地球静止轨道共位控制策略研究  

The Strategies and Algorithms Study For Multi-GEO Satellites Collocation

作　　者：李恒年[1,2] 高益军[3] 余培军[2] 李济生 黄永宣[1] 

机构地区：[1]西安交通大学系统工程研究所,西安710048 [2]中国西安卫星测控中心,西安710043 [3]中国航天科技集团公司五院502所,北京100080 [4]总装备部科学技术委员会,北京100034

出　　处：《宇航学报》2009年第3期967-973,共7页Journal of Astronautics

摘　　要：双星或多星共位是解决地球静止卫星轨位紧张的主要手段,共位控制策略是保证共位卫星安全的必然需求。综述了地球静止轨道共位控制策略的设计方法和数学原理;通过建立共位卫星最小接近距离与轨道偏置量的约束方程,给出经度隔离漂移环分配算法,绕飞隔离偏心率偏置控制算法,和外切隔离圆四星共位偏心率相对偏置算法,基于隔离带的倾角矢量四象限偏置算法;分析和比较了不同控制策略的适用条件、代价和控制精度;以实际测量的相对距离变化,分析了共位控制策略的有效性和安全性。The principle of collocation separation strategies is leaving the relative distance beyond collision risk with different set of orbit parameters for multi-GEO to share with same nominal longitude, and making use of the station keeping opportunities to maintenance the difference during the mission, to ensure the safety of collocated satellites. This paper established the relationship between the separation distance with uncertainty of OD and the orbital element off-set for each pair of collocated satellite, And put forward new methods to build such relationship to meet with the challenge of putting four GEO satellites in one slot, the algorithms for each satellite to locate the eccentricity and inclination were also given which including how to use longitude, absolute eccentricity, relative eccentricity and the combined eccentricity-inclination separation strategies. The simulations have been carried out to ascertain that the minimal distance could ensure not only the physical separation also the Radio Frequency （RF） separation with this new strategy.

关 键 词：静止轨道 共位控制 位置保持 轨道控制 

分 类 号：V247[航空宇航科学与技术—飞行器设计]