Minimum-fuel, impulsive solutions are obtained for the evasive maneuver of a satellite followed by a rendezvous with the original orbit station. The evasion distance and time are constrained. Both free and constrained final time cases are considered. Primer vector theory is used to obtain optimal solutions, which include three-impulse solutions for an arbitrarily oriented evasion radius vector of a specified magnitude, and two-impulse free-return trajectories for certain specific evasion radius vectors. On some three-impulse solutions the primer vector indicates that the addition of a fourth impulse to the return trajectory will lower the fuel cost.