Toulouse, France
Toulouse, France

Airbus SAS , German: , Spanish: ) is an aircraft manufacturing division of Airbus Group . It is based in Blagnac, France, a suburb of Toulouse, with production and manufacturing facilities mainly in France, Germany, Spain and the United Kingdom.Airbus began as a consortium of aerospace manufacturers, Airbus Industrie. Consolidation of European defence and aerospace companies in 1999 and 2000 allowed the establishment of a simplified joint-stock company in 2001, owned by EADS and BAE Systems . After a protracted sales process BAE sold its shareholding to EADS on 13 October 2006.Airbus employs around 63,000 people at sixteen sites in four countries: France, Germany, Spain and the United Kingdom. Final assembly production is based at Toulouse, France; Hamburg, Germany; Seville, Spain; and, since 2009 as a joint-venture, Tianjin, China. Airbus has subsidiaries in the United States, Japan, China and India.The company produces and markets the first commercially viable fly-by-wire airliner, the Airbus A320, and the world's largest passenger airliner, the A380. Wikipedia.

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A method for determining individual passenger aircraft boarding times includes the steps of assigning a seat in an aircraft to a mobile device of a passenger of the aircraft, transmitting a timer start notification signal to the mobile device of the passenger, detecting the presence of the mobile device of the passenger at the assigned seat, and determining a boarding timespan as a period of time that elapsed between transmittal of the timer start notification signal and detection of the presence of the mobile device at the assigned seat.


The invention refers to the manufacturing of a leading edge section (1) with hybrid laminar flow control for an aircraft comprising providing an outer hood (4), a plurality of elongated modules (2), first and second C-shaped profiles (5, 7) comprising cavities (10), and an inner mandrel (3); assembling an injection moulding tool by placing each profile (5, 7) on each end of the inner mandrel (3), arranging a first extreme of each elongated module (2) in one cavity (10) of the first profile (5) and a second extreme of the module (2) in another cavity (10) of the second profile (7), both cavities (10) positioned in the same radial direction; and placing the hood (4) on first and second profiles (5, 7) to close the tool. Further, the injection moulding tool is closed and filled with an injection compound comprising thermoplastic and short-fiber. Finally, the compound is hardened and demoulded.


Patent
Airbus | Date: 2017-09-27

A foldable seat bench (10) comprises a seat (12) comprising a seat area (14) and a backrest (16), and a carrier arrangement (18) comprising a carrier element (20) carrying the seat (12) and at least one leg (22). The backrest (16) is movable relative to the carrier element (20) between a deployed position in which it extends at an angle of approximately 70 to 110 relative to the seat area (14) and a stowed position in which it extends at an angle of approximately 0 to 20 relative to the seat area (14). The leg (22) is foldable relative to the carrier element (20) between a unfolded position and a folded position. The foldable seat bench (10) further comprises a first locking mechanism (32) which, in a locking state, is adapted to lock the backrest (16) of the seat (12) in both its deployed position and its stowed position, and a second locking mechanism (34) which, in a locking state, is adapted to lock the leg (22) of the carrier arrangement (18) in both its unfolded position and its folded position.


Patent
Airbus | Date: 2017-09-27

The invention relates to a universal joint (100) comprising:- a first band (102a) and a second band (102b) which are separated by a slot (104), are cylindrical and coaxial with one another with respect to a common axis (15),- a first stiffener (108a) whose ends are joined to the first band (102a), and a second stiffener (108b) whose ends are joined to the second band (102b),- a stem (110) which extends between the first stiffener (108a) and the second stiffener (108b),- a crown (112) around the stem (110),- four torsion bars (106a-b), of which two extend between the crown (112) and the first band (102a) and two extend between the crown (112) and the second band (102b). Such a universal joint (100) thus has a relatively simple structure.


A partition wall module for a cabin of a vehicle for an optical and mechanical separation of different cabin regions comprises a lower partition wall section having at least one first fastening means for fastening the partition wall module to at least one near-floor structurally fixed component in the cabin, a surface-like rigid upper partition wall section converging with the lower partition wall section having at least one second fastening means in a region of the partition wall module facing away from the lower partition wall section for fastening the partition wall module to at least one near-ceiling structurally fixed component in the cabin. The upper partition wall section at least in a region comprises an arched curvature around a horizontal axis for adapting to the shape of a backrest of a passenger seat. The partition wall module comprises at least one edge stiffening element, which extends between a near-floor region and a near-ceiling region of the partition wall module.


A 3D-printing or tape laying method for manufacturing a fiber reinforced composite component (10). The method comprises supplying a spread tow tape (1) containing a plurality of reinforcing fibers (2) from a tape supply (3) to a merging station (4), supplying a plurality of matrix material filaments (5) from a multi-filament supply (6) to the merging station (4), pressing together the plurality of matrix material filaments (5) with the spread tow tape (1) at the merging station (4), heating the spread tow tape (1) together with the plurality of matrix material filaments (5) at the merging station (4) to a melting temperature (T) of the matrix material filaments (5) to form an impregnated fiber ply (7), and depositing the impregnated fiber ply (7) in composite layers (8) onto a print bed (9) to form the fiber reinforced composite component (10). A 3D-printer (100) or tape-laying machine implementing such a method.


The present invention pertains to a method for manufacturing a lining panel (1) with integrated electric lines (2) for a lining of a passenger cabin of an aircraft or spacecraft. The method comprise using (M3) an additive manufacturing, AM, or 3D printing technique to form the electric lines (2) on or into a panel body (3) of the lining panel (1). The present invention further pertains to a lining panel (1) with integrated electric lines (2) for a lining of a passenger cabin of an aircraft or spacecraft. The lining panel (1) comprises a panel body (3) and electric lines (2) being formed on or into the panel body (3) using an AM or 3D printing technique.


The present invention pertains to method for manufacturing a lining panel (1) with an integrated electrical connector (5) for a lining of a passenger cabin of an aircraft or spacecraft. The method comprises using an additive manufacturing (AM) or 3D printing technique to laterally form electrically conductive pins (6) on a panel body (3) of the lining panel (1) to provide an electrical connector (5). The electrically conductive pins (6) are formed to connect to electric lines (2) attached to or formed on or into the panel body (3) of the lining panel (1). The invention further pertains to a lining panel (1) with an integrated electrical connector (5) for a lining of a passenger cabin of an aircraft or spacecraft. The lining panel (1) comprises a panel body (3), electric lines (2) being attached to or formed on or into the panel body (3), and an electrical connector (5) with electrically conductive pins (6) formed laterally on the panel body (3) of the lining panel (1) using an AM or 3D printing technique. The electrically conductive pins (6) are configured to connect to the electric lines (2).


An airframe component includes a skin panel (1), a plurality of stringers (2) attached to the skin panel, and at least one former (3) running substantially perpendicular to the plurality of stringers (2) on the skin panel (1), the at least one former (3) being generatively formed on the skin panel by an Additive Manufacturing, AM, method.


The invention refers to an aircraft aerodynamic surface (10) comprising a torsion box having an upper skin (11), a lower skin (12), and a front spar (9), and a leading edge (1) having an external shell (7) and an impact resisting structure (8). The external shell (7) may be shaped with an aerodynamic leading edge profile, being configured to provide Laminar Flow Control (LFC) to the leading edge. The impact resisting structure (8) is spanwise arranged between the external shell (7) and the front spar (9), and is configured for absorbing a bird strike to prevent damage in the front spar (9). Also, at least one of the external shell (7) and the impact resisting structure (8) is fitted with the upper and lower skins (11, 12) of the torsion box to thereby facilitate leading edge exchange.

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