GUIDED MISSILE CONTROL METHOD Russian patent published in 2011 - IPC F41G3/22 F41G5/24 

FIELD: weapons and ammunition.

SUBSTANCE: method involves formation of independent stabilised sighting line and its alignment with target, deviation of gun barrel from sighting line through sighting and lateral lead angles, firing, capture of guided missile with guidance system, measurement of deviations of missile from sighting line, formation and transmission to it of control commands corresponding to these deviations, generation and supply to missile control members of the signals corresponding to these commands. If several targets are available, their coordinates are measured, stored and entered to the field of vision. In case of missing the first (closest) target and at fulfillment of conditions ψ_2,1<{[(D₂-D₁)/V_m]-t_l}ω_nh, φ_2,1<{[(D₂-D₁)/V_m]-t_l}ω_nv, where D₁ - distance to the first (closest) target; D₂ - distance to the second target; V_m - cruise speed of controlled missile; t_l - time losses determined with response time of guidance system and operator; ω_gh, ω_nv - rational angular guidance speeds of controlled missile in horizontal and vertical planes respectively; ψ_2,1, φ_2,1 - angular discrepancies between the second and the first lines of targets in horizontal and vertical planes; movement of sighting line is performed from the first target to the second target, and then in case of bad shots to farther located targets till the target is hit or control cycle is completed.

EFFECT: increasing firing control efficiency of guided missile.