Airbus Operations Sl

Airbus Operations Gmbh

Airbus Defence and Space Gmbh

Iker Vélez De Mendizábal Alonso

Francisco Javier Honorato Ruiz

Carlos García Nieto

Jesús Javier Vázquez Castro

Enrique Guinaldo Fernández

Enrique Guinaldo Fernandez

Carlos Garcia Nieto

Soledad Crespo Peña

Francisco Jose Cruz Dominguez

David Apellaniz De La Fuente

Paula Más Más

Esteban Martino-Gonzalez

Esteban Martino González

Álvaro Torres Salas

Alberto Arana Hidalgo

Pablo Cebolla Garrofe

Fernando Pereira Mosqueira

Edouard Menard

Alfonso Parra Rubio

Álvaro Calero Casanova

Vasilis Votsios

Diego Sanchez Franco

Elena Moya Sanz

Alvaro Torres Salas

Guillermo Nicolas Gutierrez

David Matesanz Hidalgo

Jose Angel Hernanz-Manrique

Esteban Martino-Gonzalez-Aranjuez

Carlos Garcïa Nieto

Guillermo Hernáiz López

Diego Lastra Gil

Enrique Guinaldo Fernadez

Soledad Crespo PEÑA

Carlos GARCÍA Nieto

A method for manufacturing the trailing edge ribs and the bearing ribs of trailing edges of aircraft lifting surfaces, in which the trailing edge ribs and the bearing ribs are made by joining simple C-shaped parts and/or simple L-shaped parts so as to obtain the final trailing edge ribs and bearing ribs. The manufacturing of the simple C-shaped parts uses the same tooling both for the trailing edge ribs and the bearing ribs, and the manufacturing of the simple L-shaped parts uses the same tooling both for the trailing edge ribs and the bearing ribs.

Method for manufacturing the trailing edge ribs and the bearing ribs of trailing edges of aircraft lifting surfaces

A three-dimensional auxetic structure, comprising a plurality of adjoining hollow cells, each hollow cell having cell walls and a transversal cross section of the plurality hollow cells following a two-dimensional auxetic pattern, each cell wall comprising folding lines parallel to a plane containing the auxetic pattern such that peaks and valleys are defined in the cell walls and the cell walls being foldable along the folding lines.

Three dimensional auxetic structure, manufacturing method and tooling

A method for manufacturing, layer-upon-layer, an integral composite aeronautical structure, wherein the method comprises: (a) providing an additive manufacturing tool comprising a depositing mold shaping an aerodynamic surface and at least one head configured to be moved over the depositing mold and to deposit fibrous material reinforcement and/or meltable material; (b) depositing fibrous material reinforcement embedded within meltable material onto the depositing mold, at least one layer of a lower aerodynamic face-sheet being built thereby; (c) depositing meltable material onto at least a portion of the outer layer of the lower aerodynamic face-sheet, at least one layer of core structure being built thereby; and (d) depositing fibrous material reinforcement embedded within meltable material onto at least the outer layer of the core structure, at least one layer of an upper aerodynamic face-sheet being built thereby; wherein steps (b), (c) and (d) are performed using Additive Manufacturing technology.

Method for manufacturing an aeronautical structure

An auxetic bi-stable structure that comprises an auxetic curved shell movable between a first and a second stable position, and a rigid element. At least part of the surface of the auxetic curved shell is joined to the rigid element such that the curved shell is movable with respect to the rigid element between the first and second stable positions.

Auxetic bi-stable structure

A deformable auxetic structure for absorbing energy of an impact that comprises a plurality of interconnected adjoining tridimensional auxetic cells where each tridimensional auxetic cell comprises at least one surface element and a plurality of legs extending from the surface, the plurality of legs and the surface element being configured such that the sectional cut of the structure in at least two planes perpendicular to the surface element follows an auxetic pattern.

Deformable auxetic structure and manufacturing process

A lifting device including: a movable discontinuity () located in a surface of the lifting device, the movable discontinuity () being movable between: an active position in which the movable discontinuity () acts as vortex generator, and a passive position in which the movable discontinuity () is integrated into the surface of the lifting surface, a conduit () located in the spanwise direction of the lifting surface and in communication with the movable discontinuity (), the lifting surface including openings () in its surface spanwise distant from each other in communication with the conduit (), the movable discontinuity () and the conduit () being configured such that when an airflow goes through the conduit (), this airflow activates the movable discontinuity () to act as a vortex generator of the lifting surface.

Lifting surface

A lifting surface comprising a movable discontinuity located in the surface of the lifting surface. The movable discontinuity is movable between an active position in which the movable discontinuity acts as vortex generator, and a passive position in which the movable discontinuity is integrated into the surface of the lifting surface without acting as vortex generator. The lifting surface may be in an elevator, the elevator being rotatable around a hinge line with respect to the rest of the lifting surface. A bar is rigidly joined to the elevator. The bar, the elevator and the movable discontinuity are configured such that when the elevator rotates with respect to the rest of the lifting surface, the bar moves the movable discontinuity that departs from the surface of the lifting surface, acting as a vortex generator.

A modular mold for producing a panel including a panel of fiber reinforced material. The panel is configured to form hollow cells having an undulated trapezoidal cross-section. The mold includes at least three molding bars for forming each hollow cell. One of the molding bars has a trapezoidal cross shape. The other two molding bars have a triangular cross shape. The trapezoidal molding bar is located between the two triangular molding bars. The three molding bars when put together its cross-section forms the shape of the trapezoidal cross-section of the hollow cell.

Modular mold and method for manufacturing a panel of fiber reinforced material

An aircraft aerodynamic surface () including a torsion box () having a front spar () and rear spar (), a first control surface () including a front spar () and a trailing edge () and a second control surface () having a front spar (), a trailing edge (), and a pivot device () for pivotally attaching the first control surface () and the second control surface () to the rear spar () of the torsion box (), the first control surface is an inboard control surface () including two lateral ribs ('), six inner ribs () and an inner spar (), and the second control surface () is an outboard control surface which includes two lateral ribs (&#x2032;), three internal ribs (), two internal spars (&#x2032;) and one internal spar ().

Aircraft empennage

A lightweight shield for aircraft protection against threat of high energy impacts, which comprises, a structural layer that has a first side and a second side, the first side being intended for receiving the impact, and a ballistic material layer for absorbing high energy impacts, having a first side and a second side. The first side of the ballistic material layer is faced to the second side of structural layer and joined to the structural layer via a progressively detachable interface and, the second side of the ballistic material layer is a free surface.

Integrated detachable ballistic shield

This disclosure relates to the manufacturing of a leading edge section with hybrid laminar flow control for an aircraft. A manufacturing method involves: providing an outer hood, a plurality of elongated modules, first and second C-shaped profiles having comprising cavities, and an inner mandrel; assembling an injection molding tool by placing each profile on each end of the inner mandrel, arranging a first extreme of each elongated module in one cavity of the first profile and a second extreme of the module in another cavity of the second profile, both cavities positioned in the same radial direction; and placing the hood on first and second profiles to close the tool. Further, the injection molding tool is closed and filled with an injection compound comprising thermoplastic and short-fiber. Finally, the compound is hardened and demolded.

Method, injection moulding tool for manufacturing a leading edge section with hybrid laminar flow control for an aircraft, and leading edge section with hybrid laminar flow control obtained thereof

An aircraft lifting surface with a main supporting structure comprising upper and lower faces defining its aerodynamic profile, front and rear faces oriented towards, respectively, the leading and trailing edges, a first set of transverse ribs extended from the front face to the rear face and a second set of transverse ribs crossing the front face and/or the rear face. The integration of leading and trailing edge ribs in the main supporting structure allows a weight and cost reduction of aircraft lifting surfaces. A manufacturing method of said main supporting structure is also disclosed.

Main supporting structure of an aircraft lifting surface

An aircraft lifting surface with a monolithic main supporting structure of a composite material including an upper skin having at least a part of the upper aerodynamic profile of the leading edge and/or of the trailing edge, a lower skin, a front spar, a rear spar, and leading edge ribs and/or a trailing edge ribs. The main supporting structure allows a weight and cost reduction of aircraft lifting surfaces.

Highly integrated structure including leading and trailing edge ribs for an aircraft lifting surface

An aircraft lifting surface with a torsion box of a composite material including an upper skin, a lower skin, a front spar, a rear spar, one or more intermediate spars and transverse ribs arranged between the rear spar and an adjacent intermediate spar and/or between the front spar and the adjacent intermediate spar.

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Getafe, Spain

Iker Vélez De Mendizábal Alonso