LMI-based design of a structured direct adaptive satellite attitude control with actuator rate feedback

Satellite attitude control of a microsatellite of the CNES Myriade series is considered. Reduction of saturations on the angular rate of reaction wheel actuators is addressed by means of control gain adaptation. The proposed adaptive control design has the following features: performances of the adaptive law are the same as those of a predefined linear time-invariant control when the state is close to the equilibrium; adaptation is structured allowing to include engineering considerations in the design; asymptotic stability is guaranteed based on Lyapunov arguments; fine tuning of adaptive gains is made by linear matrix inequality based convex optimization. The novelties compared to previous results are: to include actuator rate information in the adaptive scheme; to provide a simplified design procedure.