Airbus Operations Sl

Airbus Operations Gmbh

Maria Almudena Canas Rios

Alberto Arana Hidalgo

Carlos Garcia Nieto

Esteban Martino-Gonzalez

Jesus Javier Vazquez Castro

Elena Arevalo Rodriguez

Melania Sanchez Perez

Fernando Iniesta Lozano

Edouard Menard

Nuria Colmenarejo Matellano

Francisco Jose Cruz-Dominguez

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

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Madrid, Spain

Maria Almudena Canas Rios