Wing square beam structure of fixed-wing unmanned aerial vehicle

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, and provides a wing square beam structure of a fixed-wing unmanned aerial vehicle, which comprises a middle-section wing beam, a middle-section wing beam and a middle-section wing beam, the square pin bodies are symmetrically arranged on the two sides of the middle section spar; the limiting pin sleeve is matched with the square pin body and used for being connected with the square pin body; wherein the limiting pin sleeve is embedded in the separation surface of the separation end wing and the fuselage end wing along the wing tip direction; and the square pin body is inserted into the limiting pin sleeve, so that the connection between the separation end wing and the fuselage end wing is completed. The connecting mode of the square pin body and the limiting pin sleeve is adopted, manufacturing is easy, and the test cost is low. The square beam fits the upper and lower surfaces of the skin, the thickness of the wing is fully utilized, the size of a gap needing to be filled between the beam and the wing skin is reduced, and the structural weight is lighter.

Description

Technical Field

[0001] The present application relates to the technical field of unmanned aerial vehicles, and in particular to a square beam structure of a fixed-wing unmanned aerial vehicle wing. Background Art

[0002] In recent years, the field of unmanned aerial vehicles has developed rapidly, and fixed-wing unmanned aerial vehicles are also increasingly applied in production and life. During the flight of an unmanned aerial vehicle, it is subjected to various forces such as its own gravity, aerodynamic force, and resistance. As the main load-bearing member of the unmanned aerial vehicle, the wing beam requires high strength. However, a stronger load-bearing capacity means a higher structural weight. The wing beam of an unmanned aerial vehicle is usually heavy, which affects the load-carrying performance of the unmanned aerial vehicle. A fixed-wing unmanned aerial vehicle needs to carry objects and fly in the air. For unmanned aerial vehicles of the same size, the lighter the empty weight, the stronger the load-carrying capacity. A reasonable structure can effectively reduce the weight of the unmanned aerial vehicle and improve its load-carrying performance.

[0003] The inventor found that compared with the commonly used plate beams and C-shaped beams, the cross-sectional area of a square beam is usually larger than that of a C-shaped beam or a plate beam with the same amount of material used. The square beam can make full use of the wing thickness, reduce the size of the gap that needs to be filled between the beam and the wing skin, and make the structure lighter. And when the square beam bears a bending moment, the neutral axis of its cross-section is located at the center of the cross-section, the stress condition is more reasonable, it can bear a larger bending moment, has a strong bearing capacity, and has a stronger torsional resistance. However, since a separation surface usually needs to be set on the wing of an unmanned aerial vehicle, this means that the beam needs to be disconnected at this point. The docking surface shape of the square beam structure is complex, and the gap size between the docking parts of the square beams directly affects the bearing capacity of the beam. And there is a certain deformation in composite material products, and a large number of tests and high labor costs are required to measure the suitable fit tolerance.

[0004] Therefore, it is very necessary to have an unmanned aerial vehicle wing beam structure that is lighter in weight and has a simple docking surface structure on the premise of ensuring strength. Summary of the Utility Model

[0005] The purpose of the present utility model is to solve the above-mentioned problems, and provides a square beam structure of a fixed-wing unmanned aerial vehicle wing. The connection between the separated wing and the fuselage wing is completed by inserting a square pin body fixedly connected to the middle wing beam into a limit pin sleeve embedded in the wing separation surface. The docking structure is simple to manufacture, quick and reliable to install. It makes use of the characteristics of the square beam with strong bearing capacity and strong torsional resistance. The size of the square beam fits the upper and lower surfaces of the skin, makes full use of the wing thickness, and realizes a lighter structural weight.

[0006] To achieve the above object, the present utility model is realized through the following technical solutions:

[0007] A square beam structure of a fixed-wing unmanned aerial vehicle wing, comprising:

[0008] A middle wing beam, which is a hollow square structural profile;

[0009] A square pin body, symmetrically arranged on both sides of the middle wing beam;

[0010] A limit pin sleeve, arranged in cooperation with the square pin body for connecting the square pin body;

[0011] Wherein, the limit pin sleeve is embedded along the wingtip direction at the separation surface between the separated wing and the fuselage wing;

[0012] The square pin body is inserted into the limit pin sleeve to complete the connection between the separated wing and the fuselage wing.

[0013] In the technical solution of the present application, a further improvement is that first inner walls are respectively arranged at both ends of the middle wing beam, and the first inner walls are used for fixedly connecting the square pin body.

[0014] For the above improvement, a further improvement is that a second inner wall is arranged along the wingtip direction at the separation surface between the separated wing and the fuselage wing, and the second inner wall is used for fixedly connecting the limit pin sleeve.

[0015] A further improvement for the square pin body is that a first inlay is filled in the square pin body for structurally reinforcing the square pin body and reducing stress concentration.

[0016] A further improvement for the limit pin sleeve is that the limit pin sleeve and the square pin body are produced in cooperation, which helps to control the fit tolerance during production.

[0017] In the technical solution of the present application, the upper and lower surfaces of the middle wing beam are attached to the wing skin, reducing the size of the gap that needs to be filled between the beam and the wing skin, and the structural weight is lighter.

[0018] In the technical solution of the present application, the first inlay is preferably made of PVC foam, the limit pin sleeve is preferably made of glass fiber material, and the middle wing beam and the square pin body are preferably made of carbon fiber material.

[0019] In the technical solution of the present application, the square pin body and the first inner wall are preferably integrally connected by adhesive glue to make up for the gap between the square pin body and the first inner wall; the limit pin sleeve and the second inner wall are selected to be integrally connected by adhesive glue to make up for the gap between the limit pin sleeve and the second inner wall; the first inner wall and the second inner wall do not directly contact and cooperate, with low dimensional tolerance requirements, simple production, and low test cost.

[0020] Advantages of the technical solution of the present application:

[0021] 1. Compared with the commonly used plate girders and C-shaped girders, the stress condition of the square beam is more reasonable, with stronger load-bearing capacity and torsional resistance. The upper and lower surfaces are fitted to the wing skin, making full use of the wing thickness, reducing the size of the gap to be filled between the beam and the wing skin, and resulting in a lighter structural weight.

[0022] 2. It is mainly made of composite materials, which are light in weight and high in strength.

[0023] 3. A square pin body filled with PVC foam is embedded at the butt joint of the beam, and the square pin body is structurally reinforced, making it not easy to cause structural damage due to stress concentration.

[0024] 4. The square pin body does not directly contact and cooperate with the wing. It is connected by the method of a square pin body plus a fiberglass pin sleeve, which is simple to manufacture and has a low test cost. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following will briefly introduce the accompanying drawings required in the embodiments. Obviously, the accompanying drawings in the following description are only some embodiments of the present application. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0026] Figure 1 FIG. 1 is a schematic diagram of the plug-in state of the square beam structure of the fixed-wing UAV wing provided by the present utility model;

[0027] Figure 2 FIG. 2 is a schematic diagram of the position of the square pin body of the square beam structure of the fixed-wing UAV wing provided by the present utility model;

[0028] Figure 3 FIG. 3 is a schematic diagram of the position of the limit pin sleeve of the square beam structure of the fixed-wing UAV wing provided by the present utility model;

[0029] Figure 4 FIG. 4 is a schematic diagram of the end structure of the square pin body of the square beam structure of the fixed-wing UAV wing provided by the present utility model;

[0030] Figure 5 FIG. 5 is a schematic diagram of the end structure of the limit pin sleeve of the square beam structure of the fixed-wing UAV wing provided by the present utility model;

[0031] Figure 6 FIG. 6 is a schematic diagram of the effect after the connection of the wing and the fuselage wing at the separation end of the square beam structure of the fixed-wing UAV wing provided by the present utility model;

[0032] Description of the reference numerals in the drawings:

[0033] 1. Middle wing beam; 2. Square pin body; 3. Limit pin sleeve; 4. First inner wall; 5. Second inner wall; 6. First inlay; 7. Separation end wing; 8. Fuselage end wing; 9. Wing skin; 10. Adhesive; Detailed implementation mode

[0034] The following will clearly and completely describe the technical solutions in the embodiments of the present application with reference to the accompanying drawings in the embodiments of the present application. Obviously, the described embodiments are only a 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 of ordinary skill in the art without creative efforts shall fall within the protection scope of the present application.

[0035] To make the above objects, features, and advantages of the present application more obvious and understandable, the present application will be further described in detail below with reference to the drawings and specific implementation modes.

[0036] One embodiment of the present utility model is, in combination with Figures 1 to 5 , a fixed-wing UAV wing square beam structure, including:

[0037] The middle wing beam 1 is a hollow square structural profile;

[0038] The square pin bodies 2 are symmetrically arranged on both sides of the middle wing beam 1;

[0039] The limit pin sleeves 3 are arranged in cooperation with the square pin bodies 2 for connecting the square pin bodies 2;

[0040] Among them, the limit pin sleeves 3 are embedded in the separation surface of the separation end wing 7 and the fuselage end wing 8 along the wingtip direction;

[0041] The square pin bodies 2 are inserted into the limit pin sleeves 3 to complete the connection between the separation end wing 7 and the fuselage end wing 8.

[0042] In a specific embodiment provided by the present application, a further improvement is that first inner walls 4 are respectively arranged at both ends of the middle wing beam 1, and the first inner walls 4 are used for fixedly connecting the square pin bodies 2.

[0043] For the above improvement, a further improvement is that a second inner wall 5 is arranged on the separation surface of the separation end wing 7 and the fuselage end wing 8 along the wingtip direction, and the second inner wall 5 is used for fixedly connecting the limit pin sleeves 3.

[0044] For a further improvement of the square pin body 2, a first inlay 6 is filled in the square pin body 2 for structurally reinforcing the square pin body 2 and reducing stress concentration.

[0045] A further improvement to the limit pin sleeve 3 is that the limit pin sleeve 3 is produced in cooperation with the square pin body 2, which helps to control the fit tolerance during production.

[0046] In a specific embodiment provided by the present application, the upper and lower surfaces of the middle wing beam 1 are attached to the wing skin 9, reducing the size of the gap that needs to be filled between the beam and the wing skin 9, and the structural weight is lighter.

[0047] In a specific embodiment provided by the present application, the first inlay 6 is preferably made of PVC foam, the limit pin sleeve 3 is preferably made of fiberglass, and the middle wing beam 1 and the square pin body 2 are preferably made of carbon fiber.

[0048] In a specific embodiment provided by the present application, the square pin body 2 and the first inner wall 4 are preferably glued together by an adhesive 10 to fill the gap between the square pin body 2 and the first inner wall 4; the limit pin sleeve 3 and the second inner wall 5 are selected to be glued together by an adhesive 10 to fill the gap between the limit pin sleeve 3 and the second inner wall 5; the first inner wall 4 and the second inner wall 5 do not directly contact and cooperate, with low dimensional tolerance requirements, simple production, and low test costs.

[0049] It should be noted that the present application only describes a square beam structure of a fixed-wing UAV wing. This structure does not include the fixing method at the wing connection. The fixing method between the wing and the fuselage can be set as a separate structure.

[0050] It is worth mentioning that the accompanying drawings provided in the embodiments of the present application are only one application example of this mechanism, including but not limited to the structures in the figures.

[0051] In the following description, specific details such as specific system structures and technologies are presented for the purpose of illustration rather than limitation, in order to thoroughly understand the embodiments of the present application. However, those skilled in the art should clearly understand that the present application can also be implemented in other embodiments without these specific details. In other cases, detailed descriptions of well-known systems, devices, circuits, and methods are omitted to avoid unnecessary details from interfering with the description of the present application.

[0052] It should be noted that in the description of the present invention, relational terms such as first and second are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations.

[0053] The orientation or positional relationship indicated by terms such as "upper", "lower", "top", "bottom", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation on the present invention.

[0054] Unless otherwise clearly specified and defined, the terms "fixed", "set", "connected" shall be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or an integral connection; for those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood through specific circumstances.

[0055] The above embodiments are only descriptions of the preferred modes of the present application, and do not limit the scope of the present application. Without departing from the design spirit of the present application, various deformations and improvements made by those of ordinary skill in the art to the technical solutions of the present application shall fall within the protection scope determined by the claims of the present application.

Claims

1. A square beam structure for the wing of a fixed-wing unmanned aerial vehicle, characterized in that, Including: The middle wing beam, which is a hollow square structural profile; Square pin bodies, symmetrically arranged on both sides of the middle wing beam; Limit pin sleeves, which are arranged in cooperation with the square pin bodies for connecting the square pin bodies; Wherein, the limit pin sleeves are embedded in the separation surface of the separated wing and the fuselage wing along the wingtip direction; The square pin bodies are inserted into the limit pin sleeves to complete the connection between the separated wing and the fuselage wing.

2. The square beam structure of the wing of a fixed-wing unmanned aerial vehicle according to claim 1, wherein, First inner walls are respectively arranged at both ends of the middle wing beam, and the first inner walls are used for fixedly connecting the square pin bodies.

3. The square beam structure of the wing of a fixed-wing unmanned aerial vehicle according to claim 2, characterized in that, Second inner walls are arranged on the separation surface of the separated wing and the fuselage wing along the wingtip direction, and the second inner walls are used for fixedly connecting the limit pin sleeves.

4. A fixed-wing UAV wing square beam structure according to claim 3, characterized in that A first inlay is filled in the square pin bodies for strengthening the structure of the square pin bodies.

5. A square beam structure for a fixed-wing UAV wing according to claim 4, characterized in that The upper and lower surfaces of the middle wing beam are attached to the wing skin.

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