Thermal control systems of dm-type upper stages of integrated launch vehicles

The paper discusses thermal control systems for DM-type upper stages (US), their purpose, configuration and evolution reflecting the changes in the US design. The upper stages used as the last stage of integrated launch vehicles are intended for the final ascent of the spacecraft to the parking orbit, and its transfer from the parking orbit to the target orbit of an artificial Earth satellite (elliptical or geostationary) or injection into trajectories of departure to other planets. Furthermore, they assure compliance with the customer requirements for attitude and insertion accuracy. At present, among the upper stages that are currently in service, only DM-type upper stage and its derived versions use environmentally friendly propellant components (liquid oxygen and kerosene). One of the scientific and technical problems that need to be solved when developing US for integrated launch vehicles is the development of a reliable and efficient thermal control system, which provides the thermal conditions required for normal operation of the US onboard system.