METHOD FOR MISSILE CONTROL AND MISSILE GUIDANCE SYSTEM Russian patent published in 2006 - IPC F41G7/24 F42B15/01 

FIELD: armament, in particular, rocketry, applicable in development of missile systems, for example, with carriers on the ground, in which beam riding guidance systems are used.

SUBSTANCE: electromagnetic radiation from the control point is transformed to electric signals of the missile co-ordinates in yaw and pitching, missile control commands in yaw and pitching are formed from the co-ordinate electric signals, the magnitude of the missile co-ordinate is integrated in yaw, then the magnitude of the electric signal co-ordinate in yaw is summed up with its integrated magnitude, and the missile yaw control command is formed from the summary magnitude.

EFFECT: introduction of an adder, integrator and an integrator switching unit in the missile guidance system in the yaw channel has enhanced the accuracy of missile guidance in the yaw channel. 2 cl, 1 dwg