Abstract We propose a magnetic plasma deorbit (MPD) system using magnetic torquers (MTQs) for inducing the deorbit of nano- and micro-satellites. Currently, orbital space debris from these satellites is a matter of increasing concern to all satellites; however, deorbit systems have not been installed in most of these satellites. In general, nano- and micro-satellites have severe constraints on their power consumption, cost, and mass; therefore, it is difficult to install additional components that are not used in their main missions. The MPD system proposed in this study utilizes a drag force caused by the interaction between in-orbit space plasma and MTQs for attitude control. Because most nano- and micro-satellites already have MTQs installed for use in their attitude control, no additional thrusters and structures need to be installed for this deorbit system. Therefore, many satellites can be made to deorbit after their missions, which will reduce the accumulation of space debris. The present study assesses the duration required for the MPD to achieve deorbit using a plasma drag force model.

    Highlights We proposed a novel de-orbit system called magnetic plasma deorbirt (MPD) system. With this method, a satellite can achieve de-orbit using only MTQs for its attitude control system. In MPD, a satellite does not need any additional components for only de-orbit. A 10-kg satellite with a 100-Am2 MTQ can complete it’s de-orbit operation in 900 days.


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    Title :

    Magnetic plasma deorbit system for nano- and micro-satellites using magnetic torquer interference with space plasma in low Earth orbit


    Contributors:

    Published in:

    Acta Astronautica ; 112 ; 192-199


    Publication date :

    2015-02-19


    Size :

    8 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English





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