Abstract
This paper proposes an adaptive fault-tolerant control scheme for nonaffine nonlinear systems. A model approximation method which is a solution that bridges the gap between affine and nonaffine control systems is developed firstly. A joint estimation approach is based on unscented Kalman filter, in which both failure parameters and states are simultaneously estimated by means of the argument state vector composed of the unknown faults and states. Then, stability analysis is given for the closed-loop system. Finally, the proposed approach is verified using a three-degree-of-freedom simulation of a typical fighter aircraft and the significantly improved system response demonstrates the practical potential of the theoretic results obtained.
Highlights
The increasing demands on the performance of many modern systems will correspondingly increase the possibility of system failures
A stability analysis was performed on the adaptive fault-tolerant control (FTC) law based on unscented Kalman filter (UKF)
The proposed model approximation method is a solution that bridges the gap between affine and nonaffine control systems
Summary
The increasing demands on the performance of many modern systems will correspondingly increase the possibility of system failures. To improve system reliability and stability, fault-tolerant control (FTC) for dynamic systems has become an attractive topic and has received considerable attention during the past two decades. The active approach is less conservative than the passive one, which has increasingly been the main methodology in designing FTC systems [9]. The existence of an inverse function can be guaranteed by the implicit function theorem [13], it is generally difficult to prescribe a technique to obtain such an inverse In another approach, an integrator, that is, u = ∫ot udt, is introduced to a new control input u. This paper addresses the fault-tolerant tracking control problem for nonaffine nonlinear systems in the presence of actuator faults. Appropriate closed-loop system stability analysis is given by using the proposed adaptive fault-tolerant tracking control structure with the UKF. The proposed approach is tested using a three-degreeof-freedom (3-DOF) unmanned aerial vehicle UAV point mass model
Sign-in/Register to view highlights & summary Sign-in/Register to access full text options 
Free) 
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 call
