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Let us consider the elliptic restricted three body problem (Elliptic RTBP)for the Jupiter Sun system with eccentricity $e=0.048$ and $\mu=0.000953339$.Let us denote by $T$ the period of their orbits. In this paper we provideinitial conditions for the position and velocity for a spacecraft such thatafter one period $T$ the spacecraft comes back to the same place, with the samevelocity, within an error of 4 meters for the position and 0.2 meters persecond for the velocity. Taking this solution as periodic, we present numericalevidence showing that this solution is stable. In order to compare thisperiodic solution with the motion of celestial bodies in our solar system, weend this paper by providing an ephemeris of the spacecraft motion from February17, 2017 to December 28, 2028.

Near Periodic solution of the Elliptic RTBP for the Jupiter Sun system