| 摘要 |
A liquid rocket engine with controlled thrust vector has a combustion chamber with nozzle, turbo-pump system for supply of fuel components to the combustion chamber, turbine exhaust collector of which is connected to circular collector of unit for exhaust gas injection to supersonic section of the nozzle. Upstream of circular slot of unit for exhaust gas injection in each one fourth section of the nozzle units for fuel component injection are installed, those are connected to fuel high-pressure line of engine placed downstream of outlet collector of cooling section of the chamber and connected to drives controlled by the system for engine thrust vector control. Each injection unit has either centrifugal, or jet injection nozzles provided in the wall of the nozzle or in movable two-position solid interceptor in the part that is introduced to supersonic flow of the nozzle, at that at inlet to each injection unit a generator of pressure pulses of liquid fuel component supplied to nozzle is installed. |
