Airbus Operations (s.a.s.)

Airbus Operations Sl

Other

Airbus Operations Gmbh

Julien Guillemaut

Jérôme Colmagro

Guillaume Gallant

Jonathan Blanc

Esteban Martino Gonzalez

Diego Folch Cortes

Pablo Goya Abaurrea

Denis Soula

Dominique Guittard

Jean Marc Durand

Philippe Blot

Enrique Guinaldo Fernandez

Eric Bouchet

Esteban Martino González

Arnaud Hormiere

Pascal Pome

Thomas Robiglio

Diego Folch Cortés

César Garnier

François Loyant

Frédéric Fort

Ludovic Fournie

Angel Pascual Fuertes

Eduardo Vinue Santolalla

Thomas Le Hetet

Sandra Linares Mendoza

Eduardo Vinué Santolalla

Sébastien Alby

Jerome Colmargo

Jean Pierre Cabanac

Aurelie Piat

Tobias Sjostrom

Jerome Comagro

In order to reduce engine deformation, the subject matter disclosed herein provides an assembly for an aircraft, comprising an aircraft rear section, an engine, a nacelle, and a mounting strut for mounting the engine on the rear section, the assembly also comprising mounting for mounting the engine on a rigid structure of the strut, the mounting comprising two engine mounts designed to react the axial thrust forces generated by the engine. According to the subject matter disclosed herein, the rigid structure of the strut comprises a first portion partially enveloping the engine, this first portion comprising an external skin forming part of an external aerodynamic surface of the nacelle, and the two engine mounts are arranged diametrically opposite each other at the rear of the rigid structure, being attached to the first portion.

Aircraft assembly comprising a mounting strut built into the nacelle and arranged at the rear section of the fuselage

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

A propeller for a turbomachine intended to be driven in rotation about a propeller rotation axis and including variable pitch blades. The propeller further includes a structure for radial retention of the blades in the event of them breaking. The retaining structure extends around the propeller rotation axis and has the aerodynamic part of each blade of the propeller pass through it. Moreover, each aerodynamic part is equipped with an abutment configured to be retained radially by the retaining structure in the event of a blade fracture causing a fracture in the aerodynamic part radially inside the abutment.

Propeller for an aircraft turbomachine, including a blade retaining structure through which the aerodynamic part of each blade passes

The invention relates to a fish joint device intended to attach securely first and second structural elements of an aircraft to one another, having two fishplates positioned either side of the structural elements, and attached to them by a set of fishplate through fastenings. According to the invention, the fish joint device includes at least one intermediate fish joint plate which is positioned between one of said fishplates and said structural elements which said intermediate plate partly covers, and which is attached to these elements by a set of intermediate plate through fastenings which includes the set of fishplate through fastenings.

Fish joint device having an improved mechanical hold

An air ejection device comprises an aerodynamic profile provided with a slot and an ejection nozzle. The device comprises a flexible tongue fixed flush with the aerodynamic profile in such a way as to obstruct the slot, the tongue being able to lift under the effect of a pressure differential between the air situated in the ejection nozzle and the outside air. The tongue makes it possible for the slot made in the profile to be obstructed during phases of flight during which the ejection of the air is unnecessary, and prevents external air from entering the slot. The flow of air over the aerodynamic profile is unaffected, and there is no increase in drag. Because the tongue lifts as a result of a pressure differential, it does not require any control mechanism to lift it.

Air ejection device comprising an aerodynamic profile provided with a slot obturating flexible tongue

In the case of an aircraft aft portion equipped with an engine mounting structure passing across the fuselage, assembly of the aft portion presents problems caused by the moving of the box structure of the mounting structure through lateral openings in the fuselage. In order to overcome these problems, a method of assembling an aircraft aft portion is proposed, in which method the box structure of the engine mounting structure is inserted into the fuselage through a top opening extending from one side of the fuselage to the other across a vertical midplane of the fuselage such that the top opening opens to the top and to the sides of the fuselage.

Method for assembling an aircraft aft portion

The link for an aircraft comprises at least two portions respectively made of metal and of composite material together forming a common section of a middle segment of the link in a plane perpendicular to a longitudinal direction of the link.

Aircraft comprising a link rod one part of which is made of composite

Internal shield in the rear fuselage of an aircraft having a propulsion system formed by two engines mounted on each side of it; the rear fuselage having at least a vertical symmetry plane; the rear fuselage being made of a composite material; the internal shield being located in said vertical symmetry plane and extended in an area that covers the possible trajectories of a set of pre-defined fragments detached from one of said engines in a failure event that would impact on critical elements of the opposite engine; the internal shield having a flat shape and an energy absorption capability that allows stopping said fragments. The invention also refers to a method for determining the area of an internal shield and to an aircraft having said internal shield.

Aircraft with fuselage-mounted engines and an internal shield

A method for producing a central wing box having an upper panel, a lower panel, a front spar and a rear spar, the upper edges of said spars approximately parallel to an axis Y being connected by the upper panel, and the lower edges of said spars approximately parallel to the axis Y being connected by the lower panel. The method includes producing at least one panel and at least one spar from composite material in one piece.

Method for producing a central wing box

The stiffening frames () of an aircraft fuselage () remain continuous while passing through an upper panel () of the wing box and extend over the ribs () situated in that box. The overall mechanical strength of the assembly is improved, despite the notches it is necessary to make in the panel ().

Connector for stiffening frames between an aircraft fuselage and a wing box

A composite structural member with fiber reinforcement comprising a plurality of layers oriented relative to a longitudinal direction of said member in directions including 0&#xb0;, 90&#xb0; and +/&#x2212;&#x3b8;, the relative proportion of layers in one of these orientations being variable along a transverse direction of said member so as to spatially adjust the rigidity of the member according to a defined distribution of mechanical stresses along this transverse axis. The rigidity of the member is adapted locally to the stress system so as to dissipate the force flux over the entire volume of said member.

Composite structural member with progressive rigidity

The invention seeks to improve the integrity in respect of tolerance to damage following the spread of cracks in failure-mitigating structures of the failsafe type. To do this, the invention proposes to form a composite hybrid structure within the failure-mitigating structure. A failure-mitigating mainframe, particularly of an aircraft fuselage, equipped with a structural element made of composite according to the invention, has profiled longitudinal structural components assembled back to back by fasteners. First sides are longitudinally aligned and bonded to the fuselage skin, and the other sides are longitudinally aligned some distance away from the first sides. Fasteners couple the composite structural element to the external face of the sides of the metal components that are longitudinally aligned some distance away from the first sides.

Method of slowing the propagation of cracks in a fail safe structure and fail safe frame, especially for fuselage

Aircraft fuselage section () subjected to impacts of external bodies, the aircraft fuselage having a curved shape with at least a vertical symmetry plane (A-A) and a central longitudinal axis and comprising a skin () and a plurality of frames () arranged perpendicularly to said longitudinal axis (), the aircraft fuselage section also comprising at least an inner reticular structure () mounted on a supporting structure () comprising longitudinal beams () attached to the skin () and interconnected with said frames (), said inner reticular structure () being arranged for creating at least one closed cell () with the skin () for improving its resistance and its damage tolerance to said impacts. Said inner reticular structure () can be formed by panels (), rods (65, 65'), cables (67, 67&#x2032;) or belts (69, 69&#x2032;).

Impact resistant and damage tolerant aircraft fuselage

An aircraft structure includes a wing spar (), with orbital frames () arranged in transverse planes, right and left horizontal spars () connected to the wing spar () at the upper panel () of the spar respectively to the right and to the left of the spar, and for each right or left horizontal spar (), a triangular panel () that includes a wall (), a first edge arranged at the horizontal spar (), a second side arranged at the wing spar (), and a third side at which a first rectilinear oblique reinforcement () connecting the horizontal spar () and the wing spar () is provided, characterized in that the triangular panel () includes at least one second rectilinear oblique reinforcement () that connects the horizontal spar () and the wing spar ().

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Toulouse, France

Julien Guillemaut