【作者】 陈健； 徐波；

【Author】 Chen Jian~1 Xu Bo~2 (1.College of Automation Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China) (2.College of Astronautics Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

【机构】 南京航空航天大学自动化学院； 南京航空航天大学航天学院；

【摘要】 以主从式卫星编队飞行为背景,在主星姿态已知的情况下,推导出从星相对主星的姿态运动学方程。在从星相对主星有大角度机动时,主从卫星姿态运动的非线性因素和耦合因素不容忽视,卫星长期运行过程中的参数摄动和外界干扰又使它成为一个不确定系统。为此本文首先针对从星的3个姿态通道设计参考模型。并运用反馈线性化理论使从星真实输出和参考模型输出构成的广义误差解耦为3个单输入单输出系统,然后运用分散滑动模态变结构控制理论对每个通道分别设计滑模变结构控制器。理论研究和数值仿真表明.所设计的控制器可以适用于从星相对主星大姿态角机动的情况,并对系统参数摄动和外界扰动输入具有较强的鲁棒性。更多还原

【Abstract】 Under the background of follower satellites flying around leader satellite and the assumption of known leader of attitude,the equation of follower relative attitude is developed.In this paper,the attitude channel of satellite is decoupled into three SISO linear systems by means of feedbaek- linearization.Then variable structure controller is designed based on the theory of decentralized sliding mode control with respect to each attitude channel,so as to obtain robustness to perturbation and disturbance.Theoretical research and numerical simulation indicate that the control system designed in this paper works properly even if in the case of large relative attitudes of follower satellite.更多还原