Sensor/Control Surface Fault Diagnosis and Reconfiguration in Aircraft Control Systems

Ch Hajiyev*, F. Caliskan

*Bu çalışma için yazışmadan sorumlu yazar

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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.

Orijinal dilİngilizce
Ana bilgisayar yayını başlığıEngineering, Construction and Operations in Challenging Environments - Earth and Space 2004
Ana bilgisayar yayını alt yazısıProceedings of the Ninth Biennial ASCE Aerospace Division International Conference
YayınlayanASCE - American Society of Civil Engineers
Sayfalar176-183
Sayfa sayısı8
ISBN (Basılı)0784407223, 9780784407226
DOI'lar
Yayın durumuYayınlandı - 2004
EtkinlikEngineering, Construction and Operations in Challenging Environments - Earth and Space 2004: Proceedings of the Ninth Biennial ASCE Aerospace Division International Conference - League City/Houston, TX, United States
Süre: 7 Mar 200410 Mar 2004

Yayın serisi

AdıEngineering Construction and Operations in Challenging Environments Earth and Space 2004: Proceedings of the Ninth Biennial ASCE Aerospace Division International Conference

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???event.eventtypes.event.conference???Engineering, Construction and Operations in Challenging Environments - Earth and Space 2004: Proceedings of the Ninth Biennial ASCE Aerospace Division International Conference
Ülke/BölgeUnited States
ŞehirLeague City/Houston, TX
Periyot7/03/0410/03/04

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