旋转板振动的滑模变结构控制方法  

Sliding Mode Control of Vibration of Rotating Plates

作　　者：罗璐[1] 胡超[1,2] 

机构地区：[1]同济大学航空航天与力学学院 [2]扬州大学建筑科学与工程学院

出　　处：《力学季刊》2012年第2期290-297,共8页Chinese Quarterly of Mechanics

基　　金：国家自然科学基金(10572045)

摘　　要：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。The flexible spacecraft was modeled as a flexible hub-plate system. By the Hamilton principle and theory of elastic thin plates, the dynamic model of the flexible hub-plate with the consideration of the centrifugal force was derived. The mode shapes of plate were presented by the beam function combination method. The active control of the flexible hub-plate system was investigated using the theory of variable structure control. The results of numerical simulation of vibration control were given by Matlab, and the results were discussed.

关 键 词：柔性航天器 变结构控制 中心刚体.柔性板模型 振动控制 

分 类 号：V474.2[航空宇航科学与技术—飞行器设计]