Elliptic displaced orbit approximation with equally spaced impulses

The aim of this paper is to extend the literature results to the case of two-body elliptic DNKOs by obtaining a general method to calculate the propulsive performance of a spacecraft that covers the corresponding CPOs. In particular, the proposed approach gives the analytical expression of the total velocity variation per revolution around the primary body, which is required to approximate an assigned DNKO with a sequence of (azimuthally) equally spaced impulsive maneuvers. The value of the total velocity variation in the continuous-thrust scenario is also obtained as a special case of the mathematical model.