Abstract
Space mission concepts based on satellite formations feature several interesting and demanding design requirements. During formation deployment, re-sizing and re-orientation, the spacecraft must reach their desired positions without incurring in collisions or interfering with each other. Conventional GNC algorithms cannot support the degree of flexibility, the accuracy in the relative positioning and the fine pointing attitude requirements of future missions. The potential function method, based upon Lyapunov’s second theorem on stability, brings the advantage of robustness and flexibility, along with a light workload for the control system. The aim of this paper is to foster the understanding of existing algorithms based on this method. In particular, the attention is focused on reducing the fuel consumption through the parametric optimization of the Lyapunov function that defines the control algorithm.
Published Version
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