An unmanned aerial vehicle detection device for steel structures
Patent Information
- Application Number
- CN202522227735.4
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-10-22
- Publication Date
- 2026-09-25
- Estimated Expiration
- 2035-10-22
AI Technical Summary
[0002]在利用无人机上的检测装置对钢结构进行近距离检测时，为确保检测精度与稳定性，通常需要其降落在安装于钢结构上的专用检测平台，然而由于检测装置较重，导致无人机降落瞬间产生的冲击动能，易对机载精密传感器及平台自身造成损害，同时引发的平台振动也破坏了初始检测阶段的稳定性，影响了检测数据的质量，为缓解此问题，现有技术多在检测平台着陆区设置简单的缓冲结构，如加装橡胶垫或采用单一弹簧作为缓冲元件，借助材料的弹性形变来吸收部分冲击能量，然而这类方案存在固有缺陷，其一，纯弹性缓冲在吸收能量后会产生迅速的回弹与往复振荡，无法使平台快速归于稳定，与降落后需立即提供稳固基准的要求相悖，其二，其缓冲过程缺乏有效的能量耗散机制，对冲击能量的吸收与平抑能力有限
本实用新型通过检测台与缓冲组件的设置，在无人机降落时，其冲击动能可驱动降落板压缩第一弹簧，从而将冲击力高效转化为弹簧的弹性势能，实现平稳缓冲，此过程能有效衰减无人机及检测装置所承受的瞬时冲击，极大提升了降落安全性，缓冲结束后，装置能迅速锁定，为后续检测任务提供一个稳定的刚性平台。
Smart Images
Figure CN224797245U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) inspection technology, and in particular to a UAV inspection device for steel structures. Background Technology
[0002] When using drones to conduct close-range inspections of steel structures, to ensure inspection accuracy and stability, the drone typically needs to land on a dedicated inspection platform mounted on the steel structure. However, due to the weight of the inspection device, the impact kinetic energy generated during the drone's landing can easily damage the onboard precision sensors and the platform itself. Simultaneously, the resulting platform vibration disrupts the stability of the initial inspection phase, affecting the quality of the inspection data. To mitigate this problem, existing technologies often incorporate simple buffer structures in the landing area of the inspection platform, such as adding rubber pads or using a single spring as a buffer element, relying on the elastic deformation of the material to absorb some of the impact energy. However, these solutions have inherent drawbacks. First, purely elastic buffers will rapidly rebound and oscillate after absorbing energy, failing to quickly stabilize the platform, contradicting the requirement to provide a stable reference point immediately after landing. Second, the buffering process lacks an effective energy dissipation mechanism, limiting its ability to absorb and mitigate impact energy. Utility Model Content
[0003] In order to overcome the shortcomings of the existing technology, this utility model provides a UAV inspection device for steel structures.
[0004] To solve the above-mentioned technical problems, this utility model provides the following technical solution: a UAV inspection device for steel structures, including an inspection platform, on the surface of the inspection platform a UAV is placed, and an inspection device is fixedly connected to the surface of the UAV. A buffer assembly is provided inside the inspection platform, the buffer assembly including a device groove, the device groove being opened inside the inspection platform, a first spring being fixedly connected to the bottom of the device groove, a landing plate being fixedly connected to the top of the first spring, a first sliding groove being opened on both sides of the inner cavity of the device groove, a limit groove being opened inside the first sliding groove, a compression groove being opened on both sides of the landing plate, a second spring being fixedly connected inside the compression groove, and a limit block cooperating with the limit groove being fixedly connected to the end of the second spring away from the compression groove.
[0005] As a preferred technical solution of this utility model, an ejection device is installed inside the device slot. The ejection device includes a threaded barrel, which is rotatably connected to the bottom of the device slot. The bottom of the threaded barrel passes through the detection table and extends to the outside of the detection table. A threaded rod is threadedly connected inside the threaded barrel. An ejection groove is opened inside the threaded rod. A second sliding groove is opened on both sides of the inner cavity of the ejection groove. A second slider is slidably connected inside the second sliding groove.
[0006] As a preferred embodiment of this utility model, an extension rod is fixedly connected to one side of the two second sliders that are close to each other. The end of the extension rod near the landing plate is fixedly connected to the landing plate. A third spring is fixedly connected to the bottom of the ejection groove cavity. The side of the third spring near the extension rod is fixedly connected to the extension rod.
[0007] As a preferred technical solution of this utility model, a guide assembly is provided inside the device slot. The guide assembly includes guide rods, two of which are fixedly connected to the bottom of the device slot. A guide sleeve is fitted onto the surface of the guide rod, and the end of the guide sleeve near the landing plate is fixedly connected to the landing plate.
[0008] As a preferred embodiment of the present invention, the surface of the detection platform is provided with a detection component, which includes a sensor, and the sensor is fixedly connected to the surface of the detection platform.
[0009] Compared with the prior art, the beneficial effects that this utility model can achieve are: This invention, through the setup of a testing platform and a buffer assembly, allows the impact kinetic energy of the UAV during landing to drive the landing plate to compress the first spring, thereby efficiently converting the impact force into the elastic potential energy of the spring and achieving smooth buffering. This process effectively attenuates the instantaneous impact borne by the UAV and the testing device, greatly improving landing safety. After the buffering is completed, the device can quickly lock, providing a stable rigid platform for subsequent testing tasks.
[0010] This invention achieves active control of the buffering process through the setting of a testing platform, landing plate, and ejection assembly. By rotating the threaded barrel to precisely adjust the extension height of the threaded rod, the third spring is pre-compressed, and its supporting force on the extension rod and landing plate can be set. This design makes the third spring and the first spring form a cooperative buffering system, which can effectively suppress the rapid rebound that the first spring may experience after absorbing a large impact. This fundamentally avoids the risk of the UAV being bounced up or even overturned due to violent platform vibration, ensuring the safety and stability of the takeoff process. Attached Figure Description
[0011] Figure 1 This is a schematic diagram of the structure of the UAV of this utility model; Figure 2 This is a schematic diagram of the structure of the testing station of this utility model; Figure 3 This is a schematic diagram of the structure of the device groove of this utility model; Figure 4 This utility model Figure 2 Schematic diagram of the structure at point A; Figure 5 This is a schematic diagram of the structure of the first slide groove of this utility model; Figure 6This is a schematic diagram of the structure of the second slide groove of this utility model; Figure 7 This is a top view of the structure of the UAV of this utility model.
[0012] Among them: 1. Testing station; 11. Unmanned aerial vehicle (UAV); 12. Testing device; Device groove; 21. First spring; 22. Drop plate; 23. First slide groove; 24. Limiting groove; 25. Extrusion groove; 26. Second spring; 27. Limiting block; 31. Threaded barrel; 32. Threaded rod; 33. Ejector groove; 34. Second slide; 35. Second slider; 36. Extension rod; 37. Third spring; Guide rod; 41. Guide sleeve; 50. Sensors. Detailed Implementation
[0013] To make the technical means, creative features, and achieved objectives and effects of this utility model easier to understand, the present utility model is further described below with reference to specific embodiments. However, the following embodiments are merely preferred embodiments of this utility model and not all of them. Other embodiments obtained by those skilled in the art based on the embodiments described herein without creative effort are all within the protection scope of this utility model. Unless otherwise specified, the experimental methods in the following embodiments are conventional methods, and the materials and reagents used in the following embodiments are commercially available unless otherwise specified.
[0014] Example: Figure 1 , Figure 2 , Figure 3 , Figure 4 and Figure 5As shown, a UAV inspection device for steel structures includes an inspection platform 1. A UAV 11 is placed on the surface of the inspection platform 1, and an inspection device 12 is fixedly connected to the surface of the UAV 11. A buffer assembly is provided inside the inspection platform 1, including a device groove 20. The device groove 20 is located inside the inspection platform 1. A first spring 21 is fixedly connected to the bottom of the device groove 20, and a landing plate 22 is fixedly connected to the top of the first spring 21. First sliding grooves 23 are formed on both sides of the inner cavity of the device groove 20, and limiting grooves 24 are formed inside the first sliding grooves 23. Extrusion grooves 25 are formed on both sides of the landing plate 22, and a second spring 26 is fixedly connected inside the extrusion grooves 25. A limiting block 27, which cooperates with the limiting groove 24, is fixedly connected to the end of the second spring 26 away from the extrusion groove 25. The inspection device includes the device groove and an inspection device, which is placed on top of the UAV. When inspecting steel structures, the control unit plans the flight path of the UAV according to the preset inspection path and drives the flight platform to carry the inspection unit to the area above or in front of the steel structure to be inspected. Then, the attitude adjustment mechanism adjusts the orientation and angle of the high-definition optical camera and thermal imaging sensor to face the part to be inspected. The high-definition optical camera continuously or fixedly photographs the surface of the steel structure to capture the appearance state image in the visible light range, which is used to identify coating damage, corrosion or macro cracks. At the same time, the thermal imaging sensor simultaneously collects infrared thermal images of the surface of the steel structure. By analyzing the abnormal temperature field distribution, it helps to identify internal defects or insulation layer damage. The control unit coordinates the movement of the flight platform and the data acquisition of the sensors to ensure full coverage of the target area. The acquired images and sensor data are transmitted to the ground station or stored in the airborne storage unit in real time for subsequent analysis and generation of inspection reports.
[0015] refer to Figure 1 , Figure 2 , Figure 3 , Figure 4 and Figure 5 As shown, after the test is completed, the UAV 11 lands on the landing plate 22 and impacts the landing plate 22. Subsequently, the landing plate 22 descends due to the impact and compresses the first spring 21. As the landing plate 22 descends and compresses the limiting block 27, the limiting block 27 compresses the second spring 26, squeezing the limiting block 27 from inside the limiting groove 24 into the extrusion groove 25. Then, the landing plate 22 continues to descend through the cooperation of the first sliding groove 23 and the limiting block 27, compressing the first spring 21.
[0016] refer to Figure 2 , Figure 4 , Figure 5 and Figure 6As shown, an ejection device is installed inside the device slot 20. The ejection device includes a threaded barrel 30, which is rotatably connected to the bottom of the device slot 20. The bottom of the threaded barrel 30 penetrates the detection table 1 and extends to the outside of the detection table 1. A threaded rod 31 is threadedly connected inside the threaded barrel 30. An ejection groove 32 is formed inside the threaded rod 31. A second sliding groove 33 is formed on both sides of the inner cavity of the ejection groove 32. A second slider 34 is slidably connected inside the second sliding groove 33. The two second sliders 34 are fixedly connected to each other on their adjacent sides. An extension rod 35 is fixedly connected to the landing plate 22 at one end. A third spring 36 is fixedly connected to the bottom of the inner cavity of the ejector slot 32. The third spring 36 is fixedly connected to the extension rod 35 at one side. A guide assembly is provided inside the device slot 20. The guide assembly includes guide rods 40. Two guide rods 40 are fixedly connected to the bottom of the device slot 20. A guide sleeve 41 is sleeved on the surface of the guide rods 40. The guide sleeve 41 is fixedly connected to the landing plate 22 at one end.
[0017] refer to Figure 2 , Figure 4 , Figure 5 and Figure 6 As shown, the landing plate 22 descends, causing the guide sleeve 41 to slide on the guide rod 40, preventing the landing plate 22 from being impacted and compressing the first spring 21, thus avoiding wobbling. Simultaneously, when the buffer level needs adjustment, the operator rotates the threaded barrel 30, causing the threaded rod 31 to rise or fall. When the landing plate 22 returns to its original position, the extension rod 35 is pushed by the third spring 36, causing the extension rod 35 to engage with the second slide groove 33 and the second slider 34, thus pushing the landing plate 22 and preventing the drone 11 on the landing plate 22 from falling due to a sudden release of pressure from the first spring 21. refer to Figure 2 and Figure 7 As shown, a detection assembly is provided on the surface of the detection stage 1. The detection assembly includes a sensor 50, which is fixedly connected to the surface of the detection stage 1.
[0018] refer to Figure 2 and Figure 7 As shown, the staff placed the drone 11 on the landing plate 22. Then, the sensor 50 detected that it needed to be inspected, and the drone 11 took off and inspected the steel structure through the inspection device 12.
[0019] Working principle: Before use: Refer to Figure 1 , Figure 2 and Figure 7As shown, the staff places the drone 11 on the landing plate 22. When the sensor 50 detects that inspection is required, the drone 11 takes off and inspects the steel structure through the inspection device 12. During the inspection of the steel structure, the control unit plans the flight path of the drone according to the preset inspection path and drives the flight platform to carry the inspection unit to the area above or in front of the steel structure to be inspected. Then, the attitude adjustment mechanism adjusts the orientation and angle of the high-definition optical camera and thermal imaging sensor to make them face the part to be inspected. The high-definition optical camera continuously or fixedly photographs the surface of the steel structure to capture the appearance state image in the visible light range, which is used to identify coating damage, corrosion or macro cracks. At the same time, the thermal imaging sensor simultaneously collects infrared thermal images of the surface of the steel structure. By analyzing the abnormal temperature field distribution, it helps to identify internal defects or insulation layer damage. The control unit coordinates the movement of the flight platform and the data collection of the sensors to ensure full coverage of the target area. The collected images and sensor data are transmitted to the ground station or stored in the airborne storage unit in real time for subsequent analysis and generation of inspection reports.
[0020] When using: Refer to Figure 2 , Figure 3 , Figure 4 , Figure 5 and Figure 6 As shown, after the test is completed, the drone 11 lands on the landing plate 22, impacting the landing plate 22. Subsequently, the landing plate 22 descends due to the impact, compressing the first spring 21. As the landing plate 22 descends, it compresses the limiting block 27, causing the limiting block 27 to compress the second spring 26, pushing the limiting block 27 from inside the limiting groove 24 into the compression groove 25. Then, the landing plate 22 continues to descend through the cooperation of the first sliding groove 23 and the limiting block 27, compressing the first spring 21. At the same time, the descent of the landing plate 22 causes the guide sleeve 41 to slide on the guide rod 40, preventing the landing plate 22 from shaking due to the impact compressing the first spring 21. When it is necessary to adjust the buffer level, the operator rotates the threaded barrel 30, causing the threaded rod 31 to rise or fall. When the landing plate 22 returns to its original position, the extension rod 35 is pushed by the third spring 36, causing the extension rod 35 to push the landing plate 22 through the cooperation of the second sliding groove 33 and the second slider 34, preventing the drone 11 from falling off the landing plate 22 due to the sudden release of pressure from the first spring 21.
[0021] The embodiments of the present invention have been described in detail above with reference to the accompanying drawings. However, the present invention is not limited thereto. Various changes can be made within the scope of knowledge possessed by those skilled in the art without departing from the spirit of the present invention.
Claims
1. A UAV inspection device for steel structures, comprising an inspection platform (1), characterized in that, A drone (11) is placed on the surface of the testing station (1), and a testing device (12) is fixedly connected to the surface of the drone (11). The testing platform (1) is equipped with a buffer assembly, which includes a device slot (20). The device slot (20) is located inside the testing platform (1). A first spring (21) is fixedly connected to the bottom of the device slot (20), and a drop plate (22) is fixedly connected to the top of the first spring (21). The device groove (20) has a first sliding groove (23) on both sides of the inner cavity. The first sliding groove (23) has a limit groove (24) inside. The dropping plate (22) has a pressing groove (25) on both sides. The pressing groove (25) has a second spring (26) fixedly connected inside. The end of the second spring (26) away from the pressing groove (25) is fixedly connected to a limit block (27) that cooperates with the limit groove (24).
2. The UAV inspection device for steel structures according to claim 1, characterized in that, An ejection device is installed inside the device slot (20). The ejection device includes a threaded barrel (30). The threaded barrel (30) is rotatably connected to the bottom of the device slot (20). The bottom of the threaded barrel (30) penetrates the detection table (1) and extends to the outside of the detection table (1). The threaded barrel (30) is internally threaded with a threaded rod (31), and the threaded rod (31) is internally provided with a top groove (32). The top groove (32) is provided with a second sliding groove (33) on both sides of its inner cavity, and a second slider (34) is slidably connected inside the second sliding groove (33).
3. The UAV inspection device for steel structures according to claim 2, characterized in that, An extension rod (35) is fixedly connected to one side of the two second sliders (34), and the end of the extension rod (35) near the landing plate (22) is fixedly connected to the landing plate (22).
4. The UAV inspection device for steel structures according to claim 2, characterized in that, A third spring (36) is fixedly connected to the bottom of the inner cavity of the ejector groove (32), and the third spring (36) is fixedly connected to the extension rod (35) on the side near the extension rod (35).
5. The UAV inspection device for steel structures according to claim 1, characterized in that, The device slot (20) is provided with a guide assembly, which includes guide rods (40). Two guide rods (40) are fixedly connected to the bottom of the device slot (20). A guide sleeve (41) is sleeved on the surface of the guide rods (40). The end of the guide sleeve (41) near the landing plate (22) is fixedly connected to the landing plate (22).
6. The UAV inspection device for steel structures according to claim 1, characterized in that, The surface of the testing station (1) is provided with a testing component, which includes a sensor (50) and the sensor (50) is fixedly connected to the surface of the testing station (1).