双视线测量相对导航方法误差分析与编队设计

Error analysis and formation design for double line-of-sight measuring relative navigation method

空间非合作目标的相对导航是在轨维护和近距离监视任务中的关键技术,目前的研究表明仅有视线测量条件下中距离相对导航沿距离方向的观测度较差,而基于双视线测量的相对导航方法可以有效解决该问题。为此,研究了两个追踪航天器所组成的编队,在双视线测量条件下进行自主相对导航的方法。首先,详细地介绍了双视线测量相对导航方案的构成以及具体的导航算法;其次,根据两个追踪航天器与目标航天器的几何构型,推导双视线测量方法中的误差传递规律,并分析其中的影响因素;然后,对两个追踪航天器的编队构型进行设计,并分析编队构型对该方法导航性能的影响;最后,通过数值仿真对上述相关的结论进行验证。

Relative navigation of the non-cooperative space target is a key technology for the missions such as on-orbit servicing and close-range surveillance.Recent research shows that a weak observation exists along the range direction when the line-of-sight angle is used as the measurement information for medium range relative navigation,and double line-of-sight relative navigation is an effective solution to this problem.This paper studies an autonomous double line-of-sight measurement relative navigation method based on the formation of dual chase spacecraft.The overall architecture and detailed algorithms for the double line-of-sight measurement relative navigation method are introduced.Based on the geometric configuration among the dual chase spacecraft and the target,the propagation equation for the errors in the double line-of-sight measurement method is developed and its in-fluencing factors are analyzed.The configuration of the dual chaser formation and its influence on the performance of the method is also discussed.Numerical simulations verifies the relevant conclusions obtained.