FIELD: armament.
SUBSTANCE: the control unit of guided spin-stabilized missile has gyroscope with contactless pickup in the form of an optron section with radiators and photodiodes fastened in it in pairs, and raster with transparent and nontransparent sectors installed in the slot between them, fastened on the axle of the outer frame of the gyroscope, and an electronic equipment with a receiver of the control signals. The raster is fastened for its free rotation and permanent shift of the plane of its symmetry, passing through the middles of the transparent and nontransparent sectors , relative to the vertical in the direction opposite the direction of missile spin through angle α equal to the angle of missile turn in flight during the delay of the execution of the control actuator control commands due to provision of a means of unbalance.
EFFECT: enhanced accuracy of target hitting by guided missile.
3 cl, 4 dwg
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