Abstract: Libration points play an important role in deep space exploration, due to the fact that they are ideal locations for spacecrafts with special purposes. Since there are always inevitable injection errors in the launch process, transfer trajectory correction maneuvers must be considered for libration point missions. From the view point of engineering development, firstly, transfer trajectory corrections sequence was determined on the basis of the experience of the past libration point missions, and the error models were concluded by summarizing previous studies of both home and abroad; then, the transfer trajectory correction problem was transformed into the transfer trajectory design problem and solved by the differential correction method. Simulation results show that the algorithm is very effective. For transfer trajectory with the flight time of 110 days in the Sun-Earth system, only 78.0 m/s of maneuver velocity was needed to keep final position error below 66.1 km on the confidence level of 95 %.