SOLID-PROPELLANT ROCKET ENGINE Russian patent published in 2012 - IPC F02K9/92 F02K9/26 

FIELD: engines and pumps.

SUBSTANCE: rocket engine includes housing, nozzle and hydrodamping assembly. Hydrodamping assembly consists of differential piston fixed with locking mechanism, and injection assemblies. Differential piston is formed with parts of large and small diameter and installed with possibility of longitudinal movement in shell filled with cooling agent. Hydrodamping assembly is fixed by means of posts inside the housing, and some part of differential piston having smaller diameter is taken out to convergent part of nozzle. Injection assemblies are made in cylindrical wall of shell or in frames and located in several rows distributed throughout the length of shell. Damper is installed at the shell edge facing the nozzle and can be moved in longitudinal direction. Damper is related to the frame located at the shell edge facing the nozzle and provided with possibility of longitudinal movement on external surface of the shell. Frame has L-shaped section the flange of which contacts the rim made on external surface of the shell and forms inner cavity of the frame, which is interconnected with inner cavity of shell.

EFFECT: invention allows increasing hydrodamping efficiency and decreasing after-effect pulse.

3 cl, 11 dwg