The invention is related to a flexbeam unit (3) comprising a plurality of flexbeam elements (3a, 3b, 3c, 3d, 3e), each defining a load passing member (9a, 9b, 9c, 9d, 9e) that is attachable to a rotor hub (4) associated with a rotor shaft (5) of said multi-blade rotor (1), said plurality of flexbeam elements defining a predetermined number of torsion elements (7a, 7b, 7c, 7d, 7e) that are connectable with associated rotor blades (2a, 2b, 2c, 2d, 2e) of said multi-blade rotor (1), wherein at least one of the predetermined number of torsion elements (7e) comprises at least one first flexbeam element (3b) defining a first longitudinal direction and at least one second flexbeam element (3c) defining a second longitudinal direction, wherein said at least one first and second flexbeam elements are interconnected by a beam connector (15) in a direction transverse to said first and/or second longitudinal directions.


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    Titel :

    Flexbeam unit for a bearingless or a hinge- and bearingless multi-blade rotor of a rotary wing aircraft


    Weitere Titelangaben:

    Flexbeam-Einheit für einen lagerlosen oder scharnierlosen und lagerlosen mehrflügeligen Rotor eines Drehflüglers
    Unité de flexion pour rotor à pales multiples sans palier ou sans palier et charnière d'aéronef à voilure tournante


    Beteiligte:
    PFALLER RUPERT (Autor:in)

    Erscheinungsdatum :

    15.07.2015


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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