The invention relates to a de-icing method carried out in a de-icing system (1) for de-icing a turboprop engine (100) comprising a fixed part (2) comprising an inverter (4) and an ice protection control unit (7), a rotating part (3) comprising a rotary control unit (5) and a heating mat (9), and a rotary transformer (8) between the fixed and rotating parts, the method comprising transferring uplink data from the rotary control unit to the ice protection control unit and downlink data from the ice protection control unit to the rotary control unit, wherein the method comprises steps of encoding: a) downlink data into frequency modulations in respect of a supply voltage delivered by the inverter around a predetermined nominal frequency; and, b) uplink data into series of predetermined changes to an electrical power consumed by the rotary control unit.
A method for controlling a hybrid turbine engine for an aircraft uses an energy storage assembly having a plurality of capacitive components. The turbine engine having a low-pressure shaft, a high-pressure shaft, and at least one power conversion device mounted on the low-pressure shaft or high-pressure shaft. The method includes precharging the capacitive components until a mean voltage reaches a first partial charge value, balancing the voltages of the capacitive components, charging the capacitive components until the mean voltage reaches a high value, and converting electrical energy stored in the storage assembly into mechanical energy delivered to the low-pressure shaft and/or to the high-pressure shaft in order to assist with maneuvering the aircraft.
B64D 31/18 - Systèmes de commande des groupes moteursAménagement de systèmes de commande des groupes moteurs sur aéronefs pour les groupes moteurs électriques pour les groupes moteurs hybrides-électriques
A twin-spool turbine engine has a low-pressure turbine connected to a low-pressure compressor by a rotating low-pressure shaft, a high-pressure turbine connected to a high-pressure compressor by a rotating high-pressure shaft, and a mechanical power feed device on at least one of the rotating shafts. The turbine engine also includes capacitive components adapted to supply the turbine engine with electrical energy through the mechanical power feed device, the capacitive components being arranged on the turbine engine or on a support structure of the turbine engine and being arranged to form at least one pair of concentric circles centered on a main axis of the turbine engine, the circles of capacitive components being radially close to one another.
The device for charging a battery of an aircraft comprises a reversible electrical power converter comprising a power inlet configured to be connected to the battery and a power outlet configured to be connected to a propulsion rotary electric machine driving a propeller of the aircraft in such a way that the power converter transfers electrical energy between the electric machine and the battery. The charging device also comprises a means for deactivating the propeller, the means being configured to prevent the rotation of the propeller and a parking socket connected between the charging contactor and the power outlet.
B60L 53/24 - Procédés de chargement de batteries spécialement adaptées aux véhicules électriquesStations de charge ou équipements de charge embarqués pour ces batteriesÉchange d'éléments d’emmagasinage d'énergie dans les véhicules électriques caractérisés par des convertisseurs situés dans le véhicule utilisant le convertisseur de propulsion du véhicule pour la charge
B60L 50/60 - Propulsion électrique par source d'énergie intérieure au véhicule utilisant de la puissance de propulsion fournie par des batteries ou des piles à combustible utilisant de l'énergie fournie par des batteries
B64D 35/021 - 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
5.
MAGNETIC HOLDING SYSTEM FOR AN ELECTRICAL PROTECTION MEMBER
The invention relates to an electrical protection member (100) comprising: - a stationary portion comprising two power terminals (101, 102); - a movable portion (120) able to come into contact with the stationary portion and to move between a position in which the electrical protection member is open and a position in which it is closed, the movable portion comprising an upper surface (120a), a lower surface (120b) facing the stationary portion and two contact points (121, 122) for contact with the stationary portion, which contact points are provided on the lower surface; - two springs (151, 152) configured to apply a pressing force that presses the two contact points of the movable portion towards the stationary portion; - a plate (130) positioned on the upper surface of the movable portion; - two magnetic bars (191, 192), each magnetic bar being positioned in a loop (1011, 1022) formed between a contact point of the movable portion and a power terminal of the stationary portion; - two magnetic flanges surrounding the movable portion, each magnetic flange being in contact with the two magnetic bars; characterised in that the electrical protection member also comprises a permanent magnet (131) positioned above the plate between the two contact points of the movable portion and between the two springs.
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
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
Transformateurs de courant électrique pour aéronefs; Convertisseurs de réseau électrique pour aéronefs; Convertisseur de tension pour aéronefs; Système de conversion électrique pour aéronefs; Equipement de conversion électrique pour aéronefs; Dispositifs de test pour pièces électroniques d’aéronefs; Appareils de régulation électrique pour aéronefs; Appareils de mesurage, de détection, de surveillance et de contrôle pour aéronefs. Réparation, révision, remise en état, adaptation, modification, entretien et maintenance des d'appareils, d'instruments, de systèmes, de matériel et d'équipements électriques et électroniques utilisés dans les domaines aéronautique et de la défense. Tests, authentification et contrôle de la qualité; Développement de systèmes de gestion d'énergie et d'électricité pour aéronefs; Services scientifiques et technologiques, Services d'assistance scientifique et technique et services de conseils, en rapport avec les produits suivants:Transformateurs de courant électrique pour aéronefs, Convertisseurs de réseau électrique pour aéronefs , Convertisseur de tension pour aéronefs , Système de conversion électrique pour aéronefs , Equipement de conversion électrique pour aéronefs , Dispositifs de test pour pièces électroniques d’aéronefs, Appareils de régulation électrique pour aéronefs, Appareils de mesurage, de détection, de surveillance et de contrôle pour aéronefs.
A housing for an electrical power storage battery includes a plate, onto which power elements of the battery are attached, and a bell cover covering the plate and means for mechanically attaching the bell cover onto the plate. The plate may include means for the electrical connection of the battery, means for the connection of communication means, and means for the thermal management of the electrical power elements.
H01M 50/262 - MonturesBoîtiers secondaires ou cadresBâtis, modules ou blocsDispositifs de suspensionAmortisseursDispositifs de transport ou de manutentionSupports avec des moyens de fixation, p. ex. des serrures
B60L 50/64 - Détails de construction des batteries spécialement adaptées aux véhicules électriques
B60L 58/24 - 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 pour la commande de la température des batteries
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
H01M 10/613 - Refroidissement ou maintien du froid
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
Economizing contact includes a fixed part, a part movable along a main direction, between a contact position and a break position, and an elastic blade attached to the fixed part forms an electric contact, as well as a stop mounted on the movable part and arranged for being away from the blade and coming to bear on the blade when the movable part is in contact position. The fixed part defines an orifice for passage of the stop facing the blade, where the orifice has an inner section substantially identical to an outer section of the stop, where the stop is movably mounted in translation in a plane on the movable part.
H01H 3/16 - Organes moteurs, c.-à-d. pour actionner le mécanisme d'entraînement par une force mécanique extérieure à l'interrupteur adaptés pour être actionnés dans une position limite ou autre position prédéterminée dans le trajet d'un corps, le mouvement relatif de l'interrupteur et du corps ayant principalement un autre but que d'actionner l'interrupteur, p. ex. un interrupteur de porte, un interrupteur de fin de course, un interrupteur de niveau d'étage d'un ascenseur
H01H 1/26 - Contacts caractérisés par la manière dont les contacts coopérants s'engagent en butant l'un contre l'autre avec montage élastique avec support par lame-ressort
H01H 3/32 - Mécanismes-moteurs, c.-à-d. pour transmettre la force motrice aux contacts
9.
DEVICE AND METHOD FOR PROTECTING AN ITEM OF EQUIPMENT SUPPLIED WITH POWER BY A HIGH-VOLTAGE DC BUS
The invention relates to a device (1) for protecting an item of equipment (E) to be supplied with power by a high-voltage DC bus (B), characterized by an inhibition circuit (15) intended to disconnect the high-voltage DC power source (S) and having a trigger (153) that is configured, in response to an activation signal (S1), to adopt a position (P1) that causes a signal (S2) commanding stoppage of the source (S) to be sent, the trigger (153) being connected to a first manual command means (154) that when actuated causes the trigger (153) to change from the position (P1) to a second position that does not cause the signal (S2) to be sent, and an abnormal voltage (VB) detection circuit (13), which is configured to send the signal (S1) when a voltage (VB) greater than a prescribed threshold (VMAX), which is greater than the nominal DC supply voltage value (HVDCNOM), is detected.
H02H 3/20 - 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 un excès de tension
H02H 9/04 - Circuits de protection de sécurité pour limiter l'excès de courant ou de tension sans déconnexion sensibles à un excès de tension
10.
SYSTEM FOR DE-ICING THE BLADES OF THE PROPELLER OF AN AIRCRAFT COMPRISING A PRIMARY MEASUREMENT WINDING
The invention relates to a contactor (1) comprising a contact chamber (23), a double electrical contact (3) in the contact chamber (23) which is movable between an open position and a closed position, and a device for extinguishing an electric arc by arc lengthening, the device comprising: - a stack of insulating walls (51a) spaced apart from one another so as to form a space (52a) between each adjacent insulating wall (51a), wherein a plurality of the insulating walls (51a) are made of polyamide-based thermoplastic; - at least one magnetic field emitter positioned against a face of a peripheral wall (2b, 2d) generating a constant-direction magnetic force in the contact chamber (23) in order to move an electric arc towards the first extinguishing zone (5a), wherein the arc appears as the double contact (3) moves between the closed state and the open state when a current flows in a first direction of current flow through the double contact.
The invention relates to a method for producing an electronic power module (100) comprising a substrate (110) comprising at least one stack (111) of several layers, the method further comprising: - a step of arranging a spacer element (115, 215, 315, 415, 515, 615, 715) on one (112b) of the layers of the at least one stack (111), or attaching said spacer element to said layer, the spacer element comprising a thickness greater than or equal to 200 µm, - and a step of attaching at least one connector (120) to the spacer element (115, 215, 315, 415, 515, 615, 715).
The invention relates to a converter (100) comprising a DC filter stage (110) and an inverter (120) connected to the filter stage (110), the filter stage (110) comprising at least common-mode capacitors (C1, C2, C3, C4). The filter stage (110) comprises a detection device (113; 114) for detecting partial discharge currents in the converter, the detection device (113; 114) comprising at least one decoupling capacitor and a current measurement circuit (1134; 1144) for measuring the current in the decoupling capacitor, the decoupling capacitor being formed by at least one of the common-mode capacitors (C1, C2; C3, C4).
H02M 1/12 - Dispositions de réduction des harmoniques d'une entrée ou d'une sortie en courant alternatif
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
14.
METHOD FOR CONTROLLING A HYBRID TURBOMACHINE INCORPORATING A TIME LIMITATION ON TORQUE, ASSOCIATED HYBRID TURBOMACHINE AND AIRCRAFT COMPRISING SUCH A TURBOMACHINE
EECEEC) to a control device in order to change the operating mode of the electric machine from a generator mode to a motor mode or vice versa, the device comprising a module configured to limit the torque variation over time between two threshold values of opposite signs, b) recovering a torque value at the output of the module and injecting the value at the input of the module so as to obtain a renewed torque value at the output of the limiter, c) repeating step b) N times, such that when the torque value injected at the input of the limiter lies between the two threshold values, the renewed torque value at the output of the limiter exhibits limited variation over time, with reference to the injected input value.
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
B64D 31/18 - Systèmes de commande des groupes moteursAménagement de systèmes de commande des groupes moteurs sur aéronefs pour les groupes moteurs électriques pour les groupes moteurs hybrides-électriques
F02K 5/00 - Ensembles fonctionnels comportant un moteur, autre qu'une turbine à gaz, entraînant un compresseur ou un ventilateur soufflant
15.
METHOD FOR MONITORING A STATE OF HEALTH OF A BATTERY ELECTRIC CELL
An electrical generation system for supplying at least one electrical network of an aircraft. The electrical generation system includes a control device configured to receive a general operating setpoint and to output a first parameterization setpoint for the first converter and a second parameterization setpoint for the second converter. Each parameterization setpoint being either a voltage regulation setpoint for slaving the converter to a distribution voltage or an auxiliary regulation setpoint for the turbomachine. The control device being configured to output a parameterization setpoint in relation to an auxiliary transition with a stabilization delay relative to a parameterization setpoint in relation to a voltage transition so that the voltage regulation is extended during an auxiliary transition.
The invention relates in particular to a power electronics device (200) comprising at least one power electronics element and at least one electronic control element (505), the device comprising a heat exchange plate (400), the plate including at least one portion of a hydraulic circuit for discharging heat energy and comprising a fluidic inlet (510) of the at least one portion of the hydraulic circuit and a fluidic outlet (405) of the at least one portion of the hydraulic circuit, the heat exchange plate being placed between the at least one power electronics element and the at least one electronic control element.
The invention relates to an electric propulsion unit (100) of an aircraft, comprising: - a DC voltage source (110); - an electric motor (130) comprising four three-phase windings (131, 132, 133, 134); and - a power and control electronic device (150) connected to the DC voltage source and to the electric motor, characterised in that the power and control electronic device of the electric motor is multi-channel (151, 152, 153, 154) and in that the electric propulsion unit comprises four electric channels (101, 102, 103, 104) each formed by a channel of the power and control electronic device of the electric motor and one of the three-phase windings, the first and second electric channels (101, 102) being configured to communicate with a control unit (120) of the aircraft and to send instructions to the third and fourth electric channels (103, 104), and in that the electric propulsion unit comprises internal communication buses (161, 162) between each channel.
H02P 25/22 - Enroulements multiplesEnroulements pour plus de trois phases
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
B64D 27/02 - Aéronefs caractérisés par le type ou la position des groupes moteurs
B64C 11/00 - Hélices, p. ex. du type carénéCaractéristiques communes aux hélices et aux rotors pour giravions
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
19.
AIRCRAFT PROPULSION ASSEMBLY COMPRISING A PROPELLER
The invention relates to an aircraft propulsion assembly of axis (X), comprising: - an electric motor (14); - a propeller (12) positioned upstream or downstream of the motor which is configured to rotate the propeller about the axis (X); - an inner cone (20) positioned upstream of the motor (14); - an outer fairing (22) mounted around the inner cone (20) and defining, jointly with the latter, an annular passage (P), the outer fairing (22) defining, at an upstream end (22a) of the passage, an inlet for the external air (E) flowing from upstream to downstream in the passage. A plurality of mechanical support elements (24, 26) are arranged in the passage (P) between the outer fairing (22) and the inner cone (20). The passage (P) and the mechanical support elements (24, 26) are configured to generate, at a downstream end (22b) of the passage, an upstream-downstream cooling air flow (F2), the flow rate whereof is sufficient to cool the electric motor.
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
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (CNRS) (France)
Inventeur(s)
Vendrame, Fernanda
Forgez, Christophe
Abrégé
Estimating the state of energy for a particular time, which includes:
Estimating the state of energy for a particular time, which includes:
receiving measurements of a temperature of the cell, of a voltage of the cell, and of a current exchanged by the cell;
Estimating the state of energy for a particular time, which includes:
receiving measurements of a temperature of the cell, of a voltage of the cell, and of a current exchanged by the cell;
estimating an internal resistance of the cell;
Estimating the state of energy for a particular time, which includes:
receiving measurements of a temperature of the cell, of a voltage of the cell, and of a current exchanged by the cell;
estimating an internal resistance of the cell;
estimating an open circuit voltage of the cell;
Estimating the state of energy for a particular time, which includes:
receiving measurements of a temperature of the cell, of a voltage of the cell, and of a current exchanged by the cell;
estimating an internal resistance of the cell;
estimating an open circuit voltage of the cell;
estimating a total energy delivered by the cell until the particular time;
Estimating the state of energy for a particular time, which includes:
receiving measurements of a temperature of the cell, of a voltage of the cell, and of a current exchanged by the cell;
estimating an internal resistance of the cell;
estimating an open circuit voltage of the cell;
estimating a total energy delivered by the cell until the particular time;
estimating a maximum energy that can be delivered by the cell, assuming that the temperature and the current remain constant; and
Estimating the state of energy for a particular time, which includes:
receiving measurements of a temperature of the cell, of a voltage of the cell, and of a current exchanged by the cell;
estimating an internal resistance of the cell;
estimating an open circuit voltage of the cell;
estimating a total energy delivered by the cell until the particular time;
estimating a maximum energy that can be delivered by the cell, assuming that the temperature and the current remain constant; and
subtracting the estimated total delivered energy from the estimated maximum energy.
G01R 31/374 - 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 avec des moyens pour corriger la mesure en fonction de la température ou du vieillissement
G01R 31/367 - Logiciels à cet effet, p. ex. pour le test des batteries en utilisant une modélisation ou des tables de correspondance
G01R 31/3842 - Dispositions pour la surveillance de variables des batteries ou des accumulateurs, p. ex. état de charge combinant des mesures de tension et de courant
G01R 31/389 - Mesure de l’impédance interne, de la conductance interne ou des variables similaires
G01R 31/396 - Acquisition ou traitement de données pour le test ou la surveillance d’éléments particuliers ou de groupes particuliers d’éléments dans une batterie
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
21.
ELECTRICAL GENERATOR SYSTEM FOR AN AIRCRAFT, AND ASSOCIATED METHOD
The invention relates to a turbine engine (1), in particular for an aircraft, comprising: - a low-pressure shaft (2) extending along a longitudinal axis (X) to a rear end (3); - a turbine engine stator (4) supporting the rear end (3) of the low-pressure shaft (2) via a rear bearing (5) arranged in a first lubrication chamber (7); and - an electric machine (15), located at the rear of the turbine engine, comprising an electric machine stator (24) secured to the turbine engine stator (4) and an electric machine rotor (25) capable of being disconnectably driven in rotation by the low-pressure shaft (2) by means of a connection device (30), wherein the electric machine (15) is at least partially contained in a second dedicated lubrication chamber (19) that is distinct from the first lubrication chamber (7), and wherein the electric machine rotor (25) is supported by at least one rotary bearing (40) arranged in the second chamber (19), the turbine engine (1) comprising a lubrication system (60) for the at least one rotary bearing (40), which lubrication system is contained in the second chamber (19).
F01D 5/02 - Organes de support des aubes, p. ex. rotors
F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
F01D 25/20 - Systèmes de lubrification utilisant des pompes de lubrification
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
23.
ARCHITECTURE FOR PARALLELIZING ELECTRICAL SOURCES OF AN ELECTRICALLY PROPELLED AIRCRAFT, AND ASSOCIATED METHOD
The invention relates to an electrical architecture (1) for supplying power to an electrical propulsion system (3) of an aircraft (5) comprising two engines (7), the electrical architecture comprising two electrical sources (9) each intended to supply power to one of the engines (7), a flight control computer (11), and two electrical buses (13) each intended to connect an electrical source (9) to a respective engine (7), and a parallelization controller (17) for parallelizing the electrical sources (9) and a switching member (19) configured to electrically connect the two electrical buses (13) upon command of the parallelization controller (17), the parallelization controller (17) being configured to order changing of the supply of power to at least one engine (7) so as to equalize the voltages across the terminals of the switching member (19).
A longitudinal cable including a first conductor, a first semiconductor layer, a first insulating layer, the first conductor including a plurality of conductor wires each including a conductive strand which is covered by an insulation sheath, the first conductor including at least one longitudinal discontinuous groove at the periphery uncovering the conductive strand of the conductor wires at the level of a contact zone, each uncovered conductive strand being a smoothing conductive strand, each smoothing conductive strand including longitudinal portions covered by an insulating sheath and uncovered longitudinal portions, the uncovered longitudinal portions being in contact with the first semiconductor layer at the level of a contact zone, the contact zones being spaced apart by the same contact pitch.
A device estimates two states of charge (SOC1, SCO2) of a battery that has a plurality of cells connected to one another, at least a fraction of the plurality of cells forming at least one set of cells having at least two cells. The device includes first determining means that are configured to determine a first state of charge (SOC1) of the battery from the voltage across the terminals of each cell and the temperature in the vicinity of each cell, and the current flowing through the terminals of the plurality of cells. The device further includes second determining means configured to determine a second state of charge (SCO2) of the battery from at least one variable measured across the terminals of the set of cells.
G01R 31/387 - Détermination de la capacité ampère-heure ou de l’état de 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 31/371 - 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 avec indication à distance, p. ex. sur des chargeurs séparés
G01R 31/374 - 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 avec des moyens pour corriger la mesure en fonction de la température ou du vieillissement
G01R 31/396 - Acquisition ou traitement de données pour le test ou la surveillance d’éléments particuliers ou de groupes particuliers d’éléments dans une batterie
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
26.
RHEOSTATIC SAFETY BRAKING FOR MOTORIZED ELECTRICAL SYSTEMS
Disclosed is a safety braking device (10) for a motorized electrical system, comprising: a polyphase motor (11) comprising a frame (12) forming a stator and a rotor (13) mounted in the frame (12) to pivot about an axis of rotation; at least one dissipative circuit (14) per phase of the motor comprising a plurality of braking resistors (15) and a plurality of activation switches (16) for activating the braking resistors; a plurality of connection switches (17) each connecting one of the dissipative circuits (14) to one of the phases of the motor and a control unit (30) connected to the switches in order to control them; the braking resistors (15) being arranged on the frame (12) and the activation switches (16) and the connection switches (17) being grouped together in an electrical box (18) fixed to the frame (12). A motorized electrical system (1) comprising such a device (10).
H02P 3/22 - Dispositions pour l'arrêt ou le ralentissement de moteurs, génératrices électriques ou de convertisseurs dynamo-électriques pour arrêter ou ralentir individuellement un moteur dynamo-électrique ou un convertisseur dynamo-électrique pour arrêter ou ralentir un moteur à courant alternatif par freinage sur court-circuit ou sur résistance
Rotating transformer intended to be installed around a shaft movable in rotation, the rotating transformer consisting of a plurality of stator annular sectors and a plurality of rotor annular sectors, the juxtaposition of these annular sectors forming a stator ring and a rotor ring consisting of elementary stator and rotor magnetic circuits including outer and inner magnetic cores and first and second electrical windings to allow a transfer of electrical energy by electromagnetic induction between the stator and rotor rings, the inner and outer magnetic cores being separated by the same air gap present on either side of the inner magnetic core and at least the outer magnetic cores have expansions at the level of the air gap to avoid a discontinuity of the magnetic field lines during the rotation of the movable shaft.
The invention relates to an electrical wiring harness (11) comprising: - at least one electric cable (23), - at least one electrical connector (10), - a mechanical protection and/or shielding braid (17) having at least one braided portion (17.1) and at least one unbraided portion (17.2) disposed on the electrical connector (10) side, - at least one protective sleeve (25) disposed around the mechanical protection and/or shielding braid 17, the protective sleeve 25 having at least one braided portion (25.1) covering at least the unbraided portion (17.2) of the mechanical protection and/or shielding braid (17).
The invention relates to a rear fitting (15) for a harness (11) that is intended to be mechanically connected to a connector (10) and comprises: a fixed body (23) comprising a front end (23.1) and a rear end (23.2), a rotary nut (24) rotatably mounted on the front end of the fixed body (23), said rotary nut (24) being intended to provide a removable mechanical connection between said rear fitting (15) and the connector (10), and a movable body (27) comprising a front end (27.1) and a rear end (27.2), the front end (27.1) of the movable body (27) being mounted rotatably with respect to the rear end (23.2) of the fixed body (23), the rear end (27.2) of the movable body (27) comprising, at the outer periphery, a connection area (28) for connecting with a screen or sheath (17) for electrical protection and/or mechanical protection.
H02G 3/02 - Installations de câbles ou de lignes électriques ou de leurs tubes de protection dans ou sur des immeubles, des structures équivalentes ou des véhicules Détails
H01R 35/04 - Connecteurs de ligne pouvant tourner d'un angle de rotation limité
H01R 39/02 - Collecteurs de courant rotatifs, distributeurs ou interrupteurs Détails
30.
HYBRID ELECTRICAL SYSTEM FOR SUPPLYING ELECTRICAL EQUIPMENT OF AN AIRCRAFT WITH POWER FROM A TURBINE ENGINE
The invention relates to a hybrid electrical system (8) for supplying electrical equipment of an aircraft with power from a turbine engine (1) comprising an HP shaft (7) and an LP shaft (3), the system (8) comprising a control unit (20), two electric machines (9, 10), each with two windings, and two electrical distribution control units (12) connected at output to a high-voltage DC electrical network (16) and to electrical loads (14), wherein one of the machines (9) is connected to the HP shaft (7) and the other machine (10) is connected to the LP shaft (3). Additionally, for each control unit (12), a first bidirectional DC-AC converter (13) is connected between a winding of the first machine (9) and the control unit (12), and a second bidirectional DC-AC converter (15) is connected between a winding of the second machine (10) and the control unit (12). For each control unit (12), the system comprises a high-voltage DC battery (17) and a third DC-DC bidirectional converter (18) connected between the battery (17) and the control unit (12), wherein the control unit (20) controls the three converters (13, 15, 18) in order to maintain a voltage quality of the network (16) within a voltage range.
The present disclosure relates to a protection system (10) for an electrical circuit (1), the protection system (10) comprising: - a conductor (11, 12, 13) comprising a first conductor part (11), a second conductor part (12) and a third conductor part (13) that electrically connects the first conductor part (11) and the second conductor part (12) together, and - a ferromagnetic body (14) arranged in the space between the first conductor part (11) and the second conductor part (12), the conductor (11, 12, 13) and the ferromagnetic body (14) being configured such that, when a current flowing in the conductor (11, 12, 13) has an amperage I greater than or equal to a threshold amperage IS, a mechanical force in the conductor (11, 12, 13) induced by this current causes mechanical breakage of the conductor (11, 12, 13).
H01H 35/00 - Interrupteurs actionnés par le changement d'une condition physique
H01H 85/00 - 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
A decentralised system for controlling an electrical network of an aircraft, the system including a plurality of distinct cells, each cell including a plurality of electrical contactors and each cell being connected to an electrical supply. Each cell has at least one microcontroller for controlling at least one contactor.
H02J 3/00 - Circuits pour réseaux principaux ou de distribution, à courant alternatif
H02J 4/00 - Circuits pour réseaux principaux ou de distribution, la nature alternative ou continue du courant n'étant pas précisée
33.
SYSTEM FOR DISCHARGING GAS FROM AIRCRAFT BATTERY CASINGS COMPRISING SYNCHRONIZED MEANS OF CONNECTION BETWEEN EACH CASING AND MEANS FOR DISCHARGING GAS FROM THE SYSTEM
This gas discharging system (1) is configured for connection to at least two casings (2) for electrical energy storage batteries of an aircraft and for connection to a common gas outlet (4) of the aircraft. The system (1) comprises, for each casing (2), a gas discharging means (3) associated with the casing (2) and connected to the common gas outlet (4). The system (1) comprises synchronized connection means (5) designed to concomitantly establish connections between each casing (2) and its associated gas discharging means (3).
H01M 50/358 - Passages externes d’évacuation des gaz sur le couvercle ou sur le boîtier de batterie
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
The invention relates to a controllable switch (IC) comprising, between two terminals (BO1, BO2): - a first branch (B1) comprising a first module (E1) having a switch that can be controlled to close and open, and a second module (E2) connected in series with the first module, the second module being able to limit the current in the first branch or store energy; - a second branch (B2) comprising a third module (E3) having a switch that can be controlled to open and close, which is able to interrupt the current flowing in the second branch and maintain the voltage between the two terminals of the switch when it is in the open state; and - a control module (E5) which is able to control the first and third modules.
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
H03K 17/0814 - Modifications pour protéger le circuit de commutation contre la surintensité ou la surtension sans réaction du circuit de sortie vers le circuit de commande par des dispositions prises dans le circuit de sortie
H03K 17/082 - Modifications pour protéger le circuit de commutation contre la surintensité ou la surtension par réaction du circuit de sortie vers le circuit de commande
H03K 17/12 - Modifications pour augmenter le courant commuté maximal admissible
H03K 17/13 - Modifications pour commuter lors du passage par zéro
H03K 17/284 - Modifications pour introduire un retard avant commutation dans les commutateurs à transistors à effet de champ
H03K 17/567 - Circuits caractérisés par l'utilisation d'au moins deux types de dispositifs à semi-conducteurs, p. ex. BIMOS, dispositifs composites tels que IGBT
35.
CONTROL UNIT FOR CONTROLLING THE POWER OF AT LEAST ONE BATTERY, AIRCRAFT COMPRISING SAID CONTROL UNIT, AND CORRESPONDING CONTROL METHOD
A control unit for controlling the power of a battery including at first and second incoming connections carrying a DC voltage and first and second outgoing connections delivering a DC voltage. The first incoming connection is connected to a first current sensor and to a high-voltage busbar via a protection member. The high-voltage busbar is connected to the first outgoing connection via a first controlled fuse and a second current sensor, and to a second outgoing connection via a second controlled fuse and a third current sensor. A control means is configured to switch the protection member, the first controlled fuse or the second controlled fuse based on received measurements so as to isolate an electrical fault.
A device for protecting against a short-circuit occurring on a high-voltage DC power supply line between a DC source and an active load, the device including a bypass circuit formed of a contactor K3 and a fuse F2 connected in series and set up parallel to the active load via a line independent of the high-voltage DC power supply line, the bypass circuit being configured such that most of the current passes through it once the fuse F2 has melted.
H02H 1/00 - Détails de circuits de protection de sécurité
H02H 7/09 - 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 surtensionCircuits 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 réduction de tensionCircuits 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 interruption de phase
H02H 7/18 - 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 pilesCircuits 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 accumulateurs
H02H 9/04 - Circuits de protection de sécurité pour limiter l'excès de courant ou de tension sans déconnexion sensibles à un excès de tension
One aspect of the invention relates to an electrical connection device comprising a cable (10) and an electrical connector (30) connected to one end of the cable (10), wherein the cable is a cable with a coaxial structure comprising a conductive core (11) surrounded successively by a first semiconductor layer (12), an insulating layer (13) and a second semiconductor layer (14).
H02G 15/103 - Jonctions de câbles protégées par des coffrets, p. ex. par des boîtes de distribution, de connexion ou de jonction avec des moyens pour atténuer la contrainte électrique
38.
METHOD AND DEVICE FOR MONITORING AN ELECTRICAL-ENERGY SUPPLY NETWORK OF AN AIRCRAFT
A method and a system for monitoring an electrical-energy supply network of an aircraft, wherein the electrical-energy supply network includes a plurality of protection and distribution devices connected together by at least one communication bus. According to the invention, each protection and distribution device: determines its location in the network, selects a configuration table associated with its location, receives a state table from each other protection and cutoff device, applies at least a part of the state tables to a job-related rule determining whether a contactor of the protection and cutoff device must be open or closed, controls the contactor according to the result of the job-related rule, and transfers an updated state table to each other protection and cutoff device.
H02H 3/00 - Circuits de protection de sécurité pour déconnexion automatique due directement à un changement indésirable des conditions électriques normales de travail avec ou sans reconnexion
39.
ELECTRICAL CIRCUIT EQUIPPED WITH TWO PYROTECHNIC SWITCHES ALLOWING TO ELECTRICALLY ISOLATE A SECTION WHEN A SHORT-CIRCUIT TYPE FAULT OCCURS
An electrical circuit of an aircraft including a power supply electrically connected to an electric charge by a conductive element, and a main electrical protection element. The electrical circuit includes a first pyrotechnic switch provided with at least one first initiator element and at least one first mechanical cut-off element, and a second pyrotechnic switch provided with at least one second initiator element and at least one second mechanical cut-off element. The first initiator element and the second initiator element are each electrically positioned in parallel with the at least one main electrical protection element.
The invention relates to a casing (5) comprising a heat sink (6) located between an inner part (10) and an outer part (11), and comprising a plurality of separate fins (8) having a body that rises from the outer face (102) of the inner part, wherein the body projects towards the outer part, and wherein these fins (8) are arranged in a plurality of rows (L) parallel to their axial direction (DA). The heat sink (6) has a plurality of separating walls (12), each extending in a plane parallel to their axial direction (DA) and defining a plurality of flow spaces (13) comprising at least one row (L) of fins comprising fins (8) whose bodies are oriented at an angle of incidence (β) with respect to their axial direction (DA), wherein (β) is non-zero for at least one fin (8) in the row (L).
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
H02K 11/33 - Circuits d’entraînement, p. ex. circuits électroniques de puissance
41.
AIRCRAFT PROPULSION SYSTEM COMPRISING A DEVICE FOR ACQUIRING THE ROTATIONAL SPEED OF THE ROTOR OF THE ELECTRIC MOTOR
The invention relates to an aircraft propulsion system (10) comprising: an electric motor (12) which comprises a wound stator (16) and a rotor (14) configured to generate a magnetic field and to be rotated, such that the magnetic field is rotating; and a device (40) for acquiring the rotational speed of the rotor, which device comprises at least one electrical measurement circuit (42) having a turn (48) comprising an electrically conductive material and extending between the first and second terminals of the electrical measurement circuit, the turn being mounted on the stator and surrounding a mounting portion of the stator, such that when the rotor is rotated, a magnetic flux from the rotor that varies over time passes through the turn, inducing a voltage across the terminals of the electrical measurement circuit, the acquisition device being configured to determine the rotational speed of the rotor on the basis of the voltage across the terminals of the electrical measurement circuit.
G01P 3/488 - Dispositifs caractérisés par l'utilisation de moyens électriques ou magnétiques pour mesurer la vitesse angulaire en mesurant la fréquence du courant ou de la tension engendrés de signaux ayant la forme d'impulsions délivrés par des détecteurs à réluctance variable
H02K 29/12 - Moteurs ou génératrices à dispositifs de commutation non mécaniques, p. ex. tubes à décharge ou dispositifs à semi-conducteurs avec des dispositifs détecteurs de la position utilisant des bobines détectrices
42.
DOUBLE-DISCONNECT DOUBLE-POLE BIDIRECTIONAL CONTACTOR WITH REVERSED MAGNETIC FIELDS
The invention relates to a double-disconnect double-pole bidirectional contactor configured to be mounted on two parallel busbars, comprising, for each pole, an interrupter chamber, in which the following are disposed:
a moving bridge having first and second moving contacts;
a first fixed contact and a second fixed contact;
a pair of magnets, able to generate a magnetic field with a constant direction, so as to generate a magnetic force for moving an arc appearing between the fixed contacts and the moving contacts of the moving bridge passing from a closed state to an open state;
four blocks of fins;
four arc guides.
The invention relates to a double-disconnect double-pole bidirectional contactor configured to be mounted on two parallel busbars, comprising, for each pole, an interrupter chamber, in which the following are disposed:
a moving bridge having first and second moving contacts;
a first fixed contact and a second fixed contact;
a pair of magnets, able to generate a magnetic field with a constant direction, so as to generate a magnetic force for moving an arc appearing between the fixed contacts and the moving contacts of the moving bridge passing from a closed state to an open state;
four blocks of fins;
four arc guides.
The two interrupter chambers are configured to simultaneously extinguish arcs having a first current direction for one pole, and arcs having a second current direction for the other pole, the first and second current directions being opposed. The first and second interrupter chambers are disposed parallel and are up against each other, defining a joining zone that is parallel to a direction of movement between the closed state and the open state of each of the two moving bridges, the first and second interrupter chambers being in fluid communication at least partly in the joining zone. There are four magnets and the pairs of magnets of the two poles are disposed so that the magnetic fields generated in the two poles are in a parallel direction but in opposite directions.
The invention relates to a method for evaluating an electrical property associated with a first part (1), comprising: - bringing first electrically conductive surfaces (1a, 2a) of the first and of a second part (1, 2) into electrical contact; - using first and second clamping members (O1, O2) to apply a predetermined compressive force on the first conductive surfaces (1a, 2a); and - measuring an electrical voltage between first and second electrodes (E1, E2) pressed against second surfaces of the first and second parts (1, 2) while an electrical current (Ix) flows from one of the parts (1, 2) to the other by passing via the first surfaces (1a, 2a); and - evaluating an electrical-resistance value (R) as a function of the measured voltage and of a value of the intensity of said electrical current (Ix).
G01N 27/04 - Recherche ou analyse des matériaux par l'emploi de moyens électriques, électrochimiques ou magnétiques en recherchant l'impédance en recherchant la résistance
G01R 27/08 - Mesure de la résistance par mesure à la fois de la tension et de l'intensité
The present disclosure relates to an electronic power module (10) for an electric motor, the electronic power module (10) comprising: - at least one electronic component, - a package (4) delimiting an interior volume (41) accommodating the at least one electronic component, - an encapsulating material at least partially filling the interior volume (41) of the package (4), wherein the package (4) comprises at least one injection opening (44) for injecting the encapsulating material and at least one degassing opening (45) configured to allow degassing of the encapsulating material from the interior volume (41) to the outside of the package (4), and wherein the package (4) is made in one piece.
H01L 23/16 - Matériaux de remplissage ou pièces auxiliaires dans le conteneur, p. ex. anneaux de centrage
H01L 21/56 - Encapsulations, p. ex. couches d’encapsulation, revêtements
H01L 23/04 - ConteneursScellements caractérisés par la forme
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 23/00 - Détails de dispositifs à semi-conducteurs ou d'autres dispositifs à l'état solide
H01L 23/31 - Encapsulations, p. ex. couches d’encapsulation, revêtements caractérisées par leur disposition
H01L 23/34 - Dispositions pour le refroidissement, le chauffage, la ventilation ou la compensation de la température
One aspect of the invention relates to a trip device (9) which trips when an electric current flowing in a conductive line (2) reaches a current threshold, the device comprising: - a magnetic armature (20) and a magnetic flap (21) suitable for surrounding a portion of the conductive line (2), the magnetic flap (21) being movable between an open position and a closed position; - a holding mechanism (35) configured to deform when a force (Fmag) applied to the magnetic flap (21) reaches a force threshold; and - an electrical switch (12) that is conductive when the magnetic flap (21) is in the closed position.
H01H 3/28 - Dispositions comportant une énergie à l'intérieur de l'interrupteur pour actionner le mécanisme d'entraînement utilisant un électro-aimant
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
H01H 89/00 - Combinaisons de plusieurs types d'interrupteurs électriques, de relais, de sélecteurs et de dispositifs de protection d'urgence, non couvertes par un des autres groupes principaux de la présente sous-classe
H01H 36/00 - Interrupteurs actionnés par la variation du champ magnétique ou champ électrique, p. ex. par le changement de la position relative d'un aimant et d'un interrupteur, par écran
H01H 9/32 - Corps isolant insérable entre les contacts
H01H 85/36 - Moyens pour appliquer une tension mécanique à l'élément fusible
46.
METHOD FOR MANAGING A MAXIMUM POWER OF AN ELECTRIC BATTERY
eq0tteq+Δteq+Δtt+Δtt+Δt of the battery for a future time t+Δt; and - determining (190) the maximum power Pmax of the battery according to: - the estimated voltage Ut+Δt of the battery for the future time t+Δt; and - the maximum predetermined current Imax of the battery or an estimated maximum current Imax of the battery.
H02J 7/00 - Circuits pour la charge ou la dépolarisation des batteries ou pour alimenter des charges par des batteries
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
47.
DEVICE AND METHOD FOR INITIATING AN ELECTRIC ARC ON ELECTRONIC EQUIPMENT, IN PARTICULAR ELECTRONIC POWER EQUIPMENT
The invention relates to a device for initiating an electric arc (9) in electronic equipment (10) in order to test the behaviour thereof under the effect of such electric arc and/or under the effect of an electric fire generated by same, the initiating device (9) comprising: - a transistor (19) including two power pins (22a, 22b) and a control pin (21), the power pins being capable of being electrically connected to a first electrical track and to a second electrical track of the equipment (10); and - a control circuit (20) of the transistor configured to apply to the control pin (21) of the transistor (19) a control signal capable of causing the irreversible shutdown of the transistor (19) and of causing the short-circuiting of the transistor (19) while the first track (13a) and the second track (13b) are powered on, and thus of generating an electric arc.
The invention relates to a battery module (1), in particular for an aircraft, comprising a cooling circuit (3) including a cooling tube (5) and a plurality of fins (7) attached to the cooling tube (5), each fin (7) having a cooperation portion (9) in contact with the cooling tube (5), the cooperation portion (9) extending at least partially along a direction (11) in which the cooling tube (5) extends, so as to define a shape-fitting cooperation between the fin (7) and the cooling tube (5); a plurality of electrochemical cells (13) each comprising two terminals (15), the electrochemical cells (13) being configured to be connected together in series and/or in parallel, each electrochemical cell (13) being configured to be in contact with at least one fin (7) or at least one element for connection to the fin (7).
H01M 10/647 - Éléments prismatiques ou plans, p. ex. éléments de type poche
H01M 10/6555 - Barres ou plaques disposées entre les éléments
H01M 10/6556 - Composants solides comprenant des canaux d'écoulement ou des tubes pour un échange de chaleur
H01M 50/211 - Bâtis, modules ou blocs de multiples batteries ou de multiples cellules caractérisés par leur forme adaptés aux cellules en forme de poche
One aspect of the invention relates to a switch for a high DC voltage, the switch comprising: - a first pair (5) of contacts (6, 7); - a second pair (8) of contacts (9, 10); - a blowout coil (2), configured to apply a magnetic field (B) to an electric arc formed within the first pair (5) of contacts (6, 7), wherein the switch (1) is characterised in that the blowout coil (2) is connected in parallel with the second pair (8) of contacts (9, 10).
H01H 9/34 - Éléments fixes pour restreindre ou sous-diviser l'arc, p. ex. plaques-barrières
H01H 9/40 - Contacts principaux multiples destinés à diviser le courant dans l'arc, ou la chute de tension le long de l'arc
H01H 9/44 - Moyens pour éteindre ou empêcher des arcs entre pièces traversées par le courant utilisant des aimants de soufflage
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
A geared motor (10), in particular for an aircraft, this geared motor (10) comprising an electric motor (12) and a mechanical reduction gearset (14), the reduction gearset (14) being of the planetary type and comprising a sun gear (26) rotatable about an axis (A), a ring gear (28) rotatable about the axis (A), and planet pinions (30) interposed between the sun gear (26) and the ring gear (28) and meshing with the sun gear (26) and the ring gear (28), the planet pinions (30) being borne by a planet carrier (32) which is fixed, the electric motor (12) being aligned with the axis (A) and comprising a rotor (16) and a stator (18), characterized in that the rotor (16) is fixed directly to the sun gear (26) or borne directly by the sun gear (26).
F16H 57/08 - Parties constitutives générales des transmissions des transmissions à organes à mouvement orbital
B64D 27/30 - Aéronefs caractérisés par des groupes moteurs électriques
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
F16H 57/021 - Structures de support d'arbres, p. ex. parois de séparation, orifices de logement de paliers, parois de carter ou couvercles avec paliers
The invention relates to an electric aircraft propulsion system (100) comprising: - an electric machine (110) configured to operate as a motor or generator and comprising a rotor; - a DC voltage source; - a power electronic device (120) connected to the DC voltage source and to the electric machine; and - a cooling device (172, 173) for cooling the electric machine and the power electronic device by heat-transfer fluid, the power electronic device comprising at least two interchangeable power electronic modules (121, 122, 123, 124) which are configured to each form an electrical path from the DC voltage source to the electric machine, each module comprising at least one first ready-to-use connector configured to be connected to the electric machine and to transmit an electrical signal, a second ready-to-use connector (151, 154) configured to be connected to the electric machine and to transmit electrical power, and a third ready-to-use connector configured to connect the cooling device to the electric machine, and in that the electrical propulsion system comprises a receiving structure (130) attached to the electric machine on which the power electronic modules are placed and delimiting an empty area (135) around the axis of the rotor of the electric 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 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 11/33 - Circuits d’entraînement, p. ex. circuits électroniques de puissance
B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur ou l'énergie de ressorts
52.
Device for detecting a short-circuit fault in a winding of an electric machine
An electric machine including at least one phase including two electrical paths in parallel, each electrical path of one and the same phase including a winding, the first electrical paths of all the phases being connected to one and the same first electrical node and the second electrical paths of all the phases being connected to one and the same second electrical node, the electric machine includes an equipotential wire electrically connecting the first and second electrical nodes and a current sensor configured to measure an electric current circulating in the equipotential wire.
G01R 15/18 - Adaptations fournissant une isolation en tension ou en courant, p. ex. adaptations pour les réseaux à haute tension ou à courant fort utilisant des dispositifs inductifs, p. ex. des transformateurs
G01R 19/165 - Indication de ce qu'un courant ou une tension est, soit supérieur ou inférieur à une valeur prédéterminée, soit à l'intérieur ou à l'extérieur d'une plage de valeurs prédéterminée
G01R 31/52 - Test pour déceler la présence de courts-circuits, de fuites de courant ou de défauts à la terre
The present invention relates to a method for manufacturing an electronic power module, comprising a step of applying a protective layer to a face of a substrate opposite the face carrying electronic power components, arranging the substrate in a mould so that the protective layer is applied to the bottom of the mould, and then injecting resin.
A process for current measurement includes a recombination of a low frequency current signal ILF coming from a low frequency current sensor and at least one high-frequency current signal IHF+offset coming from a high-frequency sensor on a single current conductor. The process includes the steps of amplification, filtering, and summing of signals suited to eliminating a direct offset created during amplification of the HF signals.
G01R 19/00 - Dispositions pour procéder aux mesures de courant ou de tension ou pour en indiquer l'existence ou le signe
G01R 15/18 - Adaptations fournissant une isolation en tension ou en courant, p. ex. adaptations pour les réseaux à haute tension ou à courant fort utilisant des dispositifs inductifs, p. ex. des transformateurs
55.
ELECTRIC OR HYBRID PROPULSION SYSTEM AND METHOD FOR COMPENSATING FOR OSCILLATORY CURRENT OSCILLATIONS
The present disclosure relates to an electric or hybrid propulsion system (10) for an aircraft, comprising: - a DC voltage bus (19), - at least two power electronics components (3) connected in parallel to the DC voltage bus (19), - a motor controller comprising a sensor (8) configured to measure electrical parameters representative of at least one of the power electronics components (3), the measured electrical parameters comprising in particular a strength of a current flowing through the DC voltage bus (19) and/or a voltage across the terminals of the DC voltage bus (19), each power electronics component (3) being electrically connected to a separate stator winding, each stator winding being contained in an electrical machine (5), the electrical machine (5) being configured to convert electrical energy transmitted by the DC voltage bus (19) to the electrical machine (5) via the power electronics components (3) into a mechanical torque in order to provide thrust to an aircraft, the propulsion system comprising an active compensation system (18) for the at least one power electronics component (3) configured to attenuate oscillatory currents flowing between the at least one power electronics component (3) and the other power electronics components (3) via the DC voltage bus (19) on the basis of the measured electrical parameters.
H02J 1/02 - Dispositions pour réduire les harmoniques ou les ondulations
H02M 1/14 - Dispositions de réduction des ondulations d'une entrée ou d'une sortie en courant continu
H02M 7/493 - 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 les convertisseurs statiques étant agencés pour le fonctionnement en parallèle
56.
DC electrical power distribution device, and associated propulsion system and aircraft
A DC electrical power distribution device for an aircraft propulsion duct having a main power supply line configured to supply at least one propulsion assembly of the propulsion duct with power from a high-voltage DC electrical power supply source and including main switching means and fast switching means for connecting the source to the propulsion assembly. The device can include a secondary power supply line configured to be connected to another distribution device and configured to supply the propulsion assembly with power from the other device when the main switching means are open.
The invention relates to a power supply architecture (1) for a hybrid-electric propulsion aircraft (0), comprising a gas turbine (2), a propulsion power supply network (5), and a non-propulsion power supply network (6); the propulsion power supply network (5) comprising a first AC generator (9), at least one first AC/DC converter (10), and at least one first battery (11) for supplying power to the propulsion equipment (7) of the aircraft; the non-propulsion power supply network (6) comprising a second AC generator (20), at least one second AC/DC converter (21), and at least one second battery (22) for supplying power to the non-propulsion equipment (8) of the aircraft.
B60L 50/12 - 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 utilisant des générateurs à courant alternatif et des moteurs à courant continu
B60L 50/61 - Propulsion électrique par source d'énergie intérieure au véhicule utilisant de la puissance de propulsion fournie par des batteries ou des piles à combustible utilisant de l'énergie fournie par des batteries par des batteries chargées par des générateurs entraînés par le moteur, p. ex. des véhicules électriques hybrides du type série
58.
CONTROL DEVICE FOR A PERMANENT-MAGNET SYNCHRONOUS THREE-PHASE ROTATING MACHINE
A permanent-magnet synchronous three-phase rotating machine equipped with a control device having a command processor for an inverter driving phases of said machine, an angular speed and position estimator module for the rotor of the machine equipped at the input thereof with an input selector module, receiving digital voltage data, where said input selector module is driven by an operating mode command for said machine to select input data for the angular speed and position estimator module of the machine.
H02P 21/18 - Estimation de la position ou de la vitesse
B64D 27/30 - Aéronefs caractérisés par des groupes moteurs électriques
B64D 31/16 - Systèmes de commande des groupes moteursAménagement de systèmes de commande des groupes moteurs sur aéronefs pour les groupes moteurs électriques
H02P 21/22 - Commande du courant, p. ex. en utilisant une boucle de commande
59.
Generic high-voltage DC electrical distribution panel
A high-voltage DC electrical distribution plate with two integrated electromechanical power contactors. Chambers of fixed and movable contact terminals of the two contactors are disposed on a first of the major surfaces of the plate, while on the second major surface of the plate are disposed complementary assemblies of the two contactors, each complementary assembly including a motor intended to activate the contact terminals of the contactor in question. The other components disposed on the second major surface of the plate leave a free space constituting an area of attachment of the complementary assemblies of the two contactors, this area being dimensioned to allow the arrangement of the complementary assemblies of the contactors in two orthogonal orientations allowing the motors to activate contact terminals of different sub-assemblies of the contact chambers and thus to make the parallel or series configurations of the contactors.
H02J 7/00 - Circuits pour la charge ou la dépolarisation des batteries ou pour alimenter des charges par des batteries
H02J 7/34 - Fonctionnement en parallèle, dans des réseaux, de batteries avec d'autres sources à courant continu, p. ex. batterie tampon
60.
ELECTRIC OR HYBRID-ELECTRIC PROPULSION AIRCRAFT WITH AERODYNAMIC BRAKING IMPLEMENTED BY THE ROTOR OF AN ELECTRIC MACHINE, AND MOTOR UNIT FOR SUCH AN AIRCRAFT
01nn x Nn0nnn of order n is strictly negative. The use of a polynomial law ensures stable operation and is not dependent on the reliability of sensors external to the motor unit, such as airspeed sensors of an aircraft.
H02P 3/14 - Dispositions pour l'arrêt ou le ralentissement de moteurs, génératrices électriques ou de convertisseurs dynamo-électriques pour arrêter ou ralentir individuellement un moteur dynamo-électrique ou un convertisseur dynamo-électrique pour arrêter ou ralentir un moteur à courant continu par freinage en récupération
B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur ou l'énergie de ressorts
61.
DEVICE FOR ELECTRICALLY JOINING TWO SECTIONS OF ELECTRICAL CABLE, METHOD FOR CONNECTING TWO SECTIONS OF ELECTRICAL CABLE BY WAY OF SUCH A DEVICE, AND POWER CABLE EQUIPPED WITH SUCH A DEVICE
An electrical joining device for connecting a first section and a second section of an electric cable, includes a first cabling head including an L-shaped first conductive element, mounted on the end of the first cable section, and a first insulating element surrounding the first conductive element; a second cabling head including an L-shaped second conductive element, mounted on the end of the second cable section, and a second insulating element covering the second conductive element, an arm of the second conductive element, covered by the second insulating element, being housed between the first conductive element and the first insulating element so as to permit a rotation between the first cabling head and the second cabling head.
One aspect of the invention relates to a method (100) for managing a state of available charge SOCDisp of an electric battery of an aircraft, the method comprising the steps of: - obtaining (110) a first intermediate state of available charge SOCDisp1 from a battery capacity table according to a temperature of the battery; - obtaining (120) a second intermediate state of available charge SOCDisp2 from a stored state of charge, a first instantaneous voltage, an instantaneous open-circuit voltage, and a predetermined minimum allowable voltage; - measuring (130) a second instantaneous voltage Ucell across the terminals of the battery; and - determining (140) a state of available charge SOCDisp from the first intermediate state of available charge SOCDisp1, the second intermediate state of available charge SOCDisp2, and the measured second instantaneous voltage Ucell (130).
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 31/367 - Logiciels à cet effet, p. ex. pour le test des batteries en utilisant une modélisation ou des tables de correspondance
G01R 31/382 - Dispositions pour la surveillance de variables des batteries ou des accumulateurs, p. ex. état de charge
G01R 31/387 - Détermination de la capacité ampère-heure ou de l’état de charge
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
63.
METHOD FOR CONTACTLESS COMMUNICATION BETWEEN A FIXED REFERENCE FRAME AND A ROTATING REFERENCE FRAME BY ENCODING A POWER SIGNAL
Disclosed is a method for communicating data for a system for de-icing a turbomachine that comprises a fixed reference frame and a rotating reference frame, the system comprising a contactless rotating electrical transformer (RTU) a primary of which is tied to the fixed reference frame and a secondary of which is tied to the rotating reference frame, the fixed reference frame comprising an ice protection and control unit (IPC) and a power supply device (DC/AC) for supplying an AC current to the primary, the protection and control unit (IPC) transmitting instructions to the power supply device (DC/AC) to adjust a level of electric power delivered to the primary, the rotating reference frame comprising a propeller (1) to which resistors are secured, and a switch for sequentially distributing, to the resistors, electric power that is transmitted to the secondary. The protection and control unit (IPC) is programmed to transmit switching orders to the switch via the power supply device (DC/AC) and the transformer (RTU), by giving the power supply device (DC/AC) instructions (Ic1, Ic2, Ic3, Ic4, Ic5, Intl) to encode a train of voltage waves (To) applied to the primary, the switch being programmed to decode the train of voltage waves (To) recovered at the secondary.
The invention relates to a battery (1) for storing electrical energy, comprising: at least one stack (7) of electrical cells (6); and a housing including a base (3) to which the stack (7) of cells of the battery (1) is attached. The battery (1) comprises: at least two compression plates (8) which are arranged on either side of the stack; means (10) for attaching the compression plates (8) to the base (3); at least one tie rod (12) which is capable of pressing the compression plates (8) against the cells (6) of the stack (7); and at least one elastic device (15) for compensating for gaps in the stack in a direction of dimensional variation of the stack, the device comprising at least one flat-wire wave spring.
H01M 50/209 - Bâtis, modules ou blocs de multiples batteries ou de multiples cellules caractérisés par leur forme adaptés aux cellules prismatiques ou rectangulaires
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 50/289 - 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
A switch includes a cut-off chamber including a contact of the switch and a fluid outlet, a channel including an inlet open on the fluid outlet of the cut-off chamber, an outlet, a fluid outlet circuit formed by the channel and the cut-off chamber, wherein the channel is elbow-shaped and includes at least two elbow ducts dividing a flow of the fluid by partitions.
H01H 9/34 - Éléments fixes pour restreindre ou sous-diviser l'arc, p. ex. plaques-barrières
H01H 33/53 - EnveloppesRéservoirs, cuves, tuyauterie ou robinetterie pour le fluide d'extinction d'arcAccessoires pour ces dispositifs, p. ex. dispositifs de sécurité, dispositifs de décompression
The invention relates to a protection device (1) for protecting a mixed electrical apparatus (M) configured to be electrically connected to an LVDC network as well as to an HVDC network, the protection device (1) comprising a first connector (C1) configured to be connected to the LVDC network, a second connector (C2) configured to be connected to the mixed electrical apparatus (M), the second connector (C2) being connected to the first connector (C1) by a power supply line, a third ground connector (C3) connected by a ground line to the power supply line at a connection point (CX), at least one first diode (D1), mounted in reverse on the ground line between the connection point (CX) and the third ground connector (C3), and at least one first fuse (F1), mounted on the power supply line, between the connection point (CX) and the second connector (C2).
H02H 1/04 - Dispositions pour prévenir la réponse à des conditions transitoires anormales, p. ex. à la foudre
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 9/00 - Circuits de protection de sécurité pour limiter l'excès de courant ou de tension sans déconnexion
67.
CONTACTOR WITH ARC GUIDES AND PROTECTION INTEGRATED INTO THE ARC GUIDES, CORRESPONDING SYSTEM AND AIRCRAFT
A contactor including a first electrical contact, a second electrical contact, and a movable bridge displaceable between a closed position and an open position, the contactor further including: a lower arc guide including a first portion connected to the first electrical contact, and a second portion connected to the second electrical contact, an upper arc guide including a first portion facing the first portion of the lower arc guide, a second portion facing the second portion of the lower arc guide, and a fuse connecting the first portion and the second portion of the upper arc guide.
The invention relates to an electric power cable (20) including: - a hybrid conductor (21) comprising: - a central Litz wire portion (22) including a plurality of electrically conductive strands (23) which are electrically insulated from one another; - a crown portion (25) including electrically conductive strands (26) which are not electrically insulated from one another, a thickness of the crown portion (25) being calculated so as to be less than or equal to a skin thickness (δ); and - an insulator (27) which is arranged around the hybrid conductor (21).
H01B 7/00 - Conducteurs ou câbles isolés caractérisés par la forme
H01B 7/30 - Conducteurs ou câbles isolés caractérisés par la forme avec dispositions pour réduire les pertes dans les conducteurs transmettant du courant alternatif, p. ex. dues à l'effet pelliculaire
The invention relates to a system for recording information in an aircraft, the system comprising: - at least two static power switches (1081, 1082, 1083); - a central computer (112); a data bus (114) to which the central computer (112) and the switches (1081, 1082, 1083) are connected. Each switch (1081, 1082, 1083) is configured to: - detect an event (EV) and a state snapshot (INST) at the time of this event (EV); - generate an identifier (ID) of the event (EV); - record a local association that groups the identifier (ID), the event (EV) and the state snapshot (INST); and - transmit the identifier (ID) of the event (EV) and an identifier of this switch to the central computer (112) via the data bus (114). The central computer (112) is configured to: - receive the identifier (ID) of the event (EV) and the identifier of the static power switch (1081, 1082, 1083) from the data bus (114); - determine a reception time of the identifier (ID); and - record a central association that groups the identifier (ID) of the event (EV), the identifier of the switch (1081, 1082, 1083) and the reception time, which is used as a timestamp (H) for the event (EV).
The invention relates to a method for protecting an electrical installation, the electrical installation comprising: - a contactor, - at least two electric current-measuring sensors, - a pyrotechnic electrical switching device, the method comprising: - measuring the strength of the current, - comparing the strength of the current and two thresholds, and - if the strength is between a first threshold and a second threshold, - transmitting a command to open the power contactor, - if the strength is greater than the second threshold, - transmitting a command to trigger opening of the pyrotechnic electrical switching device, - if the pyrotechnic electrical switching device does not open, - comparing the strength of the current and a third threshold value, - if the strength of the current is less than the third threshold value, transmitting a command to open the contactor.
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
71.
SHORT-CIRCUIT PROTECTION METHOD FOR A MOSFET POWER CONVERTER CONNECTED TO A DC POWER SUPPLY NETWORK
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
75.
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
76.
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.
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
81.
DEVICE FOR PROTECTION AGAINST BEARING DEFECTS IN ROTATING ELECTRIC MACHINES
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
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
83.
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
92.
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
93.
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.
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
97.
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.
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.
B64D 27/357 - Aménagements pour la production, la distribution, la récupération ou le stockage d'énergie électrique à bord utilisant des piles
B64D 31/18 - Systèmes de commande des groupes moteursAménagement de systèmes de commande des groupes moteurs sur aéronefs pour les groupes moteurs électriques pour les groupes moteurs hybrides-électriques
100.
DEVICE FOR CONNECTING, BY REALLOCATION OF TRANSMISSION CHANNELS, TO AN ON-BOARD PASSIVE FIBRE MULTIPLEXED COMMUNICATION NETWORK FOR AN AIRCRAFT
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
