A single acting actuator (1) for an aircraft landing gear assembly having a piston (3) mounted in a cavity (60) and moveable relative to a housing (2) between a retracted position and an extended position, the piston dividing the cavity into first and second pressure chambers (5a, 5b). At least one of the pressure chambers is associated with first and second outlets (8a, 9a, 8b, 9b), with the actuator being arranged such that, in respect of the relative movement in which the pressure chamber is the decreasing volume pressure chamber, in a first stage of the relative movement the first and second outlets are open thereby allowing actuator fluid to flow out of the pressure chamber through the first and second outlets and in a second stage of the relative movement the second outlet is open but the first outlet is closed, thereby acting to slow the relative movement of the piston with respect to the housing.


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    Titel :

    ACTUATOR FOR AN AIRCRAFT LANDING GEAR ASSEMBLY


    Weitere Titelangaben:

    AKTUATOR FÜR EINE FLUGZEUGFAHRWERKSANORDNUNG
    ACTIONNEUR POUR UN ENSEMBLE TRAINS D'ATTERRISSAGE D'AÉRONEF


    Beteiligte:
    KERR SEAN (Autor:in) / MARLES DAVID (Autor:in) / L'ALLIER PAUL GORDON (Autor:in)

    Erscheinungsdatum :

    22.09.2021


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

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



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