| 摘要 |
FIELD: transport. ^ SUBSTANCE: invention relates to spacecraft engineering and concerns providing required temperature conditions in pressurised compartments of spacecrafts and space stations. Endothermal control system of aircrafts comprises housing (1), cooling and heating loop (8), hat exchangers (3), radiator (4). In the endothermal control system, magneto-hydrodynamic pump (MHD-pump) (2) is used. As heat carrier electrically conductive exothermic coolant is used, for instance watered nitrogen tetraoxide. To prevent system breakdown heat carrier (5) reservoir with control valve (6) is additionally introduced. During system pressure drop, valve (6) provides additional heat carrier delivery, during pressure rise, excess pressure is released through valve (7). ^ EFFECT: higher efficiency of thermocontrol system in the part of increase of thermal control productivity and minimisation of serving subsystems mass to reduce spacecraft dimensions. ^ 2 dwg |
