Wing for enhancing aerodynamic performance of flapping wing based on bionic leading edge wing feathers

Abstract

The invention relates to a wing for enhancing the aerodynamic performance of a flapping wing based on bionic leading edge wing feathers, belongs to the technical field of aircraft design and manufacturing, solves the problem that the existing wing of the flapping wing is difficult to fly with high maneuverability and variable attitude, and can effectively improve the leading edge deflection of the wing and improve the flight performance of the flapping wing. The bionic front edge wing plume is introduced to the front edge of the curved wing body to form a flow direction vortex pair, and the evolution rule of an incoming flow boundary layer is improved; the separation phenomenon of the boundary layer at the large attack angle of the flapping wing is inhibited and / or improved through vortex-induced downwash and momentum transfer, and the aerodynamic performance of the flapping-wing unmanned aerial vehicle is improved; the bionic leading edge wing feather does not change the aerodynamic shape of an existing wing, hardware design can be completed only by adding a small-scale turbulent flow structure to the leading edge, the overall structure is simple, and maintenance is easy; and through free control of wing feather feature shapes, numbers and angles, the pneumatic lifting of the flapping-wing unmanned aerial vehicles with different flight working conditions and performance requirements is served.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft design and manufacturing, and in particular to a wing with enhanced flapping aerodynamic performance based on bionic leading edge wing feathers. Background Art

[0002] In nature, many animals, such as birds and insects, have excellent flying abilities and can fly, glide, and hover freely in the air. Bionic flapping-wing aircraft is an aircraft that imitates the wing structure and flight principle of flying animals in nature, and uses flapping wing motion to generate lift and propulsion. It has high flexibility and maneuverability. Its research and application fields are wide, including military reconnaissance, disaster relief, scientific research, etc. It has low noise, high efficiency, and low energy consumption, and can achieve efficient flight missions in complex environments. With the continuous development and improvement of bionic technology, bionic flapping wings are becoming an important development direction in the field of aircraft design, serving military science and technology and economic development.

[0003] However, flapping-wing flight involves continuous flapping of the wing at a large angle, during which vortices and separation flows that vary with time are generated, which have a significant impact on the aerodynamic performance of the wing. Among them, the generation of separation flow and the shedding of vortices cause the lift of flapping-wing aircraft to decrease and the drag to increase, posing a potential hazard to safe service. To avoid this risk, existing flapping-wing aircraft often sacrifice maneuverability and only achieve a single flight attitude. Therefore, the current design of the aerodynamic shape of flapping-wing wings has certain limitations and cannot fully demonstrate the high maneuverability and variable attitude flight capabilities unique to flapping wings.

[0004] In summary, in order to further improve the flight capability of flapping-wing aircraft, it is necessary to improve the aerodynamic performance of existing wings and suppress / improve the separation flow phenomenon existing in the wing flapping process. Summary of the invention

[0005] In view of the above problems, the present invention provides a wing with enhanced flapping aerodynamic performance based on bionic leading edge wing feathers, which solves the problems of poor flapping wing maneuverability and difficulty in changing attitude flight, effectively suppresses and optimizes the flow separation phenomenon existing in the flapping wing flapping process, and improves flapping wing flight performance.

[0006] The present invention provides a wing with enhanced flapping wing aerodynamic performance based on bionic leading edge wing feathers, comprising at least one bionic leading edge wing feather 1 and a curved wing body 7; the wing is a wing of a flapping wing UAV;

[0007] The curved wing body 7 includes a leading edge 2, a wing root 4, a wing tip 5 and a trailing edge 6;

[0008] Preferably, at least one of the bionic leading edge wing feathers 1 is arranged on the leading edge 2 of the curved wing body 7 to form a convex independent structure;

[0009] Furthermore, the shape and structure of the bionic leading edge wing feathers 1 can be freely adjusted according to the performance requirements of the aircraft, including barbed leading edge wing feathers, curved leading edge wing feathers, semicircular leading edge wing feathers, triangular leading edge wing feathers, rectangular leading edge wing feathers or diamond leading edge wing feathers;

[0010] Exemplarily, the barbed leading edge wing feather is a triangular leading edge wing feather with a softened edge;

[0011] Furthermore, the barbed leading edge wing feathers are barbed leading edge wing feathers in the shape of a parrot's beak;

[0012] In one embodiment of the present invention, the barbed leading edge feathers can reduce the wake velocity difference of a partially stalled wing and delay flow separation; for a fully stalled wing, a boundary layer separator can be created to prevent the stall from propagating outward.

[0013] Exemplarily, one side of the curved leading edge wing feather is an edge with a curve, and the edge is formed by the feather tips of multiple groups of feathers arranged adjacent to each other to form a continuous curved edge;

[0014] Furthermore, the feather tips of the plurality of groups of feathers are in the shape of an arc with a pointed top, and the feather tips of the plurality of groups of feathers are inclined in the same direction or in different directions;

[0015] The bionic leading edge feathers in the present invention can suppress the separation of boundary layer vortices, generate relatively higher lift, and at the same time play a role in flexibly adjusting the direction. Bionic leading edge feathers of different shapes produce vortex shapes of different shapes and different numbers, and the effect of suppressing boundary layer separation varies in strength.

[0016] The different external shapes of the bionic leading edge wing feathers 1 described in the present invention produce different flow vortex shapes, which lead to different momentum transfer and vortex transfer. The size of the transfer is related to the shape of the aircraft and the size and position of the shape.

[0017] Furthermore, the center of the bionic leading edge wing feather 1 is taken as the coordinate origin, the span direction is the x-axis, and the chord direction is the y-axis;

[0018] The geometric length of the bionic leading edge wing feather 1 in the x-axis direction is not greater than 15% of the length of the curved wing body 7;

[0019] The geometric length of the bionic leading edge wing feather 1 in the y-axis direction is not greater than 15% of the chord length of the curved wing body 7;

[0020] The proportional relationship between the geometric length of the bionic leading edge wing feather 1 and the curved wing body of the present invention is consistent with the biological characteristics of eagles in nature, and is closer to the actual proportional size of the organism. This ratio is suitable for all shapes and sizes.

[0021] Furthermore, when a bionic leading edge wing feather is provided, the bionic leading edge wing feather can be provided at any position within the range from the leading edge wing root to the wing tip 5 of the curved wing body 7;

[0022] Exemplarily, when a bionic leading edge wing feather is provided, the bionic leading edge wing feather may be provided at the leading edge 1 / 2 8, the leading edge 1 / 4 9, the leading edge 3 / 4 10 or the wing tip 5 of the curved wing body 7;

[0023] In one embodiment of the present invention, the bionic leading edge wing feather 1 is coupled with the incoming flow to generate a flow vortex, and the flow vortex induces the downwash of the bionic leading edge wing feather 1 and the boundary layer of the leading edge 2 of the curved wing body 7 to transfer momentum and vortex, thereby suppressing the boundary layer separation of the leading edge 2 of the curved wing body 7 and enhancing the flapping wing lift-to-drag ratio and stall angle; the characteristics of the flow vortex are autonomously controllable with the bionic leading edge wing feather 1 of the curved wing body 7, and are adjusted accordingly according to the incoming flow environment and aircraft performance requirements; the aircraft performance requirements include speed performance, deformation ability and control performance; the shape, size and direction of the flow vortex are adjusted by autonomously controlling the shape, size and angle of the leading edge wing feathers, thereby changing the aerodynamic performance of the wing;

[0024] Furthermore, the bionic leading edge wing feather 1 has a double degree of freedom angle; the double degree of freedom angle includes a span angle α and a chord angle β, and the direction and shape of the streamwise vortex are adjusted by changing the span angle and the chord angle;

[0025] It can be understood that, with the center of the bionic leading edge wing feather 1 as the coordinate origin, the span direction is the x-axis, and the chord direction is the y-axis, forming a span direction angle α and a chord direction angle β;

[0026] Furthermore, the spanwise angle α of the bionic leading edge wing feather 1 is expressed as:

[0027] α=f1(θ(t),γ(t),v(t))

[0028] Among them, θ is the wing flapping angle, γ is the wing attack angle, η is the wing offset angle, t is the time, and f1(·) is the spanwise angle α limiting function;

[0029] The expression of the chord angle β of the bionic leading edge wing feather 1 is:

[0030] β=f2(θ(t),γ(t),η(t))

[0031] Where f2(·) is the limiting function of the chord angle β.

[0032] Furthermore, the optional angle range of the spanwise angle α is 0 to π, and the optional angle range of the chordwise angle β is 0 to π / 2;

[0033] Exemplarily, the spanwise angle α of the bionic leading edge wing feathers 1 is π / 2; the chordwise angle β of the bionic leading edge wing feathers 1 is π / 4.

[0034] Furthermore, the double-degree-of-freedom angle of the bionic leading edge wing feather 1 is determined based on the constraint condition of the double-degree-of-freedom angle;

[0035] The constraint condition expression of the double-degree-of-freedom angle is:

[0036] 0≤α≤π;

[0037] α s =f4(α,β,Re) 0≤α≤π;

[0038] Among them, C L / C D is the lift-to-drag ratio of the wing, α s is the stall angle of the wing, Re is the Reynolds number; C L is the lift coefficient, C D Represents the drag coefficient, C L / C D is the lift-to-drag ratio of the wing, α s is the stall angle of the wing, Re is the Reynolds number; C L is the lift coefficient, C D represents the drag coefficient, f3(·) is the limiting function of the wing lift-to-drag ratio, and f4(·) is the limiting function of the wing stall angle.

[0039] Furthermore, the double-degree-of-freedom angle of the bionic leading-edge wing feather 1 changes dynamically with the wing flapping action, thereby optimizing the flapping wing flow structure in real time;

[0040] Furthermore, the bionic leading edge wing feathers 1 are distributed on the leading edge 2 of the curved wing body 7; the number and position of the bionic leading edge wing feathers 1 are variable;

[0041] Furthermore, the number of the bionic leading edge wing feathers 1 is determined by the shape characteristics of the curved wing body 7 and the performance of the aircraft;

[0042] Furthermore, the number of the bionic leading edge wing feathers is expressed as:

[0043] l a n≤0.5l w

[0044] Where n is the number of bionic leading edge wing feathers, l a is the base length of the bionic leading edge wing feather 1, l w is the leading edge length of the wing;

[0045] For example, the plurality of bionic leading edge wing feathers 1 are regularly distributed with equal spacing or irregularly distributed with non-equal spacing on the leading edge 2 of the curved wing body 7 .

[0046] It can be understood that when the overall stability of the wing is required to enhance the lift-to-drag ratio of the wing, multiple bionic leading edge wing feathers 1 are regularly distributed with equal spacing on the leading edge of the wing; when the lift-to-drag ratio at a specific position of the wing is required to be improved to achieve stable turning of the aircraft, etc., multiple bionic leading edge wing feathers 1 are irregularly distributed with non-equidistant spacing on the leading edge of the wing.

[0047] Furthermore, the bionic leading edge wing feathers and the curved wing body are integrally formed through 3D printing and assembled using a hinge structure; the hinge structure and the curved wing body have a smooth transition.

[0048] The present invention introduces a bionic wing feather structure at the leading edge of the wing to form a streamwise vortex pair, thereby improving the evolution law of the boundary layer at the leading edge of the wing; suppresses / improves the separation phenomenon of the boundary layer at a large angle of attack of the flapping wing through vortex-induced downwash and momentum transfer, thereby improving the aerodynamic performance of flapping-wing UAVs; the bionic wing feather structure does not change the existing aerodynamic shape of the wing, and only a small-scale spoiler structure is added to the leading edge to complete the hardware design, and the overall structure is simple and easy to maintain; through the free control of the characteristic shape, number and angle of the wing feathers, the aerodynamic improvement of flapping-wing UAVs with different flight conditions and performance requirements can be served.

[0049] Compared with the prior art, the present invention has at least the following beneficial effects:

[0050] (1) The wing with enhanced flapping wing aerodynamic performance based on bionic leading edge wing feathers of the present invention has a bionic wing feather structure added to the leading edge of the wing, which couples with the free flow to generate a streamwise vortex pair, thereby inducing momentum transfer and vortex transfer between the downwash and the leading edge boundary layer, inhibiting / improving its flow separation at a large angle of attack, and then improving the aerodynamic performance of the wing, laying a foundation for the high-maneuverability flight of flapping-wing aircraft;

[0051] (2) The wing of the present invention with enhanced flapping wing aerodynamic performance based on bionic leading edge wing feathers can freely adjust the shape and number of the leading edge wing feather structure according to the performance requirements of the aircraft, generate flow vortices with different rotations, shapes and numbers, and realize multifunctional adjustment of the size, direction and shape of the leading edge flow. It can be applied to multiple flight environments such as multi-directional incoming flow, aircraft steering, and aircraft ascending and descending and hovering, thereby increasing the breadth of application;

[0052] (3) The wing of the present invention with enhanced flapping aerodynamic performance based on bionic leading edge wing feathers, the double degree of freedom angle of the wing feather structure changes autonomously during the wing flapping process, which can maximize the aerodynamic efficiency at every moment during the service of the aircraft, and effectively improve its endurance and load capacity while ensuring the service safety of the aircraft;

[0053] (4) The wing of the present invention with enhanced flapping wing aerodynamic performance based on bionic leading edge feathers has a small size of bionic leading edge feathers, which can realize the regulation of the flow around the leading edge of the flapping wing. In the field of flow control, it belongs to passive flow control, and its control effect is positively correlated with the flight speed. The only energy input required is the control of the wing feather angle, which is low-energy and high-efficiency overall. BRIEF DESCRIPTION OF THE DRAWINGS

[0054] The drawings are only for the purpose of illustrating particular embodiments and are not to be construed as limiting the invention.

[0055] Figure 1 Schematic diagram of the overall structure of a wing for enhancing flapping wing aerodynamic performance based on bionic leading edge wing feathers in an embodiment of the present invention;

[0056] Figure 2 Schematic diagram of the aerodynamic principle of the bionic leading edge wing feather in an embodiment of the present invention;

[0057] Figure 3 (a)-(f) are schematic diagrams of characteristic shapes of bionic leading edge wing feathers in an embodiment of the present invention;

[0058] Figure 4 Schematic diagram of the change of the double-degree-of-freedom angles of the bionic leading edge wing feathers in an embodiment of the present invention;

[0059] Figure 5 Schematic diagram of the layout strategy of bionic leading edge wing feathers in an embodiment of the present invention.

[0060] Reference numerals:

[0061] 1. Bionic leading edge wing feathers, 2. Leading edge, 3. Base length, 4. Wing root, 5. Wing tip, 6. Trailing edge, 7. Curved wing body, 8. 1 / 2 of the leading edge, 9. 1 / 4 of the leading edge, 10. 3 / 4 of the leading edge. DETAILED DESCRIPTION

[0062] In order to more clearly understand the above-mentioned purpose, features and advantages of the present invention, the present invention is further described in detail below in conjunction with the accompanying drawings and specific embodiments. It should be noted that, in the absence of conflict, the embodiments of the present invention and the features in the embodiments can be combined with each other. In addition, the present invention can also be implemented in other ways different from those described herein, and therefore, the protection scope of the present invention is not limited by the specific embodiments disclosed below.

[0063] A specific embodiment of the present invention, as Figure 1-5 , discloses a wing with enhanced flapping aerodynamic performance based on bionic leading edge wing feathers. In order to illustrate the effectiveness of the method proposed by the present invention, the above technical solution of the present invention is described in detail through a specific embodiment below. The specific implementation steps are as follows:

[0064] The present invention provides a wing with enhanced flapping wing aerodynamic performance based on bionic leading edge wing feathers, comprising at least one bionic leading edge wing feather 1 and a curved wing body 7; the wing is a wing of a flapping wing UAV;

[0065] The curved wing body 7 comprises a leading edge 2, a wing root 4, a wing tip 5 and a trailing edge 6;

[0066] Preferably, at least one of the bionic leading edge wing feathers 1 is arranged on the leading edge 2 of the curved wing body 7 to form a convex independent structure;

[0067] Furthermore, the shape and structure of the bionic leading edge wing feathers 1 can be freely adjusted according to the performance requirements of the aircraft, including the barbed leading edge wing feathers Figure 3 (a) Curved leading edge wing feathers Figure 3 (b) Semicircular leading edge wing feathers Figure 3 (c) Triangular leading edge wing feathers Figure 3 (d) Rectangular leading edge wing feathers Figure 3 (e) or diamond-shaped leading edge wing feathers Figure 3 (f);

[0068] Exemplarily, the barbed leading edge wing feather is a triangular leading edge wing feather with a softened edge;

[0069] Furthermore, the barbed leading edge wing feathers are barbed leading edge wing feathers in the shape of a parrot's beak;

[0070] In one embodiment of the present invention, the barbed leading edge feathers can reduce the wake velocity difference of a partially stalled wing and delay flow separation; for a fully stalled wing, a boundary layer separator can be created to prevent the stall from propagating outward.

[0071] Exemplarily, one side of the curved leading edge wing feather is an edge with a curve, and the edge is formed by the feather tips of multiple groups of feathers arranged adjacent to each other to form a continuous curved edge;

[0072] Furthermore, the feather tips of the plurality of groups of feathers are in the shape of an arc with a pointed top, and the feather tips of the plurality of groups of feathers are inclined in the same direction or in different directions;

[0073] The bionic leading edge feathers in the present invention can suppress the separation of boundary layer vortices, generate relatively higher lift, and at the same time play a role in flexibly adjusting the direction. Bionic leading edge feathers of different shapes produce vortex shapes of different shapes and different numbers, and the effect of suppressing boundary layer separation varies in strength.

[0074] The different external shapes of the bionic leading edge wing feathers 1 described in the present invention produce different flow vortex shapes, which lead to different momentum transfer and vortex transfer. The size of the transfer is related to the shape of the aircraft and the size and position of the shape.

[0075] Furthermore, the center of the bionic leading edge wing feather 1 is taken as the coordinate origin, the span direction is the x-axis, and the chord direction is the y-axis;

[0076] The geometric length of the bionic leading edge wing feather 1 in the x-axis direction is not greater than 15% of the length of the curved wing body 7;

[0077] The geometric length of the bionic leading edge wing feather 1 in the y-axis direction is not greater than 15% of the chord length of the curved wing body 7;

[0078] The proportional relationship between the geometric length of the bionic leading edge wing feather 1 and the curved wing body of the present invention is consistent with the biological characteristics of eagles in nature, and is closer to the actual proportional size of the organism. This ratio is suitable for all shapes and sizes.

[0079] Furthermore, when a bionic leading edge wing feather is provided, the bionic leading edge wing feather can be provided at any position within the range from the leading edge wing root to the wing tip of the curved wing body 7;

[0080] Exemplarily, when a bionic leading edge wing feather is provided, the bionic leading edge wing feather is provided at 1 / 2 of the leading edge 8, 1 / 4 of the leading edge 9, 3 / 4 of the leading edge 10 or the wing tip 5 of the curved wing body 7;

[0081] In one embodiment of the present invention, the bionic leading edge wing feather 1 is coupled with the incoming flow to generate a flow vortex, and the flow vortex induces the downwash of the bionic leading edge wing feather 1 and the boundary layer of the leading edge 2 of the curved wing body 7 to transfer momentum and vortex, thereby suppressing the boundary layer separation of the leading edge 2 of the curved wing body 7 and enhancing the flapping wing lift-to-drag ratio and stall angle; the characteristics of the flow vortex are autonomously controllable with the bionic leading edge wing feather 1 of the curved wing body 7, and are adjusted accordingly according to the incoming flow environment and aircraft performance requirements; the aircraft performance requirements include speed performance, deformation ability and control performance; the shape, size and direction of the flow vortex are adjusted by autonomously controlling the shape, size and angle of the leading edge wing feathers, thereby changing the aerodynamic performance of the wing;

[0082] Furthermore, the bionic leading edge wing feather 1 has a double degree of freedom angle; the double degree of freedom angle includes a span angle α and a chord angle β, and the direction and shape of the streamwise vortex are adjusted by changing the span angle and the chord angle;

[0083] It can be understood that, with the center of the bionic leading edge wing feather 1 as the coordinate origin, the span direction is the x-axis, and the chord direction is the y-axis, forming a span direction angle α and a chord direction angle β;

[0084] Furthermore, the expression of the spanwise angle α of the bionic leading edge wing feathers is:

[0085] α=f1(θ(t),γ(t),η(t))

[0086] Among them, θ is the wing flapping angle, γ is the wing attack angle, η is the wing offset angle, t is the time, and f1(·) is the spanwise angle α limiting function;

[0087] The expression of the chord angle β of the bionic leading edge wing feather is:

[0088] β=f2(θ(t),γ(t),η(t))

[0089] Where f2(·) is the limiting function of the chord angle β.

[0090] Furthermore, the optional angle range of the spanwise angle α is 0 to π, and the optional angle range of the chordwise angle β is 0 to π / 2;

[0091] Exemplarily, the span-wise included angle α of the bionic leading edge wing feathers is π / 2; the chord-wise included angle β of the bionic leading edge wing feathers is π / 4.

[0092] Furthermore, the double-degree-of-freedom angle of the bionic leading edge wing feather is determined based on the constraint condition of the double-degree-of-freedom angle;

[0093] The constraint condition expression of the double-degree-of-freedom angle is:

[0094] 0≤α≤π;

[0095] α s =f4(α,β,Re) 0≤α≤π;

[0096] Among them, C L / C D is the lift-to-drag ratio of the wing, α s is the stall angle of the wing, Re is the Reynolds number; C L is the lift coefficient, C D Represents the drag coefficient, C L / C D is the lift-to-drag ratio of the wing, α s is the stall angle of the wing, Re is the Reynolds number; C L is the lift coefficient, C D represents the drag coefficient, f3(·) is the limiting function of the wing lift-to-drag ratio, and f4(·) is the limiting function of the wing stall angle.

[0097] Furthermore, the double-degree-of-freedom angle of the bionic leading-edge wing feather 1 changes dynamically with the wing flapping action, thereby optimizing the flapping wing flow structure in real time;

[0098] Furthermore, the bionic leading edge wing feathers 1 are distributed on the leading edge 2 of the curved wing body 7; the number and position of the bionic leading edge wing feathers 1 are variable;

[0099] Furthermore, the number of the bionic leading edge wing feathers 1 is determined by the shape characteristics of the curved wing body 7 and the performance of the aircraft;

[0100] Furthermore, the number of the bionic leading edge wing feathers is expressed as:

[0101] l a n≤0.5l w

[0102] Where n is the number of bionic leading edge wing feathers, l a is the base length of the bionic leading edge wing feather 1 structure, l w is the leading edge length of the wing;

[0103] For example, the plurality of bionic leading edge wing feathers 1 are regularly distributed with equal spacing or irregularly distributed with non-equal spacing on the leading edge 2 of the curved wing body 7 .

[0104] It can be understood that when the overall stability of the wing is required to enhance the lift-to-drag ratio of the wing, multiple bionic leading edge wing feathers 1 are regularly distributed with equal spacing on the leading edge of the wing; when the lift-to-drag ratio at a specific position of the wing is required to be improved to achieve stable turning of the aircraft, etc., multiple bionic leading edge wing feathers 1 are irregularly distributed with non-equidistant spacing on the leading edge of the wing.

[0105] Furthermore, the bionic leading edge wing feathers and the curved wing body are integrally formed through 3D printing and assembled using a hinge structure; the hinge structure and the curved wing body have a smooth transition.

[0106] The present invention introduces a bionic wing feather structure at the leading edge of the wing to form a streamwise vortex pair, thereby improving the evolution law of the boundary layer at the leading edge of the wing; suppresses / improves the separation phenomenon of the boundary layer at a large angle of attack of the flapping wing through vortex-induced downwash and momentum transfer, thereby improving the aerodynamic performance of flapping-wing UAVs; the bionic wing feather structure does not change the existing aerodynamic shape of the wing, and only a small-scale spoiler structure is added to the leading edge to complete the hardware design, and the overall structure is simple and easy to maintain; through the free control of the characteristic shape, number and angle of the wing feathers, the aerodynamic improvement of flapping-wing UAVs with different flight conditions and performance requirements can be served.

[0107] The above description is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by any technician familiar with the technical field within the technical scope disclosed by the present invention should be covered within the protection scope of the present invention.

Claims

1. A wing with enhanced flapping aerodynamic performance based on bionic leading edge wing feathers, characterized in that: include: A curved wing body (7) and at least one bionic leading edge wing feather (1); The at least one bionic leading edge wing feather (1) is arranged at the leading edge of the curved wing body (7) to form a convex independent structure; The bionic leading edge wing feathers (1) couple with the incoming flow to generate a streamwise vortex, and the downwash induced by the streamwise vortex transfers momentum and vortex within the leading edge boundary layer of the curved wing body (7), thereby suppressing boundary layer separation at the leading edge of the curved wing body (7), thereby enhancing the flapping wing lift-to-drag ratio and stall angle.

2. The wing with enhanced flapping aerodynamic performance based on bionic leading edge wing feathers according to claim 1, characterized in that: The external structure of the bionic leading edge wing feathers (1) can be freely adjusted according to the performance requirements of the aircraft, and includes barbed leading edge wing feathers, curved leading edge wing feathers, semicircular leading edge wing feathers, triangular leading edge wing feathers, rectangular leading edge wing feathers or diamond leading edge wing feathers.

3. The wing with enhanced flapping aerodynamic performance based on bionic leading edge wing feathers according to claim 2, characterized in that: With the center of the wing feather as the coordinate origin, the span direction of the wing feather as the x-axis, and the chord direction as the y-axis, the geometric length of the bionic leading edge wing feather (1) in the x-axis direction is not greater than 15% of the span length of the curved wing body (7); and the geometric length in the y-axis direction is not greater than 15% of the chord length of the curved wing body (7).

4. The wing with enhanced flapping aerodynamic performance based on bionic leading edge wing feathers according to claim 3, characterized in that: The bionic leading edge wing feathers (1) are arranged at any position within the range from the leading edge wing root to the wing tip (5) of the curved wing body (7).

5. The wing with enhanced flapping aerodynamic performance based on bionic leading edge wing feathers according to claim 4, characterized in that: The bionic leading edge wing feather (1) has a double degree of freedom angle; the double degree of freedom angle includes a spanwise angle α and a chordwise angle β; the double degree of freedom angle changes dynamically with the wing flapping action, thereby optimizing the flapping wing flow structure in real time.

6. The wing with enhanced flapping aerodynamic performance based on bionic leading edge wing feathers according to claim 5, characterized in that: The spanwise angle α of the bionic leading edge wing feather (1) is expressed as: α=f1(θ(t),γ(t),η(t)) Among them, θ is the wing flapping angle, γ is the wing attack angle, η is the wing offset angle, t is the time, and f1(·) is the spanwise angle α limiting function.

7. The wing with enhanced flapping aerodynamic performance based on bionic leading edge wing feathers according to claim 5, characterized in that: The expression of the chord-wise angle β of the bionic leading edge wing feather (1) is: β=f2(θ(t),γ(t),η(t)) Where f2(·) is the limiting function of the chord angle β.

8. The wing with enhanced flapping aerodynamic performance based on bionic leading edge wing feathers according to claim 5, characterized in that: The optional angle range of the spanwise angle α is 0 to π, and the optional angle range of the chordwise angle β is 0 to π / 2.

9. The wing with enhanced flapping aerodynamic performance based on bionic leading edge wing feathers according to claim 7, characterized in that: The double-degree-of-freedom angle of the bionic leading edge wing feather (1) is determined based on the constraint condition of the double-degree-of-freedom angle; the constraint condition expression of the double-degree-of-freedom angle is: Among them, C L / C D is the lift-to-drag ratio of the wing, α s is the stall angle of the wing, Re is the Reynolds number; C L is the lift coefficient, C D represents the drag coefficient, f3(·) is the limiting function of the wing lift-to-drag ratio, and f4(·) is the limiting function of the wing stall angle.

10. The wing with enhanced flapping aerodynamic performance based on bionic leading edge wing feathers according to claim 4, characterized in that: The plurality of bionic leading edge wing feathers (1) are regularly distributed at equal intervals or irregularly distributed at non-equal intervals on the leading edge of the curved wing body (7).

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