FIELD: space engineering; methods of filling hydraulic systems of temperature control systems of spacecraft (transport and cargo spacecraft, orbital station modules, cryogenic stages) with heat-transfer agents. SUBSTANCE: method includes evacuation of system, filling the system with deaerated heat- transfer agent, dissolution of residual air and setting working pressure in system. After filling the system, preliminary drainage of heat-transfer agent is performed in scope equal to thermal change in volume of filled agent within temperature range at which dissolution of air is performed; then loading and dissolution of air are performed at change of average- mass temperature of heat-transfer agent. Then, steady volume of gas chamber of compensator is measured and heat-transfer agent is finally drained from system, after which working pressure corresponding to measured average-mass temperature is set in system. Said method provides for reduction of time required for dissolution of residual air at reduced time of filling and low cost of technological process. EFFECT: reduced filling time; low cost of technological process.
