SUPERSONIC SPIN-STABILIZED MISSILE Russian patent published in 2023 - IPC F42B15/00 

FIELD: weapons and ammunition.

SUBSTANCE: invention relates to a supersonic spin-stabilized missile. A supersonic spin-stabilized missile contains a cylindrical body with a pointed nose, aerodynamic control surfaces, a jet engine and a stabilizer with deployable arcuate blades mounted on axles fixed in the fairing. The rudders are placed on a cylindrical section of the body at a distance of 0.3…3.0 of missile caliber from the point where it mates with the pointed nose. The ratio of the projection area of two rudder consoles .The projection area of two rudder consoles S_2r =(0.15...0.50)S_2bl and the distance L_r from the axis of rotation of the steering wheel to the center of mass of the projectile after burnout of the jet engine fuel is within (0.15…0.50)L_bl, where L_bl is the distance from the middle of the side chord of the arcuate blades of the stabilizer to the center of mass of the projectile after the jet engine fuel burns out. The expanding arcuate blades of the stabilizer are shifted from the rear end of the jet engine towards the rudders by 0.2…1.0 of missile caliber and mounted on axles fixed in a fairing rigidly connected to the engine housing. The arcuate blades of the stabilizer are oriented with their convex surfaces in the direction of rotation of the projectile, that is, clockwise in the rear view, and are installed at an angle δ =0.2°…0.6° to the longitudinal axis of the projectile. The leading edges of the folding arched blades of the stabilizer are made of an asymmetrical shape in the form of a flat bluntness and bevel located on the convex surface of the blades. The bevel angle in the plane perpendicular to the leading edges of the stabilizer blades is within β=5°…15°.

EFFECT: improving the aeroballistic characteristics of the missile, increasing firing accuracy and increasing the firing range.

1 cl, 1 dwg