Airbus Operations Patente

Proposed is a method for providing connectivity between a personal electronic device (110), PED, and a networked output device in an aircraft. The method comprises providing an encapsulated subnetwork within a wireless network of the aircraft. The subnetwork is dedicated to the networked output device (120). The method further comprises providing, via the networked output device (120), configuration information configured to provide access to the subnetwork for the PED (110). The subnetwork is configured to provide connectivity between the networked output device (120) and the PED (110) when the subnetwork is accessed by the PED (110) using the configuration information.

Provided is a cabin management device (10) for an aircraft cabin space. The device comprises a sensor (12); a microcontroller (14), data-connected with the sensor (12); and an output (16), data-connected with the microcontroller (14). The sensor (12) is configured to collect a plurality of distance data across a predetermined part of the cabin space (30) at a plurality of points in time and to transmit the distance data to the microcontroller (14). The microcontroller (14) is configured to evaluate the distance data by a comparison of the distance data collected at one point in time with distance data collected at another point in time and to generate space-related data based on the comparison, and to transmit the space-related data to the output (16). And the output (16) is configured to provide information about a current spatial situation based on the transmitted space-related data.

The present disclosure relates to a potable water connection (100) for a water consumer in an aircraft and comprises a main body (110) having an outer thread (112), a male fitting (120) configured to be coupled to the water consumer, a connector (130) configured to be coupled to a potable water supply means (190), and a nut plate (180) threaded onto the outer thread (112). The present disclosure further relates to an aircraft monument and an aircraft having such potable water connection.

An actuation assembly (10) is provided, The actuation assembly (10) comprises a control unit (40), a monitoring unit (50), at least one high voltage power supply (32), at least one low voltage power supply (34) and at least two power bridges (60a, 60b). The at least one low voltage power supply (34) is configured to be connected to a source to provide power to the control unit (40) and to the monitoring unit (50), wherein the control unit (40) and the monitoring unit (50) are configured to monitor elements of a sub-system comprising at least one of an electric motor, a brake or a sensor. The at least one high voltage power supply (32) is configured to be connected to a source to provide power to each of the at least two power bridges (60a, 60b). And the at least two power bridges (60a, 60b) are each configured to be coupled with an electric motor.

This high lift system architecture (22), comprises: - a first rotational sensor (46), configured to be installed on a torque transmission arrangement (24) and to measure a first angular position (A1) of the torque transmission arrangement (24), at a first measurement point (M1); - a second rotational sensor (48), configured to be installed on the torque transmission arrangement (24) and to measure a second angular position (A2) of the torque transmission arrangement (24), at a second measurement point (M2); and - an actuation control device (50), comprising: + an acquisition module (56), configured for acquiring the first angular position (A1) from the first rotational sensor (46) and the second angular position (A2) from the second rotational sensor (48), and + a determination module (58), configured for determining a torque (T) applied to the torque transmission arrangement (24) as a function of said acquired first (A1) and second (A2) angular positions.

This high lift system architecture (22) comprises: - an actuation arrangement (24), configured to move at least one moveable surface (20); - a sensor (26), configured to generate an analog sensed signal representative of a configuration of the moveable surface (20); - a flight control computer (28); and - an actuation control device (30) comprising: + an acquisition module (42) for acquiring the analog sensed signal, + a processing module (44) for processing the analog sensed signal and for generating an analog controlling signal based on the processed analog sensed signal, + a conversion module (46) for converting the analog sensed signal into a digitalized monitoring signal, + a control module (48) for controlling the actuation arrangement (24) based on the generated analog controlling signal, and + a communication module (50) for communicating the digitalized monitoring signal to the flight control computer (28)

This High lift system monitoring arrangement (24) comprises: - at least one sensor (32), - a monitoring unit (34), connected to the at least one sensor (32), the monitoring unit (34) comprising: + an acquisition module (46), configured for acquiring an analogous sensed information (Al) from the at least one sensor (32), + a processing module (48), comprising a first processing circuitry (48A) and a second processing circuitry (48B), different from the first circuitry, wherein the first processing circuitry (48A) is configured to process the analogous sensed information (Al) into a first digital sensor data (DD1), the second processing circuitry (48B) being configured to process the analogous sensed information (Al) into a second digital sensor data (DD2).

This actuation control device (30) for a high lift system (16), comprises: - an acquisition module (46), configured for acquiring a first output torque (OT1), of a first high lift system actuator (24A); - a comparison module (48), configured for comparing the acquired first output torque (OT1) to at least one predetermined first threshold torque (TT1); and - a determination module (50), configured for determining a monitoring signal (M) depending on the comparison of the acquired first output torque (OT1) to the at least one predetermined first threshold torque (TT1).

Disclosed is a pipe assembly comprising a first tubular pipe section, a second tubular pipe section and a fastener system that fastens the first tubular pipe section to the second tubular pipe section to define a flow path through the first tubular pipe section and the second tubular pipe section. The first tubular pipe section extends along a common central axis and comprises a first engagement feature. The second tubular pipe section extends along the common central axis and comprises a second engagement feature. The fastener system comprises: a first fastener sub-system and a second fastener sub-system. The first fastener sub-system has a first component on the first tubular pipe section and a first fastener arrangement that fastens the first component to the second engagement feature so that the first engagement feature is located between the first component and the second engagement feature to thereby restrict movement of the first tubular pipe section away from the second tubular pipe section in a direction of the common central axis. The second fastener sub-system has a second component on the second tubular pipe section and a second fastener arrangement that fastens the second component to the first engagement feature so that the second engagement feature is located between the second component and the first engagement feature to thereby restrict movement of the first tubular pipe section away from the second tubular pipe section in the direction of the common central axis.

An energy conversion arrangement (2) for an apparatus (1), a corresponding energy system (2), in particular for powering a propulsion unit (5) for propelling an apparatus (1), and an apparatus (1), in particular an aircraft, are provided, comprising a fuel conversion device (10), in particular a fuel cell unit, for generating electrical and/or mechanical energy by oxidising a reductant (R) contained in a fuel gas (F) by means of an oxidant (O) contained in a reactant gas (G), with at least one anode element (31) configured to take up the electrons (e) shed by the reductant (R) and to be picked up by the oxidant (O) during fuel conversion; at least one anode channel (12) configured to lead the reactant gas (G) along the at least one anode element (31); and/or at least one cathode element (32) configured to provide electrons (e) shed by the reductant (R) and to be picked up by the oxidant (O) during fuel conversion; at least one cathode channel (13) configured to lead the reactant gas (G) along the at least one cathode element (32); and at least one pre-heating duct (14) configured to at least partly recirculate the fuel gas (F) within the anode channel (12) and/or the reactant gas (G) within the cathode channel (13), respectively.

A method and system for aircraft turnaround readiness optimization, involving: receiving (301) target information data related to passengers' onboarding, selected turnaround tasks on an aircraft, and the aircraft schedule; receiving (302) progress information data related to progress of execution of passengers' onboarding and of the selected turnaround tasks; calculating (303) an estimate for the time of completion of the selected turnaround tasks, by comparing the corresponding target information data and progress information data; providing (304) the calculated estimate to at least an aircraft operator; and receiving (305) from the aircraft operator a subset of the selected turnaround tasks.

An energy conversion arrangement (2) for an apparatus (1), a corresponding energy system (2), in particular for powering a propulsion unit (5) for propelling an apparatus (1), and an apparatus (1), in particular an aircraft, are provided, comprising a fuel conversion device (10), in particular a fuel cell unit, for generating electrical and/or mechanical energy by oxidising a reductant (R) contained in a fuel gas (F) by means of an oxidant (O) contained in a reactant gas (G), with at least one cathode element (32) configured to provide electrons (e) shed by the reductant (R) and to be picked up by the oxidant (O) during fuel conversion; at least one cathode channel (13) configured to lead the reactant gas (G) along the at least one cathode element (32); and at least one preheating duct (14) configured to lead the reactant gas (G) to the cathode channel (13) and to heat up the reactant gas (G) by heat provided by the reactant gas (G) in the cathode channel (13).

- Method and system for determining an optimized set of ink colours used to print a pattern on an object - The method comprises in particular steps implemented by a computer device for defining a plurality of sets of different colours in a colour space (19), each of which consists, on the one hand, of spot colours that make it possible to reproduce one or more sensitive colours (C6, C7) of the reference pattern to be printed continuously and exactly and, on the other hand, of process colours intended to be used to produce colour combinations, so as to be able to obtain all of the colours (C1, C2, C3, C4, C5) of the reference pattern to be printed, other than the one or more sensitive colours (C6, C7), in the livery, and for selecting one of these sets of colours taking into account at least one selection criterion, in order to obtain a set of colours that is optimized in particular in terms of precision and/or ink consumption.

Die vorliegende Erfindung befasst sich mit einer Toilettenanordnung in einem Kabinenbereich eines Verkehrsflugzeugs. Um eine Toilettenanordnung zur Verfügung zu stellen, die sich für Personen mit eingeschränkter Mobilität eignet, ist eine Toilettenanordnung (10) für einen Kabinenbereich eines Verkehrsflugzeugs vorgesehen, die einen Toilettenraum (12) mit einer Toilette und eine Wandanordnung (14) aufweist, die den Toilettenraum an wenigstens zwei Seiten umschließt, mit wenigstens einer ersten Wand (16) und einer zweiten Wand (18), wobei die erste Wand und die zweite Wand aneinander angrenzen und über einen Eckbereich (20) miteinander verbunden sind. In der ersten Wand ist eine erste Öffnung (22) mit einer ersten beweglichen Verschlusseinrichtung (24) als Toilettentür vorgesehen, um einen ersten Zugang zu dem Toilettenraum durch Passagiere zu ermöglichen. In der zweiten Wand ist eine zweite Öffnung (26) mit einer zweiten beweglichen Verschlusseinrichtung (28) als bi-funktionales Wandsegment vorgesehen, das in einem geöffneten Zustand die zweite Öffnung in der zweiten Wand freigibt, um einen zweiten Zugang zu dem Toilettenraum durch Passagiere mit eingeschränkter Mobilität zu ermöglichen.

A high lift arrangement for a folding aircraft wing having a wing body with a folding wing tip comprising a high lift element arranged to have a deployed position in front of the leading edge of the folding wing tip, and an actuator for deploying the element. The actuator is mounted to the wing body such that there is no need for electrical or hydraulic cables to cross the wing fold line.

A high lift arrangement for an aircraft wing comprises a high lift element arranged to have a deployed position wherein the high lift element extends in front of at least an inboard portion of a leading edge of the wing tip. The high lift element has a sweep angle which is less than the sweep angle of the wing tip, such that a gap is formed between the element and the wing tip. A vortex is generated at the tip of the high lift element to energise the wing tip upper surface boundary layer. The gap accelerates the flow, improving low speed performance of the wing.

A composite structural member for an aircraft, the composite structural member having a ramped region and comprising a plurality of composite plies arranged upon one another in a thickness direction; wherein, in the ramped region, the composite plies include at least first and second subsets of composite plies, each subset comprising a plurality of composite plies; and wherein the second subset of composite plies is staggered in a ramp direction relative to the first subset of composite plies, the staggering producing a flat surface region on the second subset of composite plies, suitable for seating a fastener thereon in use. A method of forming such a composite structural member by resin transfer moulding, and a method of designing such a composite structural member, are also provided.

An aircraft (1) with a first tank (20) suitable for containing fuel, a second tank (30) suitable for containing a second, different fuel or fuel additive, a first fuel line (22) configured to transport the fuel from the first tank to a mixer (50), a pump (62) arrangement configured to drive a flow of fuel from the first tank along the first fuel line and a second fuel line (32) configured to transport the second, different fuel or fuel additive from the second tank to the mixer. The mixer is configured to mix the fuel and second, different fuel or fuel additive to form a blended fuel. The aircraft also includes a mixer line (52) configured to transport the blended fuel from the mixer to a combustor (40).

A method and system for assistance to on ground aircraft security is devised, which involves receiving data about planned intervention information on an aircraft (100), monitoring data about security status information for the aircraft (100), and if a at least one aircraft opening (103) is opened, determining whether it is the result of an intrusion in the aircraft (100) external and/or internal structure, by comparing the corresponding data about planned intervention information and data about security status information, and if it is determined that an intrusion in the aircraft (100) has occurred, raising an alert with at least one aircraft operator.

In order to provide a facilitated floor sub-structure, a support frame (10) for an aircraft cabin floor is provided. The support frame is provided by frame members (12) comprising at least two primary frame members (14) and at least two secondary frame members (16). The primary frame members are configured to form vertical load support columns (18). The secondary frame members are configured to form horizontal bar frame members (20). The primary frame members are arranged parallel to each other, and the secondary frame members are arranged parallel to each other, while the primary frame members are arranged transverse to the secondary frame members. One of the secondary frame members is connected to one end of the respective primary frame members and another of the secondary frame members is connected to the other end of the respective primary frame members. The primary frame members and the secondary frame members are made by cutting and forming from a single sheet.

Disclosed is a method for producing a blank 10 for deformation into a component part 100. Therein, a first section A, B, C, D, E of a sheet 1 made of a fibre reinforced composite material is designated to after the deformation become a first portion P₁, P₂, P₃, P₄, P₅ of the component part 100, and a second section A, B, C, D, E of the sheet is designated to become a second portion P₁, P₂, P₃, P₄, P₅ of the component part 100. A slit pattern is generated, within the sheet 1, whose geometry in the first section A, B, C, D, E is different from its geometry in the second section A, B, C, D, E.Further disclosed are a manufacturing method for manufacturing a component part 100, and a blank 10 for deformation into a component part 100.

A method, control program (11), computer-readable data carrier (12), control unit (3), communication system (1) and a corresponding aircraft (7) are provided, wherein for providing data objects (D) to at least one operating person (O) for operating an aircraft (7), the method comprises the steps of providing a computing device (10) on the aircraft (7) configured to handle data objects (D) containing status information (I) regarding the aircraft (7), at least one of an operational unit (U) of the aircraft (7), a transportation unit (V) to be carried by the aircraft (7) and/or the operating person (O) to be tasked with handling the aircraft (7) and/or a transportation unit (V) transported by and/or supposed to be transported by the aircraft (7); and providing at least one communication device (2), such as a mobile device, at least temporarily associated to the operating person (O) or to a further operating person (P) and adapted to send to and/or receive the data objects (D) embedded in and/or in the form of push messages (M) to provide the status information (I) to the operating person (O) and/or to the further operating person (P).

A method, control program (11), computer-readable data carrier (12), control unit (3), communication system (1) and a corresponding aircraft (7) are provided, wherein for managing work tasks (W) to be accomplished within a pre-defined time frame (T), in particular a turn-around time measured between an expected arrival timepoint (e) and a scheduled departure time point (f) of an aircraft (7), the method comprises the steps of providing a computing device (10) on the aircraft (7) configured to handle data objects (D) containing status information (I) regarding the aircraft (7), at least one of an operational unit (U) of the aircraft (7), a transportation unit (V) to be carried by the aircraft (7) and/or an operating person (O) to be tasked with handling the aircraft (7) and/or the transportation unit (V) for achieving at least one respective work task (W); and providing at least one communication device (2), such as a mobile device, at least temporarily associated to the operating person (O) or to a further operating person (P) and adapted to send to and/or receive the data objects (D) to provide the status information (I) to the operating person (O) and/or to the further operating person (P).

In order to allow an improved weld joint to be manufactured, the invention proposes a system (10, 10', 10") for ultrasonic welding which comprises a sonotrode (11) for emitting ultrasonic energy into a joint region (12) between a first part (13) and a second part (14) that are to be joined together. A consolidator (15; 15') exerts pressure on a surface (16; 17) of one of the first and second parts (13; 14) to consolidate the joint region (12). The consolidator (15, 15') is conformable to the surface (16; 17) of the one of the first and second parts (13; 14) to consolidate the joint region (12).

An aircraft maintenance system controller, and corresponding method and storage medium are provided. The aircraft maintenance system controller is configured to obtain first da data representing operational characteristics of a plurality of components in an aircraft system. The first data is processed with a model of the aircraft system using a machine learning classifier to identify a plurality of altered operational characteristics of components in the aircraft system. A cause of the plurality of altered operational characteristics is then determined and used to generate second data indicative of the determined cause of the altered operational characteristics. Third data indicative of a validation of the determined cause of the plurality of altered operational characteristics are obtained and used to update the machine learning classifier based on the third data.

A refuelling connector has an inner pipe section (e.g. defining inner region 138) for conveying cryogenic hydrogen to an aircraft and an outer pipe section (e.g. defining outer region 136) for holding a vacuum to provide thermal insulation to the inner section. Via one or more suitable valves (126, 132) the connector can, when connected to the aircraft, create a vacuum on the aircraft-side or otherwise convey fluid from / to the aircraft, via the outer pipe section (136).

Offenbart sind ein Sandwichelement mit einem Schaumkern, der an seinen zueinander entgegengesetzten Großflächen zumindest jeweils eine Decklage aufweist, wobei in die eine Großfläche des Schaumkern Vertiefungen eingebracht sind und die zumindest eine sich über diese Großfläche erstreckende Decklage mit Öffnungen versehen ist, die sich zumindest teilweise in Überdeckung mit den Vertiefungen befinden, ein Herstellungsverfahren sowie ein Kabinenelement.

The present invention provides an outer skin of an aircraft fuselage or aircraft fuselage section formed from a fibre reinforced plastic, in particular carbon fibre reinforced plastics (CFRP) in a layered configuration, comprising at least two layers (105a, b) having electrically conductive fibres (400), in particular carbon fibres, placed with alternating fibre orientations within the layers (105a, b) and embedded in a polymer matrix material, and a coating (100) consisting of or comprising magnetically active particles (101) configured to induce a change in physical properties of the coating (100) when exposed to a magnetic field (300), a method for monitoring the structural integrity of the outer skin of an aircraft fuselage or fuselage section and an aircraft having a fuselage or fuselage section provided with such an outer skin.

This fuel tank supporting arrangement (22) for an aircraft, comprises: - an inner support (30), configured for being fastened to a fuel tank (20); and - an outer support (32), configured for being fastened to a fuselage (12) of the aircraft (10); the inner support (30) and the outer support (32) being connected to each other and configured for supporting the fuel tank (20) in the fuselage (12), the inner support (30) and the outer support (32) being configured to be moveable one relative to another along a predetermined path (P) if an acceleration of the fuel tank (20) relative to the fuselage (12) reaches a predetermined excessive acceleration threshold (Ta).

A support assembly (10) for a high lift body (8), in particular a leading-edge-slat, configured to be mounted to a spar (6) of a wing (3) of an aircraft (1), as well as a corresponding high lift body arrangement (4), a wing (3) and an aircraft (1) are provided, the support assembly (10) comprising at least two hinging organs (30) each providing at least one hinge point (G) configured for hinging the high lift body (8) at the spar (6) movably between a stowed position (S) and a deployed position (T) along a motion path (E) involving a translatory component (I, J, L) extending within a deployment plane (P) extending transversely with respect to a mounting plane (H) provided by the spar (6) for mounting the hinging organs (30) to the spar (6).

- Procédé et dispositif informatique pour transformer un maillage texturé d'un objet conçu en un maillage texturé d'un objet fabriqué correspondant audit objet conçu.- Le procédé pour déterminer un maillage texturé transformé (M2) d'un objet fabriqué (O2) tridimensionnel à partir d'un maillage texturé initial (M1) d'un objet conçu (O1) tridimensionnel, le maillage texturé transformé (M2) étant destiné à être utilisé lors de l'impression d'une texture bidimensionnelle (T) correspondante sur l'objet fabriqué (O2), met en œuvre un traitement itératif pour déterminer un jeu de transformations affines à paramètres individualisés permettant de minimiser la valeur d'une fonction cible comprenant au moins un terme favorisant une propriété spécifique, le jeu de transformations affines ainsi déterminé étant appliqué aux sommets du maillage texturé initial (M1) de manière à obtenir le maillage texturé transformé (M2), ledit procédé étant relativement simple à mettre en œuvre et particulièrement avantageux.

L'invention a pour objet un réservoir cryogénique comprenant : - au moins une enceinte (14) contenant une phase liquide, - au moins une structure anti-ballottement (22) positionnée à l'intérieur de l'enceinte (14) et configurée pour le compartimenter, - au moins un système de liaison reliant la structure anti-ballottement (22) et l'enceinte (14). Le fait de compartimenter l'enceinte (14) permet de limiter les mouvements excessifs de la phase liquide à l'intérieur de l'enceinte (14). L'invention a également pour objet un aéronef comportant au moins un tel réservoir.

A sensor system (10) for monitoring characteristics of a dewar tank (20) having an inner shell (21) and an outer shell (22) is provided. The sensor system (10) comprises a sensor arrangement (16) comprising a first magnetic field sensor (11), and a first permanent magnet element (12), and a controller (13). The first magnetic field sensor (11) is connected to the controller (13). The first magnetic field sensor (11) is configured to be attached to the outer shell (22) of the dewar tank (20). The first permanent magnet element (12) is configured to be attached to the inner shell (21) or to the outer shell (22) of the dewar tank (20). The first magnetic field sensor (11) and the first permanent magnet element (12), in a mounted state on the dewar tank (20), are configured to be located in the vicinity of each other, such that the magnetic field sensor (11) is capable of detecting a magnetic field created by the first permanent magnet element (12). The controller (13) is configured to measure, via the first magnetic field sensor (11), the magnetic field of the first permanent magnet element and to infer at least one characteristic of the dewar tank (20) based on the detected magnetic field of the first permanent magnet element (12).

A support assembly (10) for a high lift body (8), in particular a trailing-edge-flap, configured to be mounted to a spar (6) of a wing (3) of an aircraft (1), a corresponding carriage assembly (20) for carrying a high lift body (8), in particular a trailing-edge-flap, a high lift device arrangement (4) for a wing (3) of an aircraft (1), a wing (3) for an aircraft (1), and a corresponding aircraft (1) are provided, the support assembly (20) comprising a track beam (60) configured for supporting the high lift body (8) at the spar (6) movably between a stowed position (S) and a deployed position (T) along a motion path (E), the track beam (60) having at least one structural profile portion (61) adapted for transferring operational loads of the high lift body (8) into the spar (6), and at least one track profile portion (62) supported at the at least one structural profile portion (61) and adapted for guiding a carriage assembly (20) for carrying the high lift body (8) movably along the motion path (E) and taking up the operational loads; wherein the at least one structural profile portion (61) and/or the at least one track profile portion (62) are or is, respectively, provided with at least one complementing profile portion (C), and wherein the at least one structural profile portion (61), the at least one track profile portion (62), and/or at least one complementing profile portion (C) are providing a main load path (A) and a redundant load path (B) configured to alternatively and/or additionally transfer and/or take up the operational loads, respectively.

L'invention concerne un système d'alimentation électrique (PSS) d'aéronef configuré pour alimenter des dispositifs électriques embarqués (D1, D2, D3, D4, D5, D6) comprenant au moins :- un sous-circuit électrique (HVDCN) de type haute tension à courant continu,- un sous-circuit électrique (LPACN) de type basse tension à courant alternatif,- un sous-circuit électrique (LPDCN) de type basse tension à courant continu,le système (PSS) comprenant en outre un circuit de commutation de batterie (HVBATSW) à haute tension (HVBAT), le système (PSS) étant tel que toute ligne d'alimentation dudit sous-circuit basse tension à courant continu, indépendante dudit circuit de commutation (HVBATSW), est dépourvue de batterie basse tension.Avantageusement, il est ainsi possible d'éviter une redondance de batteries préjudiciable au poids de l'aéronef (AC) et conduisant à une complexité de son système électrique.

A Method (100) for manufacturing a stiffened aerodynamic structure component (10) is provided, comprising the following steps:- Providing (102) an aerodynamic structure component (10), wherein the aerodynamic structure component (10) includes a plurality of spar elements (12) extending spanwise within the aerodynamic structure component (10);wherein the plurality of spar elements (12) is integrally formed with an upper skin section (14) and a lower skin section (16), thereby providing an integrally formed aerodynamic structure component (10),- Generating (104) at least one chordwise reinforcement element (18) by injecting a curable medium (32), preferably via at least one injection hole (20), in the upper skin section (14) and/or the lower skin section (16).

A method of manufacturing a composite part comprises providing a molding tool (10) comprising a tool base (14) and a tool lid (16), both configured to form a cavity (18) between the tool base (14) and the tool lid (16) tool when the molding tool (10) is closed. A fibre preform (22) is placed in the tool (10) which is tightly closed so that the fibre preform (22) is within the cavity (18). A predefined clamping pressure (PC) presses the tool lid (16) and the tool base (14) against each other, and a resin (28) is injected into the cavity (18) at an injection pressure (PI) to infiltrate the fibre preform (22) with the resin (28). The size of the cavity (18) is passively increased by allowing an opening movement (OM) of the tool lid (16) relative to the tool base (14) and I or an elastic deformation (32) of the tool, when the inner tool pressure (PI) is greater than the predefined clamping pressure (PC), while keeping the cavity (18) tightly closed.

Herein illustrated and described is a wing (5) for an aircraft (1), comprising a main wing (9) and a leading edge high lift assembly (11) comprising a slat (13) and a connection assembly (15) movably connecting the slat (13) to the main wing (9), wherein the connection assembly (15) comprises an elongate slat track (27) that extends along a track longitudinal centre axis (29) between a first end (31) and a second end (33), wherein the first end (31) of the slat track (27) is mounted to the slat (13), wherein the slat track (27) is mounted to the main wing (9) by a roller bearing (37) such that the slat track (27) is movable along the track longitudinal centre axis (29), wherein the slat track (27) is mounted to the slat (13) via a link arrangement (39) comprising at least a first link element (41), wherein the first link element (41) is mounted to the slat (13) via a first slat bearing (51) and is mounted to the slat track (27) via a first track bearing (53), the slat track (27) comprises a recess (59) opening to the upper side and/or to the lower side of the slat track (27), and at least the first link element (41) of the link arrangement (39) extends through the recess (59). Further illustrated and described is a leading edge high lift assembly and an aircraft comprising such a wing or such a leading edge high lift assembly.

A composite part for a vehicle is provided. The composite part has a first surface (22a) and an opposing second surface (22b), wherein at least part of the first surface forms an outer aerodynamic surface of a vehicle. A region of the part has a curvature in two orthogonal directions. The part has an undulation (40) defining a channel (60) in one of the first surface or the second surface, and a corresponding ridge (50) in the other of the first surface and the second surface.

Disclosed is an enclosure device configured to enclose a concave surface portion of an aerodynamic component of an aircraft wing. Disclosed also is, an aerodynamic component comprising an enclosure device, and an aircraft wing and aircraft comprising one or more enclosure devices. Also disclosed is a method of counteracting unwanted airflow circulation in a concave surface portion of an aerodynamic component of an aircraft wing.