Aircraft landing strut 50 comprising: an outer cylinder 26 having a cylinder bore, the cylinder bore defining a chamber containing a mixable damping liquid and gas; a sliding tube 28 movable between compressed and extended positions, a tube bore in fluid communication with the cylinder bore to exchange damping liquid; an elongate metering pin 34 comprising an axial channel for passage of damping liquid as the sliding tube moves between extended and compressed positions; and a flow restricting plate 52 including: a first portion 52a having a first damping orifice DO wherein the pin axially moves as the sliding tube moves between extended and compressed positions to vary the free space cross sectional area of the first damping orifice controlling axial flow of the damping liquid J moving from the tube bore to the cylinder bore as the sliding tube moves from extended to compressed positions; and a second portion 52b having a second damping orifice DO2 for passage of damping liquid as the sliding tube moves from extended to compressed positions providing a second flow of liquid J2, wherein the second orifice directs the flow of liquid towards an axial channel of the pin to disrupt the flow.


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    Titel :

    Aircraft landing gear shock absorber strut


    Beteiligte:

    Erscheinungsdatum :

    02.04.2025


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / F16F SPRINGS , Federn



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