Airbus France

Aerospatiale Societe Nationale Industrielle

Aerospatiale Matra Airbus

Eads Airbus Sa

Airbus Operations Gmbh

Airbus Operations (s.a.s.)

Francis Dazet

Pascal Chaumel

Fran&ccedil;ois Rouyre

Olivier Pautis

Danilo Ciprian

Noël Maurens

Guy Cavailles

Jean-Christian Beucher

Ludovic Debanne

Alain Depeige

A shield for a nose of a large aircraft. The shield is float-mounted on a frame of the aircraft in one embodiment. To this end, the shield and the frame are respectively provided with fingers and receptacles that engage with each other. To prevent loosening, peripheral elastic links are distributed on the rim of the shield. Through this approach, it is shown that the shield retains only about one degree of freedom relative to the frame. This degree of freedom is oriented in the direction of the fingers.

Aircraft nose with shield

Device for attachment of an aircraft windshield. The device comprises a monoblock flange (). The flange is fixed to the structure () of the aircraft by screws (), so as to trap a peripheral edge of the windshield glass () between the flange and the structure. A dry monoblock seal () surrounds the peripheral edge of the windshield, such that the seal alone provides leak tightness between the inside and the outside of the aircraft. Preferably, the screws () are in contact with the flange () through plane surfaces perpendicular to the center lines of the screws. At least one second dry monoblock seal () may also be placed between the flange () and the structure ().

Aircraft windshield attachment device

An aircraft cockpit window comprises a window pane () fitted with a frame (), and guide rails () on which the frame () is guided at three points (A, B, C) using two lower sets of rollers () and an upper set of rollers (). All these controls for locking/unlocking and opening the window pane are grouped on a handle () articulated on the lower edge of the frame (), about an axis () that is preferably approximately vertical.

Aircraft cockpit window

Articulation device for an aircraft door panel and an aircraft door integrating such a device

The nose gear of an aircraft comprises a main group of at least one wheel ( ) in permanent contact with the ground and a secondary group of at least one wheel ( ), which is normally spaced from the ground, when the aircraft is on the ground. In the case of emergency braking due to an aborted takeoff or in the case of a blowout of a tire of a wheel ( ) of the main group, the wheel or wheels ( ) come into contact with the ground. This avoids an oversizing of the nose gear.

Auxiliary nose landing gear for aircraft

The door ( ) of an aircraft incorporates a housing ( ) able to receive a slide, in a folded up state. The housing ( ) is delimited between a cover ( ) facing outwards from the door ( ) and intermediate bulkhead ( ). The cover ( ) is jettisonable outside the aircraft or able to swivel by its lower edge on a threshold of the door, by the use of setting de-setting means. In one embodiment, the housing occupies the greater part of the door surface.

Aircraft door and aircraft fitted with such a door

An aircraft fore-structure for wide- and very-wide body freight aircraft that is characterized by the presence of a unpressurized landing gear compartment in the lower fore end section. The landing gear compartment is formed by a ceiling at the top, that is preferably domed, and by a partition towards the rear. A door that is provided in the partition provides access through the landing gear compartment to the pressurized compartment located behind said partition. An opening in the fore of the landing gear compartment also provides access to the radar chamber without requiring the radome to be dismantled. The original layout of the landing gear compartment enables fore landing gear to be installed that is larger than that in existing aircraft.

Aircraft fore structure

A system for controlling a control surface articulated to a structure of a vehicle about a first axis includes a tab articulated to the trailing edge of the control surface about a second axis parallel to the first axis, an elastic link provided between the control surface and the tab, a pilot input control mechanism to which the elastic link is connected and which acts on the tab, and an actuating member provided between the control surface and the link for keeping the tab/control surface assembly in any position whatever. The elastic link and the actuating member are arranged to be at least substantially parallel to the first axis of articulation of the control surface. The first axis is disposed near, and upstream from, the elastic link and the actuating member.

Growing community of inventors

Saint Alban, France

Francis Dazet