Airbus Operations (s.a.s.)

Airbus Operations Gmbh

François Loyant

Jérôme Colmagro

Daniel Bellet

Alexandre Legardez

Guillaume Gallant

Julien Guillemaut

Dominique Guittard

Frédéric Fort

Ludovic Fournie

Olivier Eve

Jean Marc Durand

Simon Roux

Julien Gallardo

Jean Pierre Cabanac

Jean-Pierre Cabanac

Jean-Marc Durand

A double-walled tank comprising at least one connection system connecting the outer and inner enclosures and enabling them to move in relation to one another in at least a longitudinal direction parallel to an axis of displacement when in operation. The connection system has an annular linear connection between a first contact surface rigidly connected to the outer enclosure and a second contact surface rigidly connected the inner enclosure, the first and second contact surfaces arranged opposite one another and configured to be in contact with one another along a contact circle that has a center positioned on the axis of displacement.

Tank comprising inner and outer enclosures and at least one annular linear connection system connecting said enclosures

An aircraft landing gear well roof including a first reinforced main structure and a second reinforced main structure spaced from each other in a transverse direction of the roof and equipped with respective mounting for articulating a structural element of the first landing gear and mounting for articulating a structural element of the second landing gear. A membrane connecting the first reinforced main structure and the second reinforced main structure is disposed between them in the transverse direction.

Landing gear well roof

An aircraft comprising a wing box and a fuselage provided with a connecting device configured to be connected to the wing box and to transmit thereto stresses undergone by the fuselage during maneuvers of the aircraft are provided. The connecting device is formed by a keel beam and a keel beam panel connected to the beam via a connecting portion of the beam, that is moreover provided with a main portion extending in a first, generally longitudinal direction and a transfer portion extending in a second direction different from the first direction and configured to be connected to the box. The main, transfer and connecting portions are configured to direct a major part of the stresses received by the beam in the second direction and transmit said major part of the stresses to the box by compression.

Aircraft comprising a wing box and a fuselage provided with a connecting device connected to the wing box

A wing box rib, joining an aircraft wing to the wing box and to the rest of the structure, extends advantageously over an adjacent part of the fuselage, having in particular an upper line situated above a junction line of the wing upper surface panel. The connection is simplified, as is the structure of the aircraft and its manufacture, a lightening is possible, and the transmission of stresses takes place in a more favorable manner.

Connection of a fuselage to an aircraft wing

The stiffening frames () of an aircraft fuselage () remain continuous while passing through an upper panel () of the wing box and extend over the ribs () situated in that box. The overall mechanical strength of the assembly is improved, despite the notches it is necessary to make in the panel ().

Connector for stiffening frames between an aircraft fuselage and a wing box

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l'Isle Jourdain, France

François Loyant