FAILURE DETECTION BY PILOTS DURING AUTOMATIC LANDING: MODELS AND EXPERIMENTS

A model is proposed for the performance of a pilot as a failure detector of instrument failures (additive dynamic biases) during an automatic landing. The model consists of two stages: a linear estimator and a decision mechanism. The linear estimator is the Kalman filter determined from a simplified model of displayed-variable dynamics used by the pilot. The filter also accounts for the pilot's time sharing between instruments through increased noise. The decision mechanism is based on classical sequential analysis with modifications for the failure detection case. An experiment designed to test the validity of the model was conducted.

  • Availability:
  • Corporate Authors:

    American Institute of Aeronautics and Astronautics

    1290 Avenue of the Americas
    New York, NY  United States  10019
  • Authors:
    • Gai, E G
    • Curry, R E
  • Publication Date: 1977-2

Media Info

  • Features: References;
  • Pagination: p. 135-141
  • Serial:
    • Journal of Aircraft
    • Volume: 14
    • Issue Number: 2
    • Publisher: American Institute of Aeronautics and Astronautics
    • ISSN: 0021-8669

Subject/Index Terms

Filing Info

  • Accession Number: 00172744
  • Record Type: Publication
  • Source Agency: Engineering Index
  • Files: TRIS
  • Created Date: Apr 12 1978 12:00AM