At the 50th anniversary of Apollo 11, the Moon is back to the scene of scientific and commercial space exploration interests. During the next decade, the establishment of a Gateway in cislunar non-Keplerian orbits will open the space frontiers to sustainable manned and robotic missions on and around the Moon. Such infrastructure will require several logistic operations for its assembly and maintenance, which lean on rendezvous and docking capabilities. Even if few missions have flown on non-Keplerian orbits, Rendezvous and Docking (RV&D) operations have not been performed but in Low Earth Orbit (LEO). Investigations about 6 Degrees Of Freedom (DOF) relative dynamics in non-Keplerian environment are now mandatory to highlight criticalities in the design of the cislunar gateway and to translate RV&D protocols, consolidated in LEO for the International Space Station (ISS), to the new non-Keplerian environment. In this direction, the paper analyses the 6DOF natural orbit-attitude dynamics within the Circular Restricted Three-Body Problem (CR3BP) framework. A novel perspective of the dynamical structures, constituting 6DOF manifolds, allows to better characterise the natural relative dynamics in proximity of non-Keplerian orbits. The importance of orbit-attitude manifolds exploitation is underlined for designing reliable and efficient rendezvous trajectories, enhanced by natural cislunar dynamics.

Then, an ephemeris cislunar dynamical model is exploited to address guidance laws for proximity operations. The control capability is included in the dynamics of a chaser vehicle, which is employed to solve the 6DOF guidance problem in proximity of a target spacecraft. The results obtained with the controlled dynamics are compared to those available thanks to natural motion, discussing the energetic and time costs to complete the manoeuvres. A control parametrization to solve the optimal energy rendezvous problem is proposed.

Finally, a feasible operational rendezvous scenario is discussed about the identified favourable locations along the non-Keplerian orbit to perform complex proximity operations. Significant relations between RV&D time and non-Keplerian orbit’s period are discussed as well.

在阿波罗11诞辰50周年之际，月球又回到了科学和商业太空探索领域。在接下来的十年中，在月球非肯尼亚人的轨道上建立网关将为在月球及其周围进行可持续的载人和机器人飞行任务打开太空边界。这样的基础设施将需要数个后勤操作以进行组装和维护，这要取决于集合点和对接功能。即使很少有人在非基普勒斯轨道上执行过飞行任务，交会和对接（RV＆D）操作也没有执行，而是在近地轨道（LEO）中进行。现在，必须对非Keplerian环境中的6个自由度（DOF）相对动力学进行调查，以突出突触网关设计的关键性并翻译RV＆D协议，合并到国际空间站（ISS）的LEO中，以适应新的非吉普利人环境。在这个方向上，本文分析了循环约束三体问题（CR3BP）框架内的6DOF自然轨道姿态动力学。构成6DOF流形的动力学结构的新颖观点使我们可以更好地表征非Keplerian轨道附近的自然相对动力学。强调了轨道-姿态流形开发的重要性，以设计可靠和有效的交会轨迹，并通过自然的月球动力学增强了这一点。构成6DOF流形的动力学结构的新颖观点使我们可以更好地表征非Keplerian轨道附近的自然相对动力学。强调了轨道-姿态流形开发的重要性，以设计可靠和有效的交会轨迹，并通过自然的月球动力学增强了这一点。构成6DOF流形的动力学结构的新颖观点使我们可以更好地表征非Keplerian轨道附近的自然相对动力学。强调了轨道-姿态流形开发的重要性，以设计可靠和有效的交会轨迹，并通过自然的月球动力学增强了这一点。

然后，利用星历表月桂动力学模型来解决接近操作的制导律。追赶飞行器的动力学中包含控制能力，该能力用于解决目标航天器附近的6DOF制导问题。将通过受控动力学获得的结果与通过自然运动获得的结果进行比较，讨论完成操纵所需的精力和时间成本。提出了一种控制参数化方法来解决最优能量集合点问题。

最后，讨论了一个可行的交会场景，该场景涉及沿非基普勒轨道确定的有利位置，以执行复杂的邻近操作。还讨论了RV＆D时间与非Keplerian轨道周期之间的重要关系。