Two-section type wing and combined flapping wing

Abstract

The invention provides a two-section wing and a combined flapping wing, and aims to solve the problems that an existing flapping wing structure lacks segmented design, a wing surface is unstable to fix and the like, the two-section wing is of a mirror symmetry structure and is composed of two frames and a polyester film, one frame is composed of a carbon fiber rod and a carbon fiber plate, and the other frame is composed of a carbon fiber rod and a carbon fiber plate. The carbon fiber plate comprises a connecting part and two supporting rods, the connecting part covers the carbon fiber rod and is fixedly connected with the carbon fiber rod, the two supporting rods are located on the same side of the connecting part, one ends of the two supporting rods are connected with the connecting part respectively, and the two supporting rods are arranged in parallel; the polyester film covers the two frames at the same time and serves as the wing face of the two-section type wing. Through the two-section type wings and the combined structure, light weight, flexible response, reliable fixation and efficient synchronous flapping are achieved, and the flight stability, lift force and durability are remarkably improved. The method is suitable for the fields of micro flapping-wing aircrafts, bionic robots, air monitoring and reconnaissance equipment and the like.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of bionic aircraft structure design, and particularly relates to a two-section wing structure of a micro combined flapping wing. BACKGROUND

[0002] With the development of micro aerial vehicles, flapping wing structure, as one of the core components, its design trend gradually develops towards lightweight, multi-section and bionics to improve flight efficiency and maneuverability. Researchers try to optimize the material combination and structure of flapping wings to make them more close to the motion characteristics and aerodynamic performance of insect wings, and achieve high-efficiency flapping. However, in the prior art, carbon fiber material is often used as the wing frame, and polyester film is used as the wing surface. Such overall structure has advantages in weight control, but has obvious shortcomings in segmented design and flexible response, and is difficult to adapt to the change of aerodynamic load in the flight process, thereby affecting the flapping efficiency and flight stability.

[0003] In the exploration of multi-section flapping wings, the existing scheme still faces problems such as poor connection reliability, asynchronous motion and insufficient flexibility control. The fixing method of the wing surface material and the frame mainly depends on single adhesion, which leads to poor durability and maintenance, and is not conducive to structure adjustment and replacement. In addition, the overall structure lacks rigid-flexible cooperation, which makes the flapping wing prone to vibration or instability under high-frequency flapping or complex aerodynamic environment, limiting the performance of micro aerial vehicles.

[0004] Therefore, the existing flapping wing structure still has many technical bottlenecks in the aspects of segmented connection method, material fixing method and structure rigid-flexible matching, and an multi-section flapping wing scheme with simple structure, reliable connection, reasonable matching of material and wing surface is needed to realize more bionic flapping motion, efficient aerodynamic performance and stronger structure adaptability, so as to provide stable and efficient flight capability for micro aerial vehicles. SUMMARY

[0005] In order to solve the problems of lack of segmented design and unstable wing surface fixation of the existing flapping wing structure, the present application provides the following scheme: A two-section wing, which is a mirror-symmetrical structure and consists of two frames and a polyester film 3, wherein one frame is composed of a carbon fiber rod 1 and a carbon fiber plate 2; The carbon fiber plate 2 includes a connecting part 21 and two support rods 22, the connecting part 21 is fixedly connected on the carbon fiber rod 1, the two support rods 22 are located on the same side of the connecting part 21, and one end of each of the two support rods 22 is connected with the connecting part 21 and arranged in parallel; The polyester film 3 covers both frames and serves as the wing surface of the two-section wing.

[0006] Further, the diameter of the carbon fiber rod 1 is 1 mm.

[0007] Further, the width of the carbon fiber plate 2 is 2 mm, and the thickness is 0.2 mm.

[0008] Further, the included angle between the two support rods 22 and the connecting part 21 ranges from 30 to 60 degrees.

[0009] Further, the outer edge of the polyester film 3 is in an arc shape, which is an arc formed by connecting the end of the carbon fiber rod 1 and the end of the support rod 22.

[0010] Further, the thickness of the polyester film 3 is 0.125 mm.

[0011] Further, the polyester film 3 is fixed on the two frames by hot melting, bonding or clamping.

[0012] Further, the polyester film 3 between the carbon fiber rods 1 of the two frames is provided with a concave structure with an aspect ratio of 2:5.

[0013] Further, one end of the carbon fiber rod 1 adjacent to the other end extends into the concave structure, and the extension length is 3 to 5 mm.

[0014] Based on the same inventive concept, the application also provides a combined flapping wing, which comprises at least two pairs of two-segment wings according to the application, each pair of two-segment wings being arranged in mirror image, and the mirror image symmetry axes of all two-segment wings being located in the same plane.

[0015] Compared with the prior art, the application has the following beneficial effects: 1. The two-segment wing according to the application realizes a segmented lightweight load-bearing frame by adopting a combined frame structure of carbon fiber rods and carbon fiber plates. Compared with a traditional integral flapping wing, the segmented design enables the wing surface to respond flexibly to different aerodynamic loads during flapping, avoiding vibration and energy loss caused by excessive overall rigidity. The carbon fiber rods are used to bear the main load, and the carbon fiber plates form a reasonable mechanical support structure through the connecting part and the support rod, ensuring that the overall weight is light while having sufficient structural strength, thereby significantly improving the stability and efficiency of the flapping wing in continuous vibration and rapid maneuvering.

[0016] 2. The two-section wing of the present application, the angle between the connecting part and the support rod in the frame structure is designed to be in the range of 30 to 60 degrees, which ensures that the wing section has a certain elastic deformation ability in motion, while avoiding the problem of instability caused by excessive softening. The angle range is optimized to make the flapping wing form an aerodynamic deformation similar to the insect wing when flapping up and down, thereby improving the lift and propulsion efficiency. Compared with the multi-section connection lacking precise geometric constraints in the prior art, the present application matches flexibility and rigidity through angle design, improving the aerodynamic adaptability of the flapping wing.

[0017] 3. The two-section wing of the present application adopts polyester film as the wing surface material and is reliably fixed with the frame through hot melting, bonding or clamping, solving the problem of poor durability and easy falling off caused by relying on single bonding process for traditional wing surface material. The diversified fixing method makes the wing surface not only firm but also easy to disassemble and replace later, prolonging the service life of the flapping wing assembly. At the same time, the arc shape of the outer edge of the polyester film not only conforms to the aerodynamic streamline design, but also reduces the wing tip vortex effect, further improving the stability and energy efficiency of flight.

[0018] 4. The two-section wing of the present application is provided with a concave structure with a length-width ratio of 2:5 on the polyester film, so that the middle part of the wing surface has a local deformation space and can produce nonlinear flexible deformation during flapping. This design improves the matching effect of the wing surface and the airflow, avoiding the decline of aerodynamic efficiency when flapping greatly. Especially at high speed vibration, the concave structure can effectively disperse local load and reduce material fatigue, thereby enhancing the reliability and durability of the flapping wing. Compared with the existing overall flat wing surface, the present application significantly improves the adaptability and aerodynamic performance of the structure.

[0019] 5. The two-section wing of the present application, the adjacent end of the carbon fiber rod extends into the concave structure by 3 to 5 mm, forming a composite structure with rigid support and flexible transition. This design avoids the problem of fracture at the connection due to stress concentration, ensuring the structural integrity of the wing surface in high-frequency flapping. At the same time, the extended part forms local reinforcement with the polyester film, improving the carrying capacity and tear resistance of the wing surface, so that the flapping wing can maintain a stable motion posture in complex aerodynamic environment.

[0020] 6. Based on the two-section wing of the present application, a multi-wing structure flapping wing aircraft can be further combined. Through mirror image superposition arrangement, each pair of flapping wings realizes synchronous motion in the same plane. This combined structure not only improves the flapping driving force and lift output, but also effectively reduces the yaw and pitch interference caused by asymmetric motion. Compared with the existing single-section or multi-section structure with poor connection, the combined flapping wing of the present application has obvious advantages in overall coordination, power efficiency and flight stability.

[0021] The present application has the characteristics of structural lightweighting, segmented connection reliability and strong wing surface aerodynamic adaptability, and can realize bionic flexible deformation and efficient flapping effect while ensuring strength and durability, thereby improving the lift and maneuvering performance of the aircraft, and is suitable for the fields of micro flapping-wing aircraft, bionic robots, aerial monitoring and reconnaissance equipment, etc. BRIEF DESCRIPTION OF DRAWINGS

[0022] Figure 1 is a structural schematic diagram of a two-section wing described in the embodiments, and the reference signs are: carbon fiber rod 1, carbon fiber plate 2, and polyester film 3; Figure 2 is a carbon fiber plate of a two-section wing described in the embodiments, and the reference signs are: connecting part 21 and support rod 22; Figure 3 is a frequency and angle of attack relationship diagram of a two-section wing described in the embodiments; Figure 4 is a lift and drag curve diagram of a two-section wing described in the embodiments, obtained by ANSYS Fluent simulation; Figure 5 is a lift coefficient and swing amplitude relationship diagram of a two-section wing described in the embodiments; Figure 6 is a combined flapping wing described in the embodiments DETAILED DESCRIPTION The technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the drawings. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of protection of the present application.

[0023] Embodiment one A two-section wing, which is a mirror-symmetrical structure and is composed of two frames and a polyester film 3, wherein one frame is composed of a carbon fiber rod 1 and a carbon fiber plate 2; The carbon fiber plate 2 includes a connecting part 21 and two support rods 22, the connecting part 21 is fixedly connected by covering the carbon fiber rod 1, and the two support rods 22 are located on the same side of the connecting part 21, one end of each of the two support rods 22 is connected with the connecting part 21, and the two support rods 22 are arranged in parallel; The polyester film 3 covers the two frames at the same time, serving as the wing surface of the two-section wing.

[0024] The two-section wing described in the application is formed by a frame composed of carbon fiber rods and carbon fiber plates, and is covered with a polyester film to form a mirror-symmetrical two-section structure. This structure not only greatly reduces the weight, but also realizes the combination of rigidity and flexibility through the segmented design, so that the wing surface can flexibly respond to the change of aerodynamic force during flapping, thereby improving the flight efficiency and stability. Unlike the traditional whole flapping wing, the segmented design of the application is derived from the in-depth analysis of the bionic characteristics of insect wings by the team, and is innovatively combined with the material properties of carbon fiber and film, which embodies the creative labor from natural inspiration to engineering implementation.

[0025] Further, the diameter of the carbon fiber rod 1 is 1 millimeter.

[0026] The diameter of the carbon fiber rod is set to 1 millimeter, so that it can provide sufficient bearing capacity and maintain lightweight. After a large number of comparative experiments, the team determined that this diameter range can withstand long-time high-frequency flapping without adding too much weight. This precise balance between strength and quality is the result of repeated experiments and parameter optimization by the invention team.

[0027] Further, the width of the carbon fiber plate 2 is 2 millimeters, and the thickness is 0.2 millimeters.

[0028] The width of the carbon fiber plate is 2 millimeters, and the thickness is 0.2 millimeters. This ratio makes it have good bending resistance and avoids excessive rigidity due to excessive thickness. This value is not arbitrary, but is the optimal parameter combination obtained by the invention team through multiple rounds of finite element simulation and physical prototype verification, ensuring the stability and durability of the flapping wing in complex aerodynamic environments.

[0029] Further, the included angle between the two support rods 22 and the connecting part 21 is in the range of 30 to 60 degrees.

[0030] The two support rods form an included angle of 30 to 60 degrees with the connecting part, so that the wing surface has moderate flexible deformation during flapping, simulating the natural bending of insect wings. If the angle is too small, the wing surface is too hard and cannot produce a flexible effect; if the angle is too large, it will result in insufficient mechanical support. The invention team finally determined this range through repeated experiments with different angle ranges, which shows the creative labor of fine-tuning the aerodynamic performance.

[0031] Further, the outer edge of the polyester film 3 is in an arc shape, and the arc shape is an arc formed at the end of the carbon fiber rod 1 and the support rod 22.

[0032] The outer edge of the polyester film is an arc formed by the carbon fiber rod and the end of the support rod, which not only conforms to the aerodynamic streamline, but also effectively reduces the wing tip vortex. The arc edge design breaks through the traditional linear edge idea, and is an improvement proposed by the team after repeated comparison of wind tunnel tests and aerodynamic modeling, which significantly improves the energy efficiency and stability of the flapping wing.

[0033] Further, the thickness of the polyester film 3 is 0.125 mm.

[0034] The thickness of the polyester film is controlled to be 0.125 mm, which ensures the balance between flexibility and strength in vibration flapping. Too thick will increase the mass and affect the flexibility of deformation, and too thin will easily tear. The determination of this parameter is based on multiple material fatigue tests and actual flight verification by the team, which reflects the creative labor of the invention team in material selection and durability optimization.

[0035] Further, the polyester film 3 is fixed on the two frames by heat melting, bonding or clamping.

[0036] The polyester film is fixed on the frame by heat melting, bonding or clamping, which improves the reliability of the wing surface and the frame combination, and is convenient for disassembly and maintenance. Unlike the prior art which only relies on a single bonding method, the present invention has higher flexibility in process selection, ensuring durability and adaptability during long-term use.

[0037] Further, the polyester film 3 between the carbon fiber rods 1 of the two frames is provided with a concave structure with an aspect ratio of 2:5.

[0038] The polyester film between the carbon fiber rods of the two frames is provided with a concave structure with an aspect ratio of 2:5, so that the wing surface has a controllable nonlinear deformation space during flapping. This concave structure not only improves the aerodynamic performance, but also disperses stress concentration at high speed vibration. This design is derived from the team's simulation and engineering reproduction of the wing surface wrinkle pattern in nature, which reflects the organic combination of bionics and engineering design.

[0039] Further, an adjacent end of the carbon fiber rod 1 extends into the concave structure by 3-5 mm.

[0040] The adjacent end of the carbon fiber rod extends into the concave structure by 3-5 mm, forming a rigid-flexible transition reinforcement area. This extended part effectively avoids the fracture caused by load concentration at the connection, and at the same time enhances the overall stability of the wing surface. The size control here is obtained after the team tests the structural strength of different extension lengths, which shows the creative labor of repeated experiments and optimization in detail parameters.

[0041] Embodiment two As Figure 6As shown, a combined flapping wing comprises at least two pairs of two-segment wings described in embodiment one, each pair of two-segment wings is mirror-superimposed, and the mirror symmetry axes of all two-segment wings are located in the same plane.

[0042] Based on the two-segment wing described above, the combined flapping wing proposed by the present application realizes efficient lift output and flight stability by mirror-superimposing multiple pairs of two-segment wings, so that all symmetry axes are located in the same plane. This combined mode takes into account the balance of aerodynamics and the overall coordination of the structure, solves the common problems of different steps, yaw instability and other problems of existing multi-segment flapping wings, and further embodies the innovative exploration of the team in the aspects of structural integration and flight performance improvement.

[0043] Embodiment three This embodiment integrates the technical solutions described in the above-mentioned multiple embodiments, combines the actual application scenarios and the use process of the computer program product for implementing the method described in the present application, and further verifies and explains the technical effects of the present application through specific examples.

[0044] A two-segment wing, which is a mirror-symmetric structure, is composed of two frames and a polyester film 3, wherein one frame is composed of a carbon fiber rod 1 and a carbon fiber plate 2; The carbon fiber plate 2 includes a connecting part 21 and two support rods 22, the connecting part 21 is fixedly connected on the carbon fiber rod 1, the two support rods 22 are located on the same side of the connecting part 21, and one end of each of the two support rods 22 is connected with the connecting part 21 and arranged in parallel; The polyester film 3 covers both frames and serves as the airfoil of the two-segment wing.

[0045] Preferably, the combined flapping wing in this embodiment includes four two-segment wings, a total of eight wing segments, to significantly improve the aerodynamic efficiency. Each wing segment adopts optimized geometric shape and material properties to maximize lift and minimize weight, ensuring structural durability and better aerodynamic performance. The wing segments have coordinated kinematic characteristics that mimic the “flap-extension” mechanism in nature; Preferably, each wing segment is aerodynamically optimized to achieve efficient airflow and lift generation; Preferably, the flapping wing described in this embodiment uses ultra-lightweight materials, such as carbon fiber rod reinforced polyimide film, to minimize weight while maintaining structural integrity; Preferably, the geometry and segmentation of the airfoil are designed and optimized through computational fluid dynamics (CFD) simulation (ANSYS Fluent), analyzing velocity, pressure contours, and lift-drag ratio. Each wing segment generates about 0.033 Newton of lift, and eight wing segments together generate about 0.264 Newton of lift.

[0046] AsFigure 3 As shown in the figure, the horizontal axis Flapping Frequency represents the flapping frequency, and the vertical axis Max Angle of Attack represents the maximum angle of attack. It can be seen from the figure that as the flapping frequency increases, the wing generates a larger angle of attack, which is consistent with the biomimetic flight principle: at a higher flapping frequency, the wing surface swing speed increases, the angle of attack increases, and thus generates higher lift.

[0047] This verifies that the multi-segment flexible connection design in this invention enables the flapping wing to maintain a large angle of attack during high-frequency motion, which helps to improve lift efficiency.

[0048] like Figure 4 As shown in the figure, the horizontal axis Angle of Attack represents the angle of attack, the blue curve on the vertical axis represents lift, and the red curve on the vertical axis represents drag. It can be seen from the figure that within the angle of attack range, the lift response is good and the increase is gradual, indicating that the flapping wing can maintain stable lift at various angles of attack.

[0049] At low angle of attack At this time, the drag is extremely low, which is especially advantageous for low-speed flight.

[0050] By combining the polyester film airfoil and multi-segment connection of the present invention, it is possible to adapt to the aerodynamic load distribution under different angles of attack, reduce drag, and improve efficiency.

[0051] This stands in stark contrast to the existing technologies' pain points, such as "excessive structural rigidity leading to large lift fluctuations and excessive drag."

[0052] like Figure 5 As shown in the figure, the horizontal axis Angle of Attack represents the angle of attack, and the vertical axis Lif Coefcient represents the lift coefficient, reflecting the lift potential of the flapping wing under different angle of attack conditions. This demonstrates that the combined flapping wing design described in this embodiment can continuously generate positive lift over a large angle of attack range. Because this invention combines a carbon fiber frame with a flexible membrane material and uses multiple hinges to enable the wing surface to flexibly deform with the angle of attack, it improves the lift efficiency in the large angle of attack range, which is beneficial for simulating the "flapping-opening" biomimetic lift mechanism.

[0053] This embodiment verifies the technical advantages of the present invention: This invention proposes a multi-segment structure with flexible connections, which can maintain airfoil stability at high flapping frequencies and adaptively generate a large angle of attack with frequency changes, reducing the deformation drag of the rigid airfoil structure during high-speed motion. This effectively overcomes the problem in the prior art where "poor structural rigidity or material matching leads to limited angle of attack at high flapping frequencies".

[0054] The lightweight combination structure of the carbon fiber rod + carbon fiber plate + polyester film of the application not only ensures the strength of the wing frame, but also has a flexible wing surface, can realize large attack angle flapping, and can inhibit sudden increase of wing surface resistance. Through simulation verification, the structure design can significantly improve the aerodynamic performance, and compared with the background technology "wing surface rigidity is too strong to cause high attack angle resistance increase", the improvement is obvious.

[0055] The multi-section connection + concave film structure of the application can expand the lift maintaining ability in the attack angle interval through flexible deformation, and can improve the "flap-open" mechanism effect, so that the flapping wing can stably output lift in the whole attack angle range, and the defects of "lift curve instability and limited swing amplitude" in the background technology are significantly improved.

[0056] The technical solutions provided by the application are further described in detail through the above several specific embodiments, in order to highlight the advantages and benefits of the technical solutions provided by the application. However, the above several specific embodiments are not used to limit the protection scope of the application, and any reasonable modification and improvement of the application, recombination and equivalent replacement of the embodiments, etc. within the spirit and principle of the application should be included in the protection scope of the application.

[0057] Those skilled in the art can understand that the above description is only the preferred embodiments of the application, and the features described in each embodiment and / or claim of the application can be combined or combined, even if such combination or combination is not explicitly described in the disclosure of the application. Although the application has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent replacement of part of the technical features, and any modification, equivalent replacement, improvement, etc. within the spirit and principle of the application shall be regarded as falling within the protection scope of the application.

[0058] Although the preferred embodiments of the application have been described, those skilled in the art can make further changes and modifications to the embodiments once they know the basic creative concept. Therefore, the appended claims are intended to include the preferred embodiments and all changes and modifications within the scope of the application. Obviously, those skilled in the art can make various modifications and changes to the application without departing from the spirit and scope of the application. Thus, if these modifications and changes of the application fall within the scope of the claims of the application and their equivalent technologies, the application also intends to include these modifications and changes.

Claims

1. A two-section wing, characterized in that, The two-section wing is a mirror-symmetric structure, consisting of two frames and a polyester film (3), one of which is composed of a carbon fiber rod (1) and a carbon fiber plate (2); The carbon fiber plate (2) includes a connecting part (21) and two support rods (22). The connecting part (21) covers the carbon fiber rod (1) and is fixedly connected. The two support rods (22) are located on the same side of the connecting part (21). One end of the two support rods (22) is connected to the connecting part (21) respectively and is arranged in parallel. The polyester film (3) covers both frames simultaneously, serving as the wing surface of the two-section wing.

2. The two-section wing according to claim 1, characterized in that, The carbon fiber rod (1) has a diameter of 1 mm.

3. The two-section wing according to claim 1, characterized in that, The carbon fiber plate (2) has a width of 2 mm and a thickness of 0.2 mm.

4. The two-section wing according to claim 1, characterized in that, The angle between the two support rods (22) and the connecting part (21) ranges from 30 to 60 degrees.

5. The two-section wing according to claim 1, characterized in that, The outer edge of the polyester film (3) is arc-shaped, and the arc shape is formed by the end of the carbon fiber rod (1) and the support rod (22).

6. The two-section wing according to claim 1, characterized in that, The thickness of the polyester film (3) is 0.125 mm.

7. The two-section wing according to claim 1, characterized in that, The polyester film (3) is fixed to the two frames by hot melting, bonding or clamping.

8. The two-section wing according to claim 1, characterized in that, The polyester film (3) between the carbon fiber rods (1) of the two frames is provided with a concave structure with an aspect ratio of 2:

5.

9. The two-section wing according to claim 7, characterized in that, One adjacent end of the carbon fiber rod (1) extends into the concave structure, with an extension length of 3 to 5 millimeters.

10. A combined flapping wing, characterized in that, The combined flapping wing comprises at least two sets of two-segment wings as described in claim 1, each set of two-segment wings being mirror-stacked, and the mirror symmetry axes of all two-segment wings being located in the same plane.

Images