In the Earth-centered Velocity-Normal-Conormal (VNC) coordinate system, the Sun is in constant motion. Therefore, a Sun-pointing spacecraft will be in constant rotation relative to the Earth-centered VNC coordinate system. Because an individual Bumper run requires a fixed attitude, analyzing an extended period of time in constant rotation results in a large number of attitudes to be individually run in Bumper. This creates a need for a defined process for selecting appropriate attitudes to assess. An investigation into the mechanics driving attitude revealed patterns that can be leveraged to obtain the optimum attitudes to maximize fidelity while minimizing the number of Bumper runs. A key parameter to these patterns is Beta Angle, the angle between the orbit plane and Sun vector.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Process for Sun-Pointing Attitude in Earth Orbit


    Beteiligte:

    Erscheinungsdatum :

    14.03.2025


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Three‐axis global magnetic attitude control of earth‐pointing satellites in circular orbit

    Giri, Dipak / Mukherjee, Bijoy / T N, Bidul et al. | British Library Online Contents | 2017




    Magnetocoulombic Attitude Control of Earth-Pointing Satellites

    Giri, Dipak Kumar / Sinha, Manoranjan | AIAA | 2014


    Magneto Coulombic Attitude Control of Earth Pointing Satellites

    Sinha, Manoranjan / Giri, Dipak K. | AIAA | 2013