FIELD: space engineering; communication satellite temperature control systems. SUBSTANCE: proposed system includes heat exchangers, compensator, electric pumping unit and liquid loop with flow regulator and distributor. Distributor has one inlet and two outlets. Second outlet of distributor is connected with outlet of radiator-cooler by means of bypass. Parameters of line from first outlet of distributor to point of connection with bypass satisfies special condition. Repeater cooling liquid passage is connected to system before testing the satellite through hydraulic connectors. To this end, hydraulic connectors are coupled together via circular partition provided with specially selected number of holes. EFFECT: enhanced reliability; increased service life of system; reduced mass; low-cost. 2 cl, 4 dwg
Title | Year | Author | Number |
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SPACECRAFT TEMPERATURE CONTROL SYSTEM | 1998 |
|
RU2151720C1 |
SPACECRAFT TEMPERATURE CONTROL SYSTEM AND METHOD OF ITS MANUFACTURE | 2000 |
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METHOD OF TESTING TEMPERATURE CONTROL SYSTEM | 1998 |
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SPACECRAFT TEMPERATURE CONTROL SYSTEM | 1999 |
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METHOD OF TESTING SPACECRAFT AND DEVICE FOR REALIZATION OF THIS METHOD | 2000 |
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RU2200689C2 |
METHOD OF TESTING TEMPERATURE CONTROL SYSTEM | 1998 |
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RU2159728C2 |
METHOD OF TESTING SPACECRAFT AND DEVICE FOR REALIZATION OF THIS METHOD | 2001 |
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RU2209751C2 |
SPACECRAFT TEMPERATURE CONTROL SYSTEM | 1999 |
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RU2151722C1 |
Authors
Dates
2000-11-10—Published
1999-08-20—Filed