对偏差Walker星座卫星的接近轨道设计  

Orbit Design of Approaching Drifty Walker Constellation

作　　者：张敬[1] 王威[1] 郗晓宁[1] 

机构地区：[1]国防科技大学机电工程与自动化学院,长沙410073

出　　处：《宇航学报》2008年第4期1200-1204,共5页Journal of Astronautics

基　　金：武器装备预研基金(51400201013KG01);武器装备预研重点基金(6140551)

摘　　要：文献[1-3]已研究了单航天器无需变轨对理想Walker星座多星交会的轨道设计,在此基础上,针对接近偏差Walker星座多星的轨道设计开展了研究。结合最小二乘算法与启发式的搜索算法,提出了一种轨道设计的思想,并进行了建模和数值仿真分析。研究结果可为单航天器无需变轨对星座多星接近提供理论依据。Orbit design about single spacecraft intersecting multiple satellites of Walker Constellation without maneuver has been discussed in Ref. 1, 2, 3, on the base of it, the orbit design about the approach to multiple satellites of drifty Walker Constellation is researched in this paper. With the least square and heuristic search method, the Orbit design idea is put forward in this paper, and then the modeling and simulation analysis are done. The theoretical proof is provided for single spacecraft close approaching multiple constellation satellites without Orbital Maneuver by research findings.

关 键 词：WALKER星座 轨道设计 轨道摄动 最小二乘法 

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]