挠性航天器大角度机动的变结构控制  

Variable Structure Control for Large Angle Maneuvering of Flexible Spacecraft

作　　者：周连文[1] 周军[1] 

机构地区：[1]西北工业大学

出　　处：《航天控制》2003年第3期48-52,共5页Aerospace Control

摘　　要：考虑刚性主体上带有挠性梁的航天器 ,在建立挠性系统动力学模型的基础上 ,采用等速趋近率的滑模变结构控制策略进行大角度机动控制 ,并通过最优控制理论设计弹性稳态器 ,抑制由于刚体运动而激发的弹性振动 ,实现了旋转机动的同时 。This paper is concerned with large angle slew maneuvering of flexible spacecraft, consisting of a rigid central body and a flexible beam. The dynamic model is derived by the assumption mode method. The variable structure control (VSC) method is applied to drive slew maneuvering. To suppress the simultaneous elastic vibration in movement, an elastic stabilizer is designed by using the LQR control method. Numerical simulation results are presented to show the effectiveness of the proposed control strategy.

关 键 词：航天器 挠性结构 变结构控制 弹性稳态器 振动抑制 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]