Airbus Operations (s.a.s.)

Airbus Operations Gmbh

Airbus (Sas)

Patrick Lieven

Romain Delahaye

Christophe Mialhe

Pascal Chaumel

Marc Tomasi

Philippe Bernadet

Matthieu De Kergommeaux

Daniel Bellet

Samuel Burgunder

Marc Dugerie

Laurent Lache

Jérôme Colmagro

Laurent Saint-Marc

Didier Poirier

Anthony Mertes

Jacques Fournie

Henning Everth

Jérôme Phalippou

Nicolas Chatrenet

Marc Audibert

Pierre Dourel

Gilles Mercadier

Catalin Perju

Jean-Christophe Loche

Charles Lambert

Gautier Destombes

Jörg Schwickert

Philippe Rodrigo

Serge Cassagnes

Eric Chavonet

Olivier Gattus

Jean-Christope Loche

Mathieu Giraudineau

Damien Binaud

Sven Rosebrock

Bernward Mons

An assembly for reinforcing a fuselage of an aircraft, the aircraft including a fuselage including an opening and a removable panel received in the opening. The assembly including a first support fixed to an exterior face of the fuselage around and outside an opening in the fixed fuselage. A sub-assembly is to an exterior face of the removable panel and housed inside the first support. The first support is fixed to the fuselage. The sub-assembly is fixed to the removable panel.

Assembly for reinforcing the fuselage of an aircraft when removing a removable panel

An aircraft structure which extends along a longitudinal axis, a lateral axis and a vertical axis, wherein the aircraft structure includes an upper shell and a lower shell that together surround an interior compartment designed for accommodating an aircraft cabin, and a pillar arrangement with at least one support pillar which extends through the interior compartment and connects the upper shell to the lower shell and supports same in relation to each other. An aircraft structure can be provided which is particularly efficient, in particular has a low weight and requires little space and outlay on assembly is achieved in that the interior of the support pillar has at least one flow duct for the conduction of air-conditioned air.

Aircraft structure

An aircraft fuselage door with an internal and external panel, and an aircraft fuselage part with the door. The door includes a movable internal panel to be subjected to pressurization and an aerodynamic external panel, the external panel being on an external face of the internal panel by covering the surface of the external face and elastically linked to the internal panel to form an internal free space between them, the internal panel being movable relative to the external panel. The external panel includes a centering piece to ensure a self-centering function of the door allowing the internal panel to move independently with regard to the external panel when the door is in a closed position so a clearance between the periphery of the outer panel and the fuselage can be reduced, thereby reducing drag at the outer surface of the door and improving the aerodynamic performance of the aircraft.

Aircraft fuselage door comprising an internal panel and an external panel, and aircraft fuselage part comprising such a door

An aircraft including a fuselage including an opening and beams that are aligned and that are interrupted at the edges of the opening, a removable panel where for each pair of aligned beams of the fuselage interrupted at the opening a beam of the removable panel extends between the two beams of the pair and each end of the beam of the removable panel faces an end of a beam of the pair and at the end of at least one beam of the fuselage facing an end of a beam of the removable panel, fixing means providing a removable fixing between the ends.

Aircraft including a fuselage and a panel removably fixed to the fuselage with the aid of fixing means

A propeller propulsion unit, comprising at least one kinematic system comprising at least: a heat engine, an electrical energy generator, an electric motor configured to generate a rotary movement as output from the electrical energy generated by the electrical energy generator, a drive and selection device configured to assume a first configuration, in which it is coupled to the output of the electric motor, and a second configuration, in which it is coupled to the main shaft of the heat engine, and a propeller rotated by the drive and selection device. Such a propeller propulsion unit with a hybrid engine allows more power to be provided and facilitates maintenance and ergonomics and is safer.

Propeller propulsion unit comprising a heat engine and an electric motor and aircraft comprising such a propeller propulsion unit

In order to simplify the kinematics involved in opening an aircraft door, a plurality of mobile stop members is provided at the periphery of the door, these being intended to press against complementary stop arrangement provided on the door frame. A door control device is configured to bring the door from its closed position into a set-back intermediate position by moving it towards the interior of the compartment, and a stop arrangement control device is configured to allow the mobile stop members to be moved, when the door is occupying its set-back intermediate position, from a deployed locking position to a retracted unlocking position, allowing the door to be moved outward through the opening in the fuselage.

Door system for aircraft fuselage

A windshield for an aircraft cockpit is provided which includes a glazed windshield part which has a single curvature corresponding to a portion of the envelope of a cone extending between a lower plane and an upper plane which intersect an axis of the cone. The single curvature of the glazed part of the windshield enables the glazed part to be produced more easily, for example by rolling or by hydroforming. It also makes it possible to create configurations for a cockpit for two pilots, a single pilot or even no pilot, on the basis of a single aerodynamic shape of the fuselage of the aircraft by only adapting the structure of the windshield. Also provided are a windshield frame for such a windshield, a windshield assembly including such a windshield frame and such a windshield, and an aircraft equipped with such a windshield.

Unitary aircraft windshield with conical single curvature

An aircraft windshield that improves pilot and co-pilot's perception of the outside world. The windshield includes a transparent panel held inside a structure of the aircraft, in which the upper part and the lower part are bridged so that the loads applied to the panel are (at least partially) diverted. Due to part of the loads applied on the panel being diverted, it is possible to provide a larger window panel than currently available that offers better visibility to the outside.

Windshield with support rod

System for friction stir welding of two parts which includes a welding unit which includes at least one welding head fitted with a rotating pin and a counter-bearing unit which has a support surface to support the parts against a pressure exerted by the welding head, and wherein each welding head can be moved relative to the support surface in a first direction parallel to an axis of rotation of the rotating pin and in a second direction orthogonal to the axis of rotation, and wherein the support surface can be moved in the second direction and is formed of two coaxial clamp rollers which are set apart from each other.

Process for friction stir welding including a mobile counter-bearing

Process for linear transparency friction stir welding of a flange of a stiffener onto at least one panel for an aircraft, wherein a weld bead is made along the flange of the stiffener and wherein the weld bead extends in cross-section from a first lateral edge to an opposite second lateral edge of the stiffener flange. System for the implementation of the above welding process, which includes three welding heads arranged as a triangle, each of which includes a rotating pin as well as a shoulder extending at the base of said rotating pin.

Process and system for friction stir welding of a stiffener on an aircraft panel

A rudder bar for an aircraft comprising a floor, a steering connecting rod and a braking connecting rod. The rudder bar comprises a base fixed above the floor, a pedal arm mounted rotatably on the base about a first axis of rotation and having a lower end and an upper end, a pedal mounted rotatably on the lower end about a second axis of rotation, a first transmission assembly configured to transmit a movement to the steering connecting rod when the pedal arm pivots about the first axis of rotation, and a second transmission assembly configured to transmit a movement to the braking connecting rod when the pedal pivots about the second axis of rotation.

Rudder bar for an aircraft

In order to limit the number of openings in an aircraft fuselage and to reduce the mass thereof, the invention makes provision for an item of aircraft fuselage equipment which is intended to be mounted in an opening of the fuselage, the item of equipment being configured to block/release an access passage which affords access to the inner side of the aircraft and which also comprises a discharge control valve for pressurization air.

Fuselage equipment forming an access door and comprising a discharge control valve for pressurization air

The disclosure herein relates to an aircraft fuselage stiffener including a heel, a flange, and a web connecting the heel and the flange, this stiffener comprising a folded sheet extending along the length of the heel, the web and the flange. In addition, to improve the mechanical behavior of the stiffener, the folded sheet includes on the one hand a main portion extending along the length of the heel, the web and the flange, and on the other hand at least one folded-over portion forming a lining of the main portion over at least part of the web and/or the heel and/or the flange.

Aircraft fuselage stiffener formed from a sheet folded over onto itself

The sealed bottoms of aircraft passenger cabin have to be fastened with heavily sized fasteners so as to withstand loads induced by the cabin pressurization. Besides, the increase in aircrafts seating capacity makes an increase in passenger cabin widths of interest. Such a width increase however makes the structure delimiting passenger cabin less resistant to efforts induced by the cabin pressurization. The present invention proposes an aircraft wherein the structure delimiting passenger cabin extends over 360 degrees around a space defined outside structure. The invention allows structure to be more resistant to loads induced by the cabin pressurization, while allowing to reduce or even to avoid the need for a sealed bottom, and while allowing to increase the space available for passengers.

Growing community of inventors

Fronton, France

Patrick Lieven