A duct (107) for a ducted-rotor aircraft (101) includes a hub (119), a duct ring (149), and a plurality of stators (121) that extend outward from the hub (119). The duct ring (149) defines a trailing edge (155). The duct (107) includes one or more fittings (137a, 137b, 137c), such as a system of fittings. Each fitting (137a, 137b, 137c) has a body that defines a first attachment interface (159) that is configured to couple to structure of the duct ring (149) and a second attachment interface (161) that is configured to couple to one of the plurality of stators (121). The first and second attachment interfaces (159, 161) are spaced from each other such that when the fittings (137a, 137b, 137c) are coupled to the duct ring (149) and the plurality of stators (121), all or substantially all of each of the plurality of stators (121) are located aft of the trailing edge (155) of the duct ring (149).


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    Titel :

    STATOR AND DUCT RING STRUCTURAL FITTINGS


    Weitere Titelangaben:

    STATOR- UND KANALRINGSTRUKTURFORMSTÜCKE
    RACCORDS STRUCTURAUX DE STATOR ET D'ANNEAU DE CONDUIT


    Beteiligte:

    Erscheinungsdatum :

    03.05.2023


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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