REMOTELY CONTROLLED MISSILE GUIDANCE METHOD Russian patent published in 2011 - IPC F41G7/20 F42B15/01 

FIELD: weapons and ammunition.

SUBSTANCE: method involves measurement of target and missile coordinates, formation of missile guidance reference trajectory, formation of linear disagreement between missile and reference guidance trajectory, formation of missile control command proportional to linear combination of linear disagreement between missile and reference guidance trajectory, derivative of linear disagreement and to integral of linear disagreement, determination of dynamic error of missile guidance along reference trajectory and further correction of missile guidance reference trajectory by the value of the same dynamic error. Current component of missile control command proportional to integral of linear disagreement between missile and reference guidance trajectory is corrected by the value proportional to ratio of current value of the required missile overload for movement along reference guidance trajectory to current value of the determined missile overload. Current value of the required missile overload for movement along reference guidance trajectory is determined proportionally to value of the calculated dynamic error of missile guidance along reference trajectory considering transfer factor of open missile control loop.

EFFECT: improving dynamic guidance accuracy of remotely controlled missile and enlarging its application conditions.

2 cl, 2 dwg