Airbus Operations Sl

Airbus Operations Gmbh

Francisco Javier Honorato Ruiz

Enrique Guinaldo Fernandez

Iker Vélez De Mendizábal Alonso

Carlos Garcia Nieto

Carlos García Nieto

Pablo Cebolla Garrofe

Francisco Jose Cruz Dominguez

Enrique Guinaldo Fernández

Fernando Pereira Mosqueira

Soledad Crespo Peña

Álvaro Calero Casanova

Paula Más Más

Diego García Martín

Jesús Javier Vázquez Castro

Andrea Ivan Marasco

Francisco José Cruz Dominguez

Álvaro Torres Salas

Iker Vélez De Mendizabal Alonso

Alberto Arana Hidalgo

Aquilino García García

Jorge Juan Galiana Blanco

Alfonso Parra Rubio

Francisco Javier Chamorro Alonso

Alfonso González Gozalbo

René Schröder

Vasilis Votsios

Francisco José Cruz Domínguez

Angel García Sacristán

Carlos Romón Banogon

Alberto Gallegos Elvira

Luis Rodriguez Urbina

Eugenio Piñeyroa De La Fuente

Diego Sanchez Franco

Alvaro Torres Salas

Julio Núñez Delgado

Carlos Garcïa Nieto

María Muruzabal Sopelana

Eduardo González Hernando

Ángel Pascual Fuertes

Carlos Delgado Alcojor

José Francisco Alonso Rodríguez

Guillermo Hernáiz López

Diego Lastra Gil

Hugo Casado Abarquero

Enrique Guinaldo Fernadez

Jorge Martin Beato

ÁLvaro Torres Salas

Soledad Crespo PEÑA

Francisco Jose Cruz Domínguez

Aquilino GARCÍA GARCÍA

Iker VÉLEZ De Mendizabal Alonso

Carlos GARCÍA Nieto

Enrique Guinaldo FERNÁNDEZ

Francisco José Cruz DOMÍNGUEZ

Francisco Cruz Domínguez

Iker Vélez De Mendizàbal Alonso

Paula Màs Màs

Enrique Guinaldo Fernàndez

ÁLvaro Calero Casanova

David MARTÍN Palomares

Iker VÉLEZ De MENDIZÁBAL Alonso

Eduardo GONZÁLEZ Hernando

Eugenio PIÑEYROA De La Fuente

José Francisco Alonso RODRÍGUEZ

ÁNgel Pascual Fuertes

Alfonso GONZÁLEZ Gozalbo

Guillermo HERNÁIZ LÓPEZ

Luis Manuel Rodriguez Urbina

Diego GARCÍA MARTÍN

Jesús Javier VÁZQUEZ Castro

An aircraft empennage includes a vertical tail plane, a rear fuselage section attached to the vertical tail plane and including a skin and internal reinforcing members, a horizontal tail plane comprising two lateral torsion boxes and a framework located between the two lateral torsion boxes comprising a front spar, a rear spar and two ribs extending between the front and the rear spar and each adjacent to a lateral torsion box. The framework encloses a portion of the vertical tail plane along its spanwise direction. The aircraft empennage includes an attachment assembly attaching the framework to the rear fuselage section, the attachment assembly crossing the skin and extends between the internal reinforcing members of the rear fuselage section and the framework.

Aircraft empennage with a horizontal stabilizer interfacing at the vertical stabilizer root

Tooling for manufacturing multi-spar torsion boxes with different web heights, the tooling includes a mandrel module having a hollow beam geometry which comprises a first base and a second base opposite to the first base, and two walls extending between said first base and said second base, and at least one spacer module configured for coupling with the mandrel module, wherein the web height of a multi-spar torsion box is defined by the coupling between the mandrel module and at least one spacer module. A method for manufacturing multi-spar torsion boxes with different web heights.

Modular tooling for multi-spar torsion box

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 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

A composite structure () for an aircraft, having at least one insert () for receiving attachment devices, each insert () includes a core () having a major dimension and containing at least one through-hole (), and a composite strip arrangement formed by a first section () surrounding the core () and attached to said core () by an adhesive polymeric layer, and a second section () including at least one free end (). The first () and the second portion () of the composite strip arrangement are disposed over a first surface () of the composite structure (), such that the major dimension of the core () is positioned transversal to said first surface (a). The at least one insert () is co-cured with the composite structure ().

Composite structure having an integrated support

A tip structure for an aircraft airfoil, such as a control surface (ailerons, flaps, elevators, rudders, etc) and/or a lifting surface (wings, HTP's, VTP's) is a unitary body and includes a tip shell and a metallic material on the outer surface of the tip shell suitable to withstand a lighting strike. The tip shell has been obtained by a single-stage injection molding process using a thermoplastic composite material having fibers dispersed therein, and the metallic material has been integrally formed with the tip shell.

Thermoplastic moulded injected tip structure for an aircraft

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 leading edge section with laminar flow control includes: a perforated outer skin, a perforated inner skin, and a plurality of suction chambers formed between the outer skin and the inner skin. The leading edge section includes a plurality of stringers span-wise arranged at the leading edge section, and integrally formed with the outer skin, such that the inner skin is joined to the stringers. A method for manufacturing a leading edge section integrating a laminar flow control system is described, wherein a perforated inner skin is joined with a perforated outer skin having a plurality of stringers integrally formed with the outer skin, such that suction chambers are defined by a part of the outer skin, a part of the inner skin and a pair of stringers.

Leading edge with laminar flow control and manufacturing method thereof

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

A structure of a control surface for aircrafts, such as elevators, rudders, landing flaps, ailerons, and other similar lifting surfaces. The control surface includes a front spar, a rear spar, a plurality of ribs, at least one hinge fitting, and at least one actuator fitting, the hinge and actuator fittings joined with the front spar. A first rib is joined with a hinge fitting to form a first oblique angle with the front spar; a second rib is joined with an actuator fitting to form a second oblique angle with the front spar. The rear spar, located between the front spar and trailing edge of the control surface, extends only between the second rib and an outboard end of the control surface. The ribs are located in correspondence with the main torsion and bending load paths created in the control surface during flight, landing or takeoff.

Aircraft control surface

A method for manufacturing a monolithic torsion box inner structure of an aircraft lifting surface including: a) providing a set of laminated preforms of a composite material for forming said torsion box inner structure, each laminated preform being configured for constituting a part of one component of the torsion box inner structure; b) arranging the laminated preforms in a curing tooling and subjecting the assembly to an autoclave cycle to co-cure the said laminated preforms; c) demoulding the curing tooling in a vertical direction.

Highly integrated inner structure of a torsion box of an aircraft lifting surface

Method for manufacturing a base structure () of an aeronautical torsion box () for an aircraft () characterized in that it comprises the steps of:

Method for manufacturing an aeronautical torsion box, torsion box and tool for manufacturing an aeronautical torsion box

The invention refers to a composite structure for an aircraft comprising a panel and at least one stringer joined to a surface of the skin panel, the stringer having a foot and a web protruding from the foot, and a run-out section at one of its ends. The panel includes a plurality of stacked and co-cured plies of composite material, and at least part of the foot of the stringer at the run-out section, is inserted between two plies of the panel, and it is co-bonded, co-cured or secondary bonded with said two plies. The structure of the invention provides a reinforced join between the foot of the stringer and the skin panel, avoiding peeling or de-bonding problems, without substantially modifying the manufacturing process.

Composite structure for an aircraft and manufacturing method 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

Growing community of inventors

Getafe, Spain

Francisco Javier Honorato Ruiz