本文给出了全星历模型下适用于地月系统和日地系统的拟Halo轨道的设计方法。设计过程以限制三体模型下Halo轨道作为初值并以多点并行打靶法求解全星历模型下拟Halo轨道。采用多点并行打靶法中给出了一类新的可行约束条件,在数值仿真算例中,地月和日地系统L2点附近4圈目标拟Halo轨道均在分钟量级时间内收敛,表明了算法的有效性。 In this paper, the design method of quasi-Halo orbit for earth-moon system and day-earth system under full ephemeris model is given. The design process uses the Halo orbit as the initial value to limit the three-body model and solves the Quasi Halo orbit under the full ephemeris model with the multi-point parallel shooting method. A new kind of feasible constraint condition is given in the method of multi-point parallel shooting. In the numerical simulation example, the four-circle-target quasi-Halo orbit around L2 point of earth lunar and solar-earth systems all converge in minutes, indicating that The effectiveness of the algorithm.