Abstract Orbit determination of spacecraft in orbit has been mostly dependent on either GNSS satellite signals or ground station telemetry. Both methods present their limitations, however: GNSS signals can only be used effectively in earth orbit, and ground-based orbit determination presents an inherent latency that increases with the Earth–spacecraft distance. For spacecraft flying formations, an alternative method of orbit determination, independent of external signals, consists in the observation of the spacecraft’s position with respect to the central body through the relative positioning history of the spacecraft within the formation. In this paper, the potential of the relative positioning method is demonstrated in the context of the SunRISE mission, and compared with the mission’s previously proposed orbit determination methods. An optimization study is then made to find the optimal placement of a new spacecraft in the formation so as to maximize the positioning accuracy of the system. Finally, the possibility of removing part of the system’s relative bearing measurements while maintaining its observability is also studied. The resulting system is found to be observable, but ill-conditioned.
Highlights Near-GEO Spacecraft formation orbit determination through relative positioning. Absolute state estimation improves relative positioning accuracy. Addition of a new observability optimized spacecraft to improve positioning accuracy. System partially deprived of relative bearing is observable, but ill-conditioned.
Autonomous orbit determination for satellite formations using relative sensing: Observability analysis and optimization
Acta Astronautica ; 200 ; 301-315
2022-08-05
15 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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