FIELD: engines and pumps.
SUBSTANCE: liquid propellant rocket engine containing power frame, combustion chamber having the head, cylindrical part and nozzle, which is fixed on power frame by means of suspension assembly providing the possibility of rocking in two planes by means of drives, which are attached to power ring made on combustion chamber; gas generator and turbopump unit containing in its turn the turbine, oxidiser pump, fuel pump, gas line connecting the outlet of turbine to head of combustion chamber through suspension assembly; at that, roll nozzles are grouped into roll nozzle blocks in pairs and installed on the housing of rocket stage and connected to the header to which there connected is gas-generator gas extraction pipeline the other end of which is connected to gas line. Roll nozzle block containing two roll nozzles having fuel headers combined into one assembly; according to the invention, pair of roll nozzles is equipped with three-way valve installed between them and having the drive connected to it by means of the shaft; cut-off fuel valve is installed on fuel header of each roll nozzle.
EFFECT: improving control reliability of thrust vector and roll.
3 cl, 5 dwg
