While the Circular Restricted Three-Body Problem (CR3BP) provides useful structures for various applications, transitioning the solutions from the CR3BP to a higher-fidelity ephemeris model while maintaining specific characteristics remains non-trivial. An analytical approach is leveraged to provide additional insight on the perturbations that are present in an ephemeris model. For the Earth–Moon CR3BP, pulsation of the Earth–Moon distance and solar gravity are identified as key components contributing to the additional accelerations, where patterns are illustrated through simplified mathematical relationships and graphics. Utilizing these findings, capabilities and limitations of two intermediate models, the Elliptic Restricted Three-Body Problem and the Bi-Circular Restricted Four-Body Problem, are assessed within the context of transitioning from the CR3BP to a realistic ephemeris model. A sample transition process for Earth–Moon L2 halo orbits is provided, leveraging the insight from the proposed analytical approach.

虽然循环受限三体问题 (CR3BP) 为各种应用提供了有用的结构，但将解决方案从 CR3BP 转换为更高保真度的星历模型，同时保持特定特征仍然很重要。利用分析方法来提供对星历模型中存在的扰动的额外见解。对于地月 CR3BP，地月距离的脉动和太阳引力被认为是造成额外加速度的关键因素，其模式通过简化的数学关系和图形来说明。利用这些发现，在从 CR3BP 过渡到现实星历模型的背景下评估了两个中间模型（椭圆限制三体问题和双圆限制四体问题）的能力和局限性。利用所提出的分析方法的见解，提供了地月 L2 晕轨道的示例转变过程。