Abstract Formation flying in high Earth orbit relies on accurate relative navigation information for both precise formation control and accurate interpretation of science data. A relative navigation filter is developed here that enhances the linearity of the dynamic model by framing the state in Keplerian elements. The dynamic model and filter performance are presented for medium and high Earth orbits with limited measurement availability. The effect of higher order gravity terms, solar radiation pressure, the third-body effects of the Sun and Moon, and atmospheric drag on estimation accuracy is considered. Relative semimajor axis accuracy of 0.81 m and relative position accuracy of 0.89 m are obtained for vehicles separated by 10–170 km using GPS measurements only. This represents an order of magnitude improvement over previously reported relative navigation performance in high Earth orbit.
Analysis of relative navigation in high earth orbits
The Journal of the Astronautical Sciences ; 55 , 1 ; 23-52
2007-03-01
30 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Analysis of relative navigation in high earth orbits
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