ROCKET PROJECTILE STABILIZER Russian patent published in 2023 - IPC F42B15/00 

FIELD: rocket technology.

SUBSTANCE: projectile stabilizer contains a fairing (1) with unfolding arcuate blades (2) mounted thereon, the blades (2) having a combined shape of the blade leading edges, including a flat blunt (3), and convex side surfaces oriented in the direction of the projectile rotation. The leading edges of the blades are made in the form of a combination of flat blunting with a width of 0.10…0.25 blade thickness in the area of the side chord and wedges (4) and (5) with convex and concave side surfaces having a total angle of 10°…30° in a plane perpendicular to the leading edges. The tip chord of the blade is 0.6…1.2 of the said side chord. The average stabilizer blades installation angle relative to the longitudinal axis of the projectile, measured in various sections of the blades, is selected by the formula

where β - the total angle of sharpening of the leading edges of unfolding arcuate stabilizer blades in a plane perpendicular to the edges; d - projectile caliber; b «_av» =0.5(b_s +b_e ) - mean chord of the arcuate blade; b_s - side chord of the arcuate blades; b_tp - tip chord of an arcuate blade; H_st - span of unfolding arcuate blades of the stabilizer; d_f - outer diameter of the fairing, mounting the arcuate blades of the stabilizer; n_bl =3…8 - number of arcuate blades of the stabilizer.

EFFECT: creation of a stabilizer for a rocket projectile with subsonic and supersonic flight speeds with increased reliability of operation, improved main characteristics due to reduced dispersion of aero-ballistic characteristics of the projectile, reduced sensitivity to wind and ensuring resonance-free flight at zero angles of attack.

1 cl, 1 dwg