For　the　spacecraft　in　the　Quasi-period　orbit　of　Earth-Moon　libration　point,　the　stability　of　the　orbit　is　decreased　obviously　because　of　the　perturbation　of　solar　gravity　and　Moon＇s　elliptical　motion　around　Earth.　However　the　applying　of　the　control　strategy　that　eliminate　the　velocity　component　of　X　axis　when　the　spacecraft　crosses　the　X-Z　plane,　a　valid　method　in　CRTBP,　in　the　E-M　rotating　coordinate　often　causes　the　divergence　of　the　orbit.　In　this　paper,　by　analyzing　the　dynamical　characteristics　of　the　spacecraft,　a　control　strategy　is　designed　and　validated　with　Satellite　Tool　Kit　(STK)　for　the　long　time　maintenance　of　the　E-M　libration　quasi-period　orbit.　Using　the　high　precision　orbit　propagating　model　of　STK　software　and　the　auto　targeting　function　of　the　Atrogator　module,　the　simulation　scenario　is　constructed　to　optimize　the　control　maneuvers　of　the　spacecraft.　The　simulation　result　shows　that　the　spacecraft　can　keep　in　the　orbit　for　a　long　time　with　little　fuel　consumption.　©　2019　Technical　Committee　on　Control　Theory,　Chinese　Association　of　Automation.