Airbus Operations Sl

Airbus Operations Gmbh

Edouard Menard

Fernando Iniesta Lozano

Carlos Garcia Nieto

Alberto Arana Hidalgo

Esteban Martino-Gonzalez

Jesus Javier Vazquez Castro

Melania Sanchez Perez

Maria Almudena Canas Rios

Esteban Martino González

Iker Vélez De Mendizábal Alonso

Carlos García Nieto

Enrique Guinaldo Fernández

Jesús Javier Vázquez Castro

Soledad Crespo Peña

Carlos GARCÍA Nieto

Iker VÉLEZ De MENDIZÁBAL Alonso

Soledad Crespo PEÑA

Enrique Guinaldo Fernàndez

Jesús Javier VÁZQUEZ Castro

Esteban Martino GONZÁLEZ

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 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 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

An impact resistant fuselage of an aircraft, the fuselage extending along a central longitudinal direction, wherein transversal sections of the fuselage are comprised in a vertical plane perpendicular to the central longitudinal direction. The impact resistant fuselage comprises at least a ballistic material membrane extended along the longitudinal direction for absorbing high energy impacts. The membrane according to a transversal section, comprising at least one section between two tensional elements, wherein the material membrane is located inside the fuselage of the aircraft, the at least one section of the membrane is mechanically linked to the inside of the fuselage by the tensional elements, and the two tensional elements stress the membrane.

Impact resistant fuselage

An impact resistant dorsal fin structure of an aircraft comprises an upper support and ballistic material layer, wherein the ballistic material layer is configured to be joined to an aircraft fuselage and the ballistic material layer is arranged in a sliding manner around a sliding surface of the upper support.

Impact resistant dorsal fin

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

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Getafe, Spain

Edouard Menard