The present invention provides a closed composite material structure for aircraft fuselage shaped on a male jig from which it can be separated in a certain direction, said structure comprising a single outer panel and a plurality of inner longitudinal stiffeners integrated in said panel, such that the expansion coefficient of the male jig is greater than the expansion coefficient of the composite material of the structure, thus being able to remove the already manufactured structure, formed by the panel and the integrated inner stiffeners, in a single operation. The present invention further provides a process for manufacturing such a closed structure.
COMPOSITE MATERIAL STRUCTURE FOR AIRCRAFT FUSELAGE AND PROCESS FOR MANUFACTURING IT
STRUCTURE DE MATIERE COMPOSEE POUR LE FUSELAGE D'UN AERONEF ET SON PROCEDE DE FABRICATION
26.01.2016
Patent
Elektronische Ressource
Englisch
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