Wing and unmanned aerial vehicle

Abstract

The present application is about a wing and a drone, the wing includes an upper rib and a lower rib extending along a first direction and arranged at intervals, the first direction is the length direction of the wing, the wing also includes struts connected to the upper rib and the lower rib at both ends, a plurality of struts are arranged at intervals along the first direction, the wing is divided into at least two wing sections of equal length along the first direction, wherein the wing section closest to the fuselage is the first wing section, the number of struts in the first wing section is greater than the number of struts in other wing sections, the upper rib, the lower rib and the strut are all made of carbon fiber filament unidirectional ply cloth, the carbon fiber unidirectional ply cloth is formed by stacking and gluing a plurality of layers of carbon fiber filaments at a first preset angle ply angle. The upper rib, the lower rib and the strut of the wing of the present application are made of carbon fiber filament unidirectional ply cloth, which reduces the overall weight of the wing while ensuring strength, and at the same time, the number of struts in the wing section close to the fuselage is greater, which improves the structural strength and shear resistance at the wing root and improves the stability of the wing.

Description

Technical Field

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

[0002] UAVs are widely used in many fields. Currently, in related technologies, the wings of UAVs usually use metal wing spars, such as thick-walled profiles such as aluminum alloy or alloy steel, to withstand tensile pressure and shear force to ensure the structural strength of the wings.

[0003] However, the wings in the related technology are usually heavy. Although the metal wing beam has high strength, its heavy weight results in low specific strength and specific stiffness, and poor fatigue resistance, resulting in poor wing stability and the overall load-bearing capacity of the drone. Summary of the invention

[0004] In order to overcome the above-mentioned shortcomings of the related art, the present application aims to provide a wing and a UAV.

[0005] In order to achieve the above objectives, this application adopts the following technical solutions:

[0006] According to a first aspect of the present application, there is provided a wing, comprising:

[0007] An upper edge strip extending along a first direction, wherein the first direction is a length direction of the wing;

[0008] A lower edge strip extending along the first direction and spaced apart from the upper edge strip;

[0009] A strut, wherein both ends of the strut are respectively connected to the upper edge strip and the lower edge strip, the number of the struts is multiple, and the multiple struts are arranged at intervals along a first direction, the wing is divided into at least two wing sections of equal length along the first direction, the wing section closest to the fuselage among the at least two wing sections is the first wing section, and the number of the struts of the first wing section is greater than the number of the struts of the other wing sections among the at least two wing sections;

[0010] The upper edge strip, the lower edge strip and the pillar are all made of carbon fiber unidirectional ply cloth, and the carbon fiber unidirectional ply cloth is formed by stacking and laying a plurality of layers of carbon fiber filaments at a first preset ply angle and then gluing them together.

[0011] In a possible implementation manner, the carbon fiber unidirectional laminated cloth used in the upper edge strip and the lower edge strip has the same laying direction, and the carbon fiber unidirectional laminated material used in the upper edge strip and the pillar has different laying directions.

[0012] In a possible implementation, the plying direction of the carbon fiber unidirectional ply cloth used in the upper edge strip and the lower edge strip is the first direction, and the plying direction of the carbon fiber unidirectional ply cloth used in the pillar is the second direction, and the second direction is the width direction of the wing.

[0013] In a possible implementation, the wing further includes:

[0014] A front web, used to connect the upper edge strip and the lower edge strip;

[0015] A rear belly plate is used to connect the upper edge strip and the lower edge strip, and the rear belly plate and the front belly plate are spaced apart along a third direction, and the third direction is the thickness direction of the wing.

[0016] In a possible implementation manner, the pillar starting along the first direction is a first pillar, and the pillar at the end of the first direction is a second pillar;

[0017] The upper slat, the lower slat, the front web, the rear web, the first strut and the second strut together constitute the outer surface of the wing, and the outer surface of the wing is box-shaped.

[0018] In a possible embodiment, the front belly plate and the rear belly plate are made of carbon fiber composite ply cloth, and the carbon fiber composite ply cloth is formed by stacking and laying a plurality of layers of carbon fiber filaments at a second preset angle and gluing them together, and the second preset angle is 45°, -45° or 90°.

[0019] In a possible implementation manner, in a first direction and in a direction away from the fuselage, cross-sectional areas of the front web and the rear web both gradually decrease.

[0020] In a possible embodiment, the upper edge strip, the lower edge strip, the front belly plate and the rear belly plate enclose an installation space, a plurality of the pillars are arranged in the installation space, and the plurality of the pillars divide the installation space into a plurality of accommodating spaces, one accommodating space is formed between two adjacent pillars, and a filling layer is arranged in the accommodating space.

[0021] In a possible implementation, the filling layer includes a hard foam plastic layer, and the filling layer is adhesively connected to the accommodating space.

[0022] According to a second aspect of the present disclosure, there is provided an unmanned aerial vehicle, comprising a fuselage and the wing as described in the first aspect of the present disclosure, which is arranged on the fuselage.

[0023] The advantages of the present application are that the upper edge strips, lower edge strips and struts of the wing of the present application adopt carbon fiber unidirectional laminated cloth, which reduces the overall weight of the wing while ensuring the strength. At the same time, the number of struts in the wing section close to the fuselage is greater, which improves the structural strength and shear resistance at the wing root and improves the stability of the wing.

[0024] Other features and advantages of the present application will be set forth in the subsequent description, and in part will become apparent from the description, or may be understood through implementation of the present application. The objects and other advantages of the present application may be realized and obtained through the structures particularly pointed out in the description, claims and drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] The accompanying drawings, which are incorporated into the specification and constitute a part of the specification, illustrate embodiments of the present application and are used together with the description to explain the principles of the present application. In these drawings, similar reference numerals are used to identify similar elements. The drawings described below are some embodiments of the present application, rather than all embodiments. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without paying creative work.

[0026] Figure 1 is one of the schematic structural diagrams of a wing according to an exemplary embodiment.

[0027] Figure 2 This is a second schematic diagram of the structure of a wing according to an exemplary embodiment.

[0028] Figure 3 This is a third schematic diagram of the structure of a wing according to an exemplary embodiment.

[0029] Figure 4 It is one of the structural schematic diagrams of a pillar according to an exemplary embodiment.

[0030] Figure 5 This is a second schematic diagram of the structure of a pillar according to an exemplary embodiment. DETAILED DESCRIPTION

[0031] In order to make the purpose, technical scheme and advantages of the embodiments of the present application clearer, the technical scheme in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, rather than all of the embodiments. Based on the embodiments of the present application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. It should be noted that, in the absence of conflict, the embodiments in the present application and the feature vectors in the embodiments can be arbitrarily combined with each other.

[0032] UAVs are widely used in many fields. Currently, in related technologies, the wings of UAVs usually use metal wing spars, such as thick-walled profiles such as aluminum alloy or alloy steel, to withstand tensile pressure and shear force to ensure the structural strength of the wings.

[0033] However, the wings in the related technology are usually heavy. Although the metal wing beam has high strength, its heavy weight results in low specific strength and specific stiffness, and poor fatigue resistance, resulting in poor wing stability and the overall load-bearing capacity of the drone.

[0034] To solve the above problems, the present application provides a wing and a UAV, in which the upper edge strips, lower edge strips and struts of the wing are made of carbon fiber unidirectional laminated cloth, which reduces the overall weight of the wing while ensuring its strength. At the same time, the number of struts in the wing section close to the fuselage is greater, which improves the structural strength and shear resistance at the wing root and improves the stability of the wing.

[0035] According to an exemplary embodiment, Figure 1-Figure 5 As shown, the embodiment of the present application provides a wing, the wing includes an upper edge strip 11 and a lower edge strip 12. The upper edge strip 11 extends along a first direction, and the first direction is the length direction of the wing, that is, Figure 3 In the horizontal direction shown in , the lower edge strip 12 extends along the first direction, and the lower edge strip 12 and the upper edge strip 11 are arranged at intervals, that is, the upper edge strip 11 and the lower edge strip 12 are parallel and arranged at intervals. The wing also includes a strut 13. The upper edge strip 11, the lower edge strip 12 and the strut 13 together constitute the frame structure of the wing, which supports the wing and improves the structural strength and anti-bending performance of the wing. The first side 1301 of the strut 13 is connected to the upper edge strip 11, and the second side 1302 of the strut 13 is connected to the lower edge strip 12. The first side 1301 and the second side 1302 are the opposite ends of the strut 13. In addition, there are multiple struts 13, and the multiple struts 13 are arranged unevenly along the first direction.

[0036] like Figure 1-Figure 3 As shown, the wing is divided into at least two wing sections of equal length along a first direction. The embodiment of the present application is described by taking the wing divided into two wing sections as an example. The wing is divided into a first wing section 101 and a second wing section 102 along the first direction. The length of the first wing section 101 is equal to the length of the second wing section 102. The wing section closest to the fuselage (not shown in the figure) is the first wing section 101. Figure 3 Taking the orientation shown in as an example, the first wing section 101 is located at Figure 3In the wing section on the left side, the number of struts 13 in the first wing section 101 is greater than the number of struts 13 in the second wing section 102, that is, the arrangement density of the struts 13 in the wing section close to the fuselage is greater than that in other wing sections. It is worth noting that in the embodiment of the present application, the wing is divided into two wing sections. During actual production and design, those skilled in the art can also divide the wing into more wing sections according to actual needs, as long as the number of struts 13 in the first wing section 101 is greater than the number of other wing sections. The number of struts 13 in other wing sections can be equal or unequal, and the embodiment of the present application does not impose too many restrictions on this.

[0037] Among them, the upper edge strip 11, the lower edge strip 12 and the pillar 13 are all made of carbon fiber unidirectional ply cloth, and the carbon fiber unidirectional ply cloth is formed by stacking and laying several layers of carbon fiber filaments at a ply angle of a first preset angle and gluing them together. For example, the carbon fiber filaments can be impregnated with a resin matrix and then cured to form a carbon fiber fabric. The multiple layers of carbon fiber fabrics are impregnated with resin and then cured, or directly glued with adhesives such as epoxy resin to form a carbon fiber unidirectional ply cloth. Among them, the first preset angle can be, for example, 0°, that is, a ply method in which the fiber direction coincides with the load direction, and has higher tensile strength and stiffness. Of course, it can be understood that the first preset angle can be set to other angles according to the requirements for tensile strength, shear strength, bending strength, etc., and the embodiments of the present application do not impose too many restrictions on this.

[0038] In the embodiment of the present application, the upper edge strips, lower edge strips and struts of the wing are made of carbon fiber unidirectional laminated cloth, which reduces the overall weight of the wing while ensuring strength. At the same time, the number of struts in the wing section close to the fuselage is greater, which improves the structural strength and shear resistance at the wing root and improves the stability of the wing.

[0039] In some embodiments, the carbon fiber unidirectional ply fabric used for the upper edge strip 11 , the lower edge strip 12 and the support 13 may have a variety of plying methods.

[0040] In one example, the laying angles of the carbon fiber unidirectional ply cloth used for the upper edge strip 11, the lower edge strip 12 and the pillar 13 are all 0°, that is, the laying method in which the fiber direction coincides with the load direction, and the load directions to be borne by the upper edge strip 11 and the lower edge strip 12 are the same, so the laying directions of the carbon fiber unidirectional ply cloth used for the upper edge strip 11 and the lower edge strip 12 are the same; the load directions to be borne by the upper edge strip 11 and the pillar 13 are different, so the laying directions of the carbon fiber unidirectional ply cloth used for the upper edge strip 11 and the lower edge strip 12 are different.

[0041] In one example, the ply direction of the carbon fiber unidirectional ply fabric used in the upper edge strip 11 and the lower edge strip 12 is a first direction, and the ply direction of the carbon fiber unidirectional ply fabric used in the support 13 is a second direction. The first direction is the length direction of the wing, that is, Figure 3 The second direction is the horizontal direction shown in , and the second direction is the width direction of the wing, that is, Figure 3 In the vertical direction shown in the figure, the upper edge strip 11, the lower edge strip 12 and the support 13 are mainly used to withstand tension and pressure. The laying angle of the carbon fiber unidirectional ply cloth used is 0°, and the laying directions of the 0° ply of the carbon fiber unidirectional ply cloth used are respectively along their respective extension directions to improve the tensile strength and stiffness and enhance the stability of the wing.

[0042] In some embodiments, the wing further comprises a front web 14 and a rear web 15. Figure 1-Figure 3 As shown, the front web 14 and the rear web 15 are both used to connect the upper edge strip 11 and the lower edge strip 12, and the front web 14 and the rear web 15 are covered on at least part of the surface of the upper edge strip 11, the lower edge strip 12 and the strut 13, so as to form the outer surface of the wing, wherein the front web 14 and the rear web 15 are parallel, and the front web 14 and the rear web 15 are spaced apart along the third direction, and the strut 13 is arranged between the front web 14 and the rear web 15, and the third direction is the thickness direction of the wing, that is, Figure 5 The vertical direction shown in .

[0043] In some embodiments, the wing is a box-type wing. Figure 1-Figure 3 As shown, the strut 13 starting along the first direction is the first strut 131, and the strut 13 ending along the first direction is the second strut 132. It can be understood that the starting to the ending along the first direction refers to the direction from the wing root to the wing tip along the first direction, and the wing root is the end of the wing close to the fuselage. The upper edge strip 11, the lower edge strip 12, the front web 14, the rear web 15, the first strut 131 and the second strut 132 together constitute the box-shaped outer surface of the wing, thereby forming an integrated box-shaped wing.

[0044] In some embodiments, the front web 14 and the rear web 15 are made of carbon fiber material. Specifically, the front web 14 and the rear web 15 are made of carbon fiber composite ply cloth, which is formed by stacking and gluing several layers of carbon fiber filaments at a second preset angle. Among them, the second preset angle can be 45°, -45° or 90°. When the second preset angle is 45°, that is, when the ply is laid at a 45° angle, the fiber direction is at a 45° angle to the load direction, and the material after plying has a relatively uniform strength and stiffness distribution, and can simultaneously withstand certain shear and bending loads; when the second preset angle is 90°, that is, when the ply is laid at a 90° angle, the fiber direction is at a 90° angle to the load direction, and the material after plying has higher shear strength and bending strength, higher shear and bending resistance, but lower tensile strength and stiffness; when the second preset angle is 45°, it is similar to the ply at a 45° angle, and will not be repeated here.

[0045] Of course, it is understandable that the embodiment of the present application uses 45° ply and 90° ply as examples for specific explanation. The second preset angle can actually also use uncommon ply angles such as 30°, -30°, 60°, -60°, etc. The structural performance and mechanical performance distribution are also relatively uniform, but the manufacturing difficulty and cost are relatively high. Between multiple layers of carbon fiber filaments, the arrangement direction of each layer of carbon fiber filaments can also have a second preset angle with the arrangement direction of the previous layer of carbon fiber filaments, thereby improving the uniformity of the mechanical properties of the carbon fiber composite ply cloth in all directions. The embodiment of the present application does not impose too many restrictions on this.

[0046] Among them, it is worth mentioning that, according to the requirements for structural properties and mechanical properties such as strength, stiffness, bending strength, shear strength, etc. of the front belly plate 14 and the rear belly plate 15, the front belly plate 14 and the rear belly plate 15 can be made of carbon fiber composite lay-up cloth with the same lay-up angle, for example, both use carbon fiber composite lay-up cloth with a 45° angle lay-up; the front belly plate 14 and the rear belly plate 15 can also be made of carbon fiber composite lay-up cloth with different lay-up angles, for example, the front belly plate 14 uses carbon fiber composite lay-up cloth with a -45° angle lay-up, and the rear belly plate 15 uses carbon fiber composite lay-up cloth with a 90° angle lay-up, etc. The embodiment of the present application does not impose too many restrictions on this, and those skilled in the art can make settings according to actual needs.

[0047] In some embodiments, along the span direction of the wing, the cross-sectional areas of the front web 14 and the rear web 15 gradually decrease. Figure 3 As shown, the span direction of the wing is the direction along the first direction and away from the fuselage, that is, Figure 3The horizontal right direction shown in . Along the wingspan direction of the wing, that is, from the wing root to the wing tip, the cross-sectional areas of the front and rear webs 14 and 15 are gradually reduced. The cross-sectional areas of the front and rear webs 14 and 15 at the wing root are larger, so that the wing root has higher strength to avoid fracture and wear, thereby improving the stability and service life of the wing. From the wing root to the wing tip, the strength requirements of the front and rear webs 14 and 15 are gradually reduced, so the cross-sectional areas of the front and rear webs 14 and 15 are gradually reduced, so as to reduce the weight of the wing itself as much as possible while ensuring the strength, and improve the overall load-bearing capacity of the UAV.

[0048] Among them, the cross-sectional area of ​​the front web 14 and the rear web 15 gradually decreases, which may refer to at least one of the length, width and thickness gradually decreasing. In one example, along the first direction and away from the fuselage, the length and width of the front web 14 and the rear web 15 remain unchanged, and the thickness gradually decreases; in another example, along the first direction and away from the fuselage, the thickness of the front web 14 and the rear web 15 remains unchanged, and the length and width gradually decrease; in another example, the length, width and thickness of the front web 14 and the rear web 15 gradually decrease. In addition, the change trend of the reduction of the cross-sectional area of ​​the front web 14 and the rear web 15 can be a linear change or an irregular change, such as widening and / or thickening the front web 14 and the rear web 15 in certain areas where the force is more concentrated. The embodiments of the present application do not impose too many restrictions on this, and those skilled in the art can make settings according to actual needs.

[0049] In some embodiments, the width of the wing gradually decreases along the span direction of the wing. The width of the wing is the distance between the upper rib 11 and the lower rib 12. When the width of the wing gradually decreases along the span direction of the wing, the upper rib 11 and the lower rib 12 are not arranged in parallel, but there is a certain angle between them. At the same time, along the span direction of the wing, the length of the strut 13 also gradually decreases. Reducing the use of materials at the wing tip where the structural strength requirement is lower can effectively reduce the production cost without affecting the normal use of the wing.

[0050] In some embodiments, the support 13 is a plate-shaped support. Figure 4-Figure 5 As shown, the pillar 13 is formed by a first side 1301, a second side 1302, a third side 1303 and a fourth side 1304, wherein the first side 1301 and the second side 1302 are opposite to each other, the third side 1303 and the fourth side 1304 are opposite to each other, and the first side 1301 and the third side 1303 are adjacent to each other. Figure 1-Figure 3As shown, in the wing of the embodiment of the present application, the pillar 13 is perpendicular to the upper edge strip 11 and the lower edge strip 12, and the pillar 13 is perpendicular to the front web 14 and the rear web 15. The first side 1301 is connected to the upper edge strip 11, the second side 1302 is connected to the lower edge strip 12, the third side 1303 is connected to the front web 14, and the fourth side 1304 is connected to the rear web 15. When the sides of the pillar 13 are connected to other structures of the wing, adhesives such as epoxy resin, polyurethane, and chlorinated rubber can be used for bonding. Of course, it can be understood that other adhesives can also be used for bonding, or other connection methods such as snap-on and plug-in can be used. Those skilled in the art can make settings according to actual needs, and the embodiment of the present application does not impose too many restrictions on this.

[0051] In some embodiments, the third side 1303 and the fourth side 1304 of the pillar 13 are further provided with a connecting portion. Figure 1-Figure 5 As shown, a first connection portion 1305 protruding from the third side 1303 is provided on the third side 1303 of the pillar 13, and a second connection portion 1306 protruding from the fourth side 1304 is provided on the fourth side 1304 of the pillar 13. The first connection portion 1305 can be connected by snapping with a slot provided on the front web 14, or can be connected by bonding with the front web 14; the second connection portion 1306 can be connected by snapping with a slot provided on the rear web 15, or can be connected by bonding with the rear web 15. The embodiment of the present application does not impose too many restrictions on this. By providing the first connection portion 1305 and the second connection portion 1306 on the pillar 13, the stability of the connection between the pillar 13 and the front web 14 and the rear web 15 can be improved, and positioning is convenient, which is conducive to reducing the difficulty of operation.

[0052] In some embodiments, the front web 14 and the rear web 15 are both provided with a plurality of positioning holes 104 corresponding to the pillars 13. Figure 1-Figure 3 As shown, a plurality of positioning holes 104 are arranged along the first direction, a first connection portion 1305 of a third side 1303 of the pillar 13 at least partially extends into the positioning hole 104 on the front web 14 and is bonded and fixed, and a second connection portion 1306 of a fourth side 1304 of the pillar 13 at least partially extends into the positioning hole 104 on the rear web 15 and is bonded and fixed. By providing the positioning holes 104 on the front web 14 and the rear web 15, it is possible to facilitate positioning of the installation position of the pillar 13, and also to improve the stability of the connection between the pillar 13 and the front web 14 and the rear web 15 by simultaneously using the clamping and bonding methods for connection.

[0053] Among them, the height of the first connection part 1305 protruding from the third side 1303 is less than or equal to the thickness of the front belly plate 14, and the height of the second connection part 1306 protruding from the fourth side 1304 is less than or equal to the thickness of the rear belly plate 15, thereby avoiding the first connection part 1305 and the second connection part 1306 protruding from the outer surface of the wing, affecting the overall aesthetics of the wing and the stability of the connection of the pillar 13.

[0054] In some embodiments, at least one of the front web 14 and the rear web 15 is provided with a web reinforcement structure (not shown in the figure). Figure 1-Figure 3 As shown, taking the web reinforcement structure arranged on the front web 14 as an example, the length of the web reinforcement structure is less than or equal to the length of the front web 14, and the width of the web reinforcement structure is less than or equal to the width of the front web 14. The web reinforcement structure can be fixed to the front web 14 by bonding, threading, etc. The web reinforcement structure is used to improve the structural strength of the front web 14, and at the same time, it can also cover the positioning holes 104 on the front web 14 to improve the overall aesthetics. The web reinforcement structure can also be arranged on the rear web 15. The way of arranging the web reinforcement structure on the rear web 15 is similar to that on the front web 14. The embodiments of the present application will not be repeated here. Those skilled in the art can arrange the sub-plate reinforcement structure on the front web 14 and / or the rear web 15 according to actual needs, and the embodiments of the present application do not impose too many restrictions on this.

[0055] In some embodiments, the interior of the wing has a mounting space. Figure 1-Figure 3 As shown, the upper edge strip 11, the lower edge strip 12, the front web 14 and the rear web 15 enclose an installation space, that is, the inner space of the wing, and a plurality of struts 13 are arranged in the installation space.

[0056] In some embodiments, a plurality of pillars 13 divide the installation space into a plurality of accommodating spaces 103. Figure 2-Figure 3 As shown, a receiving space 103 is formed between two adjacent pillars 13, and a filling layer (not shown in the figure) is arranged in the receiving space 103. The shape of the filling layer is adapted to the shape of the receiving space 103, and the size of the filling layer can be slightly smaller than the size of the receiving space 103, so as to facilitate the placement of the filling layer, and the filling layer is fixed to the front web 14 and the rear web 15 by bonding, clamping and other connection methods. Of course, it can be understood that when the filling layer is a plastic material, its size needs to be slightly smaller than the size of the receiving space 103, and when the filling layer is a material with a certain elasticity, its size can also be equal to or larger than the size of the receiving space 103, as long as the filling layer can be installed and fixed in the receiving space 103, the embodiment of the present application does not impose too many restrictions on this.

[0057] In one example, the filling layer includes a rigid foam plastic layer. The rigid foam plastic is a foam plastic with an elastic modulus greater than 700 MPa, and the material of the rigid foam plastic layer can be PMI (poly methacrylimide) foam plastic, polyvinyl chloride foam plastic, polyurethane foam plastic, etc. Since such rigid foam plastic has the characteristics of light weight, excellent mechanical properties, high specific strength and specific modulus, it is applied to the filling of the wing, which can effectively improve the shear stability of the wing without increasing the weight of the wing too much.

[0058] In addition, the filling layer is bonded to the accommodating space 103. Specifically, when the filling layer is bonded to the accommodating space 103, adhesive can be applied only to the two surfaces of the filling layer that are in contact with the front web 14 and the rear web 15, respectively, to simplify the bonding process, reduce the amount of adhesive used, and save production costs; adhesive can also be applied to all surfaces of the filling layer that are in contact with other parts for bonding, to improve the stability and reliability of the connection. The present application embodiment does not impose too many restrictions on this, and those skilled in the art can make choices according to actual needs.

[0059] In some embodiments, the filling layer can be arranged in the front belly plate 14 and / or the rear belly plate 15. Taking the filling layer arranged in the front belly plate 14 as an example, the front belly plate 14 may include a first substrate (not shown in the figure) and a first cover plate (not shown in the figure) fixedly connected to the substrate, the first substrate faces the outside of the wing, the first cover plate faces the inside of the wing, and multiple filling layers are arranged between the first substrate and the first cover plate. When making the front belly plate 14, the first substrate is first laid flat, and then the filling layer is placed and bonded at a position corresponding to the accommodating space 103 on the first substrate, and then the first cover plate is covered on the first substrate and the filling layer, and the first cover plate is fixed to the first substrate by bonding and curing to form the front belly plate 14 with a filling layer, and multiple bulges with a filling layer are formed at a position corresponding to the accommodating space 103 on the front belly plate 14 to fill the inside of the wing and improve the structural strength of the wing.

[0060] It can be understood that the rear belly plate 15 can also adopt a structure similar to the front belly plate 14. The rear belly plate 15 includes a second substrate (not shown in the figure), a second cover plate (not shown in the figure) and a filling layer arranged between the second substrate and the second cover plate. The embodiments of the present application will not be repeated here.

[0061] In one example, the filling layer is disposed in the front web 14; in another example, the filling layer is disposed in the rear web 15; in yet another example, the filling layer is disposed in both the front web 14 and the rear web 15. By integrating the filling layer into the front web 14 and / or the rear web 15 during manufacturing, the stability of the connection of the filling layer can be improved and the assembly process can be simplified. The embodiments of the present application do not impose too many restrictions on the specific location and form of the filling layer, and those skilled in the art can select according to actual needs.

[0062] The following will be combined Figure 1-Figure 5 , the assembly process of the wing of an embodiment of the present application is described.

[0063] First, the rear belly plate 15 is laid flat; then, according to the pre-designed drawings, the upper edge strip 11, the lower edge strip 12 and the pillar 13 are fixed to the rear belly plate 15 by gluing and curing, or the upper edge strip 11, the lower edge strip 12 and the pillar 13 are bonded to form a wing frame, and then the wing frame is fixed to the rear belly plate 15; then, the filling layer is coated with glue and placed in the accommodating space 103 for fixing; finally, the front belly plate 14 is covered on the upper layer, and the front belly plate 14 is glued and cured with other parts of the wing to finally form the wing of the embodiment of the present application.

[0064] According to an exemplary embodiment, Figure 1-Figure 5 As shown, an embodiment of the present application provides a drone, including a fuselage (not shown in the figure) and a wing as described in the above embodiment arranged on the fuselage. The wing includes an upper edge strip 11, a lower edge strip 12 and a strut 13. The upper edge strip 11 extends along a first direction, the first direction is the length direction of the wing, the lower edge strip 12 extends along the first direction, and the lower edge strip 12 and the upper edge strip 11 are arranged at intervals, and the two ends of the strut 13 are respectively connected to the upper edge strip 11 and the lower edge strip 12. In addition, the number of the struts 13 is multiple, and the multiple struts 13 are arranged unevenly at intervals along the first direction. The wing is divided into at least two wing sections of equal length along the first direction, wherein the wing section closest to the fuselage is the first wing section 101, and the number of struts 13 in the first wing section 101 is greater than the number of struts 13 in other wing sections.

[0065] Among them, the upper edge strip 11, the lower edge strip 12 and the pillar 13 are all made of carbon fiber unidirectional ply cloth, and the carbon fiber unidirectional ply cloth is formed by stacking and laying a plurality of layers of carbon fiber filaments at a ply angle of a first preset angle and gluing them together. For example, the carbon fiber filaments can be impregnated with a resin matrix and then the impregnated carbon fiber filaments are cured to form a carbon fiber fabric. The multiple layers of carbon fiber fabrics are impregnated with resin and then cured, or are directly glued together with an adhesive such as epoxy resin to form a carbon fiber unidirectional ply cloth.

[0066] It should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device comprising a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the statement "include..." do not exclude the existence of other identical elements in the process, method, article or device comprising the elements.

[0067] Finally, it should be noted that the above embodiments are only used to illustrate the technical solution of the present application, rather than to limit it. The present application is described in detail with reference to the preferred embodiments only. Those skilled in the art should understand that the technical solution of the present application can be modified or replaced by equivalents without departing from the spirit and scope of the technical solution of the present application, and should be included in the scope of the claims of the present application.

Claims

1. A wing, characterized in that: include: An upper edge strip extending along a first direction, wherein the first direction is a length direction of the wing; A lower edge strip extending along the first direction and spaced apart from the upper edge strip; A strut, wherein both ends of the strut are respectively connected to the upper edge strip and the lower edge strip, the number of the struts is multiple, and the multiple struts are arranged at intervals along a first direction, the wing is divided into at least two wing sections of equal length along the first direction, the wing section closest to the fuselage among the at least two wing sections is the first wing section, and the number of the struts of the first wing section is greater than the number of the struts of the other wing sections among the at least two wing sections; The upper edge strip, the lower edge strip and the pillar are all made of carbon fiber unidirectional ply cloth, and the carbon fiber unidirectional ply cloth is formed by stacking and laying a plurality of layers of carbon fiber filaments at a first preset ply angle and then gluing them together.

2. The wing according to claim 1, characterized in that The carbon fiber unidirectional ply fabrics used in the upper edge strip and the lower edge strip have the same plying direction, while the carbon fiber unidirectional ply fabrics used in the upper edge strip and the pillar have different plying directions.

3. The wing according to claim 2, characterized in that The laying direction of the carbon fiber unidirectional ply cloth used in the upper edge strip and the lower edge strip is the first direction, and the laying direction of the carbon fiber unidirectional ply cloth used in the pillar is the second direction, and the second direction is the width direction of the wing.

4. The wing according to claim 1, characterized in that The wing also includes: A front web, used to connect the upper edge strip and the lower edge strip; A rear belly plate is used to connect the upper edge strip and the lower edge strip, and the rear belly plate and the front belly plate are spaced apart along a third direction, and the third direction is the thickness direction of the wing.

5. The wing according to claim 4, characterized in that The pillar starting along the first direction is a first pillar, and the pillar at the end of the first direction is a second pillar; The upper slat, the lower slat, the front web, the rear web, the first strut and the second strut together constitute the outer surface of the wing, and the outer surface of the wing is box-shaped.

6. The wing according to claim 4, characterized in that The front web and the rear web are made of carbon fiber composite ply cloth, which is formed by stacking and laying a plurality of carbon fiber filaments at a second preset angle and bonding them together, wherein the second preset angle is 45°, -45° or 90°.

7. The wing according to claim 4, characterized in that In the first direction and in the direction away from the fuselage, the cross-sectional areas of the front web and the rear web are gradually reduced.

8. The wing according to claim 4, characterized in that The upper edge strip, the lower edge strip, the front belly plate and the rear belly plate enclose an installation space, a plurality of the pillars are arranged in the installation space, and the plurality of the pillars divide the installation space into a plurality of accommodating spaces, one accommodating space is formed between two adjacent pillars, and a filling layer is arranged in the accommodating space.

9. The wing according to claim 8, characterized in that The filling layer comprises a hard foam plastic layer, and the filling layer is adhesively connected to the accommodating space.

10. A drone, characterized in that: The invention comprises a fuselage and a wing according to any one of claims 1 to 9 arranged on the fuselage.

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