SYSTEM OF SPACECRAFT THERMAL CONTROL

摘要

FIELD: transportation. ^ SUBSTANCE: invention relates to space engineering and may be used in development of thermal control systems (TCS) of telecommunication satellites systems. TCS comprises two independent board circulation tracks identical in composition with heat carrier, which are arranged next to each other in honeycomb panels. Each of tracks comprises inlet and outlet fueling connectors connected to according fueling connectors of detachable block of the system. The latter also comprises two identical liquid tracks, every of which includes the first and second heat exchangers. The first liquid cavities of heat exchangers are connected serially, and the second cavities are communicated to circulating track of coolant in ground system of thermal mode maintenance according to counterflow circuit of heat carrier and cooling medium circulation in cavities of heat exchangers. Outlet of this ground system is communicated to inlet of the second cavity of the second heat exchanger of the first track in detachable unit arranged in the form of single structure. Outlet of the second cavity of specified heat exchanger is communicated to inlet of the second cavity of the second heat exchanger in the second track of block. Outlet of the latter is connected to inlet of the second cavity of the first heat exchanger arranged in the same track of unit, outlet of which is communicated to inlet of the second cavity of the first heat exchanger in the first track of block. Outlet of specified second cavity is connected to inlet of ground system of thermal mode maintenance. ^ EFFECT: simplified design of TCS detachable block, ground testing facilities and procedure of spacecraft tests. ^ 3 dwg