SPACECRAFT EQUIPMENT THERMAL CONTROL SYSTEM Russian patent published in 2013 - IPC B64G1/50 F28D15/02 

FIELD: transport.

SUBSTANCE: invention relates to spacecraft thermal-control equipment. Proposed system comprises two two-chamber fluid thermal boards 22 to support the equipment. Said thermal boards are mounted at manned compartment 1. External heat sink 12 is composed of four diametrically opposite heat exchange panels 14. Panel 14 is furnished with heat pipe with condenser 15 arranged inside panel 14 and evaporator 19 integrated with self-contained heat transfer element 16 mounted at spacecraft outer surface nearby panel 14. Element 16 comprises two one-chamber fluid thermal boards 18. Evaporator 19 is furnished with steam temperature regulator 17 to shut off or open heat pipe circuit depending upon set temperature. Thermal boards 22 are hydraulically communicated by circuits 13, 21 with appropriate one-way fluid thermal boards 18 of elements 16 to make one-phase working body line. Every circuit 13, 21 comprises electrically driven pump 3, drain-fill valves 5, hydropneumatic accumulator 8, pressure and flow rate gages 4, 7, 10, flow rate controller 11 and electric heaters 23. Every circuit 13, 21 has working body temperature transducers 20. Replaceable elements of said circuits are connected in main lines via hydraulic joints. Main lines are fitted in manned comportment 1 via sealed lead-ins 6. Heat control system comprises also the two-chamber gas-fluid heat exchanger 24 with two replaceable fans included into both circuits 13, 21.

EFFECT: expanded application range, higher reliability and reparability.

1 dwg