The invention relates to a beam (13) for a rotorcraft rotor and particularly to a helicopter rotor. Said beam (13) 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 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).


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    Titel :

    Beam for a rotorcraft rotor and rotorcraft rotor


    Weitere Titelangaben:

    Träger für einen Drehflüglerrotor und Drehflüglerrotor
    Poutre pour un rotor de giravion et ledit rotor


    Beteiligte:
    BÜSING MORITZ (Autor:in)

    Erscheinungsdatum :

    17.06.2015


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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