A detection device for unmanned aerial vehicle spare parts

Abstract

This utility model relates to the field of unmanned aerial vehicle (UAV) testing technology, and discloses a testing device for UAV parts, comprising: a UAV and a first interference device, including two electric cylinders, each positioned on the front and rear sides of the UAV, with a threaded rod on the side of each cylinder furthest from the other. A fixed frame is provided between the two electric cylinders; a second interference device, comprising a material stacking cylinder and a water storage cylinder, with a first side plate fixedly installed on the right wall of the fixed frame, the material stacking cylinder positioned above the first side plate, and a second side plate fixedly installed on the left wall of the fixed frame, the water storage cylinder positioned above the second side plate. The first interference device can be used to test the strength of the UAV's surface structure, the compressive strength of the UAV's shell, and the strength of the rotating blades, while the second interference device can be used to test the core strength of the UAV and to test the UAV under different environmental conditions.

Description

Technical Field

[0001] This utility model belongs to the field of drone testing technology, specifically, it relates to a testing device for drone parts. Background Technology

[0002] Unmanned aerial vehicles (UAVs), abbreviated as URMs, are devices operated using radio remote control equipment and their own program control devices, or autonomously operated completely or intermittently by an onboard computer. During the production and manufacturing process of UAVs, it is necessary to inspect the UAV components. However, in the process of testing existing technologies, the inventors discovered the following problems: In the process of inspecting components, existing technologies typically involve placing the components on a corresponding testing platform and inspecting them using various devices. However, this method cannot detect the components' performance in actual applications or provide a clear and intuitive understanding of the effects they can achieve. Therefore, existing technologies have certain drawbacks.

[0003] In view of this, this utility model is proposed. Utility Model Content

[0004] To solve the above-mentioned technical problems, the basic concept of the technical solution adopted by this utility model is as follows: A testing device for drone parts, comprising: The unmanned aerial vehicle (UAV) and a first jamming device are included. The jamming device comprises two electric cylinders, each positioned at the front and rear sides of the UAV. A threaded rod is located on the side of each electric cylinder furthest from the other. A fixed frame is positioned between the two electric cylinders, and multiple first support rods are fixedly mounted on the bottom wall of the fixed frame. The second interference device includes a material stacking cylinder and a water storage cylinder. A first side plate is fixedly installed on the right side wall of the fixed frame, with the material stacking cylinder located above the first side plate. A second side plate is fixedly installed on the left side wall of the fixed frame, with the water storage cylinder located above the second side plate. A second left side rod is fixedly installed on the bottom wall of both the first and second side plates.

[0005] In a preferred embodiment of the present invention, a second through hole is provided on both the front and rear side walls of the fixed frame, a first through hole is provided on both the left and right side walls of the fixed frame, a side frame is fixedly installed on both the front and rear side walls of the fixed frame, and a sealing plate is fixedly installed on the side wall of the two side frames that are far apart from each other.

[0006] In a preferred embodiment of this utility model, a limiting groove is provided on the side wall of the side frame, the side wall of the sealing plate near the side frame is hollowed out, and a first motor is fixedly installed on the side wall of the cavity of the sealing plate, and the threaded rod is fixedly connected to the output end of the first motor.

[0007] In a preferred embodiment of this utility model, the other end of the threaded rod is rotatably connected to the other side wall of the cavity of the sealing plate, one end of the electric cylinder is located in the cavity of the sealing plate, the threaded rod passes through the electric cylinder and is threadedly connected to the through point of the electric cylinder, the movable end of the electric cylinder passes through the limiting groove and the second through hole and is movably connected to the through point of the limiting groove and the second through hole, and a soft pad is fixedly installed on the movable end of the electric cylinder.

[0008] In a preferred embodiment of this utility model, both the left and right side walls of the first side plate are hollowed out, and a pump body is fixedly installed on the top wall of both the first and second side plates. The material stacking cylinder and the water storage cylinder are fixedly connected to the corresponding pump body.

[0009] In a preferred embodiment of the present invention, an air inlet duct is fixedly installed on the right side wall of the first side plate, and the air inlet duct is connected to the cavity of the first side plate. A ventilation plate is fixedly installed on the right side wall of the cavity of the air inlet duct, and a second motor is fixedly installed on the left side wall of the ventilation plate. A fan is fixedly installed at the output end of the second motor.

[0010] In a preferred embodiment of the present invention, a plurality of drip nozzles are fixedly installed at equal intervals on the right side wall of the second side plate. The drip nozzles are interconnected with the cavity of the second side plate. The ends of the first side plate and the second side plate that are close to each other are fixedly connected to the inner side wall of the cavity of the first perforation.

[0011] Compared with the prior art, the present invention has the following advantages: 1. In summary, by setting up a first interference device and a second interference device, the strength of the surface structure of the UAV can be detected by the first interference device, the compressive strength of the UAV shell and the strength of the rotating blades can be tested, and the core strength of the UAV can be detected by the second interference device, and whether the drive device for the flight stability of the UAV is qualified under different environments can be tested.

[0012] 2. In summary, by setting up a drone, an electric cylinder, a first support rod, a side frame, a sealing plate, a second perforation, a first motor, a threaded rod, a soft pad, and a limiting groove, the rotation of the output end of the first motor and the drive of the moving end of the electric cylinder can move the soft pad, which in turn moves and squeezes the drone to test the strength of the drone's shell and the stability of its blades.

[0013] 3. In summary, by setting up a drone, a first side plate, a second side plate, a material stacking cylinder, a water storage cylinder, a second left side rod, a pump body, a fan, a second motor, an air inlet duct, and a drip nozzle, the pump body can control the material in the material stacking cylinder and the water storage cylinder to spray onto the drone, thereby creating different environments to interfere with the drone and thus testing the functionality of the drone's core structure under different environments.

[0014] The specific embodiments of this utility model will be described in further detail below with reference to the accompanying drawings. Attached Figure Description

[0015] In the attached diagram: Figure 1 This is a perspective view of the present utility model; Figure 2 This is a perspective view of one side of the first interference device of this utility model; Figure 3 This is a perspective view of the other side of the first interference device of this utility model; Figure 4 This is a perspective view of one side of the second interference device of this utility model; Figure 5 This is a perspective view of the other side of the second interference device of this utility model.

[0016] In the diagram: 10. Drone; 11. Fixed frame; 12. Electric cylinder; 13. First side plate; 14. Second side plate; 15. Stacking cylinder; 16. Water storage cylinder; 17. First support rod; 18. Second left side rod; 19. Side frame; 20. Sealing plate; 21. First perforation; 22. Second perforation; 23. First motor; 24. Threaded rod; 25. Soft pad; 26. Limiting groove; 27. Pump body; 28. Fan; 29. ​​Second motor; 30. Ventilation plate; 31. Air inlet duct; 32. Drip nozzle. Detailed Implementation

[0017] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the technical solutions in the embodiments will be clearly and completely described below with reference to the accompanying drawings. The following embodiments are used to illustrate this utility model.

[0018] like Figure 1 As shown, a testing device for drone parts includes: The unmanned aerial vehicle (UAV) 10 and a first jamming device are included. The jamming device includes two electric cylinders 12, which are located on the front and rear sides of the UAV 10. A threaded rod 24 is provided on the side of the two electric cylinders 12 that is far apart from each other. A fixed frame 11 is provided between the two electric cylinders 12, and multiple first support rods 17 are fixedly installed on the bottom wall of the fixed frame 11. The second interference device includes a material stacking cylinder 15 and a water storage cylinder 16. A first side plate 13 is fixedly installed on the right side wall of the fixed frame 11, and the material stacking cylinder 15 is located above the first side plate 13. A second side plate 14 is fixedly installed on the left side wall of the fixed frame 11, and the water storage cylinder 16 is located above the second side plate 14. A second left side rod 18 is fixedly installed on the bottom wall of both the first side plate 13 and the second side plate 14.

[0019] In practical use, the first interference device can interfere with and squeeze the drone 10 by extending and retracting the movable end of the electric cylinder 12 and driving the threaded rod 24 to test the drone 10's resistance to compression and resistance to external interference. The second interference device can continuously spray objects from the material stacking cylinder 15 and the water storage cylinder 16 into the drone 10 to simulate the drone 10's practicality in different environments.

[0020] It is worth noting that unmanned machinery, abbreviated as "drone" or "URM," is a device operated using radio remote control equipment and its own program control device, or operated autonomously, either completely or intermittently, by an onboard computer. Drone 10 is existing technology and will not be elaborated upon here.

[0021] In summary, by setting up a first interference device and a second interference device, the strength of the surface structure of the UAV 10 can be detected by the first interference device, the compressive strength of the UAV 10 shell and the strength of the rotating blades can be tested, and the core strength of the UAV 10 can be detected by the second interference device, and whether the drive device for the flight stability of the UAV 10 is qualified under different environments can be tested.

[0022] like Figure 1 , Figure 2 and Figure 3 As shown, a second through hole 22 is provided on both the front and rear side walls of the fixed frame 11, a first through hole 21 is provided on both the left and right side walls of the fixed frame 11, a side frame 19 is fixedly installed on both the front and rear side walls of the fixed frame 11, and a sealing plate 20 is fixedly installed on the side wall of the two side frames 19 that are far apart from each other.

[0023] A limiting groove 26 is provided on the side wall of the side frame 19. The side wall of the sealing plate 20 near the side frame 19 is hollow. A first motor 23 is fixedly installed on the side wall of the cavity of the sealing plate 20. The threaded rod 24 is fixedly connected to the output end of the first motor 23.

[0024] The other end of the threaded rod 24 is rotatably connected to the other side wall of the cavity of the sealing plate 20. One end of the electric cylinder 12 is located inside the cavity of the sealing plate 20. The threaded rod 24 passes through the electric cylinder 12 and is threadedly connected to the through-hole of the electric cylinder 12. The movable end of the electric cylinder 12 passes through the limiting groove 26 and the second through hole 22 and is movably connected to the through-hole of the limiting groove 26 and the second through hole 22. A soft pad 25 is fixedly installed on the movable end of the electric cylinder 12. Both the first motor 23 and the electric cylinder 12 are electrically connected to the power supply and the switch.

[0025] In practical use, when the output end of the first motor 23 rotates, it can drive the electric cylinder 12 to move. The electric cylinder 12 cannot rotate due to the limit in the cavity of the sealing plate 20. The electric cylinder 12 moves through the threaded connection with the threaded rod 24. The left and right movement of the electric cylinder 12, together with the extension and retraction of its movable end, drives the soft pad 25 to move. The soft pad 25 continuously moves the drone 10. The electric cylinder 12 increases its left and right movement stability through the connection with the limiting groove 26 and the second through hole 22. The side frame 19 can limit the electric cylinder 12 through the limiting groove 26 and can also seal the sealing plate 20. The first support rod 17 can provide support.

[0026] In summary, by setting up the drone 10, electric cylinder 12, first support rod 17, side frame 19, sealing plate 20, second perforation 22, first motor 23, threaded rod 24, soft pad 25 and limiting groove 26, the rotation of the output end of the first motor 23 and the drive of the moving end of the electric cylinder 12 can drive the soft pad 25 to move. The soft pad 25 can then be used to pry and squeeze the drone 10, thereby testing the shell strength and blade stability of the drone 10.

[0027] like Figure 1 , Figure 4 and Figure 5 As shown, both the left and right side walls of the first side plate 13 are hollowed out. A pump body 27 is fixedly installed on the top wall of the first side plate 13 and the second side plate 14. The material stacking cylinder 15 and the water storage cylinder 16 are fixedly connected to the corresponding pump body 27.

[0028] An air inlet duct 31 is fixedly installed on the right side wall of the first side plate 13. The air inlet duct 31 is connected to the cavity of the first side plate 13. A ventilation plate 30 is fixedly installed on the right side wall of the cavity of the air inlet duct 31. A second motor 29 is fixedly installed on the left side wall of the ventilation plate 30. A fan 28 is fixedly installed at the output end of the second motor 29.

[0029] Multiple drip nozzles 32 are fixedly installed at equal intervals on the right side wall of the second side plate 14. The drip nozzles 32 are interconnected with the cavity of the second side plate 14. The ends of the first side plate 13 and the second side plate 14 that are close to each other are fixedly connected to the inner side wall of the cavity of the first through hole 21.

[0030] In practical use, when the output end of the second motor 29 rotates, it can drive the fan 28 to rotate. The rotation of the fan 28 can draw in wind energy from the right side of the air inlet duct 31. The drawn-in wind energy is sprayed out from the left side of the first side plate 13. With the opening and closing of the pump body 27, materials such as sand and gravel in the stacking cylinder 15 cavity are sprayed out from the left side of the first side plate 13 along with the wind energy, interfering with the flying drone 10. When the pump body 27 on the second side plate 14 is turned on, water in the water storage tank 16 cavity can flow into the cavity of the second side plate 14. Through pressure, the water in the cavity of the second side plate 14 cavity is sprayed out from the drip nozzle 32, spraying out in the shape of water droplets, thereby interfering with the flying drone 10. This is to test the functionality of the core structure of the drone 10 in different environments. The second left side rod 18 can play a limiting support role for the first side plate 13 and the second side plate 14.

[0031] In summary, by setting up the drone 10, the first side plate 13, the second side plate 14, the material stacking cylinder 15, the water storage cylinder 16, the second left side rod 18, the pump body 27, the fan 28, the second motor 29, the air inlet duct 31, and the drip nozzle 32, the pump body 27 can control the material in the chambers of the material stacking cylinder 15 and the water storage cylinder 16 to spray onto the drone 10, thereby creating different environments to interfere with the drone 10, and thus testing the functionality of the core structure of the drone 10 under different environments.

[0032] It is understood that this utility model has been described through some embodiments, and those skilled in the art will recognize that various changes or equivalent substitutions can be made to these features and embodiments without departing from the spirit and scope of this utility model. Furthermore, under the teachings of this utility model, these features and embodiments can be modified to adapt to specific situations and materials without departing from the spirit and scope of this utility model. Therefore, this utility model is not limited to the specific embodiments disclosed herein, and all embodiments falling within the scope of the claims of this application are within the protection scope of this utility model.

Claims

1. A testing device for unmanned aerial vehicle (UAV) parts, characterized in that, include: The unmanned aerial vehicle (10) and the first jamming device include two electric cylinders (12), both electric cylinders (12) are located at the front and rear sides of the unmanned aerial vehicle (10), and each of the two electric cylinders (12) is provided with a threaded rod (24) at the side of the two electric cylinders (12) that is far away from each other. A fixed frame (11) is provided between the two electric cylinders (12), and multiple first support rods (17) are fixedly installed on the bottom wall of the fixed frame (11). The second interference device includes a stacking cylinder (15) and a water storage cylinder (16). A first side plate (13) is fixedly installed on the right side wall of the fixed frame (11). The stacking cylinder (15) is located above the first side plate (13). A second side plate (14) is fixedly installed on the left side wall of the fixed frame (11). The water storage cylinder (16) is located above the second side plate (14). A second left side rod (18) is fixedly installed on the bottom wall of both the first side plate (13) and the second side plate (14).

2. The drone spare part detection device of claim 1, wherein, A second through hole (22) is provided on both the front and rear side walls of the fixed frame (11), a first through hole (21) is provided on both the left and right side walls of the fixed frame (11), a side frame (19) is fixedly installed on both the front and rear side walls of the fixed frame (11), and a sealing plate (20) is fixedly installed on the side wall of the two side frames (19) that are far apart from each other.

3. The testing equipment for UAV parts according to claim 2, characterized in that, A limiting groove (26) is provided on the side wall of the side frame (19). The side wall of the sealing plate (20) near the side frame (19) is hollow. A first motor (23) is fixedly installed on the side wall of the cavity of the sealing plate (20). The threaded rod (24) is fixedly connected to the output end of the first motor (23).

4. The testing equipment for UAV parts according to claim 3, characterized in that, The other end of the threaded rod (24) is rotatably connected to the other side wall of the cavity of the sealing plate (20). One end of the electric cylinder (12) is located in the cavity of the sealing plate (20). The threaded rod (24) passes through the electric cylinder (12) and is threadedly connected to the through point of the electric cylinder (12). The movable end of the electric cylinder (12) passes through the limiting groove (26) and the second through hole (22) and is movably connected to the through point of the limiting groove (26) and the second through hole (22). A soft pad (25) is fixedly installed on the movable end of the electric cylinder (12).

5. The testing equipment for UAV parts according to claim 1, characterized in that, The left and right side walls of the first side plate (13) are hollowed out. A pump body (27) is fixedly installed on the top wall of the first side plate (13) and the second side plate (14). The stacking cylinder (15) and the water storage cylinder (16) are fixedly connected to the corresponding pump body (27).

6. The testing equipment for UAV parts according to claim 5, characterized in that, An air inlet duct (31) is fixedly installed on the right side wall of the first side plate (13). The air inlet duct (31) is connected to the cavity of the first side plate (13). A ventilation plate (30) is fixedly installed on the right side wall of the cavity of the air inlet duct (31). A second motor (29) is fixedly installed on the left side wall of the ventilation plate (30). A fan (28) is fixedly installed at the output end of the second motor (29).

7. The testing equipment for UAV parts according to claim 6, characterized in that, Multiple drip nozzles (32) are fixedly installed at equal intervals on the right side wall of the second side plate (14). The drip nozzles (32) are connected to the cavity of the second side plate (14). The ends of the first side plate (13) and the second side plate (14) that are close to each other are fixedly connected to the inner side wall of the cavity of the first perforation (21).

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