Robust adaptive finite time control for spacecraft global attitude tracking maneuvers

摘要

This paper investigates spacecraft attitude control problem to achieve global fast tracking maneuvers. The concept of state-space form is initially introduced into spacecraft attitude dynamics and kinematics based on the unit quaternion, and then robust finite-time controllers are proposed based on geometric homogeneity and integral sliding mode. Furthermore, gain adaptation laws are employed and developed to eliminate the requirement of boundaries with respect to the lumped uncertainties, while there is no overestimation of the gains. Moreover, global finite-time controllers are designed to get across the singular point caused by the unit quaternion. Finally, simulations are presented to illustrate the effectiveness of the control strategies.