A landing gear assembly is provided. The landing gear assembly includes a shock strut. The shock strut includes a shock strut cylinder and a shock strut piston slidably disposed within the shock strut cylinder. The landing gear assembly further includes a temperature control unit assembly disposed within the shock strut cylinder. The temperature control unit assembly is configured to, responsive to a temperature within the shock strut cylinder falling below a predetermined temperature, circulate heated fluid into a chamber of the shock strut cylinder to heat gas within the shock strut cylinder.


    Access

    Download


    Export, share and cite



    Title :

    Temperature compensated landing gear shock strut


    Contributors:

    Publication date :

    2025-05-06


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / F16F SPRINGS , Federn



    TEMPERATURE COMPENSATED LANDING GEAR SHOCK STRUT

    M N HEMANTH / BODKI BASAVARAJ | European Patent Office | 2025

    Free access

    TEMPERATURE COMPENSATED LANDING GEAR SHOCK STRUT

    M N HEMANTH / BODKI BASAVARAJ | European Patent Office | 2025

    Free access

    AIRCRAFT LANDING GEAR SHOCK ABSORBER STRUT

    BENNETT IAN | European Patent Office | 2025

    Free access

    AIRCRAFT LANDING GEAR SHOCK ABSORBING STRUT

    URBINATI SIMONE / HILLIARD MATT / SMITH JON | European Patent Office | 2018

    Free access

    Landing Gear Shock Strut Heat Damage

    SAE Technical Papers | 2016