RU2227892C1 - Space-air defense complex - Google Patents

Abstract

FIELD: defensive systems, in particular, antiaircraft guided missile systems. SUBSTANCE: the engine of the complex interceptor missile is made in the form of a conical target including a nuclear matter initiated by means of laser radiation for production of a thermonuclear reaction and a plasmoid for its ejection from the hole made in the vertex of the cone of the conical target, in the axis of the intercepter missile or at an angle to it. The warhead fuse is made in the form of four mutually perpendicular in pairs of conical targets containing an explosive for its initiation by means of laser radiation from the hole made in the vertex of the cone of the conical target and collapse in the space between the other cones. EFFECT: enhanced zone and probability of destruction of air, missile and space targets. 1 dwg

Description

The complex air defense missile defense (PVRKO) refers to defensive systems, and more specifically to anti-aircraft missile systems (SAM).

The main objective of the proposed complex is to increase the area and probability of destruction of air, missile and some space targets in comparison with the air defense systems currently used and being developed.

Analogs of the proposed complex are the S-300P, S-300V, S-300PMU1 (2), Antey-2500, Hawk, and Patriot air defense systems (Vasilin N.Ya., Gurinovich A.L. Anti-aircraft missile systems. Minsk , LLC Potpourri, 2002.), A-135 missile defense system (Krasnaya Zvezda newspaper, N 108 of 07/21/2002), G-PALZ missile defense system, Thaad air defense system (US space policy and space forces. Moscow, Diplomatic Academy of the Ministry of Foreign Affairs of the Russian Federation, 2002).

The proposed complex and most of the above analogues contain the following common parts: radars for space and missile guidance, launchers, interceptor missiles, a command and control station, a power plant, etc.

The PVRKO complex should hit the following classes of targets:

1. Aerial (aerodynamic) targets: airplanes with a flight altitude of up to 30 km at a range of up to 800 km, including Stealth aircraft (invisible in a certain frequency range), active jammers, unmanned aerial vehicles (UAVs) with a flight altitude from 300 m, planning Wallall bombs, helicopters with a flight height of 100 m, strategic and tactical cruise missiles with a flight height of 100 m.

2. Missile (ballistic) targets: single warheads with a speed of up to 5 km / s, complex ballistic targets (SBC) (the target includes up to 30 warheads, up to 20 false targets, a large number of dipole reflector-interference), global planning warheads with individual guidance, operational-tactical missiles such as Pershing, Lance, Scud, Sram at a speed of up to 3 km / s.

3. Space targets: satellites in geostationary and highly elliptical orbits (visible by the complex or according to the SPRN missile attack warning system or SKKP space control system), reusable Shuttle-type spacecraft, Diamond Is system (detection and tracking system ballistic missiles (BR) and warheads (MS) with an orbit height of up to 1800 km with the number of spacecraft (SC) - 50, the Diamond Pebbles system (small missile interceptor system) with an orbit height of up to 400 km When the amount of CA to 1000.

The proposed complex can be used to destroy ground and surface targets for target designation.

The following list of types of targets requires for the effective destruction of various types of interceptor missiles.

The complex should hit the above targets in all weather conditions, including rain, fog, snowfall, oncoming courses, courses with a parameter of up to 100 m and when shooting after.

The complex should be noise immunity: work in conditions of active and passive interference.

The possibility of hitting the above targets, increasing the zone and the likelihood of hitting them in the proposed complex is achieved by using an interceptor missile with a new rocket engine (application 2002110167 "High-speed nuclear missile engine" with a priority of 04/18/2002), with a new warhead (application 2001119261 " High-performance explosive device "with a priority of 07/12/2001) and an advanced dual-channel homing head (infrared and radar channel).

We give the principle of operation and characteristics of these fundamental differences of the complex. The RD rocket engine uses a conical target, from a hole in the apex of the cone which flies out along the axis of the rocket or at an angle to it at a high speed, a bunch of dense plasma formed as a result of thermonuclear synthesis of a small mass of target nuclear material under the action of laser radiation. In this case, the intranuclear energy of nuclear matter (light isotopes of hydrogen or helium) is converted into the kinetic energy of a dense plasma bunch, flying out of the target at high speed and creating engine thrust. In this case, the speed and deflection of the rocket can be changed by adjusting the period of departure of the clots. The deflection of the rocket in two planes is achieved by the departure of clots at an angle to the axis of the rocket. With a successive deviation, it is possible to create a rotation of the rocket around its axis, which stabilizes the position of the rocket in space. There is an increase in the initial (accelerating) speed of the rocket and a decrease in the final (before the defeat) speed. The method of guiding the rocket in the initial and middle sections of the trajectory is inertial-command, in the final section using the homing head.

The velocity of a plasma clot from a cone is 10 ⁵ m / s. The average value of the acceleration of the rocket for the period of departure of the clots is 130 m / s. The final speed and range of the missile in range depends on the stock of nuclear material (the number of conical targets). In one of the types of missiles, the specified reserve ensures the flight of the rocket to the height of the geostationary orbit (36,000 km).

The engine can mate with the rest of the various classes of rockets. The design of the engine is given in the application 2002110167. Thus, due to the new capabilities of the engine, the target area is significantly increased. At the same time, it is limited not by the reach of the rocket, but by the range of detection of the radar of sight and guidance.

The warhead of the warhead missile is a high-performance explosive device. The warhead consists of a fuse, a charge, a transforming layer of a safety-executive device.

The fuse for the warhead of the interceptor missile is made in the form of four conical targets, each of which has solid, smooth metal side walls (solid targets), is filled with explosive material enclosed in a conical polymer shell in the form of a mixture of deuterium with tritium or helium - 3 and has at the apex cone hole for the release of a plasma clot. The axes of each pair of cones are mutually perpendicular in space, and the holes of the vertices of the cones are adjacent to the common space between the cones.

Due to this design, the fuse is a two-stage compression of the explosive. At the first stage of compression, the following processes occur: when a laser pulse falls on the base of the cone, explosive adsorption occurs, it evaporates, and a reactive force arises, which creates shock waves, which, reflected from the walls of the cone, move to its apex and collapse in it. In this case, the explosive at the apex is compressed to such an extent that a thermonuclear regime of a “laser spark” arises, a primary plasma bunch is formed at the apex, which, under the action of a reactive force, flies out through a hole at the apex of the cone at high speed.

At the second stage of compression, the following processes take place: four escaped plasma bunches collide in the space between the cone vertices, while the degree of plasma compression increases significantly, and the temperature of the resulting secondary plasma bunch increases to a thermonuclear (10 ⁷ K), a “mode of ignition” of plasma arises, in a heat wave is formed in the charge (thermonuclear reaction wave), which propagates in the charge. The design dimensions of the fuse: the diameter of the base of the cone is 6 mm, the height of the cone is 7 mm, the diameter of the hole in the apex is 2 mm, the distance between the holes of the opposite cones is 4 mm.

The fuse of the warhead uses four pairwise mutually perpendicular conical targets, from the holes in the tops of the cones of which clots of compressed plasma fly out under the action of laser radiation and collapse in the space between the cones. Thus, two-stage compression of nuclear material is carried out.

As a result of two-stage compression, the temperature at the site of collapse of the bunch rises to the thermonuclear (10 ⁷ K) and propagates in the form of a heat wave in the charge. The charge is a spherical sector of nuclear material. Neutrons or protons emitted as a result of a thermonuclear reaction can be used in two ways, depending on the altitude of the target being hit:

- At altitudes of more than 30-40 km (where atmospheric gases are practically absent), neutrons or protons of a charge fly directly into the surrounding space (in the aperture angle of the nuclear material of the charge) and mechanically destroy the target. In this case, neutrons decay into particles after 3-5 seconds and do not reach the Earth, and protons, falling, are neutralized by the ionization layer of the atmosphere.

- At altitudes of less than 30-40 km (where 90% of the atmospheric mass is concentrated), neutrons and protons in the warhead charge are sent to its transforming layer, which is a fibrous composite, and cause cracks in the material of the layer. The occurrence, development and destruction of a crack is accompanied by acoustic emission. The pulses of this emission, merging, form a shock wave, which destroys the target. This ensures the environmentally friendly impact of warheads on the environment. The design of the warhead is given in the application 2001119261.

The TNT equivalent of warheads can vary depending on the mass of the charge and the gas pressure in it from a few kilograms to several megatons. With a warhead equivalent of 150 kt, its weight is 3 kg. Hence, the performance of the warhead is equal to 150 · 10 ^6/3 = 50 · 10 ⁶ . In 1961, a hydrogen bomb of the equivalent of 50 Mt and a mass of 24 tons was blown up at the Novaya Zemlya training ground (Secret Research. Analytical newspaper N1, Minsk, 2002). Hence, the performance of the hydrogen bomb 50 × 10 ^6/24 = 2.08 × 10 ^6. Thus, the performance of the proposed warhead is 50 · 10 ⁶ / 2.08 · 10 ⁶ ~ 25 times greater than the hydrogen bomb. Otherwise, with the same equivalent, the mass of the proposed warhead is 25 times less than the mass of a hydrogen bomb. This ratio makes it possible to concentrate a more powerful warhead on a rocket with the same mass load. In addition, due to the low weight and dimensions of warheads, its cassette design in the form of a large number of shells can be used. This warhead when flying shells is capable of hitting extended targets (SBC, Diamond Aes, Diamond Pebbles, etc.). In this case, individual shells are bred in space using a special ejection mechanism, and the detonated projectile is detonated using a radio fuse mounted on it. The specified radio fuse is a miniature radar that generates a signal detonation, for example, by the level of the reflected signal. More complex is the radio fuse, which generates a detonation signal at a certain position of the target in the radio beam of the fuse antenna. A Doppler radio fuse may be used in which Doppler frequency oscillations are emitted in the continuous mode, and a detonation signal is generated at a certain amplitude of oscillations of this frequency.

It should be emphasized that only the warhead cassette design with large equivalents of shells and a large number of them is capable of hitting the SBC today. At the same time, it is not necessary to select combat and false warheads and various kinds of interference, since when the proposed warhead is damaged, all parts of the SBC are destroyed.

The radius of a nuclear warhead’s destruction depends on its equivalent, the angle of warhead’s charge, and in the case of a warhead warhead, it also depends on the number of shells in the cartridge, and is chosen to provide compensation for missile guidance errors and significantly increase the probability of hitting a target.

The proposed complex, unlike analogues, is also intended to destroy some space targets. At the same time, space targets visible by the radar of the RLON survey and guidance are affected similarly to air and missile targets. To destroy space targets, invisible radars, namely, satellites in geostationary and highly elliptical orbits, as well as in orbits with a height of more than 1,500 km, target designation from SPRN and SKKP systems in the form of six or five elements of the orbit is used. According to the indicated data, the anticipated aiming point (the meeting point of the missile with the target) is calculated at the combat control point. Guidance missiles at the aiming point is carried out using a special guidance radar for high-flying targets of the RVC according to the method of guiding a missile through a radio beam. The initial (after launch) capture of a radio beam by a rocket is carried out as a result of the search for the RVC in the launch sector. The radio beam of the RVC is modulated in such a way that when the missile deviates from the direction of the radio beam, its receiving orientation device determines the error signal and generates the corresponding missile control commands received by the rocket engine through the MPS microprocessor system. In this case, the rocket is held in the center of the cross section of the radio beam. The indicated radio beam guidance is similar to the guidance of a Shrike type anti-radar missile. Radio beam guidance was implemented in the Adats air defense system (Canada) in the second guidance stage.

The movement of the RVC radio beam to the aiming point is carried out according to the flight task for this type of target. This task is stored in the MPS of the RVC and is adjusted for specific data of the rocket launch point and its meeting with the target.

When a radio beam is captured by a launched rocket, the radio beam and the rocket move together. After a few minutes (exactly indicated in the flight mission), on the final section of the rocket’s trajectory, on command from the RVC, the radar channel of the seeker’s homing head is turned on. The range of this channel is up to 500 km. The channel is capable of capturing a target ranging in size from 1 to 10 m. The performance of a flight task in time is controlled by the MPS RVC, which includes a timer that allows you to determine the time from the moment the rocket starts. When the target is captured by the GOS, rocket control is transferred to the GOS. In this case, the guidance of the rocket is carried out by the method of proportional approach. If during the longest flight time specified in the flight mission, near the estimated meeting point of the missile with the target, the GOS did not capture the target, then it is searched for by moving the radio beam in a spiral around the calculated meeting point.

In case of defeat of high-altitude space targets, a cassette warhead is used, in which the shells are equipped with a radio fuse. When the rocket approaches the target at a distance of about 200 m, which is determined by the radar channel of the GOS, projectiles are ejected from the cartridge into space, the radio fuse is blown up and, upon command from it, at a distance of about 50 m from the target, the shell is detonated. In this case, the target is struck by the flux of neutrons or protons. The principle of operation and the device of the radio fuse were given above. In the event of a missile, the projectile self-destructs.

It should be emphasized that only a new nuclear missile in combination with pointing it at the radio beam of the RVC and the use of radar seeker capable of defeating high-altitude space targets, invisible radar.

It should be noted that target designation from SPRN and SKKP for hitting space targets may not be necessary if lidar is used to detect and track high-flying targets, raised on an Avax-type aircraft to a height of about 10-12 km and so locked for 2-3 hours At the same time, the atmosphere above the lidar will not affect the propagation of lidar laser radiation, the absorption of radiation in space is insignificant, and long detection ranges (up to 40 thousand km) are provided.

The technical essence of the proposed complex is illustrated by the drawing, which presents a structural diagram of the complex with an indication of the composition and relationships of its parts.

The PVRKO complex consists of the following main parts:

1. The point of combat control PBU.

2. Radar survey and guidance RLON.

3. Lidar review and guidance for low-flying targets of the LSC.

4. Guidance radar for high-flying RVC targets.

5. Launchers PU.

6. Missile interceptors RP.

7. Equipment for data transmission and communication APDS.

8. Power plant ES.

The complex also includes other means of technical operation of the complex, indicated below.

PBU combat control point is intended for:

a) generalization and assessment of the aerospace situation in the area of the complex. This PBU action is performed according to data from various sources: RLON, LNTs, RVC, SPRN and SKKP systems, higher KP;

b) the appointment of targets for destruction, target allocation taking into account the priority of goals (based on an assessment of the degree of threat) and the appointment of a type of missile to hit a target;

c) the issuance of target designation based on the results of target distribution to the RLON, LNC, RVC and teams for the preparation of launchers;

d) exchange of information with RLON, LNTs, RVC, PU and a higher KP.

The PBU includes the following parts (see drawing): microprocessor system, combat control panel, all-round display, guidance display (with the results of the distribution), the combat readiness and technical condition of the complex, data and communications equipment. The information on the all-round display is displayed in the form of forms, including the target number, range, speed, flight direction, and recognition results.

The radar survey and guidance radar is a multifunctional radar designed for:

a) the detection and tracking of targets in the visibility zone, the capture of targets according to target designation data, including the setting of routes (trajectories), determining the type of targets (from trajectory data), determining the state of aerial targets (using the attached identification equipment);

b) guidance of interceptor missiles by transmitting commands on their board (speed control commands and missile deflection), turning on the seeker, detonating warheads (if necessary with a faulty seeker), receiving reports from the missile;

c) control of the launch of designated missiles, control of the seizure of targets of the SSC and RVC transferred to accompany them;

d) exchange of information with PBU, PU, LNC, RVC.

The RLON radio beam produces a line scan. The next time the beam passes through the angular direction on which the target or missile is located, it is detected, and with the next passes, it is taken for escort. At those moments when the beam is directed at the missile, missile control teams are transmitted over the radio link.

RLON is a three-coordinate coherent-pulse radar of the centimeter wave range with high energy potential. The RLON includes the following parts (see drawing): an antenna system of the PHAR type, a transmitting device, a receiving device, a noise immunity device, a microprocessor system, a visibility and guidance display, a control panel, and data and communication equipment.

The antenna system is located in four mutually perpendicular planes. Each plane (canvas) contains a transmitting headlamp and a receiving headlamp. The radio beam of the transmitting headlamp is electronically controlled from a microprocessor system. The angle of the radio beam solution is 1.5 ° * 1.5 °. The level of the side lobes is very low. The level of inclination of the headlamp plane to the horizon can vary by a small angle (about 3 °). When transporting the RLON, the headlamp canvases are folded. The deviation from the horizon of the radon antenna base bases, as well as launchers, is automatically taken into account by the microprocessor system by amending the elevation angle for the indicated deviation. This accounting is especially important when the complex operates on rough terrain and in winter. The viewing angle of each transmitting headlamp in azimuth + 45 ° - -45 °, in elevation 1-75 °. The diameter of the transmitting headlamp is 2-2.5 m, the receiving headlamp is 0.8-1 m.

The transmitting device contains a powerful generator of the centimeter wave range, operating at one of 120 fixed high frequencies. The generator performs an instantaneous (in 1 s) restructuring of the indicated frequency when active interference organized by the enemy appears and when a radar radar is captured by a radar. RLON is equipped with:

a) a warning device about the presence in the radio beam of an anti-radar missile and automatic transition to another high frequency;

b) the device of noise immunity, which detects the presence of active and passive interference, determines the coordinates of the directors of active interference, evaluates the interference situation and assigns the operating frequency of the generator, free from suppression by the enemy.

Devices a) and b) incorporate a local microprocessor.

The receiving device has a high sensitivity (up to 10 ^-13 W) and implements a digital method for moving circuit selection (SDC), digital methods for optimal (adaptive) processing of received signals. These digital methods, as well as automatic adjustment of the receiver and automatic acquisition of coordinates are carried out using a local microprocessor. Digital processing of the received signal and automatic acquisition of coordinates increases the accuracy of determining coordinates and the stability of tracking targets. Thanks to the use of microprocessors, the receiving device has a high throughput on targets. A digital SDS with a programmed change in the frequency of the probe pulses ensures the screening of passive jamming organized by the adversary, reflections from local objects and the underlying surface of the earth at small angles of the radio beam.

The microprocessor system (MPS) of the RLON manages the operation of the parts of the RLON, including local microprocessors, the exchange of information with PBU, PU, LNC, RVC and data output to the display.

The microprocessor system MPS RLON, as well as other parts of the complex, includes a microprocessor and memory on large integrated circuits. At the same time, the MPS processes large amounts of data in real time with intensive data exchange with external devices. MPS is implemented on the basis of the so-called basic chipboard architecture. Modern MPS perform up to 2 billion operations per second and have a clock frequency of up to 500 MHz. Modern MPS can contain timers and perform complex logical operations with reference to time.

The airborne target recognition equipment (“friend or foe”) is typical for the state, has an independent antenna, mounted at the top of the headlamp, and enters the identification data into the MPS RLON. The identification time is 3 s. When escorting your plane or helicopter, a missile launch blocking is provided.

We give the technical characteristics of the RLON. The radar detection range for targets with EPR of the warhead of the BR (0.5-1 m ² ) is 2500 km. This range is given in the technical specifications of the Antei-2500 air defense system developed on the basis of the S-300V air defense system (p. 276 books: Vasilin, Gurinovich, Anti-aircraft missile systems, 2002). The increase in target detection range is currently limited not by the power of the radar transmitter, but to a large extent by the mass of the radar allowed for its transportation on a wheeled or tracked track. The standard error of the range determination is 100 m, the azimuth and elevation angle is 15 ', and the velocity is ± 10 m / s. Range resolution - 200 m, azimuth and elevation - 30 '. The time of target detection with an EPR of 0.5 m ² is 5-7 s. The viewing rate in the sector of a single 90 ° headlamp can vary from 0.1 to 5 s. Slow rotation of the radio beam in sectors of ballistic targets is provided (in this case, a sector of 30 ° is visible in 0.3 s). The transition from target detection to its tracking occurs in 5-10 s. The coordinates of the target on the PBU and control commands on board the rocket are issued with a frequency of 1 Hz. The number of simultaneously detected RLON targets - up to 500, simultaneously accompanied by targets - up to 300.

In the considered RLON, the detection and guidance functions in one locator are combined. Such a combination has become possible thanks to modern improvements in the PAR technology and increased speed and memory of the MPS. The indicated combination takes place in the A-135 system (Don-2N radar), Patriot air defense system (AN / MPQ-53 radar), Vurosem air defense system (Arabel radar), etc.

Lidar review and guidance for low-flying targets LNC is intended for:

a) the detection and tracking of low-flying targets (cruise missiles, helicopters, ballistic targets, unfired at medium altitudes, etc.), capture targets according to target designation, determine the state of the goals;

b) guidance of missiles by issuing control commands on board the missile, receiving reports from the missile on the execution of commands;

c) launch control of designated missiles;

d) exchange of information with PBU, PU, RLON.

The composition of the LSC includes (Fig. 1) an infrared thermal imager (IT), a television optical system (TOS), a laser rangefinder (LD), a microprocessor system (MPS) of the LSC and the LSC display. The thermal imager includes the following parts: Cassegrain type antenna system (telescope), infrared pulsed solid-state laser, active and passive channel optical matrix receiver, microprocessor system, viewing and pointing display, and data and communication equipment. Antennas of the LNC are installed on an electrically controlled gyrostabilized base (platform).

The thermal imager can operate in sector or all-round viewing mode, as well as in passive mode as an infrared detector (IO), and in active mode as an infrared locator (IL). The thermal imager can work both day and night. Since the IL beam is very thin, it can be tilted by an elevation angle of 0.5 ° in the absence of the influence of the underlying surface of the earth, and detect targets at an altitude of 100 m at a distance of 11.5 km. In addition, the receiver of the thermal imager provides for the selection of reflections from the underlying surface of the earth and local objects. An overview of the thermal imager beam in azimuth and elevation is made by electromechanical rotation of the telescope elements.

Here are the technical characteristics of the thermal imager. The maximum radiation received by the EUT lies in the wavelength range of 3-5 microns. The working wavelength of the IL is in the range of 8-12 microns, more precisely - 10-10.5 microns (window transparency of the atmosphere). The angular divergence of the beam in azimuth and elevation is 1 °, the energy in the IL pulse is 1.2-1.5 J, the pulse duration is 20-50 ns, and the pulse repetition rate is 100 kHz. The detection range of targets depends on the presence of cooling of the photodetector. In the presence of cooling, the IR range (passive mode) is 15 km, the IL (active mode) is 100 km. The range of 100 km is given in the technical specifications of the infrared detector modified in Germany "Hawk" air defense system.

The thermal imager, together with a laser rangefinder, allows you to detect and distinguish between flying and hovering helicopters in accordance with the algorithm provided for in the MPS of the LSC.

Since the interceptor missile can develop high speed during the initial movement (up to 12 km / s), it can intercept low-flying targets with speeds of up to 4 km / s at altitudes of 10-15 km, including fragments of SBC that burst during firing with RLON at medium heights. At altitudes of 10-15 km (in the atmosphere), ballistic targets become very hot, which contributes to a more effective defeat of them with the help of the LSC. Thus, in the complex for missile targets, two echelons of destruction are created: at medium and low altitudes.

The lidar provides a miniature television-optical high-resolution TOC video surveillance system (with 10x magnification) with a passive infrared channel. The TOC contains a transmitting camera (PC), a video monitoring device (VKU), a coaxial cable line, and others. A PC is developed on the basis of charge-coupled semiconductor devices and implements digital signal processing methods using a microprocessor. For the purpose of joint observation, the PC can be rotated by the drive of the antenna system of the thermal imager. VKU is a monitor located in the cabin of the Leningrad Scientific Center. Aircraft TOC detection range is up to 15 km, and target recognition range is up to 7 km.

TOC allows you to detect and recognize targets covertly without emitting electromagnetic energy. TOC can be applied in conditions of intense interference to the thermal imager. TOS can work day and night both in conjunction with a thermal imager, and autonomously. With simultaneous operation, the TOC and the thermal imager control each other's work.

The LNC as part of a thermal imager, a television optical system and a laser rangefinder can be used to detect and destroy Stealth aircraft if these aircraft were not detected in the RLON radio range.

The guidance radar for high-flying targets of the RVC is intended for pointing missiles at satellites with an orbit of more than 1,500 km, including in geostationary and elliptical orbits, as well as for issuing and receiving the considered PBU information. The principle of guiding a rocket over a radio beam was given above.

The RVC is a coherent-pulse radar in the range of 10-20 MHz (a range of space communication systems and data relay), which ensures the passage of radio waves through the atmosphere without significant absorption. The radio beam of the RVC is induced from a predetermined launch direction of the rocket in the direction of the aiming point (target destruction). The RVC includes (see the drawing) a parabolic antenna with the radio beam moving in two planes, a transmitter, a receiver, a microprocessor system, a display, and data and communication equipment. MPS RVC includes a timer that allows you to count the time from the moment the rocket starts to the moments required when performing the flight mission for this type of target. Since the meter range of waves is used in the RVC, which is hardly absorbed in space, the distribution range of the RVC signals is 50-60 thousand km.

PU launchers are designed for storage, transportation and launch of interceptor missiles, as well as for the issuance and reception of information PBU, RLON, LNC, RVC. Interceptor missiles (RP) are installed in transport and launch containers (TPK).

PU includes (see drawing) equipment for installing TPK in the starting position, preparation for launch, including launching a gyroscope, equipment for ejecting rockets from TPK (usually with a small powder charge - pyro cartridge), microprocessor system, data and communication equipment. PU are reusable devices with a vertical rocket launch, which allows you to fire at targets flying from any direction. Since the mass and dimensions of RPs are much smaller than those of modern air defense missiles, the number of launchers is brought up to 27 - 6-10 RPs in each launcher. The combat set of the complex is 202 RP. Departure of RP from TPK is carried out using a mechanical ejector according to commands from RLON, LNTs, RVTS. After the start of the RP, the launcher can be recharged using a launcher-charging installation. Charging time - 10 minutes. Since four types of missiles are used, information about their launch is transmitted to the PBC and, by accessory, to the RLON, LNTs, and RVC.

The working time of the complex (the time between the moment of detection and the launch of the rocket) is 2-3 s.

RP interceptor missiles are designed to engage targets of the types indicated above. Four types of RP are provided depending on the type of target and its flight altitude (the purpose and composition of these types are indicated below). RP includes the following main parts (see drawing): rocket engine, warhead, homing head, inertial control system, ground communication equipment (RLON, LNC or RVC), microprocessor system, power supply.

RP is a single-stage missile with a nuclear rocket engine, a nuclear warhead and a special seeker.

The RD nuclear rocket engine contains nuclear targets of the main direction of the rocket and deviations from it, a laser device, a belt moving mechanism with nuclear targets, a synchronizer, etc. The principle of operation of a nuclear rocket engine was given above. The antennas of the communication line of the rocket with the ground are mounted on the body in the tail of the rocket. The engine thrust, speed, acceleration, deflection and rotation of the rocket can vary to some extent by adjusting the frequency of departure of the plasma clots.

The initial velocity of the rocket is 10 ⁵ m / s. The average acceleration is 130 m / s ² . A missile can perform maneuvers with an overload of up to 40 g. The flight range of a rocket depends on the stock (number) of nuclear targets. The complex provides four types of stock, ensuring the flight of a rocket at a range of 50, 500, 2000 and 40,000 km.

Engine dimensions: diameter - 30 cm, for a range of 2000 km - length 50 cm, weight - 50 kg. The length of the engine depends on the estimated longest range of the missile. These specifications are justified in the application 2002110167.

The thrust and speed of the taxiway are adjusted by the microprocessor system according to commands from the RLON, LNTs, RVTS or GSN. In this case, the velocity increases in the acceleration section of the rocket, and decreases to 10 km / s in the final section. The engine control ensures the defeat of the target in oncoming courses, on the parameter and when firing after.

A nuclear warhead of a warhead includes a fuse, a charge, a converting layer (converter), a safety-executive mechanism, etc. The principle of operation of a nuclear warhead has been given above. A gaseous mixture of deuterium with tritium can be used as a nuclear material in warheads, or when mastering the appropriate production technology, gaseous helium - 3.

The targets of the proposed warhead are defeated at altitudes of up to 500 km — by a shock wave formed by warheads, at altitudes of more than 500 km — by a neutron flux (using a mixture of deuterium with tritium) or a proton flux (using helium - 3). When targets are hit by these streams, the converter in the warhead (layer of the fibrous composite) is not used. The angle of impact of a shock wave or the emission of neutrons (protons) is determined mainly by the angle of the solution of the charge and can vary during manufacture from 30 to 150 °. In the proposed complex, this angle was chosen constant and equal to 90 ° to simplify the calculations. Although the equivalent of the warhead depends on the mass of the charge and the gas pressure in it, but since light elements are used in the charge, the mass of the warhead does not depend on the equivalent. The mass of warheads with an equivalent of up to 1 MT is approximately equal to 3 kg.

The safety-executive mechanism (PIM) ensures the safety of the service crew in handling the missile on the ground and when it is flying until it approaches the target and controls the warhead detonation when the missile approaches the warhead distance. At the same time, two modes of action are distinguished in PIM: cocking mode (the ban on undermining the warhead is lifted) and execution mode (undermining of the warhead is performed). PIM is located in type 1 and 2 rockets (see below) directly in the rocket, in type 3 and 4 rockets - in each shell of a cassette warhead. In missiles 1 and 2, the PIM type is activated in terms of arming based on the signal from the GOS (when it captures a target) or in the absence of capturing the GOS by signals from the RLON, LNTs (when approaching the target), and in terms of execution, by signals of the same means - when the missile approaches the distance of the warhead damage. At this distance, the PIM delivers a detonation pulse to the warhead synchronizer, which produces a warhead charge detonation. If a missile misses a missile, determined by the GOS, or by signals from the RLON, the LSTC a) for missiles of the 1st type, the PIM removes the cocking mode, and the warhead cannot be detonated when the missile falls to the ground, and thus the missile does not damage its troops, b) for PIM type 2 missiles undermine warheads, and thereby self-liquidate the missile. The action of PIM for rockets of types 3 and 4 is discussed below.

We give the technical characteristics of the warhead. Equivalent: 150 ct. Angle of defeat: 90 °. Dimensions warhead: diameter - 7.5 cm, length with the equivalent of 150 ct - 10 cm. These characteristics are justified in the application 2001119261.

To defeat extended targets (SBC, Brilliant Is, Brilliant Pebbles), as well as targets with high speeds (more than 7 km / s), the warhead cassette design is used. The number of shells in the cartridge with a missile diameter of 30 cm - up to 14, with a missile diameter of 60 cm - up to 54. The shells are scattered before the target is hit by an ejection mechanism that contains a powder charge (squib), detonated by a signal from the GOS. After departure, a PIM is triggered on each shell: in terms of cocking, when ejected from a rocket, in terms of execution, by a signal from a radio fuse. At a minimum distance to the target, which is determined by the radio fuse, the PIM delivers a pulse to the warhead synchronizer, which produces an undermining of the warhead projectile charge. When a missed missile is detected by a radio fuse, the PIM detonates the missile, and thereby self-destructs the missile.

The homing missile seeker is designed to detect a target by the emitted or reflected signal, to aim the missile at the target at the end of the trajectory and to undermine warheads. The target seeker can be captured in the automatic target search mode by the angular coordinates and the target range and by commands transmitted to the missile from the guidance point (RLON, LNTS, RVC).

GOS requirements are imposed on increasing the field of view, minimizing the time it takes to capture the target, minimizing the final miss of the missile, causing maximum damage to the target, and reducing the size and weight.

Currently, the main developers of the GOS are the Moscow Research Institute "Agat" and St. Petersburg JSC "LOMO". Research Institute "Agat" has developed a two-channel GOS using a microprocessor and a fiber-optic gyroscope, which replaced a mechanical gyroscope, etc. The development of algorithms for an advanced GOS is described in the candidate dissertation by O.E. Khurtin. The formation and study of the algorithm of a digital guidance system based on fiber optic gyroscopes. Moscow Institute of Physics and Technology (TU), Dolgoprudny, 2001. Thanks to the use of a fiber-optic gyroscope and microprocessor, the developed GOS largely satisfy the above requirements.

Two types of GOS are used in interceptor missiles:

a) infrared (thermal) in passive and active modes;

b) infrared (thermal) in the passive mode and radar - in the range of 10-20 GHz, single-pulse, with direction finding by an equal-signal zone.

In type b), the infrared part is switched on 3-4 seconds before the rocket arrives at the meeting point with the target. It is difficult for an adversary to create effective interferences for such a seeker.

Undermining the warhead of the GOS is carried out through the PIM approximately 50 m from the target (non-contact fuse). The easiest way to determine this range is the level of the signal reflected from the target. Since the GOS is pulsed, the range can be determined by the time of reception of the reflected pulse. The most perfect GOS, using the Doppler effect to undermine. They allow you to choose the position of the rocket relative to the target for the most effective target hit.

One of the promising directions for the development of GOS is the possibility of determining its infrared and radar part using a microprocessor of the signature (shape) of the target according to spectral and trajectory characteristics, which will significantly increase the noise immunity of the complex. This signature through the communication equipment with the missile can be transmitted to the RLON or the LSC for accounting during subsequent guidance.

Using a microprocessor, the infrared and ultraviolet parts of the seeker can isolate (identify) the target against the background of infrared traps fired from an airplane, helicopter or warhead.

In the indicated directions of improving the GOS, a lot of work has been done at LOMO JSC. GOS "LOMO", according to AO, is able to distinguish between true and false targets in the conditions of the enemy setting artificial interference in the infrared range.

We give the technical characteristics of the GOS. The reception angle (radiation) is 24 ° * 24 °, the viewing period is 0.5-0.7 s. With deep cooling of the photodetector, the sensitivity of the seeker increases by two orders of magnitude. At the same time, the GOS target is captured at a distance of 8 km in the infrared passive channel, 20 km in the infrared active channel, and 35 km in the radar channel. In a long-range intercept rocket, the range of target acquisition by the radar channel is increased to 500 km, since in the wavelength range of this channel the energy absorption in space is practically negligible. The weight of the GOS with a cowl of the order of 15 kg, diameter 150 mm, length 400 mm. GOS is located in the fairing.

Here are the characteristics of other parts of the interceptor missile. The inertial control system of the ISU contains a gyroscope that replaces the autopilot, and it is advisable to use a fiber-optic gyroscope, which has a number of advantages compared to a mechanical gyroscope. Using a gyroscope, the angular motion of the rocket is stabilized relative to its center of mass and the angular velocity of the line of sight of the rocket is determined. Having gyro data, the ISU, depending on the incoming guidance commands, controls the position of the center of mass of the rocket in space, for which it generates a mismatch parameter and, according to it, rocket engine control commands in speed and in deviation. These commands are implemented through the IPM rocket. Thus, the missile is aimed at the target (rocket engine control) through the MPS in two ways: in the initial and middle sections of the trajectory — inertial command control, and in the final section — control from the GOS.

As shown above, PIM acts as a non-contact warhead fuse. In addition, type 1 and type 2 missiles have a contact fuse of the magnetic-electric type, which fires when the rocket hits a solid object. This fuse operates on PIM in cocking mode. However, in a type 1 rocket, this fuse does not fire when the rocket falls to the ground, without causing damage to its troops.

The communication equipment of the rocket with the ground (RLON, LNC or RVC) ensures the transfer of guidance commands to the rocket and reports on the execution of these commands from the rocket. The specified communication line operates at the carrier frequency of the RLON, LNC or RVC depending on the type of rocket and has a high throughput and noise immunity, using cryptography using MPS. The receiver of this equipment issues control commands to the ISU missiles. Antennas are mounted on the body in the tail of the rocket.

Given the above characteristics of the RD, warhead and GOS, we give the types of missiles recommended for the complex:

1. Short-range missile. It is used for target heights up to 30 km. It has a warhead with one charge and a converter (hits the target with a shock wave). It has an infrared seeker with a passive and active channel. It has a non-contact and contact fuse. The range of the missile is up to 30 km. Communication with the missile is carried out at the frequency of the LSC.

2. The lower middle interception missile. It is used for target heights of 20-500 km. It has a warhead with one charge and a converter (hits the target with a shock wave). It has a seeker with an infrared passive channel and a radar channel. It has a non-contact and contact fuse. The range of the missile is up to 500 km. Communication with the missile is carried out on the frequency of the RLON.

3. The upper middle interception missile. It is used for target heights of 200-2000 km. It has a cassette-type warhead without a converter (it hits the target with a stream of particles). The diameter of the rocket is 60 cm. The number of shells in the rocket is 50. It has a seeker with an infrared passive channel and a radar channel. It has only a non-contact fuse (radio fuse). The range of the missile is up to 2000 km. Communication with the missile is carried out on the frequency of the RLON.

4. Long-range interception missile. It is used for altitude targets of 1500-40000 km. Has a cassette-type warhead (hits the target with a stream of particles). The number of shells in the cartridge is 12. Has a seeker with an infrared passive channel and a long-range radar channel. It has only a non-contact fuse (radio fuse). The range of the missile is up to 40,000 km. It has a radio beam orientation receiver. Communication with the missile is carried out at the frequency of the RVC, and the received signals are modulated for guidance by radio beam.

Launchers are distributed by type of missile as follows: 1 type -5 launchers of 10 missiles each, 2 types - 10 launchers of 8 missiles each, 3 types - 10 launchers of 6 missiles each, 4 types - 2 launchers of 6 missiles in each.

The number of simultaneously fired by a set of targets - up to 100.

The designation of the type of missiles for firing is done automatically when targeting to PBU. However, the operator of the PBU can forcibly appoint another one or two missiles to fire at a given target.

The APDS data and communication equipment provides the exchange of telecode and voice information between parts of the complex. APDS uses fiber-optic communication lines (FOCL) or radio telecode links (RTKS). FOCLs have increased strength and are protected from exposure to radioactive radiation. RTKS have cryptographic protection and are used at large distances of parts of the complex. RTX can dramatically reduce the deployment / coagulation time of the complex.

Power plant ES provides electricity to all parts of the complex. In ES, a diesel engine with an electric generator or a gas turbine unit with an electric generator can be used. For training purposes in peacetime, the complex can be powered from an industrial power grid. Local power sources RD, warhead, GSN, etc. are small-sized cadmium-lithium or lithium-sulfide elements.

In all electronic parts of the complex, a built-in functional control is carried out using the MEAs of these parts. Functional control allows you to timely identify equipment malfunctions and eliminate them. The complex should provide for the possibility of training combat crews that simulate the conduct of hostilities, excluding real missile launches.

The complex includes navigation equipment using the signals of space radio navigation systems, equipment of topographic location and relative orientation of parts of the complex. The complex also includes equipment for monitoring and protection against weapons of mass destruction.

The equipment of the complex is located in multi-axle wheeled automobile vans. There are 13 vans in the complex: PBU, RLON, LNTs, RVC, five PU vans and spare RPs, one documentation data processing van and three administrative and technical vans (repair, storage of spare parts, cable management, etc.). The issue of the possibility of deploying parts of the complex on a tracked chassis of high cross-country ability and the issue of air transportability of the complex should be worked out.

The time of the transfer of the complex from traveling to combat (combat readiness of the complex for firing targets) is 1-5 minutes. For rough terrain, the deployment / coagulation time increases and must be determined during operation.

The complex must satisfy the following reliability requirement: the average time between failures is 1000 hours.

Let us consider the dynamics of the complex for two combat operations characterized by two types of targets: a complex ballistic target and a satellite in geostationary orbit. At the same time, the SSC is hit by the complex autonomously (without a command from a higher KP), and the satellite in geostationary orbit - by a command from a higher KP.

In the "Readiness N1" mode, the RLON and the LSC make a circular overview of the surrounding space. Upon detection of the RLON, the targets are determined at each review of its coordinates. MPS RLON ties the trajectory of the target (identifies individual points with one target), determines the speed and roughly the type of target from the trajectory data. In the situation under consideration, according to the extent and composition of the target, the rate of change of its coordinates, the MPS refers the target to SBC. Data on the trajectory of the target and the type of target are reflected on the RLON overview display and are continuously output to the control room. MPS PBU performs the extension of the target, estimates its danger (by the point of incidence), solves the task of target distribution (determines the anticipated point (aiming) and the type of missile used is the 3rd type). The indicated decisions are reflected on the display of the circular review and guidance. The PBU operator decides to fire at the target and enters the command to assign the target to fire at the Ministry of Railways. According to this command, the control unit issues the coordinates of the aiming point on the RLON and the command for preparation for launch on the control unit with a type 3 missile. When the target enters the affected area, the RLON solves the preliminary targeting task and issues a command to the launcher to launch the designated missile. After receiving the signal about the launch of the missile from the launcher and determining its coordinates, the MPS RLON solves the main task of guidance using the proportional approach method. In this case, a certain midpoint of it is taken as the target’s coordinates. According to the results of solving the guidance problem, a signal is generated that is proportional to the deviation of the missile from the line of sight. The specified signal is converted to missile guidance commands. These radio link commands are transmitted aboard the rocket to the inertial control system of the ISU. The ISU, comparing the current position of the rocket and the received guidance commands, develops a mismatch parameter and, based on its command to control the rocket engine in speed, deflection and rotation of the rocket. These commands are implemented by the IPU. Thus, the RLON automatically guides the missile along the line of sight during the entire time of its flight. In this case, the rocket inclines in the direction of the aiming point, and its flight path is formed in such a way that the approach of the rocket for the purpose allows the GOS to capture the target. So inertial-command missile control is carried out.

When the rocket approaches the target at the range of the GOS, the RLON gives a signal to turn on the radar part of the GOS, and then the infrared in the passive mode. When the target is captured by the GOS, rocket engine control is transferred to the GOS. At the same time, a signal about the capture of the target's GOS is transmitted to the RLON. If such a signal does not follow, then the RLON continues to direct the missile.

When the missile approaches the range of the warhead, the GOS or RLON issue, via the MPS, a command for the release of shells on the mechanism of ejecting them from the cartridge. The shells fly apart, and after 1-2 s the PIM safety-actuating mechanism of each shell is activated. In this case, the PIM sets the cocking mode (the ban on the detonation of the projectile is lifted), and the radio fuse is turned on. When the projectile approaches the distance of the warhead damage, which is determined by the radio fuse, the latter gives a signal to detonate the warhead. In this case, a voltage pulse is applied to the synchronizer of the warhead projectile, which drives the laser. The laser initiates the detonation of a warhead shell. When a shell is detonated, a stream of neutrons or protons flies out in a certain angle, which mechanically destroy the elements of the SSC in the volume of the shells. The fact of target destruction is established by the RLON according to a sharp change in the parameters of its movement.

If some elements of the SBC were not affected, then they continue to move to Earth. At the same time, light elements burn out in the atmosphere, while heavy elements become very hot and LNC is detected. Upon detection of targets, the LNC makes a target allocation (the aiming point is determined, PU missiles of the 1st type are assigned). Next, a type 1 rocket starts and guidance is carried out according to the algorithm above for firing at medium altitudes. Thus, SBC is affected by two echelons of the complex: at medium and low altitudes. In this case, all actions to defeat the SBC are carried out automatically using microprocessor systems PBU RLON, LNTS and PU, and the interception of the target is displayed on the overview and guidance display PBU, RLON, LNTS. After the operation is completed, the PBU issues a report to the higher KP about the nature of the target, its danger and the results of the shooting.

Consider the second situation in which a satellite is struck in a geostationary orbit. Target designation (six or five elements of the orbit) from the SPRN or SKKP systems comes from this satellite, and a command to defeat it comes from a higher CP. The PBU operator duplicates the decision to fire at the target and enters the command to assign the target to fire at the Ministry of Railways. By this command, the PBU solves the target distribution problem (the aiming point (the meeting point of the rocket with the target) is determined), the PU missiles of the 4th type are assigned. Then the PBU issues the coordinates of the aiming point to the RVC, and a command to prepare for launch on the launcher with the 4th type missile. The RVC issues a command to the launcher to launch the designated missile and searches the sector. When a missile is captured by a radio beam of the RVC, which is reported from the missile via a radio link, the MPS of the RVC solves the problem of guiding the missile through the radio beam. This problem is solved by using the flight task for this type of space target - the law of the radio beam motion in time to the aiming point. At the same time, the flight task is adjusted according to the specific initial and final data. In accordance with the flight mission (with the participation of the timer), the radio beam of the RVC, and therefore the missile, are sent to the aiming point.

When the rocket approaches the range of the GOS in accordance with the flight task, the radar channel of the GOS is turned on. When the target is captured by the GOS, rocket engine control is transferred to the GOS. At the same time, a report on the capture of the target seeker is transmitted to the RVC. If such a signal does not follow, then the RVC searches for it by moving the radio beam around the aiming point. The progress of the flight mission is displayed on the display of the RVC and allows the operator to control this move.

When capturing the target of the GOS, the radar part determines the range of the missile to the target. When the missile approaches the range of the warhead, the GSN issues a departure command to the warhead to the mechanism for ejecting shells of the cassette warhead. Next, the shells hit the target similarly to the first situation.

If during the operation with SPRN or SKKP new target designations for the target arrive, then they are immediately entered through the PBU into the RVC. In this case, the guidance problem is again solved and a new guidance of the RVC radio beam is realized. The fact of defeat of the target should be fixed by means of SPRN or SKKP.

The proposed complex is characterized by a high degree of automation of all processes of conducting combat work: the operator only makes a decision on the firing of the target, the remaining actions are performed automatically using microprocessor technology.

The proposed complex can be integrated into any group of troops of the missile defense (missile defense) and controlled from a higher command post. However, it can autonomously conduct military operations, as was shown above with the defeat of the SBC.

The proposed complex solves the problem of integrating air defense, missile defense and anti-aircraft defense systems, and for the first time. SAM is capable of fulfilling the task of defeating space targets. Thanks to the use of a nuclear rocket engine, a nuclear warhead and an improved seeker, the area and probability of hitting targets has significantly increased. For the first time, it was possible to defeat a complex ballistic target.

The complex is characterized by a high degree of automation of all processes due to the use of interconnected microprocessor systems in all parts of the complex. The complex is multi-channel in terms of the number of targets and guided missiles. Therefore, it can simultaneously fire up to approximately 100 different targets. The complex has a high noise immunity. The complex is mobile.

LIST OF MAIN ABBREVIATIONS

JSC - Joint Stock Company

APDS - data and communication equipment

UAV - unmanned aerial vehicle

BR - ballistic missile

Warhead - warhead

VKU - video monitoring device

BOLC - fiber optic communication line

GOS - homing head

Warhead - head part

SAM - anti-aircraft missile system

IL - infrared locator

IO - infrared detector

IT - infrared thermal imager

KA - spacecraft

KP - command post

ISU - inertial control system

LD - laser range finder

LNC - Lidar for low-flying vision and guidance

MPS - microprocessor system

PBU - combat control point

Air Defense - Air Defense

PVRKO - anti-aircraft missile defense

PC transmitting television camera

PKO - space defense

PIM - safety actuator

ABM - missile defense

PU - launcher

RVC - guidance radar for high flying targets

RD - rocket engine

RLON - radar of review and guidance

Radar - radar station

RP - interceptor missile

RTKS - radio telecode communication

SBC - a complex ballistic goal

SDC - selection of moving targets

SKKP - space monitoring system

CPPR - missile attack warning system

TOS - television optical system

TPK - transport and launch container

HEADLAMP - phased array antenna

EPS - effective scattering area

ES - power station

Claims (1)

Air defense missile and space defense complex containing radars for viewing space and guiding missiles, a command and control station, launchers and interceptor missiles, including an engine, a warhead with a fuse and a homing head, characterized in that the interceptor missile engine is made in the form of a conical target comprising nuclear material initiated by means of laser radiation to form a thermonuclear reaction and create a plasma clot with the possibility of its escape from the hole, made at the top of the cone of the conical target, along the axis of the interceptor missile or at an angle to it, while the fuse of the warhead is made in the form of four mutually perpendicular conical targets containing explosive with the possibility of initiating it by laser radiation to create a plasma clot with the possibility of it departure from the hole made at the top of the cone of each conical target, and collapse in the space between the other cones.