RU2482581C2 - Combat laser - Google Patents

Abstract

FIELD: weapons and ammunition.

SUBSTANCE: combat laser comprises a source of energy, such as a horizontally installed liquid rocket engine with a supersonic nozzle. At the outlet of the nozzle there is an exhaust device installed as capable of rotation. Resonators are installed on the exhaust device and comprise ball hinged joints, providing for rotation of resonators in the vertical plane. The exhaust device is made as capable of regenerative cooling and comprises inner and outer walls. On the inner wall there is a layer of uranium 235, particles of uranium 235 are introduced into the wall itself.

EFFECT: invention makes it possible to increase accuracy of firing, to improve complex endurance, its fighting capacity and fire power.

15 cl, 16 dwg

Description

The invention relates to the field of weapons, and in particular to means and methods of conducting defensive operations using one or more controllable laser beams with incredible power nuclear pumping. The product code is striking.

Gas-dynamic laser G.L. [1-4] - a gas laser in which a population inversion is created in a system of vibrational energy levels of gas molecules by adiabatic cooling of heated gas masses moving at a supersonic speed. G. l consists of a heater, a supersonic nozzle (or a set of nozzles forming the so-called nozzle array), an optical resonator and a diffuser. In the heater, a specially selected mixture of gases is thermally excited (as a result of fuel combustion or heating using electric discharges and shock waves). When the gas flows in a supersonic nozzle, the mixture cools rapidly. The population inversion of the energy levels of the working component of the mixture, necessary for exciting the generation, is achieved if: 1) the rate of devastation (relaxation) of the lower level of the laser transition in the process of expansion is higher than the relaxation rate top. level; 2) top empty time. level greater than the characteristic so-called gas dynamic time (time of gas movement to the resonator). If these conditions are satisfied for determining a pair of energy levels, then due to the strong dependence of the relaxation times on the temperature and density of the gas, starting from a certain moment from the beginning of expansion, a rapid population drop is up. level is replaced by a slow, while the population of the lower continues to decrease at a noticeable speed. Part of the excess energy is up. level can be transformed in the resonator into the energy of the laser beam. The diffuser serves to inhibit the flow and increase the pressure of the gas that is released into the atmosphere.

Active environment. The specified requirements naib. vibrational states of molecules with long lifetimes (in comparison with electronic and rotational levels) fully correspond. The processes of vibrational relaxation allow: complete inversion of vibrational levels, and so-called. partial vibrational-rotational inversion. In accordance with this "working" particles, G.L. both polyatomic and diatomic heteronuclear molecules are used, which, unlike homonuclear molecules, have allowed vibrational-rotational transitions.

The first and naib. common is G.L. on the complete vibrational inversion between the levels 00 ⁰ 1 and 10 ⁰ 0 (or 02 ⁰ 0) of the CO ₂ molecule. The corresponding generation wavelengths are λ = 10.4–9.4 μm (Fig. 2). Level 00 ⁰ 1 corresponds to asymmetric vibrations of the CO ₂ molecule, levels 10 ⁰ 0 and 02 ⁰ 0 - to vibrations of deformation and symmetric types. However, in pure CO _{2, the} necessary ratio of the relaxation times of these levels is not satisfied. This ratio shifts to the right side when a certain number of H ₂ , H ₂ O molecules, He atoms, etc. are added. Their collisions with CO ₂ molecules empty the lower laser levels (10 ⁰ 0 and 02 ⁰ 0) much faster than level 00 ⁰ 1. An increase in the supply of vibrational energy in a chilled gas is also achieved by introducing a donor gas into the gas mixture in the prechamber, whose molecules relax slowly and are able to quickly transfer the energy stored in them to levels corresponding to asymmetric vibrations of the CO ₂ molecule. The role of the donor gas is usually played by excited N ₂ molecules, the vibrational levels of which are close to the levels of the CO ₂ molecule.

1%). Это обусловлено тем, что только 7-10% от энергии сгорания идет на возбуждение колебательного уровней молекулы CO₂. Кроме того, из-за релаксации потерь энергии в потоке, невысокого отношения энергии кванта лазерного излучения к энергии кванта, необходимого для возбуждения асимметричного колебания молекулы CO₂ (квантового кпд), и относительно небольшой эффективности резонатора не весь энергозапас может быть трансформирован в лазерное излучение. Реально в Г.л. на продуктах сгорания энергия, излучаемая на единицу массы сжигаемой смеси (уд. энергия излучения)

20 кДж/кг, а показатель усиления α≤0,5-1,0 M^-1.G.L. on combustion products is the simplest G.L., which has practical significance. In the prechamber, carbon-containing fuel is burned in the air, hot combustion products are passed through the nozzle apparatus and the resonator. Depending on the fuel used and the conditions of its combustion, pressure p ₀ , temperature T ₀ and chemical. the composition of the products in the prechamber varies widely (p ₀ = 5-100 atm, T ₀ = 1500-3000 K). In this way, as a rule, it is not possible to obtain high efficiency. G.L. on combustion products has a low efficiency (

one%). This is due to the fact that only 7-10% of the combustion energy goes to the excitation of the vibrational levels of the CO ₂ molecule. In addition, due to the relaxation of energy losses in the flow, the low ratio of the energy of the quantum of laser radiation to the quantum energy necessary to excite an asymmetric vibration of the CO ₂ molecule (quantum efficiency), and the relatively small resonator efficiency, not all of the energy storage can be transformed into laser radiation. Really in G.L. on combustion products, the energy emitted per unit mass of the mixture being burned (specific radiation energy)

20 kJ / kg, and the gain is α≤0.5-1.0 M ^-1 .

200-300 K). В таком варианте Г.л. (Г.л. "с подмешиванием") появляется дополнит. возможность повышения полного числа колебательно возбужденных молекул за счет нагревания донорного газа до более высоких температур T₀=4000-5000 K. Уд. энергия излучения достигает 50-100 кДж/кг, показатель усиления 3-5 м^-1, полный кпд ~2-3%.Other types of G.L. One of the ways to increase the efficiency of G. consists in reducing the relaxation of the losses of the stored vibrational energy. Due to the relatively high relaxation rates of vibrational levels of the CO ₂ molecule, almost all the energy lost by the medium is converted to heat, and this happens in the near-critical part of the nozzle, where the temperature and density of the gas are high. The absence of CO ₂ in this part of the stream minimizes energy loss. Therefore, the required amount of CO ₂ is introduced into the flow of the excited donor gas into the supersonic or transonic part of the nozzle. In this case, the temperature of the introduced CO ₂ may be low (

200-300 K). In this version, G.L. (G.L. "with mixing") appears to complement. the possibility of increasing the total number of vibrationally excited molecules by heating the donor gas to higher temperatures T ₀ = 4000-5000 K. radiation energy reaches 50-100 kJ / kg, gain of 3-5 m ^-1 , full efficiency ~ 2-3%.

Efficiency G.L. increases in the case when at least part of the stored energy can be converted into laser radiation with a large quantum efficiency. In the case of CO _2, this possibility is associated with the so-called cascade generation simultaneously at two transitions 00 ⁰ 1-10 ⁰ 0 (02 ⁰ 0) and 10 ⁰ 0 (02 ⁰ 0) -01 ¹ 0. The latter has a quantum efficiency of 71.6%. The conditions for the appearance of two-frequency generation are more stringent than in the single-frequency mode. They are easier to reach in G.L. "with mixing". As cascade radiation is removed from the resonator, the internal energy of the system decreases and the condition of two-frequency generation ceases to be satisfied. The vibrational energy remaining in the medium (upper transition) is transformed into laser radiation by the next resonator located downstream and tuned to the transitions 00 ⁰ 1-10 ⁰ 0 (02 ⁰ 0).

70-100 K. Наилучшие результаты получены для смесей CO₂ с Ar и Ne и сопловых аппаратов с большими степенями расширения. В качестве рабочего компонента в Г.л. используются и др. трехатомные молекулы (N₂O, COS, CS₂).G.L. also work on CO ₂ at other vibrational transitions, e.g. at transitions 03 ¹ 0-10 ⁰ 0, 03 ¹ 0-02 ² 0 and 02 ⁰ 0-01 ¹ 0 (λ = 18.4, 16.7 and 16.2 μm). In this case, it is necessary to freeze as much energy as possible in the system of deformation levels and symmetric vibrations of the molecule and cool the gas to temperatures

70-100 K. The best results were obtained for mixtures of CO ₂ with Ar and Ne and nozzle devices with large degrees of expansion. As a working component in G. other triatomic molecules (N ₂ O, COS, CS ₂ ) are also used.

The action of other type G.L. based on the inversion in the system of vibrational-rotational levels in diatomic heteronuclear molecules (CO, HCl, etc.). Inversion occurs between the rotational sublevels of various excited vibrational levels. If this excitation is small, then the rotational sublevels between which there is an inversion correspond to very large values of the rotational quantum number, and therefore have a small population. This, in turn, determines a small gain that is insufficient to excite the generation. Generation is excited if the so-called vibrational temperature T _count (effective temperature at which vibrational levels are populated) and gas temperature T are in the ratio T _count / T >> 1. Naib. a high value T _{col of} expanding gas can be stored in a system of weakly relaxing levels, e.g. in the system of levels of the CO molecule (λ = 5 μm). The necessary gas cooling is achieved in nozzle devices with a high degree of expansion.

Known multiple launch rocket system according to US Pat. RF №2277687, MKTU F43F 3/04, publ. 06/10/2006, which contains a wheeled chassis with a wheelhouse, a package of tubular guides with screw grooves and horizontal and vertical guidance drives of a package of tubular guides. A gyroscopic system for measuring the guidance angles of the tubular guide package is additionally placed on the package of tubular guides, and a console for setting the guidance angles of the package of tubular guides and a comparison device are located in the conning tower, the outputs of the gyroscopic measuring system and the console for setting the guidance angles are electrically connected to the input of the comparison device. The output of the comparison device is electrically connected to the drives of horizontal and vertical guidance of the tubular guide package, and the removal of the longitudinal axis of each tubular guide from the axes of horizontal and vertical guidance of the tubular guide package does not exceed a value determined by a given mathematical expression.

The disadvantage is manual reloading of the complex after each salvo.

Known articulated self-propelled anti-aircraft missile system according to the patent for the invention No. 2273815 dated 11/01/2004. This invention relates to the field of armament, in particular to an anti-aircraft missile system, which is made in the form of a base machine containing two extreme and one central section suspended between them by automatic device, with the possibility of uncoupling the extreme sections from the central. The central section is equipped with a radar station for illuminating targets and guiding missiles. Launching units with redundant control panels and an anti-aircraft guided missile launch system are installed at the extreme sections. The implementation of the complex allows to increase its maneuverability and reduce the length of the column during the march. However, the method of firing from this complex has several disadvantages:

- the impossibility of firing rockets with volley, bursts, and generally shells of the type "Smerch", "Hurricane", "Grad", and others of a similar class;

- the inability to transport, load launchers with such rockets;

- a significant decrease in the speed of movement on the march when reaching a combat position, since it is on a tracked track;

- the impossibility of delivering combat shells after firing their first salvo at the enemy.

However, the opposed complex has some common signs of firing with the claimed method of firing from the proposed complex - this is the ability to load the launcher with live shells in a combat position and the ability to transport these combat shells on a march to a combat position.

The aim of this invention is to increase the combat effectiveness of firing rockets of the "Smerch" type in one gulp, bursts and single shots by providing quick charging of the combat vehicle with a launcher with a set of rocket shells using the transport-loading vehicle of the complex, which is located directly and constantly with the combat vehicle, on which the launcher is located.

Famous multiple launch rocket launcher according to the patent of the Russian Federation No. 2400692, IPC F41F 3/04, publ. 10.27.2010 g, prototype. In this multiple launch rocket system, rockets containing a combat vehicle with a launcher in the upper part and one transport-loading vehicle on a multi-wheeled chassis.

The combat complex has many disadvantages:

Low survivability of this combat complex. He does not have his own armor, cannon and small arms for conducting close combat after firing rockets. The combat readiness and firepower of the complex is very low, its reloading takes a long time and in the inconvenient relative position of the complex's vehicles.

Known laser pumped by a patent of the Russian Federation No. 1140668, IPC H01S 3/09, publ. 06/30/1994, prototype. The following is a brief description and analysis of its shortcomings.

This is a nuclear-pumped gas laser, the cavity of a cylindrical tube of which is filled with a HE + Xe mixture (in a ratio of 200: 1) with an initial density ρ ₁ = 0.9256 · 10 ³ g / cm ³ . The outer radius of the uranium-containing layer is 2 r ₂ = 1 cm, its thickness is δ = 0.518 · 10 ^-3 cm. The material of the layer is uranium dioxide, characterized by a density ρ ₂ = 10.96 g / cm ³ and a concentration of uranium nuclei ²³⁵ UN ₁ = 2 , 4710 ²² poison / cm ³ . The outer radius of the cylindrical tube is 3 r ₃ = 1.1 cm, its thickness Δr ₃ = 0.1 cm; the tube is continuous. The tube material is alloy: zirconium with the addition of uranium ²³⁵ U, its density ρ ₃ = 6.44 g / cm ³ . The initial temperature of the entire system is T _o = 303 K. Thermogasdynamic calculations were performed on a computer with an increase in the flow of thermal pump neutrons according to the law ϕ _(t) = ϕ _o e ^{t / τ} n with a given period τ _n = 1.5 s. ϕ _{о was} assumed equal to 10 ¹³ n / cm ² s. In the calculations, the concentration of ²³⁵ U in the tube wall material was varied. Curve 5 in Fig. 2 shows the dependence of the coordinate of the boundary of the active generation region on the concentration of uranium-235 nuclei in the tube wall. Thus, direct calculations confirm that the above formulas determine the optimal value of the concentration of uranium nuclei in the tube of the laser cell, which must be provided to effectively compensate for the effects of temperature and density inhomogeneities arising in the working gas.

The efficiency of such a laser with an optimal concentration of ²³⁵ U nuclei in the tube was verified in calculations of thermogasdynamic and optical characteristics when it was operated in the mode of pumping by a thermal neutron flux, which has a time dependence close in shape to a rectangular one with a duration of τ = 1 s. The value ϕ _m = 0.683 · 10 ¹⁴ n / cm ² s is the maximum value of the thermal neutron flux. Based on the obtained spatio-temporal distributions of the temperature and density of the gas mixture using the time dependence of the thermal neutron pump pulse and the known relations describing the relationship between the gas density and its refractive index, the distribution of the refractive index and the divergence of optical radiation, etc., the change in time relative average intensity of laser radiation.

The optimal concentration of 235 uranium nuclei in the tube of the laser cell is determined by the geometric dimensions and thermophysical parameters of the tube itself, the uranium-containing layer and the working gas medium. When the concentration of uranium 235 nuclei in the tube material changes from zero to the optimal value, the output laser radiation energy monotonically increases to the maximum possible value. With a further increase in concentration, the output radiation energy remains unchanged.

Thus, the introduction of uranium 235 nuclei with an optimal concentration of N into the wall of a nuclear-pumped laser tube allows a significant 15–30-fold increase (with a pump duration of τ≈1 s) to increase the energy of the laser output radiation compared to the prototype. In addition, such a device completely eliminates the possibility of failure of heating of the tube wall and provides synchronization of tracking heating of the tube for heating the working gas medium.

Thus, the well-known gas laser with nuclear pumping according to the patent of the Russian Federation No. 1140668, IPC H01S 3/09, publ. 06/30/1994, also has disadvantages, the main of which is low efficiency and laser radiation power, which is unacceptable for a combat laser, as this will not only reduce the damaging properties of the laser, but also lead to huge gas consumption.

Over the past few years, global positioning systems (GPS) have gained great popularity in the world. This is, indeed, a very promising market. The volume of the global market for global positioning services in 2003 amounted to $ 500 million, and according to Ovum forecast, in 2005 its volume will be $ 9.75 billion (with 376 million subscribers). This article is devoted to some fundamentals of the functioning of global positioning systems and their application in the world. The first Global Positioning System (GPS) systems were developed exclusively for military purposes. The global GPS navigation system is designed to transmit navigation signals that can be simultaneously received in all regions of the world. The initiator of the GPS-system was the US Department of Defense. Its development began in 1973, when the US Department of Defense stopped arranging a radio navigation system consisting of Loran-C and Omega ground-based navigation systems and the Transit satellite system. The project of creating a satellite network for determining coordinates in real time anywhere in the world was called NAVSTAR GPS (NAVigation Satellite Timing And Ranging Global Positioning System - a navigation system for determining the time and range). The GPS abbreviation used now appeared later, when the system began to be used not only for the military, but also for peaceful purposes. The first full-time orbital constellation of the system unfolded from June 1989 to March 1994. 24 Block II navigation satellites were put into orbit. The GPS system was finally put into operation in 1995. Currently, it is operated and maintained by the US Department of Defense. The GPS-system includes 3 main segments: space, ground and user. The space segment consists of 28 autonomous satellites uniformly distributed in orbits with an altitude of 20,350 km (24 satellites are enough for a fully functional system). Each satellite emits at 2 frequencies a special navigation signal in which 2 kinds of code are encrypted. One of them is available only to a few users, among which, of course, are the US military and federal services. In addition to these 2 signals, the satellite emits a third, informing the user about additional parameters (satellite status, its operability, etc.). The parameters of the satellite’s orbits are periodically monitored by a network of ground-based tracking stations (a total of 5 stations located in tropical latitudes), with the help of which (at least 1-2 times a day): ballistic characteristics are calculated, deviations of the satellites from the calculated motion paths are recorded, the own time of the airborne hours of satellites, the health of navigation equipment is monitored, etc. At the same time, it usually takes several hours to detect satellite equipment failures using ground stations . The third segment of the GPS system is GPS receivers, manufactured both as stand-alone devices (wearable or stationary), and as boards for connecting to PCs, on-board computers and other devices. Key features of the GPS-system (in the presence of a GPS-signal receiver):

- determination of the location of the mobile subscriber;

- determination of the shortest and most convenient way to the destination;

- determination of the return route;

- determination of speed (maximum, minimum, average);

- determination of travel time (past and how much more is needed), etc.

The main characteristics of the GPS system are shown in table 1.

The number of satellites in the orbital constellation 28 The number of orbital planes 63 The number of satellites in each plane 48 Orbit height (km) 20350 Orbital inclination (degree) 55 Satellite rotation period (h) 12 Satellite mass (kg) 1055 Satellite Solar Power (W) 450 Service life (years) 7.5 Polarization right-handed Determination error 100 (C / A code); 16 (P-code) Determination error 10 (C / A code); 0.1 (P-code) Timing error (ns) 340 (C / A code); 90 (P-code) Reliability of navigation definitions (%) 95

GPS system basics

The theory of ranging is based on the calculation of the propagation distance of a radio signal from a satellite to a receiver using a time delay. If you know the propagation time of the radio signal, then the path traveled by it is easy to calculate by simply multiplying the propagation time of the radio signal by the speed of light. Each satellite of the GPS-system continuously generates radio waves of 2 frequencies - (L1 = 1575.42 MHz and L2 = 1227.60 MHz). The navigation signal is a phase-manipulated pseudo-random PRN code (Pseudo Random Number code). There are 2 types of PRN code. The first is the C / A code (Coarse Acquisition code), which is used in civilian receivers. It allows you to get only a rough estimate of the location, which is why it is called a “rough” code. The C / A code is transmitted at the frequency L1 using phase manipulation of a pseudo-random sequence of 1023 characters in length. Error protection is provided through the Gould code. The repetition period of the C / A code is 1 ms. Another code - P (precision code) provides a more accurate calculation of coordinates, but access to it is limited. Basically, the P-code is provided to the US military and (sometimes) federal services (for example, to solve problems of geodesy and cartography). This code is transmitted at L2 using an extra-long pseudo-random sequence with a repetition period of 267 days. This code is available in principle to civilians. But the algorithm for processing it is much more complicated, therefore, the equipment is more expensive. In turn, the frequency L1 is modulated by both C / A and P code. The GPS signal may also contain the so-called Y-code, which is an encrypted version of the P-code (in wartime, the encryption system may change).

In addition to navigation signals, the satellite continuously transmits various kinds of overhead information. The user of the GPS receiver is informed about the status of the satellite and its parameters: system time; ephemeris (accurate satellite orbit data); the predicted propagation delay time of the radio signal in the ionosphere (since the speed of light changes with the passage of different layers of the atmosphere), the satellite’s operability (the so-called “almanac” contains information on the status and orbits of all satellites updated every 1 ... 5 min).

The basis for determining the coordinates of the GPS receiver is the calculation of the distance from it to several satellites, the location of which is considered known (these data are in the "almanac" received from the GPS satellite). In geodesy, the method of calculating the position of an object by measuring its distance from points with given coordinates is called "trilateration".

If the distance to one satellite is known, then the coordinates of the receiver cannot be determined (it can be located anywhere in the sphere with a radius described around the satellite). Let the receiver distance from the second satellite be known. In this case, the determination of coordinates is also not possible - the object is on a circle, which is the intersection of two spheres. The distance to the third satellite reduces the uncertainty in coordinates to two points. This is already enough to uniquely determine the coordinates - the fact is that of the two possible points of location of the receiver, only one is on the surface of the Earth (or in the immediate vicinity of it), and the second, false, is either deep inside the Earth or very high above surface. Thus, for three-dimensional navigation it is theoretically sufficient to know the distance from the receiver to 3 satellites.

Global Navigation Satellite System (GLONASS) - Soviet and Russian satellite navigation system, developed by order of the USSR Ministry of Defense. One of two currently functioning global satellite navigation systems ^[1] . The basis of the system should be 24 satellites moving above the Earth's surface in three orbital planes with an inclination of orbital planes of 64.8 ° and a height of 19100 km. The measurement principle is similar to the American NAVSTAR GPS navigation system. Currently, the GLONASS project is being developed by the Federal Space Agency (Roscosmos) and Russian Space Systems OJSC ^[2] .

The Russian Global Navigation Satellite System (GLONASS) is designed for operational navigation and temporal support for an unlimited number of land, sea, air and space-based users. Access to civilian GLONASS signals anywhere in the world on the basis of a decree of the President of the Russian Federation is provided to Russian and foreign consumers free of charge and without restrictions.

In order to ensure the commercialization and mass introduction of GLONASS technologies in Russia and abroad, in July 2009, by the Decree of the Government of the Russian Federation, a “Federal Network Operator in the Field of Navigation Activities” was created, the functions of which were assigned to OJSC Navigation and Information Systems.

The main difference from the GPS system is that the GLONASS satellites in their orbital motion have no resonance (synchronization) with the rotation of the Earth, which provides them with greater stability. Thus, the GLONASS spacecraft grouping does not require additional adjustments during the entire period of active existence. Nevertheless, the service life of GLONASS satellites is noticeably shorter.

The objectives of the invention are to increase the accuracy of shooting, improve the survivability of the complex, its combat readiness, firepower, autonomy in control.

The solution of these problems was achieved in a combat laser containing an energy source and at least one resonator, in that a liquid rocket engine mounted horizontally with a supersonic nozzle, the output of which was installed with the possibility of rotation of the exhaust device, was used as an energy source. the resonators are mounted to rotate the exhaust device and contain ball joints. The exhaust device is made with the possibility of regenerative cooling from two walls: internal and external, a layer of uranium 235 is deposited on the inner wall, and uranium particles 235 are embedded in this wall itself. A combat laser may contain an electric power source. A combat laser may include an on-board computer, a Glonass system receiver and a transmitting and receiving device interconnected by electrical connections. A combat laser may comprise a nuclear reactor mounted in a combustion chamber. A combat laser may contain a nuclear reactor and a heat exchanger installed in the combustion chamber and connected by coolant circulation pipelines. A combat laser may comprise a nuclear reactor mounted in an exhaust device. The combat laser may comprise a diffuser mounted coaxially with the exhaust device. The diffuser can be made cooled. The combat laser can be mounted on a fixed platform on which a drive is connected, connected through a gearbox to an exhaust device and a power cable through a switch with an electric power source. An emphasis can be made on the exhaust device, on which a drive is connected, connected to the resonator and the power cable through a switch with an electric power source. Combat laser can be equipped with oxidizer and fuel tanks. The combat laser can be made mobile. The combat laser can be performed on a tracked undercarriage. The combat laser can be equipped with a remotely controlled small arms with a remote control unit.

The invention is illustrated in figure 1 ... 16, where:

- figure 1 and 2 shows a drawing of a combat vehicle with a combat laser,

- Fig 3 shows the design of the exhaust device with a resonator,

- figure 4 shows the layout of the LRE in the armored compartment,

- figure 5 shows a view of a combat laser with a single resonator,

- figure 6 shows a view of a combat laser with two resonators,

- Fig.7 shows a section bB,

- Fig. 8 shows a view B,

- figure 9 shows a view of G,

- Fig 10 shows a diagram of the rocket engine,

- figure 11 shows a drawing of an exhaust device with a nuclear reactor installed inside it,

- Fig.12 shows a drawing of a nozzle with a nuclear reactor installed inside it,

- Fig.13 is a drawing of an exhaust device with a heat exchanger installed inside it and with a nuclear reactor installed outside it,

- Fig.14 shows a combat laser on a tracked undercarriage,

- Fig.15 shows a drawing of a combat laser with a unit of remotely controlled small arms.

- Fig.16 is a drawing of a combat laser with a diffuser.

The combat laser (figure 1 ... 16) contains a base 1 with an armored compartment 2 mounted on it, in turn having armor 3.

In the armored compartment 2 (FIGS. 1 and 2), a horizontally liquid rocket engine - LRE 4 is installed, having a TNA 5 turbopump unit, a combustion chamber 6 with a nozzle 7.

Since there are no restrictions and requirements for the design of the liquid propellant rocket engine used for a combat laser, an example of a single-chamber liquid propellant rocket engine made in a closed circuit is further considered.

The exhaust device 8 is mounted coaxially with the nozzle 7 and can be rotated. The exhaust device 8 can be cylindrical or conical in shape and is mounted on two supports 9 and 10 and connected to a drive 12 through a reducer 11.

A rotation angle sensor 13 is connected to the drive 12. A stop 14 is mounted on the exhaust device 8, to which a drive 15 is attached, for example a hydraulic cylinder connected to the resonator 16. The resonator (s) 16 is mounted to rotate on a cylindrical hinge 17 on the exhaust device 8. C a cylindrical hinge 17 is connected to a rotation angle sensor 18. The rocket engine 4 is used as an energy source. LRE 4, mounted on the central hinge 19 and on two supports 20.

Each resonator 4 contains a cylindrical body 21 made of three coaxially mounted parts of the first 22, second 23 and middle 24. A mirror 25 is installed in the first part 22 of the body 21, a lens 26 is installed in the second part 23 of the body 21. The liquid propellant rocket engine 4 contains a combustion chamber 6 and TNA turbopump assembly 5. The combustion chamber 6 includes a head 27 and a nozzle 7, which contains a cylindrical part 28, a tapering part 29 and an expanding part 30, and a fuel manifold 31. The fuel manifold 31 is made with a cylindrical outer surface 32 and is installed in a hole 33, which is made in the exhaust device 8, and sealed with a seal 34, the exhaust device 8 is sealed relative to the armored end 35 with a seal 36 (Fig. 3). This design of the connection described above is made to prevent enormous temperature stresses in the details of the LRE 4 and to prevent atmospheric precipitation from reaching the nodes of the LRE 4.

On the side surface of the armor 3, holes are made in the upper part of the hole 37 to purge its cavity 38 in order to cool the rocket engine assemblies 4. To purge the cavity 38 inside the armor compartment 2, a purge system is made that contains a cylinder 39 with compressed air or inert gas, a purge pipe 40 and a valve purge 41.

Slots 42 are made on the exhaust device 8, in which the second parts 23 of the bodies 21 of the resonators 16 are installed (FIGS. 1 and 3). Parts 23 may be sealed to prevent atmospheric precipitation from entering the exhaust device. The base 1 is attached to the ground 43 by means of anchor bolts 44 and by means of a reaction stop 45, fixed by a hinge 46 on the armored compartment 2.

Both the tapering 29 and the expanding 30 parts of the nozzle 7 are made with the possibility of regenerative cooling (figure 3) and contain two walls; the inner wall 47 and the outer wall 48 with a gap 49 between them for the passage of cooling fuel. A layer of uranium 235-50 is deposited on the inner surface of the inner wall 47, and uranium particles 238-51 are embedded in the inner wall 47 itself (Fig. 3).

A similar design has an exhaust device 8 (Fig.3 ... 5). It is made with the possibility of regenerative cooling and contains two walls: the inner wall 52 and the outer wall 53, with a gap 54 between them for the passage of cooling fuel. A layer of uranium 235-55 is deposited on the inner surface of the inner wall 52, and uranium particles 238-56 are embedded in the inner wall 51 itself (Fig. 3). The cooling system of the exhaust device 8 includes a supply pipe 57, with a valve 58 and a discharge pipe 59.

The resonators 16 are also made with the possibility of regenerative cooling (Fig.5 ... 9). The tubes 21 are made with two walls of the inner 60 and outer 61 with a gap 62 between them. In addition, the middle part 24 is made in the form of two parallel mounted streamlined profiles 63, while it is possible to perform them cooled (Fig.6), i.e. with a cavity of 64 inside them, included in the cooling system. In this case, the cooling system of the resonators 16 additionally includes an input manifold 65, an output manifold 66, a supply pipe 67 with a valve 68 and a discharge pipe 69. In addition, uranium 235-70 can be coated on the surface of the streamlined profiles 63, and embedded in their wall uranium particles 235-71.

The turbopump unit 5 contains (Figs. 1 and 6) a main turbine 72, an oxidizer pump 73, a fuel pump 72, an additional fuel pump 75, a start turbine 76 with an exhaust pipe 77. A gas generator 78 is installed coaxially with the TNA 5, which is connected to the head by a gas duct 79 27 combustion chamber 6. TNA 5 is attached to the combustion chamber 6 using rods 80.

The combat laser (FIGS. 1 and 3) contains a compressed air cylinder 81 to which a high pressure pipe 82 is connected having a valve 83. The other end of the high pressure pipe 82 is connected to a start turbine 76. An exhaust pipe 77 is connected to the start turbine 76 to discharge air .

The combat laser (FIG. 1) contains an electric power source 84, a power cable 85 connecting the electric power source 84 to the switch 86, to which all electric power consumers, in particular drives 12 and 15, are also connected by power cables. An on-board computer 87 is installed on the military laser to which the receiver of the Glonass 89 system with the antenna 90 and the receiving and transmitting device 91 with the antenna 92 are connected by electrical connections 89. The receiver of the Glonass 89 system with the satellites 93 is connected using the antenna 90 via radio channel 94.

A possible embodiment of a combat laser with a nuclear reactor 95 mounted inside the combustion chamber 6, preferably inside its cylindrical part 27 (Fig. 9). This will not only increase the energy of laser beams by using the thermal energy of a nuclear reactor 95, but also increase its efficiency due to the radioactive pumping of combustion products and, most importantly, increase the time of continuous operation of a combat laser by reducing fuel consumption by about 10 ... 20 times) and burning it at a low (lowest possible temperature).

An embodiment of a combat laser with a nuclear reactor 95 installed inside the exhaust device 8 is possible (Fig. 10).

An embodiment of a combat laser with a nuclear reactor 95 and a heat exchanger 96 mounted inside the nozzle 6 or exhaust device 8 is possible (Fig. 11). Nuclear reactor 95 and heat exchanger 96 are connected by coolant circulation pipelines supplying 97 and discharge 98, in one of which a heat transfer pump 99 with drive 100 is installed. A temperature sensor 101 is installed in the discharge pipe, which allows simultaneous monitoring of the operation of nuclear reactor 95 and the coolant recirculation system.

Pneumohydraulic diagram of the rocket engine 4 is shown in Fig.12.

Inside the combustion chamber 6 (FIG. 10), an outer plate 102 and an inner plate 103 with a gap (cavity) between them 104 are formed. Inside the head 27 of the combustion chamber 6, oxidizer nozzles 105 and fuel nozzles 106 are installed. The oxidizer nozzles 105 communicate with the cavity 107 with an internal cavity 108 of the combustion chamber 6. On the outer surface of the combustion chamber 6, a fuel manifold 31 is installed.

A nozzle 109 is connected to the fuel manifold 31, on which the fuel valve 110 is installed, the inlet of which is connected by a fuel pipe 111 to the output of the fuel pump 74. The output of the additional fuel pump 75 is connected by a high pressure fuel line 112 containing a flow regulator 113 with an actuator 114 and a high pressure valve 115 - with a gas generator 78, specifically with its cavity 116.

The exit from the oxidizer pump 75 by the oxidizer pipe 117 through the oxidizer valve 118 is connected to the gas generator 78.

The gas generator 78 has an external and an internal plate, 119 and 120, respectively, with a cavity 121 between them and oxidizing and fuel nozzles, respectively, 122 and 123. Ignition devices 124 are installed on the head of the combustion chamber 6, and ignition devices 125 are installed on the gas generator 78 (Fig. 10).

TNA 5 has a speed sensor 127 mounted on the shaft 126. An electric connection 88 is connected to the speed sensor 127, which is connected to the on-board computer 87.

Ignition devices 124 and 125, preferably electric ignition valves, a fuel valve 110, an oxidizer valve 118, an actuator 114, a flow regulator 113, and a high pressure valve 115 are connected to an on-board computer 87 by electrical connections 88.

A purge line 128 with a purge valve 129 is connected to the fuel manifold 31.

Various options for the design of a combat laser are possible; stationary, mobile on a multi-wheeled chassis without an engine (trailer), mobile on a multi-wheeled chassis with an internal combustion engine or a diesel engine and on a tracked undercarriage. Only the last option is described in detail (Fig. 14). In this embodiment, the combat laser has a tracked undercarriage 130, an engine compartment 131, a left traction motor 132, a right traction motor 133 connected by power cables 85 to a switch 86.

The combat laser in this embodiment comprises a fuel compartment 134, which in turn contains a fuel tank 135, a fuel nozzle 136, a fuel pipe 137, a fuel flow meter 138, and a fuel valve 139. In addition, it contains an oxidizer tank 140, an oxidizer nozzle 141 , oxidizer pipe 142, oxidizer flowmeter 143, and oxidizer valve 144.

At least one unit of remote-controlled small arms 146 with a remote control system 147 can be mounted above the combat laser on a support 145 (Fig. 15). A unit of remote-controlled small arms 146 is designed to defend a mobile combat laser on the march and when the oxidizer is used up and fuel.

In Fig.16 shows a combat laser with a diffuser 148 mounted using brackets 149 on the armored hull 3.

BATTLE APPLICATION: BATTLE LASER

The combat laser is designed only for the defense of the sky in a radius of direct visibility from the side of the combat laser and with virtually no height limit. The horizontal location of the rocket engine 4 reduces the dimensions of the combat laser in height, and the use of anchor bolts 44 and a reaction stop 45 with a hinge 46 eliminates the influence of the jet thrust of the rocket engine 4 on the accuracy of the fire.

When you start the combat laser, first run a liquid rocket engine 4, then a nuclear reactor 95, if any. To start the LRE 4 open valve 83, and compressed air through the high pressure pipe 82 enters the starting turbine 76. Then open the valves 110, 115 and 118 and turn on the igniters 124 and 125 (figure 10). Fuel (oxidizer and fuel) during combustion in the combustion chamber 27 burns out at a relatively low temperature of up to 500 degrees. C. Further heating of the combustion products to 3000 ... 4000 deg. C is carried out by a nuclear reactor 95. In addition to significant heating, the combustion products are exposed to radiation, this helps to increase the laser power.

The combat laser is controlled by the on-board computer 87 using the drives 13 and 15 (Fig. 1), which rotate the resonator 16 in two planes.

The combat laser is turned off in the reverse order.

The combat laser almost instantly enters the battle and hits the target with the rays of the combat laser, using for guidance its own coordinates and the coordinates of the target obtained from the command post - CP or radar station - radar (CP and radar in figure 1 ... 16 are not shown), until complete the consumption of oxidizer and fuel, after which it is installed in such a way that the side of the tank is filled with oxidizer and fuel with its rear end, then refuel with the oxidizer and fuel of the combat vehicle, and after that it makes a second attack, and refuel The oxidizer and fuel are immediately sent for the components of the rocket fuel (oxidizer and fuel) to continue the battle.

Therefore, this technical solution meets the criterion of "novelty." To determine whether the proposed invention meets the criterion of "inventive step", an analysis of the characteristics of the identified analogues is carried out. Given that the proposed technical solution has a new set of features that for a specialist do not explicitly follow from the existing level of technology, it meets the criterion of "inventive step". The proposed method of increasing the combat effectiveness of firing allows you to provide:

- autonomous topographic location and navigation, which allows firing from an unprepared firing position in a topographic and geodetic relation, guidance of a launcher guide package without leaving the crew from the cockpit of a combat vehicle and without using a pickup point;

- simultaneous firing of one or more beams of a heavy-duty laser;

- refueling with an oxidizer and fuel of a combat laser with the help of refuellers in any order;

- the maximum speed of the complex on paved roads is about 100 km / h;

- cross in snow, swamp and desert sand,

- range in fuel - 2000 km;

- the number of laser beams - 1 ... 40 pcs.,

- full refueling time - up to 10 min.

A stationary combat laser enters battle almost instantly.

Upon arrival at a combat position, a mobile combat laser enters battle in a few seconds. When the mobile combat laser has consumed all of the oxidizing agent and fuel, it is charged with the oxidizing agent and fuel with the help of refueling machines (refueling machines in Figs. 1 ... 16 are not shown). After refueling tankers to a safe distance, the combat laser makes the necessary laser firing at the target being attacked. After refueling a combat laser, tankers are sent for the next portion of oxidizer and fuel, and so on until the end of hostilities. The combat laser conducts combat without human participation in connection with the disastrous effect of the sound stream of a working liquid propellant rocket engine on the crew and all living things within a radius of 1000 m and a high radiation background in the case of using a nuclear reactor.

The application of the invention will allow:

Increase the firing range of laser beams, especially in height to the level of space heights.

Increase the damaging power of the installation in 500 ... 1000 times.

Provide reliable and complete automation of the process of refueling the launcher with oxidizer and fuel.

Improve the invulnerability of the combat complex through powerful reservations and the use of remotely controlled small arms.

To make the shooting resource before capital repairs unlimited and the resource of the chassis equal to the resource of the tank or self-propelled guns, on the basis of the chassis of which the combat vehicle was made.

The proposed method of increased combat effectiveness of firing simultaneously with several laser beams (from 1 to 40 laser beams with a power of 10 MW to 200 MW each) allows you to hit:

- enemy planes and missiles in line of sight,

- satellites in orbit,

- space bombers,

- missile warheads on a ballistic trajectory.

The main distinctive ability of the proposed combat complex is the presence of not one but several resonators, and the difference in the method of warfare is that when conducting a defensive battle, one or more laser beams can be involved. Naturally, if only one laser beam is used, its power increases. Also, a battle can be conducted using a nuclear reactor, this will not only increase the power of laser beams, but also increase the time of active use of the laser by an order of magnitude without refueling.

A combat laser can operate without a crew using Glonass and radio control systems. In exceptional cases, the crew can be used to move the combat laser and its defense from the enemy landing. In the case of using a nuclear reactor 95 (of course only with a non-working nuclear reactor 95), only a short stay of the operating personnel near the liquid-propellant rocket in special protective suits is permissible. Tankers have a crew of 2 or 3 people to control movement, undock and undock hoses and defense. But in the event of the death of the entire crew, tankers are able to autonomously fight using small arms and navigate using radio control, taking the maximum possible measures to save the material part and after changing the crew for further fulfillment of the assigned tasks.

Having such a patent for an invention, it will be much easier for Russian enterprises manufacturing such complexes, besides ensuring the country's defense capability, to sell them abroad to allies and friendly countries, while it is possible to increase the unit price of sales by 5 ... 10 times, at a lower cost, since the inclusion of such a device and method in the technical and advertising documentation will immediately reflect in it the increased combat effectiveness of the firing of these sold complexes and their absolute invulnerability. At the same time, it is possible to quickly and easily establish mass production of this new type of weapon, given the advanced positions of the USSR in tank construction and the huge number of tanks produced in the USSR and the Russian Federation. At the same time, the income of our state from arms exports will increase tens and hundreds of times.

Literature

1. Konyukhov VK, Prokhorov AM, The second law of thermodynamics and quantum generators with thermal excitation. "Physics-Uspekhi", 1976, vol. 119, p. 511;

2. Losev S. A., Gas-dynamic lasers, M., 1977; Anderson D., Gas-dynamic lasers: introduction, trans. from English., M., 1979;

3. Biryukov AS, Scheglov VA, Gas lasers on cascade transitions of linear triatomic molecules, "Quantum Electronics", 1981, v. 8, p.2371;

4. Karlov N.V., Lectures on quantum electronics, M., 1983. A.S. Biryukov

Claims (15)

1. A combat laser containing an energy source and at least one resonator, characterized in that a horizontally mounted liquid propellant rocket engine with a supersonic nozzle is used as an energy source, the output of which is equipped with a rotatable exhaust device, resonators are mounted on the exhaust device and contain spherical joints, providing a rotation of the resonators in a vertical plane. 2. The combat laser according to claim 1, characterized in that the exhaust device is made with the possibility of regenerative cooling and consists of two walls: internal and external, a layer of uranium 235 is deposited on the inner wall, and uranium particles 235 are embedded in this wall. 3. The combat laser according to claim 1 or 2, characterized in that it contains a source of electricity. 4. The combat laser according to claim 1 or 2, characterized in that it contains an on-board computer, a Glonass receiver and a transmitting and receiving device, interconnected by electrical connections. 5. The combat laser according to claim 1 or 2, characterized in that it contains a nuclear reactor installed in the combustion chamber. 6. The combat laser according to claim 1 or 2, characterized in that it contains a nuclear reactor and a heat exchanger installed in the combustion chamber and connected by coolant circulation pipelines. 7. The combat laser according to claim 1 or 2, characterized in that it contains a nuclear reactor installed in the exhaust device. 8. The combat laser according to claim 1 or 2, characterized in that it is made with a diffuser mounted coaxially to the exhaust device. 9. The battle laser of claim 8, characterized in that the diffuser is made cooled. 10. The combat laser according to claim 1 or 2, characterized in that it is mounted on a base on which a drive is connected, connected through a gearbox to an exhaust device and a power cable through a switch with a power source. 11. The combat laser according to claim 1 or 2, characterized in that the emphasis is made on the exhaust device, on which the drive is connected, connected to the resonator and the power cable through a switch with an electric power source. 12. The combat laser according to claim 1 or 2, characterized in that it is equipped with oxidizer and fuel tanks. 13. The combat laser according to claim 1 or 2, characterized in that it is made mobile. 14. The combat laser according to item 13, characterized in that it is made on a tracked undercarriage. 15. The combat laser according to claim 1 or 2, characterized in that it is equipped with a remotely controlled small arms with a remote control unit.

Images