RU2277689C1 - Method for guidance of guided missile and guidance system for its realization - Google Patents

Abstract

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

SUBSTANCE: the method consists in the fact that before the missile take-off the program change in time of the value of tolerance U_III for the change of the output signal from the radiation photodetector, depending on the illuminance produced on the photodetector sensitive surface by the useful signal source, is determined in proportion to the range to the guided missile. After the take-off of the guided missile focusing of radiation of the background-target situation is accomplished at a photodetector with a matrix structure of the sensitive surface. At each moment of time of determination of coordinates of the guided missile determined are the current values of the output signal from each cell of the radiation photodetector, the standard value of the output signal from the cell of the radiation photodetector proportional to the dropping radiation of the useful signal source at the current range to the guided missile is computed, the obtained current values of the output signal from the cells are compared with the computer standard value of the signal from the useful signal source, and the layout relative to the central cell of those cells of the radiation photodetector at whose output a signal equal to the standard one or differing from it by a value not exceeding preset tolerance U_III is formed. The guidance system of guided missile has a series-connected optical system, radiation photodetector, coordinate discrimination unit and a command forming unit. Additionally introduced are a series-connected selection unit and a program coefficient unit. The selection unit is connected between the radiation receiver and the coordinate discrimination unit, and the radiation photodetector is made on the basis of the matrix type photodetector.

EFFECT: enhanced accuracy of discrimination of coordinates of the on-board radiation source, enhanced noise immunity of the control system.

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Description

The proposed guided missile guidance method and guidance system for its implementation relate to the development of missile control systems and can be used in anti-tank missile systems (ATGMs).

Closest to the proposed is a method of pointing an anti-tank missile, implemented in the ATGM 9K111 "Bassoon" and taken as a prototype [1. Launcher 9P135. Technical description. Order of the Red Banner of Labor Military Publishing House of the Ministry of Defense of the USSR, Moscow - 1975, pp. 11-13], including the launch of an anti-tank missile with an onboard radiation source, the passage of the light flux from the radiation source through the lens and the optical raster, modulation of the light flux using optical a raster, receiving a modulated light flux from a radiation source by a photodetector with a continuous photosensitive surface, identifying the coordinates of an onboard radiation source, determining the coordinates of an anti-tank missiles and the formation of anti-tank missile command teams.

Closest to the proposed is an anti-tank missile guidance system that implements the known method of anti-tank missile guidance and used in the 9K111 Fagot portable anti-tank missile system [1. Launcher 9P135. Technical description. Order of the Red Banner of Labor Military Publishing House of the Ministry of Defense of the USSR, Moscow - 1975, pp. 11-13]. This guidance system contains a series-connected lens that receives a signal from an onboard radiation source, an optical raster, a radiation photodetector, a photocurrent amplifier, a coordinate extraction unit and a command generation unit, as well as a reference voltage generator connected between the optical raster and the coordinate allocation unit.

A functional diagram of an anti-tank missile guidance system that implements the known method of anti-tank missile guidance is shown in FIG.

The guidance system of an anti-tank missile works as follows. The input for it is the angular deviation of the onboard radiation source of the anti-tank missile from the line of sight. Lens 1 focuses the radiation of the phono-target environment (FCO) with the onboard radiation source on the optical raster 2, which has transparent and opaque sectors located radially and performs plane-parallel movement (scanning), which provides frequency modulation and spatial selection of the light flux of the onboard radiation source. The frequency-modulated light flux is perceived by the photodetector of radiation 3 and converted into the corresponding electrical signals. The frequency-modulated signal from the photodetector enters the amplifier of the photocurrent 4, where it is amplified to the desired value. The output signal from the photocurrent amplifier contains information on the angular deviations of the rocket radiation source from the aiming line, which enters the coordinate allocation unit 5. After converting the signal of the photocurrent amplifier, the coordinate extraction unit generates voltages corresponding to linear deviations of the rocket from the aiming line. The signals from the reference voltage generator are used as the reference voltages during phase detection 7. The voltages proportional to the missile deviation from the aiming line along the course and pitch are output from the output of the coordinate allocation unit to the command generation unit 6, where they are converted into control signals intended for transmission via PLC on the rocket.

Modern conditions for the development of anti-tank systems have set the task of overcoming a number of fundamental technical difficulties inherent in this method of guiding an anti-tank missile and guidance system for its implementation. This primarily relates to the impossibility of ensuring a constant signal-to-noise ratio throughout the flight throughout the guidance system. This is due to the presence of a constant and sufficiently high level of the intrinsic noise of the photodetector under high temperature exposure, as well as a component of the background light flux, while the light flux from the onboard radiation source incident on the entrance pupil of the OS decreases inversely with the square of the distance to the rocket. Due to the continuous reduction of the difference between the useful signal and the background signal, the accuracy and reliability of the selection of the source of the useful signal is significantly reduced, especially in bright sunny days. As a result of this, the process of detecting the coordinates of the rocket worsens, while noise immunity decreases and the sensitivity of the entire control system decreases.

The objective of the invention is to develop such a guidance method for guided missiles and guidance systems for its implementation, which would improve the quality of guidance of the missile without changing the design of the missile itself, to increase the reliability and accuracy of the selection of the source of the useful signal in various phono-target environments throughout the flight time of the guided missile and good noise immunity of the entire control system without its significant complication.

The problem is solved in that in a guided missile guidance method, including launching a guided missile with an on-board source of a useful signal, receiving and focusing on a photodetector a luminous flux of a phono-target environment, extracting coordinates of a source of a useful signal, determining coordinates of a guided missile and generating control commands for transmission to a missile , before the start of the guided missile program set the time variation tolerance value U _W of the output signal change from the photodetector radiation depending on the illumination generated by the source of the useful signal on the sensitive surface of the photodetector in proportion to the distance to the guided missile, after the launch of the guided missile, the radiation of the phono-target environment is focused on the photodetector with the matrix structure of the sensitive surface, and at each instant of time determining the coordinates of the guided missile, determine the current values of the output signal from each cell of the radiation photodetector, calculate the reference value of the output signal from the cell ki of the radiation photodetector proportional to the incident radiation of the source of the useful signal at the current range to the guided missile, compare the obtained current values of the output signal from the cells with the calculated reference value of the signal from the source of the useful signal and determine the location relative to the center of those cells of the radiation detector at the output of which the signal was generated, equal to the reference or different from it by an amount not exceeding the established tolerance U _W.

The problem is also solved by the fact that in the guided missile guidance system containing a series-connected optical system, a radiation photodetector, a coordinate allocation unit and a command generation unit, a series-connected selection unit and a program coefficient block are additionally introduced, the selection unit being connected between the radiation receiver and the unit coordinate extraction, and the radiation photodetector is based on a matrix type photodetector.

Improving the reliability and accuracy of the selection of the source of the useful signal under various phono-target situations throughout the flight time of the guided missile is provided by calculating the threshold level of the useful signal that is most appropriate for the current energy of the onboard radiation source.

A functional diagram of a guided missile guidance system that implements the proposed guided missile guidance method is shown in FIG. 2.

Guided missile guidance system operates as follows. The luminous flux of the FCO with an onboard radiation source, the optical system 1 focuses directly on the photodetector of matrix type 3 radiation, made on the basis of a high-frequency charge-transfer matrix sensor, on the sensitive cells of which the image of the FCO is formed. The block of program coefficients 7, based on the program law of changing the signal at the output of the photodetector, proportional to the current range to the guided missile, calculates the current threshold value of the signal at the output of the photodetector and transmits data to selection block 8, which, on the basis of the received information, starts analyzing the output signals from all cells of the matrix space. The selection block determines the cells, the output signal from which differs from the calculated reference by an amount not exceeding the established tolerance U _W. This tolerance U _W determines the possible attenuation of the radiation of the source of the useful signal in the presence of various interference and atmospheric phenomena, and also provides for fluctuations in the radiation of the source of the useful signal. After this, the cells whose output signal satisfies the selection condition are uniquely determined, and we can say that an image of the onboard source of the useful signal of the guided missile was formed on these cells. After that, the coordinate allocation unit 5 converts data only from cells selected from the entire matrix space that carry information about the angular deviations of the onboard radiation source of the guided missile from the aiming line. Stresses proportional to the deviation of the rocket from the aiming line at the heading and pitch, from the output of the coordinate allocation unit are sent to the command formation unit 6, where they are converted into control signals designed to change the spatial position of the guided missile.

In the proposed guided missile guidance system, the optical system, the coordinate allocation unit and the command generation unit can be performed, as in the prototype. The radiation photodetector can be made on the basis of a high-frequency matrix sensor with charge transfer [2]. The selection block and the block of program coefficients can be made on the basis of signal microprocessors [3] and programmable logic integrated circuits [4].

The proposed guided missile guidance method and guidance system for its implementation in comparison with prototypes allow to achieve:

- the constant excess of the signal from the onboard source of the useful signal of the guided missile over the background signal throughout the flight range of the rocket;

- high accuracy of the coordinates of the onboard radiation source without significant complication of the control equipment;

- increase the noise immunity of the control system as a whole.

Information sources

1. Launcher 9P135. M: Technical description. Order of the Red Banner of Labor Military Publishing House of the Ministry of Defense of the USSR, 1975, pp. 11-13 - prototype.

2. Charge coupled devices. Ed. D.F.Barda, Moscow, 1982

3. User Guide for signal microprocessors ADSP-2100 / Per. from English O.V. Luneva; Ed. A.D. Viktorov; St. Petersburg State Electrotechnical University. - St. Petersburg, 1997 .-- 520 p.

4. V. B. Steshenko. FPGA from ALTERA: Designing signal processing devices. / M .: Dodeka, 2000

Claims (2)

1. A guided missile guidance method, including launching a guided missile with an onboard source of a useful signal, receiving and focusing on the photodetector a luminous flux of a phono-target environment, highlighting the coordinates of a useful signal source, determining the coordinates of a guided missile and generating control commands for transmission to a missile, characterized in that before the start of the guided missile program set the time variation tolerance value U _w of the output signal transition radiation photodetector depending on the OS the area generated by the source of the useful signal in proportion to the distance to the guided missile, after the launch of the guided missile, the radiation of the phono-target environment is focused on the detector with the matrix structure of the sensitive surface, and at each instant of time the coordinates of the guided missile are determined by determining the current values of the output signal from each cell photodetector of radiation, calculate the reference value of the output signal from the cell of the photodetector radiation proportional to the incident radiation of the source of the useful signal at the current range to the guided missile, compare the obtained current values of the output signal from the cells with the calculated reference value of the signal from the source of the useful signal and determine the location relative to the central of those cells of the radiation detector, the output of which formed a signal equal to the reference or differing from it by an amount not exceeding the established tolerance U _w . 2. Guided missile guidance system comprising a series-connected optical system, a radiation photodetector, a coordinate allocation unit and a command generation unit, characterized in that a series-connected selection block and a program coefficient block are additionally introduced into it, the selection block being connected between the radiation receiver and the block coordinate extraction, and the radiation photodetector is based on a matrix type photodetector.

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