Communication antenna inspection unmanned aerial vehicle with buffer structure

Abstract

The utility model relates to the technical field of communication equipment maintenance and detection, and discloses a communication antenna inspection unmanned aerial vehicle with a buffer structure, which comprises a vehicle body, a plurality of uniformly distributed propellers are rotatably connected to the edge of the vehicle body, a camera is mounted at the lower part of the front side of the vehicle body, and a disassembly assembly is arranged at the front side in the vehicle body. First spring rods are fixedly connected to the left side and the right side of the bottom of the machine body, first connecting rods are rotatably connected to the front side and the rear side of the lower portion of each first spring rod, and second connecting rods are rotatably connected to the sides, away from each other, of the two first connecting rods; and spring rods II are rotationally connected to the sides, close to each other, of the middle parts of the two connecting rods II. According to the utility model, the impact force generated during the landing of the unmanned aerial vehicle can be absorbed through the overall cooperation of all the components in the buffer assembly, and the fixation of the camera by the tenon can be released by sliding the slide knob, so that the camera can be quickly disassembled.

Description

Technical Field

[0001] The utility model relates to the technical field of communication equipment maintenance and detection, in particular to an unmanned aerial vehicle for inspecting communication antennas with a buffer structure. Background Technique

[0002] With the rapid development of communication technology, the number of communication antennas is increasing continuously and widely distributed. Traditional manual inspection of communication antennas is inefficient, dangerous and difficult to cover complex terrains. The unmanned aerial vehicle for inspecting communication antennas comes into being. It uses advanced flight technology and detection equipment to efficiently and accurately inspect communication antennas, timely discover potential faults and ensure the stable operation of the communication network, providing strong technical support for the high-quality development of modern communication.

[0003] The unmanned aerial vehicle for inspecting communication antennas mainly consists of a fuselage, propellers, a power system, a control system and detection equipment. The unmanned aerial vehicle is controlled by the control system to fly near the communication antenna, and the antenna is detected comprehensively by using the equipped high-definition camera and sensors. The power system provides flight power for the unmanned aerial vehicle, and the propellers generate lift force.

[0004] The existing buffer structure of the unmanned aerial vehicle for inspecting communication antennas mainly uses simple springs and rubber pads. When facing a large impact force, it will reach its elastic limit and cannot effectively absorb and disperse energy, resulting in the unmanned aerial vehicle still being subjected to a large vibration and damaging the fuselage. Therefore, an unmanned aerial vehicle for inspecting communication antennas with a buffer structure is proposed to solve the above problems. Content of the Utility Model

[0005] In order to make up for the above deficiencies, the utility model provides an unmanned aerial vehicle for inspecting communication antennas with a buffer structure, aiming to improve the problem that the buffer performance is limited due to the overly simple buffer structure in the existing technology.

[0006] In order to achieve the above purpose, the utility model adopts the following technical scheme:

[0007] An unmanned aerial vehicle for inspecting communication antennas with a buffer structure includes a fuselage. A plurality of uniformly distributed propellers are rotatably connected to the edge of the fuselage. A camera is installed at the lower part of the front side of the fuselage. A disassembly component is arranged at the front side inside the fuselage, and the disassembly component is used for quickly disassembling the camera. Spring rods I are fixedly connected to the left and right sides of the bottom of the fuselage. Link rods I are rotatably connected to the front and rear sides of the lower part of the spring rod I. Link rods II are rotatably connected to the far sides of the two link rods I. A spring rod II is rotatably connected to the adjacent sides of the middle parts of the two link rods II. Landing gears are rotatably connected to the lower parts of the two link rods II.

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

[0009] The disassembly component includes a sliding block which is slidably connected to the front side inside the body. Compression springs are installed on both the left and right sides inside the body, and the rear sides of the compression springs abut against the front side of the sliding block. Tenons are installed on both the left and right sides of the lower part of the sliding block, and the tenons abut against the upper side inside of the camera.

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

[0011] A flash lamp is installed on the upper part of the front side of the body.

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

[0013] A sliding knob is installed on the left side of the sliding block, and the sliding knob slides on the left side of the body.

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

[0015] Slide rods are installed on both the left and right sides inside the body. The sliding block slides on the outer circumference of the two slide rods, and the compression spring is sleeved on the outer circumference of the front end of the slide rod.

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

[0017] A first card slot is opened at the lower part of the front side of the body, and the upper rear side of the camera abuts against the inside of the first card slot.

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

[0019] A radar is installed in the middle of the front side of the body.

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

[0021] Second card slots are opened on both the left and right sides of the upper part of the camera, and the tenons abut against the inside of the second card slots.

[0022] The present utility model has the following beneficial effects:

[0023] 1. In the present utility model, when the lower part of the drone is impacted, the first spring rod absorbs kinetic energy and drives the first connecting rod to shake. The first connecting rod pulls the second connecting rod to shake and enables the second spring rod on one side to absorb kinetic energy. The overall cooperation realizes buffering. The buffering component can absorb kinetic energy, achieve a good buffering effect, avoid damage to the drone due to impact, protect the drone and the carried equipment, and ensure the stable progress of the inspection work.

[0024] 2. In the present utility model, sliding the sliding button causes the sliding block to compress the compression spring and slide on the outer periphery of the sliding rod, driving the movement of the tenon to release the locking of the camera. Pushing forward can remove the camera. The disassembly component can facilitate the disassembly of the camera, achieve quick replacement and maintenance, avoid the difficulty of maintenance due to camera failure affecting the inspection work, and improve the efficiency and flexibility of the UAV inspection. Description of the Drawings

[0025] Figure 1 Fig. is a three-dimensional schematic diagram of a communication antenna inspection UAV with a buffer structure proposed by the present utility model;

[0026] Figure 2 Fig. is a structural schematic diagram of the first spring rod of a communication antenna inspection UAV with a buffer structure proposed by the present utility model;

[0027] Figure 3 Fig. is a structural schematic diagram of the fuselage of a communication antenna inspection UAV with a buffer structure proposed by the present utility model.

[0028] Legend:

[0029] 1. Fuselage; 2. Flashlight; 3. Propeller; 4. Radar; 5. Camera; 6. First spring rod; 7. First connecting rod; 8. Second connecting rod; 9. Landing gear; 10. Second spring rod; 11. Slide button; 12. Sliding block; 13. Sliding rod; 14. Compression spring; 15. Tenon; 16. First card slot; 17. Second card slot. Detailed Implementation Manner

[0030] Next, the technical solutions in the embodiments of the present utility model will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present utility model. Obviously, the described embodiments are only a part of the embodiments of the present utility model, rather than all the embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present utility model.

[0031] Refer to Figure 1 and Figure 2, an embodiment provided by the present utility model: A communication antenna inspection drone with a buffer structure, comprising a fuselage 1 made of fiberglass composite material, which has good insulation performance, can effectively prevent electromagnetic interference, and has a low cost. A plurality of evenly distributed propellers 3 are rotatably connected to the edge of the fuselage 1. The propellers 3 are made of nylon material and have good toughness. A camera 5 is installed at the lower part of the front side of the fuselage 1. The camera 5 is a panoramic model and can rotate for panoramic shooting. A disassembly component is arranged at the front side inside the fuselage 1, and the disassembly component is used for quickly disassembling the camera 5. Spring rods one 6 are fixedly connected to the left and right sides of the bottom of the fuselage 1. The spring rods one 6 are made of spring steel and are used to absorb kinetic energy for buffering when the lower part of the drone collides. Connecting rods one 7 are rotatably connected to the front and rear sides of the lower part of the spring rods one 6. The connecting rods one 7 are made of aluminum alloy. The connecting rods one 7 are used to disperse the kinetic energy to other components. Connecting rods two 8 are rotatably connected to the far sides of the two connecting rods one 7. The connecting rods two 8 are made of aluminum alloy. The connecting rods one 7 can pull the connecting rods two 8 to move. A spring rod two 10 is rotatably connected to the adjacent sides of the middle parts of the two connecting rods two 8. The spring rod two 10 is made of spring steel and is used to consume the impact kinetic energy. Landing gears 9 are rotatably connected to the lower parts of the two connecting rods two 8. The landing gears 9 are made of aluminum alloy and are used for preliminary buffering when landing. A flash lamp 2 is installed at the upper part of the front side of the fuselage 1. The flash lamp 2 is used for lighting when flying in a low-light environment. A radar 4 is installed at the middle part of the front side of the fuselage 1. The radar 4 is used for detecting obstacles and avoiding them when the drone is flying, and can detect and locate the communication antenna, helping the drone quickly and accurately find the target antenna. The buffer component can effectively absorb the impact force generated during the landing of the drone, reduce the force transmitted to the fuselage and internal equipment, and prevent the fuselage from deforming, damaging internal electronic components and precise sensors.

[0032] Refer to Figure 1 and Figure 3, The disassembly component includes a sliding block 12 made of engineering plastic, which is used to drive the disassembly component of the camera 5. The sliding block 12 is slidably connected to the front side inside the body 1. Compression springs 14 are installed on both the left and right sides inside the body 1. The compression springs 14 are made of spring steel and are used to squeeze and reset the sliding block 12. The rear sides of the compression springs 14 abut against the front side of the sliding block 12. Tenons 15 are installed on both the left and right sides of the lower part of the sliding block 12. The tenons 15 are made of engineering plastic and are used to fix the camera 5. The tenons 15 abut against the upper side inside of the camera 5. A sliding knob 11 is installed on the left side of the sliding block 12. The sliding knob 11 is used to control the operation of the disassembly component. Sliding the sliding knob 11 can drive the sliding block 12 to move. The sliding knob 11 slides on the left side of the body 1. Slide bars 13 are installed on both the left and right sides inside the body 1. The slide bars 13 are made of aluminum alloy and are used to assist in guiding the movement trajectory of the sliding block 12. The sliding block 12 slides on the outer periphery of the two slide bars 13. The compression spring 14 is sleeved on the front outer periphery of the slide bar 13. When the sliding block 12 slides, it will squeeze the compression spring 14. A first slot 16 is opened at the lower front side of the body 1. The upper rear side of the camera 5 abuts inside the first slot 16. The first slot 16 can assist in fixing the camera 5. Second slots 17 are opened on both the left and right sides of the upper part of the camera 5. The tenons 15 abut inside the second slots 17. The second slots 17 are used to cooperate with the tenons 15 to connect the body 1 and the camera 5. When a fault occurs in the camera 5, the disassembly component can enable the operator to quickly disassemble the camera 5 from the UAV for maintenance and replacement, shortening the troubleshooting time and improving the availability of the UAV.

[0033] Working principle: After the inspection UAV finishes its work, it needs to land and be prepared. When landing, an impact force will be generated when colliding with the ground. The impact force will be transmitted to the first spring rod 6 through the landing gear 9. The first spring rod 6 can initially absorb the impact force and drive the two first connecting rods 7 to move. The two first connecting rods 7 can pull the two second connecting rods 8 to move by shaking to disperse the impact force. When the two second connecting rods 8 move, the second spring rod 10 in the middle of them can absorb the impact force. Through the overall cooperation of the buffer component, the buffer work during the UAV landing is completed.

[0034] After the UAV lands, the camera 5 needs to be disassembled and sorted out. Sliding the sliding knob 11 can make the disassembly component work. The sliding knob 11 can drive the sliding block 12 to squeeze the compression spring 14 and slide on the outer periphery of the slide bar 13. The sliding block 12 can drive the two tenons 15 to slide to release the fixation of the camera 5. Pushing the camera 5 forward can unlock it from inside the first slot 16, thus completing the disassembly of the camera 5.

[0035] Finally, it should be noted that the above are only the preferred embodiments of the present utility model and are not used 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 perform equivalent replacements for some of the technical features. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present utility model shall be included within the protection scope of the present utility model.

Claims

1. A communication antenna inspection UAV with a buffer structure, comprising a fuselage (1), characterized in that: A plurality of evenly distributed propellers (3) are rotatably connected to the edge of the body (1). A camera (5) is installed at the lower front side of the body (1). A disassembly component is arranged at the front side inside the body (1), and the disassembly component is used to quickly disassemble the camera (5). Both the left and right sides of the bottom of the body (1) are fixedly connected with a first spring rod (6). The front and rear sides of the lower part of the first spring rod (6) are rotatably connected with a first connecting rod (7). The far sides of the two first connecting rods (7) are rotatably connected with a second connecting rod (8). The adjacent sides of the middle parts of the two second connecting rods (8) are rotatably connected with a second spring rod (10). The lower parts of the two second connecting rods (8) are rotatably connected with a landing gear (9).

2. The inspection UAV for a communication antenna with a buffer structure according to claim 1, characterized in that: The disassembly component includes a sliding block (12). The sliding block (12) is slidably connected to the front side inside the body (1). Compression springs (14) are installed on both the left and right sides inside the body (1). The rear sides of the compression springs (14) abut against the front side of the sliding block (12). Mortise joints (15) are installed on both the left and right sides of the lower part of the sliding block (12), and the mortise joints (15) abut against the upper inner side of the camera (5).

3. The inspection unmanned aerial vehicle for a communication antenna with a buffer structure according to claim 1, wherein: A flash (2) is installed at the upper front side of the body (1).

4. The inspection unmanned aerial vehicle for a communication antenna with a buffer structure according to claim 2, wherein: A sliding button (11) is installed on the left side of the sliding block (12), and the sliding button (11) slides on the left side of the body (1).

5. The inspection UAV for a communication antenna with a buffer structure according to claim 2, wherein: Slide rods (13) are installed on both the left and right sides inside the body (1). The sliding block (12) slides on the outer periphery of the two slide rods (13), and the compression spring (14) is sleeved on the outer periphery of the front end of the slide rod (13).

6. The inspection UAV for a communication antenna with a buffer structure according to claim 2, characterized in that: A first slot (16) is formed at the lower front side of the body (1), and the rear upper part of the camera (5) abuts against the inside of the first slot (16).

7. A communication antenna inspection drone with a buffer structure according to claim 1, characterized in that: A radar (4) is installed at the middle front side of the body (1).

8. The inspection unmanned aerial vehicle for a communication antenna with a buffer structure according to claim 2, characterized in that: Second slots (17) are formed on both the left and right sides of the upper part of the camera (5), and the mortise joints (15) abut against the inside of the second slots (17).

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