The invention provides a fused composite manufactured fitting (10) comprising a first (11) substantially flat wall (11, 12) comprising a first (11) proximal edge and a first (11) distal edge, and a first (11) and a second (12) lateral edges;a second (12) substantially flat wall (11, 12) comprising a second (12) proximal edge and a second (12) distal edge, and a third and a fourth lateral edges;a first curved transition area (13) integrally merging the first (11) proximal edge of the first (11) flat wall (11, 12) with the second (12) proximal edge of the second (12) flat wall (11, 12);wherein the first curved transition area (13) is shaped as a cylindrical segment, the first (11) and second (12) substantially flat walls are at an angle with respect to each other;the first (11) and second (12) substantially flat wall (11, 12) are both parallel to a longitudinal axis of the first curved transition area (13), and at least one of the first (11) and second (12) distal edges is substantially parallel to the longitudinal axis of the curved transition area (13, 20).


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    Titel :

    FITTING FOR AN AIRCRAFT


    Weitere Titelangaben:

    FORMSTÜCK FÜR EIN FLUGZEUG
    RACCORD POUR UN AÉRONEF



    Erscheinungsdatum :

    11.05.2022


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    G06F ELECTRIC DIGITAL DATA PROCESSING , Elektrische digitale Datenverarbeitung / B64C AEROPLANES , Flugzeuge



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