METHOD OF GUIDANCE AND GUIDANCE SYSTEM OF SPIN-STABILIZED MISSILE Russian patent published in 2007 - IPC F41G7/24 

FIELD: development of the missile guidance systems, applicable in complexes of antitank and antiaircraft guided missiles.

SUBSTANCE: the method consists in compensation of variable-sign dephasings due to formation of the control commands in the vertical channel-proportionally not only to the vertical missile deviation, but also to the horizontal deviation, and in the horizontal channel-proportionally not only to the horizontal deviation, but also to the vertical deviation. The method consists in formation of radiation, reception of this radiation by the missile control equipment, formation of signals proportional to the misalignment between the missile and the beam axis in the vertical the missile and the beam axis in the vertical and horizontal planes, modulation of the misalignment signals periodic in the roll angle, shifted relative to each other by angle π/2 by reference signals, formation of the control signals in the coordinate system coupled to the spin-stabilized missile and transformation of the obtained control signals to the deflections of the controls. Prior to modulation, the signal proportional to the misalignment between the missile and the beam axis in the vertical plane amplified with coefficient k₁ is summed up with the signal proportional to the misalignment between the missile and the beam axis in the horizontal plane attenuated with coefficient k₂, and the signal proportional to the misalignment between the missile and the beam axis in the horizontal plane amplified with coefficient k₁ is summed up with the signal proportional to the misalignment between the missile and the beam axis in the vertical plane attenuated with coefficient k₂, coefficients k_1, k₂ are calculated according to the preset mathematical dependences.

EFFECT: enhanced accuracy of fire by roll-stabilized missiles.

2 cl, 3 dwg