Contrôle d’attitude d’un microsatellite, analyse multi objectives de la boucle de retour.

Abstract

This thesis deals with the study of attitude control systems and the development of control laws to ensure the stabilization of the attitude system. This was achieved by combining the dynamic systems control theory and applying this principles on the satellite attitude control system. This research was carried out from a theoretical point of view by the design of two control laws to treat the problem in two different ways. To achieve the goal a satellite attitude modeling study is first approached using mathematical relationships governing the rigid bodies rotational motion, several attitude representations have been proposed. The work focused mainly on the sliding mode control, which has the property of robustness against the model uncertainties, and external disturbances. The control concept considered in this thesis was to discuss the different characteristics of the sliding surfaces by adding a new selection criterion. In addition to the study of a PD based controller, with an estimator to compensate the effect of uncertain or unknown parameters of inertia and disturbances. In addition to the theoretical treatment, the thesis contains simulation results for the developed controllers.