Abstract
The study makes an approach to the problem of circumlunar spacecraft navigation using the measurements from the global navigation satellite systems (GNSS) GLONASS, GPS, Galileo and BeiDou. Algorithms have been developed for determining the orbits of low- and high-orbit circumlunar spacecraft, based on the method of dynamic filtering of pseudo-range measurements from “reverse” navigation satellites (NS). The solution to the navigation problem has been simulated by the measurements from four GNSS, and by those from the NS of GLONASS and GPS only. Accuracy and dynamic characteristics of the obtained solutions have been determined and compared to similar solutions for geostationary spacecraft.
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