Journal of Astronomy and Space Sciences (Sep 2019)

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

  • Goo-Hwan Shin,
  • Dong-Guk Kim,
  • Se-Jin Kwon

DOI
https://doi.org/10.5140/JASS.2019.36.3.181
Journal volume & issue
Vol. 36, no. 3
pp. 181 – 186

Abstract

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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.

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