METHOD FOR GUIDANCE OF GUIDED MISSILE AND GUIDANCE SYSTEM FOR ITS REALIZATION Russian patent published in 2006 - IPC F41G7/00 

FIELD: missile control systems, applicable in antitank missile complexes.

SUBSTANCE: the method for guidance of guided missile includes the missile take-off, reception and focusing at the photodetector of the background-target situation radiation, containing radiation of the background and radiation of the useful signal source, discrimination of the coordinates of the useful signal source, determination of the coordinates of guided missile and forming of control commands for transmission to the missile, after the take-off of the guided missile the minimum level of the output signal from the photodetector U_MIN, taking into account the noise component of the photodetector and the radiation background component of the background - target situation, is computed. The maximum level of the output signal from the photodetector U_MAX required for reliable tracking of the guided missile is computed. After focusing of the luminous flux from the on-board radiation source the exposure time of the photodetector is changed so that the output signal from the photodetector corresponding to the dropping radiation from the on-board radiation source would correspond to condition: The guidance system of guided missile having a series-connected objective lens, radiation photodetector, coordinate discrimination unit and a command forming unit additionally uses an analyzing device, series-connected illuminance estimation unit, comparison unit and a sensitivity adjustment unit. The second output of the radiation photodetector is connected to the input of the analyzing device, whose output is connected to the second input of the comparison unit, the output of the sensitivity adjustment unit is connected to the second input of the radiation photodetector. The illuminance estimation unit is connected between the radiation photodetector and the coordinate discrimination unit.

EFFECT: enhanced quality of missile guidance without any change of the missile construction, provided a high level of the signal/noise ratio during the whole flight time of the guided missile, enhanced noise immunity of the whole control system without a significant complication of it.

2 cl, 2 dwg