FIELD: space engineering. SUBSTANCE: system includes pneumatic mains connected with pressurization bottles and gas cavities of propellant tanks (fuel and oxidizer tanks), valves fitted in pneumatic mains and on board temperature control system. Pressurization systems also includes hermetic gas-filled container with on-board compressor located inside it; compressor is connected with pressurization bottles by means of high-pressure pneumatic mains and with gas cavities of propellant tanks (fuel and oxidizer tanks) by means of low-pressure pneumatic mains. heat exchanger mounted inside container is connected to on-board temperature control system; hermetic diaphragm divides inner volume of container into two isolated cavities which are communicated through compressor cavities and heat exchanger jacket. Compressor is provided with gas circulation actuator. EFFECT: enhanced efficiency of cooling of on-board compressor; enhanced reliability of propellant tank pressurization system during operation in space. 1 dwg
