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

FIELD: weapons and ammunition.

SUBSTANCE: method involves alignment of stabilised sighting line with target, measurement of deviations of guided missile from sighting line, transmission to the missile of control commands corresponding to these deviations, supply to missile control members of the signals corresponding to these commands. Missile control information area is formed and aligned with sighting line and its initial angular divergence γ₀ relative to its longitudinal axis and initial elevation angle φ₀ relative to sighting line is set in compliance with the expressions specified in the subject of invention. After missile capture the time of its movement, speed, movement time, heading angles of movement relative to target in horizontal and vertical planes, which are caused by carrier manoeuvring, is measured. Angular divergence and elevation angle of missile control information area are changed in compliance with the expressions specified in the subject of invention, and when capture of guided missile is lost, initial angular divergence γ₀ and elevation angle φ₀ is reset.

EFFECT: increasing guidance efficiency of controlled missile by increasing interference immunity of visual channel, guidance accuracy of controlled missile and introduction of additional information on parameters of guidance process of controlled missile to the target.