A hybrid laminar and shock buffet control method based on blowing and suction

Abstract

The application discloses a hybrid laminar flow and shock buffet composite control method based on blowing and suction, belongs to the field of active flow control or regulation of an aircraft, and aims to solve the problem that, under the premise of realizing the technology effect of lift increase and drag reduction, the boundary layer separation resistance is greatly weakened due to the laminar flow control, resulting in the increase of the buffet intensity. The method comprises the following steps: S1, a suction mode: under the negative pressure effect of an ejector type vacuum generator, the airflow at the leading edge of a wing enters the ejector type vacuum generator through a porous skin, a gas through hole on a skin support, a channel, a first gas pipeline and a first suction port in sequence; the gas in the ejector type vacuum generator is discharged through a third exhaust port and a third gas pipeline in sequence; S2, a blowing mode: the gas in the ejector type vacuum generator is discharged through the first suction port, the first gas pipeline, the channel, the gas through hole on the skin support and the porous skin in sequence.

Description

Technical Field

[0001] This application relates to the field of active flow control for aircraft, specifically a composite control method based on mixed laminar flow and shock wave buffeting based on blowing and sucking air. Background Technology

[0002] As large passenger aircraft currently pursue both increased lift and reduced drag, energy conservation and emission reduction for economic benefits, as well as higher flight safety, drag reduction and range extension and expanding flight safety boundaries have become major key issues in the development of large aircraft.

[0003] To address the needs of large passenger aircraft for increased lift and reduced drag, as well as energy conservation and emission reduction, laminar flow control of airfoils is a commonly used and effective technical approach. Laminar flow control of airfoils achieves this by expanding the laminar flow region with low frictional drag and reducing the turbulent flow region with high frictional drag. Laminar flow control methods mainly include: Natural Laminar Flow Control (NLFC) through hull optimization design, and Full Laminar Flow Control (FLFC) with full surface air intake. Among these, Hybrid Laminar Flow Control (HLFC), based on NLFC and using localized air intake at the leading edge to remove initial disturbances and achieve a larger laminar flow region, is considered the most promising laminar flow control method.

[0004] During flight, when the angle of attack becomes too large, reaching the buffeting initiation angle, the aircraft will buffet. Once buffeting occurs, the boundary layer becomes unstable, and the shock wave oscillates back and forth, causing periodic oscillations in the aircraft's lift, drag, and pitch moments. This can range from minor passenger discomfort and damage to transported goods to severe overload causing structural damage and ultimately, a crash. Therefore, it is generally required that the buffeting initiation angle of attack be at least 1.3 times the maximum flight angle of attack.

[0005] However, due to the effect of laminar flow control, the boundary layer's resistance to separation is greatly weakened, leading to increased chattering intensity and a lower chattering boundary, making accidents more likely. Sacrificing safety for a slight performance improvement is unacceptable.

[0006] Therefore, there is an urgent need for a new method and / or apparatus to solve the above problems. Summary of the Invention

[0007] The purpose of this invention is to address the problem that existing hybrid laminar flow control methods, while achieving lift enhancement and drag reduction, significantly weaken the boundary layer's anti-separation capability due to laminar flow control, leading to increased buffeting intensity. This invention provides a combined control method based on blowing and sucking air, integrating hybrid laminar flow and shock wave buffeting. This invention not only achieves the technical effects of lift enhancement and drag reduction for aircraft but also effectively solves the conflict between HLFC and flight safety in practical applications, ensuring flight safety and possessing significant application value.

[0008] To achieve the above objectives, this application adopts the following technical solution.

[0009] A combined control method for laminar flow and shock wave buffeting based on blowing and suction includes the following steps: S1, Inhalation Mode When the wing needs to take in air, the high-pressure air source outputs high-pressure airflow to the ejector vacuum generator and creates a negative pressure at the first air intake. Under the negative pressure of the ejector vacuum generator, the airflow at the leading edge of the wing enters the ejector vacuum generator sequentially through the porous skin, the gas passage on the skin support, the channel, the first gas pipe, and the first air intake. The gas entering the ejector vacuum generator is discharged sequentially through the third exhaust port and the third gas pipe; S2, Blowing Mode When the wing needs to blow air, the high-pressure air source outputs high-pressure airflow to the ejector vacuum generator, and the gas in the ejector vacuum generator cannot be discharged through the third exhaust port and the third gas pipe. The gas inside the ejector vacuum generator is discharged sequentially through the first intake port, the first gas pipe, the channel, the gas through hole on the skin support, and the porous skin. S3. According to the flight requirements of the aircraft, switch between steps S1 and S2 to realize the composite control of mixed laminar flow and shock wave fluttering based on blowing and sucking.

[0010] In step S1, when the wing needs to take in air, the first valve, the second valve, and the third valve are opened, and the high-pressure air source outputs high-pressure airflow to the ejector vacuum generator, and a negative pressure is formed at the first air intake. Under the negative pressure of the ejector vacuum generator, the airflow at the leading edge of the wing enters the ejector vacuum generator sequentially through the porous skin, the gas passage on the skin support, the channel, the first gas pipe, and the first air intake. The gas entering the ejector vacuum generator is discharged sequentially through the third exhaust port and the third gas pipe; In step S2, when the wing needs to blow air, the third valve is closed and the first and second valves are opened. The high-pressure gas source outputs high-pressure airflow to the ejector vacuum generator, and the gas in the ejector vacuum generator cannot be discharged through the third exhaust port and the third gas pipe. The gas inside the ejector vacuum generator is discharged sequentially through the first intake port, the first gas pipe, the channel, the gas through hole on the skin support, and the porous skin.

[0011] The device used in this method includes a wing, an ejector vacuum generator, a first support assembly, a porous skin, a first gas pipeline, a high-pressure gas source, a second gas pipeline, a third gas pipeline, a first valve, a second valve, and a third valve; The ejector vacuum generator includes a generator housing, a central contraction section disposed within the generator housing, a second air inlet, a first air intake, and a third exhaust port. The second air inlet, the first air intake, and the third exhaust port are respectively disposed on the generator housing. The high-pressure airflow entering through the second air inlet is accelerated by the central contraction section, and the static pressure drops sharply to form a local vacuum, which draws in the gas from the first air intake and then discharges it through the third exhaust port. The wing has an internal channel with an open top that cooperates with the first support component. The upper opening of the channel is referred to as the first window. The first window is located on the upper surface of the front edge of the wing's suction front and airflow can enter the channel through the first window. The first support component includes support columns and skin support members disposed in the channel. There are several support columns, and the support columns are evenly distributed in the channel. The lower end of the support column is connected to the wing and the wing can provide support for the support column. The upper end of the support column is connected to the skin support member and the support column can provide support for the skin support member. The porous skin is set on the skin support member and the skin support member can provide support for the porous skin. The porous skin is located on the first window and the curve of the upper surface of the porous skin is parallel to the surface of the wing. The skin support is provided with a number of gas through holes. The channel is connected to the first air intake through the first gas pipe. The gas entering through the porous skin can be sent into the ejector vacuum generator in sequence through the gas through holes, channel, first gas pipe and first air intake on the skin support. The high-pressure gas source is connected to the second air inlet through the second gas pipe, and the high-pressure gas flow generated by the high-pressure gas source can enter the ejector vacuum generator sequentially through the second gas pipe and the second air inlet. The third exhaust port is connected to the third gas pipe, and the gas in the ejector vacuum generator can be discharged sequentially through the third exhaust port and the third gas pipe. The first valve is installed on the first gas pipeline, the second valve is installed on the second gas pipeline, and the third valve is installed on the third gas pipeline.

[0012] The first window is located at the leading edge of the wing's suction surface, and the distance from the first window to the leading edge of the wing is 15-25% of the wing chord length. Further, the distance from the first window to the leading edge of the wing is 18-22% of the wing chord length; preferably, the distance from the first window to the leading edge of the wing is 20% of the wing chord length.

[0013] The width of the first window is 5%-10% of the wing chord.

[0014] The chord length of an aircraft wing is the straight-line distance between the leading edge and the trailing edge of the wing.

[0015] The cross-section of the supporting column along its axial direction is elliptical or rhomboid.

[0016] The supporting columns are at least three and are evenly distributed within the channel.

[0017] The supporting column and the skin support are rigidly connected by screws or bolts.

[0018] The upper surface of the skin support is parallel to the wing surface and is recessed by a set distance A, where distance A is the height of the porous skin.

[0019] The skin support is elongated.

[0020] The porosity of the skin support is ≥60%. Further, the porosity of the skin support is 60%-90%.

[0021] The porous skin has a pore diameter of 0.1mm-0.5mm, a pore spacing of 0.2mm-1mm, and a plate thickness of 0.1mm-1mm.

[0022] The porous skin is attached to the skin support and the wing surface is smooth without steps.

[0023] The porous skin is welded to the skin support.

[0024] The high-pressure gas source is the high-pressure exhaust gas generated by the aircraft engine or a high-pressure gas cylinder.

[0025] The third gas pipeline is connected to the atmosphere.

[0026] It also includes a control system, wherein the first valve, the second valve, and the third valve are all solenoid valves, and the first valve, the second valve, and the third valve are respectively connected to the control system.

[0027] The first valve, the second valve, and the third valve are all electromagnetic flow valves. Attached Figure Description

[0028] The present invention will be described by way of example and with reference to the accompanying drawings, wherein: Figure 1 This is a schematic diagram of the overall structure of the hybrid laminar flow and shock wave vibration control device based on blowing and sucking air in Example 1.

[0029] Figure 2 This is a schematic diagram of the wing structure in Example 1.

[0030] Figure 3 This is a schematic diagram of the cross-sectional structure of the channel and the airflow passage in Example 1.

[0031] Figure 4 This is a schematic diagram of the structure of the first support component in Embodiment 1.

[0032] Figure 5 for Figure 4 A magnified view of part I in the diagram.

[0033] Figure 6 for Figure 5 A side view of the rollover.

[0034] Figure 7 This is a schematic diagram of the inhalation mode in Example 1.

[0035] Figure 8 This is a schematic diagram of the blowing mode in Example 1.

[0036] The markings in the diagram are: 1. Wing, 2. Ejector-type vacuum generator, 3. Porous skin, 4. First support assembly, 5. Support column, 6. Skin support component, 7. First gas pipe, 8. First valve, 9. High-pressure gas source, 10. Second gas pipe, 11. Second valve, 21. Third gas pipe, 22. Third valve. Detailed Implementation

[0037] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention based on wind tunnel testing, and not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0038] All features disclosed in this specification, or all steps in all disclosed methods or processes, may be combined in any way, except for mutually exclusive features and / or steps.

[0039] Any feature disclosed in this specification, unless otherwise stated, may be replaced by other equivalent or similar features. That is, unless otherwise stated, each feature is merely one example of a series of equivalent or similar features.

[0040] Example 1 The hybrid laminar flow and shock wave chattering control device based on blowing and suction air used in this embodiment is as follows: Figure 1 As shown, it includes a wing, an ejector vacuum generator, a first support assembly, a porous skin, a first gas pipe, a high-pressure gas source, a second gas pipe, a third gas pipe, a first valve, a second valve, a third valve, and a control system.

[0041] The ejector-type vacuum generator used in this embodiment, also known as a vacuum ejector, jet vacuum pump, or vacuum generator, utilizes a high-speed working fluid that accelerates within the central contraction section of the nozzle, causing a sudden drop in static pressure to create a local vacuum (negative pressure). This vacuum entrains and mixes the gas being pumped, which is then decelerated and pressurized in the diffuser chamber before being discharged, thus achieving vacuuming. In this embodiment, the ejector-type vacuum generator includes a generator housing, a central contraction section disposed within the generator housing, a second air inlet, a first air intake, and a third exhaust port. The second air inlet, first air intake, and third exhaust port are respectively disposed on the generator housing. With this structure, the high-pressure airflow entering through the second air inlet is accelerated through the central contraction section, causing a sudden drop in static pressure to create a local vacuum. This airflow then draws in the gas from the first air intake and is subsequently discharged through the third exhaust port.

[0042] like Figure 3 As shown, the wing has an internal channel with an open top that mates with the first support component. The opening at the top of the channel is designated as the first window. The first window is located on the upper surface of the leading edge of the wing's suction surface, and airflow can enter the channel through the first window. In this application, the type of wing is not limited. This application is based on an existing wing and has been modified as follows: an airflow channel is arranged on the existing wing, with the intake area positioned approximately at about 20% of the chord length of the leading edge of the wing's suction surface. This avoids direct impact with insects, birds, dust, etc., in the air, which could cause blockage. In a specific example, such as... Figure 2 As shown, the distance from the first window to the leading edge of the wing is about 20% of the wing chord length, and the width of the first window is 5%-10% of the wing chord length.

[0043] The first support assembly includes support columns and skin support members disposed within a channel. Several support columns are evenly distributed within the channel. The lower ends of the support columns are connected to the wing, and the wing provides support for the support columns. The upper ends of the support columns are connected to the skin support members via screws, and the support columns provide support for the skin support members. A porous skin is disposed on the skin support members, and the skin support members provide support for the porous skin. In a specific example, the porous skin is fixed to the upper surface of the skin support members by welding. Furthermore, the support columns have an elliptical or rhomboid cross-section along their axial direction. This shape helps reduce airflow resistance within the channel, and the bottom of the support columns is provided with screw holes for tight fixation to the wing. The porous skin is a microporous thin plate, a commercially available product, with a pore diameter between 0.1mm and 0.5mm, a pore spacing between 0.2mm and 1mm, and a plate thickness between 0.1mm and 1mm. In one specific example, the porous skin has a pore diameter of 0.2 mm, a pore spacing of 0.2 mm, and a plate thickness of 0.2 mm. In this embodiment, the skin support is elongated and has several gas through holes; the porous skin is located on the first window. Figure 4 , Figure 5 , Figure 6As shown, the skin support has uniformly arranged gas vents with a diameter of not less than 2 mm and a porosity higher than 60%. In a specific example, the upper surface curve of the skin support is parallel to the wing surface and recessed by 0.2 mm. When embedded in the wing, there is a 0.2 mm recess, which is filled when it is fitted with the porous skin, resulting in a smooth, stepless surface. In this application, the skin support is elongated and has a large-pore structure to ensure ventilation. At the same time, uniformly arranged support columns are rigidly connected to the bottom of the channel by screws, etc., so that the first support component of this application can be subjected to both compression and tension. To ensure smooth airflow in the channel, the support columns are set to elliptical or rhomboid shapes to reduce flow resistance.

[0044] The channel is connected to the first intake port via a first gas pipe, and the gas entering through the porous skin can be sequentially sent into the ejector vacuum generator through the gas through-holes on the skin support, the channel, the first gas pipe, and the first intake port. The high-pressure gas source is connected to the second intake port via a second gas pipe, and the high-pressure gas flow generated by the high-pressure gas source can sequentially enter the ejector vacuum generator through the second gas pipe and the second intake port. The third exhaust port is connected to the third gas pipe, and the gas in the ejector vacuum generator can be sequentially discharged through the third exhaust port and the third gas pipe. A first valve is installed on the first gas pipe, a second valve is installed on the second gas pipe, and a third valve is installed on the third gas pipe. In this embodiment, the first, second, and third valves are electromagnetic flow valves, and the first, second, and third valves are respectively connected to the control system. In a specific example, the high-pressure gas source uses the high-pressure exhaust gas generated by the aircraft engine. Specifically, it is connected to the high-pressure exhaust gas generated by the aircraft engine through the second gas pipe; at the same time, the third gas pipe is open to the atmosphere.

[0045] In this embodiment, air blowing and suction control can be achieved between the channel and the first gas pipe. For example... Figure 1 , Figure 7 , Figure 8 As shown, the ejector vacuum generator utilizes an ejector method based on Bernoulli's principle. It connects to a high-pressure gas source through a second air inlet and to a third gas pipeline through a third exhaust port, thereby forming an internal flow channel. The flow velocity is fastest and the pressure is lowest in the region with the smallest cross-section in the middle. This application sets a first air intake at the middle contraction section, that is, at the point of lowest pressure, the first air intake is introduced, thereby generating a great suction force.

[0046] Furthermore, this embodiment provides a combined control method for mixed laminar flow and shock wave chattering based on blowing and sucking air, which includes the following steps.

[0047] S1, Inhalation Mode When the wing needs to draw in air, the first, second, and third valves are opened, and the high-pressure gas source outputs high-pressure airflow to the ejector vacuum generator, creating a negative pressure at the first intake port. Under the negative pressure of the ejector vacuum generator, the airflow at the wing's leading edge sequentially enters the ejector vacuum generator through the porous skin, gas passages on the skin support, channels, the first gas pipe, and the first intake port. The gas entering the ejector vacuum generator is then discharged sequentially through the third exhaust port and the third gas pipe.

[0048] S2, Blowing Mode When the wing needs air blowing, the third valve is closed, and the first and second valves are opened. The high-pressure gas source outputs high-pressure airflow to the ejector vacuum generator, and the gas inside the ejector vacuum generator cannot be discharged through the third exhaust port and the third gas pipe. The gas inside the ejector vacuum generator is discharged sequentially through the first intake port, the first gas pipe, the channel, the gas through holes on the skin support, and the porous skin.

[0049] S3. According to the flight requirements of the aircraft, switch between steps S1 and S2 to realize the composite control of mixed laminar flow and shock wave fluttering based on blowing and sucking.

[0050] In this application, by adjusting the operating power and airflow path of the valve adjustment device, air can be drawn from the engine or other locations with high-pressure air sources during actual operation; when laminar flow control is required, the system switches to intake mode, and the airflow direction is as follows: Figure 7 As shown; when stable control is required, switch to blowing mode, and the airflow direction is as follows. Figure 8 As shown. In suction mode, the first valve, second valve, and third valve are opened; the suction force of the ejector vacuum generator is adjusted by controlling the second and third valves; the suction intensity is controlled by adjusting the mixed laminar flow by controlling the first valve. In blowing mode, the third valve is closed, and the first and second valves are opened. The high-pressure airflow flows sequentially through the second gas pipe, the second air inlet, the ejector vacuum generator, the first air inlet, the first gas pipe, the channel, the gas through holes on the skin support, and the porous skin. The blowing intensity is controlled by the second and first valves.

[0051] Due to the adoption of the above-mentioned scheme, this application has the following advantages: (1) By adopting the design scheme of this application, the layout can effectively prevent foreign objects such as insects, birds, and dust from blocking the airflow passage, and effectively ensure good laminar flow control capability. (2) The structure of this application is simple and has good tensile and compressive strength, which effectively ensures that the structure has sufficient strength in both blowing and inhaling modes; (3) In this application, the gas source is controlled by a valve, which can realize the rapid switching of flow rate and flow direction, and can achieve the laminar flow control effect in the air intake mode and the enhanced stability and anti-bounce instability control effect in the air blowing mode. (4) When large passenger aircraft need to increase lift and reduce drag, save energy and reduce emissions, they can switch to the air-breathing mode to achieve mixed laminar flow control; when it is necessary to reduce flutter and avoid boundary layer instability, they can switch to the air-blowing mode to achieve shock wave flutter control. It can be seen that this application can realize the composite control of mixed laminar flow and shock wave flutter based on air-blowing and air-breathing, which is of great significance for promoting the development of aircraft. (5) This application has a simple structure, requires little modification, and has great engineering application value.

[0052] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

[0053] This invention is not limited to the specific embodiments described above. The invention extends to any new feature or combination disclosed in this specification, as well as any new method or process step or combination disclosed herein.

Claims

1. A hybrid laminar flow and shock wave chattering control method based on blowing and suction air, characterized in that, Includes the following steps: S1, Inhalation Mode When the wing needs to take in air, the high-pressure air source outputs high-pressure airflow to the ejector vacuum generator and creates a negative pressure at the first air intake. Under the negative pressure of the ejector vacuum generator, the airflow at the leading edge of the wing enters the ejector vacuum generator sequentially through the porous skin, the gas passage on the skin support, the channel, the first gas pipe, and the first air intake. The gas entering the ejector vacuum generator is discharged sequentially through the third exhaust port and the third gas pipe; S2, Blowing Mode When the wing needs to blow air, the high-pressure air source outputs high-pressure airflow to the ejector vacuum generator, and the gas in the ejector vacuum generator cannot be discharged through the third exhaust port and the third gas pipe. The gas inside the ejector vacuum generator is discharged sequentially through the first intake port, the first gas pipe, the channel, the gas through hole on the skin support, and the porous skin. S3. According to the flight requirements of the aircraft, switch between steps S1 and S2 to realize the composite control of mixed laminar flow and shock wave fluttering based on blowing and sucking.

2. The hybrid laminar flow and shock wave chattering control method based on blowing and suction air as described in claim 1, characterized in that, In step S1, when the wing needs to take in air, the first valve, the second valve, and the third valve are opened, and the high-pressure air source outputs high-pressure airflow to the ejector vacuum generator, and a negative pressure is formed at the first air intake. Under the negative pressure of the ejector vacuum generator, the airflow at the leading edge of the wing enters the ejector vacuum generator sequentially through the porous skin, the gas passage on the skin support, the channel, the first gas pipe, and the first air intake. The gas entering the ejector vacuum generator is discharged sequentially through the third exhaust port and the third gas pipe; In step S2, when the wing needs to blow air, the third valve is closed and the first and second valves are opened. The high-pressure gas source outputs high-pressure airflow to the ejector vacuum generator, and the gas in the ejector vacuum generator cannot be discharged through the third exhaust port and the third gas pipe. The gas inside the ejector vacuum generator is discharged sequentially through the first intake port, the first gas pipe, the channel, the gas through hole on the skin support, and the porous skin.

3. The hybrid laminar flow and shock wave chattering control method based on blowing and suction air as described in claim 1, characterized in that, The device used in this method includes a wing, an ejector vacuum generator, a first support assembly, a porous skin, a first gas pipeline, a high-pressure gas source, a second gas pipeline, a third gas pipeline, a first valve, a second valve, and a third valve; The ejector vacuum generator includes a generator housing, a central contraction section disposed within the generator housing, a second air inlet, a first air intake, and a third exhaust port. The second air inlet, the first air intake, and the third exhaust port are respectively disposed on the generator housing. The high-pressure airflow entering through the second air inlet is accelerated by the central contraction section, and the static pressure drops sharply to form a local vacuum, which draws in the gas from the first air intake and then discharges it through the third exhaust port. The wing has an internal channel with an open top that cooperates with the first support component. The upper opening of the channel is referred to as the first window. The first window is located on the upper surface of the front edge of the wing's suction front and airflow can enter the channel through the first window. The first support component includes support columns and skin support members disposed in the channel. There are several support columns, and the support columns are evenly distributed in the channel. The lower end of the support column is connected to the wing and the wing can provide support for the support column. The upper end of the support column is connected to the skin support member and the support column can provide support for the skin support member. The porous skin is set on the skin support member and the skin support member can provide support for the porous skin. The porous skin is located on the first window and the curve of the upper surface of the porous skin is parallel to the surface of the wing. The skin support is provided with a number of gas through holes. The channel is connected to the first air intake through the first gas pipe. The gas entering through the porous skin can be sent into the ejector vacuum generator in sequence through the gas through holes, channel, first gas pipe and first air intake on the skin support. The high-pressure gas source is connected to the second air inlet through the second gas pipe, and the high-pressure gas flow generated by the high-pressure gas source can enter the ejector vacuum generator sequentially through the second gas pipe and the second air inlet. The third exhaust port is connected to the third gas pipe, and the gas in the ejector vacuum generator can be discharged sequentially through the third exhaust port and the third gas pipe. The first valve is installed on the first gas pipeline, the second valve is installed on the second gas pipeline, and the third valve is installed on the third gas pipeline.

4. The hybrid laminar flow and shock wave chattering control method based on blowing and suction air as described in claim 3, characterized in that, The first window is located at the leading edge of the wing's suction surface, and the distance from the first window to the leading edge of the wing is 15-25% of the wing chord length.

5. The hybrid laminar flow and shock wave chattering control method based on blowing and sucking air as described in claim 4, characterized in that, The width of the first window is 5%-10% of the wing chord.

6. The hybrid laminar flow and shock wave chattering control method based on blowing and suction air as described in claim 3, characterized in that, The cross-section of the supporting column along its axial direction is elliptical or rhomboid.

7. The hybrid laminar flow and shock wave chattering control method based on blowing and suction air as described in claim 3, characterized in that, The porous skin is attached to the skin support and the wing surface is smooth without steps.

8. The hybrid laminar flow and shock wave chattering control method based on blowing and suction air as described in claim 3, characterized in that, The high-pressure gas source is the high-pressure exhaust gas generated by the aircraft engine or a high-pressure gas cylinder.

9. The hybrid laminar flow and shock wave chattering control method based on blowing and sucking air according to any one of claims 3-8, characterized in that, It also includes a control system, wherein the first valve, the second valve, and the third valve are all solenoid valves, and the first valve, the second valve, and the third valve are respectively connected to the control system.

10. The hybrid laminar flow and shock wave chattering control method based on blowing and sucking air as described in claim 9, characterized in that, The first valve, the second valve, and the third valve are all electromagnetic flow valves.

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