Optimized Design and Analysis of Printed Magnetorquer for a 3-U Nano-Satellite

Abstract

An active attitude control system using a novel six-layer electromagnetic embedded printed magnetorquer for a 3-U nanosatellite is presented in this paper. The proposed design was optimized in terms of size, dissipated power, torque produced, and generated magnetic dipole moment. The designed printed magnetorquer is the optimum choice for a 3-U small-satellite attitude stabilization in terms of reconfigurability, modularity, lower space occupation, low mass, and lower cost. The printed magnetorquer was designed and analyzed for a 3-U nanosatellite with CubeSat standard dimensions of 10×10×30 cm3. The design was implemented with commercial off-the-shelf (COTS) high-performance microdevices that are reliable and easily accessible for reducing procurement cost. The printed magnetorquer was embedded in internal layers of a printed circuit board (PCB) that does not require additional space on the satellite. Time-varying rotational analyses were performed for various coil arrangements to test the rotation times for spin-stabilized 3-U nanosatellites. Thermal analysis of the 3-U nanosatellite was done to sustain thermal operation and satisfy the feasibility requirements of the system. Essential performance parameters like magnetic moment generated, resultant torque, and power dissipation were examined for comparison with the existing commercial state of the art. The proposed printed magnetorquer with more configurability (2×3, 3×2, 1×18, 18×1, 9×2, 6×3 hybrid) features provides versatility to the design aspects by changing the configuration through the onboard computer according to mission needs.