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
3.
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 continu; Transformation d'une puissance d'entrée en courant continu en une puissance de sortie en courant alternatif
A quenching chamber includes, for each zone of contact between a mobile contact and two fixed contacts, respectively, two pairs of guides that extend from the mobile contact and the contact zone in question, respectively, so as to guide, under the action of a magnetic field of constant direction, an electric arc. The pairs of guides follow one after the other in the direction of the magnetic field, and each pair of guides delineates between them a guiding zone. The guiding zones overlap at least partially in the direction of the magnetic field.
The present invention relates to a system for converting and transporting electrical energy in a turbomachine-propelled aircraft, said system including:
at least a first rotary electric machine connected mechanically to the low-pressure shaft by means of a coupling device,
a second rotary electric machine connected mechanically to the high-pressure shaft by means of an accessory gearbox, and
said first electric power module and said second electric power module being connected electrically to an internal electrical network of the turbomachine,
a generator coupled to the accessory gearbox and intended to supply an electrical network of the aircraft with electricity, and
a control device for controlling start-up of the turbomachine by at least one rotary electric machine, for compensating for power consumed by the generator, and for implementing distribution between the power absorbed by the high-pressure shaft and the power absorbed by the low-pressure shaft.
A device for connection to an on-board multiplexed network of communication by multi-mode optical fibers for an aircraft, the device comprising a first optical component for modifying the spatial profile of a light beam, comprising a multi-mode optical input terminal configured to be connected to a first multi-mode optical fiber and single-mode optical output terminals, and a second optical component for modifying the spatial profile of a light beam, comprising single-mode optical input terminals and a multi-mode optical output terminal configured to be connected to a second multi-mode optical fiber. It further comprises an optical harness for switching and reassigning a transmission channel including single-mode optical inputs coupled to the single-mode optical output terminals of the first component, single-mode optical outputs coupled to the single-mode optical input terminals of the second optical component, and single-mode waveguides.
G02B 6/28 - Moyens de couplage optique ayant des bus de données, c. à d. plusieurs guides d'ondes interconnectés et assurant un système bidirectionnel par nature en mélangeant et divisant les signaux
The invention relates to a power contactor (100) comprising: - a fixed part (120); - a movable part (110) able to come into contact with the fixed part and to move between an open position and a closed position of the contactor, the movable part comprising two contact points (111, 112) for contact with the fixed part; - a first spring (141) placed on the movable part and configured to apply a pressing force on the movable part towards the fixed part; - an actuator (150) configured to actuate the movable part and bring it into contact with the fixed part; - an insulating support (101) containing the fixed part, the movable part and the first spring, characterized in that the power contactor also comprises: - a magnetic circuit (103) surrounding at least one portion of the movable part; and - a plate (102) fastened to the movable part and configured to come into contact with the magnetic circuit so as to form a closed magnetic circuit surrounding the movable part when the contactor is in the closed position, the insulating support also containing the plate and the magnetic circuit, and the distance (d1) between the plate and the magnetic circuit being strictly greater than the distance (d2) between the two contact points and the fixed part.
H01H 1/54 - Moyens pour accroître la pression de contact, empêcher la vibration des contacts, maintenir ensemble les contacts après l'entrée en contact, ou pour ramener les contacts à la position d'ouverture par force magnétique
H01H 50/42 - Circuits magnétiques auxiliaires, p.ex. pour le maintien de l'armature en position de repos ou de retour de l'armature à la position de repos, pour l'amortissement ou l'accélération du mouvement
8.
METHOD FOR REGULATING AN ELECTRIC MACHINE IN MOTOR MODE BY PARALLEL HYBRIDISATION OF AN AUXILIARY ELECTRICAL NETWORK
The invention relates to an electrical system for an aircraft, comprising a main network (110) and an auxiliary network (120) connected to the main network (110) and a device for regulating the rotary electric machine (111), the regulating device comprising: - a first regulating member (131) for regulating the voltage of the main network (110) connected to the control unit (113), the first regulating member (131) being configured to regulate the induction current of the rotor of the rotary electric machine (111); - a second member (132) for regulating the current at the terminals of the rotary electric machine (111) connected to the control module (123), the second regulating member (132) being configured to control the current generated by the converter (122), the electrical system being configured to adopt: - a generator configuration in which the rotary electric machine (111) transmits an electric current to the at least one electric component (200); and - a motor configuration in which the value of the current at the output of the converter (122) is greater than the value of the current of the at least one electric component (200), the electrical system switching from the generator configuration to the motor configuration, and vice versa, by controlling the regulating device (123).
H02P 9/14 - Dispositions pour la commande de génératrices électriques de façon à obtenir les caractéristiques désirées à la sortie par variation du champ
Disclosed is a rotary transformer that has a radial air gap and is intended to be installed around a rotatable shaft, the rotary transformer consisting of a plurality of annular stator sectors (22) and of a plurality of annular rotor sectors (24), the juxtaposition of said annular sectors forming a stator ring and a rotor ring which consist of elementary magnetic stator and rotor circuits comprising outer (30) and inner (34) magnetic cores as well as a first electrical winding (32) and a second electrical winding (36) to allow electrical energy to be transferred by electromagnetic induction between the stator and rotor rings, wherein the inner (34) and outer (30) magnetic cores, which each have a standard C-or I-shape, are axially mounted and separated by a radial air gap e_, and the outer magnetic cores and/or the inner magnetic cores have, at each of their two ends, annular flared portions (30A, 30B; 34A, 34B) that are produced by cutting into adjacent sectors a magnetic circular ring formed of an axial stack of circular metal sheets advantageously provided with notches to facilitate their assembly on the outer and inner magnetic cores.
Disclosed is a rotary transformer intended to be installed around a rotatable shaft, the rotary transformer consisting of a plurality of annular stator sectors (22) and of a plurality of annular rotor sectors (24), the juxtaposition of said annular sectors forming a stator ring and a rotor ring which consist of elementary magnetic stator and rotor circuits comprising outer (40) and inner (48) magnetic cores as well as a first electrical winding (50) and a second electrical winding (52) to allow electrical energy to be transferred by electromagnetic induction between the stator and rotor rings, the inner and outer magnetic cores being separated by two air gaps e1 and e2 located on either side of the inner magnetic core, wherein the outer magnetic cores (40) are each in the form of a C-shaped claw and the inner magnetic cores (48) are each in the form of an I-shaped bar, and the outer magnetic cores (40) and/or the inner magnetic cores (48) have, at each of the air gaps, annular flared portions (44) produced by cutting into adjacent sectors a magnetic circular ring (46) formed of a radial stack of circular metal sheets advantageously provided with notches to facilitate their assembly on the outer and inner magnetic cores.
The invention relates to a device (1) for supplying electrical power, comprising: —a power source, —a system to be supplied with power, —a first busbar (2) connected to the system to be supplied with power, —a second busbar (3) connected to the CN power source, —an elastic element (13), —a heat-sensitive element (6) configured to melt at a predefined temperature, and—a holding system (7,8,9) allowing the two busbars (2,3) and the heat-sensitive element (6) to be held in contact, —the two busbars (2,3) making p electrical contact, —the elastic element (13) being configured to move the two busbars (2,3) away from each other and to break the M electrical contact, when the heat-sensitive element (6) melts.
H01H 37/76 - Interrupteurs dans lesquels uniquement le mouvement d'ouverture ou uniquement le mouvement de fermeture d'un contact est effectué par chauffage ou refroidissement Élément de contact actionné par fusion d'une matière fusible, actionné par combustion d'une matière combustible ou par explosion d'une matière explosive
The invention relates to an inductive filtering device comprising a closed magnetic core (12) formed around a central recess (14) and at least one electrical conductor (16) wound around the magnetic core (12) so as to pass through the central recess (14), the electrical conductor (16) extending along a curved main axis (20) suitable for the winding, wherein the electrical conductor (16) has a first portion (16a) arranged in the central recess (14) and a second portion (16b) arranged outside the central recess (14), wherein a section of the first portion (16a) is defined perpendicularly to the main axis in the portion in question and a section of the second portion (16b) is defined perpendicularly to the main axis in the portion in question, and wherein a surface area of the first section is smaller than a surface area of the second section.
The invention relates to a winding configured to ensure the passage of an electric current between two main connection points, the device comprising: - a magnetic core (12); - a main electrical conductor (14) in the form of a first flat strip extending between two ends each provided with one of the main connection points (14c, 14d), and being wound around the magnetic core (12) in order to form an inductor; - an auxiliary electrical conductor (20) in the form of a second strip wound together with the main electrical conductor, and provided with an auxiliary connection point (20c); and - an electrical insulator (22) separating the main electrical conductor from the auxiliary electrical conductor in order to form a capacitor between the two electrical conductors.
The invention relates to an adapted power line and to an energy converter comprising at least one power line. The power line comprises at least one linear electrical conductor (40) and at least one resistive component (42), separate from the conductor and connected in parallel with the conductor over a portion of the linear electrical conductor (40), a value of the resistance of the resistive component being at least equal to ten times a resistance value of the linear electrical conductor (40) over the portion in question.
H02M 1/00 - APPAREILS POUR LA TRANSFORMATION DE COURANT ALTERNATIF EN COURANT ALTERNATIF, DE COURANT ALTERNATIF EN COURANT CONTINU OU VICE VERSA OU DE COURANT CONTINU EN COURANT CONTINU ET EMPLOYÉS AVEC LES RÉSEAUX DE DISTRIBUTION D'ÉNERGIE OU DES SYSTÈMES D'ALI; TRANSFORMATION D'UNE PUISSANCE D'ENTRÉE EN COURANT CONTINU OU COURANT ALTERNATIF EN UNE PUISSANCE DE SORTIE DE CHOC; LEUR COMMANDE OU RÉGULATION - Détails d'appareils pour transformation
H02M 1/44 - Circuits ou dispositions pour corriger les interférences électromagnétiques dans les convertisseurs ou les onduleurs
15.
METHOD FOR AUTOMATICALLY SETTING AN ANGULAR POSITION SENSOR
A method for automatically setting an angular position sensor of a magnet rotor in relation to a stator of a synchronous machine, including an angle error compensator which adjusts the angles measured by the angular position sensor by an angular difference calculated by imposing a direct setpoint current equal to zero and by comparing a setpoint voltage with a quadrature return current, a direct return current resulting from a direct Park transform of current measured at the stator phase outputs and a rotor electrical speed, a predetermined value corresponding to the rotor magnet flux, and a quadrature inductance.
An electrical system includes an electrical power module with a heat sink provided with heat-dissipating projections. The system further includes a cold plate of a heat-transfer fluid box. The cold plate has cavities which are complementary to the projections so as to receive said projections. Liquid metal is inserted between the heat sink and the cold plate, at least between the projections and the cavities.
Electrical cut-off device including a fuse used to open a power line in which a direct current circulates, a movable drawer connected to the fuse and capable, once the fuse is broken, of moving in a fixed chamber under the action of a compression spring mounted between the fixed chamber and the movable drawer, and an auxiliary contact whose fixed contact part is secured to the fixed chamber and movable contact part is secured to the movable drawer whose movement will cause the opening of the normally closed auxiliary contact.
limLoadLoadLoadlimLoadsuppLoadlimLoadsuppsuppsupp from the auxiliary grid into the main grid, - otherwise, not carrying out injection from the auxiliary grid into the main grid.
H02J 3/38 - Dispositions pour l’alimentation en parallèle d’un seul réseau, par plusieurs générateurs, convertisseurs ou transformateurs
H02J 3/48 - Dispositions pour l’alimentation en parallèle d’un seul réseau, par plusieurs générateurs, convertisseurs ou transformateurs contrôlant la répartition de puissance entre les générateurs, convertisseurs ou transformateurs contrôlant la répartition de la composante en phase
H02J 3/50 - Dispositions pour l’alimentation en parallèle d’un seul réseau, par plusieurs générateurs, convertisseurs ou transformateurs contrôlant la répartition de puissance entre les générateurs, convertisseurs ou transformateurs contrôlant la répartition de la composante déphasée
19.
GENERATOR WITH HYBRID EXCITATION FOR A HYBRID ELECTRIC PROPULSION SYSTEM
The invention relates to a hybrid electric propulsion system (200) for a turbojet engine, comprising: - a first permanent magnet synchronous machine (230) connected to an AC-DC converter (231) and intended to be connected to a high-pressure shaft (222) of the turbojet engine; - a hybrid excitation generator (240) comprising a brushless synchronous machine (242), a second permanent magnet synchronous machine (241) connected in series with the brushless synchronous machine, and a bridge rectifier (243) connected to the brushless synchronous machine, the hybrid excitation generator being intended to be connected to a low-pressure shaft (212) of the turbojet engine and the brushless synchronous machine comprising a generator (3421), an exciter (3422), rotating diodes placed between the generator and the exciter, and a DC-DC converter (244) connected to the exciter; - an energy storage system (250); and - a DC power supply network connected to the AC-DC converter and to the bridge rectifier.
H02P 9/10 - Commande s'exerçant sur le circuit d'excitation de la génératrice afin de réduire les effets nuisibles de surcharges ou de phénomènes transitoires, p.ex. application, suppression ou changement brutal de la charge
B64D 27/02 - Aéronefs caractérisés par le type ou la position des groupes moteurs
B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur, l'électricité ou l'énergie de ressorts
A method and a system for determining control parameters of a rotating electric machine, including: a two-phase imaginary reference frame module configured to construct two imaginary two-phase signals (xα, xβ) based on a measurement of the mechanical position θmeca of the axis of a rotor of the rotating machine received from a position sensor, an open-loop module configured to determine in open loop an estimate of the electrical speed, so-called the open-loop estimated electrical speed ωestflt, using the imaginary two-phase signals, a phase-locked loop module configured to generate the actual electrical position θ of the rotating machine from the two imaginary two-phase signals (xα, xβ) and using the open-loop estimated electrical speed ωestflt received from the open-loop module.
Two electric poles are controlled in one and the same circuit breaker by an undivided opening mechanism controlled by a pyrotechnic actuator. The opening of the circuit that is brought about by this actuator, which is fast for a large opening travel of the mobile contacts, makes it possible to extinguish electric arcs under good conditions. The poles may be placed in series on one and the same electrical circuit in order to reduce the potential difference across the terminals of each of them, thereby further increasing the effectiveness of the circuit breaker in terms of arc extinguishing.
The invention relates to an electrical energy storage battery (1) comprising at least one stack (7) of electrical cells (6), a housing comprising a base (3) to which the stack (7) of the battery (1) is attached and a shell covering the base (3). The battery (1) comprises at least two compression plates (8) arranged on either side of the stack (7), means (10) for attaching the plates (8) to the base (3) and at least one tie rod (12) capable of compressing the compression plates against the cells of the stack (7). The base (3) comprises means (13) for the thermal management of the electrical cells (6).
H01M 10/60 - Chauffage ou refroidissement; Commande de la température
H01M 50/204 - Bâtis, modules ou blocs de multiples batteries ou de multiples cellules
H01M 50/264 - Montures; Boîtiers secondaires ou cadres; Bâtis, modules ou blocs; Dispositifs de suspension; Amortisseurs; Dispositifs de transport ou de manutention; Supports avec des moyens de fixation, p.ex. des serrures pour des cellules ou des batteries, p.ex. cadres périphériques, courroies ou tiges
H01M 50/293 - Montures; Boîtiers secondaires ou cadres; Bâtis, modules ou blocs; Dispositifs de suspension; Amortisseurs; Dispositifs de transport ou de manutention; Supports caractérisés par des éléments d’espacement ou des moyens de positionnement dans les racks, les cadres ou les blocs caractérisés par le matériau
23.
MODULE FOR DETECTING A BATTERY LEVEL OF CHARGE, ASSEMBLY COMPRISING THE MODULE, AND AIRCRAFT COMPRISING THE ASSEMBLY
The invention relates to a module (1) for detecting a battery level of charge, comprising: an ammeter (10) comprising a magnetometer (15) and a current-measuring device (18), a voltmeter (20) comprising a first contact terminal (22), a second contact terminal (24) and a voltage-measuring device (28), a temperature sensor (30), a housing (50) intended to be attached to a first interconnection bar (82) and a second interconnection bar (84), the housing (50) having a receptacle (58) in which the magnetometer (15) is received, the receptacle (52) being intended to be received in a measuring hole (83) of the first interconnection bar (82), a first attachment member (52) for attaching the housing (50) to the first interconnection bar (82) and a second attachment member (54) for attaching the housing (50) to the second interconnection bar (84).
G01R 31/364 - Connexions pour bornes de batteries, munies de dispositions de mesure intégrées
H01M 10/48 - Accumulateurs combinés à des dispositions pour mesurer, tester ou indiquer l'état des éléments, p.ex. le niveau ou la densité de l'électrolyte
H01M 10/42 - Procédés ou dispositions pour assurer le fonctionnement ou l'entretien des éléments secondaires ou des demi-éléments secondaires
24.
LC INTERFACING FILTER INCORPORATING A DAMPING CIRCUIT
The invention relates to an LC interfacing filter comprising a parallel capacitor and a series inductor having eddy-current magnetic losses, the inductor (10) being configured so that the eddy-current magnetic losses are predominant with respect to the hysteresis losses, the inductor consisting of a tube (12) made of magnetic material and around which an electrical conductor (14) is wound, with an insulating sheet (16) separating the tube of magnetic material from the electrical conductor.
H01F 27/34 - Moyens particuliers pour éviter ou réduire les effets électriques ou magnétiques indésirables, p.ex. pertes à vide, courants réactifs, harmoniques, oscillations, champs de fuite
H01F 17/04 - Inductances fixes du type pour signaux avec noyau magnétique
H01F 27/32 - Isolation des bobines, des enroulements, ou de leurs éléments
H01F 17/06 - Inductances fixes du type pour signaux avec noyau magnétique avec noyau refermé sur lui-même, p.ex. tore
H01F 27/22 - Refroidissement par conduction de chaleur à travers des éléments de remplissage solides ou en poudre
A contactor includes a bridge which is movable between a closed state and an open state, including movable contacts; two fixed contacts facing the movable contacts, wherein in the closed state the movable contacts are in contact with the fixed contacts and in the open state the movable contacts are spaced apart from the fixed contacts; two magnets generating a magnetic field and generating a magnetic force in order to move an arc appearing between the fixed contacts and the movable contacts passing from a closed state to an open state; two fin blocks; and two pairs of arc guides, each being directed from the movable contacts to each of the two fin blocks, wherein at least fin slots forming a groove of the fin blocks face each guide of a pair of arc guides.
A method including calculating a total electrical charge accumulated in a battery at the current time by Coulomb counting on the basis of a total electrical charge accumulated in the battery at a previous time and on the basis of a current supplied by the battery, calculating a stored charge state, equal to the total accumulated electrical charge divided by a maximum total charge, calculating an available electrical charge on the basis of a difference between the total electrical charge and a non-extractible electrical charge which cannot be extracted from the battery because of its temperature, calculating an available charge state, equal to the available electrical charge divided by a maximum available charge.
G01R 31/367 - Logiciels à cet effet, p.ex. pour le test des batteries en utilisant une modélisation ou des tables de correspondance
G01R 31/36 - Dispositions pour le test, la mesure ou la surveillance de l’état électrique d’accumulateurs ou de batteries, p.ex. de la capacité ou de l’état de charge
G01R 31/3832 - Dispositions pour la surveillance de variables des batteries ou des accumulateurs, p.ex. état de charge utilisant l’intégration du courant sans mesurer la tension de la batterie
27.
ELECTRICAL GENERATION ARCHITECTURE FOR HYBRIDISED TURBOMACHINE
Electrical architecture for an aircraft with thermal/electrical hybrid propulsion, comprising, for each turbine engine:
an aeroplane AC electrical network,
at least one first electrical machine mechanically coupled to a high-pressure shaft of the turbine engine;
at least one second electrical machine mechanically coupled to a low-pressure shaft of the turbine engine;
a reversible AC/AC electrical energy conversion module;
switch elements; and
an electronic system for controlling the conversion module and the switch elements, configured to put the architecture;
in at least one so-called “power distribution hybridisation” operating mode corresponding to a first configuration of the switch elements in which the at least one second machine is coupled to the aeroplane network and at least one first machine is coupled to the aeroplane network via the electrical energy conversion module.
B60L 50/10 - Propulsion électrique par source d'énergie intérieure au véhicule utilisant la puissance de propulsion fournie par des générateurs entraînés par le moteur, p.ex. des générateurs entraînés par des moteurs à combustion
B64D 27/02 - Aéronefs caractérisés par le type ou la position des groupes moteurs
B64D 27/10 - Aéronefs caractérisés par le type ou la position des groupes moteurs du type à turbine à gaz
B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur, l'électricité ou l'énergie de ressorts
H02J 3/46 - Dispositions pour l’alimentation en parallèle d’un seul réseau, par plusieurs générateurs, convertisseurs ou transformateurs contrôlant la répartition de puissance entre les générateurs, convertisseurs ou transformateurs
An electrical converter includes an inverter configured to provide at least one input AC voltage from an input DC voltage (VE). The electrical converter further includes an AC-to-AC voltage converter configured to provide an output AC voltage from the at least one input AC voltage such that the output AC voltage has an amplitude that depends on a frequency of the at least one input AC voltage. A rectifier is configured to provide an output DC voltage from the output AC voltage.
H02M 5/293 - Transformation d'une puissance d'entrée en courant alternatif en une puissance de sortie en courant alternatif, p.ex. pour changement de la tension, pour changement de la fréquence, pour changement du nombre de phases sans transformation intermédiaire en courant continu par convertisseurs statiques utilisant des tubes à décharge avec électrode de commande ou des dispositifs à semi-conducteurs avec électrode de commande utilisant des dispositifs du type triode ou transistor exigeant l'application continue d'un signal de commande utilisant uniquement des dispositifs à semi-conducteurs
H02M 7/06 - Transformation d'une puissance d'entrée en courant alternatif en une puissance de sortie en courant continu sans possibilité de réversibilité par convertisseurs statiques utilisant des tubes à décharge sans électrode de commande ou des dispositifs à semi-conducteurs sans éléctrode de commande
H02M 7/539 - Transformation d'une puissance d'entrée en courant continu en une puissance de sortie en courant alternatif sans possibilité de réversibilité par convertisseurs statiques utilisant des tubes à décharge avec électrode de commande ou des dispositifs à semi-conducteurs avec électrode de commande utilisant des dispositifs du type triode ou transistor exigeant l'application continue d'un signal de commande utilisant uniquement des dispositifs à semi-conducteurs, p.ex. onduleurs à impulsions à un seul commutateur avec commande automatique de la forme d'onde ou de la fréquence de sortie
09 - Appareils et instruments scientifiques et électriques
37 - Services de construction; extraction minière; installation et réparation
42 - Services scientifiques, technologiques et industriels, recherche et conception
Produits et services
Apparatus and instruments for conducting, switching,
transforming, accumulating, regulating or controlling
electric current; electric harnesses; electric cables;
fiber-optic cables; optical fibers; connection equipment for
electric and optical cables; electric converters; protective
sheaths for electric cables and electric harnesses;
electrical equipment management systems (apparatus,
instruments and software); computer hardware and software in
the field of electricity distribution; software applied to
the protection, control, management, monitoring and
supervision of electrical installations and equipment. Repair, overhaul, reconditioning, adaptation, modification,
servicing and maintenance of electric and electronic
apparatus, instruments, systems, material and equipment for
use in the aeronautical and defense fields; repair,
overhaul, reconditioning, adaptation, modification,
servicing and maintenance of electrical installations and
electrical wiring for use in the aeronautical and defense
fields. Engineering and design office services (engineers'
services); research and development of new products;
professional consultancy and advisory service relating to
engineering; all these services relating to electrical
installations, equipment, apparatus, instruments and wiring
used in the aeronautical and defense fields.
The present invention relates to a power module (10) comprising: - a substrate (11), - electronic components (13) transferred onto the substrate (11), - a stiffening frame (25) assembled, in particular soldered, onto the substrate (11) and extending at least partially around the electronic components (13) so as to delimit an encapsulation space (26), and - an encapsulation material (20) arranged inside the encapsulation space (26), for coating the electronic components (13).
H01L 23/04 - Conteneurs; Scellements caractérisés par la forme
H01L 23/24 - Matériaux de remplissage caractérisés par le matériau ou par ses propriétes physiques ou chimiques, ou par sa disposition à l'intérieur du dispositif complet solide ou à l'état de gel, à la température normale de fonctionnement du dispositif
31.
ACCUMULATOR BATTERY WITH ACTIVE THERMAL MANAGEMENT
Battery comprising an accumulator in contact via one of its ends with a heat pipe via the stack of a strip, of a thermal pad and of a thermal-interface plate, the strip allowing electrical connection of the accumulator, the thermal pad being positioned between the strip and the thermal-interface plate so as to improve the area of contact and thermal conduction, the thermal-interface plate being thermally connected to the heat pipe, the heat pipe comprising a heat-transport fluid which transports heat energy and being connected to a heat exchanger allowing the heat-transport fluid to be heated or cooled.
The invention relates to an electrical circuit (200) comprising at least one electrical converter stage and at least one capacitor (106) arranged upstream of said at least one electrical converter stage, the electrical circuit furthermore comprising a high-voltage source (102) and a contactor (104) arranged in series between the high-voltage source and the electrical converter, the electrical circuit comprising a pre-charging circuit (208) for pre-charging said capacitor, the pre-charging circuit being arranged in parallel with said contactor, wherein the pre-charging circuit comprises the following, in series in order from the high-voltage source to the capacitor: a fuse (214), a low-voltage relay (216) housed in a metal housing (217), a transistor (218) and a pre-charging resistor (212), the housing of the low-voltage relay being connected to a terminal of the high-voltage source (102).
An electrical architecture for an aircraft includes a first propulsion power distribution system distributing a high DC voltage, a second propulsion power distribution system distributing a high DC voltage, a first AC power distribution system distributing a three-phase AC voltage, a second AC power distribution system distributing a three-phase AC voltage, a first inverter connected between the first propulsion power distribution system and the first AC power distribution system, a second inverter connected between the second propulsion power distribution system and the second AC power distribution system, and an electronics module connected to the first inverter and to the second inverter in order to control the frequency of the three-phase AC voltage generated by the first inverter and the frequency of the three-phase AC voltage generated by the second inverter.
H02J 3/38 - Dispositions pour l’alimentation en parallèle d’un seul réseau, par plusieurs générateurs, convertisseurs ou transformateurs
H02J 3/42 - Synchronisation d'un générateur pour sa connexion à un réseau ou à un autre générateur avec connexion automatique en parallèle quand le synchronisme est obtenu
H02M 7/797 - Transformation d'une puissance d'entrée en courant alternatif en une puissance de sortie en courant continu; Transformation d'une puissance d'entrée en courant continu en une puissance de sortie en courant alternatif avec possibilité de réversibilité par convertisseurs statiques utilisant des tubes à décharge avec électrode de commande ou des dispositifs à semi-conducteurs avec électrode de commande utilisant des dispositifs du type triode ou transistor exigeant l'application continue d'un signal de commande utilisant uniquement des dispositifs à semi-conducteurs
34.
BATTERY PROVIDED WITH A COOLING DEVICE COMPRISING AT LEAST ONE HEAT PIPE
The invention relates to an electric battery (10) comprising a plurality of electrochemical cells (11) arranged inside a containment structure (12). The battery (10) is provided with a cooling device comprising at least one heat pipe (1) configured to contain a heat-transfer fluid that is intended to undergo an evaporation and condensation cycle, wherein calories are drawn from an evaporation end (4) of the heat pipe (1) arranged in contact with the cells (11) and delivered to a condensation end (5) of the heat pipe (1) to a cold source (F) located outside the confinement structure (12), the at least one heat pipe (1) being overmoulded onto a base (13) of the confinement structure (12).
The invention relates to a method for evaluating the lifespan of an electrical connection between connectors each comprising at least one electrical contact housed in a housing, the housings being configured to be mechanically coupled to each other, comprising the following steps: - measuring the variation in the electrical contact resistance between the electrical contacts alone, as a function of a number of movements of the electrical contacts against each other and for a number of values of movement amplitude; - determining, from the preceding measurements, a function defining a maximum number of movements beyond which the electrical contact resistance exceeds a predefined maximum value representative of a degraded state of the connection, as a function of movement amplitude; - measuring movement amplitudes of each of the cavities of the housings in which the electrical contacts are intended to be placed, by subjecting the housings to mechanical stresses of amplitude and frequency of different values; - determining, from the measurements of amplitude, dynamic transfer functions of the housings defining the movement amplitude of the electrical contacts as a function of the amplitude and frequency of the mechanical stresses applied to the housings; - determining, for given amplitude and frequency values of the mechanical stresses applied to the connectors and using the functions determined beforehand, the lifespan of the connection between the connectors.
The invention relates to a method for monitoring and protecting an electrical hybridisation system against the risk of fire, the electrical hybridisation system comprising two rotary machines, each having at least one stator winding, each stator winding being associated with an AC-to-DC converter and a distribution box for delivering, on the basis of the DC voltages delivered by the AC-to-DC converters, a high DC voltage, on the one hand, for local loads and, on the other hand, for the electrical network of an aircraft, in which method current and voltage measurements are carried out in the distribution box, the converters and the stator windings of the rotary machines and if, once these measurements are consolidated together in a control card, the risk of fire is determined, the contactors of the distribution box and/or of the converters are selectively opened and the rotary machines are mechanically disconnected.
H02H 7/06 - Circuits de protection de sécurité spécialement adaptés pour des machines ou appareils électriques de types particuliers ou pour la protection sectionnelle de systèmes de câble ou ligne, et effectuant une commutation automatique dans le cas d'un chan pour compensateurs synchrones
H02H 7/085 - Circuits de protection de sécurité spécialement adaptés pour des machines ou appareils électriques de types particuliers ou pour la protection sectionnelle de systèmes de câble ou ligne, et effectuant une commutation automatique dans le cas d'un chan pour moteurs dynamo-électriques contre une charge excessive
H02P 29/02 - Protection contre les surcharges sans interruption automatique de l’alimentation
H02P 5/74 - Dispositions spécialement adaptées à la régulation ou la commande de la vitesse ou du couple d’au moins deux moteurs électriques pour commander au moins deux moteurs dynamo-électriques à courant alternatif
H02P 29/64 - Commande ou détermination de la température de l’enroulement
37.
AIRCRAFT TURBOMACHINE PROPELLER COMPRISING A SYSTEM FOR AUTONOMOUS SUPPLY OF HEATING MEMBERS FOR DE-ICING AND ASSOCIATED METHOD
The invention relates to an aircraft turbomachine propeller comprising a cone extending axially along an axis (X) and blades, the propeller being configured to be rotated by a shaft of the turbomachine (A), the propeller comprising a plurality of heating members (2) and a power supply system (3) for supplying power to the heating members (2), the power supply system (3) being mounted in the cone and configured to autonomously generate electrical power from the rotation of the shaft of the turbomachine (A).
B64D 15/12 - Dégivrage ou antigivre des surfaces externes des aéronefs par chauffage électrique
B64D 41/00 - Installations génératrices de puissance pour servitudes auxiliaires
F01D 25/02 - Dispositifs de dégivrage pour machines motrices dans lesquelles se produisent des phénomènes de givrage
H02K 7/18 - Association structurelle de génératrices électriques à des moteurs mécaniques d'entraînement, p.ex. à des turbines
F02C 7/00 - Caractéristiques, parties constitutives, détails ou accessoires non couverts dans, ou d'un intérêt plus général que, les groupes ; Entrées d'air pour ensembles fonctionnels de propulsion par réaction
38.
ELECTRICAL DISTRIBUTION SYSTEM FOR AN AIRCRAFT AND ASSOCIATED METHOD
The invention relates to an electrical distribution system (1) for an aircraft, comprising at least a first electrical distribution module (HV1) configured to supply at least two electrical loads (M1-1, M1-2) with power from at least a first electrical source (B1), a second electrical distribution module (HV2) configured to supply at least two electrical loads (M2-1, M2-2) with power from at least a second electrical source (B2), each electrical distribution module (HV1, HV2) comprising a first path (HV1-, HV2-) and a second path (HV1+, HV2+), each second path (HV1+, HV2+) of an electrical distribution module (HV1, HV2) being connected to the same equaliser busbar (2) by a second transfer line (LT1+, LT2+, LTi+) comprising a transfer contactor (GT1, GT2, GTi).
H02J 1/08 - Systèmes à trois fils; Systèmes ayant plus de trois fils
B60L 3/00 - Dispositifs électriques de sécurité sur véhicules propulsés électriquement; Contrôle des paramètres de fonctionnement, p.ex. de la vitesse, de la décélération ou de la consommation d’énergie
H02J 9/06 - Circuits pour alimentation de puissance de secours ou de réserve, p.ex. pour éclairage de secours dans lesquels le système de distribution est déconnecté de la source normale et connecté à une source de réserve avec commutation automatique
39.
POWER SHARING IN AN AIRCRAFT USING DISTRIBUTED CONTROL
The invention relates to a system (100) for exchanging power in an aircraft, the system comprising: - a voltage bus (160); - a low-pressure electromechanical converter (150 BP); - a high-pressure electromechanical converter (150 HP); and - for each electromechanical converter (150 BP, 150 HP), a voltage control module (125 BP, 125 HP). The system (100) further comprises: - a computer (106) designed to provide a sharing setpoint (S) between the exchanged powers (PHP, PBP), this sharing setpoint (S) varying over time; and - for at least one of the electromechanical converters (150 BP, 150 HP): a module (120 BP, 120 HP) for ensuring that the sharing setpoint (S) is observed, which module is designed to adjust the power (PHP, PBP) that is exchanged by the relevant electromechanical converter (150 BP, 150 HP) in order to observe the received sharing setpoint (S), taking into account a received evaluation (PBP°, PHP°) of the power (PBP, PHP) exchanged by the other of the electromechanical converters (150 BP, 150 HP).
B64D 31/00 - Commande des groupes moteurs; Leur disposition
B64D 41/00 - Installations génératrices de puissance pour servitudes auxiliaires
F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
F02C 7/36 - Transmission de puissance entre les différents arbres de l'ensemble fonctionnel de turbine à gaz, ou entre ce dernier et l'utilisateur de puissance
F02C 9/00 - Commande des ensembles fonctionnels de turbines à gaz; Commande de l'alimentation en combustible dans les ensembles fonctionnels de propulsion par réaction alimentés en air ambiant
H02J 1/10 - Fonctionnement de sources à courant continu en parallèle
H02J 1/12 - Fonctionnement de générateurs à courant continu en parallèle avec des convertisseurs, p.ex. avec un redresseur à arc de mercure
H02J 3/46 - Dispositions pour l’alimentation en parallèle d’un seul réseau, par plusieurs générateurs, convertisseurs ou transformateurs contrôlant la répartition de puissance entre les générateurs, convertisseurs ou transformateurs
H02J 4/00 - Circuits pour réseaux principaux ou de distribution, la nature alternative ou continue du courant n'étant pas précisée
H02J 13/00 - Circuits pour pourvoir à l'indication à distance des conditions d'un réseau, p.ex. un enregistrement instantané des conditions d'ouverture ou de fermeture de chaque sectionneur du réseau; Circuits 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
40.
POWER SHARING IN AN AIRCRAFT USING CENTRALISED CONTROL
The invention relates to a system (100) for exchanging power in an aircraft, the system comprising: - a voltage bus (160); - a low-pressure electromechanical converter (150BP); - a high-pressure electromechanical converter (150HP); and - for each electromechanical converter (150BP, 150HP): a voltage control module (130BP, 130HP) and a control module (140BP, 140HP) for ensuring that the exchange setpoint (GBP*, GHP*) is observed. The system (100) further comprises a power adjustment module (106) configured, for at least one of the electromechanical converters (150BP, 150HP): to determine a voltage correction (δVBP, δVHP); and to apply, in the voltage control module (130BP, 130HP) associated with the relevant electromechanical converter (150BP, 150HP), the voltage correction (δVBP, δVHP) to a voltage setpoint (VDC*) so that the voltage control module (130BP, 130HP) adjusts the bus voltage (VDC) to the corrected voltage setpoint (VDC*).
B64D 41/00 - Installations génératrices de puissance pour servitudes auxiliaires
F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
F02C 7/36 - Transmission de puissance entre les différents arbres de l'ensemble fonctionnel de turbine à gaz, ou entre ce dernier et l'utilisateur de puissance
F02C 9/00 - Commande des ensembles fonctionnels de turbines à gaz; Commande de l'alimentation en combustible dans les ensembles fonctionnels de propulsion par réaction alimentés en air ambiant
H02J 1/10 - Fonctionnement de sources à courant continu en parallèle
H02J 1/12 - Fonctionnement de générateurs à courant continu en parallèle avec des convertisseurs, p.ex. avec un redresseur à arc de mercure
H02J 3/46 - Dispositions pour l’alimentation en parallèle d’un seul réseau, par plusieurs générateurs, convertisseurs ou transformateurs contrôlant la répartition de puissance entre les générateurs, convertisseurs ou transformateurs
H02J 4/00 - Circuits pour réseaux principaux ou de distribution, la nature alternative ou continue du courant n'étant pas précisée
H02J 13/00 - Circuits pour pourvoir à l'indication à distance des conditions d'un réseau, p.ex. un enregistrement instantané des conditions d'ouverture ou de fermeture de chaque sectionneur du réseau; Circuits pour pourvoir à la commande à distance des moyens de commutation dans un réseau de distribution d'énergie, p.ex. mise en ou hors circuit de consommateurs de courant par l'utilisation de signaux d'impulsion codés transmis par le réseau
B64D 31/00 - Commande des groupes moteurs; Leur disposition
09 - Appareils et instruments scientifiques et électriques
37 - Services de construction; extraction minière; installation et réparation
42 - Services scientifiques, technologiques et industriels, recherche et conception
Produits et services
(1) Appareils et instruments pour la conduite, la distribution, la transformation, l'accumulation, le réglage ou la commande du courant électrique; harnais électriques; câbles électriques; câbles à fibres optiques; fibres optiques; matériels de raccordement pour câbles électriques et optiques; convertisseurs électriques; gaines de protection pour câbles électriques et harnais électriques; systèmes (appareils, instruments et logiciels) de gestion des équipements électriques; matériel informatique et logiciels dans le domaine de la distribution d'électricité; logiciels appliqués à la protection, au contrôle, à la gestion, à la surveillance et à la supervision d'installations et équipements électriques. (1) Réparation, révision, remise en état, adaptation, modification, entretien et maintenance d'appareils, d'instruments, de systèmes, de matériel et d'équipements électriques et électroniques utilisés dans les domaines aéronautique et de la défense; réparation, révision, remise en état, adaptation, modification, entretien et maintenance des installations électriques et des câblages électriques utilisés dans les domaines aéronautique et de la défense.
(2) Service d'ingénierie et de bureau d'études (travaux d'ingénieurs); recherche et développement de nouveaux produits; service de conseils et consultations professionnels relatifs à l'ingénierie; tous ces services étant relatifs aux installations, équipements, appareils, instruments et câblages électriques utilisés dans les domaines aéronautique et de la défense.
09 - Appareils et instruments scientifiques et électriques
37 - Services de construction; extraction minière; installation et réparation
42 - Services scientifiques, technologiques et industriels, recherche et conception
Produits et services
Apparatus and instruments for conducting, switching, transforming, accumulating, regulating or controlling electric current; electric harnesses; electric cables; fiber-optic cables; optical fibers; connection equipment for electric and optical cables; electric converters; protective sheaths for electric cables and electric harnesses; electrical equipment management systems (apparatus, instruments and software); computer hardware and software in the field of electricity distribution; software applied to the protection, control, management, monitoring and supervision of electrical installations and equipment. Repair, overhaul, reconditioning, adaptation, modification, servicing and maintenance of electric and electronic apparatus, instruments, systems, material and equipment for use in the aeronautical and defense fields; repair, overhaul, reconditioning, adaptation, modification, servicing and maintenance of electrical installations and electrical wiring for use in the aeronautical and defense fields. Engineering and design office services (engineers' services); research and development of new products; professional consultancy and advisory service relating to engineering; all these services relating to electrical installations, equipment, apparatus, instruments and wiring used in the aeronautical and defense fields.
Aircraft electric propulsion system including: a motor including a hollow rotor, and a power and control electronics device, in which the power and control electronics device includes at least two ring-shaped electrical tracks each including at least two inverters, the inverters being connected to each other in parallel, wherein the electrical tracks delimit a hollow circular part of the power and control electronics device, the hollow circular part being placed in the axis of the hollow rotor of the motor.
H02K 11/33 - Circuits d’entraînement, p.ex. circuits électroniques de puissance
B64C 29/00 - Aéronefs capables d'atterrir ou de décoller à la verticale, p.ex. aéronefs à décollage et atterrissage verticaux [ADAV, en anglais VTOL]
B64D 27/30 - Aéronefs caractérisés par des groupes moteurs électriques
H02K 9/19 - Dispositions de refroidissement ou de ventilation pour machines avec enveloppe fermée et circuit fermé de refroidissement utilisant un agent de refroidissement liquide, p.ex. de l'huile
H02K 21/16 - Moteurs synchrones à aimants permanents; Génératrices synchrones à aimants permanents avec des induits fixes et des aimants tournants avec des aimants tournant à l'intérieur des induits avec des noyaux d'induits annulaires à pôles saillants
The invention relates to a power electronic module (23) comprising a housing (29), a substrate (31), at least one electronic component (33) transferred onto the substrate (31), a gel (35) encapsulating the electronic component (33) on the substrate (31) and in the housing (29), the power electronic module comprising a tapped nut (37) held in a wall (39) of the housing (29), a threaded rod (41) extending through the nut (37) inside and outside the housing (29), and a base (43) transferred onto the substrate (31) and aligned with the longitudinal axis of the rod (41).
H01L 23/373 - Refroidissement facilité par l'emploi de matériaux particuliers pour le dispositif
H01L 23/053 - Conteneurs; Scellements caractérisés par la forme le conteneur étant une structure creuse ayant une base isolante qui sert de support pour le corps semi-conducteur
H01L 23/24 - Matériaux de remplissage caractérisés par le matériau ou par ses propriétes physiques ou chimiques, ou par sa disposition à l'intérieur du dispositif complet solide ou à l'état de gel, à la température normale de fonctionnement du dispositif
H01L 25/07 - Ensembles consistant en une pluralité de dispositifs à semi-conducteurs ou d'autres dispositifs à l'état solide les dispositifs étant tous d'un type prévu dans le même sous-groupe des groupes , ou dans une seule sous-classe de , , p.ex. ensembles de diodes redresseuses les dispositifs n'ayant pas de conteneurs séparés les dispositifs étant d'un type prévu dans le groupe
45.
MODULAR INTERCONNECTIONS FOR A MOTOR AND A POWER ELECTRONIC UNIT
An assembly made up of power electronics unit including three-phase outputs and a three-phase motor including three-phase inputs, wherein the assembly includes N three-phase outputs and N three-phase inputs with N>1, the three-phase inputs of the three-phase motor are opposite the three-phase outputs of the power electronic unit, the three-phase outputs and the three-phase inputs are located at the outer periphery of the power electronic unit and at the outer periphery of the three-phase motor, respectively, and the shape and the perimeter of the outer periphery of the three-phase motor are identical to those of the outer periphery of the power electronic unit.
H02K 11/33 - Circuits d’entraînement, p.ex. circuits électroniques de puissance
H02K 3/28 - Schémas d'enroulements ou de connexions entre enroulements
H02K 11/00 - Association structurelle de machines dynamo-électriques à des organes électriques ou à des dispositifs de blindage, de surveillance ou de protection
46.
ELECTRICAL CONTACTOR WITH AN INTEGRATED BREAKING DEVICE
The invention relates to an electrical contactor (10, 10') with an integrated breaking device comprising at least one arc-breaking device (20) having a first guide (21), a second guide (22), which is connected to the contact (12), and a finned breaking module (23), which comprises a series of conductive fins (24) extending between the first guide (21) and the second guide (22). The arc-breaking device (20) comprises a controlled switch (26) connected between two conductive fins (24) of the finned breaking module (23) and controlled by an electronic control unit (27).
Embodiments of the disclosure relate to a power electronics apparatus. The power electronics apparatus includes at least a first electrically conductive element and a second electrically conductive element. The elements are intended to be at a first electrical potential and at a second electrical potential, respectively. At least a first and second power electronics components are mounted on the first and second elements, respectively, a first portion and a second portion of a sink are mounted on the first conductive element and on the second conductive element, respectively, so as to permit the transfer of heat from each power component to the corresponding portion of the sink through the corresponding conductive element. An electrical insulator is present between each portion of the sink so as to prevent the risk of flashover between the two portions.
H01L 23/367 - Refroidissement facilité par la forme du dispositif
H01L 23/00 - DISPOSITIFS À SEMI-CONDUCTEURS NON COUVERTS PAR LA CLASSE - Détails de dispositifs à semi-conducteurs ou d'autres dispositifs à l'état solide
H01L 23/14 - Supports, p.ex. substrats isolants non amovibles caractérisés par le matériau ou par ses propriétés électriques
H01L 23/373 - Refroidissement facilité par l'emploi de matériaux particuliers pour le dispositif
H01L 25/07 - Ensembles consistant en une pluralité de dispositifs à semi-conducteurs ou d'autres dispositifs à l'état solide les dispositifs étant tous d'un type prévu dans le même sous-groupe des groupes , ou dans une seule sous-classe de , , p.ex. ensembles de diodes redresseuses les dispositifs n'ayant pas de conteneurs séparés les dispositifs étant d'un type prévu dans le groupe
H05K 7/20 - Modifications en vue de faciliter la réfrigération, l'aération ou le chauffage
48.
POWER MODULE, AIRCRAFT COMPRISING SUCH A POWER MODULE, AND METHOD FOR MANUFACTURING THE POWER MODULE
The power module (100) comprises: - a substrate with an electrically insulating board (204) and electrically conductive tracks; - an electrical component (106) secured against at least one of the electrically conductive tracks; - a resistor (114) secured against at least one of the electrically conductive tracks; - a capacitor (116) connected in series with the resistor (114); and - an encapsulation (302). It furthermore comprises: - two pins (218, 220) having bases secured to two of the conductive tracks, these bases being covered by the encapsulation (302), and free ends projecting outside the encapsulation (302); and the capacitor (116) is placed outside the encapsulation (302) and connected to the free ends of the pins (218, 220).
H01L 23/498 - Connexions électriques sur des substrats isolants
H01L 23/367 - Refroidissement facilité par la forme du dispositif
H01L 23/538 - Dispositions pour conduire le courant électrique à l'intérieur du dispositif pendant son fonctionnement, d'un composant à un autre la structure d'interconnexion entre une pluralité de puces semi-conductrices se trouvant au-dessus ou à l'intérieur de substrats isolants
The invention relates to a normally closed contactor (21) which comprises a fixed contact (22) and a movable contact (23) facing each other in a housing (25), the movable contact (23) being movable between a closed position and an open position. A contact pressure spring (26) pushes the movable contact towards the fixed contact. An actuator (27) comprises a movable portion (29) rigidly connected to the movable contact (23) which moves it from the closed position to the open position. A return spring (33) pushes the movable portion (29) into its closed position. The mechanical anti-rebound device (34) comprises a first locking part (35) rigidly connected to the housing and a second locking part (36) opposite the first and rigidly connected to the movable portion (29), these locking parts (35, 36) being engaged in mutual locking when the movable contact (23) is in its closed position.
The invention relates to a system comprising one of the battery modules (2) coupled to at least one control device and formed of battery cells arranged in parallel coherent chains of battery cells, the battery modules (2) being distributed in two independent networks including a high-voltage network (3) and a low-voltage network (4) coupled in series, the low-voltage network (4) including a battery module (2) including a first sub-network (4A) and a second sub-network (4B) electrically separated from the first sub-network (4A) by a physical separation element (8) arranged on the battery module (2) of the low-voltage network (4), characterised in that each battery module (2) of the high-voltage network (3) includes a number of parallel coherent chains of battery cells equal to the number of parallel coherent chains of battery cells of each battery module (2) of the first sub-network (4A).
H01M 50/249 - Montures; Boîtiers secondaires ou cadres; Bâtis, modules ou blocs; Dispositifs de suspension; Amortisseurs; Dispositifs de transport ou de manutention; Supports spécialement adaptés aux aéronefs ou aux véhicules, p.ex. aux automobiles ou aux trains
The invention relates to a high-voltage interrupter chamber (10) having a vertical main axis A and comprising two fixed contacts (18), offset with respect to each other in a transverse direction perpendicular to the main axis A, and a movable contact (20), wherein the movable contact (20) is mounted so as to be translatably movable with respect to the fixed contacts (18) between a closed position and an open position, the interrupter chamber (10) further comprising permanent magnets (28, 30) that are distributed on either side of the fixed contacts (18) and the movable contact (20), characterised in that it comprises a screen (34) made of an electrically insulating material, which is arranged between the fixed contacts (18).
The electrical installation (100) for an aircraft comprises: - a power source (102); - an electrical load (104); - first and second power supply lines (114, 116) connecting the electrical load (104) to the power source (102) in order to supply electric power to the electrical load (104); and - a double-break power contactor (118) located on the first power supply line (114), the power contactor (118) comprising two fixed contacts (118F) and one movable contact (118M). It furthermore comprises: - a branch (130) in parallel with the first power supply line (114), connected between the movable contact (118M) and a point (B) of the first power supply line (114); and - a device for opening one of the power supply lines (114, 116) on the basis of a current flowing in the branch (130).
H01H 9/38 - Contacts auxiliaires sur lesquels l'arc est transféré des contacts principaux
B60L 3/04 - Coupure de l'alimentation en énergie en cas de fausse manœuvre
H01H 9/54 - Circuits non adaptés à une application particulière du dispositif de commutation non prévus ailleurs
H01H 33/59 - Circuits non adaptés à une application particulière de l'interrupteur et non prévus ailleurs, p.ex. pour assurer le fonctionnement de l'interrupteur en un point déterminé de la période du courant alternatif
H01H 39/00 - Dispositifs de commutation actionnés par une explosion produite à l'intérieur du dispositif et amorcée par un courant électrique
H01H 85/02 - Dispositifs de protection dans lesquels le courant circule à travers un organe en matière fusible et est interrompu par déplacement de la matière fusible lorsqu'il devient excessif - Détails
53.
ELECTRICAL MODULE CONFIGURED TO BE CONNECTED TO A POWER SHAFT OF A TURBINE ENGINE FOR AIRCRAFT AND METHOD FOR ASSEMBLING SUCH A MODULE
An electrical module configured to be connected to a power shaft of a turbine engine of an aircraft. The electrical module being configured to draw off power from/inject power into the power shaft. The electrical module comprising an electric machine comprising a machine housing in which a stator and a rotor is mounted, configured to be mechanically connected to the power shaft, the machine housing having a cylindrical shape extending along a cylinder axis, a first electric converter mounted in a first housing, a second electric converter mounted in a second housing, the second converter being independent of the first converter, the first housing and the second housing each being in the shape of a half-cylinder extending along the cylinder axis so as to form a cylindrical assembly that is mounted as an extension of the machine housing of the electric machine to limit the size of the electrical module.
H02M 7/00 - Transformation d'une puissance d'entrée en courant alternatif en une puissance de sortie en courant continu; Transformation d'une puissance d'entrée en courant continu en une puissance de sortie en courant alternatif
B64D 27/35 - Aménagements pour la production, la distribution, la récupération ou le stockage d'énergie électrique à bord
H02K 11/00 - Association structurelle de machines dynamo-électriques à des organes électriques ou à des dispositifs de blindage, de surveillance ou de protection
54.
ARRANGEMENT OF CELLS OF AN ENERGY STORAGE ELEMENT AND METHOD FOR ASSEMBLING THIS ARRANGEMENT
The invention relates to an arrangement (10) of cells (11, 12) of an energy storage element comprising at least a first and a second adjacent cell (11, 12) each comprising two electrical connection tabs (13, 14) of positive polarity and negative polarity, respectively. Each of the tabs (13) of the first cell (11) comprises a folded portion (13b) extending from this first cell (11) to the second cell (12) and each of the tabs (14) of the second cell (12) comprises a folded portion (14b) extending from this second cell (12) to the first cell (11). The assembly (10) comprises a consecutive stack comprising a support (15), a first conductive bar (16), the folded portion (13b) of the connection tab (13) of the first cell (11), a second conductive bar (17), the folded portion (14b) of the connection tab (14) of the second cell (12), and a third conductive bar (18), the assembly (10) comprising means (19, 22) for the reversible fastening of this stack which are configured to apply a clamping force to the stack.
H01M 50/517 - Procédés pour interconnecter les batteries ou cellules adjacentes par des moyens de fixation, p.ex. vis, rivets ou boulons
H01M 50/503 - Interconnecteurs pour connecter les bornes des batteries adjacentes; Interconnecteurs pour connecter les cellules en dehors d'un boîtier de batterie caractérisées par la forme des interconnecteurs
H01M 50/55 - Bornes caractérisées par la position des terminaux sur les cellules sur le même côté de la cellule
Aircraft electrical propulsion system comprising at least one electric motor (10) of which a setpoint is calculated according to a first channel (ISA) comprising a first control unit (20A) and according to a second channel (18B) comprising a second control unit (20B), the at least one electric motor comprising a rotor (12) and two star-wound stators (14A, 14B) and the first control unit of the first channel is connected to one of the two star-wound stators via a first power converter (22A) and the second control unit of the second channel is connected to the other of the two star-wound stators via a second power converter (22B), each of the first and second channels being rated for half the total power of the at least one electric motor.
H02P 29/028 - Détection d’un défaut, p.ex. court circuit, rotor bloqué, circuit ouvert ou perte de charge le moteur continuant de fonctionner malgré le défaut, p.ex. élimination, compensation ou résolution du défaut
H02P 6/00 - Dispositions pour commander les moteurs synchrones ou les autres moteurs dynamo-électriques utilisant des commutateurs électroniques en fonction de la position du rotor; Commutateurs électroniques à cet effet
H02P 25/22 - Enroulements multiples; Enroulements pour plus de trois phases
56.
MOTOR WITH INTEGRATED CONTROL WITH AIR CIRCULATION IN THE ELECTRONIC CONTROL UNIT
The invention relates to a motor (10) with integrated control, comprising: - an electric machine (11) provided with at least one rotating part mounted on a drive shaft (40); - an electronic control unit (12) for controlling the electric machine; - a casing comprising a first cavity (21) in which the electric machine (11) is housed and a second cavity (22) in which the electronic control unit (12) is housed, the drive shaft passing through both the first and second cavities (21, 22), the second cavity being closed by at least one wall (23) close to the first cavity; and - an air-mixing device (50, 60), housed in the second cavity (22) and generating an air circulation within the second cavity so as to homogenise an air temperature within the second cavity.
H02K 11/33 - Circuits d’entraînement, p.ex. circuits électroniques de puissance
H02K 9/06 - Dispositions de refroidissement ou de ventilation par l'air ambiant s'écoulant à travers la machine comportant des moyens pour établir la circulation d'un agent de refroidissement avec des ventilateurs ou des dispositifs d'entraînement mûs par l'arbre de la machine
H02K 9/08 - Dispositions de refroidissement ou de ventilation par un agent de refroidissement gazeux circulant entièrement à l'intérieur de l'enveloppe de la machine
57.
POWER MODULE FOR SUPPLYING POWER TO AN ELECTRICAL LOAD OF AN AIRCRAFT, POWER SUPPLY SYSTEM AND ASSOCIATED METHOD
The invention relates to a power module (M) for supplying power to an electrical load (L) of an aircraft, the power module (M) comprising a plurality of power electronic components (2) mounted on a support substrate (1), at least one encapsulation layer (5) for encapsulating the plurality of power electronic components (2) in order to protect them, at least one power electrical connection (4) connected to at least one power electronic component (2), at least one fusible protection layer (6) in which at least one portion (40) of the power electrical connection (4) extends, the fusible protection layer (6) being configured to change state when a current greater than an allowable threshold flows in the portion (40) of the power electrical connection (4) so as to permanently stop the flow of current in the portion (40).
The invention relates to an electric contactor (10, 10') with integrated breaking device, comprising at least one arc-breaking device (20) having a first guide (21), a second guide (22), which is connected to the contact (12), and a finned breaking module (23), which is arranged between the first guide (21) and the second guide (22). Each arc-breaking device (20) has a fuse (25), which is arranged between the first arc guide (21) and the second arc guide (22), and an insulating enclosure (29), inside which the finned breaking module (23) and the fuse (25) are arranged, the fuse (25) being separated from at least one of the arc guides (21, 22) by a physical space (30).
H01H 73/18 - Moyens pour éteindre ou supprimer un arc
H01H 9/10 - Adaptation pour coupe-circuit incorporé
H01H 85/02 - Dispositifs de protection dans lesquels le courant circule à travers un organe en matière fusible et est interrompu par déplacement de la matière fusible lorsqu'il devient excessif - Détails
59.
DEVICE FOR CONTROLLING A LEAST ONE ELECTRIC MOTOR FOR AN AIRCRAFT-PROPELLING ASSEMBLY
The present invention relates to a device (1) for controlling an electric aircraft-propelling assembly, said propelling assembly comprising a propeller (3) and at least one electric motor (4) that is powered by an electric supply voltage and that delivers a torque and a rotation speed to drive the propeller (3). The control device (1) comprises at least a unit (11) for measuring an electric supply voltage, and a control unit (12) suitable for making a signal delivered to the electric motor vary as a function of said electric supply voltage, with a view to making the rotation speed of the propeller vary.
The power contactor (100) comprises: - a fixed contact (102A); - a movable contact (104A); and - an electric insulating screen (112) designed to move between a spaced position and a position interposed between the fixed contact (102A) and the movable contact (104A) in the remote position of the latter. It furthermore comprises: - a return device (116) designed to push the screen (112) from its spaced position to its interposed position; and - a fuse (118) forming a mechanical stop that prevents the screen (112) from leaving its spaced position, the fuse (118) being designed to trip in order to allow the screen (112) to leave its spaced position so as to reach its interposed position under the effect of the return device (116), under the effect of heat released by an electric arc that occurs between the contact.
The apparatus (100) comprises: - a power source (102); - an electrical load (104); - first and second supply lines (114, 116) connecting the electrical load (104) to the power source (102), with a view to supplying electrical power to the electrical load (104); and - a power contactor (118) located on the first supply line (114). The apparatus (100) further comprises: - a branch (130) parallel to the first supply line (114), connected between two points (A, B) of the first supply line (114), these two points (A, B) surrounding the power contactor (118); - on this branch (130), an auxiliary contact (132) connected to the power contactor (118) and intended to open before and close after the power contactor (118); and - a device for opening, depending on a current flowing through the branch (130), one of the supply lines (114, 116).
H01H 9/38 - Contacts auxiliaires sur lesquels l'arc est transféré des contacts principaux
B60L 3/04 - Coupure de l'alimentation en énergie en cas de fausse manœuvre
H01H 9/54 - Circuits non adaptés à une application particulière du dispositif de commutation non prévus ailleurs
H01H 33/59 - Circuits non adaptés à une application particulière de l'interrupteur et non prévus ailleurs, p.ex. pour assurer le fonctionnement de l'interrupteur en un point déterminé de la période du courant alternatif
The invention relates to an electrical device (100) for protecting an electrical installation intended to be placed between a power supply (101) and an electrical load (102), the device comprising: - a power contactor (120) comprising two contacts (121, 122) that are intended to be connected to the power supply; - at least two Hall sensors (161, 162) configured to measure the electric currents at the input of the power contactor; - an electrical precharging circuit (150) intended to be placed between the power supply and the power contactor and connected to the electrical load; - a relay (140) configured to connect or disconnect the electrical precharging circuit; - a pyrotechnic electrical cutoff device (130) intended to be connected to the power supply and to the power contactor, and - a controller (110) configured to receive the measurements from the Hall sensors and to open or close the power contactor and the relay.
H02H 3/02 - Circuits de protection de sécurité pour déconnexion automatique due directement à un changement indésirable des conditions électriques normales de travail avec ou sans reconnexion - Détails
H02H 3/087 - Circuits de protection de sécurité pour déconnexion automatique due directement à un changement indésirable des conditions électriques normales de travail avec ou sans reconnexion sensibles à une surcharge pour des systèmes à courant continu
63.
ELECTRICAL GENERATION SYSTEM FOR AIRCRAFT, AND ASSOCIATED METHOD
The invention relates to a contactor (1) comprising one or two electric arc extinguishing zones (5a) each comprising a magnetic blowout device which moves the electric arc (8a) – arising between a fixed contact (4a) and a movable contact (3a) of a movable bridge (2) switching to the open state – toward an electric arc extinguishing block (9a, 9b) comprising a plurality of stacked parallel fins (10). Each extinguishing zone is bounded in particular by two side walls (12a, 12b) each located at a distance from the fins of an electric arc extinguishing block, an upper wall (13) and a lower wall (14) which is located at a distance from the fins of the electric arc extinguishing blocks and is connected to each side wall by a concave connection (15a, 15b) of curved cross-section. The fins of each electric arc extinguishing block are inclined by an angle α of between 30 and 85 degrees with respect to the inner surface (20a, 20b) of the closest side wall.
The invention relates to a battery support comprising a base (1) and a heat transfer circuit (2), the heat transfer circuit (2) comprising a first duct and a second duct, wherein a first end of the first duct allows a heat transfer liquid to be received and a first end of the second duct allows the heat transfer liquid to be discharged, the first duct and the second duct being connected together by the second end thereof, the first duct and the second duct being delimited, on the one hand, by the base (1) and, on the other hand, by a set of walls, the first duct and the second duct sharing a common wall. The cross-section of the walls of the heat transfer circuit (2) is W-shaped and the heat transfer circuit is produced by additive manufacturing.
Assembly comprising a wall (14) and a wall feed-through system (10) configured to allow an electrical conductor (12) to be fed through the wall (14) and comprising an electrical conductor (12) intended to be mounted in a first through-hole (14a) passing through a wall (14) and comprising a shoulder (12a) and a threaded portion (17), on the opposite side to the shoulder (12a). The wall feed-through system (10) comprises a sealing member (18) configured to isolate the electrical conductor (12) from the wall (14) and configured to allow the electrical conductor (12) to be centred in the through-hole (14a) passing through the wall (14), said sealing member (18) being mounted between the shoulder (12a) of the electrical conductor (12) and a first surface (14b) of the wall (14), and a fastening member (22) configured to fasten the electrical conductor (12) and the sealing member (18) to the wall (14), and an insulating member (24, 30) partially surrounding at least the electrical conductor (12) and bearing axially between a second surface (14c) of the wall (14), the opposite surface from the first surface (14b) of the wall (14), and the fastening member (22).
The invention relates to a smart motor (10) including an electromechanical converter (12), electrical filtering means (14), an electronic control unit (16), two independent housings (18, 20) having a hollow cylindrical shape and being separated in an axial direction DA and a cooling device (24), a first housing (18) comprising a first end (180) and enclosing the electromechanical converter and a second housing (20) comprising a first end (200) and enclosing the electrical filtering means and the electronic control unit and the cooling device surrounding the first and second housings, the motor further comprising a first cover (182) enclosing a second end of the first housing (18) and a second cover (202) enclosing a second end of the second housing (20), the first and second covers facing each other and having ready-to-use connectors (40, 50), at least one of the first and second covers being made of a thermally insulating material.
H02K 11/33 - Circuits d’entraînement, p.ex. circuits électroniques de puissance
H02K 5/22 - Parties auxiliaires des enveloppes non couvertes par les groupes , p.ex. façonnées pour former des boîtes à connexions ou à bornes
H02K 7/08 - Association structurelle avec des paliers
H02K 5/20 - Enveloppes ou enceintes caractérisées par leur configuration, leur forme ou leur construction avec des canaux ou des conduits pour la circulation d'un agent de refroidissement
69.
AXIAL FAN FOR AIR COOLED ELECTRICAL AIRCRAFT MOTOR
Described is a fan assembly for an electrical aircraft motor having an axial fan with an inner hub of a first diameter and an outer hub of a second diameter. The outer hub may be concentrically aligned with the inner hub. A plurality of blades may extend between the inner hub and the outer hub. The fan assembly may also have a mounting plate connected to the inner hub. The mounting plate may attach to a component of the electrical aircraft motor.
F02K 5/00 - Ensembles fonctionnels comportant un moteur, autre qu'une turbine à gaz, entraînant un compresseur ou un ventilateur soufflant
B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur, l'électricité ou l'énergie de ressorts
B64D 33/08 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des systèmes de refroidissement des ensembles fonctionnels de propulsion
70.
AXIAL FAN FOR AIR COOLED ELECTRICAL AIRCRAFT MOTOR
Described is a fan assembly for an electrical aircraft motor having an axial fan with an inner hub of a first diameter and an outer hub of a second diameter. The outer hub may be concentrically aligned with the inner hub. A plurality of blades may extend between the inner hub and the outer hub. The fan assembly may also have a mounting plate connected to the inner hub. The mounting plate may attach to a component of the electrical aircraft motor.
H02K 5/18 - Enveloppes ou enceintes caractérisées par leur configuration, leur forme ou leur construction avec des nervures ou des ailettes pour améliorer la transmission de la chaleur
H02K 7/14 - Association structurelle à des charges mécaniques, p.ex. à des machines-outils portatives ou des ventilateurs
H02K 9/06 - Dispositions de refroidissement ou de ventilation par l'air ambiant s'écoulant à travers la machine comportant des moyens pour établir la circulation d'un agent de refroidissement avec des ventilateurs ou des dispositifs d'entraînement mûs par l'arbre de la machine
09 - Appareils et instruments scientifiques et électriques
37 - Services de construction; extraction minière; installation et réparation
42 - Services scientifiques, technologiques et industriels, recherche et conception
Produits et services
Apparatus and instruments for conducting, switching, transforming, accumulating, regulating or controlling electricity; Electric harnesses; Cables, electric; Fibre optic cables; Fiber optics; Coupling equipment for electric and optical cables; Converters, electric; Protective sheaths for electric cables and Protective sleeves, For use with the following goods: Electric harnesses; Systems (apparatus, instruments and computer software) for the management of electrical equipment; Computer hardware and computer software in the field of electricity distribution; Computer software for use in the protection, control, management, surveillance and monitoring of electrical installations and equipment. Repair, overhaul, Reconditioning, Adapting, modification, Maintenance and Maintenance In connection with the following goods: Electric and electronic apparatus, instruments, systems, hardware and equipment for use in the following fields: Aeronautic and defence; Repair, overhaul, Reconditioning, Adapting, modification, Maintenance and Maintenance In connection with the following goods: Electric installation and electrical wiring for use in the following fields: Aeronautic and defence. Engineering and surveying; Research and development of new products; Professional consultancy relating to engineering; all the foregoing In connection with the following goods: Electric installations, equipment, apparatus, instruments and cabling for use in the following fields: Aeronautics and Defense.
GENERAL ELECTRIC DEUTSCHLAND HOLDING GMBH (Allemagne)
GENERAL ELECTRIC COMPANY (USA)
Inventeur(s)
Delbosc, Philippe
Reigner, Pierre-Alain Jean Philippe
Osama, Mohamed
Zatorski, Darek
Abrégé
A turbine engine is disclosed, which comprises a first electric machine coupled to a low pressure shaft of the turbine engine and a second electric machine coupled to a high pressure shaft of the turbine engine. The turbine engine includes one or more engine loads and an external electrical connection for communicating electrical power between the turbine engine and an electrical system of an aircraft. The turbine engine includes a power management system including a high voltage DC busbar configured to communicate electrical power between the first and second electric machines and the engine loads and the external electrical connection. The power management system includes a control system configured to control power offtake from and injection to the first and second electric machines, and controls power delivered to the one or more engine loads and the external electrical connection.
F02C 3/107 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail ayant une turbine entraînant un compresseur avec plusieurs rotors raccordés par transmission de puissance
F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
F02C 7/32 - Aménagement, montage ou entraînement des auxiliaires
F02C 7/275 - Entraînement du rotor pour le démarrage mécanique
73.
ASSEMBLY OF AN ELECTRIC MOTOR AND A DEVICE FOR CONTROLLING THE ELECTRIC MOTOR, AND METHOD FOR CONTROLLING SUCH AN ASSEMBLY
The invention relates to an assembly (1) of an electric motor (2) for propelling an aircraft and a control device (5), the electric motor (2) comprising a stator (21) and a rotor (22) and at least one cooling channel (CR) configured to be supplied with a heat transfer fluid (F), the control device (5) being configured to issue a control command (01) in order to control the rotation of the rotor (22), the control device (5) also being configured to issue a heating command configured to generate a heating current in the stator (21) in order to heat the heat transfer fluid (F), the heating current comprising a non-zero DC component and a substantially zero quadratic component so as to limit the rotation of the rotor (22) during heating.
H02P 1/02 - Dispositions de démarrage de moteurs électriques ou de convertisseurs dynamo-électriques - Détails
H02P 29/60 - Commande ou détermination de la température du moteur ou de l'entraînement
H02P 29/68 - Commande ou détermination de la température du moteur ou de l'entraînement basée sur la température d’un composant d’entraînement ou d’un composant semi-conducteur
B64D 1/00 - Largage, éjection ou réception, en cours de vol, d'objets, de liquides ou similaires
74.
ELECTRICAL SYSTEM OF AN ELECTRIC PROPULSION UNIT OF AN AIRCRAFT
The invention relates to an electrical system (100) having: - an electric circuit (102) having a electrically insulating flat support (104) and two electric conductors (106, 108) secured to the flat support, the two electric conductors (106, 108) being designed to have different respective electric potentials during operation of the electric circuit (102), the two electric conductors (106, 108) being separated from one another by an air insulation distance (DI); and - an electrically insulating spacer (110) extending over the flat support (104), between the two electric conductors (106, 108), and having raised elements (112) so as to define a leakage path (DF) between the two electric conductors (106, 108) along the spacer (110), this leakage path (DF) passing via the raised elements (112).
The invention relates to a nacelle system (8) for an electric machine (2) provided with cooling fins (6), which comprises a fairing (10) configured to match the shape of the electric machine (2) and an adjustment device (12) configured to hold the fairing (10) and press it against the cooling fins (6) for cooling the electric machine (2), the fairing (4) comprising at least one portion (14) of fairing (10), the adjustment device (12) comprising at least one connection means (16) arranged between two ends (20) of portion (14) of fairing (10). In particular, the nacelle system (8) enables the electric machine (2) to be cooled more effectively by improved air circulation and improves the performance of the electric machine (2).
H02K 5/18 - Enveloppes ou enceintes caractérisées par leur configuration, leur forme ou leur construction avec des nervures ou des ailettes pour améliorer la transmission de la chaleur
H02K 9/14 - Dispositions de refroidissement ou de ventilation dans lesquels l'agent de refroidissement gazeux circule entre l'enveloppe de la machine et une chemise extérieure
76.
ELECTRICAL CONTACTOR COMPRISING A SPRING FOR RAPIDLY DRIVING CONTACTS
The invention relates to an electrical contactor (10) comprising stationary contacts (12) and movable contacts (14) which are movable relative to the stationary contacts (12) between a position of contact with the stationary contacts and a position of separation from the stationary contacts (12); an actuator (16) for driving the movable contacts (14) to move relative to the stationary contacts (12) towards either the position of contact with the stationary contacts (12) or the position of separation from the stationary contacts (12); a linkage (30) for driving the movable contacts (14) from the contact position to the separation position, independently of the actuator (16); the electrical contact being characterised in that the linkage (30) comprises a drive spring (32) and a system for disengageably locking the linkage.
The invention relates to a device for protection against short circuits occurring on a high-voltage DC power supply line (36, 38) between a DC source (10) and an active load (20), the device consisting of a bypass circuit formed of a contactor K3 and a fuse F2 connected in series and mounted in parallel with the active load via a line (32, 34) that is independent from the high-voltage DC power supply line, the bypass circuit being configured so that the current flows mainly through same once the fuse F2 has blown.
The present invention relates to a battery case comprising an electrochemical cell inside the case. A first face of the battery case comprises a first, a second and a third band, which are mutually distinct, the first, the second and the third band being delimited by two parallel straight lines passing entirely through said face of the case. The first face of the battery case comprises a fluid inlet opening situated within the first band, a fluid outlet opening situated within the second band, and a first and second opening situated within the third band, the first and the second opening forming an interface with a first and a second pole of the electrochemical cell. The present invention also relates to a connection beam for the battery cases and to an electric battery comprising said beam and at least two battery cases.
H01M 50/249 - Montures; Boîtiers secondaires ou cadres; Bâtis, modules ou blocs; Dispositifs de suspension; Amortisseurs; Dispositifs de transport ou de manutention; Supports spécialement adaptés aux aéronefs ou aux véhicules, p.ex. aux automobiles ou aux trains
H01M 50/258 - Batteries modulaires; Boîtiers pourvus de moyens d’assemblage
H01M 50/502 - Interconnecteurs pour connecter les bornes des batteries adjacentes; Interconnecteurs pour connecter les cellules en dehors d'un boîtier de batterie
79.
ELECTRICAL POWER GENERATION AND DISTRIBUTION SYSTEM FOR AN AIRCRAFT, AND AIRCRAFT COMPRISING SUCH A SYSTEM
The invention relates to an electrical power generation and distribution system 1 for a hybrid-electric propulsion aircraft powered by at least one turbojet engine (10). The system comprises at least N ≧ 2 (N integer) distribution networks (30), and at least M ≧ 1 (M integer) generation channels (20) associated with each distribution network. The electrical power supply parameters of the distribution networks are controlled by an electrical machine (22) provided on each of the generation channels, on the basis of a generator control setpoint (Cg) defined by a common mode current IC resulting from the currents IN,M generated in the generation channels. The turbojet engine comprises a high-pressure shaft, a low-pressure shaft and a control module (16) for controlling the power transferred between the shafts on the basis of an engine regulation setpoint (Cm) defined by a differential mode current Id resulting from the distribution of power drawn between the generation channels.
H02J 1/10 - Fonctionnement de sources à courant continu en parallèle
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
H02J 3/38 - Dispositions pour l’alimentation en parallèle d’un seul réseau, par plusieurs générateurs, convertisseurs ou transformateurs
H02J 4/00 - Circuits pour réseaux principaux ou de distribution, la nature alternative ou continue du courant n'étant pas précisée
F02C 6/20 - Aménagements des ensembles fonctionnels de turbines à gaz pour l'entraînement des véhicules
F02C 9/28 - Systèmes de régulation sensibles aux paramètres ambiants ou à ceux de l'ensemble fonctionnel, p.ex. à la température, à la pression, à la vitesse du rotor
F02K 5/00 - Ensembles fonctionnels comportant un moteur, autre qu'une turbine à gaz, entraînant un compresseur ou un ventilateur soufflant
80.
PROTECTIVE INSULATOR INTENDED TO BE MOUNTED ON AN ELECTRICAL CONNECTOR, AND ASSEMBLY COMPRISING SUCH PROTECTION
One aspect of the invention relates to a protective insulator (PI) intended to be fixed on an electrical connector, the electrical connector comprising a base, at least a first terminal and a second terminal, the protective insulator (PI) comprising a fixing means (CR) configured to be able to be fixed on the electrical connector in such a way as to at least partially cover the base, and an insulating separation means (P1, P2) arranged in such a way as to completely separate the first terminal from the second terminal when the protective insulator is fixed on the electrical connector.
B60R 16/02 - Circuits électriques ou circuits de fluides spécialement adaptés aux véhicules et non prévus ailleurs; Agencement des éléments des circuits électriques ou des circuits de fluides spécialement adapté aux véhicules et non prévu ailleurs électriques
H01B 17/26 - Isolateurs d'entrée; Isolateurs de traversée
H01B 17/58 - Tuyaux, manchons, perles isolantes ou bobines au travers desquels passe le conducteur
H01R 13/53 - Socles ou boîtiers pour dures conditions de service; Socles ou boîtiers avec des moyens pour éviter l'effet couronne ou l'amorçage d'un arc
81.
ELECTRICAL DISTRIBUTION METHOD AND SYSTEM, CONFIGURED TO SUPPLY ELECTRIC MOTORS OF AN AIRCRAFT FROM AT LEAST ONE ELECTRICAL SOURCE
The invention relates to an electrical distribution system (1) configured to supply at least a first electric motor (M1) and a second electric motor (M2) from at least one electrical source (B1), the electrical distribution system (1) comprising a switch (C1) connected to the electrical source (B1) by an electrical source line (LS) and to each electric motor (M1, M2) by an electrical load line (LC1, LC2), a circuit-breaking device (2), configured to open the electrical source line (LS) after a predetermined time delay in the event of the presence of a short-circuit current, and a current limiter (3) configured to, in the event of the presence of a short-circuit current, allow a limited current (Ilim) to flow through the switch (3) for a limiting period greater than the predetermined time delay.
H02H 3/093 - 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 avec des moyens de temporisation
H02H 9/02 - Circuits de protection de sécurité pour limiter l'excès de courant ou de tension sans déconnexion sensibles à un excès de courant
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
Disclosed is a twin-spool turbomachine comprising a low-pressure turbine (5) connected to a low-pressure compressor (1) by a low-pressure rotation shaft (10) and a high-pressure turbine (4) connected to a high-pressure compressor (2) by a high-pressure rotation shaft (9), the turbomachine (11) further comprising a mechanical power feed device (13) on at least one of the rotation shafts (9, 10). The turbomachine (11) comprises capacitive components (15) for supplying the turbomachine (11) with electrical energy through the mechanical power feed device (13), the capacitive components (15) being arranged on the turbomachine (11) or on a support structure for the turbomachine (11) and arranged so as to form at least one pair of concentric circles (17) centred around a main axis (A) of the turbomachine (11), the circles of the capacitive components (15) being radially adjacent to one another.
The invention relates to a method for controlling a hybrid turbine engine (11) for an aircraft, the turbine engine (11) comprising a low-pressure shaft (10), a high-pressure shaft (9), at least one power conversion device (13) mounted on the low-pressure shaft (10) or the high-pressure shaft (9) and an energy storage assembly comprising a plurality of capacitive components (15), the method comprising the steps of: - precharging the capacitive components (15) until a mean voltage reaches a first partial charging value, - balancing the voltages of the capacitive components (15), - charging the capacitive components (15) 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 (10) and/or to the high-pressure shaft (9) to assist manoeuvering of the aircraft.
The device for charging a battery (15, 16) of an aircraft (1) comprises a reversible electrical power converter (13) comprising a power inlet (132) configured to be connected to the battery (16) and a power outlet (134) configured to be connected to a propulsion rotary electric machine (5) driving a propeller (100) 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 (100) and a parking socket (42) connected between the charging contactor and the power outlet.
B60L 53/24 - PROPULSION DES VÉHICULES À TRACTION ÉLECTRIQUE; FOURNITURE DE L'ÉNERGIE ÉLECTRIQUE À L'ÉQUIPEMENT AUXILIAIRE DES VÉHICULES À TRACTION ÉLECTRIQUE; SYSTÈMES DE FREINS ÉLECTRODYNAMIQUES POUR VÉHICULES, EN GÉNÉRAL; SUSPENSION OU LÉVITATION MAGNÉTIQUES POUR VÉHICULES; CONTRÔLE DES PARAMÈTRES DE FONCTIONNEMENT DES VÉHICULES À TRACTION ÉLECTRIQUE; DISPOSITIFS ÉLECTRIQUES DE SÉCURITÉ POUR VÉHICULES À TRACTION ÉLECTRIQUE Échange 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 53/22 - PROPULSION DES VÉHICULES À TRACTION ÉLECTRIQUE; FOURNITURE DE L'ÉNERGIE ÉLECTRIQUE À L'ÉQUIPEMENT AUXILIAIRE DES VÉHICULES À TRACTION ÉLECTRIQUE; SYSTÈMES DE FREINS ÉLECTRODYNAMIQUES POUR VÉHICULES, EN GÉNÉRAL; SUSPENSION OU LÉVITATION MAGNÉTIQUES POUR VÉHICULES; CONTRÔLE DES PARAMÈTRES DE FONCTIONNEMENT DES VÉHICULES À TRACTION ÉLECTRIQUE; DISPOSITIFS ÉLECTRIQUES DE SÉCURITÉ POUR VÉHICULES À TRACTION ÉLECTRIQUE Échange d'éléments d’emmagasinage d'énergie dans les véhicules électriques caractérisés par des convertisseurs situés dans le véhicule - Détails de structure ou aménagements des convertisseurs de charge spécialement adaptés pour recharger des véhicules électriques
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
B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur, l'électricité ou l'énergie de ressorts
B64D 31/00 - Commande des groupes moteurs; Leur disposition
B64D 33/00 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs
B64D 35/00 - Transmission de la puissance du groupe moteur aux hélices ou aux rotors; Aménagements des transmissions
H02M 1/00 - APPAREILS POUR LA TRANSFORMATION DE COURANT ALTERNATIF EN COURANT ALTERNATIF, DE COURANT ALTERNATIF EN COURANT CONTINU OU VICE VERSA OU DE COURANT CONTINU EN COURANT CONTINU ET EMPLOYÉS AVEC LES RÉSEAUX DE DISTRIBUTION D'ÉNERGIE OU DES SYSTÈMES D'ALI; TRANSFORMATION D'UNE PUISSANCE D'ENTRÉE EN COURANT CONTINU OU COURANT ALTERNATIF EN UNE PUISSANCE DE SORTIE DE CHOC; LEUR COMMANDE OU RÉGULATION - Détails d'appareils pour transformation
H02M 7/04 - Transformation d'une puissance d'entrée en courant alternatif en une puissance de sortie en courant continu sans possibilité de réversibilité par convertisseurs statiques
B60L 3/00 - Dispositifs électriques de sécurité sur véhicules propulsés électriquement; Contrôle des paramètres de fonctionnement, p.ex. de la vitesse, de la décélération ou de la consommation d’énergie
B64D 35/02 - Transmission de la puissance du groupe moteur aux hélices ou aux rotors; Aménagements des transmissions caractérisée par le type de groupe moteur
The invention relates to a propulsion unit comprising: an electric motor (10), which includes an annular stator (11) about a longitudinal axis (X) and a rotor arranged radially inside the stator (11), so as to be rotated about the longitudinal axis (X); a power electronic module (20) suitable for supplying electricity to the electric motor (10), the power electronic module (20) comprising an annular casing (21) which extends along the longitudinal axis (X), the casing (21) of the power electronic module (20) comprising a first end disposed longitudinally opposite a first end of the stator (11) of the electric motor (10); means for cooling the electric motor (10) and the power electronic module (20), the cooling means comprising a heat sink (30) inserted longitudinally between the first end of the stator (11) of the electric motor (10) and the first end of the casing (21) of the power electronic module (20).
B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur, l'électricité ou l'énergie de ressorts
H01G 2/00 - CONDENSATEURS; CONDENSATEURS, REDRESSEURS, DÉTECTEURS, DISPOSITIFS DE COMMUTATION, DISPOSITIFS PHOTOSENSIBLES OU SENSIBLES À LA TEMPÉRATURE, DU TYPE ÉLECTROLYTIQUE - Détails de condensateurs non couverts par un seul des groupes
H01G 4/00 - Condensateurs fixes; Procédés pour leur fabrication
H02K 5/18 - Enveloppes ou enceintes caractérisées par leur configuration, leur forme ou leur construction avec des nervures ou des ailettes pour améliorer la transmission de la chaleur
H02K 7/18 - Association structurelle de génératrices électriques à des moteurs mécaniques d'entraînement, p.ex. à des turbines
H02K 9/00 - Dispositions de refroidissement ou de ventilation
H02K 11/33 - Circuits d’entraînement, p.ex. circuits électroniques de puissance
F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
F02C 6/02 - Ensembles fonctionnels multiples de turbines à gaz comportant une sortie de puissance commune
B60K 11/06 - Dispositions des ensembles de propulsion relatives au refroidissement avec refroidissement par air
F02C 6/20 - Aménagements des ensembles fonctionnels de turbines à gaz pour l'entraînement des véhicules
F02C 7/12 - Refroidissement des ensembles fonctionnels
F02K 3/06 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant dans lesquels une partie du fluide énergétique passe en dehors de la turbine et de la chambre de combustion l'ensemble fonctionnel comprenant des soufflantes carénées, c. à d. des soufflantes à fort débit volumétrique sous basse pression pour augmenter la poussée, p.ex. du type à double flux comprenant une soufflante avant
F02K 5/00 - Ensembles fonctionnels comportant un moteur, autre qu'une turbine à gaz, entraînant un compresseur ou un ventilateur soufflant
H02K 9/06 - Dispositions de refroidissement ou de ventilation par l'air ambiant s'écoulant à travers la machine comportant des moyens pour établir la circulation d'un agent de refroidissement avec des ventilateurs ou des dispositifs d'entraînement mûs par l'arbre de la machine
H02K 9/22 - Dispositions de refroidissement ou de ventilation par un matériau solide conducteur de la chaleur s'encastrant dans, ou mis en contact avec, le stator ou le rotor, p.ex. des ponts de chaleur
B60K 1/00 - Agencement ou montage des ensembles de propulsion électriques
B64D 27/02 - Aéronefs caractérisés par le type ou la position des groupes moteurs
86.
ELECTRICAL DISTRIBUTION SYSTEM FOR AIRCRAFT AND ASSOCIATED METHOD
The invention relates to an electrical distribution system (1) configured to supply power to at least a first electric motor (M1) and a second electric motor (M2) from at least a first electrical source (B1) and a second electrical source (B2), comprising at least a first switch (C1) and a second switch (C2), each switch (C1, C2) comprising at least a first power supply bus (BUS1A, BUS1B) and a second power supply bus (BUS2A, BUS2B), at least one electrical reconfiguration line (LR1) connecting the first switch (C1) to the second switch (C2), the electrical reconfiguration line (LR1) including at least one reconfiguration switch (II) configured to be switched into the closed position in the event of a fault in one of the electrical sources (B1, B2).
The invention relates to an electrical power harness (10) for an aircraft, comprising a plurality of cables (11), each cable (11) comprising, radially from the inside outward: - a conductive core (12), - a first layer (13) of semi-conductive material, - an insulating layer (14), and - a second layer (15) of semi-conductive material, characterized in that the harness (10) further comprises a common shield (16, 16') disposed in electrical contact with the second layers (15) of semi-conductive material of each cable (11).
H01B 9/02 - Câbles de transport d'énergie avec écrans ou couches conductrices, p.ex. en vue d'éviter des gradients de potentiel élevés
H02G 3/06 - 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 assurant la continuité électrique dans le joint
H01B 7/00 - Conducteurs ou câbles isolés caractérisés par la forme
88.
GENERIC HIGH-VOLTAGE DC ELECTRICAL DISTRIBUTION PANEL
The invention relates to a high-voltage DC electrical distribution panel for the installation of two electromechanical power contactors either in series or in parallel. Locations for the installation of the chambers for the fixed and mobile contact terminals of the two contactors are arranged on a first of the main surfaces of the panel, while locations for the installation of the complementary assemblies for the two contactors are arranged on the second main surface of the panel, each complementary assembly comprising a motor that is intended to activate the contact terminals of the relevant contactor. On the first of the surfaces, there is an installation location free of contact terminal chambers and fixed contacts at this location are protected by a protective housing incorporating a shunt which ensures continuity of the power connection. This device improves the isolation of live parts while offering greater compactness.
The invention relates to an electric machine (1000) comprising at least one phase (100, 200, 300) including two electrical pathways (101, 102, 201, 202, 301, 302) in parallel, each electrical pathway of a single phase including a winding (111, 112, 211, 212, 311, 312), the first electrical pathways of all the phases being connected to a single first electrical node (10) and the second electrical pathways of all the phases being connected to a single second electrical node (20), characterised in that the electric machine comprises an equipotential wire (400) electrically connecting the first and second electrical nodes and a current sensor (500) configured to measure an electrical current (I101 + I201 + I301 - (I102 + I202 + I302)) flowing 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 19/00 - Dispositions pour procéder aux mesures de courant ou de tension ou pour en indiquer l'existence ou le signe
91.
DEVICES FOR MONITORING AND PROTECTING POWER CIRCUITS
A device for monitoring and protecting equipment powered by at least one solid-state power controller (SSPC) including at least one current measurement circuit having a current measuring transformer receiving at a primary at least three phases of a three-phase power supply of the equipment, a measuring and testing module including a controller for measuring a current at a secondary Im, representative of a differential current Id at the primary, and a channel for injecting current into said transformer, the channel having a current Iinj generator controlled by an output of the controller and connected to an injection winding on the transformer, the injection winding including a number of turns Nin so that the current Iinj produces in said measurement windings a test current Im of said secondary in the absence of current at the primary.
H02H 3/347 - 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 angle de déphasage entre tensions ou courants comprenant la comparaison des valeurs de tension ou de courant en des points correspondants des différents conducteurs d'un même système, p.ex. de courants dans des conducteurs d'aller et retour d'un système triphasé utilisant des transformateurs sommateurs de courant
The invention relates to an energy-saving contact (1) comprising a fixed part (2) and a mobile part (3) able to move in a main direction (Z) between a contact position and a breaking position, the energy-saving contact (1) comprising a spring blade (8) fixed to the fixed part (2) and forming an electrical contact, as well as an end stop (10) mounted on the mobile part (3) and arranged so as to be distant from the blade (8) and to come to press against the blade (8) when the mobile part (3) is in the contact position. The fixed part (2) defines an orifice (11) through which the end stop (10) passes opposite the blade (8), the orifice (11) having an internal cross section substantially identical to an external cross section of the end stop (10), the end stop (10) being mounted on the mobile part (3) such as to be mobile translationally in a plane (XY).
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
H01H 47/04 - Circuits autres que ceux appropriés à une application particulière du relais et prévue pour obtenir une caractéristique de fonctionnement donnée ou pour assurer un courant d'excitation donné en vue de modifier le fonctionnement du relais en vue de retenir l'armature en position d'attraction, p.ex. avec un courant réduit ou interrompu
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
The invention relates to an electrical connector comprising: - a female contact (10), with a central element (12) having an axial internal recess (121), and a ring (14) arranged around said central element (12), the ring (14) being mounted so as to be movable with respect to the central element (12) with an internal wall (143) of the ring (14) delimiting an opening of typically conical, narrow shape complementary to a profile of an external region (125) of the central element, which can slide over this external region, said ring (14) being connected to the central element (12) via an elastic member (25) arranged between the ring (14) and the central element (12) and tending to push the central element away from the ring.
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
Inventeur(s)
Vendrame, Fernanda
Forgez, Christophe
Abrégé
The invention relates to estimating the state of energy (SOE) for a particular time, which includes: - receiving (602) measurements of a temperature (T) of the cell (111), of a voltage (U) of the cell (111) and of a current (I) exchanged by the cell (111); - estimating an internal resistance (R) of the cell (111); - estimating an open circuit voltage (OCV) of the cell (111); - estimating a total energy (Etot) delivered by the cell (111) until the particular time; - estimating a maximum energy (Emax) that can be delivered by the cell (111) assuming that the temperature (T) and the current (I) remain constant; and - subtracting the estimated total delivered energy (Etot) from the estimated maximum energy (Emax).
The invention relates to a permanent-magnet synchronous three-phase rotating machine (40), provided with a control device comprising a computer (100) for controlling an inverter (30) that drives the phases of said machine, for which purpose said computer comprises an estimator module (10) for estimating speed and angular position of the rotor of said machine, which estimator module is provided, at its input, with an input selector module (1) that receives digital voltage data, said input selector module being driven by an operating mode command (SEL) for said machine, said input selector module being configured to select: - data inputs representative of the three-phase control voltages Va_cmd, Vb_cmd, Vc_cmd of the phases A, B, C of the inverter (30), in the powered operating mode of said machine; - data inputs representative of three-phase measured voltages Va_mes, Vb_mes, Vc_mes of the phases A, B, C of said machine, in free-running mode; - voltage data inputs that are forced to zero, in the mode of short-circuiting the phases of said machine; as input data for the estimator module for estimating speed and angular position of said machine.
H02P 6/17 - Dispositions de circuits pour détecter la position et pour l’obtention d’informations sur la vitesse
H02P 6/182 - Dispositions de circuits pour détecter la position sans éléments séparés pour détecter la position utilisant la force contre-électromotrice dans les enroulements
96.
METHOD AND SYSTEM FOR ESTIMATING THE AVAILABLE STATE OF CHARGE OF A BATTERY ACCORDING TO THE INSTANTANEOUS VOLTAGE
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (CNRS) (France)
Inventeur(s)
Vendrame, Fernanda
Sayegh, Marie
Forgez, Christophe
Abrégé
The invention relates to a method for estimating the state of charge of a battery, the method comprising the following steps: • - determining the stored state of charge; • - determining the open-circuit instantaneous voltage of the battery according to a predetermined map and the stored state of charge; • - measuring the instantaneous voltage across the terminals of the battery; • - determining the available state of charge according to the stored state of charge, the instantaneous voltage, the open-circuit instantaneous voltage and the minimum acceptable voltage; • - the minimum acceptable voltage being predetermined by design.
G01R 31/382 - Dispositions pour la surveillance de variables des batteries ou des accumulateurs, p.ex. état de charge
G01R 31/3835 - Dispositions pour la surveillance de variables des batteries ou des accumulateurs, p.ex. état de charge ne faisant intervenir que des mesures de tension
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 31/385 - Dispositions pour mesurer des variables des batteries ou des accumulateurs
G01R 31/387 - Détermination de la capacité ampère-heure ou de l’état de charge
G01R 31/388 - Détermination de la capacité ampère-heure ou de l’état de charge faisant intervenir des mesures de tension
97.
DEVICE FOR DETECTING IMPACTS, ASSOCIATED DETECTION SYSTEM AND AIRCRAFT EQUIPPED WITH SUCH A SYSTEM
An autonomous impact detection device includes at least one impact detector; at least one wireless transmission device configured to transmit the information collected by the impact detector; at least one energy storage device configured to supply the impact detector and the wireless transmission device with energy; at least one Seebeck module configured to supply the storage device with energy when a temperature gradient is applied thereto; the wireless transmission device being configured to supply the storage device with energy when the temperature gradient to which the Seebeck module is exposed is not sufficient.
B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
H02J 50/20 - Circuits ou systèmes pour l'alimentation ou la distribution sans fil d'énergie électrique utilisant des micro-ondes ou des ondes radio fréquence
H10N 10/17 - Dispositifs thermoélectriques comportant une jonction de matériaux différents, c. à d. dispositifs présentant l'effet Seebeck ou l'effet Peltier fonctionnant exclusivement par les effets Peltier ou Seebeck caractérisés par la structure ou la configuration de la cellule ou du thermocouple constituant le dispositif
B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
98.
DEVICE FOR ESTIMATING TWO STATES OF CHARGE OF A BATTERY, AND ASSOCIATED SYSTEM, AIRCRAFT AND METHOD
The invention relates to a device (9) for estimating two states of charge (SOC1, SCO2) of a battery (8) comprising a plurality of cells (12) connected to one another, at least a fraction of the plurality of cells forming at least one set of cells (13, 14, 15) comprising at least two cells, the device comprising: first determining means (20) that are configured to determine a first state of charge (SOC1) of the battery from the voltage across the terminals of each cell (12) and the temperature in the vicinity of each cell, and the current flowing through the terminals of the plurality of cells. The device further comprises second determining means (21) 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 31/382 - Dispositions pour la surveillance de variables des batteries ou des accumulateurs, p.ex. état de charge
B60L 58/10 - 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
99.
SEGMENTED ROTARY TRANSFORMER HAVING A LARGE DIAMETER
The invention relates to a rotary transformer that is intended to be installed around a rotating shaft, the rotary transformer being made up of a plurality of stator annular sectors (22a, 22b) and a plurality of rotor annular sectors (24a, 24b), the juxtaposition of these annular sectors (20) forming a stator ring and a rotor ring formed of elementary stator and rotor magnetic circuits having external (30) and internal (34) magnetic cores and first (32) and second (36) electrical windings to allow power to be transferred by electromagnetic induction between the stator rings and the rotor rings, the internal and external magnetic cores being separated by one and the same air gap present on either side of the internal magnetic core and at least the external magnetic cores have shoes at the air gap to prevent any discontinuity in the magnetic field lines as the movable shaft rotates.
The invention relates to an integrated unit (220) for transferring rotary power from an electrical circuit for de-icing propeller blades and the nose cone (110) of a turbomachine, the unit comprising: - a rotary transformer (2221) comprising a static portion and a rotating portion; - a DC-to-AC voltage converter (2231) connected at its output to the static portion of the rotating transformer and intended to be connected at its input to a DC power supply (2321); and - a power switch (2211) connected to the rotating transformer and configured to transmit electrical power to at least one pair (1101, 1102) of propeller blades and to the nose cone (110) of the turbomachine.
