|For relative-orbit determination using linear, Cartesian dynamics, angles-only measurements are not sufficient. A known, impulsive maneuver performed by either the observer or resident space object can provide observability. However, some maneuvers result in singular measurement equations and therefore do not provide full-state observability. These singular maneuvers can be avoided, but no further information can be provided about desirable maneuvers. The goal of this work is to provide an iterative method to improve observability and the accuracy of the solution. Successive maneuvers planned from covariance predictions using previous state estimates give increasingly good estimates.