MISSILE GUIDANCE METHOD Russian patent published in 2011 - IPC F41G7/20 

FIELD: weapons and ammunition.

SUBSTANCE: missile guidance method involves measurement of target and missile coordinates. At that, angular offset of missile guidance trajectory relative to target sighting line is formed in proportion to parameter of missile guidance method and current difference of distances to target and missile. Guidance method parameter is determined in current time of missile guidance from the beginning of formation of the above angular offset from ratio Ǻ + U₁A = U₂W_T, where A, Ǻ - parameter of missile guidance method and its derivate respectively; U₁, U₂ - functions of parameters of relative missile approach to target, which are determined respectively as per the first and the second mathematical ratios; W_T - current value of required normal acceleration of missile, which is determined by movement of target sighting line.

EFFECT: reduction of required normal missile overloads and dynamic guidance error owing to straightening of kinematic trajectory irrespective of nature of target movement and missile approach speed to target.