REMOTELY CONTROLLED MISSILE GUIDANCE METHOD Russian patent published in 2012 - IPC F41G7/24 

FIELD: weapons and ammunition.

SUBSTANCE: in acceleration section of missile flight trajectory in heading plane of missile guidance there pre-installed, prior to missile launching, is threshold parameter value of missile movement relative to target sight line. Evaluation of current value of missile movement parameter relative to target sight line is performed as per target and missile coordinates. Current parameter value of missile movement is compared to its specified threshold value considering the direction of programme gathering trajectory relative to target sight line. If current parameter value of missile movement is less than threshold value, corrective command of missile control is formed as per the value proportional to the present missile overload, and the command leading to the side from target sight line as per the sign. Formed corrective command is added to control command proportional to linear deviation. Missile guidance is performed in acceleration section as per total control command.

EFFECT: prevention of missile guidance failure under conditions of interference created with own accelerator engine of the missile.

4 cl, 1 dwg