The Solar Dynamics Observatory (SDO) spacecraft is a sun-pointing, semi-autonomous satellite that will allow nearly continuous observations of the Sun with a continuous science data downlink. The science requirements for this mission necessitate very strict sun-pointing requirements, as well as continuous ground station connectivity through high gain antennas (HGAs). For SDO s onboard attitude control system to successfully point the satellite at the Sun and the HGAs at the ground stations with the desired accuracy, in addition to the need for accurate sensors it must have good onboard knowledge of the ephemerides of the Sun, the spacecraft, and the ground station. This paper describes the minimum force models necessary for onboard ephemeris generation in support of an attitude control system. The forces that were considered include the Sun s point mass, Moon s point mass, solar radiation pressure (SRP), and the Earth s gravity with varying degree and order of terms of the geopotential.


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    Titel :

    SDO Onboard Ephemeris Generation


    Beteiligte:
    Berry, Kevin E. (Autor:in) / Liu, Kuo-Chia (Autor:in)

    Kongress:

    AIAA Astrodynamics Specialist Conference ; 2008 ; Honolulu, HI, United States


    Erscheinungsdatum :

    2008-08-18


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    SDO Onboard Ephemeris Generation

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    SDO Onboard Ephemeris Generation

    Berry, K. / Liu, K. | British Library Conference Proceedings | 2008


    SDO Onboard Ephemeris Generation

    Berry, Kevin / Liu, Kuo-Chia | AIAA | 2008


    Compressed polynomial approach for onboard ephemeris representation

    SHEELA, B. V. / PADMANABHAN, P. | AIAA | 1990


    Design and Implementation of Software Algorithms for Topex/Poseidon Onboard Ephemeris Representations

    Leavitt, R. K. / Salama, A. H. / American Astronautical Society et al. | British Library Conference Proceedings | 1993