控制输入受限的挠性航天器有限时间姿态控制  

Finite-time Attitude Control of Flexible Spacecraft under Actuator Saturation

作　　者：汪飞舟[1] 贾庆贤[1] 王继河[1] 张德新[1] 邵晓巍[1] 

机构地区：[1]上海交通大学航空航天学院,上海200240

出　　处：《航天控制》2016年第5期59-63,69,共6页Aerospace Control

摘　　要：针对控制输入受限的挠性航天器有限时间姿态控制问题,提出一种将姿态路径优化和终端滑模控制相结合的方法。首先,为了解决控制受限以及挠性附件的振动问题,对航天器姿态机动路径进行了优化设计。其次,基于终端滑模控制思想,设计了一种有限时间控制器,利用Lyapunov稳定性理论证明了挠性航天器姿态控制系统的全局稳定性。最后的仿真结果表明,所设计的姿态控制器不仅保证了挠性航天器能在有限的时间内完成姿态机动,而且对空间环境干扰和挠性附件振动具有较强的鲁棒性。The finite -time attitude control of a flexible spacecraft under actuator saturation is researched by using a proposed method which is combining a path -planning method with terminal sliding mode control algorithm. Firstly, an optimal attitude path is suggested to solve the problem of actuator saturation and suppress vibration of flexible appendages. Then, a finite - time controller is designed, which is based on ter- minal sliding mode control, and the stability of overall system is proven by Lyapunov method and the finite- time convergence of the control system is also proven. Finally, simulation results demonstrate that the flexi- ble spacecraft is able to complete attitude maneuver in an arbitrary settling time and has an ideal robustness towards to disturbances and flexible vibration.

关 键 词：路径优化 高斯伪谱法 终端滑模控制 挠性航天器 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]