Airbus Operations (s.a.s.)

Airbus (sas)

Airbus Operations Gmbh

Benjamin Thubert

Lionel Czapla

Patrick Salgues

Julien Hervier

Julien Le Fanic

Alain Porte

Jorge Alejandro Carretero Benignos

Pascal Pome

Benedikt Bammer

Alistair Forbes

Alexis Pissavin

Antoine Abele

Abhishek Verma

Kevin Windhols

Sylvain Carrere

A support device includes a profiled element having at least one passage hole passing transversely through the profiled element, a fastening support, integral with the profiled element, to fasten the support device to a primary structure, at least one clamping element having a clamp to receive at least one cable and at least one fastening element to fasten the clamping element or elements to the profiled element. The device facilitates the fastening of cables to a primary structure.

Cable support device that is easy to install and method for fastening cables with the aid of the support device

A cable support includes an open annular body and two jaws secured to the open annular body and extending therefrom, arranged with one facing the other to form a clamp, the open annular body having an aperture. The aperture of the annular body is configured to allow insertion of at least one cable into the annular body. The terminal parts of the open annular body bordering the aperture each have a loop configured for passage of a self-locking clamping collar around the open annular body. The clamp-forming jaws each include at least one through aperture configured for the passage of a fixing structure that can be locked in position. A fixing assembly includes a cable support and an intermediate fixing support of the cable support. It is advantageously possible to carry out a fast and reliable installation of cables, notably in cramped spaces such as on board an aircraft.

Enhanced cable support element, cable support assembly, aircraft electrical system and aircraft

An aircraft propulsion assembly equipped with a thrust-reversing device which includes at least one lateral aperture, passing through the nacelle of the propulsion assembly, configured to be in an open state or a closed state, at least one inflatable barrier configured to be in a deflated state in which the barrier does not protrude into an annular duct channeling a flow of air and an inflated state in which the barrier, substantially rigid or semi-rigid, is deployed and extends across the annular duct to deflect at least a part of the flow of air toward the lateral aperture, and at least one supply system configured to supply the inflatable barrier with fluid. An aircraft is provided which includes at least one such propulsion assembly.

Aircraft propulsion assembly equipped with a thrust-reversing device comprising at least one inflatable barrier, and aircraft comprising at least one such propulsion assembly

A bypass turbofan with a nacelle delimiting a stream and including a cowl mobile in translation between an advanced position in which a window is open between the stream and the exterior, transmission systems, each of which includes at least one arm mobile in rotation between retracted and deployed positions across the stream, in which each transmission system is mobile in translation between advanced and retracted positions, for each arm, a flexible veil fastened to the arm and alternately occupying a folded or unfolded position, and, for each transmission system, an actuator configured to move the mobile cowl, the transmission system and each arm.

Bypass turbofan including a system for blocking the secondary flow including veils

A propulsion system for an aircraft, which has a chassis, a propeller able to move in rotation about an axis of rotation, a main gear as one with the propeller, an electric generator, at least one linear electric motor having a fixed element and a slider able to move in translation, for each linear electric motor, a secondary gear meshing with the main gear and mounted to be able to move in rotation about an axis of rotation perpendicular to the axis of rotation, and a rod of which one end is articulated on the corresponding slider and of which the other end is articulated on the corresponding secondary gear at an articulation that is offset with respect to the axis of rotation of the secondary gear.

Aircraft propulsion system having a linear electric motor

An aircraft including a fuselage, a wing structure, at least one turbomachine running on hydrogen and generating thrust at a propulsion unit distant from the fuselage, at least one fuel tank positioned in the fuselage and configured to store hydrogen in the cryogenic state, at least one hydrogen supply device connecting the fuel tank and the turbomachine and including at least one pump positioned in the fuselage in the vicinity of the fuel tank, at least one hydrogen heating system positioned in the fuselage in the vicinity of the pump. This solution makes it possible to reduce a length of the complex double-walled pipes configured for carrying the hydrogen in the cryogenic state between the fuel tank and the hydrogen heating system.

Aircraft comprising a hydrogen supply device incorporating a hydrogen heating system positioned in the fuselage of the aircraft

A turbofan engine with a nacelle and a flow path, in which the nacelle comprises a movable cowl that makes it possible to define a window between the flow path and the outside, veils with a first edge fixed to the movable cowl and alternately assuming a folded position or a deployed position across the flow path, and a pneumatic system displacing a second edge of the veils from the folded position to the deployed position and vice versa. The pneumatic system comprises a rigid main roll, for each veil, at least one extendable secondary roll fixed to a second edge of the veil, and a pressurization and depressurization system which, alternately, generates a pressure or a depression in each secondary roll. Replacing the reverse doors and their driving mechanisms with flexible veils and a pneumatic system allows for a weight reduction.

Turbofan engine comprising a system for blocking the flow path of the bypass stream comprising veils

A ducted fan turbine engine with a nacelle and a duct for a secondary flow. The nacelle comprises a fixed structure. A mobile cowl is able to move between a forward position and a backward position to define an opening between the duct and the outside. A plurality of rollers are mounted to freely rotate on the mobile cowl. For each roller there is a flexible screen with a first edge fixed to the roller and a second edge, in which the screen is able to adopt a furled position, wound around the roller, or a deployed position deployed across the duct. A deployment mechanism is arranged to move each second edge to move the screen from the furled position to the deployed position. A furling mechanism is arranged to drive each roller in rotation to move the associated screen from the deployed position to the furled position.

Ducted fan turbine engine comprising a system involving screens for blocking off the duct for the secondary flow

A turbofan has a nacelle delimiting a duct for a bypass flow and comprises a fixed structure comprising a guide vane support with guide vanes, a mobile cowl able to move in translation between an advanced position and a retracted position, arms, each one being mobile in rotation between a stowed position and a deployed position and comprising a distal end and a proximal end, a flexible screen, of which an exterior edge is attached to the guide vane support rearward of the guide vanes, and wherein the distal end of each arm is fixed along the interior edge, actuators to cause the mobile cowl to move, and an operating system which moves each arm. Replacing the reversal doors and their drive mechanisms with the flexible screen and the set of rotationally-mobile arms allows a reduction in weight.

Turbofan comprising a system comprising a screen for closing off the bypass duct

A turbofan having a nacelle delimiting a duct for a bypass flow and including a fixed structure including a guide vane support with guide vanes, a mobile cowl movable in translation between an advanced position and a retracted position, arms, each one being mobile in rotation on the guide vane support between a stowed position and a deployed position and comprising a distal end and a proximal end, for each pair of adjacent arms, a flexible screen extending angularly between the two arms, and of which an exterior edge is attached to the guide vane support, and wherein the distal end of each arm is fixed along the interior edge, a link rod mounted articulated between the distal ends, actuators to cause the mobile cowl to move, and an operating system which moves each arm. Such an arrangement allows a reduction in weight.

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Toulouse, France

Benjamin Thubert