An engine based on variable structure flow channel and adjustable thermal throat mode

Abstract

The present invention belongs to the field of engines, and specifically relates to an engine based on a variable structure flow channel and an adjustable thermal throat mode, which aims to solve the problems of unstable air flow, energy loss, poor flame stability and structural design limitations in the prior art, which limit its efficient and stable operation in different flight stages. The present invention includes: a central cone and a central nozzle are coaxially fixed, and an inner cone is coaxially fixed on the central cone; an outer air inlet shell is installed on the outer surface of the central nozzle; an adjustable front body is arranged between the inner cone and the outer air inlet shell, and an outer air flow channel and an inner air flow channel are formed between the adjustable front body and the outer air inlet shell and the inner cone respectively; a concave cavity is slidably provided in the outer air inlet shell, and the concave cavity and the fuel support plate form an adjustable thermal throat. The present invention effectively avoids the influence of the multi-channel structure on the incoming flow, which is beneficial to the stability and efficiency of combustion.

Description

Technical Field

[0001] The invention belongs to the field of engines, and in particular relates to an engine based on a variable structure flow passage and an adjustable thermal throat mode. Background Art

[0002] The rocket-based combined power cycle engine is a combined propulsion system that organically integrates a rocket engine with a high thrust-to-weight ratio and low specific impulse with a ramjet engine with a low thrust-to-weight ratio and high specific impulse. The RBCC engine integrates ejection mode, subsonic mode, scramjet mode and pure rocket mode. Through different working modes, it can work in a very wide speed range, and even achieve orbit entry using the highest working Mach number of the rocket mode. This allows the RBCC engine to start automatically, have a wide flight envelope, strong mission adaptability, and great application prospects.

[0003] When operating in a wide flight envelope, the RBCC engine mainly experiences four operating modes: ejection mode, subcombustion mode, scramjet mode, and pure rocket mode. The wide range of changes in the incoming flow parameters will inevitably cause the fixed structure engine operating conditions to deviate seriously from the design state. It is difficult for a fixed structure combustion chamber to have both excellent performance at the design point and non-design point. In order to improve the performance of a fixed structure engine, the combustion chamber length is often longer, which increases the engine structure mass. On the other hand, it also brings difficulties in thermal protection due to the increase in the thermal protection area. The variable geometry throat scheme can keep the injection position fixed, without the need for multi-stage injection in the combustion chamber to meet the incoming flow state at different flight Mach numbers, so the combustion chamber length can be shortened. In the ejection and subcombustion modes of the RBCC engine, the combustion chamber flow channel adopts a convergent and divergent structure to meet the efficient combustion of the combustion chamber; in the scramjet mode, in order to meet the needs of supersonic combustion, the combustion chamber flow channel remains an expansion structure. The use of variable structures of the inlet duct and combustion chamber can meet the best engine performance in each mode and even at each flight Mach number as much as possible, ensuring that the RBCC engine can operate efficiently and stably in a wide range. However, engines with fixed structures cannot simultaneously meet the requirements of the optimal performance working environment in each mode.

[0004] Most of the existing variable structure RBCC engines still use a binary structure. For the variable structure inlet with a binary structure, the throat area adjustment will cause the combustion chamber inlet to form a step structure with the adjustment of the inlet throat, which is not conducive to the engine performance and the realization of sealing. In addition, the structural mass and aerodynamic resistance are relatively large, and the variable structure actuation form and sealing are relatively difficult. In addition, for the research on the existing axisymmetric variable structure engine, due to the limitations of the structure itself, it is not suitable for setting a rotatable splitter plate like a binary structure, so the series channel layout scheme is basically adopted. The series RBCC inlet is difficult to protect the turbine module when flying at high Mach numbers. The turbine module will bring great flow losses when flying at high speeds, thereby affecting the overall performance of the engine at high Mach numbers, causing the engine to pay a certain price when converting multi-mode operations. Therefore, it is of great significance to design a parallel channel structure suitable for the axisymmetric variable structure RBCC engine.

[0005] At present, a few researchers have tried to design a scheme that can initially realize the internal parallel connection of the channel of the axisymmetric variable structure RBCC engine. However, compared with the external parallel channel design, the internal parallel type cannot be operated in an ideal state during the working mode conversion, which is easy to cause the inflow air to be unstable and cause certain energy losses. In addition, the existing internal parallel channel implementation method is based on the simultaneous operation of the two channels, and it is impossible to effectively and flexibly control the independence of the channels to ensure efficient and stable mode conversion. In addition, most of the existing axisymmetric variable structure RBCC engine designs do not consider the flame stabilization effect of the combustion chamber in the transition between the ejection mode and the sub-combustion mode and the pure rocket mode. Compared with the support plate rocket, due to the lack of the role of the fuel support plate and the concave cavity, the mixing effect of the fuel and air and the stability of the combustion are poor, and it is impossible to reliably improve the effective performance of different working modes by adjusting the thermal throat.

[0006] Based on this, the present invention proposes an engine based on a variable structure flow passage and an adjustable thermal throat mode. Summary of the invention

[0007] In order to solve the above-mentioned problems in the prior art, namely, the axisymmetric variable structure RBCC engine in the prior art has problems such as unstable air flow, energy loss, poor flame stability and limitations in structural design during mode conversion, which limits its efficient and stable operation in different flight phases, the present invention provides an engine based on a variable structure flow channel and an adjustable thermal throat mode, comprising a central cone, a central nozzle, and an adjustable front body and an outer air inlet casing symmetrically arranged along the axis of the central cone;

[0008] The central cone and the central nozzle are coaxially fixed, an inner cone is coaxially fixed on the central cone, and the inner cone is arranged in the central nozzle;

[0009] An outer air inlet housing is installed on the outer surface of the central nozzle, and the outer air inlet housing covers a part of the adjustable front body; the adjustable front body is arranged between the inner cone and the outer air inlet housing, and an outer air flow channel and an inner air flow channel are formed between the adjustable front body, the outer air inlet housing and the inner cone, respectively, and by controlling the angle and position of the adjustable front body, whether the outer air flow channel and the inner air flow channel are inlet and the size of the air intake amount are adjusted;

[0010] A concave cavity is slidably connected in the outer air inlet housing, and the concave cavity and the fuel support plate form an adjustable thermal throat;

[0011] An outer nozzle is arranged inside the outer air inlet housing, and the outer nozzle is communicated with the outer air flow channel.

[0012] In some preferred embodiments, the adjustable precursor includes a fixed end and a movable end;

[0013] The fixed end is drivingly connected to a driving device, the driving device is used to drive the fixed end to rotate, and the movable end is arranged on the fixed end and moves along the fixed end;

[0014] An outer air flow channel is formed between the moving end and the outer air inlet housing, and an inner air flow channel is formed between the moving end and the inner cone.

[0015] In some preferred embodiments, a scramjet mode combustion chamber is coaxially opened in the central nozzle.

[0016] In some preferred embodiments, the adjustable front body is arranged to protrude from the central cone.

[0017] In some preferred embodiments, the fixed end and the movable end are asymmetric semi-conical structures, and the vertical distance from the maximum protrusion position of the cone of the fixed end to the axis is greater than the vertical distance from the maximum protrusion position of the cone of the movable end to the axis.

[0018] In some preferred embodiments, the conical surface of the central cone and the conical surface of the inner cone are oriented in opposite directions.

[0019] In some preferred embodiments, a slide groove is provided on the inner surface of the outer air inlet duct housing, and the concave cavity is provided in the slide groove.

[0020] In some preferred embodiments, the cross-sectional shape of the outer air inlet housing is semicircular.

[0021] In some preferred embodiments, in a low Mach speed state, the adjustable front body is controlled to open the outer air flow channel and close the inner air flow channel.

[0022] In some preferred embodiments, in a high Mach speed state, the adjustable front body is controlled to close the outer air flow channel and open the inner air flow channel.

[0023] Beneficial effects of the present invention:

[0024] The variable structure RBCC engine of the present invention is different from most existing engines. It adopts an external parallel axisymmetric structure, which effectively eliminates the defects of the series and internal parallel structures. It can not only ensure that the damage to the internal components of the engine by the incoming flow is reduced and the interference with the combustion is reduced when working at a high Mach number, but also ensure that the low Mach number and high Mach number work are carried out in different channels, effectively avoiding the influence of the multi-channel structure on the incoming flow, which is beneficial to the stability and efficiency of combustion. The movable and adjustable precursor can change the inlet duct according to the incoming flow conditions, and the concave cavity in the combustion chamber can adjust its position in the combustion chamber to adapt to different working conditions at the same time, which can help stabilize the combustion and improve the combustion efficiency, and can also help different working modes to transition smoothly. The main design points of the present invention are simple in structure and easy to implement geometric changes, which can achieve the design purpose with high efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Other features, objects and advantages of the present application will become more apparent by reading the detailed description of non-limiting embodiments made with reference to the following drawings:

[0026] Figure 1 It is a schematic diagram of the overall structure of an engine based on a variable structure flow channel and an adjustable thermal throat mode of the present invention;

[0027] Figure 2 It is a schematic diagram of the internal structure of an engine based on a variable structure flow channel and an adjustable thermal throat mode of the present invention;

[0028] Figure 3 It is a structural schematic diagram of an adjustable front body of an engine based on a variable structure flow channel and an adjustable thermal throat mode of the present invention;

[0029] Figure 4 yes Figure 3 Dynamic change diagram of

[0030] Figure 5 It is a schematic diagram of the flow direction of an engine based on a variable structure flow channel and an adjustable thermal throat mode of the present invention.

[0031] In the figure: 1. central cone; 2. central nozzle; 3. inner cone; 4. adjustable front body; 41. fixed end; 42. movable end; 5. outer air inlet shell; 7. outer air flow channel; 8. inner air flow channel; 9. concave cavity; 10. outer nozzle. DETAILED DESCRIPTION

[0032] The present application will be further described in detail below in conjunction with the accompanying drawings and embodiments. It is to be understood that the specific embodiments described herein are only used to explain the relevant invention, rather than to limit the invention. It is also necessary to explain that, for ease of description, only the parts related to the relevant invention are shown in the accompanying drawings.

[0033] It should be noted that, in the absence of conflict, the embodiments and features in the embodiments of the present application can be combined with each other. The present application will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0034] like Figure 1-Figure 5 As shown, see Figure 1 and Figure 2 The present invention provides an engine based on a variable structure flow channel and an adjustable thermal throat mode, comprising a central cone 1, a central nozzle 2, and an adjustable front body 4 and an outer air inlet housing 5 symmetrically arranged along the axis of the central cone 1;

[0035] The central cone 1 and the central nozzle 2 are coaxially fixed, an inner cone 3 is coaxially fixed on the central cone 1, and the inner cone 3 is arranged in the central nozzle 2;

[0036] An outer air inlet housing 5 is installed on the outer surface of the central nozzle 2, and the outer air inlet housing 5 covers a part of the adjustable front body 4; the adjustable front body 4 is arranged between the inner cone 3 and the outer air inlet housing 5, and an outer air flow channel 7 and an inner air flow channel 8 are respectively formed between the adjustable front body 4, the outer air inlet housing 5 and the inner cone 3. By controlling the angle and position of the adjustable front body 4, whether the outer air flow channel 7 and the inner air flow channel 8 are inlet and the size of the air intake amount can be adjusted;

[0037] A cavity 9 is slidably connected in the outer air inlet housing 5, and the cavity 9 and the fuel support plate form an adjustable thermal throat;

[0038] An outer nozzle 10 is disposed inside the outer air inlet housing 5 , and the outer nozzle 10 is communicated with the outer air flow channel 7 .

[0039] The structure of the present invention is based on an axisymmetric engine configuration. The main frame is divided into an internal scramjet combustion chamber 21 and an outer combined combustion chamber. An external parallel dual-channel structure is formed by the front central cone 1 and the outer air inlet shells 5 on both sides and the adjustable front body 4. The air intake mode can be selected by adjusting the front body. The adjustable front body 4 is symmetrically installed on both sides of the central cone 1, and part of the surface protrudes from the surface of the central cone 1. The outer air inlet shell 5 covers a part of the exposed adjustable front body 4 to form air inlets on both sides.

[0040] The entire engine structure is composed of a central cone structure, namely a central cone 1, and two symmetrical semi-conical structures on the outside, namely an adjustable front body 4. The outer air inlet shells 5 on both sides fix the wings in accordance with the fluid movement trend.

[0041] The engine has a scramjet combustion chamber 21 inside. The forebody controls the flow from the inlet duct, and the flows on both sides merge in the internal combustion chamber to generate combustion thrust that is released from the center nozzle.

[0042] The two wing engines are combined engines, and the airflow enters the air inlets and combustion chambers on both sides through the adjustable forebody 4. The air inlets and combustion chambers are cavity structures surrounded by the shell. A support plate rocket is arranged inside the adjustable forebody 4 to provide initial modal thrust. An adjustable concave cavity 9 is arranged inside the outer air inlet shell 5 to form an adjustable thermal throat with the fuel support plate. Finally, the outer nozzle 10 releases the tail flame to generate thrust.

[0043] Therein, a concave cavity 9 is slidably connected inside the outer air inlet duct housing 5, and the specific structure of the sliding connection may be a slide rail connection, which is not specifically limited here.

[0044] All parts of this device are made of stainless steel to ensure light weight and large temperature difference adaptability.

[0045] The present invention can achieve structural control in low Mach speed state and high Mach speed state, and isolate and distinguish the working channels of the RBCC engine working mode through variable structure. In the ejection mode and the subcombustion mode, it can be controlled to select the two outer combined engines to work and provide thrust, and in the scramjet mode, it is converted to the ramjet engine inside the center body to provide thrust. It can ensure that the engine inlet is effectively isolated in the low Mach speed and high Mach speed working states to protect the rocket engine module. The rocket module will cause great flow loss when flying at high speed, accompanied by a large amount of energy waste.

[0046] The core of the design of the present invention lies in the adjustable front body 4 on both sides. The adjustable front body 4 can selectively open the outer airflow channel 7 and the inner airflow channel 8. The adjustable front body 4 is an asymmetric structure. When the outer airflow channel 7 is opened, the inner airflow channel 8 is closed at the same time, and vice versa. Different channels can be closed by rotating 180° around the central axis of the adjustable front body 4. At the same time, when the air inlet is opened, the adjustable front body 4 can also be axially translated to control the size of the air inlet area to achieve the purpose of controlling the air inlet throat. When the adjustable front body 4 moves backward, the air inlet contraction ratio becomes smaller, and the air intake flow rate becomes smaller to meet the high Mach air inlet requirements; when the adjustable front body 4 moves forward, the air inlet contraction ratio becomes larger, and the air intake flow rate becomes larger to meet the low Mach air inlet requirements.

[0047] Inside the combustion chamber, there are fuel support plates, support plate rockets, and an adjustable cavity 9, which ensure the combustion stability in the ejection mode and sub-combustion mode. The cavity 9 can translate axially to better stabilize the combustion and improve the combustion efficiency under different incoming flows and combustion conditions. Through a series of adjustments, the smoothness of the transition of working modes with different Mach numbers can be ensured and the thrust efficiency can be improved.

[0048] like Figure 3 , Figure 4 and Figure 5 As shown, the adjustable front body 4 in the present invention includes a fixed end 41 and a movable end 42;

[0049] The fixed end 41 is drivingly connected to a driving device, and the driving device is used to drive the fixed end 41 to rotate. The movable end 42 is arranged on the fixed end 41 and moves along the fixed end 41;

[0050] An outer air flow channel 7 is formed between the moving end 42 and the outer air inlet duct housing 5 , and an inner air flow channel 8 is formed between the moving end 42 and the inner cone 3 .

[0051] The fixed end 41 may be mounted on the inner surface of the outer air inlet housing 5 by means of a bearing or other means to achieve support.

[0052] The movement between the movable end 42 and the fixed end 41 can be achieved through a slider guide, specifically a dovetail slider and guide, which can make the movable end 42 and the fixed end 41 rotate synchronously and also make the movable end 42 move independently.

[0053] Among them, the driving mechanism of the fixed end 41 can be a micro motor embedded in the inner surface of the outer air intake duct shell 5, and the driving source for the movable end 42 to move along the fixed end 41 can also be a linear motor. The linear motor can be fixed on the fixed end 41 and can be fixed on the inner surface of the outer air intake duct shell 5. The above content is not limited here by the present invention, and technical personnel in this field can set it according to actual conditions.

[0054] The present invention can close the external air flow channel 7 or the internal air flow channel 8 by rotating the adjustable front body 4 and moving the movable end 42. The specific steps are as follows:

[0055] When working in the ejection mode, the combined engine air intake channels on both sides, namely the outer air intake channels 7, are first opened through the adjustable front body 4, while the inner ramjet air intake channel, namely the inner air intake channel 8, is closed. The rocket engine inside the adjustable front body 4 is turned on to provide ejection power, and the secondary injection fuel enters the combustion chamber from the fuel support plate. The concave cavity 9 cooperates with the support plate to stabilize the combustion flame. The specific steps are: rotate the movable end 42 upward, at this time, the fixed end 41 contacts the inner cone 3, at this time, the inner air intake channel 8 is closed, and at the same time, because the movable end 42 and the fixed end 41 are not symmetrical structures, the movable end 42 does not fit the inner surface of the outer air intake duct shell 5, and the outer air intake channel 7 is open at this time;

[0056] When the Mach number of the aircraft rises to the subcombustion mode range, the position of the cavity 9 in the scramjet mode combustion chamber 21 is adjusted. By axially translating the cavity 9 to the upstream end of the scramjet mode combustion chamber 21, the fuel support plate can be better coordinated for stable combustion and the combustion efficiency can be improved. In addition, the movable end 42 is axially translated toward the rear end to reduce the contraction ratio and flow rate to match the high Mach number working condition.

[0057] When the flight Mach number continues to increase to the scramjet mode, in order to reduce the impact of the structure in the combined engine channel on combustion and the adverse effects of the high Mach number on internal components, the fixed end 41 and the movable end 42 are simultaneously rotated 180° until they are in contact with the inner surface of the outer air inlet shell 5. This is the state of closing the outer air flow channels 7 on both sides. At the same time, since the movable end 42 and the fixed end 41 are not symmetrical structures, the movable end 42 does not contact the inner cone 3 at this time, and the inner air flow channels 8 on both sides are opened; the outer air flow channel 7 is closed, and the high Mach number incoming flows on both sides are merged into the internal ramjet combustion chamber for pure scramjet operation, and the tail flame is released through the tail nozzle at the middle rear end, providing effective thrust for working with ultra-high Mach number incoming flows.

[0058] The fuel support plate is arranged between the cavity 9 and the adjustable front body 4 , and is arranged on the outer air inlet housing 5 .

[0059] In the present invention, the adjustable front body 4 is arranged to protrude from the central cone 1 . Specifically, when the movable end 42 and the fixed end 41 are rotated to a side away from the inner cone 3 , both of them can protrude from the central cone 1 .

[0060] As a further explanation of the present invention, the fixed end 41 and the movable end 42 are asymmetric semi-conical structures.

[0061] The movable end 42 and the fixed end 41 in the present invention are asymmetrically arranged. Specifically, the vertical distance from the maximum protruding position of the cone of the fixed end 41 to the axis is greater than the vertical distance from the maximum protruding position of the cone of the movable end 42 to the axis. Only in this way can the fixed end 41 fit with the surface of the inner cone 3 or the outer air inlet shell 5, thereby achieving the closing or opening of the air inlet.

[0062] Among them, the support plate rocket is embedded in the adjustable front body 4, specifically embedded in the mobile end 42.

[0063] For further explanation of the present invention, see Figure 2 The conical surface of the central cone 1 and the conical surface of the inner cone 3 are oriented in opposite directions.

[0064] For further explanation of the present invention, see Figure 2 The inner surface of the outer air inlet duct housing 5 is provided with a slide groove, and the concave cavity 9 is arranged in the slide groove.

[0065] By moving the cavity 9 and adjusting its position in the combustion chamber to suit different working conditions, it can help stabilize combustion and improve combustion efficiency.

[0066] As a further explanation of the present invention, the cross-sectional shape of the outer air inlet housing 5 is a semicircle.

[0067] Specifically, the cross section of a vertical plane along its axial direction is a semicircle.

[0068] As a further explanation of the present invention, in the low Mach speed state, the adjustable front body 4 is controlled to open the outer air flow channel 7 and close the inner air flow channel 8.

[0069] As a further explanation of the present invention, in a high Mach speed state, the adjustable front body 4 is controlled to close the outer air flow channel 7 and open the inner air flow channel 8.

[0070] In the description of the present invention, the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer" and the like indicating directions or positional relationships are based on the directions or positional relationships shown in the drawings, which are only for the convenience of description, and do not indicate or imply that the device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", and "third" are used for descriptive purposes only, and cannot be understood as indicating or implying relative importance.

[0071] In addition, it should be noted that in the description of the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For those skilled in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0072] The term "comprise" or any other similar term is intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus / device that includes a list of elements includes not only those elements but also other elements not expressly listed, or also includes elements inherent to such process, method, article, or apparatus / device.

[0073] So far, the technical solutions of the present invention have been described in conjunction with the preferred embodiments shown in the accompanying drawings. However, it is easy for those skilled in the art to understand that the protection scope of the present invention is obviously not limited to these specific embodiments. Without departing from the principle of the present invention, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will fall within the protection scope of the present invention.

Claims

1. An engine based on a variable structure flow channel and an adjustable thermal throat mode, characterized in that: It comprises a central cone (1), a central nozzle (2), and an adjustable front body (4) and an outer air inlet casing (5) symmetrically arranged along the axis of the central cone (1); The central cone (1) and the central nozzle (2) are coaxially fixed, an inner cone (3) is coaxially fixed on the central cone (1), and the inner cone (3) is arranged in the central nozzle (2); An outer air inlet housing (5) is mounted on the outer surface of the central nozzle (2), and the outer air inlet housing (5) covers a portion of the adjustable front body (4); the adjustable front body (4) is arranged between the inner cone (3) and the outer air inlet housing (5), and an outer air flow channel (7) and an inner air flow channel (8) are formed between the adjustable front body (4), the outer air inlet housing (5) and the inner cone (3), respectively. By controlling the angle and position of the adjustable front body (4), whether the outer air flow channel (7) and the inner air flow channel (8) are inlet and the amount of air inlet can be adjusted; A concave cavity (9) is slidably connected inside the outer air inlet housing (5), and the concave cavity (9) and the fuel support plate form an adjustable thermal throat; An outer nozzle (10) is arranged inside the outer air inlet housing (5), and the outer nozzle (10) is connected to the outer air flow channel (7); The adjustable front body (4) comprises a fixed end (41) and a movable end (42); The fixed end (41) is drivingly connected to a driving device, the driving device is used to drive the fixed end (41) to rotate, and the movable end (42) is arranged on the fixed end (41) and moves along the fixed end (41); An outer air flow channel (7) is formed between the movable end (42) and the outer air inlet housing (5), and an inner air flow channel (8) is formed between the movable end (42) and the inner cone (3); The fixed end (41) and the movable end (42) are asymmetric semi-conical structures, and the vertical distance from the maximum protrusion position of the cone of the fixed end (41) to the axis is greater than the vertical distance from the maximum protrusion position of the cone of the movable end (42) to the axis.

2. An engine based on a variable structure flow channel and an adjustable thermal throat mode according to claim 1, characterized in that: A scramjet mode combustion chamber (21) is coaxially provided in the central nozzle (2).

3. The engine based on variable structure flow channel and adjustable thermal throat mode according to claim 1, characterized in that: The adjustable front body (4) is arranged to protrude from the central cone (1).

4. The engine based on variable structure flow channel and adjustable thermal throat mode according to claim 1, characterized in that: The conical surface of the central cone (1) and the conical surface of the inner cone (3) are oriented in opposite directions.

5. The engine based on variable structure flow channel and adjustable thermal throat mode according to claim 1, characterized in that: The inner surface of the outer air inlet duct housing (5) is provided with a slide groove, and the concave cavity (9) is arranged in the slide groove.

6. The engine based on variable structure flow channel and adjustable thermal throat mode according to claim 1, characterized in that: The cross-sectional shape of the outer air inlet duct housing (5) is a semicircle.

7. The engine based on variable structure flow channel and adjustable thermal throat mode according to claim 1, characterized in that: In a low Mach speed state, the adjustable front body (4) is controlled to open the outer air flow channel (7) and close the inner air flow channel (8).

8. The engine based on variable structure flow channel and adjustable thermal throat mode according to claim 1, characterized in that: In a high Mach speed state, the adjustable front body (4) is controlled to close the outer air flow channel (7) and open the inner air flow channel (8).

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