在给定飞行时间、着月时间、着月入射角及停泊轨道等约束条件下，建立飞月轨道数学模型；
In this paper, obtained the translunar trajectory for direct striking the moon, which satisfied some constraints including translunar flight time, lunar landing date.
文章介绍了航天器的热控涂层试验，用改变入射质子和电子能量的办法，模拟同步轨道辐射环境。
Experiments were designed and conducted on spacecraft thermal coating to simulate an absorbed dose profile from synchronous altitude radiation by varying the energy of incident electrons and protons.
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