In　this　paper　the　low　thrust　propulsion　control　strategy　of　the　low　energy　Moon　return　transfer　is　researched.　By　establishing　the　dynamical　equations　in　the　elliptical　four　body　problem,　the　characteristics　of　the　low　energy　moon　return　trajectory　is　analyzed　and　the　whole　returning　mission　is　divided　into　two　sections,　the　moon　escaping　and　the　return　manifold　injecting.　In　each　of　the　section,　the　low　thrust　propulsion　control　strategy　is　designed　with　iteration　method.　From　the　simulation　result,　the　low　thrust　low　energy　moon　return　method　is　of　significant　advantage　in　fuel　consumption.　©　2017　IEEE.