There is proposed a structural junction (11) in an aircraft or spacecraft fuselage (2), comprising a first fitting (13) attached to a portion (17a) of a fuselage skin (17) in a first fuselage section (2a), a second fitting (23) attached to a portion (17b) of the fuselage skin (17) in a second fuselage section (2b), and a pressure bulkhead skin (19) attached to an inner flange (29) of the first fitting. The inner flange is spaced apart from the fuselage skin towards an inner space (10) of the fuselage. The first and second fittings are connected or configured for being connected at least using a plurality of tension bolts (37). The tension bolts each are arranged and adapted to transfer at least tensile loads, in a direction across adjacent edges (12a, 12b) of the first and second fuselage sections in a region where the first and second fuselage sections are joined, between the first and second fittings. Furthermore, the invention relates to an aircraft or spacecraft (1) comprising a fuselage including such a structural junction, and to a method of forming a structural junction in an aircraft or spacecraft fuselage. The invention may in particular contribute to reducing the number of parts and the assembly lead time during fuselage section assembly and to improving ergonomics during the assembly process.


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    Titel :

    AN AIRCRAFT OR SPACECRAFT FUSELAGE WITH A STRUCTURAL JUNCTION


    Weitere Titelangaben:

    FLUGZEUG- ODER RAUMFAHRZEUGRUMPF MIT EINER STRUKTURELLE VERBINDUNG
    UN FUSELAGE D'AÉRONEF OU D'ENGIN SPATIAL AVEC UNE JONCTION STRUCTURELLE


    Beteiligte:
    BONNET MATHIEU (Autor:in) / NOEBEL TORSTEN (Autor:in) / DRESEL ANDREAS (Autor:in)

    Erscheinungsdatum :

    09.10.2024


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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