Airbus Operations Sl

Airbus Defence and Space S.a.

Soledad Crespo Peña

Carlos García Nieto

Enrique Guinaldo Fernández

Iker Vélez De Mendizábal Alonso

Álvaro Torres Salas

Francisco Javier Honorato Ruiz

Jesús Javier Vázquez Castro

Pablo Cebolla Garrofe

Álvaro Calero Casanova

Iker Vélez De Mendizabal Alonso

Enrique Guinaldo Fernandez

Carlos Garcia Nieto

Esteban Martino González

Jesus Javier Vazquez Castro

Edouard Menard

Alvaro Torres Salas

Carlos Garcïa Nieto

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 configuration and manufacturing method for a trailing edge of an aircraft airfoil, such as a control surface or a lifting surface is described. The trailing edge is formed and configured by upper and lower composite covers, which are stitched to each other with a metallic wire, such as the metallic wire is electrically in contact with upper and lower metallic meshes to provide electrical continuity between meshes. According to a method, upper and lower covers configuring the trailing edge, are stitched with the metallic wire before curing the covers, so that the metallic wire gets embedded within the composite material. A trailing edge for an aircraft airfoil, which is easy to manufacture and that at the same time fulfills aerodynamic, mechanical and electrical conductivity requirements is described.

Aircraft airfoil having a stitched trailing edge and manufacturing method thereof

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 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

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

Disclosed is a multi-spar torsion box structure comprising a plurality of spars of composite material arranged to form a multi-cell structure with two or more cells extending longitudinally along the torsion box, and upper and lower skin covers formed of composite material and joined to upper and lower surfaces of the multi-cell structure, respectively. The structure further comprises at least one belt-like reinforcing element extending around the outer perimeter of the torsion box, and fixed to the upper and lower surfaces of the multi-cell structure, and transversely arranged with respect to the longitudinal direction of the torsion box. The belt-like reinforcing element is made of a metallic or a composite material. The disclosed torsion box can advantageously be used in the manufacture of aircraft lifting surfaces, such as horizontal tailplanes (HTP) or wings.

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Getafe, Spain

Soledad Crespo Peña