Selection of design parameters of a spacecraft electric propulsion engine ensuring the geostationary orbit raising mission
Journal: VESTNIK of Samara University Aerospace and Mechanical Engineering
Year: 2024

The problem of selecting suboptimal parameters of an electric propulsion system as part of a spacecraft, ensuring a geostationary orbit raising mission using a Soyuz-5 launch vehicle at the initial launch stage, is investigated. An expression is obtained for the main optimality criterion – the payload relative mass. An algorithm is obtained for solving the problem of parametric optimization of an electric propulsion system as part of a hybrid transportation system. The task of selecting the opti