Abstract
In this paper we consider the coupling between the flexibility of a spacecraft equipped with variable speed control moment Gyros and its attitude control system, in the framework of command shaping techniques. The analysis is performed on the set of equation of motion written in an explicit form describing a flexible platform and N wheels gimballed to it. The attitude control system is designed upon a Lyapunov based feedback relying upon a rigid body model. Whenever the structure is not stiff enough, flexibility degrades the performances of the controller that fails to track the desired history. We therefore study the possibility of altering the tracking signal fed to the controller trying to get rid of the relevant frequencies notch filtering them in order to reduce vibrations. The results obtained for a test case attitude acquisition maneuver are presented and the benefit deriving from the command shaping technique evaluated and discussed.
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