摘要
针对基于星间相对测量的相对导航算法中由测量方程将相对轨道拟平根数转化为相对位置过程导致的模型非线性,提出一种基于约化相对轨道拟平根数的卫星编队导航方法.该方法通过编队卫星之间一段时间的切向漂移估计半长轴偏差,合理处理半长轴偏差对双星相对动力学的影响,克服了模型线性化造成的误差,能够实现长期稳定的高精度卫星编队导航.
Based on inter-satellite measurement and reduced relative orbit elements of satellites, an im- proved approach of formation navigation is investigated. The traditional navigation algorithm transforms the relative orbit elements into the relative position by measuring equations, which results in nonlinearity of the navigation model. In the improved approach, the difference of semi-axis is estimated via the excur- sion in along-track. The problem of linearization error can be solved by using the difference of semi-axis, which has an important influence on relative dynamic of satellites. The method can realize a long-term stable and high-precision navigation of satellites formation.
出处
《空间控制技术与应用》
CSCD
北大核心
2017年第1期30-35,共6页
Aerospace Control and Application
基金
上海市青年科技启明星计划资助项目(17QB1401400)
关键词
卫星编队
长期稳定
相对导航
约化相对轨道拟平根数
半长轴偏差
satellites formation
long-term stabilization
relative navigation
reduced relative orbit ele- ments
difference of semi-axis
