METHOD FOR MANUFACTURING A REAR SECTION OF AN AIRCRAFT AND AIRCRAFT REAR SECTION MANUFACTURED BY SAID METHOD

Examples herein relate to a method for manufacturing a composite assembly of an empennage and rear-fuselage having a continuous skin solution. The method obtains two or more parts of the sub-structure. For each part, it is obtained a plurality of stringers performs and frames preforms by composite t...

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Bibliographische Detailangaben
Hauptverfasser:	CANAS RIOS, Maria Almudena, GARCIA NIETO, Carlos, MARTINO-GONZALEZ, Esteban, INIESTA LOZANO, Fernando, SANCHEZ PEREZ, Melania, MENARD, Edouard, VAZQUEZ CASTRO, Jesus, Javier, ARANA HIDALGO, Alberto
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AEROPLANES AIRCRAFT AVIATION COSMONAUTICS DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING ORREPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLYADAPTED FOR USE IN CONNECTION WITH AIRCRAFT HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFTCOMPONENTS, NOT OTHERWISE PROVIDED FOR HELICOPTERS PERFORMING OPERATIONS TRANSPORTING
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Beschreibung
Zusammenfassung:	Examples herein relate to a method for manufacturing a composite assembly of an empennage and rear-fuselage having a continuous skin solution. The method obtains two or more 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 moulds and a sub-structure skin is obtained. Furthermore, the method comprises integrating the two or more parts over an integration tool comprising cavities for locating the curing frames moulds and the stringers performs. Furthermore, the method comprises co-curing the integration tool in one shot on an autoclave, demoulding the sub-structure skin sections and disassembling the curing frame moulds to obtain the composite assembly of the rear section.