Abstract
This paper investigates guidance scheme for missile with actuator failure and dynamics of autopilot. Firstly, considering first-order dynamics of autopilot, the guidance model with actuator failure is established. Secondly, an adaptive sliding mode fault-tolerant guidance law is designed on the basis of passive fault-tolerant technique and a novel nonsingular fast terminal sliding mode (NFTSM) manifold. Then, the adaptive algorithm with the feature of low-pass filter is proposed to ensure that adaptive parameters are bounded when the sliding mode is non-ideal. Finally, Lyapunov stability theory is adopted to prove that the states of closed-loop system are practical finite-time stability. Simulation results demonstrate the effectiveness and robustness of the proposed guidance strategy under the certain actuator failure.
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 callMore From: International Journal of Control, Automation and Systems
Disclaimer: 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.
