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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L_2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0.1μN到10 m N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.
In order to solve the problems that the control precision is not high and the model accuracy is overly dependent when designing the track keeping controller based on the local linearization model, The problem of how to control the relative position of the master-slave spacecraft fleet in the vicinity of the L_2 point of the earth-moon system is solved. The main spacecraft is set on the Halo orbit and the spacecraft is controlled by the ADRC Around the main spacecraft, unknown dynamics and external perturbations in the formation system are obtained from the extended state observer and compensated by nonlinear error feedback. The numerical simulation results show that with the control force of 0.1 μN to 10 mN, The spacecraft relative position error is controlled within the range of position accuracy, and the method still has good robustness in the presence of unknown interference to verify the superiority.