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

Fikret Caliskan; Chingiz Hajiyev

doi:10.1016/S1474-6670(17)35806-8

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

Fikret Caliskan, Chingiz Hajiyev

Research output: Contribution to journal › Conference article › peer-review

4 Citations (Scopus)

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.

Original language	English
Pages (from-to)	53-58
Number of pages	6
Journal	IFAC-PapersOnLine
Volume	36
Issue number	7
DOIs	https://doi.org/10.1016/S1474-6670(17)35806-8
Publication status	Published - 2003
Event	3rd IFAC Workshop on Automatic Systems for Building the Infrastructure in Developing Countries, DECOM-TT 2003 - Istanbul, Turkey Duration: 26 Jun 2003 → 28 Jun 2003

Bibliographical note

Publisher Copyright:
Copyright © 2003 IFAC.

Keywords

Extended kalman filter
F-16 aircraft model
Failure detection
Reconfigurable control

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10.1016/S1474-6670(17)35806-8

Cite this

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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.",

keywords = "Extended kalman filter, F-16 aircraft model, Failure detection, Reconfigurable control",

author = "Fikret Caliskan and Chingiz Hajiyev",

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AU - Hajiyev, Chingiz

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AB - 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.

KW - Extended kalman filter

KW - F-16 aircraft model

KW - Failure detection

KW - Reconfigurable control

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Y2 - 26 June 2003 through 28 June 2003

ER -

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

Abstract

Bibliographical note

Keywords

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