FIELD: space engineering; ensuring required temperature and moisture conditions in pressurized compartments of spacecraft and orbital stations. SUBSTANCE: proposed system includes cooling and heating loops connected through liquid-to-liquid heat exchangers. Heat from heating loop is transferred to cooling loop through above-mentioned heat exchangers. If necessary, heat may be radiated from surface of radiation heat exchanger which is provided with heat-transfer agent flow regulator with stepping motor. Cooling loop is provided with two electric pumping units (at service life up to 100000 hours). In case of derangement of flow regulator, control of flow rate may be effected with the aid of these units before replacement of flow regulator. EFFECT: enhanced operational reliability. 2 cl, 1 dwg
