A hydraulic actuator for an aircraft. The hydraulic actuator comprises: a housing to accommodate hydraulic fluid; an extension chamber and a retraction chamber each defined by the housing; and a bypass line in fluid communication with the extension chamber and the retraction chamber, wherein the bypass line comprises a flow restrictor and a bypass valve, wherein the flow restrictor restricts a rate of fluid flow through the bypass line, wherein the bypass valve has material defining a port that is openable to allow the hydraulic fluid to flow through the bypass line, and wherein the material is configured to change shape, as a temperature of the material reduces to below a predetermined temperature, to thereby open the port. Also disclosed is a hydraulic actuation system, in the form of a landing gear system, comprising the hydraulic actuator, and an aircraft comprising the hydraulic actuation system.


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    HYDRAULIC ACTUATOR


    Beteiligte:
    KERR SEAN (Autor:in)

    Erscheinungsdatum :

    12.06.2025


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

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



    Hydraulic actuator

    SEAN KERR | Europäisches Patentamt | 2025

    Freier Zugriff

    HYDRAULIC ACTUATOR

    MARGER THIBAUT / POULY FRANÇOIS / LABASCOULE JEAN-CHRISTOPHE | Europäisches Patentamt | 2019

    Freier Zugriff

    HYDRAULIC ACTUATOR

    ITO KOJI | Europäisches Patentamt | 2016

    Freier Zugriff

    Hydraulic actuator

    Europäisches Patentamt | 2024

    Freier Zugriff

    Hydraulic actuator

    SEAN KERR | Europäisches Patentamt | 2025

    Freier Zugriff