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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    Title :

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



    Conference:

    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


    Published in:

    Publication date :

    2023-07-20


    Size :

    8 pages





    Type of media :

    Conference paper


    Type of material :

    Electronic Resource


    Language :

    English



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