The redundancy control device includes three controllers that output status signals, a majority voting circuit to which a first voltage or a second voltage is supplied as an output signal through an output line of each controller, a switch provided in each output line, a voltage supply unit provided for each output line to supply the second voltage to the output line when the first voltage is lost, a latch circuit provided for each output line to latch the second voltage when the second voltage is supplied thereto and continue to output the second voltage, a comparison circuit provided for each controller to output a comparison signal based on a comparison of the status signals, and a switch control unit provided for each switch to outputs a switch signal to the switch in response to the comparison signal from the comparison circuit.


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    Title :

    REDUNDANCY CONTROL DEVICE FOR AIRCRAFT


    Contributors:

    Publication date :

    2021-09-09


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    H03K PULSE TECHNIQUE , Impulstechnik / B64C AEROPLANES , Flugzeuge



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