Design method of distributed adjustable TBCC inlet flow control device

Abstract

The invention relates to a design method of a distributed adjustable TBCC inlet flow control device, and relates to aerospace. According to the requirements of hypersonic aircraft, an adjustable inner rotating TBCC inlet is designed, and a binary structure adjustment component is adopted to ensure the rotational adjustability of the structure. In order to avoid the sudden jump phenomenon of the end shock wave in the channel near the channel entrance, a distributed adjustable rotating plate is arranged on the adjustable upper wall of the turbine channel, and a connected distributed adjustable rotating plate is arranged between the lower wall of the turbine channel and the upper wall of the ram channel, and the pressure signal transmitted by the pressure sensor arranged in each channel is used to control it; the adjustable rotating plate is flexibly controlled to open and close by the pressure signal, and a distributed discharge groove is formed to suppress the sudden jump phenomenon of the end shock wave in the channel, avoid the instability of the channel operation, eliminate the low-energy boundary layer, and weaken the shock wave / boundary layer interference phenomenon in the channel. The distributed discharge groove enhances the channel's anti-backpressure capability and improves the working stability and working margin of the inlet.

Description

Technical Field

[0001] The present invention relates to the field of aerospace technology, and in particular to a design method for a distributed adjustable TBCC inlet flow control device based on a pressure signal. Background Art

[0002] With the continuous development of aerospace technology, air-breathing hypersonic aircraft with wide speed range and horizontal take-off and landing have become an important research field for future aircraft. In order to achieve horizontal take-off and landing with wide speed range, the turbine-based combined cycle (TBCC) propulsion system came into being. Combining turbine engines suitable for low-speed operation and ramjet engines suitable for high-speed operation, these two types of engines can give full play to their advantages in each adaptive working range, forming a combined propulsion system with wide speed range continuous operation characteristics, and promoting the development of wide speed range aircraft.

[0003] As one of the important components of the air-breathing propulsion system, the performance and efficiency of the inlet have a significant impact on the combustion chamber. For the combined engine inlet, in order to provide stable and high-quality airflow to the combined cycle engine in a wide Mach number range, the inlet needs to rely on the change of its own shape during flight to adapt to the changes in flight conditions. ([1] Li Jiaxin. Research on the Inward Adjustable Inlet of Combined Power [D]. Nanjing University of Science and Technology, 2019. DOI: 10.27241 / d.cnki.gnjgu.2019.000680.) In recent years, the three-dimensional inward-turning inlet has been widely studied due to its small frontal area, high compression efficiency, high flow capture coefficient and total pressure recovery coefficient. Therefore, in order to make full use of the many advantages of the inward-turning inlet and broaden its working speed range, many research units have carried out research on the TBCC inlet based on the inward-turning inlet, aiming to improve the performance and efficiency of the combined inlet. Among them, the adjustable components of the inward-turned TBCC air intake duct are mainly of a binary structure to ensure the airtightness and structural stability of the overall structure during the adjustment process.

[0004] When the inlet is in operation, due to the high pressure generated by the combustion in the combustion chamber being transmitted forward, a complex tail shock wave or shock wave string will be generated in the channel to match the higher pressure at the outlet. As the outlet pressure increases, the tail shock wave gradually moves toward the channel entrance, and at the same time interferes with the boundary layer of the channel wall and produces complex interference phenomena. In the internal TBCC inlet, when the tail shock wave is pushed out of the channel entrance, the inlet will not work properly. In addition, when the tail shock wave is affected by the large fluctuation of the outlet pressure or interferes with the background in the channel, it will produce a sudden jump phenomenon, which will lead to the inlet's working instability, which will cause the propulsion system to stop working and fail to provide sufficient thrust, which will seriously affect the safe operation of the aircraft.

[0005] In order to control the tail shock wave in the channel and avoid the sudden jump of the tail shock wave in the channel, it is necessary to actively control the dynamic characteristics of the tail shock wave and improve the flow structure in the channel to ensure the stability of the inlet operation. Therefore, providing a design method for an adjustable component with a simple structure and easy to set up for flow control is of great significance to improving the performance of the inlet. Summary of the invention

[0006] The purpose of the present invention is to address the above-mentioned problems existing in the prior art and to provide a design method for a distributed adjustable TBCC inlet duct flow control device based on a pressure signal. By feedback from the wall pressure signal, the distributed adjustable components arranged on the channel are controlled to improve the flow state in the channel, suppress the tail shock wave, and improve the working stability and working margin of the inlet duct.

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

[0008] The distributed adjustable TBCC inlet flow control device based on pressure signals of the present invention comprises an adjustable compression section of an inner TBCC inlet, an adjustable turbine channel, a ram channel, a distributed adjustable rotating plate and a pressure monitoring sensor; the design method comprises the following steps:

[0009] 1) Design of the basic flow field with double incident shock waves: The basic flow field is an indispensable condition for designing the inward-turning inlet. According to the flight envelope of the aircraft, the design point of the basic flow field is selected, and the basic flow field with double incident shock waves is designed according to the constraints under the design state;

[0010] 2) Design of an adjustable compression section of an inward-rotating TBCC inlet: Based on the given inlet inlet shape, the streamline tracing technique is used to generate an inlet compression section with two-stage compression characteristics in the double-incident shock wave basic flow field; the model is modified, and the second-stage compression profile of the compression section is set as a rotatable front splitter, the rotation axis position is the starting position of the second-stage compression profile, and the rotation angle is the second-stage compression angle; the second-stage compression profile is rotated to be parallel to the first-stage compression profile to form the inlet of the turbine channel, and the opening and closing of the turbine channel is controlled by rotating the second-stage compression profile;

[0011] 3) Design of adjustable turbine channel: The turbine channel is composed of an adjustable expansion section and a non-adjustable expansion section; the adjustable expansion section maintains binary characteristics to ensure the adjustability of the structure; the upper wall of the adjustable expansion section is set as a rotatable rear splitter plate, which works in conjunction with the adjustable second-stage compression profile to ensure the smooth transition of the profile of the turbine channel during the adjustment process; in the turbine mode, the front splitter plate and the rear splitter plate are connected and transitioned; in the stamping mode, the front splitter plate is gradually closed, and the rear splitter plate is completely closed, and fits tightly with the lower wall of the turbine channel; the non-adjustable expansion section controls the centerline trend and area change law through the given inlet and outlet shapes;

[0012] 4) Design of stamping channel: The stamping channel is a fixed geometric surface. In order to facilitate the setting of flow control components, the front section is controlled to be a rectangular shape. Then, according to the inlet and outlet geometric shapes, the center line and area change law are controlled to generate the stamping channel surface;

[0013] 5) Design of distributed adjustable rotating plates: To ensure their rotation, the distributed adjustable rotating plates are designed to be rectangular; the distributed adjustable rotating plates are arranged at the free end of the rear splitter plate, between the lower wall of the turbine channel and the upper wall of the ram channel; the total length of the distributed adjustable rotating plates accounts for 5% to 10% of the total length of each working channel, and is close to the inlet end of the channel. The distance between two adjacent adjustable rotating plates should be greater than or equal to the width of the rotating plates themselves, so as to reduce the impact on the flow characteristics of the mainstream area in the channel;

[0014] 6) Arrangement of pressure monitoring sensors: The distributed adjustable rotating plate is controlled by a pressure signal, and its function is to open the discharge groove by rotation, thereby controlling the rapid forward movement of the end shock wave in the channel to ensure the stability of the inlet operation; at the same time, the distributed discharge groove formed can remove the boundary layer on the inner wall of the channel, enhance the energy of the near-wall airflow, and improve the channel's ability to resist back pressure; therefore, it is necessary to arrange pressure sensors for detecting the position of the end shock wave in the channel, which are arranged on the upper and lower walls of the turbine channel and the upper wall of the ram channel, respectively, and are located close to but behind the distributed adjustable rotating plate to ensure that the pressure signal of the end shock wave is monitored to control the adjustable plate;

[0015] 7) Design a control method for the distributed adjustable rotating plate: When the pressure at the pressure monitoring point in the channel suddenly increases or reaches a preset value, it indicates that the ending shock wave has reached or even exceeded the monitoring point. At this time, the distributed adjustable rotating plate enters the early warning mode, and the adjustable rotating plate of the corresponding channel opens to control the dynamic characteristics of the ending shock wave; when the pressure at the pressure monitoring point returns to normal, the adjustable rotating plate returns to normal, and the closure smoothly transitions with the channel profile.

[0016] In turbine mode, when the pressure sensor in the channel detects the pressure signal of the ending shock wave, the distributed adjustable rotating plate on the upper wall of the turbine channel opens counterclockwise to the outside of the channel to form a distributed leakage groove, and the adjustable rotating plate on the lower wall of the turbine channel opens clockwise to the outside of the channel to form a ventilation groove connected with the ram channel. The leakage groove on the upper wall of the turbine channel removes the boundary layer near the wall and suppresses the rapid movement of the ending shock wave; the ventilation grooves on the lower wall of the turbine channel and the upper wall of the ram channel can fully suppress the dynamic characteristics of the ending shock wave on the lower wall.

[0017] In the ram mode, the turbine channel stops working, the rear splitter plate of the turbine channel fits tightly with the lower wall of the turbine channel, and the distributed adjustable plate on the upper wall of the turbine channel no longer works and is completely closed. When the pressure sensor in the ram channel detects the pressure signal of the ending shock wave, the adjustable rotating plate on the lower wall of the turbine channel opens clockwise to the outside of the channel, and a distributed discharge groove is formed with the upper wall of the ram channel, which can remove the boundary layer at the inlet end of the ram channel, and at the same time suppress the dynamic characteristics of the ending shock wave in the ram channel to ensure the stable operation of the inlet.

[0018] Compared with the prior art, the technical solution of the present invention has the following beneficial effects:

[0019] The inner rotating TBCC inlet has two working modes: turbine mode and ramjet mode. Compared with the traditional fixed flow control structure, the present invention mainly provides a design method for a distributed adjustable rotating plate based on a pressure signal, which can control the distributed adjustable rotating plate according to different modes, and open an appropriate number of adjustable rotating plates according to the working conditions and the intensity of the ending shock wave. At the same time, when the ending shock wave does not affect the working stability of the inlet, the adjustable rotating plate can be restored to its original state to maintain the smooth transition of the aerodynamic surface of the inlet. It has good adjustment ability, high fault tolerance, and more sensitive flow field control. In addition, the discharge groove formed by the adjustable diverter plate can exclude part of the boundary layer, thereby increasing the momentum and energy of the near-wall flow field, so that the channel's ability to resist back pressure is improved, and the working stability of the inlet is improved. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 is the basic flow field of contraction in the double-incident shock wave. Figure 1 In the figure, (a) is a schematic diagram of the shock wave mechanism, and (b) is a cloud diagram of the Mach number distribution.

[0021] Figure 2 The TBCC inlet has an adjustable compression section. Figure 2 In the figure, (a) is the compression section of the modified two-stage compression, and (b) is the compression section of the single-stage compression in the turbine mode.

[0022] Figure 3 Schematic diagram of the aerodynamic model of the inward-turning TBCC inlet.

[0023] Figure 4 Schematic diagram of a distributed adjustable rotating plate. Figure 4 In the figure, (a) is an overall view, (b) is a partial enlarged view when the adjustable rotating plate is in a fully closed state, and (c) is a partial enlarged view when the adjustable rotating plate is in an open state.

[0024] Figure 5 It is a partial schematic diagram of the working state of the distributed adjustable rotating plate and the boundary layer airflow trend under the turbine mode.

[0025] Figure 6 It is a partial schematic diagram of the working state of the distributed adjustable rotating plate and the boundary layer airflow trend under the adopted mode.

[0026] The marks in the figure are: 1 represents the first incident shock wave, 2 represents the second incident shock wave, 3 represents the reflected shock wave, 4 represents the center body height, 5 represents the inlet profile of the inner turn inlet duct, 6 represents the first stage compression plane, 7 represents the second stage adjustable compression profile axis, 8 represents the second stage adjustable compression profile, 9 represents the inlet shape of the ram channel, 10 represents the inlet shape of the turbine channel, 11 represents the lip of the inner turn inlet duct, 12 represents the compression profile under the turbine mode, 13 represents the turbine channel adjustable expansion section splitter, 14 represents the turbine channel adjustable section splitter axis, 15 represents the turbine channel non-adjustable expansion section, 16 represents The outlet shape of the turbine channel, 17 represents the outlet shape of the ram channel, 18 represents the aerodynamic surface of the ram channel, 19 represents the position of the turbine channel adjustable expansion section diverter plate when closed, 20 represents the distributed adjustable rotating plate on the upper wall of the turbine channel, 21 represents the section of the layout position of the turbine channel pressure sensor, 22 represents the section of the layout position of the ram channel pressure sensor, 23 represents the distributed adjustable rotating plate on the lower wall of the turbine channel, 24 represents the boundary layer airflow on the upper wall of the turbine channel under the turbine mode, 25 represents the boundary layer airflow on the upper wall of the ram channel under the turbine mode, and 26 represents the boundary layer airflow on the upper wall of the turbine channel under the ram mode. DETAILED DESCRIPTION

[0027] In order to make the technical problems, technical solutions and beneficial effects to be solved by the present invention clearer and more understandable, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments.

[0028] The present invention includes the design of an inwardly rotating adjustable TBCC air inlet and a distributed adjustable flow control device. According to the requirements of hypersonic aircraft, an adjustable inwardly rotating TBCC air inlet is designed, and a binary structure adjustment component is adopted to ensure the rotational adjustability of the structure. In order to avoid the sudden jump phenomenon of the end shock wave in the channel near the channel entrance, a distributed adjustable rotating plate is arranged on the adjustable upper wall of the turbine channel, and a connected distributed adjustable rotating plate is arranged between the lower wall of the turbine channel and the upper wall of the ram channel, and the pressure signal transmitted by the pressure sensor arranged in each channel is used to control it; the opening and closing of the adjustable rotating plate can be flexibly controlled by the pressure signal, and the distributed leakage groove formed can not only suppress the sudden jump phenomenon of the end shock wave in the channel and avoid the instability of the channel operation, but also eliminate the low-energy boundary layer to a certain extent, and weaken the shock wave / boundary layer interference phenomenon in the channel. The distributed leakage groove can enhance the channel's anti-backpressure capability and improve the working stability and working margin of the air inlet.

[0029] The specific design method of the present invention comprises the following steps:

[0030] Design the double-incident shock wave internal contraction basic flow field: Figure 1 As shown, firstly, according to the flight envelope of the aircraft, the design points of the basic flow field are selected. According to the constraints under the design state, the curved shock characteristic line method (MOCC) is used to design the inward-contracting basic flow field with double incident shock waves. The basic flow field includes the first incident shock wave 1, the second incident shock wave 2, the reflected shock wave 3 and the center body height 4.

[0031] Design of the adjustable compression section of the inward-turning TBCC inlet: Based on the given inlet inlet shape, the streamline tracking technology is used to generate the compression section in the double-incidence shock wave basic flow field, and the inlet shape is projected in the flow field to track the inlet profile of the inward-turning inlet 5. After the model is trimmed, Figure 2 As shown in the middle figure (a), the starting point of the second incident shock wave 2 is set to the second-stage adjustable compression profile axis 7, and the first-stage compression profile 6 and the second-stage adjustable compression profile 8 form a compression section with two-stage compression characteristics. The second-stage adjustable compression profile 8 is rotated around the second-stage adjustable compression profile axis 7 to be parallel to the first-stage compression profile 6, as shown in FIG. Figure 2 As shown in Figure (b), a turbine channel inlet shape 10 is formed. At this time, since the second-stage adjustable compression surface 8 rotates upward to become a compression surface 12 in the turbine mode, the design of the adjustable compression section is completed.

[0032] Design an adjustable turbine channel: The turbine channel consists of an adjustable expansion section and a non-adjustable expansion section. The adjustable expansion section maintains a binary characteristic to ensure the adjustability of the structure. The upper wall of the adjustable expansion section is set as a turbine channel adjustable expansion section diverter plate 13, and the end of the upper wall of the adjustable expansion section is set as a turbine channel adjustable section diverter plate rotating shaft 14. Among them, the second-stage adjustable compression surface 8 works together with the turbine channel adjustable expansion section diverter plate 13 to control the opening and closing of the turbine channel to ensure that the modal conversion process proceeds smoothly. In the stamping mode, the turbine channel adjustable expansion section diverter plate is closed when the position 19 is as shown in FIG. Figure 3 According to the shape of the end of the adjustable expansion section and the shape of the turbine channel outlet 16, the non-adjustable expansion section 15 of the turbine channel is generated by controlling the trend of the center line and the law of area change.

[0033] Design of the stamping channel: In order to facilitate matching with the distributed adjustable rotating plate 23 on the lower wall of the turbine channel, the upper wall of the front section of the stamping channel aerodynamic surface 18 is controlled to be a rectangular shape, and then according to the stamping channel inlet shape 9 and the stamping channel outlet shape 17, the stamping channel aerodynamic surface 18 is generated by controlling the center line and area change law.

[0034] Design of distributed adjustable rotating plate includes the following points:

[0035] Design the shape and size of the distributed adjustable rotating plate: Figure 4 As shown, the distributed adjustable rotating plate is designed as a rectangle for easy rotation and adjustment. The span length of the adjustable rotating plate is 80% to 85% of the diverter plate. The flow direction size is determined according to the specific size of the model. The flow direction distance between adjacent adjustable rotating plates is 1.2 to 1.5 times the width of the rotating plate to reduce the impact of the rotating plate on the flow in the mainstream area after it is opened. The distribution length of the distributed adjustable components accounts for 5% to 10% of the total length of each working channel, and the safety margin of the inlet operation is improved through flow control. The number of distributed adjustable rotating plates in the figure can be designed according to the actual model. According to the technology to be realized by the present invention, the purpose of setting the distributed adjustable rotating plate is to suppress the movement of the end shock wave in the channel to improve the stability of the inlet operation and the ability to resist back pressure. Therefore, corresponding structures are arranged on the upper wall, lower wall and upper wall of the turbine channel and the ram channel.

[0036] Working form of pressure monitoring sensor and distributed adjustable rotating plate: According to the technology to be realized by the present invention, the distributed adjustable rotating plate arranged on the channel wall is controlled by pressure signal. The monitoring point detects a sudden rise in pressure, indicating that the ending shock wave has reached or even passed the monitoring point, and the movement of the distributed adjustable rotating plate is controlled by the pressure signal, such as Figure 4 If the monitoring point does not detect the pressure surge signal, the distributed adjustable rotating plate will not be adjusted, such as Figure 4 As shown in Figure (b). Figure 4Figure (a) shows the reference positions of the turbine channel pressure sensor layout position section 21 and the ram channel pressure sensor layout position section 22. The actual specific positions can be designed according to specific needs and can be arranged on the upper and lower walls and side walls of the channel respectively to improve the accuracy of monitoring the end shock wave.

[0037] Working mode of the distributed adjustable rotating plate in turbine mode: In turbine mode, when the pressure sensor detects a sudden pressure signal, the distributed adjustable rotating plate 20 on the upper wall of the turbine channel rotates upward, and the distributed adjustable rotating plate 23 on the lower wall of the turbine channel rotates downward. Figure 5 As shown. A distributed leakage groove is formed on the upper wall of the turbine channel. The boundary layer airflow 24 on the upper wall of the turbine channel in the turbine mode is discharged through the distributed leakage groove, which improves the airflow energy in the near-wall area and enhances the channel's ability to resist back pressure. At the same time, the distributed leakage groove can suppress the rapid forward movement of the ending shock wave and improve the safety margin of the inlet operation. A connected ventilation groove is formed between the lower wall of the turbine channel and the upper wall of the ram channel. At this time, the boundary layer airflow 25 on the upper wall of the ram channel in the turbine mode is blown into the lower wall of the turbine channel, which improves the airflow energy in the near-wall area and also achieves the effect of enhancing the ability to resist back pressure and suppressing the ending shock wave.

[0038] Working mode of the distributed adjustable rotating plate in the stamping mode: In the stamping mode, the turbine channel is no longer working, and the turbine channel adjustable expansion section diverter plate 13 has been closed and is located at the turbine channel adjustable expansion section diverter plate closed position 19, such as Figure 6 As shown in , the dotted line is the corresponding position in the turbine mode. At this time, the distributed adjustable rotating plate 23 on the lower wall of the turbine channel keeps rotating downward to form a discharge groove with the upper wall of the ram channel. The boundary layer airflow 26 on the upper wall of the turbine channel in the ram mode is discharged to the turbine channel through the discharge groove, which increases the airflow energy in the near-wall area of ​​the channel to enhance the anti-backpressure capability of the ram channel. At the same time, the formed discharge groove can suppress the rapid movement of the end shock wave in the ram channel, ensuring the stable operation of the inlet in the ram mode.

[0039] The present invention provides a design method for a distributed adjustable TBCC inlet flow control device based on a pressure signal, which adopts a distributed adjustable rotating plate based on a pressure signal to form a distributed leakage groove to remove the boundary layer, improve the momentum and energy of the airflow near the wall, and achieve the purpose of controlling the end shock wave in the channel. When the end shock wave does not affect the stable operation of the inlet, the adjustable rotating plate can be restored to its original state to maintain the smooth transition of the aerodynamic surface of the inlet. The structure has good adjustment ability, high fault tolerance, and more sensitive flow field control. At the same time, it can also enhance the channel's ability to resist back pressure, improve the working stability and safety margin of the inlet.

Claims

1. The design method of the distributed adjustable TBCC inlet flow control device is characterized by A distributed adjustable TBCC inlet flow control device based on pressure signals comprises an adjustable compression section of an inner TBCC inlet, an adjustable turbine channel, a ram channel, a distributed adjustable rotating plate and a pressure monitoring sensor; the design method comprises the following steps: 1) Design of the basic flow field with double incident shock waves: The basic flow field is an indispensable condition for designing the inward-turning inlet. According to the flight envelope of the aircraft, the design point of the basic flow field is selected, and the basic flow field with double incident shock waves is designed according to the constraints under the design state; 2) Design of an adjustable compression section of an inward-rotating TBCC inlet: Based on the given inlet inlet shape, the streamline tracing technique is used to generate an inlet compression section with two-stage compression characteristics in the double-incident shock wave basic flow field; the model is modified, and the second-stage compression profile of the compression section is set as a rotatable front splitter, the rotation axis position is the starting position of the second-stage compression profile, and the rotation angle is the second-stage compression angle; the second-stage compression profile is rotated to be parallel to the first-stage compression profile to form the inlet of the turbine channel, and the opening and closing of the turbine channel is controlled by rotating the second-stage compression profile; 3) Design of adjustable turbine channel: The turbine channel is composed of an adjustable expansion section and a non-adjustable expansion section; the adjustable expansion section maintains binary characteristics to ensure the adjustability of the structure; the upper wall of the adjustable expansion section is set as a rotatable rear splitter plate, which works in conjunction with the adjustable second-stage compression profile to ensure the smooth transition of the profile of the turbine channel during the adjustment process; in the turbine mode, the front splitter plate and the rear splitter plate are connected and transitioned; in the stamping mode, the front splitter plate is gradually closed, and the rear splitter plate is completely closed, and fits tightly with the lower wall of the turbine channel; the non-adjustable expansion section controls the centerline trend and area change law through the given inlet and outlet shapes; 4) Design of stamping channel: The stamping channel is a fixed geometric surface. In order to facilitate the setting of flow control components, the front section is controlled to be a rectangular shape. Then, according to the inlet and outlet geometric shapes, the center line and area change law are controlled to generate the stamping channel surface; 5) Design of distributed adjustable rotating plates: To ensure their rotation, the distributed adjustable rotating plates are designed to be rectangular; the distributed adjustable rotating plates are arranged at the free end of the rear splitter plate, between the lower wall of the turbine channel and the upper wall of the ram channel; the total length of the distributed adjustable rotating plates accounts for 5% to 10% of the total length of each working channel, and is close to the inlet end of the channel. The distance between two adjacent adjustable rotating plates should be greater than or equal to the width of the rotating plates themselves, so as to reduce the impact on the flow characteristics of the mainstream area in the channel; 6) Arrangement of pressure monitoring sensors: The distributed adjustable rotating plate is controlled by a pressure signal, and its function is to open the discharge groove by rotation, thereby controlling the rapid forward movement of the end shock wave in the channel to ensure the stability of the inlet operation; at the same time, the distributed discharge groove formed can remove the boundary layer on the inner wall of the channel, enhance the energy of the near-wall airflow, and improve the channel's ability to resist back pressure; therefore, it is necessary to arrange pressure sensors for detecting the position of the end shock wave in the channel, which are arranged on the upper and lower walls of the turbine channel and the upper wall of the ram channel, respectively, and are located close to but behind the distributed adjustable rotating plate to ensure that the pressure signal of the end shock wave is monitored to control the adjustable plate; 7) Design a control method for the distributed adjustable rotating plate: When the pressure at the pressure monitoring point in the channel suddenly increases or reaches a preset value, it indicates that the ending shock wave has reached or even exceeded the monitoring point. At this time, the distributed adjustable rotating plate enters the early warning mode, and the adjustable rotating plate of the corresponding channel opens to control the dynamic characteristics of the ending shock wave; when the pressure at the pressure monitoring point returns to normal, the adjustable rotating plate returns to normal, and the closure smoothly transitions with the channel profile.

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