An airplane hydraulic brake system comprises a hydraulic brake valve, a liquid-controlled conversion valve, an electro-hydraulic servo valve, an anti-slide control box and a speed sensor. The liquid-controlled conversion valve is mounted on a downstream hydraulic pipeline of the hydraulic brake valve, the electro-hydraulic servo valve is mounted on a downstream hydraulic pipeline of the liquid-controlled conversion valve, an electrical interface of the electro-hydraulic servo valve is electrically connected with the anti-slide control box through a shielding insulation wire, an oil inlet of the electro-hydraulic servo valve is in pipeline connection with an oil outlet of the liquid-controlled conversion valve, a brake opening of the electro-hydraulic servo valve is in pipeline connection with an oil inlet of a brake device of a brake airplane wheel, and an oil returning opening of the electro-hydraulic servo valve is in pipeline connection with an airplane oil returning pipeline through a hydraulic filler neck and a guide pipe. The airplane hydraulic brake system can meet the ever-growing airplane take-off line brake requirement, is reasonable in structure, easy and convenient to implement, and beneficial for reducing of burdens of a driver, conforms to the man-machine engineering principle and meanwhile the accident potentials caused by false-operation switching on of a take-off line brake switch are eliminated.


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    Title :

    Airplane hydraulic brake system


    Contributors:
    HE YONGLE (author) / WANG HONGLING (author) / ZHAO YAJUN (author)

    Publication date :

    2015-07-15


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / B60T Bremsanlagen für Fahrzeuge oder Teile davon , VEHICLE BRAKE CONTROL SYSTEMS OR PARTS THEREOF



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