摘要
航天器在空间执行任务时必须按照一定的控制指令进行高精度的姿态控制。针对航天器上转动部件的运动会对姿态控制产生干扰的问题,推导了带有转动部件的航天器姿态动力学方程,并根据干扰力矩的特点,采用了一种对干扰具有自适应能力的RBF神经滑模姿态控制方法。仿真结果表明,该方法能有效克服转动部件运动产生的干扰,所设计的控制器有很好的控制性能和鲁棒性能。
The attitude of the on-orbit servicing spacecraft must be controlled accurately according to the command. Due to the disturbance to the attitude of spacecraft by the movement of payload, the detailed der- ivation of the dynamic equations of spacecraft with mobile bodies is given. The RBFNN siding mode attitude control method is adopted based on the characteristics of the disturbance torque. The simulation results show that this method can eliminate the effects of disturbance induced by disturbance torque onboard on the atti- tude control precision and the controller has good performance and robustness.
出处
《航天控制》
CSCD
北大核心
2012年第5期61-65,共5页
Aerospace Control
基金
国家863计划
关键词
转动部件
姿态控制
干扰力矩
RBF神经滑模控制
Mobile body
Attitude control
The disturbance torque
RBFNN siding mode control
