Distributed finite-time attitude dynamic tracking control for multiple rigid spacecraft

In this study, the authors study the distributed finite-time attitude dynamic tracking control problem for multiple rigid spacecraft systems with a single dynamic leader under directed graphs. By constructing a sliding-mode estimator for each follower, they remove the requirement of the angular acceleration information. Based upon a sliding-mode observation vector, the distributed input torques are designed to guarantee that not only the attitude but also the angular velocity of the followers will converge to the leader's. Necessary and sufficient criteria are established for the proposed protocol. Finally, the theoretical result is illustrated by a numerical simulation.