Abstract
The work focuses on developing a lightweight lunar tug with an electric propulsion system for transporting cargo between promising near-Earth and near-lunar stations. The aim is to determine the ranges of transfer trajectory characteristics, considering realistic initial parameters: engine specifications, vehicle mass, launch date, and conditions. The lunar tug's design, solar panel parameters, and engine operating modes are provided. The flight scheme and method for designing transfer trajectories between near-Earth and near-Moon orbits are briefly described. The results of designing trajectories based on launch date, engine mode, and initial mass are presented and discussed.
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