Adaptive Finite-time Orbit Control for Spacecraft Formation with External Disturbances

This paper addresses the finite-time orbit control problem for spacecraft formation flying with external disturbances. A new finite-time tracking control strategy with adaptation law and the adding one power integrator method is designed to ensure that the closed-loop system is practical finite-time stable and that the tracking errors of relative position and velocity are bounded within finite-time despite with external disturbances. Finally, an example is shown to validate the effectiveness of the proposed finite-time tracking controller.