A test system for unmanned aerial vehicle (UAV) suspension devices

Abstract

This invention relates to the field of unmanned aerial vehicle (UAV) suspension device testing technology, and discloses a UAV suspension device testing system, including a first support beam, a second support beam, a first drive assembly, a second drive assembly, a suspension mechanism, a controller, and an observation device. The first drive assembly is mounted on the first support beam, and the second support beam is connected to the first drive assembly. The first drive assembly drives the second support beam to move along a first direction. The second drive assembly is mounted on the second support beam, and the suspension mechanism is mounted on the second drive assembly. The second drive assembly drives the suspension mechanism to move along a second direction, and the UAV suspension device is mounted on the suspension mechanism. The rotation axis of the winding reel is parallel to the second direction. The observation device monitors the position of the load along the first, second, and third directions. The first drive assembly, the second drive assembly, and the observation device are all communicatively connected to the controller.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) suspension device testing technology, and in particular to a UAV suspension device testing system. Background Technology

[0002] Currently, when testing the suspension devices used on drones, the suspension devices with loads are usually installed directly on the drones for testing. This often leads to accidents such as drones or loads falling during the testing process, making it difficult to guarantee the safety of personnel and equipment.

[0003] Therefore, there is an urgent need for a test system for unmanned aerial vehicle (UAV) suspension devices to solve the above problems. Summary of the Invention

[0004] The purpose of this invention is to provide a test system for UAV suspension devices, thereby improving the test safety of UAV suspension devices.

[0005] To achieve this objective, the present invention adopts the following technical solution:

[0006] A test system for a drone suspension device is provided for testing drone suspension devices. The drone suspension device includes a winding reel, a first motor, and a rope. The first motor drives the winding reel to rotate to release or wind the rope. A load is connected to the bottom end of the rope. The test system for the drone suspension device has two perpendicular directions: a first direction, a second direction, and a third direction. It includes a first support beam, a second support beam, a first drive assembly, a second drive assembly, a suspension mechanism, a controller, and an observation device.

[0007] The first drive component is disposed on the first support beam, and the second support beam is connected to the first drive component. The first drive component is used to drive the second support beam to move along the first direction.

[0008] The second drive assembly is disposed on the second support beam, the suspension mechanism is disposed on the second drive assembly, the second drive assembly is used to drive the suspension mechanism to move along the second direction, the UAV suspension device is disposed on the suspension mechanism, and the rotation axis of the winding reel is parallel to the second direction;

[0009] The observation device is used to monitor the position of the load along the first direction, the second direction, and the third direction;

[0010] The first drive component, the second drive component, and the observation device are all communicatively connected to the controller.

[0011] As an improvement to the above technical solution, two first support beams are provided, and the two first support beams are spaced apart along the second direction. The first drive assembly is provided in a one-to-one correspondence with the first support beam, and the two ends of the second support beam are respectively connected to the two first drive assemblies.

[0012] As an improvement to the above technical solution, the first drive component includes a second motor, a first gear, and a first rack;

[0013] The first support beam extends along the first direction, the first rack is fixedly mounted on the first support beam and extends along the first direction, the first gear is connected to the second motor for transmission, and the first gear meshes with the first rack.

[0014] As an improvement to the above technical solution, the second drive component includes a third motor, a second gear, a second rack, and a connecting member;

[0015] The second support beam extends along the second direction, the connector connects the third motor to the second support beam, the second rack is fixedly mounted on the second support beam and extends along the second direction, the second gear is driven by the third motor and meshes with the second rack.

[0016] As an improvement to the above technical solution, the connecting member includes a first limiting plate, a second limiting plate, and a connecting shaft. The first limiting plate and the second limiting plate are disposed on both sides of the second support beam, and the connecting shaft connects the first limiting plate and the second limiting plate.

[0017] As an improvement to the above technical solution, the suspension mechanism includes a third drive component, which is disposed on the second drive component. The UAV suspension device is disposed on the third drive component. The third drive component is used to drive the UAV suspension device to rotate around a first axis. The rotation axis of the winding reel, the first direction, and the second direction are all perpendicular to the first axis. The third drive component is communicatively connected to the controller.

[0018] As an improvement to the above technical solution, the third drive component includes a fourth motor and a mounting bracket;

[0019] The fourth motor is mounted on the second limiting plate, and the mounting frame is connected to the fourth motor in a transmission manner. The fourth motor can drive the mounting frame to rotate around the first axis, and the UAV suspension device is mounted on the mounting frame.

[0020] As an improvement to the above technical solution, the suspension mechanism further includes a fourth drive component, which is disposed on the mounting frame. The UAV suspension device is disposed on the fourth drive component. The third drive component can drive the fourth drive component to rotate around the first axis, and the UAV suspension device can rotate around the first axis with the fourth drive component. The fourth drive component is used to drive the UAV suspension device to rotate around a second axis, which is parallel to the rotation axis of the winding reel.

[0021] As an improvement to the above technical solution, the fourth drive component includes two fifth motors, the mounting frame includes a left mounting frame and a right mounting frame, the left mounting frame and the right mounting frame are respectively disposed on both sides of the fourth motor, the two fifth motors are respectively disposed on the left mounting frame and the right mounting frame, the output shafts of the two fifth motors are both connected to the UAV suspension device, and the fifth motors can drive the UAV suspension device to rotate around the second axis.

[0022] As an improvement to the above technical solution, when testing the UAV suspension device using the UAV suspension device test system, the controller controls the first drive component to drive the second support beam to move along the first direction, controls the second drive component to drive the suspension mechanism to move along the second direction, and / or controls the first motor to drive the winding reel to rotate. The controller collects the position of the suspension device and the position of the load.

[0023] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0024] The UAV suspension device testing system of the present invention includes a first drive component that drives the suspension mechanism to move along a first direction, and a second drive component that drives the suspension mechanism to move along a second direction, the first direction being perpendicular to the second direction. The UAV suspension device is connected to the suspension mechanism, thereby enabling the UAV suspension device testing system of the present invention to simulate the two-dimensional movement of a UAV in a horizontal plane, and to test the working conditions of the UAV suspension device under the horizontal two-dimensional motion state of the UAV, especially the swing angle of the suspension rope and the positional changes of the suspended weight. By using the UAV suspension device testing system to replace the UAV in the UAV suspension device experiment, safety accidents such as UAV falls are avoided, thereby improving the testing safety of the UAV suspension device. Those skilled in the art will understand that when conducting UAV suspension device tests in the UAV suspension device test system, the controller can obtain the real-time position of the second support beam based on its initial position and the distance it moves along the first direction. Similarly, the controller can obtain the real-time position of the suspension mechanism based on the distance it moves along the second direction and its initial position. The observation device observes and records the position of the load suspended by the UAV suspension device, and by combining this with the position of the suspension mechanism, it can determine the swing angle of the released portion of the rope of the UAV suspension device and the positional changes of the load suspended by the UAV suspension device. Attached Figure Description

[0025] Figure 1 This is a schematic diagram of the structure of the UAV suspension device testing system provided in this embodiment of the invention. Figure 1 ;

[0026] Figure 2 yes Figure 1 Enlarged view of point A in the middle.

[0027] In the picture:

[0028] 1. First supporting beam;

[0029] 11. First guide groove;

[0030] 2. Second support beam;

[0031] 21. Second guide groove;

[0032] 3. First drive assembly; 31. Second motor; 32. First mounting plate; 33. First guide roller;

[0033] 4. Second drive assembly; 41. Third motor; 42. Connector; 421. First limiting plate; 422. Second limiting plate; 423. Connecting shaft; 424. Second guide roller;

[0034] 5. Suspension mechanism;

[0035] 51. Third drive assembly; 511. Fourth motor; 512. Mounting bracket;

[0036] 6. Base; 61. Base plate; 62. Vertical beam;

[0037] 100. Unmanned aerial vehicle (UAV) suspension device; 1001. Winding reel; 1002. Bottom shell. Detailed Implementation

[0038] The specific embodiments of the present invention will be described in further detail below with reference to the accompanying drawings and examples. The following examples are for illustrative purposes only and are not intended to limit the scope of the invention.

[0039] In the description of this invention, unless otherwise explicitly specified and limited, the terms "connected," "linked," and "fixed" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0040] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0041] In the description of this embodiment, the terms "upper," "lower," "right," etc., refer to the orientation or positional relationship shown in the accompanying drawings. They are used only for ease of description and simplification of operation, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the present invention. In addition, the terms "first" and "second" are used only for distinction in description and have no special meaning.

[0042] like Figure 1 and Figure 2As shown, this embodiment provides a test system for a drone suspension device, used to test a drone suspension device 100. The drone suspension device 100 includes a winding reel 1001, a first motor, a rope, and a base shell 1002. The first motor drives the winding reel 1001 to rotate to release or wind the rope, thereby adjusting the length of the rope released from the winding reel 1001. A load is connected to the bottom end of the rope. The drone suspension device test system has two perpendicular directions: a first direction, a second direction, and a third direction. The winding reel 1001 and the first motor are both disposed inside the base shell 1002. A cable passage hole is provided at the bottom of the base shell 1002, through which the rope extends to the bottom of the base shell 1002.

[0043] The UAV suspension device test system includes a first support beam 1, a second support beam 2, a first drive assembly 3, a second drive assembly 4, and a suspension mechanism 5. The first drive assembly 3 is mounted on the first support beam 1, and the second support beam 2 is connected to the first drive assembly 3. The first drive assembly 3 drives the second support beam 2 to move along a first direction. The second drive assembly 4 is mounted on the second support beam 2, and the suspension mechanism 5 is mounted on the second drive assembly 4. The second drive assembly 4 drives the suspension mechanism 5 to move along a second direction. The UAV suspension device 100 is mounted on the suspension mechanism 5, and the rotation axis of the winding reel 1001 is parallel to the second direction. An observation device is used to monitor the position of the load along the first, second, and third directions. The first drive assembly 3, the second drive assembly 4, and the observation device are all communicatively connected to a controller. In this embodiment, when testing the UAV suspension device 100, the first and second directions are both horizontal, and the third direction is vertical. The device capable of monitoring the position of the load is existing equipment, and its specific structure and principle are not described here.

[0044] The UAV suspension device testing system provided in this embodiment includes a first drive component 3 that drives the suspension mechanism 5 to move along a first direction, and a second drive component 4 that drives the suspension mechanism 5 to move along a second direction. The first direction is perpendicular to the second direction. The UAV suspension device 100 is connected to the suspension mechanism 5, thereby enabling the UAV suspension device testing system of this embodiment to simulate the two-dimensional movement of a UAV in a horizontal plane. This allows for testing the working conditions of the UAV suspension device 100 under the horizontal two-dimensional motion of the UAV, particularly the swing angle of the suspension rope and the positional changes of the suspended weight. By using the UAV suspension device testing system to replace the UAV in the experiment of the UAV suspension device 100, safety accidents such as UAV falls are avoided, thereby improving the testing safety of the UAV suspension device 100.

[0045] Those skilled in the art will understand that when the UAV suspension device 100 is tested in the UAV suspension device test system, the controller can obtain the real-time position of the second support beam 2 based on the initial position of the second support beam 2 and the distance the second support beam 2 moves along the first direction. Similarly, the controller can obtain the real-time position of the suspension mechanism 5 based on the distance the suspension mechanism 5 moves along the second direction and the initial position of the suspension mechanism 5 combined with the position of the second support beam 2. The observation device observes and records the position of the weight suspended by the UAV suspension device 100, and combined with the position of the suspension mechanism 5, it can determine the swing angle of the released part of the rope of the UAV suspension device 100 and the position change of the weight suspended by the UAV suspension device 100.

[0046] Optionally, the UAV suspension device test system provided in this embodiment also includes a base 6, which includes a base plate 61 and vertical beams 62. Two vertical beams 62 are spaced apart on the base plate 61 along a first direction, and two first support beams 1 are respectively fixedly mounted on the two vertical beams 62.

[0047] Optionally, such as Figure 1 and Figure 2 As shown, two first support beams 1 are provided, spaced apart along the second direction. A first drive assembly 3 is provided in a one-to-one correspondence with each first support beam 1. The two ends of the second support beam 2 are respectively connected to the two first drive assemblies 3. Stable support and drive of the second support beam 2 are achieved through the cooperation of the two first support beams 1 and the two first drive assemblies 3.

[0048] Optionally, such as Figure 1 and Figure 2 As shown, the first drive assembly 3 includes a second motor 31, a first gear, and a first rack. A first support beam 1 extends along a first direction. The first rack is fixedly mounted on the first support beam 1 and extends along the first direction. The first gear is connected to the second motor 31 in a transmission manner, and the first gear meshes with the first rack. The second motor 31 drives the first gear to rotate. Through the engagement of the first gear and the first rack, the second motor 31 and the first gear move along the first support beam 1, thereby driving the second support beam 2 to move along the extending direction of the first support beam 1.

[0049] Furthermore, such as Figure 1 and Figure 2As shown, the first drive assembly 3 also includes a first mounting plate 32 and a first guide roller 33. The first mounting plate 32 is fixedly mounted on the housing of the second motor 31, and the first guide roller 33 is rotatably mounted on the first mounting plate 32. The rotation axis of the first guide roller 33 extends along a second direction. Multiple first guide rollers 33 are provided, with one on each of the upper and lower sides of the first support beam 1. The top and bottom of the first support beam 1 are each provided with a first guide groove 11 extending along a first direction. A first rack is fixedly mounted on the bottom of the first guide groove 11 at the top of the first support beam 1. The first guide roller 33 located above the first support beam 1 rolls within the first guide groove 11 at the top of the first support beam 1, and the first guide roller 33 located below the first support beam 1 rolls within the first guide groove 11 at the bottom of the first support beam 1. The cooperation between the first guide roller 33 and the first guide groove 11 guides the movement of the second motor 31 and the UAV suspension device 100 along the first direction.

[0050] Optionally, such as Figure 1 and Figure 2 As shown, the second drive assembly 4 includes a third motor 41, a second gear, a second rack, and a connector 42. The second support beam 2 extends along a second direction, the connector 42 connects the third motor 41 and the second support beam 2, the second rack is fixedly mounted on the second support beam 2 and extends along the second direction, the second gear is drively connected to the third motor 41, and the second gear meshes with the second rack.

[0051] Furthermore, such as Figure 1 and Figure 2 As shown, the connecting member 42 includes a first limiting plate 421, a second limiting plate 422, and a connecting shaft 423. The first limiting plate 421 and the second limiting plate 422 are disposed on both sides of the second support beam 2, and the connecting shaft 423 connects the first limiting plate 421 and the second limiting plate 422. In this embodiment, the first limiting plate 421 is disposed on the upper side of the second support beam 2, and the second limiting plate 422 is disposed on the lower side of the second support beam 2. The housing of the third motor 41 is fixedly disposed on the first limiting plate 421. Multiple connecting shafts 423 are spaced apart on both the front and rear sides of the second support beam 2.

[0052] Furthermore, such as Figure 1 and Figure 2As shown, the connector 42 also includes a second guide roller 424, which is rotatably mounted on the connecting shaft 423. Second guide grooves 21 are provided on both the front and rear sides of the second support beam 2, and a second rack is fixedly mounted on the bottom of one of the second guide grooves 21. The second guide roller 424 located on the front side of the second support beam 2 is rotatably mounted in the second guide groove 21 on the front side of the second support beam 2, and the second guide roller 424 located on the rear side of the second support beam 2 is rotatably mounted in the second guide groove 21 on the rear side of the second support beam 2. The cooperation between the second guide roller 424 and the second guide groove 21 guides the movement of the third motor 41 and the UAV suspension device 100 along the second direction.

[0053] Optionally, such as Figure 1 and Figure 2 As shown, the suspension mechanism 5 includes a third drive assembly 51, which is mounted on the second drive assembly 4. The UAV suspension device 100 is mounted on the third drive assembly 51. The third drive assembly 51 drives the UAV suspension device 100 to rotate around a first axis. The rotation axis, first direction, and second direction of the winding reel 1001 are all perpendicular to the first axis. The third drive assembly 51 is communicatively connected to the controller. By setting the third drive assembly 51, the UAV suspension device test system can drive the UAV suspension device 100 to rotate around a first axis perpendicular to the horizontal plane, thereby simulating the yaw angle of the UAV through the first axis to test the effect of the UAV yaw angle on the UAV suspension device 100.

[0054] Furthermore, such as Figure 1 and Figure 2 As shown, the third drive assembly 51 includes a fourth motor 511 and a mounting bracket 512. The fourth motor 511 is mounted on the second limiting plate 422, and the mounting bracket 512 is connected to the fourth motor 511. The fourth motor 511 can drive the mounting bracket 512 to rotate around the first axis. The UAV suspension device 100 is mounted on the mounting bracket 512. The fourth motor 511 drives the UAV suspension device 100 to rotate around the first axis through the mounting bracket 512.

[0055] Optionally, the suspension mechanism 5 further includes a fourth drive assembly, which is mounted on the mounting bracket 512. The UAV suspension device 100 is mounted on the fourth drive assembly. The third drive assembly 51 can drive the fourth drive assembly to rotate around a first axis, and the UAV suspension device 100 can rotate with the fourth drive assembly around the first axis. The fourth drive assembly is used to drive the UAV suspension device 100 to rotate around a second axis, which is parallel to the rotation axis of the winding reel 1001. By setting the fourth drive assembly, the UAV suspension device test system can drive the UAV suspension device 100 to rotate around a second axis parallel to the horizontal direction, thereby simulating the pitch angle of the UAV through the second axis to test the effect of the UAV pitch angle on the UAV suspension device 100. Preferably, the second axis is collinear with the rotation axis of the winding reel 1001.

[0056] Furthermore, the fourth drive assembly includes two fifth motors. The mounting bracket 512 includes a left mounting bracket and a right mounting bracket, which are respectively disposed on both sides of the fourth motor 511. The two fifth motors are respectively disposed on the left mounting bracket and the right mounting bracket, that is, one fifth motor is disposed on the left mounting bracket and one fifth motor is disposed on the right mounting bracket. The output shafts of both fifth motors are connected to the UAV suspension device 100 for transmission. The fifth motors can drive the UAV suspension device 100 to rotate around the second axis. The two fifth motors cooperate to drive the UAV suspension device 100 to rotate around the second axis.

[0057] Furthermore, the UAV suspension device test system of this embodiment also includes a controller. The first motor, second motor 31, third motor 41, fourth motor 511, and fifth motor are all communicatively connected to the controller. The operator controls the UAV suspension device 100, the first drive assembly 3, the second drive assembly 4, the third drive assembly 51, and the fourth drive assembly through the controller. This controls the rope release length of the UAV suspension device 100, the movement of the UAV suspension device 100 along a first direction, the movement of the UAV suspension device 100 along a second direction, the rotation of the UAV suspension device 100 around a first axis, and the rotation of the UAV suspension device 100 around a second axis, thereby testing the state of the UAV suspension device 100 under various movement states of the UAV and under different rope release lengths.

[0058] Furthermore, the UAV suspension device test system of this embodiment also includes a power supply, which is used to supply power to the first motor, the second motor 31, the third motor 41, the fourth motor 511, the fifth motor, the controller, and the observation device.

[0059] In summary, the UAV suspension device test system provided in this embodiment can simulate the two-dimensional movement of a UAV in the horizontal direction. Furthermore, during the simulation of the two-dimensional movement of the UAV in the horizontal direction, the UAV suspension device 100 can be driven to rotate around the first axis yaw axis and the second axis pitch axis to simulate the influence of the UAV yaw angle and pitch angle on the UAV suspension device 100.

[0060] This embodiment also provides a method for testing a drone suspension device, which uses the aforementioned drone suspension device testing system to test the drone suspension device 100, including:

[0061] S1. Turn on the power to the UAV suspension device test system and start the controller.

[0062] S2. Check the equipment connections, including checking whether the first drive assembly 3, the second drive assembly 4, the suspension mechanism 5, the controller, and the observation device are working properly.

[0063] S3. Initialize the controller and input the initial parameters of each component of the UAV suspension device test system, including the zero-point position of each motor, the initial length of the released portion of the rope, and the angle zero point of the suspension mechanism 5. The angle zero point of the suspension mechanism 5 includes the yaw angle zero point and the pitch angle zero point.

[0064] S4. The controller controls the first drive assembly 3 to drive the second support beam 2 to move along the first direction, controls the second drive assembly 4 to drive the suspension mechanism 5 to move along the second direction, controls the first motor to drive the winding reel 1001 to rotate, controls the third drive assembly 51 to drive the UAV suspension device 100 to rotate around the first axis, and / or drives the fourth drive assembly to drive the UAV suspension device 100 to rotate around the second axis. The controller collects the position of the suspension device, the rotation angle of the UAV suspension device 100 around the first axis, the length of the released part of the rope, the rotation angle of the UAV suspension device 100 around the second axis, and the position of the load, so as to obtain the correspondence between the swing angle of the released part of the rope and the length of the released part of the rope during the test, as well as other state parameters of the UAV suspension device 100, so as to facilitate the subsequent calculation of UAV stability index and dynamic response curve plotting.

[0065] S5. Save all raw data and processing results, and generate an experimental report.

[0066] S6. Turn off the power, unload the load and check whether the ropes, suspension mechanism 5, motors and other equipment are damaged or need maintenance. Record the operation status of the UAV suspension device test system, including equipment failures, experimental abnormalities, etc., and fill in the equipment usage record form.

[0067] The above description is only a preferred embodiment of the present invention. It should be noted that for those skilled in the art, several improvements and substitutions can be made without departing from the technical principles of the present invention, and these improvements and substitutions should also be considered within the scope of protection of the present invention.

Claims

1. A test system for a drone suspension device, used to test a drone suspension device (100), the drone suspension device (100) comprising a winding reel (1001), a first motor (1002), and a rope, the first motor (1002) being used to drive the winding reel (1001) to rotate to release or wind the rope, the bottom end of the rope being connected to a load, the drone suspension device test system having two perpendicular directions: a first direction, a second direction, and a third direction, characterized in that... It includes a first support beam (1), a second support beam (2), a first drive assembly (3), a second drive assembly (4), a suspension mechanism (5), a controller, and an observation device; The first drive assembly (3) is disposed on the first support beam (1), and the second support beam (2) is connected to the first drive assembly (3). The first drive assembly (3) is used to drive the second support beam (2) to move along the first direction. The second drive assembly (4) is disposed on the second support beam (2), the hanging mechanism (5) is disposed on the second drive assembly (4), the second drive assembly (4) is used to drive the hanging mechanism (5) to move along the second direction, the UAV suspension device (100) is disposed on the hanging mechanism (5), and the rotation axis of the winding disc (1001) is parallel to the second direction; The observation device is used to monitor the position of the load along the first direction, the second direction, and the third direction; The first drive component (3), the second drive component (4), and the observation device are all communicatively connected to the controller; There are two first support beams (1), which are spaced apart along the second direction. The first drive assembly (3) is arranged in a one-to-one correspondence with the first support beam (1). The two ends of the second support beam (2) are respectively connected to the two first drive assemblies (3). The first drive assembly (3) includes a second motor (31), a first gear, and a first rack; The first support beam (1) extends along the first direction, the first rack is fixedly disposed on the first support beam (1) and extends along the first direction, the first gear is connected to the second motor (31) for transmission, and the first gear meshes with the first rack; The second drive assembly (4) includes a third motor (41), a second gear, a second rack, and a connector (42). The second support beam (2) extends along the second direction, the connector (42) connects the third motor (41) and the second support beam (2), the second rack is fixedly mounted on the second support beam (2) and extends along the second direction, the second gear is connected to the third motor (41) in a transmission, and the second gear meshes with the second rack; The connector (42) includes a first limiting plate (421), a second limiting plate (422), and a connecting shaft (423). The first limiting plate (421) and the second limiting plate (422) are disposed on both sides of the second support beam (2), and the connecting shaft (423) connects the first limiting plate (421) and the second limiting plate (422).

2. The UAV suspension device testing system according to claim 1, characterized in that, The suspension mechanism (5) includes a third drive assembly (51), which is disposed on the second drive assembly (4). The UAV suspension device (100) is disposed on the third drive assembly (51). The third drive assembly (51) is used to drive the UAV suspension device (100) to rotate around a first axis. The rotation axis of the winding reel (1001), the first direction and the second direction are all perpendicular to the first axis. The third drive assembly (51) is communicatively connected to the controller.

3. The UAV suspension device testing system according to claim 2, characterized in that, The third drive assembly (51) includes a fourth motor (511) and a mounting bracket (512). The fourth motor (511) is mounted on the second limiting plate (422), the mounting frame (512) is connected to the fourth motor (511) in a transmission manner, the fourth motor (511) can drive the mounting frame (512) to rotate around the first axis, and the UAV suspension device (100) is mounted on the mounting frame (512).

4. The UAV suspension device testing system according to claim 3, characterized in that, The suspension mechanism (5) further includes a fourth drive assembly, which is disposed on the mounting frame (512). The UAV suspension device (100) is disposed on the fourth drive assembly. The third drive assembly (51) can drive the fourth drive assembly to rotate around the first axis, and the UAV suspension device (100) can rotate around the first axis with the fourth drive assembly. The fourth drive assembly is used to drive the UAV suspension device (100) to rotate around the second axis, which is parallel to the rotation axis of the winding disc (1001).

5. The UAV suspension device testing system according to claim 4, characterized in that, The fourth drive assembly includes two fifth motors. The mounting bracket (512) includes a left mounting bracket and a right mounting bracket. The left mounting bracket and the right mounting bracket are respectively disposed on both sides of the fourth motor (511). The two fifth motors are respectively disposed on the left mounting bracket and the right mounting bracket. The output shafts of the two fifth motors are connected to the UAV suspension device (100) for transmission. The fifth motors can drive the UAV suspension device (100) to rotate around the second axis.

6. The UAV suspension device testing system according to any one of claims 1-5, characterized in that, When the UAV suspension device (100) is tested using the UAV suspension device test system, the controller controls the first drive component (3) to drive the second support beam (2) to move along the first direction, controls the second drive component (4) to drive the suspension mechanism (5) to move along the second direction, and / or controls the first motor to drive the winding disc (1001) to rotate. The controller collects the position of the suspension device and the position of the load.

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