摘要
根据上面级飞行器存在强控制耦合和惯量耦合特性,基于上面级刚体姿态动力学简化模型,由变结构控制理论设计了上面级姿态控制律。采用趋近律减轻变结构控制引起的系统抖振。仿真结果表明:设计的控制律可自动适应强耦合对象特性,具强鲁棒性,使系统在有限时间收敛、精确跟踪。
According to the characteristics of the existence of strong control coupling and inertia coupling of top-level spacecraft,the attitude control law of top-level was designed using variable structure control theory based on the simplified model of attitude dynamics of rigid body in this paper.The buffeting caused by variable structure control was reduced by the reaching law.The simulation results showed that the designed control law could automatically adapt to the object properties of strong coupling with strong robustness,and the system was convergence and precise tracking in the limited time.
出处
《上海航天》
2011年第2期38-42,共5页
Aerospace Shanghai
关键词
多星发射上面级
姿态控制
变结构控制
趋近律
Top-level with multi-satellite
Attitude control
Variable structure control
Reaching law
