Abstract
In this paper, the dynamic sliding mode control approach is adopted to design attitude tracking control law for flexible spacecraft. First, the mathematical model of the flexible spacecraft based on attitude errors is constructed. The kinematic equation of the flexible spacecraft is described by error quaternions. Then, by introducing a dynamic switching function, an dynamical sliding mode control law is proposed for the flexible spacecraft to tackle attitude tracking issue. The proposed dynamic sliding mode control law can suppress the chattering raised by the sign function of the traditional sliding mode control law. Finally, a numerical example is employed to verify the effectiveness of the presented control law.
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