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基于平面圆形限制性三体问题模型,利用与绕月轨道相切的大幅值Lyapunov周期轨道,提出了一种新的地月转移轨道设计方法。根据Poincaré截面与限制性三体问题动力学系统对称性计算得到的大幅值Lyapunov轨道,通过与绕月轨道拼接,将地月转移问题转化为地球到大幅值Lyapunov轨道的转移问题。为保证探测器能够从近地轨道(LEO)切向逃逸到达大幅值Lyapunov轨道,通过计算其稳定流形,采用最近点作为Poincaré截面的终止条件求解探测器的初始状态,并根据初始状态完成地月轨道的设计。仿真结果表明,该地月转移策略相比于Hohmann转移,在同样只需要两次速度增量的前提下,约节约100m/s的速度增量,该研究为地月转移轨道的设计提供了一种新思路。
Based on the planar circular constrained three-body problem model, a new lunar-moon transfer orbit design method is proposed based on the large-amplitude Lyapunov periodic orbit tangent to the lunar orbit. According to the large-amplitude Lyapunov orbit calculated by the symmetry of Poincaré section and restricted three-body dynamical system, the problem of earth-moon transfer is transformed into the problem of earth-to-large-amplitude Lyapunov orbit by splicing with lunar orbit. In order to ensure that the detector can reach the large-amplitude Lyapunov orbit by tangential escape from the near-Earth orbit (LEO), the initial state of the detector can be solved by calculating the stable manifold and using the nearest point as the termination condition of the Poincaré section, and according to the initial state Moon track design. The simulation results show that compared with Hohmann transfer, the local transfer strategy saves about 100 m / s in the same speed increase of only two speed increments. This study provides a Kind of new ideas.