Method for protection of radar against antiradar missiles and radar complex for its realization

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 Dr-arm, from the radar to the anti-aircraft missile Dr-aacm and from the anti-aircraft missile to the antiradar missile Daacm-acm, and at the time moments leading the moments of radiation of the radar sounding signal by value t=(Dr-aacm+Daacm-arm-Dr-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

 

The invention relates to a method of protecting an active radar station (radar) from anti-radar missiles (PI), navodaya by radiation.

The known method and device protection radar, conducting survey zones by radiation probing signals from the PI, based on the distraction of the PI with the help of simulators traps. For example, the known technical solution is the way to protect the radar from the PI and device for its implementation for U.S. patent No. 4433333 based on simulation of radiation radar fixed by the Directors of false signals (PLC), located at certain distances from each other and from the protected radar. While the PI moves in the direction of the energy system center RLS-RLS shifted relatively PLC, and with respect to the radar, as a result you receive the bias of its guidance on the radar and on the PLC. The disadvantage of these method and device is that a necessary condition for the operation of the system is the proximity of the host PLC to protect the radar, so that the guidance system of the PI could not resolve the spatial radiation sources. This leads to the fact that at sufficiently powerful martial charge PI high probability of protection of radar and PLC can not be provided. In addition, a necessary condition for reliable protection radar is the excess of the radiation power PLC on the radar in all hazardous areas, that is almost impossible to implement.

There is also known a method and a device protection radar, based on the use of rocket-trap (patent RF №2153684), in which the simulator radiation radar onboard missiles in the direction of the PI. The disadvantage of this method and device is that they are only functional in combination with the off the radar. Otherwise, the perturbation in the path PI is created only at the time of the missile trap. At the end of the rocket flight traps trajectory PI is again installed in the direction of the station.

The closest solution to the claimed invention to the technical essence is a way of protecting the radar carrying out radiation probing signals from the PI, which consists in the detection of PI, hover over it with the missiles and the destruction of PI by detonation of the warhead missiles (Tippin V.N., Weitzel VA, Radio control, “Sov. radio”, 1962, p.131-142). This can be used as missiles, navodaya command from the acquisition radar (Tippin V.N., Weitzel VA, Radio control, “Sov. radio”, 1962, s.89-141), and homing missiles (Krynicki H., guidance System, “engineering”, 1970, pp.42-73).

The known method is implemented by a device, which is a complex consisting of radar detection, control missiles and onboard equipment missiles (Tippin V.N., Ve is the purpose of VA, Radio Control, “Sov. radio”, 1962, s, RES). The block diagram of the complex is depicted in figure 1.

The complex contains radar target detection 1, item management missiles 2, the onboard apparatus 3 missiles, and control missiles 2 includes the acquisition radar 4, the counting-critical device 5, the tracking actuator 6, a transmitter 7, the antenna device 8, and on-Board equipment missiles 3 contains the antenna missiles 9, a receiving device channel missile guidance 10, system guidance and control of missiles 11. The yield of radar target detection 1 connected to the input of the acquisition radar 4, the output of the acquisition radar 4 is connected to the input of the counting-casting device 5, the output of which is connected with the control input of the tracking actuator 6, which, in turn, mechanically connected to the antenna device 8. The output of the transmitting device 7 is connected to the input of an antenna device 8. Antenna missiles 9 is connected with the input of the receiver channel missile guidance 10, the outputs of which are connected with system guidance and control of missiles 11, and channel connections missile guidance 10 system guidance and control of missiles 11 not less than three.

The complex operates as follows. Radar target detection 1 provides an overview of a given area of space by probing radiation and reception of reflected signal is. Upon detection of the purpose of its coordinates as the target passed in the acquisition radar 4 control missiles 2. Using the counting-casting device 5 target coordinates are specified, and in accordance with them through the tracking actuator 6 antenna device 8 to control missiles 2 turns in the direction of the goal. This ravesignal area pattern of the beam generated by the antenna device 8, is aimed at the target. In ravesignal zone moves missiles. In the process of motion control missiles signal emitted from the antenna device 8, is received by the antenna missiles 9 and enters the radio receiver channel missile guidance 10, in which the error signals missile guidance, i.e. the signals proportional to deviations in the direction of the movement of missiles from the direction ravesignal zone of the beam. These signals are fed to the system guidance and control of missiles 9, where in accordance with the position of the rudders Suhr changes in the direction of decreasing error pointing.

The disadvantage of this method is not sufficiently high reliability defeat PI antiaircraft guided missile. This is explained in the following. In the process of aiming at a moving target missiles constantly adjusts the direction of its movement. However due to the finiteness of the speed of the equipment is istemi guidance and control of missiles, limited opportunities missile loading and other factors (Reference officer air defence, M, “Military publishing house, 1987, str) arise dynamic pointing errors. At a high enough speed PI dynamic errors may be so large that happens breakdown process guidance and miss missiles.

Solved problem (effect), therefore, is to reduce dynamic errors missile guidance to the PI.

This technical result is achieved in that in a known way to protect the radar from the PI, including radiation probing signals, detection of PI, guidance missiles on the PI, the destruction of PI by detonation of the warhead missiles, according to the invention, the guidance missiles, at least during the time immediately preceding the detonation of the warhead missiles, produced by the trajectory passing in the vicinity of an imaginary line connecting PI and radars constantly determine the distance from the radar to the PI DRadar-PIfrom radar to missile DRadar-Suhrand from missiles to PI DSuhr-PIand at times, leading moments of the radiation probing radar signal by the value of Δt=(DRadar-Suhr+DSuhr-PI-DRadar-PI)/C, where C is the speed of light, with the radar on the missile issue commands to the radiation signal to produce a signal of the station.

This technical cut ltat is achieved by the fact that directly after radiation missiles signal to produce a signal of the protected radar, carry off the protected radar.

This technical result is also achieved by the fact that in complex protect the radar from the PI containing radar target detection, control missiles, onboard equipment missiles, and control of missiles includes the acquisition radar, the counting-solver, a tracking actuator, a transmitter, antenna device, and on-Board equipment of the SAM contains the antenna missiles, radio receiver channel missile guidance system, guidance and control of missiles with the radar pointing connected to the input of the counting-casting device, the output of which is connected with the control input of the servo actuator that is mechanically connected to the antenna device, the output of the transmitting device connected to the input of the antenna device, the antenna missiles are connected with the input of the receiver channel missile guidance, the outputs of which are connected with system guidance and control of missiles, according to the invention, the entered output pulses synchronized radar target detection, object recognition, the input of which is connected to the information output of the radar target detection, and the output with the input of the acquisition radar, a device for the formation of teams for the radiation to produce a signal which, first input connected to the output device object recognition, and the second input - output synchronization signals, radar target detection, onboard equipment missiles entered the second group of outputs of the radio receiver channel missile guidance, the transmitter simulating signals, the inputs of which are connected with 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 protection radar from the PI is as follows (figure 2). The guidance of the PI on the radar is the radar radiation, which in the process produces the inspection area while emitting probe and receiving the reflected signals. After the discovery of the PI shall start missiles. Detection and recognition of the PI can be made of the protected radar, which gives the coordinates of the PI as target designation radar guidance. The trajectory of the missile is chosen such that the missiles, at least during the time immediately preceding the undermining of its warhead, was in sector guidance of the PI. This guidance missiles during this time carried out on a trajectory that passes in the vicinity of an imaginary line connecting PI and protect radars. On command from the protected radar missiles include a transmitter emitting a signal simulating a sounding signal RLS. The time of issuance of whom is NDI to switch on the transmitter is chosen such to the PI signal with missiles came simultaneously with the excitation signal of the protected radar. For this purpose, the radiation signal to switch on the transmitter missiles produced ahead of the probing signal radar-size Δt=(DRadar-Suhr+DSuhr-PI-DRadar-PI)/s, where DRadar-PIDRadar-Suhr,DSuhr-PIthe distances from the radar to the PI from the radar to the missile from the missile to the PI, respectively. When the angular misalignment directions on the protected radar and missile relative to the PI is that they both are in the sector guidance of the PI, the rate of PI is adjusted. While the PI moves in the direction of the energy system center Suhr-radar, i.e. the rate of PI approaches the rate for missiles. It is known that the error of aiming missiles at the target are determined by the dynamic errors resulting from processing management system SAMS control inputs from the acquisition radar (or from the head homing to homing missiles that track the movement of the target (Reference officer air defence, M, “Military publishing house, 1987, str). Because of the extremity of the performance management system SAMS, as well as limited opportunities missiles overload dynamic errors can reach values at which is the breakdown of the guidance process and miss the missiles. The approach of path PI to the counter with a SAM rate reduces the value of the maneuver the missile, required to track her movements PI, and hence, decrease and dynamic pointing errors. Thus is achieved the stated technical result.

To increase the reliability retargeting PI Suhr directly after radiation from the protected radar team at SAMS on the radiation signal to produce a signal RLS, you can disable the protected radar.

The invention is illustrated by the following drawings.

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

Figure 2 - illustration of the proposed method of missile guidance on PI;

Figure 3 - block diagram of the inventive radar system;

4 is a block diagram of radar target detection;

5 is a block diagram of the device forming teams for simulating radiation signals;

6 is a block diagram of a receiver channel missile guidance.

Radar system that implements the proposed method (figure 3), contains radar target detection 1, item management missiles 2, the onboard apparatus 3 missiles, as well as the recognition device object 18, the forming device commands to the radiation simulating signal 19, the data output of the radar target detection 1 is connected to the input recognition device 18, the output of which is connected to the input of the control missiles 2 and to the first input of the device forming teams for simulating radiation is of Ignatov 19, and the output pulses synchronized radar target detection 1 is connected with the second input device formation on radiation simulating signal 19, and the control missiles 2 includes the acquisition radar 4, the counting-critical device 5, the tracking actuator 6, a transmitter 7, the antenna device 8, and the output of the acquisition radar 4 is connected to the input of the counting-casting device 5, the output of which is connected with the control input of the tracking actuator 6, which is mechanically connected to the antenna device 8, the output of the transmitting device 7 is connected to the input of an antenna device 8 airborne equipment Suhr contains the antenna missiles 9, a receiving device channel missile guidance 10, system guidance and control of missiles 11, the transmitter simulating signals 30, the antenna 31 and the antenna missiles 9 is connected with the input of the receiver channel missile guidance 10, the outputs of which are connected with system guidance and control of missiles 11, the second group of outputs of the radio receiver channel missile guidance 10 is connected to a cascaded transmitter simulating signals 30 and the antenna 31, and the number of links a receiving device 10 with the transmitter 30 is determined by the number of controlled parameters of the transmitter 30.

Radar target detection 1 (Theoretical fundamentals of radar. Ed. W is rmana AD, M., “Soviet radio”, 1970, str) includes sequentially the United synchronizer 12, a transmitter 13, the antenna switch 14, a receiver 15, the indicator device 16 and the antenna 17, the information input/output which is connected to the input/output antenna switch 14, and a coordinate output to the second input of the indicator device 16 (figure 4).

The device object recognition 18 built well-known scheme, described, for example, in the book: Nebben VG Methods and techniques of radar recognition. - M.: Radio and communication, 1984, p.30.

The forming device commands to the radiation simulating signals 19 contains serially connected memory 20, the transmitter 21, a comparator 22, a transmitter 23 teams and the antenna 24 (figure 5).

Radio receiver channel missile guidance 10 is a known device control channel Suhr (Tippin V.N., Weitzel VA, Radio control, “Sov. radio”, 1961, s-431). It contains the receiver 25 and connected to the output of the decoders control commands 26 and 27 with cascaded with them demodulators commands 28 and 29, respectively, and the blocks 26 and 28 are decoders and demodulators command management system guidance and control of missiles 11, and the blocks 27 and 29 - decoders and demodulators command control transmitter simulating signals 30 (Fig.).

The complex operates as follows. Radar target detection 1 provides an overview and detection in a given area of space and for recognition by the Recognizer objects 18 anti-radar missiles gives its coordinates in the acquisition radar 4 control missiles 2 and the memory device 20 forming teams for the radiation simulating signals 19. In the memory device 20 records the coordinates of the points of observation radar 1. The coordinates of PI are served next to the accounts-critical device 5. Using the tracking actuator 6 antenna device 8 to control missiles 2 in accordance with the adjusted coordinates obtained from the counting-casting device 5 takes place in the direction of the PI. The transmitting device 7 operates continuously. Ravesignal area pattern of the beam generated by the antenna device 8, is aimed at the PI. To ensure finding the trajectory of missiles in close proximity to an imaginary line connecting PI and radar control missiles have 2 near radar target detection 1. Is start of SAMS. Missiles moving in ravesignal zone. Since the acquisition radar carries out constant monitoring of the PI, ravesignal area also tracks its movement. In the process of motion control missiles si is cash, radiated antenna device 8 to control missiles 2, is received by the antenna missiles 9 and enters the radio receiver channel missile guidance 10, in which the error signals missile guidance. These signals are fed to the system guidance and control of missiles 11, where the control signals by the position of the rudders missiles in the direction of decreasing error guidance. Radar target detection 1 performs detection of the SAM, the coordinates of which after its recognition by the recognition device objects 18 are received in the memory device 20 forming teams for the radiation simulating signals 19. Thus, in the memory 20 are recorded coordinates of the radar, the PI and missiles. Using these coordinates, the computer 21 determines the distance from the radar to the PI DRadar-PIfrom radar to missile DRadar-Suhrand from missiles to PI DSuhr-PIand calculates the amount of time ahead of time of radiation of the probing signal radar Δt=(DRadar-Suhr+DSuhr-PI-DRadar-PI)/s In the comparator 22 compares the values Δt with the time remaining to the radiation of the probing signal radar 1. This is done using a pulse synchronizer 12, coming from the radar target detection 1. When comparing recorded and previously known apparatus of the delay, the value of that increased value is the Δ t. At the time of coincidence of the times included transmitter commands 23 and through the antenna 24 in the form of a high frequency signal is radiated switch on the transmitter simulating signals 30. The command is received by the antenna 9 missiles receiving device 10 is converted into a control signal, which turns on the transmitter simulating signals 30. Signal simulating a signal radar target detection 1 via the antenna 31 is radiated into space. The probing signal radar target detection 1 and the signal from the missile simulating radar waves reach the PI at the same time. There is a change of direction of the PI in the direction of the energy system centre missiles, radar, resulting trajectory PI approaches the counter with a SAM rate. Changes in the trajectory of the PI needed to get back on the size of the maneuver missiles is reduced, and therefore, decreases the dynamic error of missile guidance. Thus is achieved the stated technical result.

1. The way to protect the radar station (radar) from anti-radar missiles (PIS), including radiation probing signals, detection of PI, mouse anti-aircraft guided missiles (SAMS) on the PI, the destruction of PI by detonation of the warhead missiles, characterized in that the guidance missiles, at least for a time, directly predictious is the detonation of the warhead missiles, produce trajectories that pass in the vicinity of an imaginary line connecting PI and radars constantly determine the distance from the radar to the PI DRadar-PIfrom radar to missile DRadar-Suhrand from missiles to PI DSuhr-PIand at times, leading moments of the radiation probing radar signal by the value of Δt=(DRadar-Suhr+DSuhr-PI-DRadar-PI)/C, where C is the speed of light, with the radar on the missile issue commands to the radiation signal to produce a signal of the station.

2. The method according to claim 1, characterized in that immediately after radiation missile command on the radiation signal to produce a signal RLS, carry off the protected radar.

3. Radar complex protect the radar from the PI containing radar target detection, control missiles, onboard equipment missiles, and control of missiles includes the acquisition radar, the counting-solver, a tracking actuator, a transmitter, antenna device, and on-Board equipment of the SAM contains the antenna missiles, radio receiver channel missile guidance system, guidance and control of missiles with the radar pointing connected to the input of the counting-casting device, the output of which is connected with the control input of the servo actuator that is mechanically connected to the antenna device, the output of the transmitting device, Saedinenie entrance antenna device, antenna missiles are connected with the input of the receiver channel missile guidance, the outputs of which are connected with system guidance and control of missiles, characterized in that the entered output pulses synchronized radar target detection, object recognition, the input of which is connected to the information output of the radar target detection, and the output with the input of the acquisition radar, the forming device commands for simulating radiation signals, the first input connected to the output device object recognition, and the second input - output synchronization signals, radar target detection, onboard equipment missiles entered the second group of outputs of the radio receiver channel missile guidance, the transmitter simulating signals, the inputs of which are connected with this group of outputs, and the antenna, the input of which is connected to the output of the transmitter simulating signals.



 

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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 Dr-arm, from the radar to the anti-aircraft missile Dr-aacm and from the anti-aircraft missile to the antiradar missile Daacm-acm, and at the time moments leading the moments of radiation of the radar sounding signal by value t=(Dr-aacm+Daacm-arm-Dr-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

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