对日地平动点附近的航天器编队控制问题进行研究,为解决基于局部线性化模型设计轨道保持控制器时存在的控制精度不高、模型精确性过度依赖等问题,提出基于圆型限制性三体问题的日-地/月系统L2点附近主从式航天器编队飞行的相对位置控制问题的解决方法.将主航天器设定在Halo轨道上,从航天器利用自抗扰控制方法控制在主航天器周围,编队系统内的未知动力学和外部扰动由扩张状态观测器获得,并利用非线性误差反馈对其进行补偿.数值仿真结果显示采用0.1 μN到10 mN的控制力即可使航天器相对位置误差控制在位置精度要求范围内,同时在存在未知干扰的情况下该方法依然具有很好的鲁棒性,从而验证优越性.%The problem of relative position control is addressed for spacecraft formation flying around the Sun-Earth/Moon L2 libration point.In order to avoid the problem of low precision and dependence on accurate model which occurs when controllers are designed according to linearized models,a relative position control technique is proposed that utilizes the framework of the circular restricted three-body problem.Assuming that the leader spacecraft is in a fixed halo orbit,the position of each follower relative to the leader is controlled to approach to a constant via using the active disturbance rejection control method.In this method,the unknown dynamics and external disturbances of the formation flying system are estimated by an extended state observer,which are compensated by a nonlinear state error feedback control law in real time.The numerical simulations show that the relative position errors obtained by the proposed method are all within the demanding range using the thrust from 0.1 μN to 10 mN.Meanwhile,the proposed method has good robustness against unknown disturbances and shows the superiority in control technique.
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