A piston assembly for a lead-lag damper for a blade mounted on a rotor of a helicopter includes a piston-rod that has an inside surface and a piston-head that extends radially outward therefrom. The piston-rod has two ports extending therethrough on opposing sides of the piston-head. A sleeve is positioned in the piston-rod and has two annular passages that communicate with the respective ports. A valve spool is disposed in and slidingly engages the sleeve. The valve spool has a channel which is in variable fluid communication with two passages. The piston assembly includes a biasing member that biases the valve spool axially away from it. The channel has an axial width configured to variably regulate fluid flow between the two ports to control dampening of the piston-rod in response to centrifugal forces applied to the valve spool.


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    Titel :

    ROTOR BLADE LEAD-LAG HYDRAULIC DAMPER WITH CENTRIFUGAL FORCE COMPENSATING DAMPING CHARACTERISTICS


    Beteiligte:
    ALGER MARK (Autor:in) / KOHUTH RANDALL (Autor:in) / CAMPBELL DEAN (Autor:in)

    Erscheinungsdatum :

    2021-10-14


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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