Unmanned aerial vehicle wing strength detection device

Abstract

The utility model provides a kind of unmanned aerial vehicle wing strength detection device, it is related to wing detection technical field, it includes clamping assembly, multidirectional loading assembly and detection platform, clamping assembly includes fastening seat, movable clamping seat, clamping seat, movable pressing plate and clamping driving part, fastening seat and movable clamping seat are oppositely arranged at the both ends of detection platform, clamping seat is set in the opening structure of fastening seat and movable clamping seat, the output end of clamping driving part is connected with movable pressing plate, the utility model is integrated lifting drive, rotary drive and transverse movement mechanism in multidirectional loading assembly, realize torsion, bending and extrusion comprehensive test under the once clamping of wing, and setting linkage's deformation monitoring component, make camera and movable clamping seat form motion coupling, can dynamically monitor wing deformation, through the guide structure of transmission mechanism, realize the accurate control of wing load type and the reliable simulation of complex stress field, the efficient and comprehensive evaluation of wing comprehensive mechanical property.

Description

Technical Field

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

[0002] As an important type of modern aircraft, the flight performance and safety of unmanned aerial vehicles (UAVs) largely depend on the structural strength of their components. Among these, the wing, as a primary load-bearing component, must withstand aerodynamic loads, its own weight, and various maneuvering loads during flight; its strength and reliability directly affect the overall safety of the UAV. Therefore, rigorous strength testing of the wing is a crucial step in the research, development, and production of UAVs.

[0003] Currently, strength testing of UAV wings is mostly conducted using simple mechanical testing benches. Existing testing methods typically include static bending tests and torsional stiffness tests. When conducting bending tests, one end of the wing is fixed while the other end is subjected to a vertical load or a moving support point for compression. However, when conducting torsional tests, additional clamps are needed to manually apply torque to the wing. Problems exist: (1) Bending and torsional tests often need to be conducted separately on different equipment, which is cumbersome, inefficient, and difficult to simulate the coupling effect of bending and torsional deformation of the wing under complex working conditions. (2) Existing clamping devices are difficult to firmly clamp both ends of wings with different airfoils at the same time, and uneven force during testing can easily lead to wing slippage or local stress concentration, affecting the accuracy of the test results. (3) The testing process relies heavily on manual observation and recording, lacking real-time, multi-angle monitoring and data retention of the wing deformation process, making it difficult to accurately capture the deformation state of the wing at the moment of failure. Therefore, it is necessary to propose an integrated and highly automated UAV wing strength testing device. Utility Model Content

[0004] To address the shortcomings of the existing technology, the present invention aims to provide a UAV wing strength testing device. Through the coordination of the lifting drive, rotation drive, and lateral movement mechanism in the multi-directional loading component, it achieves comprehensive testing of the wing's torsion, bending, and compression under a single clamping. Furthermore, it is equipped with a linked deformation monitoring component, which enables motion coupling between the camera and the movable clamping seat to dynamically monitor the deformation process. Through the guiding structure of the transmission mechanism, it achieves precise control of the wing load type and reliable simulation of complex stress scenarios, enabling efficient and comprehensive evaluation of the wing's overall mechanical performance.

[0005] This utility model provides a device for testing the wing strength of a UAV, comprising a clamping assembly, a multi-directional loading assembly, and a testing platform. The clamping assembly includes a fastening seat, a movable clamping seat, a clamping seat, a movable pressure plate, and a clamping drive component. The fastening seat and the movable clamping seat are positioned opposite each other at both ends of the testing platform. The clamping seat is located within the opening structure of the fastening seat and the movable clamping seat, and has a clamping groove within it. The movable pressure plate is slidably disposed within the clamping groove. The fixed end of the clamping drive component is connected to the inner wall of the opening structure of the fastening seat and the movable clamping seat, and the output end of the clamping drive component is connected to the movable pressure plate. The multi-directional loading assembly includes a lifting drive mechanism, a rotation drive mechanism, and a lateral movement mechanism. The lifting drive mechanism includes a lifting plate, a lifting drive component, a first guide rod, and a slider. The middle part of the lifting plate is connected to the movable clamping seat. The first side is rotatably connected, the output end of the lifting drive component is connected to the lifting plate, the bottom end of the first guide rod is connected to the transverse sliding plate of the transverse moving mechanism, the slider is slidably connected to the first guide rod, and the slider is connected to the lifting plate; the rotary drive mechanism includes a rotary motor, a drive gear and a driven gear ring, the driven gear ring is fixed on the outside of the movable clamping seat, the drive gear meshes with the driven gear ring, the output shaft of the rotary motor is connected to the drive gear, the transverse moving mechanism is set on the detection platform, the transverse moving mechanism includes a moving screw, a screw motor, a transverse sliding plate and a transverse guide rod, the moving screw and the transverse sliding plate are helically driven, the output shaft of the screw motor is connected to the moving screw, the transverse guide rod is arranged parallel to both sides of the moving screw, and the two ends of the transverse guide rod are connected to the detection platform, the transverse guide rod is slidably connected to the transverse sliding plate.

[0006] Preferably, it also includes a deformation monitoring component, which includes a first link, a second link, a second guide rod, and a camera. The first end of the first link is connected to the slider of the lifting drive component, the first end of the second link is connected to the transverse slide plate, the first end of the second guide rod is connected to the second link, and the second end of the second guide rod passes through the first link and is slidably connected to the first link. Multiple cameras are arranged on the side of the first link facing the detection platform.

[0007] Preferably, a baffle is provided on the movable lead screw, with a transverse sliding plate passing through both sides of the baffle and slidably connected to the transverse sliding plate, and both ends of the baffle are fixedly connected to the detection platform.

[0008] Preferably, an annular baffle is fixedly connected to the outside of the movable clamping seat, and the outer diameter of the annular baffle is larger than the outer diameter of the driven gear ring.

[0009] Preferably, a set of vertical guide bars are slidably connected to both sides of the movable pressure plate, and the vertical guide bars are fixedly connected to the inner wall of the clamping groove.

[0010] Preferably, it also includes a main controller, which is set on the detection platform and is electrically connected to the clamping drive, the lifting drive, the rotary motor and the lead screw motor.

[0011] Compared with the prior art, the beneficial effects of this utility model are reflected in: This utility model of UAV wing strength testing device integrates multiple testing functions such as wing clamping, torsion, lifting and bending, and compression bending into one unit. Through the lifting drive, rotation drive and lateral movement mechanism in the multi-directional loading component, the wing can complete multiple strength tests after one clamping, realizing precise control of wing load type and reliable simulation of complex stress scenarios, effectively improving testing efficiency and data consistency.

[0012] This utility model of a drone wing strength testing device uses an automatically linked deformation monitoring component to enable the camera and the movable clamping seat to move synchronously during lifting and lateral movement, achieving a highly efficient and comprehensive evaluation of the wing's overall mechanical properties. Furthermore, the device incorporates guide structures in each transmission system to ensure that all loads are applied accurately and stably to the wing, offering advantages such as high efficiency, precision, reliability, and a high degree of automation. Attached Figure Description

[0013] Figure 1 This is a schematic diagram of the overall structure of the UAV wing strength testing device of this utility model; Figure 2 This is a side view schematic diagram of the UAV wing strength testing device of this utility model; Figure 3 This is a schematic diagram of the right side of the UAV wing strength testing device of this utility model; Figure 4 This is a cross-sectional schematic diagram of the UAV wing strength testing device of this utility model; Figure 5 This is an enlarged structural diagram of point A in the UAV wing strength testing device of this utility model.

[0014] Figure label: Fastening seat 1, detection platform 2, movable clamping seat 3, clamping seat 4, clamping groove 5, movable pressure plate 6, clamping drive component 7, lifting plate 8, rotary motor 9, drive gear 10, driven gear ring 11, lifting drive component 12, transverse slide plate 13, baffle plate 14, first guide rod 15, slider 16, main controller 17, first connecting rod 18, second guide rod 19, camera 20, second connecting rod 21, annular baffle 22, lead screw motor 23, transverse guide rod 24, moving lead screw 25. Detailed Implementation

[0015] The embodiments of this utility model will now be described with reference to the accompanying drawings.

[0016] This utility model relates to a drone wing strength testing device, such as... Figure 1 , Figure 2 and Figure 5As shown, it includes a clamping assembly, a multi-directional loading assembly, and a detection platform 2. The clamping assembly includes a fastening seat 1, a movable clamping seat 3, a clamping seat 4, a clamping groove 5, a movable pressure plate 6, and a clamping drive 7. The fastening seat 1 and the movable clamping seat 3 are arranged opposite each other at both ends of the detection platform 2. The clamping seat 4 is disposed in the opening structure of the fastening seat 1 and the movable clamping seat 3. The clamping groove 5 is opened in the clamping seat 4. The movable pressure plate 6 is slidably disposed in the clamping groove 5. The fixed end of the clamping drive 7 is connected to the inner wall of the opening structure of the fastening seat 1 and the movable clamping seat 3. The output end of the clamping drive 7 is connected to the movable pressure plate 6. A set of vertical guide bars are slidably connected to both sides of the movable pressure plate 6, and the vertical guide bars are fixedly connected to the inner wall of the clamping groove 5. It also includes a main controller 17, which is disposed on the detection platform 2 and is electrically connected to the clamping drive 7, the lifting drive 12, the rotary motor 9, and the lead screw motor 23. The multi-directional loading assembly includes a lifting drive mechanism, a rotation drive mechanism, and a lateral movement mechanism. The lifting drive mechanism includes a lifting plate 8, a lifting drive component 12, a first guide rod 15, and a slider 16. The middle part of the lifting plate 8 is rotatably connected to the first side of the movable clamping seat 3. The output end of the lifting drive component 12 is connected to the lifting plate 8. The bottom end of the first guide rod 15 is connected to the lateral slide plate 13 of the lateral movement mechanism. The slider 16 is slidably connected to the first guide rod 15 and is also connected to the lifting plate 8.

[0017] like Figure 2 As shown, the deformation monitoring component includes a first connecting rod 18, a second connecting rod 21, a second guide rod 19, and cameras 20. The first end of the first connecting rod 18 is connected to the slider 16 of the lifting drive component. The first end of the second connecting rod 21 is connected to the transverse sliding plate 13. The first end of the second guide rod 19 is connected to the second connecting rod 21, and the second end of the second guide rod 19 passes through the first connecting rod 18 and is slidably connected to the first connecting rod 18. Multiple cameras 20 are arranged on the side of the first connecting rod 18 facing the detection platform 2. A baffle plate 14 is provided on the moving lead screw 25. Both sides of the baffle plate 14 pass through the transverse sliding plate 13 and are slidably connected to the transverse sliding plate 13, and both ends of the baffle plate 14 are fixedly connected to the detection platform 2.

[0018] like Figure 3 As shown, the rotary drive mechanism includes a rotary motor 9, a drive gear 10, and a driven gear ring 11. The driven gear ring 11 is fixedly mounted on the outside of the movable clamping seat 3. The drive gear 10 meshes with the driven gear ring 11. The output shaft of the rotary motor 9 is connected to the drive gear 10. The transverse movement mechanism is set on the detection platform 2. An annular baffle 22 is fixedly connected to the outside of the movable clamping seat 3. The outer diameter of the annular baffle 22 is larger than the outer diameter of the driven gear ring 11.

[0019] like Figure 4As shown, the lateral movement mechanism includes a movable lead screw 25, a lead screw motor 23, a lateral slide plate 13, and a lateral guide rod 24. The movable lead screw 25 and the lateral slide plate 13 are driven by a screw. The output shaft of the lead screw motor 23 is connected to the movable lead screw 25. The lateral guide rod 24 is arranged parallel to both sides of the movable lead screw 25, and both ends of the lateral guide rod 24 are connected to the detection platform 2. The lateral guide rod 24 is slidably connected to the lateral slide plate 13.

[0020] The following description, in conjunction with embodiments, further illustrates the UAV wing strength testing device of this invention: First, place the two ends of the wing of the UAV to be tested into the clamping grooves 5 of the fastening seat 1 and the movable clamping seat 3 respectively. The two clamping drive components 7 are controlled by the main controller 17. The output end of the clamping drive component 7 pushes the movable pressure plate 6 to slide upward along the vertical guide strip in the clamping groove 5, thereby firmly pressing the two ends of the wing from below and completing the clamping.

[0021] 1. Torsional strength test; The rotary motor 9 drives the drive gear 10 to rotate, and the drive gear 10 meshes with the driven gear ring 11, causing the movable clamping seat 3 to rotate around its own axis. The rotation of the movable clamping seat 3 causes one end of the wing to rotate, causing the wing to undergo torsional deformation. The main controller 17 adjusts and controls the degree of wing torsion by precisely controlling the rotation angle and number of rotations of the rotary motor 9.

[0022] 2. Lifting and bending detection; The output end of the lifting drive component 12 pushes the lifting plate 8 to move up and down. The lifting plate 8 slides along the first guide rod 15 through the sliders 16 on both sides to ensure smooth movement. The lifting plate 8 drives the movable clamping seat 3, which is rotatably connected to it, to move up or down synchronously, thereby causing one end of the wing to move up or down, causing the wing to bend. The main controller 17 precisely adjusts the bending amplitude of the wing by controlling the stroke of the lifting drive component 12.

[0023] 3. Extrusion and bending test; After the lifting and bending reaches the predetermined position, the main controller 17 controls the lead screw motor 23, which drives the moving lead screw 25 to rotate. The rotational motion of the moving lead screw 25 is converted into the linear motion of the transverse slide plate 13, causing it to move horizontally along the transverse guide rod 24 towards the fixed end clamp 1. The transverse slide plate 13 drives the movable clamping seat 3 assembly on it to move horizontally in sync, further squeezing the wing, increasing its bending curvature, and simulating a larger load. The main controller 17 controls the number of rotations of the lead screw motor 23 to precisely control the lateral movement distance and squeezing force.

[0024] 4. Real-time deformation monitoring and data transmission; The camera 20 performs real-time imaging and detection: During lifting and bending detection, the lifting plate 8 drives the first connecting rod 18 to rise and fall along the second guide rod 19 via the slider 16; during compression and bending detection, the lateral sliding plate 13 drives the second connecting rod 21 to move laterally, and guides the first connecting rod 18 to move synchronously via the second guide rod 19. The deformation monitoring component enables the camera 20 to follow the movement of the movable clamping seat 3, maintaining the shooting angle. The camera 20 transmits the captured wing deformation images to the connected video terminal in real time to observe the changes in the wing's bending, twisting, and potential cracks.

[0025] 5. Resetting after testing and evaluating results; After the test is completed, the main controller 17 controls all drive components, including the rotary motor 9, lifting drive component 12, and lead screw motor 23, to reset, so that the device returns to its initial state. The clamping drive component 7 is then retracted, the movable pressure plate 6 is released, the wing is removed, and the wing is observed to see if it is broken or has permanent plastic deformation. The wing is checked to see if it can return to its original shape, and its elastic recovery ability is evaluated.

[0026] This utility model of a UAV wing strength testing device achieves comprehensive testing of torsion, bending, and compression of the wing in a single clamping operation through the coordination of lifting drive, rotation drive, and lateral movement mechanism in a multi-directional loading component. It also features a linked deformation monitoring component that enables motion coupling between the camera 20 and the movable clamping seat 3 to dynamically monitor the deformation process. Through the guiding structure of the transmission mechanism, it achieves precise control of the wing load type and reliable simulation of complex stress scenarios, enabling efficient and comprehensive evaluation of the wing's overall mechanical performance.

[0027] The embodiments described above are merely preferred embodiments of the present utility model and are not intended to limit the scope of the present utility model. Various modifications and improvements made to the technical solutions of the present utility model by those skilled in the art without departing from the spirit of the present utility model should fall within the protection scope defined by the claims of the present utility model.

Claims

1. A device for testing the strength of a UAV wing, characterized in that: It includes a clamping component, a multi-directional loading component, and a detection platform. The clamping assembly includes a fastening seat, a movable clamping seat, a clamping seat, a movable pressure plate, and a clamping drive. The fastening seat and the movable clamping seat are arranged opposite to each other at both ends of the detection platform. The clamping seat is set in the opening structure of the fastening seat and the movable clamping seat. The clamping seat is provided with a clamping groove. The movable pressure plate is slidably set in the clamping groove. The fixed end of the clamping drive is connected to the inner wall of the opening structure of the fastening seat and the movable clamping seat, and the output end of the clamping drive is connected to the movable pressure plate. The multi-directional loading component includes a lifting drive mechanism, a rotation drive mechanism, and a lateral movement mechanism. The lifting drive mechanism includes a lifting plate, a lifting drive component, a first guide rod, and a slider. The middle part of the lifting plate is rotatably connected to the first side of the movable clamping seat. The output end of the lifting drive component is connected to the lifting plate. The bottom end of the first guide rod is connected to the lateral slide plate of the lateral movement mechanism. The slider is slidably connected to the first guide rod and is also connected to the lifting plate. The rotary drive mechanism includes a rotary motor, a drive gear, and a driven gear ring. The driven gear ring is fixed to the outside of the movable clamping seat. The drive gear meshes with the driven gear ring. The output shaft of the rotary motor is connected to the drive gear. The lateral movement mechanism is set on the detection platform. The lateral movement mechanism includes a moving lead screw, a lead screw motor, a lateral slide plate, and a lateral guide rod. The moving lead screw and the lateral slide plate are driven by a helical transmission. The output shaft of the lead screw motor is connected to the moving lead screw. The lateral guide rod is arranged parallel to both sides of the moving lead screw, and both ends of the lateral guide rod are connected to the detection platform. The lateral guide rod is slidably connected to the lateral slide plate.

2. The UAV wing strength testing device according to claim 1, characterized in that: It also includes a deformation monitoring component, which includes a first link, a second link, a second guide rod, and a camera. The first end of the first link is connected to the slider of the lifting drive component, the first end of the second link is connected to the horizontal sliding plate, the first end of the second guide rod is connected to the second link, and the second end of the second guide rod passes through the first link and is slidably connected to the first link. Multiple cameras are set on the side of the first link facing the detection platform.

3. The UAV wing strength testing device according to claim 1, characterized in that: A baffle is installed on the movable lead screw. The baffle has a transverse sliding plate running through both sides and is slidably connected to the transverse sliding plate. Both ends of the baffle are fixedly connected to the detection platform.

4. The UAV wing strength testing device according to claim 1, characterized in that: An annular baffle is fixedly connected to the outside of the movable clamping seat. The outer diameter of the annular baffle is larger than the outer diameter of the driven gear ring.

5. The UAV wing strength testing device according to claim 1, characterized in that: A set of vertical guide bars is slidably connected to both sides of the movable pressure plate, and the vertical guide bars are fixedly connected to the inner wall of the clamping groove.

6. The UAV wing strength testing device according to claim 1, characterized in that: It also includes a main controller, which is set on the detection platform and is electrically connected to the clamping drive, lifting drive, rotary motor and lead screw motor.

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