The growing interest in the cislunar domain over the past decade has led to an increasing demand for low-thrust missions to key orbits within this region. These low-thrust missions, typically characterized by long thrust arcs, are highly susceptible to operational disruptions such as unforeseen thruster outages or missed thrust events. Consequently, there is a critical need for efficient trajectory design frameworks which incorporate robustness against such anomalies. In this study, we utilize a robust trajectory design framework to explore the solution space for the Power and Propulsion Element (PPE) module to the Earth-Moon L2 Southern 9:2 Near Rectilinear Halo Orbit. We propose algorithmic enhancements to improve the global search for robust solutions, and present a comprehensive analysis of two approaches: a nonconditional approach which involves a purely random search for robust solutions versus a conditional approach which involves warm-starting the search for robust solutions using the non-robust solutions. Our results indicate that by using non-robust solutions as initial guesses for the robust solutions, it is possible to achieve significant improvements in both the rate of convergence and the robustness of the final solutions.

翻译：过去十年间，对地月空间领域日益增长的兴趣导致了对该区域内关键轨道进行低推力任务的需求不断增加。这些低推力任务通常具有长推力弧段的特点，极易受到诸如未预见的推进器故障或推力缺失事件等运行中断的影响。因此，迫切需要建立能够抵御此类异常的高效轨迹设计框架。在本研究中，我们采用一种鲁棒轨迹设计框架，探索动力与推进单元模块至地月L2点南侧9:2近直线晕轨道的解空间。我们提出了算法增强策略以改进对鲁棒解的全局搜索，并对两种方法进行了全面分析：一种是无条件方法，即对鲁棒解进行纯随机搜索；另一种是条件方法，即利用非鲁棒解作为初始条件来热启动对鲁棒解的搜索。我们的结果表明，通过使用非鲁棒解作为鲁棒解的初始猜测，可以在收敛速度和最终解的鲁棒性方面实现显著提升。