Novel unmanned aerial vehicle body structure

Abstract

The application relates to a novel unmanned aerial vehicle body structure and belongs to the technical field of unmanned aerial vehicles. The unmanned aerial vehicle body structure comprises a center frame and arms mounted on the center frame. The number of the arms is four. The four arms are detachably fixed on the center frame. The arm comprises an integrally-formed connecting portion, an arm body and a mounting portion. The connecting portion is connected with the center frame. A strip-shaped threading groove is arranged on the bottom surface of the arm body. The strip-shaped threading groove is used for arranging electric wires. The strip-shaped threading groove can increase the profile area of the arm body, thereby increasing the rigid strength of the arm body. The strength effect of replacing carbon fiber composite materials can be achieved. The magnesium alloy production body can be mass-produced by a casting process, thereby greatly reducing the production cost, greatly improving the efficiency and being more environmentally friendly than the carbon fiber unmanned aerial vehicle frame.

Description

Technical Field

[0001] This application relates to the technical field of unmanned aerial vehicles (UAVs), and in particular to a novel UAV airframe structure. Background Technology

[0002] Currently, most drone airframes are made of carbon fiber composite materials, especially the arms. These materials are lightweight and high-strength, with a specific strength and modulus far exceeding that of traditional metals, significantly improving the drone's endurance and payload capacity. They also possess good corrosion resistance and thermal stability, making them suitable for various environments. However, they are more expensive and are commonly used in key components of high-performance drones, such as the fuselage, wings, and rotors.

[0003] In actual production, the molding process of carbon fiber composite materials is relatively complex, which makes it impossible to mass-produce carbon fiber composite materials for the body. At the same time, its renewability is poor and it is not environmentally friendly.

[0004] Therefore, in order to save costs and achieve large-scale production of the body, our company uses magnesium alloy material instead of carbon fiber composite material. Magnesium alloy has the characteristics of being lightweight, high-strength, having good thermal conductivity and electromagnetic shielding ability. However, the strength of magnesium alloy is lower than that of carbon fiber composite material, so structural design improvements are needed. Utility Model Content

[0005] The purpose of this application is to provide a novel unmanned aerial vehicle (UAV) airframe structure to solve the problems mentioned in the background art.

[0006] To achieve the above objectives, this application provides a novel unmanned aerial vehicle (UAV) airframe structure employing the following technical solution:

[0007] A novel unmanned aerial vehicle (UAV) airframe structure includes a central frame and arms mounted on the central frame. The structure is characterized by having four arms, each detachably fixed to the central frame. Each arm includes an integrally formed connecting portion, an arm body, and a mounting portion. The connecting portion is connected to the central frame. A strip-shaped wire-passing groove is provided on the bottom surface of the arm body, and wire-passing holes are provided in the strip-shaped wire-passing groove near the connecting portion and the mounting portion.

[0008] The central frame includes a base plate, a top plate, a fixed plate, and several supporting members. The supporting members are arranged between the base plate and the top plate, and the machine arm is fixed to the base plate via the fixed plate.

[0009] Preferably, in order to make the structure more robust and compact, interlocking notches are provided on the sides of adjacent connecting parts, so that the connecting parts of the four arms can be on the same horizontal plane after splicing.

[0010] Preferably, for ease of maintenance and disassembly, the arm, fixing plate, and base plate are fixed together by studs.

[0011] Preferably, the support member includes several support rods and two head support blocks, the head support blocks being streamlined in shape.

[0012] By adopting the above technical solution, a space can be created between the bottom plate and the top plate by setting support rods and head support blocks, which facilitates the installation of electronic equipment. The streamlined design of the head support blocks can reduce wind resistance.

[0013] Preferably, in order to reduce the weight of the machine body, the bottom plate and the top plate are provided with several hollow holes.

[0014] Preferably, the central frame, arm, support rod, and support block are all made of magnesium alloy.

[0015] By adopting the above technical solutions, magnesium alloys can be produced on a large scale through casting, which can reduce production costs.

[0016] Preferably, the arm body surface is provided with a plurality of through holes, and the plurality of through holes are arranged in a linear manner along the length direction of the arm body.

[0017] By creating linear through holes on the arm body, the outline area of ​​the arm can be increased, thereby enhancing the rigidity and strength of the arm body, so that the arm made of magnesium alloy can also achieve the strength of the arm made of carbon fiber composite material.

[0018] In summary, this application includes at least one of the following beneficial technical effects:

[0019] 1. The new drone body structure features a strip-shaped wire-passing groove on the arm, which allows the wires to be placed inside the groove and then covered with a lightweight cover plate, resulting in a more aesthetically pleasing appearance. At the same time, the strip-shaped wire-passing groove increases the outline area of ​​the arm, thereby increasing the rigidity and strength of the arm, enabling it to achieve the strength effect of replacing carbon fiber composite materials. The magnesium alloy body can be mass-produced using casting technology, which greatly reduces production costs, significantly improves production efficiency, and is more environmentally friendly than carbon fiber drone frames.

[0020] 2. The arm body section of the machine arm is aligned with the base plate and the fixed plate after assembly, which not only meets the strength requirements but also makes it more aesthetically pleasing;

[0021] 3. The machine body structure adopts a detachable design, which facilitates mass production and assembly, and also makes subsequent maintenance easier, thereby reducing the customer's operating costs.

[0022] 4. Discarded magnesium alloy frames can be recycled, which is environmentally friendly. Attached Figure Description

[0023] Figure 1 This is a schematic diagram of the overall structure of an embodiment of this application.

[0024] Figure 2 This is an exploded structural diagram illustrating the central frame in an embodiment of this application.

[0025] Figure 3 This is a schematic diagram illustrating the structure of the robotic arm in the embodiments of this application.

[0026] Figure 4 This is a schematic diagram illustrating the connection relationship between adjacent arms in the embodiments of this application.

[0027] Figure 5 This is a schematic diagram of another embodiment of the robotic arm.

[0028] Explanation of reference numerals in the attached drawings: 1. Center frame; 11. Base plate; 12. Top plate; 13. Fixing plate; 14. Support rod; 15. Support block; 2. Arm; 21. Connecting part; 211. Notch; 22. Arm body; 221. Strip-shaped wire threading groove; 222. Wire threading hole; 223. Through hole; 23. Mounting part. Detailed Implementation

[0029] The following is in conjunction with the appendix Figure 1-5 This application will be described in further detail.

[0030] This application discloses a novel unmanned aerial vehicle (UAV) airframe structure, referring to... Figure 1-4 The system includes a central frame 1 and four machine arms 2 mounted on the central frame 1. The four machine arms 2 are detachably fixed to the central frame 1. Each machine arm 2 includes an integrally formed connecting part 21, an arm body 22, and a mounting part 23. The connecting part 21 is connected to the central frame 1. The bottom surface of the arm body 22 is provided with a strip-shaped wire threading groove 221. The strip-shaped wire threading groove 221 is provided with wire threading holes 222 near the connecting part 21 and the mounting part 23.

[0031] By incorporating the strip-shaped wire-passing groove 221, the wires can be neatly arranged within it and subsequently covered by a cover plate, resulting in a more aesthetically pleasing appearance. Furthermore, the groove 221 increases the profile area of ​​the arm 22, thereby enhancing its rigidity. The profile area of ​​the magnesium alloy refers to the two-dimensional planar projected area of ​​the magnesium alloy component in a specific application. This parameter is crucial in the design and manufacturing process, as it directly relates to material usage, cost, and the performance of the final product. A larger profile area typically signifies higher strength and rigidity.

[0032] The central frame 1 includes a base plate 11, a top plate 12, a fixing plate 13, and several supporting components. The supporting components are arranged between the base plate 11 and the top plate 12. The machine arm 2 is fixed to the base plate 11 via the fixing plate 13. The machine arm 2, the fixing plate 13, and the base plate 11 are fixed together by studs. In order to reduce the weight of the machine body, several hollow holes are opened on the surface of the base plate 11 and the top plate 12.

[0033] Reference Figure 3-4 To make the structure more robust and compact, interlocking notches 211 are provided on the sides of adjacent connecting parts 21, so that the connecting parts 21 of the four arms 2 can be on the same horizontal plane after splicing. (Note: The last part, "reference," appears to be an error and doesn't need a direct translation.) Figure 1 The arm body 22 of the arm 2 is on the same surface as the base plate 11 and the fixing plate 13 after assembly, which not only meets the strength requirements, but also makes it more aesthetically pleasing.

[0034] Reference Figure 1-2 The support includes several support rods 14 and two head support blocks 15, with the head support blocks 15 arranged in a streamlined shape.

[0035] By providing support rods 14 and head support blocks 15, space can be created between the base plate 11 and the top plate 12, which facilitates the installation of electronic equipment. The head support blocks 15 are streamlined, which can reduce wind resistance.

[0036] To facilitate large-scale mass production, the center frame 1, machine arm 2, support rod 14, and support block 15 are all made of magnesium alloy.

[0037] The implementation principle of a novel UAV airframe structure in this application is as follows:

[0038] On the one hand, the body of the machine is made of magnesium alloy. By setting the strip wire-passing groove 221, the wire can be placed in the strip wire-passing groove 221 and then covered by the cover plate, which is more aesthetically pleasing. At the same time, the strip wire-passing groove 221 can increase the outline area of ​​the arm body 22, thereby increasing the rigidity and strength of the arm 2, so that it can achieve the strength effect of replacing carbon fiber composite materials.

[0039] On the other hand, the machine body structure can be realized by casting process, thereby achieving the effect of large-scale mass production and greatly reducing production costs.

[0040] Example 2:

[0041] This application also discloses another embodiment of the arm body 22:

[0042] Reference Figure 5 The surface of the arm body 22 is provided with a plurality of through holes 223, and the plurality of through holes 223 are arranged in a linear manner along the length direction of the arm body 22.

[0043] The through hole 223 can increase the contour area of ​​the arm body 22, thereby increasing the rigidity of the arm 2, so that the arm 2 made of magnesium alloy can also achieve the strength of the arm made of carbon fiber composite material.

[0044] The above are all preferred embodiments of this application, and are not intended to limit the scope of protection of this application. Therefore, all equivalent changes made in accordance with the structure, shape and principle of this application should be covered within the scope of protection of this application.

Claims

1. A novel unmanned aerial vehicle body structure, comprising a central frame (1) and a machine arm (2) mounted on the central frame (1), characterized in that: The number of the machine arms (2) is four, four machine arms (2) are detachably fixed on the center frame (1), the machine arm (2) comprises an integral connecting part (21), an arm body (22) and a mounting part (23), the connecting part (21) is connected with the center frame (1), the bottom surface of the arm body (22) is provided with a strip-shaped threading groove (221), the strip-shaped threading groove (221) is provided with a threading hole (222) near the connecting part (21) and the mounting part (23). The center frame (1) comprises a bottom plate (11), a top plate (12), a fixed plate (13) and a plurality of supporting pieces, a plurality of supporting pieces are arranged between the bottom plate (11) and the top plate (12), the machine arm (2) is fixed on the bottom plate (11) through the fixed plate (13).

2. The novel drone airframe structure according to claim 1, wherein: The side of the adjacent connecting part (21) is provided with a notch (211) which is engaged with each other, the connecting parts (21) of the four machine arms (2) can be in the same horizontal plane after splicing.

3. The new drone airframe structure according to claim 1, characterized in that: The machine arm (2), the fixed plate (13) and the bottom plate (11) are fixed by studs.

4. The new drone airframe structure according to claim 1, characterized in that: The supporting piece comprises a plurality of supporting rods (14) and two head supporting blocks (15), the head supporting block (15) is arranged in a streamline shape.

5. The novel drone airframe structure according to claim 1, wherein: The bottom plate (11) and the top plate (12) are provided with a plurality of hollow holes on the surface.

6. The novel drone airframe structure according to claim 1, wherein: The center frame (1), the machine arm (2), the supporting rod (14) and the supporting block (15) are made of magnesium alloy.

7. The novel drone airframe structure according to claim 1, wherein: The surface of the arm body (22) is uniformly provided with a plurality of through holes (223), a plurality of through holes (223) are arranged in a linear shape along the length direction of the arm body (22).

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