Dynamics and Control of Spacecraft Using Control Moment Gyros with Friction Compensation

摘要

This study has shown that off-line parameter-estimation methods combined with a set of UKFs using online state estimation, and standard spacecraft bus and CMG controllers, can significantly reduce agile spacecraft attitude tracking errors. Attitude tracking performance was evaluated using a numerical simulation with and without friction compensation based on a truth model derived from Kane's equations. The truth model was validated using the principle of conservation of angular momentum.