The invention relates to a structural element for an aircraft fuselage, generally shaped in the form of a longitudinally elongate section. The element comprises two wings, each wing including: a portion that extends uninterrupted along the entire length of the section, and legs spaced apart from one another and extending from said uninterrupted portion such as to define an opening between two consecutive legs. One of the legs of one wing is arranged to face at least part of the opening defined between two consecutive legs of the other wing. Consequently, the structural element can be produced from a single fibrous preform on a curved tool, minimizing waste material and reducing the weight of said element.


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    Titel :

    ELÉMENT DE STRUCTURE DE FUSELAGE D'AÉRONEF ANTI DÉVERSEMENT


    Weitere Titelangaben:

    STRUCTURAL ELEMENT FOR AN AIRCRAFT FUSELAGE THAT PREVENTS LATERAL-TORSIONAL BUCKLING
    STRUKTURELEMENT FÜR EINEN FLUGZEUGRUMPF ZUR VERHINDERUNG VON LATERAL-TORSIONALEM KNICKEN


    Beteiligte:
    ALBY SÉBASTIEN (Autor:in) / GIUSEPPIN LAURENT (Autor:in) / MÜLLER MARKUS (Autor:in)

    Erscheinungsdatum :

    09.03.2016


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Französisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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