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

Ch Hajiyev*, F. Caliskan

*Corresponding author for this work

Research output: Chapter in Book/Report/Conference proceedingConference contributionpeer-review

Abstract

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.

Original languageEnglish
Title of host publicationEngineering, Construction and Operations in Challenging Environments - Earth and Space 2004
Subtitle of host publicationProceedings of the Ninth Biennial ASCE Aerospace Division International Conference
PublisherASCE - American Society of Civil Engineers
Pages176-183
Number of pages8
ISBN (Print)0784407223, 9780784407226
DOIs
Publication statusPublished - 2004
EventEngineering, 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
Duration: 7 Mar 200410 Mar 2004

Publication series

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

Conference

ConferenceEngineering, Construction and Operations in Challenging Environments - Earth and Space 2004: Proceedings of the Ninth Biennial ASCE Aerospace Division International Conference
Country/TerritoryUnited States
CityLeague City/Houston, TX
Period7/03/0410/03/04

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