Attitude stabilization of rigid spacecraft with disturbance generated by time varying uncertain exosystems

• We discuss the attitude stabilization and disturbance rejection of rigid spacecraft.
• The semi-tensor product is applied.
• A time varying internal model is introduced.
• An adaptive control law is proposed for attitude stabilization of rigid spacecraft.

This paper is concerned with the problem of attitude stabilization of rigid spacecraft in the presence of parameter uncertainty and external disturbance generated by some time varying uncertain exosystems. A time varying internal model that is free of the uncertain parameter is proposed to compensate the disturbance. An adaptive attitude controller is presented by incorporating time varying dynamic coordinate transformation, semi-tensor product and adaptive control method. Especially, the parameter uncertainties caused by the inertia matrix and uncertain exosystems are tackled by combining the semi-tensor product and adaptive control method. Finally, a simulation example is presented to illustrate the effectiveness of the proposed method.