CN113944567B - Design method and device for converting flame acceleration and deflagration into detonation - Google Patents

Abstract

The application relates to a design method and a device for converting flame acceleration and deflagration into detonation. The method comprises the following steps: providing a dynamically adjustable combined flow and solids barrier within the combustion chamber; the front end of the combustion chamber is provided with a monitoring device which is used for detecting the pressure and the speed of an incoming flow and sending a detection value to a fluid and solid combined barrier regulating and controlling device; designing a fluid and solid combined barrier regulating device, wherein the device is used for determining the flight Mach number of a mixture according to the pressure and the speed of a received incoming flow, and dynamically adjusting the lifting height of a solid barrier and the jet pressure and the jet time of a fluid barrier according to the flight height, the pressure and the flight Mach number of the incoming flow, so that the fluid and the solid barrier work in different working modes, and the rapid detonation under different flight Mach numbers is realized. The method can accelerate the flame of the pulse detonation engine and shorten the detonation distance and time under the condition of wide-speed-range flight, and can also reduce the pressure loss and excessive local hot spots under the condition of high-Mach flight by selecting different flame acceleration modes.

Description

Design method and device for flame acceleration and deflagration-to-detonation

technical field

The present application relates to the technical field of detonation engines, in particular to a design method and device for flame acceleration and deflagration-to-detonation.

Background technique

Hypersonic vehicles are currently a hot spot of competition among major powers, and the biggest technical bottleneck restricting near-space vehicles is how to develop an efficient, economical, and safe aerospace propulsion system. Detonation combustion is more efficient in combustion with less entropy increase. The propulsion system based on detonation combustion has the characteristics of more compact structure, wide flight speed range (0-20Ma), and high combustion efficiency. It is an ideal choice for future aerospace vehicle power propulsion. The air-breathing pulse detonation has more advantages in the wide speed range. How to obtain a high-frequency short-distance detonation technology is still the bottleneck restricting the pulse detonation engine. Triggering detonation by this method remains a challenge since direct detonation in a closed tube usually requires the accumulation of a large amount of energy in the mixture in a short period of time, usually several orders of magnitude higher than the energy required to ignite the mixture. Therefore, the initiation of detonation combustion is usually produced by a flame acceleration mechanism from a lower energy ignition and by a deflagration-to-detonation transition (DDT). However, the distance and time required for the DDT process of current pulse detonation engines are still large, especially for the realization of higher frequency pulse detonation engines (PDEs).

Due to the high thermal cycle efficiency of the detonation engine, the detonation combustion is used to achieve high thrust performance. However, since the working process of the pulse engine is a periodic multi-physics process such as intake, mixing, ignition, detonation, deflagration to detonation, exhaust, blowing out, and filling inert gas, the operating frequency of the engine is low, which greatly affects the engine. work efficiency and propulsion performance. At the same time, the current engine operating frequency is difficult to further increase, and the detonation distance of DDT is still more than 500mm. Therefore, how to achieve rapid detonation and obtain a shorter detonation distance is the bottleneck of detonation engine application in engineering practice. Traditionally, fixed solid obstacles, spiral tubes, etc. are used to shorten the detonation distance and time, but this will cause the engine to fly at high Mach, and cause thrust loss during long-term operation, and too many local hot spots. Therefore, it is imminent how to find a fast flame acceleration method so that the detonation engine can realize the flame propagation mode of deflagration to detonation in a shorter time and a shorter distance under different flight Mach numbers.

Contents of the invention

Based on this, it is necessary to provide a design method and device for flame acceleration and deflagration-to-detonation for the above technical problems.

A design method for flame acceleration and deflagration to detonation, said method comprising:

A dynamically adjustable fluid and solid combination obstacle is set in the combustion chamber; the fluid and solid combination obstacle includes a solid obstacle and a fluid obstacle, the lifting height of the solid obstacle is adjustable, and the jet flow of the fluid obstacle Both pressure and jet time are adjustable.

A monitoring device is arranged at the front end of the combustion chamber, and the monitoring device is used to detect the pressure and velocity of the incoming flow, and send the detected value to the combined fluid and solid obstacle control device.

Design the fluid and solid combined obstacle control device, the fluid and solid combined obstacle control device is used to determine the flight Mach number of the mixture according to the pressure and velocity of the incoming flow sent by the monitoring device received, and according to the flight height, incoming flow Pressure and flight Mach number, dynamically adjust the lifting height of solid obstacles and the jet pressure and jet time of fluid obstacles, so that fluid and solid obstacles work in different working modes, and realize rapid detonation at different flight Mach numbers.

In one of the embodiments, the number of the fluid and solid combination obstacles is multiple; the fluid obstacles are composed of nozzle holes and jets; the nozzle holes are located inside the solid obstacles; multiple fluid and solid combinations Obstacles are installed in the combustion chamber according to a preset array, and are used to rapidly accelerate the flame to achieve high-frequency short-distance detonation.

In one embodiment, the combined fluid and solid obstacle is a combined fluid and solid obstacle acceleration device formed by replacing a solid obstacle with a jet flow obstacle.

In one of the embodiments, the fluid and solid combined obstacles include a plurality of solid obstacles and a plurality of jet obstacles, and are installed in the combustion chamber according to preset rules, and the fluid formed by crossing jets and colliding jets, etc. Combined with solid obstacle acceleration devices.

In one embodiment, the different working modes include: working mode with only fixed obstacles, working mode with combined fluid and solid obstacles, and working mode with only fluid obstacles.

Design the fluid and solid combined obstacle control device, the fluid and solid combined obstacle control device is used to determine the Mach number of the incoming flow according to the pressure and velocity of the incoming flow sent by the monitoring device received, and according to the flight height, incoming flow Pressure and flight Mach number, dynamically adjust the lifting height of solid obstacles and the jet pressure and jet time of fluid obstacles, so that fluid and solid obstacles work in different working modes, and realize rapid detonation under different flight Mach numbers, including :

When 0<Ma<0.4, the fluid and solid combined obstacle is regulated by the fluid and solid combined obstacle control device to make it work in the fixed obstacle working mode, and a higher blocking ratio is selected to achieve rapid detonation; where Ma is the flight Mach number.

When 0.4<Ma<1.0, the fluid and solid combined obstacle is regulated by the fluid and solid combined obstacle control device to make it work in the fluid and solid combined obstacle working mode, and the solid obstacle is adjusted to reduce the blocking ratio. The nozzle hole realizes the injection of the horizontal jet flow obstacle and realizes rapid detonation.

When Ma>1.0, the fluid and solid combination obstacle is regulated by the fluid and solid combination obstacle control device to make it work in only the fluid obstacle working mode, and the best flame acceleration is achieved by controlling the jet pressure and jet delay time performance, to achieve rapid detonation.

In one of the embodiments, the raising or lowering of the solid obstacle is achieved by an electric control device.

A flame acceleration and deflagration-to-detonation device includes: a dynamically adjustable fluid and solid combined obstacle, a monitoring device, and a fluid and solid combined obstacle regulating device.

The combined fluid and solid obstacles are installed in the combustion chamber according to preset rules; the combined fluid and solid obstacles include solid obstacles and fluid obstacles, the lifting height of the solid obstacles is adjustable, and the fluid obstacles Both jet pressure and jet time can be adjusted.

The monitoring device is arranged at the front end of the combustion chamber to detect the pressure and velocity of the incoming flow, and transmit the detected value to the combined fluid and solid obstacle control device.

The combined fluid and solid obstacle control device is used to determine the flight Mach number of the mixture according to the pressure and velocity of the incoming flow sent by the monitoring device, and dynamically adjust the solid obstacle according to the flight height, the pressure of the incoming flow, and the flight Mach number The lifting height of the object and the jet pressure and jet time of the fluid obstacle make the fluid and solid obstacles work in different working modes, and realize rapid detonation at different flight Mach numbers.

In one of the embodiments, the number of the fluid and solid combination obstacles is multiple, and the fluid obstacles are composed of nozzle holes and jets; the nozzle holes are located inside the solid obstacles; multiple fluid and solid combinations Obstacles are installed in the combustion chamber in a predetermined array.

In one embodiment, the combined fluid and solid obstacle is a combined fluid and solid obstacle acceleration device formed by replacing a solid obstacle with a jet flow obstacle.

In one of the embodiments, the combined fluid and solid obstacles include multiple solid obstacles and multiple jet flow obstacles, and are installed in the combustion chamber according to preset rules.

The above-mentioned design method and device for flame acceleration and deflagration-to-detonation, in which a dynamically adjustable fluid and solid combination obstacle is set in the combustion chamber; a monitoring device is set at the front end of the combustion chamber, and the monitoring device is used to detect the incoming flow Pressure and velocity, and send the detection value to the fluid and solid combined obstacle control device; design the fluid and solid combined obstacle control device, which is used to determine the flight of the mixture according to the incoming pressure and velocity sent by the monitoring device Mach number, and according to the flight height, incoming flow pressure and flight Mach number, dynamically adjust the lifting height of solid obstacles and the jet pressure and jet time of fluid obstacles, so that fluid and solid obstacles work in different working modes, realizing Rapid detonation at different flight Mach numbers. This method can not only realize the flame acceleration of the pulse detonation engine under the condition of wide-speed flight, shorten the detonation distance and time of deflagration to detonation, but also reduce the flame acceleration in high Mach flight conditions by selecting different flame acceleration modes. Under pressure loss and excessive localized hotspot generation.

Description of drawings

Fig. 1 is the schematic flow chart of the design method of flame acceleration and deflagration to detonation in an embodiment;

Fig. 2 is a schematic diagram of a design method for a dynamic liftable fluid-solid combined flame acceleration in a wide-velocity domain pulse detonation in another embodiment;

Fig. 3 is a schematic diagram of a fluid and solid combined obstacle flame acceleration device in another embodiment;

Fig. 4 is a schematic diagram of another fluid and solid combined obstacle flame acceleration device in another embodiment;

Fig. 5 is the working mode of the fluid and solid combined obstacle flame acceleration device in an embodiment under different flight Machs, wherein (a) is only the fixed obstacle working mode, (b) is the fluid and solid combined obstacle working mode mode, (c) is only the fluid obstacle working mode;

Fig. 6 is the flame propagation process and flame propagation speed under two calculation examples in another embodiment, wherein (a) is the change process of the flame surface position; (b) is the flame propagation speed.

Detailed ways

In order to make the purpose, technical solution and advantages of the present application clearer, the present application will be further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the present application, and are not intended to limit the present application.

In one embodiment, as shown in Figure 1, a design method for flame acceleration and deflagration-to-detonation is provided, the method comprising the following steps:

Step 100: Setting dynamically adjustable fluid and solid combination obstacles in the combustion chamber.

The combination of fluid and solid obstacles includes solid obstacles and fluid obstacles, the lifting height of the solid obstacles is adjustable, and the jet pressure and jet time of the fluid obstacles are both adjustable.

The combination of fluid and solid obstacles, on the one hand, promotes the transformation from deflagration to detonation, and on the other hand, through the dynamic adjustment of the blockage ratio of fluid obstacles, it can reduce the starting distance and time of deflagration to detonation, and realize the transition from deflagration to detonation. Dynamic stability control, so that it can be stably applied to detonation engines.

In actual flight conditions, due to the difference in flight altitude and flight Mach number, different flame acceleration performances are required. If the solid obstacle is completely fixed in the combustion chamber, at a high Mach number, the combustion chamber will generate a strong shock wave, which will form a strong pressure loss. At low Mach, if the flame is accelerated entirely by fluid obstacles, the flow resistance will be reduced, resulting in longer detonation time and distance. At high Mach numbers, the accelerator mode is replaced by a pure fluid obstacle mode, which can prevent local hot spots caused by solid obstacles under supersonic flight conditions. Therefore, the fluid and solid combined obstacle is designed so that the blocking ratio of the solid obstacle can be adjusted up and down, and the jet pressure and jet time of the fluid obstacle can be adjusted.

Step 102: Install a monitoring device at the front end of the combustion chamber, the monitoring device is used to detect the pressure and velocity of the incoming flow, and send the detected value to the combined fluid and solid obstacle control device.

Due to different flight Mach numbers, the pressure and velocity of the combustion front will vary greatly. Therefore, the pressure and velocity monitoring devices at the combustion front can be used to determine the Mach number of the mixture in real time. And through this signal, the fluid and solid combination obstacle is controlled to work in different working modes.

Step 104: Design a combined fluid and solid obstacle control device, the fluid and solid combined obstacle control device is used to determine the flight Mach number of the mixture according to the pressure and velocity of the incoming flow sent by the monitoring device, and according to the flight height, incoming flow The pressure and flight Mach number, dynamically adjust the lifting height of solid obstacles and the jet pressure and jet time of fluid obstacles, so that the fluid and solid obstacles work in different working modes, and realize rapid detonation under different flight Mach numbers.

Specifically, the combined fluid and solid obstacle control device can determine the flight Mach number of the mixture according to the pressure and velocity of the received incoming flow, and dynamically adjust the solid obstacle blocking ratio, Jet opening time, jet pressure, jet delay time, jet position and other parameters are used to meet the fast flame acceleration and fast deflagration-to-detonation methods at different flight altitudes and flight Mach numbers. Therefore, the high-efficiency operation of the pulse detonation engine can be realized under the flight condition of wide speed range (Ma=0-4).

Different working modes include: only fixed obstacle working mode, combined fluid and solid obstacle working mode, and only fluid obstacle working mode.

The combination of fluid and solid obstacles proposed by the present invention can achieve flame acceleration and fast deflagration-to-detonation, and the schematic diagram of the design method for the combination of fluid and solid flame acceleration in a wide speed range pulse detonation dynamic lift is shown in Figure 2.

In the above-mentioned design method of flame acceleration and deflagration to detonation, a dynamically adjustable fluid and solid combination obstacle is set in the combustion chamber; a monitoring device is set at the front end of the combustion chamber, and the monitoring device is used to detect the pressure of the incoming flow and speed, and send the detected value to the fluid and solid combined obstacle control device; design the fluid and solid combined obstacle control device, which is used to determine the flight Mach of the mixture according to the incoming pressure and velocity sent by the monitoring device According to the flight height, incoming flow pressure and flight Mach number, dynamically adjust the lifting height of the solid obstacle and the jet pressure and jet time of the fluid obstacle, so that the fluid and solid obstacles work in different working modes, and realize the Rapid detonation at different flight Mach numbers. This method can not only realize the flame acceleration of the pulse detonation engine under the condition of wide-speed flight, shorten the detonation distance and time of deflagration to detonation, but also reduce the flame acceleration in high Mach flight conditions by selecting different flame acceleration modes. Under pressure loss and excessive localized hotspot generation. The current pulse detonation engine based on detonation combustion with a wide speed range is a new concept engine, and the present invention based on this focuses on the flame acceleration and detonation technology of a wide range of adjustable dynamic fluid and solid combined obstacles.

In one of the embodiments, the number of combined fluid and solid obstacles is multiple; the fluid is composed of nozzle holes and jets; the nozzle holes are located inside the solid obstacles; multiple fluid and solid combined obstacles are installed in the combustion chamber according to a preset array In the chamber, it is used to rapidly accelerate the flame to achieve high-frequency short-distance detonation.

The fluid and solid combined obstacle is a fluid and solid combined obstacle flame acceleration device that can be raised and lowered dynamically. The fluid obstacle is composed of a nozzle hole and a jet, and the nozzle hole is located inside the solid obstacle. By installing multiple fluid and solid combined obstacles in the detonation combustion chamber, the rapid acceleration effect on the flame can be achieved, so as to realize the high-frequency short-distance detonation technology.

In one of the embodiments, the fluid and solid combined obstacle is a fluid and solid combined obstacle acceleration device formed by replacing a solid obstacle with a jet flow obstacle. The structure diagram of the combined fluid and solid obstacle acceleration device is shown in FIG. 3 .

In one of the embodiments, the fluid and solid combined obstacles include a plurality of solid obstacles and a plurality of jet obstacles, and are installed in the combustion chamber according to preset rules, and the fluid and solid formed by intersecting jets and colliding jets, etc. Combined obstacle acceleration device. The structure diagram of the combined fluid and solid obstacle acceleration device is shown in FIG. 4 .

In one of the embodiments, the different working modes include: only fixed obstacle working mode, fluid and solid combined obstacle working mode and only fluid obstacle working mode; design fluid and solid combined obstacle control device, fluid Combined with the solid obstacle control device, it is used to determine the flight Mach number of the mixture according to the pressure and velocity of the incoming flow sent by the monitoring device, and dynamically adjust the elevation of the solid obstacle according to the flight height, incoming flow pressure and flight Mach number The height and jet pressure and jet time of fluid obstacles make fluid and solid obstacles work in different working modes, and realize rapid detonation at different flight Mach numbers, including: when 0<Ma<0.4, through fluid and solid The combined obstacle control device regulates the combination of fluid and solid obstacles to make it work in the mode of only fixed obstacles, and selects a higher blocking ratio to achieve rapid detonation; where Ma represents the flight Mach number; when 0.4<Ma< When 1.0, the fluid and solid combined obstacle is regulated by the fluid and solid combined obstacle control device to make it work in the fluid and solid combined obstacle working mode, the solid obstacle is adjusted to reduce the blocking ratio, and the lateral obstacle is realized through the nozzle hole. The ejection of objects can realize rapid detonation; when Ma>1.0, the fluid and solid combination obstacle can be regulated by the fluid and solid combination obstacle control device to make it work in only the fluid obstacle working mode, by controlling the jet pressure and the jet flow Delay time for optimum flame acceleration performance for fast detonation.

Specifically, the dynamic fluid and jet combination obstacle control device: according to different flight Mach numbers and working conditions, three different working modes are designed. Three different working modes are shown in Figure 5, where (a) is the working mode with only fixed obstacles, (b) is the working mode with combined fluid and solid obstacles, and (c) is the working mode with only fluid obstacles. state.

1) Only the working mode of fixed obstacles, 0<Ma<0.4, because the Mach number of the aircraft is low at this time, the mixture directly entering the combustion chamber can be compressed relatively low, so in order to quickly realize deflagration to detonation, a strong For flame acceleration performance, at this time, the mode of fluid-solid combined obstacles is selected as only fixed obstacles, and a higher blocking ratio Br=1-((Ly-2h)/Ly)^2 is selected. This enables rapid deflagration to detonation.

2) The working mode of fluid and solid combined obstacle, 0.4<Ma<1.0, at this time, the gas in the combustion chamber is already compressible, but in order to quickly realize the detonation detonation, it can be set as a fluid and solid combined obstacle object mode. Solid obstacles can reduce the blocking rate (realize the rise and fall of solid obstacles through the electric control device), and jet flow obstacles can realize the injection of lateral jet flow obstacles through the nozzle holes.

3) Only in the working mode of fluid obstacles, Ma>1.0, at this time, the mixture in the aircraft enters the supersonic flow mode, and the solid obstacles will cause a high pressure loss, so the solid obstacles in the combustion chamber are eliminated, and the electric device Lower solid obstacles. There are only fluid obstacles in the combustion chamber, and the best flame acceleration performance is achieved by controlling the jet pressure and jet delay time.

Therefore, through the mixture flow state monitoring device, different configuration modes of fluid and solid obstacles are adjusted to realize rapid detonation at different flight Mach numbers, so that the pulse detonation engine can achieve the best working conditions and performance.

In one of the embodiments, the raising or lowering of the solid obstacle is achieved by an electric control device.

It should be understood that although the various steps in the flow chart of FIG. 1 are displayed sequentially as indicated by the arrows, these steps are not necessarily executed sequentially in the order indicated by the arrows. Unless otherwise specified herein, there is no strict order restriction on the execution of these steps, and these steps can be executed in other orders. Moreover, at least some of the steps in Fig. 1 may include multiple sub-steps or multiple stages, these sub-steps or stages are not necessarily executed at the same time, but may be executed at different times, the execution of these sub-steps or stages The order is not necessarily performed sequentially, but may be performed alternately or alternately with at least a part of other steps or sub-steps or stages of other steps.

In one embodiment, a flame acceleration and deflagration-to-detonation device is provided, which includes: a dynamically adjustable combined fluid and solid obstacle, a monitoring device, and a regulating device for the combined fluid and solid obstacle.

The combination of fluid and solid obstacles is installed in the combustion chamber according to preset rules; the combination of fluid and solid obstacles includes solid obstacles and fluid obstacles, the lifting height of solid obstacles is adjustable, and the jet pressure and jet time of fluid obstacles can be adjusted Tune.

The monitoring device is arranged at the front end of the combustion chamber to detect the pressure and velocity of the incoming flow, and transmit the detected value to the combined fluid and solid obstacle control device.

The combined fluid and solid obstacle control device is used to determine the flight Mach number of the mixture according to the pressure and velocity of the incoming flow sent by the monitoring device, and dynamically adjust the flow rate of the solid obstacle according to the flight height, incoming flow pressure and flight Mach number. The height of the lift and the jet pressure and jet time of the fluid obstacle make the fluid and solid obstacles work in different working modes, and achieve rapid detonation at different flight Mach numbers.

In one of the embodiments, the number of combined fluid and solid obstacles is multiple, and the fluid obstacles are composed of nozzle holes and jets; the nozzle holes are located inside the solid obstacles; multiple fluid and solid combined obstacles are installed according to a preset array in the combustion chamber.

In one of the embodiments, the fluid and solid combined obstacle is a fluid and solid combined obstacle acceleration device formed by replacing a solid obstacle with a jet flow obstacle.

In one of the embodiments, the combined fluid and solid obstacles include multiple solid obstacles and multiple jet flow obstacles, and are installed in the combustion chamber according to preset rules.

In a verification embodiment, the high-precision numerical simulation work is carried out by the Tianhe-2 supercomputer, and it is verified that under the fluid and solid combined obstacles proposed by the present invention, the fluid jet obstacle can also realize the flame acceleration function with the solid obstacle At the same time, the turbulent mixing intensity of the combustion chamber is enhanced, the flame acceleration is promoted, and the time and detonation distance required for the transition from deflagration to detonation are shortened.

Two calculation examples are carried out in the embodiment, calculation example 1 is the case where only obstacles are arranged in the combustion chamber, and calculation example 2 is the case where fluid and solid obstacles are arranged in the combustion chamber. Figure 6 traces the development process of the flame surface and the propagation speed of the flame surface of the two calculation examples. It can be seen from (a) and (b) in Figure 6 that the combined obstacles formed by fluid and solid have obvious advantages in flame acceleration. It can be fast that the flame reaches half of the CJ speed, and the detonation time and distance are also greatly reduced.

Table 1 lists the start time and length of DDT in Cases 1 and 2. When using a single fluid jet and a solid combined obstacle, the onset time of DDT was shortened from t = 1.37514 ms to t = 1.06906 ms, a 22.26% reduction in DDT time. In addition, the required length of the combustion chamber is also shortened from L=505mm to L=336.55mm. The DDT length is shortened by 33.36%, which means that the number of solid obstacles required can be reduced from 10 pairs to 7 pairs.

Initiation time and length of calculation example 1 and calculation example 2 obtained in Table 1

In summary, the present invention uses high-precision numerical simulations to verify that the proposed transverse jet barrier can provide a suitable blocking rate and facilitate flame acceleration. Therefore, the combined obstacle method proposed by the present invention is theoretically feasible and has excellent performance.

The technical features of the above embodiments can be combined arbitrarily. To make the description concise, all possible combinations of the technical features in the above embodiments are not described. However, as long as there is no contradiction in the combination of these technical features, they should be It is considered to be within the range described in this specification.

The above-mentioned embodiments only represent several implementation modes of the present application, and the description thereof is relatively specific and detailed, but it should not be construed as limiting the scope of the patent for the invention. It should be noted that those skilled in the art can make several modifications and improvements without departing from the concept of the present application, and these all belong to the protection scope of the present application. Therefore, the scope of protection of the patent application should be based on the appended claims.

Claims (9)

1. A design method for converting flame acceleration and deflagration into detonation is characterized by comprising the following steps:

providing a dynamically adjustable combined flow and solids barrier within the combustion chamber; the fluid and solid combined barrier comprises a solid barrier and a fluid barrier, the lifting height of the solid barrier is adjustable, and the jet pressure and the jet time of the fluid barrier are adjustable;

the front end of the combustion chamber is provided with a monitoring device, and the monitoring device is used for detecting the pressure and the speed of incoming flow and sending a detection value to a fluid and solid combined barrier regulating and controlling device;

designing a fluid and solid combined barrier regulating and controlling device, wherein the fluid and solid combined barrier regulating and controlling device is used for determining the flight Mach number of a mixture according to the received pressure and speed of incoming flow sent by a monitoring device, and dynamically regulating the lifting height of a solid barrier and the jet pressure and jet time of a fluid barrier according to the flight height, the pressure and the flight Mach number of the incoming flow, so that the fluid and the solid barrier work in different working modes, and quick detonation under different flight Mach numbers is realized;

wherein, different working modes include: a fixed-barrier-only mode of operation, a fluid-and-solid-combination-barrier mode of operation, and a fluid-barrier-only mode of operation;

the method comprises the following steps: designing a fluid and solid combined barrier regulating and controlling device, wherein the fluid and solid combined barrier regulating and controlling device is used for determining the flight Mach number of a mixture according to the received pressure and speed of incoming flow sent by a monitoring device, and dynamically regulating the lifting height of a solid barrier and the jet pressure and jet time of a fluid barrier according to the flight height, the pressure of the incoming flow and the flight Mach number, so that the fluid and the solid barrier work in different working modes, and the rapid detonation under different flight Mach numbers is realized, and the fluid and solid combined barrier regulating and controlling device comprises:

when 0 & num Ma & 0.4, regulating and controlling the fluid and solid combined barriers by the fluid and solid combined barrier regulating and controlling device to work in a fixed barrier working mode only, and selecting higher blocking ratio to realize quick detonation; wherein Ma represents a flight Mach number;

when 0.4-Ma-as-woven fabric is covered with 1.0, regulating and controlling the fluid and solid combined barrier by using the fluid and solid combined barrier regulating and controlling device to enable the fluid and solid combined barrier to work in a fluid and solid combined barrier working mode, regulating the solid barrier to reduce the blocking ratio, and realizing the jet of a transverse barrier through jet holes to realize quick detonation;

when Ma is larger than 1.0, the fluid and solid combined barrier is regulated and controlled by the fluid and solid combined barrier regulating and controlling device to work in a working mode of only the fluid barrier, and the optimal flame acceleration performance is realized by controlling the jet pressure and the jet delay time, so that the rapid detonation is realized.

2. The method of claim 1, wherein the fluid and solid combination barrier number is plural;

the fluid barrier is composed of a jet hole and a jet flow; the spray hole is positioned inside the solid barrier; and the plurality of fluid and solid combined barriers are arranged in the combustion chamber according to a preset array and used for rapidly accelerating flame and realizing high-frequency short-distance detonation.

3. The method of claim 1 wherein the combined fluid and solid barrier is a combined fluid and solid barrier acceleration device formed by replacing one solid barrier with a jet barrier.

4. The method according to claim 1, wherein the combined fluid and solid obstacle comprises a plurality of solid obstacles and a plurality of jet obstacles, and is installed in the combustion chamber according to a predetermined rule, and the combined fluid and solid obstacle accelerating means is formed by cross jet and colliding jet, etc.

5. The method of claim 1, wherein the raising or lowering of the solid barrier is accomplished by an electrically controlled device.

6. An apparatus for converting flame acceleration and deflagration to detonation, said apparatus comprising: the system comprises a dynamically adjustable fluid and solid combined barrier, a monitoring device and a fluid and solid combined barrier regulating and controlling device;

the fluid and solid combined barrier is arranged in the combustion chamber according to a preset rule, the fluid and solid combined barrier comprises a solid barrier and a fluid barrier, the lifting height of the solid barrier is adjustable, and the jet pressure and the jet time of the fluid barrier are both adjustable;

the monitoring device is arranged at the front end of the combustion chamber and used for detecting the pressure and the speed of an incoming flow and transmitting a detection value to the fluid and solid combined barrier regulating and controlling device;

the fluid and solid combined barrier regulating and controlling device is used for determining the flight Mach number of a mixture according to the received pressure and speed of incoming flow sent by the monitoring device, and dynamically regulating the lifting height of a solid barrier and the jet pressure and jet time of a fluid barrier according to the flight height, the pressure of the incoming flow and the flight Mach number, so that the fluid and the solid barrier work in different working modes, and quick detonation is realized under different flight Mach numbers;

the fluid and solid combined barrier regulating and controlling device is also used for regulating and controlling the fluid and solid combined barriers through the fluid and solid combined barrier regulating and controlling device when the 0-Ma-0.4 structure works in a fixed barrier working mode only, and a high blocking ratio is selected to realize rapid detonation; wherein Ma represents a flight Mach number; when 0.4-Ma-as-woven fabric is covered with 1.0, regulating and controlling the fluid and solid combined barrier by using the fluid and solid combined barrier regulating and controlling device to enable the fluid and solid combined barrier to work in a fluid and solid combined barrier working mode, regulating the solid barrier to reduce the blocking ratio, and realizing the jet of a transverse barrier through jet holes to realize quick detonation; when Ma is larger than 1.0, the fluid and solid combined barrier is regulated and controlled by the fluid and solid combined barrier regulating and controlling device to work in a working mode of only the fluid barrier, and the optimal flame acceleration performance is realized by controlling the jet pressure and the jet delay time, so that the rapid detonation is realized.

7. The device of claim 6, wherein the number of the fluid and solid combined obstacles is plural, and the fluid and solid combined obstacles are composed of solid obstacles, jet holes and jet flows; the spray hole is positioned inside the solid barrier; a plurality of combined fluid and solid obstacles are mounted in the combustion chamber.

8. The apparatus of claim 6 wherein the combined fluid and solid barrier is an acceleration device formed by replacing a solid barrier with a fluidic barrier.

9. The apparatus of claim 6, wherein the combined fluid and solid obstacles comprise a plurality of solid obstacles and a plurality of jet obstacles, and are installed in the combustion chamber according to a predetermined rule.

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