A quick sway damping stabilizing flexible carrier for multi-copter drones

Abstract

This utility model discloses a rapid anti-sway and stabilization flexible carrier for multi-rotor drones, including a connecting unit. The connecting unit further includes a flexible connecting tube, a clamp assembly, a guide vane, and a locking body docking unit. The flexible connecting tube is multi-sectioned, and the docking portions of adjacent flexible connecting tubes are respectively equipped with an inner ring and a concave plate. This rapid anti-sway and stabilization flexible carrier for multi-rotor drones uses guide vanes to form a stabilizing surface (similar to the tail fin of a missile or arrow). The strong airflow generated by the multi-rotor drone's propellers passes through the tail fin, quickly stabilizing its attitude and achieving the purpose of anti-sway and stabilization.

Description

Technical Field

[0001] This utility model relates to the field of anti-sway in unmanned aerial vehicles (UAVs), specifically a flexible vehicle for rapid anti-sway stabilization and enhancement of multi-rotor UAVs. Background Technology

[0002] With the advancement of smart grid construction, drone technology is being used more and more widely in the operation and maintenance of power transmission lines. Power workers often use drones to carry equipment such as tower climbing fall protection devices and grounding wires, effectively improving work efficiency and safety. Currently, most drone mounting devices on the market use multi-section circular carbon fiber tubes, carbon fiber sheets, or ropes to construct flexible carriers. When carrying heavy objects, the inertia and gravity of the heavy objects can suppress the swaying caused by wind and drone movement to a certain extent.

[0003] However, once the dismantling phase begins and the flexible vehicle loses its traction, the swaying amplitude increases significantly due to strong winds and the drone's own attitude adjustments. This violent swaying makes it difficult to accurately align the flexible vehicle with the target position when dismantling equipment such as the tower fall arrestor and grounding wire. The pilot needs to repeatedly adjust the drone's attitude and make multiple attempts, which not only greatly reduces operational efficiency but also increases operational risks and can even lead to drone crashes.

[0004] To address these challenges, this invention proposes a rapid anti-sway and stabilization flexible vehicle for multi-rotor UAVs, aiming to overcome the aforementioned technical difficulties and ensure efficient and safe dismantling operations. Utility Model Content

[0005] The purpose of this invention is to provide a fast-acting anti-sway and stabilizing flexible vehicle for multi-rotor unmanned aerial vehicles (UAVs) to solve the problems mentioned in the background art.

[0006] To achieve the above objectives, this utility model provides the following technical solution:

[0007] A further embodiment of this invention is a rapid anti-sway and stabilization flexible vehicle for multi-rotor UAVs, comprising a connecting unit, which further includes a flexible connecting tube, a clamp assembly, a wind guide wing, and a locking body docking unit. The flexible connecting tube is multi-sectioned, with an inner ring and a concave plate respectively installed at the docking points of adjacent flexible connecting tubes. A lock nut is threadedly connected to the outer wall of the inner ring, and one end of the lock nut penetrates the outer wall of the inner ring and is threadedly fixed to the opening on the outer wall of the concave plate. An installation sleeve is installed on the outer wall of the end of the flexible connecting tube, and a wind guide wing is fixedly connected to the outer wall of the installation sleeve.

[0008] As a further embodiment of this utility model: the lock body docking unit includes a telescopic mechanism connected to the flexible connecting tube at the end. A left locking box and a right locking box are respectively installed on the left and right sides of the telescopic mechanism. The left locking box and the right locking box are snap-fitted together and fixed with screws.

[0009] As a further embodiment of this utility model: a first guide plate is installed on the side of the right locking box away from the left locking box, a second guide plate is installed on the side of the left locking box away from the right locking box, and a side sealing plate and a side second sealing plate are respectively installed at the front and rear parts between the first guide plate and the second guide plate.

[0010] As a further embodiment of this utility model: the clamp assembly includes a crossbar, a connecting rod is fixedly connected between the crossbar and the flexible connecting tube at the top, and a fixing block is fixedly connected to both ends of the crossbar, and a hinge member is hingedly installed on the outer side of the fixing block.

[0011] As a further embodiment of this utility model: one end of the hinge member is fixedly connected to the clamp, the front end of the clamp is hinged to the clamp, and the rear end of the clamp is provided with a groove.

[0012] As a further embodiment of this utility model: a hook is installed at the front end of the second clamp, and a pressure handle is installed at the other end of the hook. A hinge second is rotatably connected to the outer wall of the pressure handle, and the hinge second is fixed to the groove hook.

[0013] Compared with the prior art, the beneficial effects of this utility model are:

[0014] This application primarily utilizes a stabilizer (similar to the tail fin of a missile or arrow) created by installing a guide fin at the end of a flexible vehicle. The strong airflow generated by the multi-rotor drone's propellers quickly stabilizes its attitude by passing over the tail fin, achieving the purpose of eliminating swaying and enhancing stability. Actual tests showed that without the guide fin's bottom docking under strong winds and the drone's own swaying, it would continuously sway back and forth, making it difficult to aim at the target. However, with the guide fin installed, it can stabilize rapidly within 1-2 seconds. Its structure is more optimized and its design is more reasonable.

[0015] In this utility model, the flexible connecting tube installed at the top is fixed by a connecting rod and a crossbar. The crossbar is used to fix the fixing block. At the same time, the hinged part one of the fixing block is used to fix the clamp one. The clamp one, together with the clamp two hinged at the rear, can achieve the clamping and installation of the UAV bearing end. Attached Figure Description

[0016] Figure 1 This is a structural schematic diagram of a flexible vehicle for rapid sway reduction and stabilization of multi-rotor unmanned aerial vehicles.

[0017] Figure 2 This is an exploded view of a flexible vehicle for rapid sway reduction and stabilization of multi-rotor unmanned aerial vehicles.

[0018] Figure 3 This is an assembly drawing of the clamp assembly in a fast anti-sway and stabilization flexible vehicle for multi-rotor UAVs.

[0019] Figure 4 This is an enlarged view of the clamp assembly in a fast anti-sway and stabilization flexible vehicle for multi-rotor UAVs.

[0020] In the diagram: 1. Connecting unit; 2. Flexible connecting pipe; 3. Clamp assembly; 4. Air guide wing; 5. Mounting sleeve; 6. Lock body docking unit; 7. Side sealing plate; 8. Side second sealing plate; 9. First guide plate; 10. Second guide plate; 11. Left locking box; 12. Right locking box; 13. Telescopic mechanism; 14. Inner ring; 15. Concave plate; 16. Lock nut; 17. Clamp 2; 18. Pressure handle; 19. Groove; 20. Hinge 2; 21. Hook; 22. Fixing block; 23. Hinge 1; 24. Connecting rod; 25. Crossbar; 26. Detailed Implementation

[0021] 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.

[0022] Please see Figures 1-4 In this embodiment of the present invention, a flexible carrier for rapid anti-sway and stabilization of a multi-rotor UAV includes a connecting unit 1. The connecting unit 1 further includes a flexible connecting pipe 2, a clamp assembly 3, a wind guide wing 5, and a locking body docking unit 7. The flexible connecting pipe 2 is configured in multiple sections. An inner ring 15 and a concave plate 16 are respectively installed at the docking parts of adjacent flexible connecting pipes 2. A lock nut 17 is threadedly connected to the outer wall of the inner ring 15, and one end of the lock nut 17 passes through the outer wall of the inner ring 15 and is threadedly fixed to the opening part of the outer wall of the concave plate 16. An installation sleeve 6 is installed on the outer wall of the end flexible connecting pipe 2, and the wind guide wing 5 is fixedly connected to the outer wall of the installation sleeve 6.

[0023] The lock body docking unit 7 includes a telescopic mechanism 14 connected to the end flexible connecting tube 2. A left locking box 12 and a right locking box 13 are respectively installed on the left and right sides of the telescopic mechanism 14. The left locking box 12 and the right locking box 13 are snap-fitted together and fixed with screws.

[0024] A first guide plate 10 is installed on the side of the right locking box 13 away from the left locking box 12, and a second guide plate 11 is installed on the side of the left locking box 12 away from the right locking box 13. A side sealing plate 8 and a side second sealing plate 9 are respectively installed at the front and rear positions between the first guide plate 10 and the second guide plate 11.

[0025] The clamp assembly 3 includes a crossbar 26, a connecting rod 25 is fixedly connected between the crossbar 26 and the top flexible connecting pipe 2, and a fixing block 23 is fixedly connected to both ends of the crossbar 26. A hinge member 24 is hingedly installed on the outside of the fixing block 23.

[0026] One end of the hinge 24 is fixedly connected to the clamp 4, the front end of the clamp 4 is hinged to the clamp 18, and the rear end of the clamp 4 is provided with a groove 20.

[0027] The front end of the clamp 218 is equipped with a hook 22, and the other end of the hook 22 is equipped with a pressure handle 19. The outer wall of the pressure handle 19 is rotatably connected to a hinge 21, which is hooked and fixed to the groove 20.

[0028] The working principle of this utility model is as follows:

[0029] In use, multiple sets of flexible connecting pipes 2 are connected together. The inner ring 15 and concave plate 16 installed between two adjacent sets of flexible connecting pipes 2 can be adjusted in angle through the cooperation of lock nut 17.

[0030] The implementation is as follows: The lock nut 17 is threaded through the pre-drilled hole in the inner ring 15 and the concave plate 16 to connect the two adjacent sets of flexible connecting tubes 2. At the same time, the lock nut 17 in the inner ring 15 can rotate up and down, that is, the concave plate 16 rotates up and down.

[0031] The flexible connecting pipe 2 and the mounting sleeve 6 installed at the bottom are fixed, and the mounting sleeve 6 and the wind guide wing 5 are an integral unit;

[0032] Function: The installation of the wind guide wing 5 forms a stabilizing surface similar to the tail fin of a missile or arrow. The strong airflow generated by the propeller of the multi-rotor UAV can quickly stabilize its attitude by passing through the tail fin, thus achieving the purpose of eliminating sway and increasing stability.

[0033] The flexible connecting tube 2 installed at the top is fixed by the connecting rod 25 and the crossbar 26. The crossbar 26 is used to fix the fixing block 23. At the same time, the hinge 24 hinged to the fixing block 23 is used to fix the clamp 4. The clamp 4 and the clamp 18 hinged to the rear part can be used to clamp and install the UAV bearing end.

[0034] Specifically: Lift the handle 19, and drive the second hinge 21 to be hung in the groove 20 at the front of the first clamp 4. Then press down the handle 19 to lock the second clamp 18 and the first clamp 4.

[0035] Although the present invention 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 invention should be included within the protection scope of the present invention.

Claims

1. A rapid anti-sway and stabilization flexible vehicle for multi-rotor unmanned aerial vehicles, comprising a connecting unit (1), characterized in that: The connecting unit (1) also includes a flexible connecting tube (2), a clamp assembly (3), a wind guide (5), and a lock body docking unit (7). The flexible connecting tube (2) is multi-sectioned. An inner ring (15) and a concave plate (16) are respectively installed at the docking parts of adjacent flexible connecting tubes (2). A lock nut (17) is threaded to the outer wall of the inner ring (15), and one end of the lock nut (17) passes through the outer wall of the inner ring (15) and is threaded to the opening part of the outer wall of the concave plate (16). An installation sleeve (6) is installed on the outer wall of the end of the flexible connecting tube (2), and a wind guide (5) is fixedly connected to the outer wall of the installation sleeve (6).

2. The rapid anti-sway and stabilization flexible vehicle for multi-rotor UAVs according to claim 1, characterized in that: The lock body docking unit (7) includes a telescopic mechanism (14) connected to the flexible connecting tube (2) at the end. A left locking box (12) and a right locking box (13) are respectively installed on the left and right sides of the telescopic mechanism (14). The left locking box (12) and the right locking box (13) are snap-fit ​​connected and fixed by screws.

3. A rapid anti-sway and stabilization flexible vehicle for multi-rotor unmanned aerial vehicles according to claim 2, characterized in that: A first guide plate (10) is installed on the side of the right locking box (13) away from the left locking box (12), and a second guide plate (11) is installed on the side of the left locking box (12) away from the right locking box (13). A side sealing plate (8) and a side second sealing plate (9) are respectively installed at the front and rear parts between the first guide plate (10) and the second guide plate (11).

4. A rapid anti-sway and stabilization flexible vehicle for multi-rotor unmanned aerial vehicles according to claim 1, characterized in that: The clamp assembly (3) includes a crossbar (26), and a connecting rod (25) is fixedly connected between the crossbar (26) and the flexible connecting tube (2) at the top. Both ends of the crossbar (26) are fixedly connected to a fixing block (23), and a hinge component (24) is hingedly installed on the outside of the fixing block (23).

5. A rapid anti-sway and stabilization flexible vehicle for multi-rotor unmanned aerial vehicles according to claim 4, characterized in that: One end of the hinge member (24) is fixedly connected to the clamp (4), the front end of the clamp (4) is hinged to the clamp (18), and the rear end of the clamp (4) is provided with a groove (20).

6. A rapid anti-sway and stabilization flexible vehicle for multi-rotor unmanned aerial vehicles according to claim 5, characterized in that: The front end of the clamp (18) is equipped with a hook (22), and the other end of the hook (22) is equipped with a pressure handle (19). The outer wall of the pressure handle (19) is rotatably connected to a hinge (21), and the hinge (21) is hooked and fixed to the groove (20).

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