TY - JOUR
T1 - Magnetic plasma deorbit system for nano- and micro-satellites using magnetic torquer interference with space plasma in low Earth orbit
AU - Inamori, Takaya
AU - Kawashima, Rei
AU - Saisutjarit, Phongsatorn
AU - Sako, Nobutada
AU - Ohsaki, Hiroyuki
N1 - Publisher Copyright:
© 2015 IAA. Published by Elsevier Ltd. All rights reserved.
PY - 2015/7/1
Y1 - 2015/7/1
N2 - 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.
AB - 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.
KW - Deorbit
KW - Magnetic plasma deorbit
KW - Magnetic torquers
KW - Nano- and micro-satellites
KW - Space plasma
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U2 - 10.1016/j.actaastro.2015.02.025
DO - 10.1016/j.actaastro.2015.02.025
M3 - Article
AN - SCOPUS:84927132265
VL - 112
SP - 192
EP - 199
JO - Acta Astronautica
JF - Acta Astronautica
SN - 0094-5765
ER -