Wind tunnel device for UAV testing

Abstract

The present invention belongs to the technical field of wind tunnel testing, and in particular to a wind tunnel device for testing unmanned aerial vehicles, comprising: a bottom plate, a plurality of mobile frames are fixedly mounted on the top surface of the bottom plate, and the top surfaces of the plurality of mobile frames are provided with a same device body; a plurality of fixed sleeves, the plurality of fixed sleeves are respectively fixedly mounted on both sides of the device body, and the top surfaces of the plurality of mobile frames are slidably connected with two mobile blocks. The contraction section adopts a ratio of the cross-sectional areas of the two ends of 10:1, which is obtained through experiments, and can uniformly accelerate the airflow to reach the flow rate required by the test section, and at the same time further improve the flow quality of the airflow, reduce the turbulence, and adopt a direct current structure, which can save device space and make the device neater. By installing a damping net and a honeycomb in a stable section, effective rectification can be achieved, and the stability and uniformity of the airflow can be improved.

Description

Technical Field

[0001] The invention belongs to the technical field of wind tunnel testing, and in particular relates to a wind tunnel device for testing unmanned aerial vehicles. Background Art

[0002] UAV is the abbreviation of unmanned aircraft, which is an unmanned aircraft that uses radio remote control equipment and self-contained program control devices, including unmanned helicopters, fixed-wing aircraft, multi-rotor aircraft, unmanned airships, unmanned paragliders, etc.; from a certain perspective, UAVs can complete complex aerial flight tasks and various load tasks under unmanned conditions, and can be regarded as "aerial robots; and the vehicle-mounted wind tunnel test of UAVs uses high-speed airflow to simulate the environment in which UAVs fly in the air, so as to evaluate the aerodynamic performance of UAVs, understand the aerodynamic characteristics of UAVs, determine their optimal design parameters, improve their flight performance and stability, etc. The wind tunnel experiment is to arrange UAVs or other object models on special test fixtures (such as test benches), and place UAVs and other object models in the wind tunnel together, artificially create airflow, so as to simulate various complex flight states of flight or other object models in the air, obtain test data, and thus understand the aerodynamic characteristics of actual UAVs or other objects.

[0003] At present, most of the existing technologies use resin models and electrochemical deposition models. Although these two technologies can quickly realize model production and related tests, they have many difficulties in high-intensity supersonic testing. If high-strength alloy materials are used for design and processing, the production cycle is very long and the production cost is very high. If the inner cavity shape is complex, it is difficult to achieve. In addition, conventional wind tunnel test equipment has the defect of being inconvenient to fix the test fan during use, which brings inconvenience to the user to a certain extent. In view of this, we proposed a UAV test wind tunnel device. Summary of the invention

[0004] The purpose of the present invention is to provide a wind tunnel device for testing unmanned aerial vehicles to solve the problems raised in the above-mentioned background technology.

[0005] In view of this, the present invention provides a wind tunnel device for testing an unmanned aerial vehicle, comprising:

[0006] A bottom plate, a plurality of movable frames are fixedly mounted on the top surface of the bottom plate, and a same device body is disposed on the top surfaces of the plurality of movable frames;

[0007] A plurality of fixed sleeves, wherein the plurality of fixed sleeves are respectively fixedly mounted on both sides of the device body, the top surfaces of the plurality of movable frames are slidably connected to two movable blocks, the top surfaces of the plurality of movable blocks are respectively fixedly mounted with L-shaped blocks, and one end of the plurality of L-shaped blocks is respectively movably sleeved in the plurality of fixed sleeves;

[0008] A plurality of groups of adjustment components, wherein the plurality of groups of adjustment components are respectively arranged in a plurality of moving frames and are used to drive the plurality of moving blocks to move;

[0009] The bottom plate comprises a stabilizing section, a contraction section is fixedly mounted on one end of the stabilizing section, a test section is fixedly mounted on one end of the contraction section, a wind direction changing device is provided on one end of the test section, a diffusion section is fixedly mounted on the other end of the stabilizing section, a fan is fixedly mounted on one end of the diffusion section, and an air intake section is provided on one end of the fan;

[0010] A plurality of Foma wheels are fixedly mounted on the bottom surface of the bottom plate.

[0011] In the above technical solution, further, the adjustment component includes a gear, which is rotatably installed in a mobile frame, and two racks are slidably installed on one side of the interior of the mobile frame, and the two racks are meshed with the gears. Two sliding grooves are provided on the top surface of the mobile frame, and sliders are slidably installed in the two sliding grooves. The top ends of the two sliders are fixedly connected to the bottom surfaces of the two moving blocks, and one side of the two sliders is fixedly connected to one side of the two racks.

[0012] In the above technical solution, further, the adjustment assembly also includes a movable plate, which is slidably installed on the other side of the inside of the movable frame, a first mounting column is fixedly installed on one side of the movable plate, a second mounting column is fixedly installed on one side of the gear, a connecting rod is rotatably installed on the second mounting column, and the other end of the connecting rod is rotatably installed on the first mounting column.

[0013] In the above technical solution, further, a screw rod is rotatably installed in the movable frame, the screw rod is threadedly connected to the movable plate, and a handle is fixedly installed at one end of the screw rod.

[0014] In the above technical solution, further, a side plate is fixedly installed on the outer wall of the screw rod, and the side plate is located on one side of the movable frame. A plurality of first sockets are opened on the side plate, and a plurality of second sockets are opened on one side of the movable frame, and one of the second sockets is movably connected with the same pin in one of the first sockets.

[0015] In the above technical solution, further, a honeycomb is provided in the stabilizing section, a damping net is provided in the stabilizing section, and an inspection door is provided on the stabilizing section.

[0016] In the above technical solution, further, the stabilization section and the diffusion section are both provided with inspection doors, a safety net is provided in the diffusion section, and the test section is provided with a side door, and the side door is made of transparent glass.

[0017] In the above technical solution, further, the cross-sectional shape of the honeycomb grid on the honeycomb device is one of circular, rectangular and hexagonal.

[0018] In the above technical solution, further, a plurality of positioning columns are fixedly installed on the bottom surface of the device body, and a plurality of positioning holes are opened on the top surfaces of the plurality of movable frames, and the plurality of positioning columns are movably connected to the plurality of positioning holes respectively.

[0019] In the above technical solution, further, the ratio of the cross-sectional areas at both ends of the contraction section is 10:1.

[0020] The beneficial effects of the present invention are:

[0021] 1. The UAV test wind tunnel device adopts a cross-sectional area ratio of 10:1 at both ends of the contraction section, which is obtained through experiments. It can evenly accelerate the airflow to reach the flow rate required by the test section, and further improve the flow quality of the airflow and reduce turbulence. The DC structure can save device space and make the device neater. By installing damping nets and honeycombs in the stable section, it can effectively rectify and improve the stability and uniformity of the airflow.

[0022] 2. The UAV test wind tunnel device, when disassembling the device body, pull the pin outward, when the pin is disengaged from the second socket, the limit on the screw rod is released, after the limit on the screw rod is released, turn the handle to drive the screw rod to rotate, when the screw rod rotates, it will drive the movable plate to move on one side of the inner part of the movable frame, when the movable plate moves, the first mounting column, the second mounting column, and the connecting rod cooperate to drive the gear to rotate, when the gear rotates, it will drive the two racks to move, when the two racks move, the two moving blocks will be driven to move through the two sliders, adjust the spacing between the two moving blocks, when the two moving blocks are away from the device body, the L-shaped block will be disengaged from the fixed sleeve, at this time, it will contact the limit on the device body, so as to facilitate the disassembly of the device body, this method is relatively simple to disassemble and install, does not require any operating tools, and is highly practical. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 It is a schematic diagram of the overall structure of the present invention;

[0024] Figure 2 It is a three-dimensional structural schematic diagram of the present invention;

[0025] Figure 3 It is a schematic diagram of the cross-sectional structure of the mobile frame of the present invention;

[0026] Figure 4 It is a partial enlarged structural schematic diagram of the present invention;

[0027] Figure 5 It is a schematic diagram of the bottom plate structure of the present invention;

[0028] Figure 6 It is a schematic diagram of the structure of the device body of the present invention;

[0029] Figure 7 The present invention Figure 1 The enlarged structural diagram at A in the middle;

[0030] Figure 8 The present invention Figure 6 Schematic diagram of the enlarged structure at point B.

[0031] The symbols in the figure are:

[0032] 1. Bottom plate; 2. Moving frame; 3. Device body; 4. Fixed sleeve; 5. Moving block; 6. L-shaped block; 7. Gear; 8. Rack; 9. Slide groove; 10. Slider; 11. Movable plate; 12. First mounting column; 13. Second mounting column; 14. Connecting rod; 15. Screw rod; 16. Handle; 17. Side plate; 18. First plug hole; 19. Second plug hole; 20. Latch; 21. Fomar wheel; 22. Intake section; 23. Fan; 24. Diffusion section; 25. Stable section; 26. Contraction section; 27. Test section; 28. Wind direction changing device; 29. ​​Honeycomb; 30. Damping net; 31. Side door; 32. Inspection door; 33. Safety net; 34. Positioning hole; 35. Positioning column. DETAILED DESCRIPTION

[0033] The following will be combined with the drawings in the embodiments of the present application to clearly describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, rather than all the embodiments. All other embodiments obtained by ordinary technicians in this field based on the embodiments in the present application belong to the scope of protection of this application. Example

[0034] See also Figure 1 - Figure 8As shown, the present embodiment provides a wind tunnel device for testing a UAV, comprising: a bottom plate 1, a plurality of mobile frames 2 are fixedly mounted on the top surface of the bottom plate 1, and the top surfaces of the plurality of mobile frames 2 are provided with a same device body 3; a plurality of fixed sleeves 4, the plurality of fixed sleeves 4 are respectively fixedly mounted on both sides of the device body 3, the top surfaces of the plurality of mobile frames 2 are slidably connected to two mobile blocks 5, the top surfaces of the plurality of mobile blocks 5 are fixedly mounted with L-shaped blocks 6, and one ends of the plurality of L-shaped blocks 6 are respectively movably sleeved in the plurality of fixed sleeves 4; a plurality of groups of adjustment components, the plurality of groups of adjustment components are respectively arranged in the plurality of mobile frames 2, and are used to drive the plurality of mobile blocks 5 to move; the bottom plate 1 comprises a stabilizing section 25, one end of the stabilizing section 25 is fixedly mounted with a contraction section 26, and one end of the contraction section 26 is fixedly mounted with a test A test section 27 is provided at one end of the test section 27 with a wind direction changing device 28, a diffuser section 24 is fixedly installed at the other end of the stable section 25, a fan 23 is fixedly installed at one end of the diffuser section 24, and an air inlet section 22 is provided at one end of the fan 23; multiple Forma wheels 21 are fixedly installed on the bottom surface of the base plate 1, and the contraction section 26 adopts a cross-sectional area ratio of 10:1 at both ends, which is obtained through experiments, and can evenly accelerate the airflow to reach the flow rate required by the test section 27, while further improving the flow quality of the airflow, reducing turbulence, and adopting a direct current structure, which can save device space and make the device neater. By installing a damping net 30 and a honeycomb 29 in the stable section 25, it can effectively rectify and improve the stability and uniformity of the airflow. Example

[0035] This embodiment provides a wind tunnel device for testing unmanned aerial vehicles, which, in addition to the technical solutions of the above embodiments, also has the following technical features.

[0036] In this embodiment, the adjustment component includes a gear 7, which is rotatably installed in the mobile frame 2. Two racks 8 are slidably installed on one side of the interior of the mobile frame 2. The two racks 8 are meshed with the gear 7. Two slide grooves 9 are provided on the top surface of the mobile frame 2. Slide blocks 10 are slidably installed in the two slide grooves 9. The top ends of the two slide blocks 10 are fixedly connected to the bottom surfaces of the two moving blocks 5, and one side of the two slide blocks 10 is fixedly connected to one side of the two racks 8.

[0037] In this embodiment, the adjustment assembly also includes a movable plate 11, which is slidably mounted on the other side of the interior of the mobile frame 2. A first mounting column 12 is fixedly mounted on one side of the movable plate 11, and a second mounting column 13 is fixedly mounted on one side of the gear 7. A connecting rod 14 is rotatably mounted on the second mounting column 13, and the other end of the connecting rod 14 is rotatably mounted on the first mounting column 12.

[0038] In this embodiment, a screw rod 15 is rotatably installed in the movable frame 2 , the screw rod 15 is threadedly connected to the movable plate 11 , and a handle 16 is fixedly installed at one end of the screw rod 15 .

[0039] In this embodiment, a side plate 17 is fixedly installed on the outer wall of the screw rod 15, and the side plate 17 is located on one side of the mobile frame 2. A plurality of first sockets 18 are opened on the side plate 17, and a plurality of second sockets 19 are opened on one side of the mobile frame 2. One of the second sockets 19 and one of the first sockets 18 are movably connected with the same pin 20. Example

[0040] This embodiment provides a wind tunnel device for testing unmanned aerial vehicles, which, in addition to the technical solutions of the above embodiments, also has the following technical features.

[0041] In this embodiment, a honeycomb 29 is provided in the stabilizing section 25, a damping net 30 is provided in the stabilizing section 25, and an inspection door 32 is provided on the stabilizing section 25. The honeycomb 29 is used to guide and divide the large vortex of the airflow, which is beneficial to accelerate the attenuation of the vortex.

[0042] In this embodiment, an inspection door 32 is provided on the stabilizing section 25 and the diffusion section 24, a safety net 33 is provided in the diffusion section 24, and a side door 31 is provided on the test section 27. The side door 31 is made of transparent glass, which is convenient for observing and replacing the test product. The window of the side door 31 is made of transparent glass, which is convenient for test observation and taking pictures. The inspection door 32 is mainly for detection and maintenance. The safety net 33 prevents the test product from being loosely fixed and entering the moving frame 2 along the airflow to damage the fan 23.

[0043] In this embodiment, the cross-sectional shape of the honeycomb grid on the honeycomb 29 is one of circular, rectangular and hexagonal.

[0044] In this embodiment, a plurality of positioning posts 35 are fixedly installed on the bottom surface of the device body 3, and a plurality of positioning holes 34 are opened on the top surfaces of the plurality of movable frames 2. The plurality of positioning posts 35 are movably connected with the plurality of positioning holes 34 respectively, and the plurality of positioning holes 34 and the plurality of positioning posts 35 facilitate installation and positioning of the device body 3 during installation.

[0045] In this embodiment, the ratio of the cross-sectional areas at both ends of the contraction section 26 is 10:1, which is obtained through experiments and can uniformly accelerate the airflow to reach the flow rate required by the test section 27, while further improving the flow quality of the airflow and reducing turbulence.

[0046] Working principle: The ratio of the cross-sectional area at both ends of the contraction section 26 is 10:1, which is obtained through experiments. It can evenly accelerate the airflow to reach the flow rate required by the test section 27, and further improve the flow quality of the airflow and reduce the turbulence. The direct current structure can save the device space and make the device neater. By installing the damping net 30 and the honeycomb 29 in the stable section 25, it can effectively rectify and improve the stability and uniformity of the airflow.

[0047] When the device body 3 is disassembled, the latch 20 is pulled outward. When the latch 20 is disengaged from the second insertion hole 19, the limit on the screw rod 15 is released. After the limit on the screw rod 15 is released, the handle 16 is turned to drive the screw rod 15 to rotate. When the screw rod 15 rotates, it will drive the movable plate 11 to move on one side of the inner part of the movable frame 2. When the movable plate 11 moves, the first mounting column 12, the second mounting column 13, and the connecting rod 14 cooperate to drive the gear 7 to rotate. When the gear 7 rotates, it will drive the two racks 8 to move. When the two racks 8 move, the two moving blocks 5 will be driven to move through the two sliders 10 to adjust the spacing between the two moving blocks 5. When the two moving blocks 5 are away from the device body 3, the L-shaped block 6 will be disengaged from the fixed sleeve 4. At this time, it contacts the limit on the device body 3, thereby facilitating the disassembly of the device body 3. This method is relatively simple to disassemble and install, does not require any operating tools, and is highly practical.

[0048] The embodiments of the present application are described above in conjunction with the accompanying drawings. In the absence of conflict, the embodiments in the present application and the features in the embodiments can be combined with each other. The present application is not limited to the above-mentioned specific implementation methods. The above-mentioned specific implementation methods are merely illustrative and not restrictive. Under the guidance of the present application, ordinary technicians in this field can also make many forms without departing from the purpose of the present application and the scope of protection of the claims, all of which are within the protection of the present application.

Claims

1. A wind tunnel device for testing drones, characterized in that: include: A bottom plate (1), a plurality of movable frames (2) being fixedly mounted on the top surface of the bottom plate (1), and a same device body (3) being provided on the top surfaces of the plurality of movable frames (2); A plurality of fixed sleeves (4), wherein the plurality of fixed sleeves (4) are respectively fixedly mounted on both sides of the device body (3); the top surfaces of the plurality of movable frames (2) are slidably connected to two movable blocks (5); the top surfaces of the plurality of movable blocks (5) are respectively fixedly mounted with L-shaped blocks (6); and one end of the plurality of L-shaped blocks (6) is respectively movably sleeved in the plurality of fixed sleeves (4); A plurality of groups of adjustment components, wherein the plurality of groups of adjustment components are respectively arranged in a plurality of movable frames (2) and are used to drive the plurality of movable blocks (5) to move; The bottom plate (1) comprises a stabilizing section (25), a contraction section (26) being fixedly mounted on one end of the stabilizing section (25), a test section (27) being fixedly mounted on one end of the contraction section (26), a wind direction changing device (28) being provided at one end of the test section (27), a diffusion section (24) being fixedly mounted on the other end of the stabilizing section (25), a fan (23) being fixedly mounted on one end of the diffusion section (24), and an air intake section (22) being provided at one end of the fan (23); A plurality of Forma wheels (21), wherein the plurality of Forma wheels (21) are fixedly mounted on the bottom surface of the bottom plate (1); The adjustment component comprises a gear (7), the gear (7) being rotatably mounted in the moving frame (2), two racks (8) being slidably mounted on one side of the interior of the moving frame (2), the two racks (8) being meshed with the gear (7), the top surface of the moving frame (2) being provided with two slide grooves (9), sliders (10) being slidably mounted in the two slide grooves (9), the top ends of the two sliders (10) being respectively fixedly connected to the bottom surfaces of the two moving blocks (5), one side of the two sliders (10) being respectively fixedly connected to one side of the two racks (8), the adjustment component further comprises a movable plate (11), the movable plate (11) being slidably mounted on the other side of the interior of the moving frame (2), a first mounting column (12) being fixedly mounted on one side of the movable plate (11), a second mounting column (13) being fixedly mounted on one side of the gear (7), a connecting rod (14) being rotatably mounted on the second mounting column (13), the other end of the connecting rod (14) being rotatably mounted on the first mounting column (12), the moving frame (2) being provided with a plurality of movable plates (11) and a plurality of movable plates (11) being provided with a plurality of movable plates (11). A screw rod (15) is rotatably mounted in the movable frame (2), the screw rod (15) being threadedly connected to the movable plate (11), a handle (16) being fixedly mounted on one end of the screw rod (15), a side plate (17) being fixedly mounted on the outer side wall of the screw rod (15), the side plate (17) being located on one side of the movable frame (2), a plurality of first plug holes (18) being formed on the side plate (17), and a plurality of second plug holes (19) being formed on one side of the movable frame (2), one of the second plug holes (19) being connected to the movable plate (11). A same latch (20) is movably sleeved in one of the first plug holes (18), a honeycomb (29) is provided in the stabilizing section (25), a damping net (30) is provided in the stabilizing section (25), an inspection door (32) is provided on the stabilizing section (25), both the stabilizing section (25) and the diffuser section (24) are provided with an inspection door (32), a safety net (33) is provided in the diffuser section (24), and a side door (31) is provided on the test section (27), and the side door (31) is made of transparent glass.

2. The UAV test wind tunnel device according to claim 1, characterized in that: The cross-sectional shape of the honeycomb grid on the honeycomb device (29) is one of circular, rectangular and hexagonal.

3. The UAV test wind tunnel device according to claim 1, characterized in that: A plurality of positioning columns (35) are fixedly mounted on the bottom surface of the device body (3), and a plurality of positioning holes (34) are provided on the top surfaces of the plurality of movable frames (2). The plurality of positioning columns (35) are movably sleeved with the plurality of positioning holes (34) respectively.

4. The UAV test wind tunnel device according to claim 1, characterized in that: The ratio of the cross-sectional areas at both ends of the contraction section (26) is 10:1.

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