Pulse jet engine with high-frequency directed detonation for unmanned aerial vehicle and its operating method

Abstract

FIELD: pulse jet engines.SUBSTANCE: used as a power plant for unmanned aerial vehicles. A pulse jet engine with high-frequency directed detonation for an unmanned aerial vehicle, consisting of four functional units: an external air intake and compression unit, a unit for generating a pulsating flow of gas-air mixture, a detonation chamber unit, and an outlet jet nozzle unit. The output of each unit is combined with the input of the next one: the external air intake and compression unit is connected to the unit for generating a pulsating flow of gas-air mixture, the output of which is connected to the input of the detonation chamber unit, the output of which is connected to the input of the outlet jet nozzle unit. The unit for generating a pulsating flow of a gas-air mixture is an air channel with the ability to create a pulsating longitudinal flow of gas-air mixture and contains: an air flow vortex chamber with a diameter equal to the diameter of the air compressor; a channel for increasing the angular velocity, wherein the outlet opening of the air flow vortex chamber is axially aligned with the inlet of the channel for increasing the angular velocity, wherein the diameter of the channel for increasing the angular velocity is made smaller than the diameter of the air flow vortex chamber by 2–4 times. In this case, the laser device for initiating directed detonation contains 3–8 laser radiation sources, which are individually made with a power less than that required to break through the gas-air mixture.EFFECT: development of a structurally simple, energy-efficient pulse jet engine for unmanned aerial vehicles.2 cl, 2 dwg, 1 tbl

Description

[0001] The invention relates to pulse jet engines (PJE) and can be used as a power plant for unmanned aerial vehicles (UAVs).

[0002] The widespread development of unmanned aerial vehicles in industry, agriculture, civil, and military sectors in recent years has created a need for the development of low-thrust jet engines (50 to 250 kgf). Low-thrust jet engines enable the creation of high-speed, maneuverable aircraft with good load-carrying capacity, offering significant advantages over piston and electric engines. Compact, small jet engines provide new impetus to the development of unmanned technology, which in turn drives demand for them.

[0003] Gas turbine jet engines, which are now widely used, meet many modern requirements, but their high cost and manufacturing complexity are not justified when used on unmanned aerial vehicles, including those for short-term or single use.

[0004] An alternative to gas-turbine jet engines is a pulse jet engine (PuJE), in which the combustion front (detonation) forms a supersonic shock wave, providing increased thrust, while the installation of an electric drive for an air compressor in the declared PuJE leads to the simplicity of manufacturing the PuJE compared to gas-turbine engines.

[0005] Theoretically, a pulsed-jet engine provides a record power output per unit volume due to the combustion velocity during detonation being many times higher than that of deflagration. However, despite the high thermodynamic efficiency in a single pulse, the shock wave repetition rate is low, resulting in a low value of thrust efficiency - that is, the average thrust per unit time, averaged over the pulse repetition rate, taking into account losses due to flow unevenness and vibration [Ivanov I.A., Popovich N.P., Shkut K.L. Theoretical calculation of the required number of obstacles for a pulsed detonation engine in the first approximation / / Journal "Current Research". - 2025. - No. 13 (December). - Date of publication: December 13].Furthermore, the complex shock-wave structure of the detonation front—the lack of directionality—leads to instability, chaos, and difficulty in maintaining a stable wave; turbulence in the combustion chamber reduces the jet stream velocity and engine efficiency [https: / / vnh-energo.ru / Детонационные двигателя].

[0006] From the studied prior art, the applicant has identified an invention according to patent US 20220235727 A1 "Rotating detonation engine", the essence of which is a device containing an outer casing with a through hole having an inner wall, and an inner casing installed in the outer hole of the casing, and an outer wall tapering in the direction of the engine flow and located at a distance from the inner wall of the hole of the outer casing, forming a non-cylindrical channel for detonation with increased efficiency between the inner casing and the rotating detonation engine, the outer wall of the casing and the inner wall of the outer hole of the casing.

[0007] The disadvantage of the known device is that the complex multidirectional shock wave structure of the detonation front leads to a decrease in efficiency due to instability, chaotic nature of the process and difficulties in maintaining a stable wave.

[0008] An invention is known from patent RU 2793868 "Pulse air-breathing supercharged engine" containing a combustion chamber with a spark plug, a fuel supply pipe, an inlet device and a resonant exhaust pipe, characterized in that in a pulse air-breathing supercharged engine containing a combustion chamber with a spark plug, a fuel supply pipe, a pipe with a gas-dynamic diode for supplying air from a vortex chamber, the exhaust gases exit through a nozzle apparatus into a vortex chamber with intensive swirling, where atmospheric air is ejected and compressed from the peripheral zone through inlet channels and passes along the vortex chamber, dividing into cold and hot vortices, wherein the hot vortex exits into the atmosphere through an adjustable nozzle, and the cold one goes to the entrance of the combustion chamber.

[0009] The disadvantage of this device is the low efficiency and engine thrust due to a decrease in the jet flow speed due to turbulence in the vortex chamber and a decrease in the efficiency of using the fuel combustion energy in the process of ejecting the air supply; the spark plug initiated in the combustion chamber causes a complex shock wave detonation front that does not have a specific direction, which leads to instability, chaos in the process and difficulties in maintaining a stable wave due to turbulence in the combustion chamber.

[0010] A device known under patent RU 2674091 "Pulse Turbojet Engine" is equipped with an inlet diffuser, compressor, gas turbine, outlet jet nozzle and a block of pulse combustion chambers, a DC electric motor with a gearbox. The block of pulse combustion chambers contains stationary horizontal pulsating combustion chambers and two rotating valve discs. The combustion chambers are equipped with inlet air and outlet gas ports. The rotating valve discs are connected by a common shaft; the first of them, installed in front of the combustion chambers, has air ports, and the second, installed behind the combustion chambers, has gas ports. The axes of the valve discs coincide with the horizontal axis of the block of combustion chambers. The block of combustion chambers contains four pulsating combustion chambers, located along the circumference of this block with angles between the radial axes of the combustion chambers equal to 90°.The first valve disc has four air holes, the radial axes of which are positioned at angles of 45°, 135°, 225°, and 315°. The second valve disc has four gas holes, the radial axes of which are positioned at angles of 0°, 90°, 180°, and 270° relative to the central vertical axis of the combustion chamber block. This invention increases the power, thrust, efficiency, and reliability of a pulsejet engine.

[0011] The disadvantage of this device is low energy efficiency due to the consumption of part of the energy of the working fluid on the operation of the turbine, which is spent on spinning up the compressor, the complexity of manufacturing due to the complexity of the turbine design, and also reduced power due to the low frequency of closing of gas flows by rotating valve discs.

[0012] A known invention is patented under US Patent No. 6,584,765 B, "A Pulse Detonation Engine Having an Aerodynamic Valve," which is equipped with an air valve for regulating the pressure of the injected fuel components (oxygen, fuel) in an open detonation chamber. Fuel is injected at a specific pressure and velocity, and an air valve is formed in a direction primarily toward the end of the forward thrust wall of the detonation chamber, effectively blocking or preventing the fuel from escaping from the chamber. The shock wave generated by the injected fuel, after being reflected by the end of the thrust wall and in combination with the air valve, compresses and maintains or increases the pressure of the injected fuel. Carefully timed ignition creates a detonation pulse under specified conditions of maintaining or increasing pressure. Stopping the fuel supply serves to "open" the air valve, and the burnt fuel is ejected, creating thrust.Alternative embodiments of rocket fuel injection mechanisms include pulse valves, each having a slotted stationary disc and a slotted rotating disc to provide the required high-speed delivery of discrete pulses of rocket fuel for injection.

[0013] The disadvantage of this device is the low value of traction efficiency due to the low pulsation frequency, limited by the time of filling the combustion chamber with the fuel-air mixture after the previous detonation cycle, and the low value of thrust and efficiency of the engine due to the fact that the spark plug initiated in the combustion chamber causes a complex shock-wave detonation front that does not have a specific direction, which leads to instability, chaos of the process and difficulties in maintaining a stable wave of the jet flow due to turbulence,

[0014] A known invention according to patent RU 2303152 "Jet propulsion system of an aircraft", includes a device for compressing atmospheric air entering the gas path of the system, a combustion chamber, a jet nozzle, at least one electric motor for driving the air compression device and power sources electrically connected to at least one electric motor. According to the invention, the air compression device is designed as a fan, and the power sources are in the form of electrochemical generators or electric batteries, or electric machine current generators equipped for driving a piston internal combustion engine. The invention ensures an increase in the operational reliability and service life of the system by reducing the level of the maximum possible temperatures in the gas path.

[0015] The disadvantage of the known device is low thrust and energy efficiency due to the low longitudinal speed of the jet flow, limited by the speed of air supply by the fan and caused by the deflagration mode of fuel combustion, which has a significantly lower speed than the detonation mode.

[0016] An invention is known under patent RU 2728609 "Electrothermal jet engine", containing a compressor, a fuel-pump system, a combustion chamber and a jet nozzle, a plurality of thermoelectric elements connected to a consumer, one side of which is designed with the possibility of cooling with a cold jet, characterized in that the engine is made without a turbine and contains an electric motor that sets the compressor in motion, the thermoelectric elements are made in the form of Peltier modules, placed on the outer side of the combustion chamber, and the electrical energy generated by them is supplied to the electric motor.

[0017] The disadvantage of this device is low energy efficiency due to the consumption of part of the energy of the working fluid on the operation of the turbine, which is spent on spinning up the compressor, the complexity of manufacturing due to the complexity of the turbine design, low thrust due to the low speed of the jet flow caused by the deflagration mode of fuel combustion, which has a significantly lower speed than the detonation mode.

[0018] A known invention under patent RU 2695415, "Method for initiating pulse detonation," consists of generating a primary shock wave and then exerting a low-energy impact on the fuel-air mixture ahead of the leading shock wave front. The low-energy impact is achieved by using selective laser radiation, which, upon absorption, causes the oxygen molecules in the mixture to transition to the singlet-delta O2(a) state. 1Δg) and accelerate the chemical reactions of fuel combustion, and act with laser radiation on the fuel-air mixture in local areas ahead of the front of the leading shock wave with a lead time less than the relaxation time of oxygen in the singlet-delta O2(a) state 1 Δg), at the moment when the leading shock wave velocity is less than the detonation velocity in the Chapman-Jouguet regime in a fuel-air mixture, and the laser radiation energy is set to the condition of sufficiency to increase the leading shock wave velocity with a transition to a non-stationary oscillatory detonation regime. Thus, detonation initiation involves the generation of a primary shock wave with an energy impact below the critical value, ensuring the formation of self-sustaining detonation, with subsequent additional energy impact on the front of the traveling shock wave.

[0019] The disadvantage of the specified method of initiating detonation is that there is a minimum limit of singlet oxygen admixture, below which the detonation recovery effect is not achieved, as a result of which the problem of ensuring the stability of the wave of directed detonation of the fuel assembly in the combustion chamber arises, leading to a decrease in the longitudinal velocity of the jet flow, a decrease in thrust and engine efficiency.

[0020] An invention is known under patent RU 2781720 "Detonation pulse rocket-air-jet engine", characterized in that it includes in one housing a control unit, an axisymmetric adjustable air intake, the central body of which, of variable shape, has the ability to move along the axis to change the operating modes from completely closing the access of atmospheric air at the inlet to partially or completely opening the access of atmospheric air at the inlet, an air compressor, a gas turbine drive of the air compressor and an outlet jet nozzle with adjustable dimensions and shape, allowing effective operation at subsonic and supersonic speeds with or without an afterburner, as well as at least two detonation pulse jet engines secured to the outer side of the housing of the gas turbine drive of the air compressor, containing a detonation chamber of a volume explosion with a main outlet jet nozzle,at the outlet of which a damper device is installed with at least two single-leaf dampers, which are secured on torsion bars with an adjustable torque, capable of closing to prevent access of external air when filling the detonation chamber of the volume explosion with a fuel-air mixture and opening at the moment of exit of the main flow of exhaust gases of the volume explosion from the detonation chamber of the volume explosion, at least one system of an inlet-outlet damper device, located in the space between the outlet of the air compressor and the inlet of the gas turbine of the air compressor drive, containing an axisymmetric adjustable air intake, the central body of which, of variable shape, has the ability to move along the axis to change the operating modes from completely closing the access of atmospheric air at the inlet to partially or completely opening the access of atmospheric air at the inlet,with a device for forced closing of the compressed air flow inlet window on the air compressor side, a pipeline with a torsion bar-mounted, adjustable torque, two-position switching two-leaf valve for the function of supplying the compressed air flow from the air compressor side to the detonation chamber of the volume explosion through the compressed air flow inlet window opened by the switching two-leaf valve on the air compressor side and for the function of removing an additional portion of the exhaust gases of the volume explosion from the detonation chamber of the volume explosion through the outlet window opened by the switching two-leaf valve in the direction of the inlet of the gas turbine of the air compressor drive, and in the pipeline of which an incoming air mass flow sensor is installed and at least one fuel injector of the fuel supply system is installed in the internal volume of the detonation chamber of the volume explosion,at least one oxidizer supply system injector, a spark plug and / or a detonation tube of the ignition system to create the initiating pulse of the volumetric explosion,

[0021] The disadvantage of the specified technical solution is the complexity of manufacturing an engine containing a gas turbine, several combustion chambers with support systems (dampers with torsion bars and closing devices, an air pipeline, a central body, a nozzle), low energy efficiency due to the consumption of part of the energy of the working fluid for the operation of the turbine for the operation of the compressor, reduced power due to the low frequency of closing of gas flows by the dampers, low efficiency and engine thrust due to a decrease in the speed of the jet flow due to turbulence in the combustion chamber, caused by a complex shock-wave front of detonation, which does not have a specific direction.

[0022] The identified analogues coincide with the claimed technical solution in terms of individual matching features, therefore the prototype of the claimed technical solution was not identified by the applicant, and the invention formula was drawn up without a limiting part.

[0023] The technical problem solved by the declared technical solution and its technical result is the development of a structurally simple, energy-efficient pulse jet engine for unmanned aerial vehicles and a method for its operation that ensures:

[0024] - ease of manufacture and increased efficiency of fuel combustion energy use through the use of an electric motor to drive the air compressor;

[0025] - increasing the traction efficiency - average traction per unit of time - by ensuring a high pulsation frequency, which is achieved by using a unit for generating a pulsating flow of gas-air mixture (hereinafter referred to as GHW) of the declared design and an aerodynamic valve for organizing an intermittent mode of supplying GHW to the combustion chamber;

[0026] - increasing thrust and efficiency with an increase in the jet flow exhaust velocity due to laser initiation of a stable wave of directed detonation of the hot gas mixture, the velocity of which (directed detonation of the hot gas mixture) in the direction of the outlet nozzle is up to two times higher than in the cross section.

[0027] The essence of the claimed technical solution is a pulse jet engine with high-frequency directed detonation for an unmanned aerial vehicle, consisting of four functional units: an outside air intake and compression unit, a unit for generating a pulsating flow of a gas-air mixture, a detonation chamber unit, an outlet jet nozzle unit, wherein the output of each unit is combined with the input of the following: the output of the air intake and compression unit is connected to the input of the unit for generating a pulsating flow of a fuel-air mixture, the output of which is connected to the input of the detonation chamber unit, the output of which is connected to the input of the outlet jet nozzle unit;the units are installed in a single housing, which is a hollow solid pipe of variable cross-section made of three parts of different diameters, wherein the first and third parts are made with a diameter of the same order, and the middle part is made with a diameter 2-4 times smaller, and the transitions of the diameters are made in the form of bottoms with a central hole, and the open end of the first part is made with a narrowing diameter with the ability to take in outside air; the air intake and compression unit contains an axisymmetric air intake, an air compressor with an electric motor; the unit for forming a pulsating flow of gas-air mixture is an air duct with the ability to create a pulsating longitudinal flow of gas-air mixture and contains: an air flow swirling chamber with a diameter equal to the diameter of the air compressor;an angular velocity increase channel, wherein the outlet opening of the air flow swirling chamber is axially aligned with the inlet of the angular velocity increase channel, wherein the diameter of the angular velocity increase channel is made smaller than the diameter of the air flow swirling chamber by 2-4 times; a gas-air mixture nozzle; a reflector made in the form of a recess in the central body; an aerodynamic valve for preventing detonation products from entering the fuel gas and air supply system, made in the form of an annular recess in the angular velocity increase channel, wherein the aerodynamic valve comprises side walls directed at an angle of 45° towards the detonation chamber; a fuel gas supply nozzle made in the form of openings with the possibility of gas entering the recess of the aerodynamic valve;wherein the air flow swirl chamber, the gas-air mixture nozzle, the angular velocity increase channel, the aerodynamic valve, the fuel gas supply nozzle are installed in the housing, and the reflector is connected to the central body; the detonation chamber unit comprises: a detonation chamber, a laser device for initiating directional detonation, a backup detonation initiator; wherein the detonation chamber is formed as a cavity limited by the shell, the central body and the reflector, having an inlet in the form of a gas-air mixture nozzle and an outlet to the outlet nozzle;wherein the laser device for initiating directed detonation comprises 3-8 laser radiation sources, which are individually made with a power less than that required for breakdown of the gas-air mixture, wherein the laser radiation sources are installed along a circumference on the side of the outlet nozzle, the laser beams of which are directed towards the outlet of the gas-air mixture nozzle, where they form a focal point with a radiation intensity above the breakdown threshold of the gas-air mixture; wherein the focal point is located geometrically on the axis of the pulse jet engine in the cross-section of the outlet of the gas-air mixture nozzle in order to reduce the length of the pre-detonation section; wherein the laser radiation sources are installed on the outside of the housing; wherein the entrance of the laser beams to the detonation chamber is made with windows that are transparent for the type of laser radiation used, with the possibility of protecting the laser radiation sources;wherein the backup detonation initiator with the ability to ensure uninterrupted operation of the engine in the event of insufficient power of the laser device is made in the form of an electric spark spark plug or a glow plug, geometrically located in the detonation chamber on the axis of a pulse jet engine with high-frequency directed detonation with a bracket secured to the housing; wherein the detonation chamber, the laser device for initiating directed detonation, and the backup detonation initiator are installed in the housing; the outlet jet nozzle unit comprises: an outer shell of cylindrical shape; a central body in the form of a conical element of revolution; wherein the shell and the central body form an outlet nozzle, wherein the wall of the central body forms the inner wall of the outlet nozzle, wherein the central body is fixed in the outer shell by rods;wherein the cylindrical shell is attached to the body. The method of operating a pulse jet engine with high-frequency directed detonation for an unmanned aerial vehicle according to paragraph 1, characterized in that five processes of the operating cycle are carried out sequentially: the first process of the operating cycle - filling the detonation chamber with a gas-air mixture - is carried out by simultaneously carrying out three operations: intake and compression of outside air, formation of a gas-air mixture, formation of a pulsating flow, wherein the process is carried out by the joint and simultaneous operation of the unit for intake and compression of outside air and the unit for forming a pulsating flow of the gas-air mixture;Intake and compression of outside air: outside air is fed through an axisymmetric air intake into an air compressor driven by an electric motor, where the air receives rotational kinetic energy from the impeller and is compressed by centrifugal force to excess pressure, wherein adiabatic compression increases the temperature; when the unmanned aerial vehicle is not moving, air is supplied due to the vacuum created by the air compressor, while when moving, it is supplied due to the pressure of the oncoming flow; the air spun up and compressed by the air compressor enters the air flow swirling chamber, where a funnel-shaped air movement is formed with an axial outlet to the inlet of the channel for increasing the angular velocity, wherein in the latter, due to the smaller diameter of the channel for increasing the angular velocity by 2-4 times compared to the diameter of the air flow swirling chamber, the angular velocity of the air flow increases by 2-4 times;Formation of a gas-air mixture of hot water supply: as the air flow moves in the channel for increasing the angular velocity, it mixes with the fuel gas in a ratio that forms an explosive hot water mixture; The fuel gas enters the channel for increasing the angular velocity as follows: the gas supplied to the pulsating air-jet engine through the pipeline passes through the fuel gas supply nozzle and enters the annular recess of the aerodynamic valve and is mixed with the air flow in the channel for increasing the angular velocity with a swirl; The hot water mixture then enters the inlet of the hot water mixture nozzle; Formation of a pulsating flow: at the outlet of the hot water mixture nozzle, low-pressure areas are created in the detonation chamber in the center of the vortex, causing periodic rarefactions and an increase in pressure together with the flow coming from the reflector, forming a pulsating flow regime;the second process of the operating cycle - initiation of directed detonation - is carried out in the detonation chamber by a laser device for initiating directed detonation independently or in combination with a backup detonation initiator, while the initiation of detonation in combination with a backup detonation initiator is used to start the pulse jet engine in order to reduce the power of the laser radiation sources, which is ensured by their joint synchronized operation; after establishing the operating mode of the pulse jet engine, detonation is initiated independently by the laser device for initiating directed detonation without a backup detonation initiator; the third process of the operating cycle - propagation of a detonation wave in the form of a volumetric explosion with an increase in pressure at a constant volume, is implemented in the detonation chamber unit, directly in the detonation chamber;the breakdown front - an extended detonation spark of conical shape - is formed in the following sequence: laser beams with an intensity lower than that required for the breakdown of the gas-air mixture from the radiation sources are directed to the focal point, where the total intensity becomes higher and breakdown of the gas-air mixture occurs; due to the fact that lower radiation intensity is required for the propagation of detonation, a breakdown front of conical shape develops between the laser beams from the focal point to the laser radiation sources; the breakdown front initiates a detonation wave of the gas-air mixture in the detonation chamber in the form of a volumetric explosion directed from the outlet of the gas-air mixture nozzle to the outlet of the outlet nozzle in a channel limited by the shell and the central body;In the volume of the detonation chamber, uniform development of detonation directed towards the outlet nozzle occurs with increasing pressure at a constant volume, while the development of an inward-directed increase in the angular velocity of the shock wave front is prevented by an aerodynamic valve, which also prevents detonation products from entering the fuel gas and air supply system; the fourth process of the working cycle - expansion of gases directed towards the outlet nozzle in the form of a shock wave front and the creation of thrust, is implemented in the following units: detonation chamber, outlet jet nozzle, formation of a pulsating flow of hot gas mixture; the increase in pressure and temperature in the volume of the detonation chamber causes the development of expansion of gases directed towards the outlet nozzle in the form of a shock wave front; the directed shock wave from the outlet of the detonation chamber rushes to the inlet of the outlet nozzle, passing through which as an outflow of a jet stream of combustion products is ejected into the atmosphere;the fifth process of the working cycle - the pressure drop in the detonation chamber as the shock wave passes - the rarefaction phase of the shock wave - and the simultaneous start of filling the hot water supply of the next cycle, is implemented in the detonation chamber unit and in the unit for forming the pulsating flow of hot water supply; after the end of the compression phase of the shock wave, a rarefaction phase occurs in the vicinity of the hot water supply nozzle in the detonation chamber with a pressure lower than the pressure in the channel for increasing the angular velocity; such a pressure ratio opens the aerodynamic valve, while the hot water supply flow, by an active front, displaces the gas in the form of combustion products and begins to fill the detonation chamber, which marks the beginning of the implementation of the first process of the next cycle.

[0028] The claimed technical solution is illustrated in Fig. 1, Fig. 2.

[0029] In Fig. 1A structural diagram of the claimed pulse jet engine with high-frequency directed detonation for unmanned aerial vehicles (hereinafter also referred to as the claimed engine) is presented.

[0030] In Fig. 2 A diagram of the direction of laser beams of a device for initiating directional detonation is presented.

[0031] The positions on the figures indicate:

[0032] 1 - body;

[0033] 2 - axisymmetric air intake;

[0034] 3 - air compressor;

[0035] 4 - electric motor;

[0036] 5 - air flow swirling chamber;

[0037] 6 - channel for increasing angular velocity;

[0038] 7 - gas-air mixture nozzle (GAM);

[0039] 8 - reflector;

[0040] 9 - fuel gas supply nozzle;

[0041] 10 - aerodynamic valve;

[0042] 11 - detonation chamber;

[0043] 12 - laser device for initiating directional detonation;

[0044] 13 - backup detonation initiator;

[0045] 14 - shell;

[0046] 15 - central body;

[0047] 16 - outlet nozzle;

[0048] 17 - focal point;

[0049] 18 - laser radiation sources;

[0050] 19 - laser beams.

[0051] The applicant further provides a more detailed description of the above positions.

[0052] Body 1 is a hollow structure made, for example, by welding pipes of different diameters.

[0053] Axisymmetric air intake 2 is designed as a smooth narrowing of the diameter of the open end of the first (front along the gas flow) part of the housing 1, and is connected by a direct transition to the air flow swirling chamber 5.

[0054] Air compressor 3 is, for example, a centrifugal compressor with a solid impeller with blades on the front (in the direction of the air flow) side installed inside the first part of the housing pipe 1, has a front axial conical protrusion to reduce drag, and is tightly secured to the shaft of the electric motor 4.

[0055] The electric motor 4 is, for example, the brushless motor 1.

[0056] The air flow swirl chamber 5 is a cavity limited along the perimeter and at the back by the housing 1, and at the front by the disk of the impeller of the air compressor 3; it has an air flow inlet along the inner perimeter of the housing 1 and an axial outlet to the channel for increasing the angular velocity 6.

[0057] The angular velocity increase channel 6 is the middle part of the housing 1 made in the form of a hollow pipe with a diameter 2-4 times smaller than the diameter of the air flow swirling chamber 5, has an inlet at the front and an outlet for the air flow at the rear.

[0058] The gas-air mixture nozzle 7 is an angular (about 90°) welded joint of the channel for increasing the angular velocity 6 with the shell 15.

[0059] The reflector 8 is made in the form of a steel cup, installed with its open end towards the hot water supply nozzle 7, which is installed coaxially with the shell 14 and secured by welding to the central body 15.

[0060] The fuel gas supply nozzle 9 is made up of holes located at intervals of 0.5 cm around the entire circumference of the bottom of the recess of the aerodynamic valve 10, connected to the fuel gas supply pipe (not shown in the diagram), while the inclination of the walls of the recess coincides with the inclination of the axis of the holes.

[0061] The aerodynamic valve 10 is a recess with a 45° inclination of the side walls, formed by the body 1 in the pipe of the channel for increasing the angular velocity 6, has a depth and width equal to a quarter of the diameter of the latter, is located up to the hot water supply nozzle 7 at a distance equal to the depth of the recess of the aerodynamic valve 10.

[0062] Detonation chamber 11 is made in the form of a cavity formed by a shell 14, a central body 15, a reflector 8, has an input from the GVS nozzle 7 and an output to the outlet nozzle 16.

[0063] The laser device for initiating directed detonation 12 is installed on the outer side along the circumference in the openings of the housing 1 on the side of the outlet of the outlet nozzle 16, contains at least three laser radiation sources 18, and is secured with screws.

[0064] The backup detonation initiator13 is made in the form of a geometrically located detonation chamber 11 on the axis of the declared engine with a bracket of an electric spark plug or glow plug secured, for example, by welding, to the housing 1 [https: / / ru.wikipedia.org / wiki / Светча накаливания / ].

[0065] Shell 14 is part of body 1 and is made in the form of a spherical bottom with a central hole and a cylindrical part connected by welding, forming a pipe expanding along the flow of gases.

[0066] The central body 15 is located in the tail section of the shell 14 coaxially with the body 1, is part of the outlet nozzle 16 and is made in the form of a volumetric axisymmetric drop-shaped figure formed by connecting a spherical bottom directed towards the hot water supply nozzle with a cylindrical cup forming an axial recess and a cone made by flexible, rolling and welding sheet steel; wherein the central body 15 is rigidly fixed to the shell 14 by means of three brackets.

[0067] The outlet nozzle 16 is a structure that combines a shell 14 and a central body 15 connected to each other by brackets, welded to the channel for increasing the angular velocity 6 to form the actual hot water supply nozzle 7.

[0068] Focal point 17 is an imaginary point of the internal space of housing 1, located on the axis of detonation chamber 11 in the section of the GVS nozzle 7, where all laser beams 19 converge.

[0069] The laser radiation sources 18 together form a laser device for initiating directed detonation 12, and are devices with solid cooled output windows (not shown in the Fig.) that generate coherent monochromatic light with high directivity, with a total power sufficient for breaking down the gas-air mixture, while they (laser sources 12) are installed around the circumference outside the housing 1 and secured with screws.

[0070] Laser beams 19 are beams of coherent monochromatic light with high directivity.

[0071] The following is a description of the claimed technical solution.

[0072] The declared engine (Fig. 1, Fig. 2) functionally consists of four functional units (not designated by positions in the Fig.):

[0073] - outdoor air intake and compression unit,

[0074] - unit for forming a pulsating flow of gas-air mixture,

[0075] - detonation chamber unit,

[0076] - outlet jet nozzle assembly.

[0077] Each of the above-mentioned functional units is formed from the components designated above by positions 1-19 and indicated in Fig. 1 and Fig. 2. The output of each unit is combined with the input of the next: the output of the air intake and compression unit is connected to the input of the unit for forming a pulsating flow of the fuel-air mixture, the output of which is connected to the input of the detonation chamber unit, the output of which is connected to the input of the outlet jet nozzle unit, for example, by a welded joint.

[0078] The units are installed in a single housing 1, which is a hollow solid pipe of variable cross-section made of three parts of different diameters, manufactured, for example, by welding, wherein the first and third parts are made with a diameter of the same order (the cross-sectional area differs by no more than 20%), and the middle part is made with a diameter 2-4 times smaller, while the transitions of the diameters are made in the form of bottoms with a central hole and are made, for example, by rolling sheet metal, wherein the open end of the first part is made with a narrowing diameter (Fig. 1) with the possibility of taking in outside air.

[0079] Air intake and compression unit contains an axisymmetric air intake 2, an air compressor 3 with an electric motor 4, installed in a housing 1 and connected to it, for example, by a screw connection.

[0080] The use of an electric motor 4 in the air intake and compression unit to rotate the air compressor 3 allows for the simplification of the manufacture of the PURVD by eliminating the structurally complex turbine and increases efficiency by directing all the energy generated by fuel combustion to the creation of jet thrust.

[0081] Unit for generating a pulsating flow of gas-air mixture is an air duct with the ability to create a pulsating longitudinal flow of hot water and contains:

[0082] - an air flow swirling chamber 5 with a diameter equal to the diameter of the air compressor 3, wherein the outlet opening of the air flow swirling chamber 5 is axially aligned with the inlet of the channel for increasing the angular velocity 6, wherein the diameter of the channel for increasing the angular velocity 6 is made smaller than the diameter of the air flow swirling chamber 5 by 2-6 times;

[0083] - gas-air mixture nozzle 7;

[0084] - reflector 8;

[0085] - channel for increasing angular velocity 6,

[0086] - aerodynamic valve 10 for preventing detonation products from entering the fuel gas and air supply system, made in the form of an annular recess in the channel for increasing the angular velocity 6, and containing (aerodynamic valve 10) side walls directed at an angle of 45° towards the detonation chamber 11;

[0087] - fuel gas supply nozzle 9, made in the form of holes with the possibility of gas flowing into the recess of the aerodynamic valve 10.

[0088] The air flow swirl chamber 5, the hot water supply nozzle 7, the angular velocity increase channel 6, the aerodynamic valve 10, and the fuel gas supply nozzle 9 are installed in the housing 1 and connected to it, for example, by a welded joint. The reflector 8 is connected to the central body 15, for example, by a welded joint.

[0089] Detonation chamber assembly contains: a detonation chamber 11, a laser device for initiating directed detonation 12, a backup detonation initiator 13.

[0090] Detonation chamber 11 is formed as a cavity bounded by the engine's components (shell 14, central body 15, deflector 8). The cavity has an inlet in the form of a hot-air mixture nozzle 7 and an outlet at an outlet nozzle 16. This represents a type of combustion chamber where the hot-air mixture combusts at supersonic speed under the action of a detonation wave, resulting in a volumetric explosion. Due to the sharp increase in pressure and temperature caused by the detonation wave, the thermodynamic efficiency of the engine is increased.

[0091] The laser detonation initiation device 12 comprises 3-8 laser radiation sources 18, each of which has a laser beam intensity 19 lower than that required to break through the gas-air mixture. The laser radiation sources 18 are mounted circumferentially on the side of the outlet nozzle 16, the laser beams 19 of which are directed toward the outlet of the gas-air mixture nozzle 7, where they form a focal point 17 with a radiation intensity above the gas-air mixture breakdown threshold. The focal point 17 is geometrically located on the axis of the claimed engine in the cross-section of the outlet of the gas-air mixture nozzle 7 to reduce the length of the pre-detonation section.

[0092] Laser radiation sources 18 are mounted on the outside of housing 1, for example, by screw connection. The entrance of laser beams 19 into detonation chamber 11 is provided with windows transparent to the type of laser radiation used, capable of protecting laser radiation sources 18 (the windows are included in the laser radiation sources 18).

[0093] The backup detonation initiator 13, capable of ensuring uninterrupted engine operation in the event of insufficient power of the laser device 12, is designed in the form of an electric spark spark plug or glow plug [https: / / ru.wikipedia.org / wiki / Свеча накаливания / ], geometrically located in the detonation chamber 11 on the axis of the claimed engine with a bracket secured, for example, by welding, to the housing 1. The installation location of the backup detonation initiator 13, as a rule, is selected in the vicinity of the focal point of the laser device for initiating directional detonation 12 (directly at the focus or not further than the dimensions of the working area - a spark or a heater).

[0094] In this case, the detonation chamber 11, the laser device for initiating directed detonation 12, the backup detonation initiator 13 are installed in the housing 1 and connected to it, for example, by a welded or screwed connection.

[0095] Exit jet nozzle assembly contains:

[0096] - outer shell 14 of cylindrical shape;

[0097] - central body 15 in the form of a conical element of revolution.

[0098] The shell 14 and the central body 15 form the outlet nozzle 16, wherein the wall of the central body 15 forms the inner wall of the outlet nozzle 16, wherein the central body 15 is fixed in the outer shell 14 by rods, for example, by welding.

[0099] The outlet nozzle 16 can be made by, for example, molding, welding, milling, 3D printing.

[0100] The design of the outlet nozzle 16 is annular and provides high energy efficiency and specific impulse, is easy to manufacture and operate and allows for uniform distribution in the detonation chamber 11 of the detonation flow having radial and axial components from the outlet of the gas-air mixture nozzle 7 to the outlet of the outlet nozzle 16.

[0101] In this case, the cylindrical shell 14 is attached to the body 1, for example, by welding.

[0102] The following is the declared operating method of the declared engine.

[0103] Conduct five working cycle processes sequentially.

[0104] The first process of the operating cycle—filling detonation chamber 11 with a gas-air mixture—is accomplished by simultaneously performing three operations: intake and compression of outside air, formation of the gas-air mixture, and generation of a pulsating flow. This process is accomplished by the combined and simultaneous operation of the outside air intake and compression unit and the unit that generates the pulsating gas-air mixture flow.

[0105] Intake and compression of outside air

[0106] Outside air enters air compressor 3 through axisymmetric air intake 2, driven by electric motor 4. There, the air receives rotational kinetic energy from the impeller and is compressed by centrifugal force to excess pressure, whereby adiabatic compression increases the temperature. When the UAV is not moving, air is supplied due to the vacuum created by air compressor 3; when moving, it is supplied due to the pressure of the oncoming flow. The air, spun and compressed by air compressor 3, enters airflow swirl chamber 5, where a funnel-shaped air movement is formed with an axial outlet to the inlet of angular velocity increase channel 6. In the latter, due to the smaller diameter of angular velocity increase channel 6 by 2-4 times, the angular velocity of the air flow increases by 2-4 times.

[0107] Formation of a gas-air mixture

[0108] As the air flow moves through the angular velocity increase channel 6, it mixes with the fuel gas in a ratio that forms an explosive gas-air mixture. Fuel gas enters the angular velocity increase channel 6 as follows: gas supplied to the specified engine via a pipeline passes through the fuel gas supply nozzle 9 into the annular recess of the aerodynamic valve 10 and, with a swirling action, mixes with the air flow in the angular velocity increase channel 6; the gas-air mixture then enters the inlet of the hot water supply nozzle 7.

[0109] Formation of pulsating flow

[0110] At the outlet of the GVS nozzle 7 in the detonation chamber 11, low-pressure areas are created in the center of the vortex, causing periodic rarefaction and an increase in pressure together with the flow coming from the reflector 8, forming a pulsating flow movement regime.

[0111] The second process of the operating cycle—initiation of directed detonation—is performed in detonation chamber 11 by laser device for initiating directed detonation 12, independently or in conjunction with backup detonation initiator 13. Detonation initiation in conjunction with backup detonation initiator 13 is used to start the claimed engine in order to reduce the power of laser radiation sources 18, which is ensured by their joint synchronized operation. After the operating mode of the claimed engine is established, detonation initiation is performed independently by laser device for initiating directed detonation 12 without backup detonation initiator 13.

[0112] The third process of the working cycle - the propagation of a detonation wave in the form of a volumetric explosion with increasing pressure at a constant volume, is realized in the detonation chamber unit, directly in the detonation chamber 11.

[0113] The breakdown front—an extended, conically shaped detonation spark—is formed in the following sequence. Laser beams 19, having an intensity lower than that required for breakdown of the gas-air mixture, are directed from radiation sources 12 to focal point 17, where the combined intensity increases and breakdown of the gas-air mixture occurs. Because lower radiation intensity is required for detonation propagation, a conically shaped breakdown front develops between laser beams 19 from focal point 17 to laser radiation sources 12.

[0114] The breakdown front initiates in the detonation chamber 11 a detonation wave of the gas-air mixture in the form of a volumetric explosion directed from the outlet of the GVS nozzle 7 to the outlet of the outlet nozzle 16 in a channel limited by the shell 14 and the central body 15.

[0115] In the volume of the detonation chamber 11, uniform development of detonation directed towards the outlet nozzle 16 occurs with increasing pressure at a constant volume, while the development of the shock wave front directed inward into the channel of increasing angular velocity 6 is prevented by the aerodynamic valve 10. The aerodynamic valve 10 also prevents detonation products from entering the fuel gas and air supply system.

[0116] The fourth process of the working cycle - the expansion of gases directed towards the outlet of the outlet nozzle 16 in the form of a shock wave front and the creation of thrust, is implemented in the units: detonation chamber, outlet jet nozzle, and the formation of a pulsating flow of hot water mixture.

[0117] The increase in pressure and temperature in the volume of the detonation chamber 11 causes the development of an expansion of gases directed towards the outlet of the outlet nozzle 16 in the form of a shock wave front. The directed shock wave from the outlet of the detonation chamber 11 rushes to the inlet of the outlet nozzle 16, passing through which in the form of an outflow of jet stream of combustion products it is ejected into the atmosphere.

[0118] The fifth process of the working cycle - the pressure drop in the detonation chamber 11 as the shock wave passes - the rarefaction phase of the shock wave - and the simultaneous start of filling the hot water supply of the next cycle, is implemented in the detonation chamber unit and in the unit for forming the pulsating hot water supply flow.

[0119] After the end of the compression phase of the shock wave in the vicinity of the DHW nozzle 7, a rarefaction phase occurs in the detonation chamber 11 with a pressure lower than the pressure in the angular velocity increase channel 6. This pressure ratio opens the aerodynamic valve 10; the DHW flow, with its active front, displaces the gas in the form of combustion products and begins to fill the detonation chamber 11, which marks the beginning of the implementation of the first process of the next cycle.

[0120] The following are examples of the implementation of the claimed technical solution.

[0121] Testing of the claimed engine was conducted in the laboratory of Astraproekt LLC in Kazan. The applicant developed and tested the following experimental devices:

[0122] - with a diameter of the middle part of the body 1 in two versions - 2 times and 4 times smaller than the first and third parts;

[0123] - laser device for initiating directed detonation in two versions - with three and eight laser radiation sources 18.

[0124] To measure the characteristics of the declared engine, the following devices are installed on the test bench:

[0125] - strain gauge thrust meter 0-100 kgf - thrust measurement, jet flow velocity estimation;

[0126] - anemometer (Pitot probe with digital differential pressure gauge, error 10%) - measurement of incoming air flow;

[0127] - portable anemometer - measuring the flow rate of propane;

[0128] - electromagnetic and piezoelectric microphones with an oscilloscope - measurement and calculation of speeds (pressure increase in the detonation chamber, breakdown detonation speed, initial speed in the microzone, speed inside the chamber).

[0129] Example 1. Operation of the declared engine with three laser radiation sources, an electric spark backup detonation initiator, and a channel for increasing angular velocity with a diameter half that of the engine.

[0130] The claimed engine consists of four functional units: an outside air intake and compression unit, a pulsating air-fuel mixture flow generation unit, a detonation chamber unit, and an outlet jet nozzle unit. The outlet of the air intake and compression unit is connected to the inlet of the pulsating air-fuel mixture flow generation unit, the outlet of which is connected to the inlet of the detonation chamber unit, the outlet of which is connected to the inlet of the outlet jet nozzle unit. The units are installed in a single casing 1, which is a hollow one-piece pipe of variable cross-section. The diameters of casing 1 of the first and third parts are, for example, 88 mm, the diameter of the middle part is 44 mm (2 times smaller). The transitions of the diameters of casing 1 are made smooth in the form of bottoms with a central hole, while the open end of the first part is designed with a narrowing and the ability to intake outside air.

[0131] The air intake and compression unit comprises an axisymmetric air intake 2 with a narrowing of the housing in the form of an opening with a diameter of, for example, 60 mm for intake of outside air, an air compressor 3 with a diameter of, for example, 88 mm with a drive from an electric motor 4. The working wheel of the air compressor 3 (impeller) has a diameter of, for example, 65 mm; the electric motor 4 is brushless with a power of, for example, 200 W, the rotation speed is equal to, for example, 44000 rpm with a gearbox of 1:4.

[0132] The unit for forming a pulsating flow of gas-air mixture is an air channel with the possibility of creating a pulsating longitudinal flow of gas-air mixture and contains: an air flow swirling chamber 5 with a diameter of, for example, 88 mm, a channel for increasing the angular velocity 6 with a diameter 2 times smaller than the diameter of the air flow swirling chamber (44 mm), a hot water supply nozzle 7, a reflector 8, a fuel gas supply nozzle 9, an aerodynamic valve 10. In this case, the following are axially sequentially combined: the outlet opening of the air flow swirling chamber 5 with the inlet of the channel for increasing the angular velocity, the outlet of which forms the hot water supply nozzle 7 at the junction with the shell 14. In this case: the air flow swirling chamber 5, the channel for increasing the angular velocity 6, the gas-air mixture nozzle 7, the fuel gas supply nozzle 9, the aerodynamic valve 10, are installed in the housing.The reflector 8 is formed as a recess in the central body 15, geometrically shaped as a cup with a diameter of, for example, 44 mm, and a depth of, for example, 22 mm. The aerodynamic valve 10 is formed as a recess in the angular velocity increase channel 6 at a distance of, for example, 22 mm from the hot water supply nozzle 7, has a depth and width of, for example, 22 mm each, and a wall slope of 45° towards the outlet. At the bottom of the aerodynamic valve 10 along the circumference of its cross-section, holes are made every, for example, 2 mm, with a diameter of, for example, 1 mm and the same slope of 45°, constituting the elements of the nozzle 9. Gaseous propane, for example, is supplied to the nozzle 9 through a tube from an external source (not specified in this description).

[0133] The detonation chamber unit comprises: a detonation chamber 11, a laser device for initiating directed detonation 12 with laser radiation sources 18 generating laser beams 19, a backup detonation initiator 13. In this case, the detonation chamber is formed as a cavity limited by a shell 14, a central body 15 and a reflector 8, having an input in the form of a nozzle GVS7, an output - an outlet nozzle 16. In this case, the laser device for initiating directed detonation 12 contains three diode laser radiation sources 18. In this case, the laser radiation sources 18 are installed on the outer side of the housing 1 along the circumference on the side of the outlet of the outlet nozzle 16, the laser beams 19 of which are directed towards the outlet of the nozzle GVS 7, where they form a focal point 17. In this case, the focal point 17 is located geometrically on the axis of the declared engine in section of the nozzle outlet of the gas-air mixture 7 to reduce the length of the pre-detonation section.In this case, the laser radiation sources 18 have a wavelength of, for example, 520 nm, a power of, for example, 1.2 W, a lens for focusing at a point of, for example, ~0.5 mm, a window for the laser beams entering the detonation chamber 11 that is transparent for the type of laser radiation used, with the possibility of protection, for example, made of quartz glass, and a heat sink (radiator), supplying voltage of, for example, 6 V. In this case, the power of individual laser radiation 18 is insufficient for the breakdown of the GVS. In this case, three focused sources at the focal point 17 have an intensity of laser beams 19, for example, ~10⁷ W / cm², which is sufficient to initiate the breakdown of the GVS. In this case, the backup detonation initiator 13 in the form of an electric spark plug with an ignition voltage of, for example, ~ 50 kV; installed in the area of ​​the focal point 17 by a bracket on the housing 1. In this case, the control (supply) voltages to the device for initiating directional detonation 12 and the backup detonation initiator 13 are supplied from the control unit (not given in this description).

[0134] The outlet jet nozzle assembly comprises: an outer shell 14 with a diameter of, for example, 88 mm and a cylindrical shape; a central body 15 in the form of a conical element of revolution with a largest diameter of, for example, 65 mm, and a length of, for example, 70 mm. The shell 14 and the central body 15 form an outlet nozzle 16. The wall of the central body forms the inner wall of the outlet nozzle. The central body is fixed in the outer shell by rods; the cylindrical shell is attached to the body.

[0135] The operation of the claimed engine is based on a high-frequency repetition of a thermodynamic cycle similar to the Humphrey cycle. The operating cycle includes the following five sequential processes:

[0136] - filling the detonation chamber 11 with a gas-air mixture;

[0137] - initiation of directed detonation;

[0138] - propagation of a detonation wave in the form of a volumetric explosion with increasing pressure at a constant volume;

[0139] - expansion of gases directed towards the outlet of the outlet nozzle 16 in the form of a shock wave front and the creation of thrust;

[0140] - pressure drop in detonation chamber 11 as the shock wave passes (shock wave rarefaction phase) and the simultaneous start of filling the hot water supply of the next cycle.

[0141] The declared engine uses a fuel gas that can form an explosive mixture with air, for example, propane (the explosive concentration of propane with air is from 2.1% to 9.5%, the most flammable mixture is 4.2%, the autoignition temperature is 445 °, the propagation velocity is 1000-5000 m / s, the gas pressure during an explosion in a closed volume is 0.858 MPa). Other flammable gases (methane, propane / butane, acetylene, hydrogen, etc.) or liquid fuel vapors (gasoline, fuel) can also be used as a fuel gas in accordance with their characteristics [GOST 31610.20-1-2020 (ISO / IEC 80079-20-1: 2017) Explosive atmospheres. Part 20-1. Characteristics of substances for gas and vapour classification. Test methods and data (ISO / IEC 80079-20-1:2017, MOD)].

[0142] Due to the directed detonation combustion of the gas-air mixture at a constant volume, the high efficiency of the declared engine is ensured.

[0143] The declared engine operates in the declared manner as follows.

[0144] Conduct five working cycle processes sequentially

[0145] The first process of the operating cycle—filling detonation chamber 11 with a gas-air mixture—is accomplished by simultaneously performing three operations: intake and compression of outside air, formation of the gas-air mixture, and generation of a pulsating flow. This process is accomplished by the combined and simultaneous operation of the outside air intake and compression unit and the unit that generates the pulsating flow of the gas-air mixture.

[0146] Intake and compression of outside air

[0147] Outside air enters air compressor 3 through axisymmetric air intake 2, driven by electric motor 4, where the air receives rotational kinetic energy from the impeller and is compressed under centrifugal force to an excess pressure of, for example, 20 kPa, wherein adiabatic compression increases the temperature. When the UAV is not moving, air is supplied due to the vacuum created by air compressor 3, while when moving, it is supplied due to the pressure of the oncoming flow. The air, spun and compressed by air compressor 3, enters air flow swirling chamber 5, where a funnel-shaped air movement is formed with an axial outlet to the inlet of angular velocity increase channel 6. In angular velocity increase channel 6, with its diameter of 44 mm, the angular velocity of the air flow increases by 2 times due to its diameter being 2 times smaller than the diameter of the air flow swirling chamber.The air flow rate is, for example, 250 l / min (about 0.045 kg / s), the air flow speed at the outlet of nozzle 16 is, for example, ~150 m / s.

[0148] Formation of a gas-air mixture

[0149] The explosive concentration ratio of the hot water supply is achieved by manual or automatic regulation of the pressure and speed of the supplied fuel gas using methods known in the art (not given in this description).

[0150] As the air flow moves through the angular velocity increase channel 6, it is mixed with fuel gas, such as propane, in a ratio sufficient to form an explosive gas-air mixture of, for example, 8% (0.0036 kg / s of propane). Fuel gas enters the angular velocity increase channel 6 as follows: gas supplied to the specified engine via a pipeline passes through the fuel gas supply nozzle 9 into the annular recess of the aerodynamic valve 10 and is mixed with the air flow in the angular velocity increase channel 6 with a swirl; the gas-air mixture then enters the inlet of the hot water supply nozzle 7.

[0151] Formation of pulsating flow

[0152] The unit for generating a pulsating flow of gas-air mixture has a design that ensures flow disruption and a wave at the speed of sound at the outlet of the DHW nozzle 7 (this process is described in detail in US Patent 2,794,341 of 04.06.1957. Measuring instrument - sound generator for measuring liquid flow and / or pressure).

[0153] The gas-air mixture entering the GVS nozzle 7 has a high angular and longitudinal flow velocity, which ensures rapid filling of the detonation chamber 11.

[0154] At the outlet of the hot water supply nozzle 7 in the detonation chamber 11, low-pressure areas are created in the center of the vortex, causing periodic rarefaction and pressure increases in conjunction with the flow coming from the detonator 8, forming a pulsating flow regime. The velocity of the pressure increase / decrease front of the pulsating flow is higher than the speed of sound, i.e., above 340 m / s. Ensuring the hot water supply flow velocity above the speed of sound satisfies the conditions for the formation of a shock wave in a supersonic flow. The resulting pulsating flow regime ensures the operation of the specified engine in high-frequency mode. The pulsation frequency in the detonation chamber is a sound with a band from 500 Hz to 6000 Hz, with a level above 0.7 at frequencies from 1000 Hz to 3000 Hz.

[0155] The use of a unit for forming a pulsating flow of gas-air mixture, containing: an air flow swirl chamber 5, an angular velocity increase channel 6, a hot water supply nozzle 7, a reflector 8, a fuel gas supply nozzle 9, an aerodynamic valve 10, allows to increase the traction efficiency (averaged by the average thrust frequency) of the declared engine by providing a high pulsation frequency.

[0156] The second process of the operating cycle—initiation of directed detonation—is performed in detonation chamber 11 by laser device for initiating directed detonation 12, independently or in combination with backup detonation initiator 13. Detonation initiation in combination with backup detonation initiator 13 is used to start the claimed engine in order to reduce the power of laser radiation sources 18, which is ensured by their joint synchronized operation. After the operating mode of the claimed engine is established, detonation initiation is performed independently by laser device for initiating directed detonation 12 without backup detonation initiator 13.

[0157] Initiation of a laser-guided detonation device 12 in conjunction with a backup detonation initiator 13 to start the declared engine.

[0158] Detonation initiation with the addition of a backup detonation initiator 13 is used to start the claimed engine to reduce the power of laser radiation sources 18, which is achieved through their combined synchronized operation. After establishing the operating mode of the claimed engine, detonation initiation is performed independently by the laser detonation initiator device 12 without the backup detonation initiator 13. To achieve this, when an electric spark plug is installed as a backup detonation initiator 13, a spark discharge is ignited by applying an electrical pulse (see below for a description of spark plug ignition). At the same time, a pulse of laser radiation from device 12 is supplied, causing a combined intensity (of laser radiation and spark discharge) at focal point 17 that exceeds the breakdown threshold - as a result of which a conical detonation front is formed in detonation chamber 11, directed from the outlet of nozzle 7 of the gas-air mixture to the outlet of nozzle 16.The spark plug is ignited by electrical pulses from an external contactless system (DIS, coil-near-plug) with an ignition coil rated at up to 50 kV, connected to the engine control unit (not specified in this description). The pulse repetition rate depends on the specified engine operating mode, but is not lower than 100 Hz to prevent the exhaust gas mixture from escaping. The high voltage in the system ensures reliable gap breakdown and enables high-frequency synchronization of the backup detonation initiator 13 spark with the operation of the pulsating hot gas flow generator.

[0159] Using a backup detonation initiator 13 together with a laser directional detonation device 12 makes it possible to reduce the power of the laser radiation sources 18.

[0160] Initiation of the laser directional detonation device 12 independently by the laser directional detonation initiation device 12 without the backup detonation initiator 13.

[0161] At focal point 17, when the laser radiation intensity exceeds the breakdown threshold, a laser spark (the term jet is also used in technology) occurs, which develops asymmetrically: the plasma boundary moves towards the laser emitters at a speed of 10 5m / sec by the detonation mechanism [Advances in Physical Sciences. 1983, December. Vol. 111, Issue 4. G.V. Ostrovskaya, A.N. Zaidel. Laser Spark in Gases. Pp.580, 589,593]. The above effect is based on the fact that a significantly lower radiation intensity is required to maintain the detonation regime than to generate a laser spark. Thus, a breakdown front is formed in the detonation chamber 11 - an extended detonation spark of a conical shape directed from the outlet of the GVS nozzle 7 to the outlet of the outlet nozzle 16. The initial detonation velocity in the microzone of the focal point 17 is from 1500 m / s to 2200 m / s, which corresponds to the conditions for the occurrence of a shock wave in a supersonic flow.

[0162] Thus, the laser directed detonation device 12 makes it possible to initiate a high-speed, conical-shaped detonation breakdown front directed toward the outlet nozzle 16.

[0163] The third process of the working cycle - the propagation of a detonation wave in the form of a volumetric explosion with increasing pressure at a constant volume, is realized in the detonation chamber unit, directly in the detonation chamber 11.

[0164] The breakdown front—an extended, conical detonation spark—is formed in the following sequence. Laser beams 19, having an intensity lower than that required for breakdown of the gas-air mixture, are directed from radiation sources 12 to focal point 17, where the combined intensity increases and breakdown of the gas-air mixture occurs. Because lower radiation intensity is required for detonation propagation, the breakdown front develops between laser beams 19 from focal point 17 to laser radiation sources 12, forming a conical breakdown front.

[0165] The conical breakdown front initiates a detonation wave of the gas-air mixture in the detonation chamber 11 in the form of a volumetric explosion directed from the outlet of the GVS nozzle 7 to the outlet of the output nozzle 16 in a channel limited by the shell 14 and the central body 15. The velocity of detonation propagation in the direction of the outlet nozzle is approximately twice the velocity of lateral expansion in the detonation chamber [Advances in Physical Sciences. 1983. December. Vol. 111, Issue 4. G.V. Ostrovskaya, A.N. Zaidel. Laser spark in gases. Pp.580, 589,593]. The measured detonation velocity inside the detonation chamber 11 is from 700 m / s to 1200 m / s, the pressure jump in the detonation chamber 11 is ~100 kPa, which corresponds to the conditions for the occurrence of a shock wave in a supersonic flow.

[0166] In the volume of the detonation chamber 11, uniform development of detonation directed towards the outlet nozzle 16 occurs with increasing pressure at a constant volume, while the development of the shock wave front directed inward into the channel of increasing angular velocity 6 is prevented by the aerodynamic valve 10. The aerodynamic valve 10 also prevents detonation products from entering the fuel gas and air supply system.

[0167] The operation of the aerodynamic valve 10 is based on the fact that the fuel gas is injected under such a pressure and at such a speed that the detonation wave emanating from the detonation chamber 11 prevents the fuel from exiting the fuel gas supply injectors 9 during the period of excess shock wave pressure. Turbulence generated by the annular recess of the aerodynamic valve 10 prevents the detonation wave from moving in the opposite direction (toward the air flow swirl chamber 5) along the angular velocity increase channel 6. At the same time, the shock wave compresses and maintains or increases the pressure of the injected fuel. After the increased pressure of the detonation wave ceases (in the fifth process of the working cycle), the aerodynamic valve 10 switches to the fuel gas and air flow supply mode.

[0168] The laser directed detonation device 12 allows the initiation of a high-speed (about 10 5m / s) detonation breakdown front of a conical shape, causing uniform development of directional detonation in the form of a volumetric explosion with increasing pressure at a constant volume. Due to the directional detonation non-turbulent nature of the combustion of the hot-air mixture and the rapid closure of the inlet of detonation chamber 11 by aerodynamic valve 10, the degree of total pressure increase and temperature during adiabatic compression increase, which increases the efficiency of the claimed engine (the higher the pressure in the chamber during the explosion, the higher the efficiency of the pulsejet [https: / / руни.рф / Воздушно-реактный двигатель]).

[0169] The fourth process of the working cycle - the expansion of gases directed towards the outlet of the outlet nozzle 16 in the form of a shock wave front and the creation of thrust, is realized in the units: detonation chamber, outlet jet nozzle, and the formation of a pulsating flow of hot water mixture.

[0170] The increase in pressure and temperature within detonation chamber 11 causes the development of a shock wave front directed toward the outlet nozzle 16. The directed shock wave from the outlet of detonation chamber 11 rushes toward the inlet of outlet nozzle 16, passing through which it is ejected into the atmosphere as a jet stream of combustion products. The jet stream velocity at the outlet nozzle 16 is ~450 m / s.

[0171] Thus, the laser directed detonation device 12 makes it possible to initiate a high-speed (about 10 5m / s) a detonation breakdown front of conical shape, causing a volumetric explosion in the form of a uniform development of a detonation wave of the GVS directed towards the outlet nozzle 16, having a longitudinal velocity significantly higher than the velocity of the transverse expansion, while preventing a decrease in speed due to turbulence in the combustion chamber, the longitudinal velocity of the jet flow increases, as a result of which the thrust and efficiency of the declared engine increase.

[0172] The fifth process of the working cycle - the pressure drop in the detonation chamber 11 as the shock wave passes (the rarefaction phase of the shock wave) and the simultaneous start of filling the hot water supply of the next cycle, is implemented in the detonation chamber unit and in the unit for forming the pulsating hot water supply flow.

[0173] After the end of the compression phase of the shock wave in the vicinity of the hot water supply nozzle 7, a rarefaction phase occurs in the detonation chamber 11 with a pressure lower than the pressure in the angular velocity increase channel 6. This pressure ratio opens the aerodynamic valve 10; the hot water flow, which has a high angular and axial velocity, possessing a significant momentum, displaces the gas in the form of combustion products with an active front that has an increased (relative to atmospheric) pressure and begins to fill the detonation chamber 11 - i.e. this is already the beginning of the implementation of the first process of the next cycle.

[0174] The operation of the pulsating flow generation unit of the hot water supply and the detonation chamber unit ensures the rapid implementation of the working cycle processes and the non-stop transition between them, thereby allowing the declared engine to operate at a high frequency of pulsations of directed detonation, which increases the traction efficiency of the declared engine.

[0175] Based on the evaluation of the declared engine, it was established:

[0176] - thrust is 27 N,

[0177] - pulsation frequency 500 Hz,

[0178] - exhaust velocity 600 m / s.

[0179] - energy efficiency coefficient 135. The energy efficiency coefficient characterizes the share of fuel combustion energy in the creation of engine thrust and is calculated in a similar way to the energy efficiency: by calculating the product of engine thrust and the set flight speed of 100 m / s, divided by the electric motor power of 200 W.

[0180] Example 2. Operation of the claimed engine with eight laser radiation sources, a backup detonation initiator in the form of a glow plug, and a channel for increasing angular velocity with a diameter four times smaller.

[0181] The declared engine consists of four functional units: an outside air intake and compression unit, a pulsating air-fuel mixture flow formation unit, a detonation chamber unit, and an outlet jet nozzle unit. The outlet of the air intake and compression unit is connected to the inlet of the pulsating air-fuel mixture flow formation unit, the outlet of which is connected to the inlet of the detonation chamber unit, the outlet of which is connected to the inlet of the outlet jet nozzle unit. The units are installed in a single casing 1, which is a hollow one-piece pipe of variable cross-section. Casing 1 with diameters of the first and third parts, for example, 88 mm, the diameter of the middle part is 4 times smaller (22 mm) - The transitions of the diameters of casing 1 are made smooth in the form of bottoms with a central hole, while the open end of the first part is made with a narrowing and the ability to intake outside air.

[0182] The air intake and compression unit comprises an axisymmetric air intake 2 with a narrowing of the housing in the form of an opening with a diameter of, for example, 60 mm for intake of outside air. An air compressor 3 with a diameter of, for example, 88 mm driven by an electric motor 4. The impeller of the air compressor 3 has a diameter of, for example, 65 mm; the electric motor 4 is brushless with a power of, for example, 200 W, the rotation speed is equal to, for example, 44,000 rpm with a gearbox of 1:4.

[0183] The unit for forming a pulsating flow of gas-air mixture is an air channel with the possibility of creating a pulsating longitudinal flow of gas-air mixture and contains: an air flow swirling chamber 5 with a diameter of, for example, 88 mm, a channel for increasing the angular velocity 6 with a diameter 4 times smaller than the diameter of the air flow swirling chamber (22 mm), a hot water supply nozzle 7, a reflector 8, a fuel gas supply nozzle 9, an aerodynamic valve 10. In this case, the following are axially sequentially combined: the outlet opening of the air flow swirling chamber 5 with the inlet of the channel for increasing the angular velocity, the outlet of which forms the hot water supply nozzle 7 at the junction with the shell 14. In this case: the air flow swirling chamber 5, the channel for increasing the angular velocity 6, the gas-air mixture nozzle 7, the fuel gas supply nozzle 9, the aerodynamic valve 10, are installed in the housing.The reflector 8 is formed as a recess in the central body 15, geometrically shaped as a cup with a diameter of, for example, 22 mm, and a depth of, for example, 22 mm. The aerodynamic valve 10 is formed as a recess in the angular velocity increase channel 6 at a distance of, for example, 22 mm from the hot water supply nozzle 7, has a depth and width of, for example, 22 mm, and a wall slope of 45° towards the outlet. At the bottom of the aerodynamic valve 10 along the circumference of its cross-section, holes are formed every, for example, 2 mm, with a diameter of, for example, 1 mm and the same slope of 45°, constituting the elements of the nozzle 9. Gaseous propane, for example, is supplied to the nozzle 9 through a tube from an external source (not specified in this description).

[0184] The detonation chamber unit comprises: a detonation chamber 11, a laser device for initiating directed detonation 12 with laser radiation sources 18 generating laser beams 19, a backup detonation initiator 13. In this case, the detonation chamber is formed as a cavity limited by a shell 14, a central body 15 and a reflector 8, having an input in the form of a nozzle GVS7, an output - an outlet nozzle 16. In this case, the laser device for initiating directed detonation 12 contains eight diode laser radiation sources 18. In this case, the laser radiation sources 18 are installed on the outer side of the housing 1 along the circumference on the side of the outlet of the outlet nozzle 16, the laser beams 19 of which are directed towards the outlet of the nozzle GVS 7, where they form a focal point 17. In this case, the focal point 17 is located geometrically on the axis of the declared engine in the outlet section of the GVS nozzle 7 to reduce the length of the pre-detonation section.In this case, the laser radiation sources 18 have a wavelength of, for example, 520 nm, a power of, for example, 1.2 W, a lens for focusing at a point of, for example, ~0.5 mm, a window for the laser beams entering the detonation chamber 11, transparent for the type of laser radiation used, with the possibility of protection, for example, from quartz glass, and a heat sink (radiator), supplying a voltage of, for example, 6 V. In this case, the power of individual laser radiation 18 is insufficient for breakdown of the GVS. In this case, three focused sources at the focal point 17 have an intensity of laser beams 19, for example, ~10⁷ W / cm. 2, which is sufficient to initiate a breakdown of the hot water supply system. In this case, the backup detonation initiator 13 is designed as a glow plug and is mounted in the area of ​​the focal point 17 by a bracket on the housing 1. In constant mode, the temperature of the glow plug heater is set below the flash point of the gas-air mixture used, for example, for a propane-air mixture - below 445°C. When a pulse is applied from the laser device for initiating directional detonation 12 at the focal point 17, the combined intensity (of laser and thermal radiation) exceeds the breakdown threshold - a conical detonation front is formed in the detonation chamber 11, directed from the outlet of the hot water supply nozzle 7 to the outlet of the nozzle 16.

[0185] The outlet jet nozzle assembly comprises: an outer shell 14 with a diameter of, for example, 88 mm and a cylindrical shape; a central body 15 in the form of a conical element of revolution with a largest diameter of, for example, 65 mm, and a length of, for example, 70 mm. The shell 14 and the central body 15 form an outlet nozzle 16. The wall of the central body forms the inner wall of the outlet nozzle. The central body is fixed in the outer shell by rods; the cylindrical shell is attached to the body.

[0186] The sequence of actions according to Example 1 was carried out, differing in that in the channel for increasing the angular velocity 6 with its diameter of 22 mm, due to its smaller diameter by 4 times compared to the diameter of the air flow swirling chamber, the angular velocity of the air flow increases by 4 times.

[0187] Based on the evaluation of the declared engine, it was established:

[0188] - thrust is 41 N,

[0189] - pulsation frequency 950 Hz,

[0190] - exhaust velocity 800 m / s.

[0191] - energy efficiency coefficient 135.

[0192] Example 3 (comparison example). Operation of the claimed engine with a velocity-increasing channel that is half the diameter, an electric spark backup detonation initiator, and no laser detonation initiator.

[0193] Used the declared engine according to Example 1.

[0194] The sequence of actions according to Example 1 was carried out, differing in that the laser device for initiating directed detonation 12 was not turned on; initiation was carried out only by the operation of the backup detonation initiator 13 - the electric spark plug.

[0195] Testing the claimed engine in this example allows us to evaluate the degree of efficiency of using laser devices for initiating directed detonation 12.

[0196] Based on the evaluation results of the declared engine in the comparison example, it was established:

[0197] - the thrust is 18 N,

[0198] - pulsation frequency 350 Hz,

[0199] - exhaust velocity 400 m / s.

[0200] - energy efficiency coefficient 90.

[0201] From a comparison of the results obtained in Examples 1 and 2 with the results obtained in Comparison Example 3, it can be concluded that the high pulsation frequency of the declared motor indicates the effective operation of the declared design of the pulsating hot water flow generating unit.

[0202] The test results of the declared engine based on Examples 1, 2, 3 are given in the summary Table.

[0203] Table. Summary table of technical characteristics of the declared engine based on the test results for Examples 1, 2, 3

[0204] Example Essential features Thrust, N Energy efficiency coefficient Flow velocity, m / s Pulse frequency, Hz 1 The diameter of the angular velocity increase channel is 44 mm. Three laser radiation sources 27 135 600 500 2 The diameter of the angular velocity increase channel is 22 mm. Eight laser radiation sources 41 220 800 950 3 The diameter of the channel for increasing the angular velocity is 44 mm. The backup source of detonation is a glow plug (without a laser source) 18 90 400 350

[0205] The highest values ​​of the technical characteristics of the declared engine:

[0206] - thrust 41 N;

[0207] - energy efficiency 220;

[0208] - pulsation frequency 950 Hz;

[0209] - exhaust velocity 800 m / s.

[0210] According to the calculated estimates, the flight efficiency for the established flight speed of 100 m / s with the highest energy efficiency index (220, example 2) is 30%, which is a high figure for a pulsejet.

[0211] The given examples of the implementation of the claimed engine, which have a difference in the diameter of the channel for increasing the angular velocity and in the number of diode laser radiation sources in the laser device for initiating directed detonation, indicate the achievement of the claimed technical result.

[0212] Thus, from the above, it can be concluded that the applicant has solved the identified technical problem and achieved the stated technical result, namely, a structurally simple, energy-efficient pulse jet engine for unmanned aerial vehicles and a method for its operation have been developed, ensuring:

[0213] - ease of manufacture and increased efficiency of fuel combustion energy use through the use of an electric motor to drive an air compressor (Examples 1, 2);

[0214] - increasing the traction efficiency - average traction per unit of time - by ensuring a high pulsation frequency, which is achieved by using a unit for generating a pulsating flow of gas-air mixture of the declared design and an aerodynamic valve for organizing an intermittent mode of supplying hot water to the combustion chamber (Examples 1, 2, 3);

[0215] - increasing thrust and efficiency with an increase in the jet flow exhaust velocity due to laser initiation of a stable wave of directed detonation of the hot gas mixture, the velocity of which (directed detonation of the hot gas mixture) in the direction of the outlet nozzle is up to two times higher than in the cross section (Examples 1, 2, 3).

Claims

1. A pulse jet engine with high-frequency directed detonation for an unmanned aerial vehicle, consisting of four functional units: an outside air intake and compression unit, a unit for generating a pulsating flow of a gas-air mixture, a detonation chamber unit, an outlet jet nozzle unit, wherein the output of each unit is combined with the input of the following: the output of the air intake and compression unit is connected to the input of the unit for generating a pulsating flow of a fuel-air mixture, the output of which is connected to the input of the detonation chamber unit, the output of which is connected to the input of the outlet jet nozzle unit; the units are installed in a single housing, which is a hollow solid pipe of variable cross-section made of three parts of different diameters, wherein the first and third parts are made with a diameter of the same order, and the middle part is made with a diameter 2-4 times smaller, while the transitions of the diameters are made in the form of bottoms with a central hole, while the open end of the first part is made with a narrowing diameter with the possibility of taking in outside air; the air intake and compression unit contains an axisymmetric air intake, an air compressor with an electric motor; the unit for generating a pulsating flow of a gas-air mixture is an air channel with the possibility of creating a pulsating longitudinal flow of a gas-air mixture and contains: an air flow swirling chamber with a diameter equal to the diameter of the air compressor; a channel for increasing the angular velocity, wherein the outlet opening of the air flow swirling chamber is axially aligned with the inlet of the channel for increasing the angular velocity, wherein the diameter of the channel for increasing the angular velocity is made smaller than the diameter of the air flow swirling chamber by 2-4 times; a gas-air mixture nozzle; a reflector made in the form of a recess in the central body; an aerodynamic valve for preventing detonation products from entering the fuel gas and air supply system, made in the form of an annular recess in the channel for increasing the angular velocity, wherein the aerodynamic valve contains side walls directed at an angle of 45° towards the detonation chamber;a fuel gas supply nozzle, designed in the form of openings with the ability to supply gas into the recess of the aerodynamic valve; wherein the air flow swirl chamber, the gas-air mixture nozzle, the channel for increasing the angular velocity, the aerodynamic valve, the fuel gas supply nozzle are installed in the housing, and the reflector is attached to the central body; the detonation chamber unit comprises: a detonation chamber, a laser device for initiating directed detonation, a backup detonation initiator; wherein the detonation chamber is formed as a cavity bounded by a shell, a central body and a reflector, having an inlet in the form of a nozzle for the gas-air mixture and an outlet to an outlet nozzle; wherein the laser device for initiating directed detonation contains 3-8 laser radiation sources, which are individually made with a power less than that required for the breakdown of the gas-air mixture, wherein the laser radiation sources are installed along a circumference on the side of the outlet nozzle, the laser beams of which are directed towards the outlet of the nozzle of the gas-air mixture, where they form a focal point with a radiation intensity above the breakdown threshold of the gas-air mixture; wherein the focal point is located geometrically on the axis of the pulse jet engine in the section of the outlet of the nozzle of the gas-air mixture in order to reduce the length of the pre-detonation section;wherein the laser radiation sources are installed on the outside of the housing; wherein the input of the laser beams into the detonation chamber is made with windows that are transparent for the type of laser radiation used, with the ability to protect the laser radiation sources; wherein the backup detonation initiator with the ability to ensure uninterrupted operation of the engine in the event of insufficient power of the laser device is made in the form of an electric spark spark plug or a glow plug, geometrically located in the detonation chamber on the axis of a pulse jet engine with high-frequency directed detonation with a bracket secured to the housing; wherein the detonation chamber, the laser device for initiating directed detonation, and the backup detonation initiator are installed in the housing; The outlet jet nozzle assembly comprises: an outer shell of cylindrical shape; a central body in the form of a conical element of revolution; wherein the shell and the central body form an outlet nozzle, wherein the wall of the central body forms the inner wall of the outlet nozzle, wherein the central body is fixed in the outer shell by rods; wherein the cylindrical shell is attached to the body.

2. A method of operating a pulse jet engine with high-frequency directed detonation for an unmanned aerial vehicle according to paragraph 1, characterized in that five processes of the working cycle are carried out sequentially: the first process of the working cycle - filling the detonation chamber with a gas-air mixture - is carried out by simultaneously carrying out three operations: the intake and compression of outside air, the formation of a gas-air mixture, the formation of a pulsating flow, while the process is carried out by the joint and simultaneous operation of the unit for the intake and compression of outside air and the unit for the formation of a pulsating flow of gas-air mixture; Intake and compression of outside air: outside air enters an axisymmetric air intake into an air compressor driven by an electric motor, where the air receives rotational kinetic energy from the impeller and is compressed by centrifugal force to excess pressure, wherein adiabatic compression increases the temperature; when the unmanned aerial vehicle is not moving, air is supplied due to the vacuum created by the air compressor, while when moving, it is supplied due to the pressure of the oncoming flow; the air spun up and compressed by the air compressor enters the air flow swirling chamber, where a funnel-shaped air movement is formed with an axial outlet to the inlet of the channel for increasing the angular velocity, wherein in the latter, due to the smaller diameter of the channel for increasing the angular velocity by 2-4 times compared to the diameter of the air flow swirling chamber, the angular velocity of the air flow increases by 2-4 times; Formation of a gas-air mixture of hot water supply: during the movement of the air flow in the channel for increasing the angular velocity, it is mixed with the fuel gas in a ratio that forms an explosive hot water mixture; the fuel gas enters the channel for increasing the angular velocity as follows: the gas supplied to the pulse jet engine through the pipeline enters through the fuel gas supply nozzle into the annular recess of the aerodynamic valve and is mixed with the air flow in the channel for increasing the angular velocity with a swirl; then the hot water mixture enters the inlet of the hot water mixture nozzle; formation of a pulsating flow: at the outlet of the hot water supply nozzle in the detonation chamber, low-pressure areas are created in the center of the vortex, causing periodic rarefactions and an increase in pressure together with the flow coming from the reflector, forming a pulsating flow regime; the second process of the operating cycle - the initiation of directional detonation - is carried out in the detonation chamber by a laser device for initiating directional detonation independently or in combination with a backup detonation initiator, while the initiation of detonation in combination with the backup detonation initiator is used to start the pulse jet engine in order to reduce the power of the laser radiation sources, which is ensured by their joint synchronized operation; after the operating mode of the pulse jet engine has been established, the initiation of detonation is carried out independently by the laser device for initiating directional detonation without the backup detonation initiator; the third process of the working cycle – propagation of the detonation wave in the form of a volumetric explosion with increasing pressure at a constant volume, is realized in the detonation chamber unit, directly in the detonation chamber; the breakdown front – an extended detonation spark of a conical shape – is formed in the following sequence: laser beams having an intensity lower than that required for the breakdown of the gas-air mixture from the radiation sources are directed to the focal point, where the total intensity becomes higher and a breakdown of the gas-air mixture occurs; due to the fact that a lower radiation intensity is required for the propagation of detonation, a breakdown front of a conical shape develops between the laser beams from the focal point to the laser radiation sources; the breakdown front initiates a detonation wave of the gas-air mixture in the detonation chamber in the form of a volumetric explosion directed from the outlet of the gas-air mixture nozzle to the outlet of the outlet nozzle in a channel limited by the shell and the central body;in the volume of the detonation chamber, uniform development of detonation directed towards the outlet nozzle occurs with increasing pressure at a constant volume, while the development of an inward-directed increase in the angular velocity of the shock wave front is prevented by an aerodynamic valve, which also prevents detonation products from entering the fuel gas and air supply system; The fourth process of the working cycle is the expansion of gases directed towards the outlet of the outlet nozzle in the form of a shock wave front and the creation of thrust, which is realized in the following units: the detonation chamber, the outlet jet nozzle, and the formation of a pulsating flow of hot gas mixture; the increase in pressure and temperature in the volume of the detonation chamber causes the development of an expansion of gases directed towards the outlet nozzle in the form of a shock wave front; the directed shock wave from the outlet of the detonation chamber rushes to the inlet of the outlet nozzle, passing through which it is ejected into the atmosphere as an outflow of a jet stream of combustion products; The fifth process of the working cycle - the pressure drop in the detonation chamber as the shock wave passes - the rarefaction phase of the shock wave - and the simultaneous start of filling the hot water supply of the next cycle, is implemented in the detonation chamber unit and in the unit for forming the pulsating flow of hot water supply; after the end of the compression phase of the shock wave, a rarefaction phase occurs in the vicinity of the hot water supply nozzle in the detonation chamber with a pressure lower than the pressure in the channel for increasing the angular velocity; this pressure ratio opens the aerodynamic valve, whereby the hot water supply flow, by the active front, displaces the gas in the form of combustion products and begins to fill the detonation chamber, which marks the beginning of the implementation of the first process of the next cycle.

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