挠性航天器姿态机动的变结构主动振动抑制

Active vibration suppression in flexible spacecraft with mismatched uncertainty via variable structure control

针对挠性航天器大角度姿态机动的振动抑制问题,提出了一种双回路鲁棒主动振动控制方法.首先,对各低阶振动模态设计正位置反馈补偿器,增加挠性模态的阻尼,使其振动能够快速衰减;然后,基于变结构输出反馈控制理论,给出控制器的设计方法.最后,将该方法应用于挠性航天器姿态机动控制,仿真结果表明,所提出的方法是可行而有效的.

This investigation is to apply the variable structure output feedback control （VSOFC） and distributed piezoelectric sensor/actuator technology to a large-angle rotational maneuver and vibration control of a flexible spacecraft. Two separate control loops are adopted to satisfy the pointing requirements and simultaneously suppress vibrations. We use the piezoceramics as sensors and actuators to actively suppress certain flexible modes in designing a positive position feedback （PPF） compensator that adds damping to the flexible structures in certain critical modes of the inner feedback loop. Then, a second feedback loop is designed using the variable structure techniques, using only output information, to slew the space- craft. Compared with conventional methods, the proposed scheme guarantees closed-loop system stability, and yields good performance and robustness in the presence of parametric uncertainties and external disturbance. Simulation results for the spacecraft model show precise trajectory control and vibration suppression.