Several satellite formation e ying designs and their evolution through time are investigated. Satellite formation e ying designs arederived from the linearized equations of relative motion under two-body dynamics better known as Hill’ s equations (Hill, G. W., “ Researches in the Lunar Theory,”American Journal of Mathematics , Vol. 1, No. 1, 1878, pp. 5‐26). The formations are then propagated forward in time in the presence of realistic perturbations to determine the stability of each design. Formations considered include in-plane, in-track, circular, and projected circular designs. The Draper Semianalytic Satellite Theory is used to propagate mean elements of the satellites. When perturbations disrupt the satellite formations, an effort is made to quantify the cost of formation-keeping maneuvers. The goal of this effort is to provide physical insight into satellite formation e ying design and outline the effects of realistic dynamics on those designs.