Actuator failure detection and reconfigurable control for F-16 aircraft model


Çalışkan F., Hacızade C.

3rd IFAC Workshop on Automatic Systems for Building the Infrastructure in Developing Countries, DECOM-TT 2003, İstanbul, Turkey, 26 - 28 June 2003, vol.36, pp.53-58 identifier identifier

  • Publication Type: Conference Paper / Full Text
  • Volume: 36
  • Doi Number: 10.1016/s1474-6670(17)35806-8
  • City: İstanbul
  • Country: Turkey
  • Page Numbers: pp.53-58
  • Keywords: Extended kalman filter, F-16 aircraft model, Failure detection, Reconfigurable control
  • Istanbul Technical University Affiliated: Yes

Abstract

In this paper, an approach to actuator failure detection and reconfigurable control for flight control system is presented. The effects of the actuator failures in die innovation process of the Kalman fdter are investigated, and a reconfiguration in control law is proposed. In the simulations, the longitudinal and lateral dynamics of an F-16 aircraft model is considered, and actuator failure detection and reconfigurable control are examined.