An aircraft landing gear assembly comprising a first structural member 40 (for example a bogie beam 31) coupled to a second structural member 42 (for example a shock absorbing strut 28) via a joint. The joint comprises a tubular bearing 46, or bush. The bearing comprising a tubular body 46a formed from a metal matrix composite (MMC) comprising a metal, a carbide compound and tungsten disulphide. A self-lubricating liner 50 may also be provided. The carbide compound may be silicon carbide, boron carbide or titanium carbide. The metal may be magnesium or aluminium. The bearing may be provided between a pin 44 and either the bogie beam or shock absorbing strut.


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    Title :

    Aircraft landing gear assembly


    Contributors:

    Publication date :

    2025-06-18


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / F16C SHAFTS , Wellen



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