FIELD: temperature control systems in space engineering; manufacture and ground preparation of spacecraft.
SUBSTANCE: proposed method includes evacuation of system, filling of system with deaerated heat-transfer agent, preliminary drainage of excessive heat-transfer agent and dissolving of free air residues from system filled with heat-transfer agent. In dissolving the free air residues, system is loaded with maximum permissible technological pressure at monitoring this pressure for absence of any drop at circulation of heat-transfer agent in system. Then, average mass temperature of heat-transfer agent and steady-state volume of compensator gas chamber are measured, after which technological pressure is relieved at maintenance of circulation of heat-transfer agent till stationary temperature mode has been attained at points of system under test. After measurement of average mass temperature, heat-transfer agent is finally drained taking into account measured steady-state volume of compensator gas chamber and working pressure is finally set according to measured average mass temperature.
EFFECT: reduction of process duration; low cost of process due to avoidance of experiment on analog system.
