Adaptive output feedback attitude control of a LEO satellite under angular velocity constraints

In this paper an adaptive output feedback control law is proposed for attitude control of a rigid spacecraft under a-priori known angular velocity constraints. The multiple model and switching approach is employed to improve the transient response of the control system in the case of large uncertainty in parameter space of the inertia matrix. Rigorous stability analysis for the proposed control law in the non-switching case is presented. An orbit and attitude simulator for a LEO satellite is developed and used to evaluate the proposed control scheme. The reported results show the effectiveness of the introduced scheme.