近圆参考轨道卫星编队洛仑兹力控制  

NEAR-CIRCULAR LOW-EARTH-ORBIT SPACECRAFT FORMATION CONTROL WITH LORENTZ FORCE

作　　者：彭超[1,2,3] 高扬[2] 

机构地区：[1]中国科学院光电研究院,北京100094 [2]中国科学院空间应用工程与技术中心,北京100094 [3]中国科学院研究生院,北京100080

出　　处：《力学学报》2012年第5期851-860,共10页Chinese Journal of Theoretical and Applied Mechanics

摘　　要：基于运动电荷在磁场中切割磁力线受到洛仑兹力作用的物理规律,分析了两种带电模式对经典轨道根数长期变化的影响:(1)卫星恒定带电模式;(2)前半个轨道周期卫星带电、后半周期不带电的非恒定带电模式.恒定带电模式可以有效地改变轨道升交点赤经、近地点幅角以及平近点角,对轨道半长轴、偏心率和倾角几乎不产生长期影响;而非恒定带电模式则可以有效地改变轨道偏心率.基于洛仑兹力作用下轨道根数长期变化规律以及轨道根数差描述的带电副星相对于不带电主星的运动,提出了利用洛仑兹力以及两种带电模式实现地球低轨近圆参考轨道卫星编队的控制策略,包括编队绕飞椭圆大小重构与编队中心漂移控制,解析求解了副星所需的带电量,并利用数值仿真验证了洛仑兹力控制的可行性.需要指出的是,洛仑兹力轨道控制无需消耗推进工质.Based on the physical law that charged particle experiences Lorentz force in magnetic field, we have analyzed the long-term averaged changes in classical orbital elements with two different charging modes： （1） The spacecraft is charged constantly; （2） The spacecraft is charged in the first half orbital revolution and uncharged in the second half. It is found that, in the first mode, the long-term changes in the longitude of ascending node, argument of periapsis and mean anomaly, can be effectively controlled by Lorentz force, while semi-major axis, eccentricity, and inclination can not be. Meanwhile, the eccentricity can be varied in the second mode. Based on the averaged evolution of the orbital element difference between two spacecrafts in formation - one is charged deputy and the other is uncharged chief, we proposed a new propellantless means for formation control - adjusting the size of fly-around elliptical relative orbit and formation center, when the chief spacecraft＇s reference orbit is near-circular. The required charge-to-mass ratio for formation control is derived analytically and the effectiveness of Lorentz-force formation control is verified by numerical simulations.

关 键 词：带电卫星 地球磁场 洛仑兹力 卫星编队 轨道根数差 编队重构 

分 类 号：V412.41[航空宇航科学与技术—航空宇航推进理论与工程]