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Multiple-voting fault detection system for flight critical actuation control systems

  • US 5,274,554 A
  • Filed: 02/01/1991
  • Issued: 12/28/1993
  • Est. Priority Date: 02/01/1991
  • Status: Expired due to Term
First Claim
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1. A method of detecting faults in an aircraft control system having an actuator, and a plurality of control channels for r®

  • receiving control signals and processing said signals to generate output signals for driving said actuator, said method comprising;

    in each said channel, generating a monitoring signal representative of actual operation of said actuator and a model signal corresponding to expected operation of said actuator, comparing said monitoring signal to said model signal, and determining an operating status based on results of said comparing;

    communicating said monitoring signal and said model signal generated in a first one of said channels to a second one of said channels, and communicating said monitoring signal and said model signal generated in said second channel to said first channel;

    in each one of said first and second channels, independently performing comparisons of said monitoring signal and said model signal communicated from the other of said first and second channels and said monitoring signal and said model signal generated in said one of said first and second channels to determine a fault status of each of said first and second channels; and

    maintaining communication links between said channels, including a link between said first channel and said second channel; and

    providing, in each of said first and second channels, a deactivating switch responsive to a fault status signal from the other of said first and second channels.

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