An engineering hoisting heavy load unmanned aerial vehicle force transmission structure and unmanned aerial vehicle

Abstract

This utility model discloses a force transmission structure for lifting heavy-duty drones and the drone itself, including a rotor assembly and a fuselage frame. The rotor assembly includes a rotor plate and rotors at both ends. The fuselage frame includes a top plate, a frame body, a central column, multiple side columns, and multiple diagonal braces. The top plate is detachably connected to the upper part of the frame body. The central column is located at the center of the frame body and connects the top plate and the bottom of the frame body. Multiple side columns are located on the sides of the frame body and are symmetrically arranged. One end of each diagonal brace is connected to the bottom end of a side column extending from the frame body, and the other end converges and connects to the center of the bottom of the frame body. The top of the fuselage frame is connected to the rotor plate. A lifting ring is provided at the bottom of the fuselage frame to hang the object being lifted. This force transmission structure for lifting heavy-duty drones and the drone itself can efficiently transfer rotor lift to the lifting point. The structure is lightweight, rigid, and has a clear force transmission path, improving the drone's lifting capacity and flight stability.

Description

Technical Field

[0001] This utility model relates to the field of aviation technology, specifically a force transmission structure for heavy-duty unmanned aerial vehicles (UAVs) used for engineering hoisting and the UAV itself. Background Technology

[0002] Engineering hoisting drones are a new type of low-altitude aircraft. Using drones for engineering hoisting offers advantages such as advanced technology, high construction efficiency, and good economic benefits. Heavy-duty engineering hoisting drones with strong hoisting capabilities are widely used in geological exploration for drilling rig ascents, and in the construction of power grids and communication towers.

[0003] In addition to load transfer and shape maintenance, existing engineering hoisting drones must possess sufficient strength, rigidity, and reliability to ensure flight and construction safety. Simultaneously, they must maximize structural efficiency and reduce weight to save fuel, improve hoisting capacity, and enhance economic benefits.

[0004] Therefore, this application proposes a force transmission structure for heavy-duty unmanned aerial vehicles (UAVs) used in engineering hoisting, and a UAV using this force transmission structure, in order to achieve the above objectives. Utility Model Content

[0005] This utility model addresses the above-mentioned technical problems by providing a force transmission structure and drone for heavy-duty engineering hoisting. It can efficiently transmit rotor lift to the hoisting point, and the structure is lightweight, has high rigidity, and a clear force transmission path, thereby improving the hoisting capacity and flight stability of the drone. It is suitable for heavy-duty engineering hoisting scenarios.

[0006] To achieve the above objectives, the technical solution of this utility model is as follows:

[0007] A force transmission structure for heavy-duty unmanned aerial vehicles (UAVs) used for engineering hoisting includes a rotor assembly and a fuselage frame;

[0008] The rotor assembly includes a rotor plate frame and rotors disposed at both ends thereon;

[0009] The fuselage frame includes a top plate, a frame body, a central column, multiple side columns, and multiple diagonal braces. The top plate is detachably connected to the upper part of the frame body. The central column is located at the center of the frame body and connects the top plate and the bottom of the frame body. The multiple side columns are located on the sides of the frame body and are symmetrically arranged about the central column. One end of each diagonal brace is connected to the bottom end of a side column, and the other end converges and connects to the center of the bottom of the frame body.

[0010] The top of the fuselage frame is connected to the rotor plate frame; a lifting ring is provided at the bottom center of the fuselage frame to hang objects.

[0011] The lift generated by the rotor of the heavy-duty UAV's load-transfer structure is transmitted to the fuselage frame via the rotor plate frame. The fuselage frame is equipped with a central column and multiple side columns, which transmit the lift to the lower part of the fuselage frame. Multiple diagonal braces are also installed to rigidly connect the lower end of the side columns to the bottom of the fuselage frame, thereby transmitting the lift to the bottom center of the fuselage frame.

[0012] The bottom of the fuselage frame forms an umbrella-shaped structure through multiple diagonal braces, which can be considered a space truss system. A portion of the weight of the hoisted object is transferred via the diagonal braces to the lower ends of the side columns, and then to the fuselage frame. The other portion of the weight is simultaneously transferred to the top plate frame through the central column.

[0013] Ultimately, lift and gravity are balanced on the fuselage frame, particularly through the diagonal struts, side pillars, and central pillar. The core function of the umbrella-shaped structure is to efficiently distribute the gravity concentrated at the central point to multiple support points on the fuselage frame, and then combine it with the lift from the fuselage frame to form a stable and balanced mechanical system; this allows the rotor lift and the weight of the load applied to the lifting rings to converge and overlap.

[0014] Through rational mechanical design, maximum load-bearing capacity was achieved using the lightest possible structural materials. The diagonal braces, side columns, and bottom structure of the fuselage frame form an equivalent triangular stabilizing structure, enhancing the overall rigidity of the fuselage frame.

[0015] Therefore, the force transmission structure for hoisting heavy-load UAVs in this project has the characteristics of small weight, high structural efficiency, and high overall strength and rigidity, ensuring flight stability and construction safety.

[0016] A further optimized design incorporates a polyhedral frame structure formed by interconnected connecting rods. Using connecting rods to form the polyhedral frame structure results in lightweight and high-strength materials for the rods, significantly reducing the overall weight of the frame.

[0017] To further optimize the design, a side column is installed beneath each rotor. This side column ensures that the rotor lift is transmitted to the lifting ring via the shortest path, improving structural efficiency.

[0018] A further optimized solution includes a top mounting pad, several first straight rods, several second straight rods, and several annular plates.

[0019] The top pad is located at the center of the top plate frame. Several annular plates are arranged concentrically with the top pad. Several first straight rods are distributed in a spoke-like manner and connected to the top pad or annular plates. Several second straight rods are sequentially connected between two first straight rods.

[0020] In a further optimized design, the upper part of the top plate and the main frame body are each equipped with several locking devices to secure the rotor plate. The connection method of the locking devices facilitates assembly and disassembly.

[0021] In a further optimized design, the bottom of the main frame body is provided with a bottom welding pad and several bottom straight rods;

[0022] The bottom pad is located at the center, the bottom of the central column is connected to the bottom pad, and one end of each of the multiple diagonal braces is connected to the bottom pad.

[0023] Several bottom straight rods form several triangular structures with the bottom center of the frame body as the vertex.

[0024] The triangular structure is a geometrically stable shape, which ensures the stability of the structure and enhances the strength and rigidity of the main frame.

[0025] In a further optimized design, rollers are installed at the bottom of the side columns. These rollers allow for easy and convenient movement of the force-transmitting structure and the drone on the ground.

[0026] A further optimized design incorporates a side column consisting of an integrally connected side elongated plate and a side square tube. This structure helps ensure the strength, stability, and rigidity of the side column.

[0027] In a further optimized design, the central column includes an upper flange at the top and a lower flange at the bottom, which are connected by a column rod; the upper flange is connected to the top plate frame, and the lower flange is connected to the bottom of the frame body.

[0028] The lower end of the lower flange is provided with a lifting ring flange, and the lifting ring flange is provided with the lifting ring.

[0029] In a further optimized design, the main frame body is equipped with several detachable railings on its sides. These detachable railings facilitate the maintenance and replacement of components within the main frame body.

[0030] In a further optimized design, the rotor assembly consists of a fixed rotor and a folding rotor. When not in operation, the folding rotor rises and rotates via its rotor plate, overlapping the fixed rotor vertically. This overlapping arrangement of the folding and fixed rotors facilitates overall transportation and storage, saving space.

[0031] A drone, comprising the force transmission structure of a heavy-duty drone for engineering hoisting as described above.

[0032] Compared with existing technologies, the force transmission structure and the drone of this utility model for heavy-duty engineering hoisting have the following technical advantages:

[0033] 1. High structural rigidity and good flight stability: The diagonal brace, together with the central column and side columns, forms a spatial triangular stable structure, which greatly enhances the overall rigidity and deformation resistance of the fuselage frame, ensuring smooth and safe flight during heavy-load lifting.

[0034] 2. Lightweight and highly efficient structure: The force transmission structure works on the principle of truss, with a clear force transmission path. The main components bear axial tension and compression, achieving an extremely high weight-to-strength ratio, effectively reducing the weight of the UAV and improving its payload capacity and endurance.

[0035] 3. Clear force transmission path, safe and reliable: The rotor lift and the weight of the hoisted object converge at the bottom center through a clear path (rotor plate frame → fuselage frame → central column / side column → diagonal brace), resulting in a balanced distribution of internal forces and high structural efficiency.

[0036] 4. Strong overall stability and strong anti-interference ability: The formed umbrella-shaped space truss system can effectively resist crosswind loads from different directions and the torque generated by the swing of the hoisted object, enhancing the adaptability and maneuverability of the UAV in complex engineering environments. Attached Figure Description

[0037] Figure 1 This is a perspective view of a specific embodiment of the force transmission structure for lifting heavy-duty UAVs according to this utility model;

[0038] Figure 2 yes Figure 1 Top view;

[0039] Figure 3 yes Figure 1 Exploded view of the main components;

[0040] Figure 4 yes Figure 1 Exploded view of the main components of the mid-fuselage frame;

[0041] Figure 5 yes Figure 1 A perspective view showing the connection between the fixed rotor and the fuselage frame;

[0042] Figure 6 yes Figure 1 Bottom view of the mid-fuselage frame;

[0043] Figure 7 yes Figure 1 A three-dimensional view of the bottom structure of the mid-fuselage frame;

[0044] Figure 8 yes Figure 4 A three-dimensional view of the central pillar;

[0045] Figure 9 yes Figure 8 A stereoscopic view from another perspective;

[0046] Figure 10 yes Figure 1 A schematic diagram of the stress structure.

[0047] In the diagram: rotor assembly 1, rotor plate frame 11, fixed rotor 12, folding rotor 13, fuselage frame 2, locking component 21, top plate frame 22, top plate frame fixing hole 221, first straight rod 222, second straight rod 223, circular ring plate 224, top welding pad 23, frame body 24, connecting rod 241, bottom straight rod 242, railing 243, center column 25, column straight rod 251, upper flange 252, lower flange 253, lifting ring flange 254, lifting ring 255, shoulder bolt 256, side column 26, side long plate 261, side square tube 262, roller 27, diagonal brace 28, bottom welding pad 29. Detailed Implementation

[0048] The present invention will now be described in further detail with reference to the embodiments shown in the accompanying drawings.

[0049] like Figures 1 to 10 As shown, this utility model provides a specific embodiment of the force transmission structure for heavy-duty unmanned aerial vehicles used in engineering hoisting.

[0050] like Figure 1 and Figure 2 As shown, the force transmission structure of this embodiment for heavy-duty unmanned aerial vehicle (UAV) lifting includes a rotor assembly 1 and a fuselage frame 2. The rotor assembly 1 includes a rotor plate frame 11 and rotors disposed at both ends thereon. The rotor assembly 1 is divided into a fixed rotor 12 and a folding rotor 13. In the non-working state, the folding rotor 13 rises and rotates through its rotor plate frame 11, overlapping the fixed rotor 12 vertically. Specifically, there are two folding rotors 13 and two fixed rotors 12. The overlapping arrangement of the folding rotors 13 and the fixed rotors 12 facilitates overall transportation and storage, saving space.

[0051] like Figure 4 and Figure 5 As shown, the fuselage frame 2 includes a top plate frame 22, a frame body 24, a central column 25, multiple side columns 26, and multiple diagonal braces 28. The top plate frame 22 is detachably connected to the upper part of the frame body 24. The central column 25 is located at the center of the frame body 24 and connects the top plate frame 22 and the bottom of the frame body 24. Multiple side columns 26 are located on the sides of the frame body 24 and are symmetrically arranged about the central column 25. One end of each diagonal brace 28 is connected to the bottom end of one side column 26 extending out of the frame body 24, and the other end converges and connects to the center of the bottom of the frame body 24. Preferably, there are four side columns 26, and the number of diagonal braces 28 is the same as the number of side columns 26.

[0052] like Figure 1 and Figure 7 As shown, the top of the fuselage frame 2 is connected to the rotor plate frame 11; a lifting ring 255 is provided at the bottom center of the fuselage frame 2 to hang objects.

[0053] like Figure 10 As shown, the lift generated by the rotor of the heavy-duty UAV's force transmission structure is transmitted to the fuselage frame 2 via the rotor plate frame 11. The fuselage frame 2 is provided with a central column 25 and multiple side columns 26, which transmit the lift to the lower part of the fuselage frame 2. Multiple diagonal braces 28 are also provided to rigidly connect the lower end of the side columns 26 and the bottom of the fuselage frame 2, thereby transmitting the lift to the bottom center of the fuselage frame 2.

[0054] The bottom of the fuselage frame 2 forms an umbrella-shaped structure through multiple diagonal braces 28, which can be regarded as a space truss system. Part of the weight of the hoisted object is transferred to the lower end of the side columns 26 through the diagonal braces 28, and then to the fuselage frame 2. The other part of the weight is directly transferred to the top plate frame 22 through the central column 25.

[0055] Ultimately, lift and gravity are balanced on the fuselage frame 2, particularly through the diagonal struts 28, side pillars 26, and central pillar 25. The core function of the umbrella-shaped structure is to efficiently distribute the gravity concentrated at the center point to multiple support points on the fuselage frame 2, and then combine it with the lift from the frame body 24 to form a stable and balanced mechanical system; allowing the rotor lift and the weight of the hoisted object applied to the lifting ring 255 to converge and overlap.

[0056] Through rational mechanical design, maximum load-bearing capacity was achieved using the lightest possible rod materials. The diagonal brace 28, side columns 26, and the bottom structure of the fuselage frame 2 form an equivalent triangular stable structure, enhancing the overall rigidity of the fuselage frame 2.

[0057] Therefore, the force transmission structure for hoisting heavy-load UAVs in this project has the characteristics of small weight, high structural efficiency, and high overall strength and rigidity, ensuring flight stability and construction safety.

[0058] like Figure 4 As shown, the main frame 24 is a polyhedral frame structure formed by interconnecting several connecting rods 241. Using connecting rods 241 to form a polyhedral frame structure results in lightweight and high-strength materials for the rods, significantly reducing the overall weight of the main frame 24. Preferably, this polyhedral frame structure is a regular octahedral frame structure.

[0059] like Figure 5 As shown, each rotor is provided with a side support column 26. The side support column 26 under the rotor ensures that the rotor lift is transmitted to the lifting ring 255 along the shortest path, thus improving structural efficiency.

[0060] like Figure 4As shown, the top plate frame 22 includes a top pad 23, a plurality of first straight rods 222, a plurality of second straight rods 223, and a plurality of annular plates 224. The top pad 23 is located at the center of the top plate frame 22. The plurality of annular plates 224 are arranged concentrically with the top pad 23. The plurality of first straight rods 222 are distributed in a spoke-like pattern and connect to the top pad 23 or the annular plates 224. The plurality of second straight rods 223 are sequentially connected between two first straight rods 222. Preferably, there are six first straight rods 222, arranged with two long and four short rods spaced apart; there are eight second straight rods 223; and there are two annular plates 224.

[0061] like Figure 4 As shown, the end of the first straight rod 222 is also provided with eight top plate frame fixing holes 221 for connecting and fixing the top plate frame 22 and the frame body 24. The top plate frame 22 is connected and fixed to the frame body 24 with bolts, which has the advantage of facilitating disassembly. After the top plate frame 22 is completely removed from the fuselage frame 2, equipment installed inside the fuselage, such as aircraft engines, can be easily hoisted.

[0062] like Figure 2 and Figure 3 As shown, the top plate frame 22 and the upper part of the frame body 24 are respectively provided with a number of locking members 21 to lock the rotor plate frame 11. Preferably, the number of locking members 21 is sixteen. The connection method of the locking members 21 is easy to assemble and disassemble. The rotor plate frame 11 is connected to the fuselage frame 2 through the locking members 21, and the lift generated by the rotor blades is transmitted to the fuselage frame 2 by the locking members 21.

[0063] like Figure 6 As shown, the bottom of the frame body 24 is provided with a bottom pad 29 and several bottom straight rods 242; the bottom pad 29 is located at the center position, the bottom of the central column 25 is connected to the bottom pad 29, and one end of the four diagonal braces 28 is connected to the bottom pad 29. Preferably, the connection method is welding; the several bottom straight rods 242 form several triangular structures with the bottom center of the frame body 24 as the vertex.

[0064] The triangular structure is a geometrically stable shape, which ensures the stability of the structure and enhances the strength and rigidity of the main frame 24.

[0065] like Figure 3 and Figure 5 As shown, a roller 27 is provided at the bottom of the side column 26. The roller 27 can easily move the force transmission structure and the drone on the ground.

[0066] like Figure 7 As shown, the side column 26 includes an integrally connected side elongated plate 261 and a side square tube 262. This structure helps to ensure the strength, stability, and rigidity of the side column 26.

[0067] like Figure 8 and Figure 9 As shown, the central column 25 includes an upper flange 252 at the upper end and a lower flange 253 at the lower end, which are connected by a column rod 251. The upper flange 252 is connected to the top plate frame 22, and the lower flange 253 is connected to the bottom of the frame body 24. The lower end of the lower flange 253 is provided with a lifting ring flange 254, which is connected to the lower flange 253 by four shoulder bolts 256. The lifting ring flange 254 is provided with a lifting ring 255.

[0068] like Figure 4 As shown, the main frame 24 has four detachable railings 243 on its sides, each railing 243 having a cross-shaped structure. The detachable railings 243 facilitate the maintenance and replacement of components inside the main frame 24.

[0069] This utility model also discloses a drone, including the above-mentioned engineering hoisting heavy-duty drone force transmission structure.

[0070] The project's lifting structure for heavy-duty drones and the drones themselves can efficiently transfer rotor lift to the lifting point. The structure is lightweight, has high rigidity, a clear force transmission path, and high efficiency, which improves the drone's lifting capacity and flight stability, making it suitable for heavy-duty engineering lifting scenarios.

[0071] In summary, as described in the specification and figures, this utility model has been manufactured into actual samples and subjected to multiple use tests. The test results demonstrate that this utility model achieves its intended purpose, and its practicality is beyond doubt. The embodiments described above are merely for illustrative purposes and are not intended to limit the scope of this utility model. Any equivalent embodiments made by those with common knowledge in the relevant technical field, utilizing the technical content disclosed in this utility model, without departing from the scope of the technical features and similar features disclosed in this utility model, are all within the protection scope of this utility model.

Claims

1. A force transmission structure for lifting heavy-duty unmanned aerial vehicles (UAVs) in engineering, characterized in that: Including the fuselage frame (2); The fuselage frame (2) includes a top plate frame (22), a frame body (24), a central column (25), multiple side columns (26), and multiple diagonal braces (28); the top plate frame (22) is detachably connected to the upper part of the frame body (24); the central column (25) is located at the center of the frame body (24) and connects the top plate frame (22) and the bottom of the frame body (24); multiple side columns (26) are located on the sides of the frame body (24) and are symmetrically arranged about the central column (25); one end of each diagonal brace (28) is connected to the bottom end of a side column (26), and the other end is gathered and connected to the bottom center of the frame body (24).

2. The force transmission structure for heavy-duty unmanned aerial vehicles (UAVs) used in engineering hoisting according to claim 1, characterized in that, It also includes a rotor assembly (1); the rotor assembly (1) includes a rotor plate frame (11) and rotors at both ends thereon; the top of the fuselage frame (2) is connected to the rotor plate frame (11); a lifting ring (255) is provided at the bottom center of the fuselage frame (2) to hang and lift objects.

3. The force transmission structure for heavy-duty UAVs used in engineering hoisting according to claim 1, characterized in that, The main frame (24) is a polyhedral frame structure formed by connecting several connecting rods (241).

4. The force transmission structure for heavy-duty UAVs used in engineering hoisting according to claim 2, characterized in that, Each rotor is provided with a side column (26) below it.

5. The force transmission structure for heavy-duty UAVs used in engineering hoisting according to claim 1, characterized in that, The top plate frame (22) includes a top pad (23), a plurality of first straight rods (222), a plurality of second straight rods (223), and a plurality of annular plates (224). The top pad (23) is located at the center of the top plate frame (22). Several annular plates (224) are arranged concentrically with the top pad (23). Several first straight rods (222) are distributed in a spoke-like manner and connected to the top pad (23) or annular plates (224). Several second straight rods (223) are connected sequentially between two first straight rods (222).

6. The force transmission structure for heavy-duty UAVs used in engineering hoisting according to claim 2, characterized in that, The upper part of the top plate frame (22) and the frame body (24) are respectively provided with a number of locking parts (21) to lock the rotor plate frame (11).

7. The force transmission structure for heavy-duty UAVs used in engineering hoisting according to claim 1, characterized in that, The bottom of the frame body (24) is provided with a bottom welding pad (29) and several bottom straight rods (242). The bottom pad (29) is located at the center, the bottom of the central column (25) is connected to the bottom pad (29), and one end of the plurality of diagonal braces (28) is connected to the bottom pad (29). Several bottom straight bars (242) form several triangular structures with the bottom center of the frame body (24) as the vertex.

8. The force transmission structure for heavy-duty UAVs used in engineering hoisting according to claim 1, characterized in that, The bottom end of the side column (26) is provided with a roller (27).

9. The force transmission structure for heavy-duty unmanned aerial vehicles (UAVs) used in engineering hoisting according to claim 1, characterized in that, The side column (26) includes a side long plate (261) and a side square tube (262) that are integrated together.

10. The force transmission structure for heavy-duty unmanned aerial vehicles (UAVs) used in engineering hoisting according to claim 1, characterized in that, The central column (25) includes an upper flange (252) at the upper end and a lower flange (253) at the lower end, which are connected by a column rod (251); the upper flange (252) is connected to the top plate frame (22), and the lower flange (253) is connected to the bottom of the frame body (24); The lower end of the lower flange (253) is provided with a lifting ring flange (254), and the lifting ring flange (254) is provided with the lifting ring (255).

11. The force transmission structure for heavy-duty unmanned aerial vehicles (UAVs) used in engineering hoisting according to claim 1, characterized in that, The main frame (24) has several detachable railings (243) on its sides.

12. An unmanned aerial vehicle (UAV), characterized in that: The system includes the force transmission structure for heavy-duty unmanned aerial vehicles (UAVs) used in engineering hoisting, as described in any one of claims 1 to 11.

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