Design of Active PWM Control Driver Circuit for Torquer System Using CCII

This research examines a torquer system for satellite attitude control which requires low energy, or average power, to control its moment. The magnetic torquer consists of an LR component, source and switching pulse. A mathematical model and design equations are presented for the magnetic torquer. A technique of using torquer system to do 3-axis spacecraft attitude control has been presented. The main goal of this system is to attain specific current control in the torquer system by means of CCII action. CCII is used since the full operation is performed in high frequency system. The closed loop control action of the controller, the triangular wave generator, CCII and torquer system are specific parameters used in this research. This scheme's performance has been considered via analysis and simulation model. The resulting closed-loop systems are robust with respect to parametric modeling ambiguity. The result attained by OrCAD PSPICE, belonging to Cadence design systems with respect to desired amount of current value proves the efficiency of the proposed research method.