基于相对偏心率/倾角矢量的编队控制方法  

Formation control approach based on relative eccentricity/inclination vector

作　　者：贺东雷[1] 曹喜滨[2] 马骏[1] 刘品雄[1] 

机构地区：[1]中国空间技术研究院研发部,北京100094 [2]哈尔滨工业大学卫星技术研究所,黑龙江哈尔滨150080

出　　处：《系统工程与电子技术》2011年第4期833-837,共5页Systems Engineering and Electronics

摘　　要：基于高斯摄动方程,分别提出了效率高及燃耗少的两种编队脉冲控制方法。两方法均设计了同样的法向脉冲修正轨道面外队形偏差。对于轨道面内队形偏差,方法一设计了径向脉冲和径向、迹向的"合力脉冲"完成修正控制;方法二设计了两迹向脉冲实现对相对半长轴、偏心率和近地点幅角的修正,以及两径向脉冲来消除相对平近点角偏差。理论分析与仿真结果表明,与经典五脉冲控制方法相比,方法一和方法二分别具有高效和燃耗少等优点。Based on Gauss perturbation equation,two kinds of formation impulse control methods with high efficiency and small fuel consumption are put forward respectively.For the formation error out of an orbit plane,the same cross-track control impulse is designed for both methods.For the formation error within a plane,the first method designs one radial control impulse and one joint control impulse composed of radial and in-track efforts.The second method designs two in-track control impulses to correct the errors of the relative semi-major axis,eccentricity as well as an argument of perigee,and two radial control impulses to correct the relative mean anomaly error.Both theory analysis and simulation results show that compared with the traditional five-impulse control method,the two methods have the advantages of high efficiency and small fuel consumption.

关 键 词：卫星编队 队形控制 相对偏心率/倾角矢量 高斯摄动方程 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]