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.