Airbus Operations (s.a.s.)

Airbus Operations Gmbh

Daniel Bellet

Patrick Lieven

Guillaume Gallant

François Loyant

Alexandre Legardez

Philippe Bernadet

Simon Roux

Julien Gallardo

Charlotte Jeanneau

Eric Chavonet

Jean-Claude Roques

Rolland Gilabert

Emmanuel Front

Henri Rigal

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

A module includes two main landing gears and a landing gear bay containing the landing gears. The bay has two lateral walls, a roof wall, a front wall and a rear wall. The roof wall, the front wall and the rear wall together form a pressurization barrier between the bay and a pressurized compartment. By virtue of the landing gear module, it is now possible to assemble and test the main landing gears and the one or more doors and the fairing before they are installed on the aircraft.

Compact aircraft main landing gear module allowing modular mounting

In order to allow an aircraft fuselage structure to provide optimum resistance to pressurization loads in a fuselage region with a double curvature, the fuselage structure includes a circumferential frame oriented so that the web of the circumferential frame has an orientation close to the local normal to the skin of the fuselage.

Structural assembly for an aircraft fuselage with double curvature including frames with an optimized orientation

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

A device for intermediate fastening between an aircraft fuselage and an aircraft landing gear is provided. The device includes at least one semi-open support structure comprising a pair of webs, which are substantially parallel to each other. The webs comprise first support means intended to receive the main pivot shaft of the landing gear and second support means intended to receive the stay joint or joints of the landing gear. The device includes two support structures linked together by a central box structure. The central box structure includes a front wall, a rear wall and linking walls linking those two walls.

Device for intermediate fastening between an aircraft fuselage and an aircraft landing gear

An assembly of longitudinal structural stiffeners for an aircraft including, in a front portion of the fuselage, a windscreen that is slightly recessed relative to the airplane nose, and a fuselage portion extending in alignment with the airplane nose up to the base of the windscreen. The stiffeners include a bending-resistance main plane and are arranged under the flap and connected to the fuselage along a force transfer line. For one or more of the stiffeners, the bending resistance main plane substantially coincides, at at least a certain number of points of the fuselage force transfer line, with the plane predetermined by the local normal to the fuselage surface and the longitudinal axis of the airplane. A method is also provided for calculating the shape of the stiffeners.

Under-flap stiffener for aircraft

A floor section for a vehicle cabin includes juxtaposed profiled elements of identical cross section. Each profiled element includes a mainly planar elongated cross member and a generally flat elongated panel. The cross member includes a lower stiffener, is positioned in a transverse vertical plane, and is attachable at two extremities to a vehicle frame. The elongated panel is positioned in a horizontal plane and includes an overlap region along one longitudinal edge and a bearing region along another longitudinal edge. The overlap region and the bearing region are of similar width and of total thickness less than or equal to a mean panel thickness. The panel is perpendicular to the cross member, and a bearing region underside is coplanar with a lower face of the elongated panel and is secured to the cross member at two or more points substantially in line with a middle of the bearing region.

Growing community of inventors

Saint-Lys, France

Daniel Bellet