For full-scale lunar explorations, it is essential to establish constant communication with the far side of the Moon. One idea to accomplish this is telecommunication via a solar sail orbiting the L2 point. The coupled attitude-orbit control is a promising technique to reduce a solar sail mass. This paper proposes a coupled attitude-orbit control law for a combination of solar electric propulsion and a solar sail equipped with reflectivity control devices (RCDs) in the Earth-Moon system. An artificial halo orbit that takes the solar radiation pressure into consideration is designed to be used as the reference orbit. Feedback control laws to maintain the satellite onto the orbit are designed using a backstepping method. From the numerical simulations, it is shown that the use of RCDs reduces the fuel consumption required for maintaining the satellite onto the orbit. Presented as Paper 2016-5371 at the AIAA/AAS Astrodynamics Specialist Conference, Long Beach, CA, 13-16 September 2016


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    Titel :

    Solar Sail Orbital Control Using Reflectivity Variations near the Earth-Moon L 2 Point


    Beteiligte:


    Erscheinungsdatum :

    2017




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch



    Klassifikation :

    Lokalklassifikation TIB:    770/7040
    BKL:    55.54 Flugführung





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