When a satellite is separated from the launch vehicle, it spins around in an uncontrolled way. This so-called tumbling has to be stopped and the initial angular rate must be controlled within the required range before satellite three-axis stabilization, and this is called detumbling. As such, the first task of Attitude and Orbit Control Subsystem (AOCS) is detumbling. Due to the significant savings in terms of overall spacecraft mass and complexity, magnetic torquers are used instead of thrusters for detumbling especially in small LEO satellites. The simple-to-implement B-dot algorithm is widely adopted to detumble a rotating satellite from any initial angular rate down to approximately near-zero rate. However, if the sensing or actuation duration of the detumbling algorithm is not tuned appropriately, the satellite might actually spin up instead of detumbling. In order to avoid such cases, this paper presents a modified B-dot algorithm which varies the actuation duration based on the angular rate of the satellite.


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    Title :

    Detumbling of Nano Satellites with Variable Magnetic Torquer on Time—A Practical Implementation


    Additional title:

    Lect. Notes Electrical Eng.



    Conference:

    International Conference on Automation, Signal Processing, Instrumentation and Control ; 2020 February 27, 2020 - February 28, 2020



    Publication date :

    2021-03-05


    Size :

    15 pages





    Type of media :

    Article/Chapter (Book)


    Type of material :

    Electronic Resource


    Language :

    English




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