Abstract
An indirect adaptive nonlinear controller is investigated for attitude control and momentum management of evolutionary spacecraft. The control law is based on the theory of nonlinear feedback linearization. A new state transformation is introduced: one that converts the original nonlinearsystem into normal canonical form. Once in canonical form, nonlinear feedback is used to generate a linear response in the transformed coordinates. To make the nonlinear controller adaptive, a parameter identie cation scheme, utilizing an extended Kalman e lter, is added for mass property estimation. Probing signals are introduced to enhance the observability of the mass properties. Simulation results show that the adaptive nonlinear controller stabilizes the International Space Station during mass property changes, successfully performs momentum management, and provides real-time estimates of the mass properties in a realistic environment.
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
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.