METHOD FOR INCREASING THE FLIGHT RANGE OF AN ARTILLERY PROJECTILE WITH A ROCKET-RAMJET ENGINE AND AN ARTILLERY PROJECTILE IMPLEMENTING IT (OPTIONS) Russian patent published in 2022 - IPC F42B10/38 

FIELD: to artillery shells.

SUBSTANCE: inventions group relates to a method for increasing the flight range of an artillery shell and to artillery shells. The method for increasing the flight range of an artillery projectile consists in the fact that the movement of the projectile in the gun barrel is carried out under the influence of the pressure of the combustion products of the propellant charge and the projectile is guided along the barrel by means of an obturator belt sliding relative to the projectile body. The projectile contains a rocket-ramjet engine installed in the aft part of the projectile and including a gas generator body with a solid fuel charge located in it, a diaphragm, a gas generator bottom with nozzle holes, a shell of the primary volume of the afterburner connected to the gas generator body, an air intake device and a system for increasing the volume of the chamber afterburning with a threaded bushing with a collar, made with the possibility of translational movement during its rotation and locking of the translational movement when the shoulder of the threaded bushing interacts with the stop in the rearmost position of the said bushing. The threaded bushing with a shoulder of the system for increasing the volume of the afterburner is rigidly connected to the stabilizer attachment unit or assemblies and is threadedly connected to the shell of the primary volume of the afterburner, which ensures translational movement of the bush with a shoulder relative to the shell. Stabilizers are installed at an angle to the axis of the projectile and are closed with a resettable protective cap. The stop for interaction with the shoulder of the threaded bushing in its extreme rear position is located on the shell of the primary volume of the afterburning chamber. After the projectile leaves the barrel, a charge of solid fuel is ignited, which leads to the release of the protective cap, the opening of the stabilizers, which transmit the force from the oncoming air flow through the stabilizer mount or mounts to the threaded sleeve with a shoulder, which due to this rotates in the threaded connection with the shell primary volume of the afterburning chamber and progressively moves back to the rearmost position, increasing the volume of the afterburning chamber. Further, in the extreme rear position, the threaded bushing with the shoulder is locked due to the interaction of the shoulder of the threaded bushing with an emphasis on the shell of the primary volume of the afterburner chamber. The air supply path of the air intake device is formed by through slots in the shell of the primary volume of the afterburner chamber and through slots in the threaded bushing with a shoulder, which are combined with through slots in the shell at the rearmost position of the threaded bushing to ensure air flow for afterburning the products of primary combustion of solid fuel with their subsequent expiration through the nozzle and generating tractive effort.

EFFECT: increasing the flight range of an artillery projectile equipped with a rocket-ramjet engine, due to a system for increasing the volume of the afterburner chamber.

5 cl, 7 dwg