Model Problem on the Response Speed and Accuracy of a Satellite Gravity-Gradient Stabilization System

摘要

The report investigates the attitude performance of an earth orbiting gravity-gradient spacecraft. First the transient response is determined for a system which has damping about one to three orthogonal axes and is in a circular orbit. The characteristic equation is utilized to find optimal values of the spacecraft's adjustable parameters. The transient response is also studied for the separate conditions of eccentric orbit, addition of a constant speed flywheel, and addition of torques due to atmospheric drag. Finally, improvement of the steady state pointing accuracy is considered. (Author)