Hybrid Non-Fragile Attitude Stabilization for Post-Capture Spacecraft

This paper investigates the problem of hybrid non-fragile attitude stabilization for post-capture spacecraft in the presence of external disturbances, unknown and uncertain inertia and coexisting controller's gain perturbations. The aim of this work is to design a hybrid non-fragile dynamic output feedback controller such that the closed-loop attitude control system is stabilized, while the actual control input is confined into a certain range. Based on the Lyapunov stability theory, the existence condition of such non-fragile controller is derived in terms of linear matrix inequalities. It is worth mentioning that the controller's additive and multiplicative perturbations are accounted for simultaneously. Finally, an illustrative example is given to demonstrate the effectiveness of the proposed hybrid non-fragile controller.