Abstract
This paper treats the problem of nonlinear adaptive attitude tracking control of an orbiting flexible spacecraft. It is assumed that the system parameters are unknown and the truncated model of the spacecraft has finite but arbitrary dimension. An adaptive sliding mode control law is derived for a three-axis stabilized spacecraft attitude tracking control system. The control gains are designed by solving a linear matrix inequality (LMI) problem to achieve a prescribed L2-gain performance criterion. The external torque disturbance/parametric error attenuation, with respect to the performance measure, along with control input penalty are ensured in the L2-gain sense. Lyapunov analysis is employed to show that the closed-loop system is asymptotically stable and the effect of the external disturbances/parametric error on the tracking error can be attenuated to any prescribed level. Simulation results show the effectiveness of the control scheme.
Published Version
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.
