The invention provides an aircraft electro hydrostatic brake actuator. The output shaft of a brushless direct current motor is coaxially connected with a displacement-fixed two-way plunger pump, a pressurized tank is used for supplying initial pressure for the inlet of the displacement-fixed two-way plunger pump, one outlet of the displacement-fixed two-way plunger pump is connected with a hydraulic cylinder through an oil filter and a two-position two-way solenoid valve, the other outlet of the displacement-fixed two-way plunger pump is connected with the two-position two-way solenoid valve through the oil filter and a relief valve, the pickup state of the two-position two-way solenoid valve is controlled by a solenoid valve control unit, thus switching between brake pressure tracking and take-off line brake pressure maintaining functions is realized, the internal pressure of the hydraulic cylinder is measured by a pressure measuring unit, the pressure information is transmitted to a controller for pressure closed-loop control, the controller receives a brake pressure instruction through an instruction port, to further control the solenoid valve control unit and the brushless direct current motor and a brake disc is driven by the hydraulic cylinder. The aircraft electro hydrostatic brake actuator is simple in structure, high in efficiency, high in frequency response and small in size and weight, and take-off line brake pressure maintaining can be realized for a long time.


    Access

    Download


    Export, share and cite



    Title :

    Aircraft electro hydrostatic brake actuator


    Contributors:
    LI BINGQIANG (author) / ZHANG QIAN (author) / LIN HUI (author) / QI RONG (author) / LU JIULI (author) / LIU GANG (author) / WU CHUN (author) / SUN JING (author)

    Publication date :

    2015-08-26


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

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



    Electro hydrostatic actuator

    ONISHI TAKAAKI / KONDO TAKU / ONOMICHI YASUTO et al. | European Patent Office | 2015

    Free access

    ELECTRO HYDROSTATIC ACTUATOR

    LESAGE EMMANUEL / PERROCHAT JEAN-MICHEL | European Patent Office | 2019

    Free access

    Electro hydrostatic actuator

    MASUTANI KAZUHIRO / KONDO TAKU / ONISHI TAKAAKI | European Patent Office | 2018

    Free access

    Electro hydrostatic actuator

    ONOMICHI YASUTO / KONDO TAKU / HAGIHARA SHOGO et al. | European Patent Office | 2016

    Free access

    ELECTRO HYDROSTATIC ACTUATOR

    LESAGE EMMANUEL / PERROCHAT JEAN-MICHEL | European Patent Office | 2020

    Free access