A Study of Single- and Double-Averaged Second-Order Models to Evaluate Third-Body Perturbation Considering Elliptic Orbits for the Perturbing Body
Figure 6
These figures show the evolution of the eccentricity as a function of time for high-inclination orbits. The first, second, and third rows correspond to the results for eccentricity of the perturbing body () 0.0, 0.2, and 0.4. In the first column, the results are for the case of Low-altitude orbits. The second column is for the case of Medium-altitude orbits. The third column is for the case of High-altitude orbits. The lines are as follows: full elliptic restricted three-body problem (solid line), single-averaged (dashed line), and double-averaged models (dashed-dotted line). For the colors, ° (red line), 70° (blue line), 60° (green line), 50° (pink line), and 40° (orange line). The increase of the semimajor axis and the eccentricity of the primaries reduce the average distance from the spacecraft to the Moon, making the perturbations stronger.
