Airbus Operations Sl

Airbus Operations Gmbh

Pablo Cebolla Garrofe

Francisco Javier Honorato Ruiz

Álvaro Calero Casanova

Enrique Guinaldo Fernandez

Iker Vélez De Mendizábal Alonso

Alberto Arana Hidalgo

Esteban Martino González

Carlos García Nieto

Enrique Guinaldo Fernández

Jesús Javier Vázquez Castro

Diego García Martín

Soledad Crespo Peña

Francisco Javier Chamorro Alonso

Álvaro Torres Salas

Iker Vélez De Mendizabal Alonso

Carlos Romón Banogon

Aquilino Garcia Garcia

Jorge Juan Galiana Blanco

Aquilino García García

David Alfonso Cerezo Arce

Ignacio José Márquez López

Alvaro Torres Salas

Lara Barroso Fernandez

Carlos Garcïa Nieto

Julio Núñez Delgado

Lara Barroso Fernández

Felix Dominguez Escauriaza

Alejandro Fernandez Alonso

Soledad Crespo PEÑA

Aquilino GARCÍA GARCÍA

Ignacio José Marquez Lopez

Iker VÉLEZ De Mendizabal Alonso

Carlos GARCÍA Nieto

Enrique Guinaldo FERNÁNDEZ

Félix Domínguez Escauriaza

Alejandro Fernández Alonso

David MARTÍN Palomares

Francisco José Cruz DOMÍNGUEZ

ÁLvaro Calero Casanova

ÁLvaro Torres Salas

A method for forming fiber composite preforms, the preform () include a web (), a flange () and a bent part (), and the method includes: laying-up a laminate () onto a tooling (), the laminate () comprising lateral and transverse edges () and the tooling () comprising a male part () comprising a surface () and a lateral wall (), the web () being configured to be located over the surface () of the male part () and the flange () being configured to be located over the lateral wall () of the male part (); forming the preform () over the male part (); clamping the lateral edges () of the laminate () to the tooling () such that the web () and the flange () of the laid-up laminate () are kept under tensional loads, and bending a longitudinal portion of the male part ().

Method for forming fiber composite preforms

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

A hybrid tool for curing composite structures for aircrafts, such as stringers, torsion boxes, skin panels, wing surfaces, horizontal tail or vertical stabilizers, etc. The hybrid tool comprises a metallic portion and an elastic portion arranged on a surface of the metallic portion. The elastic portion and the metallic portion are permanently joined to each other so that the metallic portion and the elastic portion together define a surface having a shape which copies at least part of a surface of a piece of composite material to be cured. The tool is capable of satisfactorily curing pieces of composite material which have a minimum thickness and/or a very aggressive change of thickness.

Hybrid tool for curing pieces of composite material

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 method for manufacturing a composite part of an aircraft comprising the steps of placing a prepreg preform in a molding die between at least a molding die base part and a molding die upper part, debulking the air trapped in the prepreg, displacing the molding die upper part against the molding die base part in a direction perpendicular to the plane of the prepreg preform such that the molding die upper part presses the laminated perform until it reaches a blocking arrangement defining the position of the upper part relative to the base part for giving the prepreg preform the nominal thickness of the cured part, wherein said displacement is achieved by bolting the different parts of the molding die against each other, providing an elevated temperature to the preform such that it is cured.

Method and device for manufacturing a composite part of an aircraft

Highly integrated infused box made of composite material with two skins (), several ribs (), several stringers (), a front spar and a rear spar, comprising a first semibox () and a second semibox () joined by connecting means, in which the first semibox () comprises one skin () and the ribs (), and the second semibox () comprises one skin (), the front spar, the rear spar and the stringers (). A manufacturing method is also provided, which comprises forming processes for the first semibox (), the second semibox () and an assembly process of the first semibox () with the second semibox ().

Highly integrated infused box made of composite material and method of manufacturing

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

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Getafe, Spain

Pablo Cebolla Garrofe