A modular secondary detonation engine

Abstract

The present invention provides a modular secondary detonation engine. The pre-detonation assembly includes a first fuel inlet pipe, a fuel chamber, an oxidizer chamber, a first oxidizer inlet pipe, a pre-detonation pipe and an igniter. The oxidizer chamber is coaxially sleeved outside the fuel chamber. The first fuel inlet pipe is communicated with the fuel chamber, and the first oxidizer inlet pipe is communicated with the oxidizer chamber. The outlet ends of the fuel chamber and the oxidizer chamber are both communicated with the inlet end of the pre-detonation pipe. The main detonation assembly includes a main detonation chamber assembly, a second fuel inlet pipe, a second oxidizer inlet pipe and an expansion tail nozzle. The second fuel inlet pipe and the second oxidizer inlet pipe are both arranged on the outer wall of the main detonation chamber assembly. The inlet end of the main detonation chamber assembly is communicated with the outlet end of the pre-detonation pipe, and the outlet end of the main detonation chamber assembly is communicated with the inlet end of the expansion tail nozzle. Through modular design, the engine thrust can be changed. Secondary detonation can increase the thrust, and the self-cooling combustion chamber can extend the service life.

Description

Technical Field

[0001] This specification relates to the technical field of detonation engines, and particularly to a modular secondary detonation engine. Background Art

[0002] A pulse detonation engine is a new concept propulsion device that uses high-temperature and high-pressure gas generated by intermittent detonation waves as thrust. According to whether it uses the atmosphere as the working medium, it can be divided into an air-breathing pulse detonation engine and a rocket pulse detonation engine. Pulse detonation engines have unique advantages compared with conventional propulsion systems, such as high thermal cycle efficiency, high thrust-to-weight ratio, wide operating range, simple structure, and light weight, especially being able to operate in two modes: air-breathing and rocket modes respectively.

[0003] The application of pulse detonation engines in rocket engines has received considerable attention, partly because: (1) The fuel (hydrogen) used in rocket engines has good detonability; (2) Since rocket engines carry their own fuel and oxidizer, the injection of fuel is no longer a problem under various flight conditions. If the nozzle efficiency during the exhaust process of a pulse detonation rocket engine is equivalent to that of a rocket engine, then the performance of the detonation stage of a pulse detonation rocket engine will be significantly increased compared with that of a conventional rocket engine.

[0004] The existing pulse detonation rocket engines have the following disadvantages: 1. They are not modularly designed, cannot change the combustion chamber length and the nozzle expansion ratio, and cannot change the engine thrust. 2. There is no supplementary fuel for secondary detonation to increase the thrust. 3. There is no cooling structure, and the temperature of the combustion chamber is too high, which will reduce the service life of the combustion chamber. Summary of the Invention

[0005] In view of this, the embodiments of this specification provide a modular secondary detonation engine to achieve the purpose of being modularly designed to change the engine thrust, secondary detonation to increase the thrust, and a self-cooling combustion chamber to extend the service life.

[0006] The embodiments of this specification provide the following technical solutions:

[0007] A modular secondary detonation engine, comprising:

[0008] A pre-detonation assembly, the pre-detonation assembly includes a first fuel inlet pipe, a fuel chamber, an oxidizer chamber, a first oxidizer inlet pipe, a pre-detonation pipe, and an igniter. The oxidizer chamber is coaxially sleeved outside the fuel chamber. The first fuel inlet pipe is arranged on the outer wall of the fuel chamber and communicates with the fuel chamber. The first oxidizer inlet pipe is arranged on the outer wall of the oxidizer chamber and communicates with the oxidizer chamber. The outlet ends of the fuel chamber and the oxidizer chamber both communicate with the inlet end of the pre-detonation pipe. The igniter is arranged on the outer wall of the pre-detonation pipe;

[0009] The main detonation component, which includes a main detonation chamber component, a second fuel inlet pipe, a second oxidant inlet pipe, and an expansion tail nozzle. The second fuel inlet pipe and the second oxidant inlet pipe are both arranged on the outer wall of the main detonation chamber component. The inlet end of the main detonation chamber component is communicated with the outlet end of the pre-detonation pipe, and the outlet end of the main detonation chamber component is communicated with the inlet end of the expansion tail nozzle.

[0010] Further, the oxidant chamber and the fuel chamber are detachably connected by threads.

[0011] Further, the pre-detonation pipe and the main detonation chamber component are detachably connected by a flange, and the main detonation chamber component and the expansion tail nozzle are detachably connected by a flange.

[0012] Further, the main detonation chamber component includes a main detonation chamber inner ring, a main detonation chamber outer ring, a main detonation chamber fuel channel group, and a pressure stabilizing chamber. The main detonation chamber outer ring is coaxially sleeved outside the main detonation chamber inner ring. The pressure stabilizing chamber is an annular gap at the upstream position between the main detonation chamber outer ring and the main detonation chamber inner ring. The main detonation chamber fuel channel group is arranged at the downstream position of the gap between the main detonation chamber outer ring and the main detonation chamber inner ring.

[0013] Further, the main detonation chamber fuel channel group includes a fuel channel and an oxidant channel. Both the fuel channel and the oxidant channel are sealed tubular channels formed by the cooperation of the grooves on the outer wall of the main detonation chamber inner ring and the grooves on the inner wall of the main detonation chamber outer ring. The inlet end of the fuel channel is connected to the second fuel inlet pipe, the outlet end of the fuel channel is connected to the pressure stabilizing chamber, the inlet end of the oxidant channel is connected to the second oxidant inlet pipe, and the outlet end of the oxidant channel is connected to the pressure stabilizing chamber.

[0014] Further, the main detonation chamber component fuel channel group includes one fuel channel and one oxidant channel, and the one fuel channel and the one oxidant channel are not connected to each other and are spirally distributed.

[0015] Further, the main detonation chamber component fuel channel group includes multiple fuel channels and multiple oxidant channels, and the multiple fuel channels and the multiple oxidant channels are not connected to each other and are spirally distributed.

[0016] Further, the main detonation component further includes a baffle with a rotating shaft, and the baffle with a rotating shaft is rotatably arranged between the pressure stabilizing chamber and the channel of the main detonation chamber inside the main detonation chamber inner ring. By adjusting the position of the baffle with a rotating shaft, the pressure stabilizing chamber can be communicated with or blocked from the main detonation chamber.

[0017] Further, a thread strengthening device is arranged on the inner wall of the main detonation chamber inner ring.

[0018] Further, a thread strengthening device is arranged on the inner wall of the pre-detonation pipe.

[0019] Compared with the prior art, the beneficial effects that can be achieved by at least one of the above technical solutions adopted in the embodiments of this specification at least include:

[0020] The inner wall of the pre-detonation tube is provided with a Shchelkin thread enhancement device. Fuel and oxidizer enter the pressure stabilization chamber through the double spiral grooves, improving the mixing rate and cooling the wall surface of the main detonation chamber assembly, and increasing the injection temperature of the fuel. The detonation wave enters the main detonation chamber assembly. As the detonation wave propagates outward, the pressure inside the main detonation chamber assembly gradually decreases. When the pressure at the front end of the main detonation chamber assembly is less than the pressure in the pressure stabilization chamber, under the action of the pressure difference, the baffle rotates into the main detonation chamber assembly, and gas enters the main detonation chamber assembly. The detonation wave transmitted from the pre-detonation tube ignites the gas inside the main detonation chamber assembly, forming a secondary detonation wave inside the main detonation chamber assembly. The inner wall of the main detonation chamber assembly is provided with a Shchelkin thread enhancement device. The tail is equipped with a bell-shaped nozzle to generate a higher impulse. The modular design enables the replacement of tail nozzles with different expansion ratios and main detonation chamber assemblies with different lengths, thereby changing the thrust. Description of the Drawings

[0021] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings in the following description are only some embodiments of the present application. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on these drawings.

[0022] Figure 1 It is a schematic diagram of the overall radial cross-section of the embodiment of the present invention;

[0023] Figure 2 is Figure 1 the schematic diagram of the axial cross-section of the A-A part of

[0024] Figure 3 is Figure 1 the enlarged schematic diagram at position B of

[0025] Figure 4 It is a schematic diagram of the inner ring structure of the main detonation chamber assembly of the embodiment of the present invention;

[0026] Figure 5 It is a schematic diagram of the baffle structure with a rotating shaft of the embodiment of the present invention;

[0027] Figure 6 It is a schematic diagram of the spiral flow direction of fuel and oxidizer of the embodiment of the present invention;

[0028] Figure 7 It is a schematic diagram before the baffle rotates in the embodiment of the present invention;

[0029] Figure 8 It is a schematic diagram after the baffle rotates in the embodiment of the present invention.

[0030] Description of reference numerals in the drawings: 1. First fuel inlet pipe; 2. Fuel chamber; 3. Oxidizer chamber; 4. First oxidizer inlet pipe; 5. Pre-explosion pipe; 6. Igniter; 7. Inner ring of main explosion chamber; 8. Outer ring of main explosion chamber; 9. Second fuel inlet pipe; 10. Tail nozzle; 11. Second oxidizer inlet pipe; 12. Thread reinforcement device; 13. Baffle with rotating shaft; 1301. Baffle inclined plane; 14. Fuel channel; 15. Oxidizer channel; 16. Pressure stabilizing chamber. Detailed implementation manners

[0031] The embodiments of the present application will be described in detail below with reference to the drawings.

[0032] The following uses specific specific examples to illustrate the implementation manners of the present application. Those skilled in the art can easily understand other advantages and effects of the present application from the content disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. The present application can also be implemented or applied through other different specific implementation manners. Various details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that, without conflict, the following embodiments and the features in the embodiments can be combined with each other. All other embodiments obtained by those of ordinary skill in the art based on the embodiments in the present application without creative efforts belong to the scope of protection of the present application.

[0033] It should be noted that the following describes various aspects of the embodiments within the scope of the appended claims. It should be obvious that the aspects described herein can be embodied in a wide variety of forms, and any specific structure and / or function described herein is illustrative only. Based on the present application, those skilled in the art should understand that one aspect described herein can be implemented independently of any other aspect, and two or more of these aspects can be combined in various ways. For example, any number and aspects described herein can be used to implement the device and / or practice the method. In addition, this device can be implemented and this method can be practiced using other structures and / or functions in addition to one or more of the aspects described herein.

[0034] It should also be noted that the drawings provided in the following embodiments only schematically illustrate the basic concept of the present application. The drawings only show the components related to the present application, rather than being drawn according to the number, shape and size of the components in actual implementation. The type, quantity and ratio of each component in its actual implementation can be an arbitrary change, and the component layout type may also be more complex.

[0035] In addition, in the following description, specific details are provided to facilitate a thorough understanding of the examples. However, those skilled in the art will understand that the described aspects can be practiced without these specific details.

[0036] The following explains the technical terms in the embodiments of this specification:

[0037] Knock: It is a combustion mode of the coupling of shock waves and flames (chemical reactions). It has a fast chemical reaction rate and fast flame propagation speed, up to 1000 + km / s, and can generate extremely high pressures and temperatures. The detonation wave generates extremely high gas pressure (greater than 1.5 - 5.5 MPa) and extremely high gas temperature (greater than 2800 K);

[0038] Rocket - type pulse detonation engine: The oxidizer supply method is self - supply, and it is a new - concept engine that uses pulse detonation waves to generate thrust;

[0039] Pre - detonation tube: After the fuel mixture burns, the process of deflagration - to - detonation transition occurs in the tube, and finally a detonation wave is formed;

[0040] Main detonation chamber: It is the combustion chamber for secondary detonation, which promotes the successful transition of detonation and thus generates greater thrust;

[0041] Bell - shaped nozzle: It adopts a part with rapid expansion or radial flow in the initial diffusion zone, and then guides to a uniform axial flow at the exit of the tail nozzle. Using a bell - shaped nozzle can obtain a higher nozzle efficiency and shorten the length of the nozzle;

[0042] The following combines with the attached drawings to illustrate the technical solutions provided by each embodiment of this application.

[0043] As Figure 1 、 Figure 2 、 Figure 3 shown, the detonation engine of this embodiment includes a first fuel inlet pipe 1, a fuel chamber 2, an oxidizer chamber 3, a first oxidizer inlet pipe 4, a pre - detonation tube 5, an igniter 6, an inner ring of the main detonation chamber 7, an outer ring of the main detonation chamber 8, a second fuel inlet pipe 9, an expanding tail nozzle 10, a second oxidizer inlet pipe 11, a threaded reinforcement device 12, a baffle with a rotating shaft 13, a fuel channel 14, an oxidizer channel 15, and a pressure - stabilizing chamber 16.

[0044] The first fuel inlet pipe 1, the fuel chamber 2, the oxidizer chamber 3, the first oxidizer inlet pipe 4, the pre - detonation tube 5, and the igniter 6 form a pre - detonation assembly. The oxidizer chamber 3 is coaxially sleeved outside the fuel chamber 2. The outlet end of the fuel chamber 2 is provided with a direct - current spray hole, and there is a gas annular gap between the outer wall of the direct - current spray hole and the inner wall of the oxidizer chamber 3.

[0045] The main detonation assembly is composed of the inner ring 7 of the main detonation chamber, the outer ring 8 of the main detonation chamber, the second fuel inlet pipe 9, the expansion tail nozzle 10, the second oxidizer inlet pipe 11, the baffle plate 13 with a rotating shaft, the fuel channel 14, the oxidizer channel 15 and the pressure stabilizing chamber 16. The main detonation chamber assembly is divided into the inner ring 7 of the main detonation chamber and the outer ring 8 of the main detonation chamber. The outer ring 8 of the main detonation chamber is coaxially sleeved outside the inner ring 7 of the main detonation chamber. The inner part of the inner ring 7 of the main detonation chamber is the main detonation chamber, and a thread strengthening device 12 is arranged on the inner wall of the inner ring 7 of the main detonation chamber. The thread strengthening device 12 is a Shchelkin thread strengthening device. When the ignition energy is low, the conversion time and distance from deflagration to detonation will become longer. The Shchelkin thread strengthening device is used for flow disturbance to shorten the time and distance of the conversion from deflagration to detonation.

[0046] Among them, the fuel chamber 2 and the oxidizer chamber 3 are connected by threads, and the pre-detonation tube 5 and the main detonation chamber assembly, and the main detonation chamber assembly and the expansion tail nozzle 10 are all connected by flanges. Both connection methods are convenient for disassembly and easy to replace components with different parameters.

[0047] Reference Figure 1 , during pre-detonation, the fuel enters the fuel chamber 2 through the first fuel inlet pipe 1, and the oxidizer enters the oxidizer chamber 3 through the first oxidizer inlet pipe 4. The fuel and the oxidizer enter the inlet section of the pre-detonation tube 5 in a coaxial direct-flow manner (the fuel flows into the pre-detonation tube 5 through the central direct-flow nozzle, and the oxidizer flows into the pre-detonation tube 5 through the direct-flow nozzle of the fuel chamber 2 and the gas annular gap of the oxidizer chamber 3) for mixing. After being ignited by the igniter 6, it enters the outlet section of the pre-detonation tube 5, and a thread strengthening device 12 is arranged on the inner wall of the outlet section of the pre-detonation tube 5. The mixture of the fuel and the oxidizer first undergoes slow combustion, then the conversion from deflagration to detonation occurs, and finally a detonation wave enters the main detonation chamber assembly. In this embodiment, the equivalent ratio distribution of the combustible mixture in the pre-detonation tube 5 can be adjusted by adjusting the supply pressure and flow rate of the fuel and the oxidizer, or the equivalent ratio distribution can be changed by adjusting the volume ratio of the fuel chamber to the oxidizer chamber.

[0048] Reference Figure 2, the spiral grooves of the fuel channel 14 and the oxidizer channel 15 are formed by the nested combination of the spiral groove structure on the outer wall of the inner ring 7 of the main detonation chamber and the spiral groove structure on the inner wall of the outer ring 8 of the main detonation chamber. Before ignition, the fuel and the oxidizer enter the pressure stabilizing chamber 16 through the double spiral grooves formed by the fuel channel 14 and the oxidizer channel 15, so that they are fully mixed and homogenized. At this time, the pressure in the pressure stabilizing chamber is equal to the sum of the torsional force of the rotating shaft and the pressure in the main detonation chamber. The fuel channel 14 and the oxidizer channel 15 are arranged on the outer wall surface of the inner ring 7 of the main detonation chamber. When the main detonation chamber assembly works, heat will be generated. This heat can heat the fuel and the oxidizer and consume a part of the heat through the flowing fuel and oxidizer. At the same time, the hole-shaped cavity design of the fuel channel 14 and the oxidizer channel 15 can also carry out wall cooling. The main detonation chamber assembly is divided into the inner ring 7 of the main detonation chamber and the outer ring 8 of the main detonation chamber. By the cooperation of the inner ring and the outer ring, the processing difficulty of the thread groove is reduced, and the purpose of reducing the cost is achieved. The spiral design of the fuel channel 14 and the oxidizer channel 15 can not only reduce the temperature of the combustion chamber wall, but also increase the temperature of the fuel. After the fuel and the oxidizer are heated, they have higher energy, shorten the time for the detonation wave to be generated after the mixture burns, burn more fully when entering the main detonation chamber assembly, improve the working stability, and increase the service life of the combustion chamber.

[0049] During the main detonation, a pressure stabilizing chamber 16 is arranged at the inlet end of the main detonation chamber assembly. The pressure stabilizing chamber 16 is a chamber formed by coaxially sleeving the inner ring 7 of the main detonation chamber and the outer ring 8 of the main detonation chamber. The fuel channel 14 and the oxidizer channel 15 are located at the outlet end of the main detonation chamber assembly, and the main detonation chamber is located inside the inner ring 7 of the main detonation chamber.

[0050] The first detonation is realized through the pre-detonation assembly, the fuel and the oxidizer are supplemented through the main detonation assembly, and the second detonation is carried out in the main detonation chamber assembly, further improving the thrust.

[0051] Reference Figure 3 、 Figure 4 、 Figure 5 , a baffle 13 with a rotating shaft is arranged at the inlet end of the fuel main detonation chamber. Reference Figure 7 , before the baffle 13 with a rotating shaft rotates, the baffle 13 with a rotating shaft contacts the arc surface at the inlet end of the main detonation chamber assembly, and there is a 30° baffle inclined surface 1301 tangent to the arc surface at the rear end. When the detonation wave enters the main detonation chamber assembly, as the detonation wave propagates outward, the pressure in the main detonation chamber assembly gradually decreases. When the pressure at the front end of the main detonation chamber assembly is less than the pressure in the pressure stabilizing chamber, under the action of the pressure difference, the baffle 13 with a rotating shaft rotates into the main detonation chamber assembly until it is blocked by the baffle inclined surface 1301, and the gas enters the main detonation chamber assembly. The detonation wave transmitted by the pre-detonation tube ignites the gas in the main detonation chamber assembly, and a fully developed detonation wave is formed in the main detonation chamber assembly. The detonation products in the main detonation chamber propagate towards both ends of the main detonation chamber. Reference Figure 8, when the detonation products propagate to the front end of the main detonation chamber, the pressure at the front end of the main detonation chamber is greater than the pressure in the pressure stabilization chamber at this time, and the baffle 13 with a rotating shaft rotates into the pressure stabilization chamber 16 until it seals the inlet end of the inner ring 7 in the main detonation chamber. Thus, the front end of the main detonation chamber assembly is completely sealed. On the one hand, it plays the role of closing the end bearing surface and increasing the thrust. On the other hand, it can effectively prevent the flame from conducting forward.

[0052] As the gas in the main detonation chamber assembly is continuously discharged, the pressure of the main detonation chamber assembly gradually decreases. When the pressure in the main detonation chamber drops below the pressure in the pressure stabilization chamber 16, the baffle 13 with a rotating shaft rotates towards the inner side of the main detonation chamber assembly, and the gas enters the main detonation chamber assembly, playing the role of isolating the gas and further discharging the gas from the main detonation chamber assembly.

[0053] Refill the pre-detonation assembly with fuel and oxidizer. The valve of the main detonation chamber is always in the open state, ignition and detonation occur, and the next working cycle begins.

[0054] Reference Figure 6 , Figure 6 is the flow diagram of fuel and oxidizer. The fuel channel 14 and the oxidizer channel 15 are both spiral grooves, and the two channels form non-intersecting double spiral grooves. The supplementary fuel enters the pressure stabilization chamber 16 through the fuel channel 14, and the supplementary oxidizer enters the pressure stabilization chamber 16 through the oxidizer channel 15 to make them fully mixed and uniform. The fuel channel 14 and the oxidizer channel 15 in this embodiment are double spiral grooves. In some other embodiments, the double spiral grooves can be multi-spiral grooves, and by changing the quantity ratio of the fuel channel 14 and the oxidizer channel 15, the purpose of changing the equivalence ratio distribution in the main detonation chamber assembly is achieved.

[0055] The detonation products discharged from the main detonation carry a large amount of internal energy, and a nozzle is required to convert the internal energy into kinetic energy to improve the engine performance. In 1998, Cambier and Tegner studied the influence of 5 different expansion nozzles on the performance based on quasi-one-dimensional multi-cycle simulation and two-dimensional single-pulse detonation numerical simulation. The calculation results of single-pulse detonation show that the expansion tail nozzle 10 can increase the impulse, and the expansion tail nozzle 10 using a bell-shaped nozzle can generate a higher impulse.

[0056] This embodiment is a modular engine. By changing the main detonation chamber assemblies with different lengths and the tail nozzles with different expansion ratios, the thrust of the engine can be increased to achieve the required thrust. By adjusting the supply pressure and flow rate of fuel, oxidizer, supplementary fuel, and supplementary oxidizer, the equivalence ratio distribution of the combustible mixture in the detonation tube can be adjusted. Or adjust the volume ratio of the fuel chamber and the oxidizer chamber to change the equivalence ratio distribution.

[0057] Each embodiment in this specification is described in a progressive manner. For the same or similar parts among the embodiments, reference can be made to each other. Each embodiment focuses on the differences from other embodiments. In particular, for the method embodiments described later, since they correspond to the system, the description is relatively simple, and reference can be made to the relevant parts of the system embodiments for the related content.

[0058] The above is only a specific implementation manner of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by those skilled in the art within the technical scope disclosed by the present application should be covered within the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. A modular secondary detonation engine, characterized in that, Comprising: A pre-detonation assembly, the pre-detonation assembly including a first fuel inlet pipe (1), a fuel chamber (2), an oxidizer chamber (3), a first oxidizer inlet pipe (4), a pre-detonation pipe (5) and an igniter (6). The oxidizer chamber (3) is coaxially sleeved outside the fuel chamber (2). The first fuel inlet pipe (1) is arranged on the outer wall of the fuel chamber (2) and communicates with the fuel chamber (2). The first oxidizer inlet pipe (4) is arranged on the outer wall of the oxidizer chamber (3) and communicates with the oxidizer chamber (3). The outlet ends of the fuel chamber (2) and the oxidizer chamber (3) are both communicated with the inlet end of the pre-detonation pipe (5). The igniter (6) is arranged on the outer wall of the pre-detonation pipe (5); A main detonation assembly, the main detonation assembly including a main detonation chamber assembly, a second fuel inlet pipe (9), a second oxidizer inlet pipe (11) and an expansion tail nozzle (10). The second fuel inlet pipe (9) and the second oxidizer inlet pipe (11) are both arranged on the outer wall of the main detonation chamber assembly. The inlet end of the main detonation chamber assembly is communicated with the outlet end of the pre-detonation pipe (5). The outlet end of the main detonation chamber assembly is communicated with the inlet end of the expansion tail nozzle (10); The main detonation chamber assembly includes a main detonation chamber inner ring (7), a main detonation chamber outer ring (8), a main detonation chamber fuel channel group and a pressure stabilizing chamber (16). The main detonation chamber outer ring (8) is coaxially sleeved outside the main detonation chamber inner ring (7). The pressure stabilizing chamber (16) is an annular gap at the upstream position between the main detonation chamber outer ring (8) and the main detonation chamber inner ring (7). The main detonation chamber fuel channel group is arranged at the downstream position of the gap between the main detonation chamber outer ring (8) and the main detonation chamber inner ring (7).

2. The modular secondary detonation engine according to claim 1, wherein, The oxidizer chamber (3) and the fuel chamber (2) are detachably connected by threads.

3. The modular secondary detonation engine according to claim 1, wherein The pre-detonation pipe (5) and the main detonation chamber assembly are detachably connected by a flange. The main detonation chamber assembly and the expansion tail nozzle (10) are detachably connected by a flange.

4. The modular secondary detonation engine according to claim 1, wherein The main detonation chamber fuel channel group includes a fuel channel (14) and an oxidizer channel (15). The fuel channel (14) and the oxidizer channel (15) are both sealed tubular channels formed by the cooperation of the grooves on the outer wall of the main detonation chamber inner ring (7) and the grooves on the inner wall of the main detonation chamber outer ring (8). The inlet end of the fuel channel (14) is connected to the second fuel inlet pipe (9). The outlet end of the fuel channel (14) is connected to the pressure stabilizing chamber (16). The inlet end of the oxidizer channel (15) is connected to the second oxidizer inlet pipe (11). The outlet end of the oxidizer channel (15) is connected to the pressure stabilizing chamber (16).

5. The modular secondary detonation engine according to claim 4, wherein, The main detonation chamber assembly fuel channel group includes one fuel channel (14) and one oxidizer channel (15). One fuel channel (14) and one oxidizer channel (15) are not communicated with each other and are spirally distributed.

6. The modular secondary detonation engine according to claim 4, wherein The main detonation chamber assembly fuel channel group includes multiple fuel channels (14) and multiple oxidizer channels (15). The multiple fuel channels (14) and the multiple oxidizer channels (15) are not communicated with each other and are spirally distributed.

7. The modular secondary detonation engine according to claim 1, wherein, The main detonation component further includes a baffle plate (13) with a rotating shaft. The baffle plate (13) with a rotating shaft is rotatably arranged between the pressure stabilizing cavity (16) and the passage of the main detonation chamber inside the inner ring (7) of the main detonation chamber. By adjusting the position of the baffle plate (13) with a rotating shaft, the pressure stabilizing cavity (16) can be communicated with or blocked from the main detonation chamber.

8. The modular secondary detonation engine according to claim 1, characterized in that, A thread reinforcing device (12) is arranged on the inner wall of the inner ring (7) of the main detonation chamber.

9. The modular secondary detonation engine according to claim 1, characterized in that, A thread reinforcing device (12) is arranged on the inner wall of the pre-detonation tube (5).

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