A station keeping strategy for a spacecraft orbiting a collinear equilibrium point in the Earth-Moon system is introduced. A nominal circular solution which is derived from the Jacobi integral equation, employing elliptic integral theory, is used in a plane perpendicular to the line joining the two primaries. Thrust control inputs, which are found to be nonlinear functions of time, are used to negate the instability of the nominal orbit. Orbit parameters are chosen so that the cost of maintaining the nominal orbit is minimized. Analytical relationships for control requirements are developed.