An ultrasonic wind tunnel experimental device based on high-frequency pressure sensor

Abstract

The application discloses a supersonic wind tunnel experimental equipment based on a high-frequency pressure sensor, which comprises a first pressure stabilizing chamber and a reflux pipe, wherein the first pressure stabilizing chamber is connected with a second pressure stabilizing chamber through an experimental cover. The supersonic wind tunnel experimental equipment based on the high-frequency pressure sensor, the airflow discharged into the first pressure stabilizing chamber from the experimental cover is discharged into the inside of a gas storage tank through a shunt pipe and the reflux pipe in sequence, so that the gas storage tank can continuously output the airflow into the experimental cover through the second pressure stabilizing chamber, and a barometer is arranged, when the barometer detects that the air pressure in the gas storage tank exceeds a set value, the barometer will transmit the information to a controller, the controller opens a pressure relief valve to automatically release pressure, simultaneously controls an air compressor to stop pumping the airflow, and the working time of the air compressor is shortened, so that the energy-saving purpose is achieved, meanwhile, the sound absorber can process the noise at the same time, noise pollution to the environment is avoided, and the rationality of the structure of the device is improved.

Description

Technical Field

[0001] This invention relates to the field of wind tunnel experimental equipment technology, specifically to a supersonic wind tunnel experimental device based on a high-frequency pressure sensor. Background Technology

[0002] Wind tunnel testing is an aerodynamic experimental method that involves placing aircraft or other object models in a wind tunnel to study gas flow and its interaction with the models in order to understand the aerodynamic characteristics of actual aircraft or other objects. Currently, existing wind tunnel systems are mainly used in large-scale industrial fields, such as aerospace testing and building structure testing. The testing components are large, therefore the wind tunnel systems providing the experimental environment are correspondingly large. At the same time, wind tunnel experiments require extremely high accuracy, placing very high demands on the experimental measuring instruments and the site and cost of the entire wind tunnel system. Therefore, wind tunnel testing is not widely adopted. A search revealed that a typical example of existing wind tunnel testing equipment is a ring-shaped wind tunnel testing device (publication number CN220104454U), which relates to the technical field of wind tunnel testing equipment, including... The system comprises: a fan section (containing a fan); a dispersing section; an equalizing section (used to regulate the stability and uniformity of airflow); a contraction section (used to moderately compress the experimental airflow in the duct to increase the wind speed); a working section (including a first test section and a second test section, with a first contraction section between them; and openings on one side of both test sections for placing the test sample); a diffusion section (used to reduce the outlet wind speed of the duct); and a recirculation section. The fan section, dispersing section, equalizing section, contraction section, working section, diffusion section, and recirculation section are sequentially sealed and connected to form a closed annular wind tunnel. Its main feature is that the annular wind tunnel reduces the overall footprint of the device, allowing for better adaptation to different sites. The flow field in the working section is unaffected by external interference, resulting in lower environmental requirements.

[0003] In summary, the throttling mechanism inside the existing wind tunnel experimental equipment is not conducive to accurate data detection when simulating high-oscillation back pressure. To address these issues, improvements to the existing equipment are necessary. Summary of the Invention

[0004] The purpose of this invention is to provide a supersonic wind tunnel experimental device based on a high-frequency pressure sensor, so as to solve the problem mentioned in the background art that the throttling mechanism inside the existing wind tunnel experimental device is not convenient for accurately detecting its data when simulating high-oscillation back pressure.

[0005] To achieve the above objectives, the present invention provides the following technical solution: a supersonic wind tunnel experimental device based on a high-frequency pressure sensor, comprising a first pressure stabilizing chamber and a return pipe.

[0006] The first pressure stabilizing chamber is connected to the second pressure stabilizing chamber through the experimental cover, and the first and second pressure stabilizing chambers are connected to the inner top of the frame through a hanger. The second pressure stabilizing chamber is connected to the air storage tank through an air inlet pipe, and a pressure stabilizing valve and a gate valve are installed on the air inlet pipe. At the same time, the air storage tank is connected to the air compressor through a branch pipe.

[0007] The return pipe is connected to the other side of the first pressure stabilizing chamber via a diverter pipe. Both the first pressure stabilizing chamber and the experimental hood are connected to the amplification mechanism. The other end of the return pipe is connected to the gas storage tank. A knocking mechanism is installed inside the first pressure stabilizing chamber, and the first pressure stabilizing chamber is connected to a silencer. A high-frequency pressure sensor is connected to the bottom of the experimental hood, and a control panel is provided on the outer wall of the experimental hood. A hood assembly is provided on the outer side of the control panel.

[0008] Preferably, both the air tank and the air compressor are connected to the inner bottom of the frame via a bracket, and a one-way valve is provided on the branch pipe connecting the air tank and the air compressor.

[0009] Preferably, the amplification mechanism includes an amplifier body, a data cable, and a connector, and the amplifier body is connected to the connector via the data cable.

[0010] Preferably, multiple sets of connectors are provided, and the connectors are respectively connected to the first voltage stabilizing chamber, the experimental hood, and the second voltage stabilizing chamber. Meanwhile, a high-definition camera is provided on one side of the experimental hood.

[0011] Preferably, the diverter pipes are evenly distributed on the right side wall of the first pressure stabilizing chamber, and the first pressure stabilizing chamber is funnel-shaped, narrower on the left and wider on the right.

[0012] Preferably, a barometer is installed on the return pipe, and the return pipe is connected to the pressure relief valve through a pipe connector. At the same time, the barometer, controller, pressure relief valve and air compressor are electrically connected.

[0013] Preferably, the striking mechanism includes a device base, a motor, a rotating rod, a cam, a telescopic spring, and a fixing block, and the motor is installed inside the device base. The output end of the motor is connected to the rotating rod, and a cam is provided on the rotating rod.

[0014] Preferably, the cams are evenly distributed on the rotating rod, and the cams are connected to the fixed block by a telescopic spring.

[0015] Preferably, the high-frequency pressure sensors are evenly distributed on the experimental hood, and the high-frequency pressure sensors are electrically connected to the control panel.

[0016] Preferably, the enclosure assembly includes a fixed cover, mounting holes, a monitoring probe, and a supplementary light. The monitoring probe and supplementary light are installed on the side wall of the fixed cover, and the mounting holes are connected to the experimental cover on one side of the control panel through an external connector.

[0017] Compared with the prior art, the beneficial effects of the present invention are: the supersonic wind tunnel experimental device based on a high-frequency pressure sensor,

[0018] (1) This invention can effectively solve the problem that the throttling mechanism inside the existing wind tunnel experimental equipment is not convenient to accurately detect the data when simulating high oscillation back pressure by using a combination of high frequency pressure sensor, monitoring probe, control panel and high-definition camera. The uniformly distributed high frequency pressure sensor can detect and collect the internal pressure at the upstream, downstream and middle positions inside the experimental chamber, and transmit the detection information to the control panel in real time, so that it is convenient to view it remotely through the monitoring probe. At the same time, the shock wave / boundary layer interference flow field can be observed by using high-definition camera, i.e. schlieren technology. That is, the high frequency pressure sensor and schlieren technology are combined with the external pressure scanning valve to accurately detect the self-excited oscillation characteristics of the shock wave train, and optimize the detection structure of the device accordingly.

[0019] (2) The present invention can effectively solve the problem that existing wind tunnel experimental equipment usually needs to continuously output airflow in order to ensure the experiment, resulting in high energy consumption and high noise by using a combination of silencer, diverter pipe, return pipe, barometer and pressure relief valve. The airflow discharged from the experimental hood to the first pressure stabilizing chamber will be discharged to the inside of the gas storage tank through the diverter pipe and return pipe, so that the gas storage tank can continuously output airflow to the experimental hood through the second pressure stabilizing chamber. At the same time, a barometer is installed. When the barometer detects that the gas pressure inside the gas storage tank exceeds the set value, there is a safety hazard. The barometer will transmit this information to the controller. The controller will open the pressure relief valve to automatically relieve pressure and control the air compressor to stop pumping airflow, thereby shortening the working time of the air compressor and achieving the purpose of energy saving. At the same time, the silencer can process noise at the same time, avoid noise pollution of the working environment, and improve the rationality of the device structure.

[0020] (3) The present invention can effectively solve the problem that existing wind tunnel experimental equipment is prone to dust adhering to the inner wall of the device when the airflow is discharged, and manual cleaning is troublesome, by using the knocking mechanism and the second pressure stabilizing chamber in combination. After the experiment is completed, the motor-driven rotating rod in the knocking mechanism drives the cam to rotate. When the cam's protrusion is vertically downward, the fixed block connected to the bottom of the protrusion by the telescopic spring will contact the second pressure stabilizing chamber, thereby causing it to vibrate. At the same time, since the second pressure stabilizing chamber is connected to the first pressure stabilizing chamber through the experimental cover, the second pressure stabilizing chamber will drive the experimental cover to vibrate synchronously with the first pressure stabilizing chamber, thereby cleaning off the dust adhering to its inner wall and discharging it through the diversion pipe. Compared with manual cleaning, it is more convenient and faster. Attached Figure Description

[0021] Figure 1 This is a schematic diagram of the main cross-sectional structure of the present invention;

[0022] Figure 2 This is a schematic diagram of the connection relationship between the experimental cover and the second pressure stabilizing chamber of the present invention.

[0023] Figure 3 For the present invention Figure 1 Enlarged structural diagram at point A in the middle;

[0024] Figure 4 For the present invention Figure 1 Enlarged structural diagram at point B;

[0025] Figure 5 This is a schematic diagram of the overall structure of the cover assembly of the present invention.

[0026] In the diagram: 1. First pressure stabilizing chamber; 2. Frame; 3. Experimental hood; 4. Second pressure stabilizing chamber; 5. Inlet pipe; 6. Air tank; 7. Pressure stabilizing valve; 8. Gate valve; 9. Air compressor; 10. Check valve; 11. Amplification mechanism; 1101. Amplifier body; 1102. Data cable; 1103. Connector; 12. Hanger; 13. Diverter pipe; 14. Return pipe; 15. Barometer; 16. Pipe connector; 17. Pressure relief valve; 18. Striking mechanism; 1801. Equipment base; 1802. Motor; 1803. Rotating rod; 1804. Cam; 1805. Telescopic spring; 1806. Fixing block; 19. Silencer; 20. Control panel; 21. High-frequency pressure sensor; 22. Hood assembly; 2201. Fixing cover; 2202. Mounting hole; 2203. Monitoring probe; 2204. Supplemental light. Detailed Implementation

[0027] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0028] Please see Figure 1-5 This invention provides a technical solution: a supersonic wind tunnel experimental device based on a high-frequency pressure sensor.

[0029] Example 1

[0030] like Figure 1 , Figure 2 and Figure 3 As shown, the first pressure stabilizing chamber 1 is connected to the second pressure stabilizing chamber 4 through the experimental cover 3, and the first pressure stabilizing chamber 1 and the second pressure stabilizing chamber 4 are connected to the inner top of the frame 2 through the hanger 12. The second pressure stabilizing chamber 4 is connected to the air storage tank 6 through the air inlet pipe 5, and a pressure stabilizing valve 7 and a gate valve 8 are installed on the air inlet pipe 5. At the same time, the air storage tank 6 is connected to the air compressor 9 through the branch pipe.

[0031] In a further embodiment, both the air tank 6 and the air compressor 9 are connected to the inner bottom of the frame 2 via a bracket, and a one-way valve 10 is provided on the branch pipe connecting the air tank 6 and the air compressor 9.

[0032] In a further embodiment, the amplification mechanism 11 includes an amplifier body 1101, a data line 1102, and a connector 1103, and the amplifier body 1101 is connected to the connector 1103 via the data line 1102.

[0033] In a further embodiment, multiple sets of connectors 1103 are provided, and the connectors 1103 are respectively connected to the first voltage stabilizing chamber 1, the experimental chamber 3 and the second voltage stabilizing chamber 4. Meanwhile, a high-definition camera is provided on one side of the experimental chamber 3.

[0034] like Figure 1 , Figure 2 , Figure 3 and Figure 5 As shown, the return pipe 14 is connected to the other side of the first pressure stabilizing chamber 1 via the diversion pipe 13. Both the first pressure stabilizing chamber 1 and the experimental hood 3 are connected to the amplification mechanism 11. The other end of the return pipe 14 is connected to the gas storage tank 6. A striking mechanism 18 is installed inside the first pressure stabilizing chamber 1, and the first pressure stabilizing chamber 1 is connected to a silencer 19. A high-frequency pressure sensor 21 is connected to the bottom of the experimental hood 3, and a control panel 20 is installed on the outer wall of the experimental hood 3. A hood assembly 22 is installed on the outer side of the control panel 20.

[0035] In a further embodiment, the diverter pipes 13 are evenly distributed on the right side wall of the first pressure stabilizing chamber 1, and the first pressure stabilizing chamber 1 is funnel-shaped with a narrow left side and a wide right side.

[0036] In a further embodiment, a barometer 15 is installed on the return pipe 14, and the return pipe 14 is connected to the pressure relief valve 17 through the pipe connector 16. At the same time, the barometer 15, the controller, the pressure relief valve 17 and the air compressor 9 are electrically connected.

[0037] In a further embodiment, high-frequency pressure sensors 21 are evenly distributed on the experimental hood 3, and the high-frequency pressure sensors 21 are electrically connected to the control panel 20.

[0038] In a further embodiment, the enclosure assembly 22 includes a fixed cover 2201, a mounting hole 2202, a monitoring probe 2203, and a supplementary light 2204. The monitoring probe 2203 and the supplementary light 2204 are installed on the side wall of the fixed cover 2201. The supplementary light 2204 provides illumination for the monitoring probe 2203 to capture images, thereby ensuring the clarity of the images. Meanwhile, the mounting hole 2202 is connected to the experimental cover 3 on one side of the control panel 20 through an external connector.

[0039] Specifically, in actual operation, the air compressor 9 stores the compressed airflow into the air tank 6. The airflow inside the air tank 6 flows from the left end of the second pressure stabilizing chamber 4 through the air inlet pipe 5 to the experimental chamber 3 and the interior of the second pressure stabilizing chamber 4. The amplifier body 1101 amplifies the signal voltage through the connector 1103. At the same time, the high-frequency pressure sensor 21 detects the internal pressure of the experimental chamber 3 and transmits the monitoring data to the control panel 20 in real time, so that the staff can remotely view it through the monitoring probe 2203.

[0040] The airflow inside the second pressure regulating chamber 4 will be collected through the diverter pipe 13 and sent to the inside of the return pipe 14. Then, it will be discharged into the air storage tank 6 under the transport of the return pipe 14, thus providing support for the airflow output of the air storage tank 6. At the same time, the barometer 15 will detect the air pressure inside the air storage tank 6 in real time. If the pressure exceeds the set value, it will transmit this information to the controller because there is a risk of rupture due to excessive internal pressure. The controller will open the pressure relief valve 17 to automatically relieve pressure and at the same time control the air compressor 9 to stop pressing airflow into the air storage tank 6.

[0041] Example 2

[0042] This embodiment is a further description of the above embodiments. It should be understood that this embodiment includes all the aforementioned technical features and is further described in detail.

[0043] like Figure 2 and Figure 4 As shown, in a further embodiment, the striking mechanism 18 includes a device base 1801, a motor 1802, a rotating rod 1803, a cam 1804, a telescopic spring 1805, and a fixing block 1806. The motor 1802 is installed inside the device base 1801, and the output end of the motor 1802 is connected to the rotating rod 1803. The cam 1804 is provided on the rotating rod 1803.

[0044] In a further embodiment, cams 1804 are evenly distributed on the rotating rod 1803, and cams 1804 are connected to the fixed block 1806 through a telescopic spring 1805.

[0045] Specifically, the motor 1802 drives the rotating rod 1803 to rotate the cam 1804. When the cam 1804 rotates to a vertical downward position, the fixed block 1806 connected to the bottom of the cam by the telescopic spring 1805 will collide with the second pressure stabilizing chamber 4. When the rotating rod 1803 drives the cam 1804 to rotate away from the second pressure stabilizing chamber 4, the fixed block 1806 squeezes the telescopic spring 1805 to end the collision. This allows the second pressure stabilizing chamber 4 and the first pressure stabilizing chamber 1 and the experimental cover 3 connected to it to vibrate synchronously, thereby achieving vibration cleaning.

[0046] Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A supersonic wind tunnel experimental device based on a high-frequency pressure sensor, comprising a first pressure stabilizing chamber (1) and a return pipe (14), characterized in that: The first pressure stabilizing chamber (1) is connected to the second pressure stabilizing chamber (4) through the experimental hood (3), and the first pressure stabilizing chamber (1) and the second pressure stabilizing chamber (4) are connected to the inner top of the frame (2) through the hanger (12). The second pressure stabilizing chamber (4) is connected to the air storage tank (6) through the air inlet pipe (5), and a pressure stabilizing valve (7) and a gate valve (8) are installed on the air inlet pipe (5). At the same time, the air storage tank (6) is connected to the air compressor (9) through the branch pipe. One end of the return pipe (14) is connected to one side of the first pressure stabilizing chamber (1) via a diverter pipe (13), and both the first pressure stabilizing chamber (1) and the experimental hood (3) are connected to the amplification mechanism (11). At the same time, the other end of the return pipe (14) is connected to the gas storage tank (6). A knocking mechanism (18) is installed inside the first pressure stabilizing chamber (1), and the first pressure stabilizing chamber (1) is connected to a silencer (19). A high-frequency pressure sensor (21) is connected to the bottom of the experimental hood (3), and a control panel (20) is provided on the outer wall of the experimental hood (3). Meanwhile, a cover assembly (22) is provided on the outside of the control panel (20). The striking mechanism (18) includes a device base (1801), a motor (1802), a rotating rod (1803), a cam (1804), a telescopic spring (1805), and a fixing block (1806). The motor (1802) is installed inside the device base (1801). The output end of the motor (1802) is connected to the rotating rod (1803), and a cam (1804) is provided on the rotating rod (1803). The cam (1804) is evenly spaced. The amplification mechanism (11) includes an amplifier body (1101), a data cable (1102), and a connector (1103), with the amplifier body (1101) connected to the connector (1103) via the data cable (1102). A barometer (15) is installed on the return pipe (14), and the return pipe (14) is connected to the pressure relief valve (17) via a pipe connector (16). (15), the controller, the pressure relief valve (17) and the air compressor (9) are electrically connected. When the barometer (15) detects that the air pressure inside the air tank (6) exceeds the set value, there is a safety hazard. The barometer (15) will transmit this information to the controller. The controller will open the pressure relief valve (17) to automatically relieve the pressure and at the same time control the air compressor (9) to stop pumping airflow. The high-frequency pressure sensors (21) are evenly distributed on the experimental cover (3) and are electrically connected to the control panel (20).

2. The supersonic wind tunnel experimental device based on a high-frequency pressure sensor according to claim 1, characterized in that: The gas storage tank (6) and the air compressor (9) are both connected to the inner bottom of the frame (2) via a bracket, and a one-way valve (10) is provided on the branch pipe connecting the gas storage tank (6) and the air compressor (9).

3. The supersonic wind tunnel experimental device based on a high-frequency pressure sensor according to claim 2, characterized in that: The connector (1103) is provided in multiple sets, and the connector (1103) is connected to the first voltage stabilizing chamber (1), the experimental cover (3) and the second voltage stabilizing chamber (4) respectively. Meanwhile, a high-definition camera is provided on one side of the experimental cover (3).

4. The supersonic wind tunnel experimental device based on a high-frequency pressure sensor according to claim 1, characterized in that: The diverter pipes (13) are evenly distributed on the right side wall of the first pressure stabilizing chamber (1), and the first pressure stabilizing chamber (1) is funnel-shaped with a narrow left side and a wide right side.

5. The supersonic wind tunnel experimental device based on a high-frequency pressure sensor according to claim 1, characterized in that: The enclosure assembly (22) includes a fixed cover (2201), a mounting hole (2202), a monitoring probe (2203), and a supplementary light (2204). The monitoring probe (2203) and the supplementary light (2204) are installed on the side wall of the fixed cover (2201), and the mounting hole (2202) is connected to the experimental cover (3) on one side of the control panel (20) through an external connector.

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