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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The invention refers to a leading edge section (1) with laminar flow control, which comprises: a perforated outer skin (2), a perforated inner skin (3), and a plurality of suction chambers (4) formed between the outer skin and the inner skin. The leading edge section comprises a plurality of stringers (5) span-wise arranged at the leading edge section, and integrally formed with the outer skin, such as the inner skin is joined to the stringers. The invention also refers to a method for manufacturing a leading edge section integrating a laminar flow control system, wherein a perforated inner skin is joined with a perforated outer skin having a plurality of stringers (5) integrally formed with the outer skin, such as suction chambers (4) are defined by a part of the outer skin, a part of the inner skin and a pair of stringers.


Patent
Airbus | Date: 2017-07-19

The invention refers to an autonomous screwing robot comprising: an automated guided vehicle (2), a robotic arm (4) mounted in the automated guided vehicle (2), an automated screwing device (5) assembled with the robotic arm (4), a screws feeding system (8) mounted in the automated guided vehicle (2), a vision system (6) assembled with the robotic arm (4) and adapted to capture images of a working area for the screwing device, and an images recognition system. The guided vehicle (2) is programmed to move following a predefined path, and to stop at several static working positions within that path. The robotic arm is adapted to align the axis of the screwing device with the axis of a target hole guided by the images recognition system. The screwing machine is capable of screwing a large number of screws, into large static pieces, and it is specially adapted for its use in the aeronautical industry.


Patent
Airbus | Date: 2017-07-19

The invention relates to a method for manufacturing and monitoring a part (1). The method comprises the following steps: a) treating a substrate comprising aluminum by means of a chemical conversion method using a treatment solution comprising chromium at oxidation degree +III such as to obtain a part (1) having a chemical conversion layer (3); and b) monitoring the presence of the chemical conversion layer (3) obtained during Step a) by measuring, through the use of colorimetry, the color of said chemical conversion layer (3) and comparing said measured color with a reference color.


The invention relates to an aircraft having a fuselage and wings connected thereto, wherein a support strut extends in each case between the fuselage and the wings, said support strut being connected both to the fuselage and the wing. The support strut comprises a hydraulic working cylinder that can be subjected with hydraulic fluid for pivoting the wing in a controlled manner.


Patent
Airbus | Date: 2017-01-25

An aircraft fuel system has a bottom wall, and a rib with a bottom edge joined to the bottom wall. The rib provides a boundary between first and second compartments. At least the first compartment is arranged to carry fuel. An open recess is in the bottom edge of the rib and a rib sealing arrangement between the bottom edge of the rib and the bottom wall prevents fuel from flowing across the bottom edge of the rib except at the open recess. The system has a pump and a conduit coupled at one end to the open recess and at another end to the pump. The open recess and the conduit provide a fuel flow path across the bottom edge of the rib from the first compartment into the pump. The flow path is sealed to prevent fuel flowing out of the flow path into the second compartment.


A system for assisting in guiding of an aircraft maneuvered by an aircraft tractor on the ground, the system including at least one projection device including a laser generating a laser beam fixed to an anchor point of the fuselage of the aircraft. A fixing mechanism is configured to fix the projection device to an anchor point of the fuselage, the laser beam from each laser projector then plotting a light trace on the ground to be used to assist in guiding the aircraft on the ground. A camera can film the light trace on the ground. A remote display device includes a screen, the display device being positioned on the aircraft tractor for the screen to be visible to an operator of the aircraft tractor, each projection device being connected to the display device, the display device being configured to display the image from each projection device camera.


Patent
Airbus | Date: 2017-07-26

A computer-implemented method for space frame design involves constructing a load stress map in a geometrical boundary representation of a design space, defining a plurality of attachment points and load application points in the design space, creating a starting network of interconnecting lines between each two of the plurality of attachment points and load application points in the design space, assigning load application factors to each line of the starting network of interconnecting lines based on values of the load stress map, generating a plurality of potential space frame designs by selectively culling different subsets of lines of the starting network of interconnecting lines for each potential space frame design according to variable culling parameters, evaluating the performance score of each of the plurality of potential space frame designs with respect to a number of predefined optimization parameters, combining the culling parameters for the potential space frame designs the performance score of which is above a predefined performance threshold, and iterating the steps of generating potential space frame designs and evaluating the potential space frame designs on the basis of the combined culling parameters.


Patent
Airbus and Adhetec | Date: 2017-07-26

The invention concerns a multilayer thermoformable film (10) for protecting the surface of a workpiece (20), comprising an underlayer made from an adhesive material (11) capable of adhering to the surface of the workpiece by means of a first face (111), and at least one layer of polymer material (12) attached to a second face (112) of the adhesive underlayer. Said layer of polymer material (12) is resistant to erosion by solid particles and to erosion by liquid particles. It is formed from a polymer material chosen from a polyurethane, a polyetheretherketone and a polyethylene having a very high molecular weight, with a Shore D hardness of between 50 and 65 D. A method of surface protection of the workpiece (20) comprises thermoforming the film (10) in a shape adapted to match the shape of at least a portion of the workpiece (20), and applying the film thermoformed in this way onto the surface of the latter.


Described and illustrated is a wing (3) for an aircraft (1), comprising a main wing (7) and a wing tip device (9), wherein a front blade (21) and a rear blade (27) of the wing tip device (9) extend away from an attachment end (19) in a diverging manner, wherein a front blade leading edge (23) extends in front of a rear blade leading edge (29) and a front blade trailing edge (25) extends in front of a rear blade trailing edge (31), when viewed in a chord direction (33), wherein at a front blade tip (35) the front blade (21) extends under a different dihedral angle (v) than the rear blade (27) at a rear blade tip (37), wherein the front blade leading edge (23) and the front blade trailing edge (25), as well as the rear blade leading edge (29) and the rear blade trailing edge (31) all have a tangent-continuous developing. The object of the present invention, to provide a wing for an aircraft, wherein for a predetermined span dimension the induced drag can be significantly reduced, is achieved in that the front blade leading edge (23) extends tangent-continuously with the wing leading edge (11), and the rear blade trailing edge (31) extends tangent-continuously with the wing trailing edge (13), and the front blade trailing edge (23) at least partially extends behind the rear blade leading edge (29), when viewed in the chord direction (33).


Patent
Airbus | Date: 2017-08-02

An aircraft fuel system has a bottom wall, and a rib with a bottom edge joined to the bottom wall. The rib provides a boundary between first and second compartments, and at least the first compartment is arranged to carry fuel when the system is in use. An open recess is located in the bottom edge of the rib, and a rib sealing arrangement between the bottom edge of the rib and the bottom wall prevents fuel from flowing across the bottom edge of the rib except at the open recess. The system has a pump and a conduit coupled at one end to the open recess and at another end to the pump, the open recess and the conduit together providing a flow path for fuel to flow across the bottom edge of the rib from the first compartment into the pump. The flow path is sealed so that the fuel flowing along the flow path is prevented from flowing out of the flow path into the second compartment.

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