The spatial heliocentric flight Earth–Mars of a non-perfectly reflecting solar sail spacecraft is considered. Thin-film control devices located along the perimeter of the solar sail are proposed as a control element. These spatial orientation controls are capable of changing their reflective characteristics depending on the voltage applied to them. A mathematical model of the photon pressure on the non-perfectly reflecting surface of the solar sail is described, taking into account the functioning of thin-film reflectivity control devices. An algorithm for generating a program for the nominal motion control of a solar sail spacecraft with and without thin-film control devices is described. The results of the Earth–Mars flight of a solar sail spacecraft have been obtained.


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    Titel :

    Method for motion control of solar sail spacecraft with reflectivity control devices in case of Earth–Mars flight


    Beteiligte:
    Khabibullin, R. M. (Autor:in) / Soloviev, Vladimir A. (Herausgeber:in) / Rogozin, Dmitry O (Herausgeber:in) / Aleksandrov, Anatoly A (Herausgeber:in) / Fedorov, Igor B (Herausgeber:in) / Mayorova, Vera I (Herausgeber:in)

    Kongress:

    XLV ACADEMIC SPACE CONFERENCE, DEDICATED TO THE MEMORY OF ACADEMICIAN S.P. KOROLEV AND OTHER OUTSTANDING NATIONAL SCIENTISTS — PIONEERS OF SPACE EXPLORATION ; 2021 ; Moscow, Russia


    Erschienen in:

    Erscheinungsdatum :

    20.07.2023


    Format / Umfang :

    8 pages





    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch



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