caractérisées par leur configuration, leur forme ou leur construction avec des nervures ou des ailettes pour améliorer la transmission de la chaleur
H02K 7/14 - Association structurelle à des charges mécaniques, p. ex. à des machines-outils portatives ou des ventilateurs
H02K 9/06 - Dispositions de refroidissement ou de ventilation par l'air ambiant s'écoulant à travers la machine comportant des moyens pour établir la circulation d'un agent de refroidissement avec des ventilateurs ou des dispositifs d'entraînement mûs par l'arbre de la machine
09 - Appareils et instruments scientifiques et électriques
37 - Services de construction; extraction minière; installation et réparation
42 - Services scientifiques, technologiques et industriels, recherche et conception
Produits et services
Apparatus and instruments for conducting, switching, transforming, accumulating, regulating or controlling electricity; Electric harnesses; Cables, electric; Fibre optic cables; Fiber optics; Coupling equipment for electric and optical cables; Converters, electric; Protective sheaths for electric cables and Protective sleeves, For use with the following goods: Electric harnesses; Systems (apparatus, instruments and computer software) for the management of electrical equipment; Computer hardware and computer software in the field of electricity distribution; Computer software for use in the protection, control, management, surveillance and monitoring of electrical installations and equipment. Repair, overhaul, Reconditioning, Adapting, modification, Maintenance and Maintenance In connection with the following goods: Electric and electronic apparatus, instruments, systems, hardware and equipment for use in the following fields: Aeronautic and defence; Repair, overhaul, Reconditioning, Adapting, modification, Maintenance and Maintenance In connection with the following goods: Electric installation and electrical wiring for use in the following fields: Aeronautic and defence. Engineering and surveying; Research and development of new products; Professional consultancy relating to engineering; all the foregoing In connection with the following goods: Electric installations, equipment, apparatus, instruments and cabling for use in the following fields: Aeronautics and Defense.
GENERAL ELECTRIC DEUTSCHLAND HOLDING GMBH (Allemagne)
GENERAL ELECTRIC COMPANY (USA)
Inventeur(s)
Delbosc, Philippe
Reigner, Pierre-Alain Jean Philippe
Osama, Mohamed
Zatorski, Darek
Abrégé
A turbine engine is disclosed, which comprises a first electric machine coupled to a low pressure shaft of the turbine engine and a second electric machine coupled to a high pressure shaft of the turbine engine. The turbine engine includes one or more engine loads and an external electrical connection for communicating electrical power between the turbine engine and an electrical system of an aircraft. The turbine engine includes a power management system including a high voltage DC busbar configured to communicate electrical power between the first and second electric machines and the engine loads and the external electrical connection. The power management system includes a control system configured to control power offtake from and injection to the first and second electric machines, and controls power delivered to the one or more engine loads and the external electrical connection.
F02C 3/107 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail ayant une turbine entraînant un compresseur avec plusieurs rotors raccordés par transmission de puissance
F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
F02C 7/32 - Aménagement, montage ou entraînement des auxiliaires
F02C 7/275 - Entraînement du rotor pour le démarrage mécanique
97.
ASSEMBLY OF AN ELECTRIC MOTOR AND A DEVICE FOR CONTROLLING THE ELECTRIC MOTOR, AND METHOD FOR CONTROLLING SUCH AN ASSEMBLY
The invention relates to an assembly (1) of an electric motor (2) for propelling an aircraft and a control device (5), the electric motor (2) comprising a stator (21) and a rotor (22) and at least one cooling channel (CR) configured to be supplied with a heat transfer fluid (F), the control device (5) being configured to issue a control command (01) in order to control the rotation of the rotor (22), the control device (5) also being configured to issue a heating command configured to generate a heating current in the stator (21) in order to heat the heat transfer fluid (F), the heating current comprising a non-zero DC component and a substantially zero quadratic component so as to limit the rotation of the rotor (22) during heating.
H02P 1/02 - Dispositions de démarrage de moteurs électriques ou de convertisseurs dynamo-électriques Détails
H02P 29/60 - Commande ou détermination de la température du moteur ou de l'entraînement
H02P 29/68 - Commande ou détermination de la température du moteur ou de l'entraînement basée sur la température d’un composant d’entraînement ou d’un composant semi-conducteur
B64D 1/00 - Largage, éjection ou réception, en cours de vol, d'objets, de liquides ou similaires
98.
ELECTRICAL SYSTEM OF AN ELECTRIC PROPULSION UNIT OF AN AIRCRAFT
The invention relates to an electrical system (100) having: - an electric circuit (102) having a electrically insulating flat support (104) and two electric conductors (106, 108) secured to the flat support, the two electric conductors (106, 108) being designed to have different respective electric potentials during operation of the electric circuit (102), the two electric conductors (106, 108) being separated from one another by an air insulation distance (DI); and - an electrically insulating spacer (110) extending over the flat support (104), between the two electric conductors (106, 108), and having raised elements (112) so as to define a leakage path (DF) between the two electric conductors (106, 108) along the spacer (110), this leakage path (DF) passing via the raised elements (112).
The invention relates to a nacelle system (8) for an electric machine (2) provided with cooling fins (6), which comprises a fairing (10) configured to match the shape of the electric machine (2) and an adjustment device (12) configured to hold the fairing (10) and press it against the cooling fins (6) for cooling the electric machine (2), the fairing (4) comprising at least one portion (14) of fairing (10), the adjustment device (12) comprising at least one connection means (16) arranged between two ends (20) of portion (14) of fairing (10). In particular, the nacelle system (8) enables the electric machine (2) to be cooled more effectively by improved air circulation and improves the performance of the electric machine (2).
H02K 5/18 - Enveloppes ou enceintes caractérisées par leur configuration, leur forme ou leur construction avec des nervures ou des ailettes pour améliorer la transmission de la chaleur
H02K 9/14 - Dispositions de refroidissement ou de ventilation dans lesquels l'agent de refroidissement gazeux circule entre l'enveloppe de la machine et une chemise extérieure
100.
ELECTRICAL CONTACTOR COMPRISING A SPRING FOR RAPIDLY DRIVING CONTACTS
The invention relates to an electrical contactor (10) comprising stationary contacts (12) and movable contacts (14) which are movable relative to the stationary contacts (12) between a position of contact with the stationary contacts and a position of separation from the stationary contacts (12); an actuator (16) for driving the movable contacts (14) to move relative to the stationary contacts (12) towards either the position of contact with the stationary contacts (12) or the position of separation from the stationary contacts (12); a linkage (30) for driving the movable contacts (14) from the contact position to the separation position, independently of the actuator (16); the electrical contact being characterised in that the linkage (30) comprises a drive spring (32) and a system for disengageably locking the linkage.
