本文基于Hamilton变分原理和弹性薄板理论,考虑了板旋转时离心力的作用,对带有柔性附件的航天器建立了中心刚体-柔性板动力学模型。采用梁函数组合法对板的振动模态进行了分析。而后,基于此振动模态采用等速趋近律的方法设计了滑模变结构控制,以抑制平板旋转机动时产生的横向振动。最后,用Matlab软件给出了实施振动控制的数值仿真结果,并对结果进行了分析讨论。 Based on Hamilton variational principle and elastic thin plate theory, this paper considers the effect of centrifugal force during plate rotation, and establishes a rigid body-flexible plate dynamic model for spacecraft with flexible attachment. The vibration mode of the plate was analyzed by using the beam function combination method. Then, sliding-mode variable structure control is designed based on this mode of vibration using equal-speed approach law to suppress the lateral vibration generated when the rotating plate rotates. Finally, numerical simulation results of vibration control are given with Matlab software, and the results are analyzed and discussed.