Mathematical Problems in Engineering / 2013 / Article / Fig 3

Research Article

A Study of Single- and Double-Averaged Second-Order Models to Evaluate Third-Body Perturbation Considering Elliptic Orbits for the Perturbing Body

Figure 3

These figures show the evolution of the inclination as a function of time for near critical inclinations. On the top of each figure is shown the corresponding eccentricity of the perturbing body ( ). 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) and single-averaged (dashed line) and double-averaged models (dashed-dotted line). For the colors, ° (red line), 40° (orange line), 39° (blue line), and 38° (pink 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.

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