Unmanned aerial vehicle tail wing connecting structure with improved stability

Abstract

This utility model discloses a tail fin connection structure for improving the stability of a UAV, relating to the field of UAV tail fin connection technology. It includes a fuselage tail plate with a slot at its upper end; a tail fin plate with its lower end inserted into the slot; a screw is integrally formed and fixedly mounted on the lower end of the tail fin plate; an operating compartment communicating with the slot is opened on one side wall of the fuselage tail plate; a perforated plate is fixedly installed on the inner wall of the slot, with a through hole through the perforated plate. When the lower end of the tail fin plate is inserted into the slot, the screw passes through the through hole of the perforated plate and extends into the operating compartment. At this point, simply screwing a locking nut into the compartment and pressing its upper end against the bottom wall of the perforated plate will rigidly press the tail fin plate, perforated plate, and fuselage tail plate together along the insertion direction, forming a threaded-rigid dual force transmission path. Under long-term vibration or temperature difference deformation conditions, the helix angle of the threaded pair is less than the material friction angle, possessing self-locking characteristics and eliminating the risk of the tail fin loosening or even falling off in mid-air.

Description

Technical Field

[0001] This utility model relates to the tail fin connection structure technology of unmanned aerial vehicles (UAVs), specifically to a tail fin connection structure for UAVs that improves stability. Background Technology

[0002] Unmanned aerial vehicles (UAVs) are unmanned aircraft composed of airframes, power systems, navigation and control systems, etc. They can take off and land vertically or horizontally, hover, cruise, and perform various tasks under remote control or preset programs / autonomous intelligent algorithms. They can be controlled in real time or offline via ground control stations, satellite links, or onboard computing platforms without the need for personnel. They rely on the thrust output of internal combustion engines, electric motors, or hybrid power to drive propellers, nozzles, or fixed wings to generate lift and thrust. They are equipped with inertial navigation, BeiDou / GPS, visual / LiDAR, and multi-redundant sensor fusion algorithms to achieve attitude stabilization, trajectory planning, and obstacle avoidance. They can carry visible light, infrared, and multispectral cameras, LiDAR, synthetic aperture radar, communication relays, electronic countermeasures, or cargo pods. These payloads are widely used in military and civilian fields such as military reconnaissance, precision strikes, border patrols, disaster relief, meteorological detection, geographic mapping, power and oil and gas pipeline inspection, agricultural plant protection, logistics distribution, air traffic management training, scientific research experiments, and low-altitude tourism photography. They are characterized by small size, light weight, high mobility, rapid deployment, low cost, good concealment, diverse range and payload capabilities, high environmental adaptability and scalability. At the same time, they must comply with national airspace regulations, flight safety, electromagnetic compatibility, privacy protection and data security regulations, and have automatic return, forced landing, parachute landing or redundant backup safety strategies in the event of communication link interruption, navigation signal interference or key component failure to ensure public safety and mission reliability.

[0003] Currently, the tail fins of small drones generally use plastic clips to quickly connect to the fuselage tail plate. While this structure allows for tool-free assembly and disassembly, under conditions of long-term vibration, temperature changes, or occasional drop impacts, the base of the clips is prone to fatigue deformation. This leads to a gradual decrease in the locking force, increasing the risk of the tail fin loosening from the fuselage or even detaching in mid-air, directly threatening flight safety. Therefore, improvements to the existing technology are necessary. Utility Model Content

[0004] The purpose of this invention is to provide a tail fin connection structure for drones that improves stability. This addresses the problem that in existing small drones, the tail fin is quickly attached to the fuselage tail plate using plastic clips. While this structure allows for tool-free assembly and disassembly, under conditions of long-term vibration, temperature changes, or occasional drop impacts, the base of the clip is prone to fatigue deformation, leading to a gradual decrease in the amount of fastening. This can result in the tail fin loosening from the fuselage or even falling off in mid-air, directly threatening flight safety.

[0005] To achieve the above objectives, this utility model provides the following technical solution: a tail fin connection structure for improving the stability of a UAV, comprising:

[0006] The tail plate of the fuselage has a slot at its upper end;

[0007] The tail fin plate, the lower end of which is inserted into the slot;

[0008] The tail fin is integrally formed with a screw at its lower end. The tail plate has an operating compartment opening on one side wall that communicates with the slot. A perforated plate is fixedly installed on the inner wall of the slot. A through hole is opened through the perforated plate. When the lower end of the tail fin is inserted into the slot, the lower end of the screw passes through the through hole. A locking nut is provided below the perforated plate. The locking nut is threaded onto the outer wall of the screw, and the upper wall of the locking nut abuts against the bottom wall of the perforated plate.

[0009] Furthermore, a side cover plate is provided on one side of the operating compartment opening, and several pads are fixedly connected to the side wall of the side cover plate. An opening is provided through one side wall of the pad plate, and an internal threaded hole is provided on one side wall of the tail plate of the machine body. A connecting screw is provided inside the opening and the internal threaded hole, and the connecting screw is threadedly assembled with the internal threaded hole.

[0010] Furthermore, a reinforcing connection assembly is provided between the tail plate of the fuselage and the tail fin. The reinforcing connection assembly includes a slot block fixedly disposed on the outer wall of the tail plate of the fuselage. A first elastic member and a second elastic member are fixedly connected to one side wall inside the slot block. One end of the first elastic member and the second elastic member are fixedly connected to an inclined guide plate. A limiting groove is formed on one side wall of the slot block.

[0011] Furthermore, the length of the first elastic element is greater than the length of the second elastic element.

[0012] Furthermore, the reinforced connection assembly also includes a connecting rod fixedly disposed on the outer wall of the tail fin end. One end of the connecting rod is fixedly connected to a plug connector, and one side wall of the plug connector is fixedly connected to a snap connector. When one end of the plug connector is guided by the inclined guide plate and fully inserted into the slot block, the snap connector engages with the limiting groove.

[0013] Furthermore, the card connector is configured in a trapezoidal shape.

[0014] Compared with the prior art, the present invention provides a tail fin connection structure for drones that improves stability. When the lower end of the tail fin plate is inserted into the slot, the screw passes through the through hole of the perforated plate and extends into the operating compartment. At this time, it is only necessary to screw the locking nut into the compartment and press its upper end face against the bottom wall of the perforated plate to rigidly press the tail fin plate, the perforated plate and the tail plate of the fuselage together along the insertion direction, forming a threaded-rigid dual force transmission path. Under long-term vibration or temperature difference deformation conditions, the helix angle of the threaded pair is less than the material friction angle, which has self-locking characteristics and eliminates the hidden danger of the tail fin loosening or even falling off in the air. Attached Figure Description

[0015] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in this utility model. For those skilled in the art, other drawings can be obtained based on these drawings.

[0016] Figure 1 A schematic diagram of the overall external structure provided for this utility model;

[0017] Figure 2 This is a partial structural schematic diagram of the present invention;

[0018] Figure 3 This is a partial cross-sectional structural schematic diagram provided by the present invention;

[0019] Figure 4 Provided by this utility model Figure 1 A magnified view of the structure at point A in the middle;

[0020] Figure 5 A disassembled structural diagram of the reinforced connection component provided by this utility model.

[0021] Explanation of reference numerals in the attached figures:

[0022] 1. Fuselage tail plate; 2. Tail fin plate; 3. Slot opening; 4. Screw; 5. Operating compartment opening; 6. Perforated plate; 7. Locking nut; 8. Side cover plate; 9. Pad plate; 10. Connecting screw; 11. Slot block; 12. First elastic element; 13. Second elastic element; 14. Inclined guide plate; 15. Limiting groove; 16. Connecting rod; 17. Plug connector; 18. Clip connector. Detailed Implementation

[0023] To enable those skilled in the art to better understand the technical solution of this utility model, the present utility model will be further described in detail below with reference to the accompanying drawings.

[0024] As attached Figure 1 To be continued Figure 5 As shown:

[0025] Example 1:

[0026] This utility model provides a tail fin connection structure for improving the stability of a drone, comprising:

[0027] The tail plate 1 of the fuselage has a slot 3 at its upper end;

[0028] Tail wing 2, the lower end of which is inserted into the slot 3;

[0029] The tail fin 2 is integrally formed and fixedly provided with a screw 4 at its lower end. The tail plate 1 of the fuselage has an operation compartment 5 that communicates with the slot 3 on one side wall. The slot 3 has a perforated plate 6 fixedly installed on its inner wall. The perforated plate 6 has a through hole. When the lower end of the tail fin 2 is inserted and matched with the slot 3, the lower end of the screw 4 passes through the through hole. A locking nut 7 is provided below the perforated plate 6. The locking nut 7 is threaded onto the outer wall of the screw 4, and the upper wall of the locking nut 7 abuts against the bottom wall of the perforated plate 6.

[0030] As can be seen from the above, when the lower end of the tail fin plate 2 is inserted into the slot 3, the screw 4 passes through the through hole of the perforated plate 6 and extends into the operating compartment 5. At this time, it is only necessary to screw the locking nut 7 into the compartment and press its upper end face against the bottom wall of the perforated plate 6 to rigidly press the tail fin plate 2, the perforated plate 6 and the fuselage tail plate 1 together along the insertion direction, forming a threaded-rigid dual force transmission path. Under long-term vibration or temperature difference deformation conditions, the helix angle of the threaded pair is less than the material friction angle, which has self-locking characteristics and eliminates the hidden danger of the tail fin loosening or even falling off in the air. At the same time, all axial loads are borne by the screw 4-locking nut 7 pair, and the plastic part is only subjected to compressive stress, avoiding bending fatigue at the root of the traditional buckle, and significantly improving the connection life and flight safety.

[0031] Example 2:

[0032] This embodiment is basically the same as the previous embodiment, except that, as shown in the appendix... Figure 1 To be continued Figure 4 As shown, in order to facilitate the sealing of one side of the operating compartment opening 5, a side cover plate 8 is provided on one side of the operating compartment opening 5. Several pads 9 are fixedly connected to the side wall of the side cover plate 8. An opening is provided through one side wall of the pads 9. An internal threaded hole is provided on one side wall of the tail plate 1 of the machine body. A connecting screw 10 is provided inside the opening and the internal threaded hole, and the connecting screw 10 is threadedly assembled with the internal threaded hole.

[0033] As can be seen from the above, the side cover plate 8 forms a detachable seal with the gasket plate 9 and the connecting screw 10, which can completely seal the operating compartment opening 5 and prevent dust and rainwater from entering the threaded pair during flight, causing rust or lubrication failure.

[0034] Example 3:

[0035] This embodiment is basically the same as the previous embodiment, except that, as shown in the appendix... Figure 1 Appendix Figure 4 and appendix Figure 5 As shown, in order to enhance the connection between the fuselage tail plate 1 and the tail fin 2, a reinforcing connection assembly is provided between the fuselage tail plate 1 and the tail fin 2. The reinforcing connection assembly includes a slot block 11 fixedly disposed on the outer wall of the fuselage tail plate 1. A first elastic element 12 and a second elastic element 13 are fixedly connected to one side wall of the slot block 11. One end of the first elastic element 12 and the second elastic element 13 are fixedly connected to an inclined guide plate 14. A limiting groove 15 is provided on one side wall of the slot block 11.

[0036] The length of the first elastic element 12 is greater than the length of the second elastic element 13.

[0037] The reinforced connection assembly also includes a connecting rod 16 fixedly disposed on the outer wall of the end of the tail fin plate 2. One end of the connecting rod 16 is fixedly connected to a connector 17, and a snap connector 18 is fixedly connected to one side wall of the connector 17. When one end of the connector 17 is guided by the inclined guide plate 14 and fully inserted into the slot block 11, the snap connector 18 snaps into the limiting groove 15.

[0038] The snap-fit ​​connector 18 is configured in a trapezoidal shape.

[0039] As can be seen from the above, during the insertion process, the connector 17 first slides along the inclined guide plate 14, and the first elastic element 12 and the second elastic element 13, which are arranged with long-short differences, generate progressive compression to store elastic potential energy. When the locking connector 18 passes the highest point of the inclined guide plate 14, the elastic potential energy is released instantaneously. The trapezoidal inclined surface of the locking connector 18 and the edge of the limiting groove 15 automatically engage to form a locking structure, which blocks the micro-movement of the tail fin 2, strengthens the connection between the fuselage tail plate 1 and the tail fin 2, and improves stability.

[0040] The foregoing description only illustrates certain exemplary embodiments of the present invention. Undoubtedly, those skilled in the art can modify the described embodiments in various ways without departing from the spirit and scope of the present invention. Therefore, the above drawings and descriptions are illustrative in nature and should not be construed as limiting the scope of protection of the claims of the present invention.

Claims

1. A tail fin connection structure for improving the stability of a UAV, characterized in that, include: The tail plate (1) of the fuselage has a slot (3) at the upper end. The tail fin plate (2) is inserted and matched with the slot (3) at its lower end; Among them, the tail fin plate (2) is integrally formed and fixedly provided with a screw (4), the tail plate (1) of the fuselage has an operation compartment opening (5) that communicates with the slot opening (3) on one side wall, the slot opening (3) has a hole plate (6) fixedly installed on the inner wall, and the hole plate (6) has a through hole. When the lower end of the tail fin plate (2) is inserted and matched with the slot opening (3), the lower end of the screw (4) passes through the through hole. The hole plate (6) is provided with a locking nut (7) below it. The locking nut (7) is threadedly fitted to the outer wall of the screw (4), and the upper wall of the locking nut (7) abuts against the bottom wall of the hole plate (6).

2. The UAV tail fin connection structure for improving stability according to claim 1, characterized in that, A side cover plate (8) is provided on one side of the operating compartment opening (5). Several pads (9) are fixedly connected to the side wall of the side cover plate (8). An opening is provided through one side wall of the pad (9). An internal thread hole is provided on one side wall of the tail plate (1). A connecting screw (10) is provided inside the opening and the internal thread hole. The connecting screw (10) is threadedly assembled with the internal thread hole.

3. The UAV tail fin connection structure for improving stability according to claim 1, characterized in that, A reinforcing connection assembly is provided between the tail plate (1) and the tail fin (2). The reinforcing connection assembly includes a slot block (11) fixedly installed on the outer wall of the tail plate (1). A first elastic element (12) and a second elastic element (13) are fixedly connected to one side wall inside the slot block (11). One end of the first elastic element (12) and the second elastic element (13) are fixedly connected to an inclined guide plate (14). A limiting groove (15) is opened on one side wall of the slot block (11).

4. The UAV tail fin connection structure for improving stability according to claim 3, characterized in that, The length of the first elastic element (12) is greater than the length of the second elastic element (13).

5. The UAV tail fin connection structure for improving stability according to claim 3, characterized in that, The reinforced connection assembly also includes a connecting rod (16) fixedly installed on the outer wall of the end of the tail fin plate (2). One end of the connecting rod (16) is fixedly connected to a connector (17), and a snap connector (18) is fixedly connected to one side wall of the connector (17). When one end of the connector (17) is guided through the inclined guide plate (14) and fully inserted into the slot block (11), the snap connector (18) snaps into the limiting groove (15).

6. The UAV tail fin connection structure for improving stability according to claim 5, characterized in that, The snap-fit ​​connector (18) is arranged in a trapezoidal structure.

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