We present method for in-flight signal processing and calibration of a strap-down inertial navigation system (SINS) for the information mini-satellites at low Earth orbit. We have applied the SINS correction based on the signals of a sun-magnetic system and consider the problem at a long-term forecasting of the mini-satellite's orbital motion.


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    Title :

    Low cost attitude determination system for a LEO information mini-satellite


    Contributors:


    Publication date :

    2015-06-01


    Size :

    1349166 byte




    Type of media :

    Conference paper


    Type of material :

    Electronic Resource


    Language :

    English




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