FIELD: cosmonautics.
SUBSTANCE: invention relates to propulsion systems of spacecrafts, in particular, to providing thermal conditions of engines running on combustible fuel components stored in gaseous phase. Propulsion system comprises a controller, a rocket engine, a unit of nozzles, valves and sensors of gas state parameters. High-pressure cylinders have heat-conducting structure with perforated ribs for efficient heat exchange with rocket engine via pneumatic lines. Temperature sensors are installed in the cylinder. Heat transfer elements with thermal bridges transfer heat from engine to pneumatic system and high pressure cylinders.
EFFECT: increased efficiency of heat exchange, reduced weight and complexity of design of propulsion system.
10 cl, 4 dwg
