A side articulating main landing gear assembly for an aircraft is disclosed which includes a wheel axle fitting oriented in a horizontal plane when the landing gear is in an extended condition deployed from a landing gear bay of the aircraft, a tire supported on the wheel axle fitting and oriented in a vertical plane when the landing gear is in the extended condition, a shock absorber adapted to stroke between an extended state and a compressed state upon landing the aircraft, a set of articulating links connected to the wheel axle fitting, the shock absorber and the aircraft, and configured to maintain the tire in a vertical plane as the shock absorber strokes between the extended state and the compressed state, a set of tire planing links connected to the wheel axle fitting and the articulating links, and configured to maintain the wheel axle fitting in a horizontal plane as the shock absorber strokes between the extended state and the compressed state, and a drive crank connected to the shock absorber, the tire planing links, the articulating links and the aircraft, for moving the landing gear assembly between the extended condition and an inverted retracted condition stowed in the landing gear bay.


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    Titel :

    VERTICALLY RETRACTING SIDE ARTICULATING LANDING GEAR FOR AIRCRAFT


    Beteiligte:
    ACKS JAMES (Autor:in) / MARTIN DENNIS W (Autor:in)

    Erscheinungsdatum :

    26.05.2016


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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