This paper develops a Time Shift Governor (TSG)-based control scheme to enforce constraints during rendezvous and docking (RD) missions in the setting of the Two-Body problem. As an add-on scheme to the nominal closed-loop system, the TSG generates a time-shifted Chief spacecraft trajectory as a target reference for the Deputy spacecraft. This modification of the commanded reference trajectory ensures that constraints are enforced while the time shift is reduced to zero to effect the rendezvous. Our approach to TSG implementation integrates an LSTM neural network which approximates the time shift parameter as a function of a sequence of past Deputy and Chief spacecraft states. This LSTM neural network is trained offline from simulation data. We report simulation results for RD missions in the Low Earth Orbit (LEO) and on the Molniya orbit to demonstrate the effectiveness of the proposed control scheme. The proposed scheme reduces the time to compute the time shift parameter in most of the scenarios and successfully completes rendezvous missions.

翻译：本文针对二体问题背景下的交会对接任务，提出了一种基于时间偏移调节器的控制方案，以实现约束条件下的安全操作。该方案作为标称闭环系统的附加模块，通过生成时间偏移后的主航天器轨迹，作为从航天器的目标参考轨迹。通过调整指令参考轨迹，在保证约束条件满足的同时，逐步将时间偏移量减小至零，从而实现交会对接。在时间偏移调节器的实现中，我们引入了长短期记忆神经网络，该网络根据主从航天器历史状态序列近似计算时间偏移参数。该LSTM神经网络通过离线仿真数据进行训练。我们分别针对低地球轨道和莫尼亚轨道的交会对接任务进行了仿真验证，结果表明所提控制方案的有效性。该方案在多数场景下显著缩短了时间偏移参数的计算时间，并成功完成了交会对接任务。