Airbus Operations (s.a.s.)

Airbus France

Airbus Operations Sl

Airbus Operations Gmbh

Eric Bouchet

Jérôme Colmagro

Frederic Journade

Frédéric Vinches

Olivier Barbara

Lionel Juillen

Benjamin Mahieu

Olivier Pautis

Julien Guillemaut

Jonathan Blanc

Esteban Martino Gonzalez

Diego Folch Cortes

Denis Soula

Esteban Martino González

Pablo Goya Abaurrea

Frédéric Journade

Pascal Pome

Angel Pascual Fuertes

Romain Terral

Gerard Coudouent

Rohan Nanda

Jerome Puech

Nicolas Grosseau

Sandra Linares Mendoza

Michel Salaun

Jacques Huet

Konan Koffi

Bogdan Sina

Sylvain Cros

Cyrielle Rogeron

Celine Gallet

Michel Garcia

Antoine Mutin

Mélaine Chaix

Anais Markowski

Misael Hernandez Perez

Marie Elduayen

Sandra Liñares Mendoza

Diego Folch CORTÉS

ÁNgel Pascual Fuertes

Julien Gillemaut

Anaïs Markowski

Benjamin Mathieu

An aircraft engine assembly has a front engine mount connecting an engine and a primary structure of a pylon comprising at least one front rod having at least three front link points. A first front link point is configured to connect the front rod and the front end of the primary structure. A second front link point is configured to connect the front rod and the core of the engine. A third front link point is configured to connect the front rod and the engine core and is offset relative to the second front link point in a horizontal transverse direction. The first front link point of the front engine mount is separated from the rotation axis of the engine by a distance greater than an exterior radius of the rear casing of the core of the engine at the rear link point of the rear engine mount.

Aircraft engine assembly

An aircraft which comprises a fuselage and at least one propulsion assembly linked to the fuselage by at least two connecting rods positioned at least partially in an inner zone of the air inlet of the nacelle of the propulsion assembly. Thus, the connecting rods do not interfere with the secondary flow flowing inside the nacelle and do not affect the aerodynamic performance levels of the propulsion assembly.

Aircraft comprising at least one engine assembly linked to the fuselage of the aircraft by two connecting rods positioned at least partially in an air inlet of the engine assembly

To bring a pylon box of an aircraft engine attachment pylon as close as possible to a wing box, two lateral front fasteners are provided. Each of the fasteners comprises a clevis secured to the wing box, the clevis comprising two webs, at least one of which passes through an upper spar of the box, the upper part of one of the two opposite lateral flanges of a lower transverse rib of the box reinforcement, the upper part of an associated lateral panel, and a pin system passing through the clevis and the two upper parts.

Assembly for aircraft, comprising a primary attachment-pylon structure fixed to a wing box by fasteners partially embedded in the primary structure

An aircraft strut includes a primary structure which includes: a top stringer, a bottom stringer, at least one transverse frame which links the top stringer to the bottom stringer, a front end wall which links a front end of the top stringer to a front end of the bottom stringer, a rear end wall which links a rear end of the top stringer to a rear end of the bottom stringer, two lateral frames arranged on either side of the transverse frame, each lateral frame having a lattice form. An aircraft includes at least one strut described herein.

Aircraft strut comprising at least one lateral frame in lattice form and aircraft comprising said strut

To allow the attachment of an engine of the 'Open Rotor Puller' type to the rigid structure of an attachment pylon, an attachment structure comprises a first attachment structure shifted forwards with respect to the center of gravity of the engine and connected to the rigid structure through a pyramid, a second attachment structure laid out at the rear with respect to the first attachment structure and extending in a plane of a first stringer of the rigid structure, and a third attachment structure laid out at the rear with respect to the second attachment structure. The second attachment structure comprises two engine attachments for recovering the moment along the axis of the engine, laid out on either side of a horizontal symmetry plane of the engine.

Assembly for an aircraft comprising an engine of the 'open rotor puller' type and means for attaching the latter to the rigid structure of an attachment pylon

An aircraft engine pylon includes two side panels and an upper stringer and a lower stringer assembled to form a strut assembly extending in a longitudinal direction (AX) corresponding to the direction in which the aircraft is moving and an internal reinforcement structure including a plurality of reinforcements. The pylon also includes a reinforcement zone on each side panel and a front housing to receive a main front center reinforcement and a rear housing to receive a main rear center reinforcement.

Aircraft engine pylon

An aircraft engine mount which comprises first and second parts connected by connecting elements and wherein one of the two connected parts comprises at least one transverse hole opening onto an access face of the part and into which there open at least two passage holes each intended to house a threaded shank of one of the connecting elements. The engine mount comprises a transverse nut which comprises at least two bodies joined together each having a tapped hole configured to engage with one of the threaded shanks.

Aircraft engine mount comprising at least one transverse nut and aircraft comprising the said engine mount

An aircraft fuselage frame including a central element adapted to be located within the perimeter of the fuselage, and two lateral extensions projecting outside the perimeter of the fuselage from both sides of the central element that are a portion of a longitudinal structure of a lifting surface. The central element and the two lateral extensions are configured as an integrated piece.

Aircraft fuselage frame

The invention relates to a structural frame made from a composite material. The purpose of the invention is to obtain a structural frame with high mechanical performances while remaining simple in construction. This purpose is achieved in arranging sets of single-directional fibers in the main part of the structural frame at a predetermined angle. This system may be used as a structural frame particularly for an aircraft fuselage.

Structural frame made of a composite material and aircraft fuselage comprising such a frame

The subject of the disclosed embodiments is a method of optimizing stiffened panels under stress. In particular, the method makes it possible to determine the stress distribution in stiffened panels with postbuckling taken into account. The method proposed is a coupling between an overall, linear stress calculation approach, based on strength-of-materials results, and a local, nonlinear approach for the behavior of the stiffened panel. The disclosed embodiments fall within the field of aeronautical design, at the pilot study stage in the definition of a civil transport airplane of conventional architecture.

Method of optimizing stiffened panels under stress

A partition for an aircraft is designed to separate a cargo part from a cockpit or a passenger compartment of this aircraft. The partition includes a cellular central structure in contact with a first external wall and a second external wall of this partition. The partition also includes several stiffener elements added onto at least one of the first and second external walls. The invention also relates to an aircraft including at least one such partition.

Aircraft partition designed to separate a cargo part from a cockpit or from a passenger compartment

An aircraft includes a partition designed to separate a cargo part from a cockpit or a passenger compartment. The partition includes a corrugated structure, defining several corrugations with an approximately omega section extending along the direction of the height of the partition. The partition also includes one or several stiffener elements.

Optimized method for assembling two substantially planar parts

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Aussonne, France

Eric Bouchet