Impact resistance test device and method for manufacturing low-altitude unmanned aerial vehicle

Abstract

The invention discloses an impact resistance test device and method for low-altitude unmanned aerial vehicle manufacturing, and relates to the technical field of unmanned aerial vehicle impact resistance detection, the impact resistance test device comprises a machine base, the outer wall of the bottom of the machine base is fixedly connected with a base, and the top of the machine base is provided with an impact force generation assembly used for providing impact force for an aerial vehicle body. A rotating assembly used for adjusting the direction of the impact force generating assembly is arranged in the machine base. A visual detection assembly used for monitoring the state of the aircraft body is arranged on the top of the machine base, and the visual detection assembly is arranged on the opposite side of the impact force generation assembly. According to the invention, low-altitude complex airflow can be accurately simulated, multidirectional testing can be realized, the state of the aircraft can be monitored in real time by means of the angle-adjustable image collector, the accuracy of test data is ensured, and the defects of inaccurate airflow simulation, single function and insufficient monitoring of the existing device are overcome.

Description

Technical Field

[0001] This invention relates to the field of shock resistance testing technology for unmanned aerial vehicles (UAVs), and in particular to a shock resistance testing device and method for manufacturing low-altitude UAVs. Background Technology

[0002] During the flight of low-altitude unmanned aerial vehicles (UAVs), airflow changes are one of the key factors affecting their flight stability and safety. In low-altitude environments, airflow is characterized by high uncertainty, rapid changes in velocity, and complex directions. Sudden gusts and turbulence can exert strong impacts on UAVs. If an UAV's resistance to airflow impacts is insufficient, it may lead to loss of flight attitude control, affecting mission efficiency, or even structural damage and serious accidents such as crashes. Currently, most commercially available testing devices for unmanned aerial vehicles (UAVs) focus on performance and endurance testing, with relatively few specifically designed for testing resistance to airflow impact. Furthermore, existing devices have several shortcomings. Some devices lack accurate airflow simulation, failing to realistically reproduce the complex airflow environment at low altitudes; others have limited functionality, only capable of testing specific types or sizes of UAVs. Therefore, there is an urgent need for a shock resistance testing device and method for low-altitude UAV manufacturing to address these issues. Summary of the Invention

[0003] The purpose of this invention is to address the shortcomings of existing technologies by proposing an impact resistance testing device and method for manufacturing low-altitude unmanned aerial vehicles. Its advantages include: accurate simulation of complex low-altitude airflow and multi-directional testing; real-time monitoring of the aircraft's status via an adjustable-angle image acquisition device to ensure accurate test data; and overcoming the deficiencies of existing devices such as inaccurate airflow simulation, limited functionality, and insufficient monitoring.

[0004] To achieve the above objectives, the present invention adopts the following technical solution: An impact resistance testing device for manufacturing low-altitude unmanned aerial vehicles includes a base, a base fixedly connected to the bottom outer wall of the base, an impact force generating component for providing impact force to the aircraft body on the top of the base, and a rotating component for adjusting the direction of the impact force generating component inside the base. The top of the base is equipped with a visual inspection component for monitoring the status of the aircraft body, and the visual inspection component is located on the opposite side of the impact force generating component.

[0005] The above technical solution provides a basic installation platform, enhances overall stability, generates airflow impacts in a targeted manner, allows for flexible adjustment of the impact direction, and captures the aircraft's status in real time. The four components work together to achieve a complete test process from impact generation to status monitoring, solving the problems of limited functionality and insufficient monitoring in existing devices, and providing comprehensive support for impact resistance testing.

[0006] The present invention is further configured such that the impact force generating component includes a housing disposed above the base, a fan is fixedly connected to one outer wall of the housing, an air outlet slot is provided on the side of the housing away from the fan, and equal-distance adjustment plates are rotatably connected to the inner walls of both sides of the air outlet slot.

[0007] The above technical solutions can change the direction and speed of airflow, simulate different airflow states at low altitudes, solve the defects of inaccurate airflow simulation in existing devices, and improve the realism of test scenarios.

[0008] The present invention is further configured such that the rotating assembly includes a second motor fixedly connected to the top outer wall of the base, a second rotating column fixedly connected to the output end of the second motor, a driving gear disk fixedly connected to the outer circumference of the second rotating column, a ring tooth plate meshing with the outer circumference of the driving gear disk, a gear ring meshing with the outer circumference of the ring tooth plate, a ring plate for ensuring stable rotation of the gear ring fixedly connected to the bottom inner wall of the base, a second support column fixedly connected to the top outer wall of the gear ring, and one end of the second support column away from the gear ring fixedly connected to the bottom outer wall of the housing.

[0009] The above technical solutions enable the adjustment of the overall direction of the impact force generating component, allowing impact tests to be conducted on different positions of the aircraft body, breaking the limitations of existing testing positions and improving the adaptability of the device.

[0010] The present invention is further configured such that a support plate is fixedly connected to the bottom inner wall of the base, a circular plate is fixedly connected to the top of the support plate, the outer circumferential wall of the circular plate forms a limiting annular groove with the top of the base, and the second support column is slidably connected to the limiting annular groove.

[0011] Through the above technical solution: when the second support column rotates with the gear ring, the limiting ring groove can limit its offset, ensure the stability of the impact force generating component during rotation, avoid the impact test accuracy being affected by shaking, and further improve the reliability of the test data.

[0012] The invention is further configured such that a housing is fixedly connected to the top outer wall of the horizontal plate, a fourth rotating rod is rotatably connected to the inner wall of one side of the housing, a third helical gear is fixedly connected to the outer circumference of the fourth rotating rod, a fourth helical gear is meshed with the outer circumference of the third helical gear, and a first motor is fixedly connected to one end of the third helical gear extending to the outside of the housing.

[0013] Through the above technical solution, this transmission method can achieve precise power transmission and direction conversion, providing power support for the angle adjustment of the adjustment plate and the angle adjustment of the image acquisition device, ensuring the stable operation of the two key functions, and improving the overall linkage of the device.

[0014] The present invention is further configured such that a first vertical plate is fixedly connected to the top outer wall of the housing, a horizontal plate is fixedly connected to the top of the first vertical plate, the housing is fixedly connected to the horizontal plate, and a first support column is fixedly connected to the bottom of the other end of the horizontal plate, and the bottom end of the first support column is fixedly connected to the top outer wall of the gear ring.

[0015] The above technical solutions can form a stable connection structure of "gear ring - first support column - horizontal plate - first vertical plate - box", ensuring the integrity of the impact force generating component and the rotating component when they are linked, and avoiding loose parts from affecting the test results.

[0016] The invention is further configured such that a threaded rod is fixedly connected to the bottom outer wall of a fourth helical gear, a threaded cylinder is threadedly connected to the outer circumference of the threaded rod, a movable plate is rotatably connected to one side of the threaded cylinder, and the other end of the movable plate is rotatably connected to the adjusting plate.

[0017] The above technical solution provides a guide limit for the threaded cylinder, preventing it from rotating synchronously with the threaded rod and ensuring that it moves only in the vertical direction. This allows the movable plate to precisely push the adjusting plate to adjust the angle, ensuring the accuracy of airflow regulation.

[0018] The present invention is further configured such that a horizontal column is fixedly connected to one side of the outer wall of the threaded cylinder, and a slider is fixedly connected to one end of the horizontal column, and the slider is slidably connected to one side of the outer wall of the box.

[0019] The above technical solutions ensure that the threaded cylinder can move vertically stably.

[0020] The invention is further configured such that a first rotating column is fixedly connected to the bottom outer wall of another fourth helical gear, a first helical gear is fixedly connected to the bottom end of the first rotating column, a second helical gear meshes with the outer circumferential wall of the first helical gear, a second vertical plate is fixedly connected to the bottom outer wall of the horizontal plate, a rotating seat is fixedly connected to one side outer wall of the second vertical plate, a third rotating column is rotatably connected to the inner circumferential wall of the rotating seat, a rotating block is fixedly connected to the outer circumferential wall of the third rotating column, an image acquisition device is fixedly connected to one end of the rotating block, a second helical gear is fixedly connected to one end of the third rotating column, the second helical gear meshes with the first support column, and a positioning plate is fixedly connected to one side outer wall of the second vertical plate to ensure the stable rotation of the first rotating column.

[0021] Through the above technical solutions, the positioning plate provides stable support for the first rotating column, preventing it from shifting during rotation, ensuring that the image acquisition device can accurately capture the state of the aircraft body, realize real-time monitoring of the test process, and provide a clear basis for data analysis.

[0022] A method for testing the impact resistance of low-altitude unmanned aerial vehicles (UAVs) is applied to the impact resistance testing device for manufacturing low-altitude UAVs described in the above embodiments, and includes the following steps: S1: Adjust the low-altitude unmanned aerial vehicle to be tested to a normal flight state and place it on the opposite side of the visual inspection component on the top of the base to ensure that the aircraft is in a stable hover or preset flight attitude. S2: Start the first motor, and adjust the angle of the adjustment plate at the air outlet of the impact force generating component through the transmission structure driven by it. Set the target airflow direction and wind speed according to the test requirements, and then start the fan so that the airflow is guided by the box and blown out from the air outlet, initially forming the preset impact force on the aircraft body. S3: If it is necessary to conduct impact resistance tests on different positions of the aircraft body, start the second motor, drive the gear ring and impact force generating component to rotate along the limiting ring groove on the top of the base through the rotating component, adjust the orientation of the impact force generating component, and apply airflow impact to the key positions of the aircraft body such as front, back, left and right in sequence, while keeping the visual inspection component working continuously during the process. S4: During the entire impact test, the angle of the image acquisition device is adjusted by the transmission structure driven by the first motor, so that it can capture the attitude change, structural deformation and other state information of the aircraft body in real time, and simultaneously record the operating data of the aircraft body under different impact parameters. After the test, the monitoring data and image data are sorted out to complete the impact resistance performance analysis.

[0023] The beneficial effects of this invention are as follows: A shock resistance testing device and method for manufacturing low-altitude unmanned aerial vehicles (UAVs) is disclosed. Through an impact force generating component, airflow generated by a fan is guided by a housing and blown out through an air outlet sluice. Simultaneously, a first motor drives a related transmission structure to rotate an adjustment plate, achieving precise adjustment of the airflow direction and speed at the air outlet sluice. This design effectively solves the problem of inaccurate airflow simulation in existing devices. It can simulate airflow impacts of different angles and intensities according to test requirements, more closely reflecting the actual airflow characteristics at low altitudes. This provides a more realistic environmental basis for testing the shock resistance performance of aircraft and meets the needs of diverse test scenarios.

[0024] An impact resistance testing device and method for manufacturing low-altitude unmanned aerial vehicles (UAVs) is disclosed. In this device, a rotating component is driven by a second motor through a gear transmission structure, which drives the impact force generating component to rotate stably along a limiting ring groove on the top of the base. The sliding fit between the second support column and the limiting ring groove further ensures the rotational stability. This function breaks the limitation of existing devices that can only test the aircraft in a specific direction. Impact resistance tests of the aircraft in different directions can be completed without changing the device, which greatly improves the adaptability of the device to different testing requirements, reduces testing costs, and can also be adapted to testing more types and sizes of low-altitude UAVs.

[0025] An impact resistance testing device and method for manufacturing low-altitude unmanned aerial vehicles (UAVs) is disclosed. Through an image acquisition unit within a visual inspection component, the angle can be flexibly adjusted under the action of a transmission structure driven by a first motor. A positioning plate ensures the stability of the transmission process, enabling the image acquisition unit to capture the attitude changes and structural state of the aircraft body under impact in real time. This design avoids the problem of incomplete test data caused by the lack of effective monitoring in existing devices, achieving dynamic and comprehensive monitoring of the testing process. It provides reliable data support for staff to accurately analyze the impact resistance performance of the aircraft, facilitating subsequent optimization and improvement of the aircraft's impact resistance capabilities. Attached Figure Description

[0026] Figure 1 This is a schematic diagram of the overall right side structure of the impact resistance testing device and method for manufacturing low-altitude unmanned aerial vehicles proposed in this invention. Figure 2 This is a schematic diagram of the overall left side structure of the impact resistance testing device and method for manufacturing low-altitude unmanned aerial vehicles proposed in this invention. Figure 3 This invention proposes an impact resistance testing device and method for manufacturing low-altitude unmanned aerial vehicles. Figure 2 Enlarged structural diagram at point A; Figure 4 This is a schematic diagram of the disassembled circular plate structure of the impact resistance testing device and method for manufacturing low-altitude unmanned aerial vehicles proposed in this invention. Figure 5This invention proposes an impact resistance testing device and method for manufacturing low-altitude unmanned aerial vehicles. Figure 4 Enlarged structural diagram at point B; Figure 6 This is a schematic diagram of the overall front structure of the impact resistance testing device and method for manufacturing low-altitude unmanned aerial vehicles proposed in this invention. Figure 7 This is a cross-sectional view of the shell structure of the impact resistance testing device and method for manufacturing low-altitude unmanned aerial vehicles proposed in this invention.

[0027] In the diagram: 1. Base; 2. Circular plate; 3. Base; 4. Shell; 5. Horizontal plate; 6. First support column; 7. Aircraft body; 8. First motor; 9. First vertical plate; 10. Box; 11. Second support column; 12. Fan; 13. First rotating column; 14. Second vertical plate; 15. Positioning plate; 16. First helical gear; 17. Image acquisition device; 18. Second helical gear; 19. Drive gear disk; 20. Support plate; 21. Gear ring; 22. Ring plate; 23. Ring tooth plate; 24. Second rotating column; 25. Slider; 26. Horizontal column; 27. Adjustment plate; 28. Air outlet slot; 29. ​​Movable plate; 30. Threaded cylinder; 31. Threaded rod; 32. Second motor; 33. Rotating seat; 34. Third rotating column; 35. Rotating block; 36. Fourth rotating rod; 37. Third helical gear; 38. Fourth helical gear. Detailed Implementation

[0028] The technical solution of this patent will be further described in detail below with reference to specific embodiments.

[0029] The embodiments of this patent are described in detail below. Examples of these embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain this patent, and should not be construed as limiting this patent.

[0030] In the description of this patent, it should be understood that the terms “center,” “upper,” “lower,” “front,” “back,” “left,” “right,” “vertical,” “horizontal,” “top,” “bottom,” “inner,” and “outer,” etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this patent and simplifying the description, 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 this patent.

[0031] In the description of this patent, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "setting" should be interpreted broadly. For example, they can refer to a fixed connection or setting, a detachable connection or setting, or an integral connection or setting. Those skilled in the art can understand the specific meaning of the above terms in this patent according to the specific circumstances.

[0032] Reference Figures 1-7 An impact resistance testing device for manufacturing low-altitude unmanned aerial vehicles includes a base 1, a base 3 fixedly connected to the bottom outer wall of the base 1, an impact force generating component for providing impact force to the aircraft body 7 on the top of the base 1, and a rotating component for adjusting the direction of the impact force generating component inside the base 1. The top of the base 1 is equipped with a visual inspection component for monitoring the state of the aircraft body 7. The visual inspection component is located on the opposite side of the impact force generating component. The base 1 provides a basic installation platform, the base 3 enhances the overall stability, the impact force generating component can generate airflow impact in a targeted manner, the rotating component can flexibly adjust the impact direction, and the visual inspection component captures the state of the aircraft body 7 in real time. The four components work together to realize a complete test process from impact generation to state monitoring, solving the problems of single function and insufficient monitoring of existing devices, and providing comprehensive support for impact resistance testing.

[0033] Specifically, the impact force generating component includes a housing 10 mounted above the base 1. A fan 12 is fixedly connected to one outer wall of the housing 10. An air outlet slot 28 is provided on the side of the housing 10 away from the fan 12. Adjustment plates 27 are rotatably connected to the inner walls of both sides of the air outlet slot 28. When the fan 12 is started, it generates airflow, which is guided inside the housing 10 and blown out from the air outlet slot 28, forming the basic impact force on the aircraft body 7. At the same time, the adjustment plates 27 rotatably connected to both sides of the air outlet slot 28 can be adjusted by angle to change the direction and speed of the airflow, thereby simulating different airflow states at low altitudes, solving the defect of inaccurate airflow simulation in existing devices, and improving the realism of the test scenario.

[0034] Specifically, the rotating assembly includes a second motor 32 fixedly connected to the top outer wall of the base 3. A second rotating column 24 is fixedly connected to the output end of the second motor 32. A drive gear disk 19 is fixedly connected to the outer circumference of the second rotating column 24. A ring gear plate 23 meshes with the outer circumference of the drive gear disk 19. A gear ring 21 meshes with the outer circumference of the ring gear plate 23. A ring plate 22 for ensuring stable rotation of the gear ring 21 is fixedly connected to the bottom inner wall of the base 1. A second support column 11 is fixedly connected to the top outer wall of the gear ring 21. One end of the column 11 away from the gear ring 21 is fixedly connected to the bottom outer wall of the housing 10. The second motor 32 drives the second rotating column 24 to rotate, which in turn drives the active gear disk 19 to rotate. The active gear disk 19 drives the gear ring 21 to rotate stably along the ring plate 22 through the meshing ring tooth plate 23. The second support column 11 at the top of the gear ring 21 then drives the housing 10 to rotate synchronously, thereby realizing the adjustment of the overall direction of the impact force generating component. Impact tests can be performed on different positions of the aircraft body 7, breaking the limitations of the existing device's test position and improving the device's adaptability.

[0035] Specifically, a support plate 20 is fixedly connected to the bottom inner wall of the base 1, and a circular plate 2 is fixedly connected to the top of the support plate 20. The outer circumference of the circular plate 2 and the top of the base 1 form a limiting annular groove. The second support column 11 is slidably connected to the limiting annular groove. The support plate 20 provides stable support for the circular plate 2. The limiting annular groove formed by the circular plate 2 and the top of the base 1 provides sliding guidance for the second support column 11. When the second support column 11 rotates with the gear ring 21, the limiting annular groove can limit its displacement, ensuring the stability of the impact force generating component during rotation, avoiding the impact test accuracy due to shaking, and further improving the reliability of the test data.

[0036] Specifically, a housing 4 is fixedly connected to the top outer wall of the horizontal plate 5. A fourth rotating rod 36 is rotatably connected to the inner wall of one side of the housing 4. A third helical gear 37 is fixedly connected to the outer circumference of the fourth rotating rod 36. A fourth helical gear 38 meshes with the outer circumference of the third helical gear 37. A first motor 8 is fixedly connected to one end of the third helical gear 37 extending to the outside of the housing 4. The first motor 8 drives the fourth rotating rod 36 to rotate, which in turn drives the third helical gear 37 inside the housing 4 to rotate. The third helical gear 37 transmits power to the subsequent transmission structure through the meshing fourth helical gear 38. This transmission method can realize the precise transmission and direction conversion of power, providing power support for the angle adjustment of the adjustment plate 27 and the angle adjustment of the image acquisition device 17, ensuring the stable operation of the two key functions and improving the overall linkage of the device.

[0037] Specifically, a first vertical plate 9 is fixedly connected to the top outer wall of the housing 10, and a horizontal plate 5 is fixedly connected to the top of the first vertical plate 9. The housing 4 is fixedly connected to the horizontal plate 5, and a first support column 6 is fixedly connected to the bottom of the other end of the horizontal plate 5. The bottom end of the first support column 6 is fixedly connected to the top outer wall of the gear ring 21. The first vertical plate 9 fixes the horizontal plate 5 to the housing 10, so that the horizontal plate 5 is stably supported. The horizontal plate 5 not only provides an installation position for the housing 4, but its bottom first support column 6 is also fixed to the gear ring 21, forming a stable connection structure of "gear ring 21-first support column 6-horizontal plate 5-first vertical plate 9-housing 10", ensuring the integrity of the impact force generating component and the rotating component when they are linked, and avoiding the loosening of parts from affecting the test results.

[0038] Specifically, a threaded rod 31 is fixedly connected to the bottom outer wall of a fourth helical gear 38. A threaded cylinder 30 is threadedly connected to the outer circumference of the threaded rod 31. A movable plate 29 is rotatably connected to one side of the threaded cylinder 30. The other end of the movable plate 29 is rotatably connected to the adjusting plate 27. A horizontal column 26 fixes the slider 25 to the threaded cylinder 30. When the threaded rod 31 rotates and drives the threaded cylinder 30 to move vertically, the slider 25 slides along the outer wall of the housing 10, providing a guide limit for the threaded cylinder 30. This prevents the threaded cylinder 30 from rotating synchronously with the threaded rod 31, ensuring that it only moves in the vertical direction. Then, the movable plate 29 precisely pushes the adjusting plate 27 to adjust the angle, ensuring the accuracy of airflow regulation.

[0039] Specifically, a horizontal column 26 is fixedly connected to one side of the outer wall of the threaded cylinder 30, and a slider 25 is fixedly connected to one end of the horizontal column 26. The slider 25 is slidably connected to one side of the outer wall of the housing 10.

[0040] Specifically, a first rotating column 13 is fixedly connected to the bottom outer wall of another fourth helical gear 38. A first helical gear 16 is fixedly connected to the bottom end of the first rotating column 13. A second helical gear 18 meshes with the outer circumferential wall of the first helical gear 16. A second vertical plate 14 is fixedly connected to the bottom outer wall of the horizontal plate 5. A rotating seat 33 is fixedly connected to one side outer wall of the second vertical plate 14. A third rotating column 34 is rotatably connected to the inner circumferential wall of the rotating seat 33. A rotating block 35 is fixedly connected to the outer circumferential wall of the third rotating column 34. An image acquisition device 17 is fixedly connected to one end of the rotating block 35. A second helical gear 18 is fixedly connected to one end of the third rotating column 34. The first support column 6 meshes with the second vertical plate 14. A positioning plate 15 is fixedly connected to one side of the outer wall of the second vertical plate 14 to ensure the stable rotation of the first rotating column 13. The fourth helical gear 38 drives the first rotating column 13 to rotate, so that the first helical gear 16 drives the second helical gear 18 to rotate through meshing. The second helical gear 18 drives the third rotating column 34 to rotate along the rotating seat 33. Then, the angle of the image acquisition device 17 is adjusted by the rotating block 35. The positioning plate 15 plays a stable supporting role for the first rotating column 13, preventing it from deviating when rotating, ensuring that the image acquisition device 17 can accurately capture the state of the aircraft body 7, realize real-time monitoring of the test process, and provide a clear basis for data analysis.

[0041] A method for testing the impact resistance of low-altitude unmanned aerial vehicles (UAVs) is applied to the impact resistance testing device for manufacturing low-altitude UAVs described in the above embodiments, and includes the following steps: Step 1: Adjust the low-altitude unmanned aerial vehicle body 7 to be tested to a normal flight state, and place it on the opposite side of the visual inspection component on the top of the base 1 to ensure that the aircraft body 7 is in a stable hover or preset flight attitude. Step 2: Start the first motor 8, and adjust the angle of the adjustment plate 27 at the air outlet 28 in the impact force generating component through the transmission structure driven by it. Set the target airflow direction and wind speed according to the test requirements, and then start the fan 12 so that the airflow is guided by the box 10 and blown out from the air outlet 28, initially forming the preset impact force on the aircraft body 7. Step 3: If it is necessary to conduct impact resistance tests on different positions of the aircraft body 7, start the second motor 32, drive the gear ring 21 and the impact force generating component to rotate along the limiting ring groove on the top of the base 1 through the rotating component, adjust the orientation of the impact force generating component, and apply airflow impact to the key positions of the aircraft body 7 in sequence, such as the front, back, left and right, while keeping the visual detection component working continuously during the process. Step 4: During the entire impact test, the angle of the image acquisition device 17 is adjusted by the transmission structure driven by the first motor 8, so that it can capture the attitude change, structural deformation and other state information of the aircraft body 7 in real time, and simultaneously record the operation data of the aircraft body 7 under different impact parameters. After the test, the monitoring data and image data are sorted out to complete the impact resistance performance analysis.

[0042] Working principle: Before the test, the aircraft body 7 to be tested is started and flew to the position corresponding to the visual inspection component on the base 1. The base 3 provides stable support for the entire device, preventing the device from shaking during the test and affecting the test accuracy. In the impact force simulation stage, the fan 12 in the impact force generating component starts and generates airflow. The airflow is guided through the inside of the housing 10 and blown out from the air outlet 28 to simulate the airflow impact force in the low-altitude environment. At the same time, the first motor 8 drives the fourth rotating rod 36 and the third helical gear 37 inside the housing 4 to rotate. The third helical gear 37 drives the corresponding... One of the meshing fourth helical gears 38 rotates, which further drives the threaded rod 31 to rotate. Since the threaded cylinder 30 slides against the outer wall of the box 10 through the slider 25 connected by the horizontal column 26, the rotation of the threaded rod 31 will drive the threaded cylinder 30 to move in the vertical direction, and then push the adjustment plate 27 to rotate through the movable plate 29, so as to achieve precise adjustment of the airflow direction and wind speed at the air outlet slot 28. This solves the problem of inaccurate airflow simulation in the existing device, can more realistically reproduce the complex airflow environment at low altitude, meet the test requirements of different impact angles and intensities, and adapt to a variety of test scenarios. When the direction of the impact force needs to be changed, the second motor 32 in the rotating assembly starts, driving the second rotating column 24 and the active gear disk 19 to rotate. The active gear disk 19 drives the gear ring 21 to rotate stably along the ring plate 22 through the ring tooth plate 23. The second support column 11 and the first support column 6 at the top of the gear ring 21 then drive the housing 10 and the entire impact force generating assembly to rotate along the limiting ring groove at the top of the base 1. The sliding cooperation between the second support column 11 and the limiting ring groove further ensures the stability of the rotation process. This design allows the device to perform impact resistance tests on the aircraft in different directions, breaking the limitation of existing devices that can only test in specific directions. It improves the adaptability of the device to different testing requirements, and can complete multi-directional tests without replacing the device, reducing testing costs.

[0043] During the test monitoring phase, the third helical gear 37 driven by the first motor 8 simultaneously drives another fourth helical gear 38 to rotate. The fourth helical gear 38 drives the first helical gear 16 to rotate through the first rotating column 13. The first helical gear 16 meshes and drives the second helical gear 18 and the third rotating column 34 to rotate. The rotating block 35 on the third rotating column 34 then drives the image acquisition device 17 to adjust its angle. The positioning plate 15 ensures the stability of the rotation of the first rotating column 13. As a visual inspection component, the image acquisition device 17 can capture the attitude changes and structural state of the aircraft body 7 under impact in real time, realizing dynamic monitoring of the test process. This facilitates the staff to accurately analyze the impact resistance performance of the aircraft, avoids the problem of incomplete test data due to lack of effective monitoring, and provides comprehensive data support for subsequent performance optimization.

[0044] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any equivalent substitutions or modifications made by those skilled in the art within the scope of the technology disclosed in the present invention, based on the technical solution and inventive concept of the present invention, should be covered within the scope of protection of the present invention.

Claims

1. An impact resistance testing device for manufacturing low-altitude unmanned aerial vehicles, comprising a base (1), characterized in that, The base (1) is fixedly connected to the bottom outer wall of the base (3), and the top of the base (1) is provided with an impact force generating component for providing impact force to the aircraft body (7). The interior of the base (1) is provided with a rotating component for adjusting the direction of the impact force generating component. The top of the base (1) is provided with a visual inspection component for monitoring the status of the aircraft body (7), and the visual inspection component is located on the opposite side of the impact force generating component.

2. The impact resistance testing device for manufacturing low-altitude unmanned aerial vehicles according to claim 1, characterized in that, The impact force generating component includes a housing (10) disposed above the base (1). A fan (12) is fixedly connected to one side of the outer wall of the housing (10). An air outlet slot (28) is provided on the side of the housing (10) away from the fan (12). Adjustment plates (27) are rotatably connected to the inner walls of both sides of the air outlet slot (28).

3. The impact resistance testing device for manufacturing low-altitude unmanned aerial vehicles according to claim 2, characterized in that, The rotating assembly includes a second motor (32) fixedly connected to the top outer wall of the base (3). The output end of the second motor (32) is fixedly connected to a second rotating column (24). The outer circumferential wall of the second rotating column (24) is fixedly connected to a drive gear disk (19). The outer circumferential wall of the drive gear disk (19) is meshed with a ring tooth plate (23). The outer circumferential wall of the ring tooth plate (23) is meshed with a gear ring (21). The bottom inner wall of the base (1) is fixedly connected to a ring plate (22) for ensuring the stable rotation of the gear ring (21). The top outer wall of the gear ring (21) is fixedly connected to a second support column (11). The end of the second support column (11) away from the gear ring (21) is fixedly connected to the bottom outer wall of the housing (10).

4. The impact resistance testing device for manufacturing low-altitude unmanned aerial vehicles according to claim 3, characterized in that, A support plate (20) is fixedly connected to the bottom inner wall of the base (1), and a circular plate (2) is fixedly connected to the top of the support plate (20). The outer circumference of the circular plate (2) forms a limiting ring groove with the top of the base (1), and the second support column (11) is slidably connected to the limiting ring groove.

5. The impact resistance testing device for manufacturing low-altitude unmanned aerial vehicles according to claim 4, characterized in that, A housing (4) is fixedly connected to the top outer wall of the horizontal plate (5). A fourth rotating rod (36) is rotatably connected to the inner wall of one side of the housing (4). A third helical gear (37) is fixedly connected to the outer circumference of the fourth rotating rod (36). A fourth helical gear (38) meshes with the outer circumference of the third helical gear (37). A first motor (8) is fixedly connected to one end of the third helical gear (37) extending to the outside of the housing (4).

6. The impact resistance testing device for manufacturing low-altitude unmanned aerial vehicles according to claim 5, characterized in that, The top outer wall of the box (10) is fixedly connected to a first vertical plate (9), the top of the first vertical plate (9) is fixedly connected to a horizontal plate (5), the shell (4) is fixedly connected to the horizontal plate (5), the bottom of the other end of the horizontal plate (5) is fixedly connected to a first support column (6), and the bottom end of the first support column (6) is fixedly connected to the top outer wall of the gear ring (21).

7. The impact resistance testing device for manufacturing low-altitude unmanned aerial vehicles according to claim 6, characterized in that, A threaded rod (31) is fixedly connected to the bottom outer wall of a fourth helical gear (38). A threaded cylinder (30) is threadedly connected to the outer circumference of the threaded rod (31). A movable plate (29) is rotatably connected to one side of the threaded cylinder (30). The other end of the movable plate (29) is rotatably connected to the adjusting plate (27).

8. The impact resistance testing device for manufacturing low-altitude unmanned aerial vehicles according to claim 7, characterized in that, A horizontal column (26) is fixedly connected to one side of the outer wall of the threaded cylinder (30), and a slider (25) is fixedly connected to one end of the horizontal column (26). The slider (25) is slidably connected to one side of the outer wall of the box (10).

9. The impact resistance testing device for manufacturing low-altitude unmanned aerial vehicles according to claim 8, characterized in that, Another fourth helical gear (38) is fixedly connected to the bottom outer wall of a first rotating column (13), the bottom end of the first rotating column (13) is fixedly connected to a first helical gear (16), the outer circumferential wall of the first helical gear (16) is meshed with a second helical gear (18), the bottom outer wall of the horizontal plate (5) is fixedly connected to a second vertical plate (14), the outer side wall of the second vertical plate (14) is fixedly connected to a rotating seat (33), the inner circumferential wall of the rotating seat (33) is rotatably connected to a third rotating column (34), the outer circumferential wall of the third rotating column (34) is fixedly connected to a rotating block (35), one end of the rotating block (35) is fixedly connected to an image acquisition device (17), one end of the third rotating column (34) is fixedly connected to a second helical gear (18), the second helical gear (18) meshes with the first support column (6), and one side wall of the second vertical plate (14) is fixedly connected to a positioning plate (15) to ensure the stable rotation of the first rotating column (13).

10. A method for testing the impact resistance of low-altitude unmanned aerial vehicles, characterized in that, The impact resistance testing device for manufacturing a low-altitude unmanned aerial vehicle as described in claim 9 includes the following steps: S1: Adjust the low-altitude unmanned aerial vehicle (7) to be tested to normal flight state and place it on the opposite side of the visual inspection component on the top of the base (1) to ensure that the aircraft body (7) is in a stable hovering or preset flight attitude. S2: Start the first motor (8), adjust the angle of the adjustment plate (27) at the air outlet slot (28) in the impact force generating component through its driven transmission structure, set the target airflow direction and wind speed in combination with the test requirements, and then start the fan (12) so that the airflow is guided by the box (10) and blown out from the air outlet slot (28), initially forming the preset impact force on the aircraft body (7); S3: If it is necessary to conduct impact resistance tests on different positions of the aircraft body (7), start the second motor (32), drive the gear ring (21) and the impact force generating component to rotate along the limiting ring groove at the top of the base (1) through the rotating component, adjust the orientation of the impact force generating component, and apply airflow impact to the key positions of the aircraft body (7) in the front, back, left and right in sequence, while keeping the visual detection component working continuously during the process; S4: During the entire impact test, the angle of the image acquisition device (17) is adjusted by the transmission structure driven by the first motor (8) so that it can capture the attitude change, structural deformation and other state information of the aircraft body (7) in real time, and record the running data of the aircraft body (7) under different impact parameters. After the test, the monitoring data and image data are sorted out to complete the impact resistance performance analysis.

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