Optimal two-impulse phasing for elliptical orbits

This study analyzes optimal mission velocity change magnitudes required to perform a co-orbital phasing maneuver within an elliptical orbit. Analytical velocity change expressions are derived in terms of the chase vehicle's initial classical orbital elements. The results demonstrate that for sufficiently large times of flight, the minimum velocity change converges to a value that is a function of eccentricity and initial chase satellite true anomaly regardless of the initial phase angle. The equations derived in this investigation are used to analyze phasing maneuvers for geosynchronous, low eccentricity, and Molniya orbits.