The low-energy lunar landing trajectory design using the invariant manifolds of restricted three body problem is studied.
研究了基于三体问题的不变流形设计低成本登月轨道的问题。
Finally, the two level differential corrections method was proposed to transform the orbit designed under the circular restricted three-body problem model into the perturbed three-body problem model.
最后使用两层微分修正方法将圆型限制性三体问题模型下设计的轨道转换到受摄三体问题模型下。
Since the circular restricted three-body problem model ignores the effect of perturbations, it can not accurately describe the dynamic characters of the three-body system.
圆型限制性三体问题模型忽略了摄动因素的影响，在很多情况下不能足够准确地描述三体系统的动力学性质。
Since the circular restricted three-body problem model ignores the effect of perturbations, it can not accurately describe the dynamic characters of the three-body system.
圆型限制性三体问题模型忽略了摄动因素的影响，在很多情况下不能足够准确地描述三体系统的动力学性质。
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