ROTATING ROCKET PROJECTILE LAUNCHED FROM A TUBULAR GUIDE Russian patent published in 2023 - IPC F42B15/00 

FIELD: rocket technology.

SUBSTANCE: invention can be used in the development of rockets launched from tubular guides. A rotating missile projectile launched from a tubular guide contains a head part (1), a stabilizer (4) with opening arcuate blades (5), convex surfaces (7) oriented in the direction of projectile rotation, having one-sided bevels on the leading edges from the side of their convex surfaces with an angleβ_blade =5…15° in a plane perpendicular to the edges, and installed at an angle to the longitudinal axis of the projectile, a jet engine (2) with one central nozzle, including a device for generating torque using a jet engine jet (2), made in the form of evenly spaced in the circumferential direction on the side surface plate nozzles with a constant thickness in height and the same angle of elevation of the helix of their side surfaces to the longitudinal axis of the projectile, for projectile rotation in the same direction as from the torque generated by the blades (5) of the stabilizer (4). The surface of each plate of the rotation device, facing the longitudinal axis of the nozzle, is formed by elements of a cylindrical surface with an axis coinciding with the longitudinal axis of the nozzle, and the angle of elevation of the helix of the side surfaces of the plates of the rotation device is made within the limits determined by the dependence: _pl = (0.8 ... 2.4)_blade * S_blade / S_pl * r_blade / r_pl * n_blade / n_pl, where S_pl is the projection area of the side surface of one plate of the rotation device in a plane passing through the longitudinal axis of the projectile; S_blade - the projection area of one convex stabilizer blade in a plane passing through the longitudinal axis of the missile; r_pl - the distance from the axis of the missile to the centre of pressure of the plate of the rotation device; - the distance from the axis of the missile to the centre of pressure of the projection of the convex blade of the stabilizer; H_st - the span of the convex blades of the stabilizer; d_fair - the diameter of the fairing on which the convex blades of the stabilizer are installed; n_pl, n_blade - the number of plates of the rotation device and the arcuate blades of the stabilizer, respectively; δ_blade - the angle of installation of the convex blades of the stabilizer to the longitudinal axis of the rocket; δ_pl - the angle of elevation of the helix of the side surfaces of the plates of the rotation device.

EFFECT: creation of a rotating projectile launched from a tubular guide, with a significantly increased firing range and increased operational reliability, with improved aeroballistic characteristics by reducing the resistance of the rotation device and stabilizer blades, reducing initial disturbances and the spread of aeroballistic characteristics in flight, optimizing the rotation speed and eliminating resonant phenomena both during departure from the guides and in all parts of the trajectory.

1 cl, 1 dwg