The low-energy lunar landing trajectory design using the invariant manifolds of restrictedthreebodyproblem 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。
2
Since the circular restrictedthree-bodyproblem 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。
3
Finally, the two level differential corrections method was proposed to transform the orbit designed under the circular restrictedthree-bodyproblem model into the perturbed three-body problem model.