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.