CN110739602B - Pre-mixing type carbon dioxide pneumatic laser driven by pulse detonation rocket combustion - Google Patents
Pre-mixing type carbon dioxide pneumatic laser driven by pulse detonation rocket combustion Download PDFInfo
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- CN110739602B CN110739602B CN201911042320.2A CN201911042320A CN110739602B CN 110739602 B CN110739602 B CN 110739602B CN 201911042320 A CN201911042320 A CN 201911042320A CN 110739602 B CN110739602 B CN 110739602B
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01S—DEVICES USING THE PROCESS OF LIGHT AMPLIFICATION BY STIMULATED EMISSION OF RADIATION [LASER] TO AMPLIFY OR GENERATE LIGHT; DEVICES USING STIMULATED EMISSION OF ELECTROMAGNETIC RADIATION IN WAVE RANGES OTHER THAN OPTICAL
- H01S3/00—Lasers, i.e. devices using stimulated emission of electromagnetic radiation in the infrared, visible or ultraviolet wave range
- H01S3/09—Processes or apparatus for excitation, e.g. pumping
- H01S3/095—Processes or apparatus for excitation, e.g. pumping using chemical or thermal pumping
- H01S3/0951—Processes or apparatus for excitation, e.g. pumping using chemical or thermal pumping by increasing the pressure in the laser gas medium
- H01S3/0953—Gas dynamic lasers, i.e. with expansion of the laser gas medium to supersonic flow speeds
Abstract
The invention discloses a premixed carbon dioxide pneumatic laser driven by pulse detonation rocket combustion, which comprises a pulse detonation rocket combustion device, a transition section and CO2A pneumatic laser generating device and an exhaust section. Pulse detonationThe rocket combustion device is used for generating a high-temperature and high-pressure fuel gas heat source, is used as a total energy source for generating laser at downstream, and comprises a cylindrical shell, an oxidant injection panel and a turbulent flow spiral; the inner cavity of the cylindrical shell forms a pulse detonation combustion chamber. When the oxidant and the fuel are supplied in a pulse detonation combustion chamber in a pulse mode, collide with each other, uniformly mix and ignite, and under the action of the turbulent flow helix, pulse detonation combustion occurs in the pulse detonation combustion chamber; combustion gas is passed through CO2The pneumatic laser generating device generates pulse laser. The invention adopts the pulse detonation rocket combustion device as a pumping source, so that the produced laser has high efficiency and saves energy. When the device is used on a rocket or an aircraft, the device can generate thrust and laser without increasing the load.
Description
Technical Field
The invention relates to CO2The field of pneumatic lasers, in particular to a premixed carbon dioxide pneumatic laser driven by pulse detonation rocket combustion.
Background
The gas laser is a laser with the most varieties, the widest wavelength distribution area and the widest application in the laser family. Its outstanding advantage is: the wavelength distribution area of the emitted spectral line is wide, the quality of the light beam is high and the output power is high. Compared with other lasers, the gas laser also has the advantages of high conversion efficiency, simple structure, low manufacturing cost and the like, thereby being widely applied.
Basic working principle of gas laser: the pumping source releases energy, gas particles are selectively excited to a certain high energy level, so that particle number inversion between a certain low energy level is formed, an activated medium is generated, laser output is generated through optical cavity resonance, and the energy of the pumping source is converted into optical energy.
The gas dynamic laser can directly convert heat energy into coherent radiation energy, and the heat source form (such as combustion, chemical reaction, electric arc heating, nuclear reaction and the like) is not limited. The rocket type combustion driving pneumatic laser with the fuel and the oxidant utilizes fuel combustion as a pumping source, does not need to provide extra energy from the outside, has the advantages of stable performance, simple structure, small volume, economy, practicability, capability of outputting high-power (up to megawatt) continuous laser and the like although the energy conversion rate (about 1% -2%) of the rocket type combustion driving pneumatic laser is not dominant in the laser, and particularly does not need a large-volume pressure recovery system (such as an ejector) compared with a chemical laser. These outstanding advantages make rocket-type combustion-driven gas-powered lasers readily available as practical intense laser light sources.
Rocket-type combustion driven CO2A gas-dynamic laser, which can be fired by normal hydrocarbonThe fuel is driven by a method of combusting with oxidant (such as oxygen and air), the consumption is low, the fuel can be liquid toluene, benzene and kerosene or gaseous acetylene and methane hydrocarbon fuel, the fuel is selected according to the principle that the fuel contains more carbon and less hydrogen and is flammable and explosive, and the water content in the product is controlled by controlling the fuel proportion. The laser can not only output continuous wave high-power laser and be used for laser propulsion and other purposes requiring continuous high-power laser, but also has a wavelength suitable for damaging a far infrared detector (for laser damage). Thus rocket-like combustion drives CO2The development of gas dynamic lasers has received great attention.
However, existing conventional rocket-type combustion driven CO2The laser has the following defects to be improved:
1. traditional rocket-type combustion driven CO2Lasers convert the chemical energy of a fuel into thermal energy by isobaric combustion (the form of combustion tissue currently employed in almost all power plants), which is ultimately converted into associated radiant energy (the light energy of the laser). However, the isobaric combustion is organized combustion in a deflagration mode, the flame propagation speed is slow, the thermodynamic cycle efficiency is low, so the efficiency of converting heat energy into laser is low, and the energy conversion efficiency of the laser produced by the traditional rocket type combustion is about 1-2% generally. From a combustion thermodynamic cycle perspective, detonation combustion can reach 49% under the same conditions compared to a thermodynamic cycle efficiency where detonation is only about 27%, if used for rocket-type combustion driven CO2The laser can greatly improve the laser conversion efficiency.
2. CO driven by conventional rocket combustion2Since the laser output from the laser is inefficient, the amount of fuel required for generating a laser of a set output is large, and the energy efficiency ratio is low. And because the light-emitting rate is low and the special design is not carried out, the large equipment volume ensures that the equipment is only used for ground light-emitting experiments.
3. Conventional rocket-type combustion driven CO2The laser is in a continuous light-emitting working mode, and the system complexity is required to be additionally increased on outputting pulse laser.
Disclosure of Invention
The technical problem to be solved by the invention is to provide a pulse detonation rocket combustion driven premixed carbon dioxide pneumatic laser aiming at the defects of the prior art, wherein the pulse detonation rocket combustion driven premixed carbon dioxide pneumatic laser adopts a pulse detonation rocket combustion device as a pumping source, and fully utilizes the advantages of high detonation combustion heat release rate and high thermodynamic cycle efficiency, so that high-temperature and high-pressure gas is used as the pumping source to produce high-efficiency laser and save energy. When the pulse detonation engine is used as power on a rocket or a rocket-assisted aircraft, the multiple purposes of the core engine can be realized through reasonable design, namely the same pulse detonation rocket combustion device is adopted, the laser can be produced, the thrust can be produced, the process can be realized on the same set of exhaust device, and the process can also be realized by connecting different exhaust devices. When the laser is used on the ground, the laser can be used for generating high-power pulse laser. Because the pulse detonation device knocks at a tunable frequency (typically within 200 Hz), it is well suited for some applications where a pulsed laser is required.
In order to solve the technical problems, the invention adopts the technical scheme that:
a premixed carbon dioxide pneumatic laser driven by pulse detonation rocket combustion comprises a pulse detonation rocket combustion device, a transition section and CO2A pneumatic laser generating device and an exhaust section.
The pulse detonation rocket combustion device comprises a cylindrical shell, an oxidant injection panel, a fuel injection panel and a turbulence spiral.
The cylindrical inner cavity of the cylindrical shell forms a pulse detonation combustion chamber.
The oxidant injection panel is provided with a plurality of oxidant injection channels along the circumferential direction.
The front end of the cylindrical shell is provided with a fuel injection channel corresponding to oxidant injection along the circumferential direction.
Each oxidant injection channel and each fuel injection channel are switched on and off through an electromagnetic valve.
The turbulent flow spiral is coaxially arranged in the pulse detonation combustion chamber.
CO2The pneumatic laser generating device is connected with the pulse detonation rocket combustion device through a transition section. CO 22The pneumatic laser generating device comprises a rectangular shell, an array spray pipe and an optical cavity which are arranged in the rectangular shell, and a laser outlet is arranged on the rectangular shell corresponding to the optical cavity.
An ignition device is also provided on the cylindrical housing downstream of the fuel injection passage, which ignition device enables pulse ignition.
When all the electromagnetic valves are opened, the oxidant sprayed from the oxidant spraying channel and the fuel sprayed from the fuel spraying channel collide and are uniformly mixed in the pulse detonation combustion chamber. And starting the ignition device, igniting the uniformly mixed oxidant and fuel, and generating pulse detonation combustion in the pulse detonation combustion chamber under the action of the turbulent flow helix. Combustion gas is passed through CO2The pneumatic laser generating device generates pulse laser.
The inner diameter D of the cylindrical shell and the length L of the cylindrical shell need to satisfy that L/D is more than or equal to 20.
The turbulent flow spiral length is between 2D and 10D, and the screw pitch is between 1/2D and 1D.
The plugging ratio of the turbulator helix is 30% to 50%, preferably about 38%.
A shell cooling channel is arranged in the cylindrical shell.
The oxidant is oxygen or air.
The transition section is of a circular torque structure.
The exhaust section is arranged at CO2The tail end of the pneumatic laser generating device is configured according to the working mode of the laser, and is in a reducing configuration only for the purpose of generating laser. When used for both lasing and thrust generation, assume a zoom configuration.
The ignition device is one or two of a spark plug and a hot jet.
The invention has the following beneficial effects:
1. the pulse detonation rocket combustion device is used as a pumping source, chemical energy of fuel is converted into heat energy of fuel gas, the fuel gas is accelerated through the array spray pipe, laser is generated under the action of the optical cavity, the purpose of combustion light generation is achieved, and meanwhile residual fuel is generatedGas is discharged from the tail gas discharge section. Due to the adoption of the pulse detonation combustion technology, the pulse detonation is an implementation form of detonation combustion, and has the characteristics of adjustable pulse working output frequency besides the characteristics of detonation combustion. The working mode is the pulse detonation rocket combustion mode when the oxidizer and the fuel are carried by the fuel. The detonation combustion consumes unburned mixture in a mode of coupling shock wave and combustion wave, the propagation speed can reach thousands of meters per second, and extremely high gas pressure (more than 15-55 atm) and gas temperature (more than 2800K) can be generated. Because the detonation wave transmission speed is very high, the subsequent pulse detonation combustion process can be regarded as an isochoric combustion process, so that the thermodynamic cycle efficiency is very high, the produced laser has high efficiency, and the production efficiency can be almost doubled (the existing rocket type combustion drives CO)2Pneumatic laser level about 1% -2%).
2. Because the efficiency of the produced laser is greatly improved, when the laser with the same output quantity is produced, the required fuel quantity is small, the energy efficiency ratio is high, and compared with the traditional rocket type combustion driving laser, the same fuel can produce more lasers or work for a longer time. When used on the ground, it is a preferred solution to generate high power pulsed laser in a small space (omitting the pressure recovery system).
3. For the aircraft using the rocket type pulse detonation engine as power, because the proportion of the heat energy of detonation combustion products converted into laser is 1.8-3.6% theoretically, most of the heat energy is still converted into gas kinetic energy to be discharged, the same pulse detonation rocket combustion device is adopted, and not only can laser be produced, but also thrust can be produced, so that the energy utilization path of the aircraft is expanded.
4. The aircraft using the rocket type pulse detonation engine as power has the function of generating laser through combustion, and a special laser generation system can be reduced; the laser can be provided for the rocket-borne laser equipment at the same time, such as laser ranging, guidance and the like; the defense and attack capabilities of the aircraft can be increased, such as emitting high-power intense pulse laser to damage (intercept) an incoming target or attack an enemy space target.
Drawings
Fig. 1 shows a schematic structural diagram of a premixed carbon dioxide gas dynamic laser driven by pulse detonation rocket combustion according to the present invention.
FIG. 2 shows an enlarged schematic view of an array nozzle.
Among them are: the fuel injection device comprises a fuel injection channel 1, an oxidant injection panel 2, an oxidant injection channel 3, a panel end cover 4, a shell cooling liquid inlet 5, a spark plug 6, a shell cooling channel 7, a cylindrical shell 8, a turbulent flow spiral 9, a pulse detonation combustor 10, a shell cooling liquid outlet 11, a transition section shell 12, an array spray pipe 13, an optical cavity 14, a laser outlet 15, an exhaust section shell 16 and a material supplementing hole 17.
In addition, in fig. 1: i represents a pulse detonation rocket combustion device; II represents a transition section; III denotes CO2A pneumatic laser generating device; and IV represents an exhaust section.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and specific preferred embodiments.
In the description of the present invention, it is to be understood that the terms "left side", "right side", "upper part", "lower part", etc., indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of describing the present invention and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and that "first", "second", etc., do not represent an important degree of the component parts, and thus are not to be construed as limiting the present invention. The specific dimensions used in the present example are only for illustrating the technical solution and do not limit the scope of protection of the present invention.
As shown in figure 1, the premixed carbon dioxide pneumatic laser driven by the pulse detonation rocket combustion comprises a pulse detonation rocket combustion device I, a transition section II and CO which are coaxially arranged from left to right in sequence2A pneumatic laser generating device III and an exhaust section IV.
The pulse detonation rocket combustion device comprises a cylindrical shell 8, an oxidant injection panel 2 and a turbulent helix 9.
The cylindrical interior of the cylindrical housing forms a pulse detonation combustion chamber 10. In order to shorten the detonation distance of the pulse detonation wave and shorten the length of the pulse detonation combustion chamber as much as possible, the inner diameter D of the cylindrical shell and the length L of the cylindrical shell need to satisfy that L/D is more than or equal to 20.
The outer side of the oxidant injection panel is preferably provided with an injection panel cover 4 which connects the circumferential edge of the oxidant injection panel with the front end of the cylindrical casing.
The oxidant injection panel is provided with a plurality of oxidant injection channels 3 along the circumferential direction. Each oxidant injection channel is preferably horizontal, with an inlet end extending out of the injection panel and connected to an oxidant supply system and an outlet end communicating with the pulse detonation combustor. The oxidizing agent is oxygen, air, or the like, and preferably oxygen with a trace amount of nitrogen added thereto.
The front end of the cylindrical shell is provided with a fuel injection channel 1 which is equal to the oxidant injection channel in terms of mathematical theory along the circumferential direction. Each fuel injection channel is preferably vertical, with an inlet end connected to a fuel supply system and an outlet end communicating with the pulse detonation combustor. The provided fuel can be liquid toluene, benzene, kerosene, or gaseous acetylene, methane hydrocarbon fuel, the fuel selection principle is that the fuel contains more carbon and less hydrogen, and is flammable and explosive, the water content in the product is controlled by controlling the fuel proportion, the requirement is generally less than 1% of the total mass, and the fuel is easy to obtain.
The outlet of each oxidant injection channel and the outlet of each fuel injection channel are branches with the main path at the terminal, and the front ends of the oxidant injection channels and the fuel injection channels are provided with electromagnetic valves on the respective main paths of the oxidant and the fuel. The supply of the propellant to the pulse detonation combustion chamber is controlled by controlling the on-off of the solenoid valve. The electromagnetic valve is set with a certain on-off frequency, so that propellant pulse supply to the detonation combustion chamber is realized, the pulse detonation frequency is controlled, and finally pulse light emitting is realized.
A housing cooling channel 7 is provided in the cylindrical housing for the purpose of cooling the pulse detonation rocket combustion device. Preferably, a casing coolant inlet 5 is provided on the upper left side of the cylindrical casing, and a casing coolant outlet 11 is provided on the lower right side of the cylindrical casing.
An ignition device is also provided on the cylindrical housing downstream of the fuel injection passage, which ignition device enables pulse ignition. The ignition device is preferably one or both of a spark plug and a hot jet. The spark plug 6 is preferred in the present invention, i.e., a high energy detonation is used to ignite the propellant entering the pulse detonation combustion chamber 10 to form pulse detonation combustion.
The turbulent spiral is coaxially arranged in the pulse detonation combustion chamber, is actually similar to a thin spring wire, and has the function of increasing the turbulence and shortening the conversion distance from detonation to detonation. The turbulent flow spiral length is between (2-10) D, the spiral pitch is between (1/2-1) D, the blocking ratio is between 30% and 50% (tests show that the blockage ratio is better around 38%), and the spiral turn number can be roughly determined according to the spiral length and the spiral pitch. The blockage ratio refers to the proportion of the turbulent flow spiral in the inner cavity of the cylindrical shell.
CO2The pneumatic laser generating device is connected with the pulse detonation rocket combustion device through a transition section; namely, a cylindrical shell and a rectangular shell for connecting a pulse detonation rocket combustion device, and the transition section shell 12 is of a circular torque structure.
CO2The pneumatic laser generating device comprises a rectangular shell, an array spray pipe 13 and an optical cavity 14, wherein the array spray pipe 13 and the optical cavity 14 are arranged in the rectangular shell, and a laser outlet 15 is arranged on the rectangular shell corresponding to the optical cavity.
The array nozzle and the optical cavity are mature prior art, the structure of the array nozzle is shown in figure 2, and gas is accelerated to supersonic speed through the gap of the array nozzle. The feeding hole 17 arranged at the upper end of the array nozzle is used for supplementing insufficient components (such as CO)2、N2Etc.). The optical cavity has a specific geometry that enables the active medium to form an optical resonance that outputs coherent radiation, which is output as laser light from the laser exit. The optical cavity is preferably flanged to the exhaust section housing 16 in the exhaust section.
Transition section for connecting a cylindrical housing and a CO in a pulse detonation combustion device2The transition section shell 12 of the rectangular shell in the pneumatic laser generating device is of a circular torque structure, so that rectification is facilitated. The transition section casing including an upstreamThe longitudinal sectional area of the downstream rectangular section does not exceed the circular sectional area of the tail part of the pulse detonation rocket combustion device, and the theoretical areas of the downstream rectangular section and the circular sectional area are equal and are better.
The exhaust section is arranged at CO2The tail end of the pneumatic laser generating device and the exhaust section shell 16 can be provided with different configurations according to the use function, and the tail end and the exhaust section shell can be in a reducing configuration only for the purpose of generating laser and can be in a contracting and expanding configuration when being used for generating laser and generating thrust simultaneously.
When all the electromagnetic valves are opened, the oxidant sprayed from the oxidant spraying channel and the fuel sprayed from the fuel spraying channel collide and are uniformly mixed in the pulse detonation combustion chamber; starting an ignition device, igniting the uniformly mixed oxidant and fuel, and generating pulse detonation combustion in the pulse detonation combustion chamber under the action of the turbulent flow helix; combustion gas is passed through CO2The pneumatic laser generating device generates pulse laser.
Referring to fig. 1, in the premixed carbon dioxide gas-driven laser driven by pulse detonation rocket combustion according to the present invention, a pulse detonation combustion apparatus knocks high-temperature and high-pressure gas (whose main component is CO) generated by combustion2、N2And H2O) is CO2Working medium of the gas dynamic laser. Due to N2The vibration relaxation time of the molecule is very long, so that the main function of the molecule is to store vibration energy; n is a radical of2Vibrational energy level of molecule and CO2The high vibration energy level of the molecule is subjected to vibration coupling; and CO2The number of particles of low vibration level of the molecule is determined by the catalyst H2The deactivation of O is maintained at an equilibrium concentration near the translation temperature.
When the high-temperature mixed gas is rapidly expanded and accelerated through the array nozzle 13, the heat energy of the gas is rapidly changed into the kinetic energy of the gas, and the molecular translation temperature is rapidly reduced. CO 22The number of the molecular particles with the medium and low energy levels is also sharply reduced due to the rapid relaxation. High-level populations relax slowly and are "frozen" to maintain a high population density. This difference in relaxation rates is referred to as differential relaxation. Differential relaxation leads to CO2The number density of the high-energy-level particles exceeds that of the low-energy-level particlesNumber density, which creates the necessary condition for generating stimulated radiation, i.e., the condition for population inversion. A medium satisfying such a condition is called an activation medium. Due to CO2High energy level molecule and N2Resonance coupling of molecular vibration energy, and continuous supplement of high-energy-level particle number; due to CO2Low energy level molecule and catalyst H2The resonance coupling of O molecules and the continuous evacuation of low-level particles represent the continuous stimulated radiation. The active medium is then optically resonated by the optical cavity 14 to obtain amplification and coherent radiation output, and the laser light is finally output from the laser exit 15.
As the combustion process in the pulse detonation combustor 10 is changed from ordinary isobaric combustion to approximate isovolumetric combustion, the energy release rate and the thermodynamic cycle efficiency are obviously improved, and CO can be used2The pneumatic laser generating device provides stronger high-temperature high-pressure gas.
Referring to FIG. 1, the CO of the present invention2The part III of the pneumatic laser generating device also comprises a transition section 12 which is connected with the pulse detonation combustion device through a flange and is actually a round-square structure which is used for connecting the detonation combustion device and the pneumatic laser and leading high-temperature and high-pressure gas to the array nozzle 13. After passing through the array spray pipe, gas is expanded and accelerated to form supersonic low-pressure airflow which is inconvenient to discharge, the exhaust section 16 has the function of enabling the device to exhaust smoothly so as to work continuously, and the device is in a reduction configuration when only laser is generated, partial kinetic energy of the supersonic airflow is recovered to pressure potential energy, and the pressure is recovered to be close to the atmospheric pressure, so that the discharge is facilitated; the laser generator is in a zooming configuration when generating laser and thrust, so that the kinetic energy discharged by gas is continuously utilized while the conversion from heat energy to light energy is realized.
Although the preferred embodiments of the present invention have been described in detail, the present invention is not limited to the details of the embodiments, and various equivalent modifications can be made within the technical spirit of the present invention, and the scope of the present invention is also within the scope of the present invention.
Claims (4)
1. Pulse detonation rocketCombustion-driven mixes formula carbon dioxide pneumatic laser in advance, its characterized in that: comprises a pulse detonation rocket combustion device, a transition section and CO2The device comprises a pneumatic laser generating device and an exhaust section;
the pulse detonation rocket combustion device comprises a cylindrical shell, an oxidant injection panel, a fuel injection panel and a turbulent flow spiral;
the cylindrical inner cavity of the cylindrical shell forms a pulse detonation combustion chamber;
the oxidant injection panel is provided with a plurality of oxidant injection channels along the circumferential direction;
a fuel injection channel corresponding to oxidant injection is arranged at the front end of the cylindrical shell along the circumferential direction;
the fuel provided by the fuel injection channel is liquid toluene, benzene and kerosene or gaseous acetylene and methane hydrocarbon fuel, the fuel selection principle is that the fuel contains more carbon and less hydrogen and is inflammable and explosive, and the water content in the product is controlled to be less than 1% of the total mass by controlling the fuel proportion;
each oxidant injection channel and each fuel injection channel are switched on and off through an electromagnetic valve;
the turbulent flow spiral is coaxially arranged in the pulse detonation combustion chamber;
CO2the pneumatic laser generating device is connected with the pulse detonation rocket combustion device through a transition section; CO 22The pneumatic laser generating device comprises a rectangular shell, an array spray pipe and an optical cavity which are arranged in the rectangular shell, and a laser outlet is arranged on the rectangular shell corresponding to the optical cavity;
the cylindrical shell positioned at the downstream of the fuel injection channel is also provided with an ignition device which can realize pulse ignition;
when all the electromagnetic valves are opened, the oxidant sprayed from the oxidant spraying channel and the fuel sprayed from the fuel spraying channel collide and are uniformly mixed in the pulse detonation combustion chamber; starting an ignition device, igniting the uniformly mixed oxidant and fuel, and generating pulse detonation combustion in the pulse detonation combustion chamber under the action of the turbulent flow helix; combustion gas is passed through CO2Generating pulse laser after the pneumatic laser generating device; the pulse-detonation device detonatingThe frequency can be adjusted within 200 Hz;
the inner diameter D of the cylindrical shell and the length L of the cylindrical shell need to satisfy that L/D is more than or equal to 20; the length of the turbulent flow spiral is between 2D and 10D, and the pitch of the turbulent flow spiral is between 1/2D and 1D; the blockage ratio is 30-50%;
the transition section is of a round torque structure;
the exhaust section is arranged at CO2The tail end of the pneumatic laser generating device is configured according to the working mode of the laser, and is in a reducing configuration only when used for generating laser; when used for both lasing and thrust generation, assume a zoom configuration.
2. The pulse detonation rocket combustion driven premixed carbon dioxide pneumatic laser according to claim 1, characterized in that: a shell cooling channel is arranged in the cylindrical shell.
3. The pulse detonation rocket combustion driven premixed carbon dioxide pneumatic laser according to claim 1, characterized in that: the oxidant is oxygen or air.
4. The pulse detonation rocket combustion driven premixed carbon dioxide pneumatic laser according to claim 1, characterized in that: the ignition device is one or two of a spark plug and a hot jet.
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