Abstract
This paper deals with the problem of flight tracking control against actuator faults based on linear matrix inequality (LMI) method and adaptive method. The type of faults under consideration is loss of actuator effectiveness. An adaptive fault-tolerant flight controller design method is developed based on the on-line estimation of an eventual fault and the addition of a new control law to the normal control law in order to reduce the fault effect on the system without the need for an FDI (fault detection and isolation) mechanism. In the framework of linear matrix inequality (LMI) approach, the normal tracking performance of the resultant closed-loop system is optimized without any conservativeness and the states of fault modes asymptotically track those of the normal mode. A numerical example of an F-16 aircraft model and its simulation results are given.
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
