RU127889U1 - PASSIVE DOUBLE SPECTRAL Homing head for anti-aircraft guided missiles - Google Patents

Abstract

The proposed utility model relates to the field of anti-aircraft guided missiles with passive homing heads (hereinafter - GOS). The developed passive two-spectral seeker has the following set of essential features:

- a gyrocoordinator having an optical system and modulating rasters of infrared and optical channels mounted on the gyro rotor, channel photodetectors mounted on the inner frame of the gyroscope gimbal, signal amplifiers, channel switching key by the operator;

- site selection target and the formation of the correction signal of the axis of the gyroscope containing

a video signal processing circuit from a target, including a serially connected controlled video divider, a carrier frequency amplifier, a video signal strobe block from a target, a detector, a limiter and an envelope amplifier, a power amplifier, the output of which is connected to a gyro axis position correction coil located on the gyrocoordinator, and also a unit generating attenuation coefficients of the video signal in the controlled divider and envelope limiter as a function of the measured range to the target, connected to their second inputs;

signal conditioning circuit for gating the video signal from the target depending on the phase of rotation of the rotor, bearing of its axis relative to the axis of the rocket, connected through the second key of the operator to the second input of the strobe block of the video signal from the target, and including two corresponding sensors mounted on the housing of the seeker connected to the first and the second inputs of the signal generation block for gating the video signal from the target, depending on the phase of rotation of the rotor and the bearing of its axis relative to the axis of the rocket, as well as the signal generation block type of organized optical interference, connected to the third input of the signal conditioning unit for gating the video signal from the target;

a signal conditioning circuit for gating a video signal from a target, depending on the presence of organized optical interference, made in the form of series-connected amplifier, the input of which is connected to the output of a photodetector of an optical channel, a detector, a signal conditioning unit for gating a video signal from a target, depending on the presence of organized interference, output which through the third key of the operator is connected to the third input of the strobe block of the video signal from the target.

New features in the proposed combination characterizing a passive two-spectral seeker are:

- introduction to the structure of the target selection node and generating a correction signal for the gyroscope axis of the signal conditioning circuit for gating the video signal from the target, depending on the presence of organized optical noise _, made in the form of a series-connected amplifier, the input of which is connected to the output of the photodetector of the optical channel, detector, signal generating unit for gating the video signal from the target depending on the presence of organized optical interference, the output of which is connected to the third input through the third operator key at the gating block of the video signal from the target;

- introduction to the signal conditioning circuit for strobing the video signal depending on the phase of rotation of the rotor and bearing of its axis relative to the axis of the rocket of the signal conditioning unit of the type of organized optical interference, the output of which is connected to the third input of the signal conditioning unit for strobing the video signal of the above chain in turn, connected to the video gating block through a second operator key,

- connecting the second inputs of the controlled divider and the envelope limiter of the video signal processing circuit to the block for generating video attenuation coefficients as a function of the measured range to the target.

The technical result of the proposed utility model is to expand the range of combat use and increase the likelihood of targeting without increasing weight and size and energy characteristics of the seeker.

Currently, the applicant enterprise is working on the industrial implementation of the proposed design of the GOS.

Description

The technical field to which the utility model belongs.

The proposed utility model relates to the field of anti-aircraft guided missiles with passive homing heads (hereinafter - GOS).

The level of technology.

Currently, military conflicts taking place in different parts of the world show that when firing at air targets, especially at short ranges, the most effective anti-aircraft means are guided missiles with passive GOS (fired and forgot).

Such anti-aircraft missile systems are the most mobile (they can be used including in a portable version) and therefore are simpler in design and operation than anti-aircraft systems with active homing heads, which are much more complicated in design and with which all the world's armies have already learned to deal effectively.

Known anti-aircraft missile systems with passive GOS (MANPADS "Stinger", USA, "Mistral-1" France, "Igla-1" of the USSR), in which the infrared range of target radiation was used to control the missile.

The disadvantage of this type of passive GOS was their great dependence on meteorological conditions, because in rain, snow or fog, thermal radiation from the target in the wavelength range used is dissipated and the effectiveness of pointing the missile at the target is significantly impaired.

Known anti-aircraft missile system with a passive GOS (SAM 9M31 short-range Soviet SAM "Strela-1"), in which the missile used optical (photocontrast) range of target radiation (Anti-aircraft missile systems air defense SV "Technique and armament" No. 5-6, 99 g.).

The disadvantages of this type of passive GOS were (as well as the above thermal) their great dependence on meteorological conditions, as well as the complexity of the design due to the need for pre-cooling of the optical channel.

Known anti-aircraft missile systems with a passive guidance system, for example, "Strela-10SV" - the USSR, (Anti-aircraft missile systems air defense SV "Technics and armament" No. 5-6.99) and "93" - Japan, in which to control the missile a two-spectral GOS was used, which uses both infrared and light radiation from a target to generate a control signal for an anti-aircraft missile, which reduces the dependence of the accuracy of guidance of this type of anti-aircraft missile on weather conditions and widens the range of combat use of the missile.

The disadvantage of this type of GOS is the inability to isolate the signal from the target when it sets up organized optical interference.

This domestic passive two-spectral GOS (technical description and operating instructions. MOS Publishing House. 1980) was taken by the authors as a prototype of the proposed one, both closest in technical essence and in technical result when used.

Disclosure of a utility model.

The task that the authors solved when developing the proposed two-spectral passive GOS was to expand the range of combat use and increase the probability of targeting, including under conditions of setting organized optical interference without increasing weight and size and energy characteristics of the GOS.

This problem is solved in the developed passive two-spectral GOS, having the following set of essential features:

- gyrocoordinator

having an optical system and modulating rasters of the infrared and optical channels mounted on the gyro rotor, channel photodetectors mounted on the inner frame of the cardan suspension of the gyroscope, signal amplifiers, an operator switching key;

- site selection target and the formation of the correction signal of the axis of the gyroscope containing

a video signal processing circuit from a target, including a serially connected controlled video divider, a carrier frequency amplifier, a video signal strobe block from a target, a detector, a limiter and an envelope amplifier, a power amplifier, the output of which is connected to a gyro axis position correction coil located on the gyrocoordinator, and also a unit generating attenuation coefficients of the video signal in the controlled divider and envelope limiter as a function of the measured range to the target, connected to their second inputs;

signal conditioning circuit for gating the video signal from the target depending on the phase of rotation of the rotor, bearing of its axis relative to the axis of the rocket, connected through the second key of the operator to the second input of the strobe block of the video signal from the target, and including two corresponding sensors mounted on the housing of the seeker connected to the first and the second inputs of the signal generation block for gating the video signal from the target, depending on the phase of rotation of the rotor and the bearing of its axis relative to the axis of the rocket, as well as the signal generation block type of organized optical interference, connected to the third input of the signal conditioning unit for gating the video signal from the target;

a signal conditioning circuit for gating a video signal from a target, depending on the presence of organized optical interference, made in the form of series-connected amplifier, the input of which is connected to the output of a photodetector of an optical channel, a detector, a signal conditioning unit for gating a video signal from a target, depending on the presence of organized interference, output which through the third key of the operator is connected to the third input of the strobe block of the video signal from the target.

New features in the proposed combination characterizing a passive two-spectral seeker are:

- introduction to the structure of the target selection node and generating a correction signal for the gyroscope axis of the signal conditioning circuit for gating the video signal from the target, depending on the presence of organized optical noise, made in the form of a series-connected amplifier, the input of which is connected to the output of the photodetector of the optical channel, detector, signal generating unit for gating the video signal from the target, depending on the presence of organized optical interference, the output of which is connected to the third input through the third operator key gating the video block from the target;

- introduction to the signal conditioning circuit for strobing the video signal depending on the phase of rotation of the rotor and bearing of its axis relative to the axis of the rocket of the signal conditioning unit of the type of organized optical interference, the output of which is connected to the third input of the signal conditioning unit for strobing the video signal of the above chain, which, in in turn, connected to the video gating block through a second operator key,

- connecting the second inputs of the controlled divider and the envelope limiter of the video signal processing circuit to the block for generating video attenuation coefficients as a function of the measured range to the target.

According to the authors, despite the prominence of using the method of gating the interference signal based on the spectral selection method in the proposed passive two-spectral seeker to use in the active and semi-active homing missile seeker systems in the active and semi-active homing missile systems, this allowed, in addition to expanding the range of combat use of the seeker, to increase the probability of pointing on the target, including in terms of setting organized optical interference, without increasing the weight and size and energy character Istick GOS, which allows us to consider the above new features significant for the given population.

Brief Description of the Drawings

The developed utility model is presented in the accompanying drawings, where,

- figure 1 presents the General scheme of the developed passive GOS;

- in Fig 2. - amplifier circuit (blocks 11, 12, 29);

- figure 3 is a diagram of a channel selector (block 13);

- figure 4 is a diagram of a controlled divider (block 15);

- figure 5 is a diagram of a carrier frequency amplifier (block 16);

- Fig.6 is a block diagram of the strobe of the video signal of the target (block 17);

- Fig.7 is a diagram of an envelope detector (block 18, 30);

- Fig. 8 is a diagram of an envelope limiter (block 19);

- figure 9 is a diagram of the amplifier "envelope" (block 20);

- figure 10 is a diagram of a correction coil (block 23);

- figure 11 is a diagram of a signal generating unit 25 for gating a target video signal depending on the rotation phase of the gyro rotor and its axis bearing, gyro rotor phase rotation sensor circuit (block 26), sensor circuit of the gyro axis bearing relative to the rocket axis (block 27) and a second operator key (block 35) for connecting the circuit 21 and block 28 ;.

- Fig. 12 is a block diagram of a signal generation unit about the type of organized optical interference (block 28);

- in Fig.13 is a block diagram of the signal formation of the strobe of the video signal from the target as a function of the signal of organized optical interference (block 31);

- on Fig - block diagram of the formation of the coefficient of reduction of the video signal in proportion to the distance to the target (block 33).

Implementation of a utility model.

A passive two-spectral seeker contains a gyrocoordinator 1 and a node 2 for selecting a target and generating a correction signal for the gyro axis.

Gyrocoordinator 1 is designed to receive optical signals from the target, interference and background, convert them into electrical signals for processing in node 2, where the target is selected and the correction signal of the gyro axis is generated, to make the rocket approach with the target using the proportional guidance method.

The gyrocoordinator 1 contains a gyroscope 10, on the rotor 3 of which there is an optical system 4 and modulating disks 5 and 6 of the infrared and optical channels, located in the focal plane of the optical system 4, photodetectors 8, 9 channels mounted on the inner frame 7 of the gimbal suspension of the gyroscope 10. amplifiers signals 11, 12, through a channel switching key 13 connected to the target selection node 2 and generating a gyro axis correction signal.

The node 2 for selecting a target and generating a correction signal for the gyroscope axis contains a video signal processing circuit 14 from a target, including a serially connected controlled video splitter 15, a carrier amplifier 16, a video gate signal gating unit 17, a detector 18, a limiter 19, and an envelope amplifier 20, the output of which is connected to the correction coil of the position of the axis of the gyroscope 23, placed on the housing 24 of the GOS, as well as the block 33 of the formation of the attenuation coefficients of the video signal of the controlled divider 15 and the envelope limiter 19 in the function the measured target range, connected to their second inputs.

In addition to the above, the assembly 2 includes a control signal generating circuit 21 for gating the target video signal depending on the phase of rotation of the gyroscope rotor, bearing of its axis relative to the axis of the rocket, including sensors 26 and 27 of the rotation phase of the gyroscope rotor and bearing of its axis relative to the axis of the rocket, installed on the housing 24 GOS and connected to the first and second inputs of the block 25 of the formation of signals for gating the video signal from the target depending on the phase of rotation of the rotor and bearing of its axis relative to the axis of the rocket, and block 28 f generating a signal about the type of organized optical interference, connected to the third input of block 25, the output of which, in turn, through the second key of the operator 35 is connected to the block 17 of the gating video signal.

The structure of the node 2, in addition, includes a control signal generating circuit 22 for gating the target video signal from organized optical interference, connected to the output of the optical channel photodetector 9 and containing a series-connected amplifier 29, an interference envelope detector 30, a control signal generating unit for gating the target video signal from organized optical interference 31 and a third operator key 32 for connecting to the third input of block 17 for strobing the target video signal.

The work of a passive two-spectral seeker is as follows.

Before launching the rocket, the operator must detect the target and aim.

Target detection is carried out using ground equipment, which is part of the anti-aircraft complex. After the target is detected, its coordinates are transmitted automatically to the sight of the ground equipment for launching the rocket, and a mark of the detected target appears on the sighting screen.

The operator deploys the missile launcher onto the target and combines the crosshairs of the sight (missile axis) with the mark of the target and presses the capture button. The launch equipment in semi-automatic mode evaluates the parameters of the target’s movement (range, altitude, speed, angle, etc.) and parses the GOS.

The radiation from the target through the optical system 4 (Fig. 1) is incident on modulating rasters 5 and 6, and then on photodetectors 8 (a photodiode on indium antimonide) and 9 (a silicon photodiode), which convert the radiation modulated by rasters 5, 6 into electrical video signals.

These signals are respectively supplied to the amplifiers 11 and 12, implemented, for example, on the chip DA1 (544UD1), (figure 2).

Next, the signals are fed to the channel selector 13.

Before launching the rocket, the operator must connect either the infrared channel if the work is done at night, or the optical channel if the work is done in the daytime, using the channel switch 13.

The channel selector 13 is made according to the scheme, for example, shown in figure 3, which is implemented on the chips DA1 (590KN1) and DA2 (544UD1). Chip DA1 under the influence of a signal from the operator connects to the input of the operational amplifier DA2, either the output of the amplifier 11, or the output of the amplifier 12.

Next, the video signal from the output of block 13 is fed to a controlled divider 15, in which the attenuation of the video signal is provided.

Block 15 of the circuit 14 can be implemented, for example, (Fig. 4), on the microcircuits D1 (1533IR1), D2 (571PA1) and DA3 (544UD1). The register D1 stores the attenuation coefficient of the signal at a given time.

The divider D2 is made on the basis of a digital-to-analog converter, for attenuating the input signal by a calculated number of times and a matching amplifier - DA3, the output of which has a weakened video signal.

The attenuation coefficient of the video signal is set from block 33 depending on the measured range of the missile.

From the output of block 15, the video signal is supplied to a carrier frequency amplifier 16, assembled, for example, according to the circuit shown in FIG. 5.

Block 16 is implemented on the DA1 chip, the input of which is connected to a band-pass filter (R1, R2, R3, C1, C2. C3). The amplifier selectively amplifies the video signal at carrier purity and attenuates it at other frequencies.

Then the video signal is fed to the input of the strobe block of the video signal of the target 17, (Fig.6), implemented, for example, on an analog key DA1 (590KH1) and an operational amplifier DA2 (544UD1).

Under the influence of control signals from blocks 25 or 31, assembled on the logic elements D1 (1533LA3) and D2 (1533LN1), the DA1 key is opened, and the video signal, gated from the organized optical noise signals, passes through the operational amplifier DA2 to the input of the envelope detector 18, realized for example, according to the scheme in Fig.7.

At the envelope detector 18, the low-frequency component of the video signal from the target is extracted, which is fed to the input of block 19, where the envelope is limited in amplitude. An example of the implementation of this block is shown in Fig. 8.

The target video signal restriction coefficient is set by block 33 and stored on register D1 (15533IP1). The code set on the register sets the corresponding voltage, which is subtracted from the video signal on the operational amplifier DA4.

Then, the “limited” envelope of the video signal is amplified by the envelope amplifier 20, implemented, for example, according to the scheme in FIG. 9.

The output of the envelope amplifier 20 is connected to a correction coil 23 located in the gyrocoordinator 1.

Under the influence of the electromagnetic field generated by the coil 23, the rotor 3 of the gyroscope 10 deviates from the axis of the rocket depending on the magnitude of the amplitude and phase of the correction current that occurs in the correction coil 23.

The signal generation for gating the target video signal depending on the phase of rotation of the rotor and the bearing of its axis relative to the axis of the rocket is performed by block 25, implemented, for example, on the basis of the signal processor DD1 (PIC16F876A) and three comparators DA1, DA2 and DA3 (521CA3), (Fig. eleven.).

The sensor 26 of the rotation phase of the rotor 3 of the gyroscope is connected by its windings to DD1 through comparators DA1 and DA2.

The sensor 27 of the bearing of the position of the axis of the gyroscope relative to the axis of the rocket with its winding through the comparator DA3 is connected to DD1. The signal processor DD1, using the program recorded in it, calculates the parameters of the gates depending on the type of interference observed, the signal of which is generated by block 28, the circuit of which is shown in Fig. 12.

The second key operator 35 is implemented, for example, on the trigger D3.

The formation of a control signal for gating the target video signal depending on the presence of the optical noise signal is carried out by prohibiting the passage of the optical noise signal to the output.

Gating is performed when the operator selects the infrared channel as the working channel.

In this case, the signal of the optical channel traveling at the carrier frequency is amplified by a block 29, implemented, for example, on the basis of the chip DA1 (544UD1) of FIG. 2, then it is processed by the envelope detector 30, (FIG. 7), and then in block 31 (FIG. .13), a control signal is generated for strobing the target signal depending on the presence of an interference signal.

The block circuit 31 can be implemented, for example, on the comparator DA1 (chip 521CA3), and the key 32 - on the trigger D3 (chip 1533TM3).

Block 33 of the formation of the coefficient of reduction of the video signal in proportion to the distance to the target is also implemented on the signal processor PIC16F876A (DD), Fig.14.

DD1 is connected to the flight time counter D1 (1533IE7), launched by the operator by the “start” command.

Next, we consider four options for the operation of the GOS, depending on the start-up conditions and the interference environment.

1 option.

If the launch of the rocket occurs during the day and there is no interference, the operator prior to launching the rocket with a switch 13 connects the amplifier 11 of the optical channel to the video signal processing circuit from the target 14 and simultaneously sets the keys 32 and 35 to the “off” position.

In addition, before launching the rocket into the correction coil 23, located on the housing 24 of the gyrocoordinator 1, a signal is supplied from the external winding of the arrestor.

The current flowing through the correction coil 23 creates an electromagnetic field interacting with the rotor 3 of the gyroscope, as a result of which the axis of the gyroscope is set along the axis of the rocket - this is the arrestor mode. The operator combines the missile axis with the direction to the target and issues a “capture” command to the ground preparation for launch preparation.

The optical signal from the target by the lens 4 is focused on a rotating modulating raster 5 and enters the photodetector 9.

Photodetector 9, the optical signal from the visible radiation spectrum is converted into an electrical video signal, which without changes passes through block 15 (divider) and amplified in block 16.

In block 17, the video signal passes unchanged, since the keys 35 and 32 are disabled. Then, the envelope of the video signal is extracted at the detector 18, which is limited in block 19 and amplified in block 20.

Next, the envelope signal of the limited video signal is supplied to the correction coil 23.

The current flowing through the correction coil 23 creates an electromagnetic field that interacts with the rotor 3, as a result of which the gyroscope rotates in the corresponding direction by a value proportional to the amplitude of the correction current. The modulating raster 5 is installed relative to the poles of the rotor 3 so that the direction of rotation of the axis of the gyroscope corresponds to the direction to the target.

Ground-based equipment for launch preparation informs the operator with a sound signal that the optical signal from the target is received by the GOS.

Next, the rocket is launched by pressing the "start" button in block 33.

Block 33 programmatically, in proportion to the flight time of the rocket, changes the value of the attenuation coefficient of the video signal in block 15 and increases the threshold for limiting the envelope of the video signal in block 19.

Option 2.

If the launch of the rocket occurs at night and there is no interference, the operator prior to launching the rocket with a switch 13 connects the infrared channel amplifier 12 to the video signal processing circuit 14 (blocks 15-23) and simultaneously sets the keys 32 and 35 to the “off” position. As before, the operator in the "arresting" mode combines the missile axis with the direction to the target and issues a "capture" command to the ground preparation for launch preparation.

The optical signal from the target by the lens 4 is focused on a rotating modulating raster 6 and enters the photodetector 8, where the optical signal from the infrared spectrum is converted into an electric video signal. Next, the operation of the video signal processing circuit 14 occurs similarly to the above-described day mode.

3 option.

If the launch of the rocket occurs during the day and there is organized optical interference, the operator prior to launching the rocket with a switch 13 connects the optical channel amplifier 11 to the video signal processing chain 14 and sets the key 32 to the “off” position, and the key 35 to the “on” position

In addition, the operator in block 28 sets the type of interference, one of three: “interference at the bottom”, “interference at the back”, “interference at the top” and, as before, in the “arresting” mode combines the missile axis with the direction to the target and issues the command “ capture "in the ground preparation equipment launch.

The optical signal from the target by the lens 4 is focused on a rotating modulating raster 5 and gets on the photodetector 9. Next, by the photodetector 9, the optical signal from the visible radiation spectrum is converted into an electrical video signal, which passes through block 15 (divider) without changes, and amplified in block 16.

In block 17, the target video signal is gated from the organized optical interference signal using the control signal generated in block 25, based on the rotation phase of the gyro rotor 3 (block 26) and the bearing of the gyro axis relative to the rocket axis (block 27).

Then, the envelope of the video signal from the target, which is limited in block 19 and amplified in block 20, is extracted at the detector 18.

The envelope of the limited video signal is supplied to a power amplifier 21 to which a correction coil 23 is connected.

The current flowing through the correction coil 23 creates an electromagnetic field that interacts with the rotor 3, as a result of which the gyroscope rotates in the corresponding direction by a value proportional to the amplitude of the correction current. The modulating raster 6 is installed relative to the poles of the rotor 3 so that the direction of rotation of the axis of the gyroscope corresponds to the direction to the target.

Ground-based equipment for launch preparation informs the operator with a sound signal that the optical signal from the target is received by the GOS.

Next, the rocket is launched.

Block 33 programmatically, in proportion to the flight time of the rocket, changes the value of the attenuation coefficient of the video signal in block 15 and increases the threshold for limiting the envelope of the video signal in block 19.

4 option.

If the launch of the rocket occurs at night and there is organized optical interference, the operator prior to launching the rocket with a switch 13 connects the infrared channel amplifier 12 to the chain of video signal processing units 15-23 and simultaneously sets the key 32 to the on position and the key 35 to the off position . As before, the operator in the "arresting" mode combines the missile axis with the direction to the target and issues a "capture" command to the ground preparation for launch preparation.

The optical signal from the target by the lens 4 is focused on a rotating modulating raster 6 and enters the photodetector 8, where the optical signal from the infrared spectrum is converted into an electric video signal.

Then, the video signal passes without changes through block 15 (divider), and is amplified in block 16. In block 17, the video signal is gated from the target using the control signal generated in circuit 22 (blocks 29-31), which in this case is an interference signal. After that, the work is performed similarly to the mode described in paragraph 3.

Next, the envelope of the limited video signal is supplied to the correction coil 23. The current flowing through it creates an electromagnetic field that interacts with the rotor 3, as a result of which the gyroscope rotates in the corresponding direction by an amount proportional to the amplitude of the correction current. The modulating raster 6 is installed relative to the poles of the rotor 3 so that the direction of rotation of the axis of the gyroscope corresponds to the direction to the target.

Ground-based equipment for launch preparation informs the operator with a sound signal that the optical signal from the target is received by the GOS.

Next, the rocket is launched. Block 33 programmatically, in proportion to the flight time of the rocket, changes the value of the attenuation coefficient of the video signal in block 15 and increases the threshold for limiting the envelope of the video signal in block 19.

In the manufacture of the developed GOS, technologies and components known in the industry can be used.

Currently, the applicant enterprise is working on the industrial implementation of the proposed design of the GOS.

Claims (1)

A passive dual-spectral homing head for anti-aircraft guided missiles containing a gyrocoordinator having an optical system and modulating rasters of infrared and photo-contrast channels mounted on the gyro rotor, channel photodetectors mounted on the inner frame of the gyroscope gimbal, signal amplifiers, channel switching key by the operator, target selection unit and generating a gyro axis correction signal, including a video signal processing circuit from a target, comprising serially connected adjustable video divider, carrier amplifier, gating block of the video signal from the target, detector, limiter and envelope amplifier, the output of which is connected to the gyro axis position correction coil located on the gyrocoordinator, a signal generation circuit for gating the video signal from the target depending on the rotation phase of the gyro rotor and a bearing of its axis relative to the axis of the rocket, connected to the second input of the strobe block of the video signal from the target and including phase rotation sensors of the gyro rotor and pele nga of its axis relative to the axis of the rocket, mounted on the homing body, and connected to the first and second inputs of the signal conditioning unit for gating the video signal from the target of the given circuit, characterized in that a formation circuit is introduced into the target selection unit and generating the gyro axis correction signal signal for gating the video signal from the target, depending on the presence of organized interference, made in the form of series-connected amplifier, the input of which is connected to the output of the photodetector of the optical channel, a torus, a signal conditioning unit for gating the video signal from the target depending on the presence of organized interference, the output of which through the second key of the operator is connected to the third input of the video gating unit from the target, while the third input of the signal conditioning unit for gating the video signal depending on the phase of rotation of the rotor and the bearing of its axis relative to the axis of the rocket is connected to the signal generation unit about the type of organized interference, and its output is connected to the gate block of the video signal from the target through the third h operator, moreover, the second control input divider and the envelope limiter video signal processing circuit of the target block are connected to a video signal of the attenuation coefficient in the measurement range to the target function.

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