Anti-cracking wing structure for folding wing unmanned aerial vehicle

Abstract

The utility model discloses an anti-cracking wing structure for a folding wing unmanned aerial vehicle, and relates to the technical field of unmanned aerial vehicles. The anti-cracking wing structure for the folding wing unmanned aerial vehicle comprises a connecting wing A, one side of the connecting wing A is concave, a connecting wing B is arranged on one side of the connecting wing A, the bottom of one side of the connecting wing A is hinged to the bottom of one side of the connecting wing B, and a wing is divided into the connecting wing A and the connecting wing B. According to the anti-cracking wing structure for the folding wing unmanned aerial vehicle, the wing is divided into the connecting wing A and the connecting wing B, through hinged installation of the connecting wing A and the connecting wing B, the wing can be folded, the extension area of the wing is reduced, and the wing body or the unmanned aerial vehicle can be conveniently transported; the connecting wing A and the connecting wing B are conveniently connected, the wings are conveniently and rapidly assembled, the wings are made of carbon fibers, the connecting frames are arranged in the wings, the strength of the wings can be improved, and the phenomena of cracking, damage and the like are reduced.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles, in particular to an anti-cracking wing structure for a folding-wing unmanned aerial vehicle. Background Art

[0002] Chinese patent CN106986000A discloses a UAV wing structure, which belongs to the field of UAVs and is used for UAVs, wherein the wing mounting seat is connected to the UAV body by fastening bolts, an auxiliary plate is installed on the wing body, and the auxiliary plate is connected to the adjustment motor in the UAV body through an adjustment rod, and the front end of the arc-shaped lower plate body in the wing body is an arc-shaped protrusion, which is located in the internal space formed by the arc-shaped front baffle and an airway is left between the arc-shaped protrusion and the inner wall of the arc-shaped front baffle; a gas delivery pipeline is also installed between the arc-shaped front baffle and the arc-shaped lower plate body, one end of the gas delivery pipeline is connected to the vortex fan located in the UAV body, and an outlet is opened on the side of the gas delivery pipeline relative to the airway, which can enable the row-wing UAV to obtain better gas kinetic energy during flight, increase the flight stability of the UAV and the stability of the wing.

[0003] However, the above-mentioned wing is relatively large in size, and it is difficult to transport the wing body or the aircraft. Utility Model Content

[0004] The purpose of the utility model is to provide a crack-resistant wing structure for a folding-wing UAV to solve the problems and defects raised by the above-mentioned background technology.

[0005] To achieve the above-mentioned purpose, the utility model provides the following technical solutions: an anti-cracking wing structure for a folding-wing UAV, comprising a connecting wing A, one side of the connecting wing A is concavely arranged, one side of the connecting wing A is provided with a connecting wing B, the bottom of one side of the connecting wing A is hingedly installed with the bottom of one side of the connecting wing B, the wing is divided into a connecting wing A and a connecting wing B, the wing can be folded, the extension area of ​​the wing is reduced, and the wing body or the UAV can be conveniently transported, and also includes that a connecting structure is arranged between the connecting wing A and the connecting wing B, and the connecting structure is used to fix the connecting wing A and the connecting wing B.

[0006] Preferably, the connecting wing A comprises a fiber layer and a protective layer, the protective layer is sprayed on the outer wall of the fiber layer, the fiber layer is carbon fiber, and the protective layer is nano coating.

[0007] Preferably, the connecting wing B and the connecting wing A are made of the same material.

[0008] Preferably, the connection structure includes a connection block, a threaded frame, a pin, a guide rod, a threaded rod, and a mounting block. The connection block is fixedly installed on the outer wall of one side of the connecting wing B. The pin is fixedly installed on one side of the threaded frame. The guide rods are fixedly installed on the front and rear sides of the connecting wing A. The mounting block is fixedly installed at one end of the threaded rod. The threaded rod and the mounting block are respectively rotatably installed on the front and rear sides of the connecting wing A. The threaded frame is threadedly installed on the outer wall of the threaded rod. The threaded frame is slidably installed on the outer wall of the guide rod. A connection port is provided on one side of the connecting wing A. The connection block passes through the connection port and extends to the inner side of the connecting wing A. The connection block is provided with a jack, and the pin is inserted into the jack. An internal hexagonal groove is provided on the rear side of the mounting block, which is convenient for connecting the connecting wing A and the connecting wing B and facilitating the rapid assembly of the wing.

[0009] Preferably, connection frames are fixedly installed on the inner walls of both the connecting wing A and the connecting wing B. The connection frames are arranged in a cross shape. The wing is made of carbon fiber, and the internal connection frames can improve the strength of the wing and reduce phenomena such as cracking and damage.

[0010] Preferably, a sealing strip is provided between the connecting wing A and the connecting wing B. The sealing strip is located outside the four connection ports, strengthening the sealing between the connecting wing A and the connecting wing B and preventing rainwater from entering the connecting wing A in rainy and snowy weather.

[0011] Compared with the prior art, the beneficial effects of the present utility model are as follows:

[0012] In the anti-cracking wing structure for the folding-wing unmanned aerial vehicle, the wing is divided into the connecting wing A and the connecting wing B. Through the hinged installation of the connecting wing A and the connecting wing B, the wing can be folded, reducing the extended area of the wing, facilitating the transportation of the wing body or the unmanned aerial vehicle. Moreover, through the coordinated use of the connection structure, it is also convenient to connect the connecting wing A and the connecting wing B, facilitating the rapid assembly of the wing. Additionally, the wing body is made of carbon fiber, and connection frames are provided inside it, which can improve the strength of the wing and reduce phenomena such as cracking and damage. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] The following further illustrates the present utility model with reference to the drawings and embodiments:

[0014] Figure 1 is a schematic structural diagram of the present utility model;

[0015] Figure 2 is a schematic structural diagram of the connecting wing A of the present utility model;

[0016] Figure 3 is a schematic structural diagram of the connecting wing B of the present utility model;

[0017] Figure 4 is a schematic structural diagram of the connecting wing A of the present utility model;

[0018] Figure 5 It is a cross-sectional view of the connecting wing B of the present utility model;

[0019] Figure 6 It is a cross-sectional view of the fiber layer of the present utility model.

[0020] Reference numerals in the drawings: 1, connecting wing A; 101, fiber layer; 102, protective layer; 2, connecting wing B; 3, connecting block; 4, threaded frame; 5, plug pin; 6, guide rod; 7, threaded rod; 8, mounting block; 9, connecting frame. Specific embodiments

[0021] This part will describe in detail the specific embodiments of the present utility model. The preferred embodiments of the present utility model are shown in the drawings. The function of the drawings is to supplement the description of the text part of the specification, enabling people to intuitively and vividly understand each technical feature and the overall technical solution of the present utility model, but it should not be construed as a limitation on the protection scope of the present utility model.

[0022] Please refer to Figure 1-6 , the present utility model provides a technical solution: an anti-cracking wing structure for a folding-wing unmanned aerial vehicle, including a connecting wing A1. One side of the connecting wing A1 is concave. A connecting wing B2 is arranged on one side of the connecting wing A1. The bottom of one side of the connecting wing A1 is hingedly installed with the bottom of one side of the connecting wing B2. The wing is divided into the connecting wing A1 and the connecting wing B2, and the wing can be folded to reduce the extension area of the wing, which can facilitate the transportation of the wing body or the unmanned aerial vehicle. Further, a connecting structure is arranged between the connecting wing A1 and the connecting wing B2, and the connecting structure is used to fixedly connect the connecting wing A1 and the connecting wing B2.

[0023] The connecting wing A1 includes a fiber layer 101 and a protective layer 102. The protective layer 102 is sprayed on the outer wall of the fiber layer 101. The fiber layer 101 is made of carbon fiber, and the protective layer 102 is made of nano-coating.

[0024] The connecting wing B2 and the connecting wing A1 are made of the same material.

[0025] The connecting structure includes a connecting block 3, a threaded frame 4, a pin 5, a guide rod 6, a threaded rod 7 and a mounting block 8. The connecting block 3 is fixedly installed on one outer wall of the connecting wing B2. The pin 5 is fixedly installed on one side of the threaded frame 4. The guide rod 6 is fixedly installed on the front and rear sides of the connecting wing A1. The mounting block 8 is fixedly installed at one end of the threaded rod 7. The threaded rod 7 and the mounting block 8 are respectively rotatably installed on the front and rear sides of the connecting wing A1. The threaded frame 4 is threadedly installed on the outer wall of the threaded rod 7. The threaded frame 4 is slidably installed on the outer wall of the guide rod 6. A connecting port is provided on one side of the connecting wing A1. The connecting block 3 penetrates through the connecting port and extends to the inner side of the connecting wing A1. The connecting block 3 is provided with a jack, and the pin 5 is inserted into the jack. An internal hexagonal groove is provided on the rear side of the mounting block 8. Hold an internal hexagonal wrench and insert the internal hexagonal wrench into the internal hexagonal groove of the mounting block 8. By manually twisting the internal hexagonal wrench, the hexagonal wrench drives the mounting block 8 and the threaded rod 7 to rotate. The rotation of the threaded rod 7 drives the threaded frame 4 and the pin 5 to move backward, so that the pin 5 is removed from the jack of the connecting block 3, and thus the connecting wing B2 can be manually rotated to fold the connecting wing B2 at the bottom of the connecting wing A1, which is convenient for transporting the wing and also convenient for connecting the connecting wing A1 and the connecting wing B2, facilitating the rapid assembly of the wing.

[0026] Connecting frames 9 are fixedly installed on the inner walls of both the connecting wing A1 and the connecting wing B2. The connecting frames 9 are arranged in a cross shape. The wing is made of carbon fiber, and the internal arrangement of the connecting frames 9 can improve the strength of the wing and reduce phenomena such as cracking and damage.

[0027] A sealing strip is provided between the connecting wing A1 and the connecting wing B2. The sealing strip is located outside the four groups of connecting ports to strengthen the sealing between the connecting wing A1 and the connecting wing B2 and prevent rainwater from entering the connecting wing A1 in rainy and snowy weather.

[0028] Working principle: Hold an internal hexagonal wrench and insert the internal hexagonal wrench into the internal hexagonal groove of the mounting block 8. By manually twisting the internal hexagonal wrench, the hexagonal wrench drives the mounting block 8 and the threaded rod 7 to rotate. The rotation of the threaded rod 7 drives the threaded frame 4 and the pin 5 to move backward, so that the pin 5 is removed from the jack of the connecting block 3, and thus the connecting wing B2 can be manually rotated to fold the connecting wing B2 at the bottom of the connecting wing A1, which is convenient for transporting the wing.

[0029] The above has described the embodiments of the present invention in detail with reference to the accompanying drawings. However, the present invention is not limited to the above embodiments. Within the knowledge scope of those of ordinary skill in the art in the technical field, various changes can be made without departing from the purpose of the present invention.

Claims

1. A crack-resistant wing structure for a folding-wing UAV, comprising a connecting wing A (1), one side of the connecting wing A (1) is concavely arranged, one side of the connecting wing A (1) is provided with a connecting wing B (2), one side bottom of the connecting wing A (1) is hingedly installed with one side bottom of the connecting wing B (2), characterized in that: Also includes: A connecting structure is provided between the connecting wing A (1) and the connecting wing B (2), and the connecting structure is used to fix the connecting wing A (1) and the connecting wing B (2).

2. The anti-cracking wing structure for a folding-wing UAV according to claim 1, characterized in that: The connecting wing A (1) comprises a fiber layer (101) and a protective layer (102), wherein the protective layer (102) is sprayed on the outer wall of the fiber layer (101), the fiber layer (101) is carbon fiber, and the protective layer (102) is nano coating.

3. The anti-cracking wing structure for a folding-wing UAV according to claim 2, characterized in that: The connecting wing B (2) and the connecting wing A (1) are made of the same material.

4. The anti-cracking wing structure for a folding-wing UAV according to claim 3, characterized in that: The connection structure comprises a connection block (3), a threaded frame (4), a latch (5), a guide rod (6), a threaded rod (7) and a mounting block (8); the connection block (3) is fixedly mounted on an outer wall of one side of the connection wing B (2); the latch (5) is fixedly mounted on one side of the threaded frame (4); the guide rod (6) is fixedly mounted on the front and rear sides of the connection wing A (1); the mounting block (8) is fixedly mounted on one end of the threaded rod (7); the threaded rod (7) and the mounting block (8) are rotatably mounted on the front and rear sides of the connection wing A (1) respectively; the threaded frame (4) is threadedly mounted on the outer wall of the threaded rod (7); the threaded frame (4) is slidably mounted on the outer wall of the guide rod (6); a connection port is provided on one side of the connection wing A (1); the connection block (3) penetrates the connection port and extends to the inner side of the connection wing A (1); the connection block (3) is provided with an insertion hole; the latch (5) is inserted into the insertion hole; and a hexagonal socket is provided on the rear side of the mounting block (8).

5. The anti-cracking wing structure for a folding-wing UAV according to claim 4, characterized in that: The inner wall of the connecting wing A (1) and the inner wall of the connecting wing B (2) are both fixedly mounted with connecting frames (9), and the connecting frames (9) are cross-arranged.

6. The anti-cracking wing structure for a folding-wing UAV according to claim 5, characterized in that: A sealing strip is provided between the connecting wing A (1) and the connecting wing B (2), and the sealing strip is located outside the four groups of connecting ports.

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