Chance-constraint method for covariance control of low-thrust interplanetary missions

The importance of robustness in space trajectory optimization is growing significantly as the modern mission design approach prioritizes lightweight satellite architectures and cost reduction. However, this emphasis also raises the risk of deviating from a nominal path due to errors in navigation or incorrect maneuvers. Consequently, it is crucial to compute control laws that directly incorporate quantitative information about uncertainty in system dynamics and stochastic navigation errors during the optimization process. In this study, a systematic approach for designing a robust low-thrust trajectory and its corresponding closed-loop control system is presented. Building upon prior research on robust impulsive trajectories, the method employs a linear feedback control law to steer the state probability distribution of the spacecraft towards a predetermined target distribution at a specified final time, considering the spacecraft's mass as an additional stochastic variable.