FIELD: spacecraft.
SUBSTANCE: proposed tank pressurization system of spacecraft power units contains pneumatic main lines connected with pressurization system and gas spaces of fuel and oxidizer tanks and starter-shutoff valve, gas pressure regulator and safety valve installed in each pneumatic main line. Drain main line is connected at outlet of safety valves. Said drain main line is furnished with nozzle in form of hollow disk whose walls form circular bell. Cylindrical chamber is arranged in center of hollow disk. Through holes of equal size and similar outline are made diametrically opposite in wall of cylindrical chamber connecting converging walls of circular bell.
EFFECT: prevention of destabilization of flight of spacecraft at emergency relief of gas of pressurization system.
2 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| FUEL-TANK PRESSURISATION SYSTEM | 2006 |
|
RU2339835C2 |
| FUEL TANK SUPERCHARGING SYSTEM | 2006 |
|
RU2339834C2 |
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|
RU2339833C2 |
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|
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| PRESSURIZATION SYSTEM OF FUEL AND OXIDIZER TANKS OF SPACE FLYING VEHICLE ENGINE PLANT | 1997 |
|
RU2140003C1 |
| TOPPING UP SYSTEM (VERSIONS) | 2003 |
|
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| FUEL FEED SYSTEM | 2006 |
|
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| FUEL TANK SUPERCHARGING SYSTEM (VERSIONS) | 2006 |
|
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| PROPELLANT TANK PRESSURIZATION SYSTEM OF SPACE CRAFT PROPULSION UNIT | 1999 |
|
RU2159348C1 |
| FUEL FEED SYSTEM | 2009 |
|
RU2407907C1 |
