Abstract
A nonlinear controller is designed for achieving low-orbit stabilization and asymptotic rejection of the atmospheric drag of a two-body spinning satellite. The choice of the mechanical structure and the use of low-power actuators are inspired by a scientie c mission under study: Galileo Galilei, a small mission for a high-precision test of the equivalence principle. The feasibility of the proposed controller and its robustness are cone rmed by the results of some simulations.
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