SPACE VEHICLE TEMPERATURE CONTROL SYSTEM Russian patent published in 2009 - IPC B64G1/50 

FIELD: transportation.

SUBSTANCE: said utility invention relates to the space engineering, in particular to the telecommunication satellite instrument temperature control system. The system comprises a circuit with a bi-phase coolant. The circuit comprises a hydraulic pump, manifolds of panels, on which instruments are installed, radiator panel manifolds, and a battery connected between one another by main lines. The battery has a housing with zones for gas (coolant vapours) and the liquid phase of the coolant. The latter zone communicates with the main line running to the hydraulic pump inlet. The said circuit has a bucket pump, the inlet nipple of which is connected to the main line running from the radiator panel manifold. The first liquid phase supply outlet nipple of the bucket pump is connected to the main line running to the hydraulic pump inlet. The connection is made upstream of the connection point of the pipeline running from the battery housing and the said line. The second vapour/gas mixture supply outlet nipple of the bucket pump communicates with the gas zone in the battery housing through a normally closed valve.

EFFECT: decreased influence of temperature control system operation on reliability of general space vehicle operation.

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