| 摘要 |
FIELD: development of missile control systems, applicable in antitank missile complexes. ^ SUBSTANCE: the method for guidance of a guided missile includes the launch of the guided missile, reception and focusing on the photodetector of the luminous flux of the background-target situation containing the luminous flux of the background and the luminous flux of the useful signal source, discrimination of the co-ordinates of the useful signal source, the co-ordinates of the guided missile are determined and the control commands for transmission to the missile are formed. Before the launch of the guided missile the useful signal margin KMIN factor is assigned, after focusing of the luminous flux of the background-target situation the video frame of the image of the background-target situation is formed, the output signal is taken off each cell of the matrix type photodetector, the signal corresponding to the mean value of all the output signals from the photodetector cells is determined, the root mean square deviation of output signals from the photodetector cells is determined, threshold value Uthr of the useful signal is determined from the mathematical expression, and the co-ordinates of the image that is formed at the cells with the level of the output signal satisfying the condition Uout >= Uthr are discriminated. The guidance system has also an objective lens, radiation photodetector, series-connected co-ordinates discrimination unit, command formation unit, in addition it has series-connected useful signal margin factors unit, analyzing device and a selection unit. The output of the objective lens is connected to the input of the radiation photodetector, whose first output is connected to the second input of the selection unit, whose output is connected to the input of the co-ordinates discrimination unit. The second output of the radiation photodetector is connected to the second input of the analyzing device, the radiation photodetector is based on a matrix-type photodetector. ^ EFFECT: enhanced quality of missile guidance without any change of the missile construction, enhanced reliability and accuracy of discrimination of the useful signal source at various background-target situations during the whole flight time of the guided missile and improved interference protection of the whole control system without its essential complication. ^ 2 cl, 2 dwg |
