Effects of the Eccentricity of a Perturbing Third Body on the Orbital Correction Maneuvers of a Spacecraft
Figure 3
These figures show the evolution of the eccentricity as a function of time for near equatorial orbits. The eccentricity of the perturbing body () is shown in color codes: 0.0 (red), 0.1 (green), and 0.2 (blue). In (a), the results are for the full elliptic restricted three-body problem. (b) is for single-averaged model and (c) is for double-averaged model. The dashed curve represents the (, ) pair to perform orbital maneuvers, depending on the limit of the eccentricity variation allowed by the mission.
