Wind resistance balancing wing plate

Abstract

The utility model provides a wind resistance balancing wing plate, which belongs to the technical field of balancing wing plates, and comprises a wing plate main body, the wing plate main body is divided into a front edge, a wing-shaped middle part and a rear edge along the spanwise direction, the wing plate main body is provided with a sawtooth structure, the sawtooth structure is continuously arranged triangular sawteeth, and the triangular sawteeth are arranged in the wing plate main body. The sawtooth structures are integrated on the edge of the wing plate body to form an integrated structure, the vertex of each sawtooth is located on the edge line of the wing plate body, gears of the sawtooth structures are arranged in a staggered mode, and the sawtooth structures are continuously distributed along at least one side edge of the wing plate body. The sawtooth structures are continuously distributed along the edge of at least one side of the wing plate body, preferably distributed on the edges of the two sides, so that the airflow optimization effect is maximized, turbulent flow of a traditional wind resistance balance wing plate is reduced, the smoothness of airflow is improved, and therefore wind resistance is reduced, and stability and efficiency are enhanced.

Description

Technical Field

[0001] The utility model belongs to the technical field of balancing wing plates, and in particular relates to a wind resistance balancing wing plate. Background Art

[0002] In the field of aeronautical engineering, wing panel design, as a key component of aircraft aerodynamic performance, has long been the focus of exploration and optimization by researchers. Although traditional wing panel design has made significant progress in the past few decades and has successfully achieved effective control of wind resistance to a certain extent, with the development of flight technology and the diversification of application needs, the limitations and challenges of traditional design have gradually become prominent, becoming an important bottleneck restricting the further improvement of aircraft performance.

[0003] Under high subsonic to transonic flight conditions, the primary challenge faced by traditional wing panel design is the airflow separation phenomenon at the edge of the wing panel. The intensification of this phenomenon not only directly leads to a significant increase in the wind resistance of the aircraft, but more seriously, it also triggers complex aerodynamic effects, such as vortex shedding and the generation of aerodynamic noise. Vortex shedding will cause the aerodynamic stability of the aircraft to decrease, affecting flight safety; while the increase in aerodynamic noise may expose the position of the aircraft and threaten the stealth performance, especially in military applications, which may mean the difference between life and death. Therefore, how to effectively suppress the airflow separation in high subsonic and transonic flight has become one of the core issues that need to be solved in wing panel design. Another major limitation of traditional wing panel design is the fixedness and singleness of its aerodynamic performance. These designs are often optimized under specific flight conditions (such as a specific altitude, speed or angle of attack). Once the flight environment changes, the aerodynamic efficiency and stability of the wing panel may drop significantly. For example, a wing that performs well at low speeds may fail due to airflow separation at high speeds; and a wing that works well in the thin atmosphere at high altitudes may also have a significant performance degradation in the dense atmosphere at low altitudes. This lack of adaptability forces aircraft to compromise between sacrificing performance and increasing complexity when facing changing flight missions and environments. Utility Model Content

[0004] In view of this, the utility model provides a wind resistance balancing wing plate, which reduces the turbulence of traditional wind resistance balancing wing plates by imitating the serrated surface structure of marine organisms, improves the smoothness of airflow, thereby reducing wind resistance and enhancing stability and efficiency.

[0005] The utility model is achieved in this way:

[0006] The utility model provides a wind resistance balancing wing panel, comprising a wing panel main body, wherein the wing panel main body is divided into a leading edge, a middle part of an airfoil and a trailing edge along a span direction, wherein the wing panel main body is provided with a sawtooth structure, wherein the sawtooth structure is a continuously arranged triangular sawtooth, wherein the sawtooth structure is integrated with the edge of the wing panel main body to form an integrated structure, wherein the vertex of each sawtooth is located on the edge line of the wing panel main body, and the arrangement of the gears of the sawtooth structure is a staggered arrangement.

[0007] Leading Edge: This is the first part of the wing that faces the airflow. The edge of the wing that the airflow first contacts. The design of the leading edge is crucial to controlling airflow separation and affects the lift and drag characteristics of the wing.

[0008] Trailing Edge: The end of the wing away from the impact of the airflow, that is, the last part of the airflow to leave. The design of the trailing edge is also important, it affects the nature of the wing wake and the resulting drag.

[0009] Airfoil Section: The cross-sectional shape of the wing perpendicular to the airflow direction. A typical airfoil has a rounded leading edge and a sharper trailing edge, which helps generate lift.

[0010] On the basis of the above technical solution, a wind resistance balance wing plate of the utility model can also be improved as follows:

[0011] Wherein, the sawtooth structure is continuously distributed along at least one side edge of the wing plate body.

[0012] The serration structure is continuously distributed along at least one side edge of the wing plate body, preferably distributed on both side edges, so as to maximize the airflow optimization effect.

[0013] Furthermore, the sawtooth adopts an isosceles triangle or semicircular top design, and the vertex angle of the sawtooth is 30° to 120°.

[0014] The beneficial effects of adopting the above-mentioned improvement scheme are as follows: the use of isosceles triangle or semicircular serrations can significantly reduce the turbulence generation at the edge of the wing plate, improve the smooth transition of the airflow, thereby reducing wind resistance and reducing noise.

[0015] Furthermore, the ratio of the height of the sawtooth structure to the maximum thickness of the middle portion of the airfoil of the wing panel body is 0.05:1 to 0.2:1.

[0016] The beneficial effect of adopting the above-mentioned improvement scheme is that by accurately controlling the ratio of the sawtooth height to the maximum thickness of the wing panel, a balance between lightweight design and high-performance aerodynamic characteristics can be achieved.

[0017] Furthermore, the spacing of the sawtooth structure is equal to half the wavelength of the mainstream direction of the airflow.

[0018] Furthermore, the airfoil of the wing panel body is a NACA series airfoil.

[0019] Furthermore, the wing panel body is a NACA 0012 airfoil.

[0020] Furthermore, the leading edge of the wing panel body adopts an arc transition, the arc is tangent to the chord line of the wing panel body at the leading edge point, and the ratio of the arc to the thickness of the wing panel body is preferably 0.1:1 to 0.5:1.

[0021] Furthermore, a smooth transition design is adopted at the connection between the wing plate body and the sawtooth structure, and a transition curve between the wing plate body and the sawtooth structure includes one of a parabola, a circular arc and an elliptical arc.

[0022] The beneficial effects of adopting the above-mentioned improvement scheme are: the smooth transition design can significantly reduce the airflow separation phenomenon and further reduce the resistance and noise.

[0023] Furthermore, the number of teeth of the sawtooth structure is equal to the ratio of the length of the wing plate body to the sum of the sawtooth spacing and the sawtooth height.

[0024] Compared with the prior art, the wind resistance balancing wing provided by the utility model has the following beneficial effects:

[0025] Significantly reduce wind resistance: The unique design of the serrated edge can effectively reduce airflow separation and reduce turbulence intensity, thereby significantly reducing wind resistance, improving the aerodynamic efficiency of aircraft or high-speed moving objects, extending the range or increasing the maximum speed;

[0026] Improved aerodynamic stability: By optimizing the shape, size and arrangement of the sawtooth structure, the utility model can maintain the aerodynamic stability of the wing panel under different flight conditions, reduce aerodynamic noise, and improve flight comfort and safety;

[0027] Enhanced adaptability: The serrated edge wing panels are designed to take into account the changing flight environment and can adapt to a wide range of speeds from low speed to supersonic speeds, as well as different altitudes and temperature conditions, demonstrating excellent environmental adaptability and versatility;

[0028] Lightweight and high strength: By using advanced materials and manufacturing processes, the utility model realizes the lightweight design of the wing panel while ensuring the structural strength and durability, providing the aircraft with better load capacity and longer service life;

[0029] Reduced maintenance costs: The serrated edge wing panels have a self-cleaning effect, which can reduce the accumulation of frost, dust and other attachments, thereby reducing maintenance frequency and costs and improving operational efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] In order to more clearly illustrate the technical solutions of the embodiments of the utility model, the drawings required for use in the description of the embodiments of the utility model will be briefly introduced below. Obviously, the drawings in the following description are only some embodiments of the utility model. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0031] Figure 1 This is an example diagram of a wind resistance balancing wing panel;

[0032] Figure 2 This is an enlarged view of part A;

[0033] Figure 3 is the geometrical characteristics of the NACA 0012 airfoil;

[0034] In the accompanying drawings, the components represented by the reference numerals are listed as follows:

[0035] 10. Wing plate body; 20. Sawtooth structure. DETAILED DESCRIPTION

[0036] In order to make the purpose, technical solution and advantages of the implementation mode of the present invention clearer, the technical solution in the implementation mode of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the implementation mode of the present invention.

[0037] like Figure 1 , Figure 2 As shown, it is a first embodiment of a wind resistance balancing wing provided by the utility model. In this embodiment, it includes a wing body 10, which is divided into a leading edge, a middle part of the airfoil and a trailing edge along the span direction, wherein the wing body 10 is provided with a sawtooth structure 20, which is a continuously arranged triangular sawtooth, and the sawtooth structure 20 is integrated with the edge of the wing body 10 to form an integrated structure, and the vertex of each sawtooth is located on the edge line of the wing body 10, and the arrangement of the gears of the sawtooth structure 20 is staggered.

[0038] The material of the sawtooth structure is preferably the same as that of the wing body to ensure the consistency and strength of the structure. Based on the carbon fiber composite material, a micron-level concave-convex structure can be formed on the sawtooth surface through micro-nano processing to further reduce surface friction and improve aerodynamic performance.

[0039] The staggered serration structure can effectively increase the complexity of airflow, reduce turbulence and improve airflow smoothness.

[0040] The suction and pressure sides of a drag-balancing wing operate according to Bernoulli's principle. As air flows over a wing, the airflow path through the suction side (usually the upper surface of the wing) is longer, resulting in increased velocity and, according to Bernoulli's equation, a decrease in pressure. Conversely, the airflow path through the pressure side (usually the lower surface of the wing) is shorter, resulting in lower velocity and, therefore, higher pressure. This pressure difference creates lift and is also a factor in wind resistance.

[0041] The location of the sawtooth structure depends on its functional goal. If the main purpose of the sawtooth structure is to reduce wind resistance and improve airflow stability, then it should be set on the suction side of the wing. The reasons are as follows:

[0042] Reduce airflow separation: On the suction surface, the airflow speed is high, which is easy to cause airflow separation at the wing tip or the trailing edge of the wing plate, forming vortices. The sawtooth structure can destroy these potential vortex areas, promote smooth attachment of airflow, and reduce wind resistance.

[0043] Reduce turbulence intensity: The turbulence intensity on the suction surface is high. The serrated structure can disperse the turbulence, reduce its intensity, and further reduce wind resistance by changing the local flow pattern of the airflow.

[0044] Improve aerodynamic noise: Airflow separation on the suction surface is often the main source of aerodynamic noise. The serrated structure can reduce aerodynamic noise, which is crucial to improving the quietness of an aircraft or vehicle.

[0045] Optimizing lift-to-drag ratio: By optimizing airflow distribution on the suction surface, the serrated structure helps reduce drag while maintaining lift, improving the lift-to-drag ratio, which is critical to improving the efficiency of aircraft or high-speed moving objects.

[0046] In certain specific cases, such as when it is necessary to improve the aerodynamic performance of the pressure surface or to optimize the airflow distribution at the leading and trailing edges of the wing, a serrated structure may also be provided on the pressure surface.

[0047] Among them, in the above technical solution, the sawtooth structure 20 is continuously distributed along at least one side edge of the wing plate body 10 .

[0048] Furthermore, in the above technical solution, the sawtooth adopts an isosceles triangle or semicircular top design, and the vertex angle of the sawtooth is 30° to 120°.

[0049] Furthermore, in the above technical solution, the ratio of the height of the sawtooth structure 20 to the maximum thickness of the middle part of the airfoil of the wing panel body 10 is 0.05:1 to 0.2:1.

[0050] Furthermore, in the above technical solution, the spacing of the sawtooth structure 20 is equal to half the wavelength of the mainstream direction of the airflow.

[0051] Furthermore, in the above technical solution, the airfoil of the wing panel body 10 is a NACA series airfoil.

[0052] Furthermore, in the above technical solution, the wing panel body 10 is a NACA 0012 airfoil.

[0053] Geometric features of NACA 0012 airfoil:

[0054] like Figure 3 As shown in the figure, the naming of the NACA 0012 airfoil follows the naming rules of the NACA series airfoils, where the first two digits "00" indicate that the airfoil is a symmetrical airfoil, that is, the shapes of the upper and lower surfaces of the airfoil are exactly the same, without obvious curvature or convexity; the last two digits "12" indicate that the maximum thickness of the airfoil accounts for 12% of the chord length, and the thickness is evenly distributed from the leading edge to the trailing edge of the airfoil, forming a more rounded shape. Specifically, the cross-sectional profile of the NACA 0012 airfoil remains consistent from the wing root to the wing tip, and its maximum thickness is located in the middle of the chord length, presenting a smooth and symmetrical curve.

[0055] Furthermore, in the above technical solution, the leading edge of the wing panel body 10 adopts an arc transition, the arc is tangent to the chord line of the wing panel body 10 at the leading edge point, and the ratio of the arc to the thickness of the wing panel body 10 is preferably 0.1:1 to 0.5:1.

[0056] Furthermore, in the above technical solution, a smooth transition design is adopted at the connection between the wing plate body 10 and the sawtooth structure 20, and a transition curve between the wing plate body 10 and the sawtooth structure 20 includes one of a parabola, a circular arc and an elliptical arc.

[0057] Furthermore, in the above technical solution, the number of teeth of the serration structure 20 is equal to the ratio of the length of the wing plate body 10 to the sum of the tooth spacing and the tooth height.

[0058] Specifically, the principle of the utility model is as follows: the core technology of the utility model lies in the innovative design of the edge of the wing panel, that is, the serration structure is applied to the edge of the wing panel to change the flow pattern of the airflow and reduce wind resistance and aerodynamic noise. Specifically, each serration of the serration edge is a carefully designed isosceles triangle or semicircular structure, and its top angle is preferably 60°. This angle has been theoretically calculated and experimentally verified to effectively promote the smooth transition of the airflow and reduce the generation of turbulence;

[0059] In addition, the ratio between the height H of the sawtooth and the maximum thickness Tmax of the wing is controlled between 0.05:1 and 0.2:1, ensuring the balance between the lightness and strength of the structure while minimizing wind resistance. The sawtooth is arranged in a staggered manner, with a certain position offset between adjacent sawtooths. This design can further increase the complexity of the airflow, make the airflow more stable, and reduce the airflow separation phenomenon;

[0060] The design of the transition zone between the serrated edge and the main body of the wing is also crucial. The arc transition with a radius of R is controlled in a ratio of 0.1:1 to 0.5:1 with the thickness of the main body of the wing, ensuring a smooth transition of the airflow at the edge of the wing and reducing the possibility of airflow separation. The number of serrations is calculated based on the length L of the wing and the spacing and height of the serrations to ensure effective coverage of the wing edge and maximize aerodynamic performance optimization;

[0061] In terms of material selection, the utility model tends to use the same material as the wing body, such as carbon fiber composite materials, to ensure structural consistency and strength. By processing the material surface at the micron-nano level to form a micron-level concave-convex structure, surface friction is further reduced and aerodynamic performance is improved;

[0062] In summary, the utility model not only significantly improves the aerodynamic performance of an aircraft or a high-speed moving object, but also enhances its adaptability and reliability through the innovative design of the serrated edge wind resistance balancing wing panel.

Claims

1. A wind resistance balancing wing panel, comprising a wing panel body (10), wherein the wing panel body (10) is divided into a leading edge, a middle part of an airfoil and a trailing edge along a span direction, and characterized in that: The wing plate body (10) is provided with a sawtooth structure (20), which is a continuously arranged triangular sawtooth. The sawtooth structure (20) is integrated with the edge of the wing plate body (10) to form an integrated structure. The vertex of each sawtooth is located on the edge line of the wing plate body (10), and the gears of the sawtooth structure (20) are arranged in a staggered manner.

2. A wind resistance balancing wing panel according to claim 1, characterized in that: The sawtooth structure (20) is continuously distributed along at least one side edge of the wing plate body (10).

3. A wind resistance balancing wing panel according to claim 2, characterized in that: The sawtooth adopts an isosceles triangle or semicircular top design, and the vertex angle of the sawtooth is 30° to 120°.

4. A wind resistance balancing wing panel according to claim 3, characterized in that: The ratio of the height of the sawtooth structure (20) to the maximum thickness of the middle part of the airfoil of the wing panel body (10) is 0.05:1 to 0.2:

1.

5. A wind resistance balancing wing panel according to claim 4, characterized in that: The spacing of the sawtooth structure (20) is equal to half the wavelength of the mainstream direction of the airflow.

6. A wind resistance balancing wing panel according to claim 5, characterized in that: The airfoil of the wing panel body (10) is a NACA series airfoil.

7. The wind resistance balancing wing panel according to claim 6, characterized in that: The wing panel body (10) is a NACA0012 airfoil.

8. The wind resistance balancing wing panel according to claim 7, characterized in that: The leading edge of the wing panel body (10) adopts an arc transition, the arc is tangent to the chord line of the wing panel body (10) at the leading edge point, and the ratio of the arc to the thickness of the wing panel body (10) is 0.1:1 to 0.5:

1.

9. The wind resistance balancing wing panel according to claim 8, characterized in that: A smooth transition design is adopted at the connection between the wing plate body (10) and the sawtooth structure (20), and a transition curve between the wing plate body (10) and the sawtooth structure (20) comprises one of a parabola, a circular arc and an elliptical arc.

10. The wind resistance balancing wing panel according to claim 9, characterized in that: The number of teeth of the sawtooth structure (20) is equal to the ratio of the length of the wing plate body (10) to the sum of the sawtooth spacing and the sawtooth height.

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