摘要
为解决航天器姿态控制中考虑非主轴惯量不确定性和外干扰的问题,设计了滑模控制器组成的鲁棒控制系统来处理系统中的参数不确定性及外干扰项的影响,并在滑模控制器的到达运动控制律设计中引入一个滞后因子来减小系统所需的最大控制力矩,从而节省航天器的控制成本.仿真结果验证了所设计控制器的性能,同时验证了控制律中的符号函数对于抑制抖振现象,提高控制精度的作用.
This paper deals with the controller design of the attitude control system of spacecraft. The sliding mode controller was proposed to avoid the influence of parameters＇ uncertainty and the external disturbance. The delay factor was introduced in the reaching-law to reduce the control torque required by the system, which could save on the payload of the spacecraft. The simulation results are illustrated to verify the designed controller. The effect of improving the stability of the controller is also verified by using the sign function.
出处
《北京理工大学学报》
EI
CAS
CSCD
北大核心
2011年第10期1198-1202,共5页
Transactions of Beijing Institute of Technology
基金
国家自然科学基金资助项目(10872029)
北京市科技新星项目(2009A22)
关键词
姿态控制
滑模控制
不确定性
鲁棒控制
航天器
attitude control
sliding mode control
uncertainty
robust control
spacecraft
