FIELD: temperature control systems of large-sized space objects. SUBSTANCE: proposed method includes change in pressure during prelaunch preparation and during flight operation. Prior to launch of space object, pressure of required magnitude is set which is lesser than difference between maximum permissible pressure in system and sum of cavitation pressure with product of height of hydrostatic column of system filled to maximum level by density of heat-transfer agent used for changing the system and by axial g-load of temperature control system in injection leg. During orbital flight, pressure in system exceeds pressure of working compartment by magnitude exceeding error of measurement of working pressure in system. EFFECT: reduced mass of injected cargo; possibility of ensuring optimal pressure differential in all sections of operation.
