Airbus Operations Patente

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 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.

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 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.

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.

- 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.

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).

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.

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).

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).

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).

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.

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.

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).

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.

- 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.

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 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.

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).

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.

An aircraft maintenance system, method, and computer-readable storage medium are provided. The aircraft maintenance system comprises a processor and storage comprising a digital twin of at least part of an aircraft and a machine learning classifier. The aircraft maintenance system is configured to obtain aircraft operational data, update the digital twin based on the aircraft operational data, identify an altered operation of the aircraft based on the aircraft operational data, and determine a set of conditions responsible for the altered operation using the machine learning classifier to evaluate the digital twin. Output data indicative of the set of conditions responsible for the altered operation is generated.

A fuel mixing assembly comprising, a fuel vessel, such as a pipe 15 for conveying flow of a first fuel; and a second-fuel conduit 17 for conveying flow of, for example an additive, into the fuel vessel 15. The fuel mixing assembly further comprises a vortex generator 21, the vortex generator 21 being configured to generate vortices to mix the first fuel and the additive. The additive may be released from an outlet in the vortex generator 21.

This slat cove filling device (24) for a slat (18) of an aircraft (10) comprises a sheltering panel (46) extending along a spanwise direction (Y) and comprising a proximal edge (50), configured for being fastened to a slat body (22) of the slat (18), and a distal edge (52), configured for being slidable relative to the slat body (22),the sheltering panel (46) comprising a plurality of guiding passages, each guiding passage being configured for cooperating with a guiding element of the slat body (22) for guiding the distal edge (52) along a sliding direction (S) relative to the slat body (22).

A kinematics assembly (10) for a high lift body (8), in particular a droop nose or leading-edge-slat, configured to be mounted to a main body (5) of a wing (3) of an aircraft (1), as well as a corresponding support station (50) for supporting a high lift body (8), a high lift body arrangement (4), a wing (3) and an aircraft (1) are provided, the kinematics assembly (10) comprising an actuation organ (30) providing a drive mounting point (R) configured to mount the Kinematics assembly (10) to a drive organ (20) for moving the high lift body (8) with respect to the main body (5) between a stowed position (S) and a deployed position (T), and a deflection organ (40) configured to be connected to the actuation organ (30) and providing a central hinge point (C) for hinging the high lift body (8) at the main body (5) movably between the stowed position (S) and the deployed position (T); wherein, at least in the stowed position (S), the drive mounting point (R) is located aft of the central hinge point (C) with respect to a travel direction (F) of the aircraft (1).

Die vorliegende Offenbarung betrifft einen Flugzeugabschnitt (100) und ein Flugzeug mit einem zusätzlichen Sicherheitsgurt, dessen Gurtaufwickler an einer Primärstrukturbaugruppe befestigt ist und durch ein Seitenverkleidungselement 130 in eine Passagierkabine des Flugzeugabschnitts geführt wird.

A landing gear assembly (30) for an aircraft (10), the landing gear assembly comprising: a forward brace (40) having a first end (41) for attachment to an airframe of the aircraft, and a second end (43); an aft brace (50) having a first end (51) for attachment to the airframe of the aircraft, and a second end (53), wherein the second end (53) of the aft brace is coupled to the second end (43) of the forward brace; an actuator piston (70) having a first end (71) and a second end, wherein the first end (71) of the actuator piston is pivotally coupled to the first end (41) of the forward brace; a bellcrank linkage (60) having a first end (62), a second end (64), and a pivot point (63) between the first end and the second end, such that a first portion of the bellcrank linkage extends from the first end (62) to the pivot point (63), and a second portion of the bellcrank linkage extends from the pivot point (63) to the second end (64), wherein the pivot point of the bellcrank linkage is pivotally coupled to the first end (51) of the aft brace, and wherein the first end (62) of the bellcrank linkage is pivotally coupled to the second end of the actuator piston (70); a primary strut (90) having a first end (91) and a second end (96), wherein the first end of the primary strut is pivotally coupled to the second end (43) of the forward brace (40) and the second end (53) of the aft brace (50), and wherein one or more wheels (100) of the aircraft are mounted at the second end (96) of the primary strut (90); and a secondary strut (80, e.g. a shock absorber) having a first end (81) and a second end (83), wherein the first end of the secondary strut is pivotally coupled to the second end (64) of the bellcrank linkage (60), and wherein the second end (83) of the secondary strut (80) is pivotally coupled to a pivot point near to the second end (96) of the primary strut (90); wherein the landing gear assembly is configured to adopt a deployed configuration when the actuator piston (70) is in a retracted configuration, and wherein the landing gear assembly is configured to adopt a retracted configuration when the actuator piston (70) is in an extended configuration. Also provided is an aircraft (such as a blended wing body aircraft BWB) having such a landing gear assembly.

The present disclosure relates to an aircraft air-conditioning system (100) and corresponding aircraft, wherein ambient air is cooled by a cooling system (200) having a first cooling circuit (210) and a second cooling circuit (220) thermally coupled to one another via a common heat exchanger (205).

Disclosed are a panel element, in particular for use as an aircraft interior part, comprising at least one plate component having a front side and a rear side, and a stiffening structure forming enforced areas of the plate component, wherein the stiffening structure comprises at least an edge protection frame surrounding outer edges of the at least one plate component, and local stiffening elements extending over adjacent surface areas of the front side and the rear side, wherein the stiffening structure is visible in a final state of the panel element on both sides, and an aircraft interior part comprising at least one panel element.

A landing gear assembly for an aircraft, the landing gear assembly comprising: a forward brace having a first end for attachment to an airframe of the aircraft, and a second end; an aft brace having a first end for attachment to the airframe of the aircraft, and a second end, wherein the second end of the aft brace is coupled to the second end of the forward brace; an actuator piston having a first end and a second end, wherein the first end of the actuator piston is pivotally attachable to the airframe of the aircraft; a bellcrank linkage having a first end, a second end, and a pivot point between the first end and the second end, such that a first portion of the bellcrank linkage extends from the first end to the pivot point, and a second portion of the bellcrank linkage extends from the pivot point to the second end, wherein the pivot point of the bellcrank linkage is pivotally attachable to the airframe of the aircraft, and wherein the first end of the bellcrank linkage is pivotally coupled to the second end of the actuator piston; a primary strut having a first end and a second end, wherein the first end of the primary strut is pivotally coupled to the second end of the forward brace and the second end of the aft brace, and wherein one or more wheels of the aircraft are mounted at the second end of the primary strut; and a secondary strut (e.g. a shock absorber) having a first end and a second end, wherein the first end of the secondary strut is pivotally coupled to the second end of the bellcrank linkage, and wherein the second end of the secondary strut is pivotally coupled to a pivot point near to the second end of the primary strut; wherein the landing gear assembly is configured to adopt a deployed configuration when the actuator piston is in an extended configuration, and wherein the landing gear assembly is configured to adopt a retracted configuration when the actuator piston is in a retracted configuration. Also provided is an aircraft (such as a blended wing body aircraft) having such a landing gear assembly.