A way to improve the accuracy of the three-body problem model is taking into account the eccentricity of primary attractors. Elliptic Restricted Three-Body Problem (ER3BP) is a model for studying spacecraft trajectory within the three-body problem such that the orbital eccentricity of primaries is reflected in it. As the principal cause of perturbation in the employed dynamical model, the primaries eccentricity changes the structure of orbits compared to the ideal Circular Restricted Three-Body Problem (CR3BP). It also changes the attitude behavior of a spacecraft revolving along periodic orbits in this regime. In this paper, the coupled orbit-attitude dynamics of a spacecraft in the ER3BP are exploited to find precise periodic solutions as the spacecraft is considered to be in planar orbits around Lagrangian points and Distant Retrograde Orbits (DRO). Periodic solutions are repetitious behaviors in which spacecraft whole dynamics are repeated periodically, these periodic behaviors are the main interest of this study because they are beneficial for future mission designs and allow delineation of the system’s governing dynamics. Previous studies laid the foundation for spacecraft stability analysis or studying pitch motion of spacecraft in the ER3BP regime. While in this paper, at first, initial guesses for correction algorithms were derived through verified search methods, then correction algorithms were used to refine calculated orbit-attitude periodic behaviors. Periodic orbits and full periodic solutions are portrayed and compared to previous studies and simpler models. Natural periodic solutions are valuable information eventuate in the longer functional lifetime of spacecraft. Since the problem assumption considered in this paper is much closer to real mission conditions, these results may be the means to use natural bounded motions in the actual operational environment.

一种提高三体问题模型准确性的方法是考虑主要吸引子的偏心率。椭圆约束三体问题（ER3BP）是研究三体问题中的航天器轨迹的模型，以便在其中反映原形的轨道偏心率。作为采用的动力学模型中扰动的主要原因，与理想的圆形约束三体问题（CR3BP）相比，原形偏心率改变了轨道的结构。它也改变了航天器在这种状态下沿着周期性轨道旋转的姿态行为。在本文中，航天器在ER3BP中的耦合的轨道-高度动力学被用来寻找精确的周期解，因为该航天器被认为是在围绕拉格朗日点和远距逆转轨道（DRO）的平面轨道中。周期解是重复性行为，其中航天器的整体动力学会定期重复，这些周期性行为是本研究的主要兴趣，因为它们有益于未来的任务设计并允许描述系统的控制动力学。先前的研究奠定了航天器稳定性分析或研究ER3BP体制下航天器俯仰运动的基础。虽然在本文中，首先，首先通过经过验证的搜索方法得出对校正算法的初步猜测，然后使用校正算法对计算出的轨道-姿态周期性行为进行细化。描绘了周期轨道和完整周期解，并将其与先前的研究和更简单的模型进行比较。自然周期解是有价值的信息，可在航天器的较长使用寿命中产生。由于本文中考虑的问题假设更接近实际任务条件，因此这些结果可能是在实际操作环境中使用自然界运动的方法。