The paper presents simple methods for determining moderately eccentric orbits from the satellite; linear combinations of time-of-flight measurements are used exclusively. The method is based on a third-order expansion of the satellite law of motion in terms of orbital eccentricity epsilon. Thus, the approximation is very good for epsilon < or = 0.1. A simple technique, which is insensitive to systematic sensor errors, is proposed to circularize an orbit automatically. Another application is the automatic station-keeping of satellites, which has been realized for the first time, using the ideas of this paper, in the recently launched Lincoln Experimental Satellite LES-6. (Author)


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Orbit Determination from the Satellite


    Beteiligte:
    A. Braga-Illa (Autor:in)

    Erscheinungsdatum :

    1968


    Format / Umfang :

    9 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Orbit determination from the satellite.

    BRAGA-ILLA, A. | AIAA | 1969


    Satellite orbit determination

    Hildebrand, C. E. / Christensen, D. H. / Boggs, D. H. et al. | NTRS | 1979


    Satellite orbit determination

    Jordan, J. F. / Boggs, D. H. / Born, G. H. et al. | NTRS | 1973


    Viking satellite orbit determination

    Hildebrand, C. E. / Christensen, E. J. / Boggs, D. H. et al. | NTRS | 1977


    Viking satellite orbit determination

    HILDEBRAND, C. / CHRISTENSEN, E. / BOGGS, D. et al. | AIAA | 1977