A controllable scramjet engine and its operating method

Abstract

The present invention discloses a controllable scramjet engine and its operating method, belonging to the field of scramjet engines. The engine comprises a supersonic combustion chamber, a controllable gas generator disposed on the outer wall of the supersonic combustion chamber, the output end of the controllable gas generator being connected to the input end of the supersonic combustion chamber via a regenerative cooling pipe disposed on the wall of the tail nozzle of the supersonic combustion chamber; the controllable gas generator comprises a main body, fuel filled within the main body, and an electric pyrolysis mechanism for pyrolyzing the fuel. Using the above-mentioned controllable scramjet engine and its operating method, pyrolysis gas is used as fluidizing gas to carry powdered fuel for injection, effectively enhancing the engine's specific impulse performance. The gas fuel can also serve as a pilot fuel, first burning to increase pressure and temperature, and then carrying a flow to eject high-energy powder particles, thereby solving the problem of short residence time of powdered fuel in the combustion chamber and low combustion efficiency.

Description

Technical Field

[0001] The present invention relates to the technical field of scramjet engines, and in particular to a controllable scramjet engine and an operating method thereof. Background Art

[0002] In recent years, high Mach numbers and wide-range propulsion have become key research areas in the development of hypersonic vehicles. For hypersonic weapons, developing a matching propulsion system is paramount. As a key component of hypersonic vehicles, the propulsion system is a key technology determining their development.

[0003] Scramjets can be categorized as liquid-fueled and solid-fueled, depending on the type of fuel they use. Compared to liquid-fueled scramjets, solid-fueled scramjets offer advantages such as simpler structure, higher specific impulse, inherent solid fuel, simplified fuel supply, reliance on oxygen in the air for combustion, safe storage and transportation, low cost, high reliability, and rapid operational response. Furthermore, solid-fueled scramjets possess a high-density fuel that can be stored for long periods, offering inherent advantages in missile applications.

[0004] Since the working process of solid fuel ramjet engines is very complicated, involving gas dynamics, thermodynamics, combustion, etc., there are still some problems to be solved. For example, 1. The ignition and combustion performance of oxygen-depleted propellants is very complex, the flame stability is poor, and flameout is prone to occur; although the addition of metal particles to the propellant can significantly increase the density and specific impulse, the combustion efficiency is low and it is easy to agglomerate. When the metal particles agglomerate into the flow field, it will lead to two-phase loss, slag deposition and erosion enhancement, etc., which will have a greater impact on the solid fuel burning rate due to the airflow and heat transfer process; 2. When the solid fuel ramjet engine is working, due to the high temperature and high pressure environment in the combustion chamber, extremely high temperatures will be generated, which will cause great thermal stress and thermal damage to the structural materials and internal components of the engine, and bring challenges to the thermal protection structure.

[0005] In summary, existing solid fuel ramjet engines have problems such as the inability to actively cool the solid fuel, the inability to fully utilize the advantages of solid fuel, and the poor controllability of the solid oxygen-depleted propellant fuel. Summary of the Invention

[0006] The purpose of the present invention is to provide a controllable scramjet engine and an operating method thereof to solve the above technical problems.

[0007] To achieve the above objectives, the present invention provides a controllable scramjet engine, comprising a supersonic combustion chamber and a controllable gas generator disposed on the outer wall of the supersonic combustion chamber, wherein the output end of the controllable gas generator is connected to the input end of the supersonic combustion chamber via a regenerative cooling pipe, and the regenerative cooling pipe is disposed on the wall of the tail nozzle of the supersonic combustion chamber;

[0008] The controllable gas generator comprises a main body, fuel filled in the main body and an electric pyrolysis mechanism for pyrolyzing the fuel.

[0009] Preferably, the fuel is solid polyethylene, and the electric pyrolysis mechanism includes a heating electrode arranged on one side of the fuel and a first DC regulated power supply electrically connected to the heating electrode. A propulsion unit is also provided on the other side of the fuel for pressing the fuel onto the heating electrode.

[0010] Preferably, the propulsion unit includes a push plate, a compression spring provided on a side of the push plate facing away from the fuel, and a guide cylinder for guiding the compression spring, wherein the guide cylinder is fixed inside the body;

[0011] Alternatively, the propulsion unit includes a push plate, a nitrogen-filled propulsion chamber arranged on the side of the push plate away from the fuel, a pressure reducing valve and a nitrogen gas source connected to the nitrogen-filled propulsion chamber in sequence.

[0012] Preferably, the heating electrode is a porous structure with multiple through holes on the electrode plate;

[0013] Alternatively, the heating electrode is a mesh structure woven from resistance wires;

[0014] Alternatively, a center hole is opened in the center of the heating electrode, an igniter or flame spray gun with a nitrogen atmosphere is provided on the main body, the outlet of the igniter or flame spray gun with a nitrogen atmosphere is facing the center hole, and a plurality of through holes evenly arranged in a ring array are opened on the heating electrode and around the center hole.

[0015] Preferably, the heating electrode is an end-face burning electrode, and the resistance of the end-face burning electrode is equal to the internal resistance of the first DC regulated power supply.

[0016] Preferably, the fuel is powdered polyethylene, and the electric pyrolysis mechanism includes a porous pyrolysis chamber disposed inside the body, the porous pyrolysis chamber being electrically connected to the first DC regulated power supply, and the porous pyrolysis chamber having a plurality of through holes formed in the direction toward the output end of the controllable gas generator;

[0017] The porous pyrolysis chamber is filled with powdered polyethylene;

[0018] The resistance of the porous pyrolysis chamber is equal to the internal resistance of the first DC regulated power supply.

[0019] Preferably, the output gas flow rate of the controllable gas generator is 50 g / s-100 g / s, and the gas temperature is 300°C.

[0020] Preferably, a secondary gas heater is further provided between the controllable gas generator and the regenerative cooling pipe, the secondary gas heater comprising a shell, a spiral resistance heating wire provided inside the shell, the spiral resistance heating wire being electrically connected to the second DC regulated power supply, and the resistance of the spiral resistance heating wire being equal to the internal resistance of the second DC regulated power supply;

[0021] The two ends of the secondary gas heater are respectively connected to the controllable gas generator and the regenerative cooling pipeline;

[0022] An insulating layer is provided on the interior of the secondary gas heater.

[0023] A method for operating a controllable scramjet engine comprises the following steps: first, loading fuel, then connecting an electric pyrolysis mechanism to pyrolyze the fuel to produce 300°C pyrolysis gas, the 300°C pyrolysis gas passing through a regenerative cooling pipe to absorb heat from a tail nozzle of a supersonic combustion chamber, thereby cooling the controllable scramjet engine and raising its temperature, and finally passing the gas into the supersonic combustion chamber for combustion;

[0024] The pyrolysis gas is a fluidizing gas carrying powdered fuel.

[0025] A method for operating a controllable scramjet engine comprises the following steps: first, fuel is loaded; then, an electric pyrolysis mechanism and a second DC regulated power supply are connected to pyrolyze the fuel to produce 300°C pyrolysis gas; the 300°C pyrolysis gas enters a secondary gas heater for secondary pyrolysis; then, the 300°C pyrolysis gas enters a regenerative cooling pipe to absorb heat from a tail nozzle of a supersonic combustion chamber, thereby cooling the controllable scramjet engine; and finally, the temperature is raised to 700°C before entering the supersonic combustion chamber for combustion;

[0026] The pyrolysis gas is a fluidizing gas carrying powdered fuel.

[0027] Therefore, the present invention adopts the above-mentioned controllable scramjet engine and its operating method, which has the following beneficial effects:

[0028] 1. Efficient thermal management: Regenerative cooling design: The regenerative cooling pipe absorbs the heat from the supersonic combustor tail nozzle, which not only effectively reduces the engine temperature and extends the engine life, but also uses waste heat to increase the temperature of the pyrolysis gas, thereby improving energy utilization efficiency.

[0029] Secondary gas heater: performs secondary heating on the pyrolysis gas before it enters the combustion chamber to ensure that the gas temperature reaches the optimal combustion conditions (e.g. 700°C), thereby improving combustion efficiency and thrust;

[0030] 2. Fuel flexibility and controllability: Solid polyethylene or powdered polyethylene fuel can be used. The choice of these two fuels provides flexibility and allows the selection of different forms of fuel according to specific needs. Solid polyethylene is easy to store and transport, while powdered polyethylene is more conducive to the carrying and uniform distribution of fluidizing gas.

[0031] 3. By decomposing the fuel into high-temperature gas through electrothermal decomposition, the generation rate and temperature of the gas can be precisely controlled, thus enhancing the controllability and response speed of the engine;

[0032] 4. Structural optimization and compact design: porous electrode and screen structure: The heating electrode adopts a porous structure or screen structure, which increases the contact area between the fuel and the electrode, improves the pyrolysis efficiency, and ensures the uniform output of the gas;

[0033] End-face combustion electrode: This design makes resistance matching more accurate, reduces energy loss, and improves the efficiency of electric thermal decomposition;

[0034] Propulsion unit: Whether using a compression spring or nitrogen-filled propulsion chamber, it ensures that fuel can be evenly and continuously supplied to the heating electrode, avoiding the problem of uneven fuel supply;

[0035] 5. High reliability and safety: By precisely controlling the temperature and flow rate of pyrolysis gas (50g / s-100g / s), the stability and efficiency of the combustion process are ensured, and the occurrence of unstable phenomena such as flameout is reduced;

[0036] An insulating layer is set inside the secondary gas heater to effectively prevent heat loss, while also protecting the heating wire and other components from overheating damage, thereby improving the safety and stability of the system.

[0037] 6. Environmental protection and economy: Polyethylene is a relatively clean fuel that produces fewer pollutants during combustion and meets environmental protection requirements;

[0038] Energy recovery: The waste heat from the tail nozzle is recovered through the regenerative cooling pipe, which realizes energy reuse, reduces energy consumption and improves overall economic efficiency;

[0039] In summary, the present invention adjusts the injection fuel equivalence ratio by regulating the electric heating power. The pyrolysis gas can be actively cooled. Moreover, since the density of its high-polymer compound is greater than that of liquid kerosene, it can effectively reduce the volume of the aircraft under the same mass of fuel carried. At the same time, the pyrolysis gas contains various olefins, all of which have high calorific value and can effectively improve the specific impulse. The gas can also carry high-energy metal powder, which can provide better performance. It can solve the problems of liquid fuel being inconvenient to carry and solid fuel being unable to be actively cooled and uncontrollable. It can also take advantage of the advantages of gas fuel, significantly improve the performance and reliability of the engine, and has broad application prospects.

[0040] The technical solution of the present invention is further described in detail below through the accompanying drawings and embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0041] Figure 1 This is a schematic structural diagram of a controllable scramjet engine of the present invention that uses a single controllable gas generator for pyrolysis;

[0042] Figure 2 This is a schematic structural diagram of a controllable scramjet engine of the present invention that uses a controllable gas generator combined with a two-stage gas heater for pyrolysis;

[0043] Figure 3 This is a schematic structural diagram of a controllable gas generator using a compression spring as a propulsion mechanism according to Example 1 of a controllable scramjet engine of the present invention;

[0044] Figure 4 This is a schematic structural diagram of a controllable gas generator using nitrogen as a propulsion mechanism as described in Example 1 of a controllable scramjet engine of the present invention;

[0045] Figure 5 This is a structural diagram of a heating electrode with a porous structure as described in Example 1 of a controllable scramjet engine of the present invention;

[0046] Figure 6 This is a structural diagram of a heating electrode of a mesh structure according to Example 1 of a controllable scramjet engine of the present invention;

[0047] Figure 7 This is a schematic structural diagram of the nitrogen atmosphere igniter or flame spray gun assisted pyrolysis described in Example 1 of a controllable scramjet engine of the present invention;

[0048] Figure 8 This is a diagram of the heating electrode structure of the nitrogen atmosphere igniter or flame spray gun assisted pyrolysis described in Example 1 of a controllable scramjet engine of the present invention;

[0049] Figure 9 This is a structural diagram of the two-stage gas heater described in Example 1 of a controllable scramjet engine of the present invention;

[0050] Figure 10 This is a structural diagram of a controllable gas generator according to embodiment 2 of a controllable scramjet engine of the present invention;

[0051] Figure 11 This is a structural diagram of a porous pyrolysis chamber as described in Example 2 of a controllable scramjet engine of the present invention.

[0052] Reference numerals

[0053] 1. Controllable gas generator; 11. Main body; 12. Heating electrode; 121. Center hole; 13. Compression spring; 14. Guide cylinder; 15. Push plate; 16. Nitrogen-filled propulsion chamber; 17. Pressure reducing valve; 18. Nitrogen gas source; 19. Porous pyrolysis chamber; 110. Igniter or flame spray gun for nitrogen atmosphere; 2. Supersonic combustion chamber; 3. Regenerative cooling duct; 4. Support plate; 5. Secondary gas heater; 51. Casing. DETAILED DESCRIPTION

[0054] In order to make the purposes, technical solutions and advantages disclosed in the embodiments of the present invention clearer, the embodiments of the present invention are further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the embodiments of the present invention and are not intended to limit the embodiments of the present invention. Based on the embodiments in the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. Examples of the embodiments are shown in the accompanying drawings, where the same or similar numbers throughout represent the same or similar elements or elements with the same or similar functions.

[0055] It should be noted that the terms "including" and "having" and any variations thereof are intended to cover non-exclusive inclusions. For example, a process, method, system, product or server that includes a series of steps or units is not necessarily limited to those steps or units clearly listed, but may include other steps or units that are not clearly listed or are inherent to these processes, methods, products or devices.

[0056] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

[0057] By pyrolyzing high-polymer compounds, a fuel gas is obtained, which carries high-energy metal powders such as aluminum or boron and is injected into the combustion chamber for combustion. The pyrolysis fuel gas can be used for active cooling. Moreover, since the density of the high-polymer compound is greater than that of liquid kerosene, the volume of the aircraft can be effectively reduced under the same mass of fuel carried. In addition, the high-energy metal powder can provide a higher specific impulse, which has important academic value and engineering significance for the development of future hypersonic aircraft. The present invention is designed based on the above analysis.

[0058] Example 1

[0059] like Figure 1 as well as Figure 3-Figure 9As shown, a controllable scramjet engine includes a supersonic combustion chamber 2 and a controllable gas generator 1 arranged on the outer wall of the supersonic combustion chamber 2. The output end of the controllable gas generator 1 is connected to the input end of the supersonic combustion chamber 2 via a regenerative cooling pipe 3. In this embodiment, the regenerative cooling pipe 3 is connected to the supersonic combustion chamber 2 directly through the wall surface, or is connected to the supersonic combustion chamber 2 through a support plate 4. The regenerative cooling pipe 3 is arranged on the wall surface of the tail nozzle of the supersonic combustion chamber 2; the controllable gas generator 1 includes a main body 11, fuel filled in the interior of the main body 11, and an electric pyrolysis mechanism for pyrolyzing the fuel.

[0060] The fuel is solid polyethylene, and the electric pyrolysis mechanism includes a heating electrode 12 arranged on one side of the fuel and a first DC regulated power supply DC1 electrically connected to the heating electrode 12. A propulsion unit is also provided on the other side of the fuel to press the fuel onto the heating electrode 12 to ensure reliable pyrolysis.

[0061] The propulsion unit includes a push plate 15, a compression spring 13 provided on the side of the push plate 15 facing away from the fuel, and a guide cylinder 14 for guiding the compression spring 13. The guide cylinder 14 is fixed inside the body to prevent the compression spring 13 from sliding left and right.

[0062] The propulsion unit includes a push plate 15 , a nitrogen-filled propulsion chamber 16 disposed on a side of the push plate 15 facing away from the fuel, a pressure reducing valve 17 and a nitrogen gas source 18 that are sequentially connected to the nitrogen-filled propulsion chamber 16 .

[0063] The heating electrode 12 is a porous structure with multiple through-holes on the electrode plate, which has the advantage of high mechanical strength but the disadvantage of a small flow area. Alternatively, the heating electrode 12 is a mesh structure woven from resistance wire, which has the advantage of a large flow area but the disadvantage of low mechanical strength. Alternatively, the heating electrode 12 has a central hole 121 at its center, and a nitrogen atmosphere igniter or flame spray gun 110 is provided on the body, with the outlet of the nitrogen atmosphere igniter or flame spray gun 110 facing the central hole 121. The heating electrode 12 is provided with multiple through-holes evenly arranged in a circular array around the central hole 121 for circulating pyrolysis gas (combustible hydrocarbon gas). By combining an igniter such as a nitrogen atmosphere plasma igniter or flame spray gun with the heating electrode 12, the size of the heating electrode 12 can be effectively reduced while ensuring uniform heating, thereby reducing the volume of the gas generator.

[0064] The heating electrode 12 is an end-face burning electrode, and the resistance of the end-face burning electrode is equal to the internal resistance of the first DC regulated power supply DC1. Considering the power loss of 0.8, the output power of the first DC regulated power supply DC1 is set to 50kw.

[0065] Example 2

[0066] like Figure 10 and Figure 11 As shown, the differences between Example 2 and Example 1 are as follows: the fuel is powdered polyethylene, the electric pyrolysis mechanism includes a porous pyrolysis chamber 19 disposed within the body, the porous pyrolysis chamber 19 is electrically connected to the first DC regulated power supply DC1, and the porous pyrolysis chamber 19 has multiple through-holes facing the output end of the controllable gas generator 1; the porous pyrolysis chamber 19 is filled with powdered polyethylene; and the resistance of the porous pyrolysis chamber 19 is equal to the internal resistance of the first DC regulated power supply DC1. Compared to solid polyethylene, it is easier to load.

[0067] The output gas flow rate of the controllable gas generator 1 is 50 g / s-100 g / s, and the gas temperature is 300° C. To share the generation of the gas flow rate, multiple controllable gas generators 1 can be arranged in parallel in this embodiment.

[0068] A method for operating a controllable scramjet engine comprises the following steps: first, fuel is loaded, then an electric pyrolysis mechanism is connected to pyrolyze the fuel to produce 300°C pyrolysis gas; the 300°C pyrolysis gas passes through a regenerative cooling pipe 3 to absorb heat from the tail nozzle of a supersonic combustion chamber 2, thereby cooling the controllable scramjet engine and raising its temperature; and finally, the pyrolysis gas is passed into the supersonic combustion chamber 2 for combustion; wherein the pyrolysis gas is fluidizing gas carrying powdered fuel.

[0069] like Figure 2 As shown, a secondary gas heater 5 is further provided between the controllable gas generator 1 and the regenerative cooling pipe 3. The secondary gas heater 5 includes a shell 51 and a spiral resistance heating wire arranged inside the shell 51. The spiral resistance heating wire is electrically connected to the second DC regulated power supply DC2. The resistance of the spiral resistance heating wire is equal to the internal resistance of the second DC regulated power supply DC2. The spiral resistance heating wire is provided to fully contact the pyrolysis gas pressed by the gas generator so as to fully perform secondary pyrolysis and pyrolyze more gas fuels such as light olefins and alkanes. The two ends of the secondary gas heater 5 are respectively connected to the controllable gas generator 1 and the regenerative cooling pipe 3. An insulating heat insulation layer is provided on the interior of the secondary gas heater 5.

[0070] A method for operating a controllable scramjet engine comprises the following steps: first, fuel is loaded; then, an electric pyrolysis mechanism and a second DC regulated power supply DC2 are connected to pyrolyze the fuel to produce 300°C pyrolysis gas; the 300°C pyrolysis gas enters a secondary gas heater 5 for secondary pyrolysis; then, the 300°C pyrolysis gas enters a regenerative cooling pipe 3 to absorb heat from the tail nozzle of a supersonic combustion chamber 2, thereby cooling the controllable scramjet engine; the temperature is raised to 700°C; and finally, the pyrolysis gas is passed into the supersonic combustion chamber 2 for combustion; wherein, the pyrolysis gas is fluidizing gas carrying powdered fuel.

[0071] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention rather than to limit the same. Although the present invention has been described in detail with reference to the preferred embodiments, those skilled in the art should understand that they can still modify or replace the technical solutions of the present invention with equivalents, and these modifications or equivalent replacements cannot cause the modified technical solutions to deviate from the spirit and scope of the technical solutions of the present invention.

Claims

1. A controllable scramjet engine, characterized by: The invention comprises a supersonic combustion chamber and a controllable gas generator arranged on the outer wall of the supersonic combustion chamber, wherein the output end of the controllable gas generator is connected to the input end of the supersonic combustion chamber via a regenerative cooling pipe, and the regenerative cooling pipe is arranged on the wall of the tail nozzle of the supersonic combustion chamber; The controllable gas generator includes a main body, fuel filled in the main body, and an electric pyrolysis mechanism for pyrolyzing the fuel; The fuel is solid polyethylene or powdered polyethylene; The electric pyrolysis mechanism pyrolyzes the fuel to generate pyrolysis gas, which is fluidizing gas carrying powdered fuel.

2. A controllable scramjet engine according to claim 1, characterized in that: The fuel is solid polyethylene, and the electric pyrolysis mechanism includes a heating electrode arranged on one side of the fuel and a first DC regulated power supply electrically connected to the heating electrode. A propulsion unit is also provided on the other side of the fuel for pressing the fuel onto the heating electrode.

3. A controllable scramjet engine according to claim 2, characterized in that: The propulsion unit includes a push plate, a compression spring provided on the side of the push plate facing away from the fuel, and a guide cylinder for guiding the compression spring, wherein the guide cylinder is fixed inside the body; Alternatively, the propulsion unit includes a push plate, a nitrogen-filled propulsion chamber arranged on the side of the push plate away from the fuel, a pressure reducing valve and a nitrogen gas source connected to the nitrogen-filled propulsion chamber in sequence.

4. A controllable scramjet engine according to claim 3, characterized in that: The heating electrode is a porous structure with multiple through holes on the electrode plate; Alternatively, the heating electrode is a mesh structure woven from resistance wires; Alternatively, a center hole is opened in the center of the heating electrode, an igniter or flame spray gun with a nitrogen atmosphere is provided on the main body, the outlet of the igniter or flame spray gun with a nitrogen atmosphere is facing the center hole, and a plurality of through holes evenly arranged in a ring array are opened on the heating electrode and around the center hole.

5. The controllable scramjet engine according to claim 4, characterized in that: The heating electrode is an end-face burning type electrode, and the resistance of the end-face burning type electrode is equal to the internal resistance of the first DC regulated power supply.

6. The controllable scramjet engine according to claim 1, characterized in that: The fuel is powdered polyethylene, and the electric pyrolysis mechanism includes a porous pyrolysis chamber disposed inside the body, the porous pyrolysis chamber being electrically connected to a first DC regulated power supply, and having a plurality of through holes formed in the porous pyrolysis chamber toward the output end of the controllable gas generator; The porous pyrolysis chamber is filled with powdered polyethylene; The resistance of the porous pyrolysis chamber is equal to the internal resistance of the first DC regulated power supply.

7. The controllable scramjet engine according to claim 1, characterized in that: The output gas flow of the controllable gas generator is 50g / s-100g / s, and the gas temperature is 300℃.

8. A controllable scramjet engine according to any one of claims 1 to 7, characterized in that: A secondary gas heater is further provided between the controllable gas generator and the regenerative cooling pipe. The secondary gas heater includes a housing and a spiral resistance heating wire disposed inside the housing. The spiral resistance heating wire is electrically connected to a second DC regulated power supply. The resistance of the spiral resistance heating wire is equal to the internal resistance of the second DC regulated power supply. The two ends of the secondary gas heater are respectively connected to the controllable gas generator and the regenerative cooling pipeline; An insulating layer is provided on the interior of the secondary gas heater.

9. The method for operating a controllable scramjet engine according to any one of claims 1 to 7, wherein: The method comprises the following steps: firstly, loading fuel, then connecting an electric pyrolysis mechanism to pyrolyze the fuel to generate 300°C pyrolysis gas; the 300°C pyrolysis gas absorbs heat from the tail nozzle of the supersonic combustion chamber through a regenerative cooling pipe, cools the controllable scramjet engine, and heats it up before being passed into the supersonic combustion chamber for combustion.

10. The method for operating a controllable scramjet engine according to claim 8, wherein: The method comprises the following steps: firstly, fuel is loaded, then an electric pyrolysis mechanism and a second DC regulated power supply are connected to pyrolyze the fuel to generate 300°C pyrolysis gas, the 300°C pyrolysis gas enters a secondary gas heater for secondary pyrolysis, then enters a regenerative cooling pipe to absorb heat from the tail nozzle of the supersonic combustion chamber, cools the controllable scramjet engine, and raises the temperature to 700°C before entering the supersonic combustion chamber for combustion.

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