| 摘要 |
The utility model relates to rocket engineering. A sustainer rocket engine on unitary paste-like fuel for upper stages of launch-vehicles includes system for fuel supply with gas-pressurized generator, fuel tank separated to pressing-out and fuel cavities, and main chamber uninstalled at the back bottom of the tank with non-controlled spinneret block and nozzle. To increase reliability of operation non-controlled spinneret block is installed inside with gap with front bottom of combustion chamber and is made of two parts - the front and the back ones, placed with gap with respect to each other, this by means of channels in heat protection coating of the combustion chamber is connected to start gas generators of propulsion unit placed outside its combustion chamber. Slot between the front bottom of combustion chamber and front part of spinneret block is connected to fuel cavity of tank through openings in the front bottom of the combustion chamber, those are overlapped with shutoff valve placed in circular cavity provided in the body of the combustion chamber, which by means of pipelines with valve is connected to pressure source in the system of fuel supply.
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