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, Amerika Birleşik Devletleri, 7 - 10 Mart 2004, ss.176-183 identifier

  • Yayın Türü: Bildiri / Tam Metin Bildiri
  • Basıldığı Şehir: Texas
  • Basıldığı Ülke: Amerika Birleşik Devletleri
  • Sayfa Sayıları: ss.176-183
  • İstanbul Teknik Üniversitesi Adresli: Hayır

Özet

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.