摘要
将H∞磁姿态控制律用于有外界扰动和结构化摄动的圆轨道微小卫星姿态控制系统。给出了H∞控制算法,并从理论上证明了系统的稳定性。通过将地磁场近似为偶极子,把时变Riccati方程的求解简化为时不变Riccati方程的处理,同时引入扩张因子以避免出现饱和。理论分析和仿真试验结果表明,该姿态控制律可行,其姿态控制精度高、鲁棒性强。
The magnetic attitude H∞ control was applied to the microsatellite in a circle orbit that had external disturb and the structural perturbation in this paper. The control law was given, and the system stability was proved in theory. To simplify the computation, the Riccati equation was changed from time-varying to non-time-varying when the earth magnetic field was treated as dipolar. And the extended factor was induced to avoid saturation. The theory analysis and simulation results showed that this magnetic attitude H∞ control law was feasible, which had high attitude control accuracy and robustness.
出处
《上海航天》
北大核心
2006年第3期1-6,共6页
Aerospace Shanghai
关键词
微小卫星
姿态控制
磁力矩器
H∞控制
姿态精度
鲁棒性
Microsatellite
Attitude control
Magnetorquer
H∞ control
Attitude control accuracy
Robustness
