Pulling and twisting force testing device for heavy-load unmanned aerial vehicle

Abstract

The invention aims to provide a heavy-load unmanned aerial vehicle tension and torsion testing device which comprises a supporting assembly, a torsion testing assembly and a tension testing assembly, the supporting assembly comprises a base, a torsion plate, a tension seat, a center shaft and a material carrying plate, the torsion plate is adjustably arranged at the bottom of the base, and the tension seat is adjustably and rotatably arranged at the top of the base; the center shaft penetrates through the torsion plate and is rotationally connected with the tension seat and the base, the loading plate is arranged at the top of the center shaft, the torsion testing assembly comprises a torsion sensor and a cross rod, the torsion sensor is arranged on the torsion plate, the cross rod is arranged on the center shaft in the radial direction of the center shaft, and the center shaft is used for driving the cross rod to swing. The tension test assembly comprises a plurality of tension sensors, the tension sensors are arranged on the base in a manner of surrounding the tension seat in a circumferential distribution manner, and the test ends of the tension sensors are connected with the tension seat.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicle testing, and particularly to a pulling and torsion testing device for heavy-load unmanned aerial vehicles. Background Art

[0002] The market scale of unmanned aerial vehicles has been expanding year by year. The global unmanned aerial vehicle market has maintained rapid growth, and the industrial chain has been gradually improved, including fields such as unmanned aerial vehicle research and development, testing, production, sales, training, and maintenance. The application scenarios have gradually shifted from consumer-grade unmanned aerial vehicles to industrial-grade unmanned aerial vehicles. The "low-altitude economy" phenomenon has become increasingly obvious. In application fields such as agricultural plant protection, power line inspection, aerial mapping, police security, environmental monitoring, railway construction, and disaster relief, there is an urgent need for heavy-load application unmanned aerial vehicles in the market, and solving the load problem will become the key to its rapid development. Therefore, for heavy-load application unmanned aerial vehicles, a testing device with versatility, adaptability to different scenarios, precise measurement, strong anti-interference ability, and simulation of real stress states is required.

[0003] Chinese document with publication number CN116593055B discloses a coaxial testing device for motor pulling and torsion, and it discloses the following solution: The motor is installed on the material loading plate, and the pulling force and torsion generated by the motor are transmitted through the central axis. Among them, the pulling force is tested by the pulling force testing component, and the torsion is tested by the torsion testing component.

[0004] However, the existing such testing device has the following deficiencies in actual use: First, the heavy-load unmanned aerial vehicle has a large load. During operation, the swing amplitude of the propeller blades is large, and the torsion of the central axis and the yaw force of the propeller blades inevitably affect the measurement accuracy of the pulling force sensor. Second, the components in the existing torsion testing component are fixedly installed structures and cannot be adjusted. However, there are certain processing errors during the processing of the components, resulting in a low coaxiality between the components. Therefore, during actual measurement, the friction force between the components will be transmitted to the torsion sensor, resulting in poor torsion measurement accuracy and inability to accurately reflect the actual data of the heavy-load unmanned aerial vehicle. Therefore, in order to solve the above problems, the pulling and torsion testing device for heavy-load unmanned aerial vehicles of the present application is proposed. Summary of the Invention

[0005] The purpose of the present invention is to overcome the deficiencies in the prior art and provide a pulling and torsion testing device for heavy-load unmanned aerial vehicles that effectively improves the measurement accuracy of pulling force and torsion.

[0006] The purpose of the present invention is achieved through the following technical solutions: A pulling and torsion testing device for heavy-load unmanned aerial vehicles, comprising: Support assembly, the support assembly includes a base, a torsion plate, a tension seat, a central shaft and a material loading plate. The torsion plate is adjustably arranged at the bottom of the base. The tension seat is adjustably rotatably arranged at the top of the base. The central shaft passes through the torsion plate, and the central shaft is respectively rotationally connected to the tension seat and the base. The material loading plate is arranged at the top of the central shaft; Torsion testing assembly, the torsion testing assembly includes a torsion sensor and a cross bar. The torsion sensor is arranged on the torsion plate. The cross bar is arranged on the central shaft along the radial direction of the central shaft. When the central shaft is used to drive the cross bar to swing, the cross bar pushes against the test end of the torsion sensor; and Tension testing assembly, the tension testing assembly includes a plurality of tension sensors. Each of the tension sensors is arranged on the base in a circumferential distribution around the tension seat. The test ends of each of the tension sensors are connected to the tension seat.

[0007] Optionally, the support assembly further includes a socket and a linear bearing. The socket is adjustably arranged at the bottom of the base. The linear bearing is arranged in the socket. The bottom end of the central shaft passes through the linear bearing.

[0008] Optionally, the torsion testing assembly further includes a force receiving seat. The force receiving seat is arranged on the test end of the torsion sensor. A force receiving groove is formed in the force receiving seat. The cross bar is located in the force receiving groove.

[0009] Optionally, a roller is respectively rotatably arranged at both ends of the cross bar. When the cross bar swings, it drives the roller to push against the inner side wall of the force receiving groove.

[0010] Optionally, the support assembly further includes a plurality of coaxial blocks. Each of the coaxial blocks is arranged on the base, and each of the coaxial blocks abuts against the outer side wall of the tension seat.

[0011] Optionally, a jack is screwed on the coaxial block. The top of the jack abuts against the tension seat.

[0012] Optionally, a buffer pad is arranged between the test end of the tension sensor and the tension seat.

[0013] Optionally, a plurality of ejector rods are also screwed on the tension seat. Two of the ejector rods respectively abut against both ends of one of the buffer pads.

[0014] Optionally, a handle is respectively arranged on both opposite sides of the base.

[0015] Optionally, the material loading plate includes an adapter block and a fixing disk. The adapter block is disposed at the top end of the central axis, and the fixing disk is detachably disposed on the adapter block.

[0016] Compared with the prior art, the present invention has at least the following advantages: The heavy-duty unmanned aerial vehicle pulling and torsion testing device of the present invention includes a support assembly, a torsion testing assembly, and a tensile testing assembly. The support assembly includes a base, a torsion plate, a tensile seat, a central axis, and a material loading plate. The torsion plate is adjustably disposed at the bottom of the base, and the tensile seat is rotatably disposed at the top of the base in an adjustable manner. The central axis passes through the torsion plate and is rotatably connected to both the tensile seat and the base respectively. The material loading plate is disposed at the top of the central axis. The torsion testing assembly includes a torsion sensor and a cross bar. The torsion sensor is disposed on the torsion plate, and the cross bar is disposed on the central axis along the radial direction of the central axis. When the central axis is used to drive the cross bar to swing, the cross bar pushes against the testing end of the torsion sensor. The tensile testing assembly includes a plurality of tensile sensors, and each tensile sensor is disposed on the base in a circumferential distribution around the tensile seat, and the testing ends of each tensile sensor are connected to the tensile seat. Thus, the position of the torsion plate relative to the base can be adjusted, so that the testing end of the torsion sensor is well adapted and installed with the cross bar, thereby improving the torsion detection accuracy of the torsion sensor for the central axis; secondly, by providing a plurality of tensile sensors, the influence of the swing generated by the propeller blades and the torsion of the central axis on the tensile sensors can be effectively avoided, thereby improving the tensile detection accuracy of the tensile sensors for the central axis. Description of the Drawings

[0017] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following will briefly introduce the drawings required to be used in the embodiments. It should be understood that the following drawings only show some embodiments of the present invention, and therefore should not be regarded as a limitation of the scope. For those of ordinary skill in the art, without creative efforts, other related drawings can also be obtained based on these drawings.

[0018] Figure 1 It is a schematic structural diagram of the heavy-duty unmanned aerial vehicle pulling and torsion testing device according to an embodiment of the present invention; Figure 2 is Figure 1 a schematic cross-sectional structural diagram of the heavy-duty unmanned aerial vehicle pulling and torsion testing device shown; Figure 3 is Figure 1 a schematic cross-sectional structural diagram of the heavy-duty unmanned aerial vehicle pulling and torsion testing device shown from another angle.

[0019] Description of the Reference Numerals: 10. Heavy-duty UAV pulling and torsion testing device; 100. Support component; 200. Torsion testing component; 300. Tensile testing component; 110. Base; 120. Torsion plate; 130. Tensile seat; 140. Central axis; 150. Material loading plate; 210. Torsion sensor; 220. Cross bar; 310. Tensile sensor; 161. Sleeve seat; 162. Linear bearing; 230. Force-bearing seat; 231. Force-bearing groove; 240. Roller; 250. Flat key; 171. Coaxial block; 172. Jacking post; 320. Buffer pad; 330. Jacking rod; 180. Handle; 151. Adapter block; 152. Fixed disk. Detailed implementation manner

[0020] For ease of understanding of the present invention, the present invention will be described more comprehensively below with reference to the relevant drawings. The preferred embodiments of the present invention are shown in the drawings.

[0021] As Figures 1 to 3 shown, a heavy-duty UAV pulling and torsion testing device 10 includes a support component 100, a torsion testing component 200 and a tensile testing component 300. The support component 100 includes a base 110, a torsion plate 120, a tensile seat 130, a central axis 140 and a material loading plate 150. The torsion plate 120 is adjustably arranged at the bottom of the base 110. The tensile seat 130 is adjustably rotatably arranged on the top of the base 110. The central axis 140 passes through the torsion plate 120 and is rotatably connected to the tensile seat 130 and the base 110 respectively. The material loading plate 150 is arranged at the top of the central axis 140. The torsion testing component 200 includes a torsion sensor 210 and a cross bar 220. The torsion sensor 210 is arranged on the torsion plate 120. The cross bar 220 is arranged on the central axis 140 along the radial direction of the central axis 140. When the central axis 140 drives the cross bar 220 to swing, the cross bar 220 pushes against the test end of the torsion sensor 210. The tensile testing component 300 includes a plurality of tensile sensors 310. Each tensile sensor 310 is arranged on the base 110 in a circumferential distribution around the tensile seat 130. The test ends of each tensile sensor 310 are all connected to the tensile seat 130.

[0022] It should be noted that the material loading plate 150 is used to fix the heavy-duty unmanned aerial vehicle. When the unmanned aerial vehicle starts to be tested, the torque and tensile force generated by the unmanned aerial vehicle will be transmitted to the central shaft 140 through the material loading plate 150. Therefore, testing the torque and tensile force of the central shaft 140 is equivalent to testing the torque and tensile force of the heavy-duty unmanned aerial vehicle. Specifically, the lower structure of the central shaft 140 is rotatably connected to the base 110, and the upper structure of the central shaft 140 is connected to the base 110 through the tension seat 130 as an intermediate connecting component. Further, the cross bar 220 is horizontally and fixedly installed on the central shaft 140, and the central shaft 140 is fixedly installed at the middle position of the cross bar 220. The torque sensor 210 is installed on the torque plate 120, and the torque plate 120 is adjustably installed between the torque plate 120 and the base 110. Specifically, through holes are formed in the torque plate 120, threaded holes are formed in the base 110, and then bolts are passed through the through holes and then screwed into the threaded holes to fix the torque plate 120 on the base 110. The diameter of the through hole is larger than the outer diameter of the bolt, so that the position of the torque plate 120 relative to the base 110 can be adjusted. In this way, by adjusting the torque plate 120, the position between the torque sensor 210 and the cross bar 220 can be adjusted, so as to adjust the coaxiality between the torque sensor 210 and the central shaft 140, thereby eliminating the errors existing due to the processing of parts and improving the torque test accuracy of the torque sensor 210 for the central shaft 140. Further, a plurality of tension sensors 310 are fixedly installed on the base 110, and the tension sensors 310 are circumferentially distributed around the tension seat 130, and the test ends of the tension sensors 310 are all connected to the tension seat 130. In this way, when the heavy-duty unmanned aerial vehicle is fixed on the material loading plate 150 and starts, once the swing generated by the propeller blades and the torque of the central shaft 140 are transmitted to the tension seat 130, since the tension seat 130 is connected to the base 110 through a matrix of a plurality of tension sensors 310, the swing of the central shaft 140 will be shared by each tension sensor 310 respectively. Compared with the existing technology of installing a single tension sensor 310, the detection values of the swing of the central shaft 140 by each tension sensor 310 in this application will be significantly lower than the detection value of the single tension sensor 310 in the existing technology, effectively eliminating the influence of the swing of the central shaft 140 on the detection of the tension sensor 310 and effectively improving the tension test accuracy of the tension sensor 310.

[0023] As Figure 1 , Figure 2 and Figure 3 shown, in one embodiment, the support assembly 100 further includes a socket 161 and a linear bearing 162. The socket 161 is adjustably arranged at the bottom of the base 110, the linear bearing 162 is arranged in the socket 161, and the bottom end of the central shaft 140 passes through the linear bearing 162.

[0024] It should be noted that in order to further improve the coaxiality between the central shaft 140 and the base 110 and avoid the reduction of measurement accuracy caused by machining errors existing between the central shaft 140 and the base 110 due to part machining, the above structure is provided. Specifically, the socket 161 is adjustably mounted on the base 110, wherein the adjustable mounting structure of the socket 161 relative to the base 110 is the same as the adjustable mounting structure of the torsion plate 120 relative to the base 110. The linear bearing 162 is fixed in the socket 161, and the bottom end of the central shaft 140 is adaptively inserted through the linear bearing 162. In this way, by adjusting the position of the socket 161 relative to the base 110, the coaxiality between the linear bearing 162 and the central shaft 140 can be adjusted to ensure that the central shaft 140 rotates smoothly relative to the base 110.

[0025] As Figures 1 to 3 shown, in one embodiment, the torsion test assembly 200 further includes a force receiving seat 230. The force receiving seat 230 is disposed on the test end of the torsion sensor 210. A force receiving groove 231 is formed in the force receiving seat 230, and the cross bar 220 is located in the force receiving groove 231.

[0026] It should be noted that in order to enable the torsion of the central shaft 140 to be well transmitted to the test end of the torsion sensor 210, the force receiving seat 230 is fixedly mounted on the test end of the torsion sensor 210. A force receiving groove 231 is formed in the force receiving seat 230, and the cross bar 220 is located in the force receiving groove 231. Among them, the central shaft 140 passes through the middle position of the force receiving seat 230 and then passes through the torsion sensor 210. In this way, when the central shaft 140 rotates to drive the cross bar 220 to swing, both ends of the cross bar 220 will respectively push against the inner side walls of the force receiving groove 231, so that the force receiving seat 230 transmits the torsion to the test end of the torsion sensor 210 for detection. It should be noted that since the position of the torsion plate 120 relative to the base 110 is adjustable, it means that the position of the force receiving seat 230 relative to the cross bar 220 is adjustable, that is, the distance between the inner side wall of the force receiving groove 231 and the cross bar 220 is adjustable. In this way, by adjusting the distance between the cross bar 220 and the inner side wall of the force receiving groove 231 to be less than 0.3 mm, the impact distance is reduced, and it is in point contact with the inner side wall of the force receiving groove 231, improving the detection accuracy of the torsion sensor 210.

[0027] As Figure 1 and Figure 2 shown, in one embodiment, a roller 240 is rotatably provided at each end of the cross bar 220. The cross bar 220 is used to drive the roller 240 to push against the inner side wall of the force receiving groove 231 when swinging.

[0028] It should be noted that, for example, a ball bearing is sleeved on each end of the cross bar 220, and then two rollers 240 are respectively sleeved on the two ball bearings. In this way, while the central shaft 140 rotates to drive the cross bar 220 to swing, the central shaft 140 will also slide axially due to the tensile force, thereby driving the cross bar 220 to move axially along the central shaft 140. If the cross bar 220 is in direct contact with the inner side wall of the force receiving groove 231, a sliding friction force will be generated between the cross bar 220 and the force receiving groove 231, resulting in loss of the tensile force of the central shaft 140. The generated sliding friction force will reduce the accuracy of the tensile force sensor 310 of the tensile force testing assembly 300 for detecting the tensile force of the central shaft 140. Therefore, to avoid the above problems, the roller 240 is installed on the cross bar 220 through a ball bearing, so that the roller 240 rolls against the force receiving groove 231. In this way, compared with sliding friction, the tensile force loss of the central shaft 140 can be effectively reduced, thereby improving the accuracy of the tensile force sensor 310 for detecting the tensile force of the central shaft 140.

[0029] As Figure 2 shown, in one embodiment, a through hole is formed in the middle of the cross bar 220, the central shaft 140 is passed through the through hole, and a flat key 250 is arranged on the outer side wall of the central shaft 140 at the through hole. In this way, the flat key 250 is used to position the cross bar 220 and the central shaft 140, avoiding the cross bar 220 from rotating relative to the axis of the central shaft 140, so that the torque of the central shaft 140 can be stably transmitted to the cross bar 220. In one embodiment, two flat keys 250 are provided.

[0030] As Figures 1 to 3 shown, in one embodiment, the support assembly 100 further includes a plurality of coaxial blocks 171. Each coaxial block 171 is arranged on the base 110, and each coaxial block 171 abuts against the outer side wall of the tension seat 130.

[0031] It should be noted that, in order to improve the coaxiality between the tension seat 130 and the base 110 and at the same time reduce the friction between the tension seat 130 and the base 110, a plurality of coaxial blocks 171 are provided to jointly support the tension seat 130. Specifically, through holes are formed in the base 110, the tension seat 130 passes through the through holes, the coaxial blocks 171 are arranged on the inner side walls of the through holes, and each coaxial block 171 abuts against the outer side wall of the tension seat 130. In this way, when the central shaft 140 is pulled, the central shaft 140 drives the tension seat 130 to axially pass through the through holes, and the central shaft 140 is defined by each coaxial block 171 to slide along the axial direction of the through holes, so that the tension seat 130 pulls each tension sensor 310, thereby accurately detecting the tension received by the central shaft 140. It should be noted that each coaxial block 171 surrounds and abuts against the outer side wall of the tension seat 130, rather than the inner side wall of the through hole directly abutting against the outer side wall of the tension seat 130. Therefore, by reducing the contact area, the friction received by the tension seat 130 can be reduced. In one embodiment, four coaxial blocks 171 are provided, and the four coaxial blocks 171 are circumferentially and equally angularly distributed around the axis of the tension seat 130. Further, it should be emphasized that each coaxial block 171 jointly forms a sleeve-like structure, and each coaxial block 171 jointly limits the tension seat 130, and each coaxial block 171 is fixedly installed with the base 110, so that the tension seat 130 can stably axially slide relative to the base 110. In this way, when testing the motor, the central shaft 140 drives the tension seat 130 to axially slide, so that each tension sensor 310 simultaneously detects the axial tension of the tension seat 130. In this way, in an ideal state, when the central shaft 140 does not have yaw, it means that the tension seat 130 will not have yaw either. Therefore, the values of each tension sensor 310 should theoretically be the same. However, due to inevitable errors in workpiece processing and component assembly, the values of each tension sensor 310 are surely impossible to be exactly the same. However, through the distributed layout structure of the tension sensors 310 of the present application, the error of the testing device can be detected, and thus the assembly structure of each component can be finely adjusted according to the error, so that the readings of each tension sensor 310 approach unanimity infinitely. Therefore, within the allowable range of error, the values read by each tension sensor 310 can be regarded as the same. In the prior art, because only a single sensor is used for force detection, it is difficult to accurately control the detection error due to the lack of comparison, while the distributed layout of the tension sensors 310 of the present application well solves the above problems.

[0032] As Figure 1 shown, in one embodiment, a ejector pin 172 is screwed on the coaxial block 171, and the top of the ejector pin 172 abuts against the tension seat 130.

[0033] It should be noted that the tension seat 130 is jointly supported by the test ends of the respective tension sensors 310, and the test ends of the tension sensors 310 have a predetermined effective stroke. To prevent the gravity of the tension seat 130 from overly clamping the test ends of the tension sensors 310 and ensure that the tension sensors 310 maintain a proper position state with respect to the tension seat 130 in the initial state, a top post 172 is provided to support the tension seat 130. In this way, by rotating the top post 172, the depth of the top post 172 screwed into the coaxial block 171 can be adjusted, thereby adjusting the total height of the coaxial block 171 and the top post 172, that is, adjusting the position of the tension seat 130 relative to the base 110, and finally enabling the test ends of the tension sensors 310 to be in a proper initial state.

[0034] As Figure 2 shown, in one embodiment, a buffer pad 320 is provided between the test end of the tension sensor 310 and the tension seat 130.

[0035] It should be noted that by installing the buffer pad 320 between the tension sensor 310 and the tension seat 130, hard contact between the tension seat 130 and the tension sensor 310 can be avoided when the central shaft 140 drives the tension seat 130 to move. For example, the buffer pad 320 is made of soft rubber material.

[0036] As Figures 1 to 3 shown, in one embodiment, a plurality of ejector rods 330 are also screwed onto the tension seat 130, and two of the ejector rods 330 respectively abut against both ends of one of the buffer pads 320.

[0037] It should be noted that in order to make the buffer pad 320 abut against the test end of the tension sensor 310 flush, two ejector rods 330 are provided to adjust the horizontal state of the buffer pad 320. Specifically, both of the two ejector rods 330 are screwed onto the tension seat 130, and the two ends of the ejector rods 330 respectively abut against both ends of the same side of the buffer pad 320. In this way, by rotating the ejector rods 330 to adjust the position of the ejector rods 330 relative to the tension seat 130, the ejector rods 330 can be used to push the buffer pad 320 to adjust its position state.

[0038] As Figure 1 shown, in one embodiment, a handle 180 is respectively provided on two opposite sides of the base 110.

[0039] It should be noted that in order to facilitate the handling and transfer of the heavy-load UAV pull-torsion test device 10 of the present application, two handles 180 are fixedly installed on the base 110.

[0040] As Figures 1 to 3As shown, in one embodiment, the material loading plate 150 includes an adapter block 151 and a fixing plate 152. The adapter block 151 is disposed at the top end of the central shaft 140, and the fixing plate 152 is detachably disposed on the adapter block 151.

[0041] It should be noted that, for the convenience of fixedly installing the heavy-duty unmanned aerial vehicle on the material loading plate 150, the material loading plate 150 is configured as the above structure. Specifically, the adapter block 151 is fixedly installed on the top of the central shaft 140 by screws. After the heavy-duty unmanned aerial vehicle is fixedly installed on the fixing plate 152 by screws, the fixing plate 152 can be fixedly installed on the adapter block 151 by screws. In this way, the quick installation or disassembly of the heavy-duty unmanned aerial vehicle is achieved.

[0042] The above-described embodiments merely represent several implementation manners of the present invention. The description thereof is relatively specific and detailed, but it should not be construed as a limitation to the scope of the invention patent. It should be pointed out that for those of ordinary skill in the art, without departing from the concept of the present invention, several modifications and improvements can still be made, and these all belong to the protection scope of the present invention. Therefore, the protection scope of the present invention patent shall be subject to the appended claims.

Claims

1. An overload UAV pulling torsion test device, characterized in that, Comprising: A support assembly, the support assembly includes a base, a torsion plate, a tension seat, a central shaft and a material loading plate. The torsion plate is adjustably arranged at the bottom of the base. The tension seat is adjustably rotatably arranged at the top of the base. The central shaft passes through the torsion plate, and the central shaft is respectively rotatably connected to the tension seat and the base. The material loading plate is arranged at the top of the central shaft. A torsion test assembly, the torsion test assembly includes a torsion sensor and a cross bar. The torsion sensor is arranged on the torsion plate. The cross bar is arranged on the central shaft along the radial direction of the central shaft. When the central shaft is used to drive the cross bar to swing, the cross bar is used to push against the test end of the torsion sensor. And A tension test assembly, the tension test assembly includes a plurality of tension sensors. Each of the tension sensors is arranged on the base in a circumferential distribution around the tension seat. The test ends of each of the tension sensors are connected to the tension seat.

2. The overload drone pulling and torsion testing device according to claim 1, characterized in that The support assembly further includes a socket and a linear bearing. The socket is adjustably arranged at the bottom of the base. The linear bearing is arranged in the socket. The bottom end of the central shaft passes through the linear bearing.

3. The overload drone pulling and torsion testing device according to claim 1, characterized in that, The torsion test assembly further includes a force receiving seat. The force receiving seat is arranged on the test end of the torsion sensor. A force receiving groove is formed in the force receiving seat. The cross bar is located in the force receiving groove.

4. The overload drone pulling torque test device according to claim 3, wherein A roller is respectively rotatably arranged at both ends of the cross bar. When the cross bar swings, the cross bar is used to drive the roller to push against the inner side wall of the force receiving groove.

5. The overload drone pulling and torsion testing device according to claim 1, wherein The support assembly further includes a plurality of coaxial blocks. Each of the coaxial blocks is arranged on the base, and each of the coaxial blocks abuts against the outer side wall of the tension seat.

6. The overload drone pulling and torsion testing device according to claim 5, wherein, A jack is screwed on the coaxial block. The top of the jack abuts against the tension seat.

7. The overload UAV pulling torsion force testing device according to claim 1, characterized in that A buffer pad is arranged between the test end of the tension sensor and the tension seat.

8. The overload UAV pulling and torsion testing device according to claim 7, wherein A plurality of ejector rods are also screwed on the tension seat. Two of the ejector rods respectively abut against both ends of one of the buffer pads.

9. The overload drone pulling and torsion testing device according to claim 1, characterized in that, A handle is respectively arranged on both opposite sides of the base.

10. The overload UAV pulling and torsion testing device according to claim 1, wherein The material loading plate includes an adapter block and a fixing plate. The adapter block is arranged at the top end of the central shaft. The fixing plate is detachably arranged on the adapter block.

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