Effects of the Eccentricity of a Perturbing Third Body on the Orbital Correction Maneuvers of a Spacecraft
Figure 6
Evolution of the inclination as a function of time for the case (~1.3955 radians). In (a), the results are for the full elliptic restricted three-body problem. (b) is for the single-averaged model and (c) is for the double-averaged model. 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 inclination.
