Airbus Operations Sl

Alestis Aerospace S.l.

Airbus Operations Gmbh

Álvaro Calero Casanova

Francisco Javier Honorato Ruiz

Pablo Cebolla Garrofe

Soledad Crespo Peña

Carlos García Nieto

Enrique Guinaldo Fernández

Álvaro Torres Salas

Iker Vélez De Mendizabal Alonso

Enrique Guinaldo Fernandez

Iker Vélez De Mendizábal Alonso

Jesus Javier Vazquez Castro

Diego García Martín

Melania Sanchez Perez

David Alfonso Cerezo Arce

Alvaro Torres Salas

Asuncion Butragueno-Martinez

Ana Frutos Muñoz

Maria Del Carmen Aguilar Barroso

Jose Martin Bravo

Carlos Garcïa Nieto

Jesus Javier Vazquez De Castro

Carmen Aguilar Barraso

José PEÑA Guerra

José Cuenca Rincon

Melania Sanchez PÉREZ

ÁLvaro Torres Salas

Soledad Crespo PEÑA

Iker VÉLEZ De Mendizabal Alonso

A method for manufacturing an aeronautical sandwich panel with a honeycomb core and results in a core sealed to prevent infused resin from entering into the honeycomb core open cells while improving its mechanical properties, especially for curved or highly curved panels. In further embodiments, the invention proposes the automation of this process.

Sandwich panel with a honeycomb core and method for manufacturing thereof

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 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

The present disclosure refers to the manufacturing process of an aperture surrounding frame for an aircraft fuselage. The method includes providing a tubular braiding material () with a perimeter equal to the perimeter of the frame to be manufactured, cutting the tubular braiding material () to obtain annular-shaped braiding slices (), providing an annular-shaped inner mold () where the annular-shaped inner mold has a surface with a desired shape for the aperture surrounding frame, layering up at least one braiding slice () around the inner mold (), forming the at least one braiding slice () around the inner mold (), and curing the aperture surrounding frame pre-form. The present disclosure also refers to an aperture surrounding frame () for an aircraft fuselage formed as a continuous body by at least one annular-shaped braiding slice () with a perimeter equal to the perimeter of the desired aperture surrounding frame.

Method, forming and injection tool for manufacturing an aperture surrounding frame for an aircraft fuselage, and frame obtained thereof

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Madrid, Spain

Álvaro Calero Casanova