Implementation of a Slosh Mechanical Model during Spacecraft Approach and Docking

This paper presents the application of a slosh mechanical model to assess the effects of propellant slosh on the success of a docking maneuver between two spacecraft. The slosh model comprises a free-moving particle within a constraint surface with penalty method-based contact dynamics and an inert particle that augments the mass properties of the spacecraft. The parameters of the slosh model are tuned with computational fluid dynamics (CFD) simulations of a representative scenario. The slosh model is then integrated into the approach and docking phase simulations. Results indicate that the slosh model can be used to inform when and how propellant slosh affects the performance and robustness of the system during the approach and docking phases.