The　low　energy　moon　return　orbit　has　evident　advantages　in　the　fuel　consumption　but　it＇s　much　sensitive　to　the　initial　states　of　the　probe.　To　solve　this　problem,　in　this　paper,　the　problem　of　accurate　orbit　control　for　low　energy　Moon　return　mission　is　studied.　Firstly,　based　on　the　elliptical　four　body　dynamical　model,　the　dynamical　characteristics　of　the　low　energy　return　orbit　is　analyzed.　Then,　the　covariance　analysis　method　is　introduced　to　clarify　the　propagation　properties　of　initial　orbit　errors.　Finally,　a　three　maneuvers　orbit　adjusting　strategy　is　proposed　according　to　the　sensitiveness　of　the　constraint　against　the　accuracy　of　navigation　and　control　impulse.　By　the　simulation　results,　the　strategy　is　able　to　guarantee　an　accurate　height　of　reentry　effectively.　©　2015　IEEE.