Saturation avoidance method for control moment gyros during spacecraft attitude maneuvers

摘要

This article investigates the spacecraft large-angle attitude maneuver control considering control moment gyros (CMGs) saturation. In order to design the control laws to avoid CMGs saturation during attitude maneuvers, novel potential functions for spacecraft are proposed based on the artificial potential function (APF), in which the distance between the present attitude and the aiming attitude is used as an attractive potential function and the saturation state of CMGs is employed as a repulsive potential function. And then, the control laws for stable and unstable terminal attitudes are proposed respectively using Lyapunov method. Numerical examples show that the proposed control laws can avoid CMGs saturation during the large-angle attitude maneuvers.