Airbus Operations (s.a.s.)

Airbus Operations Gmbh

Christophe Casse

Didier Reynes

Damien Fraysse

Lionel Alonso

Steve Fernandez

Marie Bayle

An aircraft includes first and second zones, and a sealing system, interposed between a doorframe and a door providing access to the second zone, including: a peripheral seal secured to the door, a stop secured to the doorframe, and including a body in the form of at least one plate which extends around the perimeter of the doorframe, parallel to the door when the door is in the closed position, a peripheral groove positioned on the stop in such a way that the peripheral seal closes off the peripheral groove around the perimeter of the opening when the door is in the closed position, and at least one passage configured to cause the peripheral groove and the first zone to communicate.

Aircraft comprising a hold door fitted with an improved sealing system

An antifreeze system for a pipework, the antifreeze system comprising a framework configured to be fixed to the pipework, and at least one thermally insulating sleeve maintained around the pipework by the framework. Each sleeve is configured so that a space is produced between the sleeve and the pipework. The framework has an inlet and an outlet which are configured to produce a fluid communication between the outer side of the antifreeze system and the space. The inlet is fluidly connected to a source of hot air. Such an antifreeze system thus enables a flow of hot air around the pipework which thus prevents the liquid which flows therein from freezing.

Antifreeze system for a pipework

An aircraft with a landing gear, a compartment to stow the landing gear and doors for the compartment movable between an open position and a closed position. The movement of the doors is controlled by a maneuvering system having two transmission chains or linkages each connecting one of the doors to an actuation member that includes a rotatable arm and an actuating cylinder. Each transmission chain or linkage has a relay element mounted pivotably on a structural element of the aircraft, a first connection element between the arm and the relay element, and a second connection element between the door and the relay element.

Aircraft having landing gear doors and a system for maneuvering the doors

An aircraft comprising a first door and a second door, each being mobile between an open position and a closed position, and a maneuvering system. The maneuvering system includes an actuation mechanism, a first transmission chain configured to transmit the movements of the actuation mechanism to the first door, a second transmission chain configured to transmit the movements of the actuation mechanism to the second door. Such a maneuvering system uses a single actuation mechanism, which results in a simplification of the mechanism and a weight saving.

Aircraft comprising two landing gear doors and a maneuvering system intended to maneuver said doors

A cover plate, to cover part of a space between a door and a door surround, comprising at least one pressure element secured to at least part of the external face of the cover plate. The pressure element comprises two sheets, an external sheet and an internal sheet, these two sheets being superposed and fixed together. The internal and external sheets are respectively made from materials that have different thermal expansion properties causing at least a contraction of the internal sheet with respect to the external sheet, at least for a range of temperatures comprised between &#x2212;20&#xb0; C. and &#x2212;50&#xb0; C.

Cover plate for aircraft door

A routing support () for a conduit line fastened in openings and the line includes a plurality of conduits connected end-to-end along a longitudinal axis. The routing support () incorporates an outer body () with a structure () for fastening the body in an opening. The routing support also includes a housing structure to accommodate the ends of two conduits in an end-to-end arrangement and the structure may include two separate structures (one for each conduit end ()) or a single common structure (accommodating respective ends of the two conduits). The routing support also includes a flexible interface () connecting the housing structure () to the outer body (). In addition, the flexible interface () and the outer body () and the housing structure () are integral. Embodiments include a line for transporting fuel with this routing support, and an aircraft wing in which such a line/support transports fuel.

Support for routing conduits in an aircraft wing

A movable panel such as an aileron is connected to a load-bearing structure such as a wing of an aircraft by hinges which comprise flexible, elastic plates which are juxtaposed and are provided at opposite angles so as to allow the panel to rotate in an easy manner in response to the movements of an actuator; the hinges are, however, rigid in regard to other loads, such as aerodynamic suction loads, such that inadmissible travel of the panel is avoided.

Aircraft hinge arranged between a movable panel and a load-bearing structure

A cutting plate includes a planar interface able to accept electrical connectors, two ramps for supporting harnesses and two lateral walls, the dimensions of the interface and of the two ramps in a longitudinal direction being adapted to suit the number of connectors of the cutting plate and the dimensions in the directions other than the longitudinal direction and the dimensions of the lateral walls conforming to standard dimensions.

Growing community of inventors

Fenouillet, France

Christophe Casse