SPIN-STABILIZED SUPERSONIC MISSILE Russian patent published in 2001 - IPC

FIELD: rocketry. SUBSTANCE: spin- stabilized supersonic missile has a tapered nose, military bay, jet engine and on aerodynamic stabilizing fin. The arched blades of the stabilizing fin are installed with their convex surfaces in the direction of missile spinning, and the concave surfaces are oriented towards the missile nose. The front and rear edges of each blade are made with a one-sided sharpening with a bevel located on the convex surface of the blade. The relationship between the average blade angle and the bevel angle is within (0.02-0.03)H/d. The relationship between the length of the tapered nose section and the span of the stabilizing fin equals 1.2-1.5, when H-span of the stabilizing fin, d-missile caliber. EFFECT: enhanced range of fire, enhanced combat efficiency and reliability of missile functioning. 1 dwg