Abstract
This paper studies the vibration control of gyroelastic spacecraft. The dynamics of gyroelastic spacecraft considering the angular momentum devices are derived using Kane's method. A novel control strategy combining input shaping (IS) and variable-speed control moment gyros (VSCMGs) is proposed to suppress the flexible vibration of gyroelastic spacecraft. Input shaping technique is used to suppress the flexible vibration due to attitude motion. An adaptive controller is designed to further reduce the residual vibration using VSCMGs. Considering that the modal variable cannot be measured in practice, a novel modal observer is designed to estimate the modal variables for vibration control. Simulations are conducted to verify the effectiveness of the proposed control strategy.
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