1. Mission scenario

1.1 Earth orbit

A terrestrial orbit is an ellipse defined by its orbital parameters noted (a, e, i, Ω, ω, θ). The orbital plane is defined by the inclination i (angle with the Equator) and the longitude of the ascending node Ω. The ascending node A is the point over the Equator in the south-north direction (figure 1 a). The argument of perigee is the angle between node A and perigee P. The shape of the ellipse is defined by the semi-major axis a and eccentricity e. The true anomaly θ is the angle between the perigee and the current...