METHOD FOR GUIDANCE OF GUIDED MISSILE AND GUIDANCE SYSTEM FOR ITS REALIZATION Russian patent published in 2004 - IPC

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

SUBSTANCE: the method includes formation of the wide and narrow control fields, launching of the guided missile, guidance of the guided missile during time t₁ in the wide control field in accordance with the attitude of the radiation source relative to the sight line, guidance of the missile in the narrow control field in accordance with the attitude of the radiation source relative to the sight line, time moments t_ph, t_d1, t_d2, t_d3 are determined before launching of the guided missile. At guidance of the guided missile in the wide control field the band of transmission of the photocurrent amplifier is limited at reaching of time moment t_ph, at reaching of time moment t_d1 a decrease of the solid angle of exposure of the photodetecting element is accomplished, at guidance of the missile in the narrow control field at time moments t_d2 and t_d3 the solid angle of exposure of the photodetecting element is also decreased. The missile guidance system has series-connected objective lens, optical raster, radiation photodetector, photocurrent amplifier, series-connected co-ordinate discrimination and a command formation unit, as well as a reference voltage generator, whose input is connected to the second output of the optical raster, and the output - to the second input of the co-ordinate discrimination unit, in addition use is made of a time counter, switch, diaphragm change-over unit, diaphragm unit and a narrow-band servo filter, the output of the photocurrent amplifier is connected to the input of the time counter and the second input of the switch. The output of the time counter is connected to the first input of the switch, whose first output is connected to the first input of the co-ordinate discrimination init, the second output - to the input of the narrow-band servo filter, the third output - to the input of the diaphragm change-over unit whose output is connected to the input of the diaphragm unit, installed for mechanical correction of the solid angle of radiation photodetector exposure, the output of the narrow-band servo filter is connected to the third input of the coordinate discrimination unit.

EFFECT: enhanced quality of missile guidance in the wide control field with any change of the structure of the missile proper, enhanced antijum capacity of the whole control system of the missile without an essential complication.

2 cl, 2 dwg