Fast Attitude Maneuver of Spacecraft Based on Variable Structure Control

Abstract

This article chooses large reconnaissance satellites with ultrahigh resolution power for study. It describes the mathematical model of the satellites and proposes a control algorithm based on multi-mode switching of control moment gyros. The proposed algorithm is effective to avoid the singularity of control moment gyros while making the satellite achieve fast attitude maneuver. Sliding-mode variable structure controller is designed to minimize the error attitude and further accelerates the attitude convergence speed. At last, referring to the vibration equation, a strain rate feedback controller is used to suppress the satellite vibration quickly. The effectiveness of the proposed scheme is illustrated with a numerical simulation example.