An aircraft landing gear shock absorbing strut 10 having a first end provided with a mounting bearing 14 for coupling to an aircraft, and a second end provided with a wheel assembly, bogie beam or similar. The shock absorbing strut comprises: an oleo-pneumatic shock absorber comprising an inner cylinder 16 slidably coupled within an outer cylinder 12 defining a variable volume chamber containing a liquid and a gas. A temperature sensor 20 senses the temperature of the gas within the shock absorber and an electrical heating element 22 heats the gas within the shock absorber. A controller 30 is coupled to the temperature sensor and electrical heating element and operates the electrical heating element to heat the gas within the shock absorber until the temperature sensor senses a predetermined temperature.


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    Title :

    Aircraft landing gear shock absorbing strut


    Contributors:

    Publication date :

    2025-03-12


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / F16F SPRINGS , Federn



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