In　this　paper　the　low　thrust　control　strategy　for　the　low　energy　Moon　return　is　designed　and　simulated　in　Satellite　Tool　Kit　(STK).　By　using　backward　integration　method,　the　orbit　injection　problem　is　transferred　to　an　orbit　circularize　problem.　An　apolune-perilune　control　strategy　is　proposed　to　send　the　spacecraft　into　the　nominal　low　energy　return　orbit　with　low　thrust　propulsion　from　lunar　orbit.　The　control　strategy　is　tested　and　verified　via　STK　which　is　more　meaningful　than　the　simplified　dynamic　model.　©　2018　IEEE.