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.


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    Titel :

    COMPOSITE MATERIAL STRUCTURE FOR AIRCRAFT FUSELAGE AND PROCESS FOR MANUFACTURING IT


    Weitere Titelangaben:

    STRUCTURE DE MATIERE COMPOSEE POUR LE FUSELAGE D'UN AERONEF ET SON PROCEDE DE FABRICATION



    Erscheinungsdatum :

    26.01.2016


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / B29C Formen oder Verbinden von Kunststoffen , SHAPING OR JOINING OF PLASTICS



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