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  • Device for passive CubeSats deorbiting

    Paper number

    IAC-19,E2,4,5,x52670

    Author

    Dr. Vera Mayorova, Russian Federation, Bauman Moscow State Technical University

    Coauthor

    Dr. Nikolay Nerovny, Russian Federation, Bauman Moscow State Technical University

    Coauthor

    Ms. Ekaterina Timakova, Russian Federation, Bauman Moscow State Technical University

    Coauthor

    Ms. Valeriia Melnikova, Russian Federation, Bauman Moscow State Technical University

    Coauthor

    Mr. Maxim Koretskii, Russian Federation, Bauman Moscow State Technical University

    Coauthor

    Mr. Shapovalov Anatoly, Russian Federation, Bauman Moscow State Technical University

    Coauthor

    Mr. Aleksandr Borovikov, Russian Federation, Bauman Moscow State Technical University

    Coauthor

    Ms. Anastasiia Ignateva, Russian Federation, Bauman Moscow State Technical University

    Coauthor

    Mr. Alexandr Zakharchenko, Russian Federation, Bauman Moscow State Technical University

    Coauthor

    Mr. Sergei Polschikov, Russian Federation, Bauman Moscow State Technical University

    Coauthor

    Ms. Svetlana Porseva, Russian Federation, Bauman Moscow State Technical University

    Coauthor

    Mr. Nikita Lazarev, Russian Federation, Bauman Moscow State Technical University

    Year

    2019

    Abstract
    Currently, CubeSat satellites are becoming an increasingly popular design solution. The development of the payload makes it possible to perform more and more serious tasks for small spacecraft, such as remote sensing of the Earth, conducting astronomical observations, conducting technological and scientific experiments, providing communications, and performing tasks of automatic interplanetary stations. The small dimensions of the CubeSats and, consequently, the small atmospheric drag allow such devices to exist in low orbits for a long time after the end of their service life.
    
    In this work, the students developed a rotary sail device, which provides deorbiting of the nanosatellites in passive mode. 
    
    Due to small dimensions, the device can be integrated into CubeSat of any typical size. At the end of the nanosatellite service life the onboard sail can be opened, which makes the deorbiting process much faster due to increased atmospheric drug. 
    
    The paper presents the feasibility of this device for nanosatellites weighting up to 12 kg, taking into account the different solar activity, the orientation of the spacecraft, the orbit parameters, as well as the design of the device corresponding to the CubeSat Design Specification standard. Currently experimental prototype of the sail device has been developed and its operability in simulated space environment is confirmed. 
    
    Flight testing of the device is planned in 2020 within the space experiments conducted by Bauman Moscow State Technical University.
    Abstract document

    IAC-19,E2,4,5,x52670.brief.pdf

    Manuscript document

    IAC-19,E2,4,5,x52670.pdf (🔒 authorized access only).

    To get the manuscript, please contact IAF Secretariat.