RU2256191C1 - Method for protection of radar against antiradar missiles and radar complex for its realization - Google Patents

Abstract

FIELD: methods for protection of an active radar against antiradar missiles.

SUBSTANCE: in the method and device for protection of radar against antiradar missiles accomplished are radiation of sounding signals, detection of antiradar missiles, guidance of anti-aircraft missiles on the antiradar missile, destruction of the anti-radar missile by blasting of the warhead of the anti-aircraft missile, guidance of the anti-aircraft missile at least during a time period directly preceding the blasting of the warhead of the anti-aircraft missile, all this is conducted on the trajectory passing in the vicinity of the imaginary line connecting the antiradar missile and the radar, in this case constantly are determined the distance from the radar to the antiradar missile D_r-arm, from the radar to the anti-aircraft missile D_r-aacm and from the anti-aircraft missile to the antiradar missile D_aacm-acm, and at the time moments leading the moments of radiation of the radar sounding signal by value t=(D_r-aacm+D_aacm-arm-D_r-arm)/v, where v - velocity of light, commands are given from the radar to the anti-aircraft missile for radiation of a signal simulating the radar signal.

EFFECT: reduced dynamic errors of guidance of anti-aircraft missile on antiradar missile.

3 cl, 6 dwg

Description

The invention relates to methods for protecting an active radar station (radar) from anti-radar missiles (PRR) induced by radio emission.

A known method and device for the protection of radar, providing an overview of the zone by emitting sounding signals from the PRR, based on the distraction of the PRR using simulator traps. So, for example, a well-known technical solution is a method of protecting a radar from PRS and a device for its implementation according to US Pat. No. 4,433,333, based on simulating radar radiation by fixed false signal resolvers (PLCs) located at certain distances from each other and from the protected radar. In this case, the PRR moves towards the energy center of the radar-radar system, offset both relative to the radar and relative to the radar, as a result of which there is a systematic error of pointing it at the radar and radar. The disadvantage of these methods and devices is that the necessary condition for the system to work is the proximity of the PLC to the protected radar, so that the guidance system of the PRR could not resolve the spatial sources of radiation. This leads to the fact that with a sufficiently powerful combat charge of the PRR, a high probability of protection for the radar and the submarine cannot be provided. In addition, a necessary condition for reliable protection of the radar is the excess radiation power of the radar over the radar in all hazardous directions, which is almost impossible to implement.

There is also a known method and device for radar protection based on the use of trap-rockets (RF patent No. 2153684), in which a radar radiation simulator is placed on board a rocket launched in the direction of the PRR. The disadvantage of this method and device is that they are functional only in combination with turning off the radar. Otherwise, disturbance in the PRR trajectory is created only for the duration of the trap missile flight. At the end of the flight of the trap missile, the PRR trajectory is again set in the direction of the radar.

The closest solution to the claimed invention in technical essence is a method of protecting a radar that emits sounding signals from PRR, which consists in detecting PRS, pointing missiles at it and destroying PRS by undermining the warhead of a missile defense (Tipugin V.N., Weitzel V.A. ., Radio control, “Sov. Radio”, 1962, p.131-142). In this case, they can be used as missiles, guided by commands from the guidance radar (Tipugin V.N., Veitsel V.A., Radio control, “Sov. Radio”, 1962, p. 89-141), and homing missiles ( Krinetskii E.I., Homing systems, “Engineering”, 1970, p. 42-73).

The known method is implemented by the device, which is a complex consisting of a radar detection, control center for missiles and on-board equipment for missiles (Tipugin V.N., Weitzel V.A., Radio control, “Sov. Radio”, 1962, p.135, fig.2.23). The block diagram of the complex is shown in figure 1.

The known complex contains a radar for detecting targets 1, a control center for a missile launcher 2, on-board equipment for a missile launcher 3, and the control center for a missile launcher 2 includes a radar guidance 4, calculating and solving device 5, servo drive 6, transmitting device 7, antenna device 8, and on-board equipment SAM 3 contains an antenna SAM 9, a radio receiver of the guidance channel missiles 10, the orientation and control system of missiles 11. Moreover, the output of the radar target detection 1 is connected to the input of the radar guidance 4, the output of the radar guidance 4 is connected to the input of the computing devices 5, the output of which is connected to the control input of the servo power drive 6, which, in turn, is mechanically connected to the antenna device 8. The output of the transmitting device 7 is connected to the input of the antenna device 8. The antenna of the SAM 9 is connected to the input of the radio receiver of the guidance channel of the missile 10 the outputs of which are connected to the guidance and control system of the missiles 11, and the links of the guidance channel of the missiles 10 with the guidance and control system of the missiles 11 are at least three.

A well-known complex works as follows. The radar station for detecting targets 1 reviews a given area of space by emitting sounding signals and receiving reflected signals. Upon detection of the target, its coordinates are transmitted to the guidance radar of the 4 missile control center 2 as a target designation. Using the calculating device 5, the coordinates of the target are specified and, using the follow-up power drive 6, the antenna device 8 of the missile control system 2 is deployed in the direction on target. In this case, the equal-signal area of the radiation pattern formed by the antenna device 8, is aimed at the target. In an equal-signal zone moves SAM. In the process of controlling the movement of missiles, the signal emitted by the antenna device 8 is received by the antenna of the missiles 9 and enters the radio receiver of the guidance channel of the missiles 10, in which missile guidance errors are generated, i.e. signals proportional to deviations of the direction of movement of SAMs from the direction of the equal-signal zone of the radio beam. These signals are fed to the guidance and control system of the missile launcher 9, where, in accordance with them, the position of the rudder of the missile launcher changes in the direction of reducing guidance errors.

The disadvantage of this method is not sufficiently high reliability of the defeat of the PRP anti-aircraft guided missile. This is explained by the following. In the process of pointing to a moving target, the missile system constantly adjusts the direction of its movement. Moreover, due to the finite speed of the equipment of the guidance and control system for missiles, the limited capabilities of missiles for overloading and other factors (Handbook of an air defense officer, M., Military Publishing House, 1987, p. 211), dynamic guidance errors occur. At a sufficiently high PRR speed, dynamic errors can turn out to be so large that the guidance process will fail and missiles will miss.

The problem being solved (technical result), therefore, is to reduce the dynamic errors of pointing missiles at the PRR.

The specified technical result is achieved by the fact that in the known method of protecting the radar from missile defense, including the emission of sounding signals, detecting missile defense, guiding missile defense on missile defense, destroying missile defense by undermining the warhead of the missile defense, according to the invention, guidance of missile defense, at least for a period of time, immediately preceding undermining warhead ZUR produce on a trajectory passing in the vicinity of the imaginary line joining the RLP and RLS, while constantly determines the distance from the radar to _radar RLP _d-RLP from the radar to _radar-d ZUR _ZUR ZUR and by d RLP _{ZUR D-RLP,} and at times outstripping moments probing radar signal radiation by an amount Δt = _{(D-radar ZUR ZUR} + _{D-RLP radar -D-RLP)} / c, where c - velocity of light, with a radar at ZUR issue commands to emit a signal simulating a radar signal.

The indicated technical result is also achieved by the fact that immediately after the radiation from the SAM, a signal simulating the signal of the protected radar, the protected radar is turned off.

The specified technical result is also achieved by the fact that in the complex of radar protection against PRR, containing radar target detection, missile control center, on-board missile defense equipment, and the missile control center includes guidance radar, calculating and solving device, tracking power drive, transmitting device, the antenna device, and the on-board equipment of the SAM, contains the antenna of the SAM, the radio receiving device of the guidance channel of the SAM, the guidance and control system of the SAM, while the output of the radar guidance is connected to the input of the computer, the output to which is connected to the control input of the tracking power drive, which is mechanically connected to the antenna device, the output of the transmitting device is connected to the input of the antenna device, the SAM antenna is connected to the input of the radio receiver of the missile guidance channel, the outputs of which are connected to the guidance and orientation system of the missile defense, according to the invention, are introduced the output of the synchronization pulses of the target detection radar, an object recognition device, the input of which is connected to the information output of the target detection radar, and the output from homing radar, a device for generating commands for emitting simulated signals, the first input of which is connected to the output of the object recognition device, and the second input is the output of synchronization pulses of the radar for detecting targets, the second group of outputs of the radio-receiving device of the guidance channel of the SAM, the transmitter simulating signals, the inputs of which are connected to this group of outputs, and the antenna, the input of which is connected to the output of the transmitter simulating signals.

The essence of the proposed method of protecting the radar from the PRR is as follows (figure 2). Guidance of the PRR on the radar is carried out by the radar, which in the process produces an inspection of the zone, emitting probing signals and receiving reflected signals. After the detection of PRR launch missiles. Detection and recognition of PRS can be carried out by a protected radar, which provides the coordinates of the PRP as target designation for radar guidance. The missile trajectory is chosen so that the missile, at least for the time immediately preceding the undermining of its warhead, is in the guidance sector of the PRR. For this, guidance of missiles during this time is carried out along a trajectory passing in the vicinity of an imaginary line connecting the PRR and the radar being protected. On command from the protected radar to the SAM, a transmitter is emitted that emits a signal simulating a radar probe signal. The moment of issuing the command to turn on the transmitter is chosen so that the signal from the missile launcher arrives at the PRR simultaneously with the probing signal of the protected radar. To do this, the radiation signal to turn on the SAM missiles is produced ahead of the probing radar signal by the value Δt = (D _RLS-ZUR + D _SAM-PRR- D _Radar-PRR ) / s, where D _Radar-PRR, D _Radar-SAM, D _{SAM -PRR} - the distance from the radar to the PRR, from the radar to the SAM and from the missile to the PRR, respectively. When the angular mismatch of the directions to the radar being protected and to the SAM with respect to the PRS is such that they both end up in the PRP guidance sector, the PRP course is adjusted. At the same time, the PRR moves towards the energy center of the SAM-radar system, i.e. the PRR course is approaching the course for missiles. It is known that missile guidance errors on a target are determined by dynamic errors resulting from the development of a missile defense control system by the control actions of a guidance radar (or from a homing head for a homing missile) tracking the target’s movement (Reference book of an air defense officer, M., Military Publishing House in, 1987, p. 211). Due to the finiteness of the speed of the missile control system, as well as the limited ability of the missile to overload, dynamic errors can reach values at which the guidance process is missed and missiles miss. The approach of the PRR trajectory to the heading course with the missile launcher reduces the magnitude of the missile maneuver required to track the displacement of the missile, and, therefore, the dynamic guidance errors are reduced. Thus, the claimed technical result is achieved.

To increase the reliability of redirection of the PRR to missiles immediately after radiation from the protected radar command to missiles to emit a signal simulating a radar signal, it is possible to turn off the protected radar.

The invention is illustrated by the following drawings.

Figure 1 - block diagram of an implementation of the known method;

Figure 2 - illustration of the proposed method of pointing missiles at the PRR;

Figure 3 - block diagram of the inventive radar system;

4 is a block diagram of a radar target detection;

5 is a block diagram of a device for generating commands for the emission of simulating signals;

6 is a block diagram of a receiver of a guidance channel for missiles.

The radar system that implements the proposed method (figure 3), contains radar for detecting targets 1, control center for missiles 2, on-board equipment for missiles 3, and also a device for recognizing objects 18, a device for generating commands for emitting simulation signals 19, while the information output of the radar is detecting goals 1 is connected to the input of the recognition device 18, the output of which is connected to the input of the control center SAM 2 and the first input of the device forming the command for the emission of simulating signals 19, and the output of the synchronization pulses RL With the detection of targets 1 is connected to the second input of the device for generating commands for the emission of imitating signals 19, and the control center of the SAM 2 includes a radar guidance 4, calculating and solving device 5, tracking power drive 6, transmitting device 7, antenna device 8, and the output Guidance radar 4 is connected to the input of the computing device 5, the output of which is connected to the control input of the servo power drive 6, which is mechanically connected to the antenna device 8, the output of the transmitting device 7 is connected to the input of the antennas of the device 8, the on-board equipment of the missile launcher contains an antenna for the missile launcher 9, a radio receiver for the guidance channel of the missile launcher 10, an orientation and control system for the missile launcher 11, a transmitter of simulating signals 30, an antenna 31, the antenna of the missile 9 is connected to the input of the radio receiver device of the guidance channel for the missile launcher 10, the outputs of which connected to the guidance and control system of the missile launcher 11, the second group of outputs of the radio receiver of the guidance channel of the missile launcher 10 is connected to the transmitter of the simulating signals 30 and the antenna 31 connected in series, the number of connections p diopriemnogo device 10 with the transmitter 30 is determined by the number of controllable parameters of the transmitter 30.

Radar detection targets 1 (Theoretical foundations of radar. Edited by Shirman Y.D., M., "Soviet Radio", 1970, p. 211) includes a series-connected synchronizer 12, transmitter 13, antenna switch 14, receiver 15, the indicator device 16, as well as the antenna 17, the information input / output of which is connected to the input / output of the antenna switch 14, and the coordinate output is connected to the second input of the indicator device 16 (Fig. 4).

The object recognition device 18 is constructed according to a well-known scheme described, for example, in the book: Nebabin V.G. Methods and techniques of radar recognition. - M .: Radio and communications, 1984, p. 30.

The device for generating commands for the emission of simulating signals 19 contains serially connected memory 20, a calculator 21, a comparison device 22, a command transmitter 23 and an antenna 24 (Fig. 5).

The radio receiving device of the guidance channel of the missile launcher 10 is a known device of the control channel of the missile launcher (Tipugin V.N., Weitzel V.A., Radio control, “Sov. Radio”, 1961, p.430-431). It contains a receiver 25 and decoders of control commands 26 and 27 connected to its output with command demodulators 28 and 29 connected in series with them, respectively, with blocks 26 and 28 being decoders and demodulators of control commands for the guidance and control system of missiles 11, and blocks 27 and 29 - decoders and demodulators of the control commands of the transmitter simulating signals 30 (Fig.6).

The complex works as follows. A target detection radar 1 reviews and detects targets in a given area of space, and when it is detected using an object recognition device 18, an anti-radar missile provides its coordinates in the radar of guidance 4 of the control center of the SAM 2 and in the memory 20 of the device for generating commands for the emission of simulating signals 19. V ZU 20 also recorded the coordinates of the radar station 1. The coordinates of the PRR are then sent to the calculating device 5. Using a tracking power drive 6 antenna device 8 control point eniya SAM 2 in accordance with the specified coordinates obtained from the resolver 5, takes place in the direction of the RLP. The transmitting device 7 operates continuously. The equal-signal area of the beam pattern generated by the antenna device 8, is aimed at the PRR. To ensure that the missile defense trajectory is in close proximity to an imaginary line connecting the PRR and the radar, the missile control center 2 is located near the radar for detecting targets 1. The missile is launched. SAM moves in an equal-signal zone. Since the guidance radar constantly monitors the PRR, the equal-signal zone also monitors its movement. In the process of controlling the movement of missiles, the signal emitted by the antenna device 8 of the control center of the missiles 2 is received by the antenna of the missiles 9 and enters the radio receiver of the guidance channel of the missiles 10, which generates error signals pointing missiles. These signals are fed into the guidance and control system of the missile launcher 11, where signals are generated to control the position of the rudder of the missile launcher in the direction of reducing guidance errors. The radar for detecting targets 1 detects missiles, the coordinates of which, after being recognized by the object recognition device 18, are transferred to the memory 20 of the command generation device for emitting simulated signals 19. Thus, the coordinates of the radar, PRS and missiles are recorded in the memory 20. Using these coordinates in the calculator 21, the distances from the radar to the PRD D of the _radar-PRR , from the radar to the missile defense D of the _{radar-missile system} and from the missile defense to the radar detector D of the _{radar-missile} defense _{system are determined} and the value of the lead time of the radiation moment of the radar probe signal Δt = (D _{radar -ZUR} + D _SAM-PRR -D _Radar-PRR ) / s. In the comparison device 22, the value of Δt is compared with the time remaining until the probe signal of the radar 1 is emitted. This is done using synchronizer pulses 12 coming from the radar for target detection 1. The comparison also takes into account previously known hardware delays, the value of which increases the value for this Δt. At the moment of coincidence of times, the command transmitter 23 is turned on and a command is sent in the form of a high-frequency signal through the antenna 24 to turn on the transmitter of the simulating signals 30. The command is received with the help of the SAM 9 by the radio receiving device 10, is converted into a control signal, by which the transmitter of the simulating signals 30 is turned on. , simulating a radar signal detecting targets 1, using the antenna 31 is radiated into space. The probe signal of the radar target detection 1 and the signal from SAM, simulating the radar radiation, achieve PRR at the same time. There is a change in the direction of movement of the PRR in the direction of the energy center of the SAM-radar system, as a result of which the trajectory of the PRR approaches the counter course with the SAM. With such a change in the PRR trajectory, the amount of missile defense maneuver required to aim at it decreases, which means that the dynamic error of guidance of the missile is reduced. Thus, the claimed technical result is achieved.

Claims (3)

1. A method of protecting a radar station (radar) from anti-radar missiles (PRR), which includes emitting sounding signals, detecting PRS, guiding an anti-aircraft guided missile (SAM) on the PRS, destroying the PRS by detonating the warhead of a missile defense, characterized in that the guidance of the SAM at least during the time immediately preceding the detonation of the warhead of a missile launcher, it is carried out along a trajectory in the vicinity of an imaginary line connecting the PRS and radar, while the distances are constantly determined: from radar to PRR D _radar-PRR , from radar d about ZUR _{ZUR-D radars} and from SAM to _SAM-D PRR _PRR, and in times that are ahead of the emission points of the probing radar signal by the value Δt = _{(D-radar ZUR ZUR} + _{D-RLP radar -D-RLP)} / s, where c is the speed of light, from the radar to the SAM, commands are issued to emit a signal simulating a radar signal. 2. The method according to claim 1, characterized in that immediately after the radiation on the missile launcher commands to emit a signal simulating a radar signal, the protected radar is turned off. 3. A radar complex for protecting radar from PRR, containing a radar for detecting targets, a missile control station, on-board missile defense equipment, and the missile control center includes guidance radar, a computing device, a tracking power drive, a transmitting device, an antenna device, and on-board equipment SAM contains an antenna SAM, a radio receiver of the guidance channel of the missiles, an orientation and control system for missiles, while the output of the radar guidance is connected to the input of the computer, the output of which is connected to the control input main drive, which is mechanically connected to the antenna device, the output of the transmitting device is connected to the input of the antenna device, the antenna of the SAM is connected to the input of the radio receiver of the guidance channel of the missiles, the outputs of which are connected to the orientation and control system of the missiles, characterized in that the output of the synchronization pulses Target detection radar, an object recognition device, the input of which is connected to the information output of the target detection radar, and the output - with the guidance radar input, the device is configured In order to emit emitting signals, the first input of which is connected to the output of the object recognition device, and the second input is the output of synchronization pulses of the radar for detecting targets, the second group of outputs of the radio-receiving device of the guidance channel of the SAM, the transmitter of the simulating signals, the inputs of which are connected with this group of outputs, and an antenna, the input of which is connected to the output of the transmitter of simulating signals.

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