An onboard hydraulic system for an aircraft is disclosed having a motor-pump unit including an electric motor and a hydraulic pump driven by the motor, a hydraulic consumer supplied with pressurized hydraulic fluid from the motor-pump unit, a fluid reservoir, a pressure sensor for sensing pressure of the pressurized hydraulic fluid, a control unit for controlling the motor-pump unit, and a pressure setting mechanism for adapting a pressure setting of the motor-pump unit for ground service or maintenance or specific flight conditions.
An aircraft tank device for increasing a flight range and a wing area of an aircraft includes a fairing which is formed and configured to at least partly cover an aircraft wing-aircraft fuselage intersection, to store a fuel, and to provide a lifting function. An aircraft including such an aircraft tank device is also disclosed.
A liner segment system for a frame bay of a fuel tank structure, comprising: a liner segment base body, wherein the liner segment base body is adapted to float on fuel in the fuel tank structure, a displacement body, wherein the displacement body is arranged next to a lowest point of the liner segment base body, such that a remaining portion of fuel within the fuel tank structure is reduced by displacing the fuel at the lowest point of the liner segment base body.
A hydraulic system (12) for an aircraft (10), wherein the hydraulic system (12) includes a hydraulic power pack (14), a hydraulic fluid reservoir (28) and a hydraulic pump (30), a hydraulic consumer (18), a high-pressure supply line (38) supplying the hydraulic consumer (18) with hydraulic fluid under higher pressure, and a low-pressure return line (40) returning hydraulic fluid under lower pressure from the hydraulic consumer (18); heating device (42) with a short-cut line (44) connecting the high-pressure supply line (38) with the low-pressure return line (40) and a heater valve (46) for opening and closing the short-cut line (44), and a control and monitoring unit (43). Temperature management includes automatically controlling a fluid temperature by monitoring the fluid temperature and controlling the heater valve (46).
An adaptable fixation interface for an aircraft cabin floor with a plurality of connection studs that comprise a mounting foot region and a connection head region. The mounting foot region is configured to be inserted into one of a plurality of interface points in a floor arrangement. The connection head region is configured to be engaged by a fitting of an equipment to be fixed to the floor arrangement. The connection studs are configured to be releasably connected to adjacent interface points in a floor arrangement to provide a longitudinally extending fixation interface segment for mounting of equipment.
An aircraft fuselage for releasing a fuel tank from inside the aircraft fuselage in case of emergency includes an outer structure, a mounting device to releasably secure a sled device for carrying a fuel tank in an inside of the outer structure, and a first openable release door separating the inside from an outside of the outer structure, wherein the first release door is positioned in relation to the mounting device such that the fuel tank is released through the first release door when the mounting device releases the sled device. A method is disclosed for releasing a fuel tank from inside the aircraft fuselage in case of emergency as well as an aircraft including such an aircraft fuselage.
A leading-edge device for an aerodynamic component is disclosed having a first skin element having an inner surface and an aerodynamic outer surface, and further includes a second skin element having an inner surface and an aerodynamic outer surface. The leading-edge device includes a first coupling element protruding from the inner surface of the first skin element and a second coupling element protruding from the inner surface of the second skin element. The first and second coupling elements are coupled to each other in a coupling region. The first skin element and the first coupling element are formed as a single-piece structure.
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.
Systems and methods for providing a barrier assembly that prevents access to a secure area can include a panel movable between an open position and a closed position in which the panel substantially obstructs a passageway, but where the panel width is less than the width of the passageway. A first locking pin is movable from a retracted position within the panel to an extended position protruding out of the top edge of the panel, and a second locking pin is movable from a retracted position within the panel to an extended position protruding out of the bottom edge of the panel. An actuator is on or within the panel and is configured to trigger extension of the locking pins to respective extended positions when the actuator contacts a stopper in the passageway. The barrier assembly can further prevent retraction of the locking pins for a predetermined time delay.
A method performed by a mobile user equipment, UE, comprising: obtaining measurement information from a mobile phased array antenna, PAA, separate from the UE, the measurement information indicating, for at least one signal received by the PAA from a plurality of base stations, a received power, RP; determining, for the signal, a quality measure based on the RP of the signals; and transmitting, to a network node, a first message indicating the determined quality measure and enabling the network node to select at least one of the plurality of base stations as a target base station for a communication connection with the UE. Also a computer program, a UE, and a system.
A method for automatically testing a hydraulic system of an aircraft during ground service is disclosed. The hydraulic system includes, onboard of the aircraft, a hydraulic pump, a hydraulic reservoir, a hydraulic conduct system, a hydraulically driven unit, and a control and monitoring unit, the method includes the steps a) pressurizing the hydraulic system by the hydraulic pump, b) monitoring at least one parameter indicative of an external leakage of the hydraulic system during the pressurisation of the hydraulic system, c) determining whether an external leakage of the hydraulic system exists on basis of the at least one parameter.
B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
F15B 19/00 - Test des systèmes ou appareils de manœuvre utilisant la pression d'un fluide, dans la mesure où ils ne sont pas prévus ailleurs
G01M 3/26 - Examen de l'étanchéité des structures ou ouvrages vis-à-vis d'un fluide par utilisation d'un fluide ou en faisant le vide par mesure du taux de perte ou de gain d'un fluide, p. ex. avec des dispositifs réagissant à la pression, avec des indicateurs de débit
A method for manufacturing a monolithic component with integral branching points, including providing a sheet metal comprising a first section and a second section, thinning, via rollforming, the first section of the sheet metal, splitting, via split-rollforming, the second section of the sheet metal in a plane parallel to a surface area of the second section, such that a first flange portion and a second flange portion is formed.
B64F 5/10 - Fabrication ou assemblage d’aéronefs, p. ex. gabarits à cet effet
B21B 1/08 - Méthodes de laminage ou laminoirs pour la fabrication des produits semi-finis de section pleine ou de profilésSéquence des opérations dans les trains de laminoirsInstallation d'une usine de laminage, p. ex. groupement de cagesSuccession des passes ou des alternances de passes pour laminer des pièces de section particulière, p. ex. des cornières
B21B 1/28 - Méthodes de laminage ou laminoirs pour la fabrication des produits semi-finis de section pleine ou de profilésSéquence des opérations dans les trains de laminoirsInstallation d'une usine de laminage, p. ex. groupement de cagesSuccession des passes ou des alternances de passes pour laminer des bandes ou des feuilles en longueurs indéfinies selon un processus continu par laminage à froid
A carrier structure for electrodes of a fuel cell. The structure has a duct wall and a tubular ducting volume. The duct wall forms the tubular ducting volume and includes an outer surface facing a surrounding and an inner surface facing the tubular ducting volume. The tubular ducting volume conducts a first supply flow comprising an oxidant. The duct wall provides a second supply flow within the duct wall, the second supply flow being a reductant. The duct wall separates the first supply flow in the tubular ducting volume from the second supply flow within the duct wall and the surrounding of the carrier structure. A primary power coating layer is applied on the inner surface of the duct wall, arranged between the first supply flow and the second supply flow. The coating layer generates electrical energy from the first supply flow and the second supply flow.
H01M 8/0252 - CollecteursSéparateurs, p. ex. séparateurs bipolairesInterconnecteurs caractérisés par la forme tubulaire
B64D 27/355 - Aménagements pour la production, la distribution, la récupération ou le stockage d'énergie électrique à bord utilisant des piles à combustible
H01M 8/04082 - Dispositions pour la commande des paramètres des réactifs, p. ex. de la pression ou de la concentration
A hydraulic system for reducing mechanical loads or noise development is disclosed having at least two hydraulic pumps including a pump element, such as a piston or rotary gear. The hydraulic pumps can be speed-controlled by a pump controller to achieve a nominal pressure P0. The pump controller further includes an offset (Δx) between the pump elements and controls one of the hydraulic pumps such that the pump elements move in an anti-cyclic manner, that is, a phase shift of about 180°.
F04B 49/20 - Commande des "machines", pompes ou installations de pompage ou mesures de sécurité les concernant non prévues dans les groupes ou présentant un intérêt autre que celui visé par ces groupes en modifiant la vitesse d'entraînement
F04B 17/03 - Pompes caractérisées par leur combinaison avec des machines motrices ou moteurs particuliers qui les entraînent ou par leur adaptation à ceux-ci entraînées par des moteurs électriques
A hot air duct for an aircraft, particularly a bilge area of the aircraft. The hot air duct comprises a body and an inlet in the body which is configured to receive hot air. The body is made of a flexible material and is configured to be inflated, when air is received through the inlet. Also an aircraft section as well as an aircraft including such hot air duct.
B64D 13/08 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacements réservés au fret l'air étant climatisé l'air étant réchauffé ou refroidi
An aircraft fuselage includes fore and aft sections, a barrier wall separating the sections and an opening therebetween, a rail attached to the barrier wall, a door moveable across the barrier wall between an open position offset from the opening and a closed position covering the opening, a first roller and a second roller rotatably fixed to the door and moveable on the rail along first and second paths to move the door, the rail including a first ramp engaging the first roller as it moves along the first path and to direct the first roller towards the barrier wall, and a second ramp engaging the second roller as it moves along the second path and to direct the second roller towards the barrier wall, the first roller configured to engage the first ramp as the second roller engages the second ramp to move the door towards the barrier wall.
A seat mounting system having a seat rail and a seat fitting, wherein the seat rail has an upper flange with a plurality of heads thereon. The seat fitting comprises a main body having a void configured to receive the upper flange and at least some of the plurality of heads.
A storage tank arrangement, optionally suitable for a vehicle, includes a storage tank for storage of volatile liquids including a tank inner wall and a tank outer wall separated by an insulating inter-wall region, inner and outer feedthrough arrangements, each configured to form a seal with a respective surface of the storage tank arrangement and to permit passage therethrough, and/or permit connection of, of one or more sensors, and a container external of the storage tank outer wall, configured to inhibit egress of the contents of the storage tank in the event of a failure of at least one of the inner and outer feedthrough arrangements. A vehicle including such a storage tank arrangement is also disclosed.
A greywater reuse lavatory for an aircraft and a corresponding aircraft equipped therewith. The greywater reuse lavatory buffers greywater from a water consumer and allows flushing a toilet bowl through a flushing supply pipe having a plurality of nozzles, wherein the flushing supply pipe can be flushed out or cleaned via a discharge.
A support for coaxial flanges of a double-coaxial coupling includes a circular support structure providing a primary mounting zone for attaching a primary flange for connecting a primary outer tube, and a secondary mounting zone for attaching a secondary flange for connecting a coaxial secondary inner tube. The primary and the secondary mounting zones are spaced apart from each other in a radial direction for centering the primary and the secondary flanges in a radially spaced coaxial manner. The primary mounting zone provides an outer circumferential connection region with at least three mounting points for attaching the primary flange. The secondary mounting zone provides an inner circumferential connection region with at least three mounting points for attaching the secondary flange. A thermal path within the circular support structure between the mounting points of the primary and secondary mounting zones is longer than the distance between the two points.
A fuel cell system comprising a fuel cell, a fuel tank, a fuel distribution pipe fluidly connecting the fuel tank with a fuel inlet of the fuel cell. The fuel distribution pipe has an inner pipe and an outer pipe, the latter of which receives a stream of inert gas from an inert gas separator that is fluidly connected to a gas outlet of the fuel cell.
H01M 8/04082 - Dispositions pour la commande des paramètres des réactifs, p. ex. de la pression ou de la concentration
B64D 27/355 - Aménagements pour la production, la distribution, la récupération ou le stockage d'énergie électrique à bord utilisant des piles à combustible
H01M 8/0662 - Traitement des réactifs gazeux ou des résidus gazeux, p. ex. nettoyage
22.
SYSTEM AND METHOD FOR A MANUFACTURING ENVIRONMENT WITH ROBOTIC SYSTEM MOUNTS HAVING ONE OR MORE END EFFECTORS POSITIONED SYMPATHETIC TO THE UNDERLYING MANUFACTURED ITEM
A method of manufacturing with a robotic manufacturing system including a track extending along a length of a component of a partially manufactured item, wherein the component has a non-constant longitudinal shape, the track being supported independently of the partially manufactured item. The system includes a jointed member having an elongated arcuate shape, a mount longitudinally movable along the track and configured to receive the jointed member in an articulating manner, and an end effector movably mounted on the jointed member. The jointed member moves along a portion of the component length in a radial position sympathetic to the non-constant component longitudinal shape. The jointed member longitudinally moves relative to the mount along its elongated arcuate shape such that the jointed member moves in an arc spaced from and around an outer component surface. A portion of the end effector moves along a length of the jointed member.
A heat-protecting fuel supply arrangement includes a manifold, being a duct arrangement that includes at least one fuel supply line and at least one coolant duct and a heat protection shielding. The manifold is formed to be mounted to an end connection portion of the fuel cell. The manifold is formed to supply the fuel cell with a fuel via the at least one fuel supply line and to provide cooling at least to the fuel supply line via the at least one coolant duct. The manifold is made from a polymeric material defining the structural integrity of the manifold. The heat protection shielding protects at least a portion of an outer surface of the at least one fuel supply line against external thermal sources to mitigate thermal changes of the manifold.
An aircraft cabin floor arrangement with air distribution. The arrangement comprises a plurality of floor panels and at least one air supply. The at least one air supply is configured for being arranged in a longitudinal direction of an aircraft. The plurality of floor panels are configured for being arranged in a spanning direction transverse to the longitudinal direction of the aircraft. The plurality of floor panels each comprise a plurality of elongate cavities aligned with the spanning direction of the floor panels. The at least one air supply is fluidly connected to at least a part of the elongate cavities of the floor panels for supplying air from the at least one air supply to the elongate cavities. The fluidly connected elongate cavities are providing supply air to passenger seat areas in an aircraft cabin.
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
A method for assembling a component to an aircraft body portion comprises using a funnel device to guide a portion of the component relative to the body portion for movement into a desired position for assembly. Also a funnel device which is configured to be supported by a body portion in a predetermined position and orientation relative to an orifice of the body portion during an assembly process. Also, a pintle mounting portion of an aircraft landing gear assembly is funneled into a predetermined position relative to a pintle mount portion of an aircraft body.
A support apparatus to support a component such as an aircraft landing gear assembly in an installation location for assembly to a body. The apparatus is adapted to assist movement of the supported component in a direction of a vertical axis to reduce an external force necessary to reposition the component from an approximate alignment position into a desired final alignment position. A method of assembly comprising resiliently supporting a component on a platform to assist vertical movement of a mounting portion of the component to align with a mount portion of the body. A pin having a tapered end portion is inserted through an orifice of a pintle mounting and an orifice of a pintle mount to align an aircraft landing gear assembly with a body.
An aircraft floor arrangement with customizable load-bearing capabilities is provided that comprises a plurality of floor panels and at least one support profile. The at least one support profile is configured to reinforce at least one of the floor panels such that the load-bearing capabilities are increased. The floor panels are provided with a plurality of interface points arranged at least along one direction. The interface points are configured for mounting of one of the support profiles to one of the floor panels via the interface points to reinforce the floor panels.
For leakage detection and evaluation to provide an improved assessment of a leakage, a leakage characterization arrangement includes a compound with at least two emission generating markers. The compound is applicable at an outside of an enclosure, encapsulating a fuel from the surroundings. The applied compound is configured to physically react and/or chemically react upon exposure to an activation energy resulting from leaking fuel from an inside of the enclosure. The physical reaction and/or the chemical reaction actively produce a detectable emission that indicates at least one measurable parameter of a leakage site based on the at least two emission generating markers.
G01M 3/04 - Examen de l'étanchéité des structures ou ouvrages vis-à-vis d'un fluide par utilisation d'un fluide ou en faisant le vide par détection de la présence du fluide à l'emplacement de la fuite
A double-wall pipe for an aircraft fuel system includes an inner wall defining a first open end, a second open end, and an inner region connecting the first open end to the second open end and via which a fuel is flowable through the double-wall pipe, in use. The double-wall pipe includes an outer wall at least in part around the inner wall to define an interspace, between the inner wall and the outer wall, that is fluidically isolated from the inner region. The double-wall pipe includes at least one barrier that is openable to create a passage that fluidically connects the interspace to the inner region. The at least one barrier is configured to open when a pressure in the interspace is higher than a pressure in the inner region.
A tool system for producing a component from a fiber-reinforced plastic includes a molding tool with a tool surface having a peripheral edge, a compensating body having a coefficient of thermal expansion greater than that of the molding tool, a closure device, and a heating device for heating the molding tool. The tool surface is configured to receive, at a first temperature, at least one ply of a semifinished fiber product having a peripheral contour within the peripheral edge, and of the compensating body, along the peripheral edge, so the compensating body extends from the peripheral edge in a direction of the peripheral contour. The closure device is configured to close the molding tool to form a closed mold and, at a same time, to enclose the at least one ply of the semifinished fiber product and the compensating body. The closed mold includes a resin conduit for receiving resin.
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]
B29C 33/38 - Moules ou noyauxLeurs détails ou accessoires caractérisés par la matière ou le procédé de fabrication
B29C 33/40 - Matière plastique, p. ex. mousse ou caoutchouc
B29C 70/44 - Façonnage ou imprégnation par compression pour la fabrication d'objets de longueur définie, c.-à-d. d'objets distincts utilisant une pression isostatique, p. ex. moulage par différence de pression, avec un sac à vide, dans un autoclave ou avec un caoutchouc expansible
A hydraulic actuator comprising a housing, a piston, first to third pressure chambers, and a plurality of arrangements of piezoelectric elements arranged inside one of the plurality of chambers. A computer implemented internal brake for selectively switching between a braking mode and a non-braking mode of the piston comprises the third chamber, and fluid connections between the first to third chambers with flow control elements.
F15B 15/24 - Autres parties constitutives pour limiter la course
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
F15B 13/044 - Dispositifs de distribution ou d'alimentation du fluide caractérisés par leur adaptation à la commande de servomoteurs pour utilisation avec un servomoteur unique actionnés par des moyens commandés électriquement, p. ex. des solénoïdes, des moteurs à couple
32.
CABIN LINING ELEMENT FOR AN AIRCRAFT CABIN AND RIB FOR AN AIRCRAFT FUSELAGE STRUCTURE
A cabin lining element for an aircraft cabin which is arranged in the interior of an aircraft fuselage structure, having a fuselage structure side and a cabin side. The cabin lining element comprises an electrically contactable heating lacquer layer at least in regions on its fuselage structure side. A rib is provided for an aircraft fuselage structure, having at least one foot portion on the outer skin facing side and a cabin facing side head portion. The rib comprises an electrically contactable heating lacquer layer at least in regions on a side of the head portion facing the cabin.
H05B 3/14 - Éléments chauffants caractérisés par la composition ou la nature des matériaux ou par la disposition du conducteur caractérisés par la composition ou la nature du matériau conducteur le matériau étant non métallique
An aircraft wing (3) including a main wing (5), a slat (7), and a connection assembly (9) movably connecting the slat (7) to the main wing (5). The connection assembly (9) includes an elongate slat track (17) extending along a track longitudinal axis (19) having a front end (21) an intermediate portion (25) and a rear end (23). The front end (21) and/or the intermediate portion (25) is mounted to the slat (7). The rear end (23) and/or the intermediate portion (25) is mounted to the main wing (5) by a roller bearing (27). The roller bearing (27) includes a guide rail (29) mounted to the main wing (5) and a first roller unit (31) mounted to the rear end (23) of the slat track (17) and engaging the guide rail (29), and wherein the guide rail (29) includes an upper rail portion (32) and a lower rail portion (34).
A drive assembly for driving a movable flow body of an aircraft, includes: a power drive unit, a flight control computer, a first flex shaft connecting the power drive unit to an inboard drive station, a second flex shaft connecting the inboard drive station to an outboard drive station, a first actuator connected to the inboard drive station and being couplable with the movable flow body, a second actuator connected to the outboard drive station and being couplable with the movable flow body. The second actuator includes a redundant position feedback sensor. The power drive unit includes a power-off brake, wherein the position feedback sensor is configured to send a position feedback signal to the flight control computer, and the flight control computer is configured to control the power drive unit.
A wing for an aircraft, comprising a main wing and a high lift assembly which includes a body, and an assembly connecting the body to the main wing, so the body is movable between a retracted position and an extended position. The assembly comprises a track extending along a longitudinal axis between first and second ends, with an intermediate portion therebetween. A roller bearing ensures that the track moves along the longitudinal axis. The roller bearing comprises bearing units, each mounted to the main wing and having a bearing surface for engaging the elongate track. The units include a first and second end units and an intermediate unit wherein, relative to the longitudinal axis, the intermediate unit is positioned between the first end unit and the second end unit. The elongate track comprises a recessed portion which, in the retracted position, aligns the intermediate unit.
An aircraft wing includes a main wing and a high lift assembly having a high lift body and a connection assembly movably connecting the high lift body to the main wing, such that the high lift body is movable between retracted and extended positions. The connection assembly includes an elongate track extending along a longitudinal axis between first and second ends and has an intermediate portion. The first end is mounted to the high lift body, and the second end is mounted to the main wing by a roller bearing such that the track is movable along the longitudinal axis. The roller bearing includes a roller unit mounted to the main wing and having a circumferential roller surface engaging an engagement surface of the track and an internal elastic bearing allowing the roller surface, in a cross section parallel to the roller rotation axis, to adapt its orientation or form.
An aircraft wing includes a main wing and a high lift assembly having a high lift body, and a connection assembly movably connecting the high lift body to the main wing to be movable between a retracted and an extended position, and having an elongate track extending along a longitudinal axis between a first end and a second end. The first end of the track is mounted to the high lift body. The track is mounted to the main wing via a roller bearing to be movable along the longitudinal axis. The roller bearing includes a first and a second roller mounted to at least one of the main wing and the track via first and second eccentric connector assembly, respectively. The first and second eccentric connector assemblies are configured to be engaged simultaneously by a single alignment member for synchronous rigging of the first and second rollers.
A wing (3) for an aircraft (1) including a fixed wing (5), a foldable wing tip portion (9) mounted to the fixed wing (5) via a hinge (11) in a manner rotatable about a hinge axis (13) between an extended position and a folded position, an actuation device (24) for actuating the foldable wing tip portion (9) for movement between the extended position and the folded position, and an arresting device (37) for arresting the foldable wing tip portion (9) in the extended position and/or in the folded position. The arresting device (37) includes a clutch device (39) configured for selectively holding the foldable wing tip portion (9) in a fixed position relative to the fixed wing (7) and releasing the foldable wing tip portion (9) for movement relative to the fixed wing (7) about the hinge axis (13).
An aircraft with a potable water system enabling the connection of monuments to preinstalled aircraft potable water interfaces by customized piping, which is routed within raceways for example directly along seat rails, and an installation method.
An aircraft with a potable water system to feed potable water from a potable water tank to a consumer equipment of a monument in the aircraft cabin, including potable water interfaces, and at least one monument, with at least one opening in the monument to establish a fluid connection to the consumer equipment, wherein at least one potable water interface is accessible through the at least one opening, and an assembly method for installing a potable water system wherein standard parts of the potable water system are preinstalled and customized parts are installed later on.
B64D 11/00 - Arrangements pour passagers ou équipageInstallations de postes de pilotage non prévues ailleurs
E03B 11/02 - Aménagements ou adaptations de réservoirs pour l'alimentation en eau pour l'alimentation en eau à usage domestique ou alimentation locale analogue
41.
PAINTING DEVICE HAVING A MOVABLE ROBOTIC ARM CARRYING A TOOL AND A MOVABLE PIECE OF EQUIPMENT CONNECTED BY AN UMBILICAL CONNECTION TO THE TOOL
A painting device including at least one guide system, at least a first movable support configured to move along the guide system, a robotic arm secured to the first movable support, at least a first tool connected to the free end of the robotic arm, and at least a first piece of equipment connected to the first tool by at least one umbilical connection, the first piece of equipment being movable and connected to the first movable support. This configuration makes it possible to reduce the length of the umbilical connection. A painting installation having at least one such painting device is also provided.
A painting system suitable for painting a fuselage of an aircraft, including a paint booth which is positioned on a platform. This paint booth includes at least first and second lateral openings which are configured to permit the wings of the aircraft to pass through the paint booth, in addition to at least two elements, at least one thereof being mobile between an adjacent position corresponding to a closed state of the paint booth in which the two elements are joined together, in addition to a spaced-apart position corresponding to an open state of the paint booth in which the fuselage can be positioned between the two elements.
An aircraft cooling device for cooling a fluid in a fluid supply and/or drainage device of an aircraft in flight, the aircraft cooling device being configured as a skin component for the aircraft, the skin component including an integrated ply of one or more hollow fibers, each hollow fiber being configured for conducting the fluid from one end portion to another end portion of the hollow fiber such that the fluid supply and/or drainage device is enabled to pump the fluid through the one or more hollow fibers when in fluid connection with ply.
B64D 33/08 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des systèmes de refroidissement des ensembles fonctionnels de propulsion
B64C 1/00 - FuselagesCaractéristiques structurales communes aux fuselages, voilures, surfaces stabilisatrices ou organes apparentés
B64C 1/12 - Structure ou fixation de panneaux de revêtement
B64C 7/00 - Structures ou carénages non prévus ailleurs
B64D 27/355 - Aménagements pour la production, la distribution, la récupération ou le stockage d'énergie électrique à bord utilisant des piles à combustible
F28D 21/00 - Appareils échangeurs de chaleur non couverts par l'un des groupes
H01M 8/0267 - CollecteursSéparateurs, p. ex. séparateurs bipolairesInterconnecteurs comprenant des moyens de chauffage ou de refroidissement, p. ex. des éléments de chauffage ou des canaux d’écoulement du réfrigérant
44.
ADJUSTABLE WATER SUPPLY SYSTEM AND AIRCRAFT EQUIPPED WITH A WATER SUPPLY SYSTEM
A water supply system for an aircraft includes a water supply tank, water consumers, a pressurization unit to convey water from the water supply tank to the water consumers, water consumer supply units, each of the water consumer supply units configured to control water supply from the pressurization unit to one of the water consumers, and a controller. Each of the water consumer supply units is configured to output a consumer signal indicating a water supply of the respective water consumer, wherein the controller is configured to receive the consumer signal of the water consumer supply units and to control a flow rate and/or pressure of the pressurization unit depending on the consumer signal.
A polar plate for use in a fuel cell device, the polar plate including an integrated fiber arrangement of one or more hollow fibers, each hollow fiber being configured for conducting a fluid from one end portion to another end portion of the hollow fiber such that the fluid can be pumped through the one or more hollow fibers. Also a fuel cell device, a method for producing the polar plate, an additive manufacturing device, a computer program.
H01M 8/0267 - CollecteursSéparateurs, p. ex. séparateurs bipolairesInterconnecteurs comprenant des moyens de chauffage ou de refroidissement, p. ex. des éléments de chauffage ou des canaux d’écoulement du réfrigérant
B33Y 80/00 - Produits obtenus par fabrication additive
B60L 58/33 - Procédés ou agencements de circuits pour surveiller ou commander des batteries ou des piles à combustible, spécialement adaptés pour des véhicules électriques pour la surveillance et la commande des piles à combustible pour la commande de la température des piles à combustible, p. ex. en commandant la charge électrique par refroidissement
H01M 8/0263 - CollecteursSéparateurs, p. ex. séparateurs bipolairesInterconnecteurs caractérisés par la configuration des canaux, p. ex. par le champ d’écoulement du réactif ou du réfrigérant comprenant des chemins zigzagants ou en serpentins
46.
HIGH PRESSURE WATER SUPPLY SYSTEM AND AIRCRAFT EQUIPPED WITH SUCH SYSTEM
A high pressure water supply system for an aircraft includes a main water supply tank, water consumers, pressurization units configured to convey water from the main water supply tank to the water consumers, and a controller. One pressurization unit of the pressurization units conveys water to a first subset of water consumers of the water consumers via a corresponding high pressure water supply line, and the controller is configured to control an output pressure of the one pressurization unit depending on a hydraulic resistance length of the high pressure water supply line.
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 reaction transmitting device includes an emission generating compound provided as an elongate transmitting structure having first and second ends, the emission generating compound reaching from the first to the second end. The emission generating compound can be exposed to local thermal energy release at a trigger location between the first and second end along the elongate structure resulting from leaked substance from an enclosure, the enclosure configured to encapsulate a substance from surroundings. The emission generating compound provides an emission reaction upon being triggered by the local thermal energy release and relays the emission reaction from the trigger location along the elongate transmitting structure to the second end which is configured to be exposed to a sensing unit configured to detect a transmitted emission reaction as a signal indicative of the leaked substance.
G01M 3/04 - Examen de l'étanchéité des structures ou ouvrages vis-à-vis d'un fluide par utilisation d'un fluide ou en faisant le vide par détection de la présence du fluide à l'emplacement de la fuite
G01M 3/00 - Examen de l'étanchéité des structures ou ouvrages vis-à-vis d'un fluide
H01M 8/04082 - Dispositions pour la commande des paramètres des réactifs, p. ex. de la pression ou de la concentration
A high lift assembly (7) including: a high lift body with a high lift structure (8) and an internal volume (22), and a connection assembly (10) extending through an aperture (18) in an outer skin (20) of a leading edge of a main wing (5), the connection assembly (10) includes an elongate track (16) and a first and second connectors (12, 14), the elongate track (16) is mounted to the main wing (5) and moves along a track longitudinal axis (24), and the first and second connectors (12, 14) connect the elongate track (16), the first connector (12) is between the internal volume (22) and the outer skin (20), the second connector (14) has a longitudinal axis transverse to the leading edge of the high lift body and connects to the high lift body and the high lift structure has an opening (40) for the elongate track.
A rod with attachment sockets for a truss structure of a vehicle. The rod comprises an elongated body having a plurality of attachment sockets formed on and distributed over an outer side of the body. The plurality of attachment sockets comprises at least a first number of attachment sockets facing in a first direction and a second number of attachment sockets facing in a second direction different from the first direction. The plurality of attachment sockets each comprises a cavity open to the outer side of the body and comprising at least one bearing surface.
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 reinforcing device to provide an alternative improvement in the structural stability of laminated components includes a body structure having an abutment surface and at least one fastening area. The abutment surface extends along a first direction. In a cross-sectional direction, transverse to the first direction, the abutment surface includes a rounded contour section so abutment surface is configured to conform with a concave edge section of a laminated structural member. The at least one fastening area is provided at the body structure opposite to the abutment surface. The at least one fastening area is configured to secure the abutment surface against the concave edge section of the laminated structural member.
A structural element for a passenger cabin of an aircraft is built using biomimicry methods. The structural element includes a generative structure, and a functional component. The generative structure includes at least one accommodating space. The functional component is arranged within the at least one accommodating space. The generative structure includes a load topology optimized structure based on a bioinspired generative design that is configured to enable the structural integrity of the structural element while simultaneously providing integrated functionalities via the functional component. Further, an interior component for an aircraft is disclosed that includes at least one such structural element, and an aircraft including at least one structural element. For example, an aircraft galley may include a structural component that may therefore, for example, include integrated wiring, plumbing or other functionalities.
The present disclosure relates to an aircraft galley. In order to provide an aircraft galley with improvements for operation and ergonomics, a galley module for an aircraft is provided that comprises a galley support structure providing a plurality of storage compartments and a countertop arranged above lower storage compartments and below upper storage compartments. The countertop is provided as permanent working surface for onboard services. At least one portion of the countertop is an extendable countertop portion that is movable between a retracted position and an extended position.
A passenger seat arrangement for a passenger aircraft includes a passenger seat assembly having at least one passenger seat with a seat supporting frame and a backrest, and a wireless charging system integrated into the backrest. The wireless charging system includes a PED holder having an assembly of permanent magnets embedded within the PED holder configured to a physically hold a PED on the PED holder in place, and a charging pad configured to electromagnetically transfer power to a PED held on the PED holder.
A water supply system for an aircraft and a method for draining water from or passing air into or out of a buffer tank of a water supply system in an aircraft. The system includes a water buffer tank having a fluid inlet and outlet, a supply arrangement for selective flow from the fluid outlet to a user equipment, and a relief arrangement for permitting fluid flow from the fluid outlet. The relief arrangement includes a relief conduit having a separation element with a separation element inlet positioned above a separation element outlet and separated therefrom by a separation distance such that water flowing in a forwards direction therethrough flows from the inlet to the outlet across the separation distance, and water flowing in a reverse direction therethrough flows into the separation element outlet and is retained therein, and wherein the separation element is defined by the user equipment.
Individual air supply duct for connecting a main air supply duct to a passenger service unit in an aircraft, wherein the duct is an extruded profile with a longitudinal extension direction (x). An individual air supply assembly comprising the duct and a passenger service unit configured to be mounted thereto, wherein the duct comprises individual connection ports, located on the outer surface of the duct, at equal intervals, wherein the passenger service unit comprises a port, located on the outer surface of the passenger service unit, and wherein, when the passenger service unit is mounted to the duct, the port is brought into close proximity and/or into alignment with a corresponding connection port.
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
A mounting rail interface comprises an elongate body. The body comprises two elongate lateral portions; and an elongate central portion arranged between the two lateral portions. The lateral portions are defined for providing a transition portion to an adjacent surface. The central portion comprises a plurality of openings with a respective circumferential edge flange. The openings are defined as elongate openings configured to allow a range of different orientations of a connector. The edge flange is defined with a concave curved contour on its bottom side. The concave curved contour provides an abutting surface for a connector configured to engage with the edge flange of the opening. The curved contour provides an abutting surface over at least an angular range.
A fuel cell comprising a tubular body, an inner and outer electrolyte layer disposed on the tubular body, an inner and outer electrically conductive layer disposed on the respective electrolyte layer, and a first electric terminal arranged at an interruption of the outer electrolyte layer and the outer electrically conductive layer. Also fuel cell systems having a plurality of such fuel cells, which are electrically connected in axial direction to form subgroups and in radial direction.
B60L 50/72 - Détails de construction des piles à combustible spécialement adaptées aux véhicules électriques
H01M 8/0252 - CollecteursSéparateurs, p. ex. séparateurs bipolairesInterconnecteurs caractérisés par la forme tubulaire
H01M 8/0258 - CollecteursSéparateurs, p. ex. séparateurs bipolairesInterconnecteurs caractérisés par la configuration des canaux, p. ex. par le champ d’écoulement du réactif ou du réfrigérant
H01M 8/12 - Éléments à combustible avec électrolytes solides fonctionnant à haute température, p. ex. avec un électrolyte en ZrO2 stabilisé
H01M 8/1226 - Éléments à combustible avec électrolytes solides fonctionnant à haute température, p. ex. avec un électrolyte en ZrO2 stabilisé caractérisés par la combinaison électrode/électrolyte ou par le matériau de support caractérisés par la couche de support
H01M 8/243 - Groupement d'éléments élémentaires de forme tubulaire ou cylindrique
60.
CRYOGENIC TANK WITH ACCESS OPENING, AND AIRCRAFT EQUIPPED THEREWITH
A cryogenic tank for an aircraft providing a tank access for maintenance and repairing services of equipment inside the tank onboard of the aircraft. An access opening is closed by a removable closure including a multiple wall panel which is vacuum insulated and which is configured and fitted to the multiple tank wall in a manner that the heat ingress into the cryogenic tank is minimized and that no vacuum is impacted by opening and closing the removable closure.
A display device for an aircraft cabin, comprising a first display directed to a first direction, a second display directed to a second direction different from the first direction, a mount for mounting the first display and the second display to a wall of the aircraft cabin, and a controller configured to control a first image displayed on the first display and a second image displayed on the second display, wherein the first direction and the second direction form an angle (γ) of greater than about 90°. Also an aircraft cabin, comprising the display device, and a method for assembling an aircraft cabin.
A leakage sensitive arrangement to improve detection of a leakage of a substance includes an emission generating compound that is applicable on an outside of an enclosure encapsulating a substance from the surroundings. The applied emission generating compound is configured to be exposed to an activation energy resulting from leaking substance from the inside of the enclosure. The activation energy causes a chemical reaction of the emission generating compound. The chemical reaction actively produces an emission detectable by a detector.
An aerodynamic system includes a support structure and an aerodynamic component movably coupled to the support structure via first and second coupling units such that the aerodynamic component can be moved relative to the support structure. The first and second coupling units can transfer a load from the aerodynamic component to the support structure. The system further includes an auxiliary coupling unit coupled between the aerodynamic component and the support structure, and configured to switch from a decoupling state to a coupling state, wherein, in the decoupling state, a load transfer via the at least one auxiliary coupling unit is prevented, and wherein, in the coupling state, a load transfer via the at least one auxiliary coupling unit is enabled.
A fastening element for fastening a first component to a second component. The fastening element includes an elastically deformable body and an elongated actuating member. The actuating member is movably guided relative to the body to be selectively movable further into or further out of the body. The body is configured to be elongated by moving the actuating member further into the body and applying a corresponding load onto the body and to elastically deform back by moving the actuating member further out of the body and releasing the load applied thereto. Further, the body is configured to have a smaller outer diameter when correspondingly elongated than when non-elongated and/or deformed back.
A ventilation device comprising a ventilation grille comprising a frame delimiting at least one opening, at least one flap designed to be in an open state in which the flap at least partially opens the opening and a closed state in which the flap blocks the opening, at least one articulation connecting the flap and the frame, a closed position holding system that is elastically deformable and designed to push and hold the flap in the closed state, an open position holding system that is fusible and designed to hold the flap in the open state against the closed position holding system, enabling the flap to be closed automatically. Also an aircraft having at least one such ventilation device.
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
66.
DEVICE FOR TRANSFORMATION OF THERMAL INTO ELECTRICAL ENERGY
Devices and methods for transformation of thermal energy directly into electrical energy. A fluid having particles to accept and emit electrons is in a container. At the container, a cathode is configured to emit electrons, wherein the particles of the fluid accept electrons emitted by the cathode, and an anode is configured to accept electrons, wherein the particles of the fluid emit electrons accepted by the anode. A heat transfer unit is configured to exchange heat with the fluid so the particles of the fluid are accelerated, and an electric field generator is configured to generate an electric field so negatively charged particles of the fluid are driven in a direction towards the cathode, while positively charged particles are driven towards the anode. Kinetic energy can be transformed directly into electrical energy.
H02N 3/00 - Générateurs dans lesquels l'énergie thermique ou cinétique est convertie en énergie électrique par ionisation d'un fluide et enlèvement de sa charge
67.
FLANGE COUPLING SYSTEM FOR CONNECTING PIPES IN AN AIRCRAFT
A flange coupling system for connecting pipes in an aircraft, comprises a first flange element and a second flange element, each flange element comprising a flange ring surrounding an opening for transporting a liquid or gaseous medium. Each flange ring comprises a sealing surface for mutual connection of both flange elements. Each flange element comprises one or more fixation members configured for mutual fixation of both flange elements so that their sealing surfaces are pressed against each other in a sealing plane. The fixation members of both flange elements are arranged in a way that both flange elements are fixed to each other in a fixation plane which is located away from the sealing plane.
F16L 23/036 - Raccords à brides les brides étant raccordées par des organes tendus axialement caractérisés par les moyens de mise en tension, p. ex. colliers de serrage en forme de C ou boulons spécialement adaptés
68.
FUEL CELL SYSTEM AND AIRCRAFT HAVING AN INERTING SYSTEM
A fuel cell system comprising a fuel cell, a fuel tank, a fuel distribution pipe fluidly connecting the fuel tank with a fuel inlet of the fuel cell, a shroud surrounding at least a portion of the fuel distribution pipe, an inerting system configured to generate nitrogen enriched air, NEA, and oxygen enriched air, OEA, and an NEA pipe conducting the nitrogen enriched air into the shroud.
H01M 8/22 - Éléments à combustible dans lesquels le combustible est à base de matériaux comprenant du carbone, de l'oxygène ou de l'hydrogène et d'autres élémentsÉléments à combustible dans lesquels le combustible est à base de matériaux comprenant uniquement des éléments autres que le carbone, l'oxygène ou l'hydrogène
B64D 27/355 - Aménagements pour la production, la distribution, la récupération ou le stockage d'énergie électrique à bord utilisant des piles à combustible
B64D 37/30 - Circuits de carburant pour carburants particuliers
H01M 8/04082 - Dispositions pour la commande des paramètres des réactifs, p. ex. de la pression ou de la concentration
A connector for enabling an electrical connection between principal surfaces of two planar panels by being sandwiched between the two planar panels. The connector comprises a deformable main body having a first elongated cuboid shape and having, perpendicular to the longitudinal direction of the first elongated cuboid shape, a first rectangular cross-section, and a conductive layer fully enclosing the perimeter of the first rectangular cross-section along a portion of the longitudinal direction of the deformable main body.
An interior aircraft section having a cover for a gap between a lining and a monument. The cover comprises a basic body, at least one mounting end configured to be fixedly mounted to the monument, and a connector configured to fixedly mount the basic body to the lining. The connector is arranged in an area of the basic body overlapping the lining. Also, an aircraft having such interior aircraft section.
An interior component for a passenger cabin. The interior component comprises a plate, which itself comprises a rigid section, and a compressible section. The rigid section and the compressible section form an integral body, and the compressible section is arranged at an end or side of the plate. Also an aircraft having such interior component and a method of manufacturing such interior component using additive manufacturing.
A multi-slot compartment for a plurality of containers or trolleys includes a plate defining an upper limit of the compartment, wherein a removable T-divider is arranged at a lower surface of the plate so the T-divider separates spaces for the containers or trolleys. The removable T-divider includes at least one separating element and an operating element, the at least one separating element being coupled to the operating element and adapted to move from a first condition in which lateral movements of the containers are blocked to a second condition in which the containers are allowed to freely move beneath the plate.
A display device for a vehicle cabin is disclosed including a first display layer having a plurality of first picture elements and configured to emit light towards a light emission side, a second display layer having a plurality of second picture elements and arranged adjacent to the first display layer opposite to the light emission side, a first control device connected to the first display layer and configured to control the plurality of first picture elements to display a first image on the first display layer, and a second control device connected to the second display layer and configured to control the second picture elements to display a second image on the second display layer. The second display layer is configured as an e-ink layer.
G09G 3/34 - Dispositions ou circuits de commande présentant un intérêt uniquement pour l'affichage utilisant des moyens de visualisation autres que les tubes à rayons cathodiques pour la présentation d'un ensemble de plusieurs caractères, p. ex. d'une page, en composant l'ensemble par combinaison d'éléments individuels disposés en matrice en commandant la lumière provenant d'une source indépendante
G02F 1/167 - Dispositifs ou dispositions pour la commande de l'intensité, de la couleur, de la phase, de la polarisation ou de la direction de la lumière arrivant d'une source lumineuse indépendante, p. ex. commutation, ouverture de porte ou modulationOptique non linéaire pour la commande de l'intensité, de la phase, de la polarisation ou de la couleur basés sur le mouvement de translation des particules dans un fluide sous l’influence de l’application d’un champ caractérisés par l’effet électro-optique ou magnéto-optique par électrophorèse
A transition for a sidewall and a monument in an aircraft. The transition comprises a transition wall bridging a gap between the sidewall and the monument, a side fitting arranged at a side edge of the transition wall facing the sidewall, the side fitting being configured to overlap and/or mate the sidewall, and a mount attached to the transition wall and configured to be mounted to the monument.
Airbus (China) Enterprise Management and Services Company Limited (Chine)
Inventeur(s)
Bauer, Michael
Mai, Yiwen
Sweers, Ronald Pieter
Abrégé
An inventory management system for managing consumer products on a vehicle, in particular an aircraft, includes a portable product-identification device configured to identify a consumer product presented to the product-identification device, wherein the product-identification device is configured to communicatively connect to a wireless network of the vehicle to update a central inventory of the vehicle based on the identified consumer product, and a detachable holder having a clamping arm configured to releasably clamp the holder to a service device within the vehicle and having a mounting plate configured to releasably attach to the product-identification device to mount the product-identification device on the holder and thereby on the respective service device within the vehicle.
G06Q 10/087 - Gestion d’inventaires ou de stocks, p. ex. exécution des commandes, approvisionnement ou régularisation par rapport aux commandes
G06K 7/14 - Méthodes ou dispositions pour la lecture de supports d'enregistrement par radiation électromagnétique, p. ex. lecture optiqueMéthodes ou dispositions pour la lecture de supports d'enregistrement par radiation corpusculaire utilisant la lumière sans sélection des longueurs d'onde, p. ex. lecture de la lumière blanche réfléchie
G06V 10/70 - Dispositions pour la reconnaissance ou la compréhension d’images ou de vidéos utilisant la reconnaissance de formes ou l’apprentissage automatique
An aircraft wing, including a main wing, a leading edge high lift assembly including a high lift body, and an assembly connecting the high lift body to the main wing. The high lift body is movable relative to the main wing between stowed and deployed positions. The connection assembly includes at least one rotation element mounted to the high lift body and rotatably mounted to the main wing. The main wing comprises an upper panel with a leading edge portion and a lower skin panel. The high lift body has a leading and a trailing edge. The high lift body trailing edge moves along the main wing upper skin panel leading edge portion when the high lift body is moved between the stowed and deployed positions. The upper skin panel leading edge portion is elastically deformed when the high lift body is moved from the stowed to the deployed position.
B64C 13/30 - Dispositifs de transmission sans amplification de puissance ou dans les cas où l'amplification de puissance est sans objet mécaniques utilisant des mécanismes à câbles, chaînes ou tiges
77.
PREPARATION FOR PRE-TREATING SURFACES BY CHEMICALLY CONVERTING OXIDE LAYERS OF TITANIUM OR TITANIUM ALLOYS
A preparation and a process for the surface pretreatment of titanium or titanium alloys containing 200 to 400 g/l NaOH and 10 to 150 g/l MGDA in water, wherein the preparation has a pH of at least 12, and preferably 13, and wherein a content of further substances is less than 1 g/l.
A water supply system for use in an aircraft, and a method for preventing blockages in a water supply system in an aircraft. The system comprises a central water tank comprising a fluid inlet and a fluid outlet, a supply conduit for permitting fluid flow from the outlet of the central water tank to a user equipment. At least a section of the supply conduit is connected and thermally coupled to an aircraft air duct so as to enable a transfer of thermal energy to the supply conduit therefrom to maintain the temperature of the water in the supply conduit above the freezing temperature thereof.
A fastener bracket configured to be installed on a holding structure. The fastener bracket is formed as a single piece comprising a plate portion and at least two pins protruding in parallel from a first surface of the plate portion. The at least two pins are at least partially made of a remoldable material. Also a fastener kit comprising such fastener bracket and at least one counter component. Moreover, an aircraft structure comprising at least one fastener bracket or fastener kit. Also an installation method of installing a fastener bracket.
A tank comprising one or several anti-sloshing wall arrangements, with a frame portion and a door portion wherein the frame portion is fixed to a tank wall of the tank, and it edges an opening, and wherein the door portion is configured to selectively close or unclose the opening. Also an aircraft comprising such tank and at least one engine, the engine being configured to be fed with fuel, in particular with liquid hydrogen, contained in the tank.
A cabin air ventilation system for a plurality of seat rows in an aircraft and an aircraft with such a cabin air ventilation system. The air ventilation system comprises a main body configured to be mounted to an underside of an overhead stowage compartment, the main body defining an inner volume, and a plurality of air ventilation outlets arranged in the main body, each of the ventilation outlets being configured to generate an airflow from the inner volume of the main body to one of the plurality of seat rows. At least some of the plurality of air ventilation outlets are arranged to generate the respective airflow to different seat rows.
B64D 13/00 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacements réservés au fret
B64D 11/00 - Arrangements pour passagers ou équipageInstallations de postes de pilotage non prévues ailleurs
A connector configured to enable an electrical connection between a first flexible carrier with electrically conductive tracks on its principal surface and a second flexible carrier with electrically conductive tracks on its principal surface. The connector includes a connector base part having a first planar shape and being configured to accommodate a first surface of the first flexible carrier opposed to the principal surface of the first flexible carrier, and a connector locking part having a second planar shape and being configured to accommodate a second surface of the second flexible carrier opposed to the principal surface of the second flexible carrier. In a closed state of the connector, the electrically conductive tracks of the first and second flexible carriers are urged to contact one another and are fixed in a defined position.
H01R 12/78 - Dispositifs de couplage pour circuits imprimés flexibles, câbles plats ou à rubans ou structures similaires se raccordant à d'autres circuits imprimés flexibles, à des câbles plats ou à rubans ou à des structures similaires
H01R 12/88 - Dispositifs de couplage raccordés avec une force d'insertion faible ou nulle moyens produisant une pression de contact, contacts activés après insertion des circuits imprimés ou des structures similaires agissant manuellement par rotation ou pivotement des pièces du boîtier du connecteur
H01R 12/89 - Dispositifs de couplage raccordés avec une force d'insertion faible ou nulle moyens produisant une pression de contact, contacts activés après insertion des circuits imprimés ou des structures similaires agissant manuellement par déplacement linéaire des pièces du boîtier du connecteur, p. ex. coulisseau
H01R 13/629 - Moyens additionnels pour faciliter l'engagement ou la séparation des pièces de couplage, p. ex. moyens pour aligner ou guider, leviers, pression de gaz
83.
FUEL TANK FOR AN AIRCRAFT, FUSELAGE OF AN AIRCRAFT, AND AIRCRAFT
A tank for an aircraft, the tank comprising two pressure bulkheads which are connected to each other by a tank wall which is at least partially formed by a portion of a skin of the aircraft's fuselage. The tank further comprises at least one anti-sloshing wall at least partially enclosing one or several openings and at least partially formed by a belonging frame stabilizing the skin. Also a fuselage with such tank, and an aircraft with such fuselage.
A mounting system for a cabin divider in an aircraft includes a curtain rail configured to hold and guide the cabin divider, a holding structure arranged at the curtain rail, a stretcher frame mounted to the holding structure, and a fabric cover spanned over the stretcher frame and covering the holding structure. Further disclosed is an aircraft having such mounting system.
An aircraft section for aircraft. The aircraft section comprises at least one flight component, such as a wing assembly and a tail assembly, and a first fuselage component. The flight component is mounted on the first fuselage component. The first fuselage component has a first coupling point designed for releasable connection to a second coupling point on a second fuselage component, in order to form an integrated fuselage of an aircraft when in a coupled state. The first coupling point provides a mechanical coupling with a second coupling point, forms a system infrastructure interface, and provides a data transmission device for integrity checking when the aircraft section is coupled to another aircraft section. The first coupling point likewise provides positioning sensors for guided docking of the aircraft section with another aircraft section in a target position.
HELMUT-SCHMIDT-UNIVERSITÄT/UNIVERSITÄT DER BUNDESWEHR HAMBURG (Allemagne)
AIRBUS OPERATIONS GMBH (Allemagne)
Inventeur(s)
Scholl, Gerd
Heynicke, Ralf
Bretthauer, Lars-Michel
Hoffmeister, Thomas
Abrégé
A measuring system for determining shape, deformations and/or change in orientation of a measurement object (12), the measuring system comprising a plurality of sensor probes (1) attachable as a sensor probe network on a measurement object surface (11). The sensor probes (1) are each directly coupled to a neighboring sensor probe (1) by a mechanical link (19). Sensor devices detect the orientation of a surface normal (13) of the surface (11) at the location of the respective sensor probe (1) relative to a predetermined reference axis and the orientation of each of the mechanical links (19) coupled to the respective sensor probe (1) relative to said surface normal (13) at the location of the respective sensor probe (1) or said predetermined reference axis. An analysis unit determines position and orientation of each of the sensor probes (1) from the measurement signals of the sensor devices.
G01B 5/207 - Dispositions pour la mesure caractérisées par l'utilisation de techniques mécaniques pour mesurer des contours ou des courbes en utilisant plusieurs transducteurs fixes fonctionnant simultanément
G01B 21/20 - Dispositions pour la mesure ou leurs détails, où la technique de mesure n'est pas couverte par les autres groupes de la présente sous-classe, est non spécifiée ou est non significative pour mesurer des contours ou des courbes, p. ex. pour déterminer un profil
87.
Liner Segment For A Frame Bay Of A Fuel Tank Structure And System For A Tank Structure, Comprising Such a Liner Segment
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.
An interface system for cabin trolleys for a vehicle includes a first interface device attachable to a monument, second interface device attachable to a cabin trolley, the first interface device including a first electrical port, first hot water port and first cold water port, a first guide element and first locking element, the second interface device including a second electrical port, second hot water port and second cold water port, a second guide element and second locking element, the first interface device and second interface device complementary to each other, so the first electrical port, first hot water port and first cold water port, and second electrical port, second hot water port and second cold water port connect to each other, the first guide element and second guide element engageable to guide the interface devices into connecting position, and the locking elements can releasably lock to arrest the interface devices.
An aircraft part with a door for accessing inside an aircraft and a fuselage part includes a cavity between an upstream edge of the door in the closed position and a downstream edge of the fuselage part, the cavity opening to the outside of the aircraft part and having a bottom connected to the upstream edge of the door and to the downstream edge of the fuselage part. The aircraft part includes a chamfer on the outer face of an outer plate of the door at the upstream edge of the door, as well as possibly other technical features such as a sharp ridge and/or an add-on component, allowing for reducing noise generated by the cavity.
A fairing arrangement for a high-lift mechanism for an aircraft is disclosed including a flap to be arranged at a trailing edge of an aircraft wing, and a mounting and guiding mechanism for the flap. The fairing arrangement includes a flap side fairing unit and a wing side fairing unit. The flap side fairing unit includes a flap side fairing for covering an aft part of the mounting and guiding mechanism and a flap side fairing mount for mounting the flap side fairing to the flap. The wing side fairing unit includes a wing side fairing for covering a forward part of the mounting and guiding mechanism, and a wing side fairing mount for mounting the wing side fairing to the wing. The wing side fairing mount is configured for movably connecting the wing side fairing to the wing such that the wing side fairing is rotatable around an axis directed at least partially in a vertical direction.
An aircraft system includes a support structure, an aerodynamic component, a first coupling unit and a second coupling unit. The first coupling unit includes a first coupling mechanism movably coupling the aerodynamic component to a first coupling point at the support structure, and a second coupling mechanism coupling the aerodynamic component to a second coupling point at the support structure. The first and second coupling points are spatially separated from each other, wherein the first coupling mechanism and the second coupling mechanism interact with each other to enable a rotational movement of the aerodynamic component with respect to the support structure such that, during the rotational movement of the aerodynamic component, a center of rotation of the aerodynamic component is translated from a neutral position to an adjusted position. The second coupling unit pivotably moves the aerodynamic component about a pivot axis at the support structure.
A grommet for feeding a stranded element through an opening includes a first grommet element having an elongated first body with a first collar radially extended relative to the first body. The grommet includes a second grommet element having an elongated second body with a second collar radially extended relative to the second body. The first grommet element and the second grommet element are formed separately from each other. A feedthrough includes the grommet, and a method includes feeding a stranded element through an opening.
B60R 16/02 - Circuits électriques ou circuits de fluides spécialement adaptés aux véhicules et non prévus ailleursAgencement des éléments des circuits électriques ou des circuits de fluides spécialement adapté aux véhicules et non prévu ailleurs électriques
An aerodynamic system for an aircraft. The aerodynamic system includes a first aerodynamic component configured to be movably coupled to a primary structure of the aircraft, a second aerodynamic component which is movably coupled to the first aerodynamic component and a first panel element coupled to the first aerodynamic component. The first panel element at least partially covers a gap between the first aerodynamic component and the second aerodynamic component. The aerodynamic system further includes a sealing element arranged between the first aerodynamic component and the second aerodynamic component. The sealing element is configured to at least partially block an airflow between the first aerodynamic component and the second aerodynamic component.
To allow the in-situ manufacture of a protective liner for an elongated finished structural part, it is proposed to mechanically attach a sealant mold portion to the elongated finished structural part, specifically the surface to be protected. The sealant mold portion in cooperation with the elongated finished structural part forms a mold cavity which gets injected with a wet sealant. The wet sealant cures into a cured sealant member which is bonded to the surface and acts as a protective liner.
A health monitoring method for checking a functionality of a flight control surface driving apparatus using a load sensor for sensing a load imposed on a control surface drive device by: comparing a load sensor output signal of the load sensor with a first while operating the control surface drive device to move the at least one control surface to a predetermined extended position; or, comparing a load sensor output signal of the load sensor with a second threshold while operating the control surface drive device to move the control surface from an extended position to a retracted position; or both. Also a flight control surface drive apparatus, a flight control system and an aircraft.
To manufacture a protected profile structural part of a fuselage of an aircraft, a sealant mold having a mold cavity having a cross-section that matches a portion of the profile structural part on which the surface to be protected is disposed is prepared. The mold cavity is filled with uncured wet sealant which is subsequently cured into a cured sealant member. The cured sealant member is then attached to the finished structural profile part in a non-movable manner to form a protective liner on the surface to be protected and to generate the protected profile structural part.
B29C 45/00 - 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
B29K 63/00 - Utilisation de résines époxy comme matière de moulage
B29K 75/00 - Utilisation de polyurées ou de polyuréthanes comme matière de moulage
B29K 81/00 - Utilisation de polymères contenant dans la chaîne principale uniquement du soufre avec ou sans azote, oxygène ou carbone comme matière de moulage
B29L 31/26 - Dispositifs d'étanchéité, p. ex. garniture pour pistons ou raccords de tuyaux
B29L 31/30 - Véhicules, p. ex. bateaux ou avions, ou éléments de leur carrosserie
97.
FRICTION STIR WELDING METHOD AND DEVICE, AS WELL AS WORKPIECE COMPRISING A BUTT WELD SEAM
A method for friction stir welding along a butt joint weld line (40). A welding device (70) includes a probe assembly (90) including at least a first and second probe device (100a, 100b). A first and second part (31a, 31b) to be joined along the weld line (40) are provided, wherein the parts are each formed as a laminate (1; 1′) including at least a first layer (2a, 2b) formed with a first material and a second layer (5a, 5b) formed with a second material. The first and second materials have different material properties. The method friction stir welds of the parts using the welding device, wherein simultaneously the first probe device acts on the first layers and the second probe device acts on the second layers.
B23K 20/12 - Soudage non électrique par percussion ou par une autre forme de pression, avec ou sans chauffage, p. ex. revêtement ou placage la chaleur étant produite par frictionSoudage par friction
B23K 11/00 - Soudage par résistanceSectionnement par chauffage par résistance
B23K 101/00 - Objets fabriqués par brasage, soudage ou découpage
98.
LATCH MECHANISM FOR AN OVERHEAD STOWAGE COMPARTMENT
A latch mechanism for a lid of an overhead stowage compartment. The latch mechanism comprises a plurality of locking members, and a plurality of latches. Each latch is configured to engage one of the locking members, wherein the plurality of latches is configured to be mounted into a bottom of the overhead stowage compartment, and wherein the plurality of locking members is associated with a single lid of the overhead stowage compartment.
E05B 63/14 - Disposition de plusieurs serrures ou de serrures comportant plusieurs pênes, p. ex. placés l'un derrière l'autre
B64D 11/00 - Arrangements pour passagers ou équipageInstallations de postes de pilotage non prévues ailleurs
E05B 47/00 - Fonctionnement ou commande des serrures ou autres dispositifs d'immobilisation par des moyens électriques ou magnétiques
E05B 51/02 - Fonctionnement ou commande des serrures ou autres dispositifs d'immobilisation par d'autres moyens non mécaniques par des moyens pneumatiques ou hydrauliques
A sealing strip for sealing a gap between convexly curved aerodynamic surface elements of an aircraft. The sealing strip has a convexly curved outer side, welting sections at both longitudinal edges of the sealing strip for fixing the sealing strip at the aerodynamic surface elements, and a mid-seal section between the welting sections. The welting sections protrude on an inner side from the mid-seal section. The sealing strip has a first, second, and third length regions, the second length region being located longitudinally between the first and third length region. The welting sections are omitted in the second length region or the welting sections in the second length region are less rigid than the welting sections in the first and third length regions. Further, a control surface arrangement, a wing and an aircraft with such a sealing strip.
A thermal control system and transport container with a thermal control system for transporting a payload. The thermal control system comprises a case, and an intermediate floor dividing an interior space of the case in a first section and a second section. The thermal control system further comprises a first air passage arranged in the case and fluidly connecting the first section with an exterior environment of the case. The intermediate floor comprises a phase-change material and is configured to allow air to pass through the intermediate floor and to exchange heat with the phase-change material.
