Airbus Patente

There is disclosed an apparatus for monitoring electrical aircraft components, the apparatus comprising: a pulse generator configured to transmit an electrical pulse to an electrical bus, the electrical bus being electrically connected to a plurality of loads; a pulse receiver configured to receive a reflection of the transmitted electrical pulse from the electrical bus; and a processor configured to: perform a wavelet transformation on the received reflected pulse to identify a plurality of component signals of the reflected pulse; identify an electrical condition associated with the plurality of loads based on the transformed reflection of the electrical pulse, and identify a load associated with the identified electrical condition based on a component signal associated with said load.

A trolley arrangement (10, 10'), in particular for use in an aircraft cabin, comprises a trolley body (12) defining an interior space, a plurality of carriers (26) removably accommodated in the interior space of the trolley body (12), a plurality of heating devices (32, 32'), each heating device (32, 32') being associated with at least one of the plurality of carriers (26) and being configured to heat an item (28) arranged in at least a partial region (34a-c) of the carrier (26), a power distribution network (38) connectable to each of the heating devices (32, 32'), and a control unit (54) configured to receive an individual heating command for each of the heating devices (32, 32') and to control the power distribution network (38) so as to individually provide power to a selected one of the plurality of heating devices (32, 32') in response to a respective individual heating command.

The present invention provides an optical terminal (1) for lidar and optical communication, comprising a transmitter section (2), including a first transmitter unit (21) configured to emit a first communication signal (211) at a first wavelength, a second transmitter unit (22) configured to emit a first quantum signal (221) at a second wavelength; and a receiver section (3), including a first receiver unit (31) configured to receive a second communication signal (311) at a third wavelength, a second receiver unit (32) configured to receive a lidar signal (321) at the first wavelength, and a controller (4) configured to control an emission of the first transmitter unit (21) and the second transmitter unit (22), extract data from the received communication signal (311), and determine a time-of-flight of the lidar signal (321) based on the emission of the first communication signal (211). Further, the present invention provides a corresponding method for operating an optical terminal (1).

The present invention relates to method (M) for operating an autonomous certificate management system for technical devices placed in a vehicle, particularly in an aircraft (100), comprising: providing in a vehicle an onboard certificate management system (OCMS) (1) which is designed to be coupled with at least one technical device (4) to be placed within the vehicle, providing to the OCMS (1) a respective list of information from respective technical devices (4) to be placed in the vehicle, qualifying respective technical devices (4) to be placed within the vehicle with a certificate signing request method (5) which is designed to determine at least one unique information about the respective technical device (4) and to transmit a created certificate signing request (CSR) comprising the at least one unique information to the OCMS (1), creation and transmission of a digital certificate by the OCMS (1) to the respective technical device (4) depending on a comparison of stored and received information about the respective technical device (4) in the OCMS (1) carried out by the OCMS (1). In addition, a system (2) for vehicles and an aircraft (100) according to the invention are presented.

In order to provide a compact lightweight transformer for use at cryogenic temperatures, the transformer comprises a ferrite core with an air gap and comprising a relative permeability at 77K, µ_r(77K), wherein 50 ≤ µ_r (77K) ≤ 1000, at least one primary winding and at least one secondary winding.

In order to provide a power supply circuit which reliably functions in a cryogenic environment, the invention provides a power supply (10) for producing electrically isolated auxiliary supply voltages at cryogenic temperatures. The power supply (10) comprising an input power supply (11) supplying electric power to a power stage (14), an oscillation circuit (19) coupled to the power stage (14) and a transformer (20) comprising at least one primary winding (21) and at least one secondary winding (22). The primary winding (21) is coupled to a capacitive half bridge (23) and the secondary winding (22) is coupled to a plurality of outputs, each output comprising a rectifier (27) and an auxiliary supply terminal (28).

Set (1) for a modular antenna arrangement (2) for an aircraft (50), comprising a base module (10) for connecting at least one plate shaped antenna element (20a, 20b) with a fuselage (51) of the aircraft (50), wherein the base module (10) has a bottom surface (11) mechanically connectable with the fuselage (51) of the aircraft (50) and a top surface (12) comprising at least one accommodation recess (13a, 13b) for accommodating, at least partially, the at least one plate shaped antenna element (20a, 20b); at least one interchangeable antenna adapter module (30a, 30b) connectable to the base module (10) and the at least one plate shaped antenna element (20a, 20b), wherein the interchangeable antenna adapter module (30a, 30b) is configured to be arranged in the accommodation recess (13a, 13b) between a bottom (14a, 14b) of the accommodation recess (13a, 13b) and the plate shaped antenna element (20a, 20b); and a cover module (40) configured for at least partially covering the base module (10), wherein the cover module (40) comprises at least one opening (41a, 41b), wherein an opening cross-section of the at least one opening (41a, 41b) is adapted to a cross-section of the at least one plate shaped antenna element (20a, 20b).

L'invention a pour objet un procédé de détermination du niveau de contamination d'une surface (11) comprenant un recouvrement (E1) de tout ou partie d'une surface (11) par des gouttes de fluide incolore (12) ayant toutes sensiblement le même volume, lesdites gouttes (12) étant déposées sur ladite surface (11), selon un schéma de dépose défini en fonction des contraintes suivantes : la distance entre deux gouttes de fluide incolore (16) déposées successivement est sensiblement constante et chaque goutte de fluide incolore (16) est espacée d'une distance non nulle des autres gouttes de fluide incolores (16) l'entourant. Le procédé comprend également les étapes successives : acquisition (E2) d'une image de la surface (11) à analyser, une étape de calcul (E3), une étape de comparaison (E4) et une étape de décompte (E5) afin d'obtenir la position des gouttes (16) pour lesquelles la surface (11) sous lesdites gouttes (16) est dite contaminée.

The invention relates to a protection device, comprising:- at least one head protection cover (18) configured to cover at least one printhead (12.1) of a printing device (12),- at least one frame (24),- at least one flexible connection system (26) connecting the head protection cover (18) and the frame (24),- at least one automatic fastening system (28) configured to connect the frame (24) and the printing device (12).This solution allows automatic mounting of the protective cover on the corresponding printhead.The invention also relates to an item of printing equipment including at least one protection device.

- Procédé et système pour augmenter la précision du suivi d'une trajectoire par un outil d'un robot.- Le procédé comprend notamment une étape d'acquisition de données, au cours de laquelle le robot (2) exécute la trajectoire souhaitée sans que l'outil (3) réalise la tâche qui lui est assignée et un dispositif de mesure inertielle (10) effectue des mesures inertielles représentatives de petites imprécisions répétables de la trajectoire, ainsi qu'une étape d'opération au cours de laquelle le robot (2) exécute de nouveau la même trajectoire, l'outil (3) réalise la tâche qui lui est assignée, et on commande des actionneurs (9) pour compenser des imprécisions de l'outil (3), en tenant compte du traitement desdites mesures inertielles, réalisé par un dispositif informatique (13), ce qui permet de minimiser de petites imprécisions de trajectoire de faibles amplitudes de l'outil (3), sans avoir à agir sur la trajectoire du robot (2), et ainsi d'augmenter la précision du suivi d'une trajectoire lisse.

L'invention concerne un moteur supraconducteur (100) comportant un rotor (102) portant des aimants permanents (110) et mobiles en rotation autour d'un axe longitudinal (X), un stator (103) traversé par des orifices (116) répartis autour du rotor (102), et pour chaque orifice (116), deux bobines (150) constituées d'un matériau supraconducteur et alimentées électriquement pour générer un champ magnétique, où chaque bobine (150) comporte une première section rectiligne (152a) traversant ledit orifice (116), une deuxième section rectiligne (152b) traversant un autre orifice (116), et deux sections courbes (154a-b) où chacune relie entre elles une extrémité de la première section rectiligne (152a) et une extrémité de la deuxième section rectiligne (152b), où les sections rectilignes (152a) des deux bobines (150) traversant ledit orifice (116) sont empilées radialement. La disposition particulière des bobines permet de limiter les pertes.

The present invention relates to an electrode device.In order to provide an improved thermal management of a battery system, the electrode device (10), comprises a support structure (12), an electroactive structure (14) and a heat transfer structure (16). The support structure is configured for carrying the electroactive structure and the heat transfer structure. The electroactive structure is configured for storing and releasing of charge carriers (18). The heat conductivity of the heat transfer structure is higher than the heat conductivity of any of the support structure or the electroactive structure. The electroactive structure is arranged at the support structure. The heat transfer structure is arranged at the electroactive structure. The heat transfer structure is oriented to guide heat (20) away from a surface (22) of the electroactive structure to prevent thermal tensions (24) in its vicinity while providing diffusivity of the charge carriers to the surface

In order to improve that analysis and predictions of complex tasks such as material degradation prediction the invention proposes a machine learning model that is suitable for reservoir computing and comprises a computer-implemented input module configured for receiving input data; a plurality of reservoir networks, each reservoir network configured for receving data from the input module and for outputting reservoir state data; and computer-implemented readout module that is configured for receiving the reservoir state data from the reservoirs and for outputting readout data based on the reservoir state data. The reservoir networks can be computer-implemented or physically-implemented and at least one of them may involve a plurality of quibits.

The present invention relates to a monomer, a vitrimer produced using one or more of such monomers, the use of such a vitrimer, as well as a method of manufacturing a vitrimer.

The present invention relates to a compound, a composition comprising one or more of such compounds, a vitrimer produced using one or more of such compounds, the use of such a vitrimer, as well as a method of manufacturing a vitrimer.

L'invention concerne un aéronef, comprenant Aéronef, comprenant un ensemble d'au moins une aile munie d'au moins une structure de propulsion, appelée nacelle, et d'un fuselage, l'ensemble comprenant une zone, dite zone chaude (Zc), comportant des éléments à des températures, dites températures chaudes, supérieures ou égales à une température, dite température de zone chaude (Tc), et une autre zone, dite froide (Zf), comportant des éléments à des températures, dites températures froides, inférieures ou égale à une température, dite température de zone froide, la zone chaude (Zc) et la zone froide (Zf) étant distinctes l'une de l'autre, et la température de zone froide (Tf) étant strictement inférieure à la température de zone chaude (Tc), dans la zone chaude (Zc) se trouvant un système de production d'électricité (7), et dans la zone froide se trouvant au moins un réservoir (9) de stockage de composition de fuel pour alimenter ledit système de production d'électricité, et une unité de propulsion électrique comportant un moteur et une unité de contrôle moteur (MCU) conformé pour être alimenté électriquement par le système de production d'électricité pour produire une poussée.

The present invention relates to a composition, a vitrimer produced using such a composition, the use of such a vitrimer, as well as a method of manufacturing a vitrimer.

L'invention concerne un système de protection électrique pour une liaison électrique d'un circuit électrique d'un aéronef, par exemple un aéronef à propulsion à hydrogène, comprenant un élément, dit élément fusible, réalisé en matériau qui présente des propriétés supraconductrices dans un premier état, dit état supraconducteur, et des propriétés non supraconductrices dans un deuxième état, dit état normal, la transition de l'état supraconducteur à l'état normal dégageant une énergie de transition, le système de protection comprenant également un dispositif, dit dispositif de sécurité, conformé pour ouvrir la liaison électrique lorsque l'élément fusible passe de l'état supraconducteur à l'état normal.

The invention relates to a mobile power train (18) for connecting to a mobile reactor (12) for generating thermal power (14) based on an exothermal reaction triggered by electric power (16) supplied to the reactor (12), the power train (18) including a heat engine (20) for converting thermal energy into mechanical energy and an electric generator device (28) for converting mechanical energy into electric energy and being mechanically connected to the heat engine (20).

- Method and system for determining an optimized set of ink colours used to print a pattern on an object - The method comprises in particular steps implemented by a computer device for defining a plurality of sets of different colours in a colour space (19), each of which consists, on the one hand, of spot colours that make it possible to reproduce one or more sensitive colours (C6, C7) of the reference pattern to be printed continuously and exactly and, on the other hand, of process colours intended to be used to produce colour combinations, so as to be able to obtain all of the colours (C1, C2, C3, C4, C5) of the reference pattern to be printed, other than the one or more sensitive colours (C6, C7), in the livery, and for selecting one of these sets of colours taking into account at least one selection criterion, in order to obtain a set of colours that is optimized in particular in terms of precision and/or ink consumption.

An enhanced device (12) and an enhanced method for active EMI reduction in a power electronic system (10), especially of an aircraft (100) have been described. The device (12) is configured to carry out the method comprising the steps: I) sensing EMI noise and outputting an EMI noise signal (16), II) generating an EMI reduction signal (20) by inverting the EMI noise signal (16), III) amplifying the EMI reduction signal (20) and IV) injecting the amplified EMI reduction signal (20) in the power electronic system (10), wherein step III) is conducted by means of a half bridge with a first power semiconductor and a second power semiconductor which are driven by the EMI reduction signal (20), a) wherein the first and second power semiconductors are operated in a linear operation mode, wherein step II) comprises generating an analogue EMI reduction signal (44) for driving the first and second power semiconductors, or b) wherein, as the first and second power semiconductors, GaN semiconductors (46) are used, wherein step II) comprises generating a digital EMI reduction signal (20) for driving the first and second GaN semiconductors (46).

An aircraft has an energy storage system comprising a first battery 6a comprising first and second battery modules 10, 11. A venting system 7 is provided comprising a first battery module exhaust 18, a second battery module exhaust 19 and a first battery manifold 20 arranged to connect the first and second battery module exhausts to a first flow path extending to an exhaust port 8 of the aircraft. The first battery manifold 20 includes a first valve 28 comprising a first flap 29 having a first position in which fluid flow from one of the first and second battery module exhausts is restricted; a second position in which fluid flow from the other of the first and second battery module exhausts is restricted; and a neutral position in which fluid can flow from both first and second battery module exhausts to the first flow path. The first valve 28 is biassed towards the neutral position. The venting system of the present invention is more lightweight than was hitherto achievable, protects other modules and components of the energy storage system from the heat of gas emissions and reduces pressure losses, so that the emitted gas is more likely to exit the aircraft, typically via a burst disc

L'invention a pour objet un dispositif de régulation de pression d'encre pour une machine d'impression, ledit dispositif comprenant au moins un boîtier (42) rigide, au moins une membrane (44) souple reliée au boîtier (42) de manière étanche afin de délimiter une première cavité (46), au moins une cloison (52) située dans la première cavité (46) et configurée pour générer dans la première cavité (46) au moins un chemin d'écoulement (54) reliant des orifices d'entrée et de sortie (48, 50) de la première cavité (46) ; la membrane (44) étant configurée pour occuper un premier état dans lequel la membrane (44) est distante de ladite au moins une cloison (52) ainsi qu'un deuxième état dans lequel la membrane (44) est en contact avec ladite au moins une cloison (52) de manière à former le chemin d'écoulement (54), au moins un système de commande (56) étant configuré pour contrôler l'état de la membrane (44).

The invention relates to a safety device (10) for an equipment (18) containing potentially flammable and/or potentially explosive media, such as for example a fuel cell (42). The safety device (10) comprises a housing (12) with an internal chamber (20) for encapsulating the equipment. In order to improve the safety device (10) for use on vehicles, especially aircraft, the safety device (10) further comprises a flexible membrane (53) separating a gas-tight volume (55) from the chamber (20) wherein the gas-tight volume (55) is filled during operation with a filling gas (56) differing from the media. In preferred embodiments, the flexible membrane (53) is provided in form of a balloon (54) filled with the filling gas (56) and located within the chamber (20), especially in a top portion (84) of the chamber (20).

The invention relates to a computer-implemented method for managing network communication between interconnected network devices (12, 12a, 12b, 12c) in a network system (10).

Proposed is a method and an apparatus (100) for compressing a neural network. The processing circuitry (110) is configured to receive a neural network comprising a set of parameters being in at least one floating-point number format of a first precision. Further, the processing circuitry (110) is configured to apply at least one mathematical model on the neural network to determine errors introduced by using arithmetic of a second precision lower than the first precision and propagation through network layers of the neural network due to using the arithmetic of the second precision instead of the first precision. The processing circuitry (110) is further configured to apply a solver to an optimization problem formulated based on the errors determined by the at least one mathematical model to determine a set of optimized parameters. Further, the processing circuitry (110) is configured to compress the neural network based on the set of optimized parameters to output a compressed neural network.

- Procédé et dispositif informatique pour transformer un maillage texturé d'un objet conçu en un maillage texturé d'un objet fabriqué correspondant audit objet conçu.- Le procédé pour déterminer un maillage texturé transformé (M2) d'un objet fabriqué (O2) tridimensionnel à partir d'un maillage texturé initial (M1) d'un objet conçu (O1) tridimensionnel, le maillage texturé transformé (M2) étant destiné à être utilisé lors de l'impression d'une texture bidimensionnelle (T) correspondante sur l'objet fabriqué (O2), met en œuvre un traitement itératif pour déterminer un jeu de transformations affines à paramètres individualisés permettant de minimiser la valeur d'une fonction cible comprenant au moins un terme favorisant une propriété spécifique, le jeu de transformations affines ainsi déterminé étant appliqué aux sommets du maillage texturé initial (M1) de manière à obtenir le maillage texturé transformé (M2), ledit procédé étant relativement simple à mettre en œuvre et particulièrement avantageux.

A sensor system (10) for monitoring characteristics of a dewar tank (20) having an inner shell (21) and an outer shell (22) is provided. The sensor system (10) comprises a sensor arrangement (16) comprising a first magnetic field sensor (11), and a first permanent magnet element (12), and a controller (13). The first magnetic field sensor (11) is connected to the controller (13). The first magnetic field sensor (11) is configured to be attached to the outer shell (22) of the dewar tank (20). The first permanent magnet element (12) is configured to be attached to the inner shell (21) or to the outer shell (22) of the dewar tank (20). The first magnetic field sensor (11) and the first permanent magnet element (12), in a mounted state on the dewar tank (20), are configured to be located in the vicinity of each other, such that the magnetic field sensor (11) is capable of detecting a magnetic field created by the first permanent magnet element (12). The controller (13) is configured to measure, via the first magnetic field sensor (11), the magnetic field of the first permanent magnet element and to infer at least one characteristic of the dewar tank (20) based on the detected magnetic field of the first permanent magnet element (12).

A protection arrangement (10), an energy storage device (2), in particular an electrochemical battery for an apparatus (1), and an apparatus (1), in particular, a vehicle, such as an aircraft, are provided, wherein for protecting the energy storage device (2), such as an electrochemical battery in the event of a technical failure (F) of at least one energy storage unit (20) of the energy storage device (2), the protecting arrangement (10) comprises a discharging circuit (13) with a switching device (15) configured to reduce an electrical charging level of the at least one energy storage unit (20) by electrically closing the discharging circuit (13) upon detection of the technical failure (F).

Un moteur supraconducteur comporte un rotor, un stator et un boîtier moteur. Le boitier moteur comporte une chambre commune (300) mise au vide et incluant plusieurs compartiments hermétiques (302, 302a, 302b) qui sont aussi mis au vide, chaque compartiment hermétique (302, 302a, 302b) enfermant une ou plusieurs bobines (304, 304a, 304b) du stator, de sorte que la ou les bobines (304, 304a, 304b) que chaque compartiment hermétique (302, 302a, 302b) renferme est isolée thermiquement par deux couches de vide, une première couche de vide (305, 305a, 305b) dans le compartiment hermétique (302, 302a, 302b) en question et une deuxième couche de vide (301) dans la chambre commune (300). Ainsi, d'éventuelles particules qui pourraient se détacher d'une bobine défaillante n'endommagent pas la barrière d'isolation thermique de toute autre bobine qui serait logée dans un autre compartiment.

Le système comprend un système de gestion de vol (14) et un système anticollision (20) installés à bord de l'aéronef, ainsi qu'un transpondeur (38) installé à une position prédéfinie sur l'aéroport et relié à un calculateur (40) d'un centre de contrôle aérien (34). Le transpondeur (38) est configuré pour recevoir des informations environnementales transmises par ledit calculateur (40). Le système anticollision (20) est configuré pour interroger le transpondeur (38), pour recevoir en réponse lesdites informations environnementales et pour déterminer une position du transpondeur. L'un du système anticollision (20) ou du système (14) de gestion de vol est configuré pour comparer la position du transpondeur déterminée par le système anticollision avec une position théorique enregistrée à bord de l'aéronef de façon à authentifier les informations environnementales reçues uniquement si la position déterminée correspond à la position théorique. Le système de gestion de vol (14) est configuré pour commander une trajectoire de vol de l'aéronef en fonction des informations environnementales reçues lorsqu'elles sont authentifiées.

Un moteur supraconducteur (100) comporte un rotor (102) portant des aimants permanents (112) et mobile en rotation autour d'un axe longitudinal, un stator (103) portant des bobines (113) destinées à être alimentées électriquement pour générer un champ magnétique entraînant en rotation le rotor grâce aux aimants permanents et un boîtier moteur (120). Le boitier moteur comporte plusieurs compartiments (126) hermétiques les uns par rapport aux autres. Chaque compartiment (126) enfermant une ou plusieurs bobines (113) du stator (103). Chaque compartiment (126) étant mis au vide afin de former une barrière d'isolation thermique pour la ou les bobines (113) que le compartiment (126) en question renferme. Ainsi, d'éventuelles particules qui pourraient se détacher d'une bobine défaillante n'endommagent pas la barrière d'isolation thermique de toute autre bobine qui serait logée dans un autre compartiment.

A filling level monitoring device (100) for monitoring a filling level (210) of a fluid container (200) is provided that includes an exciting element (10), a sensing element (21), a signal source (30), a suspension element (70) with a defined stiffness, and a processing unit (40). The exciting element (10) is configured to mount on the fluid container (200) or suspension element (70) to activate a specific suspension mode (25) of vibration. The suspension element (70) attaches rigidly to the fluid container (200) so that both vibrate together. The sensing element (21) detects these vibrations and sends data to the processing unit (40). The signal source (30) generates a multi-frequency input signal (31) for the exciting element (10). The processing unit (40) uses the vibration data to identify the suspension mode (25), determine its modal frequency (80), and calculate the fluid container's (200) current filling level (210) based on this frequency.

A method (200) for manufacturing an electrolyte-supported fuel cell structure (100) is provided. The method (200) includes providing (210) a continuous electrolyte layer (110) with a first side (111) and a second side (112), coating (221) the first side (111) with an anode material (121) to form a continuous anode layer (120), and coating (222) the second side (112) with a cathode material (131) to form a continuous cathode layer (130). Portions of the anode layer (120) and cathode layer (130) are removed (231, 232) via laser ablation, creating separated anode and cathode sections. Through holes (113) are created (240) in the electrolyte layer (110) coinciding with areas where the anode or cathode layers have been removed. Conductive material (160) is arranged in the through holes to connect anode and cathode sections, thereby forming a serial connection between corresponding fuel cell segments.

A method (200) for manufacturing a fuel cell structure (100) is provided. The method (200) comprises providing (210) a continuous support layer (110) with a first and second side (111, 112), depositing (220) a continuous first electrode layer (120) of a first electrode material (121) onto the first side (111), removing (230) portions (124) of the first electrode layer (120), leaving individual sections (122, 123) side-by-side, depositing (240) a continuous electrolyte layer (140) above the first electrode layer (120), removing (250) portions (144) of the electrolyte layer (140) coincident with the removed first electrode sections (122, 123), depositing (260) a continuous second electrode layer (130), removing (270) portions (134) of the second electrode layer (130) coincident with the removed sections of the previous layers (120, 140), and depositing (280) an electrically conductive material (150) within the created cavities, electrically interconnecting in series adjacent sections of the first and second electrode layers (120, 130) via the conductive material (150).

The present invention relates to a method for bonding a conductive member to a substrate providing a conductive path in aircraft components. The method comprises providing a substrate comprising a top layer with a primary conductive member, providing a secondary conductive member on the top layer, providing a surface structured layer between the primary conductive member and the secondary conductive member, bonding the secondary conductive member to the top layer by means of the surface structured layer to conductively couple the primary conductive member and the secondary conductive member. Also disclosed is a conductive component comprising materially and conductively bonded primary and secondary conductive members.

A method, control program (11), computer-readable data carrier (12), control unit (24), communication system (1) and a corresponding apparatus (7) are provided, configuring a network structure (N) of a communication system (1) for providing a data connection (C) to transfer a data object (D) between a sender (A) and at least one receiver (B), in particular a vehicle (1), such as an aircraft, via at least one routing path (R) provided by network nodes (O) of the network structure (N), the method comprising the steps of assigning a global number (k) of network nodes (O) of the network structure (N) to a global domain (K) being controlled by a global controller (H); providing a global model of the global domain (K) based on routing parameters representing routing capabilities associated to the network nodes (O) assigned to the global domain (K); assigning a local number (I) of respective network nodes (O) assigned to the global domain (K) as subsets of the global number (k) to at least two local domains (L) each being controlled by a respective local controller (J); and providing respective local models of the local domains (L) based on routing parameters representing routing capabilities associated to the network nodes (O) assigned to each of the local domains (L); wherein the global controller (H) interacts with the local controllers (J) to identify at least one of the network nodes (O) which according to the global model and/or the local models provides routing capabilities allowing the at least one network node (O) to serve as a local proxy (P) enabling to place the data object (D) along the at least one routing path (R) such that it can be provided to the receiver (B) from the local proxy (P).

L'invention concerne un moteur électrique (1) de roue d'aéronef (1000) comprenant un alésage traversant et des couronnes concentriques de pôles (P) permettant d'obtenir un couple capable d'opérer un roulage de l'aéronef tout en conservant un encombrement semblable aux solutions conventionnelles. L'invention concerne également une roue d'aéronef comprenant un tel moteur (1), un ensemble de commande de roue d'aéronef, et un aéronef (1000).Avantageusement il est ainsi possible d'utiliser une roue électrique d'aéronef à la place d'une roue conventionnelle, et ce sans modification substantielle des trains de l'aéronef.

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …