An aircraft wing is provided having a fixed wing with a gulled wing tip rotatably mounted at the tip thereof, the gulled wing tip extending below a wing plane defined by the end of the fixed wing such that the centre of gravity of the gulled wing tip is located below the wing plane. Lowering the centre of gravity of the gulled wing tip has been found to reduce the onset of flutter. The gulled wing tip may be gulled about a hinge axis where it meets the fixed wing, or may be otherwise folded or curved to lower the centre of gravity of the gulled wing tip.
A wing defines a chord which runs from a leading edge to a trailing edge. The wing has a main portion and a flap which is movable relative to the main portion to change the aerodynamics of the wing, for instance to maximize lift, or to reduce drag at the expense of some loss of lift. The wing has a guide mechanism which guides movement of the flap. The guide mechanism uses a pair of runners which run along respective tracks. The tracks are positioned at different locations along the direction of the chord, but overlap one another in the direction of the chord.
In an aircraft wing structure where space and weight considerations are a principal concern, there may be significant challenges in providing a moveable slat and/or a spoiler, particularly in combination with one another. A control device for an aircraft includes upper and lower flaps pivotably mountable adjacent to a slot in a wing behind a leading edge, wherein the control device is operable in a lift configuration to move the upper and lower flaps towards each other to abut opposing surfaces of the slot, to permit airflow along the slot.
A pipe spacer (50) for separating inner and outer pipes of a double- walled pipe assembly, the pipe spacer comprising: an annular body (60) for positioning in an interspace between inner and outer pipes of a double-walled pipe assembly, wherein the annular body (60) defines an axis of the pipe spacer; a plurality of springs (70) extending radially from the annular body (60), wherein each spring (70) is configured to deform inwardly towards the annular body (60) on contact with one of the inner and outer pipes; and a plurality of projecting stops (80) extending from the annular body (60) which are configured to limit the inward deformation of the springs (70).
F16L 39/00 - Raccords ou accessoires de raccordement pour tuyaux à double paroi ou à canaux multiples ou pour assemblages de tuyaux
F16L 7/00 - Support de tuyaux ou de câbles à l'intérieur d'autres tuyaux ou manchons, p.ex. pour permettre la pose ou le retrait de tuyaux ou de câbles sous des routes ou des voies ferrées sans devoir interrompre la circulation
A pipe spacer 50 for separating inner and outer pipes of a double-walled pipe assembly, the pipe spacer 50 comprising: an annular body 60 for positioning in an interspace between inner and outer pipes of a double-walled pipe assembly, the annular body 60 formed of a composite material; a plurality of outer arms 70a extending radially outwardly from the annular body 60 for contacting the outer pipe and/or a plurality of inner arms 70b extending radially inwardly from the annular body 60 for contacting the inner pipe; and wherein each of the inner and/or outer arms are springs 71 that extend radially from the annular body 60 and are configured to deform inwardly towards the annular body 70 on contact with the respective outer or inner pipe, the arms formed of a composite material.
F16L 7/00 - Support de tuyaux ou de câbles à l'intérieur d'autres tuyaux ou manchons, p.ex. pour permettre la pose ou le retrait de tuyaux ou de câbles sous des routes ou des voies ferrées sans devoir interrompre la circulation
F16L 39/00 - Raccords ou accessoires de raccordement pour tuyaux à double paroi ou à canaux multiples ou pour assemblages de tuyaux
F16L 3/01 - Supports pour tuyaux, pour câbles ou pour conduits de protection, p.ex. potences, pattes de fixation, attaches, brides, colliers pour supporter ou guider les tuyaux, les câbles ou les conduits de protection entre des points mobiles les uns par rapport aux autres, p.ex. canaux mobiles
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.
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 clutch is coupled to the geared rotary actuator by a shaft and the shaft is fixed in rotation to a mass disposed radially outwardly from the shaft.
The invention provides an aircraft fuel supply arrangement for delivering liquid hydrogen to an aircraft engine (19), the arrangement comprising: a fuel tank (2) for the storage of liquid hydrogen; an aircraft engine (19) configured to be powered by liquid hydrogen; a primary pump (3) for delivering liquid hydrogen fuel from the fuel tank (2) to the aircraft engine; one or more fuel delivery conduits (4,5) for carrying fuel from the fuel tank to the primary pump (3), one or more fuel delivery conduits (18) providing a fuel supply volume for carrying fuel; and a secondary pump (6) for delivering liquid hydrogen fuel to the primary pump (3). An aircraft comprising such an aircraft fuel supply arrangement, and a method of supplying liquid hydrogen to an aircraft engine are also provided.
A speed determination system for an aircraft including one or more interfaces arranged to receive first speed data from a first speed measurement system and second speed data from a second speed measurement system. The first speed measurement system provides the first speed data using global positioning system data. The second speed measurement system provides the second speed data based on a second speed measurement. The speed determination system includes a processor arranged to determine whether the data received from the first speed measurement system is reliable. If global positioning data is determined to be reliable, the speed determination system determines a speed from the first speed data and determines correction values for the second speed measurement system. If global positioning data is determined to be unreliable, the speed determination system determines a speed from the second speed data and the correction values.
G01S 19/47 - Détermination de position en combinant les mesures des signaux provenant du système de positionnement satellitaire à radiophares avec une mesure supplémentaire la mesure supplémentaire étant une mesure inertielle, p.ex. en hybridation serrée
G01S 19/48 - Détermination de position en combinant ou en commutant entre les solutions de position dérivées du système de positionnement par satellite à radiophares et les solutions de position dérivées d'un autre système
G01S 19/45 - Détermination de position en combinant les mesures des signaux provenant du système de positionnement satellitaire à radiophares avec une mesure supplémentaire
G01S 19/49 - Détermination de position en combinant ou en commutant entre les solutions de position dérivées du système de positionnement par satellite à radiophares et les solutions de position dérivées d'un autre système l'autre système étant un système de position inertielle, p.ex. en hybridation lâche
A fuel storage structure for an aircraft. The fuel storage structure comprises a first container configured to store a first type of fuel and a second container arranged within the first container. The second container has a variable volume and is configured to store a second type of fuel. The fuels storage structure comprises a fuel release apparatus operable to provide the first type of fuel and the second type of fuel stored by the first container and the second container, respectively, to an engine of the aircraft.
An aircraft fuel tank monitoring system is disclosure including at least one first sensor for sensing a pressure of fuel within a fuel tank; at least one second sensor for sensing a pressure of an ullage space above the fuel within the fuel tank; a processor for monitoring the change in the pressure of the fuel within the fuel tank over a time period and for monitoring the change in the pressure of the ullage space within the fuel tank over the time period, and to determine a fault if the monitored pressure changes exceed normal operating conditions.
A cover for covering an access port of a fuel storage structure of an aircraft, the access port is configured to allow a human operator to access an interior of a first container of the fuel storage structure. The cover comprises an inlet port configured to interface with and receive fuel from an aircraft refueling apparatus, and an outlet port fluidically connectable to the inlet port and operable to provide the fuel received at the inlet port to the interior of the first container when the cover is arranged to cover the access port.
An antenna element includes a first thin-film membrane, second thin-film membrane essentially parallel to and spaced apart from the first thin-film membrane, an electromagnetic metasurface on a first side of the first thin-film membrane opposite of the second thin-film membrane, and a metallic coating on a first side of the second thin-film membrane opposite of the first thin-film membrane. An antenna array is also disclosed.
H01Q 15/00 - Dispositifs pour la réflexion, la réfraction, la diffraction ou la polarisation des ondes rayonnées par une antenne, p.ex. dispositifs quasi optiques
H01Q 21/06 - Réseaux d'unités d'antennes, de même polarisation, excitées individuellement et espacées entre elles
Disclosed is a spark containment cap plate (20) comprising: a base (22); and two or more spark containment caps (21a,21b,21c); each spark containment cap (21a,21b,21c) comprising a cover portion (24) which extends from the base (22), the cover portion (24) defining a cavity (26) inside the spark containment cap (21a,21b,21c) inside which the end (203) of a fastener (202) can be enclosed. Also disclosed is a fastener joint (200) comprising: a structure (28); two or more fasteners (202), each fastener (202) having a fastener end (203) protruding from a surface of the structure (28); and a spark containment cap plate (20), the spark containment cap plate (20) comprising: a base (22); and two or more spark containment caps (21a,21b,21c); each of the spark containment caps (21a,21b,21c) comprising a cover portion (24) extending from the base (22), the cover portion (24) defining a cavity (26) inside the spark containment cap (21a,21b,21c) inside which the end (203) of a fastener (202) can be enclosed; and a cured sealing material (27) provided between the spark containment cap plate (20) and the structure (28) which secures the spark containment cap plate (20) to the structure (28) in such a position that each end (203) of each fastener (202) is enclosed within a spark containment cap (21a,21b,21c).
A multi-material component is provided including two members formed of different materials joined together at a multi-material join. The two members have complementary protrusions that form a multi-material join with a zig-zag interface, such that a tension between them is experienced in at least part as a shear force at the interface between the protrusions. The component further includes a third member connected to the first member by a lattice, which is capable of elastic deformation so as to substantially isolate the interface between the complementary protrusions from deformation of the third member such as that caused by thermal expansion. Methods of designing and constructing such a component in a single piece via additive manufacturing are provided. The component is particularly suitable for use in pylons connecting jet engines to aircraft wings.
An assembly is provided for preventing the relative rotation of a fastener and a nut by way of a nut plate that engages with a drive feature of the nut and a fastener plate that engages with a drive feature of the fastener. The nut plate and fastener plate are secured together to prevent their relative rotation. A base plate is secured to a workpiece in which the nut and fastener are located that is further secured to the nut plate and the fastener plate to prevent the relative rotation of the fastener and nut with respect to the workpiece. The plates have locking members that extend away from the fastener and can be secured together e.g. by drilling and fastening.
F16B 39/10 - Blocage des vis, boulons ou écrous dans lequel le verrouillage s'effectue après vissage par une plaque ou un anneau immobile par rapport au boulon ou à l'objet
17.
METHOD OF CHECKING THE ACCURACY OF A DRILLING ROBOT
A method of checking the accuracy of a robot is disclosed providing a component; fitting a tool jig to the component; using the tool jig to guide a stamp tool against the component to create a first mark on the component representative of a calibrated drilling location; removing the tool jig; providing a robot, the robot including an end effector holding a marking tool; operating the robot according to a program to manoeuvre the marking tool against the component to create a second mark representative of a robot drilling location; and comparing the position of the first mark to the position of the second mark to measure a distance between the first mark and the second mark.
A seal between two aircraft surfaces which are able to move relative to each other. A wing tip device moves between a flight configuration and a ground configuration, in which ground configuration the wing tip device is moved away from the fixed wing such that the span of the aircraft wing is reduced. The fixed wing and wing tip device each comprise an outer surface, and a male seal and female seal are arranged such that when the wing tip device is in the flight configuration the female seal receives the male seal, and the female seal and male seal cooperate to provide a smooth transition from the fixed wing outer surface to the wing tip device outer surface.
An aircraft wing having a wing profile and a multi-functional pop-up spoiler unit. The pop-up spoiler unit has a first spoiler panel having at least one cut out and a second spoiler panel. The first spoiler panel is moveable between a retracted position in which the first spoiler panel is within the wing profile and an extended position in which the first spoiler panel is projected outside the wing profile. The second spoiler panel is moveable between a retracted position in which the second spoiler panel is within the wing profile and an extended position in which the second spoiler panel is projected outside the wing profile. The pop-up spoiler unit is arranged to move between: a first configuration in which the first and second spoiler panels are in their retracted positions; a second configuration in which the first spoiler panel is in an extended position with the at least one first cut out exposed to an airflow over the wing profile; and a third configuration in which the first and second spoiler panels are in their extended positions and exposed to an airflow over the wing profile.
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
B64C 9/14 - Surfaces ou éléments de commande réglables, p.ex. gouvernes de direction formant des fentes
An aircraft fuel tank venting and inerting arrangement comprising a fuel tank, a venting fluid flow path between the fuel tank and a venting outlet, an inerting fluid flow path for delivering inerting fluid to the fuel tank, at least part of the venting fluid flow path being provided by a fluid flow conduit and at least part of the inerting fluid flow path being provided by the fluid flow conduit. An aircraft comprising such an arrangement and a method of venting and inerting an aircraft fuel tank.
A liner segment for a frame bay of a fuel tank structure includes a liner segment base body adapted to float on fuel in the fuel tank structure, a liner segment side wall extending from the liner segment base body, a multitude of drainage holes arranged in the liner segment base body, and adapted to provide a bidirectional fluid connection from an upper side to a bottom side of the liner segment facing the fuel tank structure, a valve, arranged in a cut out of the liner segment and adapted to provide an unidirectional fluid connection from the bottom side of the liner segment to the upper side of the liner segment, such that the unidirectional fluid connection is blocked in the opposite direction, such that a remaining portion of fuel within the fuel tank structure is reduced.
A method of suppressing contrails emitted by a propulsion system of an aircraft. A first fuel composition is fed into the propulsion system for a predetermined period. The expiry of the predetermined period is detected with a timer. Upon expiry of the predetermined period, a second fuel composition is fed into the propulsion system. The second fuel composition is more prone to cause contrails than the first fuel composition. Contrails generated by the propulsion system are detected as the second fuel composition is fed into the propulsion system. If a contrail is detected, the steps of the method are repeated.
F02C 9/28 - Systèmes de régulation sensibles aux paramètres ambiants ou à ceux de l'ensemble fonctionnel, p.ex. à la température, à la pression, à la vitesse du rotor
F02C 9/40 - Commande de l'alimentation en combustible spécialement adaptée à l'utilisation d'un combustible particulier ou de plusieurs combustibles
A wing tip device for a fixed wing aircraft is disclosed having an alular-like projection, a first leading edge region having a first sweep angle, a second leading edge region outboard of the first leading edge region in a spanwise direction and having a second sweep angle greater than the first sweep angle, a third leading edge region outboard of the second leading edge region in the spanwise direction and adjacent a tip end of the wing tip device and having a third sweep angle greater than the first sweep angle. The second leading edge region is adapted to generate a first vortex, and the third leading edge region is adapted to generate a second vortex which builds towards the tip end of the wing tip device.
An aircraft assembly jig for fitting a number of landing gear door components to an aircraft. The jig includes a lifting device for elevating the components towards the aircraft for fitting, and a number of adjustable platforms attached to the lifting device, each of which holds one of the landing gear door components. The adjustable platforms allow each of the components to be positioned independently so that when elevated together towards the aircraft by the lifting device, each component is correctly and independently aligned and positioned for installation at the aircraft.
An aircraft having a port over which a first connector is mounted for connecting to a second connector to transfer fluid to and/or from the aircraft is disclosed. The first connector includes a first fluid path extending from the port towards an aircraft fluid tank and a second, different, fluid path which extends from the port towards an aircraft fluid tank.
A temporary pintle support which can attach between upper prongs of a landing gear, and which is arranged to hold pintle pins prior to installation of the landing gear assembly at an aircraft. The pintle support is attached at the landing gear to align the pintle pins with their respective attachment bearings on each of the prongs. The pintle support may be removed once the pintle pins are fully inserted.
A coupling for a double-walled pipe having an inner wall and an outer wall, the inner wall having an inner lumen, and the inner wall and the outer wall delimiting an outer lumen. The coupling comprises an inner section forming a passage in fluid communication with the inner lumen, and an outer section arranged radially adjacent to the inner section. A material of the outer section is interrupted in a radial direction multiple times in an area corresponding to a radial range between the inner wall and the outer wall. A further exemplary coupling may have an outer section that is interrupted multiple times in the longitudinal direction.
The Manufacturing Technology Centre Limited (Royaume‑Uni)
Inventeur(s)
Hardi, Robin
Brookes, Harvey
Mumford, John
Blain, Richard Cameron
Abrégé
A programmable robot is configurable between a measuring configuration, in which a probe is operable, and a machining configuration, in which a tool is operable. The robot includes a carrier for carrying the probe and the tool, a position sensing arrangement for determining coordinate data, and a controller 7. The controller is configured to cause the carrier, in the measuring configuration, to move the probe to each of a plurality of reference features in a template held in a first orientation by a jig, wherein feedback via the probe enables the position sensing arrangement to determine coordinate data associated with the reference features. The controller is configured to, based on the determined data, cause the carrier, in the machining configuration, to return to each position corresponding to each reference feature location and machine a workpiece held in the first orientation.
A sealant application includes an interface structure having an interface for interfacing with a source of sealant and a nozzle structure including a nozzle for dispensing sealant. A gear pump module including a gear pump is configured to be detachably connectable to each of the interface structure and the nozzle structure such that sealant provided at the interface is pumpable by the gear pump from the interface to the nozzle.
F04C 15/00 - "MACHINES" À LIQUIDES À DÉPLACEMENT POSITIF, À PISTON ROTATIF OU OSCILLANT; POMPES À DÉPLACEMENT POSITIF, À PISTON ROTATIF OU OSCILLANT - Parties constitutives, détails ou accessoires des "machines", des pompes ou installations de pompage non couverts par les groupes
THE MANUFACTURING TECHNOLOGY CENTRE LIMITED (Royaume‑Uni)
Inventeur(s)
Moore, Ian
Cantle, David
Foster, Matthew
Edwards, Dan
Abrégé
An automated clamp for clamping a rib web to a rib post or rib foot of an aircraft wing box is disclosed including a clamp frame having a first arm and a second arm extending from the base of the clamp frame. The second arm is moveable towards and away from the first arm; a robot end effector connector coupled to the clamp frame; clamp jaws including a first jaw fixed at a distal end of the first arm, and a second jaw fixed at a distal end of the second arm, the clamp jaws configured to clamp a rib web to a rib post or clamp a rib web to a rib foot. The first jaw and/or second jaw includes a contact normalisation system, the contact normalisation system including: a jaw body fixed relative to the respective arm.
THE MANUFACTURING TECHNOLOGY CENTRE LIMITED (Royaume‑Uni)
Inventeur(s)
Moore, Ian
Cantle, David
Foster, Matthew
Edwards, Dan
Abrégé
An automated clamp for clamping a rib web to a rib post or rib foot of an aircraft wing box is disclosed including a clamp frame having a first arm and a second arm extending from the base of the clamp frame. The second arm is moveable towards and away from the first arm; a robot end effector connector coupled to the clamp frame; clamp jaws including a first jaw fixed at a distal end of the first arm, and a second jaw fixed at a distal end of the second arm, the clamp jaws configured to clamp an aircraft assembly. One of the jaws includes a tool module docking aperture into which a tool module is insertable for accessing the aircraft assembly; and a swarf channel extending into the tool module docking aperture, the swarf channel fluidically connected to a vacuum source and configured to extract waste material adjacent the aircraft assembly.
A method of fabricating an aircraft structural component for an aircraft includes providing a component precursor with a web and a flange. The web has a length, height shorter than the length, thickness shorter than the height, first end proximal to the flange and second end distal from the flange. A force is applied to the component precursor with a magnitude varying along the web height from a minimum at one of the first and second ends to a maximum at another of the first and second ends to increase length of the web to different extents. Then shaping the component precursor includes curving the component precursor into a curved shape having a first radius of curvature at the one of the first and second ends and a second radius of curvature at the another of the first and second ends, the second radius of curvature greater than the first.
A method of fabricating an aircraft structural component for an aircraft includes providing a component precursor with a web and a flange extending from the web, wherein the web has a length, a height which is shorter than the length, a thickness which is shorter than the height, a first end proximal to the flange and a second end distal from the flange, applying tension to the component precursor in a direction parallel to the length of the web and with a magnitude that varies along the height of the web so as to increase the length of the web to different extents between the first end of the web and the second end of the web, sectioning the component precursor, and releasing the tension to allow shaping of the component precursor into a form required for the aircraft structural component.
THE MANUFACTURING TECHNOLOGY CENTRE LIMITED (Royaume‑Uni)
Inventeur(s)
Moore, Ian
Cantle, David
Foster, Matthew
Edwards, Dan
Abrégé
An automated clamp for clamping a rib web to a rib post or rib foot of an aircraft wing box is disclosed including a clamp frame, a first arm and a second arm extending from the base of the clamp frame, the second arm is moveably mounted to the base of the clamp so as to be moveable towards and away from the first arm; a robot end effector connector coupled to the clamp frame. The clamp jaws include a first jaw fixed at a distal end of the first arm, and a second jaw fixed at a distal end of the second arm, the clamp jaws configured to clamp the rib web to the rib post or rib foot. One of the clamp jaws defines a tool module docking aperture configured to receive a tool module for providing access to the rib web and rib post or rib foot clamped between the clamp jaws.
THE MANUFACTURING TECHNOLOGY CENTRE LIMITED (Royaume‑Uni)
Inventeur(s)
Moore, Ian
Edwards, Dan
Abrégé
An automated self-aligning system is disclosed including a first robot arm attached to a clamping end effector including clamp jaws for clamping either side of a workpiece and with an aperture in one of the clamp jaws. A second robot arm is attached to a tooling end effector including a tool module carrying a tool. The tool module is insertable into the aperture and the tool is adapted to perform an operation on the workpiece. The second robot arm is arranged to move the tool module so as to move the tool module in a direction of insertion so as to insert the tool module into the aperture. A load sensor coupled to the tooling end effector and is arranged to determine a load in the direction of insertion of the tool module. The tooling end effector is further arranged to move the tool module with respect to the second robot arm in a plurality of degrees of freedom different than the insertion direction.
B64F 5/50 - Manipulation ou transport des composants d'aéronefs
B23B 35/00 - Méthodes d'alésage ou de perçage ou autres méthodes de travail impliquant l'utilisation de machines à aléser ou à percer; Utilisation d'équipements auxiliaires en relation avec ces méthodes
G05D 3/12 - Commande de la position ou de la direction utilisant la contre-réaction
36.
MONITORING AN AIRCRAFT FLUID STORAGE TANK ASSEMBLY
A system for monitoring an aircraft fluid storage tank assembly is disclosed including a pressure sensor configured to receive an acoustic signal emitted from a location within the aircraft fluid storage tank assembly in use and a controller. The controller is configured to receive information indicative of the acoustic signal from the pressure sensor and perform a determination process to determine, on the basis of the received acoustic signal, whether to output an indicator of a fault condition of the aircraft fluid storage tank assembly.
A method of determining configuration status of a component of an aircraft landing gear assembly. The component with a lidar system is scanned to generate a set of position data points. A subset of the position data points is determined, the subset having position data points corresponding to positions in a predetermined region of the landing gear assembly, the predetermined region including a part of the component. The representative position point of the subset of position data points is determined, and it is determining if the position is beyond a predetermined threshold position. If the point is beyond the predetermined threshold position, a signal indicating the component of the landing gear assembly has a first configuration status is output, and if the representative position point is not beyond the predetermined threshold position, a signal indicating the component of the landing gear assembly has a second configuration status is output.
B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
G01S 7/48 - DÉTERMINATION DE LA DIRECTION PAR RADIO; RADIO-NAVIGATION; DÉTERMINATION DE LA DISTANCE OU DE LA VITESSE EN UTILISANT DES ONDES RADIO; LOCALISATION OU DÉTECTION DE LA PRÉSENCE EN UTILISANT LA RÉFLEXION OU LA RERADIATION D'ONDES RADIO; DISPOSITIONS ANALOGUES UTILISANT D'AUTRES ONDES - Détails des systèmes correspondant aux groupes , , de systèmes selon le groupe
An aircraft wing including a wing structure supporting a wing cover having an outer aerodynamic surface, and a pop-up spoiler unit including an actuation mechanism and a spoiler coupled to the actuation mechanism. The spoiler is moveable by the actuation mechanism to deploy through an aperture in the wing cover. The pop-up spoiler unit is mounted to the wing structure to be substantially isolated from wing bending deflections. The wing structure has a neutral plane which is substantially neither stretched nor compressed during bending of the wing structure. The pop-up spoiler unit is mounted to the wing structure at only two pin joints each having a respective pin axis about which the pop-up spoiler unit is substantially free to rotate, and each pin axis substantially lies in the neutral plane.
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 assembly is disclosed having a cover with an outer aerodynamic surface and an aperture with a stop adjacent an edge of the aperture, and a moveable device for extending through the aperture in the cover. The moveable device carries a panel attached to the moveable device by a plurality of leaf springs. The assembly is configured so that when the moveable device is moved towards a retracted position the panel bears against the stop forming a substantially flush surface with the outer aerodynamic surface of the cover surrounding the aperture. The panel is displaced from the moveable device by elastic deformation of at least some of the leaf springs.
A computer-implemented method of determining a position of a component of an aircraft landing gear assembly. The method includes obtaining an image of the aircraft landing gear assembly; determining a region of interest within the image, the region of interest contains the component of the aircraft landing gear assembly; calculating a coordinate of a centroid of the bounding box and comparing the coordinate of the centroid to a corresponding predetermined threshold coordinate to determine the position of the component of the aircraft landing gear assembly.
An aircraft including: a source of inert gas; a fuel system for containing fuel; a containment area of the aircraft outside the fuel system and configured to contain oxygen and/or fuel vapour leaked from the fuel system; and a piccolo tube located in the containment area, the piccolo tube connected to the source of inert gas and configured to flow inert gas from the source of inert gas through holes of the piccolo tube and into the containment area to reduce the concentration of oxygen and/or fuel vapour within the containment area.
A computer-implemented method of determining a steering angle of an aircraft landing gear is disclosed including obtaining a set of position data points, wherein the set of position data points comprises position data points of a component of the aircraft landing gear and calculating a centroid of the set of position data points. The method also includes determining an angle of an intersection between a straight line that passes through both the centroid and an axis of rotation of the aircraft landing gear and an axis that is orthogonal to a strut of the aircraft landing gear when the aircraft landing gear is at a previously known steering angle, and determining the steering angle of the aircraft landing gear based on the determined angle of intersection.
B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
G01S 7/48 - DÉTERMINATION DE LA DIRECTION PAR RADIO; RADIO-NAVIGATION; DÉTERMINATION DE LA DISTANCE OU DE LA VITESSE EN UTILISANT DES ONDES RADIO; LOCALISATION OU DÉTECTION DE LA PRÉSENCE EN UTILISANT LA RÉFLEXION OU LA RERADIATION D'ONDES RADIO; DISPOSITIONS ANALOGUES UTILISANT D'AUTRES ONDES - Détails des systèmes correspondant aux groupes , , de systèmes selon le groupe
G01S 17/08 - Systèmes déterminant les données relatives à la position d'une cible pour mesurer la distance uniquement
G01S 17/89 - Systèmes lidar, spécialement adaptés pour des applications spécifiques pour la cartographie ou l'imagerie
G01S 17/933 - Systèmes lidar, spécialement adaptés pour des applications spécifiques pour prévenir les collisions d’aéronefs ou d'engins spatiaux
A method of contrail suppression. Data is generated with a sensing system onboard a first aircraft during a flight of the first aircraft. The data includes atmospheric information indicative of an atmospheric condition and/or contrail information indicative of a presence or absence of contrails generated by the first aircraft. A second aircraft is operated to perform one or more contrail suppression measures on a basis of the data.
An aircraft includes a ground maneuver control system that automatically steers a nose landing gear wheel to compensate for asymmetrical braking of the wheels of the aircraft resulting from a failure on one side in comparison to the other. A control system detects such a failure in order to be able to effect such automatic steering. The system may be retrofitted by the installation of software on an existing aircraft, having a braking and steering computer system with a pre-existing steering control functional block and a pre-existing braking control functional block.
B64C 25/50 - Atterrisseurs orientables; Amortissement du shimmy
B60T 8/17 - Utilisation de moyens de régulation électriques ou électroniques pour la commande du freinage
B60T 8/1755 - Régulation des freins spécialement adaptée pour la commande de la stabilité du véhicule, p.ex. en tenant compte du taux d'embardée ou de l'accélération transversale dans une courbe
B60T 17/22 - Dispositifs pour surveiller ou vérifier les systèmes de freins; Dispositifs de signalisation
B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
45.
AIRCRAFT SUB-ASSEMBLY MANUFACTURING SYSTEM AND METHOD
An aircraft sub-assembly manufacturing system is arranged over multiple floors of a manufacturing facility. A production line of workstations is provided at locations at both a first floor and a second floor of the facility, each of the workstations being arranged for providing manufacturing steps for the aircraft sub-assembly. Elevator apparatus is arranged to transport the assembled aircraft sub-assembly between the first floor and the second floor of the facility.
An aircraft fuel storage system is disclosed including a fuel tank comprising a chamber for storing fuel, the chamber comprising a first side, a second side, and a base connecting the first side to the second side; a collector; and a first conduit and a second conduit, each of the first and second conduits fluidically coupling the chamber to the collector so that fuel is freely passable from the chamber to the collector via the respective first and second conduits. The first and second conduits open into the chamber at respective first and second conduit openings, the first conduit opening is nearer to the first side than the second conduit opening is to the first side, and the second conduit includes a second conduit lock portion that is nearer to the first side than the second conduit opening is to the first side. Also disclosed is an aircraft including the aircraft fuel storage system.
A method of manufacturing an aircraft assembly is disclosed including forming a first tension hole in a first aircraft component and a second tension hole in a second aircraft component. The first and second aircraft components are positioned relative to each other such that the first tension hole at least partially overlies the second tension hole, to define a pair of tension holes. The first aircraft component is secured relative to the second aircraft component by providing a first fastener between the first tension hole and the second tension hole of the pair of tension holes. A first shear hole is formed in the first aircraft component and a second shear hole is formed in the second aircraft component. The first shear hole is axially aligned with the second shear hole, to define a pair of shear holes.
A VTOL aircraft (100) including a wheel braking system and a hydraulically coupled shock absorber (5) and brake piston (7). The shock absorber (5) carries the weight of the aircraft (100) when a wheel (1) connected to the shock absorber (5) is in contact with a ground surface. A hydraulic pressure within the shock absorber (5) is proportional to the weight of the aircraft (100) carried by the shock absorber (5). The shock absorber (5) and brake piston (7) are hydraulically coupled such that, when the pressure within the shock absorber (5) exceeds a threshold pressure, the pressure within the shock absorber (5) actuates the brake piston (7) to apply a braking torque to the wheel (1) of the VTOL aircraft (100).
An aircraft wing section assembly is disclosed having a structural spine, a movement mechanism including a support rod 1 extending through the structural spine, a first lever, for connection to and for moving a first moveable control surface, pivotally mounted to the support rod, a second similar lever for connection to and for moving a second moveable control surface, and a connection mechanism for connecting the first and second levers such that pivotal movement of the first lever causes pivotal movement of the second lever, and an actuation mechanism for actuating pivotal movement of the first lever, such that, in use, when the actuation mechanism actuates pivotal movement of the first lever, the second lever also pivotally moves, thus causing movement of both the first and second moveable control surfaces. Also disclosed is an aircraft wing assembly, an aircraft and a method of operating an aircraft.
A control device for an aircraft is disclosed including a push-button switch that is configured to be held in a depressed position by a pilot during taxiing of the aircraft. The push-button switch is configured to return automatically to a released position if it is not held in the depressed position by the pilot. The control device is configured to output a command for braking to a braking system of the aircraft, if the push-button switch moves to the released position during taxiing of the aircraft and does not return to the depressed position within a set time. The button may be provided on a tiller. A method of detecting on-board pilot incapacitation during an aircraft taxi phase is also disclosed.
B60T 7/14 - Organes d'attaque de la mise en action des freins par déclenchement non soumis à la volonté du conducteur ou du passager commandés par l'affaissement du conducteur
B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
G05G 1/02 - Organes de commande actionnés à la main par un mouvement linéaire, p.ex. boutons poussoirs
G05G 5/05 - Moyens pour faire revenir ou tendant à faire revenir les organes de commande vers une position de repos ou une position neutre, p.ex. en prévoyant des ressorts de retour ou des butées de fin de course élastiques
G05G 9/00 - Mécanismes de commande manuelle équipés d'un seul organe de commande travaillant avec plusieurs organes commandés, p.ex. en sélection ou simultanément
An aircraft landing gear is disclosed having a landing gear leg attachable at a first end to an aircraft, and an axle beam, both the landing gear leg and the axle beam being rotatably mounted. The axle beam is rotatable between a first position, in which a first end of the axle beam is a first (shorter) distance from the first end of the landing gear leg, and a second position, in which said first end of the axle beam is a second (longer) distance from the first end of the landing gear leg. A biasing member is configured to be able to bias the axle beam towards the second position. An aircraft, a blended wing body aircraft, and a method of operating an aircraft are also disclosed.
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 structure component (1) for laminar flow including an outer skin (3) having an aerodynamic surface (5), wherein the aerodynamic surface (5) has a leading edge portion (7) and a downstream portion (11) adjacently downstream from the leading edge portion (7), wherein the downstream portion (11) of the aerodynamic surface (5) comprises a paint layer (13) or a foil layer that is not present in the leading edge portion (7), so that a border line (15) is formed between the leading edge portion (7) and the downstream portion (11) by the beginning paint layer (13) or foil layer, and wherein the outer skin (3) comprises an attachment surface (17) to which the paint layer (13) or the foil layer is attached.
B64C 21/10 - Moyens permettant d'influencer l'écoulement d'air sur les surfaces des aéronefs en agissant sur la couche limite par utilisation d'autres caractéristiques de la surface, p.ex. la rugosité
A routine maintenance procedure performed in respect of a wheel of an aircraft landing gear is disclosed. Consumable brake lining material is integrated with the wheel. Re-treading or replacing the wheel tyre and inspecting or replacing the consumable brake lining material tyre are performed at the same successive intervals as part of the routine maintenance procedure. The sum volume and mass of brake material present on the aircraft may thus be reduced. Brake material providing for the demands of a maximum energy rejected take-off may be provided separately. The wheel may be made in one or two parts from carbon-fibre composite material. At least some of the brake material may be provided on an outwardly facing planar surface of the wheel.
A method of extending a landing gear of an aircraft is disclosed. The aircraft includes an uplock arranged to retain the landing gear in a retracted position, a primary landing gear system configured to retract and extend the landing gear, and an alternate landing gear system, independent from the primary landing gear system. The method includes the primary landing gear system holding the landing gear in place while the uplock is moved from a first configuration to a second configuration by the alternate landing gear system.
A method of extending a landing gear 201 of an aircraft 10 is disclosed. The aircraft 10 comprises an uplock 61 arranged to retain the landing gear 201 in a retracted position, a primary landing gear system 220 configured to retract and extend the landing gear 201, and an alternate landing gear system 230, independent from the primary landing gear system 220. The method comprises the primary landing gear system 220 holding the landing gear 201 in place while the uplock 61 is moved from a first configuration to a second configuration by the alternate landing gear system 230.
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
B64D 45/04 - Aides à l'atterrissage; Dispositifs de sécurité pour éviter la prise de sol brutale
G01B 7/00 - Dispositions pour la mesure caractérisées par l'utilisation de techniques électriques ou magnétiques
A load-bearing structure is disclosed and configured to, during operation of the structure, transfer load from a first part of the structure to a second part of the structure via a load path. The component includes a matrix material, a plurality of longitudinal first reinforcing elements embedded in the matrix material, and a plurality of longitudinal second reinforcing elements embedded in the matrix material. The long axis of each first reinforcing element is substantially aligned with a first direction and the long axis of each second reinforcing element is substantially aligned with a second direction, the second direction being substantially perpendicular to the first direction. The structure has a predefined crack-propagation region configured to control the propagation of a crack in the structure. The crack-propagation region either comprises multiple first reinforcing elements and does not comprise any second reinforcing elements; or comprises multiple second reinforcing elements and does not comprise any first reinforcing elements.
An aircraft is disclosed including a fuel tank, and a refuelling system configured to feed fuel into the fuel tank. The refuelling system includes a sensor. The sensor is configured to measure a composition of fuel in the refuelling system before it is fed into the fuel tank, and the sensor is further configured to generate an output based on the measured composition.
B64D 37/04 - Disposition de ceux-ci à l'intérieur ou sur les aéronefs
B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
58.
HYDROGEN SUPPLY DEVICE COMPRISING A HYDROGEN TANK AS WELL AS EQUIPMENT ITEMS DISTRIBUTED IN AT LEAST ONE CONTAINER CONNECTED TO THE TANK AND AT LEAST ONE REMOVABLE CONTAINER
A hydrogen supply device including at least one hydrogen tank, at least one hydrogen circuit and at least one upstream container joined to the hydrogen tank, as well as at least one removable downstream container. The upstream and downstream containers are configured to occupy an assembled state, in which the upstream and downstream containers are connected, and a detached state in which the upstream and downstream containers are not joined. The hydrogen circuit has an upstream segment positioned in the upstream container, a downstream segment positioned in the downstream container, as well as a first connection system which connects the upstream and downstream segments when the upstream and downstream containers are in the assembled state. Thus, each downstream container may be uninstalled and removed from the aircraft without it being necessary to uninstall the hydrogen tank.
An aircraft control surface system for an aircraft structure, that can be a pop-up spoiler for an aircraft wing, includes a deployable control surface member and a deployment mechanism. The deployment mechanism moves the deployable control surface member between a retracted position and a deployed position. In the retracted position, the deployable control surface member is curled to facilitate stowage within the aircraft structure. In the deployed position, the deployable control surface member is uncurled and extends from a surface of the aircraft structure. The deployment mechanism enables the deployable control surface member to extend to have a straight portion with a length greater than the local depth of the aircraft structure.
An aircraft pipework assembly is disclosed including an aircraft structure; pipework; a fixture arrangement between the pipework and the aircraft structure; a tie rod connecting the pipework to the aircraft structure; a first tie rod bearing which connects the tie rod to the pipework; and a second tie rod bearing which connects the tie rod to the aircraft structure. The fixture arrangement includes a spherical bearing, the spherical bearing comprising a ball mounted to the pipework, and a housing coupled to the aircraft structure. The ball includes a convex spherical bearing surface; and the housing comprises a concave spherical bearing surface which mates with the convex spherical bearing surface of the ball. The fixture arrangement is configured to enable the pipework to translate relative to the ball in an axial direction aligned with a longitudinal axis of the pipework.
F16L 27/02 - 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
An aircraft assembly including: an aircraft structure; a pipe assembly; a fixture arrangement attached to the aircraft structure, the fixture arrangement contacting the pipe assembly via a curved bearing surface having curvature in two orthogonal directions; the curved bearing surface configured to enable the pipe assembly to rotate relative to the fixture arrangement about three perpendicular axes; wherein the pipe assembly comprises a stop member adjacent the fixture arrangement, a contact surface of the stop member configured to abut a contact surface of the fixture arrangement so as to restrict axial movement of the pipe assembly relative to the fixture arrangement, and wherein a distance between the contact surface of the fixture arrangement and the contact surface of the stop member increases radially from the longitudinal pipe axis.
B64D 37/30 - Circuits de carburant pour carburants particuliers
F16L 3/10 - Supports pour tuyaux, pour câbles ou pour conduits de protection, p.ex. potences, pattes de fixation, attaches, brides, colliers entourant pratiquement le tuyau, le câble ou le conduit de protection fractionnés, c. à d. à deux éléments en prise avec le tuyau, le câble ou le conduit de protection
F16L 5/00 - Dispositifs utilisés pour le passage des tuyaux, des câbles ou des conduits de protection au travers des murs ou des cloisons
An aircraft wing assembly includes a wing box including an upper surface, a lower surface, and a leading edge structure connecting the upper surface to the lower surface and secured to the upper surface at a connection point. The aircraft wing assembly includes a drive mechanism secured to the wing box and a high lift device mounted to the drive mechanism. The drive mechanism is configured to move the high lift device between a retracted position and an extended position in use, and wherein the high lift device is configured to overlap the connection point when in the retracted position.
A canister for hot isostatic pressing is disclosed including a body arranged to define a cavity for containing a powder arranged to be subjected to hot isostatic pressing; and an opening defined in the body through which a powder can be inserted into the body, and the opening being closeable so as to seal the canister for hot isostatic pressing; wherein the body comprises a weakened area, the weakened area defining a part of the body which is designed to dissolve in acid faster than the rest of the body.
A test system for modifying a graph-based trained classifier, configured to output control data for controlling the aircraft system according to a graph model representing the aircraft system. The test system is configured to obtain scenario data, control data, and validation data. The test system generates a custom loss score based on differences between the validation data and the control data and modifies the graph-based trained classifier based on the custom loss score, the scenario data, and the control data. A computer-implemented method for modifying the graph-based trained classifier and a storage medium comprising instructions to perform the method are also provided.
An aircraft control surface deployment system for an aircraft structure, that can be a spoiler deployment system for an aircraft wing, includes a cam body, an actuator, and a coupling mechanism. The actuator moves the cam body such that it raises and lowers the aircraft control surface. The actuator is connected to the cam body via the coupling mechanism. The coupling mechanism has a first portion connected to the cam body and a second portion connected to the actuator, configured such that the coupling mechanism allows some free relative movement and rotation of the first and second portions. Loads transverse to the axis of movement of the actuator, resulting from relative movement of the cam body, are not transferred to the actuator.
B64C 13/32 - Dispositifs de transmission sans amplification de puissance ou dans les cas où l'amplification de puissance est sans objet mécaniques utilisant des mécanismes à cames
A pipe spacer for separating inner and outer pipes of a double-walled pipe is disclosed including an inner circumferential bearing surface for contacting an inner pipe of a double-walled pipe assembly; an outer circumferential bearing surface for contacting an outer pipe of the double-walled pipe assembly; at least three inner lobes, each of the inner lobes having an apex on which lies the inner circumferential bearing surface; and the outer circumferential bearing surface is curved in two orthogonal directions.
An aircraft including a wing, a first pressure sensor and a second pressure sensor, wherein each pressure sensor is configured to measure pressure of a liquid within the wing and has a known position within the wing. The aircraft includes a processing system configured to receive first pressure data from the first pressure sensor, receive second pressure data from the second pressure sensor, and determine a bending state of the wing based on the first pressure data, the second pressure data, and the known positions of the first and second pressure sensors within the wing.
An aircraft wing including: a wingbox; a fuel tank; a fuel cell system with a fuel cell; a fuel line configured to deliver fuel from the fuel tank to the fuel cell system; a propulsion system carried by the wingbox; and an electrical power line configured to deliver electrical power from the fuel cell system to the propulsion system. The fuel tank and the fuel cell system are located inside the wingbox, and the propulsion system is located outside the wingbox.
An aircraft engine incudes: a catalyst, e.g. platinum, applied to turbine blades (580c, 590c) and/or to a catalytic grid downstream of the engine's combustion chamber. An exhaust fluid additive injection system is incorporated upstream of the catalyst via a line 560, in a stator blade within the engine. The catalyst is used to reduce NOx emissions from the engine by a Selective Catalytic Reduction reaction.
F23R 3/40 - Chambres de combustion à combustion continue utilisant des combustibles liquides ou gazeux caractérisées par l'emploi de moyens catalytiques
F02C 3/20 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail utilisant un combustible, un oxydant ou un fluide de dilution particulier pour produire les produits de combustion
An aircraft wing (5) has a fixed wing (7) with a tip (7'), and a wing tip device (9) rotatably mounted on a hinge (11) at the tip of the fixed wing. The wing tip device is rotatable about the hinge. An actuation system (20') rotates the wing tip device about the hinge. The actuation system has a motor (22'), a plurality of geared mechanical actuators (24'), and an angle gearbox (29) 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 aircraft structural component includes a flange having a non-planar side and a web having a first end extending from the non-planar side of the flange and a second end distal from the first end and from the non-planar side of the flange wherein the web has a non-planar shape that deviates from a plane normal to the non-planar side of the flange and extending in a longitudinal direction of the aircraft structural component, so that a deviation of the non-planar shape of the web from the plane increases with distance along the web in a direction from one of the first and second ends to the other of the first and second ends, and so that the deviation extends over at least 10 cm of a length of the aircraft structural component.
A wing tip device for fixing to the outboard end of a wing, the wing defining a wing plane, the wing tip device comprising: an upper wing-like element projecting upwardly with respect to the wing plane and having a trailing edge; and a lower wing-like element fixed with respect to the upper wing-like element and having a root chord and a trailing edge, the lower wing-like element root chord intersecting with the upper wing-like element, and the lower wing-like element projecting downwardly from the intersection, wherein the upper wing-like element is larger than the lower wing-like element and the trailing edge of the lower wing-like element is adjacent the trailing edge of the upper wing-like element at the intersection, and wherein an included angle between the upper and lower wing-like elements at the intersection is less than, or equal to, 160 degrees.
An aircraft wing has a fixed wing and a moveable wing tip device. The wing is operable in a fixed flight configuration, in which the wing tip device is fixed relative to the fixed wing and the wing tip device is forward swept, and a moving flight configuration in which the wing tip device is free to move relative to the fixed wing. The forward moveable swept wing tip device may provide particular synergy with a forward swept fixed wing.
An aircraft access cover for an opening in the surface of an aircraft. The aircraft access cover includes a first panel and a second panel, the first panel and second panel configured to be attachable to each other such that the surface of the aircraft is clampable between the first panel and second panel when the first panel and the second panel are attached to each other. A device that is operable to perform a function while attached to the aircraft access cover is attachable by a connector to the first panel of the aircraft access cover, the connector allowing the device to be movable between a first orientation relative to the first panel and a second orientation relative to the first panel.
Disclosed is an aircraft power system 800 comprising a first driveable component 120, 130 of the aircraft, and a mechanical flywheel 250, wherein the mechanical flywheel is connectable to the first driveable component such that the mechanical flywheel is arranged to drive the first driveable component of the aircraft, such that, in a first driveable mode of operation, the first driveable component is driven by the mechanical flywheel, and wherein the first driveable component is connectable to the mechanical flywheel such that the first driveable component is arranged to drive the mechanical flywheel, such that, in a first regenerative mode of operation, the mechanical flywheel is driven by the first driveable component. Also disclosed is an aircraft landing gear drive system 700, an aircraft 1000, a method of operating an aircraft and other aircraft power systems.
Disclosed is an aircraft power system (800) comprising a hydraulic reservoir (801, 803), a bidirectional hydraulic pump (212) for pumping hydraulic fluid to and from the reservoir, and an electric motor (230), wherein the hydraulic pump is connectable to the electric motor such that the hydraulic pump is arranged to drive the electric motor as a generator, such that, in an electrical generation mode of operation, the electric motor is driven by the hydraulic pump. Also disclosed is an aircraft landing gear drive system (700), an aircraft (1000) and a method of operating an aircraft.
A method of determining an operating condition of a valve of an aircraft system includes obtaining a first time period associated with actuating the valve, and a second time period associated with actuating the valve. The method includes providing an indication of an altered operating condition associated with actuation of the valve based on the first and second time periods.
F02C 7/232 - Soupapes pour combustible; Systèmes ou soupapes de drainage
B64D 37/00 - Aménagements relatifs à l'alimentation des groupes moteurs en carburant
B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
F16K 37/00 - Moyens particuliers portés par ou sur les soupapes ou autres dispositifs d'obturation pour repérer ou enregistrer leur fonctionnement ou pour permettre de donner l'alarme
78.
METHOD OF JOINING COMPONENTS OF AN AIRCRAFT STRUCTURE
Two components of an aircraft structure are joined by providing a threaded opening in one of them and supporting an alignment insert in that opening. The alignment insert is used to guide drilling of the second component such that a hole is produced which is aligned with the threaded opening, for instance using an alignment projection which physically guides a drill. The alignment insert may then be removed. A fastener is then inserted through that hole and into the threaded opening, then tightened to form the completed joint.
An aircraft wing structure includes first and second unitary shell structures formed from a fiber-reinforced composite material. Each shell structure includes a partial front spar, a partial rear spar and a wing skin. The partial front spars of each shell structure and the partial rear spars of each shell structure are arranged to overlap to form front and rear spars respectively. A wing box structure is lightweight, strong and durable, with a lower overall part count than has been conventionally achievable. Aircraft systems equipment may be attached to the shell structures prior to, or after, assembly into a wing box.
An aircraft brake system includes a supply line for supplying hydraulic fluid to wheel brakes, and an associated return line. Hydraulic fluid is replenished in at least a portion of the return line both before applying a braking force to the one or more wheels of the aircraft during landing, and before an intervening, optional, step if so performed of testing the brake system before landing of the aircraft. Replenishing the hydraulic fluid can be conducted by a control unit automatically and/or in response to a pressure drop in the return line measure by a transducer.
F15B 13/04 - Dispositifs de distribution ou d'alimentation du fluide caractérisés par leur adaptation à la commande de servomoteurs pour utilisation avec un servomoteur unique
A hydraulic brake system for activating the wheel brakes of an aircraft landing gear assembly includes a hydraulic fluid supply line and an associated return line. There is a valve which separates a source of hydraulic fluid from a portion of the return line and an associated leak path associated with the valve that in use maintains the pressure and/or volume of hydraulic fluid in the portion of the return line above a minimum acceptable level. The leak path may be provided by a hole drilled in a part (e.g. the poppet) of a non-return check valve.
B60T 13/12 - Transmission de l'action de freinage entre l'organe d'attaque et les organes terminaux d'action, avec puissance de freinage assistée ou relais de puissance; Systèmes de freins incorporant ces moyens de transmission, p.ex. systèmes de freinage à pression d'air avec assistance, entraînement ou relâchement par fluide le fluide étant un liquide
F15B 13/06 - Dispositifs de distribution ou d'alimentation du fluide caractérisés par leur adaptation à la commande de servomoteurs pour utilisation avec plusieurs servomoteurs
82.
VALVE ACTUATION MECHANISM, VALVE ARRANGEMENT AND PIPE INSTALLATION FOR LH2 APPLICATIONS AS WELL AS USE THEREOF
A valve actuation mechanism for actuating a rotatable closing valve element for cryogenic applications and/or H2 applications, including a housing defining an inner area sealed by a membrane from an outer area, an input shaft configured to receive a rotational movement, the input shaft being in the outer area, an output shaft configured to be connected to the closing element, wherein the output shaft is in the inner area, and a strain wave gearing connecting the input and output shafts. The strain wave gearing includes a wave generator connected to one of the input and output shafts, a rotatable outer gear wheel connected to the other one of the input and output shafts and a stationary flexible ring gear with external teeth deformed by the wave generator to engage with internal gear teeth of the outer gear wheel. The flexible ring gear is a portion of the sealing membrane.
A method of monitoring a mechanical connection between a first aircraft component and a second aircraft component. The method includes securing, using a securing device, the first aircraft component to the second aircraft component; obtaining information indicative of an acoustic signal emitted during the securing the first aircraft component to the second aircraft component; and inputting the information indicative of the acoustic signal into a machine learning model. The machine learning model is configured to provide an output indicative of a fault condition of the mechanical connection.
G01N 29/44 - Traitement du signal de réponse détecté
G01N 29/14 - Recherche ou analyse des matériaux par l'emploi d'ondes ultrasonores, sonores ou infrasonores; Visualisation de l'intérieur d'objets par transmission d'ondes ultrasonores ou sonores à travers l'objet utilisant des techniques d'émission acoustique
An aircraft brake control system for controlling antiskid braking of an aircraft wheel is disclosed including a control assembly having a mode controller which sets the mode of operation of an antiskid brake calculator, configured to set a first mode, when an input of the indication of a brake energy supply configuration indicates a first brake energy supply being used, in which the antiskid brake calculator applies a first restriction level on a rise rate of the antiskid brake command, and a second mode, when the input 305 indicates a second brake energy supply being used, in which the antiskid brake calculator applies a second, lower, restriction level on a rise rate of the antiskid brake command.
A aircraft braking system is disclosed including a plurality of brakes each for braking one of a plurality of aircraft wheels using hydraulic pressure, a first hydraulic pressure supply unit, and a second hydraulic pressure supply unit. The first hydraulic pressure supply unit is connected to only a first subset of the plurality of brakes, such that the first hydraulic pressure supply unit can enable only the first subset of the plurality of brakes to provide braking. The second hydraulic pressure supply unit is connected to only a second subset of the plurality of brakes, the second subset not including any of the brakes of the first subset, such that the second hydraulic pressure supply unit can enable only the second subset of the plurality of brakes to provide braking.
B60T 13/14 - Dispositions relatives à l'alimentation en pression utilisant des accumulateurs ou des réservoirs
B60T 8/17 - Utilisation de moyens de régulation électriques ou électroniques pour la commande du freinage
B60T 8/94 - 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 comportant des moyens sensibles au fonctionnement défectueux, c. à d. des moyens pour détecter et indiquer un fonctionnement défectueux des moyens sensibles à la condition de vitesse à action corrective automatique sur un régulateur de pression fluidique
B60T 13/68 - Commande électrique des systèmes de freins à fluide sous pression par valves commandées électriquement
A sensor carrier for sensing forces acting upon an axle of an aircraft landing gear assembly is disclosed being arranged to fit within the axle and includes an end coupling for fixing to one end of the axle, and a central coupling for fixing to a central portion of the axle where the axle attaches to a main leg of the assembly. The sensor carrier includes a sensor arrangement arranged to detect strain occurring between the end coupling and the central coupling so that in use, the sensor arrangement indicates strain occurring between the end of the axle and the main leg of the aircraft.
G01L 5/16 - Appareils ou procédés pour la mesure des forces, du travail, de la puissance mécanique ou du couple, spécialement adaptés à des fins spécifiques pour la mesure de plusieurs composantes de la force
B64C 25/32 - Trains d'atterrissage caractérisés par les éléments de contact avec le sol ou une surface analogue
B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
An aircraft wing with a moveable leading edge device mounted towards the leading edge of the wing. The leading edge device is moveable between a first configuration, a second configuration and a third configuration. In the first configuration, the leading edge device is retracted fully within the wing profile. In the second configuration, a portion of a surface of the leading edge device is extended away from the wing profile and into the oncoming airflow on the lower surface of the wing as the wing moves through the airflow to increase lift produced by the wing. In the third configuration, a portion of the surface of the leading edge device is extended away from the wing profile into the oncoming airflow over the upper surface of the wing to impair lift produced by the wing.
An aircraft wing with a moveable leading edge device mounted towards the leading edge of the wing is disclosed. The leading edge device is moveable between a first configuration and a second configuration. In the first configuration, the leading edge device is substantially flush with the low pressure surface. In the second configuration, the surface of the leading edge device is retracted into the wing profile. The second configuration creates a void in the lower surface of the wing which modifies the airflow over the surfaces. The oncoming airflow can enter the void. In the second configuration, the leading edge device reduces the lift on the wing, acting to reduce the lift induced strain on the wing during high speed flight or to help manoeuvre the wing. The leading edge device may also be configured to move into a third configuration.
A method of controlling an inerting system of an aircraft is disclosed. The inerting system feeds inert gas into a fuel tank of the aircraft, the method includes: a) obtaining a location of the aircraft, the location comprising a current location or an expected future location; b) assessing an environmental impact of releasing of fuel vapour at the location obtained in step a); and c) controlling the inerting system based on the assessment of step b).
A coupling for insulated piping is disclosed having first and second parts for forming the coupling. The first and second parts include an inner conduit portion for fluid communication with an inner tube of an insulated pipe and an outer conduit portion, the inner conduit portion and outer conduit portion forming therebetween a space for fluid communication with the insulating part of an insulated pipe. In use, cold liquid is transported in the inner conduit portions. The first and second parts comprise flanges. The inner conduit portion of the first part has a projection comprising a lower thermal expansion region. The second part has a projection-receiving portion for receiving the projection of the first part, the projection-receiving portion having a co-efficient of thermal expansion that is greater than the lower thermal expansion region of the projection.
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 23/12 - Raccords à brides spécialement adaptés à des tuyaux particuliers
An aircraft wing with an array of moveably flight control surfaces is disclosed. Each flight control surface includes a trailing edge with a moveable tab attached to the flight control surface trailing edge. A flight control system coupled to a flight control surface drive system which moves the flight control surfaces; a tab drive system which moves the moveable tabs and one or more aircraft angle of attack sensors. The flight control system stores a set of angular deflections to deflect the tabs upwardly when the angle of attack reaches a threshold.
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.
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.
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.
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.
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
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.
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.
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.
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.
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.
brevets
