An aircraft pylon mounting fitting comprising a connecting portion and a clevis portion, wherein the connecting portion is configured for attaching to an aircraft wing structure, tail structure or fuselage structure, and wherein the clevis portion comprises mutually-opposing first and second fork parts arranged to receive a lug of a pylon therebetween, the first fork part incorporating a first bore and the second fork part incorporating a second bore, the first and second bores being configured to receive a pin or bolt for attaching the clevis portion to the lug of the pylon; wherein at least the first bore incorporates an eccentric bush. Also provided is an aircraft wing-to-pylon subassembly comprising: a wing structure; a pylon; and a pylon mounting fitting as outlined above, wherein the connecting portion is attached to the wing structure and the clevis portion is attached to a lug of the pylon by a pin or bolt passing through the first and second bores and the lug of the pylon. Aircraft tail-to-pylon and fuselage-to-pylon subassemblies are similarly provided. An aircraft comprising one or more such subassemblies is also provided, as is a method of constructing such a subassembly.
An aircraft component (800) comprising a curved composite panel (700) having a stiffener support region (709) is disclosed. The stiffener support region (709) is substantially planar along a first direction (Y) of the panel (700) and is formed by a resin-infused fibre preform (300). The composite panel (700) also comprises a curved region (707) which is curved along the first direction (Y) of the panel (700) and is formed by a further resin infused fibre preform (200). Methods of manufacturing the aircraft component (800) are also disclosed.
An aircraft component (800) comprising a curved composite panel (700) having a stiffener support region (709) is disclosed. The stiffener support region (709) is substantially planar along a first direction (Y) of the panel (700) and is formed by a resin-infused fibre preform (300). The composite panel (700) also comprises a curved region (707) which is curved along the first direction (Y) of the panel (700) and is formed by a further resin infused fibre preform (200). Methods of manufacturing the aircraft component (800) are also disclosed.
FIG. 9 to accompany abstract on publication.
B29C 70/34 - Façonnage par empilage, c.-à-d. application de fibres, de bandes ou de feuilles larges sur un moule, un gabarit ou un noyauFaçonnage par pistolage, c.-à-d. pulvérisation de fibres sur un moule, un gabarit ou un noyau et façonnage ou imprégnation par compression
An aircraft fuel delivery system having a first tank for storing a first fluid, second tank for storing a second fluid and a shut-off valve. The shut-off valve includes a first inlet port for introducing the first fluid into an internal valve chamber and a second inlet port for introducing the second fluid into the internal valve chamber such that the second fluid can be combined with the first fluid to create a fluid mixture. The shut-off valve also includes a valve member the position of which can be adjusted for controlling the delivery of the first fluid and/or the fluid mixture to the aircraft power plant.
A non-crimp fabric blanket includes fiber reinforced plies stitched together. At least one of the plies includes continuous fibers having a first fiber orientation in a first region in a plane of the ply, and a second fiber orientation in a second region in the plane of the ply. The second fiber orientation is different than the first fiber orientation.
D04H 3/05 - Non-tissés formés uniquement ou principalement de fils ou de matériaux filamenteux similaires de bonne longueur caractérisés par la méthode de formation des voiles ou couches, p. ex. par la réorientation des fils ou filaments dans un autre dessin, p. ex. zig-zag, sinusoïde
D04H 3/115 - Non-tissés formés uniquement ou principalement de fils ou de matériaux filamenteux similaires de bonne longueur caractérisés par la méthode de renforcement ou de consolidation avec liages faits mécaniquement entre fils et filaments par application ou insertion d'éléments de liage filamenteux
An aircraft wing assembly, comprising: a stringer, the stringer comprising a first flange, a second flange, and a web extending between, and connecting, the first flange and the second flange; a skin section; and a rib; wherein the first flange is joined to the skin section and the second flange is joined to the rib. Also a method of fabricating the aircraft wing assembly and an aircraft comprising the aircraft wing assembly.
A pipe assembly with first and second tubular pipe sections and fastener system fastening the sections defining a flow path. The first section extends along a common central axis. The second tubular pipe section extends along the common central axis. The fastener system includes a first fastener sub-system having a first component on the first tubular pipe section and a first fastener fastening the first component to a second engagement feature. The first engagement feature is between the first component and second engagement feature restricting movement of the first tubular pipe section. A second fastener sub-system has a second component on the second tubular pipe section and a second fastener fastening the second component to the first engagement feature. The second engagement feature is between the second component and the first engagement feature restricting movement of the first tubular pipe section.
F16L 19/02 - Extrémités de tuyaux pourvues de colliers ou de brides formant corps ou non avec les tuyaux, maintenues en contact par un organe vissé
B64D 37/00 - Aménagements relatifs à l'alimentation des groupes moteurs en carburant
F16L 19/025 - Extrémités de tuyaux pourvues de colliers ou de brides formant corps ou non avec les tuyaux, maintenues en contact par un organe vissé les colliers ou les brides formant partie intégrante des extrémités du tuyau
7.
RAMPED COMPOSITE STRUCTURAL MEMBER FOR AIRCRAFT, AND METHOD OF FORMING THE SAME
A composite structural member for an aircraft, the composite structural member having a ramped region and comprising a plurality of composite plies arranged upon one another in a thickness direction; wherein, in the ramped region, the composite plies include at least first and second subsets of composite plies, each subset comprising a plurality of composite plies; and wherein the second subset of composite plies is staggered in a ramp direction relative to the first subset of composite plies, the staggering producing a flat surface region on the second subset of composite plies, suitable for seating a fastener thereon in use. A method of forming such a composite structural member by resin transfer moulding, and a method of designing such a composite structural member, are also provided.
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 noyauFaçonnage par pistolage, c.-à-d. pulvérisation de fibres sur un moule, un gabarit ou un noyau
B29C 70/48 - Façonnage ou imprégnation par compression pour la fabrication d'objets de longueur définie, c.-à-d. d'objets distincts utilisant des moules opposables, p. ex. pour déformer des préimprégnés [SMC] ou des "prepregs" avec une imprégnation des renforcements dans le moule fermé, p. ex. moulage par transfert de résine [RTM]
B29K 63/00 - Utilisation de résines époxy comme matière de moulage
An aircraft with a first tank suitable for containing fuel, a second tank suitable for containing a second, different fuel or fuel additive, a first fuel line configured to transport the fuel from the first tank to a mixer, a pump arrangement configured to drive a flow of fuel from the first tank along the first fuel line and a second fuel line configured to transport the second, different fuel or fuel additive from the second tank to the mixer. The mixer is configured to mix the fuel and second, different fuel or fuel additive to form a blended fuel. The aircraft also includes a mixer line configured to transport the blended fuel from the mixer to a combustor.
A high lift arrangement for an aircraft wing includes a high lift element arranged to have a deployed position wherein the high lift element extends in front of at least an inboard portion of a leading edge of the wing tip. The high lift element has a sweep angle which is less than the sweep angle of the wing tip, such that a gap is formed between the element and the wing tip. A vortex is generated at the tip of the high lift element to energize the wing tip upper surface boundary layer. The gap accelerates the flow, improving low speed performance of the wing.
B64C 9/22 - Surfaces ou éléments de commande réglables, p. ex. gouvernes de direction formant des fentes à l'avant de l'aile
B64C 9/34 - Surfaces ou éléments de commande réglables, p. ex. gouvernes de direction repliables ou escamotables contre ou à l'intérieur d'autres surfaces ou d'autres éléments
A high lift arrangement for a folding aircraft wing having a wing body with a folding wing tip including a high lift element arranged to have a deployed position in front of the leading edge of the folding wing tip, and an actuator for deploying the element. The actuator is mounted to the wing body such that there is no need for electrical or hydraulic cables to cross the wing fold line.
B64C 9/22 - Surfaces ou éléments de commande réglables, p. ex. gouvernes de direction formant des fentes à l'avant de l'aile
B64C 9/34 - Surfaces ou éléments de commande réglables, p. ex. gouvernes de direction repliables ou escamotables contre ou à l'intérieur d'autres surfaces ou d'autres éléments
A refueling connector has an inner pipe section, for example, defining inner region, for conveying cryogenic hydrogen to an aircraft and an outer pipe section, for example, defining outer region, for holding a vacuum to provide thermal insulation to the inner section. Via one or more suitable valves the connector can, when connected to the aircraft, create a vacuum on the aircraft-side or otherwise convey fluid from/to the aircraft, via the outer pipe section.
F17C 5/02 - Procédés ou appareils pour remplir des récipients sous pression de gaz liquéfiés, solidifiés ou comprimés pour le remplissage avec des gaz liquéfiés
12.
CRYOGENIC TANK COMPRISING AT LEAST ONE ANTI-SLOSHING STRUCTURE, AIRCRAFT COMPRISING AT LEAST ONE TANK OF THIS KIND
A cryogenic tank with at least one enclosure containing a liquid phase and having at least one anti-sloshing structure formed from walls and positioned inside the enclosure and configured to compartmentalize the enclosure and at least one connection system connecting the anti-sloshing structure and the enclosure. Also an aircraft with at least one such tank.
A spark containment cap plate with a base and two or more spark containment caps. Each cap has a cover portion which extends from the base and defines a cavity inside the cap, inside which an end of a fastener is enclosed. Also a fastener joint with a structure; two or more fasteners, each fastener having an end protruding from a surface of the structure; and a spark containment cap plate. The plate has a base and two or more spark containment caps. Each cap has a cover portion extending from the base and defining a cavity inside the spark containment cap inside which the ends of the fasteners. A cured sealing material is provided between the cap plate and the structure which secures the cap plate to the structure in such a position that each end of each fastener is enclosed within a spark containment cap.
An aircraft wing having a fixed wing with a tip, and a wing tip device rotatably mounted on a hinge at the tip of the fixed wing. The wing tip device is rotatable about the hinge. An actuation system rotates the wing tip device about the hinge. The actuation system has a motor, a plurality of geared mechanical actuators, and an angle gearbox coupled between the plurality of geared mechanical actuators and the motor. Each geared mechanical actuator is driveable by the motor and arranged to convert rotary motion into a different rotary motion. Each geared mechanical actuator is arranged along a hinge line of the hinge. The angle gearbox is arranged along the hinge line and between two of the plurality of geared mechanical actuators.
An inerting system, for instance an aircraft enclosure inerting system, is configured to separate an inlet air flow into nitrogen enriched air (NEA) and oxygen enriched air (OEA). The inerting system has a vortex tube with a vortex chamber in which the inlet air flow is separated into the NEA and the OEA. The inlet air flow enters the vortex chamber through an inlet passage which intersects the vortex chamber at a chamber inlet aperture. A warming device of the inerting system warms the inlet passage or the inlet air flow before the inlet air flow gets to the chamber inlet aperture.
B01D 53/24 - Séparation de gaz ou de vapeursRécupération de vapeurs de solvants volatils dans les gazÉpuration chimique ou biologique des gaz résiduaires, p. ex. gaz d'échappement des moteurs à combustion, fumées, vapeurs, gaz de combustion ou aérosols par force centrifuge
B64D 13/06 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacements réservés au fret l'air étant climatisé
B64D 37/32 - Mesures de sécurité non prévues ailleurs, p. ex. contre les explosions
A fuel mixing assembly is disclosed including a fuel vessel, such as a pipe for conveying flow of a first fuel, and a second-fuel conduit for conveying flow of, for example an additive, into the fuel vessel. The fuel mixing assembly further includes a vortex generator, the vortex generator is configured to generate vortices to mix the first fuel and the additive. The additive may be released from an outlet in the vortex generator.
B64D 37/00 - Aménagements relatifs à l'alimentation des groupes moteurs en carburant
B01F 23/40 - Mélange de liquides avec des liquidesÉmulsion
B01F 23/451 - Mélange de liquides avec des liquidesÉmulsion en utilisant le mélange à écoulement en injectant un liquide dans un autre
B01F 25/10 - Mélange en créant un flux tourbillonnaire, p. ex. par l'introduction tangentielle de composants du flux
B01F 25/313 - Mélangeurs à injecteurs dans des conduits ou des tubes dans lesquels circule le composant principal dans lesquels des composants supplémentaires sont introduits au centre du conduit
An aircraft maintenance system, method, and computer-readable storage medium are disclosed. The aircraft maintenance system includes a processor and a storage having a digital twin of at least part of an aircraft and a machine learning classifier. The aircraft maintenance system is configured to obtain aircraft operational data, update the digital twin based on the aircraft operational data, identify an altered operation of the aircraft based on the aircraft operational data, and determine a set of conditions responsible for the altered operation using the machine learning classifier to evaluate the digital twin. Output data indicative of the set of conditions responsible for the altered operation is generated.
B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
G06Q 10/20 - Administration de la réparation ou de la maintenance des produits
G07C 5/00 - Enregistrement ou indication du fonctionnement de véhicules
G07C 5/08 - Enregistrement ou indication de données de marche autres que le temps de circulation, de fonctionnement, d'arrêt ou d'attente, avec ou sans enregistrement des temps de circulation, de fonctionnement, d'arrêt ou d'attente
A method of securing a first structure to a second structure is disclosed including providing a jig assembly having spark containment caps carried by a jig; mounting the jig assembly on a structure so that the spark containment caps and the jig contact the first structure; securing the spark containment caps to the first structure by injecting adhesive material into contact with the first structure and the spark containment caps and then curing the adhesive material; removing the jig after the adhesive material has cured; and securing the first structure to the second structure with fasteners, each fastener having a tail which is inserted through the first and second structures and into a respective one of the spark containment caps.
An enclosure device configured to enclose a concave surface portion of an aerodynamic component of an aircraft wing is disclosed including an aerodynamic component having an enclosure device, and an aircraft wing and aircraft including one or more enclosure devices. Also disclosed is a method of counteracting unwanted airflow circulation in a concave surface portion of an aerodynamic component of an aircraft wing.
A hinge arrangement for an aircraft wing is provided, for providing a folding wingtip. The hinge arrangement comprises a first mount for securing in a first wing section and a second mount for securing to a second relatively foldable wing section, each having a plurality of hinge elements arranged along a hinge axis. The arrangement comprises a latching arrangement for securing the mounts against folding movement, the latch arrangement having a latch axis being spaced from the hinge axis in a substantially spanwise direction for example so as to extend into the wing box. This can provide an efficient arrangement which may be contained within the outer mould line of the wing which can reduce the need for a fairing.
A composite part for a vehicle is provided. The composite part has a first surface and an opposing second surface, wherein at least part of the first surface forms an outer aerodynamic surface of a vehicle. A region of the composite part has a curvature in two orthogonal directions. The composite part has an undulation defining a channel in one of the first surface or the second surface, and a corresponding ridge in the other of the first surface and the second surface.
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 noyauFaçonnage par pistolage, c.-à-d. pulvérisation de fibres sur un moule, un gabarit ou un noyau
B29K 105/08 - Présentation, forme ou état de la matière moulée contenant des agents de renforcement, charges ou inserts de grande longueur, p. ex. ficelles, mèches, mats, tissus ou fils
B29C 70/34 - Façonnage par empilage, c.-à-d. application de fibres, de bandes ou de feuilles larges sur un moule, un gabarit ou un noyauFaçonnage par pistolage, c.-à-d. pulvérisation de fibres sur un moule, un gabarit ou un noyau et façonnage ou imprégnation par compression
B29K 105/00 - Présentation, forme ou état de la matière moulée
A riblet for a fixed leading edge (FLE) assembly is disclosed including a first riblet portion having a first aft mounting for attaching the first riblet portion to a wing box assembly and also having a forward mounting opposite the first aft mounting. The riblet also includes second riblet portion having a second aft mounting for attaching the second riblet portion to the forward mounting of the first riblet portion.
A method for use in assembling an aerofoil structure. A torsion box has a first mounting feature and a second mounting feature. A fixed leading or trailing edge structure has a third mounting feature and a fourth mounting feature. The first mounting feature and the third mounting feature each have a fastener hole prior to aligning the leading or trailing edge structure to the torsion box. The second mounting feature and the fourth mounting feature are without fastener holes for joining the torsion box to the fixed leading or trailing edge structure prior to aligning the leading or trailing edge structure to the torsion box. The method includes aligning the fixed leading or trailing edge structure to the torsion box so as to align the fastener holes of the first mounting feature and the third mounting feature.
An inerting system is provided with a vortex tube for separating air into nitrogen enriched air (NEA) and oxygen enriched air (OEA). The inerting system has a warming device which warms NEA as it flows between an NEA outlet of the vortex tube and an NEA port of the inerting system. A method is also provided of supplying conditioned NEA to an enclosure, in which air is centrifugally separated into NEA and OEA in a vortex tube and the NEA is warmed so as to produce the conditioned NEA.
A method of measuring deformation of a structure by image correlation, including generating a non-periodic tiling with a set of prototiles; generating a non-periodic pattern based on the non-periodic tiling; applying the non-periodic pattern to a structure; generating a reference image of the non-periodic pattern on the structure; generating a deformed image of the non-periodic pattern on the structure; and measuring deformation of the structure by comparing the deformed image with the reference image.
A landing gear assembly for an aircraft with: a forward brace for attaching to an aircraft airframe; an aft brace for attaching to the airframe, the aft brace coupled to the forward brace; a piston pivotally attachable to the airframe; a bellcrank linkage having a first end, a second end, and a pivot point between the ends, wherein the pivot point of the bellcrank linkage is pivotally attachable to the airframe of the aircraft and pivotally coupled to the actuator piston; a primary strut pivotally coupled to the forward brace and the aft brace; and a secondary strut (e.g. a shock absorber) pivotally coupled to the bellcrank linkage and to a pivot point near to the second end of the primary strut. The landing gear assembly is configured to adopt a deployed configuration when the actuator piston is extended and a retracted configuration when the piston is retracted.
A method of processing a piece of composite material for recycling is disclosed using that processed composite material to form a new composite part. The composite material is scored in order to weaken the material and make it more pliable, this scoring creating a series of substantially parallel notches and ridges which may be complementary in size to permit interlocking. The composite material is cut in a different direction to the scoring to form strips suitable for recycling. The strips may be recycled into a new composite part by pressing them in a mould with a resin.
B29C 43/18 - Moulage par pressage, c.-à-d. en appliquant une pression externe pour faire couler la matière à moulerAppareils à cet effet pour la fabrication d'objets de longueur définie, c.-à-d. d'objets séparés en incorporant des parties ou des couches préformées, p. ex. moulage par pressage autour d'inserts ou sur des objets à recouvrir
B29B 17/00 - Récupération de matières plastiques ou d'autres constituants des déchets contenant des matières plastiques
B29C 70/00 - Façonnage de matières composites, c.-à-d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p. ex. des inserts
B29L 31/30 - Véhicules, p. ex. bateaux ou avions, ou éléments de leur carrosserie
A vortex tube assembly for an aircraft enclosure inerting system has a plenum chamber and a swirl generator which has an inlet passage that allows air in the plenum chamber to enter a vortex chamber whereupon the air can be centrifugally separated into nitrogen enriched air (NEA) and oxygen enriched air (OEA). A throttle pin is positioned within the inlet passage, an outer surface of the throttle pin and an inner surface of the inlet passage co-operatively defining a flow path for air to enter the vortex chamber from the plenum chamber. The throttle pin is movable between a restrictive position and a permissive position, with the flow path being more constricted when the throttle pin is in the restrictive position than when the throttle pin is in the permissive position. The throttle pin is biased to the permissive position and movable to the restrictive position against this bias.
A method of clearing a swirl generator of a vortex tube for an aircraft enclosure inerting system. The vortex tube has an inlet chamber and a vortex chamber which can receive air from the inlet chamber via flow paths in the swirl generator. The method comprises operating the vortex tube in a foreign matter clearance mode in which a reversed flow of gas is passed from the vortex chamber into the inlet chamber through the flow paths and dislodges accumulated foreign matter therefrom. Dislodged foreign matter is then exhausted from the vortex tube then the vortex tube is operated in a normal mode of operation.
B04C 5/22 - Appareils dans lesquels la direction axiale du tourbillon est inversée comportant des moyens de nettoyage
A62C 3/08 - Prévention, limitation ou extinction des incendies spécialement adaptées pour des objets ou des endroits particuliers dans les véhicules, p. ex. les véhicules routiers dans les avions
A62C 99/00 - Matière non prévue dans les autres groupes de la présente sous-classe
B01D 53/24 - Séparation de gaz ou de vapeursRécupération de vapeurs de solvants volatils dans les gazÉpuration chimique ou biologique des gaz résiduaires, p. ex. gaz d'échappement des moteurs à combustion, fumées, vapeurs, gaz de combustion ou aérosols par force centrifuge
B04C 5/20 - Appareils dans lesquels la direction axiale du tourbillon est inversée comportant des moyens de chauffage ou de refroidissement, p. ex. de trempage
An inerting system has an inerting apparatus which receives an inlet air flow and separates it into nitrogen enriched air and oxygen enriched air. The inerting system also has an oxygen concentration sensor and a controller connected to the oxygen concentration sensor. The controller adjusts operation of the inerting system during use, based at least in part on feedback received from the oxygen concentration sensor.
Monitoring a landing gear shock absorber by monitoring a tire gas pressure of a landing gear tire; at a first time, when the aircraft is stationary before a flight, recording a first ambient temperature and a first tire gas pressure and recording, at a second time, when the landing gear is unloaded during the flight, a second tire gas pressure and a shock absorber pressure. A second ambient temperature is calculated at the second time and the recorded shock absorber pressure is compared with a predetermined pressure range for the second temperature. An alert is provided if the recorded shock absorber pressure is outside the predetermined pressure range.
A landing gear assembly for an aircraft with a forward brace to attach to an airframe of the aircraft; an aft brace to attach to the airframe and coupled the forward brace; a piston pivotally coupled to forward brace; a bellcrank linkage having a first end, a second end, and a pivot point therebetween such that a first portion of the linkage extends from the first end to the pivot point, and a second portion of the linkage extends from the pivot point to the second end, and the pivot point is pivotally coupled to the aft brace and to the piston; a primary strut pivotally coupled to forward brace and the aft brace; and a secondary strut pivotally coupled to linkage and a pivot point proximate the primary strut. The assembly has a deployed configuration when the piston is retracted, and a retracted configuration when the piston is extended.
B64C 25/26 - Systèmes de commande ou de verrouillage à cet effet
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
An aircraft wing including: a wing structure supporting a wing cover, the wing cover having an outer aerodynamic surface, which forms part of an aerofoil profile of the wing, and a recess stepped back from the wing aerofoil profile; and a spoiler device includes a spoiler coupled to the wing structure by a spoiler actuation mechanism for moving the spoiler between a retracted position and a deployed position, the spoiler having a surface which follows a contour of the wing aerofoil profile and where the spoiler is housed entirely in the recess when the spoiler is in the retracted position, and wherein the spoiler surface is extended away from the wing cover when the spoiler is in the deployed position.
B64C 9/34 - Surfaces ou éléments de commande réglables, p. ex. gouvernes de direction repliables ou escamotables contre ou à l'intérieur d'autres surfaces ou d'autres éléments
An aircraft wing assembly with a fixed wing and a wing tip device are disclosed. The wing tip device is moveable between a flight configuration and a ground configuration. In the ground configuration the span of the aircraft wing assembly is reduced. The fixed wing includes a fixed wing lug and the wing tip device comprises a wing tip lug. A locking pin is provided. In the flight configuration the fixed wing lug and wing tip device lug are aligned such that the locking pin may be inserted through the fixed wing lug and wing tip device lug into a locking position to lock the wing tip device in the flight configuration. The locking pin is hollow and includes a heating element.
B64C 3/56 - Repliage ou rabattement pour réduire l'encombrement de l'aéronef
B64D 15/12 - Dégivrage ou antigivre des surfaces externes des aéronefs par chauffage électrique
H05B 3/26 - Éléments chauffants ayant une surface s'étendant essentiellement dans deux dimensions, p. ex. plaques chauffantes non flexibles le conducteur chauffant monté sur une base isolante
A wing hinge assembly is disclosed a wing tip fitting pivotally mounted to a fixed wing fitting. The wing tip fitting is rotatable about a hinge axis (H) with respect to the fixed wing fitting. One of the wing tip fittings and the fixed wing fitting defines a locking channel. The other of the wing tip fitting and the fixed wing fitting includes a locking member which defines a locking member axis. The wing hinge assembly is configurable to a locked configuration in which the locking member is received in the locking channel by moving the locking member in a direction perpendicular to the locking member axis.
A wing assembly for an aircraft including a fixed wing and a wing tip device rotatable about a joint assembly. The wing assembly is configurable between a flight configuration for use during flight and a ground configuration for use during ground-based operations. The wing assembly includes joint-bordering structure located adjacent the joint assembly, the joint-bordering structure having a rib, an upper cover and a lower cover. The joint assembly includes a moveable panel. The panel includes a first hard stop element, and the joint-bordering structure includes a second hard stop element. The first hard stop element is integrally formed in the panel, and the second hard stop element is integrally formed in one of the rib, the upper cover or the lower cover of the joint-bordering structure. The hard stop elements may be configured to self-align.
An aircraft wing is disclosed having a fixed wing with a tip, and a wing tip device rotatably mounted on a hinge at the tip of the fixed wing, such that the wing tip device is rotatable about the hinge, and an actuation system for rotating the wing tip device about the hinge. The actuation system includes a motor, at least one geared rotary actuator, a reduction gearbox, a clutch for selectively decoupling rotation of the motor from rotation of the geared rotary actuator, the geared rotary actuator is driveable by the motor and arranged to convert rotary motion into a different rotary motion and is arranged to rotate the wing tip device relative to the tip of the fixed wing. The reduction gearbox is positioned between the clutch and the geared rotary actuator along a drive train between the motor and the geared rotary actuator.
A latch mechanism for locking an aircraft folding wing is disclosed including at least one lug having an aperture and a latch pin moveable within the aperture between a latched configuration in which the latch pin is received in the aperture, and an unlatched configuration in which the latch pin is withdrawn from the aperture. At least part of one of the pin and the aperture has a hydrophobic coating. A hydrophobic coating may be applied to all apertures in the mechanism and/or to the latch pin. The provision of a hydrophobic coating helps to prevent the formation of moisture and hence ice on the latch pin and/or in the aperture, which ice can inhibit the pin from moving along the aperture into and out of its latching position.
An aircraft assembly includes an aircraft structure, a flexible panel having a supported end attached to the aircraft structure and configured to bend about the supported end relative to the aircraft structure. A rigid stopper extends from and fixedly attached to the aircraft structure and is configured to restrict bending of the flexible panel about the supported end in a first direction and permit bending of the flexible panel in an opposing second direction. The flexible panel has a first deformed configuration wherein the flexible panel is bent towards the rigid stopper in the first direction and abuts the rigid stopper and the rigid stopper restricts bending of the flexible panel in the first direction. The flexible panel has a second deformed configuration wherein the flexible panel is bent away from the rigid stopper in the second direction and spaced from the rigid stopper in the second direction.
An aircraft wing assembly (31) is disclosed. The aircraft wing assembly (31) comprises a wing tip device (11) rotatable about a hinge axis (H) between a flight configuration and a ground configuration and a wing tip device actuation system (20) comprising a bell crank (21) and a linear actuator (23). The bell crank (21) is rotatably mounted to the aircraft wing assembly (31) and is rotatable about a bell crank axis (C) which is offset from the hinge axis (H). The linear actuator (23) is operable to rotate the bell crank (21) about the bell crank axis (C) to thereby move the wing tip device (11) about the hinge axis (H), between the flight configuration and the ground configuration.
A valve apparatus for a fluid delivery system is disclosed having a valve housing including a fluid flow path, a valve member, a valve actuator operably connected to the valve member and configured to move the valve member between first and second positions, and a thermally-activated locking mechanism which provides the valve apparatus with an additional passive safety feature which will automatically lock and inhibit movement of the valve member upon reaching a pre-determined activation temperature.
A cryogenic liquid storage system is disclosed having an outer tank; an inner tank inside the outer tank and configured to store a cryogenic liquid; an isolation valve; a collection chamber outside the outer tank and fluidically connected to the inner tank to enable fluid to flow from the inner tank to the collection chamber via the isolation valve, and the isolation valve can be actuated to isolate the collection chamber from the inner tank; and a measurement probe movable between the inner tank and the collection chamber.
F17C 5/02 - Procédés ou appareils pour remplir des récipients sous pression de gaz liquéfiés, solidifiés ou comprimés pour le remplissage avec des gaz liquéfiés
An aircraft including a control system configured to receive: an indication of the deceleration of the aircraft during landing, an indication of a target deceleration level for the aircraft, and an indication of factors that might prevent the aircraft from meeting that target deceleration level. The control system is configured to output a command to indicate to the pilot that the target deceleration level of the aircraft is not being met. The control system is configured to indicate whether this was caused by one of the brake systems of the aircraft being skid-limited or whether the aircraft is achieving maximum available braking and is still not able to meet the target deceleration level. The control system may be retrofitted by the installation of software on an existing aircraft. A method for determining and indicating scenarios that limit the aircraft's ability to decelerate during landing.
A wing assembly for an aircraft, the wing assembly having a fixed wing and a wing tip device moveably mounted at the end of the fixed wing. A wiring harness extends between the fixed wing and the wing tip device, a length of the wiring harness being encased in a length of protective sleeve. The protective sleeve is pre-shaped, for example pre-molded, to follow a path along a helical curve.
B64C 3/38 - Réglage des ailes complètes ou de certaines parties de ces ailes
H02G 3/40 - Installations de câbles ou de lignes dans les murs, les sols ou les plafonds les câbles ou lignes étant installés dans des conduits ou des canalisations préétablis utilisant des tubes de protection séparés dans les conduits ou les canalisations
A mold for molding a sleeve of protective material onto a wiring harness. The mold includes: a mold body; an inlet; an outlet; and a channel extending through the mold body and connecting the inlet to the outlet. The mold also has a plurality of centralizing spacers, configured to hold the wiring harness centrally within the channel as the wiring harness extends between the inlet and the outlet. The mold also includes an injection port and an exit port arranged to convey fluid sleeve material into and out of the channel. The channel follows a path along a helical curve as it extends between the inlet and the outlet of the mold.
B29C 45/14 - Moulage par injection, c.-à-d. en forçant un volume déterminé de matière à mouler par une buse d'injection dans un moule ferméAppareils à cet effet en incorporant des parties ou des couches préformées, p. ex. moulage par injection autour d'inserts ou sur des objets à recouvrir
The invention provides an aircraft wing with a wing tip device movable between a flight configuration for use during flight and a ground configuration for use during ground-based operations. In the 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 fixed wing and the wing tip device. The hinge arrangement comprises a plurality of fixed wing interface rings, a plurality of wing tip device interface rings, and a geared rotary actuator (GRA) partially located within the fixed wing interface rings and wing tip device interface rings. The GRA is arranged to drive the wing tip device interface rings to move the wing tip device between the flight configuration and ground configuration.
An aircraft has a landing gear with a main leg, a support leg, and a wheel arm which has a wheel support and is pivotably connected to the main leg and support leg. The main leg and support leg are pivotably connected to the airframe of the aircraft, and can be pivoted aft to move the wheel arm aft and upward and move the landing gear from a deployed configuration to a stowed configuration. With the landing gear in the deployed configuration, the support leg is positioned forward of the main leg. The main leg, support leg and wheel arm form a triple-rocker four bar linkage such that pivoting the main leg and support leg aft pivots the wheel arm and retracts the wheel support.
An aircraft wing tip that is movable by an actuator between a flight configuration, and a ground configuration which has a shorter wingspan for use in ground-based operations. Lugs that connect to arms of the actuator are integrally formed as part of the primary structure of either the fixed wing or outboard wing section, such as a folding tip section.
A structure for refuelling an aircraft with cryogenic fuel includes a walkway to allow personnel to access the aircraft and a pipework arrangement attached to the walkway. The pipework arrangement includes a feed line, a return line and a bypass valve between the feed line and the return line and fluidically connecting the inlet line to the return line. A first end of the feed line is configured to connect to a source of cryogenic fuel, and a second, opposite end of the feed line is configured to connect to the aircraft. The bypass valve is switchable between a refuelling configuration in which the bypass valve prevents fluid flow between the feed line and return line through the bypass valve, and a chill down configuration in which the bypass valve allows fluid flow between the feed line and the return line through the bypass valve.
A compliant mount for an aircraft, for attaching equipment (such as a latching unit, for example) to a structural member of the aircraft, the compliant mount comprising: a mounting member for attachment to the structural member of the aircraft; a receptacle for supporting the equipment, the receptacle being coupled to the mounting member along a longitudinal axis; and one or more spring elements arranged to resiliently bias the receptacle into alignment with the longitudinal axis and to allow angular movement of the receptacle away from the longitudinal axis. Also provided is an aircraft equipment assembly comprising such a compliant mount, and aircraft equipment supported by the receptacle, and an aircraft having one or more such equipment assemblies. The aircraft may be a folding wingtip aircraft and the equipment assembly may be part of a folding wingtip actuation mechanism.
A landing gear assembly for an aircraft having a main body on which one or more wheels of the aircraft are mounted, the main body aftwardly pivotable, about a pintle line, into a landing gear bay of the aircraft; and a bracing structure coupled to the main body, the bracing structure movable between an extended configuration to support the main body in a deployed configuration, and into a folded configuration in which the main body is held in a retracted configuration. The bracing structure includes at least a first component of preferential weakness configured to fail when subjected to a critical load when the main body is in the deployed configuration, to thereby decouple the main body from at least part of the bracing structure and enable the main body to pivot aftwards, into the landing gear bay. Also an aircraft having such a landing gear assembly.
A free-space optical communications (FSO) terminal including a first arm having a combined transmit-receive system configured to produce a data beam, encoding data, for transmission to a target and receive a received data beam from the target, a second arm having a component configured to transmit a further transmitted beam or utilise a further received beam, a pointing unit configured to steer the data beam to the target or the received data beam received from the target, and an optical fibre including a single-mode portion configured to carry the transmitted data beam and received data beam and couple the first arm to the pointing unit, and a multi-mode portion configured to carry the further transmitted beam or the further received beam and couple the second arm to the pointing unit.
An aircraft wing including a skin and a framework for supporting the skin. The framework includes a spar extending along a length of the wing, the length extending between a root end and a tip end of the wing, a plurality of ribs extending chordwise between a leading edge of the wing and a trailing edge of the wing; and a plurality of stringers attached to the skin. The plurality of stringers includes a first stringer extending along the length of the wing, wherein a proximal end of the first stringer is arranged nearer the root end and a distal end of the stringer is arranged nearer the tip end; and an auxiliary stringer extending non-parallel with the first stringer and arranged such that a portion of the auxiliary stringer is proximal to the distal end of the first stringer.
B32B 5/10 - 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 caractérisés par une couche fibreuse renforcée par des filaments
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
An aircraft including an aircraft wing wherein the aircraft wing includes a fixed wing, a wing tip device at an end of the fixed wing, and a wing tip device actuator configured to move the wing tip device between a flight configuration and a ground configuration. The wing tip device actuator includes a shaft which is rotatable about a shaft axis to selectively displace respective first and second elbows of the wing tip device actuator towards or away from the shaft. The first elbow is connected to the wing tip device and the second elbow is connected to the fixed wing such that movement of the respective elbows away from the shaft causes the wing tip device to move away from the flight configuration and such that movement of the respective elbows towards the shaft causes the wing tip device to move towards the flight configuration.
A sensor arrangement has a structure extending along a length, an optical fibre carrier, and an optical fibre sensor carried by the optical fibre carrier. The optical fibre carrier is fixed to the structure proximal to each end of the structure and is formed of a first carrier portion and a second carrier portion that are movable relative to each other and is formed substantially of a material having a first coefficient of thermal expansion. The optical fibre sensor has a single measurement point and is fixed to the optical fibre carrier either side of the single measurement point; and the structure is formed of a material having a second coefficient of thermal expansion which is different to the first coefficient of thermal expansion
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
B64D 37/00 - Aménagements relatifs à l'alimentation des groupes moteurs en carburant
G01K 1/08 - Dispositifs de protection, p. ex. étuis
G01K 1/14 - SupportsDispositifs de fixationDispositions pour le montage de thermomètres en des endroits particuliers
G01K 3/06 - Thermomètres donnant une indication autre que la valeur instantanée de la température fournissant des valeurs moyennesThermomètres donnant une indication autre que la valeur instantanée de la température fournissant des valeurs intégrées par rapport à l'espace
G01K 13/00 - Thermomètres spécialement adaptés à des fins spécifiques
A joint assembly has an eccentric bush for rotatably mounting to the first aircraft component. The eccentric bush has a rotational axis. A projection is mounted on the eccentric bush such that rotation of the eccentric bush about its rotational axis causes movement of the projection in both a first and a second orthogonal direction relative to the first aircraft component. The first and second orthogonal directions are substantially perpendicular to the rotational axis of the eccentric bush. A rail rotatably mounts to the second aircraft component. The rail has a longitudinal axis which extends in a direction substantially parallel to the second orthogonal direction. The projection has an aperture for receiving the rail. The rail has a threaded surface which is configured to engage with a correspondingly threaded surface of the aperture.
A joint assembly for joining a first aircraft structural component to a second aircraft structural component. The joint assembly has a double eccentric bush for mounting to one of the first and second aircraft structural components, and a spigot mounted on the double eccentric bush. Rotating elements of the double eccentric bush enable adjustment of the spigot relative to the respective aircraft structural component in two orthogonal directions normal to a longitudinal axis of the spigot prior to joining the first aircraft structural component to the second aircraft structural component. A spigot receptacle is provided for mounting to, or is integrally formed with, the other of the first and second aircraft structural components. The spigot receptacle is arranged to receive the spigot. At least one fastener joins the first and second aircraft structural components together when the spigot is received in the spigot receptacle.
A vacuum-insulated pipe assembly having an outer pipe and an inner pipe within the outer pipe, the inner pipe distanced from the outer pipe to provide a space, the space evacuated to define a vacuum. The vacuum-insulated pipe assembly has an annular wall extending inwardly from the outer pipe and defining an aperture about a central axis, the annular wall defining a closed end of the space. The vacuum-insulated pipe assembly has a first connector connected to the inner pipe, and a second connector extending through the aperture and connected to the first connector. The first connector and the second connector are each hollow and connected such that the inner pipe is in fluid communication with the second connector through the aperture. Also a system and a method for making a vacuum-insulated pipe assembly.
A latch for locking an aircraft folding wing is disclosed having a lug including an aperture, and a latch pin moveable within the aperture. The latch further includes a seal configured to inhibit fluid transfer between the aperture and the latch pin as the latch pin moves within the aperture.
A vacuum-insulated pipe assembly including an outer pipe and an inner pipe within the outer pipe, the inner and outer pipes concentric along a common central axis, the outer pipe spaced from the inner pipe to define a space, the space evacuated to define a vacuum. The outer pipe includes first and second outer pipe sections, the first outer pipe section includes a first outer connector, and the second outer pipe section includes a second outer connector, the first outer connector removably connected to the second outer connector at an outer connection interface. The inner pipe includes first and second inner pipe sections, the first inner pipe section includes a first inner connector, and the second inner pipe section includes a second inner connector, the first inner connector removably connected to the second inner connector at an inner connection interface.
A vacuum insulated pipe assembly including a first pipe section and a second pipe section. The first pipe section has a first outer wall and a first inner wall within the first outer wall. The first outer and inner walls are concentric along a common central axis, and the first outer wall is spaced from the first inner wall to define a first space. The second pipe section has a second outer wall and a second inner wall within the second outer wall. The second outer and inner walls are concentric along the common central axis, and the second outer wall is spaced from the second inner wall to define a second space. The first inner wall includes a first inner connector and the second inner wall includes a second inner connector connected to the first inner connector.
F16L 59/075 - Dispositions utilisant une couche d'air ou le vide la couche d'air ou le vide étant délimités par des canaux longitudinaux répartis sur la périphérie d'un tube
B64D 37/30 - Circuits de carburant pour carburants particuliers
A bush is provided including a sleeve for receiving a pin; a shoulder extending from the sleeve, the shoulder for delimiting insertion of the sleeve into an aperture; and a sensor mount for mounting a sensor such that the sensor may detect the presence of a pin within the sleeve. Installing such a bush within an aperture of a component may negate the requirement for lugs and/or brackets on the component. This may enable reduction of the weight, size and/or complexity of the component.
A Coriolis flow sensor for sensing a flow of a cryogenic fluid is disclosed having a flow member for the passage of a flow of cryogenic fluid therethrough, a driver for vibrating the flow member, and one or more detectors configured to generate output signals corresponding to Coriolis deflections of the vibrating flow member with flow of cryogenic fluid therethrough. The flow member includes at least 50 wt % indium.
Disclosed is a wing assembly for an aircraft. The wing assembly comprises a fixed wing, a wing tip device, a wiring harness and a harness guide. The wing tip device is moveably mounted at a joint at an end of the fixed wing. The wing tip device is moveable about the joint between: (i) a flight configuration for use during flight, and (ii) a ground configuration for use during ground-based operations, in which ground configuration the wing tip device is moved relative to the fixed wing such that the span of the wing is reduced. The wiring harness extends between the fixed wing and the wing tip device. The wiring harness comprises a plurality of conductors and is arranged to transmit electrical power and/or data to the wing tip device. The harness guide is located between the fixed wing and the wing tip device. The harness guide comprises a helical channel configured to receive the wiring harness and guide the wiring harness between the fixed wing and the wing tip device.
An aircraft wing having a fixed wing and a moveably mounted wing tip device is disclosed. A first cable harness and a second cable harness which are received in a protective sleeve extend between the fixed wing and the wing tip device. The protective sleeve is in a secured configuration in which at least two opposing parts of the protective sleeve are secured together between the first cable harness and the second cable harness to provide the sleeve with a first channel in which the first cable harness is received a second channel in which the second cable harness is received, and a webbing region extending between the first channel and the second channel such that the first and second cable harnesses are held apart by the webbing region.
A device including a layer of resin-encapsulated carbon is disposed in the vicinity of an outlet of a hydrogen vent. The vent carries gaseous hydrogen from a hydrogen store on an aircraft, to a location external of the aircraft. Upon pressure-relief of the hydrogen store, hydrogen travels through the vent and out the outlet. In the event of ignition of the hydrogen, the heat of the hydrogen flame melts the resin and releases the carbon. The carbon combusts in the hydrogen flame, thus producing a visible flame. The device is easily removeable and replaceable.
An aircraft assembly is disclosed including a wing structure, and a pipe assembly rotatably coupled to the wing structure by a fixture arrangement. The pipe assembly extends 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.
B64D 37/30 - Circuits de carburant pour carburants particuliers
B64D 37/00 - Aménagements relatifs à l'alimentation des groupes moteurs en carburant
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
Disclosed is an aircraft structure comprising: at least one aircraft structural element defining a volume; a fuel distribution component, arranged within the volume, configured to hold fuel internally and transport held fuel through the volume; and at least one packing element formed of a reticulated foam, arranged within the volume, and at least partially surrounding the fuel distribution component. An aircraft comprising the aircraft structure is also disclosed.
A landing gear attachment member for an aircraft is provided, the landing gear attachment member including a body comprising metal; and a lug comprising a metal matrix composite, wherein the lug is fused to the body via a joint. The lug may be brazed to the body, and the joint may comprise one or more scarf joints.
Disclosed is an aircraft structure comprising at least one aircraft structural element defining a volume; a fuel-handling component arranged within the volume and configured to handle a fuel; a purging system comprising an inlet and an outlet, the purging system configured to provide a flow of purge gas from the inlet, through the volume, to the outlet, to thereby purge leaked fuel from the volume; and a flow guide member formed of a reticulated foam, arranged within the volume and externally to the fuel-handling component, and configured to guide the flow of purge gas within the volume. An aircraft comprising the aircraft structure is also disclosed.
An aircraft assembly is disclosed including a rib of a wing, an aperture in the rib, and a pipe assembly extending through the aperture. The pipe assembly includes a first rigid pipe section, a second rigid pipe section and a flexible pipe section between the first and second rigid pipe sections; and a fixture arrangement that couples one of the pipe sections to the wing rib. The flexible pipe section 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.
B64D 37/00 - Aménagements relatifs à l'alimentation des groupes moteurs en carburant
F16L 9/22 - Tuyaux composés d'une pluralité de segments
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
A fluid assembly comprising: a first conduit extending in an axial direction and configured to carry a fluid, a double walled outer second conduit extending in the axial direction; the second conduit having an inner wall and outer wall and a first interspace between the inner and outer walls, wherein the first conduit is housed inside the second conduit to form a second interspace between the first conduit and the inner wall of the second conduit.
F16L 9/19 - Tuyaux à canaux multiples ou assemblages de tuyaux
F16L 59/065 - Dispositions utilisant une couche d'air ou le vide utilisant le vide
F17C 1/12 - Récipients sous pression, p. ex. bouteilles de gaz, réservoirs de gaz, cartouches échangeables avec des moyens pour assurer une isolation thermique
74.
METHOD OF CONTROLLING PRESSURE IN A HYDROGEN FUEL TANK
A method of controlling a pressure in a hydrogen fuel tank of an aircraft hydrogen fuel system. The hydrogen fuel tank stores hydrogen fuel. The method comprises receiving leak information indicative of a leak of hydrogen fuel from the hydrogen fuel system. The method also comprises, based on the leak information received, causing control of the pressure in the hydrogen fuel tank.
An aircraft system is disclosed including a hydraulic actuator, an inlet line for supplying hydraulic fluid to the hydraulic actuator, an outlet line for removing hydraulic fluid from the hydraulic actuator, a first one-way valve configured to allow fluid flow along the inlet line in a direction toward the hydraulic actuator, and a second one-way valve configured to allow fluid flow along the outlet line in a direction away from the hydraulic actuator.
A hydraulic actuator for a hydraulic actuation system of an aircraft includes a housing defining a cavity, a piston dividing the cavity into extension and retraction chambers and movable relative to the housing to increase volume of one chamber and decrease volume of another of the chambers. A bypass includes first and second bypass ports and a connecting bypass line, and first and second chamber ports opening into the extension and retraction chambers at all positions of the piston relative to the housing for passage of hydraulic fluid. The first and second bypass ports open into one of the extension chamber and retraction chamber when the piston is at a first position relative to the housing so the first bypass port and the second bypass port open into respective ones of the extension chamber and the retraction chamber when the piston is at a second position relative to the housing.
F15B 11/024 - Systèmes comportant essentiellement des moyens particuliers pour commander la vitesse ou la puissance d'un organe de sortie au moyen d'une liaison différentielle des circuits du servomoteur, p. ex. circuits à récupération de fluide
A method of actuating a wing tip device on an aircraft, from a flight configuration to a ground configuration in which the span is reduced. The method includes receiving data indicative of a condition, such as the location or speed of the aircraft, and determining an actuation profile in dependence on the condition. The actuation profile may include determining a time period, and/or speed profile of the wing tip actuation over that time period. In this manner the actuation of the wing tip device can be tailored to minimize loads and wear on the actuator assembly.
An aircraft structural element configured to be assemblable into an aircraft structure is disclosed having a sensor disposed on or within the aircraft structural element. The sensor is configured to sense a parameter during assembly of the aircraft structural element into the aircraft structure, and to output a signal indicative of the parameter during assembly of the aircraft structural element into the aircraft structure. An aircraft assembly system, and method of assembly based on the same are also disclosed.
An aircraft wing (3) comprising an aerofoil structure (5) is disclosed. The aerofoil structure (5) comprises a load-carrying member (10) having stiffness properties selected such that the load-carrying member (10) twists in a predefined manner in response to bending of the load-carrying member (10). The aerofoil structure (5) further comprises an actuator (15A, 15B) which is fixedly mounted to the load-carrying member (10) and which is operable to bend the load-carrying member (10) to thereby cause the load-carrying member (10) to twist. An aircraft comprising the aircraft wing and a method of adjusting the twist in an aircraft wing are also disclosed.
An aircraft structural element configured to be assemblable into an aircraft structure, the aircraft structural element including an external surface having an integrally formed photogrammetry target. The aircraft structural element, the integrally formed photogrammetry target and the external surface are formed of a common material composition and are a single piece structure. A photogrammetry system, aircraft assembly system and method of assembly of the aircraft structural element into the aircraft structure.
B64F 5/10 - Fabrication ou assemblage d’aéronefs, p. ex. gabarits à cet effet
G01C 11/02 - Dispositions de prises de vues spécialement adaptées pour la photogrammétrie ou les levers photographiques, p. ex. pour commander le recouvrement des photos
An aircraft control system and method for controlling electrical power distribution in an aircraft are disclosed. The aircraft control system and method obtain state signals from electrical systems in the aircraft, control characteristics of a power source, and control characteristics of the electrical systems. The control characteristics of the electrical systems are dependent on a flight phase status of the aircraft. Output control data is generated, based on the control characteristics and state signals, and used to control electrical power distribution in the aircraft.
An interface for a wing folding mechanism of an aircraft. The interface has a central region comprising an internal surface, the internal surface being suitable for engaging a driven gear of a rotary actuator, and an attachment pad extending away from the central region in a first direction for attaching a surface to the interface. The interface can be used as part of the casing of a Geared Rotary Actuator. Also described are related wing assemblies, and aircraft and related methods.
B64C 13/34 - Dispositifs de transmission sans amplification de puissance ou dans les cas où l'amplification de puissance est sans objet mécaniques utilisant des engrenages
B64C 3/56 - Repliage ou rabattement pour réduire l'encombrement de l'aéronef
83.
COMPUTER-IMPLEMENTED METHOD OF ESTIMATING CHARACTERISTICS OF A HYDRAULIC ACCUMULATOR OF AN AIRCRAFT
A computer-implemented method of estimating characteristics of a hydraulic accumulator of an aircraft. The computer-implemented method includes obtaining pressure information representative of a pressure of hydraulic fluid in the hydraulic accumulator at a plurality of times during a mission of the aircraft, and estimating the characteristics based on the pressure information and a model including relationships between pressure and time for respective variants of the characteristics.
B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
B64C 13/42 - Dispositifs de transmission avec amplification de puissance utilisant la pression d'un fluide comportant des dispositifs de doublement de la commande ou de mise en position de secours
A tire monitoring system including a tire monitoring device and a remote device. The tire monitoring device includes a first processor, and a first wireless communication interface. The remote device includes a second processor, a display device, and a second wireless communication interface. The first processor monitors the tire monitoring device to determine an altered operational mode of the tire monitoring device and causes transmission of a signal encoding an indication of the altered operational mode of the tire monitoring device to the remote device via the first and second wireless communication interfaces. The second processor determines, based on the signal encoding the indication of the altered operational mode of the tire monitoring device, a maintenance message corresponding to the altered operational mode of the tire monitoring device and causes the maintenance message to be displayed on the display device.
G07C 5/00 - Enregistrement ou indication du fonctionnement de véhicules
B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
G01K 3/00 - Thermomètres donnant une indication autre que la valeur instantanée de la température
G01L 17/00 - Dispositifs ou appareils pour mesurer la pression des pneumatiques ou la pression dans d'autres corps gonflés
G01L 19/00 - 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
A tire monitoring system that includes a tire monitoring device and a remote device. The tire monitoring device includes a processor, a memory, and a first wireless communication interface. The remote device includes a second wireless communication interface. The processor monitors the tire monitoring device to determine unauthorized interactions with the tire monitoring device, stores a log of determined unauthorized interactions in the memory, and transmits a signal encoding the log to the remote device via the first and second wireless communication interfaces.
A fuel line terminating in a refuel connector is used to fuel or defuel an aircraft, for example with liquid hydrogen. A supply of nitrogen housed on an aircraft, for example a Nitrogen Generating System, is used in conjunction with a gas line to supply nitrogen into the fuel line, to flush out potentially combustible materials before liquid hydrogen is supplied through the fuel line. The aircraft supply of nitrogen is also used to supply inert gas, via a gas line, to the Ground Support Equipment refuelling or defuelling the aircraft. This can provide redundancy for the Ground Support Equipment's systems, and may allow the aircraft to operate at less well-equipped airports.
A pipe support assembly (114), suitable for supporting pipework handling cryogenic fluids, where the pipework passes through a fuel tank support. The pipe support assembly includes first and second pipe supports (116) each having male (119) and female (152) portions that interlock with male (119) and female (152) portions of the other pipe support (116). The pipe supports (116) have an internal surface (121) that contacts a section of the pipe outer surface (112). Each pipe support (116) has a split (140) which allows for a change in dimension of the internal surface (121) of the pipe support (116) contacting the pipe (110). This allows the pipe support assembly (114) to provide a consistent clamping force to the pipe (110) during thermal contraction or expansion. Longitudinal movement of the pipe (110) is permitted if the pipe (110) overcomes the frictional force between itself and the pipe support assembly (114).
A joint assembly in an aircraft, for example between a wing skin and rib foot. The joint assembly includes fasteners mechanically holding the wing skin and rib foot together. The rib foot includes circular faying surfaces and a layer of material is sandwiched between the faying surfaces and the wing skin. The layer of material has adhesive properties such that the joint is a hybrid joint. The layer of material also has structural properties to function as a solid shim, for example once it has cured after application.
A machining system includes an automated manipulator configurable between a measuring configuration, in which a position probe is operable, and a machining configuration, in which a tool is operable, a fixture for holding a template or a workpiece, and a controller. The controller is configured cause the automated manipulator, in the measuring configuration, to move the position probe to at least one reference feature of the template held in the fixture, to determine coordinate data associated with the at least one reference feature. Then, the controller provides the determined coordinate data to a machine learning agent which is trained to provide an estimate of machining coordinate deviation based on the determined coordinate data. If the estimated machining coordinate deviation is below a threshold coordinate deviation, the automated manipulator is allowed to proceed to machine a workpiece.
An aircraft with a folding wing tip arrangement having a wing tip device mounted at a joint at the end of a fixed wing. It is desirable to transfer power and/or data into a folding wing tip, which presents challenges such as repeated exposure to potentially harsh environmental conditions, with movement, and/or with changes in tensional loads. A wiring harness includes a plurality of conductors and is arranged to transmit electrical power and/or data to the wing tip device. A length of the harness is received in a protective sleeve, and the sleeve extends over a length of the wiring harness spanning the joint, the sleeve being removable from the wiring harness.
An aircraft with a folding wing tip arrangement and a wiring harness extending between a fixed wing and a wing tip device is disclosed. It is desirable to transfer power and/or data into a folding wing tip, which presents challenges such as repeated exposure to potentially harsh environmental conditions, with movement, and/or with changes in tensional loads. The wiring harness includes a plurality of conductors and is arranged to transmit electrical power and/or data to the wing tip device. The harness is received in a protective sleeve. The sleeve includes a fluorosilicone polymer.
An aircraft enclosure inerting system has an inerting apparatus which receives air from an inlet, separates that air into nitrogen enriched air to be delivered to one or more enclosures of the aircraft, and oxygen enriched air. The inerting apparatus comprises at least first and second air separators. The first and second air separators are configured differently to one another. In some embodiments one of the air separators is a vortex tube and the other is a membrane-based air separation module. In some embodiments the inerting apparatus has at least two vortex tubes which are configured differently to one another.
An aircraft with a folding wing tip arrangement and first and second wiring harnesses extending between a fixed wing and a wing tip device is disclosed. It is desirable to transfer power and/or data into a folding wing tip, which presents challenges such as repeated exposure to potentially harsh environmental conditions, with movement, and/or with changes in tensional loads. The wiring harnesses include a plurality of conductors and are arranged to transmit electrical power and/or data to the wing tip device. The sleeve includes two channels to receive the harnesses, the position of the channels being fixed, relative to one another, such that the harnesses are held apart.
A method of inspecting an aircraft fuel tank fastener assembly. The assembly includes a fuel tank with a fuel chamber; a fastener comprising a head and a tail at opposite ends of the fastener; and a cap inside the fuel chamber, wherein the cap surrounds the tail of the fastener. The method includes: heating the tail of the fastener; obtaining a thermal image of the tail of the fastener; and inspecting the thermal image of the tail of the fastener.
A robot arrangement is disclosed including one or more robots for moving a component into an assembly position adjacent a fixed structure. The robots are configured to operate collectively to move the component from an initial position located in a coarse adjustment zone into a fine rotational adjustment zone within a set distance of the fixed structure. The coarse adjustment zone is at least the set distance from the fixed structure; and in the fine rotational adjustment zone, robots are configured to collectively perform a rotational alignment cycle to rotationally align the component with the assembly position of the component ready for joining the component to the fixed structure and, upon completion of the rotational alignment cycle, collectively perform a translational movement to move the component into the assembly position.
B23P 21/00 - Machines pour l'assemblage de nombreuses pièces différentes destinées à composer des ensembles, avec ou sans usinage de ces pièces avant ou après leur assemblage, p. ex. à commande programmée
A robot arrangement for interacting with an object is disclosed including a plurality of robots adjacent an object; the plurality of robots configured to interact with the object sequentially such that: a first robot of the plurality of robots is configured to perform a first portion of a first task on the object and then, whilst the first robot is not interacting with the object, a second robot of the plurality of robots is configured to perform a second portion of the first task on the object, and the plurality of robots are configured to simultaneously interact with the object, before or after completion of the first task, so as to collectively perform a second task on the object.
A method of joining a wing skin to a structural element of an aircraft wing. A locating through hole is formed in the structural element, extending along a path between a first side of the structural element and a second side of the structural element. A spark containment cap is attached to the first side of the structural element to covering an opening of the locating through hole. A portion of the wing skin is positioned on the second side of the structural element. A fastening through hole having a larger diameter than the locating through hole is formed through both the wing skin and the structural element and along the path of the locating through hole. A fastener is inserted into the fastening through hole and the structural element secured to the wing skin, an end of the fastener being covered by the spark containment cap.
A method comprising moving a vehicle between a plurality of parked aircraft; at each aircraft, receiving aircraft-to-ground data from the aircraft at the vehicle by free-space-optical communication and storing the aircraft-to-ground data at the vehicle; and transferring the stored aircraft-to-ground data from the vehicle, wherein stored aircraft-to-ground data from two or more of the aircraft accumulates at the vehicle before it is transferred from the vehicle. Also a vehicle used in such a method.
H04B 10/112 - Transmission dans la ligne de visée sur une distance étendue
G07C 5/08 - Enregistrement ou indication de données de marche autres que le temps de circulation, de fonctionnement, d'arrêt ou d'attente, avec ou sans enregistrement des temps de circulation, de fonctionnement, d'arrêt ou d'attente
An aircraft comprising an aircraft transceiver to transfer data to and from the aircraft by free-space-optical communication when parked. The aircraft transceiver comprises a transmitter to generate outgoing light carrying aircraft-to-ground data; a lens to collimate the outgoing light to generate a collimated beam; a beam steering device to transform the collimated beam to generate a steered beam; a control system to operate the beam steering device to adjust an angle of the steered beam; and a receiver to sense incoming light carrying ground-to-aircraft data. The receiver receives the incoming light via the beam steering device and the lens. Also a vehicle with a similar transceiver to transfer data to and from a parked aircraft by free-space-optical communication.
H04B 10/112 - Transmission dans la ligne de visée sur une distance étendue
B64C 1/36 - FuselagesCaractéristiques structurales communes aux fuselages, voilures, surfaces stabilisatrices ou organes apparentés adaptés pour recevoir des antennes ou des radômes
METHOD FOR DETERMINING AT LEAST ONE CHARACTERISTIC OF A MOVEMENT OF A MOBILE STRUCTURE OF AN AIRCRAFT AND AIRCRAFT COMPRISING A DEVICE FOR ITS IMPLEMENTATION
A method for determining, at a given moment in time, at least one characteristic of a movement of a mobile structure of an aircraft. The method includes determining a pair of coordinates in a reference plane corresponding to a projection of a reference feature forming part of the mobile structure in the reference plane, determining the characteristic of the movement of the mobile structure by comparing the pair of coordinates previously determined with reference coordinate pairs, at least one characteristic of the movement of the mobile structure being associated with each pair of reference coordinates. Also an aircraft having a device for implementing the method.
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