Unmanned aerial vehicle wing and preparation method thereof

Abstract

The invention provides an unmanned aerial vehicle wing and a preparation method thereof, and relates to the field of unmanned aerial vehicles. The preparation method of the unmanned aerial vehicle wing comprises the following steps: dissolving epoxy resin in an organic solvent to obtain an epoxy resin solution; putting flame-retardant powder into the epoxy resin solution, and uniformly stirring to obtain powder slurry; adding deionized water into the powder slurry, uniformly stirring, and separating out wet powder; and drying the wet powder to obtain the flame retardant, silicon carbide fibers, carbon fibers, a flame retardant, carbon fibers and silicon carbide fibers are sequentially laid on a mold, the mold is closed, and resin is injected into a mold cavity of the mold; and carrying out curing treatment, demolding and molding, and trimming to a required size to obtain the unmanned aerial vehicle wing. The prepared unmanned aerial vehicle wing has good mechanical properties and fireproof performance, and is good in high-temperature stability.

Description

Technical Field

[0001] The present invention relates to the field of unmanned aerial vehicles (UAVs), and in particular to a wing of an unmanned aerial vehicle (UAV) and a preparation method thereof. Background Art

[0002] Drones are widely used in military, aerospace, firefighting and rescue fields due to their high cost-effectiveness, safe operation, strong flexibility, good durability, easy operation and strong data collection capabilities. The wing of a drone is a key component in the design of a drone. It not only directly affects the flight performance, stability and maneuverability, but also determines the energy efficiency, load capacity, safety performance and durability. The structural integrity of the wing ensures the stability of the drone under various flight conditions, while its fire resistance, corrosion resistance and oxidation resistance are crucial to the safety and environmental adaptability of the drone. Traditional drone wing materials are mainly carbon fiber and glass fiber resin-based composite materials, which have low fire resistance, corrosion resistance and oxidation resistance, affecting the performance and service life of the drone. Summary of the invention

[0003] In view of the above problems existing in the prior art, the present invention provides a UAV wing and a preparation method thereof to improve the performance and service life of the UAV.

[0004] To achieve the above-mentioned object and other related objects, the present invention provides a method for preparing a wing of a drone in a first aspect, comprising:

[0005] dissolving epoxy resin in an organic solvent to obtain an epoxy resin solution;

[0006] Placing the flame retardant powder in the epoxy resin solution and stirring evenly to obtain a powder slurry;

[0007] Adding deionized water to the powder slurry and stirring evenly to separate wet powder;

[0008] Drying the wet powder to obtain a flame retardant;

[0009] Laying silicon carbide fiber, carbon fiber, flame retardant, carbon fiber and silicon carbide fiber in sequence on the mold, closing the mold and injecting resin into the mold cavity of the mold;

[0010] After curing, demoulding and trimming to the required size, the UAV wing is obtained.

[0011] In one embodiment of the present invention, the mass ratio of the organic solvent to the epoxy resin is 10:1 to 10:4.

[0012] In one embodiment of the present invention, the organic solvent includes any one of ethyl acetate, cyclohexanone, and N,N-dimethylformamide.

[0013] In one embodiment of the present invention, the flame retardant powder includes any one or more of silicon carbide, tungsten carbide, silicon oxide, and aluminum oxide, and the particle size of the flame retardant powder is 1 to 30 μm.

[0014] In one embodiment of the present invention, the mass ratio of the epoxy resin solution to the flame retardant powder is 10:2 to 10:5.

[0015] In one embodiment of the present invention, the mass ratio of the powder slurry to the deionized water is 1:2 to 1:4.

[0016] In one embodiment of the present invention, when the wet powder is dried, vacuum drying is selected, the drying temperature is 70 to 120° C., and the drying time is 2 to 10 hours.

[0017] In one embodiment of the present invention, the curing temperature during the curing is 60-100° C., and the curing time is 4-10 hours.

[0018] In one embodiment of the present invention, based on the mass percentage of the drone wing, the content of the carbon fiber is 30-40wt.%, the content of the silicon carbide fiber is 10-30wt.%, the content of the flame retardant is 5-15wt.%, and the content of the resin is 35-45wt.%.

[0019] A second aspect of the present invention provides a UAV wing, which is manufactured using the above-mentioned UAV wing preparation method, and the UAV wing comprises a silicon carbide fiber layer, a flame retardant layer, a carbon fiber layer, a flame retardant layer and a silicon carbide fiber layer arranged in sequence.

[0020] The outermost layer of the drone wing provided by the present invention is configured as a silicon carbide fiber layer, and a flame retardant layer composed of flame retardant powder coated with epoxy resin is arranged on the inner side of the silicon carbide fiber layer, which can not only greatly improve the mechanical properties, oxidation resistance, corrosion resistance and other properties of the wing, but also improve the fire resistance and flame retardant properties of the wing, and improve the performance and service life of the drone. In addition, the preparation method of the drone wing of the present application is simple, the preparation cost is low, and the drone wing can be used for fire rescue drones. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings in the following description are only some embodiments of the present invention. For ordinary technicians in this field, other embodiments can be obtained based on these drawings without paying creative work.

[0022] Figure 1 is a flow chart of the preparation of the drone wing in one embodiment of the present invention;

[0023] Figure 2 This is a schematic structural diagram of a drone wing in one embodiment of the present invention;

[0024] Figure 3 for Figure 2 Section view along AA.

[0025] Component number description:

[0026] 10. UAV wing; 100. Silicon carbide fiber layer; 200. Flame retardant layer; 300. Carbon fiber layer. DETAILED DESCRIPTION

[0027] The following is an explanation of the embodiments of the present invention by specific examples, and those skilled in the art can easily understand other advantages and effects of the present invention from the contents disclosed in this specification. The present invention can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present invention. It should be noted that the features in the following embodiments and the embodiments can be combined with each other without conflict. It should also be understood that the terms used in the embodiments of the present invention are intended to describe specific embodiments, rather than to limit the scope of protection of the present invention. The test methods for which specific conditions are not specified in the following examples are usually carried out under conventional conditions or according to the conditions recommended by the manufacturers.

[0028] When numerical ranges are given in the embodiments, it should be understood that unless otherwise specified in the present invention, both endpoints of each numerical range and any value between the two endpoints can be selected. Unless otherwise defined, all technical and scientific terms used in the present invention are familiar to those skilled in the art and the description of the present invention, and any method, device and material of the prior art similar or equivalent to the method, device and material in the embodiments of the present invention can also be used to implement the present invention.

[0029] It should be noted that the terms such as "upper", "lower", "left", "right", "middle" and "one" etc. used in this specification are only for the convenience of description and are not intended to limit the scope of implementation of the present invention. Changes or adjustments to their relative relationships, without substantially changing the technical content, should also be regarded as the scope of implementation of the present invention.

[0030] See also Figure 1 The present invention provides a method for preparing a wing of a UAV, comprising the following steps:

[0031] S1, dissolving epoxy resin in an organic solvent to obtain an epoxy resin solution;

[0032] S2, placing the flame retardant powder in the epoxy resin solution and stirring evenly to obtain a powder slurry;

[0033] S3, adding deionized water to the powder slurry and stirring evenly to separate the wet powder;

[0034] S4, drying the wet powder to obtain a flame retardant;

[0035] S5. Laying silicon carbide fiber, carbon fiber, flame retardant, carbon fiber and silicon carbide fiber on the mold in sequence, closing the mold and injecting resin into the mold cavity of the mold;

[0036] S6, curing treatment, demoulding and trimming to the required size to obtain the UAV wing.

[0037] In step S1, the mass ratio of the organic solvent to the epoxy resin is 10:1 to 10:4, for example, any value in the range of 10:1 to 10:4, such as 10:1, 10:2, 10:3, 10:4, etc. In one embodiment, the organic solvent includes any one of ethyl acetate, cyclohexanone, and N,N-dimethylformamide. That is, the organic solvent can be ethyl acetate or cyclohexanone, or N,N-dimethylformamide. In other embodiments, other commonly used organic reagents in the art can also be selected, as long as they can dissolve the epoxy resin and do not react with the epoxy resin.

[0038] In step S2, the mass ratio of the epoxy resin solution to the flame retardant powder is 10:2 to 10:5, for example, any value of 10:2, 10:3, 10:4, and 10:5. The flame retardant powder includes any one or more of silicon carbide, tungsten carbide, silicon oxide, and aluminum oxide. That is, the flame retardant powder can be any one of the types listed above, such as silicon carbide and tungsten carbide; it can also be a combination of any two or more of the types listed above, such as a combination of silicon carbide and tungsten carbide, or a combination of silicon oxide and aluminum oxide, or a combination of silicon carbide, tungsten carbide and silicon oxide, or a combination of silicon carbide, tungsten carbide, silicon oxide and aluminum oxide. If the flame retardant powder is a combination of the listed types, the proportion of each component is not limited and can be mixed in any proportion. In some embodiments, the type and proportion of the flame retardant powder can be adjusted according to the required density of the drone wing. In this embodiment, the particle size of the flame retardant powder is 1 to 30 μm, for example, any value between 1 μm, 5 μm, 10 μm, 20 μm, 25 μm or 30 μm. The flame retardant powder is placed in an epoxy resin solution and stirred to improve the dispersion of the flame retardant powder in the epoxy resin solution. Exemplarily, the stirring time is 30 to 60 minutes, for example, any value between 30 minutes, 40 minutes, 50 minutes or 60 minutes.

[0039] In step S3, the mass ratio of the powder slurry to the deionized water is 1:2 to 1:4, for example, any value between 1:1 and 1:4, such as 1:2, 1:3 or 1:4. In one embodiment, the wet powder can be separated by centrifugation. In other embodiments, the wet powder can also be separated by standing. For example, the slurry stirred evenly after adding deionized water is left to stand for 4 to 6 hours, and the powder is settled by its own gravity.

[0040] In step S4, vacuum drying is used when drying the wet powder, for example, it is carried out in a conventional vacuum drying oven in the art, and the drying oven is evacuated to negative pressure during drying. In one embodiment, the drying temperature is 70 to 120°C, for example, 70°C, 90°C, 100°C, or 120°C, etc., any value in the range of 70 to 120°C; the drying time is 2 to 10 hours, for example, 1h, 5h, 7h or 10h, etc., any value in the range of 2 to 10h. The flame retardant of the present application is an epoxy resin coated flame retardant powder, and the flame retardant powder has flame retardant and high temperature resistance. The epoxy resin coated flame retardant powder can improve the surface bonding force between the flame retardant powder and the resin during the subsequent resin pouring and curing, improve the efficiency of the resin impregnation flame retardant powder, and achieve the effect of powder, resin, and fiber composite.

[0041] In step S5, the content of carbon fiber is 30-40wt.%, the content of silicon carbide fiber is 10-30wt.%, the content of flame retardant is 5-15wt.%, and the content of resin is 35-45wt.%. In one embodiment, a light resin transfer molding (LRT) process is used for preparation and casting. Specifically, the mold uses a closed mold, and the mold cavity is vacuumed before injecting resin into the mold cavity. Vacuuming can remove the air in the mold cavity, reduce the formation of bubbles and voids, thereby improving the strength and surface quality of the product, and can also promote the flow of resin, improve the impregnation effect, shorten the production cycle, improve production efficiency, reduce the porosity in the final product, and improve the strength and durability of the composite material. Carbon fiber and silicon carbide fiber can be cut according to actual needs. In other embodiments, in order to enhance the firmness of the paving material, viscose can be sprayed on the surface of the paved material before laying the next layer of material. In the present application, a suitable mold is selected according to the shape and size of the required UAV wing, for example, a non-metallic mold is selected. Non-metallic molds are simple to make, low in cost, have no direct impact on the product, and are suitable for the preparation process of the present application.

[0042] In step S6, the curing temperature is 60-100°C, for example, any value in the range of 60°C, 70°C, 80°C or 100°C; the curing time is 4-10h, for example, any value in the range of 4h, 6h, 8h or 10h. After demolding, post-processing such as cutting and polishing is performed according to the required size of the drone wing to obtain the drone wing.

[0043] See also Figure 2 and Figure 3 The present invention also provides a drone wing 10, which is prepared by the preparation method described above. The drone wing 10 includes a silicon carbide fiber layer 100, a flame retardant layer 200, a carbon fiber layer 300, a flame retardant layer 200 and a silicon carbide fiber layer 100 arranged in sequence. The outermost layer in the drone wing 10 of the present application is configured as a silicon carbide fiber layer 100, which can improve the fire resistance, oxidation resistance, corrosion resistance and other properties of the material; the flame retardant layer 200 of the drone wing 10 uses epoxy resin including flame retardant powder to further improve its fire resistance and flame retardant properties.

[0044] The technical scheme of the present invention is described in detail below through several specific examples. Unless otherwise specified, the raw materials and reagents used in the following examples are all commercially available products, or can be prepared by conventional methods in the art, and the instruments used in the examples are all commercially available.

[0045] Example 1

[0046] The preparation method of the drone wing in this embodiment is as follows: dissolve epoxy resin in an organic solvent to obtain an epoxy resin solution, place the flame retardant powder in the epoxy resin solution and stir for 60 minutes to obtain a powder slurry; add deionized water to the powder slurry and stir evenly, and separate the wet powder; vacuum dry the wet powder at 80°C for 8 hours to obtain a flame retardant. Silicon carbide fiber, carbon fiber, flame retardant, carbon fiber and silicon carbide fiber are laid on the mold in sequence, the mold is closed and resin is injected into the mold cavity of the mold; after curing at 70°C for 8 hours, demolding and trimming to the required size to obtain a drone wing.

[0047] In this embodiment, ethyl acetate is selected as the organic solvent, and the mass ratio of the organic solvent to the epoxy resin is 10:4; the mass ratio of the epoxy resin solution to the flame retardant powder is 10:2, and the flame retardant powder is selected from a composition of silicon carbide, tungsten carbide, silicon oxide and aluminum oxide, and the mass ratio of silicon carbide, tungsten carbide, silicon oxide and aluminum oxide is 1:1:1:1, the particle size of silicon carbide and tungsten carbide is 10μm, and the particle size of silicon oxide and aluminum oxide is 2μm; the mass ratio of powder slurry to deionized water is 1:4; in terms of the mass percentage of the drone wing, the content of carbon fiber is 30wt.%, the content of silicon carbide fiber is 30wt.%, the content of flame retardant is 5wt.%, and the content of resin is 35wt.%.

[0048] Example 2

[0049] The preparation method of the drone wing in this embodiment is as follows: dissolve epoxy resin in an organic solvent to obtain an epoxy resin solution, place the flame retardant powder in the epoxy resin solution and stir for 30 minutes to obtain a powder slurry; add deionized water to the powder slurry and stir evenly, and separate the wet powder; vacuum dry the wet powder at 100°C for 6 hours to obtain a flame retardant. Silicon carbide fiber, carbon fiber, flame retardant, carbon fiber and silicon carbide fiber are laid on the mold in sequence, the mold is closed and resin is injected into the mold cavity of the mold; after curing at 70°C for 8 hours, demolding and trimming to the required size to obtain a drone wing.

[0050] In this embodiment, cyclohexanone is selected as the organic solvent, and the mass ratio of the organic solvent to the epoxy resin is 10:1; the mass ratio of the epoxy resin solution to the flame retardant powder is 10:3, and the flame retardant powder is selected from a composition of silicon carbide, tungsten carbide, silicon oxide and aluminum oxide, and the mass ratio of silicon carbide, tungsten carbide, silicon oxide and aluminum oxide is 1:1:1:1, the particle size of silicon carbide and tungsten carbide is 20μm, and the particle size of silicon oxide and aluminum oxide is 18μm; the mass ratio of powder slurry to deionized water is 1:3; in terms of the mass percentage of the drone wing, the content of carbon fiber is 30wt.%, the content of silicon carbide fiber is 20wt.%, the content of flame retardant is 15wt.%, and the content of resin is 35wt.%.

[0051] Example 3

[0052] The preparation method of the drone wing in this embodiment is as follows: dissolve epoxy resin in an organic solvent to obtain an epoxy resin solution, place the flame retardant powder in the epoxy resin solution and stir for 50 minutes to obtain a powder slurry; add deionized water to the powder slurry and stir evenly, and separate the wet powder; vacuum dry the wet powder at 120°C for 2 hours to obtain a flame retardant. Silicon carbide fiber, carbon fiber, flame retardant, carbon fiber and silicon carbide fiber are laid on the mold in sequence, the mold is closed and resin is injected into the mold cavity of the mold; after curing at 100°C for 5 hours, demolding and trimming to the required size to obtain a drone wing.

[0053] In this embodiment, ethyl acetate is selected as the organic solvent, and the mass ratio of the organic solvent to the epoxy resin is 10:3; the mass ratio of the epoxy resin solution to the flame retardant powder is 10:5, the flame retardant powder is silicon carbide, and the particle size of silicon carbide is 10μm; the mass ratio of the powder slurry to deionized water is 1:4; in terms of the mass percentage of the UAV wing, the content of carbon fiber is 35wt.%, the content of silicon carbide fiber is 15wt.%, the content of flame retardant is 5wt.%, and the content of resin is 45wt.%.

[0054] Example 4

[0055] The preparation method of the drone wing in this embodiment is as follows: dissolve epoxy resin in an organic solvent to obtain an epoxy resin solution, place the flame retardant powder in the epoxy resin solution and stir for 30 minutes to obtain a powder slurry; add deionized water to the powder slurry and stir evenly, and separate the wet powder; vacuum dry the wet powder at 70°C for 10 hours to obtain a flame retardant. Silicon carbide fiber, carbon fiber, flame retardant, carbon fiber and silicon carbide fiber are laid on the mold in sequence, the mold is closed and resin is injected into the mold cavity of the mold; after curing at 100°C for 4 hours, demolding and trimming to the required size to obtain a drone wing.

[0056] In this embodiment, the organic solvent is N,N-dimethylformamide, and the mass ratio of the organic solvent to the epoxy resin is 10:2; the mass ratio of the epoxy resin solution to the flame retardant powder is 10:4, the flame retardant powder is alumina, and the particle size of the alumina is 1 μm; the mass ratio of the powder slurry to deionized water is 1:2; in terms of the mass percentage of the UAV wing, the content of carbon fiber is 40wt.%, the content of silicon carbide fiber is 10wt.%, the content of flame retardant is 10wt.%, and the content of resin is 40wt.%.

[0057] Example 5

[0058] The preparation method of the drone wing in this embodiment is as follows: dissolve epoxy resin in an organic solvent to obtain an epoxy resin solution, place the flame retardant powder in the epoxy resin solution and stir for 60 minutes to obtain a powder slurry; add deionized water to the powder slurry and stir evenly, and separate the wet powder; vacuum dry the wet powder at 90°C for 7 hours to obtain a flame retardant. Silicon carbide fiber, carbon fiber, flame retardant, carbon fiber and silicon carbide fiber are laid on the mold in sequence, the mold is closed and resin is injected into the mold cavity of the mold; after curing at 60°C for 10 hours, demolding and trimming to the required size to obtain a drone wing.

[0059] In this embodiment, cyclohexanone is selected as the organic solvent, and the mass ratio of the organic solvent to the epoxy resin is 10:4; the mass ratio of the epoxy resin solution to the flame retardant powder is 10:3, and the flame retardant powder is tungsten carbide, and the particle size of the tungsten carbide is 15μm; the mass ratio of the powder slurry to deionized water is 1:3.5; in terms of the mass percentage of the UAV wing, the content of carbon fiber is 35wt.%, the content of silicon carbide fiber is 15wt.%, the content of flame retardant is 15wt.%, and the content of resin is 35wt.%.

[0060] Example 6

[0061] The preparation method of the drone wing in this embodiment is as follows: dissolve epoxy resin in an organic solvent to obtain an epoxy resin solution, place the flame retardant powder in the epoxy resin solution and stir for 45 minutes to obtain a powder slurry; add deionized water to the powder slurry and stir evenly, and separate the wet powder; vacuum dry the wet powder at 80°C for 8 hours to obtain a flame retardant. Silicon carbide fiber, carbon fiber, flame retardant, carbon fiber and silicon carbide fiber are laid on the mold in sequence, the mold is closed and resin is injected into the mold cavity of the mold; after curing at 80°C for 7 hours, demolding and trimming to the required size to obtain a drone wing.

[0062] In this embodiment, cyclohexanone is selected as the organic solvent, the mass ratio of ethyl acetate to cyclohexanone is 1:1, and the mass ratio of the organic solvent to the epoxy resin is 10:3; the mass ratio of the epoxy resin solution to the flame retardant powder is 10:3, and the flame retardant powder is silicon oxide, and the particle size of silicon oxide is 30μm; the mass ratio of the powder slurry to deionized water is 1:4; in terms of the mass percentage of the drone wing, the content of carbon fiber is 38wt.%, the content of silicon carbide fiber is 17wt.%, the content of flame retardant is 5wt.%, and the content of resin is 40wt.%.

[0063] The drone wing 10 prepared in Examples 1 to 6 includes a silicon carbide fiber layer 100, a flame retardant layer 200, a carbon fiber layer 300, a flame retardant layer 200 and a silicon carbide fiber layer 100 arranged in sequence. The tensile properties, bending properties and high temperature resistance properties of the drone wings prepared in Examples 1 to 6 were tested in sequence, and the test results are shown in Table 1:

[0064] Table 1 Parameters and performance tests of the drone wings of Examples 1 to 6

[0065]

[0066] The high temperature resistance of the UAV wings prepared in Examples 1 to 6 was tested. At 1000° C., the mechanical properties of the UAV wings did not decrease.

[0067] Experiments show that the drone wing of the present application has good tensile and bending properties, as well as good fire resistance and high temperature resistance.

[0068] The outermost layer of the drone wing provided by the present invention is configured as a silicon carbide fiber layer, and a flame retardant layer composed of flame retardant powder coated with epoxy resin is arranged on the inner side of the silicon carbide fiber layer. Silicon carbide fiber belongs to ceramic fiber, which has good corrosion resistance and oxidation resistance. Therefore, the drone wing of the present application not only has good mechanical properties, but also has good oxidation resistance and corrosion resistance. At the same time, the fireproof performance and flame retardant performance of the wing are greatly improved, which can improve the performance and service life of the drone. In addition, the preparation method of the drone wing of the present application is simple, and the preparation cost is low. The drone wing can be used for firefighting and rescue drones. Therefore, the present invention effectively overcomes some practical problems in the prior art and has high utilization value and use significance.

[0069] The above embodiments are merely illustrative of the principles and effects of the present invention, and are not intended to limit the present invention. Anyone familiar with the art may modify or alter the above embodiments without departing from the spirit and scope of the present invention. Therefore, all equivalent modifications or alterations made by a person of ordinary skill in the art without departing from the spirit and technical concept disclosed by the present invention shall still be covered by the claims of the present invention.

Claims

1. A method for preparing a drone wing, characterized in that: include: dissolving epoxy resin in an organic solvent to obtain an epoxy resin solution; Placing the flame retardant powder in the epoxy resin solution and stirring evenly to obtain a powder slurry; Adding deionized water to the powder slurry and stirring evenly to separate wet powder; Drying the wet powder to obtain a flame retardant; Laying silicon carbide fiber, carbon fiber, flame retardant, carbon fiber and silicon carbide fiber in sequence on the mold, closing the mold and injecting resin into the mold cavity of the mold; After curing, demoulding and trimming to the required size, the UAV wing is obtained.

2. The preparation method according to claim 1, characterized in that: The mass ratio of the organic solvent to the epoxy resin is 10:1 to 10:

4.

3. The preparation method according to claim 1, characterized in that: The organic solvent includes any one of ethyl acetate, cyclohexanone and N,N-dimethylformamide.

4. The preparation method according to claim 1, characterized in that: The flame retardant powder includes any one or more of silicon carbide, tungsten carbide, silicon oxide, and aluminum oxide, and the particle size of the flame retardant powder is 1 to 30 μm.

5. The preparation method according to claim 1, characterized in that: The mass ratio of the epoxy resin solution to the flame retardant powder is 10:2 to 10:

5.

6. The preparation method according to claim 1, characterized in that: The mass ratio of the powder slurry to the deionized water is 1:2 to 1:

4.

7. The preparation method according to claim 1, characterized in that: When the wet powder is dried, vacuum drying is selected, the drying temperature is 70 to 120° C., and the drying time is 2 to 10 hours.

8. The preparation method according to claim 1, characterized in that: The curing temperature during the curing is 60-100° C., and the curing time is 4-10 hours.

9. The preparation method according to claim 1, characterized in that: Calculated by mass percentage of the UAV wing, the content of the carbon fiber is 30-40wt.%, the content of the silicon carbide fiber is 10-30wt.%, the content of the flame retardant is 5-15wt.%, and the content of the resin is 35-45wt.%.

10. A drone wing, characterized in that: The UAV wing is manufactured using the preparation method of any one of claims 1 to 9, wherein the UAV wing comprises a silicon carbide fiber layer, a flame retardant layer, a carbon fiber layer, a flame retardant layer and a silicon carbide fiber layer arranged in sequence.

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