A helicopter rotor head (fig.1,10) has a rotor blade 202 with a first end held in an opening (fig.2,400) of a blade grip 101 so it can pivot. A damper 100 has a rigid connection 203 to the rotor blade, and a connection (fig2, 114),104 to the blade grip allowing it to pivot, and a rigid plate 112 which pivots with pivoting movement of the rotor blade. The damper prevents pivoting movement beyond a selected range, for example, the plate having a tang 121 which is restricted by recess123. An arrangement is claimed where the damper resists the pivoting movement within a selected range, for example by use of friction washers (fig.2,102a,102b). Another arrangement is claimed there the rigid connection to the rotor blade can be selectively released to allow pivoting movement beyond the selected range, for example, by use of a sprung pin 203 disengaging a hole 122 in the plate, enabling the blade to be stowed.


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    Titel :

    Rotor damping mechanism


    Beteiligte:
    ROBERT MANLEY (Autor:in) / MICHAEL EMPATAGE (Autor:in)

    Erscheinungsdatum :

    15.01.2025


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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