FIELD: spacecraft engine plants; operation of spacecraft jet engines. SUBSTANCE: propellant tank pressurization system includes control unit of electropneumatic valves 9 and hermetic gas-filled container 1 with on-board compressor 2 arranged in it. It is connected with gas cavities 5,6 of respective propellant tanks 7,8 by means of low-pressure pneumatic mains 3,4. One main 14 of pressurization system is provided with filter 10, electropneumatic valve 11, gas pressure-reducing valve 12 and pressure indicator 13 fitted in series. This main is brought in communication with container volume by means of additional main. Electropneumatic valve is electrically connected with pressure indicator through control unit of electropneumatic valves. EFFECT: reduced mass and simplified construction of compressor unit at simultaneous enhanced reliability of compressor and pressurization system as a whole in space orbital flights. 1 dwg
