RU2586436C1 - Bogdanov method for target destruction and device therefor - Google Patents

Abstract

FIELD: weapons and ammunition.

SUBSTANCE: invention relates to anti-missile defence systems, as well as to means for elimination of manpower and equipment of possible enemy. According to method for target hitting, combat laser designed to shoot down missiles is launched to flight with rocket and strikes target using laser radiation.

EFFECT: device for implementing method for target striking contains combat laser mounted on rocket with guidance system configured to shoot down missiles.

68 cl, 14 dwg

Description

The invention relates to the field of methods and devices for air defense systems (air defense).

It can be used in missile defense systems (ABM).

It can also be used in systems for protecting ships and aircraft from missiles.

It can also be used as a means of defeating enemy aircraft and drones and as a means of defeating manpower and equipment.

It can also be used in missile defense systems, such as ballistic missiles such as Poplar M or Yars, against missile defense.

There is a method of hitting a target and a device for its implementation of the US missile defense system, in which targets are hit with a battering ram. For example, due to the kinetic energy of a rocket [Article “US missile defense system”, Internet, Wikipedia].

The disadvantage of this method of hitting a target and a device for its implementation is that it is impossible for them to hit the warheads of the last stage of a ballistic missile, which arbitrarily change the flight paths, as in Topol M and Yars.

The next disadvantage of this method of hitting a target and a device for its implementation is that it is difficult for them to hit a remote ballistic missile at the time of launch, since the device does not have time to reach a ballistic missile from a long distance until its final stage is divided into multiple warheads.

A known method of hitting a target and a device for its implementation by a combat flying laser [Article "Boeing YAL-1", Internet, Wikipedia].

In this method, a combat laser, configured to shoot down a missile, is launched into a flight on an airplane and the laser is aimed at a target in flight. Then turn on the laser, and laser radiation hit a target, such as a rocket.

On February 3, 2010, successful in-flight laser tests were conducted to defeat a solid-fuel ballistic missile.

February 11, 2010 continued testing. Missile Defense Agency (MDA), an American missile defense agency, has tested a combat laser in flight to destroy ballistic missiles. According to a press release from the agency, the laser system was fired at two targets simulating solid and liquid fuel ballistic missiles in the accelerating section of the trajectory.

Tests of an air-based laser were conducted at the Point Mugu Air Force Base in California. Ballistic missile with LRE launched from a mobile platform at sea. The defeat of the target was carried out in several stages. At the first stage, the target was detected using on-board sensors and the target was tracked by the beam of the first TILL laser. Then a second BILL laser was used to evaluate the effect of the atmosphere on the accuracy of the hit. After that, a shot was fired by a third laser, a megawatt-class combat laser at full power, which heated the rocket to a critical temperature and caused an irreversible violation of its design. Reported damage to the target (the rocket was in the active part of the trajectory). About two minutes passed from the start to the defeat of the target.

A device for implementing the method of hitting a target contains a YAL-1 platform — a modified Boeing 747-400 aircraft with a chemical chemical laser mounted in the bow capable of shooting down a missile.

The disadvantage of this method and device for its implementation is the low rate of increase of the laser radiation power incident on a target, for example a missile of a likely enemy, due to the inability to quickly approach the laser with the target, to reduce the distance between the target and the laser before turning on the laser.

This drawback is due to the low speed of the aircraft, compared with the speed of a rocket of a modern missile defense system. At the same time, even if the plane moves towards the target, the distance between them decreases much more slowly than if a missile of the modern missile defense system flew instead of the plane.

The next disadvantage of this method and device for its implementation is the inability of the aircraft to remove the laser into outer space to hit a target in space, due to the fact that planes do not fly in space.

A further disadvantage of this method and device for its implementation is that it is not provided that it is possible to first hit the target with laser radiation, and then with the kinetic energy of the rocket that carries this laser.

The challenge facing the invention is to enable the acceleration of increasing the radiation power of the laser incident on the surface of the target, due to the rapid approach of the device in order to reduce the distance between the target and the laser before turning on the laser.

An additional task facing the invention is the ability to increase the specific energy content of laser radiation per unit weight of an aircraft with a laser.

The second additional task facing the invention is the ability to first hit the target with laser radiation, and then with the kinetic energy of the rocket that this laser carries.

The specified main problem is solved due to the fact that in the method of hitting a target, then simply in the method, namely, that a combat laser, configured to shoot down a missile, is launched into flight and sent to the target, while the laser is turned on, the laser radiation is generated, and the laser is hit by the laser, the laser is additionally launched on a rocket in the direction of the target, the rocket is aimed at the target, the distance is reduced to the target by the rocket, and the laser is turned on, the laser radiation is generated, and the laser is hit by the laser distance to the target.

The laser is lifted by a rocket beyond the atmosphere.

The rocket is launched into the flight by the launch complex of the rocket, and in addition, an additional laser from the launch complex is sent to the flame of the working rocket engine, the laser is turned on, a laser beam is created and the flame of the working rocket engine is heated with a laser beam.

The radiation of the flame of the operating rocket engine is directed to the inner surface of the resonator, made below the bottom of the rocket around the outlet of the nozzles of the rocket engine and around the axis of the rocket at a safe distance from the nozzles, while the radiation is reflected by a mirror layer of the inner surface of the resonator and is directed at least once in the direction of the opposite side of the resonator, and the flame of a working rocket engine is heated by reflected radiation.

The flame of a working rocket engine is directed inside the working volume of the laser, mounted below the bottom of the rocket, and the flame is used as an active medium for generating laser radiation, and the laser is turned on and creates laser radiation.

A rotary mirror made on the axis of propagation of laser radiation is rotated with the possibility of directing laser radiation to the target, while the laser is turned on and the laser radiation is generated, the radiation from the laser is output and directed to the rotary mirror, while the laser radiation is reflected from the rotary mirror and directed to the target.

The flame of a working rocket engine is directed into the working volume of the direct energy conversion unit installed below the bottom of the rocket, and the installation creates an electric current and directs it to the laser pump system, while the laser pump system turns on the laser and creates laser radiation.

The flames of a working rocket engine are directed inside the working volume of the MHD generator installed below the bottom of the rocket, and the MHD generator creates an electric current and directs it to the laser pump system, while the laser pump system turns on the laser and creates laser radiation.

The rocket is launched from the protected object, while the rocket is launched in the direction of the target.

The target is found by the target detection system, while the target is found by at least one radar station of the system using radar, and information about the target is transmitted from the system to the rocket and to the laser.

The target is found by the target detection system, while the target is found by at least one satellite by receiving radiation from the target, and information about the target is transmitted from at least one satellite to the rocket and to the laser.

An additional missile launches a cartridge with a warhead, and from the cartridge then launches at least one warhead in the form of a laser rocket.

A rocket with a laser is launched into flight by an additional booster block.

A laser rocket is launched into flight with an additional rocket.

A rocket with a laser is launched into flight from a protected object made in the form of an additional rocket.

A laser rocket is launched into flight from a protected object made in the form of an airplane.

A laser rocket is launched into flight from a protected object made in the form of a ship.

Launch a rocket made in the form of an anti-tank guided missile.

This problem is solved due to the fact that the device for implementing the method of hitting a target, then simply a device containing a combat laser configured to shoot down a missile, further comprises a missile and a missile guidance system, the laser being connected to the missile and the missile being connected to the guidance system rockets.

The device comprises a laser guidance system, wherein the laser guidance system is connected to the laser.

The laser is mounted on a gimbal connected to a rocket.

A system of gyroscopes is connected to the laser, containing at least two gyroscopes configured to stabilize the position of the laser in space.

The laser is mounted in the bow of the rocket.

The axis of the laser radiation coincides with the axis of the rocket.

The axis of laser radiation is parallel to the axis of the rocket.

The laser is connected to the fairing made in front of the laser along the direction of the rocket.

The laser is connected to a removable fairing made in front of the laser along the rocket.

The fairing is connected to the squib.

On the axis of the laser optical radiation, an inclined mirror is made connected to the laser guidance system.

The device comprises a fairing made in front of the laser from the side of the nose of the rocket, and on the axis of the laser optical radiation an inclined mirror is made connected to the laser guidance system, and a window is made in front of the inclined mirror in the fairing, while it is possible to pass laser radiation through the window.

The fairing is made of a material transparent to laser radiation, and it is possible to pass the laser radiation through the fairing.

The laser is made in the form of a chemical laser.

The fairing is made of heat resistant material.

The device includes an additional fairing made around the first fairing with the ability to separate from the rocket, and the first fairing is made of a material transparent to the laser radiation.

The missile is made in the form of a cruise missile.

The device contains an MHD generator, and the laser contains a pumping system, while the MHD generator is made from the tail of the rocket, connected to the rocket so that it is possible to direct the flame of the working rocket engine into the MHD generator, and the MHD generator is configured to generate current when it enters MHD flame generator operating rocket engine and direct current to the laser pump system.

MHD generator is self-excited.

The missile is made in the form of a missile defense system.

The missile is coated with a mirror coating, made with the ability to reflect optical radiation.

The fairing is coated with a mirror coating, made with the ability to reflect optical radiation.

The side surface of the laser is coated with a mirror coating, made with the ability to reflect optical radiation.

The missile is coated with a mirror coating, made with the ability to reflect optical radiation.

The fairing is coated with a mirror coating, made with the ability to reflect optical radiation.

The side surface of the laser is coated with a mirror coating, made with the ability to reflect optical radiation.

The laser guidance system contains two additional lasers and a computer.

The device comprises a rocket launch complex, configured to send a rocket into flight, and an additional laser connected to the launch complex, configured to direct a laser beam to the flame of a working rocket engine during a rocket flight and heat the flame with a laser beam.

The device comprises a resonator made below the rocket bottom around the exit openings of the rocket engine nozzles and around the rocket axis at a safe distance from the nozzles, while the inner surface of the resonator is coated with a mirror layer and is configured to direct the radiation of the flame of the working rocket engine towards the opposite side of the resonator.

The rocket contains a nozzle block containing a nozzle lattice, and the lattice contains at least two nozzles.

The missile contains a nozzle, while the nozzle is made in the form of a Laval nozzle.

The nozzle block is made on the side surface of the rocket, and the nozzle is made inclined with respect to the axis of the rocket.

The nozzle block is made on the side surface of the rocket, and the nozzles are made inclined with respect to the axis of the rocket, and the device contains at least one pair of blocks made from different sides of the rocket symmetrically with respect to the axis of the rocket.

The nozzle block is made on the side surface of the rocket, and the nozzles are made inclined with respect to the axis of the rocket, and the device contains at least one pair of blocks made on different sides of the rocket symmetrically with respect to the axis of the rocket, with a laser connected to the block and the possibility pass the flame of a working rocket engine through the nozzles of the block and use the flame as a working active medium to create laser radiation.

The nozzle block is connected to a direct energy conversion unit.

The laser is made on the side of the rocket.

A device for implementing the method of hitting a target contains at least one pair of lasers made from different sides of the rocket symmetrically with respect to the axis of the rocket.

The rocket contains at least two stages, while at least one stage has a laser.

A device for implementing the method of hitting a target contains a nuclear or thermonuclear charge, and the laser is made in the form of a laser with a nuclear pump.

A device for implementing a method for hitting a target contains at least two nuclear-pumped lasers.

The rocket contains at least two stages, while a nuclear or thermonuclear charge is connected to one stage, and a nuclear-pumped laser is made outside the side surface of the stage.

The missile contains at least two stages, while a nuclear or thermonuclear charge is connected to one stage, and at least two nuclear-pumped lasers are made outside the side surface of the stage, and it is possible to individually target the laser to an individual target.

The missile contains at least two stages, while a nuclear or thermonuclear charge is connected to one stage, and at least two nuclear-pumped lasers are made outside the side surface of the stage, and it is possible to individually target the laser to an individual target, and at the same time lasers are made around the stage.

Such a technical solution allows the Bogdanov method of hitting a target with a device for its implementation to provide the ability to accelerate the rapid convergence of a laser device with a target due to a rocket. For example, it is possible to provide the possibility of accelerating the rapid approach of the laser device with a missile of a potential enemy to reduce the distance between the target and the device before turning on the laser. Rapid rapprochement of the missile with the target is also provided by the missile guidance system due to the fact that the missile is aimed at the target by the system. Due to the use of a rocket, the approach speed for a laser target on a rocket significantly exceeds the speed of approach for a laser target on an airplane, since, for example, a missile of a modern missile defense system flies much faster than an airplane.

An increase in the radiation power of the laser incident on the target’s surface is also ensured by pointing the laser at the target with the laser guidance system at the moment of the desired approach between the laser and the target. In this case, an increase in the power of radiation incident on the target is carried out by reducing the distance between the laser and the target, and is inversely proportional to the square of the decrease in the distance between them.

Moreover, in the second variant of the method, the acceleration of increasing the radiation power of the laser incident on the surface of the target is provided due to the fact that the flame of the working rocket engine is directed inside the working volume of the laser installed below the bottom of the rocket, the flame being used as an active medium for generating laser radiation, in this case, the laser is turned on and creates laser radiation,

A rotary mirror made on the axis of propagation of laser radiation is rotated with the possibility of directing laser radiation to the target, while the laser is turned on and the laser radiation is generated, the radiation from the laser is output and directed to the rotary mirror, while the laser radiation is reflected from the rotary mirror and directed to the target.

The flame of a working rocket engine is directed into the working volume of the direct energy conversion unit installed below the bottom of the rocket, and the installation creates an electric current and directs it to the laser pump system, while the laser pump system turns on the laser and creates laser radiation.

The flames of a working rocket engine are directed inside the working volume of the MHD generator installed below the bottom of the rocket, and the MHD generator creates an electric current and directs it to the laser pump system, while the laser pump system turns on the laser and creates laser radiation.

Additionally, the laser radiation power can be increased by using the energy of a nuclear explosion to pump the laser.

For this, a nuclear pumped laser is used.

Previously, a multi-stage rocket is launched into flight and directed at the target, while the laser is turned on, laser radiation is generated, and the target is hit by laser radiation. Moreover, the laser is launched into a flight on a rocket in the direction of the target, while the rocket is aimed at the target, the distance to the target is reduced by the rocket, and the laser is turned on, the laser radiation is generated, and laser radiation hits the target at a reduced distance to the target.

At the same time, several nuclear-pumped lasers individually target individual targets.

Carry out a nuclear charge explosion. Radiation from a nuclear explosion pump lasers, create powerful radiation and hit individual targets with laser radiation.

No technical solutions were found that fulfill the task with the same technical means.

In FIG. 1 shows a schematic diagram of a first embodiment of a device for implementing the Bogdanov method of hitting a target, then simply a device, the main view.

In FIG. 2 shows a schematic diagram of a first embodiment of the device, front view.

In FIG. 3 shows a schematic diagram of a first embodiment of the device, rear view.

In FIG. 4 shows a section aa.

In FIG. 5 shows a schematic diagram of a second embodiment of the device, the main view.

In FIG. 6 shows a schematic diagram of a second embodiment of the device, front view.

In FIG. 7 shows a schematic diagram of a second embodiment of the device, rear view.

In FIG. 8 shows a section BB.

In FIG. 9 shows a section BB.

In FIG. 10 shows a schematic diagram of a third embodiment of the device, the main view.

In FIG. 11 shows a schematic diagram of a third embodiment of the device, a top view.

In FIG. 12 is a schematic diagram of a third embodiment of the device, bottom view.

In FIG. 13 shows a section GG.

In FIG. 14 shows a section DD.

Bogdanov’s method of hitting a target, then simply a method, a device for its implementation in the first embodiment is as follows.

Rocket 1 is launched into flight with a 2 megawatt power laser, capable of shooting down a rocket. Rocket 1 is sent to the target. In this case, before turning on the laser beam, the radiation axis of the laser 2 is directed at the target. A laser made in the form of a chemical laser is used.

When the rocket 1 moves, a fairing 3 made of heat-resistant material reduces the drag of the air.

A missile guidance system 4 directs a missile 1 at a target. A laser guidance system 5 directs a laser at a target 2. With a missile 1, a device is brought closer to a target, for example, a missile of a likely enemy, and a radiation beam is directed from a reduced (close) distance by a laser 2 at a target. In this case, the radiation power on the target is increased inversely with the decrease in the squared distance compared with the case if the laser created a beam without approaching the target on the rocket. As a rocket, they launch a missile of a modern missile defense system.

A device for implementing the method consists of the following elements.

In the bow of the rocket 1 a combat laser of 2 megawatt power is installed, made with the ability to shoot down a rocket. The axis of the rocket and the axis of radiation of laser 2 coincide. The laser is made in the form of a chemical laser.

In front of the rocket in front of the laser 2, a fairing 3 is made of transparent material for laser radiation. The fairing is made of heat-resistant material.

Rocket 1 is connected to the missile guidance system 4. Laser 2 is connected to a laser guidance system 5.

The missile is made in the form of a missile modern missile defense system.

Second option

In the second embodiment, they also solve the additional problem facing the invention, which is to provide the opportunity to increase the specific content of radiation energy per unit weight of an aircraft with a laser.

Moreover, in the second variant of the method, the acceleration of increasing the radiation power of the laser incident on the target’s surface is ensured by the flame of the working engine of the rocket 6 being directed inside the working volume of the laser 7 installed below the bottom of the rocket 6, the flame being used as an active medium for generating laser radiation, while the laser is turned on and creates laser radiation.

The missile is aimed at the target by the guidance system of 8 missiles.

A rotary mirror made on the axis of propagation of laser radiation is rotated by the laser guidance system 9 and directs the laser radiation onto the target, while the laser 7 is turned on and the laser radiation is generated, the radiation from the laser is output and directed to the rotary mirror of the laser guidance system 9, while the laser radiation is reflected from the rotary mirror and direct to the target.

The flame of a working rocket engine is directed inside the working volume of the direct energy conversion unit 10 installed below the bottom of the rocket, and the installation creates an electric current and directs it to the laser pump system, while the laser pump system turns on the laser and creates laser radiation with the laser.

In front of the rocket in front of the laser 7, in front of the rocket guidance system 8 and in front of the laser guidance system 9, the cowling 11 made of heat-resistant material transparent to the laser radiation rejects the air streams incident upon rocket motion.

A device for implementing the second variant of the method consists of the following elements.

A laser 7 is installed below the bottom of the rocket 6. A rocket guidance system 8 is connected to the rocket 6.

It is possible to direct the flame of the operating rocket 6 engine into the working volume of the laser 7 and to pass the flame through the volume, and it is possible to use the flame as an active medium for generating laser radiation and it is possible to exit the flame from the volume to create reactive thrust.

A laser guidance system 9 is connected to the laser 7. Moreover, on the axis of propagation of the laser laser radiation, a rotary mirror of the laser guidance system 9 is made.

At the same time, a direct energy conversion unit 10 containing a self-excited MHD generator was made below the rocket 6 and the laser 7.

In front of the rocket in front of the laser 7, in front of the rocket guidance system 8 and in front of the laser guidance system 9, the fairing 11 is made. The fairing is made with the possibility of deflecting air streams incident upon the rocket movement. The fairing 11 is made of a heat-resistant material transparent for laser radiation with the ability to transmit radiation in the wavelength range at which the missile guidance system 8 and the laser guidance system 9 operate.

In the second embodiment, an additional task facing the invention, which is to provide the opportunity to increase the specific content of radiation energy per unit weight of an aircraft with a laser, is solved by using a rocket engine to create radiation.

Evidence

1. All the energy of the rocket’s fuel can go into the energy of motion, and the jet of fuel can also be used to create laser radiation on the same principles in a chemical laser as in a prototype Boeing laser, or in a laser on a rocket in a device, including a winged one missile, that is, they have approximately the same efficiency.

2. Boeing engines are not used to create laser radiation, which means that the indicated ratio of the proposed device is higher.

Third option

In the third embodiment, they also solve the additional problem facing the invention, which is to provide the opportunity to increase the specific content of radiation energy per unit weight of an aircraft with a laser.

In the third embodiment, they also solve the additional problem facing the invention, which is to provide the opportunity to increase the speed of speeding of an aircraft with a laser.

Moreover, in the third embodiment, the method is as follows. Additional acceleration of the rocket, an increase in the laser radiation energy and an acceleration of the increase in the radiation power of the laser incident on the target surface are ensured by the fact that the central part 12 of the rocket directs fuel to the pairs of nozzle blocks 13, 14 and 15, 16, made in the form of nozzle arrays. Moreover, pairs of nozzle blocks made in the form of nozzle arrays are made symmetrically with respect to the axis of the rocket on the side surfaces of the rocket. And their nozzles are made inclined with respect to the axis of the rocket. For example, at an angle of 30-45 degrees relative to the axis of the rocket.

Inclined nozzles in pairs of nozzle blocks 13, 14 and 15, 16 with their nozzle arrays create a flame inclined with respect to the axis of the rocket, for example, directed at an angle of 30-45 degrees with respect to the axis of the rocket in the direction from the nose of the rocket, and directed into the working volumes pairs of lasers 17, 18 and 19, 20, made symmetrically with respect to the axis of the rocket. The fuel components are passed through the nozzle block, while the fuel components are passed through the nozzle grate, and the fuel components are passed through small nozzles and the total flow is divided into small-section jets - of the order of 1-2 mm. Fuel components, such as fluorine and deuterium, mix, ignite and create a flame. In lasers 17, 18, 19, 20, flame is used as an active medium to create laser radiation. In this case, the flame is passed through the working volumes of the lasers 17, 18, 19, 20 and create a jet thrust by the flame.

A jet engine of the central part 12 of the rocket directs the flame into the working volume of the direct energy conversion unit 21, for example, into the self-excited MHD generator, creates an electric current and directs the current to the pump systems of the lasers 17, 18, 19, 20, turns on the lasers and creates laser radiation. The missile guidance system 22 directs the missile at the target, and the laser guidance system 23 directs the lasers at the target. In this case, the fairing 24 deflects the air streams incident on the rocket. Moreover, the flame is removed from the working volume of the installation 21 direct energy conversion and create reactive thrust.

In a third embodiment, a device for implementing the method consists of the following elements.

The central part 12 of the rocket is connected to pairs of nozzle blocks 13, 14 and 15, 16, made in the form of nozzle arrays made around the central part 12 of the rocket.

In this case, pairs of nozzle blocks made in the form of nozzle arrays are made on the side surfaces of the rocket symmetrically with respect to the axis of the rocket with the possibility of creating a jet thrust by flame. And the nozzle pairs of nozzle blocks made in the form of nozzle arrays are made oblique with respect to the axis of the rocket. For example, at an angle of 30-45 degrees relative to the axis of the rocket.

The nozzle block contains a nozzle lattice containing small inclined nozzles of small cross section — of the order of 1-2 mm.

Pairs of nozzle blocks 13, 14 and 15, 16 are connected to pairs of lasers 17, 18 and 19, 20, made symmetrically with respect to the axis of the rocket along the nozzle blocks.

In lasers 17, 18, 19, 20, it is possible to pass the flame of the working nozzle blocks 13, 14, 15, 16 through the working volumes of the lasers 17, 18, 19, 20 and it is possible to use the flame as an active medium to create laser radiation.

The jet engine of the central part 12 of the rocket is connected to the direct energy conversion unit 21, for example, with a self-excited MHD generator, and is configured to direct the flame inside the working volume of the installation, pass the flame through the volume and create reactive thrust.

A direct energy conversion unit is configured to create an electric current and direct current to the pump systems of the lasers 17, 18, 19, 20. The missile guidance system 22 is connected to the central part 12 of the missile, and the laser guidance system 23 is connected to the lasers 17, 18, 19 , 20. The fairing 24 is made in front of the central part 12 of the rocket from the side of the nose of the rocket, in front of the rocket guidance system 22 and in front of the laser guidance system 23 with the ability to deflect the air currents incident on the rocket.

In the third embodiment, an additional task facing the invention, which is to provide the opportunity to increase the specific content of radiation energy per unit weight of an aircraft with a laser, is solved by using side nozzle blocks to generate radiation. The proof can be given for the second option, which is simply combined with the third option, and all of their elements are combined in one variant. In this case, the logic of the proof can be completely cited from the proof for the second option, adding all the same, but also for nozzle blocks in the form of nozzle arrays with inclined nozzles.

In the third embodiment, the additional problem facing the invention, which is to provide the ability to increase the speed of speed gain of an aircraft with a laser, is solved by using the side blocks of nozzles to create additional thrust. Their thrust increases the thrust of a jet engine made on the bottom of the rocket, and therefore increases the acceleration of the rocket.

The following options and additions

The axis of laser radiation is parallel to the axis of the rocket.

When the laser radiation axes and the missile axis are parallel, it is easier to direct the laser at the target with the laser guidance system, since it is not necessary to additionally significantly change the angle of the laser to the axis of the missile flying at the target.

There is a simple option when the axis of propagation of laser radiation is not only parallel to the axis of the rocket, but also, in addition, coincides with the axis of the rocket. For this simple option, a laser guidance system may not be available. In this case, the laser is automatically aimed at the target by the missile guidance system. If the rocket flies directly at the target, then there are options when the axis of the rocket in flight is directed at the target. This means that the axis of propagation of laser radiation is simultaneously directed at the target, since the axes coincide for this variant. And in this case, the functions of the laser guidance system are performed by the missile guidance system.

The device comprises a laser guidance system, wherein the laser guidance system is connected to the laser. In this embodiment, the laser guidance system further aims the laser at the target.

The laser is mounted on a gimbal connected to a rocket.

In this supplement, the laser can be stabilized by a system of gyroscopes in order to achieve a more accurate aiming, and the cardan suspension sets the exact direction of the axis of propagation of laser radiation to the target.

The laser is mounted in the bow of the rocket.

In this add-on, the laser is more simply aimed at the target by the coordinated actions of the missile guidance system and the laser guidance system.

The laser is connected to the fairing made in front of the laser along the direction of the rocket.

In this supplement, fairings reduce air resistance during missile flight.

The laser is connected to a removable fairing made in front of the laser along the rocket. The fairing is connected to the squib.

In this supplement, the fairing can be disconnected from the rocket before turning on the laser beam. For example, using a squib.

On the axis of the laser optical radiation, an inclined mirror is made connected to the laser guidance system. The device comprises a fairing made in front of the laser from the side of the nose of the rocket, and on the axis of the laser optical radiation an inclined mirror is made connected to the laser guidance system, and a window is made in front of the inclined mirror in the fairing, while it is possible to pass laser radiation through the window.

In this embodiment, turn on the laser, create a laser beam and direct it at an inclined mirror. The optical laser radiation is directed to an inclined mirror, reflected, directed to the window and brought out of the fairing through the window. In this case, the laser guidance system rotates the mirror and directs the laser beam at the target.

The fairing is made of a material transparent to laser radiation, and it is possible to pass the laser radiation through the fairing.

In this supplement, laser radiation is freely passed through the fairing.

The laser is made in the form of a chemical laser.

This add-on uses the well-known military version of a chemical laser. You can use well-known versions of chemical warfare lasers that are used to shoot down missiles.

The fairing is made of heat resistant material.

In this embodiment, a heat-resistant cowl is used to protect it from overheating. Fairing at high, for example, supersonic, rocket speeds are heated by friction against air. Therefore, heat-resistant material is used when creating a fairing.

The device includes an additional fairing made around the first fairing with the ability to separate from the rocket, and the first fairing is made of a material transparent to the laser radiation.

In this embodiment, an additional fairing protects the first fairing from heating during friction against air until the time when a command is issued to prepare for the inclusion of the laser beam. Before giving such a command, the additional (external) fairing is disconnected. For example, using a squib. For a short time before turning on the laser beam, the first (internal) fairing does not have time to heat up very much before turning on the laser beam. After disconnecting the additional fairing, the laser is turned on, and its beam is freely passed through the first (internal) fairing, transparent for its radiation.

The missile contains a nozzle, while the nozzle is made in the form of a Laval nozzle.

In this addition, a Laval nozzle creates a supersonic flow.

The nozzle block is connected to a direct energy conversion unit.

In this supplement, a second method variant is carried out. The rocket engine contains small nozzles with a cross section of 1-2 mm, which create a jet of fuel to create laser radiation.

The missile is made in the form of a cruise missile.

In this embodiment, the device can be sent flying with its cruise missile at a low altitude, inaccessible to radars. In this case, various targets of a potential adversary can hit in flight with laser radiation. In this case, the device can be used as a means of destroying manpower and equipment, and can destroy a living beam and equipment of a potential enemy with a laser beam.

Alternatively, a device with its own cruise missile or with its own missile, which is part of the device, can be released into flight, for example, from an object. For example, from an airplane, from another rocket or from a ship.

And then in the device with a laser beam, his laser can destroy manpower and equipment of a potential enemy.

Alternatively, the device can be produced with its cruise missile or with its missile, which are part of the device, from the object protected by the device. For example, from a ship, from an airplane, or from a large rocket. For example, from Poplar M or Yars.

In this embodiment, the device destroys missiles of a potential enemy flying to the protected object with a laser beam. Previously, the device is brought closer to them, and from a reduced distance destroyed by a laser beam.

At the same time, fragments from the explosion of missiles of the probable enemy cannot hit the protected object due to the large distance of the protected objects from the place of the explosion.

The device contains an MHD generator, and the laser contains a pumping system, while the MHD generator is made from the tail of the rocket, connected to the rocket so that it is possible to direct the flame of the working rocket engine into the MHD generator, and the MHD generator is configured to generate current when it enters MHD flame generator operating rocket engine and direct current to the laser pump system.

MHD generator is self-excited.

In these embodiments, the flame of a working rocket engine is sent to a self-amplifying MHD generator. Due to this, an electric current is created in it, which is released according to the positive feedback scheme. And due to this, the current is amplified by a known method. In this case, the current is directed to the laser pumping system. The pump system includes a laser and generates radiation, and increase the radiation power as the rocket engine continues to operate. When the power of the pumping system is increased to a maximum, the current growth is slowed down and the current strength is set to the maximum value. For example, due to an increase in electrical resistance in the pump system. This can be achieved by using materials in the pumping system in which the electrical resistance increases with increasing temperature. And in this mode, with a maximum radiation power, the laser is forced to work until the target is destroyed by its radiation.

The flames of a working rocket engine are directed inside the working volume of the MHD generator installed below the bottom of the rocket, and the MHD generator creates an electric current and directs it to the laser pump system, while the laser pump system turns on the laser and creates laser radiation.

The missile is coated with a mirror coating, made with the ability to reflect optical radiation.

The fairing is coated with a mirror coating, made with the ability to reflect optical radiation.

The side surface of the laser is coated with a mirror coating, made with the ability to reflect optical radiation.

In these additions, the mirror coating reflects the laser optical radiation of the combat lasers of the likely enemy attacking the device.

Specifically, the optical coating reflects the optical radiation of the combat lasers of a potential adversary, incident on the surface of the rocket, on the fairing and on the side surface of the laser.

The laser guidance system contains two additional lasers and a computer. In this supplement, a combat laser is aimed at a target with one additional laser, and weather conditions are assessed with a second additional laser. Data is transmitted to a computer, and the computer sets the optimal direction and time for turning on the combat laser. Like in the prototype.

The laser is lifted by a rocket beyond the atmosphere.

The rocket is launched into the flight by the launch complex of the rocket, and in addition, an additional laser from the launch complex is sent to the flame of the working rocket engine, the laser is turned on, a laser beam is created and the flame of the working rocket engine is heated with a laser beam. Heating the flame increases the rate of expiration of the working fluid from the rocket. And, thereby, additionally accelerates the rocket.

The device comprises a rocket launch complex, configured to send a rocket into flight, and an additional laser connected to the launch complex, configured to direct a laser beam to the flame of a working rocket engine during a rocket flight and heat the flame with a laser beam.

The radiation of the flame of the operating rocket engine is directed to the inner surface of the resonator, made below the bottom of the rocket around the outlet of the nozzles of the rocket engine and around the axis of the rocket at a safe distance from the nozzles, while the radiation is reflected by a mirror layer of the inner surface of the resonator and is directed at least once in the direction of the opposite side of the resonator, and the flame of a working rocket engine is heated by reflected radiation.

In this embodiment, the flame of the rocket is additionally heated to increase traction.

Also, this addition can be used in a laser to create laser radiation by repeatedly reflecting radiation from the cavity wall, amplifying the radiation due to its generation by the active medium and subsequent removal from the resonator. For example, using a translucent mirror on one of the walls of the resonator.

For this addition, the device comprises a resonator made below the rocket bottom around the exit holes of the rocket engine nozzles and around the rocket axis at a safe distance from the nozzles, while the inner surface of the resonator is coated with a mirror layer and is configured to direct the flame of the working engine towards the opposite side of the resonator. rockets.

The device comprises a resonator made below the rocket bottom around the exit openings of the rocket engine nozzles and around the rocket axis at a safe distance from the nozzles, while the inner surface of the resonator is coated with a mirror layer and is configured to direct the radiation of the flame of the working rocket engine toward the opposite side of the resonator, this rocket is configured to direct and pass the flame of a working rocket engine through the working volume of the resonator.

The device comprises a rocket launch complex, configured to send a rocket into flight, and an additional laser connected to the launch complex, configured to direct a laser beam to the flame of a working rocket engine during a rocket flight and heat the flame with a laser beam.

In this addition, the laser beam of the additional laser of the launch complex of the rocket additionally heats the flame of the rocket to increase its specific impulse.

In the method, the rotary mirror of the laser guidance system, made on the axis of propagation of laser radiation, is rotated to direct the laser radiation to the target, while the flame of the working rocket engine is directed inside the working volume of the laser mounted below the bottom of the rocket, and the flame is used as an active medium for generating laser radiation wherein the laser is turned on, laser radiation is generated, the radiation from the laser being removed and directed to a rotary mirror, while the laser radiation is reflected from the rotary mirror and direct to the target.

In this embodiment, a well-known method of generating laser radiation in a supersonic gas stream is used [Chemical lasers (AN ORAEVSKIY, 1999), PHYSICS].

To obtain lasing in a chemical laser for a long time, it is necessary to change the reagents in the reactor rather quickly and be able to produce chemically active centers continuously throughout the entire laser operation time. Since reactions involving radicals are very fast, transonic or even supersonic pumping speeds are needed to change the substance in the reactor.

A long-acting chemical laser consists of a source of chemically active centers; systems for mixing free atoms or radicals with another component, the reaction with which gives excited molecules; the reactor where the active laser medium is created, and the optical cavity. In addition, you need a quick supply of source and pumping of spent reagents.

Let us consider how this general scheme is practically realized in various types of chemical lasers of continuous (continuous) action.

(DF-CO2) laser. This laser is based on energy transfer from vibrationally excited DF molecules to CO2 molecules in a mixture of D2 + F2 + CO2. The reaction is initiated by the radical:

NO + F2 NOF + F,

and then comes the chain edition of deuterium with fluoride. The resulting DF molecules quickly transfer energy to the CO2 molecules, which serve as the emitter.

If carbon dioxide molecules are not introduced into the reacting mixture, it is possible to obtain generation in the same laser circuit also due to the emission of DF * molecules. However, experiments have shown that DF (or HF -) - lasers operating according to such a scheme are noticeably inferior to a (DF-CO2) laser. The fact is that the excited molecules live noticeably longer than the DF or HF molecules, so when the CO2 molecules are added to the mixture, the chemolaser chain length noticeably increases. To obtain lasing by radiation of HF (DF) molecules, the thermal method for producing atomic fluorine (thermal reaction initiation) is more effective.

HF (DF -) - laser with thermal reaction initiation. A diagram of such a laser is shown in FIG. 4. Molecular fluorine, hydrogen and helium are introduced into the combustion chamber. Fluorine is in large excess with respect to hydrogen. In the chamber, the usual equilibrium combustion of hydrogen in fluorine occurs with the release of heat sufficient to dissociate an excess of molecular fluorine.

The ratio of the components in the combustion chamber is selected so as to ensure almost complete dissociation of the excess fluorine molecules (the degree of dissociation is greater than 95%). This requires a temperature of 1500-1800 K. The reaction in a highly heated mixture cannot be used to create an active medium: the mixture must be cooled. To do this, it is passed through a set of nozzles (nozzle lattice), accelerating the flow in them to supersonic speeds, which is accompanied by gas cooling. At the exit of the nozzles, a stream of deuterium molecules is mixed into the supersonic flow. As a result of mixing these two flows, a working mixture is formed, the reaction in which F + D2 DF * + D leads to the formation of vibrationally excited deuterium fluoride molecules that generate laser radiation.

The rocket contains a nozzle block containing a nozzle lattice, and the lattice contains at least two nozzles.

The nozzle is made in the form of a Laval nozzle.

In this embodiment, the method of the device for its implementation is as follows.

The key issue here is the mixing process. He must be fast. Therefore, the nozzle block is not a separate nozzle, but a nozzle lattice consisting of small nozzles dividing the total flow into jets of small cross section - of the order of 1-2 mm. Deuterium is supplied in the form of jets of small cross section, which ensures a sufficiently effective mixing of reagents [Chemical lasers (AN ORAEVSKIY, 1999), PHYSICS].

Passing the stream through the Laval nozzle, make the jet supersonic.

Acceleration of the jet in the nozzle block also solves other problems. The reaction of atomic fluorine with deuterium is very fast. At a low flow velocity, the width of the active (generating) zone in the direction of flow is small and it is difficult to obtain a laser beam. With a supersonic flow velocity of more than 10 km / s practically achieved and a reagent pressure in the generation zone of 5-10 torr, its width is several centimeters, and this is quite acceptable for obtaining a beam of good quality. The supersonic flow also provides a quick pumping of matter, making it possible to obtain high radiation powers with relatively small surfaces of nozzle arrays.

Why do you need helium? The fact is that significant energy is released in the reaction of atomic fluorine with deuterium. Part of this energy (about 15%) is carried away by laser radiation. The remainder ultimately heats the stream. It is known from gas dynamics that heating can greatly inhibit a supersonic jet and even suppress the supersonic outflow process (converting it to subsonic). And this will completely upset the harmony of the conditions necessary for the generation of laser radiation. Dilution of a supersonic jet with an inert gas that does not enter into a chemical reaction and reduces the amount of heat released per unit mass of the gas stream prevents dangerous overheating, leading to disruption of the supersonic flow.

In order to avoid misunderstandings, we note that the HF molecules leaving the atomic fluorine and helium from the combustion chamber are only an accompanying reaction product. They are not emitters in the laser and, moreover, in the future they play a negative role, deactivating the excited molecules in the laser zone. Such deactivation occurs especially actively if vibrationally excited molecules of the same sort emit. That is why deuterium is introduced into the laser zone if hydrogen was used as fuel in the combustion chamber.

The use of hydrogen and fluorine compounds in rocket engines as a fuel has been well known for a long time. See, for example, [Space Engines: Status and Prospects. Moscow, Mir, 1988, p. 416]. Therefore, a rocket with such an engine and with such fuel can be used to supply the active substance to a chemical laser, which also uses such chemical elements and substances as an active medium for creating laser radiation.

The radiation of the flame of the operating rocket engine is directed to the inner surface of the resonator, made below the bottom of the rocket around the outlet of the nozzles of the rocket engine and around the axis of the rocket at a safe distance from the nozzles, while the radiation is reflected by a mirror layer of the inner surface of the resonator and is directed at least once in the direction of the opposite side of the resonator, and the flame of a working rocket engine is heated by reflected radiation.

The flame of a working rocket engine is directed inside the working volume of the laser, mounted below the bottom of the rocket, and the flame is used as an active medium for generating laser radiation, while the laser is turned on and the laser radiation is generated,

A rotary mirror made on the axis of propagation of laser radiation is rotated with the possibility of directing laser radiation to the target, while the laser is turned on and the laser radiation is generated, the radiation from the laser is output and directed to the rotary mirror, while the laser radiation is reflected from the rotary mirror and directed to the target.

The flame of a working rocket engine is directed into the working volume of the direct energy conversion unit installed below the bottom of the rocket, and the installation creates an electric current and directs it to the laser pump system, while the laser pump system turns on the laser and creates laser radiation.

The flames of a working rocket engine are directed inside the working volume of the MHD generator installed below the bottom of the rocket, and the MHD generator creates an electric current and directs it to the laser pump system, while the laser pump system turns on the laser and creates laser radiation.

The rocket is launched from the protected object, while the rocket is launched in the direction of the target.

In this addition, the protected object is connected to the rocket launch complex. The rocket is connected to the protected object and it is possible to launch the rocket in the direction of the target.

The target is found by the target detection system, while the target is found by at least one radar station of the system using radar, and information about the target is transmitted from the system to the rocket and to the laser.

In this supplement, the device comprises a target detection system, the system comprising at least one radar station and the possibility of transmitting information from the system to the rocket and to the laser is provided.

The target is found by the target detection system, while the target is found by at least one satellite by receiving radiation from the target, and information about the target is transmitted from at least one satellite to the rocket and to the laser.

In this supplement, the device comprises a satellite target detection system comprising at least one satellite, and it is possible to transmit information from at least one satellite to a rocket and to a laser.

An additional missile launches a cartridge with a warhead, and from the cartridge then launches at least one warhead in the form of a laser rocket.

In this supplement, the device comprises a cartridge with a warhead, and at least one warhead contains a missile with a laser.

A rocket with a laser is launched into flight by an additional booster block.

In this supplement, a laser rocket is connected to an additional booster block.

A rocket with a laser is launched into flight with an additional rocket.

In this supplement, a laser rocket is connected to an additional rocket.

A rocket with a laser is launched into flight from a protected object made in the form of an additional rocket.

In this supplement, the protected object is made in the form of an additional missile, for example, a Topol M or Yars ballistic missile.

A laser rocket is launched into flight from a protected object made in the form of an airplane.

In this supplement, the protected object is designed as an airplane.

A laser rocket is launched into flight from a protected object made in the form of a ship.

In this supplement, the protected object is made in the form of a ship.

A missile is launched flying in the form of an anti-tank guided missile with a cumulative charge. In this case, the laser connected to the rocket is turned on, the rocket and the laser are directed by the missile guidance system at the tank, the laser is turned on and the recess is burned in the dynamic armor of the tank. Explosives of dynamic tank armor are evaporated from the cavity by heating with a laser. Then, a missile, made in the form of an anti-tank guided missile (pturs), enters the deepening of the dynamic armor of the tank. The rocket in the recess is pushed with the remaining armor of the tank and the cumulative charge of a purt is blown up. In this case, a cumulative stream is created and then the remaining part of the tank’s armor is burned through a depression deprived of the dynamic explosive armor of the tank evaporated by the cumulative jet of the cumulative charge of the pts.

In this embodiment, the missile is made in the form of an anti-tank guided projectile (pturs) with a cumulative charge.

The rocket may contain at least two stages, while the stage is made of a laser.

After the stage is disconnected, the target detection system finds the target, for example, a missile intercepting the intercept, the laser guidance system directs the laser at the target and destroys the target.

In this embodiment, the disconnected stages additionally protect with their lasers from the enemy anti-missile the stage whose engine is running.

This will allow to launch into space and leave in orbit detached stages of missiles with lasers to destroy launching missiles, anti-missiles and enemy aircraft.

This will make it possible to quickly deploy in space a global missile defense system from detached stages of missiles with lasers in the event of a military conflict. This will make it possible to deliver a preemptive nuclear strike and avoid a retaliation strike.

It will also allow destroying the enemy’s missiles from the outer space with outer lasers from outer space and delivering a nuclear strike by those stages of missiles that continue to accelerate from outer space. And protect the accelerated stages with their lasers and anti-missile warheads with lasers.

The method and device for its implementation can be used to destroy planes and drones, as well as to defeat manpower and equipment of a potential enemy.

In this case, a missile is simply aimed at them as a target. Then at the right distance turn on the laser and destroy them with a laser beam as a target.

Below are examples of the combat use of the device in the Russian missile defense system (ABM), which can change the country's military doctrine in the event of a possible nuclear war.

Examples of combat use of the device in the missile defense system (ABM) of Russia

1. A concrete example of a probable attack by a probable adversary on Russia when a country is hit by a ballistic nuclear missile.

Probable adversary’s ballistic missiles are flying. At the same time, missiles of the Russian missile defense system are sent to fly and are brought closer to the probable enemy’s missiles.

At the moment of separation of the last stages of missiles of a probable enemy, lasers of devices from reduced (close) distances shoot targets, for example, the last stages of missiles. At the same time, an increased amount of laser energy is directed to the surface of the last stages of missiles (targets) by reducing the distance between them in proportion to decreasing the distance squared, which significantly increases the likelihood of damage to the last stages of missiles (targets).

2. A concrete example of a probable attack by a probable adversary on Russia, when a country strikes back with a nuclear strike by Fields M and Yarsami.

Poplars M and Yars start. The missiles of a potential adversary of his missile defense system are attacked at the start of Topol M and Yars, when they are most vulnerable. At the Russian border, missile systems of the Russian missile defense system produce devices - missiles with lasers. The missiles of the devices are sent to the missiles of the probable enemy’s missile defense system, they are brought closer to them to the minimum distance, and laser devices from the minimum distance they are shot with laser beams. Moreover, with this option they can destroy missile defense systems of a potential enemy even when missiles of the Russian missile defense system cannot catch missiles of a potential enemy. For example, due to the fact that they started much earlier and have due to this a gain in speed. Or performed a successful missile defense maneuver. Or are located outside the missile strike zone of the Russian missile defense system.

Next set of options

Good results are obtained by the simultaneous use in the device of several fundamentally different lasers designed to destroy fundamentally different targets.

For example, a rocket is launched into flight, on which a chemical laser and one or more nuclear-pumped lasers are connected, connected to a nuclear or thermonuclear charge.

In this case, first, a missile of a potential adversary going to intercept devices is struck with a chemical laser, and then ballistic missiles of a possible adversary are hit by nuclear-pumped lasers.

The operation of the device with a chemical laser is described above.

One or more nuclear-pumped lasers hit one or more targets as follows.

Previously, a multistage rocket is launched into flight and directed at the target, while the laser is turned on, laser radiation is generated and laser radiation hits the target. Moreover, the laser is launched into a flight on a rocket in the direction of the target, while the rocket is aimed at the target, the distance to the target is reduced by the rocket, and the laser is turned on, laser radiation is generated and laser radiation hits the target at a reduced distance to the target.

At the same time, one of the stages is brought together with a nuclear or thermonuclear charge and with lasers with nuclear pumping to the desired distance to hit the target.

At the same time, several nuclear-pumped lasers individually target individual targets.

Carry out a nuclear charge explosion. Radiation from a nuclear explosion pump lasers, create powerful radiation and hit individual targets with laser radiation.

In this embodiment, the device for implementing the method of target destruction contains a nuclear or thermonuclear charge, and the laser is made in the form of a laser with a nuclear pump.

A device for implementing a method for hitting a target contains at least two nuclear-pumped lasers.

The rocket contains at least two stages, while a nuclear or thermonuclear charge is connected to one stage, and a nuclear-pumped laser is made outside the side surface of the stage.

The missile contains at least two stages, while a nuclear or thermonuclear charge is connected to one stage, and at least two nuclear-pumped lasers are made outside the side surface of the stage, and it is possible to individually target the laser to an individual target.

The missile contains at least two stages, while a nuclear or thermonuclear charge is connected to one stage, and at least two nuclear-pumped lasers are made outside the side surface of the stage, and it is possible to individually target the laser to an individual target, and at the same time lasers are made around the stage.

There is an article on the Internet about a nuclear-pumped laser [A nuclear-pumped laser. Wikipedia]. We take the elements of the device, the principle of operation, and the parameters of a nuclear-pumped laser from this article. Also from this article we take evidence that such lasers are quite real and comply with the principle of practical real applicability. Accordingly, new in the invention in comparison with the information from this article is that a laser brings the laser closer together with the target to the desired distance to the target, and only then the laser is turned on. This provides an increase in the radiation power incident on the target, necessary to hit the target. Accordingly, the rate of increase in the intensity of the laser radiation incident on the target is also increased by approaching the laser using a rocket with the aim of:

“During the underground nuclear explosions in 1983 (Nevada training ground), evaluation tests of the first X-ray lasers were carried out).

In 1983, the first report was published on the parameters of laser radiation measured during the experiment: a wavelength of about 14 Ǻ, a pulse duration of J 10 ^-9 s, and the radiation power obtained from an X-ray laser during an atomic explosion exceeded 400 TW (!). The design of the laser was not described in detail, but it became known that thin metal rods were its working medium.

After the explosion of a nuclear charge, the substance of the working rods turns into a fully ionized plasma. When the electron temperature decreases slightly and recombination begins mainly at the lower levels, radiation occurs in the x-ray part of the spectrum. Since the time of plasma emission is measured in picoseconds, and the cloud of plasma heated to millions of degrees does not have time to significantly change its geometry, it preserves the shape and direction of the working rod. Since mirrors for working with X-rays with a wavelength of about 10 Ǻ do not yet exist, the X-ray laser should probably work without a resonator. Therefore, the beam divergence will be determined by two factors: diffraction and rod geometry. More precisely, the largest value of them. Taking a small divergence value, we obtain the optimal diameter value: D = (lL) ^1/2 . For wavelengths of about 10-14 Ǻ and L = 7 m, this gives D = 0.1 mm. Even if in the process of ionization and recombination of a substance its geometry changes insignificantly, the beam divergence reaches ~ 10 ^-5 rad. However, a more detailed calculation shows that by the time of recombination the plasma bunch can expand to 0.8-1 mm, in which case the laser beam divergence will be of the order of 10 ^-4 to 10 ^-5 .

To destroy an intercontinental missile, that is, to achieve energy densities of about 10-20 kJ / cm ² at a distance of up to 1000 kilometers with a beam divergence of 10 ^-5 , the pulse of such a laser should have an energy of ~ 10 ¹⁰ J. At a laser efficiency of about 8-10 % and when the distance of the rod from the nuclear charge is ~ 1 m, the charge power should be about 10 ¹⁵ J, or about two hundred kilotons of TNT equivalent. In this case, the supposedly lion's share of the energy of a nuclear explosion will go to the evaporation of the working rods (rod), and the string itself is oriented toward the charge not by the end but by the side surface. However, in the literature on this subject, charges of much lower power are mentioned. It is possible to use not one, but several dozen (about 50-100) parallel-oriented rods aimed at the target. It is also possible that engineers will try to create an explosion energy concentrator on a single string using the effect of X-ray reflection from crystals or multilayer X-ray mirrors (with high reflection characteristics), and significant success is expected in this area.

Modern technologies allow the creation of fairly compact x-ray lasers (weighing about 1-2 tons), convenient for launching into orbit using ballistic missiles. Computer control of individual rods allows you to hit up to several dozen targets at the same time or guaranteed to hit one. Thus, from a number of publications it can be concluded that the X-ray laser with the appropriate development of technology can become one of the main tools in space weapons and missile defense systems. ”

The combination of a chemical laser and a group of nuclear-pumped lasers in the device makes it possible to solve a complete set of problems facing a ballistic missile with a cartridge with multiple warheads.

A missile connected to a chemical laser and to a cartridge with separable warheads containing nuclear-pumped lasers is sent flying in the direction of the intended target. A chemical laser is used to hit the missiles of a potential enemy’s missile defense system, and then the warheads are divided into cassettes. In this case, the warheads are removed from each other to a safe distance, for example, 100 km, the lasers with the nuclear pumping of one of the warheads are pointed at the ballistic missiles of the probable enemy, and the nuclear-pumped lasers are pumped with an explosion of a nuclear or thermonuclear charge. Lasers create radiation and hit ballistic missiles of a potential enemy. The remaining warheads then hit the new targets with their nuclear or thermonuclear charges. At the same time, other warheads can also have chemical lasers for hitting missiles of a potential enemy and lasers with nuclear pumping, which can be used to hit missiles that intercept other warheads, ballistic missiles of a potential enemy, and other targets.

Such a set of ballistic missile lasers can significantly increase the country's defense capability and qualitatively reduce the effectiveness of the probable enemy’s missile defense system.

Claims (68)

1. The method of hitting a target, which consists in the fact that the combat laser, configured to shoot down a rocket, is launched into flight and directed at the target, the laser being turned on, laser radiation is generated and laser radiation is used to hit the target, characterized in that the laser is launched into flight on the rocket in the direction of the target, while the rocket is directed to the target, the distance to the target is reduced by the rocket, and the laser is turned on, laser radiation is generated and laser radiation hits the target at a reduced distance to the target. 2. The method of hitting a target according to claim 1, characterized in that the laser is lifted by a rocket out of the atmosphere. 3. The method of hitting a target according to claim 1, characterized in that the rocket is launched into the flight by the launch complex of the rocket, and in addition, an additional laser from the launch complex is sent to the flame of the working engine of the rocket, the laser is turned on, a laser beam is created and the flame of the working rocket engine is heated with a laser beam. 4. The method of hitting a target according to claim 1, characterized in that the flame of the working rocket engine is directed inside the working volume of the resonator, which is made from the bottom of the rocket bottom around the exit openings of the nozzles of the rocket engine and around the axis of the rocket at a safe distance from the nozzles, while the radiation of the flame working rocket engine is directed to the inner surface of the resonator, while the radiation is reflected by a mirror layer of the inner surface of the resonator and at least once directed in the direction of the opposite side of the resonator nator, moreover, the flame of a working rocket engine is heated by reflected radiation. 5. The method for hitting a target according to claim 1, characterized in that the flame of the working rocket engine is directed inside the working volume of the laser mounted below the bottom of the rocket, the flame being used as an active medium for generating laser radiation, the laser being turned on and the laser radiation is generated, 6. The method of hitting a target according to claim 1, characterized in that the rotary mirror made on the axis of the laser radiation propagation is rotated to direct the laser radiation to the target, the laser is turned on and the laser radiation is generated, and the radiation from the laser is output and directed to the rotary mirror while the laser radiation is reflected from the rotary mirror and sent to the target. 7. The method of hitting a target according to claim 1, characterized in that the flame of the working rocket engine is directed inside the working volume of the direct energy conversion unit installed below the bottom of the rocket, the installation creating an electric current and directing it to the laser pump system, while the laser pump system turn on the laser and create laser radiation with the laser. 8. The method of hitting a target according to claim 1, characterized in that the flame of the working rocket engine is directed inside the working volume of the MHD generator installed below the bottom of the rocket, and the MHD generator creates an electric current and directs it to the laser pump system, and the laser pump system is turned on laser and create a laser laser radiation. 9. The method of hitting a target according to claim 1, characterized in that the rocket is launched from the protected object, while the rocket is launched in the direction of the target. 10. The method for hitting a target according to claim 1, characterized in that the target is found by the target detection system, while the target is found by at least one radar station of the system using radar, and information about the target is transmitted from the system to the rocket and to the laser. 11. The method for hitting a target according to claim 1, characterized in that the target is found by the target detection system, while the target is found by at least one satellite by receiving radiation from the target, and information about the target is transmitted from at least one satellite to the rocket and to laser. 12. The method for hitting a target according to claim 1, characterized in that an additional missile launches a cartridge with a warhead, and from the cartridge then launches at least one warhead in the form of a laser missile. 13. The method of hitting a target according to claim 1, characterized in that the rocket with the laser is launched into flight by an additional booster block. 14. The method of hitting a target according to claim 1, characterized in that the missile with the laser is launched into the flight with an additional missile. 15. The method of hitting a target according to claim 1, characterized in that the missile with the laser is launched into flight from the protected object, made in the form of an additional missile. 16. The method of hitting a target according to claim 1, characterized in that the rocket with the laser is launched into flight from the protected object, made in the form of an airplane. 17. The method of hitting a target according to claim 1, characterized in that the rocket with the laser is launched into flight from the protected object, made in the form of a ship. 18. A device for implementing a method of hitting a target, comprising a combat laser configured to shoot down a missile, characterized in that it comprises a missile and a missile guidance system, the laser being connected to the missile and the missile being connected to the missile guidance system. 19. A device for implementing the method of hitting a target according to claim 18, characterized in that it comprises a laser guidance system, wherein the laser guidance system is connected to the laser. 20. A device for implementing the method of hitting a target according to claim 18, characterized in that the laser is mounted on a gimbal suspension connected to a rocket. 21. A device for implementing the method of hitting a target according to claim 18, characterized in that the system of gyroscopes containing at least two gyroscopes configured to stabilize the position of the laser in space is connected to a laser. 22. A device for implementing the method of hitting a target according to claim 18, characterized in that the laser is mounted in the bow of the rocket. 23. A device for implementing the method of hitting a target according to claim 18, characterized in that the axis of the laser radiation coincides with the axis of the rocket. 24. A device for implementing the method of hitting a target according to claim 18, characterized in that the axis of the laser radiation is parallel to the axis of the rocket. 25. A device for implementing the method of hitting a target according to claim 18, characterized in that the laser is connected to a fairing made in front of the laser along the direction of the rocket from the side of the nose of the rocket. 26. A device for implementing the method of hitting a target according to claim 18, characterized in that the laser is connected to a removable fairing made in front of the laser along the direction of the rocket from the side of the nose of the rocket. 27. A device for implementing the method of hitting a target according to any one of paragraphs. 18, 25 or 26, characterized in that the fairing is connected to the squib. 28. A device for implementing the method of hitting a target according to any one of paragraphs. 18 or 19, characterized in that on the axis of the optical radiation of the laser made an inclined mirror connected to the laser guidance system. 29. A device for implementing the method of hitting a target according to claim 18, characterized in that it comprises a cowl made in front of the laser from the side of the nose of the rocket, and an inclined mirror connected to the laser guidance system and an inclined mirror in a window is made in the fairing, while it is possible to pass through the laser radiation window. 30. A device for implementing the method of hitting a target according to any one of paragraphs. 18, 25, 26 or 29, characterized in that the fairing is made of a material transparent to laser radiation, and it is possible to pass the laser radiation through the fairing. 31. A device for implementing the method of hitting a target according to claim 18, characterized in that the laser is made in the form of a chemical laser. 32. A device for implementing the method of hitting a target according to any one of paragraphs. 18, 25, 26 or 29, characterized in that the fairing is made of heat-resistant material. 33. A device for implementing the method of hitting a target according to any one of paragraphs. 18, 25, 26 or 29, characterized in that it contains an additional fairing made around the first fairing with the ability to separate from the rocket, and the first fairing is made of a transparent material for laser radiation. 34. A device for implementing the method of hitting a target according to claim 18, characterized in that the missile is made in the form of a cruise missile. 35. The device for implementing the method of hitting a target according to claim 18, characterized in that it contains an MHD generator, and the laser contains a pump system, while the MHD generator is made from the tail of the rocket, connected to the rocket so that it is possible to direct the flame of a working engine rockets into the working volume of the MHD generator and removed from the volume, and the MHD generator is made with the ability to create a current when the flame generator of the working engine of the rocket enters the working volume of the MHD generator and direct the current to the pump system azera. 36. A device for implementing the method of hitting a target according to any one of paragraphs. 18 or 35, characterized in that the MHD generator is self-excited. 37. A device for implementing the method of hitting a target according to claim 18, characterized in that the missile is made in the form of a missile of a missile defense system. 38. A device for implementing the method of hitting a target according to claim 18, characterized in that the missile is coated with a mirror coating made with the ability to reflect optical radiation. 39. A device for implementing the method of hitting a target according to any one of paragraphs. 18, 25, 26 or 29, characterized in that the fairing is coated with a mirror coating made with the ability to reflect optical radiation. 40. A device for implementing the method of hitting a target according to any one of paragraphs. 18 or 19, characterized in that the laser guidance system contains two additional lasers and a computer. 41. A device for implementing the method of hitting a target according to claim 18, characterized in that it comprises a rocket launch complex configured to send a rocket into flight, and an additional laser connected to the launch complex, configured to direct rockets to the flame of a working engine during fly the laser beam rockets and heat the flame with a laser beam. 42. A device for implementing the method of hitting a target according to claim 18, characterized in that it contains a resonator made below the bottom of the rocket around the outlet of the nozzles of the rocket engine and around the axis of the rocket at a safe distance from the nozzles, while the inner surface of the resonator is coated with a mirror layer and made with the ability to direct the radiation of the flame of a working rocket engine in the direction of the opposite side of the resonator, while the rocket is made with the ability to direct and pass the flame of a running engine p chum through the working volume of the cavity. 43. The device for implementing the method of hitting a target according to claim 18, characterized in that a rotary mirror is made on the laser propagation axis, and it is possible to rotate the mirror so that the mirror reflects laser radiation onto the target, while the laser is mounted below the bottom of the rocket and it is possible to direct the flame of a working rocket engine into the working volume of the laser and pass the flame through the volume, and it is possible to use the flame as an active medium for generating laser of radiation. 44. A device for implementing the method of hitting a target according to claim 18, characterized in that it contains a direct energy conversion unit, and the laser contains a pump system, the installation being made from the tail of the rocket and connected to the rocket so that it is possible to direct the flame of the worker rocket engine into the working volume of the direct energy conversion unit and removed from the volume, the installation is configured to generate current when the flame of the working engine enters the working volume of the installation of the flame I rockets and direct current to the laser pump system. 45. A device for implementing the method of hitting a target according to claim 18, characterized in that the rocket is connected to the protected object and it is possible to launch the rocket in the direction of the target. 46. A device for implementing the method of hitting a target according to claim 18, characterized in that it comprises a target detection system, the system comprising at least one radar station and the possibility of transmitting information from the system to the rocket and to the laser. 47. A device for implementing the method of hitting a target according to claim 18, characterized in that it comprises a satellite target detection system containing at least one satellite, and it is possible to transmit information from at least one satellite to a rocket and to a laser . 48. A device for implementing the method of hitting a target according to claim 18, characterized in that it contains a cartridge with a warhead, and at least one warhead contains a missile with a laser. 49. A device for implementing the method of hitting a target according to claim 18, characterized in that the rocket with a laser is connected to an additional booster block. 50. A device for implementing the method of hitting a target according to claim 18, characterized in that the protected object is made in the form of an additional rocket. 51. A device for implementing the method of hitting a target according to claim 18, characterized in that the protected object is made in the form of an airplane. 52. A device for implementing the method of hitting a target according to claim 18, characterized in that the protected object is made in the form of a ship. 53. A device for implementing the method of hitting a target according to claim 18, characterized in that the laser is mounted below the bottom of the rocket and it is possible to direct the flame of the working rocket engine into the laser’s working volume and pass the flame through the volume, and it is possible to use the flame as an active medium for generating laser radiation. 54. A device for implementing the method of hitting a target according to claim 18, characterized in that the rocket comprises a nozzle block containing a nozzle grill, the grill containing at least two nozzles. 55. A device for implementing the method of hitting a target according to claim 18, characterized in that the rocket contains a nozzle, wherein the nozzle is made in the form of a Laval nozzle. 56. A device for implementing the method of hitting a target according to any one of paragraphs. 18 or 54, characterized in that the nozzle block is made on the side surface of the rocket, and the nozzle is made inclined with respect to the axis of the rocket. 57. A device for implementing the method of hitting a target according to any one of paragraphs. 18 or 54, characterized in that the nozzle block is made on the side surface of the rocket, and the nozzle is made inclined with respect to the axis of the rocket, and the device contains at least one pair of blocks made on different sides of the rocket symmetrically with respect to the axis of the rocket. 58. A device for implementing the method of hitting a target according to any one of paragraphs. 18 or 54, characterized in that the nozzle block is made on the side surface of the rocket, and the nozzles are made inclined with respect to the axis of the rocket, and the device contains at least one pair of blocks made on different sides of the rocket symmetrically with respect to the axis of the rocket, with a laser is connected by the unit and it is possible to pass the flame of a working rocket engine through the nozzles of the block and use the flame as a working active medium to create laser radiation. 59. A device for implementing the method of hitting a target according to any one of paragraphs. 18 or 54, characterized in that the nozzle block is connected to a direct energy conversion unit. 60. A device for implementing the method of hitting a target according to claim 18, characterized in that the laser is made on the side of the rocket. 61. A device for implementing the method of hitting a target according to any one of paragraphs. 18 or 60, characterized in that it contains at least one pair of lasers made on different sides of the rocket symmetrically with respect to the axis of the rocket. 62. A device for implementing the method of hitting a target according to claim 18, characterized in that the rocket contains at least two stages, while at least one stage has a laser. 63. A device for implementing the method of hitting a target according to claim 18, characterized in that it contains a nuclear or thermonuclear charge, and the laser is made in the form of a nuclear-pumped laser. 64. A device for implementing the method of hitting a target according to any one of paragraphs. 18 or 63, characterized in that it contains at least two nuclear-pumped lasers. 65. A device for implementing the method of hitting a target according to any one of paragraphs. 18 or 63, characterized in that the rocket contains at least two stages, while a nuclear or thermonuclear charge is connected to one stage, and a nuclear-pumped laser is made outside the side surface of the stage. 66. A device for implementing the method of hitting a target according to any one of paragraphs. 18 or 63, characterized in that the rocket contains at least two stages, while a nuclear or thermonuclear charge is connected to one stage, and at least two nuclear-pumped lasers are made outside the side surface of the stage, and it is possible to individually direct the laser to an individual target. 67. A device for implementing the method of hitting a target according to any one of paragraphs. 18 or 63, characterized in that the rocket contains at least two stages, while a nuclear or thermonuclear charge is connected to one stage, and at least two nuclear-pumped lasers are made outside the side surface of the stage, and it is possible to individually direct the laser to an individual the target and the lasers are made around the stage. 68. A device for implementing the method of hitting a target according to any one of paragraphs. 18 or 63, characterized in that the missile contains a cartridge with separable warheads containing at least two warheads, while at least one warhead contains a nuclear or thermonuclear charge and a nuclear-pumped laser, and it is possible to individually target the laser to an individual target.

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