FIELD: rocket technology.
SUBSTANCE: invention relates to rocket engineering and can be used in making solid fuel pulsed engines, to which raised requirements of different impulses during operation in pair or in whole cluster are applied. Pulsed solid-propellant engine comprises combustion chamber with charge from all-round burning cylindrical channel cartridges, located between support grates, nozzle, igniter, fixed on front support grate on combustion chamber bottom part side, and explosive cartridge installed in combustion chamber bottom part. Between nozzle and support grate located on nozzle side, elliptic shape perforated thin-walled heat-resistant partition is installed, with convex surface facing towards nozzle and with perforation in form of through holes. Partition through holes axis make acute angle with nozzle axis with top towards nozzle throat. Partition holes total area exceeds nozzle throat area.
EFFECT: invention reduces spread of solid-fuel pulsed engine burst of power due to increased duration of fuel particles residing in nozzle path.
3 cl, 2 dwg
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