Airbus Operations Limited

Royaume‑Uni

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        États-Unis 874
        International 369
        Canada 7
Propriétaire / Filiale
[Owner] Airbus Operations Limited 1 153
Airbus UK Limited 97
Date
Nouveautés (dernières 4 semaines) 7
2024 mars (MACJ) 2
2024 février 6
2024 janvier 4
2023 décembre 8
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Classe IPC
B64C 3/18 - Longerons; Nervures; Lisses 119
B64C 23/06 - Moyens permettant d'influencer l'écoulement d'air sur les surfaces des aéronefs, non prévus ailleurs par génération de tourbillons 105
B64C 3/56 - Repliage ou rabattement pour réduire l'encombrement de l'aéronef 79
B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact 76
B64C 3/26 - Construction, forme ou fixation des revêtements distincts, p.ex. panneaux 71
Voir plus
Statut
En Instance 223
Enregistré / En vigueur 1 027
Résultats pour  brevets
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1.

RECOVERING FUEL VAPOUR FROM AIRCRAFT FUEL TANK

      
Numéro d'application 18470763
Statut En instance
Date de dépôt 2023-09-20
Date de la première publication 2024-03-21
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s)
  • Gadd, Matthew
  • Fallon, Adam

Abrégé

A method of recovering fuel vapour from a fuel tank of an aircraft, is disclosed. The aircraft includes a fuel tank; a wing with an upper surface and a lower surface; and an opening in the lower surface of the wing. The method includes coupling an inlet of a vapour recovery system to the opening; capturing fuel vapour from the fuel tank which flows out of the opening with the inlet of the vapour recovery system; and collecting the captured fuel vapour in a vapour storage tank of the vapour recovery system.

Classes IPC  ?

  • B64D 37/34 - Conditionnement du carburant, p.ex. réchauffage

2.

TYRE MONITOR

      
Numéro d'application 18257701
Statut En instance
Date de dépôt 2021-12-15
Date de la première publication 2024-03-14
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s) Bill, Andrew

Abrégé

A tyre monitor is disclosed including a sensor device configured to operate within an enclosed space formed by the wheel and the tyre, and an energy harvester unit. The energy harvester is arranged to convert a first type of energy experienced by the harvester unit in use (e.g. mechanical energy, thermal energy) into electrical energy to energise the sensor device. The energy harvester may be, for example, a piezoelectric device or a thermoelectric generator. In use, mechanical stresses experienced by the tyre monitor are converted into electrical energy which can be used to energise the sensor as a supplement to energy from the battery within the tyre monitor, thus prolonging its service life.

Classes IPC  ?

  • B60C 23/04 - Dispositifs avertisseurs actionnés par la pression du pneumatique montés sur la roue ou le pneumatique

3.

AIRCRAFT ATTITUDE CONTROLLER AND WING SYSTEM

      
Numéro d'application 18454552
Statut En instance
Date de dépôt 2023-08-23
Date de la première publication 2024-02-29
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s) Liberson, Alexis Anthony

Abrégé

An aircraft attitude controller configured to obtain information representative of an attitude of an aircraft is disclosed. On the basis of the information, the attitude controller is configured to control the attitude of the aircraft by actively controlling a position of a winglet at a distal end of a wing portion of a wing of the aircraft, relative to the wing portion, thereby to control an angle of incidence of the winglet.

Classes IPC  ?

  • G05D 1/08 - Commande de l'attitude, c. à d. élimination ou réduction des effets du roulis, du tangage ou des embardées
  • B64C 3/38 - Réglage des ailes complètes ou de certaines parties de ces ailes

4.

AIRCRAFT ARRANGEMENT

      
Numéro d'application 18455252
Statut En instance
Date de dépôt 2023-08-24
Date de la première publication 2024-02-29
Propriétaire
  • AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
  • Imperial College Innovations Limited (Royaume‑Uni)
Inventeur(s)
  • Muir, Martin
  • Hewson, Robert W.
  • Santer, Matthew
  • Nightingale, Morgan D.

Abrégé

An aircraft arrangement is provided, the aircraft arrangement including a first aircraft component for converting at least one input vibration into an output vibration suitable for driving an energy harvester, and an energy harvester coupled to the first aircraft component and configured to generate electrical energy in response to the output vibration of the first aircraft component, the first aircraft component including a three-dimensional lattice structure including a multiplicity of unit cells, the unit cells including multiple lattice-forming members, the unit cells having a mean greatest dimension of at least 10 nm.

Classes IPC  ?

  • H02N 2/18 - Machines électriques en général utilisant l'effet piézo-électrique, l'électrostriction ou la magnétostriction fournissant une sortie électrique à partir d'une entrée mécanique, p.ex. générateurs
  • B64D 41/00 - Installations génératrices de puissance pour servitudes auxiliaires

5.

FAIRING FOR FOLDING WING TIP

      
Numéro d'application 18458814
Statut En instance
Date de dépôt 2023-08-30
Date de la première publication 2024-02-29
Propriétaire Airbus Operations Limited (Royaume‑Uni)
Inventeur(s)
  • Family, Oliver
  • Mills, Robert
  • Gray, Christopher
  • Wilson, Thomas

Abrégé

An aircraft wing is disclosed having a main fixed wing portion and a wing tip device at a tip thereof. The wing tip device is configurable between a flight configuration and a ground configuration, in which ground configuration the wing tip device is moved away from the flight configuration such that the span of the aircraft wing is reduced. A hinge arrangement connects the main fixed wing portion and the wing tip device and enables the wing tip device to rotate between the ground configuration and the flight configuration. The hinge arrangement protrudes beyond an outer surface of the main fixed wing portion and wing tip device. A fairing covers at least part of the hinge arrangement on at least a suction side of the wing.

Classes IPC  ?

  • B64C 3/56 - Repliage ou rabattement pour réduire l'encombrement de l'aéronef
  • B64C 23/06 - Moyens permettant d'influencer l'écoulement d'air sur les surfaces des aéronefs, non prévus ailleurs par génération de tourbillons

6.

TYRE MONITORING DEVICE CONFIGURATION

      
Numéro d'application 18386171
Statut En instance
Date de dépôt 2023-11-01
Date de la première publication 2024-02-22
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s) Bill, Andrew

Abrégé

A method of configuring a tire monitoring device including, at the tire monitoring device: entering a configuration mode; responsive to entering the configuration mode, transmitting a first message to a second device, the message indicating that the second device should transmit configuration data to the tire monitoring device; receiving configuration data from the second device in response to the first message; and configuring the tire monitoring device based on the configuration data.

Classes IPC  ?

  • B60C 23/04 - Dispositifs avertisseurs actionnés par la pression du pneumatique montés sur la roue ou le pneumatique

7.

METHOD AND APPARATUS FOR CONTROLLING AIRCRAFT GROUND MANOEUVRES

      
Numéro d'application 18450223
Statut En instance
Date de dépôt 2023-08-15
Date de la première publication 2024-02-22
Propriétaire Airbus Operations Limited (Royaume‑Uni)
Inventeur(s)
  • Bidmead, Ashley
  • Johnson, Mark

Abrégé

An aircraft is disclosed including a ground manoeuvre control unit for automatically controlling ground manoeuvres. The aircraft has control mechanisms such as a rudder, nose wheel steering, spoilers, wheel brakes and the like for controlling motion of the aircraft. The control unit is configured to receive lateral input demands concerning lateral motion of the aircraft (e.g. heading control) and longitudinal input demands concerning longitudinal motion of the aircraft (e.g. deceleration). The control unit passes on the input demands as output demands to the relevant control mechanisms of the aircraft with, if so required, a modification which prioritises one of the lateral input demand and longitudinal input demand based on the risk of a lateral runway excursion and the risk of a longitudinal runway excursion.

Classes IPC  ?

  • G08G 5/06 - Systèmes de commande du trafic aérien pour la commande lorsque l'appareil est au sol
  • B64C 25/50 - Atterrisseurs orientables; Amortissement du shimmy
  • G08G 5/00 - Systèmes de commande du trafic aérien
  • B64C 25/32 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue

8.

WHEEL ASSEMBLY SENSOR APPARATUS

      
Numéro d'application 18257823
Statut En instance
Date de dépôt 2021-12-16
Date de la première publication 2024-02-15
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s) Bill, Andrew

Abrégé

A sensor apparatus for measuring a property of a wheel assembly is disclosed including at least one sensor configured to acquire measurement data; and a mounting member attached to the at least one sensor. The mounting member is configured to engage with a wheel such as to retain the sensor on the wheel within an enclosed space formed by the wheel and a tire mounted on the wheel. The mounting member is further configured to enable the sensor to move around the circumference of the wheel when the mounting member is engaged with the wheel.

Classes IPC  ?

  • B60C 23/06 - Dispositifs avertisseurs actionnés par la déformation du pneumatique
  • B60C 23/04 - Dispositifs avertisseurs actionnés par la pression du pneumatique montés sur la roue ou le pneumatique

9.

TYRE MONITOR

      
Numéro d'application 18257771
Statut En instance
Date de dépôt 2021-12-15
Date de la première publication 2024-02-15
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s) Bill, Andrew

Abrégé

A tire monitor 11 includes a sensor device 12 arranged to detect an operating parameter of a tire and a protective housing 14 for the device, the device being retained on a ring 15 having spaced end portions 16a, 16b, the ring being resiliently radially biased. The provision of a retaining ring facilitates installation of the tire monitor within a tire assembly, so that the sensor device can directly monitor the operating parameter of the tire. The protective housing protects the sensor device from impact, vibration and temperature extremes.

Classes IPC  ?

  • B60C 23/04 - Dispositifs avertisseurs actionnés par la pression du pneumatique montés sur la roue ou le pneumatique

10.

SENSOR FOR WHEEL ASSEMBLY

      
Numéro d'application 18258163
Statut En instance
Date de dépôt 2021-12-16
Date de la première publication 2024-02-15
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s) Bill, Andrew

Abrégé

A sensor device for use in determining at least one property of a wheel assembly including a tire mounted on a wheel. The sensor device is configured to be attachable to an outer circumferential surface of the wheel which faces an inner circumferential surface of the tire. The sensor device is configured to measure a distance between the sensor device and an object remote from the sensor device.

Classes IPC  ?

  • B60C 23/04 - Dispositifs avertisseurs actionnés par la pression du pneumatique montés sur la roue ou le pneumatique
  • B60C 11/24 - Aménagements pour indiquer l'usure
  • B60C 23/20 - Dispositifs pour mesurer ou signaler la température des pneumatiques

11.

AIRCRAFT COMPONENT SELECTION

      
Numéro d'application 18359473
Statut En instance
Date de dépôt 2023-07-26
Date de la première publication 2024-02-01
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s)
  • Howell, George
  • Cooper, Jonathan

Abrégé

Computer-implemented methods and systems for selecting components to be used in an aircraft system including: a reliability evaluation function, to produce a reliability score, and a complexity evaluation function, to produce a complexity score, are provided; and a multi-objective optimisation function is performed to determine at least one set of candidate components for the aircraft system that satisfy one or more conditions. The multi-objective optimisation function includes selecting a new set of candidate components, performing at least one of the reliability evaluation function and the complexity evaluation function, and evaluating at least one of the reliability score and the complexity score according to the conditions. The new set of candidate components are stored in associated with an indication of the outcome of the evaluation. An aircraft comprising a set of components that have been selected from one or more of the stored sets of components is also provided.

Classes IPC  ?

  • G06F 30/15 - Conception de véhicules, d’aéronefs ou d’embarcations

12.

AIRCRAFT TEST SYSTEM

      
Numéro d'application 18347336
Statut En instance
Date de dépôt 2023-07-05
Date de la première publication 2024-01-25
Propriétaire
  • Airbus Operations Limited (Royaume‑Uni)
  • Airbus Operations (S.A.S) (France)
Inventeur(s)
  • Howell, George
  • Au, Ting Yu
  • Cooper, Jonathan
  • Perez, Asier
  • Capelleras Magana, Laura
  • Scott, David James
  • Gudimella, Sushmita

Abrégé

A test apparatus and method for testing a trained classifier configured to control an aircraft system. Scenario data includes operating inputs representing an operational state of an aircraft and classifier outputs for controlling the aircraft system, is obtained. Model data representing a model of the at aircraft system is obtained. Error categorisation data for each aircraft operating scenario is generated based on respective classifier outputs applied to the model.

Classes IPC  ?

  • B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
  • B64C 25/42 - Aménagement ou adaptation des freins
  • G06N 20/00 - Apprentissage automatique

13.

HEAT EXCHANGER

      
Numéro d'application 18354555
Statut En instance
Date de dépôt 2023-07-18
Date de la première publication 2024-01-25
Propriétaire
  • AIRBUS OPERATIONS, S.L.U. (Espagne)
  • AIRBUS OPERATIONS LTD (Royaume‑Uni)
  • AIRBUS DEFENCE AND SPACE GMBH (Allemagne)
Inventeur(s)
  • Martino González, Esteban
  • Linares Villegas, Mario
  • Bayona Revilla, Lucía
  • Milbourn, Gareth
  • Jullien, David
  • Carretero Benignos, Jorge

Abrégé

A heat exchanger module including: a hollow chamber having an inner volume configured through which flows a first fluid in fluidic communication with a source of the first fluid, and a fluid outlet; a hollow enclosure extending outwardly from a surface of the hollow chamber wherein the hollow enclosure includes an inner volume through which flows a second fluid that undergoes a phase change in an operative mode of the heat exchanger module, wherein the hollow enclosure is in fluidic communication with a source of the second fluid, and an enclosure root of the hollow enclosure is inserted in the hollow chamber extending into the inner volume such that in an operative mode a second fluid flowing through the hollow chamber from the inlet to the outlet bathes the outer surface of said enclosure root.

Classes IPC  ?

  • F28D 9/00 - Appareils échangeurs de chaleur comportant des ensembles de canalisations fixes en forme de plaques ou de laminés pour les deux sources de potentiel calorifique, ces sources étant en contact chacune avec un côté de la paroi d'une canalisation
  • F28F 3/02 - Eléments ou leurs ensembles avec moyens pour augmenter la surface de transfert de chaleur, p.ex. avec des ailettes, avec des évidements, avec des ondulations

14.

AIRCRAFT WING TRAILING EDGE DEVICE

      
Numéro d'application 18352033
Statut En instance
Date de dépôt 2023-07-13
Date de la première publication 2024-01-18
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s) Family, Oliver

Abrégé

An aircraft wing is disclosed having a trailing edge system including a pivotable spoiler and a moveable flap. The flap has a pivotable trailing edge device, which is for example able to rotate independently of the flap by up to +/−20 degrees. The flap is translatable and rotatable relative to the wing independently of the movement of the spoiler. The trailing edge system is configured to adopt one of several different configurations or modes of operation facilitating all of camber and/or wing chord change during cruise, high speed and low speed roll control mode, enhanced high lift, and load alleviation. As such, the wing may not need any separate ailerons or other trailing edge control surfaces, and may also offer improved aerodynamics, reduced drag and other efficiency improving benefits.

Classes IPC  ?

  • B64C 9/18 - Surfaces ou éléments de commande réglables, p.ex. gouvernes de direction formant des fentes à l'arrière de l'aile par volet unique

15.

STRUCTURE WITH LIGHTNING-STRIKE PROTECTION LAYER

      
Numéro d'application 18347844
Statut En instance
Date de dépôt 2023-07-06
Date de la première publication 2024-01-11
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s) Thompson, Sam

Abrégé

A structure is disclosed including a laminate having layers of fibre-reinforced composite material; and a lightning-strike protection (LSP) layer. The LSP layer has an outer face and an inner face opposite to the outer face. A connector has an LSP connection surface which overlaps with, and is electrically connected to, the inner or outer face of the LSP layer. A bore passes through the LSP layer, the laminate and the connector. A fastener secures together the structure to a second structure. Therein the fastener is received in the bore and the connector electrically connects the LSP layer to the fastener.

Classes IPC  ?

  • B32B 7/08 - Liaison entre couches par des moyens mécaniques
  • B32B 5/02 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par les caractéristiques de structure d'une couche comprenant des fibres ou des filaments
  • B32B 3/26 - Produits stratifiés caractérisés essentiellement par le fait qu'une des couches comporte des discontinuités ou des rugosités externes ou internes, ou bien qu'une des couches est de forme générale non plane; Produits stratifiés caractérisés essentiellement par des particularismes de forme caractérisés par une couche comportant des cavités ou des vides internes
  • B32B 7/12 - Liaison entre couches utilisant des adhésifs interposés ou des matériaux interposés ayant des propriétés adhésives
  • B32B 38/18 - Manipulation des couches ou du stratifié
  • B32B 5/26 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par la présence de plusieurs couches qui comportent des fibres, filaments, grains ou poudre, ou qui sont sous forme de mousse ou essentiellement poreuses une des couches étant fibreuse ou filamenteuse un autre couche également étant fibreuse ou filamenteuse
  • B32B 15/14 - Produits stratifiés composés essentiellement de métal adjacent à une couche fibreuse ou filamenteuse
  • B64D 45/02 - Dispositifs de protection contre la foudre; Déperditeurs de potentiel

16.

DOOR FAIRING FOR AN AIRCRAFT LANDING GEAR LEG

      
Numéro d'application 18332328
Statut En instance
Date de dépôt 2023-06-09
Date de la première publication 2023-12-21
Propriétaire Airbus Operations Limited (Royaume‑Uni)
Inventeur(s)
  • Chasteau, Dominique
  • Barsali, Guilherme

Abrégé

A door fairing for a retractable landing gear leg of an aircraft is disclosed having an outer member which covers a portion of a landing gear bay of the aircraft when the landing gear leg is retracted. An inner member of the door fairing is coupled to the outer member via a number of configurable couplings which allow adjustment of the position of the outer member with respect to the inner member. The inner member has mounting points for mounting the door fairing to the landing gear leg. Prior to fitting the door fairing at the aircraft, measured or derived dimensional parameters of the landing gear bay are used to adjust the configurable couplings such that the door fairing is preconfigured to fit the landing gear bay of the aircraft.

Classes IPC  ?

  • B64C 25/16 - Carénages mobiles en liaison avec des éléments de l'atterrisseur

17.

AIRCRAFT LANDING GEAR

      
Numéro d'application 18337897
Statut En instance
Date de dépôt 2023-06-20
Date de la première publication 2023-12-21
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s)
  • Wilson, Fraser
  • Bishop, Benjamin

Abrégé

A trailing link landing gear (6) has a main arm (20) which extends from a proximal end (22) attachable to an aircraft (2) to a distal end (24), and a trailing arm (30) which extends from a pivotable connection at the distal end (24) of the main arm (20) to one or more wheels (39). A shock absorber (40) extends between the main arm (20) and the trailing arm (30). An adjustment member (50) mounted to one of the arms can be moved to move an end of the shock absorber (40) and thereby change the angle that the trailing arm (30) makes with the main arm (20). This, in turn, changes the height of the landing gear (6) and in doing so changes the angle of attack (10) of an aircraft (2) including the landing gear (6).

Classes IPC  ?

  • B64C 25/22 - Mécanismes de manœuvre à fluide
  • B64C 25/62 - Amortisseurs à ressorts; Ressorts
  • B64C 25/34 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue du type à roues, p.ex. bogies à roues multiples

18.

AIRCRAFT

      
Numéro d'application 18127485
Statut En instance
Date de dépôt 2023-03-28
Date de la première publication 2023-12-21
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s) Sakota, Nebojsa

Abrégé

An aircraft is disclosed including a fuel tank for storing liquid hydrogen, an aircraft power plant and/or an aircraft refuelling port, and a hydrogen fuel line extending from a first end to a second end, the first end at the fuel tank and the second end at one of the aircraft power plant and the aircraft refuelling port. The hydrogen fuel line is rigidly continuous and substantially unconstrained along an axial direction of the hydrogen fuel line between the first end and the second end. The first and/or second end is moveable in the axial direction of the hydrogen fuel line.

Classes IPC  ?

  • B64D 37/16 - Systèmes de remplissage
  • B64D 37/30 - Circuits de carburant pour carburants particuliers

19.

AN AIRCRAFT ASSEMBLY

      
Numéro d'application GB2023051549
Numéro de publication 2023/242565
Statut Délivré - en vigueur
Date de dépôt 2023-06-14
Date de publication 2023-12-21
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s)
  • Phillips, Samuel
  • Bryant, Anthony

Abrégé

An aircraft assembly (25) comprising: a wing structure; and a pipe assembly (30a, 30b) rotatably coupled to the wing structure by a fixture arrangement (25), the pipe assembly extending along a longitudinal direction, the fixture arrangement configured to restrict movement of at least a portion of the pipe assembly in the longitudinal direction relative to the wing structure and allow rotation of the pipe assembly relative to the wing structure.

Classes IPC  ?

  • B64D 37/00 - Aménagements relatifs à l'alimentation des groupes moteurs en carburant
  • B64D 37/30 - Circuits de carburant pour carburants particuliers
  • F16L 39/04 - Raccords ou accessoires de raccordement pour tuyaux à double paroi ou à canaux multiples ou pour assemblages de tuyaux permettant réglage ou déplacement
  • F16L 39/00 - Raccords ou accessoires de raccordement pour tuyaux à double paroi ou à canaux multiples ou pour assemblages de tuyaux
  • F16L 27/04 - Raccords universels, c. à d. avec une liaison mécanique permettant un mouvement angulaire ou un réglage des axes des parties raccordées dans une direction quelconque avec surfaces de contact partiellement sphériques
  • F16L 3/16 - Supports pour tuyaux, pour câbles ou pour conduits de protection, p.ex. potences, pattes de fixation, attaches, brides, colliers avec disposition particulière permettant au tuyau de bouger

20.

AN AIRCRAFT ASSEMBLY

      
Numéro d'application 18127333
Statut En instance
Date de dépôt 2023-03-28
Date de la première publication 2023-12-21
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s) Sakota, Nebojsa

Abrégé

An aircraft assembly is disclosed including an aircraft panel, a channel attached to the aircraft panel, a fuel line for carrying cryogenic fuel, the fuel line disposed in the channel, and a sealed containment space around the fuel line for containing cryogenic fuel leaked from the fuel line, the containment space defined between the channel, the fuel pipe, and the aircraft panel.

Classes IPC  ?

  • B64D 37/30 - Circuits de carburant pour carburants particuliers
  • B64D 37/32 - Mesures de sécurité non prévues ailleurs, p.ex. contre les explosions
  • B64C 3/26 - Construction, forme ou fixation des revêtements distincts, p.ex. panneaux

21.

AN AIRCRAFT ASSEMBLY

      
Numéro d'application GB2023051547
Numéro de publication 2023/242564
Statut Délivré - en vigueur
Date de dépôt 2023-06-14
Date de publication 2023-12-21
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s)
  • Phillips, Samuel
  • Bryant, Anthony

Abrégé

An aircraft assembly comprising: a rib (10) of a wing; an aperture (11) in the rib; a pipe assembly (30a, 30b) extending through the aperture, the pipe assembly comprising a first rigid pipe section (30a), a second rigid pipe section (30b) and a flexible pipe section (33) between the first and second rigid pipe sections; and a fixture arrangement (25) that couples one of the pipe sections to the wing rib (10), wherein the flexible pipe section (33) is located at a plane of the rib and configured to allow relative movement between the first rigid pipe section and the second rigid pipe section. [Figure 5]

Classes IPC  ?

  • F16L 27/10 - Raccords réglables; Raccords permettant un déplacement des parties raccordées comportant uniquement une connexion flexible
  • B64C 3/34 - Réservoirs fabriqués intégralement avec les ailes, p.ex. de carburant ou d'eau
  • F16L 5/00 - Dispositifs utilisés pour le passage des tuyaux, des câbles ou des conduits de protection au travers des murs ou des cloisons
  • B64D 37/00 - Aménagements relatifs à l'alimentation des groupes moteurs en carburant
  • B64D 37/30 - Circuits de carburant pour carburants particuliers

22.

AIRCRAFT SYSTEM, AIRCRAFT FUEL SYSTEM AND METHOD

      
Numéro d'application 18333324
Statut En instance
Date de dépôt 2023-06-12
Date de la première publication 2023-12-14
Propriétaire Airbus Operations Limited (Royaume‑Uni)
Inventeur(s)
  • Thorner, Callum
  • James, Dylan Benedict
  • Savin, David

Abrégé

An aircraft system for handling cryogenic liquid. The aircraft system comprises a vessel configured to store cryogenic liquid, a vacuum ejector operable to cause at least some of the cryogenic liquid to be moved from the vessel, and a pump downstream of the vacuum ejector, wherein the vacuum ejector is fluidically connected to the pump.

Classes IPC  ?

  • B64D 37/30 - Circuits de carburant pour carburants particuliers
  • B64D 37/34 - Conditionnement du carburant, p.ex. réchauffage

23.

FLOW CONTROL DEVICE

      
Numéro d'application 18250195
Statut En instance
Date de dépôt 2021-09-29
Date de la première publication 2023-12-07
Propriétaire
  • AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
  • THE UNIVERSITY OF BRISTOL (Royaume‑Uni)
Inventeur(s)
  • Cosentino, Enzo
  • Llewellyn-Jones, Catherine
  • Arena, Gaetano
  • Groh, Rainer
  • Pirrera, Alberto

Abrégé

A flow control device on a structure such that strain in the structure is at least partially transferred to the flow control device is disclosed having at least two states, or shapes, separated by an elastic instability region. The flow control device is arranged to rapidly transition, or snap through, from the first state to the second state when strain in the structure exceeds an activation threshold of the flow control device. A spoiler on an aerofoil has a rest position where it is substantially flush with the low pressure surface and an activated position where it protrudes from the low pressure surface and modifies the airflow over that surface. The spoiler bends to move from the rest position to the activated position when the strain in the aerofoil crosses a threshold. The deployed spoiler reduces the lift on the aerofoil, acting to reduce the lift induced strain of the aerofoil to which the spoiler is attached.

Classes IPC  ?

  • B64C 3/44 - Variation de la courbure
  • B64C 23/06 - Moyens permettant d'influencer l'écoulement d'air sur les surfaces des aéronefs, non prévus ailleurs par génération de tourbillons
  • B64C 3/58 - Voilures comportant des barrières de couche limite ou des destructeurs de portance (spoilers)
  • B64C 3/14 - Profil de la surface portante
  • B64C 3/26 - Construction, forme ou fixation des revêtements distincts, p.ex. panneaux

24.

METHOD OF MANUFACTURING AIRCRAFT AEROFOIL

      
Numéro d'application 18249010
Statut En instance
Date de dépôt 2021-10-07
Date de la première publication 2023-11-30
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s)
  • Barnett, Thomas
  • Proudler, Lee

Abrégé

A method of manufacturing an aircraft aerofoil such as a winglet. The aircraft aerofoil includes: a first cover, a second cover, an aerofoil leading edge, and an aerofoil trailing edge where the first and second cover are joined at a trailing edge interface. The first cover is formed by: a lay-up step in which a plurality of fibre plies are laid up to obtain a preform, wherein the preform has a thickness and a preform trailing edge, and the preform is laid up during the lay-up step with a ramp of decreasing thickness where the thickness of the preform decreases towards the preform trailing edge; and a curing step in which the preform is cured to form the first cover, wherein the ramp of decreasing thickness cures during the curing step to form a contact surface of the first cover.

Classes IPC  ?

  • B29C 70/30 - Façonnage par empilage, c.à d. application de fibres, de bandes ou de feuilles larges sur un moule, un gabarit ou un noyau; Façonnage par pistolage, c.à d. pulvérisation de fibres sur un moule, un gabarit ou un noyau
  • B64F 5/10 - Fabrication ou assemblage d’aéronefs, p.ex. gabarits à cet effet

25.

AIRCRAFT LANDING GEAR ASSEMBLY

      
Numéro d'application 18323099
Statut En instance
Date de dépôt 2023-05-24
Date de la première publication 2023-11-30
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s) Barsali, Guilherme

Abrégé

A retractable landing gear assembly for an aircraft is disclosed having a main strut arranged to pivot between a retracted position and an extended position, and a sidestay having an unfolded position and a folded position. A telescopic actuator is coupled between the main strut and the sidestay, so that when the actuator has a first length the sidestay locks the main strut in the extended position, and when the actuator has a second length the sidestay is in the folded position and the main strut is in the retracted position.

Classes IPC  ?

  • B64C 25/12 - Atterrisseurs non fixes, p.ex. largables escamotables, repliables ou ayant un mouvement apparenté latéralement
  • B64C 25/26 - Systèmes de commande ou de verrouillage à cet effet
  • B64F 5/10 - Fabrication ou assemblage d’aéronefs, p.ex. gabarits à cet effet

26.

WING ASSEMBLIES AND STRUCTURES FOR SUPPORTING WING TIP DEVICES

      
Numéro d'application 18323041
Statut En instance
Date de dépôt 2023-05-24
Date de la première publication 2023-11-30
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s) Bate, Christopher Alan

Abrégé

A wing structure is disclosed having a first span portion including a depth that reduces in a spanwise outward direction, and a second span portion outboard of the first span portion and having a substantially uniform spanwise depth D3. The second span portion may be non-tapered, and may include parallel fore and aft spar portions. In some embodiments the non-tapered portion supports a movable wing tip device. A wing assembly and an aircraft are also disclosed.

Classes IPC  ?

  • B64C 3/56 - Repliage ou rabattement pour réduire l'encombrement de l'aéronef

27.

MOVEABLE WING TIP ARRANGEMENTS

      
Numéro d'application 18323788
Statut En instance
Date de dépôt 2023-05-25
Date de la première publication 2023-11-30
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s) Bate, Christopher Alan

Abrégé

A wing assembly for an aircraft is disclosed having an actuation assembly configured to move a wing tip device between a flight configuration and a ground configuration. The actuation assembly includes at least two linear actuation devices mounted within the wing assembly. A wing and a wing tip device for the wing assembly, and an aircraft comprising the wing assembly, wing or wing tip, are also disclosed.

Classes IPC  ?

  • B64C 3/56 - Repliage ou rabattement pour réduire l'encombrement de l'aéronef

28.

COMPOSITE CORE STRUCTURES FOR AIRCRAFT

      
Numéro d'application 18324690
Statut En instance
Date de dépôt 2023-05-26
Date de la première publication 2023-11-30
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s)
  • Barsali, Guilherme
  • Chasteau, Dominique

Abrégé

A core structure (300) for a composite panel for an aircraft, for example a door fairing for a landing gear bay, including a sandwich structure in which core cells (301) are sandwiched between first and second body sides (skins 303, 305). The core cells are square or rectangular in shape and each have a void formed by cell walls (307). The first and second body sides and the cell walls include laminated composite material of multiple layers. Drainage holes (320) in the cell walls form one or more direct drainage paths (P2, P3) for the flow of fluid from the core structure. The core cells include first and second sheets of cells reversibly mounted to each other, such that the void of each cell is formed in part by the first sheet and in part by the second sheet.

Classes IPC  ?

  • B64C 1/00 - Fuselages; Caractéristiques structurales communes aux fuselages, voilures, surfaces stabilisatrices ou organes apparentés
  • B64F 5/00 - Tracé, fabrication, assemblage, nettoyage, entretien ou réparation des aéronefs, non prévus ailleurs; Manipulation, transport, test ou inspection de composants d’aéronefs, non prévus ailleurs
  • B32B 3/12 - Produits stratifiés caractérisés essentiellement par le fait qu'une des couches comporte des discontinuités ou des rugosités externes ou internes, ou bien qu'une des couches est de forme générale non plane; Produits stratifiés caractérisés essentiellement par des particularismes de forme caractérisés par une couche discontinue, c. à d. soit continue et percée de trous, soit réellement constituée d'éléments individuels caractérisés par une couche d'alvéoles disposées régulièrement, soit formant corps unique dans un tout, soit structurées individuellement ou par assemblage de bandes indépendantes, p.ex. structures en nids d'abeilles
  • B32B 3/06 - Caractérisés par des caractéristiques de forme en des endroits déterminés, p.ex. au voisinage des bords pour attacher le produit à quelque chose d'autre p.ex. à un support
  • B32B 37/14 - Procédés ou dispositifs pour la stratification, p.ex. par polymérisation ou par liaison à l'aide d'ultrasons caractérisés par les propriétés des couches
  • B32B 37/18 - Procédés ou dispositifs pour la stratification, p.ex. par polymérisation ou par liaison à l'aide d'ultrasons caractérisés par les propriétés des couches toutes les couches existant et présentant une cohésion avant la stratification impliquant uniquement l'assemblage de feuilles ou de panneaux individualisés
  • B32B 5/02 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par les caractéristiques de structure d'une couche comprenant des fibres ou des filaments
  • B32B 27/38 - Produits stratifiés composés essentiellement de résine synthétique comprenant des résines époxy
  • B32B 27/12 - Produits stratifiés composés essentiellement de résine synthétique adjacente à une couche fibreuse ou filamenteuse

29.

CRADLE FOR AN AIRCRAFT LANDING GEAR ASSEMBLY

      
Numéro d'application 18324796
Statut En instance
Date de dépôt 2023-05-26
Date de la première publication 2023-11-30
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s)
  • Chasteau, Dominique
  • Barsali, Guilherme

Abrégé

A cradle for supporting an aircraft landing gear assembly is disclosed including a chassis for transporting the cradle and an arm movable between a stowed position and an elevated position with respect to the chassis. The arm has a set of clamps for securing the landing gear assembly to the cradle. In this way the landing gear assembly is held securely in the stowed position for storage and transport, and held securely in the elevated position for installation to an aircraft, such that damage to the landing gear assembly during transportation and installation is minimised.

Classes IPC  ?

  • B64F 5/50 - Manipulation ou transport des composants d'aéronefs
  • B66F 9/12 - Plates-formes; Fourches; Autres organes soutenant ou saisissant la charge
  • B66F 9/18 - Moyens pour saisir ou maintenir la charge

30.

TOW-BAR FITTING

      
Numéro d'application 18318235
Statut En instance
Date de dépôt 2023-05-16
Date de la première publication 2023-11-23
Propriétaire
  • Airbus Operations Limited (Royaume‑Uni)
  • Airbus Operations (S.A.S.) (France)
Inventeur(s)
  • Sauven, James
  • Tizac, Laurent

Abrégé

A tow-bar fitting for connecting a tow-bar to an aircraft landing gear is disclosed including a tow-bar attachment to which, in use, the tow-bar is coupled. The tow-bar fitting also includes a first fuse member via which linear loads but not torque loads are transmitted from the tow-bar attachment to the rest of the landing gear. The first fuse member is configured to fail at a predetermined linear load threshold. The tow-bar fitting includes a second fuse member via which torque loads are transmitted from the tow-bar attachment to the rest of the landing gear. The second fuse member is configured to fail at a predetermined torque load threshold. A method of towing an aircraft is also disclosed.

Classes IPC  ?

  • B64D 3/00 - Adaptations des aéronefs au remorquage ou à la prise en remorque
  • B64C 25/00 - Trains d'atterrissage

31.

LANDING GEAR ASSEMBLY

      
Numéro d'application 18320346
Statut En instance
Date de dépôt 2023-05-19
Date de la première publication 2023-11-23
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s) Bishop, Benjamin

Abrégé

A landing gear assembly is disclosed having a trailing arm for carrying a wheel, a shock absorber pivotally coupled to the arm for damping movement of the arm, and an articulated lock mechanism. The mechanism includes an upper and lower lock links each with a distal end respectively pivotally coupled to the shock and arm. Proximal ends of the lock links are pivotally coupled about a common axis to enable a distance between the distal ends to vary. The mechanism is lockable to lock the assembly in an extended or retracted configuration. When the assembly is in the extended or retracted configuration, the mechanism is locked respectively in an extended or retracted locking configuration, such that the distance between the distal ends of the lock links is substantially the same in either extended or retracted locking configuration.

Classes IPC  ?

  • B64C 25/26 - Systèmes de commande ou de verrouillage à cet effet
  • B64C 25/58 - Aménagements ou adaptations des amortisseurs ou des ressorts

32.

AIRCRAFT TIRE MONITORING SYSTEM

      
Numéro d'application 18319327
Statut En instance
Date de dépôt 2023-05-17
Date de la première publication 2023-11-23
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s) Bill, Andrew

Abrégé

An aircraft tire monitoring system including a processor, and a data carrier having machine readable instructions that, when executed, cause the processor to, based on a plurality of sets of values indicative of tire parameters of aircraft tires, each set of values corresponding to an aircraft comprising a plurality of the aircraft tires, perform operations including determining a remedial action associated with each set of values. The operations include determining a priority associated with the determined remedial actions, and generating, based on the determined remedial actions, a list of aircraft, the list of aircraft ranked based on the determined priority of remedial action. The operations include causing a display device to display the list of aircraft, such that aircraft with a relatively higher priority remedial action are shown higher up the list on the display than aircraft with a relatively lower priority remedial action.

Classes IPC  ?

  • B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
  • B60C 23/04 - Dispositifs avertisseurs actionnés par la pression du pneumatique montés sur la roue ou le pneumatique

33.

AIRCRAFT LANDING GEAR ASSEMBLY

      
Numéro d'application 18320443
Statut En instance
Date de dépôt 2023-05-19
Date de la première publication 2023-11-23
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s) Bishop, Benjamin

Abrégé

An aircraft landing gear assembly is disclosed including a leg assembly having a trailing arm configured to rotate about an axis and carry a wheel, a shock absorber coupled to the arm and enabled to dampen rotation of the arm about the axis within a normal operating range, and to limit the rotation of the arm about the first trailing arm axis to the normal operating range, and a fuse member coupled to the shock absorber. The fuse member is configured to fail in the event a vertical load on the wheel exceeds a pre-determined threshold, wherein failure of the fuse member allows the first trailing arm to rotate about the first trailing arm axis beyond the normal operating range.

Classes IPC  ?

  • B64C 25/58 - Aménagements ou adaptations des amortisseurs ou des ressorts
  • B64C 25/12 - Atterrisseurs non fixes, p.ex. largables escamotables, repliables ou ayant un mouvement apparenté latéralement

34.

AIRCRAFT LANDING GEAR

      
Numéro d'application 18320619
Statut En instance
Date de dépôt 2023-05-19
Date de la première publication 2023-11-23
Propriétaire Airbus Operations Limited (Royaume‑Uni)
Inventeur(s) Bishop, Benjamin

Abrégé

An aircraft is disclosed having a landing gear with a main support supporting one or more wheels. The landing gear has at least two sidestays by which landing gear loads can be propagated from the landing gear to the body of the aircraft. The sidestays are attached at one end to a rotatable yoke via joints which allow relative movement between the sidestays and the yoke so that the yoke can rotate about a yoke axis. Rotation of the yoke about the yoke axis, permitted by the joints, can help distribute loads between the two sidestays and/or combat negative effects resulting from an unfavourable tolerance stack during assembly, for example.

Classes IPC  ?

  • B64C 25/10 - Atterrisseurs non fixes, p.ex. largables escamotables, repliables ou ayant un mouvement apparenté

35.

A COVER PANEL

      
Numéro d'application 18029071
Statut En instance
Date de dépôt 2021-08-11
Date de la première publication 2023-11-23
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s)
  • Barnett, Thomas
  • Proudler, Lee

Abrégé

A cover panel for an aircraft including: a first region, a second region for forming an overlap with a second panel, and a ramp, wherein at least a portion of the ramp is between the first and second regions, wherein the ramp includes a tapered region such that a width of the ramp tapers towards a free-edge of the first region, and wherein the free-edge is configured to form a butt-joint with the second panel.

Classes IPC  ?

  • B64C 3/26 - Construction, forme ou fixation des revêtements distincts, p.ex. panneaux
  • B64C 23/06 - Moyens permettant d'influencer l'écoulement d'air sur les surfaces des aéronefs, non prévus ailleurs par génération de tourbillons
  • B64C 3/20 - Structures monoblocs ou en sandwich

36.

METHOD OF MONITORING A STATE OF A MACHINE LEARNING CLASSIFIER

      
Numéro d'application 17990502
Statut En instance
Date de dépôt 2022-11-18
Date de la première publication 2023-11-16
Propriétaire
  • AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
  • AIRBUS OPÉRATIONS (S.A.S.) (France)
Inventeur(s)
  • Howell, George
  • Capelleras Magana, Laura

Abrégé

Techniques for monitoring a state of a machine learning classifier to determine an operational mode of an aircraft system are provided. The techniques include applying to each input node of the machine learning classifier an operational mode status of a respective component an aircraft system and a node priority determined by the order of priority of the respective series component path of the aircraft system. Varying, for an operational mode status combination, an input node state of an input node having a relatively low node priority. Indicating a normal state of the machine learning classifier where output node states do not vary in response to the varying, and indicating an altered state of the machine learning classifier where a hidden layer node state and an output node state vary in response to the varying of the input node state.

Classes IPC  ?

  • G06N 3/063 - Réalisation physique, c. à d. mise en œuvre matérielle de réseaux neuronaux, de neurones ou de parties de neurone utilisant des moyens électroniques

37.

METHOD OF DETERMINING A TIRE PERFORMANCE CHARACTERISTIC OF A TIRE

      
Numéro d'application 18316097
Statut En instance
Date de dépôt 2023-05-11
Date de la première publication 2023-11-16
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s) Bill, Andrew

Abrégé

A method of determining a tire performance characteristic of a tire. The method includes obtaining, using a processing system, a performance coefficient of the tire corresponding to performance of the tire during a first time period, wherein the performance coefficient is based on a first plurality of values indicative of a tire parameter over the first time period. The method includes obtaining a second plurality of values indicative of the tire parameter over a second time period, and determining, based on the second plurality of values and the performance coefficient, the tire performance characteristic.

Classes IPC  ?

  • B60C 23/04 - Dispositifs avertisseurs actionnés par la pression du pneumatique montés sur la roue ou le pneumatique

38.

TIRE PERFORMANCE MONITORING SYSTEM

      
Numéro d'application 18316774
Statut En instance
Date de dépôt 2023-05-12
Date de la première publication 2023-11-16
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s) Bill, Andrew

Abrégé

A tire performance monitoring system including: a tire monitoring device configured to obtain, values indicative of a tire parameter of a tire over a time period, the tire monitoring device comprising a local memory configured to store a performance coefficient corresponding to performance of the tire; and a processing system configured to determine a tire performance characteristic based on the values and the performance coefficient.

Classes IPC  ?

  • G01M 17/02 - Pneumatiques
  • G01L 17/00 - Dispositifs ou appareils pour mesurer la pression des pneumatiques ou la pression dans d'autres corps gonflés
  • G01L 19/00 - MESURE DES FORCES, DES CONTRAINTES, DES COUPLES, DU TRAVAIL, DE LA PUISSANCE MÉCANIQUE, DU RENDEMENT MÉCANIQUE OU DE LA PRESSION DES FLUIDES - Détails ou accessoires des appareils pour la mesure de la pression permanente ou quasi permanente d'un milieu fluent dans la mesure où ces détails ou accessoires ne sont pas particuliers à des types particuliers de manomètres
  • B60C 23/04 - Dispositifs avertisseurs actionnés par la pression du pneumatique montés sur la roue ou le pneumatique
  • B60C 23/20 - Dispositifs pour mesurer ou signaler la température des pneumatiques

39.

METHOD OF DETERMINING A TIRE PERFORMANCE CHARACTERISTIC OF A TIRE

      
Numéro d'application 18315903
Statut En instance
Date de dépôt 2023-05-11
Date de la première publication 2023-11-16
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s) Bill, Andrew

Abrégé

A method of determining a tire performance characteristic of a tire including querying, using a processing system, a memory as to a presence of a first set of values indicative of a tire parameter of a tire in the memory, and determining, using the processing system, that the first set of values is insufficient to determine the tire performance characteristic of the tire, The method includes performing steps, using the processing system, comprising one or more of providing an indication that a second set of values indicative of the tire parameter is required to determine the tire performance characteristic of the tire, and retrieving, from the memory, a performance coefficient of the tire corresponding to performance of the tire associated with the first set of values, and determining, based on the performance coefficient, the tire performance characteristic of the tire.

Classes IPC  ?

  • B60C 23/04 - Dispositifs avertisseurs actionnés par la pression du pneumatique montés sur la roue ou le pneumatique

40.

METHOD OF DETERMINING A TIRE PERFORMANCE CHARACTERISTIC OF A TIRE

      
Numéro d'application 18315976
Statut En instance
Date de dépôt 2023-05-11
Date de la première publication 2023-11-16
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s) Bill, Andrew

Abrégé

A method of determining a tire performance characteristic of a tire. The method includes determining that a remote memory, remote from a tire monitoring device associated with the tire, is unavailable, and the remote memory is configured to store a performance coefficient of the tire corresponding to performance of the tire during a first time period. Where the remote memory is unavailable, the method includes either calculating the performance coefficient at a remote device or, obtaining, using the remote device, the performance coefficient from a local memory of the tire monitoring device. The method includes obtaining, using the remote device and from the tire monitoring device, a plurality of values indicative of a tire parameter of the tire during a second time period, and determining, at the remote device and based on the plurality of values and the performance coefficient, the tire performance characteristic.

Classes IPC  ?

  • G01M 17/02 - Pneumatiques
  • B60C 23/20 - Dispositifs pour mesurer ou signaler la température des pneumatiques
  • B60C 23/04 - Dispositifs avertisseurs actionnés par la pression du pneumatique montés sur la roue ou le pneumatique

41.

VENTILATION OF AIRCRAFT FUEL SYSTEM

      
Numéro d'application 18309484
Statut En instance
Date de dépôt 2023-04-28
Date de la première publication 2023-11-02
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s)
  • Gadd, Matthew
  • Fallon, Adam

Abrégé

A fuel system for an aircraft is disclosed including a fuel tank; a valve; and a valve actuator with a control input. The valve actuator is configured to open and close the valve in response to command signals on the control input, and the opening of the valve ventilates the fuel tank. A control system is coupled to the control input and is configured to generate command signals and apply the command signals to the control input. A further aspect of the invention provides a method of ventilating a fuel system of an aircraft, the method comprising: assessing a suitability of a location of the aircraft or an environmental condition local to the aircraft for release of fuel vapour; and opening the valve on a basis of the assessment. The opening of the valve causes fuel vapour to be released from the fuel tank via the valve.

Classes IPC  ?

  • B64D 37/32 - Mesures de sécurité non prévues ailleurs, p.ex. contre les explosions

42.

MULTI-MATERIAL JOINT

      
Numéro d'application EP2023060319
Numéro de publication 2023/208728
Statut Délivré - en vigueur
Date de dépôt 2023-04-20
Date de publication 2023-11-02
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s) Xu, Xiangfang

Abrégé

A multi-material component is provided, comprising two members formed of a nickel-based superalloy and titanium joined together by a transition member. The transition member is formed to be complementary to both the nickel-based superalloy and titanium member. The transition member may comprise a solid layer of tantalum or BAu-4. The transition member may be joined to the two members by virtue of growing the members via additive manufacturing on the transition member. Accordingly the transition member and optionally the whole component may be obtained via additive manufacture. The multi-material component may be suitable for use on aircraft.

Classes IPC  ?

  • B22F 5/00 - Fabrication de pièces ou d'objets à partir de poudres métalliques caractérisée par la forme particulière du produit à réaliser
  • B22F 10/00 - Fabrication additive de pièces ou d’objets à partir de poudres métalliques
  • B23K 35/00 - Baguettes, électrodes, matériaux ou environnements utilisés pour le brasage, le soudage ou le découpage
  • B23K 35/32 - Emploi de matériaux spécifiés pour le soudage ou le brasage dont le principal constituant fond à plus de 1550°C
  • B33Y 10/00 - Procédés de fabrication additive
  • B33Y 80/00 - Produits obtenus par fabrication additive

43.

MULTI-MATERIAL JOINT

      
Numéro d'application EP2023060322
Numéro de publication 2023/208730
Statut Délivré - en vigueur
Date de dépôt 2023-04-20
Date de publication 2023-11-02
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s) Xu, Xiangfang

Abrégé

A multi-material component is provided, comprising two members formed of a nickel-based superalloy and a titanium-based material joined together by a transition member. The transition member is formed to be complementary to both the nickel-based superalloy and titanium-based material member. The transition member comprises a layer of titanium and Inconel that have been joined together by a low heat welding method, such as explosion welding, linear friction welding or rotary welding. The layers of the transition member may be separated by a diffusion barrier, which may be tantalum. The transition member may be joined to the two members by virtue of growing the members via additive manufacturing on the transition member. The multi-material component may be suitable for use on aircraft.

Classes IPC  ?

  • B22F 5/00 - Fabrication de pièces ou d'objets à partir de poudres métalliques caractérisée par la forme particulière du produit à réaliser
  • B22F 10/00 - Fabrication additive de pièces ou d’objets à partir de poudres métalliques
  • B23K 20/08 - Soudage par explosion
  • B23K 20/12 - Soudage non électrique par percussion ou par une autre forme de pression, avec ou sans chauffage, p.ex. revêtement ou placage la chaleur étant produite par friction; Soudage par friction
  • B23K 35/00 - Baguettes, électrodes, matériaux ou environnements utilisés pour le brasage, le soudage ou le découpage
  • B23K 35/32 - Emploi de matériaux spécifiés pour le soudage ou le brasage dont le principal constituant fond à plus de 1550°C
  • B33Y 10/00 - Procédés de fabrication additive
  • B33Y 80/00 - Produits obtenus par fabrication additive

44.

Aircraft Fuselage Intended to Receive Two Tanks Designed to Contain Liquid Hydrogen

      
Numéro d'application 18127052
Statut En instance
Date de dépôt 2023-03-28
Date de la première publication 2023-10-26
Propriétaire
  • AIRBUS SAS (France)
  • Airbus Operations SAS (France)
  • AIRBUS OPERATIONS LTD (Royaume‑Uni)
  • Airbus Operations SL (Espagne)
  • Airbus Operations GmbH (Allemagne)
Inventeur(s)
  • López-Herrero, Elisa Alvarez
  • Wolff, Matthias
  • Broer, Alexander
  • Tegtmeyer, Rainer
  • Wießmeier, Michael
  • Marquardt, Till
  • Anger, André
  • Wengorra, Anna-Katrin
  • Figueiredo, Marco Dias
  • Martinez Munoz, Jose Luis
  • Elvira, Alberto Gallegos
  • Sahin, Kaya
  • Gallant, Guillaume
  • Leoviriyakit, Kasidit
  • Wright, Philip

Abrégé

An aircraft fuselage is configured to receive two tanks designed to contain liquid hydrogen. The fuselage includes a first section for a cockpit, a second section for a passenger cabin and a third section (T3) distinct from the first section (T1) and from the second section (T2). The third section (T3) includes two housings each to house a tank. The two housings are arranged symmetrically with respect to a vertical plane of symmetry (P1). This arrangement of the tanks in a section distinct from the other sections allows them to be located as close as possible to the motors that they have to supply.

Classes IPC  ?

45.

SYNCHRONISING A PLURALITY OF AIRCRAFT TIRE MONITORING DEVICES

      
Numéro d'application 18299164
Statut En instance
Date de dépôt 2023-04-12
Date de la première publication 2023-10-19
Propriétaire Airbus Operations Limited (Royaume‑Uni)
Inventeur(s) Bill, Andrew

Abrégé

A method of synchronising a plurality of aircraft tire monitoring devices, wherein the method includes providing a synchronisation signal, and synchronising the plurality of aircraft tire monitoring devices such that each of the plurality of aircraft tire monitoring devices is available to connect to a remote device in a same time interval.

Classes IPC  ?

  • B60C 23/04 - Dispositifs avertisseurs actionnés par la pression du pneumatique montés sur la roue ou le pneumatique
  • B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs

46.

AIRCRAFT TIRE MONITORING DEVICE

      
Numéro d'application 18299594
Statut En instance
Date de dépôt 2023-04-12
Date de la première publication 2023-10-19
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s) Bill, Andrew

Abrégé

An aircraft tire monitoring device including a wireless communication interface and configured to operate in a first mode in which the wireless communication interface is periodically activated and available for connection to a remote device with a first interval between activations, and a second mode in which the wireless communication interface is periodically activated and available for connection to the remote device with a second interval between activations. The second interval between activations is different to the first interval between activations.

Classes IPC  ?

  • B60C 23/04 - Dispositifs avertisseurs actionnés par la pression du pneumatique montés sur la roue ou le pneumatique
  • B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs

47.

AIRCRAFT POWER SYSTEM

      
Numéro d'application 18335903
Statut En instance
Date de dépôt 2023-06-15
Date de la première publication 2023-10-19
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s) Sadler, Andrew David

Abrégé

Aircraft power system is disclosed having a hydraulic reservoir, a bi-directional hydraulic pump for pumping hydraulic fluid to and from the reservoir, and an electric motor. The electric motor is connectable to a first driveable component of the aircraft such that the electric motor is arranged to drive the first driveable component of the aircraft. The hydraulic pump is connectable to the first driveable component of the aircraft such that the hydraulic pump is arranged to pump hydraulic fluid from the reservoir to drive the first driveable component of an aircraft. Thus, in a first driveable mode of operation, the first driveable component is driven by both the electric motor and the hydraulic pump.

Classes IPC  ?

  • F15B 15/18 - Ensembles combinés comportant moteur et pompe
  • B64C 25/22 - Mécanismes de manœuvre à fluide
  • B64C 25/24 - Mécanismes de manœuvre électriques
  • F15B 13/044 - Dispositifs de distribution ou d'alimentation du fluide caractérisés par leur adaptation à la commande de servomoteurs pour utilisation avec un servomoteur unique actionnés par des moyens commandés électriquement, p.ex. des solénoïdes, des moteurs à couple

48.

BISCUIT JOINT REPAIR OF CONTINUOUS UD STRUCTURAL ELEMENTS

      
Numéro d'application 18299385
Statut En instance
Date de dépôt 2023-04-12
Date de la première publication 2023-10-19
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s)
  • Gaitonde, John Martin
  • Heaysman, Chris

Abrégé

A method of repairing a composite beam having a longitudinal direction including: removing material from a damaged area of the composite beam to form a cut out region; machining a plurality of elongate slots into the composite beam, the elongate slots each having a length in the longitudinal direction of the composite beam and spanning across the damaged area, the elongate slots extending into the composite beam to a depth greater than a depth of the cut out region; introducing a plurality of reinforcing inserts into the respective elongate slots and fixing the reinforcing inserts into the slots with adhesive.

Classes IPC  ?

  • B29C 73/26 - Appareils ou accessoires non prévus ailleurs pour le prétraitement mécanique
  • B29C 73/04 - Réparation d'articles faits de matières plastiques ou de substances à l'état plastique, p.ex. d'objets façonnés ou fabriqués par utilisation de techniques couvertes par la présente sous-classe ou la sous-classe utilisant des éléments préformés
  • B64F 5/40 - Entretien ou réparation d’aéronefs

49.

AIRCRAFT STRUCTURE

      
Numéro d'application 18302039
Statut En instance
Date de dépôt 2023-04-18
Date de la première publication 2023-10-19
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s) Edwards, Henry

Abrégé

An aircraft structure including a first surface and a second surface. The first surface and the second surface are bonded together via a plurality of discrete adhesive sections arranged in a herringbone pattern or a support between the first surface and the second surface, wherein the support includes spaced apart ribs with discrete adhesive sections located between the spaced apart ribs.

Classes IPC  ?

  • B64C 3/20 - Structures monoblocs ou en sandwich
  • B64F 5/10 - Fabrication ou assemblage d’aéronefs, p.ex. gabarits à cet effet

50.

MONITORING FRICTION ASSOCIATED WITH A PLURALITY OF AIRCRAFT WHEELS

      
Numéro d'application 18125656
Statut En instance
Date de dépôt 2023-03-23
Date de la première publication 2023-10-12
Propriétaire
  • AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
  • AIRBUS OPERATIONS (S.A.S.) (France)
Inventeur(s)
  • Nicolas, Vincent
  • Mcgirr, Jamie

Abrégé

A method of monitoring friction associated with a plurality of aircraft wheels of an aircraft, the method including, for each of the plurality of aircraft wheels, obtaining wheel speed data associated with the aircraft wheel. The method includes determining, based at least in part on the wheel speed data, deceleration of the aircraft wheel during a time interval, and determining, based at least in part on the determined deceleration, a value indicative of friction associated with the aircraft wheel. The method includes providing, based at least in part on the determined value, a signal indicative of a level of friction associated with the aircraft wheel.

Classes IPC  ?

  • B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
  • B64C 25/42 - Aménagement ou adaptation des freins
  • B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs

51.

DETERMINING A LOAD CONDITION OF AN AIRCRAFT

      
Numéro d'application 18126913
Statut En instance
Date de dépôt 2023-03-27
Date de la première publication 2023-10-12
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s)
  • Zhang, Junwei
  • Asadi-Aghdam, Daniel Farid
  • Youings, Martin

Abrégé

Disclosed are methods and devices for determining a load condition of an aircraft. A sensing device is mountable relative to an aircraft strut during loading operations and demountable after loading operations. A data processing device is operable to process output from the sensing device together with aircraft specific data, to determine a load condition of the aircraft.

Classes IPC  ?

  • B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs

52.

WING-BOX STRUCTURE

      
Numéro d'application 18297310
Statut En instance
Date de dépôt 2023-04-07
Date de la première publication 2023-10-12
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s) Edwards, Henry

Abrégé

A wing-box structure for an aircraft is disclosed having an upper cover, a lower cover, longitudinal forward and rearward spars, and a plurality of transverse ribs. One of the transverse ribs is retained by a pair of opposed captive features disposed on an interior side of either the forward and rearward spars or the upper and lower covers. The rib is bonded rib to the forward and rearward spars and/or the upper and lower covers at a location where the rib is retained.

Classes IPC  ?

53.

TIRE PRESSURE MONITORING DEVICES

      
Numéro d'application 18128173
Statut En instance
Date de dépôt 2023-03-29
Date de la première publication 2023-10-05
Propriétaire
  • AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
  • AIRBUS OPERATIONS GMBH (Allemagne)
  • AIRBUS OPERATIONS (S.A.S.) (France)
  • MEGGITT SA (Suisse)
Inventeur(s)
  • Bill, Andrew
  • Marwedel, Stephan
  • Duchossoy, Christelle
  • Stanley-Adams, Kevin

Abrégé

A method of performing a configuration procedure for first and second tire pressure monitoring devices. The method includes loading the first tire pressure monitoring device with first configuration data, and subsequently transmitting, from the first tire pressure monitoring device, a first configuration data signal which encodes the first configuration data. The method includes subsequently loading the second tire pressure monitoring device with second configuration data, and subsequently ending the configuration procedure without transmitting a second configuration data signal which encodes the second configuration data.

Classes IPC  ?

  • B60C 23/04 - Dispositifs avertisseurs actionnés par la pression du pneumatique montés sur la roue ou le pneumatique
  • B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs

54.

METHOD OF CONFIGURING A NETWORK OF TIRE MONITORING DEVICES

      
Numéro d'application 18128285
Statut En instance
Date de dépôt 2023-03-30
Date de la première publication 2023-10-05
Propriétaire
  • AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
  • AIRBUS OPERATIONS GmbH (Allemagne)
  • AIRBUS OPERATIONS (S.A.S.) (France)
  • MEGGITT SA (Suisse)
  • AIRBUS DEFENCE AND SPACE GmbH (Allemagne)
Inventeur(s)
  • Bill, Andrew
  • Marwedel, Stephan
  • Duchossoy, Christelle
  • Blass, Erik-Oliver
  • Stanley-Adams, Kevin

Abrégé

A method of configuring a network of tire monitoring devices using an untrusted device is provided. An untrusted device transmits first configuration data to a first tire monitoring device, and then receives a first input verifying that the first configuration data has been loaded to the first tire monitoring device and matches expected first configuration data. The untrusted device transmits second configuration data to a second tire monitoring device, and receives a second input verifying that the second configuration data has been loaded to the second tire monitoring device and matches expected second configuration data. The untrusted device transmits a command initializing generation of a cryptographic parameter by the first tire monitoring device, and causes the cryptographic parameter to be exchanged with the second tire monitoring device such that secure future communication is established between the first and second tire monitoring devices.

Classes IPC  ?

  • B60C 23/04 - Dispositifs avertisseurs actionnés par la pression du pneumatique montés sur la roue ou le pneumatique
  • H04L 67/12 - Protocoles spécialement adaptés aux environnements propriétaires ou de mise en réseau pour un usage spécial, p.ex. les réseaux médicaux, les réseaux de capteurs, les réseaux dans les véhicules ou les réseaux de mesure à distance
  • H04L 9/40 - Protocoles réseaux de sécurité

55.

WASHER DEVICE

      
Numéro d'application 18128156
Statut En instance
Date de dépôt 2023-03-29
Date de la première publication 2023-10-05
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s) Tulloch, William

Abrégé

A washer device is disclosed including two annular components each having a main face arranged to contact the main face of the other component. Each main face has surface regions of different levels along an axis of the component, such as a step and/or a helical ramp. Relative rotation of one component with respect to the other about their common axis alters the effective thickness of the washer device. The washer device 1 further includes at least one radial projection on one of the annular components arranged to engage with a corresponding notch on the other annular component such that the annular components may be oriented in predetermined angular positions corresponding to different predetermined effective thicknesses of the washer device.

Classes IPC  ?

  • F16B 43/00 - Rondelles ou dispositifs équivalents; Autres dispositifs de support pour têtes de boulons ou d'écrous
  • B64F 5/10 - Fabrication ou assemblage d’aéronefs, p.ex. gabarits à cet effet

56.

AIRCRAFT NOSE LANDING GEAR ASSEMBLY

      
Numéro d'application 18128808
Statut En instance
Date de dépôt 2023-03-30
Date de la première publication 2023-10-05
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s) Wilson, Fraser

Abrégé

An aircraft nose landing gear assembly is disclosed including two wheels, motors, brakes, and a controller. The wheels are separated by a steering axis and independently rotatable about a rotation axis in a rotation direction. The motors and brakes are each arranged to selectively engage a respective wheel. The motors and brakes supplement and resist rotation of the respective wheel in the rotation direction, respectively. On the basis of an indication to the controller of rotation of the two wheels in the rotation direction, the controller is arranged to: cause one motor to engage its respective wheel and supplement rotation, and cause the brake associated with the other wheel to engage the other wheel and resist rotation. Engagement of the motor and brake causes the wheels to pivot about the steering axis during a turning event.

Classes IPC  ?

  • B64C 25/36 - Aménagements ou adaptations des roues, des pneumatiques ou des essieux
  • B64C 25/50 - Atterrisseurs orientables; Amortissement du shimmy
  • B64C 25/32 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue
  • B60T 8/17 - Utilisation de moyens de régulation électriques ou électroniques pour la commande du freinage
  • B60L 7/10 - Freinage dynamo-électrique par récupération

57.

A BRAKE COMPONENT

      
Numéro d'application EP2023058204
Numéro de publication 2023/187013
Statut Délivré - en vigueur
Date de dépôt 2023-03-29
Date de publication 2023-10-05
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s) Nagliati, Marco

Abrégé

Disclosed is a brake component (151) comprising a composite material (200), the composite material comprising a matrix (202) and reinforcements (201) embedded in and supported by the matrix, wherein the matrix is a glass-ceramic matrix. Also disclosed is a braking system, an aircraft braking system, an aircraft and a method of operating an aircraft.

Classes IPC  ?

  • F16D 69/02 - Composition des garnitures
  • F16C 33/04 - Coussinets; Bagues; Garnitures antifriction
  • F16D 65/14 - Mécanismes d'actionnement pour freins; Moyens pour amorcer l'opération de freinage à une position prédéterminée

58.

SEALANT APPLICATOR

      
Numéro d'application 18126052
Statut En instance
Date de dépôt 2023-03-24
Date de la première publication 2023-09-28
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s)
  • Brookes, Harvey
  • Humphrys, Henry

Abrégé

A sealant applicator is disclosed for applying sealant to a surface of one or more aircraft parts. The sealant applicator includes a sealant inlet for receiving sealant from a source of sealant; a sealant outlet for the dispensing of sealant therethrough; and a main body, the main body includes one or more sealant-contacting surfaces for contacting dispensed sealant; and one or more spacers for abutting against a surface of the one or more aircraft parts and for maintaining the one or more sealant-contacting surfaces in spaced relationship with the surface of the one or more aircraft parts.

Classes IPC  ?

  • B05C 17/00 - Outils à main ou appareils utilisant des outils tenus à la main pour appliquer ou étaler des liquides ou d'autres matériaux fluides sur des surfaces, pour enlever partiellement des liquides ou d'autres matériaux fluides des surfaces

59.

SENSOR DEVICE AND METHOD FOR AIRCRAFT SHOCK-ABSORBER

      
Numéro d'application 18121288
Statut En instance
Date de dépôt 2023-03-14
Date de la première publication 2023-09-21
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s) Marles, David

Abrégé

A sensor and method for sensing gas absorbed in hydraulic fluid in an aircraft shock absorber are disclosed. The hydraulic fluid and a gas are in fluid communication with each other. The sensor may be incorporated in the shock absorber or in servicing apparatus such as a servicing cart. The amount of gas absorbed in the hydraulic fluid is provided as a parameter which in combination with other parameters allows a user an improved means to determine the maintenance state of the shock absorber and to derive servicing actions.

Classes IPC  ?

  • B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
  • B64C 25/60 - Jambes amortisseuses hydrauliques
  • B64F 5/40 - Entretien ou réparation d’aéronefs

60.

LEADING EDGE FLAP

      
Numéro d'application 17773362
Statut En instance
Date de dépôt 2020-10-26
Date de la première publication 2023-09-14
Propriétaire Airbus Operations Limited (Royaume‑Uni)
Inventeur(s)
  • Commis, Ben
  • Lyons, Neil
  • Kay, Edmund

Abrégé

An aircraft wing including a leading edge slat and a fixed aerofoil portion. The leading edge slat is moveable between a stowed position and deployed position. In the deployed position a trailing edge of the leading edge slat includes a sealed portion and an unsealed portion. The sealed portion forms a seal with the fixed aerofoil portion and the unsealed portion provides an airflow gap between the leading edge flap and the fixed aerofoil portion. The invention provides substantially the same benefits as a sealed leading edge slat whilst improving stall control behavior in local zones around the unsealed portion.

Classes IPC  ?

  • B64C 21/02 - Moyens permettant d'influencer l'écoulement d'air sur les surfaces des aéronefs en agissant sur la couche limite par utilisation de fentes, de conduits, de surfaces poreuses ou de dispositifs similaires

61.

MANAGING MICROBIAL CONTAMINATION OF FUEL TANK

      
Numéro d'application GB2023050526
Numéro de publication 2023/170396
Statut Délivré - en vigueur
Date de dépôt 2023-03-07
Date de publication 2023-09-14
Propriétaire
  • AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
  • AIRBUS SAS (France)
Inventeur(s)
  • Fallon, Adam
  • Lee, Martin
  • Dautelle, Jean-Marie
  • Brousse, Pierre-Henri

Abrégé

A computer-implemented method of determining a maintenance schedule or maintenance plan for a fuel tank of an aircraft. In a training phase, a predictive model is trained with training data. The training data is associated with fuel tanks of plural aircraft. The training data comprises environmental data indicative of an environmental parameter at locations of the plural aircraft, and test data which is indicative of a level of microbial contamination of fuel in fuel tanks of the plural aircraft. In a prediction phase, input data is received and the predictive model is operated, along with an optimisation algorithm, to determine a maintenance schedule or maintenance plan. One or more microbial contamination maintenance tasks are performed on the fuel tank based on the maintenance schedule or maintenance plan.

Classes IPC  ?

  • G06Q 10/20 - Administration de la réparation ou de la maintenance des produits

62.

GAS DETECTION IN AN ENCLOSED SPACE

      
Numéro d'application 18088403
Statut En instance
Date de dépôt 2022-12-23
Date de la première publication 2023-09-07
Propriétaire
  • AIRBUS OPERATIONS, S.L.U. (Espagne)
  • AIRBUS OPERATIONS LTD (Royaume‑Uni)
Inventeur(s)
  • Vicente Oliveros, David
  • Woods, Christopher J.

Abrégé

A gas detection system that detects gas inside an enclosed space of an aircraft system on board in an aircraft. The system is used in a method for determining the presence of a gas inside an aircraft system by means of a detection system installed on the aircraft system. The system monitors and/or detects a vacuum leak or of fire inside an aircraft system arranged in an aircraft.

Classes IPC  ?

  • G01N 21/3504 - Couleur; Propriétés spectrales, c. à d. comparaison de l'effet du matériau sur la lumière pour plusieurs longueurs d'ondes ou plusieurs bandes de longueurs d'ondes différentes en recherchant l'effet relatif du matériau pour les longueurs d'ondes caractéristiques d'éléments ou de molécules spécifiques, p.ex. spectrométrie d'absorption atomique en utilisant la lumière infrarouge pour l'analyse des gaz, p.ex. analyse de mélanges de gaz
  • G01N 21/85 - Analyse des fluides ou solides granulés en mouvement
  • G08B 21/12 - Alarmes pour assurer la sécurité des personnes réagissant à l'émission indésirable de substances, p.ex. alarmes de pollution
  • B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs

63.

AIRCRAFT STEERING ANGLE DETERMINATION

      
Numéro d'application 18115244
Statut En instance
Date de dépôt 2023-02-28
Date de la première publication 2023-08-31
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s)
  • Moss, Ethan
  • Au, Ting Yu

Abrégé

A computer-implemented method of determining a steering angle of an aircraft landing gear including: obtaining an input image of the aircraft landing gear; comparing the input image against a plurality of reference images, the plurality of reference images comprising images of the aircraft landing gear at known steering angles; determining a most similar reference image, the most similar reference image comprising the reference image of the plurality of reference images most closely matched to the input image; and determining, based at least in part on the most similar reference image, the steering angle of the aircraft landing gear.

Classes IPC  ?

  • G06T 7/73 - Détermination de la position ou de l'orientation des objets ou des caméras utilisant des procédés basés sur les caractéristiques
  • G01B 11/26 - Dispositions pour la mesure caractérisées par l'utilisation de techniques optiques pour tester l'alignement des axes
  • G06T 5/00 - Amélioration ou restauration d'image
  • B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs

64.

AIRCRAFT STEERING ANGLE DETERMINATION

      
Numéro d'application 18115296
Statut En instance
Date de dépôt 2023-02-28
Date de la première publication 2023-08-31
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s) Moss, Ethan

Abrégé

A method of determining a steering angle of an aircraft landing gear including: obtaining an image of the aircraft landing gear; performing edge detection on the image; determining, based at least in part on an edge obtained by the edge detection, a relative position of a component of the aircraft landing gear; and determining, based at least in part on the relative position of the component, the steering angle of the aircraft landing gear.

Classes IPC  ?

  • G06T 7/73 - Détermination de la position ou de l'orientation des objets ou des caméras utilisant des procédés basés sur les caractéristiques
  • G01B 11/26 - Dispositions pour la mesure caractérisées par l'utilisation de techniques optiques pour tester l'alignement des axes
  • G06T 7/12 - Découpage basé sur les bords
  • G06T 7/194 - Découpage; Détection de bords impliquant une segmentation premier plan-arrière-plan
  • G06T 7/60 - Analyse des attributs géométriques

65.

METHOD FOR MANUFACTURING AT LEAST ONE PORTION OF A BOX STRUCTURE OF AN AIRCRAFT COMPRISING A FORMING STEP, AND A CENTRAL WINGBOX THUS OBTAINED

      
Numéro d'application 18164119
Statut En instance
Date de dépôt 2023-02-03
Date de la première publication 2023-08-24
Propriétaire
  • Airbus Operations SAS (France)
  • Airbus Operations LTD (Royaume‑Uni)
  • Airbus Operations S.L. (Espagne)
Inventeur(s)
  • Duthille, Bertrand
  • Price, Jonathan
  • Pridie, Jago
  • Menendez Martin, Jose Manuel

Abrégé

A method for manufacturing at least a portion of a box structure obtained from an outer skin and a plurality of sections each having a joining face in contact with the outer skin. The method comprises a step of positioning the sections on a mold, a step of obtaining a flat fiber preform having a thickness substantially equal to the outer skin, a step of placing a central portion of the fiber preform on the sections positioned on a first face of the mold and a step of forming a lateral extension of the fiber preform to press the fiber preform against a forming surface. A central wingbox obtained by the method is provided and a forming tool for carrying out the method.

Classes IPC  ?

  • B64C 1/26 - Fixation de la voilure, des empennages ou des surfaces stabilisatrices
  • B29C 70/30 - Façonnage par empilage, c.à d. application de fibres, de bandes ou de feuilles larges sur un moule, un gabarit ou un noyau; Façonnage par pistolage, c.à d. pulvérisation de fibres sur un moule, un gabarit ou un noyau

66.

AIRCRAFT BRAKING SYSTEM

      
Numéro d'application 18172234
Statut En instance
Date de dépôt 2023-02-21
Date de la première publication 2023-08-24
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s)
  • Gale, Julian
  • Bidmead, Ashley
  • Hebborn, Andrew

Abrégé

A method of parking an aircraft is disclosed including flight crew pedal braking to cause a brake force to be applied to the aircraft wheel brakes to slow the aircraft to a stationary state in which it is ready to be parked. Flight crew then activate a parking brake device and then release the pedal braking. An electronic control device, forming part of the aircraft’s braking system for example, automatically intervenes, following the manual release of the pedal braking, to cause a brake force to continue to be applied to the wheels. This may be until sufficient brake force is applied, as a result of the activation of the parking brake device, to hold the aircraft in its parked state or may be for a predetermined period of time, say, ten seconds.

Classes IPC  ?

  • B64C 25/42 - Aménagement ou adaptation des freins
  • B60T 8/17 - Utilisation de moyens de régulation électriques ou électroniques pour la commande du freinage
  • B60T 7/04 - Organes d'attaque de la mise en action des freins par l'entremise d'une personne actionnés au pied
  • B60T 8/58 - Dispositions pour adapter la force de freinage sur la roue aux conditions propres au véhicule ou à l'état du sol, p.ex. par limitation ou variation de la force de freinage selon une condition de vitesse, p.ex. accélération ou décélération selon une condition de vitesse et une autre condition, ou selon une pluralité de conditions de vitesse

67.

METHOD AND APPARATUS FOR OPERATING AN AIRCRAFT HAVING TWO ENGINES

      
Numéro d'application 18170910
Statut En instance
Date de dépôt 2023-02-17
Date de la première publication 2023-08-17
Propriétaire
  • Airbus SAS (France)
  • Airbus Operations Limited (Royaume‑Uni)
  • Airbus Operations SAS (France)
Inventeur(s)
  • Buisson, Marcellin
  • Reynolds, Dylan
  • Gouillou, Jerome
  • Loupiac, Gabriel
  • Chippa, Kiran Kumar

Abrégé

Processes and systems for operating an aircraft having a first engine and a second engine, a non-transitory computer readable media comprising computer executable instructions that when executed cause a processor to execute the steps of the present processes. A plurality of taxiways are determined and zones for changing to or from single engine taxing operations are also determined and displayed. Additionally, countdown timers for takeoff or engine shutdown may be displayed.

Classes IPC  ?

  • G08G 5/06 - Systèmes de commande du trafic aérien pour la commande lorsque l'appareil est au sol
  • G08G 5/00 - Systèmes de commande du trafic aérien

68.

AIRCRAFT LANDING GEAR ASSEMBLY

      
Numéro d'application 18105622
Statut En instance
Date de dépôt 2023-02-03
Date de la première publication 2023-08-17
Propriétaire Airbus Operations Limited (Royaume‑Uni)
Inventeur(s) Hogg, Kevin

Abrégé

An aircraft landing gear assembly 1 includes a wheel 10, a disc brake 20 comprising one or more discs 21, 22 and a filter 30. The disc brake is operable to inhibit rotation of wheel 10 during a braking event thereby resulting in the formation of brake dust from the one or more discs 21, 22. The filter 30 is positioned relative to the disc brake 20 such that air flows over the one or more discs 21,22, through the filter 30 and away from the assembly 1, wherein the filter 30 is configured to separate and remove at least part of the brake dust from the air and while allowing the air to pass.

Classes IPC  ?

  • F16D 65/00 - ACCOUPLEMENTS POUR LA TRANSMISSION DES MOUVEMENTS DE ROTATION; EMBRAYAGES; FREINS - Éléments constitutifs ou détails des freins
  • B64C 25/42 - Aménagement ou adaptation des freins

69.

AIRCRAFT WING

      
Numéro d'application 18105627
Statut En instance
Date de dépôt 2023-02-03
Date de la première publication 2023-08-17
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s)
  • Walega, Janusz
  • Harding, Matt

Abrégé

An aircraft wing including: a main wing portion with a tip end, and a wing tip device rotatably coupled to the tip end of the main wing portion at a joint, the wing tip device rotatable at the joint about a first axis between a flight configuration and a ground configuration; and a seal panel assembly including: a seal panel extending across the joint; a first connecting element having a first end non-rotatably coupled to the seal panel and a second end rotatably coupled to the main wing portion such that the seal panel is rotatable about a second axis; and a second connecting element having a first end rotatably coupled to the seal panel and a second end rotatably coupled to the wing tip device, such that rotation of the wing tip device about the first axis causes the seal panel to rotate about the second axis.

Classes IPC  ?

  • B64C 3/26 - Construction, forme ou fixation des revêtements distincts, p.ex. panneaux
  • B64C 3/56 - Repliage ou rabattement pour réduire l'encombrement de l'aéronef

70.

FUEL TANK STRINGER WITH FLOW PASSAGE

      
Numéro d'application 18109672
Statut En instance
Date de dépôt 2023-02-14
Date de la première publication 2023-08-17
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s)
  • Gaitonde, John Martin
  • Heaysman, Chris

Abrégé

A fuel tank is disclosed including a lower cover and an upper cover. The lower cover or the upper cover includes a panel assembly. The panel assembly includes a panel and a stringer attached to the panel. The stringer includes a pair of portions which are spaced apart in a lengthwise direction of the stringer and connected to each other by a bridge. Each portion is connected to a respective end of the bridge, and each end of the bridge deviates away from the panel. The stringer includes reinforcement fibres which extend between the portions via the bridge. Each reinforcement fibre deviates away from the panel at each end of the bridge. The stringer includes a stringer recess between the bridge and the panel, and a flow passage in the stringer recess through which fluid can flow across the stringer.

Classes IPC  ?

  • B64C 3/34 - Réservoirs fabriqués intégralement avec les ailes, p.ex. de carburant ou d'eau

71.

LOW TEMPERATURE PIPE SYSTEM TESTING

      
Numéro d'application 18167596
Statut En instance
Date de dépôt 2023-02-10
Date de la première publication 2023-08-17
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s) Iyengar, Parthasarathy

Abrégé

A method of testing a pipe system with a testing apparatus is disclosed including a container, a cooling chamber in the container, and a cold head in the cooling chamber. The method includes loading the pipe system into the container; cooling a fluid, such as Helium gas, in the cooling chamber with the cold head to generate a cooled fluid; feeding the cooled fluid into the pipe system in the container; and taking a test measurement of the pipe system containing the cooled fluid.

Classes IPC  ?

  • G01M 3/28 - Examen de l'étanchéité des structures ou ouvrages vis-à-vis d'un fluide par utilisation d'un fluide ou en faisant le vide par mesure du taux de perte ou de gain d'un fluide, p.ex. avec des dispositifs réagissant à la pression, avec des indicateurs de débit pour soupapes
  • G01M 5/00 - Examen de l'élasticité des structures ou ouvrages, p.ex. fléchissement de ponts ou d'ailes d'avions

72.

TYRE MONITORING DEVICE AND METHOD

      
Numéro d'application 18137969
Statut En instance
Date de dépôt 2023-04-21
Date de la première publication 2023-08-10
Propriétaire
  • Airbus Operations Limited (Royaume‑Uni)
  • Airbus Operations GmbH (Allemagne)
Inventeur(s)
  • Bill, Andrew
  • Warns, Timo

Abrégé

A tire monitoring device configured to be mounted on a wheel and including: a pressure sensor for sensing an inflation pressure of a tire on the wheel; a wireless communication interface configured to receive data indicative of a command to indicate tire pressure, wherein the wireless communication interface is configured to communicate with at least one other tire monitoring device; a storage storing a predetermined pressure value; an indicator configured to provide a first indication and a second indication, wherein the first indication is different from the second indication; and a processing system configured to operate the indicator to provide the first indication or the second indication responsive to receipt of the command to indicate tire pressure, and based at least in part on the inflation pressure and the predetermined pressure value.

Classes IPC  ?

  • B60C 23/04 - Dispositifs avertisseurs actionnés par la pression du pneumatique montés sur la roue ou le pneumatique
  • B60C 23/20 - Dispositifs pour mesurer ou signaler la température des pneumatiques
  • G01K 1/14 - Supports; Dispositifs de fixation; Dispositions pour le montage de thermomètres en des endroits particuliers

73.

SPAR ARRANGEMENT IN A WING TIP DEVICE

      
Numéro d'application 18125399
Statut En instance
Date de dépôt 2023-03-23
Date de la première publication 2023-08-10
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s)
  • Bhatia, Sarabpal-Singh
  • Phillips, Samuel

Abrégé

An aircraft wing assembly including a wing (3) and a wing tip device (4) at the tip of the wing (3), the wing tip device (4) having front and rear spars (14, 13), wherein the wing tip device (4) has a cross-brace spar (18) that links the front and rear spars and is oriented such that it is oblique to the front and rear spars (14, 13).

Classes IPC  ?

  • B64C 3/18 - Longerons; Nervures; Lisses
  • B64C 23/06 - Moyens permettant d'influencer l'écoulement d'air sur les surfaces des aéronefs, non prévus ailleurs par génération de tourbillons
  • B64F 5/10 - Fabrication ou assemblage d’aéronefs, p.ex. gabarits à cet effet
  • B64C 3/58 - Voilures comportant des barrières de couche limite ou des destructeurs de portance (spoilers)

74.

AIRCRAFT WING WITH MOVABLE WING TIP DEVICE

      
Numéro d'application 18102924
Statut En instance
Date de dépôt 2023-01-30
Date de la première publication 2023-08-03
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s)
  • Edwards, Henry
  • Driffill, Helen

Abrégé

An aircraft wing is disclosed including a main wing element and a movable wing tip device attached to a tip end of the main wing element. The movable wing tip device can move relative to the main wing element to vary a span of the aircraft wing. An inductive coupler is arranged to inductively transmit data and/or power between the main wing element and the movable wing tip device. The inductive coupler removes the need for wires and cables to pass across a joint between the main wing element and a movable wing tip device. Additional embodiments include a method of maintenance, and a method of operating the aircraft wing to transmit data and/or power between the main wing element and the movable wing tip device.

Classes IPC  ?

  • B64C 3/56 - Repliage ou rabattement pour réduire l'encombrement de l'aéronef
  • B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
  • B64C 13/38 - Dispositifs de transmission avec amplification de puissance
  • H04B 5/00 - Systèmes de transmission à induction directe, p.ex. du type à boucle inductive

75.

AIRCRAFT WITH MOVABLE WING TIP DEVICE

      
Numéro d'application 18102966
Statut En instance
Date de dépôt 2023-01-30
Date de la première publication 2023-08-03
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s)
  • Edwards, Henry
  • Driffill, Helen

Abrégé

An aircraft is disclosed having a device and an aircraft wing. The aircraft wing includes a main wing element and a movable wing tip device attached to a tip end of the main wing element. The movable wing tip device includes an accumulator configured to store energy and the movable wing tip device can move relative to the main wing element to vary a span of the aircraft wing. The accumulator is configured to transmit power to the device. The accumulator enables energy to trickle between the main wing element and the movable wing tip device whilst still providing a suitable power source to the device. Additional embodiments include a method of maintenance, and a method of operating the aircraft wing to store energy in the movable wing tip device.

Classes IPC  ?

  • B64C 23/06 - Moyens permettant d'influencer l'écoulement d'air sur les surfaces des aéronefs, non prévus ailleurs par génération de tourbillons

76.

RELATING TO WING CONSTRUCTION

      
Numéro d'application 18162303
Statut En instance
Date de dépôt 2023-01-31
Date de la première publication 2023-08-03
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s)
  • Tulloch, William
  • Ruiz De Pablo, Javier
  • Dean, Paul
  • Bird, James

Abrégé

An aircraft wing structure (100) including a spar (101) and a systems module (200) that is releasably secured to brackets (300) on a first side of the spar (101) and the second, opposite side of the spar is configured to define a wall of a fuel tank of an aircraft wing.

Classes IPC  ?

  • B64C 3/18 - Longerons; Nervures; Lisses
  • B64C 3/34 - Réservoirs fabriqués intégralement avec les ailes, p.ex. de carburant ou d'eau

77.

AN AIRCRAFT CONTROL SYSTEM

      
Numéro d'application 18100316
Statut En instance
Date de dépôt 2023-01-23
Date de la première publication 2023-07-27
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s)
  • Izquierdo Civera, Fernando
  • Piddock, Alex Robert
  • Johnson, Mark

Abrégé

An aircraft control system 100 including a control assembly 110 having control units, including a first control unit 130 for controlling actuation of the aircraft component during a first time period, using electrical resource 512 from a first electrical resource device 510, and a second control unit 140 for controlling actuation of the aircraft component during a second time period, and a switch mechanism 120 for switching control of the actuation of the aircraft component between the first and second control units, wherein the switch mechanism has a first electrical resource device status input 513 for indicating the status of the first electrical resource device 510 and wherein, the switch mechanism is configured to switch control between the first 130 and second 140 control units based on the first electrical resource device status input 513.

Classes IPC  ?

  • B64C 19/02 - Commandes associées
  • B64C 13/16 - Dispositifs amorçant la mise en œuvre actionnés automatiquement, p.ex. répondant aux détecteurs de rafales

78.

SYSTEMS AND METHODS FOR PROCESSING AIRCRAFT SENSOR DATA

      
Numéro d'application 18156158
Statut En instance
Date de dépôt 2023-01-18
Date de la première publication 2023-07-20
Propriétaire
  • AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
  • Airbus (SAS) (France)
Inventeur(s)
  • Bill, Andrew
  • Smart, Colin

Abrégé

A system including an aircraft, and a computing system remote from the aircraft. The aircraft includes a sensor, an aircraft component associated with the sensor, a first transmitter, and a first receiver. The computing system includes a processor, a second transmitter, and a second receiver. The aircraft transmits sensor data sensed by the sensor to the computing system. The computing system is configured to process the received sensor data to generate status data indicative of an operational mode of the aircraft component, and to transmit, when the status data is indicative of an altered operational mode of the aircraft component, the status data to the aircraft via the second transmitter. The aircraft is configured to indicate, based at least partially on the status data received by the first receiver, the altered operational mode of the aircraft component.

Classes IPC  ?

  • B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
  • B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs

79.

AIRCRAFT LANDING GEAR

      
Numéro d'application 17992598
Statut En instance
Date de dépôt 2022-11-22
Date de la première publication 2023-07-20
Propriétaire
  • AIRBUS OPERATIONS (SAS) (France)
  • AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s)
  • Huber, Jerome
  • Scotto, Aline
  • Itasse, Maxime
  • Northam, Robert

Abrégé

An aircraft landing gear 100 includes a structural main leg 110, having a substantially circular cross-section and defining a front side for facing upstream in use and a rear side for facing downstream in use. The landing gear includes a shaped element 151 attached to an attachment point located on the rear side of the structural main leg. The shaped element extends rearwards from the structural main leg to provide a combined cross-sectional shape of the structural main leg and shaped element that is elongated in the upstream-downstream direction compared to the structural main leg.

Classes IPC  ?

  • B64C 25/10 - Atterrisseurs non fixes, p.ex. largables escamotables, repliables ou ayant un mouvement apparenté

80.

PREDICTING TIRE PRESSURE OF A TIRE OF AN AIRCRAFT

      
Numéro d'application 18098424
Statut En instance
Date de dépôt 2023-01-18
Date de la première publication 2023-07-20
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s)
  • Bill, Andrew
  • Orford, Michael

Abrégé

A computer-implemented method of predicting tire pressure of a tire of an aircraft, the method including obtaining first data indicative of an inflation pressure of the tire, obtaining second data indicative of a brake temperature of a brake associated with an aircraft wheel to which the tire is mounted, obtaining third data indicative of a gas temperature of the tire, and obtaining fourth data indicative of one or more predicted operational conditions of the aircraft during a future time period. The method includes determining, based at least in part on the first, second, third and fourth data, predicted tire pressure characteristics of the tire during the future time period.

Classes IPC  ?

  • B60C 23/04 - Dispositifs avertisseurs actionnés par la pression du pneumatique montés sur la roue ou le pneumatique

81.

COUPLING FOR INSULATED PIPING

      
Numéro d'application 18098355
Statut En instance
Date de dépôt 2023-01-18
Date de la première publication 2023-07-20
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s)
  • Phillips, Samuel
  • Bryant, Anthony

Abrégé

A coupling for vacuum-insulated piping is disclosed having first and second parts for forming the coupling; each of the first and second parts comprising an inner portion for fluid communication with an inner part of a vacuum-insulated pipe and an outer portion for fluid communication with an outer, low pressure part of a vacuum-insulated pipe; the inner portions of the first and second parts form an inner region for the passage of fluid therethrough; each of the first and second parts comprising an interface portion for forming an interface with interface portion of the other of the first and second parts, the interface portion comprising a flange for connecting the first and second parts; each of the first and second parts comprises a sleeve surrounding the outer portion, the sleeve comprising a thermally-conducting portion that is in thermal communication with the interface portion so as to conduct heat away from the interface portion.

Classes IPC  ?

  • F16L 59/18 - Dispositions spécialement adaptées aux nécessités localisées telles qu'à l'endroit des brides, des jonctions, des soupapes ou d'autres éléments similaires adaptées aux raccords
  • F16L 39/00 - Raccords ou accessoires de raccordement pour tuyaux à double paroi ou à canaux multiples ou pour assemblages de tuyaux
  • F16L 59/065 - Dispositions utilisant une couche d'air ou le vide utilisant le vide

82.

LIGHTNING STRIKE PROTECTION LAYER

      
Numéro d'application 18096473
Statut En instance
Date de dépôt 2023-01-12
Date de la première publication 2023-07-13
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s) Thompson, Sam

Abrégé

A lightning strike protection layer for an aircraft is disclosed having a first portion and a second portion, the first portion includes a first fibre reinforced polymer composite layer and a first electrically conductive metal layer and the second portion includes a second fibre reinforced polymer composite layer and a second electrically conductive metal layer, and the first and second portions are joined at a butt joint, with the first and second fibre reinforced polymer composite layers abutting and the first and second electrically conductive metal layers abutting; and a butt-strap extending across the butt joint, the butt-strap comprising a third electrically conductive metal layer electrically connected to the first and second electrically conductive metal layers.

Classes IPC  ?

  • B64D 45/02 - Dispositifs de protection contre la foudre; Déperditeurs de potentiel
  • B32B 5/02 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par les caractéristiques de structure d'une couche comprenant des fibres ou des filaments
  • B32B 15/14 - Produits stratifiés composés essentiellement de métal adjacent à une couche fibreuse ou filamenteuse
  • B32B 3/06 - Caractérisés par des caractéristiques de forme en des endroits déterminés, p.ex. au voisinage des bords pour attacher le produit à quelque chose d'autre p.ex. à un support
  • B32B 15/02 - Produits stratifiés composés essentiellement de métal autrement que sous forme de feuille, p.ex. en fils, en parcelles
  • B32B 15/20 - Produits stratifiés composés essentiellement de métal comportant de l'aluminium ou du cuivre
  • B32B 15/04 - Produits stratifiés composés essentiellement de métal comprenant un métal comme seul composant ou comme composant principal d'une couche adjacente à une autre couche d'une substance spécifique
  • B32B 5/26 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par la présence de plusieurs couches qui comportent des fibres, filaments, grains ou poudre, ou qui sont sous forme de mousse ou essentiellement poreuses une des couches étant fibreuse ou filamenteuse un autre couche également étant fibreuse ou filamenteuse
  • B64F 5/10 - Fabrication ou assemblage d’aéronefs, p.ex. gabarits à cet effet

83.

AIRCRAFT LANDING GEAR WITH PIVOTING DRIVE TRANSMISSION

      
Numéro d'application 18179115
Statut En instance
Date de dépôt 2023-03-06
Date de la première publication 2023-06-29
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s)
  • Wilson, Fraser
  • Bedarrides, Jeremy
  • Platagea, Vladimir

Abrégé

An aircraft landing gear is disclosed including a shock-absorbing main leg having a sprung part for attachment to an aircraft and an un-sprung part including a slider and an axle carrying at least one wheel, the wheel having a toothed ring gear; a drive transmission mounted externally on the sprung part, or on the un-sprung part, of the main leg, the drive transmission having at least one motor and a drive pinion for meshing with the toothed ring of the wheel; and an actuator for lifting the drive transmission into and out of driving engagement with the toothed ring and for maintaining the driving engagement as the landing gear deflects during a ground taxiing operation. Also, a method of operating the aircraft landing gear.

Classes IPC  ?

  • B64C 25/40 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue un mouvement rotatif étant communiqué aux éléments avant l'impact

84.

MOVEABLE WING TIP ARRANGEMENTS

      
Numéro d'application 18066502
Statut En instance
Date de dépôt 2022-12-15
Date de la première publication 2023-06-22
Propriétaire Airbus Operations Limited (Royaume‑Uni)
Inventeur(s) Bate, Christopher Alan

Abrégé

A wing assembly for an aircraft has a wing, a moveable wing tip device and an actuation assembly to move the wing tip device. The actuation assembly is disposed externally of the wing assembly. In a further aspect, the actuation assembly has a first connector member connected externally of the wing assembly at the actuator and pivotably connected at a lower portion of the wing or wing tip. This can facilitate the provision of effective internal supporting structure for transferring flight loads across the interface of the wing and wing tip device, especially in wing assemblies having a high aspect ratio. In a still further aspect, the wing assembly has a seal extending chordwise within the wing assembly, for resisting passage of air through an interface region between the wing and the wing tip device.

Classes IPC  ?

  • B64C 3/56 - Repliage ou rabattement pour réduire l'encombrement de l'aéronef
  • B64C 23/06 - Moyens permettant d'influencer l'écoulement d'air sur les surfaces des aéronefs, non prévus ailleurs par génération de tourbillons

85.

BARREL NUT POSITIONING FRAME

      
Numéro d'application 18079356
Statut En instance
Date de dépôt 2022-12-12
Date de la première publication 2023-06-15
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s) Tulloch, William

Abrégé

A barrel nut positioning frame for maintaining a barrel nut in a desired position in a bore of a component is disclosed having a frame body configured to receive a barrel nut therein, the frame body being adapted to fit, together with a received barrel nut, within a bore, and a bore engagement element configured to engage with a positioning feature in the bore so as to restrict movement of the frame within the bore.

Classes IPC  ?

  • F16B 37/04 - Dispositifs pour fixer les écrous à des surfaces, p.ex. à des feuilles, à des plaques
  • F16B 39/24 - Blocage des vis, boulons ou écrous dans lequel le verrouillage se fait en même temps que le vissage ou le serrage par rondelles, rondelles à ressort ou plaques élastiques qui bloquent contre l'objet

86.

KIT OF PARTS FOR FORMING AN AEROFOIL ASSEMBLY

      
Numéro d'application 17952900
Statut En instance
Date de dépôt 2022-09-26
Date de la première publication 2023-06-08
Propriétaire Airbus Operations Limited (Royaume‑Uni)
Inventeur(s) Ibanez-Gil, German

Abrégé

A kit of parts for forming an aerofoil assembly is disclosed having a torsion box structure including a first attachment point and a second attachment point, the first and second attachment points being separated from each other along a separation axis, and a fixed leading or trailing edge structure including corresponding first and second attachment points, wherein a first structure includes a slidebly mounted abutment piece slideable along a slide path extending in a direction parallel to the separation axis and a fixing mechanism for fixing the slidebly mounted abutment piece. A second structure includes a corresponding abutment feature having a first abutment surface facing in a direction parallel to the separation axis of the second structure, such that, in use, the abutment piece prevents relative movement of the first and second structures.

Classes IPC  ?

  • B64C 3/28 - Bords d'attaque ou de fuite fixés aux structures primaires, p.ex. formant des fentes fixes

87.

TEMPERATURE SENSING DEVICE WITH ANTENNA

      
Numéro d'application 18071437
Statut En instance
Date de dépôt 2022-11-29
Date de la première publication 2023-06-01
Propriétaire
  • AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
  • AIRBUS OPERATIONS (SAS) (France)
Inventeur(s)
  • Da Cunha, Mauricio Pereira
  • Lad, Robert J.
  • White, Ian
  • Bruggemann, Kurt
  • Downing, Richard
  • Consola, Maud

Abrégé

A temperature sensing device for sensing aircraft wheel brake temperature is disclosed including a sensor antenna electrically coupled to a surface acoustic wave, SAW, sensor element, wherein: the sensor antenna comprises a conductive loop disposed on a surface of a substrate, the conductive loop surrounding an attachment region of the substrate, the attachment region having substantially no conductor material thereon. Also disclosed is a brake disc for an aircraft wheel brake comprising the temperature sensing device, and aircraft comprising the brake disc and a method of manufacturing a temperature sensing device.

Classes IPC  ?

  • G01K 11/26 - Mesure de la température basée sur les variations physiques ou chimiques, n'entrant pas dans les groupes , , ou utilisant la mesure d'effets acoustiques de fréquences de résonance
  • B60C 23/20 - Dispositifs pour mesurer ou signaler la température des pneumatiques
  • G01K 1/14 - Supports; Dispositifs de fixation; Dispositions pour le montage de thermomètres en des endroits particuliers

88.

HOLDER FOR COMPONENT OF TEMPERATURE SENSING SYSTEM

      
Numéro d'application 18071464
Statut En instance
Date de dépôt 2022-11-29
Date de la première publication 2023-06-01
Propriétaire
  • Airbus Operations Limited (Royaume‑Uni)
  • Airbus Operations (SAS) (France)
Inventeur(s)
  • Da Cunha, Mauricio Pereira
  • Lad, Robert J.
  • White, Ian
  • Bruggemann, Kurt
  • Downing, Richard
  • Consola, Maud

Abrégé

A holder for a wireless relay device is disclosed including a rigid hollow arm member to be received in a groove in a torque tube spline of an aircraft wheel brake; and a support member to support the wireless relay device, the support member mechanically coupled to the rigid hollow arm member towards a first end of the rigid hollow arm member, wherein: the rigid hollow arm member provides a conduit for a communications cable to couple to the wireless relay device. Also disclosed is an aircraft wheel brake comprising the holder and an aircraft comprising the aircraft wheel brake.

Classes IPC  ?

  • G01K 1/14 - Supports; Dispositifs de fixation; Dispositions pour le montage de thermomètres en des endroits particuliers
  • G01K 11/26 - Mesure de la température basée sur les variations physiques ou chimiques, n'entrant pas dans les groupes , , ou utilisant la mesure d'effets acoustiques de fréquences de résonance
  • G01K 1/024 - Moyens d’indication ou d’enregistrement spécialement adaptés aux thermomètres pour l’indication à distance
  • B64C 25/42 - Aménagement ou adaptation des freins

89.

TEMPERATURE SENSING DEVICE FOR AIRCRAFT WHEEL BRAKE

      
Numéro d'application 18071529
Statut En instance
Date de dépôt 2022-11-29
Date de la première publication 2023-06-01
Propriétaire
  • AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
  • AIRBUS OPERATIONS (SAS) (France)
Inventeur(s)
  • Da Cunha, Mauricio Pereira
  • Lad, Robert J.
  • White, Ian
  • Bruggemann, Kurt
  • Downing, Richard
  • Consola, Maud

Abrégé

A temperature sensing device for sensing aircraft wheel brake temperature, the temperature sensing device including a surface acoustic wave, SAW, sensor element with a resonant frequency within a frequency range between 175 megahertz and 190 megahertz at a predetermined temperature. The temperature sensing system also includes a wireless relay device, a method for sensing temperature of a wheel brake of an aircraft.

Classes IPC  ?

  • B64C 25/42 - Aménagement ou adaptation des freins
  • G01K 11/26 - Mesure de la température basée sur les variations physiques ou chimiques, n'entrant pas dans les groupes , , ou utilisant la mesure d'effets acoustiques de fréquences de résonance

90.

AERODYNAMIC CONTROL SURFACE

      
Numéro d'application 17993176
Statut En instance
Date de dépôt 2022-11-23
Date de la première publication 2023-06-01
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s) Healy, Daren

Abrégé

An aerodynamic control surface assembly includes a structure (2) with an aerodynamic surface (8) and a curved aerodynamic control surface (20) configured to move between an extended (24) and a retracted position (22). The aerodynamic control surface is arranged to deploy through an aperture (18) in the aerodynamic surface and into an oncoming airflow (A). An actuation mechanism (52, 152, 252) coupled to the aerodynamic control surface (20) moves the aerodynamic control surface (20) between extended and retracted positions. The actuation mechanism (52, 152, 252) is configured such that the control surface (20) follows a curved kinematic path (40, 140, 240) as the control surface moves between the extended (24) and retracted positions (22). The actuation mechanism (52, 152, 252) remains fully behind the aerodynamic surface (8) throughout the movement of the aerodynamic control surface (20) between the extended (24) and retracted positions (22).

Classes IPC  ?

  • B64C 13/38 - Dispositifs de transmission avec amplification de puissance
  • B64C 9/10 - Surfaces ou éléments de commande réglables, p.ex. gouvernes de direction dont une surface est réglée par le mouvement d'une autre, p.ex. servo-compensateurs
  • B64C 1/00 - Fuselages; Caractéristiques structurales communes aux fuselages, voilures, surfaces stabilisatrices ou organes apparentés
  • B64C 21/08 - Moyens permettant d'influencer l'écoulement d'air sur les surfaces des aéronefs en agissant sur la couche limite par utilisation de fentes, de conduits, de surfaces poreuses ou de dispositifs similaires réglables

91.

WINGLET AND WINGLET COVER ASSEMBLY

      
Numéro d'application 18102469
Statut En instance
Date de dépôt 2023-01-27
Date de la première publication 2023-06-01
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s)
  • Barnett, Thomas
  • Scaife, Andrew
  • Proudler, Lee
  • Hewson, Richard

Abrégé

A winglet is disclosed including first and second covers, a front spar, a rear spar, a rib, and a mid spar between the front spar and the rear spar. The rib and each spar are joined to the first cover and to the second cover. The mid spar has a length and the mid spar curves along all or part of its length. The length of the mid spar extends from an inboard end of the mid spar to an outboard end of the mid spar, and the rib wraps around the inboard or outboard end of the mid spar.

Classes IPC  ?

  • B64C 23/06 - Moyens permettant d'influencer l'écoulement d'air sur les surfaces des aéronefs, non prévus ailleurs par génération de tourbillons
  • B64C 3/18 - Longerons; Nervures; Lisses

92.

AIRCRAFT SYSTEM AND METHOD

      
Numéro d'application 17978757
Statut En instance
Date de dépôt 2022-11-01
Date de la première publication 2023-06-01
Propriétaire
  • Airbus Operations Limited (Royaume‑Uni)
  • Airbus Operations GmbH (Allemagne)
  • Airbus Operations (S.A.S.) (France)
Inventeur(s)
  • Bill, Andrew
  • Marwedel, Stephan
  • Duchossoy, Christelle

Abrégé

A method of communicating configuration data of a tire pressure monitoring device configured to be affixed to a wheel in use. The method includes, at the tire pressure monitoring device, receiving a request to confirm configuration data, and responsive to receipt of the request to confirm configuration data, transmitting a configuration data signal which encodes the configuration data. The configuration data signal is configured to be received and understood by a human. The configuration data signal is indicative of any of an aircraft wheel location at which the tire pressure monitoring device is intended to be located, and a security code representative of security parameters of the tire pressure monitoring device

Classes IPC  ?

  • B60C 23/04 - Dispositifs avertisseurs actionnés par la pression du pneumatique montés sur la roue ou le pneumatique

93.

WHEEL BRAKE AND TEMPERATURE SENSING DEVICE

      
Numéro d'application 18071047
Statut En instance
Date de dépôt 2022-11-29
Date de la première publication 2023-06-01
Propriétaire
  • AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
  • AIRBUS OPERATIONS (SAS) (France)
Inventeur(s)
  • Da Cunha, Mauricio Pereira
  • Lad, Robert J.
  • White, Ian
  • Bruggemann, Kurt
  • Downing, Richard
  • Consola, Maud

Abrégé

A brake disc for an aircraft wheel brake including: a temperature sensing device comprising a surface acoustic wave (SAW) sensor element and a sensor antenna, wherein the temperature sensing device is attached to the brake disc by means of a ceramic adhesive and one or more ceramic bolts. A method of attaching a temperature sensing device to a brake disc of an aircraft wheel brake.

Classes IPC  ?

  • F16D 66/00 - Dispositions pour la surveillance des conditions de fonctionnement des freins, p.ex. de l'usure ou de la température
  • G01K 11/26 - Mesure de la température basée sur les variations physiques ou chimiques, n'entrant pas dans les groupes , , ou utilisant la mesure d'effets acoustiques de fréquences de résonance
  • G01K 1/14 - Supports; Dispositifs de fixation; Dispositions pour le montage de thermomètres en des endroits particuliers
  • B64C 25/42 - Aménagement ou adaptation des freins

94.

TEMPERATURE SENSING DEVICE FOR AIRCRAFT WHEEL BRAKE

      
Numéro d'application 18071188
Statut En instance
Date de dépôt 2022-11-29
Date de la première publication 2023-06-01
Propriétaire
  • AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
  • AIRBUS OPERATIONS (SAS) (France)
Inventeur(s)
  • Da Cunha, Mauricio Pereira
  • Lad, Robert J.
  • White, Ian
  • Bruggemann, Kurt
  • Downing, Richard
  • Consola, Maud

Abrégé

A temperature sensing device for sensing aircraft wheel brake temperature, the temperature sensing device including: a surface acoustic wave (SAW) sensor element having an interdigital transducer that has electrodes disposed along the surface of a substrate forming a periodic structure. The electrodes having a thickness, in a direction perpendicular to the surface, of between 120 and 190 nanometres.

Classes IPC  ?

  • G01K 11/26 - Mesure de la température basée sur les variations physiques ou chimiques, n'entrant pas dans les groupes , , ou utilisant la mesure d'effets acoustiques de fréquences de résonance
  • B64C 25/42 - Aménagement ou adaptation des freins
  • F16D 66/00 - Dispositions pour la surveillance des conditions de fonctionnement des freins, p.ex. de l'usure ou de la température

95.

CABLE STRUCTURE FOR USE IN AIRCRAFT WHEEL BRAKES

      
Numéro d'application 18071493
Statut En instance
Date de dépôt 2022-11-29
Date de la première publication 2023-06-01
Propriétaire
  • AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
  • Airbus Operations (SAS) (France)
Inventeur(s)
  • Da Cunha, Mauricio Pereira
  • Lad, Robert J.
  • White, Ian
  • Bruggemann, Kurt
  • Downing, Richard
  • Consola, Maud

Abrégé

A cable structure to carry signals to and from a component of a temperature sensing arrangement in an aircraft wheel brake is disclosed including elongate elements including a plurality of cables and/or wires, one or more ceramic spacer layers, a ceramic cover layer and a metallic layer surrounding the one or more ceramic spacer layers and the ceramic cover layer. Also disclosed is an aircraft wheel brake comprising the cable structure and an aircraft comprising the aircraft wheel brake.

Classes IPC  ?

  • B64C 25/42 - Aménagement ou adaptation des freins
  • B60T 17/22 - Dispositifs pour surveiller ou vérifier les systèmes de freins; Dispositifs de signalisation

96.

TEMPERATURE SENSING DEVICE FOR AIRCRAFT WHEEL BRAKE

      
Numéro d'application 18071506
Statut En instance
Date de dépôt 2022-11-29
Date de la première publication 2023-06-01
Propriétaire
  • AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
  • Airbus Operations (SAS) (France)
Inventeur(s)
  • Da Cunha, Mauricio Pereira
  • Lad, Robert J.
  • White, Ian
  • Bruggemann, Kurt
  • Downing, Richard
  • Consola, Maud

Abrégé

A temperature sensing device to sense aircraft wheel brake temperature is disclosed including a sensing device substrate; and one or more package layers attached to the sensing device substrate, wherein: the sensing device substrate carries one or more electronic components for sensing temperature. Also disclosed is a wireless relay device to wirelessly transmit an interrogation signal to a temperature sensing device and wirelessly receive an output signal from the temperature sensing device, the temperature sensing device to sense aircraft wheel brake temperature, the wireless relay device comprising: a relay substrate; and one or more package layers attached to the relay substrate, wherein: the relay substrate carries one or more electronic components of the wireless relay device. Also disclosed is a method of manufacturing a temperature sensing device to sense aircraft wheel brake temperature.

Classes IPC  ?

  • G01K 11/26 - Mesure de la température basée sur les variations physiques ou chimiques, n'entrant pas dans les groupes , , ou utilisant la mesure d'effets acoustiques de fréquences de résonance
  • G01K 1/024 - Moyens d’indication ou d’enregistrement spécialement adaptés aux thermomètres pour l’indication à distance
  • G01K 1/08 - Dispositifs de protection, p.ex. étuis

97.

AIRCRAFT LANDING GEAR BAY DOOR

      
Numéro d'application 17992731
Statut En instance
Date de dépôt 2022-11-22
Date de la première publication 2023-05-25
Propriétaire
  • AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
  • AIRBUS OPERATIONS GMBH (Allemagne)
  • AIRBUS OPERATIONS (S.A.S.) (France)
Inventeur(s)
  • Scotto, Aline
  • Itasse, Maxime
  • Büscher, Alexander
  • Perkins, Christopher
  • Mann, Alan
  • Ip, Kevin
  • Lyons, Neil
  • Mills, Robert

Abrégé

An aircraft landing gear bay door 140 including an attachment mechanism suitable for pivotally mounting the door to an aircraft, a first side 141 arranged to face inwardly in relation to the aircraft landing gear bay when the door is closed and face towards one side of a main leg of the landing gear when the door is open and the landing gear is deployed, and a second opposite side 142. The shape formed from the first and second sides provides an aerofoil profile of the door. The invention also provides an aircraft landing gear arrangement 100, an aircraft 1000, methods of operating an aircraft and a method of reducing noise.

Classes IPC  ?

  • B64C 25/16 - Carénages mobiles en liaison avec des éléments de l'atterrisseur
  • B64C 25/20 - Mécanismes de manœuvre mécaniques
  • B64C 25/36 - Aménagements ou adaptations des roues, des pneumatiques ou des essieux
  • G10K 11/16 - Procédés ou dispositifs de protection contre le bruit ou les autres ondes acoustiques ou pour amortir ceux-ci, en général

98.

SENSOR ASSEMBLY

      
Numéro d'application 17915978
Statut En instance
Date de dépôt 2021-03-30
Date de la première publication 2023-05-11
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s)
  • Barad, Kayvon
  • Wood, Christopher
  • Ramshaw, Andrew

Abrégé

An assembly having a bearing with an axis of rotation, and a fibre-based sensor for sensing strain or temperature of the bearing is disclosed. The sensor extends in a direction parallel to the axis of rotation. An aircraft system is disclosed including a wheel supported on an axle by a first bearing and a second bearing. The system further includes a first fibre optic sensor for sensing a strain or temperature of the first bearing, a second fibre optic sensor for sensing a strain or temperature of the second bearing, and an interrogator to analyse optical signals from the sensors to determine differences in the strains or temperatures of the first bearing and the second bearing.

Classes IPC  ?

  • G01L 1/24 - Mesure des forces ou des contraintes, en général en mesurant les variations des propriétés optiques du matériau quand il est soumis à une contrainte, p.ex. par l'analyse des contraintes par photo-élasticité
  • G01L 5/00 - Appareils ou procédés pour la mesure des forces, du travail, de la puissance mécanique ou du couple, spécialement adaptés à des fins spécifiques
  • G01K 11/3206 - Mesure de la température basée sur les variations physiques ou chimiques, n'entrant pas dans les groupes , , ou utilisant des changements dans la transmittance, la diffusion ou la luminescence dans les fibres optiques en des endroits distincts de la fibre, p.ex. utilisant la diffusion de Bragg

99.

PANEL ASSEMBLY

      
Numéro d'application 17981861
Statut En instance
Date de dépôt 2022-11-07
Date de la première publication 2023-05-11
Propriétaire Airbus Operations Limited (Royaume‑Uni)
Inventeur(s)
  • Gaitonde, John Martin
  • Heaysman, Chris

Abrégé

A panel assembly is disclosed having a panel, a beam attached to the panel, and a plurality of stiffeners attached to the panel. Each stiffener includes a respective bridge which crosses over the beam at an intersection from a first side of the beam to a second side of the beam. Each bridge has an outer surface facing away from the panel and an inner surface facing towards the panel. The inner surface of each bridge deviates away from the panel to form a recess at the intersection, and the outer surface of each bridge deviates away from the panel to form a protrusion at the intersection.

Classes IPC  ?

  • B64C 3/18 - Longerons; Nervures; Lisses
  • B64C 3/26 - Construction, forme ou fixation des revêtements distincts, p.ex. panneaux

100.

STIFFENER WITH CORE AND SHELL

      
Numéro d'application 17982301
Statut En instance
Date de dépôt 2022-11-07
Date de la première publication 2023-05-11
Propriétaire AIRBUS OPERATIONS LIMITED (Royaume‑Uni)
Inventeur(s)
  • Gaitonde, John Martin
  • Heaysman, Chris

Abrégé

A stiffener is disclosed including a core and a shell which surrounds the core. The shell is formed from a fibre material, and the core includes first and second battens arranged side by side, and a foam spacer between the battens. The stiffener extends in a lengthwise direction, and the battens and the foam spacer have respective lengths which extend in the lengthwise direction of the stiffener. The core is assembled with the spacer between the battens, then surrounded with the shell. The stiffener may be a stringer for an aircraft wing.

Classes IPC  ?

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