A shock absorber includes a housing and an end wall slidably disposed within the housing. The end wall and the housing cooperate to define at least a portion of a cavity within the housing. The cavity is filled with a fluid, and a piston is slidably disposed within the cavity. Movement of the piston within the cavity compresses the fluid to provide a spring force. The shock absorber further includes a compensator coupled to the end wall. The compensator positions the end wall within the housing to change a volume of the cavity in response to a change in a temperature of a first element of the compensator.


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    TEMPERATURE COMPENSATED SHOCK ABSORBER


    Beteiligte:

    Erscheinungsdatum :

    14.07.2022


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F16F SPRINGS , Federn / B64C AEROPLANES , Flugzeuge



    Temperature compensated shock absorber

    SCHMIDT ROBERT KYLE | Europäisches Patentamt | 2022

    Freier Zugriff

    TEMPERATURE COMPENSATED SHOCK ABSORBER

    SCHMIDT ROBERT KYLE | Europäisches Patentamt | 2022

    Freier Zugriff

    Temperature compensated landing gear shock strut

    M N HEMANTH / BODKI BASAVARAJ | Europäisches Patentamt | 2025

    Freier Zugriff

    TEMPERATURE COMPENSATED LANDING GEAR SHOCK STRUT

    M N HEMANTH / BODKI BASAVARAJ | Europäisches Patentamt | 2025

    Freier Zugriff

    TEMPERATURE COMPENSATED LANDING GEAR SHOCK STRUT

    M N HEMANTH / BODKI BASAVARAJ | Europäisches Patentamt | 2025

    Freier Zugriff