We consider a small information satellite which may be placed on an orbit with altitude from 600 up to 1000 km. The satellite attitude and orbit control system contains a strap-down inertial navigation system, cluster of four reaction wheels, magnetic driver and a correcting engine unit with eight electro-reaction engines. We study problems on design of algorithms for spatial guidance, in-flight identification and adaptive-robust control of the satellite motion on sun-synchronous orbit.


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    Title :

    Guidance and adaptive-robust attitude & orbit control of a small information satellite


    Contributors:
    Somov, Ye. (author) / Butyrin, S. (author) / Somov, S. (author) / Somova, T. (author) / Testoyedov, N. (author) / Rayevsky, V. (author) / Titov, G. (author) / Yakimov, Ye. (author) / Ovchinnikov, A. (author) / Mathylenko, M. (author)

    Conference:

    ICNPAA 2016 WORLD CONGRESS: 11th International Conference on Mathematical Problems in Engineering, Aerospace and Sciences ; 2016 ; La Rochelle, France


    Published in:

    Publication date :

    2017-01-27


    Size :

    10 pages





    Type of media :

    Conference paper


    Type of material :

    Electronic Resource


    Language :

    English



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