Wind tunnel test device for testing the performance of an aircraft metal skin

Abstract

This utility model belongs to the field of wind tunnel testing and relates to a wind tunnel testing device for performance testing of aerospace metal skin. It includes: a high-pressure blower, a gas storage tank, a test air duct, a first barometer, and a controller. The high-pressure blower is connected to the inlet end of the gas storage tank, and the outlet end of the gas storage tank is connected to the test air duct. The first barometer is located inside the gas storage tank, and the first barometer, the high-pressure blower, and the controller are electrically connected. The gas storage tank is a spherical tank, and its interior is equipped with a honeycomb flow guide grid and a turbulence damping net. The honeycomb flow guide grid and the turbulence damping net divide the internal space of the gas storage tank into a first space and a second space. The first space is connected to the inlet end of the gas storage tank, and the second space is connected to the outlet end of the gas storage tank. After the high-pressure blower injects airflow into the first space, the airflow sequentially passes through the honeycomb flow guide grid and the turbulence damping net into the second space. This utility model is suitable for dynamic load identification tests on square plate-shaped aerospace metal skin.

Description

Technical Field

[0001] This utility model belongs to the field of wind tunnel testing, specifically relating to a wind tunnel testing device for testing the performance of aerospace metal skin. Background Technology

[0002] Wind tunnel dynamic load tests on aerospace metal skins can analyze and determine the dynamic loads on the surface skin of an aircraft during high-speed operation, providing experimental data and theoretical support for subsequent engineering applications and aircraft structural safety.

[0003] In current experimental research, self-made small wind tunnels are often used to complete wind tunnel dynamic load tests. According to the specifications, wind tunnel structures mostly adopt square cross sections. At the same time, in order to increase the wind speed in the wind tunnel, a structural design of large fans or multiple small fans combined with a converging air duct is generally adopted.

[0004] However, when the test piece is a square plate-shaped aerospace metal skin, the wind tunnel structure with a square cross-section contains a large amount of useless airflow, and the converging duct structure is complex, requiring a lot of rectification structures to make the airflow entering the wind tunnel stable. This results in problems such as high fan air volume and output static pressure, and excessively long converging duct structure. Utility Model Content

[0005] To overcome the deficiencies in the aforementioned related technologies, this utility model proposes a wind tunnel testing device for testing the performance of aerospace metal skin, which is suitable for dynamic load identification tests on square plate-shaped aerospace metal skin.

[0006] To achieve the above technical objectives, this utility model provides a wind tunnel testing apparatus for testing the performance of aerospace metal skin. The wind tunnel testing apparatus for testing the performance of aerospace metal skin includes: a high-pressure blower, a gas storage tank, a test air duct, a first barometer, and a controller;

[0007] The gas storage tank is provided with an inlet end and an outlet end. The inlet end of the gas storage tank is connected to the high-pressure blower, and the outlet end of the gas storage tank is connected to the test air duct. The first pressure gauge is installed inside the gas storage tank. The first pressure gauge and the high-pressure blower are both electrically connected to the controller.

[0008] The gas storage tank is a spherical tank. The interior of the gas storage tank is equipped with a honeycomb flow guide grid and a turbulence damping mesh, which divide the internal space of the gas storage tank into a first space and a second space. The first space is connected to the inlet end of the gas storage tank, and the second space is connected to the outlet end of the gas storage tank. The first barometer is installed in the second space of the gas storage tank. After the high-pressure blower injects airflow into the first space inside the gas storage tank, the airflow then passes through the honeycomb flow guide grid and the turbulence damping mesh sequentially before entering the second space inside the gas storage tank.

[0009] The test air duct is a long box structure with a rectangular cross-section. The width-to-height ratio of the test air duct is 3.5:1 to 4:1. The test air duct and the outlet end of the gas storage tank are connected by a smooth transition.

[0010] Preferably, a guide duct is provided between the outlet end of the gas storage tank and the test air duct. The guide duct has a tubular structure and both ends of the guide duct have square cross sections. The cross section of the end of the guide duct that connects to the outlet end of the gas storage tank is larger than the cross section of the end that connects to the test air duct, and the cross sections of the two ends of the guide duct are similar.

[0011] Preferably, the wind tunnel experimental apparatus further includes a second barometer, which is disposed inside the test duct and is used to detect the air pressure inside the test duct.

[0012] Preferably, the cross-section of the test air duct is rectangular, with a width of 750 mm.

[0013] Preferably, the high-pressure blower is a vortex blower, and the output air volume of the high-pressure blower is 10800m³ / h~13500m³ / h, and the output static pressure is 500Pa~600Pa.

[0014] Preferably, the wind tunnel experimental device further includes a frequency converter, the output terminal of which is electrically connected to the high-pressure blower, and the input terminal of which is electrically connected to the controller.

[0015] The beneficial effects of this utility model are as follows:

[0016] In this invention, the cross-section of the test air duct is rectangular, and the ratio of the width to the height of the test air duct is 3.5:1 to 4:1. This can ensure that the airflow inside the test air duct is relatively stable, while reducing the output air volume and output static pressure of the high-pressure fan, and reducing the test cost of dynamic load identification of aviation metal skin.

[0017] The gas storage tank, honeycomb guide grid, and turbulence damping net in this invention can ensure that there is a stable high-pressure gas flow inside the second space. After passing through the guide air duct, the gas flow velocity entering the test air duct is stabilized and there is very little turbulence. This can provide a uniform and stable airflow for the dynamic load identification test of aerospace metal skin. Attached Figure Description

[0018] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0019] Figure 1 This is a structural diagram of the present invention;

[0020] Figure 2 This is a cross-sectional view of the gas storage tank of this utility model;

[0021] Figure 3 This is a cross-sectional view of the test air duct of this utility model. Detailed Implementation

[0022] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0023] In the description of this utility model, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the accompanying drawings and are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this utility model; the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance. In addition, unless otherwise explicitly specified and limited, the terms "installed," "connected," and "linked" should be interpreted broadly. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; it can be a connection within two components. For those skilled in the art, the specific meaning of the above terms in this utility model can be understood according to the specific circumstances.

[0024] like Figures 1 to 3 As shown, this utility model provides a wind tunnel testing device for testing the performance of aerospace metal skin. The wind tunnel testing device for testing the performance of aerospace metal skin includes: a high-pressure blower 1, a gas storage tank 2, a test air duct 3, a first barometer 4, and a controller.

[0025] The gas storage tank 2 is equipped with an inlet end 21 and an outlet end 24. The inlet end 21 of the gas storage tank 2 is connected to the high-pressure blower 1, and the outlet end 24 of the gas storage tank 2 is connected to the test air duct 3. The first pressure gauge 4 is installed inside the gas storage tank 2. The first pressure gauge 4 and the high-pressure blower 1 are both electrically connected to the controller.

[0026] The gas storage tank 2 is a spherical tank. The interior of the gas storage tank 2 is equipped with a honeycomb flow guide 22 and a turbulence damping net 23. The honeycomb flow guide 22 and the turbulence damping net 23 divide the internal space of the gas storage tank 2 into a first space and a second space. The first space is connected to the inlet end 21 of the gas storage tank 2, and the second space is connected to the outlet end 24 of the gas storage tank 2. The first barometer 4 is installed in the second space. After the high-pressure blower 1 injects airflow into the first space inside the gas storage tank 2, the airflow then passes through the honeycomb flow guide 22 and the turbulence damping net 23 in sequence and enters the second space inside the gas storage tank 2.

[0027] Based on the above implementation, the gas storage tank 2 is a spherical tank with a diameter of 800mm, made of Q235 carbon steel plate with a thickness of 3.0mm, which ensures the rigidity of the gas storage tank 2 and prevents it from deforming during use. Of course, the larger the diameter of the gas storage tank 2, the better the airflow stability inside the test air duct 3.

[0028] In this embodiment, the test air duct 3 is a long box structure with a rectangular cross-section. The width to height ratio of the test air duct 3 is 3.5:1 to 4:1. The test air duct 3 and the outlet end 24 of the gas storage tank 2 are connected by a smooth transition.

[0029] Among them, a guide air duct 5 is also provided between the outlet end 24 of the gas storage tank 2 and the test air duct 3. The guide air duct 5 is a tubular structure with square cross-sections at both ends. The cross-section of the end of the guide air duct 5 that connects to the outlet end 24 of the gas storage tank 2 is larger than the cross-section of the end that connects to the test air duct 3, and the cross-sections at both ends of the guide air duct 5 are similar. The guide air duct 5 enables a smooth transition connection between the outlet end 24 of the gas storage tank 2 and the test air duct 3.

[0030] Specifically, the cross-section of the test air duct 3 is rectangular, with a width of 750mm, which can satisfy the requirement that the gap between the two sides of the aerospace metal skin and the corresponding sidewall of the test air duct 3 is greater than or equal to 75mm.

[0031] In this embodiment, the test duct 3 has a width of 750mm, a height of 200mm, and a length of 1.5m to 2m. It should be noted that the width-to-height ratio of the test duct 3 ranges from 3.5:1 to 4:1. Compared to the current square-section test duct 3, the vertical height is compressed, and the distance between the upper and lower sidewalls of the test duct 3 is reduced. An airflow boundary layer is generated at both the upper and lower sidewalls of the test duct 3, and the thickness of the airflow boundary layer together accounts for 1 / 10 to 1 / 5 of the height. In this embodiment, the test... The test duct 3 has a height of 200mm, which can ensure that there is a sufficient area within the test duct 3 with a uniform and stable airflow field, while avoiding excessive height that would generate a large amount of useless airflow. The width of the test duct 3 is 3.5 to 4 times its height, and the distance between its left and right walls is relatively large, ensuring that the airflow velocity in the central area of ​​the test duct 3 is uniform and stable. At the same time, because the vertical height of the test duct 3 is compressed, the output air volume and output static pressure of the high-pressure fan 1 are reduced, thereby reducing the test cost of dynamic load identification of aerospace metal skin.

[0032] It should be noted that the dimensions of the test air duct 3 are based on its internal space length, height and width, and the test air duct 3 can be made of thicker steel plates, such as Q235 cold-rolled steel plates as the side walls of the test air duct 3, with a thickness of 2.5mm. Reinforcing ribs can also be set on the outside of the test air duct 3, specifically to ensure that the side walls of the test air duct 3 do not produce obvious flutter at 25m / s; the maximum airflow velocity in the test air duct 3 can be 25m / s, that is, the gas static pressure at the inlet of the test air duct 3 reaches 500Pa.

[0033] In this embodiment, the wind tunnel experimental device also includes a second barometer 6, which is installed inside the test air duct 3 and is used to detect the air pressure inside the test air duct 3.

[0034] Among them, the high-pressure blower 1 adopts a vortex blower, and the output air volume of the high-pressure blower 1 is 10800m³ / h~13500m³ / h, and the output static pressure is 500Pa~600Pa.

[0035] In addition, the wind tunnel experimental device also includes a frequency converter, the output of which is electrically connected to the high-pressure blower 1, and the input of which is electrically connected to the controller.

[0036] Based on the above embodiments, the controller includes a microcontroller, specifically an STM32 series; the controller is also electrically connected to the second barometer 6, and the controller also needs to be equipped with a USB output interface; the frequency converter in this embodiment can control the output power of the high-pressure blower 1 to facilitate different airflow speed requirements in the test duct 3.

[0037] In some embodiments, the aerospace metal skin to be tested can be a square structure with a side width of 400mm to 600mm.

[0038] In this embodiment, mounting holes are provided on the upper part of both the left and right side walls of the test air duct 3 for mounting the aviation metal skin to be tested.

[0039] In the specific experiment, the aerospace metal skin to be tested needs to be fixed in the test air duct 3, and the aerospace metal skin is placed horizontally in the middle of the test air duct 3 in the vertical direction; a metal foil strain gauge is fixed on the surface of the aerospace metal skin, and the metal foil strain gauge is connected to the controller. When the airflow in the test air duct 3 causes the aerospace metal skin to vibrate, the vibration amplitude of the aerospace metal skin is detected by the metal foil strain gauge.

[0040] The working principle of this utility model is as follows: The aviation metal skin to be tested is fixed in the test air duct 3. The high-pressure blower 1 is started. The gas generated by the high-pressure blower 1 enters the first space in the gas storage tank 2, and then passes through the honeycomb guide grid 22 and the turbulence damping net 23 in sequence into the second space of the gas storage tank 2. The gas in the second space of the gas storage tank 2 enters the test air duct 3 through the guide air duct 5. After the air pressure in the second space measured by the first barometer 4 tends to stabilize, the data detected by the metal foil strain gauge on the upper surface of the aviation metal skin is collected, and the data of the second barometer 6 is obtained at the same time. The stabilization of the air pressure in the second space of the gas storage tank 2 can confirm that the airflow in the test air duct 3 is a uniform and stable airflow field. The wind speed in the test air duct 3 can be calculated from the data of the second barometer 6.

[0041] In the description of this specification, specific features, structures, materials, or characteristics may be combined in any suitable manner in one or more embodiments or examples.

[0042] Finally, it should be noted that the above description is only a preferred embodiment of the present utility model and is not intended to limit the present utility model. Although the present utility model 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 utility model should be included within the protection scope of the present utility model.

Claims

1. A wind tunnel testing apparatus for testing the performance of aerospace metal skin, characterized in that, include: High-pressure blower, air storage tank, test air duct, first pressure gauge and controller; The gas storage tank is provided with an inlet end and an outlet end. The inlet end of the gas storage tank is connected to the high-pressure blower, and the outlet end of the gas storage tank is connected to the test air duct. The first pressure gauge is installed inside the gas storage tank. The first pressure gauge and the high-pressure blower are both electrically connected to the controller. The gas storage tank is a spherical tank. The interior of the gas storage tank is equipped with a honeycomb flow guide grid and a turbulence damping mesh, which divide the internal space of the gas storage tank into a first space and a second space. The first space is connected to the inlet end of the gas storage tank, and the second space is connected to the outlet end of the gas storage tank. The first barometer is installed in the second space of the gas storage tank. After the high-pressure blower injects airflow into the first space inside the gas storage tank, the airflow then passes through the honeycomb flow guide grid and the turbulence damping mesh sequentially before entering the second space inside the gas storage tank. The test air duct is a long box structure with a rectangular cross-section. The width-to-height ratio of the test air duct is 3.5:1 to 4:

1. The test air duct and the outlet end of the gas storage tank are connected by a smooth transition.

2. The wind tunnel testing apparatus for testing the performance of aerospace metal skin according to claim 1, characterized in that, A guide duct is also provided between the outlet end of the gas storage tank and the test air duct. The guide duct has a tubular structure and both ends of the guide duct have square cross sections. The cross section of the end of the guide duct that connects to the outlet end of the gas storage tank is larger than the cross section of the end that connects to the test air duct, and the cross sections of the two ends of the guide duct are similar.

3. The wind tunnel testing apparatus for testing the performance of aerospace metal skin according to claim 2, characterized in that, The wind tunnel experimental apparatus also includes a second barometer, which is installed inside the test duct and is used to detect the air pressure inside the test duct.

4. The wind tunnel testing apparatus for testing the performance of aerospace metal skin according to claim 3, characterized in that, The test air duct has a rectangular cross-section with a width of 750 mm.

5. The wind tunnel testing apparatus for testing the performance of aerospace metal skin according to claim 4, characterized in that, The high-pressure blower is a vortex blower, and the output air volume of the high-pressure blower is 10800m³ / h~13500m³ / h, and the output static pressure is 500Pa~600Pa.

6. The wind tunnel testing apparatus for testing the performance of aerospace metal skin according to claim 5, characterized in that, The wind tunnel experimental device also includes a frequency converter, the output of which is electrically connected to a high-pressure blower, and the input of which is electrically connected to a controller.

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