Wind resistance simulation equipment for unmanned aerial vehicle

Abstract

The invention belongs to the technical field of unmanned aerial vehicle testing, and particularly relates to unmanned aerial vehicle wind resistance simulation equipment. Comprising a testing mechanism; the testing mechanism comprises a top frame and a bottom frame; the top frame and the bottom frame are fixed through two stand columns. First mounting frames are uniformly arranged between the two stand columns on the same side; first fans which are uniformly arranged are mounted in the first mounting frame; an arc plate is mounted on the left side of the stand column on the left side; second mounting frames are uniformly arranged between the two arc plates; second fans which are uniformly arranged are mounted in the second mounting frame; a platform is arranged in the middle of the bottom frame, and an unmanned aerial vehicle needing to be tested is placed on the platform; an electric push rod is mounted at the bottom of the platform, and the other side of the electric push rod is mounted at the top of the rail intelligent trolley; by arranging the testing mechanism, all-working-condition scenes such as route cruise, maneuvering flight, crosswind, headwind and downwind all-directional flight and the like in the real operation process of the unmanned aerial vehicle can be completely covered.

Description

Technical Field

[0001] This invention belongs to the field of drone testing technology, specifically a drone wind resistance simulation device. Background Technology

[0002] With the rapid iteration and popularization of civilian drone technology, the application demand for drones in scenarios such as consumer-grade aerial photography, industrial-grade plant protection, power line inspection, emergency rescue, and logistics transportation continues to expand. As a core flight performance indicator of drones, wind resistance directly determines the drone's environmental adaptability, operational stability, and flight safety. It is an indispensable core test item in the drone product development and finalization, factory performance testing, and compliance certification process.

[0003] Currently, in laboratory wind field simulation tests of existing drones, these tests mainly rely on wind wall equipment. The existing working principle for drone wind resistance testing using wind walls is as follows: multiple axial flow fans are arranged in a matrix array to form the main wind field. The output speed of the fans is adjusted by a variable frequency speed control unit to precisely control the airflow speed output by the wind wall, thereby simulating different levels of natural wind environments. During the test, the drone under test is placed in the test area on the wind outlet side of the wind wall. The wind speed data of the test area is collected in real time by a wind field measurement unit. At the same time, core parameters such as the attitude maintenance accuracy, position control capability, flight control system response characteristics, and power system load status of the drone under test at the corresponding wind speed are collected. Finally, the wind resistance performance level of the drone under test is determined based on the above parameters.

[0004] However, in the actual application of existing wind wall testing, there are serious deficiencies in the coverage of operating conditions: due to the open structural characteristics of the wind wall itself, it can only form a relatively uniform and stable effective wind field within a very small area on the windward side. The effective test area is very limited. Therefore, during the testing process, it can almost only carry out basic operating condition tests such as fixed-point hovering and direct windward flight of the drone, and cannot cover all operating conditions such as flight path cruising, maneuvering flight, crosswind, and headwind flight during the actual operation of the drone. The wind resistance performance data obtained by only the basic operating condition test of fixed-point hovering and direct windward flight cannot reflect the actual wind resistance performance of the drone in real operating scenarios. The product wind resistance rating marked based on this test data is very likely to mislead users to carry out operations in wind conditions that exceed the actual wind resistance capability of the drone, thereby causing safety accidents such as drone loss of control and crashes, resulting in property damage or even personal injury to users. Summary of the Invention

[0005] To overcome the shortcomings of existing technologies and solve the aforementioned technical problems, this invention proposes a wind-resistant simulation device for unmanned aerial vehicles (UAVs). By setting up a testing mechanism, it can fully cover all working conditions of UAVs in real operation, including flight path navigation, maneuvering flight, crosswind, headwind, and tailwind flight in all directions. The specific structure is as follows.

[0006] A wind resistance simulation device for unmanned aerial vehicles (UAVs) includes a testing mechanism; the testing mechanism includes a top frame and a bottom frame.

[0007] The top frame and the bottom frame are fixed together by two columns; a first mounting frame is provided between the two columns on the same side, and multiple first mounting frames are distributed vertically; a first fan is installed in the first mounting frame.

[0008] An arc plate is installed on the left side of the column located on the left side, and the arc plate is fixedly connected to the top frame and the bottom frame respectively;

[0009] A second mounting frame is provided between the two arc plates, and multiple second mounting frames are distributed along the top and bottom of the arc plates; a second fan is installed in the second mounting frame.

[0010] The top frame has an opening in the middle; two connecting plates are installed in the opening; a traction block is provided between the connecting plates; two traction ropes are provided at the bottom of the traction block; and threaded rods are connected to the bottom of the traction ropes.

[0011] The bottom frame is mounted on the top of the track-guided intelligent vehicle via support legs, and the track-guided intelligent vehicle is set on a track, which is an elongated oval shape.

[0012] The base frame is U-shaped; a platform is provided in the middle of the base frame, and the platform is used to place the drone to be tested; two threaded cylinders are fixedly installed on the top of the drone, and the threaded cylinders are threadedly engaged with the threaded rod.

[0013] An electric actuator is installed at the bottom of the platform, and the other side of the electric actuator is installed on the top of the track-guided intelligent vehicle.

[0014] In a preferred embodiment of the present invention, sliders are fixed on both sides of the traction block, and the sliders are perpendicular to the connecting plate.

[0015] The two sliders have a sliding track on opposite sides inside the top frame, and the sliders slide within the sliding track.

[0016] There is a distance between the connecting plate and the traction block; pressure sensors are installed on the side of the two connecting plates facing the traction block, and the signal output terminals of the two pressure sensors are electrically connected to the motion controller of the track-guided intelligent vehicle.

[0017] In a preferred embodiment of the present invention, the traction block has a cavity inside;

[0018] A rotating rod is rotatable within the cavity; the rotating rod is driven by a first motor, which is installed inside the cavity; the traction rope extends into the cavity and is connected to the rotating rod.

[0019] The traction rope passes through one side of the traction block and is slidably connected to the traction block;

[0020] The bottom of the traction block is equipped with a vertical cylinder, and the inner diameter of the vertical cylinder is larger than the outer diameter of the threaded rod; the two traction ropes pass through the two vertical cylinders respectively;

[0021] The bottom inner rings of the two vertical cylinders are rounded; the top outer rings of the two threaded rods are rounded.

[0022] In a preferred embodiment of the present invention, a placement compartment is installed on the top of the top frame;

[0023] The placement chamber is equipped with a rotating belt, which is driven by a second motor, and the second motor is installed on the outside of the placement chamber.

[0024] The outer ring surface of the conveyor belt is fixed with evenly arranged partitions, and the partitions are attached to the top frame at the bottom; the left side of the conveyor belt is provided with a drop opening on the top frame.

[0025] In a preferred embodiment of the present invention, a liquid tank is installed on the left side of the placement chamber, and water is placed in the liquid tank;

[0026] The bottom of the placement chamber is equipped with evenly distributed nozzles, and the nozzles are in communication with the inside of the liquid tank.

[0027] As a preferred embodiment of the present invention, both of the two arc plates are provided with arc-shaped grooves on one side of each other;

[0028] Each of the second mounting frames has an arc-shaped plate fixed on both sides facing the arc-shaped groove, and the arc-shaped plates slide in the corresponding arc-shaped groove respectively;

[0029] The surfaces of the two arc-shaped plates are provided with evenly arranged toothed grooves; a mounting plate is fixed to the opposite side of each of the two arc-shaped plates; a third motor is mounted on each of the mounting plates.

[0030] The output shaft of the third motor is equipped with a gear, which rotates within the arc plate and meshes with the tooth groove.

[0031] In a preferred embodiment of the present invention, a drive plate is fixed on both sides of the plurality of first mounting frames;

[0032] The drive plate has a lead screw for screw transmission, and the cylinder rotates on the top frame and the bottom frame; the lead screw is driven by a fourth motor, and the fourth motor is mounted on the top frame;

[0033] The two columns have grooves on the side facing the drive plate, and the drive plate slides within the grooves.

[0034] In a preferred embodiment of the present invention, the bottom of the drone is also equipped with a threaded cylinder, and a threaded rod is also threadedly engaged inside the threaded cylinder.

[0035] The threaded rod is connected to a weight via a pull rope.

[0036] In a preferred embodiment of the present invention, the bottom of the weight is connected to an elastic rope, and the other side of the elastic rope is connected to the platform.

[0037] An extra elastic rope is provided between the weight and the platform.

[0038] The beneficial effects of this invention are as follows:

[0039] 1. The wind resistance simulation device for unmanned aerial vehicles (UAVs) described in this invention integrates the testing mechanism onto a track-guided intelligent vehicle. This mechanism, along with a track perfectly aligned with the UAV's preset trajectory, enables synchronous movement of the testing mechanism and the UAV under test along the same trajectory and at the same speed. This ensures that the UAV remains within a stable and effective wind field created by the testing mechanism during all dynamic operational conditions, including flight path cruising and maneuvering. This completely breaks the limitations of traditional wind walls, which can only create an effective wind field in a very small fixed area and can only conduct basic tests such as fixed-point hovering and direct wind. It can comprehensively cover all operational scenarios of UAVs in real-world operations, including flight path cruising, maneuvering, crosswinds, headwinds, and tailwinds. The wind resistance performance data obtained from the test accurately reflects the UAV's wind resistance performance in actual operating environments, avoiding the industry's practice of falsely labeling wind resistance levels based on fixed-point hovering test data. This reduces the risk of UAV loss of control and crashes caused by users operating in wind conditions exceeding the standard due to misleading parameters, thus protecting the personal and property safety of users.

[0040] 2. The wind-resistant simulation device for unmanned aerial vehicles (UAVs) described in this invention, when a UAV crashes, the first motor drives a rotating rod to rotate. The rotating rod wraps around the traction rope, gradually shortening the traction rope and pulling the threaded cylinder towards the vertical cylinder. Simultaneously, it pulls the UAV towards the vertical cylinder. Because the outer ring of the threaded rod and the inner ring of the vertical cylinder are rounded, the threaded rod can be inserted into the vertical cylinder more easily. Once the threaded rod is inserted into the vertical cylinder, it can lock and fix the UAV, thus preventing the UAV from being pulled by the traction rope. When the controlled intelligent trolley stops, the UAV will shake, causing it to collide with the top frame and potentially damage the UAV. This further improves the safety of the UAV under test during the testing process.

[0041] 3. The wind-resistant simulation device for unmanned aerial vehicles (UAVs) described in this invention can simultaneously deploy debris and spray water during testing, thereby simulating extreme weather conditions where strong winds carry rain and debris. It can continuously complete standardized tests in multiple scenarios, including pure wind fields, combined wind and rain, and wind with debris, without requiring changes to the testing equipment or adjustments to the testing layout. This solves the problems of existing testing equipment having limited scenarios and cumbersome testing procedures. Furthermore, the entire composite environment simulation mechanism is integrated into the top frame of the testing mechanism, allowing it to move synchronously and at the same speed as the testing mechanism, the tracked intelligent vehicle, and the UAV under test. This ensures that the debris deployment area and the spray coverage area are always precisely matched with the flight area of ​​the UAV under test, overcoming the shortcomings of traditional fixed testing equipment that cannot continuously and stably simulate composite environments during the dynamic cruise of UAVs. This adapts to the testing requirements of the equipment under full dynamic flight conditions. Attached Figure Description

[0042] The invention will now be further described with reference to the accompanying drawings.

[0043] Figure 1 This is a perspective view of the testing mechanism of the present invention;

[0044] Figure 2 This is a perspective view of the testing mechanism of the present invention from another angle;

[0045] Figure 3 This is a diagram showing the state of the testing mechanism of this invention during testing on the track;

[0046] Figure 4 This is a diagram of the internal structure of the testing mechanism in this invention;

[0047] Figure 5 This is a diagram showing the separate structure of the testing mechanism in this invention;

[0048] Figure 6 This is the present invention. Figure 5 Enlarged view of a portion of point A in the middle;

[0049] Figure 7 This is a state diagram of the drone after connection in this invention;

[0050] Figure 8 This is a top view of the testing mechanism in this invention;

[0051] Figure 9 This is the present invention. Figure 8 Sectional view at point BB;

[0052] Figure 10 This is the present invention. Figure 9 Enlarged view of a section at point C;

[0053] Figure 11 This is the present invention. Figure 9 Enlarged view of a section at point D.

[0054] In the diagram: 1. Top frame; 11. Column; 12. Connecting plate; 121. Pressure sensor; 13. Traction block; 131. Slider; 132. Rotating rod; 14. Traction rope; 15. Threaded rod; 16. Vertical cylinder; 2. Bottom frame; 21. First mounting frame; 211. Drive plate; 212. Lead screw; 22. First fan; 23. Rail-guided intelligent vehicle; 24. Platform; 25. Drone; 26. Threaded cylinder; 27. Electric actuator; 3. Arc plate; 31. Second mounting frame; 32. Second fan; 33. Arc groove; 34. Arc plate; 35. Gear groove; 36. Gear; 4. Placement chamber; 41. Transfer belt; 42. Liquid tank; 43. Nozzle; 44. Drop outlet; 5. Pull rope; 51. Weight; 52. Elastic rope. Detailed Implementation

[0055] To make the technical means, creative features, objectives and effects of this invention easier to understand, the invention will be further described below in conjunction with specific embodiments.

[0056] like Figures 1 to 11 As shown, the wind resistance simulation device for unmanned aerial vehicles (UAVs) of the present invention includes a testing mechanism; the testing mechanism includes a top frame 1 and a bottom frame 2.

[0057] The top frame 1 and the bottom frame 2 are fixed together by two columns 11; a first mounting frame 21 is evenly arranged between the two columns 11 on the same side, and multiple first mounting frames 21 are distributed vertically; a first fan 22 is evenly arranged inside the first mounting frame 21.

[0058] An arc plate 3 is installed on the left side of the column 11 located on the left side, and the arc plate 3 is fixedly connected to the top frame 1 and the bottom frame 2 respectively;

[0059] A second mounting frame 31 is provided between the two arc plates 3, and multiple second mounting frames 31 are distributed vertically along the arc plates 3; a second fan 32 is installed in the second mounting frame 31.

[0060] The top frame 1 has an opening in the middle; two connecting plates 12 are installed in the opening; a traction block 13 is provided between the connecting plates 12; two traction ropes 14 are provided at the bottom of the traction block 13; and a threaded rod 15 is connected to the bottom of the traction rope 14.

[0061] The bottom frame 2 is mounted on the top of the track-guided intelligent vehicle 23 via support legs, and the track-guided intelligent vehicle 23 is set on a track, which is an elongated oval shape.

[0062] The bottom frame 2 is U-shaped; a platform 24 is provided in the middle of the bottom frame 2, and the platform 24 is used to place the drone 25 to be tested; two threaded cylinders 26 are fixedly installed on the top of the drone 25, and the threaded cylinders 26 are threadedly engaged with the threaded rod 15.

[0063] An electric actuator 27 is installed at the bottom of the platform 24, and the other side of the electric actuator 27 is installed on the top of the track-guided intelligent vehicle 23.

[0064] When testing the drone 25, the drone 25 to be tested is first placed on the platform 24. After power-on self-test and initialization, the platform 24 is controlled by the first electric actuator 27 to move the drone 25 upward. Then, the threaded rod 15 connected to the traction rope 14 is turned into the threaded cylinder 26 on the top of the drone 25. The drone 25 is then controlled to take off vertically to the preset test reference height and then switch to the altitude hold mode to keep the drone 25 at a constant altitude throughout the flight. At this time, the traction rope 14 between the drone 25 and the traction block 13 is in a slack state to eliminate the initial force interference. Then, the ground station presets the flight trajectory and test flight speed of the drone 25 to be completely superimposed on the horizontal projection of the trolley's running track, and sends the driving parameters consistent with the flight speed of the drone 25 to the trolley motion controller. Finally, the drone 25 and the tracked intelligent trolley 23 are started simultaneously by the synchronous control unit so that the two run on the same trajectory and at the same speed, and the wind resistance performance test of the drone 25 under dynamic working conditions can begin.

[0065] Specifically, since the drone 25 and the tracked intelligent vehicle 23 have the same trajectory and speed, the drone 25 under test can always be confined to the test area between the top frame 1 and the bottom frame 2 of the test mechanism, and moves synchronously with the tracked intelligent vehicle 23. When the test mechanism moves with the tracked intelligent vehicle 23, the second fan 32 in the second mounting frame 31 between the arc plates 34 is started and outputs airflow. The airflow directly acts on the drone 25 under test in flight, thereby simulating the real working condition of the drone 25 under test flying into the wind. During the test, multiple sets of different constant operating parameters can be preset when setting the operating parameters of the drone 25 and the tracked intelligent vehicle 23. The speed can be used to conduct graded tests, and the output air volume and outlet air speed of the second fan 32 can be adjusted to simulate the wind resistance performance and flight status changes of the test drone 25 during dynamic cruise flight under different wind conditions. At the same time, the second fan 32 in the second mounting frame 31 near the top frame 1 and the bottom frame 2 of the test mechanism can be selectively controlled to start operation. The second fan 32 in the top second mounting frame 31 outputs downward airflow, and the second fan 32 in the bottom second mounting frame 31 outputs upward airflow, thereby simulating the flight conditions of the test drone 25 when it is disturbed by the downward airflow from the top or the upward airflow from the bottom during flight, so as to achieve accurate simulation of wind disturbance environment in different directions.

[0066] More specifically, depending on the testing requirements, the first fan 22 in the first mounting frame 21 on one side of the UAV 25 can be selectively started or operated, or the first fans 22 in the first mounting frames 21 on both sides can be started and operated synchronously to simulate the interference of single-sided crosswind or double-sided lateral wind on the flight state of the UAV 25 during dynamic flight. During the test, the output air volume and outlet air speed of the first fan 22 can be adjusted by the frequency conversion control unit to simulate the lateral wind disturbance environment of different wind levels and complete the wind resistance performance test of the UAV 25 under crosswind conditions. In addition, by adjusting the driving direction of the UAV 25 and the rail-guided intelligent vehicle 23, the movement direction of the two can be made completely consistent with the airflow direction generated by the second fan 32 in the second mounting frame 31, thereby simulating the dynamic flight scenario of the UAV 25 under tailwind conditions and completing the wind resistance performance test of the UAV 25 under tailwind conditions, achieving full coverage testing of all wind direction flight conditions.

[0067] Furthermore, throughout the entire testing process, the threaded cylinder 26 on the top of the UAV under test 25 remains locked and engaged with the threaded rod 15 connecting the traction rope 14, and the other end of the traction rope 14 is fixedly connected to the traction block 13 of the rail-guided intelligent vehicle 23. When the UAV under test 25 in flight experiences abnormal conditions such as loss of control and falling due to wind disturbance, the traction rope 14 can limit the falling direction and distance of the UAV under test 25 through the connection structure between the threaded rod 15 and the threaded cylinder 26, and stably pull the UAV under test 25 within the testing area, avoiding collisions between the UAV under test 25 and the side column 11, the bottom frame 2, or surrounding components of the testing mechanism, effectively preventing structural damage to the UAV under test 25 due to a crash, and ensuring equipment safety during the testing process.

[0068] Furthermore, by integrating the testing mechanism onto the track-guided intelligent vehicle 23, and using a track that perfectly overlaps with the preset trajectory of the drone 25, the testing mechanism and the drone under test can move synchronously along the same trajectory and at the same speed. This ensures that the drone under test 25 remains within the stable and effective wind field formed by the testing mechanism during all dynamic operating conditions, such as flight path cruising and maneuvering. This completely breaks the limitations of traditional wind walls, which can only form an effective wind field in a very small fixed area and can only conduct basic tests such as fixed-point hovering and headwind. It can fully cover all operating scenarios of the drone 25 in real-world operations, including flight path cruising, maneuvering, crosswind, headwind, and tailwind. The wind resistance performance data obtained from the test can truly reflect the wind resistance performance of the drone 25 in the actual operating environment, avoiding the industry chaos of falsely labeling wind resistance levels based on fixed-point hovering test data. This reduces the risk of drone 25 loss of control and crashes caused by users operating under excessive wind conditions due to misleading parameters, thus protecting the personal and property safety of users.

[0069] As one embodiment of the present invention; sliders 131 are fixed on both sides of the traction block 13, and the sliders 131 are perpendicular to the connecting plate 12;

[0070] The two sliders 131 have a sliding track on opposite sides inside the top frame 1, and the sliders 131 slide within the sliding track;

[0071] There is a distance between the connecting plate 12 and the traction block 13; a pressure sensor 121 is installed on the side of the two connecting plates 12 facing the traction block 13, and the signal output terminals of the two pressure sensors 121 are electrically connected to the motion controller of the track-guided intelligent vehicle 23.

[0072] In this embodiment, the traction block 13 has a cavity inside; a rotating rod 132 rotates inside the cavity; the rotating rod 132 is driven by a first motor, and the first motor is installed inside the cavity; the traction rope 14 extends into the cavity and is connected to the rotating rod 132.

[0073] The traction rope 14 passes through one side of the traction block 13 and is slidably connected to the traction block 13; a vertical cylinder 16 is installed at the bottom of the traction block 13, and the inner diameter of the vertical cylinder 16 is larger than the outer diameter of the threaded rod 15; the two traction ropes 14 pass through the two vertical cylinders 16 respectively.

[0074] The bottom inner rings of the two vertical cylinders 16 are rounded; the top outer rings of the two threaded rods 15 are rounded.

[0075] When the drone 25 is flying alongside the test mechanism, if the drone 25 is flying against the wind, its speed will gradually decrease due to wind interference, causing a speed deviation with the speed of the test mechanism driven by the tracked intelligent vehicle 23. When the drone 25 moves away from the test mechanism, it will pull the traction rope 14. The traction rope 14 will pull the traction block 13 to move to the right side of the pressure sensor 121 and press the corresponding pressure sensor 121. The pressure sensor 121 will transmit the real-time pressure signal to the vehicle motion controller. According to the preset pressure standard range, when the detected value exceeds the threshold, the controller will output a deceleration command to adjust the vehicle's speed until the pressure value falls back to the standard range. Then, the controller will control the vehicle to maintain a constant speed, thereby achieving synchronous speed following between the vehicle and the drone 25.

[0076] Specifically, when the drone 25 crashes, the first motor will drive the rotating rod 132 to rotate. The rotating rod 132 will wrap around the traction rope 14, thereby gradually shortening the traction rope 14 and pulling the threaded cylinder 26 to move towards the vertical cylinder 16. At the same time, it will pull the drone 25 to move towards the vertical cylinder 16. Since the outer ring of the threaded rod 15 is rounded and the inner ring of the vertical cylinder 16 is rounded, the threaded rod 15 can be inserted into the vertical cylinder 16 more easily. After the threaded rod 15 is inserted into the vertical cylinder 16, the drone 25 can be locked and fixed, thereby preventing the drone 25 from being pulled by the traction rope 14. When the control rail intelligent vehicle 23 stops, the drone 25 will shake, causing the shaking drone 25 to collide with the top frame 1, resulting in damage to the drone 25. This further improves the protection and safety of the drone 25 under test during the test.

[0077] As an embodiment of the present invention; a placement compartment 4 is installed on the top of the top frame 1; a rotating belt 41 is rotatable inside the placement compartment 4, and the rotating belt 41 is driven by a second motor, and the second motor is installed on the outside of the placement compartment 4; evenly arranged partitions are fixed on the outer ring surface of the rotating belt 41, and the partitions are in contact with the bottom of the top frame 1; a drop opening 44 is opened on the left side of the rotating belt 41 on the top frame 1.

[0078] In this embodiment, a liquid tank 42 is installed on the left side of the placement chamber 4, and water is placed inside the liquid tank 42; a uniformly arranged nozzle 43 is installed at the bottom of the placement chamber 4, and the nozzle 43 communicates with the interior of the liquid tank 42.

[0079] When conducting wind resistance tests on the drone 25, leaves, branches, sand, and other debris can be placed in the placement compartment 4. During the test, the second motor drives the conveyor belt 41 counterclockwise, causing the leaves, branches, or sand to rotate. When the debris moves to the drop point 44, it can fall and impact the drone 25, thus simulating the scenario of the drone 25 being hit by debris carried by the wind in strong winds. At the same time, since the liquid tank 42 has a nozzle 43 at the bottom, the nozzle 43 can be controlled to spray water during the test, thus simulating the scenario of rainwater impacting the drone 25 in strong winds, and simultaneously simulating the impact of strong winds carrying rainwater and debris on the drone 25.

[0080] During testing, debris and water can be simultaneously deployed, thus simulating extreme weather conditions where strong winds carry rain and debris. Standardized tests can be continuously completed for multiple scenarios, including pure wind fields, combined wind and rain, and wind with debris, without requiring equipment replacement or layout adjustments. This solves the problems of existing testing equipment having limited scenarios and cumbersome testing procedures. Furthermore, the entire composite environment simulation mechanism is integrated into the top frame 1 of the testing mechanism, allowing it to move synchronously and at the same speed as the testing mechanism, the tracked intelligent vehicle 23, and the drone under test 25. This ensures that the debris deployment area and the spray coverage area are always precisely matched with the flight area of ​​the drone under test 25. This overcomes the shortcomings of traditional fixed testing equipment in continuously and stably simulating composite environments during the dynamic cruise of the drone 25, adapting to the testing requirements of the equipment's full dynamic flight conditions.

[0081] In one embodiment of the present invention, each of the two arc plates 3 has an arc groove 33 on one side of each other; multiple second mounting frames 31 are fixed with arc plates 34 on both sides facing the arc groove 33, and the arc plates 34 slide in the corresponding arc groove 33 respectively; the surfaces of the two arc plates 34 are provided with evenly arranged toothed grooves 35; mounting plates are fixed on opposite sides of the two arc plates 3; and a third motor is mounted on each mounting plate.

[0082] The output shaft of the third motor is equipped with a gear 36, which rotates within the arc plate 3 and meshes with the tooth groove 35.

[0083] In this embodiment, drive plates 211 are fixed on both sides of multiple first mounting frames 21; a lead screw 212 is screwed inside the drive plate 211, and a cylinder rotates on the top frame 1 and the bottom frame 2; the lead screw 212 is driven by a fourth motor, and the fourth motor is mounted on the top frame 1.

[0084] The two columns 11 have grooves on one side facing the drive plate 211, and the drive plate 211 slides in the grooves.

[0085] Since multiple second mounting frames 31 are fixed together on the arc plate 34, when the second fan 32 is used to test the drone 25, the third motor is controlled to drive the gear 36 to rotate forward and backward. As the gear 36 rotates with the tooth groove 35, when the gear 36 rotates forward and backward, it will drive the arc plate 34 to move up and down in the arc groove 33, thereby driving the second fan 32 in the second mounting frame 31 to move up and down, thereby dynamically changing the direction of the airflow acting on the drone 25 under test. This avoids the defect of the airflow direction being fixed and unable to simulate the irregular changes in airflow acting on the drone 25 in real field operation scenarios, and greatly improves the realism of wind field simulation and the comprehensiveness of test scenarios.

[0086] Simultaneously, the fourth motor drives the lead screw 212 to rotate in both directions, thereby driving the drive plate 211 and the first mounting frame 21 to move up and down. The up-and-down displacement of the first mounting frame 21 synchronously drives the first fan 22 installed inside it to move synchronously, thereby dynamically changing the airflow direction of the lateral airflow acting on the side of the UAV under test 25. This avoids the problem that the airflow direction of the side wind field of the UAV 25 is fixed, which cannot simulate the irregular lateral wind disturbance acting on the UAV 25 in the real operation scenario. It further improves the simulation capability of the dynamic wind field in all dimensions and ensures a high degree of fit between the test conditions and the real operation environment of the UAV 25.

[0087] As an embodiment of the present invention, the bottom of the drone 25 is also equipped with a threaded cylinder 26, and the threaded cylinder 26 is also threaded with a threaded rod 15; the threaded rod 15 is connected to a weight 51 by a pull rope 5; in this embodiment, the bottom of the weight 51 is connected to an elastic rope, and the other side of the elastic rope is connected to the platform 24; an excess elastic rope is reserved between the weight 51 and the platform 24.

[0088] When the drone 25 is being tested, a weight 51 can be suspended from the bottom of the drone 25, connecting the weight 51 to the pull rope 5. The threaded rod 15 at the top of the pull rope 5 engages with the threaded cylinder 26 at the bottom of the drone 25. An elastic rope is reserved between the platform 24 and the pull rope 5. During testing, the force interference of the elastic rope on the drone 25 can be eliminated, thus simulating the scenario of the drone 25 transporting the weight 51. In the event of a crash, when the rotating rod 132 winds the traction rope 14, the control platform 24 moves down, thereby tightening the elastic rope and initially fixing the drone 25. This prevents the drone 25 from swaying during the winding of the traction rope 14 by the rotating rod 132. Due to the presence of the elastic rope, once the elastic rope is straightened, the pull rope 5 can continue to be pulled, thus preventing the drone 25 from being fixed by the elastic rope and unable to move upward.

[0089] In the description of this invention, it should be noted that the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicate the orientation or positional relationship based on the appendix. Figure 1 The orientations or positional relationships shown are for the convenience of describing the present invention and simplifying the description only, and are not intended to 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 limiting the scope of protection of the present invention. In addition, the terms "first", "second", "third", etc. are only used to distinguish the description and should not be construed as indicating or implying relative importance.

[0090] The foregoing has shown and described the basic principles, main features, and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited to the above embodiments. The embodiments and descriptions in the specification are merely illustrative of the principles of the invention. Various changes and modifications can be made to the invention without departing from its spirit and scope, and all such changes and modifications fall within the scope of the present invention as claimed. The scope of protection of the present invention is defined by the appended claims and their equivalents.

Claims

1. A wind resistance simulation device for unmanned aerial vehicles (UAVs), characterized in that, Includes a testing mechanism; the testing mechanism includes a top frame (1) and a bottom frame (2); The top frame (1) and the bottom frame (2) are fixed together by two columns (11); a first mounting frame (21) is provided between the two columns (11) on the same side; a first fan (22) is installed in the first mounting frame (21) in a uniform manner; An arc plate (3) is installed on the left side of the column (11) located on the left side, and the arc plate (3) is fixedly connected to the top frame (1) and the bottom frame (2) respectively; A second mounting frame (31) is provided between the two arc plates (3); a second fan (32) is installed in the second mounting frame (31) in a uniform manner; The top frame (1) has an opening in the middle; two connecting plates (12) are installed in the opening; a traction block (13) is provided between the connecting plates (12); two traction ropes (14) are provided at the bottom of the traction block (13); and a threaded rod (15) is connected to the bottom of the traction rope (14). The bottom frame (2) is mounted on the top of the track-guided intelligent vehicle (23) via support legs, and the track-guided intelligent vehicle (23) is set on the track; The bottom frame (2) is U-shaped; a platform (24) is provided in the middle of the bottom frame (2), and the platform (24) is used to place the drone (25) to be tested; two threaded cylinders (26) are fixedly installed on the top of the drone (25), and the threaded cylinders (26) are threadedly engaged with the threaded rod (15); The platform (24) is equipped with an electric push rod (27) at the bottom, and the other side of the electric push rod (27) is installed on the top of the rail-guided intelligent vehicle (23).

2. The wind resistance simulation device for unmanned aerial vehicles (25) according to claim 1, characterized in that: The traction block (13) has sliders (131) fixed on both sides, and the sliders (131) are perpendicular to the connecting plate (12); The two sliders (131) are provided with slides on opposite sides of the top frame (1), and the sliders (131) slide within the slides; There is a distance between the connecting plate (12) and the traction block (13); pressure sensors (121) are installed on the side of the two connecting plates (12) facing the traction block (13), and the signal output terminals of the two pressure sensors (121) are electrically connected to the motion controller of the track-guided intelligent vehicle (23).

3. The wind resistance simulation device for unmanned aerial vehicles (25) according to claim 2, characterized in that: The traction block (13) has a cavity inside; A rotating rod (132) is rotatable inside the cavity; the rotating rod (132) is driven by a first motor, and the first motor is installed inside the cavity; the traction rope (14) extends into the cavity and is connected to the rotating rod (132); The traction rope (14) passes through one side of the traction block (13) and is slidably connected to the traction block (13); The bottom of the traction block (13) is equipped with a vertical cylinder (16), and the inner diameter of the vertical cylinder (16) is larger than the outer diameter of the threaded rod (15); the two traction ropes (14) pass through the two vertical cylinders (16) respectively; The bottom inner rings of the two vertical cylinders (16) are rounded; the top outer rings of the two threaded rods (15) are rounded.

4. The wind resistance simulation device for unmanned aerial vehicles (25) according to claim 1, characterized in that: The top frame (1) is equipped with a storage compartment (4); The placement chamber (4) has a rotating conveyor belt (41) inside, and the conveyor belt (41) is driven by a second motor, which is installed on the outside of the placement chamber (4). The outer ring surface of the conveyor belt (41) is fixed with evenly arranged partition strips, and the partition strips are attached to the bottom top frame (1); the left side of the conveyor belt (41) is provided with a drop opening (44) on the top frame (1).

5. The wind resistance simulation device for unmanned aerial vehicles (25) according to claim 4, characterized in that: A liquid tank (42) is installed on the left side of the placement chamber (4), and water is placed inside the liquid tank (42); The bottom of the placement chamber (4) is equipped with evenly arranged nozzles (43), and the nozzles (43) are connected to the interior of the liquid tank (42).

6. The wind resistance simulation device for unmanned aerial vehicles (25) according to claim 1, characterized in that: Both of the two arc plates (3) have arc-shaped grooves (33) on one side of each other; Multiple second mounting frames (31) are fixed with arc plates (34) on both sides facing the arc groove (33), and the arc plates (34) slide in the corresponding arc groove (33); The surfaces of the two arc-shaped plates (34) are provided with evenly arranged toothed grooves (35); each of the two arc-shaped plates (3) has a mounting plate fixed on its opposite side; each of the mounting plates has a third motor mounted on it. A gear (36) is mounted on the output shaft of the third motor, and the gear (36) rotates within the arc plate (3) and meshes with the tooth groove (35).

7. The wind resistance simulation device for unmanned aerial vehicles (25) according to claim 6, characterized in that: A drive plate (211) is fixed on both sides of each of the first mounting frames (21); The drive plate (211) has a screw (212) for screw transmission, and the cylinder rotates on the top frame (1) and the bottom frame (2); the screw (212) is driven by a fourth motor, and the fourth motor is mounted on the top frame (1); The two columns (11) have grooves on the side facing the drive plate (211), and the drive plate (211) slides in the grooves.

8. The wind resistance simulation device for unmanned aerial vehicles (25) according to claim 7, characterized in that: The bottom of the drone (25) is also equipped with a threaded cylinder (26), and a threaded rod (15) is also threaded inside the threaded cylinder (26); the threaded rod (15) is connected to a weight (51) by a pull rope (5).

9. The wind resistance simulation device for unmanned aerial vehicles (25) according to claim 8, characterized in that: The bottom of the weight (51) is connected to an elastic rope, and the other side of the elastic rope is connected to the platform (24); an extra elastic rope is reserved between the weight (51) and the platform (24).

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