ROCKET PROJECTILE WITH A GAS-DYNAMIC STABILIZATION SYSTEM Russian patent published in 2021 - IPC F42B12/02 F42B10/30 

FIELD: rocket technology.

SUBSTANCE: invention relates to the field of rocket technology, namely to rocket projectiles with a gas-dynamic angular stabilization system, mainly for multiple launch rocket systems. The nozzles of the gas-dynamic system are installed on the cylindrical section of the body of the head part and the distance from the place of its interface with the pointed section of the body to the middle of the output sections of the nozzles is 0.2-2.0 caliber of the projectile. The width of the output section of the nozzle in the direction of the longitudinal axis of the projectile does not exceed 0.2 caliber of the projectile. The output section of each nozzle is recessed into the body of the head part and is separated from its outer surface by a value of 0.02-0.2 of the nozzle width, while the axes of the output sections of the nozzles are located in a plane perpendicular to the longitudinal axis of the head part, and the length of the pointed section of the body is 1.5-3.5 caliber of the projectile. The stabilizer blades are mounted on a cylindrical fairing with a diameter exceeding 1.05-1.15 times the diameter of the output section of the jet engine nozzle, and the trailing edges of the blades in the area of the root chord are removed from the output section of the nozzle by a distance of 0.3-1.0 of the diameter of its output section.

EFFECT: invention makes it possible to create a rocket projectile of increased combat efficiency with reliable operation by providing maximum gas-dynamic stabilizing moment, minimizing the weight of the gas-dynamic stabilization system, hence an increase in the weight of the warhead, increase the accuracy and close grouping of firing by reliably parrying angular perturbations in the initial active section of the flight and eliminating the negative impact of the engine jet on the blades and aerodynamic characteristics of the stabilizer, to ensure the improvement of the aeroballistic characteristics of the projectile.

1 cl, 3 dwg