摘要
对于三轴角动量飞轮式卫星的姿态控制提出了一种鲁棒控制设计方法。针对挠性卫星中存在的未建模动态以及参数不确定性问题,基于H∞控制理论对姿态控制器进行了设计,通过选取合适的加权函数将姿态控制问题转化为标准H∞控制问题,进而获得所需控制器。并与PID控制器进行了仿真实验对比,仿真结果表明,对于系统中存在的干扰和参数不确定性,H∞控制具有良好的鲁棒稳定性与动态性能。
A robust control method is derived for attitude control of a three-axis angular momentum wheel satellite. This paper is intended to propose a new method solving neglected dynamics and parameter uncertainties for flexible satellite. The attitude controller is designed using H∞ control method. Attitude control problem is converted into a standard H∞control problem through choosing suitable weighting functions. Experiments have been taken compared with PID controller by simulation. The simulation results show the present H~ control system is robust stable and has good dynamic performance against the parameter uncertainties and various disturbances for the satellite attitude control system.
出处
《黑龙江大学工程学报》
2012年第2期104-108,共5页
Journal of Engineering of Heilongjiang University
关键词
姿态控制
鲁棒控制
H∞控制
挠性卫星
attitude control
robust control
H∞ control
flexible satellite
