The solutions originating at the Lagrangian points $L_1$ and $L_2$ of the restricted three-body problem are used in space flight dynamics to find useful station-keeping orbits as well as convenient low-energy transfers between planets and satellites of the Solar System. The circular restricted three-body problem (CR3BP) provides the simplest model where the Lagrangian points, as well as the related stable and unstable manifold tubes, are defined. Nevertheless, their use for Solar System applications requires to consider hierarchical extensions of the model. The elliptic restricted three-body problem (ER3BP) is the most important extension to consider for space flight dynamics. In this paper we discuss the differences of the manifold tubes of the ER3BP with respect to the CR3BP which have an impact in the transfers between orbits in the manifold tubes related to different planets. We find that there is a threshold value for the eccentricity of the planet, depending on its reduced mass, which changes drastically the distribution of the longitudes of the first perycenter (or apocenter) of the orbits in the manifold tubes leaving or approaching the Lagrangian points $L_1$, $L_2$. For example, such a difference changes the design of the Hohmann transfers between two orbits of the manifold tubes when the planets Mercury or Mars are concerned.

源自拉格朗日点的解${\mathrm{大号}}_1$和${\mathrm{大号}}_2$受限三体问题的概念被用于太空飞行动力学中，以找到有用的保持轨道以及太阳系行星和卫星之间方便的低能量传输。圆形受限三体问题 (CR3BP) 提供了最简单的模型，其中定义了拉格朗日点以及相关的稳定和不稳定歧管。然而，它们在太阳能系统应用中的使用需要考虑模型的层次扩展。椭圆受限三体问题 (ER3BP) 是空间飞行动力学要考虑的最重要的扩展。在本文中，我们讨论了 ER3BP 的歧管相对于 CR3BP 的差异，这些差异对与不同行星相关的歧管中的轨道之间的转移产生了影响。${\mathrm{大号}}_1$,${\mathrm{大号}}_2$. 例如，当涉及行星水星或火星时，这种差异会改变歧管的两个轨道之间的霍曼传输设计。