RU2368857C1 - Method for functioning of information-computing system of rocket and device for its realisation - Google Patents

Abstract

FIELD: weapons and ammunition.

SUBSTANCE: group of inventions is related to the field of aviation controlled rockets. According to method for functioning of information-computing system of rocket, they perform narrow-band beam scanning of electromagnet oscillations in sector specified relative to rocket axis, then frequency bands that correspond to frequencies of air target power plant vibrations are separated from spectrum reflected from extended target of signal. Maximum value of vibration amplitude is defined in specified band of frequencies of reflected signal spectrum from extended target, values of current and maximum amplitude of vibrations are compared in each angular position of antenna with further scanning of extended air target, angular position is defined for power plant of air target at the moment of equality of current and maximum value of reflected signal vibration amplitude. Rocket is re-aimed at power plant of air extended target, radiation and reception of electromagnet vibrations is carried out by means of narrow beam scanning in specified sector relative to rocket axis as rocket approaches the second specified distance, frequency bands that correspond to frequencies of target structure elements vibrations are separated from spectrum of signal reflected from target, values of reflected signal maximum amplitude are defined in this frequency band, radiation and reception of electromagnet oscillations is fixed in direction specified relative to axis of rocket, target structure element having maximum vibration amplitude is recognised, and signal is generated for explosion of rocket warhead during combination of fixed beam of electromagnet vibrations with this element of structure. Device is developed for method realisation.

EFFECT: higher efficiency of war using of the rocket.

8 cl, 3 dwg

Description

  The invention relates to aircraft guided missiles and can be used to redirect a missile to a target power plant in the near section of a missile approach path with an extended target and to information support the functioning of combat equipment of an aircraft guided missile.

A known method of functioning of an information-computer system (IVS) of a rocket, including preparing the rocket on board the carrier aircraft for operation, measuring the parameters of the target’s motion and the rocket’s own motion, forming an estimate of the necessary parameters of the relative motion of the target and the absolute motion of the rocket, choosing the method of pointing the rocket at the target best according to any criterion for the given conditions of use, calculation for the selected method of the mismatch parameters characterizing the degree of discrepancy parameters of the rocket’s movement to their required values, generating a training and control signal for a radio fuse, emitting and receiving electromagnetic oscillations by scanning with a narrow beam in a given sector relative to the axis of the rocket when the rocket approaches the target at a distance when it becomes extended, highlighting the reflected from the spectrum the signal of the frequency band corresponding to the frequencies of the oscillation of the structural elements of the target, the definition in this frequency band of the magnitude of the maximum amplitude of the reflected a signal, fixing radiation and receiving electromagnetic waves in a direction specified with respect to the axis of the rocket, recognizing a target structural element having a maximum vibration amplitude, generating a signal to detonate the rocket’s warhead while combining a fixed beam of electromagnetic waves with this structural element; preparation of the rocket for work on board the carrier aircraft is carried out by supplying voltage from the fighter’s equipment, tuning the synchronization receivers and the reflected signal to the target’s illumination frequency, testing the performance of the entire rocket equipment, determining the readiness of the rocket information and computing system for operation using control signals received in fighter equipment for feedback circuits, preparation of meters and a calculator for tracking a target selected for destruction by target commands s; preparation of meters and calculators for tracking the target selected for destruction by target designation commands is carried out by turning the antenna of the homing head in the direction of the target, or at an anticipated point where the target will be at the moment of taking it for auto tracking, execution of target designation commands in range and speed rapprochement; range targeting commands are formed depending on the guidance method and the target illumination signal, while if a continuous target illumination signal is used in the homing radar, then a target designation command is formed according to the approach speed, according to which only the target radio signals are selected, the approach speed with which corresponds to the target designation speed, if a pulsed target illumination signal is used in the homing radar, then the command range indication, in accordance with which the reflected signal receiver will be unlocked only for the time of arrival of signals reflected from the target, which is far from the target aircraft at the target range, with a quasi-continuous target illumination signal, target designation commands both in range and speed are generated, target designation commands for range, approach speed and angular speeds of the line of sight are given as initial conditions to calculators that extrapolate the parameters of the relative motion of the rocket and the target in auto the multimode of operation of the rocket information-computing system, preceding the capture of the target on the trajectory, and in the case of exposure to radio interference; when deciding whether the reflected signal belongs to the intercepted target, the radar homing meters switch to its automatic tracking according to the Doppler frequency performed by the auto-selector and in the direction carried out by the goniometer, and the homing radar is put into homing mode (Efanov V.V., Muzhichek S.M., RF patent for invention No. 2225306, class B64D 7/00, F41G 3/22, F41G 7/22, F42B 15/01, dated May 27, 2008).

A device for the operation of a rocket information-computing system is known, comprising a first antenna and a synchronization signal receiver connected in series, a second antenna and a reflected signal receiver, a third antenna and an information processing unit, an information processing module, a mismatch parameter calculator, an autonomous sensor system, a power amplifier and a drive antennas, and the information processing module consists of a device for searching, detecting, selecting and analyzing signals, a channel for estimating range and the proximity of the control channel of the second antenna, the output of the synchronization receiver is connected to the second input of the reflected signal receiver, the output of which is connected to the first input of the information processing module, the second, third, fourth, fifth, sixth, seventh inputs of which are respectively connected to the first output of the synchronization signal receiver , the first and second output of the system of autonomous sensors, with the output of the training and target designation commands from the fighter equipment, the output of which is simultaneously connected to the third input of the calculator mismatch parameters, with the output of the autonomous system calculator, the first output of the power amplifier and the antenna drive, the second output of which is mechanically connected to the reflected signal antenna, the first, second, third and fourth outputs of the information processing module are connected respectively to the input of the control and feedback signals of the fighter’s equipment, the first and second input of the mismatch parameter calculator, the input of the power amplifier and the antenna drive, the second output of the information processing module, in addition, is connected to the input m information processing unit, the second output of which is the output of the command to undermine the warhead of the rocket, the information processing unit consists of a transceiver unit, a scanning device, a digital-to-analog converter, a counter, a pulse generator, the first and second elements And, the first trigger, the first threshold device, the element AND NOT, the first signal generator, differentiating circuit, filter, second threshold devices, second triggers, first keys, summing device, second key, third threshold device properties of the second signal generator, the second input of the information processing module connected to the first input of the first threshold device, the second input of which is connected to the first signal generator, and the output of the first threshold device, through the AND-NOT element, is connected simultaneously with the input of the differentiating circuit and the first input the first element And, the second input of which is connected to the second output of the trigger, and the third input is connected to the output of the pulse generator, the output of the first element And is connected to the second input of the counter, the first input of which connected to the first output of the trigger, and the group of outputs of the counter is connected to the group of inputs of the digital-to-analog converter, the output of which is connected to the first input of the scanning device, the second input / output of which is connected to the third antenna, and the third input / output is connected to the first input / output of the transceiver unit, the second output of which is connected to the input of the filter, the output of which is connected to the first inputs of the second threshold devices, the second inputs of which are connected to the first outputs of the second signal generator, and the outputs to the first the strokes of the second triggers, the second inputs of which are connected to the output of the differentiating circuit, the output of which is also connected to the third input of the counter and the second input of the first trigger, the outputs of the second triggers are connected to the first inputs of the first keys, the second outputs of which are connected to the second outputs of the second signal generator, and the outputs the first keys, through an adder, are connected to the first input of the second key, the second input of which is connected to the first output of the trigger, and the output to the first input of the third threshold device, the second the stroke of which is connected to the output of the filter, the last bit of the counter is connected to the first input of the second element And, the first input of which is connected to the output of the summing device, and the output to the first input of the first trigger, the second input, the output of the scanning device and the output of the third threshold device are respectively the first the input / output and the second output of the information processing unit (Efanov V.V., Muzhichek S.M., RF patent for the invention No. 225306, cl. B64D 7/00, F41G 3/22, F41G 7/22, F42B 15/01, dated May 27, 2008).

The disadvantage of the data of the method and device is the insufficient effectiveness of the combat use of an aircraft guided missile due to the lack of a regime of re-targeting the missile at the power plant of the target in the near section of the trajectory of approach of the missile with the target.

An object of the invention is to increase the effectiveness of the combat use of the rocket by introducing a regime of re-targeting the rocket at the power plant of the air target in the near section of the trajectory of approach of the rocket with the target.

The solution to the technical problem is achieved by the fact that in the method of functioning of an information-computer system (IVS), which includes preparing a rocket on board a carrier aircraft for operation, measuring the parameters of the target’s motion and the rocket’s own motion, forming an estimate of the necessary parameters of the relative motion of the target and the absolute motion of the rocket, the choice of the method of guiding the missile at the target, the best by any criterion for the given conditions of use, the calculation for the selected method of the mismatch parameters characterizing the degree of discrepancy between the actual parameters of the rocket’s movement and their required values, the formation of a preparation and control signal for a radio fuse, the emission and reception of electromagnetic waves by scanning with a narrow beam in a given sector relative to the axis of the rocket when the rocket approaches the target at a distance when it becomes extended, highlighted from the spectrum reflected from the target signal of the frequency band corresponding to the frequencies of the structural elements of the extended target, often defined in this band t the magnitude of the maximum amplitude of the reflected signal, fixing radiation and receiving electromagnetic waves in a direction specified relative to the axis of the rocket, recognizing a target structural element having a maximum vibration amplitude, generating a signal to detonate the warhead of the rocket when combining a fixed beam of electromagnetic waves with this structural element, additionally, carry out repeated narrow-beam scanning with a beam of electromagnetic waves in a given sector relative to the axis of the rocket, you dividing from the spectrum of the signal reflected from the target a frequency band corresponding to the vibration frequencies of the power plant of the air target, determining the maximum value of the vibration amplitude in a given frequency band of the spectrum of the reflected signal from the extended target based on its scanning, comparing the values of the current and maximum vibration amplitude in each angular position antennas during subsequent scanning of an extended air target, determine the angular position of the power plant of the air target at the moment of equality of the current and the maximum value of the amplitude of vibration of the reflected signal, carry out the re-targeting of the rocket to the power plant of an air extended target.

In addition, the preparation of the rocket for work on board the carrier aircraft is carried out by supplying voltage from the fighter’s equipment, tuning the synchronization receivers and the reflected signal to the target’s illumination frequency, testing the operability of the entire rocket equipment, determining the readiness of the rocket’s information and computer system for operation using control signals entering the fighter’s equipment via feedback circuits, preparing meters and a computer for tracking the target selected for destruction by commands target designation.

In addition, the preparation of meters and a calculator for tracking a target selected for destruction by target designation commands is carried out by turning the antenna of the homing head in the direction of the target, or at an anticipated point where the target will be at the moment of taking it for auto tracking, execution of target designation commands range and speed of approach.

In addition, range targeting commands are formed depending on the targeting method and target illumination signal used, and if a continuous target illumination signal is used in the homing radar, then a target designation command is formed according to the approach speed, according to which only the target radio signals are selected , the approach speed with which corresponds to the target designation speed; if a target illumination pulse signal is used in the homing radar, then the target designation command is sent to the processing module according to which the reflected signal receiver will be unlocked only for the time of arrival of signals reflected from the target, which is away from the carrier aircraft at the target designation range; with a quasi-continuous target illumination signal, target designation commands both in range and speed are generated, while target designation teams in range, approach speed, and angular velocities of the line of sight are fed as initial conditions to calculators that extrapolate the relative motion of the rocket and the target in autonomous mode of information - the computing system of the rocket, preceding the capture of the target on the trajectory, and in the case of exposure to radio interference.

In addition, when deciding whether the reflected signal belongs to the intercepted target, the radar homing meters switch to its automatic tracking according to the Doppler frequency performed by the auto-selector and in the direction carried out by the goniometer, and the homing radar is put into homing mode.

The proposed method is implemented in a device for operating a rocket information and computing system, comprising a first antenna and a synchronization signal receiver, a second antenna and a reflected signal receiver, a third antenna and an information processing unit, an information processing module, an error parameter calculator, an autonomous sensor system, an amplifier power and antenna drive, and the information processing module consists of a device for searching, detecting, selecting and analyzing signals, the estimation range and approach speed, the second antenna control channel, the second output of the synchronization receiver is connected to the second input of the reflected signal receiver, the output of which is connected to the first input of the information processing module, the second, third, fourth, fifth, sixth, seventh inputs of which are respectively connected to the first output of the synchronization signal receiver, the first and second output of the system of autonomous sensors, with the output of the training and target designation commands from the fighter equipment, the output of which is simultaneously connected connected with the third input of the mismatch parameter calculator, with the output of the autonomous system calculator, the first output of the power amplifier and the antenna drive, the second output of which is mechanically connected to the reflected signal antenna, the first, second, third, and fourth outputs of the information processing module are connected respectively to the input of the control signals and feedback of fighter equipment, the first and second input of the mismatch parameters calculator, the input of the power amplifier and the antenna drive, the second output of the information processing module The station, in addition, is connected to the input of the information processing unit, the second output of which is the output of the command to undermine the warhead of the rocket, the fourth antenna and the unit for determining the angular coordinates of the power plant of the air target, a key, an AND-NOT element, an OR element, are additionally introduced the second output of the information processing module is connected to the input of the unit for determining the angular coordinates of the power plant of the air target, the second output of which is connected simultaneously with the input of the AND-NOT element and with the second electronic input ment OR having a first input connected to the output switch, the first and second inputs of which are connected respectively with the fourth outlet information processing unit and the output of AND-NO.

In addition, the information processing unit consists of a transceiver unit, a scanning device, a digital-to-analog converter, a counter, a pulse generator, a first and second AND element, a first trigger, a first threshold device, an NAND element, a first signal generator, a differentiating circuit, a filter, and a second threshold devices, second triggers, first keys, summing device, second key, third threshold device, second signal generator, and the second input of the information processing module is connected to the first input of the first threshold device, the second input of which is connected to the first signal generator, and the output of the first threshold device, through the AND-NOT element, is connected simultaneously with the input of the differentiating circuit and the first input of the first AND element, the second input of which is connected to the second trigger output, and the third input is connected to the output of the pulse generator, the output of the first element And is connected to the second input of the counter, the first input of which is connected to the first output of the trigger, and the group of outputs of the counter is connected to the group of digital inputs an analog converter, the output of which is connected to the first input of the scanning device, the second input / output of which is connected to the third antenna, and the third input / output is connected to the first input / output of the transceiver unit, the second output of which is connected to the input of the filter, the output of which is connected to the first inputs second threshold devices, the second inputs of which are connected to the first outputs of the second signal setter, and the outputs - to the first inputs of the second triggers, the second inputs of which are connected to the output of the differentiating circuit, the output to It is also connected to the third input of the counter and the second input of the first trigger, the outputs of the second triggers are connected to the first inputs of the first keys, the second outputs of which are connected to the second outputs of the second signal generator, and the outputs of the first keys are connected to the first input of the second key, the second input which is connected to the first output of the trigger, and the output to the first input of the third threshold device, the second input of which is connected to the output of the filter, the last bit of the counter is connected to the first input of the second second AND gate having a first input connected to the output of the summing device, and an output - to the first input of the first flip-flop, a second input, the output of the scanning device and the output of the third threshold devices are respectively first input / output and the second output information processing unit.

In addition, the unit for determining the angular coordinates of the power plant of the air target consists of a transceiver unit, a scanning device, a digital-to-analog converter, a counter, a pulse generator, the first and second, n third elements And, the first and n second triggers, the first, n second, third threshold devices, an NAND element, a first and second signal generator, a differentiating circuit, a filter, n first and second keys, an adder, a delay line, a first and second OR element, while the input of the determination unit the angular coordinates of the design element of the aerial target is the first input of the first threshold device, the second input of which is connected to the output of the first signal generator, and the output of the threshold device, through the AND-NOT element, is connected simultaneously with the input of the differentiating circuit and the first input of the first AND element, the second input of which connected to the second output of the first trigger, and the third input connected to the output of the pulse generator, the output of the first element And connected to the first input of the counter, the group of outputs of which are connected to the group the inputs of the digital-analog converter, the output of which is connected to the first input of the scanning device, the second input / output of which is connected to the fourth antenna, and the third input / output is connected to the first input / output of the transceiver unit, the second output of which is connected to the input of the filter, the output of which is connected with the first inputs of n second threshold devices, the second inputs of which are connected to the first outputs of the second signal generator, and the outputs are with the first inputs of n second triggers, the second inputs of which are connected to the differential output an output circuit, the output of which is also connected to the second input of the counter and, through the second input of the first OR element, to the second input of the first trigger, the outputs of the n second triggers are connected to the first inputs of the first keys, the second inputs of which are connected to the second outputs of the second signal sources, and the outputs, through the summing device, are connected to the first input of the second key, the second input of which is connected to the first output of the first trigger, and the output to the second input of the third threshold device, the first input of which is connected to the output liter, the last bit of the counter output is connected to the first input of the second AND element, the second input of which is connected to the output of the summing device, and the output is connected simultaneously with the first input of the first trigger and the input of the delay line, the output of which is connected to the first input of the first OR element, in addition, the group of outputs of the counter is connected to the first inputs of the n third AND elements, the second inputs of which are connected to the output of the third threshold device, and the outputs to the inputs of the second OR element, the second input / output of the scanning device and the output of the second OR element is, respectively, the first input-output and the second output of the unit for determining the angular coordinates of the power plant of the air target.

New features that have significant differences in the method is the following set of actions.

1. Carry out re-narrow beam scanning with a beam of electromagnetic waves in a given sector relative to the axis of the rocket.

2. Select from the spectrum of the signal reflected from the target a frequency band corresponding to the vibration frequencies of the power plant of the air target.

3. Determine the maximum value of the amplitude of the vibration in a given frequency band of the spectrum of the reflected signal from the extended target based on its scan.

4. Compare the values of the current and maximum amplitude of vibration in each angular position of the antenna during subsequent scanning of an extended air target.

5. Determine the angular position of the power plant of the air target at the moment of equality of the current and maximum values of the amplitude of vibration of the reflected signal.

6. Carry out the re-targeting of the rocket to the power plant of an air extended target.

The essential distinguishing elements of the device are the fourth antenna in series and the unit for determining the angular coordinates of the power plant of the air target, the key, the AND element, the OR element, and the communication between known and new elements.

Figure 1 shows the structural diagram of the information and computing system of the rocket, figure 2 is the same, the information processing unit, figure 3 is the same, the unit determining the angular coordinates of the power plant of the air target.

A device for operating a rocket information and computing system comprises a first 1 antenna and a synchronization signal receiver 2 connected in series, a second 3 antenna and a reflected signal receiver 4, a third 5 antenna and an information processing unit 6, a fourth antenna 7 and an angular coordinate determination unit 8 of the airborne power plant goals, information processing module 9 and mismatch parameters calculator 10, as well as a system of autonomous sensors 11, power amplifier 12 and antenna drive, key 13, AND-NOT element 14, OR element 15 The information processing module 9 consists of a device 16 for searching, detecting, selecting and analyzing signals, a channel 17 for estimating the range and speed of approach, a channel 18 for controlling the second antenna. The second output of the synchronization receiver 3 is connected to the second input of the reflected signal receiver 4, the output of the reflected signal receiver 4 is connected to the first input of the information processing unit 9, the second, third, fourth, fifth, sixth, seventh inputs of which are respectively connected to the first output of the receiver 2 synchronization signals, the first and second output of the system of 11 autonomous sensors, with the output of the training and target designation commands from the fighter equipment, the output of which is simultaneously connected to the third input of the 10 param mismatch, with the output of the calculator of the autonomous system, the first output of the power amplifier 12 and the antenna drive, the second output of which is mechanically connected to the second antenna 3 of the reflected signal. The first, second, third and fourth outputs of the information processing module 9 are connected respectively to the input of the control and feedback signals of the fighter equipment, the first and second input of the mismatch parameters calculator 10, with the first input of the key 13, the second input of which is connected to the output of the AND-NOT 14 element the input of which is connected to the second output of the unit 8 for determining the angular coordinates of the power plant of the air target, the output of which is also simultaneously connected to the second input of the OR element 15, the first input of which is connected to the output of the yucha 13, the output of the OR element 15 is connected to the input of the power amplifier 12 and the antenna drive.

The information processing unit 6 consists of a transmitting and receiving unit 19, a scanning device 20, a digital-to-analog converter 21, a counter 22, a pulse generator 23, the first 24 and second 25 And elements, the first 26 and n second 27 triggers, the first 28, n second 29, the third 30 threshold devices, AND-NOT element 31, first 32 and second 33 signal adjusters, differentiating circuits 34, filter 35, n of the first 36 and second 37 keys, summing device 38. In this case, the input of information processing unit 6 is the first input of the first 28 threshold device, second input to it is connected to the output of the first 32 signal generator, and the output of the threshold device 28, through the AND-31 element, is connected simultaneously with the input of the differentiating circuit 34 and the first input of the first 24 AND elements, the second input of which is connected to the second output of the first 26 trigger, and the third the input is connected to the output of the pulse generator 23, the output of the first 20 element And is connected to the second input of the counter 22, the first input of which is connected to the first output of the first 26 trigger, and the group of outputs is connected to the group of inputs of the digital-to-analog converter 21, you One of which is connected to the first input of the scanning device 20, the second input / output of which is connected to the third 12 antenna, and the third input / output is connected to the first input / output of the transceiver unit 19, the second output of which is connected to the input of the filter 35, the output of which is connected with the first inputs of n second 29 threshold devices, the second inputs of which are connected to the first outputs of the second 33 signal picker, and the outputs are with the first inputs of the second 27 triggers, the second inputs of which are connected to the output of the differentiating circuit 34, the output of which is connected It is also with the third input of counter 22 and the second input of the first 26 trigger. The outputs n of the second 27 triggers are connected to the first inputs n of the first 36 keys, the second inputs of which are connected to the second outputs of the second 33 signal generator, and the outputs, through the adder 38, are connected to the first input of the second 37 key, the second input of which is connected to the first output of the first 26 trigger, and the output is with the first input of the third 30 threshold device, the second input of which is connected to the output of the filter 35, the output of the last discharge of the counter 22 is connected to the first input of the second 25 element And, the second input of which is connected to the output of the adder 38, and the output is with the first input of the first 26 trigger, the second output-input of the scanning device 20, the output of the third 30 threshold devices are respectively the first input-output and second output of the information processing unit 6.

Block 8 for determining the angular coordinates of the design element of an air target consists of a transceiver unit 39, a scanning device 40, a digital-to-analog converter 41, a counter 42, a pulse generator 43, a first 44 and a second 45, n third 46 AND elements, the first 47 and n second 48 flip-flops, first 49, n second 50, third 51 threshold devices, AND-NOT element 52, first 53 and second 54 signal adjusters, differentiating circuit 55, filter 56, n first 57 and second 58 keys, summing device 59, delay line 60 , first 61 and second 62 elements OR. The input of the unit 8 for determining the angular coordinates of the power plant of the air target is the first input of the first 49 threshold device, the second input of which is connected to the output of the first 53 signal generator, and the output of the threshold device 28, through the AND-NOT element 52, is connected simultaneously with the input of the differentiating circuit 55 and the first input of the first 44 And element, the second input of which is connected to the second output of the first 47 trigger, and the third input is connected to the output of the pulse generator 43, the output of the first 44 And element is connected to the first input counter 42, the group of outputs of which is connected to the group of inputs of the digital-to-analog converter 41, the output of which is connected to the first input of the scanning device 40, the second input / output of which is connected to the fourth 14 of the antenna, and the third input / output is connected by the first input / output of the transceiver unit 39, the second output of which is connected to the input of the filter 56, the output of which is connected to the first inputs n of the second 50 threshold devices, the second inputs of which are connected to the first outputs of the second 54 signal setter, and the outputs to the first inputs n of the second 48 tr ggerov, second inputs of which are connected to the output of the differentiating circuit 55, whose output is also connected to a second input of the counter 22 and via a second input of the first OR gate 61, to a second input of the first flip-flop 47. The outputs n of the second 47 triggers are connected to the first inputs of the first 57 keys, the second inputs of which are connected to the second outputs of the second 54 signal pickups, and the outputs, through the adder 59, are connected to the first input of the second 58 key, the second input of which is connected to the first output of the first 47 the trigger, and the output is with the second input of the third 30 threshold device, the first input of which is connected to the output of the filter 56, the last bit of the output of the counter 42 is connected to the first input of the second 45 And element, the second input of which is connected to the output of the adder 59, and the output connected simultaneously with the first input of the first 47 trigger and the input of the delay line 60, the output of which is connected to the first input of the first element 61 OR, in addition, the group of outputs of the counter 42 is connected to the first inputs n of the third 46 AND elements, the second inputs of which are connected to the output of the third threshold devices, and the outputs with the inputs of the second OR element 62, the second input / output of the scanning device 40 and the output of the second OR element 62 are the first input-output and second output of the block 8 for determining the angular coordinates of the element truktsii aerial target.

The device operates as follows.

The functioning of the air-to-air missile detention system is carried out in the following modes: target designation, search, detection and capture of the target along the trajectory, formation of a mismatch parameter and formation of a command to undermine the warhead of the rocket.

The first two modes are preparatory, and, in fact, homing and team formation to undermine the warhead of the rocket is carried out in the third mode. In the target designation mode (CC) from the equipment of the fighter to the information processing module 9, commands are received for preparing the rocket for operation and command for the control (Fig. 1). According to the preparation commands, supply voltages to the IVS are supplied, the receivers of 2, 4 synchronization channels and the reflected signal are tuned to the frequency of the target illumination signal (TWS), and the operability of the entire rocket equipment is tested. At the command of the controllers, the meters and calculators are prepared to track the target selected for destruction. In accordance with these commands, the antenna 3 of the homing head is deployed in the direction of the target, or at the anticipated point at which the target will be located at the time of taking it for auto tracking. The presence of target designation commands for the range D _tsu and the approach speed V _tsu is determined by the guidance method used and the target illumination signal.

If a continuous TWS is used in the homing radar (RGS), then the command is given for the approach speed V _zu (Doppler frequency), in accordance with which radio signals will be selected only for that target, the approach speed with which corresponds to the target designation speed. If the CSG SPO uses pulse, the processing unit 9 is supplied by MC-range command, whereby the reflected signal receiver 4 will be unlocked only during the arrival of the signals reflected from the target, separated from the fighter in the desired distance D _zu. With a quasi-continuous TWS, the command of the control center is issued both in range and speed. In addition, the command of the control center in range, approach speed, and angular velocities of the line of sight comes as initial conditions to calculators that extrapolate the relative motion of the rocket and the target in the autonomous mode of the IVS, preceding the capture of the target on the trajectory, and in the event of interference with it. The readiness of the IVS for work is controlled by a special control signal supplied to the fighter’s equipment via feedback circuits (Fig. 1).

It should be noted that, depending on the type of target illumination signal (TWS), the search and selection of the signal reflected from the intercepted target are performed differently.

After the coincidence in time of the tracking half-gates of the rangefinder and the pulse u _c reflected from the target, the search stops, and the detection problem is solved. In the process of solving this problem, signals are accumulated with the aim of increasing the probability of correct detection. In addition, the detected signal is analyzed for its belonging to the target or to the jammer. The analysis is performed on the basis of energy, since the direct signal of active interference is many times higher than the signal reflected from the target.

If a decision is made about the ownership of the detected signal of an intercepted target, then the IVS meters go into automatic tracking of the target in range and direction, and the IVS is transferred to the mode of generating a mismatch (homing) parameter and forming a command to undermine the warhead of the rocket.

и

а в угломерном канале 18 - оценки углов

и приращений угловых скоростей

In this mode, in the rangefinder channel 17 estimates are formed

and

and in the goniometer channel 18 - estimates of the angles

and increments of angular velocities

и

а также рассчитываемые вычислителем автономной системы (АС) оценки

используются для формирования параметра рассогласования маневрирующей цели Δ_c1,2=N₀V_сб(ω_1,2+Δω_1,2)-j_1,2, где ω₁₂ - угловые скорости линии визирования, рассчитанные при условии, что цель не маневрирует, а Δω₁₂ - измеряемые комплексным угломером РГС приращения угловой скорости линии визирования, вызванные маневром цели, а оценки

- для вычисления параметров рассогласования Δ_у1,2=К_ф(φ_1,2+φ_ldon1,2) при методе наведения с постоянным углом упреждения, где φ_1,2 - бортовые пеленги цели в плоскостях управления, φ_доп.1,2 - допустимые углы визирования в этих плоскостях, при которых маневр цели не приводит к срыву ее сопровождения по направлению.Grades

and

as well as estimates calculated by the calculator of the autonomous system (AC)

are used to form the mismatching parameter of the maneuvering target Δ _c1,2 = N ₀ V _sb (ω _1,2 + Δω _1,2 ) -j _1,2 , where ω ₁₂ are the angular velocities of the line of sight calculated under the condition that the target does not maneuver , and Δω ₁₂ are the increments of the angular velocity of the line of sight, measured by the RGS complex goniometer, caused by the target’s maneuver, and the estimates

- to calculate the mismatch parameters Δ _у1,2 = K _f (φ _1,2 + φ _ldon1,2 ) with the guidance method with a constant lead angle, where φ _1,2 - side bearings of the target in the control planes, φ _add.1,2 - allowable viewing angles in these planes, at which the maneuver of the target does not lead to the disruption of its tracking in the direction.

Knowing the estimate of D allows you to select the range of pulses reflected from the intercepted target by unlocking the receiver 4 of the reflected signals only for the time of their arrival. This feature allows to increase the noise immunity of the IVS as a whole.

The reference point, to estimate the range, set the TWS pulses entering the receiver 2 of the synchronization signals through the antenna 1.

In space (direction), the target is selected due to the directional properties of the antenna 3 by rotating it in the direction determined by the estimates of the angles

где

- оценка скорости, экстраполированной в автономной системе наведения ракеты. Поиск осуществляется путем изменения по линейному закону частоты специального гетеродина. При некотором значении этой частоты сигнал промежуточной частоты приемника отраженных сигналов (ПРМОС) попадает в узкополосный фильтр, после чего поиск прекращается и начинается этап обнаружения и анализа.With a continuous TWS, for the selection of signals reflected from the target, the Doppler frequency F _{rts is used} , which is proportional to the speed of approach of the rocket to the target. In a semi-active CWG, the frequency F _rc is allocated as the frequency difference of two signals. One of them, reflected from the target, received by the antenna 3 A _os and amplified in the receiver 4 of the reflected signals, contains a Doppler frequency offset due to the speed of approach of the fighter with the target and target with the rocket. The second signal, u _c , received by antenna 1 and amplified by receiver 2, contains a Doppler frequency offset caused by the speed of the rocket moving away from the fighter. After subtracting the frequencies of the signals entering the receivers 4, 2, reflected and synchronizing signals, a signal is generated, the search and selection of which is performed in the processing module 9. At a range of D _p ≤ D _{s, the} search for this signal is carried out relative to the frequency F _tsu = 2V _tsu / l, which is set by the target designation team V _tsu at the speed measured in the radar of the fighter. If D _p > D _{s the} search is performed relative to the frequency

Where

- an estimate of the speed extrapolated to an autonomous missile guidance system. The search is carried out by changing according to the linear law of the frequency of a special local oscillator. At a certain value of this frequency, the signal of the intermediate frequency of the reflected signal receiver (PRMOS) falls into the narrow-band filter, after which the search stops and the detection and analysis stage begins.

The selectable signal is analyzed for its belonging not only to the target, or to the jammer, but also to the ground. This eliminates the capture and tracking of a signal reflected from the ground, instead of a signal reflected from a low-flying target. The analysis is based on the energy and frequency differences of the signals emitted by the jammer and reflected from the ground, or from the target.

Making a decision on whether the detected signal belongs to the jammer leads to the same thing as when using pulsed signals, namely, if it is decided that the detected signal belongs to the ground, a command is issued to resume the search for the target signal in frequency. When deciding whether the analyzed signal belongs to the intercepted target, the CWG meters switch to its automatic tracking according to the Doppler frequency performed by the auto-selector (channel 17 for evaluating V _sat ) and in the direction carried out by the goniometer, and the CWG is switched to homing mode.

The estimate formed by the auto-selector speed based on the measurement of the Doppler frequency F _rc is supplied to the computer 10 mismatch parameters for the implementation of guidance methods. The goniometer channel 18, with a continuous TWS, functions in the same way as with a pulsed signal with LF.

и скорости

При этом Д оценивается по времени запаздывания отраженного сигнала, а скорость - по частоте F_рц. Наличие информации о дальности позволяет повысить помехозащищенность РЭСУ за счет отпирания приемника только на время прихода сигналов, отраженных от цели.When using a quasicontinuous signal, the search and selection of the target is performed both in range and in Doppler frequency. In the process of detecting a target, the same signal analysis takes place on its belonging to the jammer, ground, or target, as when using a continuous TWS. After the transition to automatic tracking of the target in range, speed and direction of the estimating device, D and V _Sat, form range estimates

and speed

In this case, D is estimated by the delay time of the reflected signal, and the speed by the frequency F _rts . The availability of information on the range allows to increase the noise immunity of the RESU due to the unlocking of the receiver only at the time of arrival of signals reflected from the target.

With a quasi-continuous TWS, it is necessary to eliminate the ambiguity of the range reading, since the delay time of the reflected signal can exceed the pulse repetition period of the TWS. If it is impossible to ensure the uniqueness of the reference, the range is not estimated, and tracking is not implemented. In this situation, the reflected signal is selected not by range, but by the repetition period, which also allows the receiver to be gated for the time of arrival of the reflected pulses. The expediency of this technique is due to the fact that when calculating the mismatch parameters, knowledge of the current range is not required. The principle of operation of the goniometer channel 18 remains the same as when using TWS of other types.

и

используемые при вычислении параметров рассогласования. Гироскопические датчики позволяют развязать антенну 3 РГС от угловых колебаний ракеты, что повышает точность и устойчивость сопровождения целей по направлению.The self-motion parameters measuring instruments included in the system 11 of autonomous sensors (Fig. 1), which primarily include accelerometers and gyroscopes, provide information on longitudinal j _x , lateral accelerations j _1,2 , pitch angles ϑ and yaw Ψ. Based on the measurement of j _x and j _1,2 , estimates are formed in the calculator of the autonomous system

and

used in calculating the mismatch parameters. Gyroscopic sensors allow you to decouple the antenna 3 of the CWG from the angular oscillations of the rocket, which increases the accuracy and stability of target tracking in the direction.

When a missile approaches a target at a certain distance, the target becomes extended / R. Ostrovityanov, F. Basalov Statistical theory of radar extended targets. M .: Radio and communication, 1982, p. 4 /. In this case, it becomes possible to re-target the rocket to the power plant of the air target.

Information signs to determine the location of the engine is the frequency and amplitude of the vibration of an extended air target. It is known that the power plant of the aircraft creates vibration of the surface of the object and is characterized by a local increase in the level of amplitude of oscillations of the surface of the object / V.P. Karasev, Maximov and others. Vibration diagnostics of gas turbine engines. M .: Mechanical Engineering, 1978 /.

The vibration of the engines occurs due to the rotating rotor of the turbocharger, the circumferential unevenness of the gas (air) flow flowing through the movable and fixed lattices of the blade devices, acoustic noise, not only generated by the compressor and turbine, but also arising during the operation of the input device, jet nozzle and combustion chamber, gears etc.

The vibration spectrum of the engine, as a rule, has a combined structure and is the sum of the broadband vibrational noise (background) and the line spectrum, consisting of a number of discrete harmonic components.

Disturbing loads having an aerodynamic nature make the largest contribution to the formation of the background; discrete components are caused by forces of both mechanical and gas-dynamic origin.

The main source of vibration of the gas turbine engine is the rotor rotor of the turbocompressor. Static and dynamic imbalance of the rotor lead to the emergence of forces and moments that cause vibration of both the rotor itself and the entire turbomachine as a whole.

The imbalance is a consequence of the inaccuracy in the manufacture of parts and assemblies of the rotor and stator of a gas turbine engine, heterogeneity of materials, elastic residual deformations that occur during assembly and operation of the engine, imperfection of balancing technology, etc. / Doroshko S.M. Monitoring and diagnosing the technological state of gas turbine engines by vibration parameters. M .: Transport, 1989.

The frequency range of the vibration generated by the rotor of the turbocompressor varies slightly from the engine operating mode, and it can be distinguished relatively simply from the general vibration of the object’s body with a narrow-band filter that suppresses other components of the spectrum.

The determination of the angular coordinates of the power plant of an air target is as follows.

From the second output of the information processing module 9, the signal is input to the block 8 for determining the angular coordinates of the power plant of the air target, and accordingly to the first input of the first 49 threshold device, the second input of which receives a signal from the output of the first 53 signal setter (Fig. 3).

When the rocket approaches the target at a distance when the target becomes extended, the threshold device 49 stops issuing a signal, while providing a signal from the output of the AND-NOT 52 element at the same time to the input of the differentiating circuit 55 and the first input of the first 44 element I.

The signal from the output of the differentiating circuit 55 provides “zeroing” through the second inputs of the second 48 flip-flops, counter 42 and through the first 61 OR elements of the first 47 flip-flops, preparing them for work. In this case, the signal from the second output of the first trigger 47 is fed to the second input of the first 44 And element, providing, through its third input, pulses from the pulse generator 43 through the first input of the counter 42, the digital-to-analog converter 41, to the first input of the scanning device 40. Signals from the first input / output of the transceiver unit 39, through the scanning device 40, enter the input of the fourth 7 antennas, thereby providing electromagnetic radiation in a given sector relative to the rocket.

The signals reflected from the target from the output of the fourth 7 antennas through the scanning device 40, the transceiver unit 39, the filter 56, are fed to the first inputs n of the second 50 threshold devices, the second inputs of which receive signals from the first outputs of the second 54 signal generator.

Depending on the intensity of vibration of the structures of an extended target, a sequence of n second 50 threshold devices, n second 48 triggers, n first 57 keys is triggered, thereby ensuring the passage of signals from the second outputs of the second 54 master, through n first 57 keys, the summing device 59 , simultaneously to the second input of the second AND element and the first input of the second 58 key.

At the output of the second element 45, the signal appears after scanning the specified area by the scanning beam due to the input of the second element And 45 of the signal from the output of the maximum discharge of the counter 42. The signal from the output of the And 45 element goes to the first input of the trigger 47, from the first (direct) the output of which is supplied to the second input of the key 58, thereby ensuring the passage of the signal to the second input of the second 51 threshold devices, at the same time, the signal from the second output of the trigger 47 is removed, thereby stopping the pulse through the second input of the first member 44, with the pulse generator 43.

Thus, at the second input of the second 51 threshold device, a signal is generated corresponding to the maximum vibration amplitude after the scan cycle.

Determination of the angular position of the power plant is based on subsequent scanning of a given sector of space.

Determining the angular position of the power plant is as follows. From the output of the second 45 AND element, the signal enters, through the delay line 60, the first input of the first 61 OR element to the second input of the first 47 trigger, zeroing it. In this case, the signal from the second output of the first 47 trigger is fed to the second input of the first 44 element And, providing the passage of signals from the pulse generator through the third input of the element And, to the first input of the counter 42. The signals from the group of outputs of the counter 42 are sent simultaneously to the first inputs n third 46 And elements, and, through a digital-to-analog converter 41, to a scanning device 40.

The signals from the first input / output of the transceiver unit 39, through the scanning device 40, are fed to the input of the fourth 7 antennas, thereby providing electromagnetic radiation in a given sector relative to the rocket.

The signals reflected from the target from the output of the fourth 7 antennas, through the scanning device 40, the transceiver unit 39, the filter 56 are fed to the first inputs n of the second 50 threshold devices and the third 51 threshold devices. At the moment of equal current and maximum vibration values, at the corresponding angular positions of the antenna, the third 51 threshold device is triggered, from the outputs of which the signal goes to the second inputs of n third 46 elements I. In this case, depending on the angular position of the target, one of the And elements of the n third 46 AND elements, from the output of which, through the second OR element 62, the signal is fed simultaneously to the input of the AND-NOT element 14 (Fig. 1) and the second input of the OR element 16. At the same time, the signal from the output of the element is removed and AND NOT 14 and, respectively, from the second input of the key 13. In this case, the signal from the fourth output of the information processing module 9 is blocked, and the signal is output from the output of the unit 8 for determining the angular coordinates of the power plant of the air target, through the second input of the OR element 16, to the input power amplifier 12 and the antenna drive, thereby ensuring the re-targeting of the rocket to the power plant of an air target.

In the future, when the missile approaches an extended air target at a closer distance, a signal is generated to undermine the warhead relative to the power plant. This is done as follows.

When the rocket approaches the extended target for a second predetermined distance, the signal from the output of the threshold device 28 is removed, and a signal arises at the output of the AND-NOT 31 element, which is fed simultaneously to the input of the differentiating circuit 34 and the first input of the first 24 AND elements (Fig. 2).

From the output of the differentiating circuit 34, the “zeroing” signal is supplied to the third input of the counter 22, the second input of the first 26 triggers, and the second inputs of the second 27 triggers, ensuring the readiness of these elements for work.

The second and third input of the first element And 24 receives signals, respectively, from the first output of the first 26 trigger and pulse generator 23.

From the output of the first 24 AND elements, the signal is supplied to the second input of the counter 22, the first input of which receives the signal from the first output of the first 26 trigger.

From the group of outputs of the counter 22, through the digital-to-analog converter 21, the first output of the scanning device 20, the signal is supplied to the input of the third 5 antenna, which provides electromagnetic radiation in a given sector of space through the third input / output of the scanning device 20 from the output of the transceiver unit 19.

The signal reflected from the extended target through the third 5 antenna, the scanning device 20, the transceiver 19, the filter 35 is supplied to the first inputs n of the second 29 threshold devices, the second inputs of which receive a signal from the first outputs of the second 33 signal generator.

The filter 35 is tuned to a frequency band determined by the static and dynamic imbalance of the rotor of the turbocompressor of the gas turbine engine of an air target.

Depending on the amplitude of the vibration, n second 29 threshold devices and, accordingly, n second 27 triggers, n first 36 keys are triggered. In this case, the signals from the second outputs of the second 33 master through n the first 36 keys, the adder 38 simultaneously arrive at the second input of the element And 25 and at the first input of the second 37 key.

At the output of the second element 25, the signal appears after scanning the specified area with the scanning beam due to the signal at the second input of the second element And 25 from the output of the maximum discharge of the counter 22.

The signal from the output of the And 25 element goes to the first input of the trigger 26, from the first (direct) output of which goes to the first (control) input of the counter 22, which generates a certain code that sets the fixed position of the electromagnetic oscillation beam, at the same time, the signal from the second output trigger 26 is removed, thereby stopping the supply of a pulse, through the second input of the first 24 elements, from the pulse generator 23.

In this case, the signal from the first output of the trigger 26 enters the second input of the key 37, thereby providing a signal to the second input of the second 30 threshold device, setting the signal threshold corresponding to the maximum amplitude of vibration of the target structure.

Thus, after scanning with a narrow beam in a given sector relative to the axis of the rocket, the frequency band of the vibrational elements of the target structure corresponding to the vibration frequencies of the power plant is isolated from the spectrum of the reflected signal, and the maximum vibration amplitude is determined in this frequency band.

Due to the fixation of a beam of electromagnetic oscillations in a predetermined position relative to the longitudinal axis of the rocket, and as the extended target moves relative to the rocket, the spectral components are magnified in sequence due to the passage of the signal from the output of the antenna 5 through the scanning device 20, the transmitter-receiver unit 19, the filter 35 to the first input of the third 30 threshold device.

At the moment of correspondence of the current values of the vibration signal to the maximum level, the third 30 threshold device is triggered and a command is issued to undermine the warhead of the rocket relative to the power plant of the air target.

Thus, when a missile approaches a distance when the target becomes extended, the missile is retargeted at the power plant of the air target and its defeat.

Information sources

1. Efanov V.V., Muzhichek S.M., patent of the Russian Federation for invention No. 2225306, class. B64D 7/00, F41G 3/22, F41G 7/22, F42B 15/01, 05/27/2008

2. Ostrovityanov R.V., Basalov F.A. Statistical theory of radar extended targets. M .: Radio and communication, 1982, p. 4.

3. Karasev VP, Maksimov et al. Vibration diagnostics of gas turbine engines. M .: Engineering, 1978

4. Doroshko S.M. Monitoring and diagnosing the technological state of gas turbine engines by vibration parameters. M .: Transport, 1989

Claims (8)

1. The method of functioning of the information and computing system of the rocket, including preparing the rocket on board the carrier aircraft for operation, measuring the parameters of the target’s motion and the rocket’s own motion, forming an estimate of the necessary parameters of the relative motion of the target and the absolute motion of the rocket, choosing the method of guiding the rocket at the target, the best by any criterion for the given conditions of use, the calculation for the selected method of the mismatch parameters characterizing the degree of mismatch of the actual param the ditch of the rocket’s movement to their required values, the formation of a preparation and control signal for a radio fuse, the emission and reception of electromagnetic waves by scanning with a narrow beam in a given sector relative to the axis of the rocket when the rocket approaches the target at a distance when it becomes extended, highlighting the spectrum reflected from the target the signal of the frequency band corresponding to the frequencies of oscillations of the structural elements of the target, the determination in this frequency band of the magnitude of the maximum amplitude of the reflected signal, radiation and receiving electromagnetic waves in a direction specified with respect to the axis of the rocket, recognizing a target structural element having a maximum vibration amplitude, generating a signal to detonate the rocket’s warhead while combining a fixed beam of electromagnetic waves with this structural element, characterized in that the beam is again narrowly focused electromagnetic oscillations in a given sector relative to the axis of the rocket, a band is isolated from the spectrum of the signal reflected from the target the frequencies corresponding to the vibration frequencies of the power plant of the air target, determine the maximum value of the amplitude of the vibration in a given frequency band of the spectrum of the reflected signal from the extended target based on its scan, compare the values of the current and maximum amplitude of vibration in each angular position of the antenna during subsequent scanning of the extended air target, determine the angular position of the power plant of the air target at the moment of equality of the current and maximum values of the amplitude of the vibration reflected signal, carry out the re-targeting of the rocket to the power plant of an air extended target. 2. The method according to claim 2, characterized in that the preparation of the rocket for work on board the carrier aircraft is carried out by supplying voltage from the fighter’s equipment, tuning the synchronization receivers and the reflected signal to the target’s illumination frequency, testing the operability of the entire rocket equipment, determining readiness for information - the rocket computing system to work on control signals received by the fighter’s equipment via feedback circuits, by preparing meters and a calculator to track the target selected A defeat of the teams target designation. 3. The method according to claim 2, characterized in that the preparation of the meters and calculator for tracking the target selected for destruction by target designation teams is carried out by rotating the homing antenna in the direction of the target, or at a pre-empted point where the target will be at the moment taking it for auto tracking, performing target designation commands for range and approach speed. 4. The method according to claim 3, characterized in that the target range commands are formed depending on the guidance method and the target illumination signal, while if a continuous target illumination signal is used in the homing radar, then a target designation command is formed according to the approach speed, in accordance with which radio signals are selected only for that target, the approach speed with which corresponds to the target designation speed, if a pulse target illumination signal is used in the homing radar, then a range targeting command is sent to the processing module, according to which the reflected signal receiver will be unlocked only for the time of arrival of signals reflected from the target, which is distant from the carrier aircraft at the targeting range, with a quasicontinuous target illumination signal, targeting commands both in range and in speed, while targeting commands for range, approach speed and angular velocities of the line of sight are given as initial conditions to the calculators, extrapolating the relative movement of the rocket and the target in the autonomous mode of operation of the information and computer system of the rocket, preceding the capture of the target on the trajectory and in the event of exposure to radio interference. 5. The method according to claim 1, characterized in that when deciding whether the reflected signal belongs to the intercepted target, the radar homing meters switch to its automatic tracking at the Doppler frequency performed by the auto-selector and in the direction carried out by the goniometer, and the radar homing put into homing mode. 6. A device for operating a rocket information and computing system, comprising a first antenna and a synchronization signal receiver, a second antenna and a reflected signal receiver, a third antenna and an information processing unit, an information processing module, a mismatch parameter calculator, an autonomous sensor system, a power amplifier, and an antenna drive, wherein the information processing module consists of a device for searching, detecting, selecting and analyzing signals, a channel for estimating range and speed with proximity, control channel of the second antenna, the output of the synchronization receiver is connected to the second input of the reflected signal receiver, the output of which is connected to the first input of the information processing module, the second, third, fourth, fifth, sixth, seventh inputs of which are respectively connected to the first output of the synchronization signal receiver, the first and second output of the system of autonomous sensors, with the output of the training and target designation commands from the fighter equipment, the output of which is simultaneously connected to the third input of the calculator parameter mismatch, with the output of the calculator of the autonomous system, the first output of the power amplifier and the antenna drive, the second output of which is mechanically connected to the antenna of the reflected signal, the first, second, third and fourth outputs of the information processing module are connected respectively to the input of the control and feedback signals of the fighter’s equipment, the first and second input of the mismatch parameter calculator, the input of the power amplifier and the antenna drive, the second output of the information processing module, in addition, is connected to the input of the block information processing, the second output of which is the output of the command to undermine the warhead of the rocket, characterized in that a fourth antenna and a unit for determining the angular coordinates of the power plant of the air target are introduced in series, as well as a key, an AND-NOT element, an OR element, with a second output the information processing module is connected to the input of the unit for determining the angular coordinates of the power plant of the air target, the second output of which is connected simultaneously with the input of the AND-NOT element and with the second input of the OR element, the first input to orogo connected to the output switch, the first and second inputs of which are connected respectively with the fourth outlet information processing unit and the output of AND-NO. 7. The device according to claim 6, characterized in that the information processing unit consists of a transceiver unit, a scanning device, a digital-to-analog converter, a counter, a pulse generator, the first and second AND elements, the first trigger, the first threshold device, the AND-NOT element, the first a signal generator, a differentiating circuit, a filter, second threshold devices, second triggers, first keys, an adder, a second key, a third threshold device, a second signal generator, the second input of the processing module Information chambers are connected to the first input of the first threshold device, the second input of which is connected to the first signal generator, and the output of the first threshold device through the AND-NOT element is connected simultaneously with the input of the differentiating circuit and the first input of the first AND element, the second input of which is connected to the second output of the trigger and the third input is connected to the output of the pulse generator, the output of the first element And is connected to the second input of the counter, the first input of which is connected to the first output of the trigger, and the group of outputs of the counter is connected is connected to the group of inputs of the digital-to-analog converter, the output of which is connected to the first input of the scanning device, the second input / output of which is connected to the third antenna, and the third input / output is connected to the first input / output of the transceiver unit, the second output of which is connected to the input of the filter, the output of which connected to the first inputs of the second threshold devices, the second inputs of which are connected to the first outputs of the second signal setter, and the outputs are connected to the first inputs of the second triggers, the second inputs of which are connected to the output of of a phasing circuit, the output of which is also connected to the third input of the counter and the second input of the first trigger, the outputs of the second triggers are connected to the first inputs of the first keys, the second outputs of which are connected to the second outputs of the second signal generator, and the outputs of the first keys are connected to the first input of the second key, the second input of which is connected to the first output of the trigger, and the output - to the first input of the third threshold device, the second input of which is connected to the output of the filter, the last bit of the counter with one with a first input of a second AND gate having a first input connected to the output of the summing device, and an output - to the first input of the first flip-flop, a second input / output scanning device and the output of the third threshold devices are respectively first input / output and the second output information processing unit. 8. The device according to claim 6, characterized in that the unit for determining the angular coordinates of the power plant of the air target consists of a transceiver unit, a scanning device, a digital-to-analog converter, a counter, a pulse generator, the first and second, n third elements And, the first and n second triggers , the first, n second, third threshold devices, the NAND element, the first and second signal generator, the differentiating circuit, the filter, the n first and second keys, the summing device, the delay line, the first and second OR elements, the input of the unit for determining the angular coordinates of the design element of the air target is the first input of the first threshold device, the second input of which is connected to the output of the first signal generator, and the output of the threshold device through the AND gate is connected simultaneously with the input of the differentiating circuit and the first input of the first AND element, the second the input of which is connected to the second output of the first trigger, and the third input is connected to the output of the pulse generator, the output of the first element And is connected to the first input of the counter, the group of outputs to is connected to the group of inputs of the digital-analog converter, the output of which is connected to the first input of the scanning device, the second input / output of which is connected to the fourth antenna, and the third input / output is connected to the first input / output of the transceiver unit, the second output of which is connected to the input of the filter, the output of which connected to the first inputs of n second threshold devices, the second inputs of which are connected to the first outputs of the second signal generator, and the outputs to the first inputs of n second triggers, the second inputs of which are inens with the output of the differentiating circuit, the output of which is also connected to the second input of the counter and through the second input of the first element OR to the second input of the first trigger, the outputs of n second triggers are connected to the first inputs of the first keys, the second inputs of which are connected to the second outputs of the second signal sources and the outputs through the summing device are connected to the first input of the second key, the second input of which is connected to the first output of the first trigger, and the output to the second input of the third threshold device, the first input of which connected to the output of the filter, the last bit of the counter output is connected to the first input of the second AND element, the second input of which is connected to the output of the summing device, and the output is connected simultaneously with the first input of the first trigger and the input of the delay line, the output of which is connected to the first input of the first element OR in addition, the group of outputs of the counter is connected to the first inputs of the n third AND elements, the second inputs of which are connected to the output of the third threshold device, and the outputs to the inputs of the second OR element, the second input / output with the canning device and the output of the second OR element are respectively the first input-output and the second output of the unit for determining the angular coordinates of the power plant of the air target.

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