Airbus Operations Sl

Airbus Operations Gmbh

Alberto Arana Hidalgo

Jesus Javier Vazquez Castro

Carlos Garcia Nieto

Esteban Martino-Gonzalez

Francisco Javier Honorato Ruiz

Iker Vélez De Mendizábal Alonso

Esteban Martino González

Fernando Iniesta Lozano

Melania Sanchez Perez

Carlos García Nieto

Jesús Javier Vázquez Castro

Pablo Cebolla Garrofe

Enrique Guinaldo Fernández

Pedro Nogueroles Viñes

Edouard Menard

Maria Almudena Canas Rios

Guillermo Hernaiz Lopez

Jorge Ballestero Méndez

Ignacio Outon Hernández

Manuel Kempf

Juan Zúñiga Sagredo

Luis Rodriguez Urbina

Pedro Nogueroles Vines

Raúl Carlos Llamas Sandín

Pablo Vazquez Sanchez

Asuncion Butragueno-Martinez

Tomas Rodriguez Hernandez

Julio Núñez Delgado

Guillermo Hernáiz López

Emilio José Gutiérrez Santos

Diego Lastra Gil

Jorge Ballestero Mendez

Javier Guerrero Martín

Jesús Javier VÁZQUEZ Castro

Jesus Javier Vazquez De Castro

Asuncion BUTRAGUEÑO Martinez

Guillermo HERNÁIZ LÓPEZ

Carlos GARCÍA Nieto

Iker VÉLEZ De MENDIZÁBAL Alonso

José Luis MARTÍNEZ MUÑOZ

David MARTÍN Palomares

Francisco José Cruz DOMÍNGUEZ

Luis Manuel Rodriguez Urbina

Enrique Guinaldo Fernàndez

Tomás Rodríguez Hernández

A device () and a method for manufacturing composite parts such as aircraft bulkheads (), in which a component of the composite part is placed on a first mold () with a robotic device (), a component of another composite part is placed on a second mold () with a robotic device (), the second mold () having a surface identical to the surface the first mold (), and the first mold and the second mold being mounted on a frame in a central symmetric arrangement around a symmetry central point (), such that components are placed on the molds () symmetrically so as to obtain two identical composite parts at the same time.

Device and method for manufacturing composite parts for an aircraft bulkhead

A fireproof and thermal insulator product () including an Alkaline Earth Silicate (AES) material (), and at least one of the following: a liquid barrier film (), an FRP (Fiber Reinforcement Plastic) layer (), cork (), wherein the liquid barrier film () and the FRP layer () are staked onto the AES material (), and wherein the cork () material is also staked onto the AES material () or embedded into said AES material () in where said cork () is configured as a plurality of strips performing a grid structure infilled with the AES material ().

Fireproof and thermal insulator product

A method for manufacturing a composite assembly with a continuous skin for a rear end of an aircraft by obtaining an upper part of the rear end by composite tooling. The upper part comprises a multi-spar vertical tail plane. The spars of the vertical tail plane comprise widening roots that form an upper shell of the rear end and an upper skin. Furthermore, a lower part comprises a lower shell of the rear end including semi-complete frames and stringers and a lower skin. The upper and lower parts are assembled with a joining procedure. The upper and lower skins are joined to obtain the composite assembly with the continuous skin.

Method for manufacturing a multi-spar box with a continuous skin upper shell of a tail cone section for a rear end of an aircraft and a composite assembly

A method for manufacturing an aircraft rear section including a tail cone and a vertical tail plane, the method includes: providing pre-cured frames () each of which includes a section of the tail cone () and a section of the vertical tail plane (); providing pre-cured stringers (); placing the pre-cured stringers () each in respective positions within the pre-cured frames (); placing a skin () around an external surface of the pre-cured frames (); and curing the pre-cured frames (), the pre-cured stringers (), and the skin (), forming the final aircraft rear section.

Method for manufacturing a rear section of an aircraft and aircraft rear section manufactured by said method

A retractable vortex generator system for an aircraft. The system comprises a skin, a slot arranged on the skin, a plate comprising a contour configured for energizing the boundary layer of an air current, and driving means configured for rotating the plate between a first and a second position. In the first position at least part of the contour of the plate protrudes through the slot, and in the second position the plate is retracted within the slot.

Retractable vortex generator system for an aircraft

A method for manufacturing a composite assembly of an empennage and rear-fuselage having a continuous skin solution. The method obtains parts of the sub-structure. For each part, it is obtained a plurality of stringers performs and frames preforms by composite tooling. The frames are transferred to curing frames molds and a sub-structure skin is obtained. Furthermore, the method includes integrating the parts over an integration tool having cavities for locating the curing frames molds and the stringer performs. Furthermore, the method includes co-curing the integration tool in one shot on an autoclave, demolding the sub-structure skin sections and disassembling the curing frame molds to obtain the composite assembly of the rear section.

Method for manufacturing a rear section of an aircraft and aircraft rear section

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 method for manufacturing a composite rear section assembly having a continuous skin solution including obtaining a vertical tail plane tooling that has intermediate tooling for tooling intermediate preforms of a vertical tail plane (), obtaining a fuselage barrel tooling (), (), () and () the fuselage barrel tooling having a cut-out (), (), () and longitudinal cavities (), (), () and (), attaching the vertical tail plane tooling to the fuselage barrel tooling by the cut-out of the fuselage barrel tooling, performing a composite skin lay-up () over the fuselage barrel tooling and the vertical tail plane tooling to obtain a continuous skin, curing the composite skin lay-up, the vertical tail plane tooling and the fuselage barrel tooling and demolding the tools to obtain the composite assembly with a continuous skin (), ().

Composite fuselage assembly and methods to form the assembly

A box structural arrangement () for an aircraft including first () and second composite layers (), at least one spar web () extended between opposite edges of the first and second composite layers () along a longitudinal direction, and a conduit piece () extended between opposite edges of the first and second composite layers (). The conduit piece () has a hollow section () comprising at least one conduit () dimensioned to receive pipes or harnesses and surrounded by a resilient material (). The conduit piece () is mounted on the spar web () to provide a channeled box structural arrangement (). The box structural arrangement can be applicable in a torsion box or a wing. The invention further refers to a method for manufacturing the box structural arrangement for an aircraft.

Box structural arrangement for an aircraft and manufacturing method thereof

A virtual reality (VR) system for providing a real time VR visualization of a target area of an aircraft that comprises one or more reference targets established in known locations in the target area of an aircraft, hand gloves, a plurality of sensing elements established on at least the operator's hand gloves, a reception device that receives the information provided by the sensing elements to provide relative locations of the sensing elements against the one or more reference targets. The reception device comprises processing means to build the real time VR visualization that represents at least the operator's hands against the target area of the aircraft based on the sensing elements. The VR system also comprises display means that display the real time VR visualization to the operator.

Real time virtual reality (VR) system and related methods

A stringer made of composite material for reinforcing aircraft skin panels. Plies are introduced at 90&#xb0; in a segment close to the stringer run-out, and progressively reducing the number of plies at 0&#xb0;, such that the majority of the number of plies is at 90&#xb0; in an segment adjacent to the run-out, so the stiffness of the run-out is reduced, and the load it supports is also therefore reduced. This is an alternative solution to the solutions already existing for getting the stringer run-outs to support a smaller load, thereby reducing both the risk of the plies of the stringer peeling off and the risk of separation between stringer and skin panel. A method of manufacturing said stringer is also provided.

Stringer made of composite material with an elastic run-out and method of manufacturing same

Aircraft component with panels () stiffened with stringers () configured with a central section () and some feet () in which there are zones of potential intersections or interferences of said stringers () with spars () and ribs (), in which the configuration of the ends of the stringers () affected by said intersections or interferences includes a first section () in which the height of the central section () of the stringer () is reduced until it disappears and the width of the feet () is increased until it reaches a predetermined width A and a second section () with some extended feet () of said predetermined width A and no central section (), including in said first section () the mechanical means () for binding the end of the stringer () to the skin (). The invention also relates to a method for manufacturing said panels ().

Aircraft component with panels stiffened with stringers

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Getafe, Spain

Alberto Arana Hidalgo