Air heating device for hypersonic direct connection test

Abstract

The application discloses an air heating device for hypersonic direct connection test, comprising: a combustion chamber, the front end of which is provided with an injection panel, and an igniter is arranged on the injection panel for ignition; a first mixing mechanism arranged at the front end of the combustion chamber for mixing oxygen and air and conveying the mixed oxygen and air into the combustion chamber; and a second mixing mechanism arranged at the front end of the combustion chamber for mixing oxygen and fuel and conveying the mixed oxygen and fuel into the combustion chamber. The structure can make a part of oxygen pre-mixed with fuel by the first mixing mechanism before entering the combustion chamber, thereby facilitating to improve the combustion reaction speed in the combustion chamber and the heating efficiency, and another part of oxygen is pre-mixed with air by the second mixing mechanism before entering the combustion chamber, thereby facilitating to prevent the oxygen concentration around the fuel entering the combustion chamber from being too high, and thereby facilitating to prevent the injection panel at the front end of the combustion chamber from being melted and damaged due to heat concentration.

Description

Technical Field

[0001] This application relates to the field of direct connection testing technology, and in particular to an air heating device for hypersonic direct connection testing. Background Technology

[0002] In recent years, with the rapid development of the aerospace industry, air-breathing propulsion systems for aircraft and spacecraft have become a research hotspot, necessitating related research through direct-drive experiments. One key issue is that the low temperature of the air drawn into air-breathing propulsion systems results in a significant temperature difference between the cold and hot ends, increasing heat loss during fuel combustion and fuel consumption. To reduce heat loss and fuel consumption, air heating devices are needed to heat the drawn-in air. Currently, mainstream air heating devices fall into two categories. The first type has a mixing section at the front of the combustion chamber to mix oxygen and air. The mixed oxygen and air then enter the combustion chamber to assist fuel combustion, producing combustion products that are close to air but at a higher temperature. The second type of air heating device also has a mixing section at the front of the combustion chamber to mix oxygen and fuel. The mixed oxygen and fuel then enter the combustion chamber for combustion, producing combustion products that are close to air but at a higher temperature. In this second type, the oxygen and air are not mixed before entering the combustion chamber.

[0003] The first type of air heating device has the disadvantage that the pre-mixing of oxygen and air before entering the combustion chamber reduces the oxygen concentration, resulting in a slow combustion reaction and thus lower heating efficiency. The second type of air heating device, compared to the first, increases the speed of the combustion reaction and improves heating efficiency. However, the pre-mixing of oxygen and fuel before entering the combustion chamber leads to an excessively high oxygen concentration around the fuel, causing intense, localized combustion within the combustion chamber. This intense combustion not only fails to achieve optimal heating efficiency but also results in uneven combustion and uneven heat transfer. This leads to heat concentration on the injection panel at the front of the combustion chamber, which can melt and damage the injection panel, causing economic losses and safety hazards. Summary of the Invention

[0004] This application aims to at least solve one of the technical problems existing in the prior art. To this end, this application proposes an air heating device for hypersonic direct-drive testing, which enables a portion of the oxygen to be premixed with the fuel before entering the combustion chamber, thereby improving the combustion reaction rate in the combustion chamber and thus increasing the heating efficiency. The other portion of the oxygen is premixed with the air before entering the combustion chamber, which helps to prevent the oxygen concentration around the fuel entering the combustion chamber from being too high, thereby helping to prevent the injection panel at the front end of the combustion chamber from melting and being damaged due to heat concentration.

[0005] An air heating device for hypersonic direct-drive testing according to an embodiment of this application includes:

[0006] A combustion chamber, wherein a spray panel is provided at the front end of the combustion chamber, and an igniter for ignition is installed on the spray panel;

[0007] A first mixing mechanism is disposed at the front end of the combustion chamber. The first mixing mechanism is used to mix oxygen and air and deliver the mixed oxygen and air into the combustion chamber.

[0008] The second mixing mechanism is located at the front end of the combustion chamber and is used to mix oxygen and fuel and deliver the mixed oxygen and fuel into the combustion chamber.

[0009] The air heating device for hypersonic direct-drive testing according to the embodiments of this application has at least the following beneficial effects: When the air heating device for hypersonic direct-drive testing is in operation, it can pre-mix a portion of the oxygen with the fuel through the first mixing mechanism before entering the combustion chamber, thereby improving the combustion reaction speed in the combustion chamber and increasing the heating efficiency. Meanwhile, another portion of the oxygen is pre-mixed with the air through the second mixing mechanism before entering the combustion chamber, which helps to prevent the oxygen concentration around the fuel entering the combustion chamber from being too high, thereby helping to prevent the injection panel at the front end of the combustion chamber from melting or being damaged due to heat concentration.

[0010] According to some embodiments of this application, the first mixing mechanism includes a mixing inner chamber, a mixing outer chamber, a first oxygen intake pipe, an air intake pipe, and a jet pipe. The mixing inner chamber is disposed at the front end of the combustion chamber, and the mixing outer chamber is disposed at the front end of the combustion chamber and covers the mixing inner chamber. A gap exists between the side wall of the mixing outer chamber and the side wall of the mixing inner chamber to form a first confluence cavity. A plurality of first air inlets communicating with the first confluence cavity and the mixing inner chamber are arranged circumferentially at intervals on the side wall of the mixing inner chamber. The first oxygen intake pipe is connected to the side wall of the mixing outer chamber and communicates with the first confluence cavity. The air intake pipe is connected to the side wall of the mixing outer chamber and communicates with the first confluence cavity. One end of the jet pipe is disposed inside the mixing inner chamber, and the other end of the jet pipe passes through the injection panel.

[0011] According to some embodiments of this application, the air intake pipe includes a main intake pipe and a plurality of branch pipes. The plurality of branch pipes are distributed circumferentially at intervals along the main intake pipe. One end of the plurality of branch pipes is connected to the main intake pipe and communicates with the interior of the main intake pipe. The other end of the plurality of branch pipes is connected to the side wall of the mixing outer chamber and communicates with the first confluence chamber. The number of first oxygen intake pipes is plurality, and the plurality of first oxygen intake pipes are distributed circumferentially at intervals along the side wall of the mixing outer chamber.

[0012] According to some embodiments of this application, the second mixing mechanism includes an oxygen chamber, a fuel chamber, a second oxygen inlet pipe, a fuel delivery pipe, and an injector. The oxygen chamber and the fuel chamber are both located at the front end of the combustion chamber, and the oxygen chamber and the fuel chamber share a common sidewall. The second oxygen inlet pipe is connected to the oxygen chamber, and the fuel delivery pipe is connected to the fuel chamber. The output end of the injector passes through the injection panel, and the other end of the injector passes through the common sidewall between the oxygen chamber and the fuel chamber. The portion of the injector located inside the oxygen chamber is provided with a first input end for drawing in oxygen, and the portion of the injector located inside the fuel chamber is provided with a second input end for drawing in fuel.

[0013] According to some embodiments of this application, the oxygen chamber includes an inner oxygen chamber and an outer oxygen chamber. The inner oxygen chamber is disposed at the front end of the combustion chamber, and the outer oxygen chamber is disposed at the front end of the combustion chamber and covers the inner oxygen chamber. A gap exists between the sidewall of the inner oxygen chamber and the sidewall of the outer oxygen chamber to form a second confluence cavity. A plurality of second air inlets communicating with the second confluence cavity and the inner oxygen chamber are circumferentially spaced on the sidewall of the inner oxygen chamber. The number of second oxygen inlet pipes is plurality of, and the plurality of second oxygen inlet pipes are circumferentially spaced along the sidewall of the outer oxygen chamber.

[0014] According to some embodiments of this application, the portion of the injector located on the side of the injection panel facing away from the combustion chamber is provided with an annular step that is in close contact with the injection panel.

[0015] According to some embodiments of this application, a tapered nozzle is provided at the rear end of the combustion chamber.

[0016] According to some embodiments of this application, the igniter includes a spark plug, a spark plug sleeve is provided on the injection panel, and the spark plug is built into the spark plug sleeve.

[0017] According to some embodiments of this application, the spark plug sleeve extends into the region of the first mixing mechanism that mixes oxygen and air, and the spark plug sleeve is provided with a pressure relief hole that connects the interior of the spark plug sleeve with the region of the first mixing mechanism that mixes oxygen and air.

[0018] According to some embodiments of this application, the number of spark plugs is multiple, and the multiple spark plugs are used for alternating ignition.

[0019] Additional aspects and advantages of this application will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of this application. Attached Figure Description

[0020] The above and / or additional aspects and advantages of this application will become apparent and readily understood from the description of the embodiments taken in conjunction with the following drawings, in which:

[0021] Figure 1 This is a schematic diagram of the air heating device used for hypersonic direct connection testing according to an embodiment of this application;

[0022] Figure 2 yes Figure 1 AA section diagram;

[0023] Figure 3 yes Figure 2 A partial schematic diagram of the structure shown.

[0024] Figure label:

[0025] Combustion chamber 100, injection panel 110, tapered nozzle 120, mixing inner chamber 210, first air inlet 211, mixing outer chamber 220, first oxygen intake pipe 230, air intake pipe 240, main intake pipe 241, splitter pipe 242, jet pipe 250, oxygen chamber 310, oxygen inner chamber 311, second air inlet 3111, oxygen outer chamber 312, fuel chamber 320, second oxygen intake pipe 330, fuel delivery pipe 340, injector 350, spark plug sleeve 400. Detailed Implementation

[0026] The embodiments of this application are described in detail below. Examples of these embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain this application, and should not be construed as limiting this application.

[0027] In the description of this application, it should be understood that if directional descriptions are involved, such as up, down, front, back, left, right, etc., indicating the directional or positional relationship based on the directional or positional relationship shown in the accompanying drawings, it is only for the convenience of describing this application and simplifying the description, and does not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this application.

[0028] In the description of this application, if words such as several, greater than, less than, exceeding, above, below, or within appear, "several" means one or more, "more than" means two or more, "greater than," "less than," "exceeding," etc. are understood to exclude the number itself, and "above," "below," "within," etc. are understood to include the number itself.

[0029] In the description of this application, the use of terms such as "first" and "second" is for the purpose of distinguishing technical features only, and should not be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated or the order of the technical features indicated.

[0030] In the description of this application, unless otherwise expressly defined, terms such as "setup," "installation," and "connection" should be interpreted broadly, and those skilled in the art can reasonably determine the specific meaning of the above terms in this application in conjunction with the specific content of the technical solution.

[0031] Reference Figure 1 An air heating device for hypersonic direct-drive testing according to an embodiment of this application includes a combustion chamber 100, a first mixing mechanism, and a second mixing mechanism.

[0032] A spray panel 110 is provided at the front end of the combustion chamber 100, and an igniter for ignition is installed on the spray panel 110. A first mixing mechanism is provided at the front end of the combustion chamber 100, which is used to mix oxygen and air and deliver the mixed oxygen and air into the combustion chamber 100. A second mixing mechanism is provided at the front end of the combustion chamber 100, which is used to mix oxygen and fuel and deliver the mixed oxygen and fuel into the combustion chamber 100. The fuel used is alcohol because alcohol has high combustion efficiency and its combustion products are closer to air, which is closer to the incoming air simulated in the direct connection test.

[0033] When the air heating device used for hypersonic direct connection testing is in operation, it can premix a portion of the oxygen with the fuel through a first mixing mechanism before entering the combustion chamber 100, thereby improving the combustion reaction speed in the combustion chamber 100 and increasing the heating efficiency. Meanwhile, another portion of the oxygen is premixed with the air through a second mixing mechanism before entering the combustion chamber 100, which helps to prevent the oxygen concentration around the fuel entering the combustion chamber 100 from being too high, thereby helping to prevent the injection panel 110 at the front end of the combustion chamber 100 from melting or being damaged due to heat concentration.

[0034] Reference Figures 1 to 3In some embodiments, the first mixing mechanism includes a mixing inner chamber 210, a mixing outer chamber 220, a first oxygen intake pipe 230, an air intake pipe 240, and an injection pipe 250. The mixing inner chamber 210 is disposed at the front end of the combustion chamber 100 and has a cylindrical structure. The mixing outer chamber 220 is disposed at the front end of the combustion chamber 100 and covers the mixing inner chamber 210. A gap exists between the sidewall of the mixing outer chamber 220 and the sidewall of the mixing inner chamber 210 to form a first... The mixing chamber 210 has multiple first air inlets 211 arranged circumferentially on its side wall, which connect the first mixing chamber to the mixing chamber 210. The first oxygen inlet pipe 230 is connected to the side wall of the mixing outer chamber 220 and communicates with the first mixing chamber. The air inlet pipe 240 is connected to the side wall of the mixing outer chamber 220 and communicates with the first mixing chamber. One end of the jet pipe 250 is located inside the mixing inner chamber 210, and the other end of the jet pipe 250 passes through the injection panel 110. During operation, a portion of oxygen enters the first junction cavity through the first oxygen inlet pipe 230, and air enters the first junction cavity through the air inlet pipe 240. The oxygen and air entering the first junction cavity mix within it and simultaneously enter the mixing chamber 210 through the first air inlet holes 211. Multiple first air inlets 211 are spaced circumferentially along the side wall of the mixing chamber 210, ensuring thorough mixing of the oxygen and air flowing into the first junction cavity. Multiple jet pipes 250 are used, with their output ends spaced through the injection panel 110. This allows the pre-mixed oxygen and air to be evenly injected into the combustion chamber 100, which, compared to a single jet pipe 250, helps prevent localized accumulation of the pre-mixed oxygen and air after injection into the combustion chamber 100. It should be noted that in some other embodiments, the first mixing mechanism may also consist of only one mixing chamber; this is not a limitation.

[0035] Reference Figures 1 to 3 In some embodiments, the air intake pipe 240 includes a main intake pipe 241 and a plurality of branch pipes 242. The plurality of branch pipes 242 are distributed circumferentially around the main intake pipe 241. One end of the plurality of branch pipes 242 is connected to the main intake pipe 241 and communicates with the interior of the main intake pipe 241. The other end of the plurality of branch pipes 242 is connected to the side wall of the mixing outer chamber 220 and communicates with the first junction cavity. There are multiple first oxygen intake pipes 230, which are distributed circumferentially around the side wall of the mixing outer chamber 220. During operation, this allows the oxygen and air entering the first junction cavity to be evenly distributed within the first junction cavity, which helps to avoid local accumulation of oxygen and air entering the first junction cavity, thereby facilitating thorough mixing of the oxygen and air entering the first junction cavity.

[0036] Reference Figures 1 to 3In some embodiments, the second mixing mechanism includes an oxygen chamber 310, a fuel chamber 320, a second oxygen inlet pipe 330, a fuel delivery pipe 340, and an injector 350. The oxygen chamber 310 and the fuel chamber 320 are both located at the front end of the combustion chamber 100, and the oxygen chamber 310 and the fuel chamber 320 share a common sidewall. The second oxygen inlet pipe 330 is connected to the oxygen chamber 310, and the fuel delivery pipe 340 is connected to the fuel chamber 320. The output end of the injector 350 is inserted through the injection panel 110, and the other end of the injector 350 is inserted through the common sidewall between the oxygen chamber 310 and the fuel chamber 320. The portion of the injector 350 located in the oxygen chamber 310 is provided with a first input end for drawing in oxygen, and the portion of the injector 350 located in the fuel chamber 320 is provided with a second input end for drawing in fuel. During operation, a portion of the oxygen enters the oxygen chamber 310 through the second oxygen inlet pipe 330, and fuel enters the fuel chamber 320 through the fuel delivery pipe 340. The injector 350 draws in the oxygen from the oxygen chamber 310 and mixes it with the fuel from the fuel chamber 320 before injecting it into the combustion chamber 100. Specifically, the injector 350 is a dual-component injector, and there are multiple injectors 350. The output ends of the multiple injectors 350 are spaced apart on the injection panel 110, so that the pre-mixed oxygen and fuel can be evenly injected into the combustion chamber 100, which helps to avoid local accumulation of the pre-mixed oxygen and fuel after injection into the combustion chamber 100.

[0037] Reference Figures 1 to 3 In some embodiments, the oxygen chamber 310 includes an inner oxygen chamber 311 and an outer oxygen chamber 312. The inner oxygen chamber 311 is located at the front end of the combustion chamber 100 and has a cylindrical structure. The outer oxygen chamber 312 is located at the front end of the combustion chamber 100 and covers the outer side of the inner oxygen chamber 311. There is a gap between the side wall of the inner oxygen chamber 311 and the side wall of the outer oxygen chamber 312 to form a second confluence cavity. A plurality of second air inlets 3111 connecting the second confluence cavity and the inner oxygen chamber 311 are circumferentially spaced on the side wall of the inner oxygen chamber 311. There are multiple second oxygen inlet pipes 330, which are circumferentially spaced along the side wall of the outer oxygen chamber 312.

[0038] It should be noted that in some embodiments, the portion of the injector 350 located on the side of the injection panel 110 facing away from the combustion chamber 100 is provided with an annular step (not shown in the figure) that is close to the injection panel 110. The annular step that is close to the injection panel 110 blocks the connection between the injector 350 and the injection panel 110, which helps to improve the sealing of the connection between the injector 350 and the injection panel 110 and helps to prevent the high-pressure gas generated by combustion in the combustion chamber 100 from escaping through the connection between the injector 350 and the injection panel 110.

[0039] Reference Figure 1 and Figure 2 In some embodiments, a tapered nozzle 120 is provided at the rear end of the combustion chamber 100 to maintain the pressure balance within the combustion chamber 100 and to block the impact force generated by the combustion reaction, thereby reducing the impact on subsequent experimental research.

[0040] Reference Figures 1 to 3 In some embodiments, the igniter includes a spark plug (not shown in the figure), and a spark plug sleeve 400 is provided on the injection panel 110. The spark plug is built into the spark plug sleeve 400, which has a simple structure and is easy to implement.

[0041] Reference Figure 2 and Figure 3 In some embodiments, the spark plug sleeve 400 extends into the region of the first mixing mechanism that mixes oxygen and air. The spark plug sleeve 400 is provided with a pressure relief hole (not shown in the figure) that connects the interior of the spark plug sleeve 400 to the region of the first mixing mechanism that mixes oxygen and air (i.e., the mixing chamber 210). This allows the high-pressure gas generated by combustion in the combustion chamber 100 to flow back into the region of the first mixing mechanism that mixes oxygen and air when it flows back through the spark plug sleeve 400, which helps to prevent leakage of the high-pressure gas generated by combustion in the combustion chamber 100.

[0042] It should be noted that in some embodiments, there are multiple spark plugs used for alternating ignition, which helps to extend the lifespan of the spark plugs while ensuring high-frequency ignition. It should also be noted that in other embodiments, the igniter can be a torch ignition device, which is not limited here.

[0043] Reference Figure 1 and Figure 2 In some embodiments, the combustion chamber 100 has a cylindrical structure. The combustion chamber 100, fuel chamber 320, oxygen chamber 311, mixing chamber 210, and intake manifold 241 are arranged sequentially along the axis of the combustion chamber 100 so that the high-pressure air supplied through the intake manifold 241 can smoothly enter the combustion chamber 100. The jet pipe 250 passes sequentially through the oxygen chamber 311, fuel chamber 320, and injection panel 110, and the spark plug sleeve 400 passes sequentially through the mixing chamber 210, oxygen chamber 311, fuel chamber 320, and injection panel 110.

[0044] In the description of this specification, the use of terms such as "one embodiment," "some embodiments," "illustrative embodiment," "example," "specific example," and "some examples" indicates that the specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of this application. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0045] Although embodiments of this application have been shown and described, those skilled in the art will understand that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of this application, the scope of which is defined by the claims and their equivalents.

Claims

1. An air heating device for hypersonic direct-drive testing, characterized in that, include: Combustion chamber (100), the front end of which is provided with injection panel (110), and an igniter for ignition is provided on injection panel (110); A first mixing mechanism is disposed at the front end of the combustion chamber (100). The first mixing mechanism is used to mix oxygen and air and deliver the mixed oxygen and air into the combustion chamber (100). The second mixing mechanism is disposed at the front end of the combustion chamber (100). The second mixing mechanism is used to mix oxygen and fuel and deliver the mixed oxygen and fuel into the combustion chamber (100). The first mixing mechanism includes a mixing inner chamber (210), a mixing outer chamber (220), a first oxygen intake pipe (230), an air intake pipe (240), and a jet pipe (250). The mixing inner chamber (210) is located at the front end of the combustion chamber (100), and the mixing outer chamber (220) is located at the front end of the combustion chamber (100) and covers the mixing inner chamber (210). A gap exists between the side wall of the mixing outer chamber (220) and the side wall of the mixing inner chamber (210) to form a first confluence cavity. Multiple first air inlets (211) are provided circumferentially on the side wall, connecting the first confluence chamber and the mixing chamber (210). The first oxygen inlet pipe (230) is connected to the side wall of the mixing chamber (220) and communicates with the first confluence chamber. The air inlet pipe (240) is connected to the side wall of the mixing chamber (220) and communicates with the first confluence chamber. One end of the jet pipe (250) is located inside the mixing chamber (210), and the other end of the jet pipe (250) passes through the injection panel (110). The air intake pipe (240) includes an intake main pipe (241) and a plurality of branch pipes (242). The plurality of branch pipes (242) are distributed circumferentially along the intake main pipe (241). One end of the plurality of branch pipes (242) is connected to the intake main pipe (241) and communicates with the interior of the intake main pipe (241). The other end of the plurality of branch pipes (242) is connected to the side wall of the mixing outer chamber (220) and communicates with the first confluence chamber. There are a plurality of first oxygen intake pipes (230). The plurality of first oxygen intake pipes (230) are distributed circumferentially along the side wall of the mixing outer chamber (220).

2. The air heating device for hypersonic direct-drive testing as described in claim 1, characterized in that, The second mixing mechanism includes an oxygen chamber (310), a fuel chamber (320), a second oxygen inlet pipe (330), a fuel delivery pipe (340), and an injector (350). The oxygen chamber (310) and the fuel chamber (320) are both located at the front end of the combustion chamber (100). The oxygen chamber (310) and the fuel chamber (320) share a common sidewall. The second oxygen inlet pipe (330) communicates with the oxygen chamber (310), and the fuel delivery pipe (340) communicates with the fuel chamber (350). The fuel chamber (320) is connected, and the output end of the injector (350) is provided on the injection panel (110). The other end of the injector (350) is provided on the side wall shared between the oxygen chamber (310) and the fuel chamber (320). The part of the injector (350) located in the oxygen chamber (310) is provided with a first input end for inhaling oxygen, and the part of the injector (350) located in the fuel chamber (320) is provided with a second input end for inhaling fuel.

3. The air heating device for hypersonic direct-drive testing as described in claim 2, characterized in that, The oxygen chamber (310) includes an inner oxygen chamber (311) and an outer oxygen chamber (312). The inner oxygen chamber (311) is located at the front end of the combustion chamber (100), and the outer oxygen chamber (312) is located at the front end of the combustion chamber (100) and covers the inner oxygen chamber (311). There is a gap between the side wall of the inner oxygen chamber (311) and the side wall of the outer oxygen chamber (312) to form a second confluence cavity. A plurality of second air inlets (3111) are arranged circumferentially on the side wall of the inner oxygen chamber (311) to connect the second confluence cavity and the inner oxygen chamber (311). There are multiple second oxygen inlet pipes (330), and the multiple second oxygen inlet pipes (330) are arranged circumferentially on the side wall of the outer oxygen chamber (312).

4. The air heating device for hypersonic direct-drive testing as described in claim 2, characterized in that, The injector (350) is provided with an annular step close to the injector panel (110) on the side of the injector panel (110) facing away from the combustion chamber (100).

5. The air heating device for hypersonic direct-drive testing as described in claim 1, characterized in that, The combustion chamber (100) is provided with a tapered nozzle (120) at its rear end.

6. The air heating device for hypersonic direct-drive testing as described in claim 1, characterized in that, The igniter includes a spark plug, and a spark plug sleeve (400) is provided on the injection panel (110), with the spark plug housed inside the spark plug sleeve (400).

7. The air heating device for hypersonic direct-drive testing as described in claim 6, characterized in that, The spark plug sleeve (400) extends into the region of the first mixing mechanism that mixes oxygen and air, and the spark plug sleeve (400) is provided with a pressure relief hole that connects the interior of the spark plug sleeve (400) with the region of the first mixing mechanism that mixes oxygen and air.

8. The air heating device for hypersonic direct-drive testing as described in claim 6, characterized in that, The number of spark plugs is multiple, and the multiple spark plugs are used for alternating ignition.

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