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.
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