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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Patent
Airbus | Date: 2017-02-01

A flight management system architecture with separate core and supplementary modules. In the core module, generic functionalties relative to the flight management of the aircraft are implemented. In the supplementary module, supplementary functions are implemented. The supplementary functionalities include functionalties specific to an entity to which the aircraft belongs such as the specific aircraft model, a family of airdraft, a company, an alliance, and so on. The flight management system also includes a message exchange interface in which enables the core and supplementary modules to exchanges messages with each other. The core and supplementary modules includes corresponding core module and supplementary module interfacing functionaltities that respectively interface with generic ans specific man-machine interfaces.


A cap for forming a sealed cavity around one end of a fastener, the cap having a two-piece construction comprising an outer cap member and an inner cap member. A quantity of sealant is provided between the inner and outer cap members which, upon installation of the cap, is urged to flow between the inner and outer cap members and collect at the base of the outer cap member, to form a bead of sealant around the circumference of the cap, sufficient to adhere the cap to the structure when the sealant cures. A plurality of channels are provided between the inner and outer cap members to facilitate the flow of sealant.


Patent
Airbus | Date: 2017-05-24

The invention relates to a braiding bobbin (10) for a braiding device. The braiding bobbin (10) comprises a cylindrical braiding spool (14), from which a previously wound, multilayer ribbon (16) can be unwound, wherein a first layer of the ribbon (16) consists of a pre-impregnated fiber film (18), and a second layer of the ribbon (16) consists of a protective film (20). In addition, the braiding bobbin (10) comprises a bracket (22) to which the braiding spool (14) is frontally and rotatably fastened. Additionally provided for the braiding bobbin (10) is a cylindrical additional spool (24) for winding the protective film (20) of the unwound ribbon (16) and a deflection element (26). The deflection element (26) is fastened to the bracket (22), wherein the deflection element (26) is secured spaced apart in the radial direction R to the braiding spool (14) and designed for deflecting the protective film (20) from the braiding spool (14) to the additional spool (24).


Patent
Airbus | Date: 2017-05-24

A decompression assembly (10) for use in an aircraft comprises a cabin lining element (12), an opening (18) formed in the cabin lining element (12), and an air channel (22) which is arranged adjacent to a rear face (24) of the cabin lining element (12) and connected to the opening (18) formed in the cabin lining element (12). The air channel (22) is provided with an air outlet (28) which, during normal operation of the decompression assembly (10), is adapted to discharge air exiting an aircraft cabin region (26) delimited by the cabin lining element (12) through the opening (18) formed in the cabin lining element (12) into an aircraft area (30) located between the cabin lining element (12) and an aircraft outer skin (32), a first decompression opening (42), and a first decompression flap (46) which, during normal operation of the decompression assembly (10), is adapted to close the first decompression opening (42) provided in the air channel (22) and which, in the event of a rapid decompression, is adapted to open the first decompression opening (42) so as to allow a pressure equalization between the aircraft cabin region (26) delimited by the cabin lining element (12) and the aircraft area (30) located between the cabin lining element (12) and the aircraft outer skin (32).


The present invention pertains to a manufacturing method for thermoforming a fiber-reinforced composite laminate (1). The fiber-reinforced composite laminate (1) includes fiber rovings (2) embedded within a thermoplastic matrix (4). The manufacturing method comprises mounting fiber rovings (2) to a transport frame (5), wherein the mounted fiber rovings (2) are arranged to form a support grid layer (3) that is laterally framed by the transport frame (5), each fiber roving (2) being mounted on both ends under tension to the transport frame (5); placing a matrix material layup of thermoplastic material on top of the support grid layer (3) on the transport frame (5), wherein the tension of the fiber rovings (2) and a density of the support grid layer (3) are configured such that the support grid layer (3) supports the matrix material layup; softening the matrix material layup by heating the support grid layer (3) together with the matrix material layup within a heating station (8); forming a semi-finished composite laminate (1) by pressing the support grid layer (3) together with the softened matrix material layup within a press (6); and consolidating the semi-finished composite laminate (1) to form the fiber-reinforced composite laminate (1).


An aircraft for the transport of passengers comprises a passenger cabin having a cabin floor (6), a cargo compartment situated below the cabin floor (6), a first access unit (4) for accessing the cargo compartment from the passenger cabin, the first access unit (4) being located on the cabin floor (6) and a utility space module (20) arranged in the cargo. At least one part of the cargo compartment comprises a first lateral half and a second lateral half in relation to a longitudinal axis of the aircraft, which lateral halves together form the at least one part of the cargo compartment. The utility space module (20) comprises a utility space cross-section in a direction normal to the longitudinal axis, which utility space cross section is dimensioned such that it conforms a cross-section of one of the first lateral half and the second lateral half of the cargo compartment. Further, the utility space module (20) is placed exclusively in the first lateral half or the second lateral half of the cargo compartment directly below the first access unit (4).


A foldable wing for an aircraft, comprises a base wing having a base wing end region, a wing tip having a connection region, a first engagement means integrated into the base wing, a second engagement means (122, 124) integrated into the wing tip, and a drive mechanism (86) coupled with the wing tip for moving the wing tip relative to the base wing. The first engagement means and the second engagement means (122, 124) are adapted for engaging each other along a sliding course from a first position, in which the connection region of the wing tip and the base wing end region are in a flush contact to form a continuous wing, up to a second position, in which the first engagement means and the second engagement means (122, 124) disengage. The drive mechanism (86) comprises a first movement element (102) and a second movement element (106) at least partially extending in a spanwise direction, wherein the first movement element (102) and the second movement element (106) are supported in a linear guide (88) each, an outboard end of the first movement element (102) being coupled with the wing tip in a first lateral position and an outboard end of the second movement element (106) being coupled with the wing tip in a second lateral position. The drive mechanism (86) is configured to move the first movement element (102) and the second movement element (106) at the same time to move the wing tip relative to the base wing at least along the sliding course between the first position and the second position.


The present invention provides production methods for producing a fibre-reinforced metal component (1) having a metal matrix (2) which is penetrated by a plurality of reinforcing fibres (3). One production method comprises depositing in layers reinforcing fibres (3) in fibre layers,depositing in layers and liquefying a metal modelling material (4) in matrix material layers (5), and consolidating in layers the metal modelling material (4) in adjacently deposited matrix material layers (5) to form the metal matrix (2) of the fibre-reinforced metal component (1). Here, the metal component (1) is formed integrally from alternately deposited matrix material layers (5) and fibre layers (6). An alternative production method comprises introducing an open three-dimensional fibrewoven fabric consisting of reinforcing fibres (3) into a casting mould, pouring a liquid metal modelling material (4) into the casting mould and consolidating the metal modelling material (4) to form the metal matrix (2) of the fibre-reinforced metal component (1). Here, the metal component (1) is formed integrally from the consolidated metal modelling material (4) and the reinforcing fibres (3).


A decompression assembly (10) for use in an aircraft, the decompression assembly (10) comprises a cabin lining element (12), an opening (18) formed in the cabin lining element (12) and an air channel (22) which is arranged adjacent to a rear face (24) of the cabin lining element (12) and connected to the opening (18) formed in the cabin lining element (12). The air channel (22) is provided with an air outlet (28) which, during normal operation of the decompression assembly (10), is adapted to discharge air exiting an aircraft cabin region (26) delimited by the cabin lining element (12) through the opening (18) formed in the cabin lining element (12) into an aircraft area (30) located between the cabin lining element (12) and an aircraft outer skin (32), a first decompression opening (36), and a first decompression flap (40) which, during normal operation of the decompression assembly (10), is adapted to close the first decompression opening (36) provided in the air channel (22) and which, in the event of a rapid decompression, is adapted to open the first decompression opening (36) so as to allow a pressure equalization between the aircraft cabin region (26) delimited by the cabin lining element (12) and the aircraft area (30) located between the cabin lining element (12) and the aircraft outer skin (32). The decompression assembly (10) further comprises a second decompression opening (50) formed in the cabin lining element (12), and a second decompression flap (52) which, during normal operation of the decompression assembly (10), is adapted to close the second decompression opening (50) formed in the cabin lining element (12) and which, in the event of a rapid decompression, is adapted to open the second decompression opening (50) so as to allow a pressure equalization between the aircraft cabin region (26) delimited by the cabin lining element (12) and the aircraft area (30) located between the cabin lining element (12) and the aircraft outer skin (32).


The invention relates to a container for effecting at least one non-lethal change in inherent properties of a non-human biological system, in particular of a plant or of a fungus, under the influence of zero gravity, comprising a carrier plate which is configured to receive two capacitor plates of a plate capacitor, wherein the plates are situated parallel to one another and in each case perpendicularly on the carrier plate, at least one sample container which is arranged horizontally on the carrier plate, is adjacent to each of the two capacitor plates and is configured to receive the biological system, and an electromagnet which is arranged substantially half way between the capacitor plates and, when seen from the carrier plate, is arranged above the horizontal at least one sample container. The invention relates additionally to a European modular cultivation system, EMCS, for use in the International Space Station, ISS, comprising a centrifuge, wherein the container is received in the centrifuge.

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