Heavy-load UAV tension and torque testing device

Abstract

The present invention aims to provide a heavy-load unmanned aerial vehicle tension and torque testing device, which includes a support assembly, a torque testing assembly and a tension testing assembly. The support assembly includes a base, a torsion plate, a tension seat, a central shaft and a loading plate. The torsion plate is adjustably arranged at the bottom of the base, and 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 rotatably connected to the tension seat and the base respectively. The loading plate is arranged at the top of the central shaft. The torque testing assembly includes a torque sensor and a cross bar. The torque sensor is arranged on the torsion plate, and the cross bar is arranged on the central shaft along the radial direction of the central shaft. The central shaft is used to drive the cross bar to swing so that the cross bar pushes the test end of the torque sensor. The tension testing assembly includes a plurality of tension sensors, and each tension sensor is arranged on the base in a circular distribution around the tension seat, and the test end of each tension sensor is connected to the tension seat.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicle (UAV) testing, and in particular to a heavy-loaded UAV tension and torque testing device. Background Art

[0002] The drone market continues to expand annually, maintaining rapid global growth. The industry chain is also evolving, encompassing areas such as drone R&D, testing, production, sales, training, and maintenance. Application scenarios are shifting from consumer drones to industrial drones. The "low-altitude economy" phenomenon is becoming increasingly pronounced. Heavy-load drones are in urgent need in applications such as agricultural plant protection, power inspection, aerial photography and mapping, police security, environmental monitoring, railway construction, and disaster relief. Addressing payload requirements will be key to their rapid development. Therefore, for heavy-load drones, a test device is needed that is versatile, adaptable to diverse scenarios, provides precise measurements, exhibits strong anti-interference capabilities, and simulates realistic load conditions.

[0003] Chinese document publication number CN116593055B discloses a motor tension-torsion coaxial testing device, which discloses the following scheme: the motor is installed on a loading plate, and the tension and torque generated by the motor are transmitted through the central axis, wherein the tension is tested by a tension test assembly, and the torque is tested by a torque test assembly.

[0004] However, the existing testing device has the following deficiencies in actual use: First, heavy-loaded drones carry a large load, and during operation, the blades swing widely. The torque of the central axis and the yaw force of the blades inevitably affect the measurement accuracy of the tension sensor. Second, the components of the existing torque testing assembly are fixedly mounted and cannot be adjusted. However, there are certain processing errors during the processing of the components, resulting in low coaxiality between the components. Therefore, during actual measurement, the friction between the components will be transmitted to the torque sensor, resulting in poor torque measurement accuracy and an inability to accurately reflect the actual data of the heavy-loaded drone. Therefore, in order to solve the above problems, the heavy-loaded drone tension torque testing device of the present application is proposed. Summary of the Invention

[0005] The purpose of the present invention is to overcome the shortcomings of the prior art and provide a heavy-load UAV tension and torque testing device that effectively improves the tension and torque measurement accuracy.

[0006] The object of the present invention is achieved through the following technical solutions:

[0007] A heavy-load UAV tension and torque testing device, comprising:

[0008] A support assembly, comprising a base, a torsion plate, a tension seat, a central shaft, and a loading plate, wherein the torsion plate is adjustably disposed at the bottom of the base, the tension seat is adjustably rotatably disposed at the top of the base, the central shaft passes through the torsion plate, and is rotatably connected to the tension seat and the base, respectively, and the loading plate is disposed on top of the central shaft;

[0009] A torque testing assembly, comprising a torque sensor and a crossbar, wherein the torque sensor is disposed on the torque plate, and the crossbar is disposed on the central axis along a radial direction of the central axis, wherein the central axis is configured to drive the crossbar to swing so that the crossbar pushes against the test end of the torque sensor; and

[0010] A tension test assembly includes a plurality of tension sensors, each of which is arranged on the base in a circumferential distribution around the tension seat, and a test end of each tension sensor is connected to the tension seat.

[0011] Optionally, the support assembly further includes a sleeve and a linear bearing, the sleeve is adjustably arranged at the bottom of the base, the linear bearing is arranged in the sleeve, and the bottom end of the central shaft passes through the linear bearing.

[0012] Optionally, the torque testing assembly further includes a force bearing seat, which is arranged on the testing end of the torque sensor. A force bearing groove is provided in the force bearing seat, and the cross bar is located in the force bearing groove.

[0013] Optionally, a roller is rotatably provided on each end of the cross bar, and the cross bar is used to drive the roller to push the inner side wall of the force-bearing groove when swinging.

[0014] Optionally, the support assembly further includes a plurality of coaxial blocks, each of the coaxial blocks is disposed on the base, and each of the coaxial blocks abuts against an outer side wall of the tension seat.

[0015] Optionally, a top column is screwed onto the coaxial block, and the top of the top column abuts against the tension seat.

[0016] Optionally, a buffer pad is provided between the test end of the tension sensor and the tension seat.

[0017] Optionally, a plurality of push rods are screwed onto the tension seat, and two of the push rods respectively abut against two ends of one of the buffer pads.

[0018] Optionally, a handle is provided on two opposite sides of the base.

[0019] Optionally, the carrier plate includes an adapter block and a fixed plate, the adapter block is arranged at the top end of the central axis, and the fixed plate is detachably arranged on the adapter block.

[0020] Compared with the prior art, the present invention has at least the following advantages:

[0021] The heavy-loaded unmanned aerial vehicle tension and torque testing device of the present invention includes a support assembly, a torque testing assembly and a tension testing assembly. The support assembly includes a base, a torsion plate, a tension seat, a central shaft and a loading plate. The torsion plate is adjustably arranged at the bottom of the base, and 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 rotatably connected to the tension seat and the base respectively. The loading plate is arranged at the top of the central shaft. The torque testing assembly includes a torque sensor and a cross bar. The torque sensor is arranged on the torsion plate, and the cross bar is arranged on the central shaft along the radial direction of the central shaft. The central shaft is used to drive the cross bar to swing so that the cross bar pushes the test end of the torque sensor. The tension testing assembly includes a plurality of tension sensors, and each tension sensor is arranged on the base in a circular distribution around the tension seat, and the test end of each tension sensor is connected to the tension seat. In this way, the position of the torsion plate can be adjusted relative to the base, so that the test end of the torque sensor can be well adapted and installed with the cross bar, thereby improving the torque detection accuracy of the torque sensor on the central axis; secondly, by setting up multiple tension sensors, the influence of the swing of the blades and the torque of the central shaft on the tension sensor can be effectively avoided, thereby improving the tension detection accuracy of the tension sensor on the central axis. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following briefly introduces the drawings required for use in the embodiments. It should be understood that the following drawings only illustrate certain embodiments of the present invention and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other relevant drawings can be obtained based on these drawings without paying any creative work.

[0023] Figure 1 Schematic diagram of the structure of a heavy-load UAV tension and torque testing device according to one embodiment of the present invention;

[0024] Figure 2 for Figure 1 The cross-sectional structure diagram of the heavy-load UAV tension and torque testing device shown;

[0025] Figure 3 for Figure 1 The cross-sectional structure diagram of the heavy-load UAV tension and torque testing device shown is shown from another angle.

[0026] Description of reference numerals:

[0027] 10. Heavy-load UAV tension and torque test device; 100. Support assembly; 200. Torque test assembly; 300. Tension test assembly; 110. Base; 120. Torque plate; 130. Tension seat; 140. Center axis; 150. Loading plate; 210. Torque sensor; 220. Crossbar; 310. Tension sensor; 161. Sleeve; 162. Linear bearing; 230. Force seat; 231. Force groove; 240. Roller; 250. Flat key; 171. Coaxial block; 172. Push column; 320. Buffer pad; 330. Push rod; 180. Handle; 151. Adapter block; 152. Fixing plate. DETAILED DESCRIPTION

[0028] In order to facilitate understanding of the present invention, the present invention will be described in more detail below with reference to the accompanying drawings, in which preferred embodiments of the present invention are shown.

[0029] like Figures 1 to 3 As shown, a heavy-load UAV tension and torque testing device 10 includes a support assembly 100, a torque testing assembly 200 and a tension testing assembly 300. The support assembly 100 includes a base 110, a torque plate 120, a tension seat 130, a central shaft 140 and a loading plate 150. The torque plate 120 is adjustably arranged at the bottom of the base 110, the tension seat 130 is adjustably rotatably arranged at the top of the base 110, the central shaft 140 is passed through the torque plate 120, and the central shaft 140 is rotatably connected to the tension seat 130 and the base 110 respectively. The loading plate 150 is arranged on the central shaft 140. At the top, the torque testing assembly 200 includes a torque sensor 210 and a cross bar 220. The torque 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. The central axis 140 is used to drive the cross bar 220 to swing so that the cross bar 220 pushes the test end of the torque sensor 210. The tension testing assembly 300 includes a plurality of tension sensors 310. Each tension sensor 310 is arranged on the base 110 in a circular distribution around the tension seat 130. The test ends of each tension sensor 310 are connected to the tension seat 130.

[0030] It should be noted that the loading plate 150 is used to fix the heavy-loaded drone. When the drone is started for testing, the torque and tension generated by the drone will be transmitted to the central shaft 140 through the loading plate 150. Therefore, testing the torque and tension of the central shaft 140 is to test the torque and tension of the heavy-loaded drone. 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 a connecting component. Furthermore, the cross bar 220 is fixedly installed laterally on the central shaft 140, wherein the middle position of the central shaft 140 and the cross bar 220 is fixedly installed. The torque sensor 210 is installed on the torque plate 120, wherein the torque plate 120 and the base 110 are adjustable. Specifically, a through-hole is provided on the torsion plate 120, and a threaded hole is provided on the base 110. Bolts are then passed through the through-holes and then screwed into the threaded holes to secure the torsion plate 120 to the base 110. The diameter of the through-holes is larger than the outer diameter of the bolts, allowing the position of the torsion plate 120 relative to the base 110 to be adjustable. Thus, by adjusting the torsion plate 120, the position between the torque sensor 210 and the crossbar 220 can be adjusted, thereby adjusting the coaxiality between the torque sensor 210 and the central axis 140. This eliminates errors caused by component processing and improves the accuracy of the torque test performed by the torque sensor 210 on the central axis 140. Furthermore, a plurality of tension sensors 310 are fixedly mounted on the base 110. Each tension sensor 310 is distributed in a circular pattern around the tension base 130, and the test end of each tension sensor 310 is connected to the tension base 130. In this way, when the heavy-loaded drone is fixed on the loading plate 150 and started, once the swing generated by the 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 multiple tension sensors 310 in a matrix, the swing of the central shaft 140 will be shared by each tension sensor 310 respectively. Compared with the solution of installing a single tension sensor 310 in the prior art, the detection value of the swing of the central shaft 140 by each tension sensor 310 in the present application will be significantly lower than the detection value of a single tension sensor 310 in the prior art after the swing is shared, thereby 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.

[0031] like Figure 1 、 Figure 2 and Figure 3 As shown, in one embodiment, the support assembly 100 further includes a sleeve 161 and a linear bearing 162 . The sleeve 161 is adjustably disposed at the bottom of the base 110 , the linear bearing 162 is disposed in the sleeve 161 , and the bottom end of the central shaft 140 is passed through the linear bearing 162 .

[0032] It should be noted that in order to further improve the coaxiality between the center shaft 140 and the base 110 and avoid reduced measurement accuracy due to machining errors between the center shaft 140 and the base 110 due to part processing, the above-mentioned structure is provided. Specifically, the sleeve 161 is adjustably mounted on the base 110, wherein the adjustable mounting structure of the sleeve 161 relative to the base 110 is equivalent to the adjustable mounting structure of the torsion plate 120 relative to the base 110. The linear bearing 162 is fixed within the sleeve 161, and the bottom end of the center shaft 140 is adaptively inserted into the linear bearing 162. In this way, by adjusting the position of the sleeve 161 relative to the base 110, the coaxiality between the linear bearing 162 and the center shaft 140 can be adjusted, ensuring that the center shaft 140 rotates smoothly relative to the base 110.

[0033] like Figures 1 to 3 As shown, in one embodiment, the torque testing assembly 200 further includes a force seat 230 , which is disposed on the testing end of the torque sensor 210 . A force groove 231 is defined in the force seat 230 , and the cross bar 220 is located in the force groove 231 .

[0034] It should be noted that in order to ensure that the torque of the central shaft 140 can be effectively transmitted to the test end of the torque sensor 210, a force-bearing seat 230 is fixedly installed on the test end of the torque sensor 210, wherein a force-bearing groove 231 is formed on the force-bearing seat 230, and the crossbar 220 is located within the force-bearing groove 231. The central shaft 140 passes through the middle of the force-bearing seat 230 and then passes through the torque sensor 210. In this way, when the central shaft 140 rotates to drive the crossbar 220 to swing, the two ends of the crossbar 220 will respectively push against the inner sidewalls of the force-bearing groove 231, thereby causing the force-bearing seat 230 to transmit the torque to the test end of the torque 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 seat 230 relative to the cross bar 220 is adjustable, that is, the distance between the inner wall of the force groove 231 and the cross bar 220 is adjustable. In this way, by adjusting the distance between the cross bar 220 and the inner wall of the force groove 231 to be less than 0.3 mm, the impact distance is reduced, and point contact is made with the inner wall of the force groove 231, thereby improving the detection accuracy of the torque sensor 210.

[0035] like Figure 1 and Figure 2 As shown, in one embodiment, a roller 240 is rotatably provided on both ends of the cross bar 220 , and the cross bar 220 is used to drive the roller 240 to push the inner wall of the force-bearing groove 231 when swinging.

[0036] It should be noted that, for example, a ball bearing is mounted on each end of the crossbar 220, and the two rollers 240 are mounted on the two ball bearings. In this way, while the central shaft 140 rotates to drive the crossbar 220 to swing, the central shaft 140 will also slide axially due to the tension, thereby driving the crossbar 220 to move axially along the central shaft 140. If the crossbar 220 directly contacts the inner sidewall of the force-bearing groove 231, sliding friction will be generated between the crossbar 220 and the force-bearing groove 231, resulting in a loss of tension on the central shaft 140. This generated sliding friction will reduce the accuracy of the tension sensor 310 of the tension testing assembly 300 in detecting the tension of the central shaft 140. Therefore, in order to avoid the above problems, the roller 240 is installed on the cross bar 220 through a ball bearing, so that the roller 240 and the force groove 231 have rolling friction. In this way, compared with sliding friction, the tension loss of the central shaft 140 can be effectively reduced, thereby improving the tension detection accuracy of the tension sensor 310 on the central shaft 140.

[0037] like Figure 2 As shown, in one embodiment, a through-hole is formed in the middle of the crossbar 220, through which the central shaft 140 is inserted. A flat key 250 is provided on the outer wall of the central shaft 140 at the through-hole. Thus, the flat key 250 is used to lock the crossbar 220 and the central shaft 140 in place, preventing the crossbar 220 from rotating relative to the axis of the central shaft 140, thereby allowing the torsional force of the central shaft 140 to be stably transmitted to the crossbar 220. In one embodiment, two flat keys 250 are provided.

[0038] like Figures 1 to 3 As shown, in one embodiment, the support assembly 100 further includes a plurality of coaxial blocks 171 . Each coaxial block 171 is disposed on the base 110 , and each coaxial block 171 abuts against an outer side wall of the tension seat 130 .

[0039] It should be noted that in order to improve the coaxiality between the tension seat 130 and the base 110 and reduce the friction between the tension seat 130 and the base 110, multiple coaxial blocks 171 are provided to jointly support the tension seat 130. Specifically, a through hole is provided in the base 110, through which the tension seat 130 passes. The coaxial blocks 171 are disposed on the inner sidewall of the through hole, and each coaxial block 171 abuts against the outer sidewall of the tension seat 130. Thus, when the central shaft 140 is pulled, the central shaft 140 drives the tension seat 130 axially through the through hole. The central shaft 140 is restrained by the coaxial blocks 171 to slide axially along the through hole, causing the tension seat 130 to pull each tension sensor 310, thereby accurately detecting the tension applied to the central shaft 140. It should be noted that each coaxial block 171 surrounds and abuts against the outer wall of the tension seat 130, rather than the inner wall of the through hole directly abutting against the outer wall of the tension seat 130. Therefore, by reducing the contact area, the friction force on the tension seat 130 can be reduced. In one embodiment, four coaxial blocks 171 are provided, and the four coaxial blocks 171 are distributed at equal angles in a circle with the axis of the tension seat 130 as the center. Further, it should be emphasized that each coaxial block 171 together forms a sleeve-like structure, and each coaxial block 171 together 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 slide axially relative to the base 110. In this way, when testing the motor, the central shaft 140 drives the tension seat 130 to slide axially, so that each tension sensor 310 simultaneously detects the axial tension of the tension seat 130. In this way, under ideal conditions, when the central shaft 140 is not out of When deflection occurs, it means that the tension seat 130 will not deflect either. Therefore, the values ​​of each tension sensor 310 should be consistent in theory. However, due to the inevitable errors in workpiece processing and component assembly, the values ​​of each tension sensor 310 cannot be completely consistent. However, through the distributed layout structure of the tension sensor 310 of the present application, the error of the test device can be detected, and the assembly structure of each component can be finely adjusted according to the error, so that the readings of each tension sensor 310 are infinitely close to consistency. Therefore, within the allowable error range, the values ​​read by each tension sensor 310 can be regarded as consistent. 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. The distributed layout of the tension sensor 310 of the present application solves the above problem well.

[0040] like Figure 1 As shown, in one embodiment, a top column 172 is screwed onto the coaxial block 171 , and the top of the top column 172 abuts against the tension seat 130 .

[0041] It should be noted that the tension base 130 is jointly supported by the test ends of the tension sensors 310, and the test ends of the tension sensors 310 have a predetermined effective stroke. To prevent the gravity of the tension base 130 from excessively clamping the test ends of the tension sensors 310 and to ensure that the tension sensors 310 maintain a suitable position relative to the tension base 130 in the initial state, a top post 172 is provided to support the tension base 130. Thus, by rotating the top post 172, the depth to which the top post 172 is screwed into the coaxial block 171 can be adjusted, thereby adjusting the total height of the coaxial block 171 and the top post 172. In other words, the position of the tension base 130 relative to the base 110 can be adjusted, ultimately ensuring that the test ends of the tension sensors 310 are in a suitable initial state.

[0042] like Figure 2 As shown, in one embodiment, a buffer pad 320 is provided between the test end of the tension sensor 310 and the tension seat 130 .

[0043] It should be noted that a buffer pad 320 is installed between the tension sensor 310 and the tension seat 130 to avoid hard contact between the tension seat 130 and the tension sensor 310 when the central shaft 140 drives the tension seat 130 to move. For example, the buffer pad 320 is made of soft rubber.

[0044] like Figures 1 to 3 As shown, in one embodiment, a plurality of push rods 330 are screwed onto the tension seat 130 , and two of the push rods 330 respectively abut against two ends of one of the buffer pads 320 .

[0045] It should be noted that, in order to ensure that the buffer pad 320 abuts flush against the test end of the tension sensor 310, two push rods 330 are provided to adjust the horizontal position of the buffer pad 320. Specifically, both push rods 330 are threadedly connected to the tension base 130, with the ends of the push rods 330 abutting the ends of the same side of the buffer pad 320. Thus, by rotating the push rods 330 to adjust their position relative to the tension base 130, the push rods 330 can push against the buffer pad 320 to adjust its position.

[0046] like Figure 1 As shown, in one embodiment, a handle 180 is provided on two opposite sides of the base 110 .

[0047] It should be noted that, in order to facilitate the transportation and transfer of the heavy-load UAV tension and torque testing device 10 of the present application, two handles 180 are fixedly installed on the base 110 .

[0048] like Figures 1 to 3As shown, in one embodiment, the carrier plate 150 includes an adapter block 151 and a fixed plate 152 . The adapter block 151 is disposed at the top end of the central shaft 140 , and the fixed plate 152 is detachably disposed on the adapter block 151 .

[0049] It should be noted that the aforementioned structure is used to facilitate the secure mounting of the heavy-load drone on the loading plate 150. Specifically, an adapter block 151 is screwed to the top of the central shaft 140. After the heavy-load drone is screwed to the fixing plate 152, the fixing plate 152 is then screwed to the adapter block 151. This allows for quick installation and removal of the heavy-load drone.

[0050] The above-described embodiments merely illustrate several implementations of the present invention, and while their descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the patent. It should be noted that a person skilled in the art would be able to make numerous variations and improvements without departing from the spirit of the present invention, all of which fall within the scope of protection of the present invention. Therefore, the scope of protection of the patent for this invention shall be determined by the appended claims.

Claims

1. A heavy-load UAV tension and torque testing device, characterized in that: include: A support assembly, the support assembly includes a base, a torsion plate, a tension seat, a central shaft, a loading plate, and a plurality of coaxial blocks, the torsion plate being adjustably arranged at the bottom of the base, the tension seat being adjustably rotatably arranged at the top of the base, each of the coaxial blocks being arranged on the base, and each of the coaxial blocks being in contact with the outer side wall of the tension seat, the central shaft being passed through the torsion plate, and being rotatably connected to the tension seat and the base respectively, and the loading plate being arranged on the top of the central shaft; A torque testing assembly, comprising a torque sensor and a crossbar, wherein the torque sensor is disposed on the torque plate, and the crossbar is disposed on the central axis along a radial direction of the central axis, wherein the central axis is configured to drive the crossbar to swing so that the crossbar pushes against the test end of the torque sensor; and A tension test assembly includes a plurality of tension sensors, each of which is arranged on the base in a circumferential distribution around the tension seat, and a test end of each tension sensor is connected to the tension seat.

2. The heavy-load UAV tension and torque testing device according to claim 1, characterized in that: The support assembly further includes a sleeve and a linear bearing. The sleeve is adjustably arranged at the bottom of the base. The linear bearing is arranged in the sleeve. The bottom end of the central shaft passes through the linear bearing.

3. The heavy-load UAV tension and torque testing device according to claim 1, characterized in that: The torque testing assembly further includes a force bearing seat, which is arranged on the testing end of the torque sensor. A force bearing groove is provided in the force bearing seat, and the cross bar is located in the force bearing groove.

4. The heavy-load UAV tension and torque testing device according to claim 3, characterized in that: A roller is rotatably provided on both ends of the cross bar, and the cross bar is used to drive the roller to push the inner side wall of the force-bearing groove when swinging.

5. The heavy-load UAV tension and torque testing device according to claim 1, characterized in that: A top column is screwed onto the coaxial block, and the top of the top column abuts against the tension seat.

6. The heavy-load UAV tension and torque testing device according to claim 1, characterized in that: A buffer pad is provided between the test end of the tension sensor and the tension seat.

7. The heavy-load UAV tension and torque testing device according to claim 6, characterized in that: A plurality of push rods are screwed onto the tension seat, and two of the push rods respectively abut against the two ends of one of the buffer pads.

8. The heavy-load UAV tension and torque testing device according to claim 1, characterized in that: Two opposite sides of the base are respectively provided with a handle.

9. The heavy-load UAV tension and torque testing device according to claim 1, characterized in that: The material loading plate includes an adapter block and a fixed disk. The adapter block is arranged at the top end of the central shaft, and the fixed disk is detachably arranged on the adapter block.

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