A kind of unmanned aerial vehicle carbon tube strength detection device

Abstract

The utility model discloses a kind of unmanned vehicle carbon tube strength detection devices, belong to unmanned vehicle detection technical field, including rack, detection mechanism and detection table, the rack is movably provided with the detection mechanism for carrying out strength detection to carbon tube, the detection table is set in the rack below, the detection table is provided with the limiting assembly for limiting carbon tube;The upper surface of the rack is provided with electric slide rail, the detection mechanism includes press and strength detection component, the press and the strength detection component are slidably arranged on the electric slide rail by moving plate, the moving plate is slidably connected with the electric slide rail, and one side of the moving plate is suspended outside the electric slide rail, the utility model is detected by being arranged mechanism, so that unmanned vehicle carbon tube hot melt joint part can be detected for strength, prevent carbon tube strength is not enough and cause unmanned vehicle flight time machine arm to break and cause crash.

Description

Technical Field

[0001] This utility model relates to the field of drone testing technology, and in particular to a device for testing the strength of carbon fiber tubes in drones. Background Technology

[0002] The arms of drones typically use carbon fiber tubing (referred to as carbon tubing) as the main structural component. The consistency of its length and the strength of its connections directly affect the drone's flight balance and safety. Currently, the following problems exist in the incoming inspection process of carbon tubing: the heat-fused joints of the carbon tubing may have internal weaknesses due to insufficient strength. Existing processes can only visually inspect for surface defects such as cracks, and cannot effectively test the internal structural strength. If substandard carbon tubing is installed and used, the arm is prone to breakage during flight, causing a crash.

[0003] Therefore, a carbon nanotube testing device capable of reliable strength testing is needed to meet the requirements of incoming carbon nanotube quality control. Utility Model Content

[0004] In order to solve the above-mentioned technical problems, this utility model provides a device for testing the strength of carbon tubes in unmanned aerial vehicles (UAVs).

[0005] The technical solution of this utility model is implemented as follows:

[0006] A carbon fiber tube strength testing device for unmanned aerial vehicles (UAVs) includes a frame, a testing mechanism, and a testing platform. The testing mechanism for testing the strength of carbon fiber tubes is movably mounted on the frame. The testing platform is located below the frame and is equipped with a limiting component for limiting the movement of the carbon fiber tubes.

[0007] Preferably, the upper surface of the frame is provided with an electric slide rail, and the testing mechanism includes a press and a strength testing component. The press and the strength testing component are slidably mounted on the electric slide rail via a movable plate. The movable plate is slidably connected to the electric slide rail, and one side of the movable plate is suspended outside the electric slide rail.

[0008] Preferably, the press is fixedly mounted on the upper surface of the suspended side of the moving plate, the strength detection component is mounted on the lower surface of the suspended side of the moving plate, the output end of the press is fixedly connected to the strength detection component, and a cylinder for driving the press is provided on one side of the press.

[0009] Preferably, the strength testing component includes a telescopic part and a testing head. The testing head is movably mounted on both sides below the moving plate via positioning shafts. The telescopic part is disposed between the testing head and the moving plate, with one end of the telescopic part connected to the output end of the press and the other end of the telescopic part fixedly connected to the testing head.

[0010] Preferably, there are two positioning shafts, which are respectively movably inserted through both sides of the movable plate, and move up and down with the telescopic part under the drive of the press output end.

[0011] Preferably, the limiting component includes a first limiting member, a second limiting member, and a third limiting member. The first limiting member is disposed on one side of the detection stage and is used to limit the position of the head of the carbon nanotube. The second limiting member is disposed on the other side of the detection stage and is used to fix the tail of the carbon nanotube. The third limiting member is disposed between the first limiting member and the second limiting member and is close to the first limiting member, and is used to fix the head of the carbon nanotube.

[0012] Preferably, the side of the testing station is also provided with a clamping assembly for fixing the carbon nanotube body.

[0013] Preferably, a length detection element is movably disposed on the lower surface of the cylinder, and a displacement sensor is disposed on one side of the cylinder for cooperating with the length detection element to detect the length of the carbon tube.

[0014] Compared with the prior art, the beneficial effects of this utility model are as follows:

[0015] This invention provides a device for testing the strength of carbon fiber tubes in unmanned aerial vehicles (UAVs). The device uses a testing mechanism to drive a press to descend via a cylinder, which in turn lowers the testing head to contact the carbon fiber tube placed on the testing platform and apply pressure to it. This allows for strength testing of the heat-fused joint of the carbon fiber tube in the UAV, preventing insufficient strength of the carbon fiber tube from causing the UAV arm to break during flight and resulting in a crash. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the overall structure of a carbon tube strength testing device for unmanned aerial vehicles according to this utility model;

[0017] Figure 2 This is a front view of a carbon tube strength testing device for unmanned aerial vehicles according to this utility model.

[0018] 1. Frame; 2. Testing mechanism; 3. Testing table; 4. Limiting assembly; 401. First limiting component; 402. Second limiting component; 403. Third limiting component; 5. Electric slide rail; 6. Press; 7. Strength testing assembly; 701. Telescopic part; 702. Testing head; 8. Moving plate; 9. Cylinder; 10. Positioning shaft; 11. Pressing assembly; 12. Length testing component; 13. Displacement sensor; 14. Carbon tube. Detailed Implementation

[0019] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0020] like Figure 1-2 This utility model is a carbon tube strength testing device for unmanned aerial vehicles (UAVs), including a frame 1, a testing mechanism 2 and a testing platform 3. The testing mechanism 2 for testing the strength of carbon tubes 14 is movably mounted on the frame 1. The testing platform 3 is located below the frame 1 and is equipped with a limiting component 4 for limiting the carbon tubes 14.

[0021] Specifically, the upper surface of the frame 1 is provided with an electric slide rail 5, and the testing mechanism 2 includes a press 6 and a strength testing component 7. The press 6 and the strength testing component 7 are slidably mounted on the electric slide rail 5 via a moving plate 8. The moving plate 8 is slidably connected to the electric slide rail 5, and one side of the moving plate 8 is suspended outside the electric slide rail 5.

[0022] In this embodiment, the movable plate 8 is mounted on the electric slide rail 5 as a support member, and one side of the movable plate 8 is suspended outside the electric slide rail 5, so that the press 6 and the strength detection component 7 can be mounted on the suspended side, which facilitates the strength detection component 7 to perform strength detection on the carbon tube 14 on the detection table 3.

[0023] Furthermore, the press 6 is fixedly mounted on the upper surface of the suspended side of the movable plate 8, the strength detection component 7 is mounted on the lower surface of the suspended side of the movable plate 8, the output end of the press 6 is fixedly connected to the strength detection component 7, and a cylinder 9 for driving the press 6 to work is provided on one side of the press 6.

[0024] Specifically, the strength testing component 7 includes a telescopic part 701 and a testing head 702. The testing head 702 is movably mounted below the moving plate 8 on both sides via positioning shafts 10. The telescopic part 701 is disposed between the testing head 702 and the moving plate 8, with one end of the telescopic part 701 connected to the output end of the press 6 and the other end of the telescopic part 701 fixedly connected to the testing head 702. There are two positioning shafts 10, which are movably inserted through both sides of the moving plate 8 and move up and down with the telescopic part 701 under the drive of the output end of the press 6.

[0025] In this embodiment, the cylinder 9 drives the output end of the press 6 to move downward, thereby causing the telescopic part 701 to move downward, which in turn causes the detection head 702 and the positioning shaft 10 to move vertically downward along the direction of the positioning shaft 10, so that the detection head 702 connected to the positioning shaft 10 contacts the carbon tube 14 and generates pressure on the carbon tube 14 to detect the strength of the carbon tube 14.

[0026] Furthermore, the limiting component 4 includes a first limiting member 401, a second limiting member 402, and a third limiting member 403. The first limiting member 401 is disposed on one side of the detection table 3 and is used to limit the position of the head of the carbon tube 14. The second limiting member 402 is disposed on the other side of the detection table 3 and is used to fix the tail of the carbon tube 14. The third limiting member 403 is disposed between the first limiting member 401 and the second limiting member 402 and is close to the first limiting member 401, and is used to fix the head of the carbon tube 14.

[0027] In this embodiment, the first limiting member 401 is "L"-shaped, with one side perpendicular to the upper surface of the testing platform 3 serving as a reference surface. When performing strength testing on the carbon tube 14, the head of the carbon tube 14 is placed against the reference surface. The second limiting member 402 is disposed on the side of the testing platform 3 opposite to the first limiting member 401. The second limiting member 402 has a placement groove adapted to the curvature of the tail of the carbon tube 14, used to place the tail of the carbon tube 14 and limit its position. There are two third limiting members 403, which are arranged adjacent to each other. The third limiting member 403 closer to the first limiting member 401 has a placement groove adapted to the curvature of the head of the carbon tube 14, used to limit the head of the carbon tube 14. The third limiting member 403 closer to the second limiting member 402 has a placement groove adapted to the curvature of the body of the carbon tube 14, used to limit the body of the carbon tube 14.

[0028] Furthermore, the side of the testing station 3 is also provided with a clamping assembly 11 for fixing the carbon tube 14.

[0029] In this embodiment, there are two clamping components 11, namely rotary clamping cylinders 9. The rotary clamping cylinders 9 align the clamping member with the carbon tube 14 body by rotating the piston rod, and then press down by the cylinder 9 to achieve clamping of the carbon tube 14 body. At this time, when the detection mechanism 2 is used to perform strength detection on the carbon tube 14, the carbon tube 14 will not be displaced under the pressure of the detection head 702, thus affecting the accuracy of the detection.

[0030] Furthermore, a length detection element 12 is movably disposed on the lower surface of the cylinder 9, and a displacement sensor 13 is disposed on one side of the cylinder 9 for cooperating with the length detection element 12 to detect the length of the carbon tube 14.

[0031] In this embodiment, the length detection component 12 is based on the reference surface formed by the first limiting component 401. The length detection component 12 is moved to the end of the carbon tube 14 by moving the electric slide rail 5 to touch the end of the carbon tube 14. At this time, the displacement sensor 13 reads the measurement data and calculates the length of the carbon tube 14 to prevent the UAV from becoming unbalanced due to excessive deviation in the length of the carbon tube 14.

[0032] The working principle of the UAV carbon tube strength testing device provided by this utility model is as follows:

[0033] In use, the carbon tube 14 to be tested is first placed in the placement grooves opened on the first limiting member 401, the second limiting member 402 and the third limiting member 403 with its head abutting against the side wall of the first limiting member 401. Then, the tube wall of the carbon tube 14 is pressed by the pressing assembly 11. Then, the cylinder 9 is started to control the press 6 to drive the detection head 702 downward to apply pressure to any position on the surface of the carbon tube 14. Finally, the length detection member 12 is moved to the end of the carbon tube 14 to measure the strength of the carbon tube 14.

[0034] This utility model provides a carbon tube strength testing device for unmanned aerial vehicles (UAVs). The device is equipped with a testing mechanism 2, which drives the press 6 to descend via a cylinder 9, thereby causing the testing head 702 to descend and contact the carbon tube 14 placed on the testing platform 3 and apply pressure to it. This enables the testing of the strength of the heat-fused joint of the carbon tube 14 in the UAV, preventing the arm from breaking and causing the UAV to crash due to insufficient strength of the carbon tube 14.

[0035] It should be noted that the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0036] It will be apparent to those skilled in the art that this invention is not limited to the details of the exemplary embodiments described above, and that it can be implemented in other specific forms without departing from the spirit or essential characteristics of this invention. Therefore, the embodiments should be considered exemplary and non-limiting in all respects, and the scope of this invention is defined by the appended claims rather than the foregoing description. Thus, it is intended that all variations falling within the meaning and scope of equivalents of the claims be included within this invention.

Claims

1. A device for testing the strength of carbon fiber tubes in unmanned aerial vehicles (UAVs), characterized in that: It includes a frame (1), a testing mechanism (2) and a testing table (3). The testing mechanism (2) for strength testing of carbon nanotubes (14) is movably arranged on the frame (1). The testing table (3) is arranged below the frame (1). A limiting component (4) for limiting the carbon nanotubes (14) is arranged on the testing table (3).

2. The UAV carbon tube strength testing device according to claim 1, characterized in that: The upper surface of the frame (1) is provided with an electric slide rail (5). The testing mechanism (2) includes a press (6) and a strength testing component (7). The press (6) and the strength testing component (7) are slidably mounted on the electric slide rail (5) via a moving plate (8). The moving plate (8) is slidably connected to the electric slide rail (5), and one side of the moving plate (8) is suspended outside the electric slide rail (5).

3. The UAV carbon tube strength testing device according to claim 2, characterized in that: The press (6) is fixedly installed on the upper surface of the suspended side of the moving plate (8), the strength detection component (7) is installed on the lower surface of the suspended side of the moving plate (8), the output end of the press (6) is fixedly connected to the strength detection component (7), and a cylinder (9) is provided on one side of the press (6) to drive the press (6) to work.

4. The UAV carbon tube strength testing device according to claim 3, characterized in that: The strength testing component (7) includes a telescopic part (701) and a testing head (702). The testing head (702) is movably mounted on both sides below the moving plate (8) via positioning shafts (10). The telescopic part (701) is disposed between the testing head (702) and the moving plate (8). One end of the telescopic part (701) is connected to the output end of the press (6), and the other end of the telescopic part (701) is fixedly connected to the testing head (702).

5. The UAV carbon tube strength testing device according to claim 4, characterized in that: There are two positioning shafts (10), which are respectively movably inserted through both sides of the movable plate (8) and move up and down with the telescopic part (701) under the drive of the output end of the press (6).

6. The UAV carbon tube strength testing device according to claim 1, characterized in that: The limiting component (4) includes a first limiting member (401), a second limiting member (402), and a third limiting member (403). The first limiting member (401) is disposed on one side of the detection table (3) and is used to limit the position of the head of the carbon tube (14). The second limiting member (402) is disposed on the other side of the detection table (3) and is used to fix the tail of the carbon tube (14). The third limiting member (403) is disposed between the first limiting member (401) and the second limiting member (402) and is close to the first limiting member (401) and is used to fix the head of the carbon tube (14).

7. The UAV carbon tube strength testing device according to claim 1, characterized in that: The side of the testing station (3) is also provided with a clamping assembly (11) for fixing the carbon tube (14) body.

8. The UAV carbon tube strength testing device according to claim 3, characterized in that: A length detection element (12) is movably disposed on the lower surface of the cylinder (9), and a displacement sensor (13) is disposed on one side of the cylinder (9) for cooperating with the length detection element (12) to detect the length of the carbon tube (14).

Images