Airbus Operations (s.a.s.)

Airbus Operations Gmbh

Laurent Gauthie

Philippe Bernadet

Frédéric Fort

Sebastien Alby

Phillippe Bernadet

To facilitate the assembly of the wing unit of an aircraft, this wing unit includes two wings each having a lateral wing box extended toward the interior by a center wing box half having an interior end, the two wings being attached to one another using attachment bolts linking the two interior ends of the two center wing box halves, and passing through an intermediate wall connecting two fuselage frame walls.

Aircraft wing unit comprising two wings attached to one another

An aircraft panel, notably a fuselage panel of the aircraft, includes at least one opening equipped with a surround intended to accept a closing-off device that closes off the opening. The panel includes at least one exterior surface. The surround surrounding the opening is fixed to the panel, forming an interface for fitting the closing-off device, and includes at least one lip extending towards the center of the opening. The lip supports the closing-off device. The surround has an external face interposed between the exterior surface of the panel and the closing-off device. The surround includes fixing apparatus which works by gripping the edge of the opening of the panel.

Aircraft panel comprising an opening equipped with a surround

The invention concerns a pressurized flooring for aircraft, provided with beams () including an upper sole (), a vertical web plate (), and a lower sole (), the lower sole being provided with two oblique feet () arranged on both sides of the vertical web plate and presenting a support surface () provided for supporting pressurized curved membranes (), characterized in that the lower sole includes a linking element () connecting the two oblique feet, so that said lower sole presents an enclosed section. Such a structure can be advantageously realized in composite material.

Aircraft pressurized floor

A system for transmitting stresses at the intersection between a reinforcing frame and a stiffener in a fuselage and to a method for producing one such system. An aircraft fuselage includes stiffeners interrupted by reinforcing frames. At aforementioned interruptions, the stresses experienced by the stiffeners must be transmitted despite the presence of the reinforcing frames. Known solutions are difficult to manufacture and install and do not provide a simple stress transmission path when produced solely from composite materials. In order to solve this problem, the disclosed embodiments include the creation of battens that cover the ends of consecutive sections of a stiffener and the skin of the fuselage, extending under the reinforcing frame in order to join aforementioned two consecutive sections.

Aircraft including stiffener edge junctions and method for producing one such aircraft

A beam for reinforcing the structure of an aircraft is located inside the fuselage of the aircraft. The fuselage includes at least one pressurized zone (P) that is separated by at least one airtight wall () of at least one other non-pressurized zone (), the beam and the at least one airtight wall being intersecting. The beam traverses the at least one airtight wall () that includes a cutaway that is adapted to the section of the beam, whereby sealing elements () are provided to ensure the sealing between the beam and the airtight wall () that is traversed.

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Tournefeuille, France

Laurent Gauthie