Searching for Orbits with Minimum Fuel Consumption for Station-Keeping Maneuvers: An Application to Lunisolar Perturbations
Figure 1
Perturbation integral (m/s) for one period of the spacecraft as a function of its inclination (rad) considering only the Moon as the perturbing body. The true anomalies of the Moon at time zero are zero (dotted line), (dot-dashed line), (dashed line), and (continuous line).
