A design method of TBCC exhaust system based on intermediate splitter plate adjustment

Abstract

The present invention discloses a TBCC exhaust system design method based on the adjustment of the intermediate splitter plate, including: designing an asymmetric single-side expansion ramjet engine nozzle three-dimensional model; designing a turbine engine channel adjustment mechanism in the form of an intermediate splitter plate and a turbine engine nozzle three-dimensional model; designing a ramjet engine channel adjustment mechanism in the form of a connecting rod hinge + slide rail. The present invention uses a linear motor to drive the slide rail to move forward and backward, and drives the passive rod to rotate around a common rotating shaft through a connecting rod hinged with the slide rail to achieve throat adjustment of the ramjet engine channel; uses a torque motor to drive the intermediate splitter plate to rotate around a common rotating shaft to achieve throat adjustment and working mode conversion of the turbine engine channel.

Description

Technical Field

[0001] The invention relates to the technical field of a dual-channel exhaust system for a parallel turbine-based combined power engine, and in particular to a TBCC exhaust system design method based on intermediate splitter plate regulation. Background Art

[0002] Horizontal take-off and landing, reusable hypersonic aircraft have broken through the boundaries of traditional aerospace vehicles and are an important direction and strategic commanding height for the development of aerospace technology in the future. Among them, the power system has always been the most important factor in determining the upper limit of aircraft performance, and the realization of hypersonic flight depends on the development level of high-speed power system technology. At present, any single engine cannot meet the requirements of hypersonic aircraft for power units such as horizontal take-off and landing, wide envelope adaptability and strong maintainability. Therefore, it has become an inevitable trend to select two or more power units for organic integration and develop combined cycle engines.

[0003] The combined cycle propulsion systems that are currently being studied are mainly rocket-based combined cycle engines (RBCC) and turbine-based combined cycle engines (TBCC). Each type of combined power scheme has its own scope of application and technical difficulties. TBCC is one of the most likely combined power schemes to be applied to hypersonic vehicles due to its significant advantages such as high specific impulse, conventional horizontal takeoff and landing, strong reusability, high load capacity and low technical risk.

[0004] According to the power layout, TBCC can be divided into two categories: series and parallel. The ramjet engine of the series layout is arranged behind the turbine engine along the incoming flow direction. The two share the main components such as the intake and exhaust and the combustion chamber. The structure is compact and the technology is highly mature. However, the two types of engines share too many flow passages, and there is strong interference between them, which is difficult to coordinate and control, resulting in a low upper limit of their working. The parallel layout arranges the ramjet engine and the turbine engine separately up and down. The two have their own independent flow passages, which greatly reduces the mutual interference between the two sets of engines and improves the maximum working Mach number upper limit and propulsion performance. However, there are also problems such as large space occupation and difficulty in integration with the fuselage. As one of the core components of the parallel TBCC, the dual-channel exhaust system has a great impact on the acceleration performance, fuel consumption and attitude stability control of the aircraft. How to design a simple structure and highly integrated adjustment mechanism with the rear body is one of the core problems to be solved in the exhaust system design. The traditional rotating lower lip plate + rotating splitter plate solution has problems such as excessive control torque and interference with the position of the middle splitter plate.

[0005] Therefore, it is necessary to propose a new design method to solve the above-mentioned problems. Summary of the invention

[0006] In view of this, the purpose of the present invention is to provide a TBCC exhaust system design method based on intermediate splitter plate adjustment to solve the problem of mutual interference between the positions of the two channel adjustment mechanisms, while reducing the operating torque required for ramjet engine channel throat adjustment.

[0007] In order to achieve the above object, the present invention adopts the following technical solution:

[0008] A TBCC exhaust system design method based on intermediate splitter plate adjustment, the design method comprising the following steps:

[0009] Step S1, designing an asymmetric unilateral expansion ramjet engine nozzle three-dimensional model, wherein the ramjet engine nozzle three-dimensional model includes: a contraction section, an expansion section and a side wall surface of the ramjet engine nozzle;

[0010] Step S2, designing a channel adjustment mechanism of a turbine engine and a three-dimensional model of a turbine engine nozzle, wherein the channel adjustment mechanism of the turbine engine adopts a structure of an intermediate splitter plate;

[0011] Step S3, designing a channel regulating mechanism of a ramjet engine, the channel regulating mechanism of the ramjet engine comprises: a motor, a slide rail, upper and lower supports of the slide rail, a connecting rod, a hinge pin and a passive rod, wherein the motor is used to provide power for the slide rail, one end of the slide rail is arranged in the upper and lower supports of the slide rail, and the other end thereof is connected to one end of the connecting rod, the other end of the connecting rod is connected to one end of the passive rod through the hinge pin, and the other end of the passive rod is connected to the rotating shaft of the middle diverter plate, and the connecting rod and the passive rod are driven to rotate by controlling the forward and backward movement of the slide rail to realize the control of the channel flow of the ramjet engine.

[0012] Furthermore, the step S1 specifically includes:

[0013] Step S101, obtaining a two-dimensional profile of a single-side expansion ramjet nozzle based on a design method of a characteristic line method and a two-dimensional maximum thrust nozzle theory;

[0014] Step S102: performing lateral stretching according to the span-wise width of the binary exhaust system to obtain a three-dimensional model of the unilateral expansion ramjet nozzle.

[0015] Furthermore, the step S2 specifically includes:

[0016] Step S201: for the ramjet engine nozzle three-dimensional model obtained in step S1, a position is selected as the rotation axis position of the middle splitter plate at the downstream of the ramjet engine nozzle throat, and then the axial length of the middle splitter plate is set;

[0017] Step S202, designing the profile of the middle manifold, wherein the profile of the middle manifold includes: the rear half of the profile on the middle manifold, the front half of the profile on the middle manifold, and the lower profile of the middle manifold;

[0018] Step S203, with respect to the expansion profile of the ramjet engine channel nozzle, the upper half of the profile that has not been intercepted is used as the upper expansion section of the turbine engine channel outlet;

[0019] Step S204, designing an upper contraction section of the turbine engine channel, which includes: firstly determining the turbine engine channel nozzle inlet height according to the turbine engine combustion chamber outlet height, and then selecting a smooth curve to transition to the end point of the upper contraction section;

[0020] Step S205, taking the rotation axis position of the middle splitter plate determined in step S201 as the starting point, extending a straight line forward to the inlet position of the turbine engine passage to obtain a lower contraction section of the turbine engine passage;

[0021] Step S206, according to the turbine engine flow demand provided by the parallel TBCC combination engine, the physical throat area of ​​each state point of the turbine engine nozzle is calculated, and the minimum distance from the intersection of the middle splitter plate and the upper profile to the straight section of the rear half of the contraction section on the turbine engine channel is made equal to the physical throat height required by the turbine engine by rotating the middle splitter plate in the fully closed state, so as to obtain a two-dimensional model of the turbine engine nozzle;

[0022] Step S207: According to the span-wise width of the binary exhaust system, the two-dimensional model obtained in step S206 is stretched to obtain a three-dimensional model of the turbine engine nozzle.

[0023] Furthermore, the step S202 specifically includes:

[0024] Step S2021, with respect to the expansion profile of the ramjet engine channel nozzle, cutting on the profile to obtain the lower profile of the splitter plate;

[0025] Step S2022, taking 25% of the axial length of the middle splitter plate at the outlet of the turbine engine passage as the rear half of the upper profile of the splitter plate;

[0026] Step S2023, drawing a tangent line from the starting point of the rear half of the profile on the manifold plate through the rotation axis of the middle manifold plate as the front half of the profile on the manifold plate.

[0027] Furthermore, formula (1) is used to determine the physical throat area of ​​the nozzle, which is expressed as:

[0028]

[0029] In formula (1), γ is the specific heat ratio of the gas, R is the gas constant, and P t is the total inlet pressure, T t is the inlet total temperature, q(Ma) is the flow function, the function value is 1 at the throat section, A t That is, the required physical throat area of ​​the nozzle, It represents the mass flow rate of air flowing into the nozzle.

[0030] Furthermore, the step S3 specifically includes:

[0031] Step S301, with respect to the expansion profile of the ramjet nozzle, the lower half of the profile that has not been intercepted is used as a passive part of the adjustment mechanism;

[0032] Step S302, selecting 35% of the total length of the contraction section of the punching channel as a connecting rod, and then using the remaining part of the contraction section of the punching channel as a slide rail, and setting a hinge pin between the connecting rod and the slide rail, and connecting the connecting rod and the slide rail through the hinge pin;

[0033] Step S303, for the slide rail, firstly, upper and lower slide rail supports matching with it are respectively arranged above and below it, which include: a lower slide rail support and an upper slide rail support, and then a linear motor is arranged in front of the contraction section of the stamping channel to drive the slide rail so that the slide rail can move forward and backward.

[0034] Furthermore, the profiles of the lower support and the upper support of the slide rail are continuous smooth curved surfaces.

[0035] Furthermore, when the flow demand of the ramjet channel changes, the required physical throat area is calculated using formula (1), and then the linear motor drives the slide rail to move forward and backward, driving the connecting rod and the passive rod to rotate until the minimum distance between the hinge pin and the lower lip plate of the ramjet channel meets the physical throat height required by the ramjet nozzle.

[0036] The beneficial effects of the present invention are:

[0037] 1. The present invention does not have the problem of position interference between the two-channel adjustment mechanisms.

[0038] 2. The present invention can solve the problem of excessively large operating torque by optimizing the length of the connecting rod and the passive rod.

[0039] 3. The present invention maintains the horizontal state of the lower lip plate of the ramjet engine channel during the whole process, which is beneficial to reducing the asymmetry of the exhaust system and solving the intake and exhaust torque balancing problem existing in the design of the wide-range exhaust system. BRIEF DESCRIPTION OF THE DRAWINGS

[0040] Figure 1This is a schematic diagram of the structure of the unilateral expansion ramjet nozzle model provided in Example 1, wherein: Figure 1 a is the side view of the single-side expansion ramjet nozzle model. Figure 1 b is a three-dimensional diagram of a unilateral expansion ramjet nozzle;

[0041] Figure 2 A three-dimensional diagram of a parallel TBCC dual-channel exhaust system using a connecting rod articulation + slide rail + intermediate splitter plate adjustment solution provided in Example 1;

[0042] Figure 3 A lateral schematic diagram of a parallel TBCC dual-channel exhaust system in a turbine engine / ramjet engine joint working mode, provided in Example 1, which adopts a connecting rod articulation + slide rail + intermediate splitter plate adjustment solution;

[0043] Figure 4 A lateral schematic diagram of a parallel TBCC dual-channel exhaust system in a ramjet engine single working mode, provided in Example 1, which adopts a connecting rod articulation + slide rail + intermediate splitter plate adjustment solution;

[0044] In the attached figure:

[0045] 1-upper contraction section of the turbine engine channel, 2-upper expansion section of the turbine engine channel outlet, 3-rear half of the profile on the intermediate splitter plate, 4-front half of the profile on the intermediate splitter plate, 5-lower profile of the intermediate splitter plate, 6-passive rod, 7-hinge pin, 8-connecting rod, 9-slide rail, 10-lower lip plate of the ramjet engine channel, 11-lower support of the slide rail, 12-upper support of the slide rail, 13-lower contraction section of the turbine engine channel. DETAILED DESCRIPTION

[0046] In order to make the purpose, technical solution and advantages of the embodiments of the present invention clearer, the technical solution in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0047] Example 1

[0048] See also Figure 1-Figure 4 This embodiment provides a TBCC exhaust system design method based on the adjustment of the intermediate splitter plate. The design method is used to design a parallel TBCC dual-channel exhaust system using a connecting rod articulation + slide rail + intermediate splitter plate adjustment scheme. The method includes the following steps:

[0049] Step S1, designing an asymmetric unilateral expansion ramjet engine nozzle three-dimensional model, wherein the ramjet engine nozzle three-dimensional model includes: a contraction section, an expansion section and a side wall surface of the ramjet engine nozzle.

[0050] Specifically, in this embodiment, the step includes:

[0051] Step S101, obtaining a two-dimensional profile of a single-side expansion ramjet nozzle based on a design method of a characteristic line method and a two-dimensional maximum thrust nozzle theory;

[0052] Step S102: performing lateral stretching according to the span-wise width of the binary exhaust system to obtain a three-dimensional model of the unilateral expansion ramjet nozzle.

[0053] Step S2, designing a channel adjustment mechanism of a turbine engine and a three-dimensional model of a turbine engine nozzle, wherein the channel adjustment mechanism of the turbine engine adopts a structure of an intermediate splitter plate;

[0054] Specifically, in this embodiment, the step includes:

[0055] Step S201: for the ramjet engine nozzle three-dimensional model obtained in step S1, a position is selected as the rotation axis position of the middle splitter plate at the downstream of the ramjet engine nozzle throat, and then the axial length of the middle splitter plate is set;

[0056] Step S202, designing the profile of the middle manifold, wherein the profile of the middle manifold includes: a rear half 3 of the profile on the middle manifold, a front half 4 of the profile on the middle manifold, and a lower profile 5 of the middle manifold;

[0057] More specifically, in this embodiment, step S202 includes the following sub-steps:

[0058] Step S2021, with respect to the expansion profile of the ramjet engine channel nozzle, cutting on the profile to obtain the lower profile 5 of the splitter plate;

[0059] Step S2022, taking 25% of the axial length of the middle splitter plate at the outlet of the turbine engine passage as the rear half 3 of the upper profile of the splitter plate;

[0060] Step S2023, drawing a tangent line from the starting point of the rear half of the profile on the manifold plate through the middle manifold axis as the front half 4 of the profile on the manifold plate;

[0061] Step S203, with respect to the expansion profile of the ramjet engine channel nozzle, the upper half of the profile that has not been intercepted is used as the upper expansion section 2 of the turbine engine channel outlet;

[0062] Step S204, designing the upper contraction section 1 of the turbine engine channel, which includes: firstly determining the turbine engine channel nozzle inlet height according to the turbine engine combustion chamber outlet height, and then selecting a smooth curve to transition to the end point of the upper contraction section;

[0063] Step S205, taking the rotation axis position of the middle splitter plate determined in step S201 as the starting point, extending a straight line forward to the inlet position of the turbine engine passage to obtain the lower contraction section 13 of the turbine engine passage;

[0064] Step S206, according to the turbine engine flow demand provided by the parallel TBCC combination engine, the physical throat area of ​​each state point of the turbine engine nozzle is calculated, and the minimum distance from the intersection of the middle splitter plate and the upper profile to the straight section of the rear half of the contraction section on the turbine engine channel is made equal to the physical throat height required by the turbine engine by rotating the middle splitter plate in the fully closed state, so as to obtain a two-dimensional model of the turbine engine nozzle;

[0065] Step S207: According to the span-wise width of the binary exhaust system, the two-dimensional model obtained in step S206 is stretched to obtain a three-dimensional model of the turbine engine nozzle.

[0066] More specifically, in this embodiment, formula (1) is used to determine the physical throat area of ​​the nozzle, which is expressed as:

[0067]

[0068] In formula (1), γ is the specific heat ratio of the gas, R is the gas constant, and P t is the total inlet pressure, T t is the inlet total temperature, q(Ma) is the flow function, the function value is 1 at the throat section, A t That is, the required physical throat area of ​​the nozzle, It represents the mass flow rate of air flowing into the nozzle.

[0069] Step S3, designing a channel regulating mechanism of a ramjet engine, the channel regulating mechanism of the ramjet engine comprises: a motor, a slide rail, upper and lower supports of the slide rail, a connecting rod, a hinge pin and a passive rod, wherein the motor is used to provide power for the slide rail, one end of the slide rail is arranged in the upper and lower supports of the slide rail, and the other end thereof is connected to one end of the connecting rod, the other end of the connecting rod is connected to one end of the passive rod through the hinge pin, and the other end of the passive rod is connected to the rotating shaft of the middle diverter plate, and the rotation of the connecting rod and the passive rod is driven by controlling the forward and backward movement of the slide rail to realize the control of the channel flow of the turbine engine.

[0070] Specifically, in this embodiment, step S3 specifically includes:

[0071] Step S301: For the expansion profile of the ramjet nozzle, the lower half of the profile that has not been cut off is used as a passive component of the adjustment mechanism. In this embodiment, the passive component can be a passive rod 6 or other structural forms;

[0072] Step S302, selecting 35% of the total length of the contraction section of the aforementioned punching channel as the connecting rod 8, and then using the remaining part of the contraction section of the punching channel as the slide rail 9, and setting a hinge pin 7 between the connecting rod 8 and the slide rail 9, and connecting the connecting rod 8 and the slide rail 9 through the hinge pin 7;

[0073] Step S303, for the slide rail 9, firstly, supporting members matching with it are respectively arranged above and below it, which include: a lower support 11 of the slide rail and an upper support 12 of the slide rail, and then a linear motor is arranged in front of the contraction section of the stamping channel to drive the slide rail 9 so that the slide rail 9 can move forward and backward.

[0074] More specifically, in this embodiment, in order to ensure that the airflow cross section does not change suddenly, the support surface in the form of a traditional step is changed into a continuous smooth curved surface.

[0075] More specifically, when the flow demand of the ramjet channel changes, the required physical throat area is calculated using formula (1), and then the linear motor drives the slide rail 9 to move forward and backward, driving the connecting rod 8 and the passive rod 6 to rotate until the minimum distance between the hinge pin 7 and the lower lip plate 10 of the ramjet channel meets the physical throat height required by the ramjet nozzle.

[0076] More specifically, when the middle diverter plate rotates counterclockwise until the turbine channel is completely closed, and the slide rail 9 moves forward until the connecting rod 8 is horizontal with the slide rail 9, the upper expansion section 2 at the turbine engine channel outlet, the lower profile 5 of the middle diverter plate and the passive rod 6 together constitute the expansion section of the ramjet engine nozzle, and the connecting rod 8 and the slide rail 9 together constitute the contraction section of the ramjet engine nozzle.

[0077] Working principle:

[0078] according to Figure 3 and Figure 4 , with respect to the dual-channel exhaust system designed in this embodiment, its specific working process and the motion characteristics of the regulating mechanism are further described, including:

[0079] Initially, under low Mach number conditions, the parallel TBCC exhaust system is in a turbine engine / ramjet engine joint working mode, and correspondingly, there is gas flow through both channels in the figure. The flow demand of the turbine engine channel is achieved by rotating the middle diverter plate. The clockwise rotation of the diverter plate corresponds to an increase in the physical throat area, and the counterclockwise rotation of the diverter plate corresponds to a decrease in the physical throat area. The flow demand of the ramjet channel is achieved by the forward and backward movement of the slide rail 9 to drive the connecting rod 8 and the passive rod 6. The backward movement of the slide rail 9 corresponds to a decrease in the physical throat area, and the forward movement of the slide rail 9 corresponds to an increase in the physical throat area.

[0080] Then, as the flight altitude and speed of the aircraft increase, the parallel TBCC combination engine reaches the predetermined mode conversion point, at which time the exhaust system needs to change from the turbine engine / ramjet engine dual-channel joint working mode to the ramjet engine single-channel independent working mode. The specific implementation method is:

[0081] The middle splitter plate rotates counterclockwise until the profile 3 on the splitter plate is completely in surface contact with the straight section of the rear half of the upper contraction section 1 of the turbine engine passage. At the same time, the slide rail 9 moves forward to the maximum position until the slide rail 9 and the connecting rod 8 are completely horizontal. At this time, the straight-line distance between the hinge pin 7 and the lower lip plate 10 of the ramjet engine passage is exactly the designed throat height of the ramjet engine.

[0082] The passive rod 6, the lower profile of the splitter plate 5 and the profile of the upper expansion section 2 of the turbine engine nozzle are tightly closed to form Figure 1 The expansion section profile of the unilateral expansion ramjet nozzle in the ramjet engine enters the design state.

[0083] In summary, the present invention proposes a TBCC exhaust system design method based on the adjustment of the intermediate diverter plate, which uses a linear motor to drive the slide rail to move forward and backward, and drives the passive rod to rotate around the common rotating shaft through the connecting rod hinged to the slide rail to achieve the throat adjustment of the ramjet engine channel. The torque motor is used to drive the intermediate diverter plate to rotate around the common rotating shaft to achieve the throat adjustment and working mode conversion of the turbine engine channel. The problem of excessive operating torque and interference with the position of the intermediate diverter plate in the adjustment scheme based on the lower lip plate of the rotating ramjet engine channel is solved. The turbine engine / ramjet engine channel adjustment mechanism of this scheme has no conflict, and can meet the continuous flow adjustment requirements of the wide-range exhaust system; at the same time, the lower lip plate of the ramjet engine channel always remains in a horizontal state during the whole process, which is conducive to reducing the asymmetry of the exhaust system and alleviates the intake and exhaust torque balancing problem in the design of the wide-range exhaust system to a certain extent.

[0084] The matters not described in detail in the present invention are all known technologies to those skilled in the art.

[0085] The preferred specific embodiments of the present invention are described in detail above. It should be understood that a person skilled in the art can make many modifications and changes based on the concept of the present invention without creative work. Therefore, any technical solution that can be obtained by a person skilled in the art through logical analysis, reasoning or limited experiments based on the concept of the present invention on the basis of the prior art should be within the scope of protection determined by the claims.

Claims

1. A TBCC exhaust system design method based on intermediate splitter plate adjustment, characterized in that: The design method comprises the following steps: Step S1, designing an asymmetric unilateral expansion ramjet engine nozzle three-dimensional model, wherein the ramjet engine nozzle three-dimensional model includes: a contraction section, an expansion section and a side wall surface of the ramjet engine nozzle; Step S2, designing a channel adjustment mechanism of a turbine engine and a three-dimensional model of a turbine engine nozzle, wherein the channel adjustment mechanism of the turbine engine adopts a structure of an intermediate splitter plate; Step S3, designing a channel regulating mechanism of a ramjet engine, the channel regulating mechanism of the ramjet engine comprises: a motor, a slide rail, upper and lower supports of the slide rail, a connecting rod, a hinge pin and a passive rod, wherein the motor is used to provide power for the slide rail, one end of the slide rail is arranged in the upper and lower supports of the slide rail, and the other end thereof is connected to one end of the connecting rod, the other end of the connecting rod is connected to one end of the passive rod through the hinge pin, and the other end of the passive rod is connected to the rotating shaft of the middle diverter plate, and the connecting rod and the passive rod are driven to rotate by controlling the forward and backward movement of the slide rail, so as to realize the control of the channel flow of the ramjet engine; The step S2 specifically includes: Step S201: for the ramjet engine nozzle three-dimensional model obtained in step S1, a position is selected as the rotation axis position of the middle splitter plate at the downstream of the ramjet engine nozzle throat, and then the axial length of the middle splitter plate is set; Step S202, designing the profile of the middle manifold, wherein the profile of the middle manifold includes: the rear half of the profile on the middle manifold, the front half of the profile on the middle manifold, and the lower profile of the middle manifold; Step S203, with respect to the expansion profile of the ramjet engine channel nozzle, the upper half of the profile that has not been intercepted is used as the upper expansion section of the turbine engine channel outlet; Step S204, designing an upper contraction section of the turbine engine channel, which includes: firstly determining the turbine engine channel nozzle inlet height according to the turbine engine combustion chamber outlet height, and then selecting a smooth curve to transition to the end point of the upper contraction section; Step S205, taking the rotation axis position of the middle splitter plate determined in step S201 as the starting point, extending a straight line forward to the inlet position of the turbine engine passage to obtain a lower contraction section of the turbine engine passage; Step S206, according to the turbine engine flow demand provided by the parallel TBCC combination engine, the physical throat area of ​​each state point of the turbine engine nozzle is calculated, and the minimum distance from the intersection of the middle splitter plate and the upper profile to the straight section of the rear half of the contraction section on the turbine engine channel is made equal to the physical throat height required by the turbine engine by rotating the middle splitter plate in the fully closed state, so as to obtain a two-dimensional model of the turbine engine nozzle; Step S207: According to the span-wise width of the binary exhaust system, the two-dimensional model obtained in step S206 is stretched to obtain a three-dimensional model of the turbine engine nozzle.

2. A TBCC exhaust system design method based on intermediate splitter plate adjustment according to claim 1, characterized in that: The step S1 specifically includes: Step S101, obtaining a two-dimensional profile of a single-side expansion ramjet nozzle based on a design method of a characteristic line method and a two-dimensional maximum thrust nozzle theory; Step S102: performing lateral stretching according to the span-wise width of the binary exhaust system to obtain a three-dimensional model of the unilateral expansion ramjet nozzle.

3. A TBCC exhaust system design method based on intermediate splitter plate adjustment according to claim 1, characterized in that: The step S202 specifically includes: Step S2021, with respect to the expansion profile of the ramjet engine channel nozzle, cutting on the profile to obtain the lower profile of the splitter plate; Step S2022, taking 25% of the axial length of the middle splitter plate at the outlet of the turbine engine passage as the rear half of the upper profile of the splitter plate; Step S2023, drawing a tangent line from the starting point of the rear half of the profile on the manifold plate through the rotation axis of the middle manifold plate as the front half of the profile on the manifold plate.

4. A TBCC exhaust system design method based on intermediate splitter plate adjustment according to claim 3, characterized in that: Formula (1) is used to determine the physical throat area of ​​the nozzle, expressed as: In formula (1), γ is the specific heat ratio of the gas, R is the gas constant, and P t is the total inlet pressure, T t is the inlet total temperature, q(Ma) is the flow function, the function value is 1 at the throat section, A t That is, the required physical throat area of ​​the nozzle, It represents the mass flow rate of air flowing into the nozzle.

5. A TBCC exhaust system design method based on intermediate splitter plate adjustment according to claim 4, characterized in that: The step S3 specifically includes: Step S301, with respect to the expansion profile of the ramjet nozzle, the lower half of the profile that has not been intercepted is used as a passive part of the adjustment mechanism; Step S302, selecting 35% of the total length of the contraction section of the punching channel as a connecting rod, and then using the remaining part of the contraction section of the punching channel as a slide rail, and setting a hinge pin between the connecting rod and the slide rail, and connecting the connecting rod and the slide rail through the hinge pin; Step S303, for the slide rail, firstly, upper and lower slide rail supports matching with it are respectively arranged above and below it, which include: a lower slide rail support and an upper slide rail support, and then a linear motor is arranged in front of the contraction section of the stamping channel to drive the slide rail so that the slide rail can move forward and backward.

6. A TBCC exhaust system design method based on intermediate splitter plate adjustment according to claim 5, characterized in that: The profiles of the lower support of the slide rail and the upper support of the slide rail are continuous smooth curved surfaces.

7. A TBCC exhaust system design method based on intermediate splitter plate adjustment according to claim 6, characterized in that: When the flow demand of the ramjet channel changes, the required physical throat area is calculated using formula (1), and then the linear motor drives the slide rail to move forward and backward, driving the connecting rod and the passive rod to rotate until the minimum distance between the hinge pin and the lower lip plate of the ramjet channel meets the physical throat height required by the ramjet nozzle.

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