RKF-based fault tolerant integrated INS/radar altimeter

Hacızade C., Saltoglu R.

Aircraft Engineering and Aerospace Technology, cilt.76, sa.1, ss.38-46, 2004 (Scopus) identifier

  • Yayın Türü: Makale / Tam Makale
  • Cilt numarası: 76 Sayı: 1
  • Basım Tarihi: 2004
  • Doi Numarası: 10.1108/00022660410514991
  • Dergi Adı: Aircraft Engineering and Aerospace Technology
  • Derginin Tarandığı İndeksler: Scopus
  • Sayfa Sayıları: ss.38-46
  • Anahtar Kelimeler: Aircraft components, Aircraft navigation, Fault tolerance, Integrated software, Radar
  • İstanbul Teknik Üniversitesi Adresli: Evet

Özet

In this study, the integrated navigation system, consisting of radio and inertial navigation system (INS) altimeters, is presented. INS and the radio altimeter have different benefits and drawbacks. The integration is achieved by using an indirect Kalman filter. Hereby, the error models of the navigators are used by the Kalman filter to estimate vertical channel parameters of the navigation system. In the open loop system, INS is the main source of information, and radio altimeter provides discrete aiding data to support the estimations. At the next step of the study, in case of abrupt faults, the performance of the integrated system is examined. The optimal Kalman filter reacts with abnormal estimates to this situation as expected. To recover such a possible malfunctioning, the robust Kalman filter algorithm is suggested.