A wing fixing structure of a patrol unmanned aerial vehicle

Abstract

The utility model relates to a kind of wing fixing structure of inspection unmanned aerial vehicle, belong to unmanned aerial vehicle wing fixing technology, including fixed seat fixed on machine body and connecting seat fixed on wing, connecting seat is detachably connected between docking portion and fixed seat, docking portion is composed of clockwork drive assembly and threaded rod by interconnection, clockwork drive assembly is fixed on connecting seat, threaded rod is threadedly connected between fixed seat, threaded rod is provided with the ratchet lock that can be manually released, a plurality of guide rods are equipped on connecting seat, control shell is arranged on guide rod, driving wheel located in control shell is fixed on threaded rod, both sides of control shell are left with opening, the outer side of driving wheel is exposed outside through opening, the utility model realizes wing installation automatic locking by clockwork drive assembly cooperation ratchet lock, manually release locking when disassembling can be quickly tripped, greatly improve dismounting efficiency.

Description

Technical Field

[0001] This utility model relates to the field of drone wing fixing technology, and in particular to a wing fixing structure for an inspection drone. Background Technology

[0002] Currently, inspection drones often require wing disassembly for transport and storage to save space. Traditional wing fixing structures mostly use bolts or clips for connection, and the disassembly and assembly process requires tools and manual operation of multiple locking points, which is cumbersome and time-consuming. Especially in field operation environments, frequent disassembly and assembly can easily lead to thread wear or loosening of connectors, affecting structural reliability. While some structures adopting quick-release designs simplify operation, they lack effective automatic locking mechanisms and pose a risk of loosening in flight vibration environments. Therefore, this application is made. Utility Model Content

[0003] To overcome the technical defects of the existing technology, this utility model provides a wing fixing structure for an inspection drone, which has the technical effect of stable connection and high assembly and disassembly efficiency.

[0004] The technical solution adopted by this utility model is as follows: it includes a fixed seat fixed on the fuselage and a connecting seat fixed on the wing. The connecting seat is detachably connected to the fixed seat through a docking part. The docking part consists of a spring drive assembly and a threaded rod connected to each other. The spring drive assembly is fixed on the connecting seat. The threaded rod is threadedly connected to the fixed seat. The threaded rod is provided with a manually release ratchet lock.

[0005] Preferably, the connecting seat is provided with several guide rods, and a control housing is provided on the guide rods. An actuating wheel located inside the control housing is fixed on the threaded rod. During the installation of the wing, the guide rods are used for the preliminary calibration and positioning of each structure. The operator can hold the connecting seat and bring it close to the fixed seat, and then accurately insert the guide rod into the guide hole to complete the preliminary positioning work.

[0006] Preferably, the control housing has openings on both sides, and the outer side of the actuating wheel is exposed through the opening. In use, the threaded rod can be screwed into the fixing seat by the actuating wheel to achieve fixation.

[0007] Preferably, the outer wall of the ratchet lock is fixed to the guide rod for automatic locking and manual release of the threaded rod. In use, when the threaded rod rotates under the action of the spring drive assembly, the ratchet lock will automatically activate to firmly lock the threaded rod in the current position, preventing the threaded rod from reversing. After the threaded rod is connected to the fixed seat, it can also effectively prevent the threaded rod from loosening or retracting due to external factors such as vibration and airflow impact, further ensuring the stability of the wing connection.

[0008] Preferably, the fixing base has at least two side walls with a plurality of guide holes corresponding to the guide rod for positioning and guiding after the guide rod is inserted. In use, after the guide rod is inserted into the guide hole, it can slide smoothly along a predetermined direction, which facilitates preliminary positioning. The inside of the guide hole is finely polished, and the surface is smooth and flawless, which reduces the frictional resistance between the guide rod and the guide hole, making the sliding of the guide rod smoother, reducing energy loss, and also extending the service life of the guide rod and the guide hole.

[0009] Preferably, an adsorption ring is provided inside the guide hole, and one end of the guide rod is provided with an adsorption end that can be adsorbed and fixed by the adsorption ring. In use, after the guide rod is inserted into the guide hole, the adsorption end will adsorb with the adsorption ring, thereby firmly fixing the guide rod in the guide hole. This effectively prevents the guide rod from shifting or falling off due to vibration or external force during use, and further improves the stability and reliability of the wing fixing structure.

[0010] Preferably, the surface of the mounting base is provided with a magnetic shielding layer, which can effectively prevent magnetic field interference to the UAV's electronic equipment.

[0011] Preferably, at least two side walls of the fixing seat are provided with a docking cylinder, and the docking cylinder has an internal thread for the insertion and connection of the docking part, specifically for the connection of the threaded rod.

[0012] Preferably, the spring drive assembly consists of a housing and a spring disposed within the housing, the spring being connected to a threaded rod.

[0013] Preferably, the ratchet lock consists of a ratchet fixed to the outer periphery of the threaded rod, a housing, and a pawl fixed to the housing by a coil spring. Under the action of the internal coil spring, the tip of the pawl continuously presses against the ratchet tooth surface.

[0014] The beneficial effects of this utility model are: 1. This utility model achieves automated locking of the wing connection through the cooperation of the spring drive assembly and the threaded rod. During installation, the wing connecting seat approaches the fixed seat, and the guide rod is inserted into the guide hole to complete the initial positioning. Then, the threaded rod is controlled to rotate, so that the threaded rod is screwed into the fixed seat. At the same time, the ratchet lock automatically locks the threaded rod. The entire process can be completed without the assistance of tools. When disassembling, it is only necessary to manually release the restriction of the ratchet lock. The spring drive assembly, which has accumulated potential energy, immediately drives the threaded rod to rotate in the opposite direction and disengage from the threaded connection, realizing the automatic release of the wing. While ensuring the stability of the wing connection, it effectively improves the efficiency of disassembly and assembly. A single person can complete the wing disassembly and assembly in a few seconds. 2. This utility model, through the cooperation of the guide rod and the adsorption ring, utilizes the magnetic attraction between the adsorption end and the adsorption ring to ensure guidance during the docking process and enhance the fit stability between the connecting seat and the fixed seat. The magnetic shielding layer on the surface of the fixed seat effectively avoids the interference of the magnetic field on the electronic equipment of the UAV, and the cooperation between the actuation wheel and the control shell facilitates manual control. Attached Figure Description

[0015] Figure 1 This is a schematic diagram showing the connection between the docking section and the mounting base when the wing is in use. Figure 2 This is a schematic diagram of the structure of the fixed base, the docking part, and the connecting base in this utility model; Figure 3 This is a schematic diagram of the structure of the fixing base in this utility model; Figure 4 and Figure 5 This is a schematic diagram of the structure of the connecting seat, guide rod, and docking part in this utility model; Figure 6 This is a schematic diagram showing the connection between the docking section and the mounting base when the wing is retracted.

[0016] Explanation of reference numerals in the attached drawings: 1. Body; 2. Fixing base; 201. Docking cylinder; 202. Internal thread; 203. Guide hole; 3. Connecting seat; 4. Guide rod; 401. Adsorption end; 5. Docking part; 501. Spring drive assembly; 502. Threaded rod; 503. Control housing; 504. Actuating wheel; 6. Ratchet lock. Detailed Implementation

[0017] The present invention will be further described below with reference to the accompanying drawings: like Figures 1-6 As shown, this embodiment provides a wing fixing structure for an inspection drone, including a fixing seat 2 fixed on the body 1 and a connecting seat 3 fixed on the wing. The connecting seat 3 is detachably connected to the fixing seat 2 through a docking part 5. The docking part 5 consists of a spring drive assembly 501 and a threaded rod 502 connected to each other. The spring drive assembly 501 is fixed on the connecting seat 3, and the threaded rod 502 is threadedly connected to the fixing seat 2. The threaded rod 502 is provided with a manually release ratchet lock 6.

[0018] In use, this invention allows the threaded rod 502 to be manually rotated into the fixed seat 2. During this process, the ratchet lock 6 automatically locks the threaded rod 502, ensuring a stable connection. The entire installation process can be completed efficiently without any tools. When disassembly is required, the operator simply needs to manually release the ratchet lock 6. At this time, the spring drive assembly 501, which has accumulated potential energy, will immediately respond, driving the threaded rod 502 to rotate in the opposite direction, thus smoothly disengaging the threaded connection and achieving automatic release of the wing. This design not only ensures the stability of the wing connection but also greatly improves the efficiency of disassembly and assembly. Even with single-person operation, the wing disassembly and assembly can be easily completed in just a few seconds, greatly improving work efficiency and ease of operation.

[0019] As a technical optimization solution of this utility model, specifically as follows: Figure 4 and Figure 5 As shown, the connecting seat 3 is provided with several guide rods 4, and a control housing 503 is provided on the guide rod 4. A turn wheel 504 located inside the control housing 503 is fixed on the threaded rod 502. During the installation of the wing, the guide rods 4 are used for the preliminary calibration and positioning of each structure. The operator can hold the connecting seat 3 and bring the connecting seat 3 close to the fixed seat 2, and then accurately insert the guide rods 4 into the guide holes 203 to complete the preliminary positioning work.

[0020] The control housing 503 has openings on both sides, and the outer side of the actuating wheel 504 is exposed through the openings. In use, the threaded rod 502 can be screwed into the fixing seat 2 by the actuating wheel 504 to achieve fixation.

[0021] The outer wall of the ratchet lock 6 is fixed to the guide rod 4 and is used for the automatic locking and manual release of the threaded rod 502. In use, when the threaded rod 502 rotates under the action of the spring drive assembly 501, the ratchet lock 6 will automatically activate and lock the threaded rod 502 firmly in the current position to prevent the threaded rod 502 from reversing. After the threaded rod 502 is connected to the fixed seat 2, it can also effectively prevent the threaded rod 502 from loosening or retracting due to external factors such as vibration and airflow impact, further ensuring the stability of the wing connection. When it is necessary to disassemble the wing, the operator only needs to manually operate the release button or lever on the ratchet lock 6 to easily release the lock on the threaded rod 502. The spring drive assembly 501, which accumulates potential energy, rotates the threaded rod 502 in the opposite direction to realize the automatic release of the wing. The whole process is both safe and efficient.

[0022] In this invention, the spring drive assembly 501 consists of a housing and a spring disposed within the housing. The spring is connected to a threaded rod 502. When the operator rotates the threaded rod 502 clockwise, the torque drives the spring to twist, thereby converting mechanical energy into elastic potential energy for storage.

[0023] The ratchet lock 6 consists of a ratchet fixed to the outer periphery of the threaded rod 502, a housing, and a pawl fixed to the housing by a coil spring. The housing is fixed to the guide rod 4. Under the action of the internal coil spring, the tip of the pawl continuously presses against the ratchet tooth surface. When the threaded rod 502 attempts to rotate counterclockwise due to the spring drive, the pawl will instantly engage with the ratchet tooth groove, forming a rigid support to prevent reverse rotation. The lock is released by a separate release button. Pressing the button will forcibly lift the pawl through the linkage or push rod mechanism, separating it from the ratchet tooth surface. Once the pawl is disengaged, the stored energy will drive the threaded rod 502 to rotate counterclockwise quickly, completing the entire release process. The structures of the spring drive assembly 501 and the ratchet lock 6 are mature existing technologies, so detailed structures will not be described in detail.

[0024] The fixed base 2 has at least two side walls with several guide holes 203 corresponding to the guide rod 4 for positioning and guidance after the guide rod 4 is inserted. During use, after the guide rod 4 is inserted into the guide hole 203, it can slide smoothly along a predetermined direction, facilitating initial positioning. The interior of the guide hole 203 is finely polished, resulting in a smooth and flawless surface, reducing frictional resistance between the guide rod 4 and the guide hole 203, making the sliding of the guide rod 4 smoother, reducing energy loss, and extending the service life of both the guide rod 4 and the guide hole 203. Furthermore, a chamfered structure is provided at the entrance of the guide hole 203, facilitating quick and accurate insertion of the guide rod 4 into the guide hole 203, further improving the convenience and efficiency of operation.

[0025] An adsorption ring is installed inside the guide hole 203, and one end of the guide rod 4 is provided with an adsorption end 401 that can be adsorbed and fixed by the adsorption ring. During use, after the guide rod 4 is inserted into the guide hole 203, the adsorption end 401 will adsorb with the adsorption ring, thus firmly fixing the guide rod 4 inside the guide hole 203. This effectively prevents the guide rod 4 from shifting or falling off due to vibration or external force during use, further improving the stability and reliability of the wing fixing structure. At the same time, this adsorption fixing method also facilitates the operation when the guide rod 4 needs to be adjusted or removed. Only a certain external force needs to be applied to overcome the adsorption force to easily remove the guide rod 4, improving the efficiency of maintenance and repair. The surface of the fixing base 2 is provided with a magnetic shielding layer, which effectively prevents magnetic field interference to the UAV's electronic equipment.

[0026] As a technical optimization solution of this utility model, specifically as follows: Figure 3As shown, at least two side walls of the fixed base 2 are provided with docking cylinders 201, and the docking cylinders 201 are provided with internal threads 202 for the insertion and connection of the docking part 5, specifically for the connection of the threaded rod 502.

[0027] The foregoing has shown and described the basic principles, main features and advantages of this invention. Those skilled in the art should understand that this invention is not limited to the above embodiments. The embodiments and descriptions in the specification are only illustrative of the principles of this invention. Various changes and modifications can be made to this invention without departing from the spirit and scope of this invention. All such changes and modifications fall within the scope of this invention as defined by the appended claims and their equivalents.

Claims

1. A wing fixing structure for an inspection drone, comprising a fixing seat (2) fixed to the fuselage (1) and a connecting seat (3) fixed to the wing, characterized in that: The connecting seat (3) is detachably connected to the fixed seat (2) via the docking part (5). The docking part (5) consists of a spring drive assembly (501) and a threaded rod (502) connected to each other. The spring drive assembly (501) is fixed on the connecting seat (3). The threaded rod (502) is threadedly connected to the fixed seat (2). The threaded rod (502) is provided with a manually release ratchet lock (6).

2. The wing fixing structure of the inspection drone according to claim 1, characterized in that: The connecting seat (3) is provided with several guide rods (4), and a control housing (503) is provided on the guide rods (4). A turn wheel (504) located inside the control housing (503) is fixed on the threaded rod (502).

3. The wing fixing structure of the inspection drone according to claim 2, characterized in that: The control housing (503) has openings on both sides, through which the outer side of the actuation wheel (504) is exposed.

4. The wing fixing structure of the inspection drone according to claim 2, characterized in that: The outer wall of the ratchet lock (6) is fixed to the guide rod (4) for automatic locking and manual release of the threaded rod (502).

5. The wing fixing structure of the inspection drone according to claim 2, characterized in that: The fixing base (2) has at least two side walls with a plurality of guide holes (203) corresponding to the guide rod (4) for positioning and guiding the guide rod (4) after it is inserted.

6. The wing fixing structure of the inspection drone according to claim 5, characterized in that: An adsorption ring is provided inside the guide hole (203), and one end of the guide rod (4) is provided with an adsorption end (401) that can be adsorbed and fixed by the adsorption ring.

7. The wing fixing structure of the inspection drone according to claim 1, characterized in that: The surface of the fixed base (2) is provided with a magnetic shielding layer.

8. The wing fixing structure of the inspection drone according to claim 1, characterized in that: The fixing base (2) is provided with a docking cylinder (201) on at least two side walls, and the docking cylinder (201) is provided with an internal thread (202) for the docking part (5) to be inserted and connected.

9. The wing fixing structure of the inspection drone according to claim 1, characterized in that: The spring drive assembly (501) consists of a housing and a spring disposed within the housing, the spring being connected to a threaded rod (502).

10. The wing fixing structure of the inspection drone according to claim 1, characterized in that: The ratchet lock (6) consists of a ratchet fixed to the outer periphery of the threaded rod (502), a housing, and a pawl fixed to the housing by a coil spring. Under the action of the internal coil spring, the tip of the pawl continuously presses against the ratchet tooth surface.

Images