A redundant seal assembly for an aircraft shock absorber comprises a changeover unit and dual dynamic seals for sealing a fluid chamber formed between an inner member and an outer member of the shock absorber. The first dynamic seal functions as a primary seal, and the second dynamic seal functions as a backup seal in the initial operation of the shock absorber. A fluid passage is formed from the fluid chamber to the first dynamic seal. The changeover unit has a spool provided in the fluid passage. The spool has a channel that forms pat of the fluid passage. A changeover activator is movable to open and close the fluid passage at the spool to apply or remove the fluid pressure on or from the first dynamic seal so as to change over the functionality as the primary seal between the first dynamic seal and the second dynamic seal.


    Access

    Download


    Export, share and cite



    Title :

    AIRCRAFT SHOCK ABSORBER REDUNDANT SEAL ASSEMBLY


    Contributors:
    LEE V-BOND (author)

    Publication date :

    2016-01-21


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F16F SPRINGS , Federn / B64C AEROPLANES , Flugzeuge



    Aircraft shock absorber redundant seal assembly

    LEE V-BOND | European Patent Office | 2017

    Free access

    AIRCRAFT SHOCK ABSORBER REDUNDANT SEAL ASSEMBLY

    LEE V-BOND | European Patent Office | 2016

    Free access

    Aircraft landing gear shock absorber assembly

    MANSFIELD RICKY PETER | European Patent Office | 2022

    Free access

    AIRCRAFT LANDING GEAR SHOCK ABSORBER ASSEMBLY

    MANSFIELD RICKY PETER | European Patent Office | 2020

    Free access

    Aircraft landing gear shock absorber assembly

    SCHMIDT ROBERT KYLE | European Patent Office | 2020

    Free access