FIELD: supersonic guided missile.
SUBSTANCE: supersonic guided missile, configured according to the aerodynamic “canard” design, comprises blade stabilizers, a cruise engine, a nozzle block, a body with a pointed nose part with aerodynamic rudders placed thereon, and a control system. The launching stage is mounted on the nozzle block. The launching stage contains a solid-propellant rocket engine, a gas-dynamic actuator with nozzles located on the side surface perpendicular to the longitudinal axis of the projectile, and an attachment unit connecting the launching stage and the nozzle block. The separation of the starting stage occurs due to the destruction of the attachment unit under the influence of the pressure generated by the combustion products of the cruise engine on the front end of the launching stage after launch of the stage.
EFFECT: increasing the grouping and accuracy of firing a supersonic guided missile.
3 cl, 3 dwg
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