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In this paper, a control method is proposed for spacecraft with unknown disturbances. For attitude subsystem, an adaptive estimator is designed to deal with the unknown disturbances. For angular velocity subsystem, the actual control input is designed. If the designed control law is added to angular velocity subsystem, a nonlinear closed-loop system of angular velocity error is arrived. The convergence of closed-loop system is proved by input-output stability theory. The derivative of virtual control and unknown disturbances in the actual control are also estimated using adaptive estimator. It can be proved that, with the proposed controller, the attitude can converge to a small-neighbourhood of the designed attitude. Theoretical results are illustrated by numerical simulation.

A Spacecraft Attitude Tracking Control Method based on Disturbance Estimation