SPACECRAFT HEAT REGULATION SYSTEM Russian patent published in 2016 - IPC B64G1/50 F28D15/04 

FIELD: heating.

SUBSTANCE: invention relates to heat regulation systems (HRS) of spacecrafts (SC) with thermal load from 13 to 18 kW. HRS comprises closed liquid circuits and thermal pipes (TP), and also opened radiator panels (ORP). Each circuit comprises communicated subcircuits of service system modules (SSM) and useful load modules (ULM). TPs are built into cellular instrumental panels ("+Z" or "-Z") of ULM, and liquid headers are installed on panels (built into other instrumental panels). One of ORPs is made with headers on a double-phase working medium, produced in an evaporator with a capillary pump installed on the panel "+Z" or "-Z" of ULM. The evaporator body contacts with the ULM subcircuit coolant. Cold efficiency of another ORP (with liquid coolant) is selected so that without the first ORP instrument temperature of instruments is provided as not exceeding the maximum permissible.

EFFECT: provision of ORP qualification under flight conditions and under positive results - possibility to use HRS designed for 13 kW, within a SC with thermal load of up to 18 kW.

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