Intelligent unmanned aerial vehicle stability testing device

Abstract

The utility model discloses an intelligent unmanned aerial vehicle stability test equipment, include: test cabin, test cabin is by hollow cabin body side plate no.

Description

Technical Field

[0001] This utility model relates to the technical field of unmanned aerial vehicle (UAV) testing equipment, specifically an intelligent UAV stability testing device. Background Technology

[0002] Intelligent unmanned aerial vehicle stability testing equipment is a specialized instrument used to detect and evaluate the stability performance of drones, multi-rotor aircraft, and other unmanned aerial vehicles under various environments and operating conditions. Its main function is to simulate different flight conditions, such as wind speed, airflow disturbance, and tilt angle, and analyze their anti-interference ability, attitude maintenance accuracy, and control responsiveness. This helps R&D personnel to discover design defects, optimize control algorithms, ensure that the aircraft has reliable stability in actual flight, and guarantee flight safety and successful mission execution.

[0003] For example, the UAV stability performance testing device disclosed in Chinese patent literature (announcement number: CN216783894U) can connect each suspension rope to a cantilever of the UAV under test 11. By adjusting the length of the suspension ropes through retractable suspension ropes, the length of the suspension ropes can be ensured to be at an appropriate length. Then, the UAV under test, as well as the front air supply device and / or the left air supply device and / or the right air supply device, can be started, allowing the UAV under test to maintain a suspended state using its own power. At this time, each suspension rope does not exert tension on the UAV under test, and does not affect the maintained suspended state. Then, by adjusting the air volume of the front air supply device and / or the left air supply device and / or the right air supply device, various natural environments can be simulated to apply controllable air disturbances to the UAV under test in order to test the stability performance of the UAV under test.

[0004] However, this equipment has significant shortcomings in airflow simulation: it relies solely on fixed ducts on the front, left, and right side walls of the flight cabin for air supply. The fixed installation position and angle of these ducts mean that airflow adjustment can only be achieved through single-dimensional power control, making it impossible to accurately match the differences in airflow intensity at different altitudes according to testing requirements. Utility Model Content

[0005] The purpose of this invention is to provide an intelligent unmanned aerial vehicle stability testing device in order to solve the above problems.

[0006] To achieve the above objectives, this utility model provides the following technical solution: a stability testing device for an intelligent unmanned aerial vehicle, comprising: a test cabin, the test cabin being composed of a hollow cabin side panel one, a hollow cabin side panel two, a hollow cabin side panel three, a top inclined plate, and a rear cabin panel; the hollow cabin side panels one, two, and three are sequentially arranged and fixedly connected to one side below the top inclined plate, and the rear cabin panel is fixedly connected to one side of the hollow cabin side panels three and the rear cabin panel; a driving wind mechanism is provided on the back of the hollow cabin side panel one.

[0007] As a further embodiment of this utility model: the driving wind power mechanism includes a top support plate, a base plate, and limiting support slide rods. The top support plate is fixedly connected to the upper back of the first side panel of the hollow cabin, and the base plate is fixedly connected to the lower back of the first side panel of the hollow cabin. There are four sets of limiting support slide rods, which are symmetrically fixedly connected between the top support plate and the base plate. The mechanism also includes a winch, a wind power component, and a connecting frame. The winch is fixedly connected to the top of the top support plate, the wind power component is positioned between the four sets of limiting support slide rods, and the connecting frame is positioned above the wind power component. One end of the rope inside the winch passes through the top support plate and is fixedly connected to the connecting frame.

[0008] As a further embodiment of this utility model: the wind power component includes a fan, side frames, and sliding frames. The side frames are symmetrically and fixedly connected to both sides of the fan. The connecting frame is fixedly connected between the two sets of side frames. The sliding frames are symmetrically and fixedly connected to one side of each of the two sets of side frames. The sliding frames are vertically and slidably connected to the limiting support slide rod. A telescopic folding tube and an air outlet pipe are also included. The telescopic folding tube is fixedly connected to the air outlet of the fan, and the air outlet pipe is fixedly connected to one end of the telescopic folding tube. An extension frame, a rotating shaft, and a motor are also included. The extension frame is symmetrically and fixedly connected to the lower ends of the two sets of side frames. The rotating shafts are symmetrically and fixedly connected to the inner sides of the two sets of extension frames, and both sets of rotating shafts are fixedly connected to the air outlet pipe. The motor is fixedly connected to the outer side of one set of extension frames, and the other end of the rotating shaft on the inner side of the extension frame passes through the extension frame and is fixedly connected to the motor output end.

[0009] As a further improvement of this utility model: multiple sets of mounting brackets are fixedly connected around the bottom surface of the top inclined plate, and a camera is fixedly connected to the bottom of each set of mounting brackets.

[0010] As a further improvement of this utility model: the front of the test chamber is provided with an outer chamber, and the inner side of the outer chamber near the test chamber is provided with a transparent door via a hinge. The two sides inside the outer chamber are fixedly connected to an operating table.

[0011] As a further embodiment of this utility model: there are two sets of each of the hollow cabin side plate one, hollow cabin side plate two, and hollow cabin side plate three. The other set of hollow cabin side plate one, hollow cabin side plate two, and hollow cabin side plate three is arranged sequentially on the other side below the top inclined plate. Each set of hollow cabin side plate one, hollow cabin side plate two, and hollow cabin side plate three has a set of wind-driving mechanism on its back.

[0012] Compared with the prior art, the beneficial effects of this utility model are:

[0013] During testing, the aircraft is placed inside the test cabin. Closing the viewing hatch allows for safe observation from the outside while isolating it from airflow interference. The control panel facilitates the placement of control equipment. The test cabin utilizes stepped side panels and a sloping top panel to create a gradually rising space, providing the aircraft with continuous movement space from low to high, avoiding structural interference, and simulating different altitude scenarios, making altitude-related tests more realistic. The wind-driven mechanism adjusts the fan height via a winch and the airflow direction via a motor, while the telescopic folding tube adapts to angle changes. The symmetrical design on both sides can simulate complex airflows at multiple heights, directions, and intensities, comprehensively testing the aircraft's anti-interference capabilities. Multiple cameras capture the aircraft's attitude from multiple angles, and combined with its own sensor data, a comprehensive assessment of stability, attitude maintenance capabilities, etc., is achieved, enabling comprehensive testing. The overall design balances safety and practicality, providing rich test scenarios and comprehensive, reliable data that accurately reflects the aircraft's true stability performance under different operating conditions. Attached Figure Description

[0014] Figure 1 This is a schematic diagram of the overall structure of this utility model;

[0015] Figure 2 This is a schematic diagram of the test chamber in this utility model;

[0016] Figure 3 This is a schematic diagram of the top inclined plate in this utility model;

[0017] Figure 4 This is a schematic diagram of the wind-driving mechanism in this utility model;

[0018] Figure 5 This is a schematic diagram of the wind power component in this utility model.

[0019] In the diagram: 1. Test chamber; 11. Hollow chamber side panel one; 12. Hollow chamber side panel two; 13. Hollow chamber side panel three; 14. Top inclined plate; 15. Rear chamber panel; 2. Drive wind power mechanism; 21. Top support plate; 22. Base plate; 23. Limiting support slide bar; 24. Winch; 25. Wind power component; 251. Fan; 252. Side frame; 253. Sliding frame; 254. Telescopic folding tube; 255. Air outlet duct; 256. Extension frame; 257. Rotating shaft; 258. Motor; 26. Connecting frame; 3. Mounting frame; 4. Camera; 5. Outer chamber; 6. Transparent door; 7. Control panel. Detailed Implementation

[0020] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0021] In the description of this utility model, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this utility model 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 utility model. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance. In the description of this utility model, 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, a detachable connection, or an integral connection; 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; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances. The embodiments of this utility model will be described below based on its overall structure.

[0022] Reference Figures 1 to 5 In this embodiment of the utility model, an intelligent unmanned aerial vehicle stability testing device includes: a test cabin 1, which is composed of a hollow cabin side plate 11, a hollow cabin side plate 2 12, a hollow cabin side plate 3 13, a top inclined plate 14, and a rear cabin plate 15.

[0023] Hollow cabin side panel 11, hollow cabin side panel 2, and hollow cabin side panel 3 are arranged and fixedly connected to one side below the top inclined plate 14 in sequence, and the rear cabin panel 15 is fixedly connected to one side of hollow cabin side panel 3 13 and rear cabin panel 15.

[0024] A wind-driving mechanism 2 is installed on the back of the side panel 11 of the hollow cabin.

[0025] Two sets of each of the three hollow cabin side panels 11, 12, and 13 are provided. Another set of three hollow cabin side panels 11, 12, and 13 is arranged sequentially on the other side below the top inclined plate 14. Each set of three hollow cabin side panels 11, 12, and 13 has a wind-driving mechanism 2 on its back. The two sets of three hollow cabin side panels 11, 12, and 13 increase in height along the longitudinal direction of the test chamber 1, with their tops... The resulting stepped height difference is adapted to the tilt shape of the top inclined plate 14, together forming a spatial structure that gradually rises from the opening end of the test cabin 1 inward. This design provides the intelligent unmanned aerial vehicle with a gradually increasing motion space along the height direction during the test process, which makes it easier for the aircraft to smoothly complete continuous height change tests from low to high when simulating different altitude conditions, such as airflow environment with increasing low altitude and attitude adjustment range, avoiding interference from the cabin structure to its vertical movement, thereby more accurately detecting the stability performance of the aircraft at different altitude positions.

[0026] Reference Figure 1 , Figure 4 and Figure 5 The wind-driving mechanism 2 includes a top support plate 21, a base plate 22, and a limiting support slide bar 23. The top support plate 21 is fixedly connected to the upper back of the side plate 11 of the hollow cabin, and the base plate 22 is fixedly connected to the lower back of the side plate 11 of the hollow cabin. The limiting support slide bar 23 is provided in four sets, symmetrically fixedly connected between the top support plate 21 and the base plate 22.

[0027] The winch 24, the wind turbine assembly 25, and the connecting frame 26 are all included. The winch 24 is fixedly connected to the top of the top support plate 21. The wind turbine assembly 25 is located between four sets of limiting support slide bars 23. The connecting frame 26 is located above the wind turbine assembly 25. One end of the rope inside the winch 24 passes through the top support plate 21 and is fixedly connected to the connecting frame 26. The wind turbine mechanism 2 can simulate airflow environments of different directions and intensities. When the winch 24 is working, it drives the connecting frame 26 and the wind turbine assembly 25 to slide up and down along the limiting support slide bars 23 through the rope, thereby adjusting the height position of the fan 251.

[0028] Reference Figure 1 , Figure 4 and Figure 5 The wind power assembly 25 includes a fan 251, side frames 252 and sliding frames 253. The side frames 252 are symmetrically fixedly connected to both sides of the fan 251. The connecting frame 26 is fixedly connected between the two sets of side frames 252. The sliding frames 253 are symmetrically fixedly connected to one side of the two sets of side frames 252 respectively. The sliding frames 253 are vertically slidably connected to the limiting support slide rod 23.

[0029] Telescopic folding pipe 254 and air outlet pipe 255, the telescopic folding pipe 254 is fixedly connected to the air outlet of the fan 251, and the air outlet pipe 255 is fixedly connected to one end of the telescopic folding pipe 254.

[0030] The system comprises an extension frame 256, a rotating shaft 257, and a motor 258. The extension frame 256 is symmetrically and fixedly connected to the lower ends of two sets of side frames 252. The rotating shaft 257 is symmetrically and fixedly connected to the inner sides of the two sets of extension frames 256, and both sets of rotating shafts 257 are fixedly connected to the air outlet duct 255. The motor 258 is fixedly connected to the outer side of one set of extension frames 256, and the other end of the rotating shaft 257 on the inner side of the extension frame 256 passes through the extension frame 256 and is fixedly connected to the output end of the motor 258. The airflow generated by the fan 251 is sent into the test chamber 1 through the telescopic folding tube 254 and the air outlet duct 255. The telescopic folding tube 254 can adaptively extend and deform according to the angle adjustment of the air outlet duct 255. The symmetrically arranged drive wind mechanism 2 on both sides works in concert to simulate complex airflow disturbance scenarios. This simulates airflow and complex disturbance scenarios at different heights, directions, and intensities. The symmetrical design on both sides can form multi-angle airflow interaction, comprehensively testing the aircraft's anti-interference capability.

[0031] Reference Figure 1 and Figure 2 Multiple sets of mounting brackets 3 are fixedly connected around the bottom of the top inclined plate 14. Each set of mounting brackets 3 is fixedly connected to a camera 4 at the bottom. The multiple sets of cameras 4 can capture the attitude and motion status of the aircraft in real time from different angles. In a simulated airflow environment, the cameras 4 collect the flight data of the aircraft. Combined with the information of the aircraft's own sensors, the stability, attitude maintenance ability and anti-interference performance under different airflow conditions can be comprehensively evaluated, so as to achieve a comprehensive test of the stability of the intelligent unmanned aerial vehicle.

[0032] The test cabin 1 has an outer cabin 5 on its front. The inner side of the outer cabin 5, near the test cabin 1, is equipped with a hinged transparent hatch 6. The two sides of the inner side of the outer cabin 5 are fixedly connected to the control panel 7. The intelligent unmanned aerial vehicle is placed inside the test cabin 1. The transparent hatch 6 is closed to facilitate observation inside the outer cabin 5 and to prevent the airflow inside the test cabin 1 from interfering with the personnel inside the outer cabin 5. The control panel 7 is convenient for placing control equipment.

[0033] The working principle of this utility model is as follows: During testing, the intelligent unmanned aerial vehicle is placed inside the test cabin 1, and the transparent cabin door 6 is closed to facilitate observation from the outer cabin 5, preventing the airflow inside the test cabin 1 from interfering with the personnel inside the outer cabin 5. The control equipment can be placed through the control panel 7.

[0034] The two sets of hollow cabin side panels 11, 12, and 13 increase in height along the longitudinal direction of the test cabin 1. The stepped height difference formed at the top is adapted to the tilt shape of the top inclined plate 14, and together they form a space structure that gradually rises from the opening end of the test cabin 1 inward. This design provides the intelligent unmanned aerial vehicle with a gradually increasing motion space along the height direction during the test. This makes it easier for the aircraft to smoothly complete the continuous height change test from low to high when simulating different altitude conditions, such as the airflow environment with increasing low altitude and attitude adjustment range. It avoids the cabin structure interfering with its vertical movement, thereby more accurately detecting the stability performance of the aircraft at different altitude positions. This gradually rising space design not only meets the test requirements of the aircraft for continuous height change from low to high and avoids structural interference, but also simulates flight scenarios at different altitudes, making the altitude-related stability test more in line with actual working conditions.

[0035] The driving wind mechanism 2 can simulate airflow environments of different directions and intensities: When the winch 24 is working, it drives the connecting frame 26 and the wind power component 25 to slide up and down along the limiting support slide bar 23 via a rope, adjusting the height position of the fan 251; the motor 258 drives the rotating shaft 257 to rotate, causing the air outlet pipe 255 to rotate around the rotating shaft 257, thereby changing the air outlet direction; the airflow generated by the fan 251 is sent into the test chamber 1 through the telescopic folding pipe 254 and the air outlet pipe 255. The telescopic folding pipe 254 can adaptively expand and contract with the angle adjustment of the air outlet pipe 255. The driving wind mechanism is symmetrically arranged on both sides. 2. Working in tandem, it can simulate complex airflow disturbance scenarios, thus simulating airflow and complex disturbance scenarios at different altitudes, directions, and intensities. The symmetrical design on both sides can form multi-angle airflow interaction, comprehensively testing the aircraft's anti-interference capabilities. Meanwhile, multiple sets of cameras 4 can capture the aircraft's attitude and motion status in real time from different angles. In the simulated airflow environment, the cameras 4 collect the aircraft's flight data, and combined with the aircraft's own sensor information, it can comprehensively evaluate its stability, attitude maintenance ability, and anti-interference performance under different airflow conditions, realizing a comprehensive test of the stability of the intelligent unmanned aerial vehicle.

[0036] The above description is only a preferred embodiment of the present utility model, but the protection scope of the present utility model is not limited thereto. Any equivalent substitutions or changes made by those skilled in the art within the technical scope disclosed in the present utility model, based on the technical solution and the inventive concept of the present utility model, should be included within the protection scope of the present utility model.

Claims

1. A stability testing device for intelligent unmanned aerial vehicles, characterized in that, include: The test chamber (1) is composed of a hollow cabin side panel one (11), a hollow cabin side panel two (12), a hollow cabin side panel three (13), a top inclined plate (14), and a rear cabin panel (15); The hollow cabin side panel one (11), hollow cabin side panel two (12) and hollow cabin side panel three (13) are arranged in sequence and fixedly connected to one side below the top inclined plate (14), and the rear cabin panel (15) is fixedly connected to one side of the hollow cabin side panel three (13) and the rear cabin panel (15); A wind-driving mechanism (2) is provided on the back of the side panel (11) of the hollow cabin.

2. The intelligent unmanned aerial vehicle stability testing equipment according to claim 1, characterized in that, The wind-driving mechanism (2) includes: The top support plate (21), the base plate (22), and the limiting support slide rod (23) are provided. The top support plate (21) is fixedly connected to the upper back of the side plate of the hollow cabin (11). The base plate (22) is fixedly connected to the lower back of the side plate of the hollow cabin (11). The limiting support slide rod (23) is provided in four sets, symmetrically fixedly connected between the top support plate (21) and the base plate (22). The winch (24), the wind power component (25), and the connecting frame (26) are fixedly connected to the top of the top support plate (21). The wind power component (25) is located between four sets of limiting support slide bars (23). The connecting frame (26) is located above the wind power component (25). One end of the rope inside the winch (24) passes through the top support plate (21) and is fixedly connected to the connecting frame (26).

3. The intelligent unmanned aerial vehicle stability testing equipment according to claim 2, characterized in that, The wind turbine component (25) includes: The fan (251), side frame (252) and sliding frame (253) are provided. The side frame (252) is symmetrically fixedly connected to both sides of the fan (251). The connecting frame (26) is fixedly connected between the two sets of side frames (252). The sliding frame (253) is symmetrically fixedly connected to one side of the two sets of side frames (252). The sliding frame (253) is vertically slidably connected to the limiting support slide rod (23). Telescopic folding tube (254) and air outlet tube (255), wherein the telescopic folding tube (254) is fixedly connected to the air outlet of the fan (251), and the air outlet tube (255) is fixedly connected to one end of the telescopic folding tube (254); The extension frame (256), the rotating shaft (257), and the motor (258) are symmetrically fixedly connected to the lower ends of two sets of side frames (252). The rotating shaft (257) is symmetrically fixedly connected to the inner side of the two sets of extension frames (256), and both sets of rotating shafts (257) are fixedly connected to the air outlet pipe (255). The motor (258) is fixedly connected to the outer side of one set of extension frames (256), and the other end of the rotating shaft (257) on the inner side of the extension frame (256) passes through the extension frame (256) and is fixedly connected to the output end of the motor (258).

4. The intelligent unmanned aerial vehicle stability testing equipment according to claim 1, characterized in that, The top inclined plate (14) has multiple sets of mounting brackets (3) fixedly connected around its bottom surface, and each set of mounting brackets (3) has a camera (4) fixedly connected to its bottom.

5. The intelligent unmanned aerial vehicle stability testing equipment according to claim 1, characterized in that, The test chamber (1) has an outer chamber (5) on its front side. The inner side of the outer chamber (5) near the test chamber (1) is provided with a transparent door (6) via a hinge. The two sides inside the outer chamber (5) are fixedly connected to an operating table (7).

6. The intelligent unmanned aerial vehicle stability testing equipment according to claim 1, characterized in that, The number of hollow cabin side panels one (11), hollow cabin side panels two (12) and hollow cabin side panels three (13) are all provided in two sets. The other set of hollow cabin side panels one (11), hollow cabin side panels two (12) and hollow cabin side panels three (13) is arranged in sequence on the other side below the top inclined plate (14). Each set of hollow cabin side panels one (11), hollow cabin side panels two (12) and hollow cabin side panels three (13) is provided with a set of wind-driving mechanism (2) on the back.

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