The invention relates to a beam (13) for a rotorcraft rotor and particularly to a helicopter rotor. Said beam comprises a hub connection portion (14), a blade connection portion (15), a first flexure portion (16) located between the hub connection portion (14) and the blade connection portion (15) and having a bending stiffness about a first axis (yy, zz) which is orthogonal to the longitudinal axis (X) of the blade (12), said bending stiffness being smaller than that of the hub connection portion (14) and that of the blade connection portion (15) and a shear portion (17) located between the hub connection portion (14) and the blade connection portion (15) and having a shear stiffness parallel to a second axis which is orthogonal to the longitudinal axis (X) of the blade (12) and non-parallel to the first axis. Said shear stiffness is smaller than that of the hub connection portion (14) and that of the blade connection portion (15). According to the invention, actual offset of the hinge joint of a hingeless rotor and a bearinglesss rotor can be reduced.


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    Titel :

    Beam for a rotorcraft rotor and rotorcraft rotor


    Beteiligte:
    MORITZ BUSING (Autor:in)

    Erscheinungsdatum :

    10.06.2015


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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