Design And Implementation Of The High-performance Magnetic Torquers For Low Earth Orbit Small Satellites

Since the concept of small satellites was proposed in the 1980s, its techniqueshave made great progress in recent years. The development of small satellites putsforward new demands for the Satellite's Attitude Control System (ACS) which is a veryimportant part of satellite. It requires the ACS to have the characteristics of simpleconfiguration, lightweight, long working time, and high reliability. Because magnetictorquers are relatively reliable, lightweight, and energy efficient, they are found to beattractive for small satellites especially low Earth orbit (LEO) small satellites. Thisthesis presents the design and implementation of the high-performance magnetictorquers for LEO satellites.After thoroughly collecting and investigating the literature in the field of magnetictorquers , the work principles of the magnetic torquers is analyzed, and the magneticfield of Earth and magnetic materials are discussed. The characteristic of dipolemagnetic moment of current-carrying wire is discussed and the material of the magneticrods is determined. The magnetic rods and control drive circuit are designed andconstructed. A measurement system on the Earth's magnetic field circumstance hasbeen established. Measurement of magnetic rods and control driver circuit has beencarried out. Test results show that the magnetic torquers had the characteristics of highmagnetic moment output, low remanence, the circuit is low power dissipation, easy tocontrol, and satisfied to the demands of designing.A new design of control circuit is developed. By analyzing the function of thecomponents in the circuit , the model of the control circuit is built and simulated. Theresult of simulation shows that this circuit has advantages of simple control algorithm,highly linearity of the magnetic moment output and easy to eliminate the remanence.