Effects of the Eccentricity of a Perturbing Third Body on the Orbital Correction Maneuvers of a Spacecraft
Figure 5
Evolution of the eccentricity as a function of time for the case (~1.3955 radians). The results are for the full elliptic restricted three-body problem. Similar results have been obtained for single- and double-averaged models. The eccentricity of the perturbing body () is shown in color codes: 0.0 (red), 0.1 (green), and 0.2 (blue). The dashed curves represent the (, ) pair to perform orbital maneuvers for each limit assumed for the variation in eccentricity.
