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.


    Zugriff

    Zugriff prüfen

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Analysis of relative navigation in high earth orbits


    Beteiligte:

    Erschienen in:

    Erscheinungsdatum :

    2007-03-01


    Format / Umfang :

    30 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




    Analysis of relative navigation in high earth orbits

    Lane, Christopher / Axelrad, Penina | Online Contents | 2007


    Analysis of Relative Navigation in High Earth Orbits

    Lane, Christopher | Online Contents | 2007


    Relative Semimajor Axis Uncertainty in High Earth Orbits

    Christopher Lane / Penina Axelrad | AIAA | 2007


    GPS World, Innovation: Autonomous Navigation at High Earth Orbits

    Bamford, William / Winternitz, Luke / Hay, Curtis | NTRS | 2005


    Analysis of Relative Navigation in Eccentric Orbits (AAS 06-047)

    Lane, C. / Axelrad, P. / American Astronautical Society | British Library Conference Proceedings | 2006