Aircraft surface airflow control device, method and component

Abstract

The invention relates to an aircraft surface airflow control device, method and component, and relates to the field of aircraft surface airflow separation control. The device comprises a first electrode, a second electrode and an insulating dielectric layer, the first electrode is arranged on the surface of one side of the insulating dielectric layer and is directly exposed in airflow on the surface of the aircraft; the second electrode is embedded into the other side of the insulating dielectric layer and clings to the surface of the aircraft; the first electrode is a conductor which continuously extends along the length direction; the second electrode comprises a plurality of conductor sections which are spaced along the length direction; the first electrode and the second electrode are parallel to each other along respective length directions; the overlapping part of the first electrode and the plurality of conductor sections is a first area, the non-overlapping part of the first electrode and the second electrode is a second area, and the ratio of the total length of the first area to the total length of the second area is greater than or equal to a preset threshold value. The device can solve the problems of high consumption and low efficiency, and the energy consumption is reduced while the separation flow control effect is kept.

Description

Technical Field

[0001] The present invention relates to the field of controlling the separation of airflow on the surface of an aircraft, and particularly to an airflow control device, method and component for the surface of an aircraft. Background Art

[0002] When an aircraft is flying, the airflow flows along the surface of its wing. In the adverse pressure gradient region, especially at high angles of attack, the low-energy fluid in the boundary layer cannot overcome the adverse pressure gradient. The airflow separates from the surface to form a separated flow. The separated flow will cause a sharp drop in the lift of the aircraft and a significant increase in drag, which may lead to wing stall. Therefore, a device is needed to keep the airflow attached to the wing surface for as long as possible.

[0003] In the prior art, a common device for preventing airflow separation is a plasma excitation device. It usually includes an upper electrode (also called an exposed electrode), a lower electrode (also called a covered electrode) and an insulating dielectric layer between the electrodes. Its working principle is: by applying an alternating excitation voltage with a certain frequency and amplitude between the upper and lower electrodes, a high electric field is generated between the electrodes, and then the gas near the dielectric layer is excited to form a plasma. This plasma has a high energy and ion concentration, and can introduce additional momentum and heat energy into the boundary layer, thereby improving the stability and attachment performance of the fluid in the boundary layer and suppressing the separation of the flow field.

[0004] However, due to the continuous distribution of the excitation region in the traditional continuous plasma excitation device, continuous excitation needs to maintain the excitation of the plasma over the total length, resulting in excessive energy consumption of the device, an increase in the weight of the device and a high use cost. Some other discontinuous exciters mainly achieve this by changing the shape of the upper electrode (such as changing from a straight bar shape to a curved shape), but this device has poor aerodynamic characteristics and the flow control effect is uncontrollable. 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 airflow control device, method and component for the surface of an aircraft to solve the problem of high energy consumption and low efficiency.

[0006] The present invention is achieved by the following technical solutions: According to the first aspect of the present application, there is provided an airflow control device for an aircraft surface, which is used to be installed on the surface of an aircraft and includes: a first electrode, a second electrode and an insulating dielectric layer; The first electrode is disposed on one side surface of the insulating dielectric layer and is used 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 that continuously extends 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 overlapping part of the first electrode and the plurality of conductor segments is the first region. When the high-voltage electricity is applied to the aircraft surface airflow control device to work, the first region is used to generate plasma under the excitation of high-voltage electricity. The plasma is used to form a directional plasma excitation airflow on the aircraft surface to prevent the airflow on the aircraft surface from separating from the aircraft surface; The non-overlapping part of the first electrode and 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.

[0007] 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 position on one side surface of the insulating dielectric layer.

[0008] In one embodiment, at least one side of each of the conductor segments in the width direction has an angular offset from the width direction of the first electrode.

[0009] In one embodiment, the shape of each of the conductor segments is any one of a trapezoid, a triangle, and a wavy shape.

[0010] In one embodiment, the shape of the first electrode is a quadrilateral with opposite sides parallel to each other.

[0011] In one embodiment, 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 perpendicularly connected to the lower bases of the plurality of trapezoidal conductor segments; The shape of the first electrode is a rectangle.

[0012] In one embodiment, the dimensional parameters of the first electrode and the second electrode satisfy the following relationship:

[0013] wherein, 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.

[0014] According to a second aspect of the present application, there is provided an aircraft surface airflow control method, which is applied to an aircraft surface airflow control device provided in the first aspect of the present application, and includes: 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; Controlling the ratio of the total length of the first region to the total length of the second region to decrease, so as to decrease the flow range of the plasma generated by the aircraft surface airflow control device.

[0015] In an embodiment, the 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 includes: 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 the total length of the moved first region increases; The controlling the ratio of the total length of the first region to the total length of the second region to decrease includes: 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 the total length of the moved first region decreases.

[0016] According to a third aspect of the present application, there is provided an aircraft component, including: The aircraft surface airflow control device provided in the first aspect of the present application; High-voltage wires; 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 wires.

[0017] Compared with the prior art, the present application has the following advantages and beneficial effects: This aircraft surface airflow control device, through its continuous first electrode and discontinuous second electrode, and the structure in which the total length of the first region is greater than or equal to a preset threshold value compared with the total length of the second region, can significantly reduce the power supply power and equipment weight of the device on the premise of ensuring that the excitation effect is equivalent to that of the traditional continuous plasma excitation device, and also avoid the disadvantages of the intermittent excitation device in the related art, such as increasing the surface roughness of the wing and the uncertainty associated with spanwise excitation, providing a better device for the aircraft to achieve separated flow control under conditions such as large angles of attack. Brief Description of the Drawings

[0018] To more clearly illustrate the technical solutions of the exemplary embodiments of the present invention, the following will briefly introduce the drawings required for use in the embodiments. It should be understood that the following drawings only show certain embodiments of the present invention, and thus should not be regarded as limiting the scope. For those of ordinary skill in the art, without creative efforts, other related drawings can also be obtained based on these drawings. In the drawings: Figure 1 is a planar projection schematic diagram of an airflow control device on the surface of an aircraft provided by the present application; Figure 2 is a planar projection diagram of a continuous plasma excitation device; Figure 3 is a planar projection diagram of an intermittent plasma excitation device; Figure 4 is the lift characteristic curve of the continuous plasma excitation device; Figure 5 is the lift characteristic curve of an airflow control device on the surface of an aircraft provided by the present application; Figure 6 is the dimensional drawing of the planar projection of an airflow control device on the surface of an aircraft provided by the present application; Figure 7 is an airflow control method on the surface of an aircraft provided by the present application.

[0019] Reference numerals in the drawings and corresponding component names: First electrode 110, second electrode 120, insulating dielectric layer 130. Specific embodiments

[0020] In the following, the term "comprising" or "may comprise" that can be used in various embodiments of the present invention indicates the presence of the functions, operations or elements of the present invention, and does 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 "comprising", "having" and their cognates are only intended to indicate a specific feature, number, step, operation, element, component or combination of the foregoing items, and should not be construed as first excluding the existence or addition of the possibility of one or more other features, numbers, steps, operations, elements, components or combinations of the foregoing items.

[0021] In various embodiments of the present invention, the expression "or" or "at least one of A or / and B" includes any combination 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.

[0022] Expressions used in various embodiments of the present invention (such as "first", "second", etc.) may modify various constituent elements in the various embodiments, but do 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 for the purpose of distinguishing one element from other elements. For example, the first user device and the 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, the first element may be referred to as the second element, and similarly, the second element may also be referred to as the first element.

[0023] It should be noted that: if it is described that one constituent element is "connected" to another constituent element, the first constituent element may be directly connected to the second constituent element, and a third constituent element may be "connected" between the first constituent element and the second constituent element. Conversely, when one constituent element is "directly connected" to another constituent element, it can be understood that there is no third constituent element between the first constituent element and the second constituent element.

[0024] The terms used in the various embodiments of the present invention are only for the purpose of describing 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 defined, all terms (including technical terms and scientific terms) used herein have the same meaning as commonly understood by those of ordinary skill in the art to which the various embodiments of the present invention pertain. The terms (such as those defined in a commonly used dictionary) will be interpreted as having the same meaning as the contextual meaning in the relevant technical field and will not be interpreted as having an idealized meaning or an overly formal meaning, unless clearly defined in the various embodiments of the present invention.

[0025] To make the objectives, technical solutions and advantages of the present invention clearer and more understandable, the present invention will be further described in detail below in conjunction with embodiments and drawings. The illustrative embodiments and descriptions thereof of the present invention are only for explaining the present invention and do not serve as a limitation to the present invention.

[0026] Figure 1 It is a schematic plan view of an airflow control device for the surface of an aircraft provided by this application. As Figure 1As shown, the device is for installation on the surface of an aircraft 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 surface of the insulating dielectric layer 130 and is used to be directly exposed to the airflow on the surface of the aircraft; the second electrode 120 is embedded in the other side of the insulating dielectric layer 130 and is used to closely adhere to the surface of the aircraft; the first electrode 110 is a conductor continuously extending along its length direction; the second electrode 120 includes a plurality of conductor segments spaced along the length direction; the first electrode 110 and the second electrode 120 are parallel to each other along their respective length directions; the overlapping part of the first electrode 110 and the plurality of conductor segments is the first region, and in the case where the device operates with high voltage applied, the first region is used to generate plasma under the excitation of high voltage, and the plasma is used to form a directional plasma excitation airflow on the surface of the aircraft to prevent the airflow on the surface of the aircraft from separating from the surface of the aircraft; the non-overlapping part of the first electrode 110 and 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, and the preset threshold is 0.5.

[0027] As Figure 1 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, and the overlapping area is the first region, and the non-overlapping area in the grid area corresponding to the first electrode is the second region.

[0028] The insulating dielectric layer is also a non-conductive material layer, which is used for electrically isolating the first electrode and the second electrode, and for jointly forming an electric field and an excitation effect with the first electrode and the second electrode to generate plasma. The side of the insulating dielectric layer where the first electrode is located refers to the side facing the fluid. The other side of the insulating dielectric where the second electrode is located refers to the side facing away from the fluid and also the side facing the component (such as the aircraft wing) to which the device is to be installed.

[0029] Continuously extending means that the first electrode has no interruption or segmentation in the entire extension direction. If the first electrode has an intermittent structure, it will increase the airflow interference and form unnecessary spanwise excitation. Compared with the intermittent structure, the continuous structure of the first electrode makes the wing surface of the aircraft equipped with the device smoother, thereby reducing the airflow interference, and can be evenly distributed along a specific direction (such as the chordwise position of the wing), so that plasma excitation can be generated in the chordwise direction.

[0030] Different from the first electrode, there is a preset physical distance between the conductor segments in the second electrode, such that the conductor segments are discontinuously distributed, thereby forming alternating first regions (also known as excitation regions) and second regions (also known as non-excitation regions, i.e., 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, which belongs to a discontinuous structure. Since the second electrode does not directly contact the fluid, its discontinuous structure will not interfere with the air flow, and compared with the continuous structure, it saves the material for manufacturing the second electrode. The first electrode and the second electrode can be made of conductive materials such as copper foil.

[0031] Overlap refers to the overlap of the multiple conductor segments of the first electrode and the second electrode in the normal projection. The ratio of the total length of the first region to the total length of the second region reflects the plasma excitation effect. Since the plasma is mainly generated at the edges of the first region, the length ratio can be used to measure the excitation effect. Through experimental verification, when this ratio is not less than 0.5, the device can achieve the same plasma excitation effect as that of a continuous plasma excitation device. Therefore, the preset threshold can be set to 0.5.

[0032] When actually using this device, a preset excitation voltage needs to be applied between the first electrode and the second electrode. After applying the excitation voltage, a plasma excitation region is formed in the first region. The plasma generated in these regions enhances the fluid energy in the boundary layer through the action of the electric field and hydrodynamic force, and improves the fluid attachment ability. In addition to directly disturbing the air flow in the excitation region, the air flow in the excitation region also has an entrainment effect, and the separated flow in the region where no excitation is applied can also be controlled. Experiments have found that when the ratio of the total length of the excitation region to the discontinuous region is not less than 1:2, the same control effect as that of a continuous plasma excitation device can be obtained, and at the same time, the power consumption is reduced by about 2 / 3.

[0033] When applying the device provided by this application, the device should be arranged along the chord direction of the leading edge of the aircraft wing, where the first electrode should face the fluid side and be directly exposed to the air, and the side of the insulating dielectric layer where the second electrode is located faces the wing. A preset high-voltage alternating current is applied between the first electrode and the second electrode to form a plasma excitation region in the first region, and the boundary layer attachment is improved through local aerodynamic disturbance, thereby achieving the effect of separated flow control.

[0034] Figure 2 and Figure 3 are schematic diagrams of two types of plasma excitation devices in the related art. Among them, Figure 2 is a planar 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. As Figure 2The projection of the shown lower electrode 220 completely covers the projection of the upper electrode 210. In this traditional continuous plasma excitation device, due to the continuous distribution of the excitation region, continuous excitation requires maintaining the plasma excitation of the total length, resulting in excessive energy consumption of the device, increased device weight, and high usage costs.

[0035] Figure 3 is a plan projection view of a discontinuous plasma excitation device, and this projection plane is parallel to the plane of the insulating dielectric layer of the device. As Figure 2 shown, the upper electrode 310 is a discontinuous structure, the lower electrode 320 is a continuous structure, and the projection of the upper electrode 310 and the projection of the lower electrode 320 partially overlap. This excitation device is mainly achieved by changing the shape of the upper electrode (such as changing from a straight bar shape to a curved shape), but this method makes the structure complicated, equivalent to increasing the surface roughness of the wing, resulting in the premature transition of the laminar boundary layer and the deterioration of aerodynamic characteristics. In addition, this discontinuous actuator will discharge along the spanwise direction during discharge, not only consuming more energy, but also the spanwise jet generated will cause the flow control effect to be uncontrollable.

[0036] The aircraft surface airflow control device provided by the present disclosure can use a continuous first electrode and a discontinuous second electrode, and set the total length of the first region and the total length of the second region to be greater than or equal to a preset threshold, which can significantly reduce the power supply power and device weight of the device on the premise of ensuring that the excitation effect is equivalent to that of the traditional continuous plasma excitation device. Figure 4 is the lift characteristic curve of the continuous plasma excitation device. Figure 5 is the lift characteristic curve of an aircraft surface airflow control device provided by the present application. Figure 4 and Figure 5 The abscissa of is the angle of attack, that is, the angle between the chord line of the wing and the airflow direction, and the ordinate is the lift coefficient, that is, it is used to describe the ability of the plasma excitation device to generate lift in the airflow. As Figure 4 and Figure 5 shown, an aircraft surface airflow control device provided by the present application can increase the wing lift coefficient and achieve the same effect as the continuous plasma excitation device. And it can also avoid the disadvantages of the discontinuous excitation device in the related technology, such as increasing the wing surface roughness and the uncertainty associated with spanwise excitation, and provide a better device for the aircraft to achieve separated flow control under conditions such as large angles of attack.

[0037] 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 position on one side surface of the insulating dielectric layer.

[0038] In the device provided by this application, the first electrode is designed as a movable element, which is installed on the surface of the insulating dielectric layer facing the fluid. As a movable element, the first electrode can be adjusted in position on the surface of the insulating dielectric layer by means such as disassembly and sliding. Since the first electrode is not embedded in the insulating dielectric layer but is directly installed on its surface, by adjusting the position of the first electrode, the overlapping situation with the conductor segment of the second electrode can be changed without disassembling the insulating layer to modify the lower electrode.

[0039] Specifically, when the device is installed at the leading edge of the aircraft wing, the position of the first electrode can be adjusted along the chord direction of the wing to achieve the following flow control strategies. When it is necessary to enhance the flow field control effect, by moving the first electrode, the total length of the first region is increased and the total length of the second region is decreased, thereby increasing the ratio between the two and enhancing the excitation intensity. When it is necessary to reduce the flow control effect or lower the energy consumption, the position of the first electrode is adjusted to decrease the total length of the first region and increase the total length of the second region, reducing the ratio and achieving energy-saving operation.

[0040] It should be noted that the device provided by this application does not limit the form of the specific first electrode moving mechanism, and various mechanical or electric control systems can be adopted according to the actual application requirements to realize the position adjustment of the first electrode on the surface of the insulating dielectric layer.

[0041] Adopting the movable first electrode enables the device to flexibly adjust the ratio of the excitation region to the non-excitation region according to the flow field control requirements of different states or flight conditions of the aircraft, so as to adapt to the differentiated control requirements under various flight conditions.

[0042] In an embodiment, at least one side of each conductor segment in the width direction has an angular offset from the width direction of the first electrode.

[0043] Here, the width direction of the conductor segment refers to the direction orthogonal to the extension of the second electrode along the length direction. Similarly, the width direction of the first electrode refers to the direction orthogonal to the extension of the first electrode along the length direction. At least one side of the conductor segment has an angular offset from the side of the first electrode, and this angular offset enables the conductor segment not to adopt the common rectangular structure but can be designed as a trapezoid, triangle or other non-rectangular shapes, and the offset angle can be determined according to the specific application requirements. By way of example, as Figure 1 shown, multiple conductor segments in the second electrode can be trapezoids, and the first electrode can be a rectangle. As can be seen from Figure 1 , there is an angular offset between the hypotenuse of the trapezoidal grid region and the long side of the narrow strip grid region, that is, there is an angular offset between the projection of the conductor segment and the side of the first electrode in the width direction.

[0044] With this structure, when the first electrode moves in the width direction, the overlapping situation formed by it and the second electrode conductor segments changes, thereby changing the total lengths of the excitation region (the first region) and the non-excitation region (the second region) and their ratio. The angular offset causes the plasma intensity to gradually change along the flow direction, forming a smoother control transition region, thereby reducing the flow field disturbance and improving the fluid control effect.

[0045] In one embodiment, the shape of each conductor segment is any one of a trapezoid, a triangle, and a wavy shape.

[0046] Here, each conductor segment can be set to the same or different shapes, and the shape can be any one of a trapezoid, a triangle, and a wavy shape. When the first electrode moves in the width direction, the trapezoidal, triangular, and wavy shapes of the conductor segments can improve the transition between the excitation region and the non-excitation region, making the plasma intensity gradually change, which helps to reduce the flow field disturbance and transient effect.

[0047] In one embodiment, the shape of the first electrode is a quadrilateral with opposite sides parallel to each other.

[0048] Here, the first electrode is a quadrilateral structure with opposite sides parallel to each other. For example, it can be a rectangle or a parallelogram. The quadrilateral structure with opposite sides parallel can make the overlapping region between the first electrode and the second electrode conductor segments maintain a relatively stable shape and size, so that the excitation region is evenly distributed. Compared with an irregular shape, the quadrilateral of the first electrode with opposite sides parallel can make the change of the overlapping situation formed by it and the second electrode conductor segments easier to calculate when the first electrode moves in the width direction.

[0049] As Figure 1 shown, in one embodiment, multiple 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 perpendicular to the lower bases of the multiple trapezoidal conductor segments; the shape of the first electrode is a rectangle.

[0050] Here, the trapezoidal conductor segments with equal size and equal intervals can make the excitation region generate a uniform and stable electric field distribution, thereby forming a continuous and controllable plasma excitation effect. The geometric shape of the trapezoidal conductor segment is gradually changing when adjusting the edge of the excitation region, which can reduce the disturbance of the flow field transition region. At the same time, the vertically connected rectangular conductor segment makes the second electrode a whole through its continuity, which is convenient for production and processing.

[0051] Figure 6 is the dimensional drawing of the planar projection of an aircraft surface airflow control device provided by this application, and the projection plane is parallel to the plane of the insulating dielectric layer of the device. As Figure 6 shown, in one embodiment, the dimensional parameters of the first electrode and the second electrode satisfy the following relational expression:

[0052] Wherein, 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 length of the upper base of the trapezoidal conductor segment, d2 is the length of the lower base of the trapezoidal conductor segment, and d3 is the distance between adjacent trapezoidal conductor segments.

[0053] 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 (h - c - b) is: d1 + (h - c - b) / (h - c)×(d2 - d1). The length of a single excitation region is: Ls = d1 + (h - c - b) / (h - c)×(d2 - d1) = (h - c - b)(d2 - d1) / (h - c) + d1, which simplifies to: Ls = [(h - c - b)(d2 - d1) + (h - c)d1] / (h - c). The length of a period of a complete excitation region and discontinuous region is (d2 + d3). Therefore, the length of the discontinuous region = the length of the period - the length of the excitation region: Lg = (d2 + d3) - Ls, which expands to: Lg = (d2 + d3) - [(h - c - b)(d2 - d1) + (h - c)d1] / (h - c), and is arranged in a common denominator form: Lg = [(d2 + d3)(h - c) - (h - c - b)(d2 - d1) - (h - c)d1] / (h - c) = [(d2 + d3 - d1)(h - c) - (h - c - b)(d2 - d1)] / (h - c). Therefore, the ratio of the total length of the first region to the total length of the second region = Ls / Lg = [(h - c - b)(d2 - d1) + (h - c)d1] / [(d2 + d3 - d1)(h - c) - (h - c - b)(d2 - d1)].

[0054] During the production and processing of the above device, the above dimensional parameters can be referred to, but the specific parameters are not limited thereto. In addition, in practical applications, after moving the first electrode, the ratio of the total lengths of the first region and the second region can be recalculated and determined according to the above relationship.

[0055] Specifically, when the first electrode moves parallel to the upper base side of the trapezoidal conductor segment by a distance t, it is equivalent to b becoming (b + t): Ls = [(h - c - b - t)(d2 - d1) + (h - c)d1] / (h - c). Similarly, the length of the discontinuous region after movement: Lg = [(d2 + d3 - d1)(h - c) - (h - c - b - t)(d2 - d1)] / (h - c). Therefore, the ratio τ after movement = Ls / Lg = [(h - c - b - t)(d2 - d1) + (h - c)d1] / [(d2 + d3 - d1)(h - c) - (h - c - b - t)(d2 - d1)].

[0056] Figure 7 It is an air flow control method for the surface of an aircraft provided by this application. Based on the same concept, this method can be applied to the above-mentioned air flow control device for the surface of an aircraft, including the following steps.

[0057] Step S710: Control the ratio of the total length of the first region of the air flow control device for the surface of the aircraft to the total length of the second region of the air flow control device for the surface of the aircraft to increase, so as to increase the flow range of the plasma generated by the air flow control device for the surface of the aircraft.

[0058] Step S720: Control the ratio of the total length of the first region of the air flow control device for the surface of the aircraft to the total length of the second region of the air flow control device for the surface of the aircraft to decrease, so as to decrease the flow range of the plasma generated by the air flow control device for the surface of the aircraft.

[0059] Increasing the ratio of the total length of the first region to the total length of the second region will expand the excitation range of the first region, thereby increasing the plasma coverage area excited by the air flow control device for the surface of the aircraft, which 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 will contract the excitation range of the first region, reducing the flow range of the plasma, which is suitable for occasions of local or fine flow field control.

[0060] This method controls the flow range of the generated plasma by adjusting the total length ratio of the two excitation regions (the first region and the second region) in the device. By changing the ratio, the dynamic adjustment of the size of the plasma excitation region can be realized in the application scenario, so as to achieve the purpose of accurately controlling the separated flow.

[0061] In one embodiment, step S710 includes: controlling a first electrode of the aircraft surface air flow control device to move along the chord direction of the wing where the aircraft surface air flow control device is located on one surface of the insulating dielectric layer of the aircraft surface air flow control device, and the total length of the moved first area increases. Step S720 includes: controlling the first electrode of the aircraft surface air flow control device to move along the chord direction of the wing where the aircraft surface air flow control device is located on one surface of the insulating dielectric layer of the device, and the total length of the moved first area decreases.

[0062] Here, by controlling the first electrode to move along the chord direction of the wing, the total length of the first area covered by it increases, and the plasma flow range excited by the device expands relative to other areas. Similarly, by controlling the first electrode to move along the chord direction of the wing, the total length of the first area decreases, and the excited plasma flow range contracts accordingly. This method can flexibly adjust the excitation area range through simple displacement control.

[0063] The present application also provides an aircraft component, including: a high-voltage wire, a high-voltage power supply, and the aircraft surface air flow control device described in the above embodiment; the first electrode and the second electrode of the aircraft surface air flow control device are connected to the high-voltage power supply through the high-voltage wire.

[0064] The specific embodiments described above further elaborate on the purpose, technical solutions, and beneficial effects of the present invention. It should be understood that the above description is only the specific embodiments of the present invention and is not used to limit the protection scope of the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention shall be included in the protection scope of the present invention.

Claims

1. An airflow control device for the surface of an aircraft, which is used to be installed on the surface of the aircraft, and is characterized in that, Comprising: A first electrode, a second electrode, and an insulating dielectric layer; The first electrode is disposed on one side surface of the insulating dielectric layer and is used 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 closely adhere to the surface of the aircraft; The first electrode is a conductor continuously extending 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 overlapping part of the first electrode and the plurality of conductor segments is a first region. When the airflow control device on the aircraft surface works under high voltage, the first region is used to generate plasma under the excitation of high voltage. The plasma is used to form a directional plasma excitation airflow on the surface of the aircraft to prevent the airflow on the surface of the aircraft from separating from the surface of the aircraft; The non-overlapping part of the first electrode and the second electrode is a 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.

2. The airflow control device for the surface of an aircraft according to claim 1, characterized in that, 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 position on one side surface of the insulating dielectric layer.

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

4. The airflow control device for the surface of an aircraft according to claim 3, wherein The shape of each of the conductor segments is any one of a trapezoid, a triangle, and a wavy shape.

5. The airflow control device for the surface of an aircraft according to claim 4, wherein The shape of the first electrode is a quadrilateral with opposite sides parallel to each other.

6. The airflow control device for the surface of an aircraft according to claim 5, wherein 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 perpendicularly connected to the lower bases of the plurality of trapezoidal conductor segments; The shape of the first electrode is a rectangle.

7. The airflow control device for the surface of an aircraft according to claim 6, characterized in that, The dimensional parameters of the first electrode and the second electrode satisfy the following relational expression: , where 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 length of the upper base of the trapezoidal conductor segment, d2 is the length of the lower base of the trapezoidal conductor segment, and d3 is the spacing between adjacent trapezoidal conductor segments.

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

9. A method for controlling the airflow on the surface of an aircraft according to claim 8, characterized in that, The increase in the ratio of the total length of the first region of the airflow control device on the aircraft surface to the total length of the second region of the airflow control device on the aircraft surface includes: Controlling the first electrode of the airflow control device on the aircraft surface to move along the chord direction of the wing where the airflow control device on the aircraft surface is located on one side surface of the insulating dielectric layer of the airflow control device on the aircraft surface, and the total length of the moved first region increases; The control of the ratio of the total length of the first region to the total length of the second region to decrease includes: Controlling the first electrode of the airflow control device on the aircraft surface to move along the chord direction of the wing where the airflow control device on the aircraft surface is located on one side surface of the insulating dielectric layer of the airflow control device on the aircraft surface, and the total length of the moved first region decreases.

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

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