FIELD: spacecraft temperature control systems; ground servicing of upper stages of launch vehicles.
SUBSTANCE: proposed method includes evacuation of system, filling the system with de-aerated amount of heat-transfer agent, flow test of heat-transfer agent, calibrated drainage and setting the working pressure. Subjected to evacuation is inner cavity of system including liquid cavity of compensator; atmospheric pressure is built in gas cavity of compensator separated from its liquid cavity by membrane; filling the system with de-aerated heat-transfer agent is effected at excessive pressure in liquid cavity of compensator equal to 2 atm. In filling the system with heat-transfer agent, remaining air passing through liquid cavity of compensator is accumulated before respective drainage valve. Air is evacuated through this valve when heat-transfer agent flows through main communicated with valve.
EFFECT: reduction of air content in system after filling it with heat-transfer agent.
1 dwg
