IMPULSE DETONATION ROCKET ENGINE Russian patent published in 2012 - IPC F02K7/02 F02K9/50 

FIELD: propulsion engineering.

SUBSTANCE: impulse detonation rocket engine contains the burner section (the entrance of this section is using for portion supply of detonation fuel), the impulse sparking system and the locking device for burner section output at the moment of it's filling-up by detonation fuel; the draught asymmetrical nozzle and the locking device. The draught asymmetrical nozzle is mounted on the output of burner section and it contains Laval's nozzle as a channel. That channel is tapered and quick-divergent at the direction of detonation product's expiration. Locking device is performed as rotor valve, which is situated at the nozzle's critical cut and is performed as cylindrical drive body with a rotation axis that interpenetrates draught nozzle's critical cut perpendicular to its axis. The end-to-end channel with the inner profile (the profile coincides with draught nozzle circuit on the length of cylindrical body's transverse size) is performed in the cylindrical body in the direction of nozzle's axis. The rotation axis of the cylindrical body and the axis of draught nozzle are situated at the one plane. The engine also contains a laser impulse system for sparking by laser spark (that spark is generating in the burner section); the command spark impulse synchronous feeding and burner section output locking sensor, and the rotor valve, which has one entry connected to the laser system and the other entry connected to the rotor valve drive.

EFFECT: increased stability of engine performance and expanded range of its operation modes, decreased vibration capacity.

4 cl, 2 dwg