Sensor/control surface fault diagnosis and reconfiguration in aircraft control systems

Hajiyev C., Caliskan F.

9th Biennial International Conference on Engineering, Construction and Operations in Challenging Environment, Texas, United States Of America, 7 - 10 March 2004, pp.176-183 identifier

  • Publication Type: Conference Paper / Full Text
  • City: Texas
  • Country: United States Of America
  • Page Numbers: pp.176-183
  • Istanbul Technical University Affiliated: No


In this paper, an approach to detect and isolate the aircraft sensor/control surface faults affecting the mean of the Kalman filter innovation sequence is proposed, and a new structure for a fault tolerant aircraft control system is presented. In the simulations, the longitudinal and lateral dynamics of an F-16 aircraft model is considered, and detection and isolation of pitch rate gyro faults and control surface faults are examined. The principal block diagram of a fault tolerant aircraft control system is illustrated.