Anti-interference structure of high-altitude monitoring unmanned aerial vehicle

Abstract

The utility model relates to an anti-interference structure of a high-altitude monitoring unmanned aerial vehicle, which comprises a vehicle body, a plurality of side rods and wings, the plurality of side rods are fixedly connected to the side of the vehicle body, each side rod is connected with a sliding block in a sliding manner, the top side of each sliding block is connected with a motor, the wings are connected with the output ends of the corresponding motors, and the wings are connected with the output ends of the corresponding motors. And a synchronous control piece is arranged on the bottom side of the machine body. The utility model relates to the technical field of unmanned aerial vehicle anti-interference. When the anti-interference structure of the high-altitude monitoring unmanned aerial vehicle is used, the distance between the sliding block and the unmanned aerial vehicle body can be controlled through the size of wind resistance, interference of the unmanned aerial vehicle caused by strong wind and high wind resistance is reduced, then the length of a vehicle arm formed by the side rod and the sliding pipe is controlled, the load of a power source in the unmanned aerial vehicle is reduced, and the anti-interference performance of the unmanned aerial vehicle is improved. Therefore, the endurance of the unmanned aerial vehicle in use is improved, and the performance of the unmanned aerial vehicle in use is improved.

Description

Technical Field

[0001] This utility model relates to the technical field of anti-interference for unmanned aerial vehicles (UAVs), and in particular to an anti-interference structure for a high-altitude monitoring UAV. Background Technology

[0002] During the flight of a drone, wind resistance needs to be taken into account. When the wind resistance is high, the length of the drone's arms needs to be extended to improve the drone's wind resistance and anti-interference ability. However, this will reduce the drone's maneuverability. When the wind resistance decreases, the drone needs to be retracted and the length of the drone's arms needs to be shortened.

[0003] A novel anti-interference structure for unmanned aerial vehicles (UAVs) disclosed in CN222062308U includes: a main body comprising a fuselage; and an adjustment mechanism comprising a fixed block fixedly connected to the surface of the fuselage, a first motor fixedly connected to the surface of the fixed block, a rotating shaft fixedly connected to the output shaft of the first motor, the first motor driving the rotating shaft to rotate via the output shaft, and a rotating rod fixedly connected to the surface of the rotating shaft. This invention uses a cylinder piston rod to drive a movable rod to slide on the surface of the rotating rod. During the sliding process of the movable rod on the rotating rod, the length of the UAV arm is changed, allowing the UAV to adjust the arm length during flight. Lengthening the arm improves the UAV's stability, while shortening the arm improves its maneuverability, fully utilizing the UAV's advantages and enhancing its flexibility.

[0004] The aforementioned patent utilizes a cylinder piston rod to drive a movable rod to slide on the surface of a rotating rod, thereby adjusting the length of the boom and improving the stability of the drone under high wind resistance. However, the extension and retraction of the cylinder piston rod needs to be controlled during use, which increases the load on the drone's power supply, thereby reducing the drone's battery life and affecting its usability. Utility Model Content

[0005] In view of the shortcomings of the existing technology, the purpose of this utility model is to provide an anti-interference structure for a high-altitude monitoring UAV, so as to solve the technical problems mentioned in the background art.

[0006] The above-mentioned technical objective of this utility model is achieved through the following technical solution:

[0007] An anti-interference structure for a high-altitude monitoring UAV includes a body, a number of side rods and wings. The side rods are fixedly connected to the sides of the body. Each side rod is slidably connected to a slider. A motor is connected to the top side of the slider. The wings are connected to the corresponding output end of the motor. A synchronization control component is provided on the bottom side of the body.

[0008] The synchronization control component includes a guide block, a number of air ducts, a corrugated pipe, a cavity, and a compression ball. The guide block is fixedly connected to the bottom side of the machine body. The number of air ducts are respectively opened on the outer side wall of the guide block. The cavity is opened in the top of the guide block. The top end of the corrugated pipe is fixedly connected to the top of the air duct and communicates with the cavity. The compression ball is slidably connected to the bottom of the air duct and is connected to the bottom end of the corrugated pipe. A transmission component is provided between the guide block and each of the side rods.

[0009] In a preferred embodiment, the present invention can be further configured such that: a limiting cavity tube is connected to both the side of the guide block and the air duct, and the side of the limiting cavity tube away from the guide block is tapered.

[0010] In a preferred embodiment, the present invention can be further configured as follows: the transmission component includes a slide tube, the slide tube is slidably connected to the side rod, the end of the slide tube is slidably connected to the corresponding slider, a connecting pipe is slidably connected to the side wall of the slide tube away from the slider, and is dynamically sealed, the end of the connecting pipe is connected to the cavity, and the connecting pipe is fixedly connected to the side of the machine body.

[0011] In a preferred embodiment, the present invention can be further configured such that: each of the defined cavities is connected to a flared tube on the side away from the guide block, and the flared tube is constricted on the side closer to the guide block.

[0012] In a preferred embodiment, the present invention can be further configured such that the top end of the corrugated pipe is sealed to the inner circumferential sidewall of the air duct, and the bottom end of the corrugated pipe is closed.

[0013] In a preferred embodiment, the present invention can be further configured such that: a gap is left between each of the air ducts, and hydraulic oil is injected into each of the bellows and the cavity.

[0014] In summary, this utility model has at least one of the following beneficial technical effects:

[0015] 1. The anti-interference structure of this high-altitude monitoring drone can control the distance between the slider and the body by utilizing the wind resistance, thereby reducing interference from strong winds and high wind resistance. It also controls the length of the arm formed by the side rod and the sliding tube, reducing the power load on the drone, thus improving the drone's endurance and performance.

[0016] 2. The anti-interference structure of the high-altitude monitoring UAV has a limiting cavity tube connected to the side of the guide block at the position of the air duct, and the side of the limiting cavity tube away from the guide block is set to be constricted. The limiting cavity tube is used to limit the extrusion ball and prevent the extrusion ball from sliding out of the air duct, thereby affecting subsequent use.

[0017] 3. This anti-interference structure for a high-altitude monitoring UAV, when the air inside the cavity is compressed, will be compressed into several connecting pipes, and at the same time, the air in the connecting pipes will be transported into the side wall of the sliding tube, thereby using air pressure to push the sliding tube to slide on the side rod, as shown in the reference. Figure 1 When the side rod slides, it will drive the slider connected to it to move, thereby allowing the slider to extend outward from the side rod, increasing the distance between the wing and the fuselage, increasing the length of the drone's arm, and thus improving the stability of the drone in high wind and strong wind conditions.

[0018] 4. The anti-interference structure of this high-altitude monitoring UAV has a flared tube connected to the side of the cavity tube away from the guide block. The side of the flared tube near the guide block is constricted, while the side away from the guide block is flared. This allows the airflow to be gathered and blown toward the compression ball when it blows toward the guide block under conditions of high wind resistance and strong winds, thereby achieving the effect of pushing the compression ball, so as to extend the UAV's arms and improve the stability of the UAV. Attached Figure Description

[0019] To more clearly illustrate the technical solutions of the embodiments of this utility model, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0020] Figure 1 This is a schematic diagram of the overall structure of the anti-interference structure of a high-altitude monitoring drone according to this utility model.

[0021] Figure 2 This is a schematic diagram of the synchronization control component of an anti-interference structure for a high-altitude monitoring drone according to the present invention.

[0022] Figure 3 This is a schematic diagram of the bottom structure of a high-altitude monitoring drone, which is an anti-interference structure of the present invention.

[0023] Figure 4 This is a schematic diagram of the transmission component structure of an anti-interference structure for a high-altitude monitoring drone according to the present invention.

[0024] In the diagram, 1. fuselage; 2. side rod; 3. wing; 4. slider; 5. motor; 6. synchronization control component; 7. guide block; 8. air duct; 9. bellows; 10. cavity; 11. extrusion ball; 12. transmission component; 13. limiting cavity tube; 14. slide tube; 15. connecting tube; 16. flared tube. Detailed Implementation

[0025] The present invention will be further described in detail below with reference to the accompanying drawings.

[0026] Example:

[0027] Reference Figure 1 - Figure 4 The present invention discloses an anti-interference structure for a high-altitude monitoring drone, comprising a body 1, a number of side rods 2 and wings 3. The side rods 2 are fixedly connected to the side of the body 1, and each side rod 2 is slidably connected to a slider 4. A motor 5 is connected to the top side of the slider 4, and the wings 3 are connected to the output end of the corresponding motor 5. A synchronization control component 6 is provided on the bottom side of the body 1.

[0028] The synchronization control component 6 includes a guide block 7, a number of air ducts 8, a corrugated pipe 9, a cavity 10, and a compression ball 11. The guide block 7 is fixedly connected to the bottom side of the body 1. The number of air ducts 8 are respectively opened on the outer side wall of the guide block 7. The cavity 10 is opened in the top of the guide block 7. The top end of the corrugated pipe 9 is fixedly connected to the top of the air duct 8 and communicates with the cavity 10. The compression ball 11 is slidably connected to the bottom of the air duct 8 and is connected to the bottom end of the corrugated pipe 9. A transmission component 12 is provided between the guide block 7 and each of the side rods 2.

[0029] In this embodiment, reference Figure 1 The body 1 has a side rod 2 connected to its side, and a slider 4 is slidably connected to the side rod 2, allowing the slider 4 to move on the side rod 2. At the same time, a motor 5 is connected to the slider 4, and the wing 3 is connected to the motor 5 to facilitate the use of the drone.

[0030] When drones are operating at high altitudes, refer to Figure 2In the case of a strong wind, the airflow velocity of the synchronous control component 6 is high, which blows towards the air duct 8. At the same time, the airflow also blows the compression ball 11, causing it to slide within the air duct 8. As the compression ball 11 slides, it compresses the bellows 9, causing it to contract. The air inside the bellows 9 is then compressed into the cavity 10, increasing the air pressure within the cavity 10. This increased air pressure then delivers air to several transmission components 12, which in turn drives the slider 4 to slide on the side rod 2. The side rod 2 can be extended through the transmission component 12 to achieve the effect of extending the drone's arm. When the wind resistance is reduced, the thrust on the extrusion ball 11 decreases. The extrusion ball 11 descends in the wind duct 8 using its own weight, thereby straightening the bellows 9 and allowing the bellows 9 to extend. This allows the extruded air to be recovered, thereby driving the wing 3 back to its original position. This enables the drone to fly stably under high wind resistance and strong winds. When the wind resistance decreases, maneuverability can be restored, and the stability of its high-altitude operation can be avoided by strong winds.

[0031] In a further preferred embodiment of this utility model, such as Figure 2 As shown, the guide block 7 is connected to a limiting cavity tube 13 on its side and at the air duct 8. The limiting cavity tube 13 is tapered on the side away from the guide block 7.

[0032] In this embodiment, reference Figure 2 The guide block 7 is connected to the limiting cavity tube 13 on the side of the air duct 8. The limiting cavity tube 13 is closed on the side away from the guide block 7. The limiting cavity tube 13 is used to limit the extrusion ball 11 and prevent the extrusion ball 11 from sliding out of the air duct 8, thus affecting subsequent use.

[0033] In a further preferred embodiment of this utility model, such as Figure 2 and Figure 4 As shown, the transmission component 12 includes a slide tube 14, which is slidably connected to the side rod 2. The end of the slide tube 14 is slidably connected to the corresponding slider 4. A connecting pipe 15 is slidably connected to the side wall of the slide tube 14 away from the slider 4, and is dynamically sealed. The end of the connecting pipe 15 is connected to the cavity 10, and the connecting pipe 15 is fixedly connected to the side of the body 1.

[0034] In this embodiment, reference Figure 2 The guide block 7 is connected to a connecting pipe 15, which communicates with the cavity 10. When the air in the cavity 10 is compressed, it is forced into several connecting pipes 15. Simultaneously, the air in the connecting pipes 15 is transported to the side wall of the slide tube 14, thereby using air pressure to push the slide tube 14 to slide on the side rod 2. (Refer to...) Figure 1When the side rod 2 and the slide tube 14 slide, they will drive the slider 4 connected to them to move, thereby allowing the slider 4 to extend outward from the side rod 2, increasing the distance between the wing 3 and the body 1, increasing the length of the drone's arm, and thus improving the stability of the drone in high wind and strong wind conditions.

[0035] In a further preferred embodiment of this utility model, such as Figure 2 As shown, each of the defined cavity tubes 13 is connected to a flared tube 16 on the side away from the guide block 7, and the flared tube 16 is constricted on the side near the guide block 7.

[0036] In this embodiment, reference Figure 2 The limiting cavity 13 is connected to the flared tube 16 on the side away from the guide block 7. The side of the flared tube 16 near the guide block 7 is narrowed, while the side away from the guide block 7 is widened. This allows the airflow to be gathered and blown toward the extrusion ball 11 when it blows toward the guide block 7 under conditions of high wind resistance and strong winds, thereby pushing the extrusion ball 11 to extend the drone's arms and improve the drone's stability.

[0037] In a further preferred embodiment of this utility model, such as Figure 2 As shown, the top end of the corrugated pipe 9 is sealed to the inner circumferential sidewall of the air duct 8, and the bottom end of the corrugated pipe 9 is closed.

[0038] In this embodiment, reference Figure 2 The bellows 9 has its top sidewall connected to the inner wall of the air duct 8 and is sealed to prevent air from leaking from the top of the bellows 9. The bottom of the bellows 9 is also sealed to prevent air from leaking out, which would affect the air delivery to the sidewall of the slide tube 14 and thus the movement of the slider 4.

[0039] In a further preferred embodiment of this utility model, such as Figure 2 As shown, there is a gap between each of the air ducts 8, and hydraulic oil is injected into each of the bellows 9 and the cavity 10.

[0040] In this embodiment, reference Figure 2 The air ducts 8 are spaced apart, allowing high wind resistance and strong winds from each direction to independently push the corresponding compression balls 11, thereby extending the drone's arms. This improves the drone's stability during use, especially when facing high wind resistance and strong winds from different directions. Hydraulic oil is injected into the bellows 9 and the cavity 10 to prevent the compressed air from rebounding and affecting the extension of the drone's arms, which would otherwise affect the drone's stability.

[0041] The implementation principle of the above embodiment is as follows: In the case of strong winds, the airflow velocity is relatively high, which blows towards the air duct 8. At the same time, the airflow also blows the compression ball 11, causing the compression ball 11 to slide within the air duct 8. When the compression ball 11 slides, it will compress the bellows 9, causing the bellows 9 to contract after being compressed. The air inside the bellows 9 will be compressed into the cavity 10, thereby increasing the air pressure inside the cavity 10. When the air pressure inside the cavity 10 increases, the air will be transported to several connecting pipes 15. At the same time, the air in the connecting pipes 15 will be transported to the side wall of the slide pipe 14, thereby using air pressure to push the slide pipe 14 to slide on the side rod 2. When the slide pipe 14 slides, it will drive the slider 4 connected to it to move, thereby allowing the slider 4 to extend outward from the side rod 2, increasing the distance between the wing 3 and the body 1, increasing the length of the UAV arm, and thus improving the stability of the UAV in high wind and strong wind conditions.

[0042] The embodiments described herein are preferred embodiments of this utility model and are not intended to limit the scope of protection of this utility model. Therefore, all equivalent changes made to the structure, shape, and principle of this utility model should be included within the scope of protection of this utility model.

Claims

1. An anti-interference structure for a high-altitude monitoring UAV, comprising a body (1), a plurality of side rods (2), and wings (3), wherein the plurality of side rods (2) are fixedly connected to the sides of the body (1), characterized in that, Each of the side bars (2) is slidably connected to a slider (4), and a motor (5) is connected to the top side of the slider (4). The wing (3) is connected to the output end of the corresponding motor (5), and a synchronization control component (6) is provided on the bottom side of the body (1). The synchronization control component (6) includes a guide block (7), a number of air ducts (8), a bellows (9), a cavity (10), and a compression ball (11). The guide block (7) is fixedly connected to the bottom side of the body (1). The number of air ducts (8) are respectively opened on the outer side wall of the guide block (7). The cavity (10) is opened in the top of the guide block (7). The top end of the bellows (9) is fixedly connected to the top of the air duct (8) and communicates with the cavity (10). The compression ball (11) is slidably connected to the bottom of the air duct (8). The compression ball (11) is connected to the bottom end of the bellows (9). A transmission component (12) is provided between the guide block (7) and each of the side rods (2).

2. The anti-interference structure of a high-altitude monitoring UAV according to claim 1, characterized in that, The guide block (7) is connected to a limiting cavity tube (13) on its side and at the air duct (8), and the limiting cavity tube (13) is closed on the side away from the guide block (7).

3. The anti-interference structure of a high-altitude monitoring UAV according to claim 2, characterized in that, The transmission component (12) includes a slide tube (14), which is slidably connected to the side rod (2). The end of the slide tube (14) is slidably connected to the corresponding slider (4). A connecting pipe (15) is slidably connected to the side wall of the slide tube (14) away from the slider (4), and it is dynamically sealed. The end of the connecting pipe (15) is connected to the cavity (10), and the connecting pipe (15) is fixedly connected to the side of the body (1).

4. The anti-interference structure of a high-altitude monitoring UAV according to claim 2, characterized in that, Each of the defined cavity tubes (13) is connected to a flared tube (16) on the side away from the guide block (7), and the flared tube (16) is constricted on the side near the guide block (7).

5. The anti-interference structure of a high-altitude monitoring UAV according to claim 1, characterized in that, The top end of the corrugated pipe (9) is sealed to the inner circumferential side wall of the air duct (8), and the bottom end of the corrugated pipe (9) is closed.

6. The anti-interference structure of a high-altitude monitoring UAV according to claim 1, characterized in that, A gap is left between each of the air ducts (8), and hydraulic oil is injected into each of the bellows (9) and the cavity (10).

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