Abstract
The aim of this paper is to design a globally robust and globally finite-time convergent attitude controller for a rigid spacecraft. Second order sliding mode control in integral sliding mode is proposed to design the controller. To eliminate the need of advance information about uncertainty and external disturbance bounds, the gains of the proposed controller are calculated using the adaptive laws. The second order sliding mode controller applied is based on geometric homogeneity approach. The finite-time stability is proved by using both the Lyapunov stability and negative homogeneity approach. Simulations are conducted for the attitude tracking and attitude stabilization under the effect of spacecraft mass inertia uncertainty and external disturbances; and the outcomes reveal the effectiveness of the proposed control method.
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.
