接近多颗Walker星座卫星的轨道选择和优化  

Orbital Selection and Optimization for Approaching Multiple Walker Constellation Satellites

作　　者：唐荣[1] 王威[2] 付晓峰[2] 

机构地区：[1]中国国防科技信息中心八室,北京100036 [2]国防科技大学3院,湖南长沙410073

出　　处：《计算机仿真》2008年第4期53-56,共4页Computer Simulation

基　　金：武器装备预研重点基金项目(6140551)

摘　　要：由于Walker星座的结构特性,通过航天器轨道设计可实现航天器对多颗非共轨Walker星座卫星的近距离接近。在距离约束条件下,从理论上分析了航天器平台近距离接近Walker星座卫星时两者之间的时空关系,重点分析了角度关系,特别是分析了航天器接近星座卫星过程中的方位角变化规律。通过轨道相位的调整,对航天器平台轨道进行了优化;以此为基础对航天器轨道进行了选择和优化设计,结果表明:在百公里级的距离内,航天器在接近Walker星座卫星过程中能找到满足较高角度控制率要求的时间区间。最后给出仿真算例。There are a series of orbits on which spacecraft can close approach multiple non - coplane Walker Constellation satellites by orbital design, since Walker Constellation has special characteristics in construction. Based on distance constraint, theoretically the time and space relationships have been analyzed between the spacecraft and Walker constellation satellite when the spacecraft close approaches the Walker constellation satellite, especially the angular relationship, and the paper has analyzed the rule of azimuth variation in the course of the spacecraft approaching the Constellation satellites. The spacecraft＇s orbit has been optimized by orbital phase adjusting. The spacecraft orbits have been selected and optimized on the basis of the rule of azimuth variation. The results show that when the distance is confined to a level of hundreds of kilometers, the time range in which the requirement of angular rate can be met will be found in the course of approaching multiple Walker constellation satellites. A concrete example is also given.

关 键 词：近距离接近 星座 轨道优化 方位角 

分 类 号：V324.2[航空宇航科学与技术—人机与环境工程]