Effects of the Eccentricity of a Perturbing Third Body on the Orbital Correction Maneuvers of a Spacecraft
Figure 4
Evolution of the eccentricity and inclination as a function of time for the case (~0.6803 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 (, ) and (, ) pairs for eccentricity and inclination, respectively, to perform orbital maneuvers, depending on the limit of the eccentricity and inclination variations allowed by the mission. In the plots for the inclination, it showed the dashed lines for the limits of variation for times higher than 1 year for better graphic visibility.
