Abstract: AmethodwaspresentedfordesigningthetransfertrajectoriestotheSun-EarthL3periodicorbitsbasedonthepseudomanifoldsinthecircularrestrictedthreebodyproblem.Thedynamicsofthepseudomanifolds,constructedbygivingalargeperturbationtoL1orL2orbits,wereusedtoconstructthetransfers.Threedeterministicmaneuverswererequiredtocompletetheorbittransfer:first，leavethelow  Earth  orbit; second, transferintothepseudomanifold; third, injecttotheL3orbit.Numericalsimulationresultsshowthat, comparedwiththetransfersbasedoninvariantmanifolds,thismethodreducesthetransformationalenergyconsumptionfrom4398m/sto4014m/s, andtheflightdurationisshortenedfrommorethan9yearstolessthan7.3years, thusimprovingtheefficiencyofthespacecraft.

Key words: Circularrestrictedthree-bodyproblem, Orbittransfers, Pseudomanifold, Librationpoint