Impulsive Control of Satellite Formation Flying using Orbital Period Difference

This paper is mainly concerned with impulsive control of satellite formation flying using orbital period difference. Gauss's Variational Equation is used as a main equation and corresponding six orbital elements represent satellite status. Schaub and Alfriend's three-impulse algorithm constitutes a basic algorithm of this paper. In three-impulse algorithm, required impulses are determined by orbit element difference between current and desired orbit. Among orbit element difference, mean anomaly difference is an only time-varying term, and it comes from orbital period difference. In this paper, we analytically derive an impulse time which minimizes required impulse magnitude using orbital period difference, based on three-impulse algorithm. In addition, considering a case when proposed delayed impulse maneuver is not useful, alternative impulse maneuver is suggested. Finally, simulation studies are presented with artificial mission examples.