Retraction of a landing gear assembly (4, fig 3) on an aircraft (1, fig 3) is actuated by a hydraulic actuator 12. The actuator 12 includes a piston 28 that travels within a cylinder 26 along a stroke length between a first position corresponding to the landing gear assembly when extended and a second position corresponding to the landing gear assembly when retracted. Movement of the piston 28 along its stroke length is snubbed at different levels, for example by use of a snubbing spear 40 having one or more fluid channels 46, 48 formed herein. Differential snubbing is thus provided, which enables the landing gear to retract faster.


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    Title :

    Aircraft landing gear system


    Contributors:

    Publication date :

    2021-03-24


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / F15B SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL , Druckmittelbetriebene Systeme allgemein



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