The invention is related to a flexbeam unit (3) for a multiblade rotor (1) of a rotary wing aircraft, said flexbeam unit comprising a plurality of flexbeam elements (3a, 3b, 3c, 3d, 3e) that define a predetermined number of torsion elements (7a, 7b, 7c, 7d, 7e) and a ring-shaped connection zone (6) for attachment to a rotor hub (4) associated with a rotor shaft (5) of said multiblade rotor (1), each flexbeam element (3a, 3b, 3c, 3d, 3e) passing said ring-shaped connection zone (6) in a tangential manner and uninterruptedly connecting a first torsion element to a second torsion element of said predetermined number of torsion elements, wherein each flexbeam element overlaps at least one in the circumferential direction of said ring-shaped connection zone (6) immediately following flexbeam element and is overlapped by at least one in the circumferential direction of said ring-shaped connection zone (6) immediately preceding flexbeam element.


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    Title :

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


    Additional title:

    Verwindungsträger-Einheit für einen gelenklosen oder gelenk- und lagerlosen Mehrblattrotor eines Rotorflügelluftfahrzeuges
    Unité de poutre flexible pour un rotor multipale sans charnières ou sans charnières et paliers d'un véhicule aérienne à ailes rotatives


    Contributors:

    Publication date :

    2015-07-15


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge