Aircraft surface airflow control device, method and components

Abstract

The present application relates to an aircraft surface airflow control device, method and components, and relates to the field of aircraft surface airflow separation control. The above-mentioned device includes: a first electrode, a second electrode and an insulating dielectric layer; the first electrode is arranged on one side surface of the insulating dielectric layer, for being directly exposed to the airflow on the aircraft surface; the second electrode is embedded in the other side of the insulating dielectric layer, for being closely attached to the aircraft surface; the first electrode is a conductor extending continuously along its length direction; the second electrode includes a plurality of conductor segments spaced along the length direction; the first electrode and the second electrode are parallel to each other along their respective length directions; the portion where the first electrode overlaps with the plurality of conductor segments is the first region, and the portion where the first electrode does not overlap with the second electrode is the second region, and the ratio of the total length of the first region to the total length of the second region is greater than or equal to a preset threshold. The device can solve the problem of high consumption and low efficiency, and reduce energy consumption while maintaining the separation flow control effect.

Description

Technical Field

[0001] The present invention relates to the field of aircraft surface airflow separation control, and in particular to an aircraft surface airflow control device, method and components. Background Art

[0002] When an aircraft is in flight, air flows along its wing surface. In regions of adverse pressure gradient, especially at high angles of attack, the low-energy fluid within the boundary layer cannot overcome the adverse pressure gradient. The airflow separates from the surface, forming a detached flow. This detached flow causes a sharp drop in lift and a significant increase in drag, potentially leading to wing stall. Therefore, a device is needed to keep the airflow attached to the wing surface for as long as possible.

[0003] A common device used to prevent airflow separation is a plasma excitation device. It typically consists of an upper electrode (also known as an exposed electrode), a lower electrode (also known as a covered electrode), and an insulating dielectric layer between the electrodes. Its operating principle is that an alternating excitation voltage of a certain frequency and amplitude is applied between the upper and lower electrodes, generating a high electric field between the electrodes. This in turn excites the gas near the dielectric layer to form a plasma. This plasma, with its high energy and ion concentration, introduces additional momentum and heat into the boundary layer, thereby improving the stability and adhesion of the fluid within the boundary layer and suppressing flow separation.

[0004] However, traditional continuous plasma excitation devices require maintaining plasma excitation along the entire length of the excitation zone due to their continuous distribution. This results in excessive energy consumption, increased weight, and high operating costs. Other intermittent exciters primarily achieve this by changing the shape of the top electrode (for example, from a straight strip to a curved shape). However, these devices suffer from poor aerodynamic characteristics and uncontrollable flow control. Summary of the Invention

[0005] The technical problem to be solved by the present invention is how to reduce the energy consumption of the device while maintaining the separation flow control effect. The purpose is to provide an aircraft surface airflow control device, method and components to solve the problem of high consumption and low efficiency.

[0006] The present invention is achieved through the following technical solutions:

[0007] According to a first aspect of the present application, there is provided an aircraft surface airflow control device for installation on an aircraft surface, comprising: a first electrode, a second electrode, and an insulating dielectric layer;

[0008] The first electrode is provided on one side surface of the insulating dielectric layer and is configured to be directly exposed to the airflow on the surface of the aircraft;

[0009] The second electrode is embedded in the other side of the insulating dielectric layer and is used to be closely attached to the surface of the aircraft;

[0010] The first electrode is a conductor extending continuously along its length;

[0011] The second electrode includes a plurality of conductor segments spaced apart along a length direction;

[0012] The first electrode and the second electrode are parallel to each other along their respective length directions;

[0013] The portion where the first electrode overlaps with the plurality of conductor segments is a first region. When the aircraft surface airflow control device is operated by high voltage electricity, the first region is used to generate plasma under high voltage electricity excitation. The plasma is used to form a directional plasma-excited airflow on the aircraft surface to prevent the airflow on the aircraft surface from separating from the aircraft surface.

[0014] The portion of the first electrode that is not overlapped with the second electrode is a second region, and a ratio of a total length of the first region to a total length of the second region is greater than or equal to a preset threshold.

[0015] In one embodiment, the first electrode is a movable element, and the ratio of the total length of the first region to the total length of the second region is changed by moving the first electrode on one side surface of the insulating dielectric layer.

[0016] In one embodiment, at least one side of each of the conductor segments in the width direction is angularly offset from the width direction of the first electrode.

[0017] In one embodiment, the shape of each conductor segment is any one of a trapezoidal, triangular, and wavy shape.

[0018] In one embodiment, the first electrode is in the shape of a quadrilateral with opposite sides parallel to each other.

[0019] In one embodiment, the plurality of conductor segments are all trapezoidal conductor segments of the same size and are arranged at equal intervals;

[0020] The second electrode further includes a rectangular conductor segment vertically connected to the lower bases of the plurality of trapezoidal conductor segments;

[0021] The first electrode is in a rectangular shape.

[0022] In one embodiment, the size parameters of the first electrode and the second electrode satisfy the following relationship:

[0023]

[0024] in, is the ratio of the total length of the first region to the total length of the second region, h is the total width of the second electrode, c is the width of the rectangular conductor segment, b is the horizontal distance between the first electrode and the rectangular conductor segment, d1 is the upper base length of the trapezoidal conductor segment, d2 is the lower base length of the trapezoidal conductor segment, and d3 is the spacing between adjacent trapezoidal conductor segments.

[0025] According to a second aspect of the present application, a method for controlling airflow on an aircraft surface is provided, which is applied to an aircraft surface airflow control device provided in the first aspect of the present application, comprising:

[0026] controlling the ratio of the total length of the first region of the aircraft surface airflow control device to the total length of the second region of the aircraft surface airflow control device to increase, so as to increase the flow range of the plasma generated by the aircraft surface airflow control device;

[0027] The ratio of the total length of the first region to the total length of the second region is controlled to decrease, so as to reduce the flow range of the plasma generated by the airflow control device on the aircraft surface.

[0028] In one embodiment, the increasing of the ratio of the total length of the first region of the aircraft surface airflow control device to the total length of the second region of the aircraft surface airflow control device comprises:

[0029] Controlling the first electrode of the aircraft surface airflow control device to move along the chord direction of the wing where the aircraft surface airflow control device is located on one side surface of the insulating dielectric layer of the device, and increasing the total length of the first region after the movement;

[0030] The controlling the ratio of the total length of the first region to the total length of the second region to decrease includes:

[0031] The first electrode controlling the aircraft surface airflow control device moves along the chord direction of the wing where the aircraft surface airflow control device is located on one side surface of the insulating medium layer of the aircraft surface airflow control device, and the total length of the first area after the movement is reduced.

[0032] According to a third aspect of the present application, there is provided an aircraft component, comprising:

[0033] The aircraft surface airflow control device provided in the first aspect of the present application;

[0034] high-voltage power lines;

[0035] High voltage power supply;

[0036] The first electrode and the second electrode of the aircraft surface airflow control device are connected to the high-voltage power supply through the high-voltage wire.

[0037] Compared with the prior art, this application has the following advantages and beneficial effects:

[0038] This aircraft surface airflow control device, through its continuous first electrode and discontinuous second electrode, and a structure in which the total length of the first region and the total length of the second region are greater than or equal to a preset threshold, can significantly reduce the device's power supply and equipment weight while ensuring an excitation effect equivalent to that of a traditional continuous plasma excitation device. It also avoids the shortcomings of the discontinuous excitation device in the related art, such as increased wing surface roughness and the uncertainty associated with spanwise excitation, and provides a more optimal device for achieving separated flow control in aircraft under conditions such as high angles of attack. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] In order to more clearly illustrate the technical solutions of the exemplary embodiments of the present invention, the following briefly introduces the drawings required for use in the examples. It should be understood that the following drawings only illustrate certain embodiments of the present invention and should not be considered as limiting the scope. A person of ordinary skill in the art can also derive other relevant drawings based on these drawings without inventive effort. In the drawings:

[0040] Figure 1 This is a schematic plan projection diagram of an aircraft surface airflow control device provided by the present application;

[0041] Figure 2 It is a plan projection diagram of a continuous plasma excitation device;

[0042] Figure 3 It is a plan projection diagram of an intermittent plasma excitation device;

[0043] Figure 4 is the lift characteristic curve of the continuous plasma excitation device;

[0044] Figure 5 This is a lift characteristic curve of an aircraft surface airflow control device provided by the present application;

[0045] Figure 6 This is a dimensional drawing of a plane projection of an aircraft surface airflow control device provided in this application;

[0046] Figure 7 This application provides a method for controlling airflow on the surface of an aircraft.

[0047] Markings and corresponding parts names in the accompanying drawings:

[0048] A first electrode 110 , a second electrode 120 , and an insulating dielectric layer 130 . DETAILED DESCRIPTION

[0049] Hereinafter, the terms "include" or "may include" used in various embodiments of the present invention indicate the presence of the invented function, operation or element, and do not limit the addition of one or more functions, operations or elements. In addition, as used in various embodiments of the present invention, the terms "include", "have" and their cognates are intended only to indicate specific features, numbers, steps, operations, elements, components or combinations of the foregoing, and should not be understood as excluding the presence of one or more other features, numbers, steps, operations, elements, components or combinations of the foregoing or the possibility of adding one or more features, numbers, steps, operations, elements, components or combinations of the foregoing.

[0050] In various embodiments of the present invention, the expression "or" or "at least one of A or / and B" includes any or all combinations of the words listed simultaneously. For example, the expression "A or B" or "at least one of A or / and B" may include A, may include B, or may include both A and B.

[0051] The expressions (such as "first", "second", etc.) used in the various embodiments of the present invention may modify the various constituent elements in the various embodiments, but may not limit the corresponding constituent elements. For example, the above expressions do not limit the order and / or importance of the elements. The above expressions are only used to distinguish one element from other elements. For example, a first user device and a second user device indicate different user devices, although both are user devices. For example, without departing from the scope of the various embodiments of the present invention, a first element may be referred to as a second element, and similarly, a second element may also be referred to as a first element.

[0052] It should be noted that when a component is described as being “connected” to another component, the first component may be directly connected to the second component, and a third component may be “connected” between the first and second components. Conversely, when a component is described as being “directly connected” to another component, it can be understood that there is no third component between the first and second components.

[0053] The terms used in various embodiments of the present invention are only used to describe the purpose of specific embodiments and are not intended to limit the various embodiments of the present invention. As used herein, the singular form is intended to also include the plural form, unless the context clearly indicates otherwise. Unless otherwise limited, all terms used here (including technical terms and scientific terms) have the same meaning as those of ordinary skill in the art generally understood by the various embodiments of the present invention. The terms (such as those defined in generally used dictionaries) will be interpreted as having the same meaning as the contextual meaning in the relevant technical field and will not be interpreted as having idealized meaning or too formal meaning, unless clearly defined in various embodiments of the present invention.

[0054] In order to make the objectives, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with examples and drawings. The exemplary embodiments of the present invention and their descriptions are only used to explain the present invention and are not intended to limit the present invention.

[0055] Figure 1 This is a schematic diagram of a plane projection of an aircraft surface airflow control device provided by this application. Figure 1 As shown, the device is for installation on an aircraft surface and includes: a first electrode 110, a second electrode 120, and an insulating dielectric layer 130. The first electrode 110 is disposed on one side of the insulating dielectric layer 130 for direct exposure to airflow on the aircraft surface. The second electrode 120 is embedded in the other side of the insulating dielectric layer 130 for close contact with the aircraft surface. The first electrode 110 is a conductor extending continuously along its length. The second electrode 120 includes a plurality of conductor segments spaced apart along its length. The first electrode 110 and the second electrode 120 are parallel to each other along their respective lengths. The portion where the first electrode 110 overlaps with the plurality of conductor segments is a first region. When the device is operated by high voltage electricity, the first region is used to generate plasma under high voltage excitation. The plasma is used to form a directional plasma-excited airflow on the aircraft surface to prevent the airflow on the aircraft surface from separating from the aircraft surface. The portion where the first electrode 110 does not overlap with the second electrode is a second region. The ratio of the total length of the first region to the total length of the second region is greater than or equal to a preset threshold value, which is 0.5.

[0056] like Figure 1 As shown, the dotted area is the projection area of the insulating dielectric layer, and the grid area is the projection area of the first electrode and the second electrode. It can be seen that there are two grid areas in the figure. The overlapping area is the first area, and the non-overlapping area of the grid area corresponding to the first electrode is the second area.

[0057] The insulating dielectric layer, also known as a non-conductive material layer, electrically isolates the first and second electrodes and, together with the first and second electrodes, forms an electric field and excitation effect to generate plasma. The side of the insulating dielectric layer where the first electrode resides is the side facing the fluid. The other side of the insulating dielectric layer where the second electrode resides is the side facing away from the fluid and toward the component to which the device is installed (e.g., an aircraft wing).

[0058] Continuous extension means the first electrode extends without interruption or segmentation throughout its entire length. A discontinuous first electrode structure would increase airflow disturbances and generate unnecessary spanwise excitation. Compared to a discontinuous structure, a continuous first electrode structure allows for a smoother wing surface, minimizing airflow disturbances and enabling uniform distribution along a specific direction (e.g., the chordwise direction of the wing), ensuring plasma excitation throughout the chordwise direction.

[0059] Unlike the first electrode, the conductor segments in the second electrode have a preset physical spacing between them, resulting in a discontinuous distribution of the conductor segments, forming alternating first regions (also known as excitation regions) and second regions (also known as non-excitation regions, or discontinuous regions). The multiple conductor segments of the second electrode are discretely arranged along its main extension direction, forming a structure with alternating first and second regions, representing a discontinuous structure. Because the second electrode does not directly contact the fluid, its discontinuous structure does not interfere with airflow and saves material compared to a continuous structure. The first and second electrodes can be made of conductive materials such as copper foil.

[0060] Overlap refers to the overlap of the normal projections of multiple conductor segments of the first and second electrodes. The ratio of the total length of the first region to the total length of the second region reflects the plasma excitation effect. Since plasma is primarily generated at the edges of the first region, the length ratio can be used to measure the excitation effect. Experimental verification has shown that when this ratio is no less than 0.5, the device can achieve the same plasma excitation effect as a continuous plasma excitation device. Therefore, the preset threshold can be set to 0.5.

[0061] In actual use, the device requires applying a preset excitation voltage between the first and second electrodes. Upon application of the excitation voltage, plasma excitation zones form in the first region. The plasma generated in these regions enhances the fluid energy within the boundary layer through electric fields and hydrodynamic forces, improving fluid adhesion. In addition to directly disturbing the airflow in the excitation region, the airflow in the excitation region also creates an entrainment effect, allowing control of the separated flow in unexcited regions. Experiments have shown that when the total length ratio of the excitation region to the discontinuity region is no less than 1:2, the same control effect as a continuous plasma excitation device can be achieved, while reducing power consumption by approximately two-thirds.

[0062] When using the device provided in this application, it should be arranged along the chordwise direction of the leading edge of an aircraft wing, with the first electrode facing the fluid side and directly exposed to the air, and the side of the insulating dielectric layer on which the second electrode is located facing the wing. A predetermined high-voltage alternating current is applied between the first and second electrodes to form a plasma excitation region within the first region. This localized aerodynamic disturbance improves boundary layer adhesion, thereby achieving separation flow control.

[0063] Figure 2 and Figure 3 Schematic diagram of two types of plasma excitation devices in related art. Figure 2 It is a plane projection diagram of a continuous plasma excitation device, and the projection plane is parallel to the plane of the insulating dielectric layer of the device. Figure 2 The projection of the lower electrode 220 completely covers the projection of the upper electrode 210. Since the excitation area of the conventional continuous plasma excitation device is continuously distributed, continuous excitation needs to maintain the plasma excitation along the entire length, resulting in excessive energy consumption, increased equipment weight, and high operating costs.

[0064] Figure 3 It is a plane projection diagram of an intermittent plasma excitation device, and the projection plane is parallel to the plane of the insulating dielectric layer of the device. Figure 2 As shown, the upper electrode 310 is a discontinuous structure, while the lower electrode 320 is a continuous structure. The projections of the upper electrode 310 and the lower electrode 320 partially overlap. This excitation device is primarily implemented by changing the shape of the upper electrode (for example, from a straight strip to a curved shape). However, this approach complicates the structure and increases the surface roughness of the wing, leading to an early transition to the laminar boundary layer and deteriorating aerodynamic characteristics. Furthermore, this discontinuous exciter discharges along the spanwise direction, consuming more energy and generating a spanwise jet that makes the flow control effect uncontrollable.

[0065] The aircraft surface airflow control device provided by the present disclosure can use a continuous first electrode and an intermittent second electrode, and set the total length of the first area and the total length of the second area to be greater than or equal to a preset threshold. Under the premise of ensuring that the excitation effect is equivalent to that of a traditional continuous plasma excitation device, the power supply power and equipment weight of the device can be significantly reduced. Figure 4 It is the lift characteristic curve of the continuous plasma excitation device. Figure 5 The present application provides a lift characteristic curve of an aircraft surface airflow control device. Figure 4 and Figure 5 The horizontal axis is the angle of attack, that is, the angle between the chord line of the wing and the direction of the airflow, and the vertical axis is the lift coefficient, which is used to describe the ability of the plasma excitation device to generate lift in the airflow. Figure 4 and Figure 5As shown, the aircraft surface airflow control device provided in this application can improve the wing lift coefficient, achieving the same effect as a continuous plasma excitation device. It also avoids the shortcomings of related art discontinuous excitation devices, such as increased wing surface roughness and the uncertainty associated with spanwise excitation, providing a more optimized device for achieving separated flow control under conditions such as high angles of attack.

[0066] In one embodiment, the first electrode is a movable element, and the ratio of the total length of the first region to the total length of the second region is changed by moving the first electrode on one side surface of the insulating dielectric layer.

[0067] In the device provided herein, the first electrode is designed as a movable element, mounted on the surface of the insulating dielectric layer facing the fluid. As a movable element, the first electrode can be adjusted on the surface of the insulating dielectric layer by disassembly, sliding, or other methods. Because the first electrode is not embedded in the insulating dielectric layer but mounted directly on its surface, adjusting the first electrode's position can alter the overlap of the conductor segment with the second electrode without removing the insulating layer or modifying the lower electrode.

[0068] Specifically, when the device is installed at the leading edge of an aircraft wing, the position of the first electrode can be adjusted along the chordwise direction of the wing to implement the following flow control strategy. To enhance flow control, the first electrode is moved to increase the total length of the first region and decrease the total length of the second region, thereby increasing the ratio between the two and enhancing the excitation intensity. To reduce flow control or lower energy consumption, the first electrode is adjusted to decrease the total length of the first region and increase the total length of the second region, thereby reducing the ratio and achieving energy-saving operation.

[0069] It is worth noting that the device provided in this application is not limited to a specific form of the first electrode moving mechanism, and a variety of mechanical or electrical control systems can be used to adjust its position on the surface of the insulating dielectric layer according to actual application requirements.

[0070] The use of a movable first electrode allows the device to flexibly adjust the ratio of the excitation area to the non-excitation area according to the flow field control requirements of different aircraft states or flight conditions, so as to adapt to the differentiated control requirements under various flight conditions.

[0071] In one embodiment, at least one side of each conductor segment in the width direction is angularly offset from the width direction of the first electrode.

[0072] Here, the width direction of the conductor segment refers to the direction perpendicular to the length direction of the second electrode. Similarly, the width direction of the first electrode refers to the direction perpendicular to the length direction of the first electrode. At least one side of the conductor segment is angularly offset from the side of the first electrode. This angular offset makes the conductor segment no longer adopt the common rectangular structure, but can be designed as a trapezoid, triangle or other non-rectangular shape. The offset angle can be determined according to the specific application requirements. For example, Figure 1 As shown, the plurality of conductor segments in the second electrode may be trapezoidal, and the first electrode may be rectangular. Figure 1 It can be seen that there is an angle offset between the hypotenuse of the trapezoidal grid area and the long side of the narrow strip grid area, that is, there is an angle offset between the projection of the conductor segment and the side in the width direction of the first electrode.

[0073] With this structure, as the first electrode moves along its width, its overlap with the second electrode conductor segment changes, thereby altering the total length and ratio of the energized region (first region) to the non-energized region (second region). This angular offset creates a gradual change in plasma intensity along the flow direction, creating a smoother control transition zone, thereby reducing flow field disturbances and improving fluid control.

[0074] In one embodiment, the shape of each conductor segment is any one of a trapezoid, a triangle, and a wave.

[0075] Here, each conductor segment can be configured to have the same or different shapes, including trapezoidal, triangular, and wavy shapes. When the first electrode moves along the width direction, the trapezoidal, triangular, or wavy shapes of the conductor segments can improve the transition between the excited and unexcited regions, resulting in a gradual change in plasma intensity, which helps reduce flow field disturbances and transient effects.

[0076] In one embodiment, the first electrode is in the shape of a quadrilateral with opposite sides parallel to each other.

[0077] Here, the first electrode has a quadrilateral structure with parallel opposite sides, such as a rectangle or parallelogram. This quadrilateral structure maintains a relatively stable shape and size of the overlap region between the first electrode and the second electrode conductor segment, thereby ensuring a uniform distribution of the excitation area. Compared to an irregular shape, a quadrilateral with parallel opposite sides of the first electrode makes it easier to calculate the change in overlap between the first electrode and the second electrode conductor segment as the first electrode moves along the width direction.

[0078] like Figure 1 As shown, in one embodiment, the multiple conductor segments are all trapezoidal conductor segments of the same size and are arranged at equal intervals; the second electrode also includes rectangular conductor segments vertically connected to the lower bases of the multiple trapezoidal conductor segments; the first electrode is rectangular in shape.

[0079] Here, the equally sized and equally spaced trapezoidal conductor segments create a uniform and stable electric field distribution in the excitation region, resulting in a continuous and controllable plasma excitation effect. The geometric shape of the trapezoidal conductor segments gradually changes as the edges of the excitation region adjust, reducing disturbances in the flow field transition region. Furthermore, the continuity of the vertically connected rectangular conductor segments ensures a unified second electrode, facilitating production and processing.

[0080] Figure 6 This is a dimension drawing of a plane projection of an aircraft surface airflow control device provided by this application, and the projection plane is parallel to the plane of the device's insulating medium layer. Figure 6 As shown, in one embodiment, the size parameters of the first electrode and the second electrode satisfy the following relationship:

[0081]

[0082] in, is the ratio of the total length of the first region to the total length of the second region, h is the total width of the second electrode, c is the width of the rectangular conductor segment, b is the horizontal distance between the first electrode and the rectangular conductor segment, d1 is the upper base length of the trapezoidal conductor segment, d2 is the lower base length of the trapezoidal conductor segment, and d3 is the spacing between adjacent trapezoidal conductor segments.

[0083] Here, the above relationship can be derived through the following process. According to the properties of similar triangles, the horizontal cross-sectional length of the trapezoidal conductor segment at the height (hcb) is: d1+(hcb) / (hc)×(d2-d1). The length of a single excitation area is: Ls=d1+(hcb) / (hc)×(d2-d1)=(hcb)(d2-d1) / (hc)+d1, which is simplified to: Ls=[(hcb)(d2-d1)+(hc)d1] / (hc). The length of the period of a complete excitation area and discontinuity area is (d2+d3). Therefore, the length of the discontinuity area = the period length - the excitation area length: Lg=(d2+d3)-Ls, which is expanded to:

[0084] Lg = (d2 + d3) - [(hcb)(d2 - d1) + (hc)d1] / (hc), which can be organized into a common denominator: Lg = [(d2 + d3)(hc) - (hcb)(d2 - d1) - (hc)d1] / (hc) = [(d2 + d3 - d1)(hc) - (hcb)(d2 - d1)] / (hc). Therefore, the ratio of the total length of the first region to the total length of the second region = Ls / Lg = [(hcb)(d2 - d1) + (hc)d1] / [(d2 + d3 - d1)(hc) - (hcb)(d2 - d1)].

[0085] During the production and processing of the above device, the above dimensional parameters may be used as a reference, but the specific parameters are not limited thereto. In addition, in actual applications, after moving the first electrode, the total length ratio of the first region to the second region may be recalculated and determined based on the above relationship.

[0086] Specifically, when the first electrode moves parallel to the upper base of the trapezoidal conductor segment by a distance t, b becomes (b + t): Ls = [(hcbt)(d2-d1) + (hc)d1] / (hc). Similarly, the length of the discontinuous region after movement is: Lg = [(d2+d3-d1)(hc) - (hcbt)(d2-d1)] / (hc). Therefore, the ratio after movement is τ = Ls / Lg = [(hcbt)(d2-d1) + (hc)d1] / [(d2+d3-d1)(hc) - (hcbt)(d2-d1)].

[0087] Figure 7 This application provides a method for controlling airflow on an aircraft surface. Based on the same concept, the method can be applied to the above-mentioned airflow control device on the aircraft surface, and includes the following steps.

[0088] Step S710 , controlling the ratio of the total length of the first region of the aircraft surface airflow control device to the total length of the second region of the aircraft surface airflow control device to increase, so as to increase the flow range of the plasma generated by the aircraft surface airflow control device.

[0089] Step S720 , controlling the ratio of the total length of the first region of the aircraft surface airflow control device to the total length of the second region of the aircraft surface airflow control device to decrease, so as to reduce the flow range of the plasma generated by the aircraft surface airflow control device.

[0090] Increasing the ratio of the total length of the first region to the total length of the second region expands the excitation range of the first region, thereby increasing the plasma coverage area generated by the airflow control device on the aircraft surface. This is suitable for flow field adjustment when a larger excitation range is required. Decreasing the ratio of the total length of the first region to the total length of the second region shrinks the excitation range of the first region, reducing the plasma flow range. This is suitable for applications where local or fine flow field control is required.

[0091] This method controls the range of the generated plasma flow by adjusting the total length ratio of the two excitation regions (the first region and the second region) in the device. By changing this ratio, the size of the plasma excitation region can be dynamically adjusted in the application scenario, thereby achieving the goal of precise control of the separation flow.

[0092] In one embodiment, step S710 includes: controlling the first electrode of the aircraft surface airflow control device to move along the chordwise direction of the wing on which the aircraft surface airflow control device is located on one side surface of the insulating dielectric layer of the aircraft surface airflow control device, and increasing the total length of the first region after the movement. Step S720 includes: controlling the first electrode of the aircraft surface airflow control device to move along the chordwise direction of the wing on which the aircraft surface airflow control device is located on one side surface of the insulating dielectric layer of the device, and decreasing the total length of the first region after the movement.

[0093] Here, controlling the first electrode's movement along the chordwise direction of the wing increases the total length of the first region it covers, expanding the range of plasma flow excited by the device relative to other regions. Similarly, controlling the first electrode's movement along the chordwise direction of the wing decreases the total length of the first region, thereby shrinking the range of plasma flow excited by the device. This method allows for flexible adjustment of the excited region through simple displacement control.

[0094] The present application also provides an aircraft component, comprising: a high-voltage wire, a high-voltage power supply, and the aircraft surface airflow control device described in the above embodiment; the first electrode and the second electrode of the aircraft surface airflow control device are connected to the high-voltage power supply via the high-voltage wire.

[0095] The specific implementation methods described above further illustrate the objectives, technical solutions and beneficial effects of the present invention in detail. It should be understood that the above description is only a specific implementation method of the present invention and is not intended to limit the scope of protection of the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. An aircraft surface airflow control device, for installation on an aircraft surface, characterized in that: include: a first electrode, a second electrode and an insulating dielectric layer; The first electrode is provided on one side surface of the insulating dielectric layer and is configured to be directly exposed to the airflow on the surface of the aircraft; The second electrode is embedded in the other side of the insulating dielectric layer and is used to be closely attached to the surface of the aircraft; The first electrode is a conductor extending continuously along its length; The second electrode includes a plurality of conductor segments spaced apart along a length direction; The first electrode and the second electrode are parallel to each other along their respective length directions; The portion where the first electrode overlaps with the plurality of conductor segments is a first region. When the aircraft surface airflow control device is operated by high voltage electricity, the first region is used to generate plasma under high voltage electricity excitation. The plasma is used to form a directional plasma-excited airflow on the aircraft surface to prevent the airflow on the aircraft surface from separating from the aircraft surface. The portion of the first electrode that is not overlapped with the second electrode is a second region, and a ratio of a total length of the first region to a total length of the second region is greater than or equal to a preset threshold.

2. The aircraft surface airflow control device according to claim 1, characterized in that: The first electrode is a movable element, and changes the ratio of the total length of the first region to the total length of the second region by moving its position on one side surface of the insulating dielectric layer.

3. The aircraft surface airflow control device according to claim 2, characterized in that: At least one side of each of the conductor segments in the width direction is angularly offset from the width direction of the first electrode.

4. The aircraft surface airflow control device according to claim 3, characterized in that: The shape of each conductor segment is any one of a trapezoid, a triangle and a wave.

5. The aircraft surface airflow control device according to claim 4, characterized in that: The first electrode is in the shape of a quadrilateral with opposite sides parallel to each other.

6. The aircraft surface airflow control device according to claim 5, characterized in that: The plurality of conductor segments are all trapezoidal conductor segments with the same size and are arranged at equal intervals; The second electrode further includes a rectangular conductor segment vertically connected to the lower bases of the plurality of trapezoidal conductor segments; The first electrode is in a rectangular shape.

7. The aircraft surface airflow control device according to claim 6, characterized in that: The size parameters of the first electrode and the second electrode satisfy the following relationship: ,in, is the ratio of the total length of the first region to the total length of the second region, h is the total width of the second electrode, c is the width of the rectangular conductor segment, b is the horizontal distance between the first electrode and the rectangular conductor segment, d1 is the upper base length of the trapezoidal conductor segment, d2 is the lower base length of the trapezoidal conductor segment, and d3 is the spacing between adjacent trapezoidal conductor segments.

8. A method for controlling airflow on an aircraft surface, applied to an aircraft surface airflow control device according to any one of claims 1 to 7, characterized in that: include: controlling the ratio of the total length of the first region of the aircraft surface airflow control device to the total length of the second region of the aircraft surface airflow control device to increase, so as to increase the flow range of the plasma generated by the aircraft surface airflow control device; The ratio of the total length of the first region to the total length of the second region is controlled to decrease, so as to reduce the flow range of the plasma generated by the airflow control device on the aircraft surface.

9. The method for controlling airflow on an aircraft surface according to claim 8, wherein: The ratio of the total length of the first region of the aircraft surface airflow control device to the total length of the second region of the aircraft surface airflow control device is increased, including: Controlling the first electrode of the aircraft surface airflow control device to move along the chord direction of the wing where the aircraft surface airflow control device is located on one side surface of the insulating dielectric layer of the aircraft surface airflow control device, and increasing the total length of the first region after the movement; The controlling the ratio of the total length of the first region to the total length of the second region to decrease includes: The first electrode controlling the aircraft surface airflow control device moves along the chord direction of the wing where the aircraft surface airflow control device is located on one side surface of the insulating medium layer of the aircraft surface airflow control device, and the total length of the first area after the movement is reduced.

10. An aircraft component, characterized in that: include: The aircraft surface airflow control device according to any one of claims 1 to 7; high-voltage power lines; High voltage power supply; The first electrode and the second electrode of the aircraft surface airflow control device are connected to the high-voltage power supply through the high-voltage wire.

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