Mathematical Problems in Engineering / 2013 / Article / Fig 1

Research Article

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).