An airfoil profile for an aircraft, such as an unmanned aerial system. The airfoil profile includes a leading edge portion and a trailing edge portion that are spaced apart along a chordwise direction, an airfoil centroid; and an upper airfoil surface and a lower airfoil surface. The airfoil surfaces are shaped such that the pressure center of the lifting force is arranged at the same chord location as the airfoil centroid or closer to the trailing edge portion along the chordwise direction than the airfoil centroid. With this, a pitch-down momentum is generated that urges the leading edge portion towards a lower angle of attack.
An arrangement and method for manufacturing a composite part includes a mold, a composite material including fiber material and matrix material on a forming surface of the mold. To provide a simple and cheap technology for forming and optionally curing the component at the mold, the method includes providing a pressing tool made of semi-crystalline thermoplastic material in an amorphous state on the forming surface of the mold, forming the pressing tool by applying a pressure, that can be by expanding a hollow mandrel, and pressing the pressing tool against the mold, conducting crystallization of the pressing tool material by increasing the temperature of the pressing tool so material of the pressing tool is crystallized. Afterwards, the composite part may be hardened, such as by curing the composite part between the mold and the crystallized tube mandrel.
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
3.
GAP COVER FOR A DEVICE COMPONENT IN A PASSENGER CABIN
A gap cover (3) for a device component (1), preferably for a cabin attendant seat, for visually closing a gap (2) relative to a further cabin component (6) in a passenger cabin (7) is provided. The gap cover (3) has at least one covering element (29) composed of flexible material for spanning the gap (2), wherein a frame body, which has a frame base element and a flexible frame element, is arranged on the rear wall (13) of the device component (1), wherein the frame body also contains at least one functionally coupled spring element which is designed to push the flexible frame element into a state which increases the depth of the frame body.
AIRBUS (BEIJING) ENGINEERING CENTRE COMPANY LIMITED (Chine)
AIRBUS (CHINA) ENTERPRISE MANAGEMENT AND SERVICES COMPANY LIMITED (Chine)
AIRBUS (S.A.S.) (France)
AIRBUS OPERATIONS GMBH (Allemagne)
Inventeur(s)
Valette, Cedric
Maurmaier, Andreas
Morales Anton, Alejandro
Chen, Changming
Buffle, Clement
Edwards, Paul
Cao, Liyun
Yu, Jie
Abrégé
The present disclosure relates to an aircraft seat and an aircraft. The aircraft seat includes: a headrest; a backrest; and a seat plate pivotably mounted to the backrest and configured to be pivotable relative to the backrest from a seat plate stowed position to a seat plate expanded position for seating by a user and to be automatically pivotable from the seat plate expanded position to the seat plate stowed position in response to the user's departure. The aircraft seat is further provided with a display configured to displace as the seat plate pivots. The aircraft includes the above aircraft seat. The aircraft seat and the aircraft according to the present disclosure can facilitate the cabin crew to observe the situation in the cabin compartment when sitting on the aircraft seat, and ensure the utilization rate of the compartment space.
A movable cargo support for an aircraft cargo hold or passenger cabin includes a base member with its bottom surface having one or more support sections to support the base member on a floor surface. The base member includes wheel assemblies having a wheel member rotatable about a rotation axis and movably mounted on the base member to pivot about a steering axis of the wheel assembly and which can be altered between an extended position where the wheel member protrudes beyond the support plane and a retracted position where the wheel member does not extend beyond the support plane. Each wheel assembly has a biasing member biasing the wheel member towards the extended position and configured so the biasing force exceeds the force by X % at most which forces the wheel member towards the retracted position when the wheel members are on a floor surface and one or more cargo elements are on the support surface having the maximum allowable weight of the one or more cargo elements for the cargo support.
A multifunctional thermal and acoustic insulation system having a multilayer structure and a plurality of functional components formed integrally and non-exchangeably with the multilayer structure. The multilayer structure has a thermal and acoustic damping performance and comprises, in a stacked arrangement, a continuous first outer layer, a core layer and a continuous second outer layer. The core layer is between the outer layers so that the outer layers cover the core layer at least on opposite sides thereof. Functions of the functional components are related to at least one of the thermal and the acoustic damping performance of the multilayer structure and the functional components are provided on a first outer layer side of the core layer and/or on a second outer layer side of the core layer.
A thermal and acoustic insulation system for an aircraft, to be received between an inner surface of an aircraft primary structure, such as an aircraft fuselage structure, and a surface of a panel arrangement delimiting an aircraft cabin, the surface facing away from the aircraft cabin, comprises an insulation package and at least one sensor adapted to measure a level of humidity present in the insulation package. The insulation package comprises a core layer having a thermal and acoustic damping performance, and a packing layer enclosing the core layer. The packing layer is provided with a plurality of normally closed and selectively openable drainage openings which are actuatable to change between their normally closed state and an open state.
An aircraft cabin floor arrangement includes two floor support part-structures, each having vertical support members, a beam member, cantilevering members and a seat rail. The beam member and the seat rail extend in a first direction with the seat rail being carried by the beam member. The cantilevering members cantilever in a second direction transverse to the first direction. The vertical support members extend in a third direction transverse to the first and second directions. The two floor support part-structures are each configured to be arranged along opposing side portions within an aircraft fuselage structure and are configured to transfer load from the cantilevering members and the beam member to the fuselage structure. The cantilevering members and the beam member are configured to carry a cabin floor configured to provide a load transfer in a plane direction of the floor and to contribute to a stiffening of the fuselage structure.
A stolen aircraft shutdown system comprising a processor, a communications unit configured to receive information relating to a status indicator of an aircraft, corresponding to either a safe or a stolen value, and to provide a status input to the processor unit, a ground determination unit configured to receive aircraft operational data from an aircraft, corresponding to either a grounded or an airborne value, and to provide a location input to the processor. The processor unit is configured to determine the value of the status indicator and the value of the location indicator, and to provide immobilisation instructions to a control system of an aircraft to disable an aircraft function when the value of the status indicator is determined to be stolen, and the value of the location indicator is determined to be grounded.
A fastening device (1) for fastening mechanical element (2) with support structure (3) to fasten a cabin fitting element to a frame of an aircraft, fastening device (1) includes: enclosure (4) mountable to support structure (3); locator bush (5) in enclosure (4 and slidable along longitudinal axis (X) in an unlocked position of the fastening device (1); retaining element (6) around the longitudinal axis (X) and mechanically coupled to locator bush (5); and locking bolt (7) with a bolt head (8) mounting mechanical element (2) between bolt head (8) and enclosure (4), wherein locking bolt (7) is slidable into locator bush (5), and locking bolt (7) has a recess (9) on at least a section of a shell surface of locking bolt (7) and is positively-locking connectable with retaining element (6).
A network discovery method includes: sending, by a master node in a logical root hierarchy level of a data network, a discovery message including a forwarding counter to a first slave node in the data network first logical hierarchy level via a child port; increasing, by the first neighboring slave node, the forwarding counter; forwarding the discovery message with the increased forwarding counter to a second slave node in the first logical hierarchy level; receiving, by the first and second slave nodes, context information from the master node regarding the identities of the master node and the child port; determining, by the first and second slave nodes, its own functional designation based on the forwarding counter and the received context information by comparison with a mapping table; and updating the mapping table by matching the recorded functional designation in the mapping table with the first and slave node identities.
A wing component for an aircraft, comprising a leading edge part and a trailing edge part pivotably mounted to the leading edge part so as to pivot about a pivot axis, an actuator unit configured for moving the trailing edge part relative to the leading edge part, and a damper device configured for damping uncontrolled movement between the leading edge part and the trailing edge part. The trailing edge part comprises a first part portion and a second part portion arranged next to each other in a span direction and configured to pivot about the pivot axis individually, the damper device comprises a damping element coupled between the first part portion and the second part portion to damp relative movement of the first part portion and the second part portion.
B64C 13/38 - Dispositifs de transmission avec amplification de puissance
F16F 15/02 - Suppression des vibrations dans les systèmes non rotatifs, p.ex. dans des systèmes alternatifs; Suppression des vibrations dans les systèmes rotatifs par l'utilisation d'organes ne se déplaçant pas avec le système rotatif
13.
MODULAR LINE ASSEMBLY FOR INSTALLATION IN AN AIRCRAFT FUSELAGE
A line assembly for installation in an aircraft fuselage includes a first line section having a first diameter, a second line section having a second diameter, a set of first line brackets, and a set of second line brackets. The first line brackets include a first receiving space configured to hold the first line section and a first support portion for attaching the first line brackets to a fuselage structural part. The second line brackets include a second receiving space configured to hold the second line section and a second support portion for attaching the second line brackets to the first line section. The second line section includes a higher flexibility than the first line section. The second line section is attached to the first line section through a plurality of second line brackets arranged at a distance to and independent from the first line brackets.
B64F 5/10 - Fabrication ou assemblage d’aéronefs, p.ex. gabarits à cet effet
F16L 3/02 - Supports pour tuyaux, pour câbles ou pour conduits de protection, p.ex. potences, pattes de fixation, attaches, brides, colliers entourant partiellement le tuyau, le câble ou le conduit de protection
14.
SYSTEM AND METHOD FOR CLEANING A WASTE TANK IN AN AIRCRAFT
A system for cleaning a waste tank (4) in an aircraft is proposed, comprising a service device, at least one spray nozzle, and a first adaptor (12) for each of the at least one spray nozzle, wherein the service device comprises a descaling fluid tank (14), a service device outlet, a service device inlet and a pump in fluid communication with the service device outlet, wherein the at least one spray nozzle is coupled with the service device outlet or the pump through a first conduit (30), wherein the at least one spray nozzle is adapted for ejecting at least one descaling fluid jet into the waste tank, wherein the service device inlet is coupled with a second conduit (38) attachable to a waste tank outlet, wherein the first adaptor is couplable with the respective spray nozzle and comprises fastening means to attach the first adaptor to an opening of the waste tank in a substantially fluid-tight manner, and wherein the service device is designed to continuously circulate the descaling fluid through the service device outlet, the first conduit, the at least one spray nozzle, the waste tank outlet, the second conduit and the service device inlet.
B08B 3/02 - Nettoyage par la force de jets ou de pulvérisations
B08B 9/08 - Nettoyage de récipients, p.ex. de réservoirs
B08B 9/093 - Nettoyage de récipients, p.ex. de réservoirs par la force de jets ou de pulvérisations
B08B 9/032 - Nettoyage de conduites ou de tubes ou des systèmes de conduites ou de tubes Élimination des bouchons par l'action mécanique d'un fluide en mouvement, p.ex. par effet de chasse d'eau
B05B 13/06 - Machines ou installations pour appliquer des liquides ou d'autres matériaux fluides sur des surfaces d'objets ou de matériaux par pulvérisation, non couverts par les groupes conçus spécialement pour traiter l'intérieur de corps creux
B08B 3/04 - Nettoyage impliquant le contact avec un liquide
A system for positioning vehicle components relative to each other on a floor to prepare an assembly. A plurality of carriers receive a vehicle component. A plurality of positioning tables have a lower portions which can be fixed to the floor and a upper portions which receive a carrier. A location device having at least one base and mobile units moveable relative to the base. At some of the positioning tables moves the respective upper portion along at least two movement axes relative to the respective lower portion to position a carrier located thereon. A transport device guides the carriers from an external position to a positioning table and to place them on the upper portion. The location device determines the positions of the respective mobile units relative to the at least one base. A position control unit controls a movement of the upper portions to a predetermined target position.
B64F 5/10 - Fabrication ou assemblage d’aéronefs, p.ex. gabarits à cet effet
G01S 5/02 - Localisation par coordination de plusieurs déterminations de direction ou de ligne de position; Localisation par coordination de plusieurs déterminations de distance utilisant les ondes radioélectriques
G01S 5/14 - Localisation par coordination de plusieurs déterminations de direction ou de ligne de position; Localisation par coordination de plusieurs déterminations de distance utilisant les ondes radioélectriques déterminant des distances absolues à partir de plusieurs points espacés d'emplacement connu
G01S 13/46 - Détermination indirecte des données relatives à la position
16.
BLIND RIVET, AND SYSTEM AND METHOD FOR MAKING SEALED BLIND RIVET JOINTS
A blind rivet, for connecting workpieces, comprising a hollow, deformable rivet body with a bearing collar and a sleeve attached thereto, a rivet mandrel in the sleeve and extending through the bearing collar, having a tool holder head, and a sealing ring. The sealing ring is arranged between the bearing collar and the tool holder head and is made of a curable and not fully cured sealing material. During contraction of the blind rivet, the sealing ring is pressed axially towards the bearing collar by a tool that can be connected to the tool holder head or by a section of the rivet mandrel. The sealing ring is designed to flow radially and axially into gaps and spaces on the bearing collar and between the bearing collar and the workpieces while the sealing ring is compressed, and to adhere there.
A system for scanning or inspecting an aircraft or spacecraft surface. A ground vehicle has a first inspection device, a hovering platform has a second inspection device. The first inspection device is on a first arm of the ground vehicle. The ground vehicle comprises a vertical pole and a transverse holding element extends therefrom. The hovering platform is electrically connected to the ground vehicle through a cable for transferring electrical power and/or data to the hovering platform. The vertical pole and/or transverse holding element carry the cable. The hovering platform is flexibly held on the vertical pole and/or the transverse holding element through the cable or an additional component. The inspection devices determine a characteristic of the surface and identify points of shape deviation by comparison with an intended characteristic. The system successively inspects the surface through the inspection devices being arranged in different heights at the same time.
A method for operating an on-board water supply and distribution system of an aircraft for supplying water includes a central tank, consumer assemblies with a supply device and a buffer tank, pump operable in a supply mode and reverse mode, filter device, and high-pressure conduit system. The central tank connects to the pump's upstream side. The conduit system connects the downstream side and consumer assemblies. The pump in supply mode delivers water from the downstream side to the buffer tank. In reverse mode, the pump can convey water from the downstream side to the upstream side. The method includes operating the pump in supply mode so water from the central tank goes to a consumer assembly in a first time interval to fill the buffer tank, and operating the pump in reverse mode in a second time interval so water from the buffer tank passes through the filter device.
A trailing edge system for a wing of an aircraft comprises a flap device arrangement configured for being mounted at a trailing edge of an aircraft wing, wherein at least two movable flap devices of the flap device arrangement are spaced apart from each other. A torque element is connecting the movable flap devices for transmitting a torque to the movable flap devices in order to actuate a rotational movement of the movable flap devices. An actuator for rotationally driving the torque element is provided. Also a method of operating control surfaces of an aircraft wing and an aircraft and aircraft wing with such a system.
A water tank for operation in an aircraft includes a rigid tank shell, and a pressure compensation mechanism to equalize a pressure inside of the rigid tank shell with an environment. The pressure compensation mechanism includes a shutoff member to move between a closed position, a first open position allowing air to enter the rigid tank shell and a second open position allowing air to leave the rigid tank shell.
A system for determining the number of passengers in a vehicle, comprising a plurality of sensors arranged to collect data concerning a cabin of the vehicle, wherein the plurality of sensors comprises at least one mm-wave-radar-sensor, and a computation unit, wherein the computation unit is connected to the plurality of sensors and configured to evaluate the data collected by the plurality of sensors in order to determine the number of passengers within the vehicle. Also provided is the vehicle with the system and a method for determining the number of passengers in the vehicle.
A method for operating an on-board water supply and distribution system of an aircraft for supplying water includes a central water tank, first consumer assemblies with buffer tanks each including a heater to heat up water in the buffer tank to a disinfection temperature, pump having upstream and downstream sides to operate in supply and reverse modes, and high-pressure conduit system. The central water tank connects to the pump's upstream side. The conduit system connects the downstream side with a first consumer assembly. The method includes operating the pump in supply mode where water from the central tank goes to a first consumer assembly to fill a buffer tank, operating a buffer tank heater so water heats to a predetermined disinfection temperature, and operating the pump in reverse mode so heated water passes through a part of the conduit system and the upstream side of the pump.
A cabin monument having a monument body and a transparent film which is connected to the monument body. The transparent film has a large number of light-emitting elements. Further provided is an aircraft having at least one such cabin monument and a control device.
A fluid transport device including a first line connector, second line connector and inner line component that fluidly connects the first line connector to the second line connector via respective first and second coupling ends. In a mounted state, an outer line component of the device is attached to the first line connector and to the second line connector, so the outer line component covers the first and second coupling ends. In a demounted state, the outer line component is detached from the first and second line connector, wherein the outer line component is movable relative to the inner line component to uncover the first coupling end or the second coupling end. A method for assembling and disassembling a fluid transport device is also disclosed.
A rail system for the installation of objects in a cabin of a vehicle having a base rail, an installation rail, and connecting devices for connecting the base rail and the installation rail to one another in a mutually parallel orientation. The base rail has a bottom side, with a securing portion for securing the base rail on a structural component of the vehicle, and a top side. The installation rail has an installation surface on which the objects can be mounted and connected to the installation rail. The rail system is configured to position the installation surface with a predetermined spacing to the top side such that at least one lateral intermediate space is formed between the installation surface and the base rail for the purposes of form-fittingly holding a floor panel.
A wing assembly (5) including: a fixed wing portion (7), a first high-lift device (9), a first connecting assembly (19) which allows the first high-lift device (9) to move between a retracted position and an extended position, a second high-lift device (11), a second connecting assembly (21) which allows the second high-lift device (11) to move between a retracted position and an extended position, a drive unit (23) attached to the fixed wing portion (7), and a drive assembly (25) having a first portion (27) is attached to the drive unit (23) and a second portion (29) attached to the second high-lift device (11), wherein the drive unit (23) moves the second high-lift device (11) via the drive assembly (25) between the retracted position and the extended position.
A system for producing a component or semifinished product with a fibre-reinforced foam core, includes a substrate on which the foam core having a first main surface and an opposite second main surface is to be laid; a sewing device having a needle configured to be moved at least linearly; a fibre supply device for three-dimensional supply of a fibre; and a coating device. The sewing device is configured to position the needle at the first main surface and to pierce the foam core, such that a needle tip penetrates through the first main surface and then through the second main surface. The fibre supply device is configured to position a reinforcing fibre such that the reinforcing fibre is hooked into the needle tip. The coating device is configured to coat a reinforcing fibre hooked into the needle tip with resin immediately before the reinforcing fibre enters the foam core.
B29C 70/08 - Façonnage de matières composites, c. à d. de matières plastiques comprenant des renforcements, des matières de remplissage ou des parties préformées, p.ex. des inserts comprenant uniquement des renforcements, p.ex. matières plastiques auto-renforçantes des renforcements fibreux uniquement comprenant des combinaisons de différentes formes de renforcements fibreux incorporés dans une matrice, formant une ou plusieurs couches, avec ou sans couches non renforcées
B29C 44/56 - Post-traitement d'objets, p.ex. pour changer leur forme
B32B 5/18 - Produits stratifiés caractérisés par l'hétérogénéité ou la structure physique d'une des couches caractérisés par le fait qu'une des couches contient un matériau sous forme de mousse ou essentiellement poreux
28.
A WINDOW MOUNTING STRUCTURE FOR SNAP AND CLICK MOUNTING OF A WINDOW ASSEMBLY OF AN AIRCRAFT
In order to improve installing and maintaining aircraft windows (18), the invention proposes a window mounting structure (24) (24) that has a mounting support interface (38) which is installed on the fuselage (12). The window pane assembly (26) is inserted in the window opening (34) and a mounting frame (46) is pressed onto the mounting support interface (38). The mounting frame (46) may be locked in place with a locking member (59).
An end plate for clamping one or more fuel cells in a fuel cell arrangement, the end plate including one or more integrated storage devices for storing electrical energy. A fuel cell arrangement includes one or more fuel cells and a clamp device for clamping the one or more fuel cells, the clamp device having an end plate including one or more integrated storage device for storing electrical energy, the end plate clamping the one or more fuel cells in the fuel cell arrangement.
H01M 16/00 - Combinaisons structurelles de différents types de générateurs électrochimiques
H01M 8/248 - Moyens pour comprimer les empilements d’éléments à combustible
H01M 8/04007 - Dispositions auxiliaires, p.ex. pour la commande de la pression ou pour la circulation des fluides relatives à l’échange de chaleur
H01M 10/0525 - Batteries du type "rocking chair" ou "fauteuil à bascule", p.ex. batteries à insertion ou intercalation de lithium dans les deux électrodes; Batteries à l'ion lithium
MANUFACTURING METHOD FOR MANUFACTURING A PROFILE RAIL, PROFILE RAIL OBTAINABLE THEREBY, MOUNTING SYSTEM AND VEHICLE EQUIPPED THEREWITH AND USE OF THE PROFILE RAIL
A method for manufacturing a profile rail including a base made of a first material and a top portion to be exposed during use of the profile rail in the floor of a vehicle including a second material that is harder and/or less corrosive as the first material. The method includes the steps of providing the base made of the first material, coating at least the top portion of the base with the second material by a cold spray process, and machining the coating to provide a predefined surface structure of the top portion.
A wing assembly is disclosed having a fixed wing portion, a high-lift device, and a connecting assembly movably connecting the high-lift device to the fixed wing portion, such that the high-lift device is movable between a retracted position and at least one extended position. The connecting assembly includes a first connecting element, which extends from a first end portion, at which the first connecting element is rotatably connected to the fixed wing portion, to a second end portion, and a second connecting element, which extends from a first end portion, at which the second connecting element is rotatably connected to the second end portion of the first connecting element, to a second end portion.
A wing (3) for an aircraft (1) including a main wing (5) and a trailing edge high lift assembly (9) movably arranged at a trailing edge of the main wing (5). The trailing edge high lift assembly (9) includes a flap (11) and a connection assembly (13) movably mounting the flap (11) to the main wing (5). The connection assembly (13) includes an actuator unit (35) moving the flap (11) between a retracted position and at least one extended position. The flap (11) includes a leading edge part (23) and a trailing edge part (27) mounted to the leading edge part (23) pivotable about a pivot axis (31).
A coupling kit-of-parts is provided for mounting an interior substructure to a primary structure of an aircraft. The kit includes a locking member and a mounting member. When the locking member is inserted into the mounting member, a first member part and a second member part are pushed radially outward to engage the primary structure in a form-fitting manner. When the locking member is removed, the first and second member parts are urged radially inward thereby disengaging from the primary structure.
F16B 13/06 - Chevilles ou autres dispositifs fixés à des parois ou autres emplacements par insertion dans des trous préparés à cet effet avec parties s'agrippant dans le trou ou derrière la paroi après insertion et combinées avec un manchon extensible
B64F 5/10 - Fabrication ou assemblage d’aéronefs, p.ex. gabarits à cet effet
34.
REFERENTIAL POSITIONING DEVICE INTENDED TO POSITION RELATIVE TO EACH OTHER AT LEAST ONE CABIN FLOOR GRID AND ONE SIDE SHELL OF AN AIRCRAFT IN ORDER TO ASSEMBLE A FUSELAGE BARREL OF THE AIRCRAFT
A referential positioning device configured to position relative to each other at least one cabin floor grid and one side shell of an aircraft in order to assemble a fuselage barrel of the aircraft is disclosed having at least one fixing support for fixing the referential positioning device to the top of an alignment post of an assembly platform, and a partially spherical support having a spherical surface (S) intended to receive the V-shaped surface of an end of an arm of a transport system for a cabin floor grid of an aircraft. The referential positioning device makes it possible to arrange the cabin floor grid precisely on the assembly platform with respect to the other elements of the fuselage barrel.
A wing for an aircraft includes a leading edge, a trailing edge, an upper skin extending between the leading edge and the trailing edge, a lower skin extending between the leading edge and the trailing edge, at least one spar extending between the upper skin and the lower skin in a spanwise direction to create a wing box with the upper skin and the lower skin, and at least one droop nose at the leading edge, wherein the at least one droop nose is coupled with a forward end of a hinge arm that extends in a chordwise direction, and wherein a rearward end of the hinge arm is swivably supported directly at or in the wing box.
B64C 3/48 - Variation de la courbure par parties semi-mobiles des structures d'ailes
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
36.
DEVICE FOR LATCHING A DOOR OF AN OXYGEN MASK CONTAINER IN AN AIRCRAFT CABIN
A device for latching a door of an oxygen mask container in an aircraft cabin includes a door for an oxygen mask container having an inner side, outer side and hinge, a first latching device attached to the inner side, and a second latching device movable relative to the first latching device to selectively engage or disengage the second latching device. A retaining element is attachable to a structural part inside the oxygen mask container. A test control device on the inner side of the door includes a movable hook element and can move the hook element to a first or second position. The hook element can engage the retaining element in the first position to restrict an opening degree of the door. The hook element is placed in the second position such that when the door is opened, the hook element is moved past the retaining element.
E05B 85/00 - SERRURES; LEURS ACCESSOIRES; MENOTTES - Détails de serrures de véhicule non prévus dans les groupes
B64D 11/00 - Arrangements pour passagers ou équipage; Installations de postes de pilotage non prévues ailleurs
E05B 81/06 - Serrures de véhicule actionnées par une force motrice caractérisées par le type d´actionneur utilisé électrique par moteurs rotatifs
E05B 81/08 - Serrures de véhicule actionnées par une force motrice caractérisées par le type d´actionneur utilisé électrique par électroaimants ou solénoïdes
E05B 81/18 - Serrures de véhicule actionnées par une force motrice caractérisées par la fonction ou les fins des éléments d’actionnement pour déplacer des pênes
E05B 81/70 - Contrôle ou détection, p.ex. par des interrupteurs ou des détecteurs de la position du battant
E05B 83/00 - Serrures de véhicule spécialement adaptées aux types particuliers de battant ou de véhicule
37.
METHOD FOR MANUFACTURING A COMPLEX COMPOSITE PART USING A SINGLE-USE INFLATABLE MANDREL
A mandrel is 3D-printed from a thermoplastic material that exhibits a glass transition. The mandrel has a mandrel wall made from the thermoplastic material and a cavity. The mandrel is coated with an elastomer coat and a fiber material is arranged on the elastomer coat. A composite part is formed from the fiber material by inserting the mandrel into a mold, pressurizing the mandrel, and heating the mold to a mold temperature greater than the glass transition temperature without melting the mandrel wall. The mandrel expands and presses the fiber material against the mold. The composite part is cured by increasing the mold temperature and simultaneously melting the mandrel wall.
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]
B64F 5/10 - Fabrication ou assemblage d’aéronefs, p.ex. gabarits à cet effet
B29C 33/48 - Moules ou noyaux; Leurs détails ou accessoires comportant des moyens ou conçus spécialement pour faciliter le démoulage d'objets, p.ex. des objets à contre-dépouille avec des moyens rétractables ou démontables
B29C 33/52 - Moules ou noyaux; Leurs détails ou accessoires comportant des moyens ou conçus spécialement pour faciliter le démoulage d'objets, p.ex. des objets à contre-dépouille solubles ou fusibles
A wing for an aircraft includes a leading edge as a first chordwise edge, a trailing edge as a second chordwise edge, an upper skin extending between the leading edge and the trailing edge, a lower skin extending between the leading edge and the trailing edge, at least one spar extending between the upper skin and the lower skin in a spanwise direction to create wing box with the upper skin and the lower skin, and at least one of a fluid line, an electrical line, and a mechanical power transfer device attached inside or reaching into the wing box at least partially.
Methods for fastening two fiber composite parts to each other with a fastener that includes electroactive polymer material. The parts have an opening within an inner circumferential surface. Fibers protrude from the inner circumferential surface into the opening and interlock with chains of micrograins of the electroactive polymer material. The fastener may switch between an activated state and a deactivated state and in the deactivated state, the fastener engages the exposed fibers.
A coupling for a hydrogen pipe for coupling multi-wall pipe sections which is equipped with an inner seal and an outer seal and a pressing device that presses the pipe sections together. The hydrogen pipe coupling arrangement comprises at least one spring element configured to apply a pre-pressing force onto the inner seal in addition to a pressing force of the pressing device.
A method for detecting aircraft surface portion characteristics including applying a marking sticker with grid markings adjacent to the aircraft surface portion, simultaneously optically detecting one region of the marking sticker and one region of the surface portion via an optical detection device, removing the optical detection device, hand guiding a sensing device to a predetermined position relative to the marking sticker within the surface portion and detecting a material characteristic there, correlating the detected material characteristic with the respective position in a data set, and generating and storing a damage map in which an optically detected structure of the surface portion is combined with the additional material characteristic at the one position, wherein guiding the sensing device includes projecting a laser line outwardly from the sensing device and moving the sensing device to align the laser line with at the grid marking.
G01N 29/22 - 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 - Détails
A compartment for a cabin in a vehicle includes a compartment enclosure assembly defining an outer boundary of the compartment and having a receiving space, a stop body supported on or in the compartment enclosure assembly, and a locking device. The receiving space is accessible from a front of the compartment enclosure assembly, wherein the stop body is pivotally mounted on or in the compartment enclosure assembly about a pivot axis or slidably along an axis between a retracted position, in which the stop body does not project from the front, and an extended position, in which the stop body projects from the front to provide an end stop for a door of the compartment or for a door of an insert to be inserted into the receiving space, wherein the locking device is configured to selectively lock and unlock the stop body in its retracted position.
A honeycomb structure including a first external side, a second external side, and an anti-friction agent buffer for receiving an anti-friction agent. An opening to an anti-friction agent inlet and an opening to an air outlet are present on the first external side. This honeycomb structure may be useful in an aircraft as part of a belly-landing system for the aircraft.
A pump arrangement for providing a saturated or subcooled liquid includes a tank for saturated liquid, a heat exchanger for cooling the saturated liquid, a pump, an expansion valve, and an output for feeding saturated or subcooled liquid to a consumer. A tank outlet is in fluid communication with a liquid inlet of the heat exchanger, such that saturated liquid stored inside the tank can flow into the heat exchanger designed to sub-cool the saturated liquid. A liquid outlet of the heat exchanger is in fluid communication with a pump inlet. The expansion valve outlet is in fluid communication with a coolant inlet of the heat exchanger. An expansion valve inlet is arranged for receiving and expanding a fraction of liquid flowing through the pump arrangement and routing it into the coolant input to at least partially evaporate and receive evaporation enthalpy of the liquid to be subcooled.
F04B 15/08 - Pompes adaptées pour travailler avec des fluides particuliers, p.ex. grâce à l'emploi de matériaux spécifiés pour la pompe elle-même ou certaines de ses parties avec des liquides près de leur point d'ébullition, p.ex. à une pression anormalement basse les liquides ayant une température d'ébullition peu élevée
F02M 59/38 - Pompes caractérisées par leur adaptation à des utilisations ou conditions particulières
H01M 8/04007 - Dispositions auxiliaires, p.ex. pour la commande de la pression ou pour la circulation des fluides relatives à l’échange de chaleur
45.
VARIABLE FAIRING FOR A HYDROGEN DUCT SYSTEM INSTALLATION AND USES OF THE SAME
A variable fairing for covering a hydrogen duct system installation on the outside of an aircraft part, wherein the fairing comprises at least one fairing body to be mounted on the aircraft part, an air inlet and an air outlet and at least one movable closure mechanism configured to open and close a top portion of the fairing.
A semi-active noise control system includes a layer configured to be part of an interior panel of an aircraft The layer includes conductive tracks, a driver arrangement, tuned mass dampers, and sensors. Each tuned mass damper has an eigenfrequency that depends on a control signal applied to the tuned mass damper and is connected to the driver arrangement via a conductive track and configured to receive control signals from the driver arrangement. Each sensor is connected to the driver arrangement via a conductive track and is configured to sense vibrations and/or acoustic sounds and send measurement signals to the driver arrangement. The driver arrangement is configured to analyze the measurement signals and to generate and send control signals to the tuned mass dampers such that the eigenfrequency of the tuned mass dampers is matched with the frequency of the vibrations and/or acoustic sounds sensed by the sensors.
A reinforcing element for a structural profile, in particular for a round, oval or elliptical structural tube, includes a composite structure, which has a hollow-cylindrical, helically wound mesh of fiber strands which form an inner shell surface configured to receive the structural profile, wherein the fiber strands are respectively embedded in a matrix material, which has an electroactive polymer which can be stretched along a longitudinal extent of the fiber strands by application of an electrical voltage, such that the composite structure can be expanded by application of the electrical voltage to introduce the structural profile into the composite structure and can be shrunk by switching off the electrical voltage to fix the structural profile on the shell surface in the composite structure.
B29C 63/42 - Garnissage ou gainage, c. à d. application de couches ou de gainages préformés en matière plastique; Appareils à cet effet par libération de contraintes internes en utilisant des couches ou des gainages tubulaires
B29C 63/00 - Garnissage ou gainage, c. à d. application de couches ou de gainages préformés en matière plastique; Appareils à cet effet
F16L 3/12 - 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 comportant un élément entourant pratiquement le tuyau, le câble ou le conduit de protection
48.
HYDROGEN ACCUMULATION CONTROL SYSTEM FOR MONITORING AND CONTROLLING LEAKED HYDROGEN WITHIN AN INTERIOR SPACE
A hydrogen accumulation control system for monitoring and controlling leaked hydrogen within an interior space, in particular of an aircraft, includes a hydrogen detection system installed within the interior space to detect the presence of gaseous hydrogen in the interior space and to provide occurrence data on the detected hydrogen within the interior space, a system control configured to assess the occurrence data and to determine and initiate a remedial procedure for reduction of the detected hydrogen within the interior space, and a venting system configured to vent the interior space from the detected hydrogen according to the remedial procedure.
B64D 13/06 - Aménagements ou adaptations des appareils de conditionnement d'air pour équipages d'aéronefs, passagers ou pour emplacement réservé au fret l'air étant climatisé
B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
B01D 53/22 - SÉPARATION Épuration chimique ou biologique des gaz résiduaires, p.ex. gaz d'échappement des moteurs à combustion, fumées, vapeurs, gaz de combustion ou aérosols par diffusion
A mounting member configured to support a cabin component to be mounted to a mounting rail. The rail mounting arrangement comprises a disengagement locking mechanism that prevents a removal of the mounting member along a transversal direction of the mounting rail, while still allowing movement along the longitudinal direction. The rail mounting arrangement includes a securing mechanism that is configured to secure the mounting member at the desired location along the mounting rail.
A sealing device for covering an aperture in a wing part of an aircraft. The sealing device has a cover plate covering at least a part of the aperture and having an outer surface delimited by a cover plate edge, and at least one holding device coupled with the cover plate. The at least one holding device having a resilient element, the at least one holding device resiliently holds the cover plate in a distance to an actuation element. The distance is variable in a first direction substantially perpendicular to the outer surface. The at least one holding device holds the cover plate in a substantially fixed spatial alignment in a second direction perpendicular to the first direction. The resilient element urges the cover plate towards the actuation element in a mounted state of the sealing device.
A panel for covering a part of a structure in an interior space of an aircraft is disclosed including a main panel section having an interior side and an exterior side, and at least one attachment device coupled with the exterior side. The main panel section is exclusively made from a single thermoplastic material, and the at least one attachment device is adapted for attaching the panel to the respective interior structure.
A bipolar plate for use in a fuel cell device, the bipolar plate including an integrated ply, the ply including one or more electrically conductive fibers and being configured and electrically connectable to a power supply such that the one or more fibers are heated when power is supplied to the ply.
A method for producing an armored wall for an aircraft by determining an available thickness of the wall, an allowable areal mass of the wall, and an available space for a wall deformation due to ballistic impact. The method includes retrieving a parameterization of a plurality of armoring materials, which includes a parameter for each of a plurality of material characteristics for each of the plurality of armoring materials. The method also includes comparing the available wall thickness, the allowable areal mass, and the available deformation space with a corresponding parameter of the parameterization, selecting one armoring material for the wall from the plurality of armoring materials based on a result of comparing, and manufacturing a wall by supplementing the selected armoring material to a basic wall structure.
An aircraft cabin dismantling and recycling system including: a device (10) for transferring aircraft cabin parts to secondary utilization is provided that includes a data input (12), a data processor (14) and an output interface (16). The data input provides cabin base types from a database and initial equipment installation states of the aircraft cabin from an installation state database. The data processor is configured to identify a cabin base type for a current part of the aircraft cabin; assign an initial equipment installation state of the aircraft cabin; estimate changes of the current part and determine a current parameter; identify implementable transferring options for the current part of the aircraft cabin from a database of transferring options based on the current parameter, and select one of the identified transferring options.
A support arrangement for a leading-edge high lift device comprising a support arm for movably supporting the leading-edge high lift device on a wing structure. In order to accommodate the supply of the leading-edge high lift device with a fluid such as an anti-ice fluid, for example pressurized hot air, the support arm is configured as a fluid conduit for feeding fluid to and/or from the leading-edge high lift device. The leading-edge high lift device may be configured as a droop nose device.
Leakage detection for pressurized fuel tanks. To provide facilitated leakage detection, a leakage detection device for pressurized fuel tanks for storing a pressurized fuel includes a fuel-sensing tracer and a light-wave conducting component. The fuel sensing tracer is configured to alter its optical properties in the presence of a predetermined fuel. The light-wave conducting component is in optical contact with the fuel sensing tracer. Light travelling within the light-wave conducting component is modifiable by altered optical properties of the fuel sensing tracer such that modified light is indicative of the presence of fuel at the location of the fuel sensing tracer.
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 3/22 - 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 en utilisant des révélateurs particuliers, p.ex. teinture, produits fluorescents, produits radioactifs pour soupapes
B64D 37/32 - Mesures de sécurité non prévues ailleurs, p.ex. contre les explosions
57.
SEALING DEVICE FOR COVERING AN APERTURE IN A WING PART
A sealing device for covering an aperture in a wing part of an aircraft is disclosed having an interface section for fixedly mounting the sealing device to a surface of the wing part adjacent the aperture, a connecting section, and a cover section for covering at least a part of the aperture. The connecting section is arranged between the interface section and the cover section and connects the interface section and the cover section. The connecting section is adapted to resiliently hold the cover section in a predetermined orientation relative to the interface section to cover at least a part of the aperture. The cover section comprises a contact portion for contacting a surface of an actuation element that protrudes through the aperture.
A load introduction system is disclosed including an aerodynamic structure component having an upper skin section and a lower skin section, an attachment unit and a load introduction unit configured to couple the attachment unit to the aerodynamic structure component. The load introduction unit includes a longitudinal connection element with its first end positioned at the upper skin section. The longitudinal connection element extends through the lower skin section such that its second end is positioned outside of the aerodynamic structure component. The first end is anchored to the upper skin section and the second end is anchored to the attachment unit such that the longitudinal connection element forces the attachment unit against the lower skin section.
A actuator arrangement is disclosed in which the high-lift device support that supports and guides movement of a high-lift device, such as a flap, is in axial alignment with a control actuator assembly that controls one or more control surfaces. This allows a single support fairing to be sufficient for covering both the track member and the control actuator assembly and allowing for reduced drag and weight.
A pipe for heating a cryogenic liquefied gas, the pipe having a peripheral wall including a ply of one or more electrically conductive carbon fibers, the ply being configured and electrically connectable to a power supply such that the one or more carbon fibers are heated when power is supplied to the ply.
F16L 53/37 - Chauffage par résistance ohmique le courant de chauffage circulant directement à travers le tuyau devant être chauffé
F16L 9/10 - Tuyaux rigides en verre ou en céramique, p.ex. en argile, en poterie, en porcelaine
H05B 3/14 - Eléments 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
H05B 1/02 - Dispositions de commutation automatique spécialement adaptées aux appareils de chauffage
61.
METHOD FOR PNEUMATICALLY DRAINING A WATER SUPPLY SYSTEM
A method for draining a water supply system onboard an aircraft which supplies water from a central water tank to consumers. Water is supplied by a supply pump from the central water tank through supply lines of a conduit system to consumers. Each consumer is associated with a supply valve for drawing water from the conduit system. The supply lines have a maximum internal diameter of 8 mm or less. The method includes closing the supply valves of all consumers, subjecting the supply lines of the conduit system at the at the supply pump to a draining pressure and sequentially opening the supply valves of all consumers for removing water from the supply lines of the conduit system. A corresponding water supply system and an aircraft are disclosed.
A method for draining a local water distribution system including a buffer, supply lines connecting one or more consumers to the buffer and consumer valves associated with the one or more consumers. The buffer is configured for locally storing water from an aircraft water supply system to be distributed to the one or more consumers. Water from the buffer can be dispensed through a consumer of the one or more consumers by opening the consumer valve associated with the respective consumer. Water is drained from the supply lines by opening the consumer valves. Water is drained from the buffer through one of the supply lines and the consumer valves or through a drain valve connecting the buffer to a wastewater system of an aircraft. A corresponding local water distribution system and an aircraft are disclosed.
A luggage compartment, for use in a vehicle, having a housing with an inner volume defining a storage space of the luggage compartment and a flap which is attached to the housing with at least one fastening device. The fastening device has a first portion attached to the flap and a second portion, wherein the second portion of the fastening device is releasably coupled to the first portion of the fastening device and attached to an outer surface of a top wall of the housing. Also a cabin component assembly with the luggage compartment and a ceiling panel arranged adjacent to the top wall of the housing of the luggage compartment and an aircraft with the cabin component assembly.
A component for an aircraft includes at least one connection interface, wherein the connection interface is configured to simultaneously establish an electrical connection and a mechanical connection. An electrical system for an aircraft and a method for connecting components for an aircraft are disclosed.
An expansion tank system for a liquid cooling system includes a first chamber for receiving a coolant, a second chamber for pressurized gas, a first gas conveying device for conveying gas from the first to the second chamber, a second gas conveying device for conveying gas from the second to the first chamber, a first pressure sensor in fluid communication with the first chamber, and a control unit connected to the first gas conveying device, the second gas conveying device and the first pressure sensor for controlling the second conveying device to selectively convey gas from the second to the first chamber if a pressure measured through the first pressure sensor is below a predefined first threshold value, and for controlling the first conveying device to convey gas from the first to the second chamber if a pressure measured through the first pressure sensor is above a second threshold value.
A fuel cell system comprises a fuel cell unit in a housing and comprising an anode part and a cathode part, a hydrogen source for supplying hydrogen to the fuel cell unit, an air supply unit for supplying air to the fuel cell unit, and a catalytic converter for catalytically converting oxygen and hydrogen to generate an inert gas mixture and supplying it to the interior of the housing. The catalytic converter comprises a cathode exhaust gas intake for receiving a cathode exhaust gas from the cathode part of the fuel cell unit. In a method for generating inert gas for a fuel cell system, a purge gas is supplied from the anode part of the fuel cell unit, and/or fresh hydrogen is supplied from a hydrogen supply unit of the fuel cell unit to the catalytic converter, to generate the inert gas mixture.
H01M 8/0662 - Traitement des réactifs gazeux ou des résidus gazeux, p.ex. nettoyage
H01M 8/04223 - Dispositions auxiliaires, p.ex. pour la commande de la pression ou pour la circulation des fluides pendant le démarrage ou l’arrêt; Dépolarisation ou activation, p.ex. purge; Moyens pour court-circuiter les éléments à combustible défectueux
H01M 8/04089 - Dispositions pour la commande des paramètres des réactifs, p.ex. de la pression ou de la concentration des réactifs gazeux
A bipolar plate for a fuel cell stack comprises a first main boundary surface and a second main boundary surface, arranged parallel and at a distance to each other and define an interior space. A plurality of lateral delimiting surfaces extend between outer edges of the first and second main boundary surfaces to enclose the interior space. At least one of the lateral delimiting surfaces comprises a plurality of lateral openings and at least one of the main boundary surfaces comprises a plurality of axial openings. Internal distribution channels are arranged inside the interior space in a distance to the first main boundary surface and the second main boundary surface, and lateral openings are in fluid connection with the axial openings through at least a part of the internal distribution channels.
H01M 8/0258 - Collecteurs; Séparateurs, p.ex. séparateurs bipolaires; Interconnecteurs caractérisés par la configuration des canaux, p.ex. par le champ d’écoulement du réactif ou du réfrigérant
68.
Fluid Transport Device And Method For Manufacturing A Fluid Transport Device
University of Ioannina-Special Account for Research Funds (Grèce)
Inventeur(s)
Friedberger, Alois
Krakowski, Dariusz
Paipetis, Alkiviadis S.
Karalis, George
Abrégé
A fluid transport device includes a conduit unit having a wall for separating an inside from an outside of the conduit unit. The device also includes an energy supply unit coupled to the conduit unit and configured to provide electrical energy based on a temperature gradient between the inside and the outside of the conduit unit. The device also includes a monitoring unit configured to monitor a state of the conduit unit and to generate data representative for the state of the conduit unit. The energy supply unit supplies the electrical energy to the monitoring unit, thereby enabling the monitoring unit to monitor the state of the conduit unit. A method for manufacturing a fluid transport device is also described.
G01M 3/40 - Examen de l'étanchéité des structures ou ouvrages vis-à-vis d'un fluide par utilisation de moyens électriques, p.ex. par observation de décharges électriques
A dynamically adjustable surveillance system including: a surveillance camera having a field of vision encompassing an object to be monitored and generating an image stream of the field of vision, a surveillance camera controller configured to control operation parameters of the surveillance camera, the operation parameters indicating operation conditions of the camera, a surveillance controller coupled to the surveillance camera controller, and a sensing device coupled to the surveillance controller and configured to output an object state signal to the surveillance controller indicating a sensed state of the object to be monitored. The surveillance controller is configured to output a control signal to the surveillance camera controller to change some of the operation parameters of the surveillance camera if the object state signal received from the sensing device indicates a sensed state of the object to have changed.
H04N 7/18 - Systèmes de télévision en circuit fermé [CCTV], c. à d. systèmes dans lesquels le signal vidéo n'est pas diffusé
H04N 23/66 - Commande à distance de caméras ou de parties de caméra, p. ex. par des dispositifs de commande à distance
G06V 20/17 - Scènes terrestres transmises par des avions ou des drones
G06V 20/52 - Activités de surveillance ou de suivi, p.ex. pour la reconnaissance d’objets suspects
H04N 23/667 - Changement de mode de fonctionnement de la caméra, p. ex. entre les modes photo et vidéo, sport et normal ou haute et basse résolutions
H04N 23/69 - Commande de moyens permettant de modifier l'angle du champ de vision, p. ex. des objectifs de zoom optique ou un zoom électronique
70.
ARRANGEMENT INCLUDING A FIBER-REINFORCED COMPOSITE COMPONENT OR ASSEMBLY, AIRCRAFT OR SPACECRAFT, METHOD OF PRODUCING AN ARRANGEMENT, AS WELL AS METHOD OF MONITORING STRUCTURAL INTEGRITY
An arrangement includes a fiber-reinforced composite component or assembly and a monitoring device. The composite component or assembly includes at least first and second reinforcing fiber formation sections stitched to each other using a yarn to connect the fiber formation sections along a seam, the yarn being electrically conductive along a length thereof. The monitoring device is configured and coupled to the yarn so as to be capable of sending an electrical input signal along at least a section of the yarn that forms the seam or part thereof and receiving a response signal on the yarn. Furthermore, an aircraft or spacecraft is provided including at least one arrangement of this type, as well as a method of producing an arrangement including a fiber-reinforced composite component or composite assembly, and a method of monitoring the structural integrity of a fiber-reinforced composite component or assembly.
A filling level monitoring device for monitoring a filling level of a fluid in a container includes exciter(s), sensor(s), a signal source connected to the exciter(s), a processor, at least one spatial orientation and acceleration sensor, and a filling level indicator. The device uses the signal source and the exciter(s) to couple vibrational loads having multiple frequency components into the container. Sensors measure vibrations in the container after the exciters transmit the vibrational loads into the container. The processor performs spectral analysis of the input signal and of vibration signals from the sensors, comparing these respective spectral functions to extract resonance frequencies of the container, which are based on the spatial orientation of the container. The filling level indicator calculates a current filling level of the container from the extracted resonance frequencies and a spatial orientation signal from a spatial orientation sensor by correlating the collected data with reference data.
A wing for an aircraft is disclosed having a fixed wing, a foldable wing tip portion mounted to the fixed wing via a hinge rotatable about a hinge axis between an extended position and a folded position, and an actuation mechanism for moving the foldable wing tip portion. The actuation mechanism includes a drive arm mounted to the fixed wing in a manner rotatably driven about a drive axis, and the drive arm is configured to effect movement of the foldable wing tip portion between the extended position and the folded position upon rotation of the drive arm about the drive axis.
A filling level monitoring device (100) for monitoring a filling level (210) of a fluid in a container (200) includes exciter(s) (10), sensor(s) (20), a signal source (30) connected to the exciter(s) (10), a processor (40), at least one spatial orientation and acceleration sensor (60), and a filling level indicator (50). The device (100) uses the signal source (30) and the exciter(s) (10) to couple vibrational loads having multiple frequency components into the container (200). Sensors (20) measure vibrations in the container (200) after the exciters (10) transmit the vibrational loads into the container (200). The processor (40) performs spectral analysis of the input signal (31) and of vibration signals (21) from the sensors (20), comparing these respective spectral functions to extract resonance frequencies of the container (200), which are based on the spatial orientation of the container (200). The filling level indicator (50) calculates a current filling level (210) of the container (200) from the extracted resonance frequencies and a spatial orientation signal from a spatial orientation sensor (60) by correlating the collected data with reference data.
A connection system includes at least a first part and at least a second part, both comprising a connection surface and being configured to be connected to each other. A plurality of engagement elements is protruding from the connection surface of the first part and from the connection surface of the second part. For connecting different components, the parts are positioned such that their connection surfaces are facing each other. A ductile material is positioned between the connection surfaces of the parts to be connected to each other. The parts are pressed together, wherein the engagement elements are pressed into the ductile material at required positions, thereby compensating position deviations.
A fairing attachment system for a wing of an aircraft includes a high lift support structure configured to movably support a high-lift airfoil element of a wing of an aircraft relative to the wing. The system includes a fairing device extending in a lengthwise direction, configured to provide an aerodynamic housing of the high lift support structure when attached to a surface of the wing, and an adjustable attachment element configured to attach the fairing device to the high lift support structure. The adjustable attachment element is longitudinally extending and adjustable in length to compensate for tolerances of the high lift support structure relative to the wing during assembly. An aircraft wing includes the fairing attachment system. The fairing attachment system is used in a method for mounting a fairing device to a wing of an aircraft.
A multimedia distribution network, useful on board a passenger aircraft, includes a first network node configured as a head controller, a plurality of second network nodes configured as intermediate controllers connected to the first network node, and a plurality of third network nodes configured as end device controllers, each connected to one of the second network nodes. The head controller is configured to transmit a multicast stream of multimedia control signal packets to control the end device controllers to the intermediate controllers. The intermediate controllers are configured to periodically transmit unicast delay queries to the head controller, to process the received multimedia control signal packets to the end device controllers and to distribute processed multimedia control signal packets with a controllable delay based on the content of unicast delay indicator signals sent by the head controller to the intermediate controllers in response to the unicast delay queries.
H04L 65/611 - Diffusion en flux de paquets multimédias pour la prise en charge des services de diffusion par flux unidirectionnel, p.ex. radio sur Internet pour la multidiffusion ou la diffusion
H04L 67/12 - Protocoles spécialement adaptés aux environnements propriétaires ou de mise en réseau pour un usage spécial, p.ex. les réseaux médicaux, les réseaux de capteurs, les réseaux dans les véhicules ou les réseaux de mesure à distance
A wing for an aircraft has a main wing and a trailing edge high lift assembly which has a flap and a connection assembly movably mounting the flap to the main wing. The connection assembly has a first actuator unit for moving the flap between the retracted position and at least one extended position. The flap has a leading edge part and a trailing edge part pivotably mounted to the leading edge. The flap has a second actuator unit for moving the trailing edge part relative to the leading edge part within an operating range between an upper operating position and a lower operating position.
An aircraft fuselage is configured to receive two tanks designed to contain liquid hydrogen. The fuselage includes a first section for a cockpit, a second section for a passenger cabin and a third section (T3) distinct from the first section (T1) and from the second section (T2). The third section (T3) includes two housings each to house a tank. The two housings are arranged symmetrically with respect to a vertical plane of symmetry (P1). This arrangement of the tanks in a section distinct from the other sections allows them to be located as close as possible to the motors that they have to supply.
A fire detection, localization and monitoring system for a vehicle compartment, in particular of an aircraft, includes a thermal imaging camera configured to provide thermal monitoring data on heat sources within a monitored area of the vehicle compartment; an optical camera configured to provide visual monitoring data of the monitored area; and a system control configured to analyze the thermal monitoring data and to determine temperature hot spots indicating a potential fire within the monitored area based on the analyzed thermal monitoring data. The system control is further configured to provide a visual indication of determined temperature hot spots within the visual monitoring data.
A lavatory door system for a vehicle, in particular an aircraft, with a lavatory door; a pneumatic actuator configured to open and close the lavatory door based on a differential pressure, wherein the pneumatic actuator is coupled to a vacuum toilet system of the vehicle to generate the differential pressure; and an operating interface configured to receive a user control operation and to selectively release the differential pressure from the vacuum toilet system for operation of the pneumatic actuator based on the received user control operation.
E05F 15/51 - Mécanismes pour battants mus par une force motrice utilisant des actionneurs à pression de fluide pour battants repliables
E05B 81/78 - Détection du maniement de la poignée; Détection d’un utilisateur s'approchant d'une poignée; Actions de commutation électrique effectuées par les poignées en tant que partie d’un verrouillage ou déverrouillage mains libres
E05B 83/00 - Serrures de véhicule spécialement adaptées aux types particuliers de battant ou de véhicule
E05F 15/73 - Mécanismes pour battants mus par une force motrice avec déclenchement automatique sensible au déplacement ou à la présence de personnes ou d’objets
A method of performing a configuration procedure for first and second tire pressure monitoring devices. The method includes loading the first tire pressure monitoring device with first configuration data, and subsequently transmitting, from the first tire pressure monitoring device, a first configuration data signal which encodes the first configuration data. The method includes subsequently loading the second tire pressure monitoring device with second configuration data, and subsequently ending the configuration procedure without transmitting a second configuration data signal which encodes the second configuration data.
A method of configuring a network of tire monitoring devices using an untrusted device is provided. An untrusted device transmits first configuration data to a first tire monitoring device, and then receives a first input verifying that the first configuration data has been loaded to the first tire monitoring device and matches expected first configuration data. The untrusted device transmits second configuration data to a second tire monitoring device, and receives a second input verifying that the second configuration data has been loaded to the second tire monitoring device and matches expected second configuration data. The untrusted device transmits a command initializing generation of a cryptographic parameter by the first tire monitoring device, and causes the cryptographic parameter to be exchanged with the second tire monitoring device such that secure future communication is established between the first and second tire monitoring devices.
B60C 23/04 - Dispositifs avertisseurs actionnés par la pression du pneumatique montés sur la roue ou le pneumatique
H04L 67/12 - Protocoles spécialement adaptés aux environnements propriétaires ou de mise en réseau pour un usage spécial, p.ex. les réseaux médicaux, les réseaux de capteurs, les réseaux dans les véhicules ou les réseaux de mesure à distance
A method for temporarily closing openings in an aircraft part during a manufacturing process by providing a first part that has a first opening and positioning a temporary closure member inside that first opening. The temporary closure member has an RFID tag that has stored on it a unique identification. At a later stage in the aircraft manufacturing process, a scanning device is used to scan for the RFID tag based on the identification. The temporary closure member is removed from the first opening and subsequently replaced by a permanent member.
G05B 19/418 - Commande totale d'usine, c.à d. commande centralisée de plusieurs machines, p.ex. commande numérique directe ou distribuée (DNC), systèmes d'ateliers flexibles (FMS), systèmes de fabrication intégrés (IMS), productique (CIM)
G06K 19/077 - Supports d'enregistrement avec des marques conductrices, des circuits imprimés ou des éléments de circuit à semi-conducteurs, p.ex. cartes d'identité ou cartes de crédit avec des puces à circuit intégré - Détails de structure, p.ex. montage de circuits dans le support
84.
FIRE DETECTION SYSTEM AND METHOD FOR MONITORING AN AIRCRAFT COMPARTMENT AND SUPPORTING A COCKPIT CREW WITH TAKING REMEDIAL ACTION IN CASE OF A FIRE ALARM
A fire detection system for monitoring an aircraft compartment and supporting a cockpit crew with taking remedial action in case of a fire alarm with a fire detector within the compartment; a monitoring system within the compartment to provide live monitoring data on cargo; a cargo tracking system configured to provide cargo data of the cargo; an aircraft control system configured to provide aircraft status data; a system control configured to assess a fire warning data, the cargo data and the aircraft status data and to provide a recommended remedial procedure based on the assessment in case the fire detector raises a fire alarm at least in an affected portion of the compartment; and a display device configured to display the live monitoring data and the recommended remedial procedure to the cockpit crew in case of a fire alarm
A method for generating improved machine control data. Event series is generated from input machine control data that is linked with a mesh data that is also generated from the input machine control data. Thus, an activation time (t_act) is determined which indicates the point in time at which the additive manufacturing machine prints a portion of the object that is represented by that mesh element. A full 3D-thermal simulation is run on the mesh elements. Each time the element temperature (T_el) exceeds a predetermined threshold, the activation time (t_act) is increased by a predetermined time increment and the event series is updated. Finally the event series is converted back to output machine control data.
A wing for an aircraft is disclosed including a main wing and a trailing edge high lift assembly movably arranged at a trailing edge of the main wing, the trailing edge high lift assembly having a flap and a connection assembly movably mounting the flap to the main wing, such that the flap is movable between a retracted position and at least one extended position. The connection assembly includes an actuator unit for moving the flap between the retracted position and the at least one extended position. The flap includes a leading edge part and a trailing edge part mounted to the leading edge part in a manner pivotable about a pivot axis.
A method for determining flow properties of a fluid flowing along a surface by: modulating the current through a heating element of a thermal flow sensor located on the surface with at least one modulation frequency, thereby emitting a thermal wave into the fluid flowing along the surface having a penetration depth inversely proportional to the modulation frequency; measuring an amplitude of a voltage across the heating element at the third harmonic of the at least one modulation frequency, the voltage depending on the thermal conductivity and the volumetric heat capacity of the fluid flowing along the surface; determining a flow velocity at the penetration depth from the attenuation value of the determined amplitude of the voltage; and estimating whether the flow at the penetration depth is laminar or turbulent on the basis of the determined flow velocity. Also, a system and an aircraft with such a system.
G01P 5/12 - Mesure de la vitesse des fluides, p.ex. d'un courant atmosphérique; Mesure de la vitesse de corps, p.ex. navires, aéronefs, par rapport à des fluides en mesurant des variables thermiques en utilisant la variation de la résistance d'un conducteur chauffé
88.
EVACUATION SUPPORT SYSTEM, METHOD FOR SUPPORTING AN EVACUA-TION PROCEDURE, AND AIRCRAFT
An evacuation support system comprising a signaling device configured to produce signals guiding evacuees (E) away from overcrowded exit points and towards less crowded exit points. The signaling device may include at least one visual signal and/or at least one audio signal. Also a method for supporting an evacuation procedure and an aircraft having the evacuation support system.
A method for bonding two fiber composite components with each other to form a fiber composite structure includes integrating conductive fibers underneath a bonding surface of at least one of the two fiber composite components, each conductive fiber comprising a carbon fiber coated with an electrically insulating coating, the conductive fibers running along the bonding surface and protruding at least at their ends from the respective fiber composite component; arranging the two fiber composite components against each other at their respective bonding surfaces; passing an electric current through the conductive fibers by electrically contacting the conductive fibers at their protruding ends so that the respective fiber composite component is heated at the bonding surface to a curing temperature; and joining the two fiber composite components with each other at their bonding surfaces via secondary bonding, co-bonding and/or co-curing at the curing temperature, thereby forming the fiber composite structure.
B29C 65/34 - Assemblage d'éléments préformés; Appareils à cet effet par chauffage, avec ou sans pressage avec des éléments chauffés qui restent dans le joint, p.ex. un "élément de soudage perdu"
B29C 65/00 - Assemblage d'éléments préformés; Appareils à cet effet
B29C 65/48 - Assemblage d'éléments préformés; Appareils à cet effet en utilisant des adhésifs
90.
APPARATUS FOR THREADING A TOOL UNIT ONTO AN ELONGATE STRUCTURAL ELEMENT
An apparatus for threading a tool unit onto an elongate structural element. The apparatus has a holding arrangement for holding it on a feed device, a tool unit to be threaded onto the elongate structural element. The tool unit has a tool axis and a vibration unit connected to the tool unit and configured to generate a periodic force in at least one first spatial direction that runs transversely with respect to the tool axis. First and second coupling components, held elastically on one another, are provided. The first coupling component is connected to the holding arrangement, the second coupling component is connected to the tool unit. The vibration unit is operated, during a feed movement of the holding arrangement for threading the tool unit onto the elongate structural element, to add an additional, periodically varying transverse component to a feed force acting on the tool unit.
B21J 15/12 - Machines à riveter avec outils ou parties d'outils possédant un mouvement propre s'ajoutant au mouvement d'avance, p.ex. repoussage
B21J 15/26 - Entraînements pour machines à riveter; Moyens de transmission correspondants actionnés par un entraînement rotatif, p.ex. par des moteurs électriques
91.
POTTING SEALANT COMPOUND FOR A PROTECTIVE LINING OF A PART, IN PARTICULAR AN AIRCRAFT PART, AND ASSOCIATED METHOD
A protective lining which includes a self-curing potting sealant compound. The lining can be used for an aircraft part, such as a tank wall liner which can be manufactured in-situ by casting the sealant into a prepared mold that is formed at least at the bottom side by the part to be protected by the tank wall liner. Specifically, for fuel tanks, the bottom portion forms the bottom side of the mold, whereas the ribs and stringers form a circumferential wall of the mold that prevents flowing of the potting sealant compound into neighboring molds.
A leading edge structure (11) for a flow control system of an aircraft (1), including a leading edge panel (13) surrounding a plenum (17) and having a first side portion (21), a second side portion (27), an inner surface (33) facing the plenum (17) and an outer surface (37) in contact with an ambient flow (39), wherein the leading edge panel (13) includes micro pores (45), wherein a first port device (49) is arranged in the first side portion (21) fluidly connected to the plenum (17) via a duct (53) defined by a duct structure (105), and wherein the first port device (49) comprises a first door (55) pivotable by a first hinge (57) about a first hinge axis (59).
B64C 21/08 - Moyens permettant d'influencer l'écoulement d'air sur les surfaces des aéronefs en agissant sur la couche limite par utilisation de fentes, de conduits, de surfaces poreuses ou de dispositifs similaires réglables
B64C 3/50 - Variation de la courbure par volets de bord d'attaque ou de bord de fuite
93.
A LEADING EDGE STRUCTURE FOR A FLOW CONTROL SYSTEM OF AN AIRCRAFT
A leading edge structure (11) for a flow control system of an aircraft (1), including a leading edge panel (13) that surrounds a plenum (17), wherein the leading edge panel (13) has a first side portion (21), a second side portion (27), an inner surface (33) and an outer surface (37), wherein the leading edge panel (13) having micro pores (45) forming a fluid connection between the plenum (17) and the ambient flow (39), wherein a first air inlet/outlet device (49) is arranged in the first side portion (21) and a second air inlet outlet/device (51) is arranged in the second side portion (27), fluidly connected to the plenum (17), and wherein the first air inlet/outlet device (49) comprises a pivotable first door (55) and the second air inlet outlet/device (51) comprises a pivotable second door (61).
B64C 21/08 - Moyens permettant d'influencer l'écoulement d'air sur les surfaces des aéronefs en agissant sur la couche limite par utilisation de fentes, de conduits, de surfaces poreuses ou de dispositifs similaires réglables
A buffer for storing liquid at a consumer pressure includes a storage volume for holding a liquid and a gas. The storage volume may be separated by a partition element into a liquid compartment for holding the liquid and a gas compartment for holding the gas. A pressurizer is configured for increasing the pressure of gas in the storage volume to an operating pressure when liquid is or has been drained from the storage volume. A ventilator reduces the pressure of gas in the storage volume back to the operating pressure when the storage volume is filled with liquid. A water supply system for an aircraft including the buffer and an aircraft including such a water supply system are disclosed.
A wastewater tank arrangement for an aircraft, including a wastewater tank and a drain pipe having a first end and an opposite second end, the drain pipe fastened with its first end to the wastewater tank and having a second end for connection to a service panel in the aircraft structure. Providing a wastewater tank arrangement can effectively compensate tolerances between the wastewater tank and the service panel, and can effectively compensate installation and manufacturing tolerances during the course of the initial installation, in that the wastewater tank arrangement has a tolerance compensation device configured to connect the second end of the drain pipe to the service panel and compensate tolerances between the second end of the drain pipe and the service panel.
F16L 27/11 - Raccords réglables; Raccords permettant un déplacement des parties raccordées comportant uniquement une connexion flexible les extrémités des tuyaux étant assemblées au moyen d'un manchon flexible le manchon ayant la forme d'un soufflet avec des ondulations multiples
F16L 27/10 - Raccords réglables; Raccords permettant un déplacement des parties raccordées comportant uniquement une connexion flexible
96.
METHOD AND SYSTEM FOR MONITORING A LAMINAR FLOW ON A SURFACE OF AN AIRCRAFT
A method and a system for monitoring a laminar flow on a surface of an aircraft is disclosed including observing a surface of an aircraft by an optical sensor, and processing an image data of that surface by an image processing system in order to determine an actual extend of a laminar flow on the surface. The actual extend of the laminar flow on the surface is compared with a previous extend of the laminar flow on the surface, and/or with a potential maximum extend of laminar flow on the surface determined from flight parameters of the aircraft. A reduction or a possible optimization of the laminar flow is detected and further processed to improve the laminar flow.
A wing for an aircraft. The wing includes a main wing and a trailing edge high lift assembly movably arranged at a trailing edge of the main wing. The trailing edge high lift assembly includes a flap and a connection assembly movably mounting the flap to the main wing, such that the flap is movable between a retracted position and at least one extended position, wherein the connection assembly is configured such that the flap is movable relative to the main wing in a linear and/or rotational manner. The connection assembly is configured such that the flap is movable relative to the main wing in a decoupled linear and rotational manner.
A tank wall liner for a fuel tank includes a liner body made of a liner material. The liner material is a sealant or composite of sealant and fiber and/or textile materials. Multiple tank wall liners are installed on a tank wall and form a lining surface that seals the fuel in the tank from the tank skin. Also, a tank with the tank wall liner, an aircraft with a tank forming a portion of the fuselage, and methods of manufacturing the tank wall liner and the tank.
A centrifugal reservoir pump for processing a hydrogen stream in an aircraft. In particular, a centrifugal reservoir pump including a pump casing, a hydrogen stream inlet, a rotor being rotatably arranged in the interior part of the pump and including rotor vanes for accelerating the hydrogen stream, and two hydrogen stream outlets. Further provided is a tank unit including the centrifugal reservoir pump and a reservoir for hydrogen. Further provided is an aircraft including a centrifugal reservoir pump or a tank unit. Further provided is a method of processing hydrogen in an aircraft.
F04D 31/00 - Pompage simultané de liquides et de fluides compressibles
F04D 7/02 - Pompes adaptées à la manipulation de liquides particuliers, p.ex. par choix de matériaux spéciaux pour les pompes ou pièces de pompe du type centrifuge
F04D 29/42 - Carters d'enveloppe; Tubulures pour le fluide énergétique pour pompes radiales ou hélicocentrifuges
F04D 29/22 - Rotors spécialement pour les pompes centrifuges
F04D 29/58 - Refroidissement; Chauffage; Réduction du transfert de chaleur
100.
Cabin module with integrated drainage and aircraft with a cabin module
A cabin module for an aircraft comprises a section which has an upward-facing surface in an installed state of the cabin module, wherein the upward-facing surface of the section comprises an integrated drainage channel. An aircraft furthermore comprises at least one such cabin module.
