METHOD FOR TARGET DESIGNATION BY DIRECTION OF GUIDANCE SYSTEM OF CONTROLLED OBJECT Russian patent published in 2021 - IPC F41G7/00 F41G7/34 G01S13/00 

FIELD: target designation systems.

SUBSTANCE: invention relates to methods for target designation in the direction of the guidance system of a controlled object and can be used in the creation of new and modernization of existing methods and devices for target designation in the direction of guidance systems of controlled objects - both remotely piloted (unmanned) aircraft, and in manned aviation. The method for target designation in the direction of the guidance system of the controlled object consists in registering measurement information from a strapdown inertial navigation system (SINS), an optoelectronic system (OES), a radio altimeter installed on an aircraft, performing calculations and processing measurement information. At first, a data array is formed, including the latitude and longitude of the aircraft, the azimuth angle of the OES and the elevation angle of the OES, the maximum rotation speed of the OES. The coordinates of the target are fixed (target latitude, target longitude). The height of the target is determined. The difference between the height of the aircraft and the height of the target is calculated. The difference between the position of the target and the position of the aircraft in the north and east coordinates is calculated. A vector is built, originating from the aircraft, aimed at the target. The azimuth and elevation values of the vector originating from the aircraft and aimed at the target are calculated. The difference between the position of the OES line of sight vector and the position of the vector originating from the aircraft, aimed at the target in azimuth and elevation is calculated. The angular velocities of the azimuth and elevation angles are calculated by which it is necessary to rotate the line of sight vector. The angular velocities of the azimuth and elevation angles, by which it is necessary to rotate the line of sight vector, are corrected using the feedback loop for the mismatch of the current and specified coordinates, which is a combined linear-nonlinear filter.

EFFECT: invention simplifies the implementation of the method; increases the accuracy of aiming the line of sight vector to the target by using a feedback loop on the mismatch of the current and specified coordinates, correcting the contour along each of the axes by using a combined linear-nonlinear filter; increases the speed of implementation of the method, since all operations for the implementation of the method are performed directly on the aircraft.

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