“…From the usual equations for the perturbations of the keplerian elements of an elliptical orbit, due to the secular perturbative potential (Roy, 1978), and from equation (15), we can derive the orbital elements at time t j , that is after k j ∆t from t 0 , our reference epoch. We have that the semi-major axis a, the eccentricity e and the inclination i change only for short periodic perturbations, thus by O¢ J 2 £ , while for the other elements we have…”