Motor - rocket a propellant fluid with a plug of the propulsion chamber.

摘要

The liquid propellant rocket engine - with a plug of the propulsion chamber, comprises a combustion chamber (5), a device (8) of the injection of fuel is disposed at a first upstream end (51) of the combustion chamber (5), a nozzle throat (3) disposed at a second downstream end of the combustion chamber (5) which is remote from said first upstream end (51) and a divergent nozzle (9) located downstream of the nozzle throat (3). A device for selectively closing of the nozzle throat (3) comprises a closure member is axially symmetrical (1) placed downstream of the nozzle throat (3), a rod (7) of the control of the shut-off member (1), a first short centering member (6) of the control rod (7) situated at the first upstream end (51) of the combustion chamber at the level of the device (8) of the injection of fuel, a second short centering member (4) of the control rod (7) situated in the combustion chamber (5) in the vicinity of the nozzle throat (3) and upstream of that - latter, and a system (2) for returning to the closed position of the control rod (7) of the device for selectively closing of the nozzle throat (3).