一种GEO卫星太阳光遮挡轨迹设计与控制方法  

A Design and Control Method of Sun Occlusion Trajectory for GEO Satellite

作　　者：黎飞[1] 雷拥军[1,2] 冯佳佳 LI Fei;LEI Yong-jun;FENG Jia-jia(Beijing Institute of Control Engineering,Beijing 100094,China;Science and Technology on Space Intelligent Control Laboratory,Beijing 100094,China)

机构地区：[1]北京控制工程研究所,北京100094 [2]空间智能控制技术重点实验室,北京100094

出　　处：《宇航学报》2022年第2期198-205,共8页Journal of Astronautics

基　　金：国家重点研发计划(2018YFA0703800);空间智能控制技术国防科技重点实验室基金项目(ZDSYS-2018-04)。

摘　　要：为满足未来GEO卫星空间对抗手段多样化的需求,提出了一种对太阳光进行遮挡的新型空间攻防系统。首先,分析了太阳矢量在目标航天器轨道坐标系中的运动特性,基于近距离相对运动方程设计了追踪航天器的圆锥面绕飞轨迹,推导了N等份遮挡轨迹下的总速度增量表达式。其次,考虑非线性误差和复杂空间环境摄动的影响,采用自抗扰控制方法设计了闭环控制律。最后,仿真结果表明,圆锥面绕飞轨迹设计可行,在闭环控制律的作用下具有较高的太阳光遮挡精度,可成为一种有效的空间攻防手段。A new space attack and defense system that shields sunlight is proposed in order to meet the diversified requirements of future GEO satellite space confrontation means.Firstly,the motion characteristics of the sun vector in the target spacecraft’s orbital coordinate system are analyzed,and the trajectory of the conical surface of the tracking spacecraft is designed based on the close-distance relative motion equation,and the total speed incremental expression under the N equal parts occlusion trajectory is derived.Secondly,considering the influence of nonlinear error and complex space environmental perturbation,a closed-loop control law is designed based on ADRC method.Finally,the simulation results show that the design of conical surface trajectory is feasible,and the closed loop control law has a high accuracy of solar shielding,which can be an effective means of space attack and defense.

关 键 词：空间对抗 GEO卫星 太阳光遮挡 圆锥面绕飞轨迹 自抗扰控制方法 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]