Airbus Operations Sl

Airbus Operations Gmbh

Carlos García Nieto

Enrique Guinaldo Fernández

Francisco Javier Honorato Ruiz

Iker Vélez De Mendizábal Alonso

Enrique Guinaldo Fernandez

Soledad Crespo Peña

Jesús Javier Vázquez Castro

Álvaro Torres Salas

Iker Vélez De Mendizabal Alonso

Pablo Cebolla Garrofe

Álvaro Calero Casanova

Francisco José Cruz Domínguez

Alberto Arana Hidalgo

Esteban Martino González

Edouard Menard

Vasilis Votsios

Nuria Colmenarejo Matellano

Juan Pablo Juste Mencía

Guillermo Hernáiz López

Alejandro Martínez Cañizares

Diego Lastra Gil

Julio Núñez Delgado

David MARTÍN Palomares

Francisco José Cruz DOMÍNGUEZ

ÁLvaro Calero Casanova

ÁLvaro Torres Salas

Soledad Crespo PEÑA

Iker VÉLEZ De Mendizabal Alonso

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 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 pressure bulkhead for an aircraft comprising a pressurized zone, the pressure bulkhead made of a composite material and comprising a front panel intended to be faced towards the pressurized zone; and a rear panel, substantially parallel to the front panel and intended to be located farther from the pressurized zone than the front panel. The pressure bulkhead further comprises a plurality of longerons located between the front panel and the rear panel, each one of them being attached to the front panel and to the rear panel; and a plurality of stiffeners, some of them being attached to the front panel and a remainder of them being attached to the rear panel.

Pressure bulkhead

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

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.

Growing community of inventors

Getafe, Spain

Carlos García Nieto