Low-speed wind tunnel taking laser velocimeter as standard
By introducing slide rails and transmission mechanisms into the low-speed wind tunnel, the problem of inconvenient aircraft replacement operations was solved, the precise positioning and speed measurement accuracy of the aircraft were improved, and the operation process was simplified.
Patent Information
- Application Number
- CN202423128142.4
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-12-18
- Publication Date
- 2025-12-09
- Estimated Expiration
- 2034-12-18
AI Technical Summary
In conventional low-speed wind tunnels, aircraft replacement operations are cumbersome, and the support structure cannot adapt to aircraft replacement work, affecting speed measurement accuracy and ease of operation.
A low-speed wind tunnel based on a laser velocimeter is used, combined with a sliding rail structure and transmission mechanism, including telescopic cylinders, sliding rails, sliders, limit plates and buttons, to achieve the movement of the wind tunnel tube and the precise positioning of the aircraft.
It improves the accuracy of flight data simulation for aircraft at different locations, ensures precise alignment of speed measuring equipment, simplifies aircraft disassembly and assembly operations, and enhances operational convenience and speed measuring accuracy.
Smart Images
Figure CN223650129U_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The utility model relates to low speed wind tunnel technical field especially relates to low speed wind tunnel with laser speed measuring instrument as standard. BACKGROUND
[0002] The conventional wind tunnel refers to the wind tunnel that the wind speed of test section is less than 140m / s, also called low speed wind tunnel. In the field of aerospace, the basic research about low speed flow and the layout and performance research of various aircrafts are all carried out in the conventional wind tunnel.
[0003] When the aircraft simulates flight under different wind speed conditions, the aircraft needs to be placed in the wind tunnel, and since the position of aircraft experiment is usually in the middle position of the wind tunnel, when the aircraft is replaced, the operation is very troublesome, that is, the support structure for placing the aircraft in the wind tunnel is fixed, and cannot well adapt to the aircraft replacement operation.
[0004] Therefore, the low speed wind tunnel with laser speed measuring instrument as standard is proposed. UTILITY MODEL CONTENT
[0005] The utility model discloses a low speed wind tunnel with laser speed measuring instrument as standard.
[0006] In order to realize the above-mentioned purpose, the utility model adopts the following technical scheme:
[0007] The low speed wind tunnel with laser speed measuring instrument as standard, including the wind tunnel pipe, the bottom plate is arranged below the wind tunnel pipe, the speed measuring equipment is connected to the bottom plate upper end, the support rod is connected to the bottom plate upper symmetry, the fixed frame is connected to the support rod outside, the mounting plate is connected to the other end of the fixed frame, the transmission mechanism for driving the wind tunnel pipe reciprocating movement is connected to the wind tunnel pipe outside.
[0008] Preferably, the transmission mechanism includes telescopic air cylinder, the fixed sleeve is connected to the wind tunnel pipe outside, the slide rail is connected to the fixed sleeve outside, and the slide rail one end is fixedly connected in telescopic air cylinder output end.
[0009] Preferably, the support rod one end is connected with the sliding block, and the sliding block is slidably connected on the slide rail.
[0010] Preferably, the telescopic air cylinder outside is connected with the air cylinder hoop, and the air cylinder hoop is fixedly connected on the support rod outside.
[0011] Preferably, the support rod outside is connected with the connecting frame, the cross bar is connected on the connecting frame, the limiting plate is connected to the fixed sleeve upper end, and the cross bar is slidably connected above the limiting plate.
[0012] Preferably, the limiting plate both ends are connected with the button, and the button is arranged at the same height with the cross bar.
[0013] Therefore, the low-speed wind tunnel has the advantages that:
[0014] 1、The sliding rail structure is adopted, the wind tunnel pipe can be moved in the horizontal direction by the sliding rail, the position of the mounting plate can be changed, the flight data of the aircraft at each position can be simulated, the button is arranged to stop the extension and retraction of the telescopic cylinder in time, the extension and retraction of the telescopic cylinder is avoided, and the transmission accuracy is improved.
[0015] 2、The mounting plate structure is adopted, the aircraft can be accurately installed by the mounting plate, the aircraft can be accurately located above the speed measuring equipment when the equipment enters the test, and the speed measuring accuracy is improved. BRIEF DESCRIPTION OF DRAWINGS
[0016] Figure 1 Fig. 1 shows a structural schematic diagram of a low-speed wind tunnel provided by the embodiment of the present application;
[0017] Figure 2 Fig. 2 shows an exploded structural schematic diagram of a connection of the low-speed wind tunnel provided by the embodiment of the present application;
[0018] Figure 3 Fig. 3 shows a structural schematic diagram of a connection of the limiting plate provided by the embodiment of the present application.
[0019] LEGEND:
[0020] 1、The wind tunnel pipe; 2、The base; 3、The speed measuring equipment; 4、The support rod; 5、The fixed sleeve; 6、The limiting plate; 7、The button; 8、The sliding rail; 9、The cylinder hoop; 10、The telescopic cylinder; 11、The fixed frame; 12、The connecting frame; 13、The cross rod; 14、The mounting plate; 15、The sliding block. DETAILED DESCRIPTION
[0021] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of protection of the present application.
[0022] Please refer to Figures 1-3 The present application provides a technical solution:
[0023] Low-speed wind tunnel with laser speedometer as standard, the low-speed wind tunnel is composed of an inlet section, a stable section, a contraction section, a test section, a diffusion section, a power section, a corner section and an exhaust section, under the premise of not affecting the uniformity and stability of the airflow of the working section of the wind tunnel, a ninety-degree elbow pipe is added at the tail end of the wind tunnel, wherein the working section includes the entire structure from the inlet section to the power section, the low-speed wind tunnel has the characteristics of good flow field quality, high uniformity and stability indexes, compact structure, beautiful appearance, small occupied area and convenient installation and movement, stable wind speed control, high precision and simple operation, including a wind tunnel pipe 1, a base 2 is arranged below the wind tunnel pipe 1, a speed measuring device 3 is connected to the upper end of the base 2, support rods 4 are symmetrically connected to the upper end of the base 2, the support rods 4 are provided in two, a fixed frame 11 is connected to the outer side of the support rods 4, an installation plate 14 is connected to the other end of the fixed frame 11, and a transmission mechanism for driving the wind tunnel pipe 1 to move back and forth is connected to the outer side of the wind tunnel pipe 1.
[0024] Specifically, as shown in Figure 1 , the transmission mechanism includes telescopic air cylinders 10, the telescopic air cylinders 10 are provided in two, a fixed sleeve 5 is connected to the outer side of the wind tunnel pipe 1, a slide rail 8 is connected to the outer side of the fixed sleeve 5, the slide rail 8 is provided in two, the two slide rails 8 are symmetrically arranged on the left and right sides of the wind tunnel pipe 1, and one end of the slide rail 8 is fixedly connected to the output end of the telescopic air cylinder 10; when the telescopic air cylinder 10 is telescoped, the slide rail 8 will move synchronously.
[0025] Specifically, as shown in Figure 2 , one end of the support rod 4 is connected with a sliding block 15, and the sliding block 15 is slidingly connected to the slide rail 8; by arranging the sliding block 15 structure, the stability of the slide rail 8 sliding on one side of the support rod 4 is improved.
[0026] Specifically, as shown in Figure 1 , a cylinder hoop 9 is connected to the outer side of the telescopic air cylinder 10, and the cylinder hoop 9 is fixedly connected to the outer side of the support rod 4; the cylinder hoop 9 ensures the firmness of the connection of the telescopic air cylinder 10.
[0027] Specifically, as shown in Figure 1 , a connecting frame 12 is connected to the outer side of the support rod 4, a cross rod 13 is connected to the connecting frame 12, a limiting plate 6 is connected to the upper end of the fixed sleeve 5, and the cross rod 13 is slidingly connected above the limiting plate 6; the limiting plate 6 can limit the cross rod 13 structure.
[0028] Specifically, as shown in Figure 1 , buttons 7 are connected to the two ends of the limiting plate 6, the buttons 7 are arranged at the same height as the cross rod 13, and the telescopic air cylinder 10 stops telescoping when the button 7 structure is pressed.
[0029] In summary, the low-speed wind tunnel provided by the embodiment takes the laser speedometer as a standard. When the aircraft needs to be disassembled, the telescopic cylinder 10 is controlled to retract, so that the mounting plate 14 is in a relative position with the low-speed wind tunnel, that is, the mounting plate 14 moves out of the inside of the wind tunnel. At this time, the wind tunnel is still above the speed measuring device 3, and the speed measuring device 3 can be well protected by the structure of the wind tunnel. When the mounting plate 14 moves out of one end of the wind tunnel pipe 1, the operator can disassemble and assemble the aircraft on the mounting plate 14 at will. When the cross rod 13 contacts and presses the button 7, the telescopic cylinder 10 stops running, that is, after the telescopic cylinder 10 moves to the corresponding state after starting, the telescopic cylinder 10 automatically stops telescoping, greatly improving the convenience of operation.
[0030] The above description of the embodiments enables those skilled in the art to implement or use the present application. Various modifications to these embodiments will be apparent to those skilled in the art, and the general principles defined herein can be implemented in other embodiments without departing from the spirit or scope of the present application. Therefore, the present application will not be limited to these embodiments shown herein, but will conform to the widest scope consistent with the principles and novel features disclosed herein.
Claims
1. Low speed wind tunnel with laser anemometer as standard, comprising a wind tunnel tube (1), characterised in that, The wind tunnel pipe (1) is provided below with a base (2), the upper end of the base (2) is connected with a speed measuring device (3), the base (2) is connected with a support rod (4) symmetrically, the outer side of the support rod (4) is connected with a fixing frame (11), the other end of the fixing frame (11) is connected with a mounting plate (14), the outer side of the wind tunnel pipe (1) is connected with a transmission mechanism for driving the wind tunnel pipe (1) to move reciprocatingly.
2. The laser velocimeter-standard low-speed wind tunnel of claim 1, wherein, The transmission mechanism comprises a telescopic air cylinder (10), the outer side of the wind tunnel pipe (1) is connected with a fixing sleeve (5), the outer side of the fixing sleeve (5) is connected with a sliding rail (8), one end of the sliding rail (8) is fixedly connected with the output end of the telescopic air cylinder (10).
3. The laser velocimeter based low speed wind tunnel of claim 2, wherein, One end of the support rod (4) is connected with a sliding block (15), the sliding block (15) is slidingly connected with the sliding rail (8).
4. The laser velocimeter based low speed wind tunnel of claim 2 wherein, The outer side of the telescopic air cylinder (10) is connected with an air cylinder hoop (9), the air cylinder hoop (9) is fixedly connected with the outer side of the support rod (4).
5. The laser velocimeter based low speed wind tunnel of claim 2 wherein, The outer side of the support rod (4) is connected with a connecting frame (12), the connecting frame (12) is connected with a cross rod (13), the upper end of the fixing sleeve (5) is connected with a limiting plate (6), the cross rod (13) is slidingly connected above the limiting plate (6).
6. The laser velocimeter based low speed wind tunnel of claim 5 wherein, The limiting plate (6) is connected with a button (7) at both ends, the button (7) is arranged at the same height with the cross rod (13).