SPIN-STABILIZED MISSILE Russian patent published in 2004 - IPC

Abstract RU 2241953 C1

FIELD: applicable in spin-stabilized guided missiles with a single-channel control system, having a wide range of variation of flight speed from the subsonic to the supersonic one.

SUBSTANCE: the missile has a body with a fighting compartment located in it, jet engine and a tailplane installed on the body. The tailplane cantilevers are installed at an angle to the body longitudinal axis. The missile spin rate stabilization components are installed around its longitudinal axis and made in the form of destabilizers. The cantilevers of the destabilizers are installed at an angle to the body longitudinal axis. They are made with an unsymmetrical profile due to the chamfers of their front and rear edges on the side of the cantilever surface facing the side of the missile spin. The bevel angle of the rear edge of the cantilever makes up 5 to 12 deg, and the relationship between the bevel angle of the front edge and the angle of installation of the cantilever of the destabilizers makes up 5 to 16.

EFFECT: enhanced accuracy of missile guidance.

6 dwg

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RU 2 241 953 C1

Authors

Afonin A.G.

Bol'Shun V.G.

Grishin V.V.

Gushchin N.I.

Kashin V.M.

Rjutin V.B.

Dates

2004-12-10—Published

2003-10-20—Filed