The invention provides a solar array driving swinging method for a low-dip-angle orbit radar satellite. The method comprises the following steps of firstly, determining the variation range of the included angle beta between the solar vector and a satellite orbit plane according to the dip angle i of an orbit; secondly, determining an installation plane and an installation angle of a solar array according to the oblique flying state and the configuration layout of the radar satellite; thirdly, determining the swinging angle of the solar array according to the satellite flying attitude and the included angle beta between the solar vector and the satellite orbit plane, and then determining the driving state of the solar array. According to the solar array driving swinging method, a satellite has five in-orbit states totally according to the angle beta variation condition of the satellite and has the three flying attitudes including 45-degree on left side viewing, level flight and 45-degree on right side viewing. According to the tip angle of the orbit, the solar array driving swinging state of the radar satellite is reasonably set, and it is ensured that the illumination angle within the whole service life of the satellite is larger than 50 degrees.


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    Titel :

    Solar array driving swinging method for low-dip-angle orbit radar satellite


    Beteiligte:
    LU QING (Autor:in) / SUN YONGYAN (Autor:in) / WAN XIANGCHENG (Autor:in) / CHEN YUNLI (Autor:in)

    Erscheinungsdatum :

    2015-11-11


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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