Unmanned aerial vehicle wing structure with flexible connection

By adopting flexible materials and modular production for the drone wing structure, the weight and lifespan issues of hard alloy hinge connections have been solved, achieving a lightweight and flexibly combinable wing design, which improves the drone's endurance and production efficiency.

CN223878230UActive Publication Date: 2026-02-06CHANGCHUN CHANGGUANG HIGH PERFORMANCE MATERIALS CO LTD
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Patent Information

Application Number
CN202520665323.6
Authority / Receiving Office
CN · China
Patent Type
Utility models(China)
Current Assignee / Owner
Filing Date
2025-04-10
Publication Date
2026-02-06
Estimated Expiration
2035-04-10

AI Technical Summary

Technical Problem

In existing UAV wing structures, the carbide hinge connection method has problems such as large weight, short service life, and complex assembly process, and it is difficult to quickly respond to different production needs.

Method used

Flexible materials such as Kevlar are used as connecting materials. The main and ailerons are flexibly connected by modularly producing parts and assembling them as a whole. The main wing skin and flaps are made of carbon fiber materials, combined with wing root connectors and winglet connecting rods, and have internal container chambers for storing fuel or batteries.

Benefits of technology

The reduced wing weight improves service life and production efficiency, lowers production costs, expands the drone's operating range, and ensures controllable component quality, enabling rapid response to different production needs.

✦ Generated by Eureka AI based on patent content.

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Abstract

The utility model belongs to the technical field of unmanned aerial vehicle wing structures, and particularly relates to an unmanned aerial vehicle wing structure with flexible connection. Comprising a wing flexible connecting structure, a wing root connecting piece, a winglet and a winglet connecting rod, the wing flexible connecting structure comprises a wing upper skin, a main wing lower skin, a flap and a flexible connecting piece; the flap side of the main wing upper skin is connected with the flap through a flexible connecting piece; one end of the main wing upper skin and one end of the main wing lower skin are butted and spliced through a wing root connecting piece to form a main wing; the interior of the main wing is a cavity; the winglet sleeves the other end of the main wing upper skin and the other end of the main wing lower skin, and is connected with the wing root connecting piece through the winglet connecting rod; the unmanned aerial vehicle body is connected with the wing root connecting pieces through bolts. The unmanned aerial vehicle has the advantages that the weight of the main wings is effectively reduced, unmanned aerial vehicle fuel or batteries can be stored in the container cavities in the main wings, and the endurance mileage is increased.
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Description

TECHNICAL FIELD

[0001] The utility model belongs to unmanned aerial vehicle wing structure technical field, concretely relates to an unmanned aerial vehicle wing structure with flexible connection. BACKGROUND

[0002] In recent years along with the development of information technology, unmanned aerial vehicle plays a more and more important role in the field of battlefield reconnaissance, earthquake relief, agricultural production etc. To adapt to the more and more complex flight environment, the wing with main wing and auxiliary wing combination mode can adjust the auxiliary wing overturn angle to deal with the complex wind force and wind direction change. At present, the mainstream unmanned aerial vehicle commonly adopts hard alloy hinge to connect with main wing and auxiliary wing, and this connection mode has problems such as heavy hinge quality, short service life, complex assembly process etc. Using heterocyclic aramid cloth or kevlar cloth etc. Flexible material replaces the traditional hard alloy hinge as the connecting material of unmanned aerial vehicle wing, which can reduce overall weight, simplify assembly process, improve wing service life, reduce production cost and expand application range.

[0003] The unmanned aerial vehicle wing is disassembled into multiple parts for synchronous production, and then the required parts are integrated for whole wing production, which can realize rapid and large-scale production of wings with different structures according to different use requirements, effectively improve production efficiency and reduce production cost. The quality of independently produced parts is controllable, and the forming quality of whole wing can be improved. UTILITY MODEL CONTENTS

[0004] The utility model provides a kind of unmanned aerial vehicle wing structure with flexible connection to solve above-mentioned problems.

[0005] The utility model aims at providing a kind of unmanned aerial vehicle wing structure with flexible connection, including wing flexible connection structure, wing root connecting piece, aileron, aileron connecting rod;

[0006] The wing flexible connection structure includes main wing upper skin, main wing lower skin, flap, flexible connecting piece;

[0007] The main wing upper skin is connected with the flap by the flexible connecting piece;One end of the main wing upper skin and one end of the main wing lower skin are butted by the wing root connecting piece to form the main wing;The aileron is sleeved on the other end of the main wing upper skin and the main wing lower skin, and the aileron is connected with the wing root connecting piece by the aileron connecting rod;The unmanned aerial vehicle body is connected with the wing root connecting piece by bolts;

[0008] The main wing is provided with container cavity, and the container cavity is used for storing unmanned aerial vehicle fuel or battery.

[0009] Preferably, the wing root side of the main wing upper skin is further provided with an upper skin lip; the front side of the upper skin lip is provided with an upper inner convex front edge, and the rear side of the upper skin lip is provided with an upper inner convex rear edge.

[0010] The wing root side of the main wing lower skin is also provided with a lower skin lip edge; the front side of the lower skin lip edge is provided with a lower inner convex front edge, and the rear side of the lower skin lip edge is provided with a lower inner convex rear edge;

[0011] The upper inner convex front edge and the lower inner convex front edge are connected to form an inner convex front edge; the upper inner convex rear edge and the lower inner convex rear edge are connected to form an inner convex rear edge; the inner convex front edge and the inner convex rear edge are in the same horizontal plane.

[0012] Preferably, the wing root connecting piece comprises a main connecting piece and a secondary connecting piece;

[0013] The body of the main connecting piece is provided with two wing connecting rod holes, and the main connecting piece is provided with a screw rod; the secondary connecting piece is connected with the main connecting piece through the screw rod; the main connecting piece and the secondary connecting piece are both fish-shaped components; the upper end face and the lower end face of the main connecting piece and the secondary connecting piece are respectively attached to the inner wall of the main wing; the front end of the main connecting piece is provided with a front engagement notch, and the front engagement notch engages the inner convex front edge; one side of the secondary connecting piece is provided with a rear engagement notch, and the rear engagement notch engages the inner convex rear edge.

[0014] Preferably, the upper end of the main wing upper skin is upwardly raised, the lower end of the main wing lower skin is downwardly raised, and the curvature of the main wing lower skin is smaller than the curvature of the main wing upper skin.

[0015] Preferably, the winglet is a shuttle-shaped plate; the winglet is provided with a skin sleeve joint groove, and the skin sleeve joint groove is provided with a connecting rod through hole; one end of the main wing upper skin and one end of the main wing lower skin are sleeved in the skin sleeve joint groove; the winglet connecting rod is sleeved in the connecting rod through hole; and the end of the winglet connecting rod is fixedly connected with the winglet connecting rod hole through a nut.

[0016] Preferably, the main wing upper skin, the main wing lower skin and the flap are all made of carbon fiber material; and the flexible connecting piece is made of Kevlar cloth.

[0017] Compared with the prior art, the unmanned aerial vehicle wing structure provided by the present application can achieve the following beneficial effects:

[0018] The unmanned aerial vehicle wing forming technology of the present application can realize the flexible connection of the main wing and the auxiliary wing, improve the service life of the wing, reduce the production cost, and expand the working range of the unmanned aerial vehicle; meanwhile, the internal parts of the wing are produced through modular production, the forming process of each part is simple and the quality is controllable, the types and quantities of the parts can be flexibly adjusted, different combinations of the internal parts of the wing can be made according to actual needs, and the disadvantages of uncontrollable internal quality and inability to quickly respond to different production demands in the integral forming process are avoided. BRIEF DESCRIPTION OF DRAWINGS

[0019] Figure 1 is a whole schematic view of the unmanned aerial vehicle wing structure with flexible connection of the utility model;

[0020] Figure 2 is a cross section schematic view of the unmanned aerial vehicle wing structure with flexible connection of the utility model;

[0021] Figure 3 is an upper adhering flexible connection schematic view of the unmanned aerial vehicle wing structure with flexible connection of the utility model;

[0022] Figure 4 is a sandwich adhering flexible connection schematic view of the unmanned aerial vehicle wing structure with flexible connection of the utility model;

[0023] Figure 5 is a structure bearing view of the unmanned aerial vehicle wing structure with flexible connection of the utility model;

[0024] Figure 6 is an upper skin structure schematic view of the unmanned aerial vehicle wing structure with flexible connection of the utility model;

[0025] Figure 7 is an upper skin local structure schematic view of the unmanned aerial vehicle wing structure with flexible connection of the utility model;

[0026] Figure 8 is a lower skin structure schematic view of the unmanned aerial vehicle wing structure with flexible connection of the utility model;

[0027] Figure 9 is a wing root connecting piece schematic view of the unmanned aerial vehicle wing structure with flexible connection of the utility model;

[0028] Figure 10 is a wing root connecting piece connection state schematic view of the unmanned aerial vehicle wing structure with flexible connection of the utility model.

[0029] Reference signs:

[0030] 1, main wing;

[0031] 11, main wing upper skin; 111, main wing clamping groove; 112, upper skin front edge opening; 113, upper skin rear edge opening; 114, upper skin lip edge; 1141, upper inner convex front edge; 1142, upper inner convex rear edge; 115, upper servo slot; 12, main wing lower skin; 122, lower skin front edge opening; 123, lower skin rear edge opening; 124, lower skin lip edge; 1241, lower inner convex front edge; 1242, lower inner convex rear edge; 125, lower servo slot;

[0032] 2, flap;

[0033] 211, flap clamping groove;

[0034] 3, flexible connecting piece;

[0035] 4, wing root connecting piece;

[0036] 41, main connecting piece; 411, front snap groove; 412, winglet connecting rod hole; 413, fuselage connecting threaded hole; 414, sub connecting rod; 415, first nut; 42, sub connecting piece; 422, rear snap groove;

[0037] 5, winglet;

[0038] 51, skin sleeve groove;

[0039] 6, winglet connecting rod. DETAILED DESCRIPTION

[0040] Hereinafter, embodiments of the present application will be described with reference to the accompanying drawings. In the following description, the same modules are denoted by the same reference numerals. In the case of the same reference numerals, their names and functions are also the same. Therefore, detailed descriptions thereof will not be repeated.

[0041] In order to make the purpose, technical scheme and advantages of the present application more clear, the present application will be further described in detail below with reference to the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are only used to explain the present application and do not constitute a limitation on the present application.

[0042] Embodiment 1

[0043] Referring to Figures 1 to 4 The present embodiment provides a wing flexible connecting structure, which comprises: a main wing 1, a flap 2, and a flexible connecting piece 3.

[0044] The main wing 1 comprises: a main wing upper skin 11 and a main wing lower skin 12.

[0045] The main wing upper skin 11, the main wing lower skin 12 and the flap 2 are all made of carbon fiber material.

[0046] The flap side of the main wing upper skin 11 is connected with the flap 2 through the flexible connecting piece 3.

[0047] The flexible connecting piece 3 is made of Kevlar cloth, and the flexible connecting piece 3 (Kevlar cloth) is a kind of aromatic polyamide fiber.

[0048] Embodiment 2

[0049] Referring to Figure 2 , Figure 3As shown, the embodiment provides a flexible connection method of the wing, the flap side of the upper skin 11 of the main wing is connected with the flap 2 through the flexible connection piece 3 according to the description of the embodiment 1;

[0050] When the upper skin 11 of the main wing and the flap 2 are preliminarily formed by carbon fiber, the two sides of the flexible connection piece 3 (Kevlar cloth) are connected with the upper surface of the upper skin 11 of the main wing and the upper surface of the flap 2 respectively through adhesive, and then the outer surfaces of the upper skin 11 of the main wing and the flap 2 are respectively coated; after the coating is cured, the connection between the flap 2 and the upper skin 11 of the main wing has a certain elasticity, and the connection seam between the upper skin 11 of the main wing and the flap 2 is reduced.

[0051] Embodiment 3

[0052] Referring to Figure 2 、 Figure 4 As shown, the embodiment provides another flexible connection method of the wing, the connection of the upper skin 11 of the main wing, the flap 2 and the flexible connection piece 3 according to the description of the embodiment 1 can also adopt the following method:

[0053] The flap side of the upper skin 11 of the main wing is provided with a main wing clamping groove 111, and the side opposite to the main wing 1 of the flap 2 is provided with a flap clamping groove 211;

[0054] When the upper skin 11 of the main wing and the flap 2 are preliminarily formed by carbon fiber, one side of the flexible connection piece 3 (Kevlar cloth) is fixed in the main wing clamping groove 111, and the other side of the flexible connection piece 3 (Kevlar cloth) is fixed in the flap clamping groove 211; after the two ends of the flexible connection piece 3 are fixed, the outer surfaces of the upper skin 11 of the main wing and the flap 2 are then coated respectively; after the coating is cured, the connection seam between the upper skin 11 of the main wing and the flap 2 is reduced, and the flap 2 and the upper skin 11 of the main wing are connected through the flexible connection piece 3.

[0055] Embodiment 4

[0056] Referring to Figures 1 to 10 As shown, the embodiment provides a flexible connection unmanned aerial vehicle wing structure, which comprises: a wing flexible connection structure, a wing root connecting piece, a winglet 5, and a winglet connecting rod 6;

[0057] The wing flexible connection structure is the wing flexible connection structure prepared in the embodiment 2 or the embodiment 3, and comprises: a main wing 1, a flap 2, and a flexible connection piece 3;

[0058] The main wing 1 comprises: an upper skin 11 of the main wing, and a lower skin 12 of the main wing;

[0059] The main wing upper skin 11 is made of carbon fiber material, and the upper end of the main wing upper skin 11 is upwardly raised; the two sides of the lower end of the main wing upper skin 11 are respectively provided with an upper skin front edge 112 and an upper skin rear edge 113; and on the wing root side of the main wing upper skin 11, between the upper skin front edge 112 and the upper skin rear edge 113, an upper skin lip 114 is further arranged;

[0060] The front side of the upper skin lip 114 is provided with an upper inner convex front edge 1141, and the rear side of the upper skin lip 114 is provided with an upper inner convex rear edge 1142;

[0061] The upper inner convex front edge 1141 and the upper inner convex rear edge 1142 are both semicircular arcs;

[0062] The two ends of the main wing upper skin 11 on the flap side are both provided with an upper steering machine groove 115.

[0063] The main wing lower skin 12 is made of carbon fiber material, and the lower end of the main wing lower skin 12 is downwardly raised;

[0064] The curvature of the raised end of the main wing lower skin 12 is smaller than the curvature of the raised end of the main wing upper skin 11;

[0065] The two sides of the upper end of the main wing lower skin 12 are respectively provided with a lower skin front edge 122 and a lower skin rear edge 123; and on the wing root side of the main wing lower skin 12, between the lower skin front edge 122 and the lower skin rear edge 123, a lower skin lip 124 is further arranged;

[0066] The front side of the lower skin lip 124 is provided with a lower inner convex front edge 1241, and the rear side of the lower skin lip 124 is provided with a lower inner convex rear edge 1242;

[0067] The upper inner convex front edge 1141 can be connected with the lower inner convex front edge 1241, and the two are combined to form a semicircular inner convex front edge; the upper inner convex rear edge 1142 can be connected with the lower inner convex rear edge 1242, and the two are combined to form a semicircular inner convex rear edge; and the inner convex front edge and the inner convex rear edge are on the same horizontal plane.

[0068] The two ends of the main wing lower skin 12 on the flap side are both provided with a lower steering machine groove 125;

[0069] The upper steering machine groove 115 and the lower steering machine groove 125 correspond to each other, and the upper steering machine groove 115 and the lower steering machine groove 125 form a flap steering machine cavity, in which a flap tilting steering machine or other equipment for driving the flap to flip can be installed.

[0070] The wing root connecting piece 4 comprises a main connecting piece 41 and a secondary connecting piece 42;

[0071] The main connecting piece 41 and the auxiliary connecting piece 42 are both fish-shaped members, the front end of the main connecting piece 41 is a front shuttle-shaped part which can be attached to the front end of the inner wall of the upper wing skin 11 and the main wing lower skin 12, and the rear end of the auxiliary connecting piece 42 is a rear shuttle-shaped part which can be attached to the rear end of the inner wall of the upper wing skin 11 and the main wing lower skin 12.

[0072] The front end of the main connecting piece 41 is provided with a front engagement notch 411, the body of the main connecting piece 41 is provided with two winglet connecting rod holes 412, and a plurality of fuselage connecting threaded holes 413 are further provided beside the winglet connecting rod holes 412; the tail end of the main connecting piece 41 is provided with two auxiliary piece connecting rods 414.

[0073] The two auxiliary piece connecting rods 414 are the same in structure, the rod body of the auxiliary piece connecting rod 414 is a light axis shaft rod, and the end part of the auxiliary piece connecting rod 414 is a threaded rod, the diameter of the threaded rod part is larger than that of the light axis shaft rod part.

[0074] One side of the auxiliary connecting piece 42 is provided with two shaft rod through holes, the positions of the two shaft rod through holes correspond to the two auxiliary piece connecting rods 414; the two auxiliary piece connecting rods 414 can be respectively sleeved in the two shaft rod through holes and locked and fixed in position through the first nut 415.

[0075] The other side of the auxiliary connecting piece 42 is provided with a rear engagement notch 422.

[0076] After the main connecting piece 41 and the auxiliary connecting piece 42 are threadedly locked and fixed, the front engagement notch 411 and the rear engagement notch 422 are in the same horizontal plane.

[0077] The winglet 5 is a shuttle-shaped plate or a plate-shaped member provided with a circular arc on the upper and lower sides, and the winglet 5 is provided with a skin sleeving groove 51; the skin sleeving groove 51 is provided with a connecting rod through hole.

[0078] The winglet connecting rod 6 is provided with two, and the two winglet connecting rods 6 are the same in structure; one end of the winglet connecting rod 6 is provided with a top cap, and the other end of the winglet connecting rod 6 is provided with a threaded rod.

[0079] One end of the main wing upper skin 11 and one end of the main wing lower skin 12 are butted and spliced, the other end of the main wing upper skin 11 and the other end of the main wing lower skin 12 are sleeved in the skin sleeving groove 51; the front engagement notch 411 engages the inner convex front edge; the rear engagement notch 422 engages the inner convex rear edge; the two winglet connecting rods 6 are respectively sleeved in the connecting rod through holes of the winglet 5; the other ends of the two winglet connecting rods 6 are respectively threaded out from the two winglet connecting rod holes 412, and then are fixedly connected with the winglet connecting rod 6 through the second nut;

[0080] The fuselage of the unmanned aerial vehicle is threadedly locked and fixed with the fuselage connecting threaded holes 413 on the main connecting piece 41 through bolts;

[0081] The main wing 1 can further be provided with a container cavity which stores fuel or batteries of the unmanned aerial vehicle.

[0082] Embodiment 5

[0083] The embodiment provides a forming method of a UAV wing structure with a flexible connection, and the carbon fiber composite material of a main wing and a flap is connected by using a flexible connection material, and the forming method comprises the following steps:

[0084] S1. According to the shape of the main wing 1 and the flap 2 to be produced, the locking die structure parts of the main wing 1 and the flap 2 are respectively made;

[0085] When the locking structure internal die part is made, the sheet-shaped die material is weighed according to the design weight, is placed in the cavity of the forming mold, and each part of the mold is positioned by using a stop and a positioning pin; the mold is placed on the flat plate of the press, the temperature of the press is set to 90 DEG C, the pressure is set to 0.2-0.4 MPa, the holding time is set to 30-60 min, and the die part is taken out after curing.

[0086] S2. The cavity internal carbon fiber framework is made of prepreg; the core mold of the framework is assembled, each part of the core mold is positioned by using a stop and a positioning pin; the prepreg is laid on the core mold, and vacuum prepressing is performed 1-3 times according to the thickness of the prepreg; after curing, the vacuum auxiliary material is removed, and the wing internal carbon fiber framework is taken out.

[0087] S3. The main wing upper skin 11 is made of prepreg and flexible connection material;

[0088] The manufacturing method specifically comprises the following steps: half-thickness skin prepreg is laid on the main wing and the flap position of the mold respectively, and a layer of flexible connection material is laid above the half-thickness skin prepreg; then the remaining skin prepreg is laid above the flexible connection material, and vacuum prepressing is performed; after curing, the vacuum auxiliary material is removed, and the wing internal carbon fiber framework is taken out;

[0089] S4. The main wing lower skin 12 and the flap 2 skin are made of prepreg;

[0090] The manufacturing method specifically comprises the following steps: the skin prepreg is laid on the main wing and the flap position of the mold respectively, and vacuum prepressing is performed 1-3 times according to the thickness of the prepreg; after curing, the vacuum auxiliary material is removed, and the wing internal carbon fiber framework is taken out;

[0091] S5. The parts are placed into the integral forming mold, the joint part of the main wing upper skin 11 and the main wing lower skin 12 is pasted with the body adhesive film, and the mold is cured and formed by using the press;

[0092] The manufacturing method specifically comprises the following steps: the parts in steps S1 to S4 are placed into the integral forming mold, the integral mold is assembled and placed into the press for curing and pressing, and the mold is disassembled to take out the product after curing.

[0093] Further, the parts in steps S1, S2, S3 and S4 can be produced simultaneously, and the production processes of the parts are independent of each other; when assembling the skeleton core mold, the types and quantities of the mold blocks can be adjusted according to needs to achieve the purpose of making different skeletons;

[0094] Further, the forming sequence in step S3 can be adjusted, i.e., the upper skins of the main wing and the auxiliary wing are formed first, and then the soft connecting material is post-cured; that is, the overall upper skin is composed of the upper skin of the main wing, the upper skin of the auxiliary wing and the soft connecting material.

[0095] Further, the parts produced in steps S1 and S2 can be supplemented or deleted according to actual needs during the pre-production preparation or the production process.

[0096] Further, in step S5, the whole wing mold can be changed to quickly change the wing shape.

[0097] Further, in step S5, foaming foam or PMI foam can be selectively filled into the wing according to different load conditions to reduce the wing deflection and improve the structural stability.

[0098] It should be understood that the various forms of the flow shown above can be used to reorder, add or delete steps. For example, the steps recorded in the present disclosure can be executed in parallel, sequentially or in different orders, as long as the desired results of the technical solutions of the present disclosure can be achieved, and the present text does not limit this.

[0099] The above specific embodiments do not constitute a limitation on the scope of protection of the present disclosure. Those skilled in the art should understand that various modifications, combinations, sub-combinations and substitutions can be made according to design requirements and other factors. Any modification, equivalent substitution and improvement within the spirit and principles of the present disclosure should be included in the scope of protection of the present disclosure.

Claims

1. An unmanned aerial vehicle wing structure having a flexible connection, characterized by: The wing flexible connection structure, wing root connecting piece, winglet, winglet connecting rod are included. The wing flexible connection structure includes main wing upper skin, main wing lower skin, flap, flexible connecting piece. The main wing upper skin and the flap are connected through the flexible connecting piece; one end of the main wing upper skin and one end of the main wing lower skin are butted and spliced through the wing root connecting piece to form the main wing; the winglet is sleeved on the other end of the main wing upper skin and the main wing lower skin, and the winglet is connected with the wing root connecting piece through the winglet connecting rod; the unmanned aerial vehicle body is connected with the wing root connecting piece through bolts. The main wing is internally provided with a container cavity for storing fuel or batteries of the unmanned aerial vehicle.

2. The UAV wing structure with flexible connection of claim 1, wherein: The wing root side of the main wing upper skin is further provided with an upper skin lip along; the front side of the upper skin lip along is provided with an upper inner convex front along, and the rear side of the upper skin lip along is provided with an upper inner convex rear along. The wing root side of the main wing lower skin is further provided with a lower skin lip along; the front side of the lower skin lip along is provided with a lower inner convex front along, and the rear side of the lower skin lip along is provided with a lower inner convex rear along. The upper inner convex front along and the lower inner convex front along are butted to form an inner convex front along. The upper inner convex rear along and the lower inner convex rear along are butted to form an inner convex rear along; the inner convex front along and the inner convex rear along are in the same horizontal plane.

3. The UAV wing structure with flexible connection of claim 2, wherein: The wing root connecting piece includes a main connecting piece and a secondary connecting piece. The body of the main connecting piece is provided with two winglet connecting rod holes, and the main connecting piece is provided with a screw rod; the secondary connecting piece is connected with the main connecting piece through the screw rod; the main connecting piece and the secondary connecting piece are both fish-shaped components; the upper end face and the lower end face of the main connecting piece and the secondary connecting piece are respectively attached to the inner wall of the main wing; the front end of the main connecting piece is provided with a front occlusion slot, and the front occlusion slot occludes the inner convex front along; one side of the secondary connecting piece is provided with a rear occlusion slot, and the rear occlusion slot occludes the inner convex rear along.

4. The UAV wing structure with flexible connection of claim 3, wherein: The upper end of the main wing upper skin is upwardly raised, and the lower end of the main wing lower skin is downwardly raised; the curvature of the main wing lower skin is smaller than the curvature of the upper end of the main wing upper skin.

5. The UAV wing structure with flexible connection of claim 4, wherein: The winglet is a shuttle-shaped plate; the winglet is provided with a skin sleeve groove, and the skin sleeve groove is provided with a connecting rod through hole; one end of the main wing upper skin and one end of the main wing lower skin are sleeved in the skin sleeve groove; the winglet connecting rod is sleeved in the connecting rod through hole; the end of the winglet connecting rod is fixedly connected with the winglet connecting rod hole through a nut.

6. The UAV wing structure with flexible connection of claim 5, wherein: The main wing upper skin, the main wing lower skin and the flap are all made of carbon fiber material; the flexible connecting piece is made of Kevlar cloth.