An electronic control architecture for an aircraft actuation system may include a first channel and a second channel. The first channel may be configured to receive one or more inputs comprising a movement command, to produce an output to control a component of the system, and to receive feedback from the component respective of movement of the component. The first channel may comprise a fault detection module configured to compare the feedback to the command to determine if the first channel is functioning properly. The second channel may be configured to receive the one or more inputs and, if the first channel is not functioning properly, to produce an output to control the component.


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    Title :

    FAULT TOLERANT ELECTRONIC CONTROL ARCHITECTURE FOR AIRCRAFT ACTUATION SYSTEM



    Publication date :

    2016-03-10


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / G05D SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES , Systeme zum Steuern oder Regeln nichtelektrischer veränderlicher Größen



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