In　this　paper　the　orbit　construction　of　the　low　energy　Moon　return　mission　is　researched　that　is　achieved　by　low　thrust　propulsion.　In　the　elliptical　four　body　problem,　the　dynamical　model　and　the　orbit　energy　expression　of　the　spacecraft　is　given　to　study　the　characteristics　of　the　low　energy　Moon　return　orbit　that　starts　from　lunar　vicinity　and　connects　the　Earth-Moon,　Earth-Sun　libration　point　and　Earth.　The　designing　of　the　low　thrust　low　energy　Moon　return　is　divided　into　two　phases.　Firstly,　the　nominal　trajectory　is　designed　via　the　patching　manifolds　method.　Then　the　low　thrust　perilune-apolune　control　strategy　is　proposed　to　achieve　a　rapid　and　fuel-effectively　transfer　from　lunar　orbit　to　the　low　energy　return　orbit.　The　simulation　result　showed　that　the　low　thrust　low　energy　Moon　return　had　great　advantage　in　fuel　consumption.　©　2018　IEEE.