ESA GNC Conference Papers Repository

This paper addresses a concept of nonlinear dynamic inversion applied to agile satellites with control momentum gyros. Analytic formulation of nonlinear dynamic inversion based on input-output linearization is given and extended to the satellite rotational dynamics with control moment gyros. Three study cases are outlined, which deal with different selection of the input signal for control. Stability analysis of the internal dynamics is considered. Simulation results are performed on each study case and compared with the performance of conventional proportional-integral-derivative controllers. It is shown that under agile operation conditions, the controller synthesized by the input-output linearization approach provides significantly better performance characteristics compared to the conventional one.