| 摘要 |
A group of inventions relates to the rocket technology and can be used to pressurize the fuel tanks of propulsion systems of launchers. When refueling tanks 1, 2 of the propulsion system (PS) with an opened drain valve fill-discharge valve 18 is opened and the coolant is fed through the line 17 into a special tank 3, which is located in the tail compartment 23. Upon reaching the level of the coolant detected by the level sensor 15 filling of the tank 3 stops and starts refilling helium into cylinders 9. To do this, an automatic unit 10 is opened and the conduit 11 is used for filling helium into the cylinders 9. To maintain the desired temperature of the coolant in the tank discharge valve 4 is closed, and an ejector 16 is turned on. When the coolant level drops below a predetermined level detected by the sensor command for opening a fill-discharge valve 18 is issued, and the makeup of the tank starts with a coolant starts. The presence of thermal insulation capacity 5 of the tank 3 significantly reduces the effect of the invention on the temperature regime of the tail compartment 23 and reduces the required power of an ejector 16. Before the start of the launcher a drain valve 4 is opened, and the ejector16 is turned off and the fill-discharge valve 18 is opened. The coolant is discharged by gravity to the start storage. Further, the fill-discharge valve 18 is opened, the valve 20 is opened too and when the propulsion system comes to operation the fuel at a nominal temperature from the high pressure tank 22 through a metering element 21 on the conduit 19 enters into a special tank 3, where it heats the cylinders 9. Helium for pressurization after opening of the automatic unit 13 via pipe 12 through a heat exchanger 14 enters the free volume of the tank 1 for oxidizer. Further the valve 6 is opened and by the drain conduit 7 the cooled fuel is discharged into a supply line 8 and then to the pump inlet 24 of high pressure fuel. |
