RU2581704C1 - Method and device for protection of radar station - Google Patents

Abstract

FIELD: weapons and ammunition.

SUBSTANCE: proposed invention relates to weapons, particularly to protection of mobile ground-based radar stations against anti-radar missiles (PRR) by means of assignment of distracting interfering transmitters. Method consists in installation directly at radar station or near it at the distance not less than one radius of hitting warhead of anti-radar missiles, of an additional radiation source emitting interfering signals at simultaneous deactivation of the radar station; herewith radar signals are used to calculate the time of missile approach to the position of radar station, over the additional radiation source to the moment of missile approach an aerosol-dipolar cloud is formed with dimensions at plane equal to at least 15×15 metres so the lower edge of the cloud is located on the ground level. Proposed device comprises a radar station, unit for connection of additional radiator, additional radiation source, unit for calculating the start-up time of grenades, grenade starting unit, launchers with aerosol-dipole grenades, connected to each other in a certain manner.

EFFECT: high probability of protecting radar station against anti-radar missiles.

2 cl, 2 dwg

Description

The claimed inventions relate to the field of armaments, in particular to the protection of mobile ground-based radar stations (radar) from anti-radar missiles (PRR) by the installation of distracting jamming transmitters.

Radars are objects that have an additional unmasking sign - radar radiation, therefore radars are susceptible to attacks of a specific type of high-precision weapon - PRR equipped with homing heads (GOS), which are built on the use of this unmasking sign.

Modern PRR, for example, the main US Air Force missile AGM-88 "HARM", has a GOS, which is a radio intelligence station. After capturing the target of the GOS, the missile is launched from the side of the aircraft and flies to the radar with a climb on a given path [1]. In the target area, the missile begins to dive on the radar at an angle of 50 ... 60 °. At this stage, a remote contactless fuse is turned on, which provides for the detonation of a fragmentation warhead at a given height in the range of 10 ... 20 m above the target so that the stream of heavy fragments optimally affects the entire combat position of the radar. If the non-contact fuse does not fire, the warhead is blown up by the contact fuse when the PRR hits the ground.

A known method of protecting the radar from the PRR by turning the antenna away from the direction to the PRR to illuminate the PRR radiation reflected from a nearby screen of metal mesh [2]. A cloud of dipole reflectors created by the rupture of a specially launched ammunition [1] can also be used as such a reflective screen. If such a shift does not exceed the threshold of angular resolution of the GPR PRR, then the rocket will reorient to such a screen.

There are also ways to disrupt the attack of PRR by initiating the premature operation of a non-contact fuse (radio or laser) at the final stage of flight. They are divided into two groups. The first group includes methods of emitting counterpropagating active interference in the direction of approach of the PRR. An instrument of such interference is an interference station located next to the radar, which is a repeater of the signal of a non-contact rocket fuse [3] and distorts the reflected signal of the fuse generator with its radiation. This method may be ineffective when encoding a fuse signal. The second group of methods for influencing non-contact fuses is based on setting an aerosol-dipole cloud simulating a target on the flight path of a PRR [1, 4]. A scheme for implementing the method of premature operation of a non-contact fuse by setting an aerosol-dipole cloud on the flight path of a rocket is presented in [4].

Having received a signal reflected from the cloud, a non-contact fuse issues a command to detonate the warhead of the PRR at an altitude of 10 ... 20 m above the cloud. In this case, the radar remains outside the limits of the main stream of fragments. The described method is convenient in that it does not depend on the noise immunity of the rocket fuse, but at present there are techniques for isolating such a cloud as interference.

In non-contact fuses of ammunition, including PRR, the basic scheme has found wide application. In it, the transmitting and receiving systems of a non-contact fuse are separated by a base distance B [5]. The transmitting optical system focuses a narrow beam of rays, which intersects with the field of view of the receiving optical system and forms a sensitivity zone. When the PRR approaches the reflecting surface, the overlapping area of the transmitting and reflected beams will change from zero at a point corresponding to the height H ₁ , reach a certain maximum value (points H ₂ , H _cf , H ₃ ) and then decrease again to zero at the point H ₄ . The stream reflected from the surface enters the photodetector, where it is converted into an electrical signal. The graph [5] below shows the nature of the signal change when the PRR approaches the reflecting surface, which has different reflection coefficients ρ, and ρ ₂ > ρ ₁ . The fuse is triggered when the reflected radiation reaches a threshold value of P _then , in other words, at a given distance from the object.

To prevent false alarms in the cloud, the PRR fuse is made dual-channel. It has a primary laser channel and an additional one. Both channels are built according to the basic scheme. Each channel contains its own laser generator and its own photodetector of reflected radiation, mutually oriented so that the reflected radiation of the generator is perceived by the photodetector when a reflecting object appears at a given distance from the rocket. The main laser channel is designed to issue a command to operate the warhead. An additional channel is introduced for the selection of aerosol interference. It is more sensitive than the main one, and has a wider observable base. An additional channel is triggered first by an extended lockable object (in this case, by a cloud) and blocks the main channel from triggering through it until the rocket completely passes through the cloud. The main channel is configured for the appearance of an object that rises sharply (by several meters) above the background recorded by the additional channel. These two-channel non-contact laser fuses are equipped with HARM, ALARM missiles and almost all other modern PRRs.

The closest in technical essence to the claimed method is a method of installing next to the radar one or more additional emitters, in frequency and structure of the radiation simulating a radar signal [6], adopted as a prototype. An additional emitter is located at a distance of about 200 m from the station. This distance is determined by the effective range of the fragments generated by undermining the warhead of the PRR.

When an attacking PRR is detected, the radar is turned off, and the additional emitter starts to work. If the angular resolution of the GOS missile does not allow, at the time of such a switch, to fix a sharp change in the coordinates of the radiation source, then the PRR will reorient and attack the additional emitter.

The closest in technical essence to the claimed device is a device for protecting a group of radar stations from anti-radar missiles [6], taken as a prototype, structural and functional diagram, which is presented in FIG. 1, where the following notation is accepted:

1 ... 1.M - protected radar;

2 - control unit for changing frequencies and viewing the space;

3 ... 3.N - additional sources;

7 ... 7.K - sensors.

A device for protecting a group of radars from PRR, consisting of M≥2 radar stations, characterized in that they additionally introduce a control unit, N additional radiation sources, K sensors, while M outputs of the control unit are connected to M radars, the outputs of K sensors are connected to K the inputs of the control unit, each of the additional radiation sources is located at a direct line of sight from each radar, but not less than the distance equal to the radius of destruction of the warhead of the PRR.

The disadvantage of prototypes is the difficulty of meeting the requirements for installing an additional emitter. They are contradictory. On the one hand, it must be brought to a sufficient range so that heavy high-speed fragments of the warhead of the rocket do not hit the radar when it is air-blasted over an additional source. On the other hand, radar reconnaissance stations of GOS of new modifications of the PRR have an increased angular resolution that allows you to record the change in the coordinates of the source of radar radiation and, in accordance with the established algorithm, continue using the onboard inertial navigation system to “recall” the old target, i.e. on the radar.

The technical result of the claimed inventions is to increase the likelihood of radar protection from PRR.

To achieve a technical result, a method for protecting a radar station from anti-radar missiles is claimed, including installing at a position of a radar station, at a distance from it not less than the radius of destruction of the warhead of anti-radar missiles, an additional radiation source, radiation by an additional radiation source of distracting signals while turning off the radar station, according to the invention according to the signals of the radar station calculate the time of flight of the rocket to p zitsii station over an additional transmitter to the moment the missile is formed of approach aerosol cloud-dipole measurement routine plane is not less than 15 × 15 meters so that the lower edge of the cloud located at ground level.

Also, to solve the problem, a device for protecting a radar station from anti-radar missiles is claimed, comprising an additional emitter connected through an additional emitter switching unit to a radar station, according to the invention, a grenade launch unit is introduced into it, N outputs of which are connected to electric ignition circuits of launching aerosol-dipole grenades, charged in the trunks of launchers, a unit for calculating the launch time of grenades, the input of which is connected to the second output of the radar, and the output - with the input of grenade launching unit.

The implementation of the method consists in the fact that in order to increase the likelihood of protecting the radar from PRS at the stage of rocket approach, an extended aerosol-dipole cloud is placed directly above the additional radiator, the lower edge of which lies at ground level. When approaching the PRR, reoriented to an additional emitter, the additional channel of a non-contact fuse first perceives the cloud as an obstacle and blocks the operation of the main channel. A rocket that enters the cloud sticks into the ground without being triggered and is blown up by an impact fuse. Ground-based detonation of a missile’s warhead at a previously prepared (planed) site of the position dramatically reduces the number and radius of flight of fragments, and therefore the threat of radar damage, allows more than halving the distance between the radar and the additional emitter, which, in turn, , provides an increase in the probability of reorientation of the GOS missile to it.

The technical result is achieved by the synchronized joint interfering action of an additional emitter on the GPR PRS and a system for remotely placing aerosol-dipole curtains on a PRR fuse, which allows to achieve a qualitatively new effect - removing PRR from the radar to an additional radiator, eliminating air blasting of PRR and reducing the radius of damage of PRR due to her ground blast.

In FIG. 2 shows a structural diagram of the inventive protection device that implements the described method, where the following notation:

1 - protected radar;

2 - block enable additional emitter;

3 - additional emitter;

4 - unit for calculating the launch time of grenades;

5 - grenade launch unit;

6 - launchers with aerosol-dipole grenades.

The inventive device contains a protected radar 1, the output of which is connected in series with the power unit of the additional emitter 2 and the additional emitter 3, the other output of the radar 1 is connected in series with the unit for calculating the launch time of grenades 4 and the launch unit of grenades 5, Ν (N≥1) of the outputs of which are connected with N inputs of launchers with aerosol-dipole grenades 6.

The device operates as follows.

There are methods for recognizing radar attacks namely PRR [7, 8]. When such an attack is registered, a command is issued from radar 1 to the input of block 2, located at a distance from radar 1, larger than the radius of the destruction of the station by fragments during air blasting of the warhead of the PRR (about 200 m). From the output of block 2, power is supplied to turn on the emitter 3. The output to the radiation mode of the emitter 3 is synchronized with the moment the radar 1 stops operating on radiation. If the missile seeker registers the radar 1 and the emitter 3 in one common element of angular resolution, then the PRR continues pointing to the emitter 3.

Simultaneously with the inclusion of the emitter 3 from the radar 1 to the input of block 4 receives a sign of attack PRR and information about the range to the PRR and its flight speed. In block 4, on the basis of the trajectory data of the missile’s flight, the time for shooting aerosol-forming grenades is calculated, which, when ruptured, should form a dense, extended aerosol-dipole formation at the time of the launch of the missile. If aerosol-forming grenades are fired earlier than necessary, the wind can blow the cloud to the side, if later than necessary, the cloud will not have time to form. Radar 1 determines the distance to the approaching rocket D and its speed V, and the time remaining before the launch of the rocket to the target is calculated accordingly: t = D / V. When the estimated time of launch of the rocket is compared with the known predetermined time of setting the curtain, a command is sent to the input of block 5 from the output of block 4. Current pulses from the output of block 5 are fed into the electric ignition circuits of the aerosol-dipole grenades charged into the launchers 6. When the grenade breaks, they form over emitter 3 aerosol-dipole cloud with dimensions in the planned plane of not less than 15 × 15 meters (the dimensions of the aerosol cloud in the planned plane are selected on the basis that it simulates the dimensions of the protected object), moreover, the elevation angles of the launchers 6 are selected so that the lower edge of the cloud lies at ground level. When approaching the PRR, the additional channel of the laser fuse first detects the appearance of an extended object, identifies it as an interference aerosol-dipole cloud and blocks the operation of the main channel. A rocket enters the cloud and flies in it to the ground, after which a fuse blows. In a ground-based explosion of a PRR in a section bunched from the side of radar 1, the fragments are delayed by the earthen rampart and do not reach radar 1. In this way, the distance between radar 1 and emitter 3 can be reduced from 200 ... 300 to 50 ... 80 m. Calculations show that this is enough so that the radar 1 and emitter 3 are within the same element of the angular resolution of the GOS of modern PRS, and after turning off the station, the rocket deviated from it to the emitter 3.

The inventive protection device can be implemented:

2 - an additional emitter switching unit can be implemented on control boards based on microcontrollers (processors), including a high-performance x51-compatible core and Flash memory [9, 10, 11];

3 - an additional radiator can be implemented on the basis of a radiator, the frequency and structure of the radiation of which imitate radar signals;

4 - a unit for calculating the launch time of grenades can be implemented on the basis of a computing device such as a calculating and decisive device used in fire control systems for artillery weapons;

5 - the grenade launch unit can be implemented on transistor switches under the control of a microcontroller [9, 10, 11];

6 - launchers with aerosol-dipole grenades can be implemented on the basis of system 902 with aerosol-forming ammunition type 3D17 and ammunition with combined equipment of type 3D17M.

Information sources

1. E.G. Borisov, V.I. Evdokimov. Precision weapons and the fight against it. - M.: Lan, 2013, pp. 63-72, 430-431, 319-326, 437.

2. RF patent №2210089, G01S 7/38, dated 12.02.2001.

3. US patent No. 3806925, G01S 7/36, H04K 3/00 from 04/23/1974.

4. RF patent No. 2261457, G01S 7/36, dated 03.11.2003.

5. V.N. Sidorin. Lasers in aviation. Slash. - M.- L .: 17 Military publishing house, 1982, p. 160.

6. RF patent No. 2099734, G01S 7/38, dated 23.02.1996.

7. RF patent No. 2095822, G01S 13/02, dated October 31, 1995.

8. RF patent No. 2097782, G01S 13/02, dated 05.21.1996.

9. Ball Steward R. Analog interfaces of microcontrollers. M.: Dodeka-XX1 Publishing House, 2007, p. 360.

10. Olsson G. Digital automation and control systems. Olsson G., Piani J. St. Petersburg: Nevsky Dialect, 2001, p. 557.

11. http.//www.altera.ru/cgi-bin/go?38 - ALTERA electronic components.

Claims (2)

1. A method of protecting a radar station from anti-radar missiles, including installing at a position of a radar station, at a distance from it not less than the radius of destruction of the warhead of anti-radar missiles, an additional radiation source, radiation by an additional radiation source of distracting signals while turning off the radar station, characterized in that the signals of the radar station calculate the time of the rocket's approach to the station’s position, above the additional emitter to m The approach moment of the rocket is formed by an aerosol-dipole cloud with dimensions in the planned plane of at least 15 × 15 meters so that the lower edge of the cloud is at ground level. 2. A device for protecting a radar station from anti-radar missiles, comprising an additional emitter connected through an additional emitter switching unit to a radar station, characterized in that a grenade launch unit is introduced into it, N outputs of which are connected to electrically ignition launch chains of aerosol-dipole grenades charged in trunks of launchers, a unit for calculating the launch time of grenades, the input of which is connected to the second output of the radar, and the output is with the input of the launch unit of grenades.

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