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.
METHOD FOR MANUFACTURING A REAR SECTION OF AN AIRCRAFT AND AIRCRAFT REAR SECTION MANUFACTURED BY SAID METHOD
VERFAHREN ZUR HERSTELLUNG EINES HECKABSCHNITTS EINES FLUGZEUGS UND DURCH DAS BESAGTE VERFAHREN HERGESTELLTER FLUGZEUGHECKABSCHNITT
PROCÉDÉ DE FABRICATION D'UNE SECTION ARRIÈRE D'AÉRONEF ET SECTION ARRIÈRE D'AÉRONEF FABRIQUÉE PAR LEDIT PROCÉDÉ
2024-05-01
Patent
Electronic Resource
English
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