Modular carbon fiber unmanned aerial vehicle fuselage bay section quick docking structure

Abstract

This utility model relates to the field of unmanned aerial vehicle (UAV) equipment and discloses a modular carbon fiber UAV fuselage section quick-connection structure, including a support plate. A locking block is fixedly connected to the top of the support plate, a fixing block is installed inside the locking block, a spring is fixedly connected inside the fixing block, a pressing post is fixedly connected to one end of the spring, and a locking pin is fixedly connected to the outside of the pressing post. A support rod is fixedly connected to the bottom of the support plate, and a shock-absorbing component is fixedly connected to the outside of the support rod. In this utility model, when replacing the main body plate, pressing the pressing post compresses the spring, causing the locking pin to move laterally and disengage from the locking block's limiting groove, thus releasing the locking block from the locking block and allowing the main body plate to be removed. After replacement, pressing the pressing post aligns the locking pin with the locking block's groove, and releasing the spring pushes the locking pin into the groove, ensuring a tight engagement between the main body plate and the support plate.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) equipment, and in particular to a modular carbon fiber UAV fuselage section quick docking structure. Background Technology

[0002] The modular carbon fiber UAV fuselage section quick-connect structure uses carbon fiber composite material to build the main body of the section. Its high strength and lightweight characteristics ensure structural performance and flight efficiency. The structure is reinforced with embedded metal parts to enhance connection strength, and sealing rings ensure the airtightness of the section. The modular design allows for independent replacement of functional sections such as payload compartment and power compartment, improving the convenience of UAV maintenance and mission adaptability.

[0003] Existing modular carbon fiber UAV fuselage section docking structures mostly use mechanical connectors, bolts or tenon joints to connect the sections. However, such structures have problems such as alignment accuracy relying on manual operation, connectors being easily loosened by vibration, time-consuming disassembly and assembly, and high maintenance and replacement costs. At the same time, the complex connection mechanism increases the weight of the fuselage and manufacturing cost, making it difficult to meet the needs of rapid assembly and modular function switching of UAVs.

[0004] Existing modular carbon fiber UAV fuselage sections lack efficient positioning and guidance mechanisms, resulting in time-consuming alignment during section docking, easy misjudgment of installation direction, and impact on assembly efficiency. Furthermore, the integrated molding design necessitates complete disassembly for maintenance, and the high customization of parts leads to high replacement costs. To address these issues, a rapid docking structure for modular carbon fiber UAV fuselage sections is proposed. Utility Model Content

[0005] To overcome the above shortcomings, this utility model provides a modular carbon fiber UAV fuselage section quick docking structure, which aims to improve the problem of the inability to quickly dock in the prior art.

[0006] To achieve the above objectives, the present invention adopts the following technical solution:

[0007] A modular carbon fiber UAV fuselage section quick docking structure includes a support plate, a locking block fixedly connected to the top of the support plate, a fixing block installed inside the locking block, a spring fixedly connected inside the fixing block, a pressing column fixedly connected to one end of the spring, a locking pin fixedly connected to the outside of the pressing column, a support rod fixedly connected to the bottom of the support plate, and a shock-absorbing component fixedly connected to the outside of the support rod.

[0008] As a further description of the above technical solution:

[0009] The shock absorption assembly includes a limiting block, a telescopic column is rotatably connected inside the limiting block, a second spring is sleeved on the outside of the telescopic column, a limiting frame is fixedly connected to the bottom of the telescopic column, a first rotating rod is rotatably connected to the outside of the support rod, and a second rotating rod is rotatably connected to the outside of the support rod.

[0010] As a further description of the above technical solution:

[0011] A support column is fixedly connected to the bottom of the support plate, a connecting plate is fixedly connected to the bottom of the support column, and a camera is fixedly connected to the bottom of the connecting plate.

[0012] As a further description of the above technical solution:

[0013] A connecting block is fixedly connected to the top of the fixed block, a main plate is fixedly connected to the top of the connecting block, and a propeller is rotatably connected to the top of the main plate.

[0014] As a further description of the above technical solution:

[0015] The other end of the second rotating rod is rotatably connected to the outer wall of the limiting frame, and the other end of the first rotating rod is rotatably connected to the outer wall of the limiting frame;

[0016] As a further description of the above technical solution:

[0017] The outer wall of the pressing column is slidably connected to the inside of the fixing block, and the outer wall of the locking pin is slidably connected to the inside of the fixing block;

[0018] As a further description of the above technical solution:

[0019] The outer wall of the latch contacts the groove of the latch block, and one end of the second spring is fixedly connected to the top of the limiting frame;

[0020] As a further description of the above technical solution:

[0021] The inner part of the limiting frame is rotatably connected to a pulley, and the outer wall of the limiting block is fixedly connected to the outer wall of the support rod.

[0022] This utility model has the following beneficial effects:

[0023] 1. In this utility model, when replacing the main body plate, pressing the pressing column compresses the spring and stores energy, causing the locking pin to move laterally and disengage from the locking block's limiting groove, thereby disengaging the fixing block from the locking block to remove the main body plate. After replacement, pressing the pressing column aligns the locking pin with the locking block's groove. After releasing the spring, the spring releases energy and pushes the locking pin into the groove, ensuring that the main body plate and the support plate are tightly engaged.

[0024] 2. In this utility model, when the UAV lands, the pulley touches the ground first, which drives the limiting frame to squeeze the telescopic column to generate elastic potential energy. The deformation absorbs the impact and achieves shock absorption. At the same time, the limiting frame is squeezed and drives rotating rod one and rotating rod two to rotate, forming a triangular support structure, which enhances the stability of the fuselage when landing. Attached Figure Description

[0025] Figure 1 This is a three-dimensional schematic diagram of the modular carbon fiber UAV fuselage section quick docking structure proposed in this utility model.

[0026] Figure 2 This is a schematic diagram of the main plate of the modular carbon fiber UAV fuselage section quick docking structure proposed in this utility model.

[0027] Figure 3 This is a schematic diagram of the support plate of the modular carbon fiber UAV fuselage section quick docking structure proposed in this utility model.

[0028] Figure 4 for Figure 2 Enlarged view of point A in the middle.

[0029] Legend:

[0030] 1. Support plate; 2. Connecting block; 3. Support rod; 4. Camera; 5. Main body plate; 6. Propeller; 7. Support column; 8. Connecting plate; 9. Locking block; 10. Fixing block; 11. Spring 1; 12. Pressing column; 13. Locking pin; 14. Rotating rod 1; 15. Rotating rod 2; 16. Limiting frame; 17. Telescopic column; 18. Spring 2; 19. Pulley; 20. Limiting block. Detailed Implementation

[0031] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0032] Reference Figure 1 and Figure 3This utility model provides an embodiment of a modular carbon fiber UAV fuselage section quick-connection structure, including a support plate 1. A locking block 9 is fixedly connected to the top of the support plate 1. The locking block 9 is fixed to the top of the support plate 1. A fixing block 10 is installed inside the locking block 9, and the fixing block 10 is locked inside the locking block 9. A spring 11 is fixedly connected inside the fixing block 10, providing elastic restoring force. A pressing post 12 is fixedly connected to one end of the spring 11. The pressing post 12 compresses the spring 11, generating elastic potential energy. The outer wall of the pressing post 12 is slidably connected to the inside of the fixing block 10. The fixing block 10 provides a sliding track for the pressing post 12, constraining its movement direction and ensuring the linear motion accuracy of the pressing post 12. A locking pin 13 is fixedly connected to the outside of the pressing post 12, pressing the pressing post... 12 drives the pin 13 to move, the outer wall of the pin 13 contacts the groove of the block 9, the pin 13 is embedded in the groove of the block 9 to connect, the outer wall of the pin 13 is slidably connected to the inside of the fixing block 10, the fixing block 10 provides sliding support for the pin 13 to ensure that the pin 13 is smoothly inserted into or removed from the groove, the bottom of the support plate 1 is fixedly connected to the support rod 3, the support rod 3 is fixed to the bottom of the support plate 1, the bottom of the support plate 1 is fixedly connected to the support column 7, the bottom of the support column 7 is fixedly connected to the connecting plate 8, the bottom of the connecting plate 8 is fixedly connected to the camera 4, the camera 4 is installed at the bottom of the connecting plate 8 for environmental monitoring and shooting of the drone, the top of the fixing block 10 is fixedly connected to the connecting block 2, the top of the connecting block 2 is fixedly connected to the main plate 5, and the top of the main plate 5 is rotatably connected to the propeller 6;

[0033] Reference Figure 2 and Figure 4A shock-absorbing assembly is fixedly connected to the outside of the support rod 3. The shock-absorbing assembly includes a limiting block 20, the outer wall of which is fixedly connected to the outer wall of the support rod 3. A telescopic column 17 is rotatably connected inside the limiting block 20. The telescopic column 17 rotates within the limiting block 20. A second spring 18 is sleeved on the outside of the telescopic column 17, providing elastic restoring force. When the telescopic column 17 is compressed and contracts, it stores energy. After the pressure is released, it pushes the telescopic column 17 to return to its original position, thus achieving the shock-absorbing function. A limiting frame 16 is fixedly connected to the bottom of the telescopic column 17. A rotating rod 14 and a rotating rod 15 are rotatably connected to the outside of the support rod 3. The other end of the second rotating rod 15 is rotatably connected to the outer wall of the limiting frame 16. One end of the second rotating rod 15 rotates outside the support rod 3, and the other end rotates outside the limiting frame 16 to provide support. The other end of the first rotating rod 14 is rotatably connected to the outer wall of the limiting frame 16. One end of the first rotating rod 14 rotates outside the support rod 3, and the other end rotates outside the limiting frame 16 to provide support. One end of the second spring 18 is fixedly connected to the top of the limiting frame 16. A pulley 19 is rotatably connected inside the limiting frame 16. The pulley 19 serves as a contact component when the UAV lands. By rotating, it reduces friction with the ground and transmits the impact force to the shock absorption component for buffering.

[0034] Working principle: When replacing the main body plate 5, press the pressing column 12. The pressing column 12 compresses the spring 11, generating elastic potential energy. The pressing column 12 drives the locking pin 13 to move laterally, disengaging from the limiting groove of the locking block 9. This causes the fixing block 10 to disengage from the locking block 9, allowing the main body plate 5 to be replaced. After replacement, press the pressing column 12 to align the locking pin 13 with the groove of the locking block 9. After releasing the press, the spring 11 releases its elastic potential energy, pushing the locking pin 13 precisely into the groove, ensuring that the main body plate 5 and the support plate 1 form a tight and stable locking structure. When the drone lands, it will generate shock absorption, and the pulley 19 will be the first to engage. Upon contact with the ground, pulley 19 causes the limiting frame 16 to compress the telescopic column 17. The telescopic column 17 generates elastic potential energy, which absorbs the impact of landing through deformation to achieve shock absorption. At the same time, the limiting frame 16 is compressed, causing rotating rod 2 15 and rotating rod 14 to rotate, forming a triangular support structure to enhance the stability of the fuselage. Support column 7 is fixed to the bottom of support plate 1, connecting plate 8 is fixed to the bottom of support column 7, and camera 4 is fixed to the bottom of connecting plate 8. Camera 4 can perform real-time environmental monitoring and image acquisition. Multiple propellers 6 are fixed to the top of the main plate 5 to provide flight power for the drone.

[0035] Finally, it should be noted that the above description is only a preferred embodiment of the present utility model and is not intended to limit the present utility model. Although the present utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present utility model should be included within the protection scope of the present utility model.

Claims

1. A modular carbon fiber UAV fuselage section quick-connection structure, including a support plate (1), characterized in that: A locking block (9) is fixedly connected to the top of the support plate (1). A fixing block (10) is installed inside the locking block (9). A spring (11) is fixedly connected inside the fixing block (10). A pressing column (12) is fixedly connected to one end of the spring (11). A locking pin (13) is fixedly connected to the outside of the pressing column (12). A support rod (3) is fixedly connected to the bottom of the support plate (1). A shock-absorbing component is fixedly connected to the outside of the support rod (3).

2. The modular carbon fiber UAV fuselage section quick-connection structure according to claim 1, characterized in that: The shock absorption assembly includes a limiting block (20), a telescopic column (17) is rotatably connected inside the limiting block (20), a second spring (18) is sleeved on the outside of the telescopic column (17), a limiting frame (16) is fixedly connected to the bottom of the telescopic column (17), a first rotating rod (14) is rotatably connected to the outside of the support rod (3), and a second rotating rod (15) is rotatably connected to the outside of the support rod (3).

3. The modular carbon fiber UAV fuselage section quick-connection structure according to claim 1, characterized in that: The bottom of the support plate (1) is fixedly connected to a support column (7), the bottom of the support column (7) is fixedly connected to a connecting plate (8), and the bottom of the connecting plate (8) is fixedly connected to a camera (4).

4. The modular carbon fiber UAV fuselage section quick-connection structure according to claim 1, characterized in that: The top of the fixed block (10) is fixedly connected to the connecting block (2), the top of the connecting block (2) is fixedly connected to the main body plate (5), and the top of the main body plate (5) is rotatably connected to the propeller (6).

5. The modular carbon fiber UAV fuselage section quick-connection structure according to claim 2, characterized in that: The other end of the second rotating rod (15) is rotatably connected to the outer wall of the limiting frame (16), and the other end of the first rotating rod (14) is rotatably connected to the outer wall of the limiting frame (16).

6. The modular carbon fiber UAV fuselage section quick-connection structure according to claim 1, characterized in that: The outer wall of the pressing column (12) is slidably connected to the inside of the fixing block (10), and the outer wall of the locking pin (13) is slidably connected to the inside of the fixing block (10).

7. The modular carbon fiber UAV fuselage section quick docking structure according to claim 2, characterized in that: The outer wall of the latch (13) is in contact with the groove of the latch block (9), and one end of the second spring (18) is fixedly connected to the top of the limiting frame (16).

8. The modular carbon fiber UAV fuselage section quick docking structure according to claim 2, characterized in that: The inner part of the limiting frame (16) is rotatably connected to a pulley (19), and the outer wall of the limiting block (20) is fixedly connected to the outer wall of the support rod (3).

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