METHOD FOR INCREASING THE FLIGHT RANGE OF ACTIVE-REACTIVE PROJECTILE AND ACTIVE-REACTIVE PROJECTILE WITH MONOBLOCK COMBINED ENGINE UNIT (VERSIONS) Russian patent published in 2021 - IPC F42B10/40 

FIELD: weaponry.

SUBSTANCE: group of inventions relates to a method for increasing the flight range of an active-rocket projectile and to variants of an active-rocket projectile. Disclosed is a method for increasing the flight range of an active-rocket projectile containing a propulsion system with a solid fuel charge located in the rear part of the projectile, a bottom with nozzle inserts located in a circle around the longitudinal axis of the projectile, and a shell of the afterburner chamber. The method consists in the fact that the movement of an active-rocket projectile in the gun barrel is carried out under the influence of the pressure of the combustion products of the propellant charge. Some propellant charge combustion products are passed through the bottom nozzle liners into the cavity of the propulsion system to ignite the solid fuel charge. Further, after the projection of the active-rocket projectile from the bore of the gun barrel, the products of the primary combustion of solid fuel flow through the support tube-gas pipe into the space formed by the diaphragm and the bottom, and then through the nozzle inserts into the volume limited by the bottom and shell of the afterburner chamber, which forms the afterburner and is open from the side of the bottom cut of the projectile. The nozzles of the nozzle inserts are profiled tapering towards the center from their both ends with the possibility of creating thrust during the outflow of the products of the primary combustion of the solid fuel and passing part of the products of the combustion of the propellant to ignite the charge of the solid fuel. Afterburning of the primary combustion products of the fuel flowing out through the nozzle inserts nozzles is carried out in the air flow entering the afterburning chamber from the vortex flow formed during the supersonic flow around the active-rocket projectile in flight.

EFFECT: technical result consists in providing conditions for creating thrust by the propulsion system while reducing the force of the aerodynamic resistance of the projectile and, as a consequence, in increasing the range of the projectile.

5 cl, 7 dwg