The invention discloses an all-electric aircraft brake system and an aircraft electric brake redundancy control method. Redundancy design is performed for elements, easy to damage, of a brake system, and drive control can simultaneously drive EMAs (electro-mechanical actuators) of four channels to actuate; a core control unit including DSPs (digital signal processors) and CPLDs (complex programmable logic devices) adopts double-redundancy design, and an electric circuit adopts four-redundancy design; power-driven circuits, motors, force sensors and Hall position sensors of a channel A and a channel B are divided into one group, and a 1#DSP and a 1#CPLD are taken as primary control units; power-driven circuits, motors and force sensors of a channel C and a channel D are divided into the other group, and a 2#DSP and a 2#CPLD are taken as secondary control units; the primary and secondary control units simultaneously drive the EMAs of the four channels to actuate. Double redundancy of the control units and four redundancy of the drive units are realized; the 1#DSP and the 2#DSP communicate with each other through an SPI (serial peripheral interface).


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    Title :

    All-electric aircraft brake system and aircraft electric brake redundancy control method


    Contributors:
    XIANG LIKANG (author) / MA RUIQING (author) / ZHANG QINGCHAO (author) / HAN WEIJIAN (author)

    Publication date :

    2015-07-22


    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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