提出了一种将圆锥曲线拼接法与历表相结合，快速设计月球卫星地月转移轨道的方法。
A fast design method for the lunar satellite transfer trajectory is presented by combining patched conic technique and ephemeris.
其中轨道运动学约束包括地球停泊轨道约束、地月转移轨道约束和月球卫星轨道约束。
The restriction of orbital kinematics includes that of earth parking paths earth-moon transfer path, and lunar satellite path.
采用精确轨道动力学模型，得到了满足共面交会约束的发射窗口，以及地月转移轨道特性。
The launch window meeting the restriction of coplanar rendezvous and the characteristics of trans-lunar trajectory is obtained by precise dynamics model.
典型的月球探测器飞行轨道包括地球停泊轨道段、地月转移轨道段、月球卫星轨道段和着月轨道段。
A typical orbit of lunar probe includes earth parking orbit segment, earth-moon transfer orbit segment, lunar satellite orbit segment and moon-landing orbit segment.
利用重叠圆锥曲线方法，针对着陆型和月球卫星型两种地月转移轨道，给出了一种地月转移轨道的快速设计方法。
A fast design method for transfer orbit of lunar probe is presented using overlap conic curve method aimed at lunar landing transfer orbit and lunar satellite transfer orbit.
利用重叠圆锥曲线方法，针对着陆型和月球卫星型两种地月转移轨道，给出了一种地月转移轨道的快速设计方法。
A fast design method for the lunar satellite transfer trajectory is presented by combining patched conic technique and ephemeris.
基于地月信息提出了一种奔月转移轨道的自主光学导航算法。
The autonomous optical navigation algorithm based on Earth-Moon information during the cislunar transfer orbit phase is presented.
从地月系L1点晕轨道向月球圆停泊轨道具有多种零消耗转移轨道，但不同轨道的能耗和转移时间等指标不尽相同；
There are many kinds of zero-cost transfer trajectories from L1 to round parking orbits, but the energy cost, time cost of different trajectories are also different.
从地月系L1点晕轨道向月球圆停泊轨道具有多种零消耗转移轨道，但不同轨道的能耗和转移时间等指标不尽相同；
There are many kinds of zero-cost transfer trajectories from L1 to round parking orbits, but the energy cost, time cost of different trajectories are also different.
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