Selecting a Thermodynamic Cycle for the Closed Gas Turbine Power Plant of Spacecraft in Order to Minimize Surface of the Cooler-Radiator

The influence of the thermodynamic cycle scheme selected for a closed gas-turbine power plant of spacecraft on the specific surface of its cooler-radiator are evaluated. The dependence of the cooler-radiator characteristics on the regeneration, intermediate cooling, and heating of the working medium are analyzed.