Analysis of Magnetic Dipole Moment for a 300-W Solar-Cell Array

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The attitude information of spacecraft can be obtained by the sensors attached to it using a star tracker, three-axis magnetometer, three-axis gyroscope, and a global positioning signal receiver. By using these sensors, the spacecraft can be maneuvered by actuators that generate torques. In particular, electromagnetic-torque bars can be used for attitude control and as a momentum-canceling instrument. The spacecraft momentum can be created by the current through the electrical circuits and coils. Thus, the current around the electromagnetic-torque bars is a critical factor for precisely controlling the spacecraft. In connection with these concerns, a solar-cell array can be considered to prevent generation of a magnetic dipole moment because the solar-cell array can introduce a large amount of current through the electrical wires. The maximum value of a magnetic dipole moment that cannot affect precise control is 0.25 A.m(2), which takes into account the current that flows through the reaction-wheel assembly and the magnetic-torque current. In this study, we designed a 300-W solar cell array and presented an optimal wire-routing method to minimize the magnetic dipole moment for space applications. We verified our proposed method by simulation.
Publisher
KOREAN SPACE SCIENCE SOC
Issue Date
2019-09
Language
English
Article Type
Article
Citation

JOURNAL OF ASTRONOMY AND SPACE SCIENCES, v.36, no.3, pp.181 - 186

ISSN
2093-5587
DOI
10.5140/JASS.2019.36.3.181
URI
http://hdl.handle.net/10203/267726
Appears in Collection
RIMS Journal PapersAE-Journal Papers(저널논문)
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