A complex wind environment simulation test device

Abstract

This application relates to the field of wind tunnel simulation testing technology, specifically to a complex wind environment simulation testing device, used to solve the problem in existing wind tunnels where direct convergence of airflow can easily lead to turbulence and impede airflow quality improvement. It includes a support frame and a wind tunnel assembly connected to the support frame; wherein the wind tunnel assembly includes multiple sub-wind tunnels, each sub-wind tunnel having an inlet and an outlet. All the inlets are arranged in a spherical array, and all the outlets are arranged in a rectangular array. The inlets have an arc-shaped flared structure, and the outlets of all the sub-wind tunnels are arranged adjacently so that the overall structure of all the sub-wind tunnels forms a contraction shape. This application utilizes the inlets to provide guidance, reducing airflow rebound, and since each sub-wind tunnel is independent, turbulence is less likely to occur, resulting in a relatively high quality of the final output airflow.

Description

Technical Field

[0001] This application relates to the field of wind tunnel simulation testing technology, specifically to a complex wind environment simulation testing device. Background Technology

[0002] Wind tunnel testing is an experimental method that simulates real-world airflow conditions in a wind tunnel to test models or actual objects such as aircraft and automobiles. It can accurately measure aerodynamic and aerothermal parameters, helping to optimize designs and verify performance. Widely used in aerospace, automotive manufacturing, and other fields, it is an important tool for studying aerodynamics.

[0003] The invention patent application with publication number CN119666302A discloses a wind tunnel that can simulate a multi-angle fan array. By controlling the angle of the fans, airflow in different directions can be obtained. After the fans rotate, their air intake surfaces will face the inner wall of the air duct, and the airflow taken in by multiple fans will directly merge, which can easily generate turbulence. The airflow quality needs to be improved. Summary of the Invention

[0004] This application provides a complex wind environment simulation test device to solve the problem that direct convergence of airflow during wind tunnel intake in the prior art easily leads to turbulence and the airflow quality needs to be improved.

[0005] This application is achieved through the following technical solution:

[0006] A complex wind environment simulation test device, comprising a support frame and a wind tunnel assembly connected to the support frame;

[0007] The wind tunnel assembly includes multiple sub-wind tunnels, each having an air inlet and an air outlet. All the air inlets are arranged in a spherical array, and all the air outlets are arranged in a rectangular array. The air inlets have an arc-shaped flared structure, and the air outlets of all the sub-wind tunnels are arranged adjacent to each other so that the overall structure of all the sub-wind tunnels forms a contracted shape.

[0008] In some alternative embodiments, adjacent air inlets have a gap of 2 ± 0.25 mm in the first array direction and a gap of 40 ± 1.5 mm in the second array direction.

[0009] In some optional embodiments, in the second array direction, the number of sub-wind tunnels is not less than 6, and the included angle between the centers of the first and last two sub-wind tunnels is not less than 36°.

[0010] In some alternative embodiments, the number of sub-wind tunnels is no less than eight in the first array direction.

[0011] In some optional embodiments, the sub-wind tunnel includes a fan section, a diffuser section, a stabilizing section, a contraction section, and a buffer section connected in sequence;

[0012] The buffer segment extends in a broken line direction.

[0013] In some optional embodiments, the bending angle of the buffer section is 132° to 176°.

[0014] In some alternative embodiments, the inlet and outlet of the contraction section are both rectangular, wherein the profile of the contraction section is defined by a Vickers curve, and its four outer wall surfaces are generated by the profile.

[0015] In some alternative embodiments, the diffuser section is configured as a square-to-round diameter reducer.

[0016] In some optional embodiments, the complex wind environment simulation test apparatus further includes a damping section, and the air outlets of all the sub-wind tunnels are connected to the damping section.

[0017] In some alternative embodiments, a counterweight plate is mounted on the support.

[0018] Compared with the prior art, this application has the following advantages and beneficial effects:

[0019] This application provides a complex wind environment simulation test device. By designing the air inlets of the sub-wind tunnels as arc-shaped flared structures, the arc-shaped air inlet surface has a guiding effect, which can reduce airflow rebound and reduce airflow turbulence and other phenomena that may occur within the sub-wind tunnels. The air inlets of all sub-wind tunnels are arranged in a spherical array, which has a larger air inlet area. In each direction, the air inlet direction of the sub-wind tunnel coincides with the extension direction of the air inlet channel behind it, and the airflow does not rebound after entering the air inlet channel. At the same time, each sub-wind tunnel is an independent wind tunnel structure, which isolates the airflow in each direction from each other and guides it individually, ensuring the quality of the airflow entering from each direction. Finally, the air outlets of all sub-wind tunnels extend in parallel directions, and the airflows from each direction are uniformly mixed when they flow out, without mutual impact, ensuring the quality of the final airflow. Compared with wind tunnels in the prior art, this application reduces the occurrence of airflow turbulence and has better airflow quality, making it suitable for complex wind environment simulation tests. Attached Figure Description

[0020] To more clearly illustrate the technical solutions of the exemplary embodiments of this application, the accompanying drawings used in the embodiments will be briefly described below. It should be understood that the following drawings only show some embodiments of this application and should not be considered as a limitation of the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort. In the drawings:

[0021] Figure 1 A schematic diagram of the isometric structure of the complex wind environment simulation test device provided in the embodiments of this application;

[0022] Figure 2 This is a front view structural diagram of the complex wind environment simulation test device provided in the embodiments of this application;

[0023] Figure 3 This is a top view of the complex wind environment simulation test device provided in the embodiments of this application;

[0024] Figure 4 This is a side view of the complex wind environment simulation test device provided in the embodiments of this application;

[0025] Figure 5 This is a rear view structural diagram of the complex wind environment simulation test device provided in the embodiments of this application;

[0026] Figure 6 This is a schematic diagram of the sub-wind tunnel structure provided in an embodiment of this application;

[0027] Figure 7 A simplified flow simulation model for a single sub-wind tunnel;

[0028] Figure 8 A simulated velocity contour map for a single sub-wind tunnel fan;

[0029] Figure 9 A calculation model for multi-fan interference;

[0030] Figure 10 Velocity contour plot of the test section cross section when the Widosinski curve is used in the contraction section;

[0031] Figure 11 Velocity contour plot of the test section cross section when using a bicubic curve in the contraction section;

[0032] Figure 12 The velocity contour plot of the test section cross-section when the fifth power curve is used in the contraction section;

[0033] Figure 13 The streamline diagram of the longitudinal section of the wind tunnel when the Vidosinski curve is used for the contraction section;

[0034] Figure 14 Streamline diagram of the longitudinal section of the wind tunnel when a bicubic curve is used for the contraction section;

[0035] Figure 15 The streamline diagram of the longitudinal section of the wind tunnel when the fifth power curve is used for the contraction section;

[0036] Figure 16 Static pressure cloud diagram of the longitudinal section of the sub-wind tunnel when the Vidosinski curve is used for the contraction section;

[0037] Figure 17 Static pressure cloud diagram of the longitudinal section of the sub-wind tunnel when using a bicubic curve for the contraction section;

[0038] Figure 18 Static pressure cloud diagram of the longitudinal section of the sub-wind tunnel when the fifth power curve is used for the contraction section;

[0039] Figure 19 The motor speed versus wind speed fitting curve;

[0040] Figure 20 A line graph showing the dynamic pressure stability coefficient at the center of the test section;

[0041] Figure 21 This is a velocity contour map of the central section of the test section at a wind speed of 7 m / s.

[0042] Figure 22 This is a velocity contour map of the central section of the test section at a wind speed of 12 m / s.

[0043] The attached diagram shows the markings and corresponding component names:

[0044] 1-Support, 2-Sub-wind tunnel, 21-Fan section, 22-Diffuser section, 23-Stabilizing section, 24-Contraction section, 25-Buffer section, 3-Counterweight plate, 4-Adjustable support, 5-Cast wheel, 6-Shock absorption section. Detailed Implementation

[0045] To make the objectives, technical solutions, and advantages of this application clearer, the following detailed description is provided in conjunction with the embodiments and accompanying drawings. The illustrative embodiments and descriptions of this application are only for explaining this application and are not intended to limit this application.

[0046] Please refer to them together. Figures 1-5 This application provides a complex wind environment simulation test device, which includes a support 1 and a wind tunnel assembly connected to the support 1.

[0047] The wind tunnel assembly includes multiple sub-wind tunnels 2, each sub-wind tunnel 2 having an air inlet and an air outlet. All the air inlets are arranged in a spherical array, meaning that the centers of all the air inlets are located on the same spherical surface. All the air outlets are arranged in a rectangular array, meaning that the extension directions of all the air outlets are parallel to each other. The air inlets have an arc-shaped flared structure, thereby ensuring that each air inlet has a large air intake area. The air outlets of all the sub-wind tunnels 2 are arranged adjacently so that the overall structure of all the sub-wind tunnels 2 forms a contraction shape, meaning that the arrangement area on the air outlet side of the sub-wind tunnel 2 is smaller than the arrangement area on the air inlet side, thus making the overall shape of the wind tunnel assembly form a contraction shape with one side larger and the other side smaller.

[0048] The support 1 in this embodiment can adopt a frame structure, for example, it can be composed of several rectangular tubes to form a frame with an overall rectangular shape. The support 1 includes at least two rectangular frames with different areas. The larger rectangular frame is used to support the air inlet side structure of the wind tunnel assembly, and the smaller rectangular frame is used to support the air outlet side structure of the wind tunnel assembly.

[0049] Compared with existing wind tunnel testing devices, the complex wind environment simulation testing device provided in this application embodiment designs the air inlet of the sub-wind tunnel 2 as an arc-shaped flared structure. The arc-shaped air inlet surface has a guiding effect, which can reduce airflow rebound and reduce airflow turbulence and other phenomena that may occur in the sub-wind tunnel 2. At the same time, the air inlet structure makes the sub-wind tunnel 2 have a larger air inlet area. The airflow from each direction is divided into multiple paths entering the wind tunnel assembly. Each path of airflow is isolated by the sub-wind tunnel 2, and each sub-wind tunnel 2 is a complete wind tunnel structure. The airflow quality of each path of airflow flowing out of the sub-wind tunnel 2 is better. Since the air outlets of each sub-wind tunnel 2 extend in parallel directions, when the wind tunnel assembly exits, the airflows will not collide with each other, and each path of airflow has better airflow quality. Finally, they can be smoothly merged, thereby ensuring the final airflow quality of the wind tunnel assembly.

[0050] It should be noted that, in the embodiments of this application, the adjacent arrangement means that the outer walls of the air outlets of the two sub-wind tunnels 2 are in contact with each other. For example, if the air outlet of the sub-wind tunnel 2 is a rectangular opening, then the four outer walls of the air outlet are in contact with the outer walls of the other four sub-wind tunnels 2 respectively.

[0051] In some alternative embodiments, adjacent air inlets have a gap of 2 ± 0.25 mm in the first array direction and a gap of 40 ± 1.5 mm in the second array direction.

[0052] In this embodiment, since the air inlets are arranged in a spherical array, both the first and second array directions are arc curves, and they are perpendicular to each other in three-dimensional space. In the first array direction, each air inlet has a gap with its adjacent air inlet. This gap prevents collisions between adjacent air inlets due to minor vibrations during operation. The small gap design ensures sufficient air intake for the sub-wind tunnel 2 in the first array direction. In the second array direction, each air inlet has a larger gap with its adjacent air inlet. The spacing ensures that the air inlets occupy a large area in the second array direction, thus enabling all sub-wind tunnels 2 to have a large airflow intake area in three-dimensional space, thereby ensuring that the test device as a whole has a large air intake volume. In particular, since the air inlets are flared, adjacent air inlets can take in airflow from the space within the gap in the second array direction. The gap of 40±1.5mm ensures that the airflow intake range of two adjacent air inlets reaches the maximum and does not interfere with each other, ensuring that the airflow taken in by the air inlet of each sub-wind tunnel 2 is relatively stable, thereby ensuring the airflow quality when the device is vented.

[0053] It should be noted that the gaps in the first array direction and the gaps in the second array direction of the sub-wind tunnel 2 are both positioned with the edge of the air inlet flare structure as the positioning reference.

[0054] In some optional embodiments, in the second array direction, the number of sub-wind tunnels 2 is not less than 6, and the included angle between the centers of the first and last two sub-wind tunnels 2 is not less than 36°.

[0055] In this embodiment, the design of the number of sub-wind tunnels 2 in the second array direction and the overall angle range design make the air inlets of the sub-wind tunnels 2 form a continuous and wide air intake surface in three-dimensional space. Since the air inlets adopt an flared structure, the adjacent air inlets have a large gap in the second array direction, so that the air intake area of ​​all air inlets is much larger than the simple superposition of the area of ​​a single air inlet. This expands the overall air intake capture range of the wind tunnel assembly, enabling it to capture airflow from a wider spatial angle. At the same time, a sufficient number of sub-wind tunnel 2 units ensures that the air intake is sufficient and evenly distributed under the condition of multi-channel coordinated air intake, providing a structural basis for the airflow and flow field of the stable and uniform high-quality test wind field to be generated at the rear air outlet, effectively improving the accuracy and reliability of complex wind environment simulation.

[0056] In some alternative embodiments, the number of sub-wind tunnels 2 is not less than 8 in the first array direction.

[0057] like Figure 6As shown, in some optional embodiments, the sub-wind tunnel 2 includes a fan section 21, a diffuser section 22, a stabilizing section 23, a contraction section 24, and a buffer section 25 connected in sequence; wherein the buffer section 25 extends in a zigzag direction.

[0058] In this embodiment, the extension direction of the buffer section 25 is designed as a broken line, giving it a geometrically abrupt structure. This structure can induce the collision, breakup, and dissipation of tiny vortices that may be generated in the contraction section 24. By utilizing the flow channel turning characteristics, the turbulent kinetic energy can be effectively converted into heat energy and dissipated, reducing the turbulence of the final outgoing airflow and ensuring the stability of the final outgoing airflow. In addition, if there are air layers with different flow velocities in the buffer section 25, they can be remixed at the turning point due to centrifugal force. This can effectively smooth out any tiny velocity gradients that may exist from the front end, ensuring uniform airflow velocity at the outlet and reducing the velocity difference between the outlet center and the vicinity of its wall, thereby ensuring the consistency of the flow field in the subsequent test section.

[0059] In some optional embodiments, the bending angle of the buffer segment 25 is 132° to 176°.

[0060] In this embodiment, if the bending angle of the buffer section 25 is too small, a sudden turn will occur. Although the energy dissipation effect is good, it will cause excessive pressure loss. When the airflow passes through the turn, it may generate flow separation and large low-frequency vortices, which will have a significant impact on the airflow quality. If the bending angle of the buffer section 25 is too large and the airflow path is too gentle, it will not be able to generate effective flow separation and vortices, reducing the turbulence dissipation capacity. In this embodiment, the bending angle of the buffer section 25 is designed to be 132°~176°. At the turn, a stable separation zone with moderate intensity and controllable scale can be generated. When the airflow passes through the turn, a small disturbance occurs, and the generated vortices are small in scale and high in frequency, which can effectively dissipate the residual turbulent kinetic energy from the front section, while the energy loss is within the expected range. At the same time, at this bending angle, the central area and the edge area of ​​the airflow can have sufficient momentum exchange, which will enable the uniformity of the flow velocity distribution at the air outlet to reach the optimal level.

[0061] In some alternative embodiments, the inlet and outlet of the contraction section 24 are both rectangular, wherein the profile of the contraction section 24 is defined by a Vickers curve, and its four outer wall surfaces are generated by the profile.

[0062] In this embodiment, the portion between the inlet and outlet of the contraction segment 24 is equivalent to being formed based on a Vickers curve scan, meaning that regardless of whether the contraction segment 24 is observed from the top, bottom, left, or right, both the upper and lower outer wall surfaces of the contraction segment 24 are Vickers curves.

[0063] The usual airflow conditioning method is to dampen first and then accelerate to avoid amplifying turbulence during acceleration. In this embodiment, according to the direction of airflow, the contraction section 24 is configured before the buffer section 25, and the contraction section 24 is designed as a three-dimensional contraction structure, which can accelerate the airflow of the stabilization section 23 without deviation. The buffer section 25 will be able to receive high-speed airflow with good directional consistency and uniform kinetic energy. Thus, the buffer section 25 can efficiently and selectively act on the small lateral pulsations and high-speed vortices that may remain in the airflow.

[0064] A typical contraction section 24 usually consists of two planar walls and two Vickers curved walls forming a two-dimensional contraction structure. The two curved sidewalls of this structure can generate a pressure gradient, causing the airflow to accelerate towards the center. However, the two planar walls cannot generate the same pressure gradient. This can lead to a large lateral pressure difference forming in the corner region between the Vickers curved wall and the planar wall. This lateral pressure difference can force the airflow to spiral from the center towards the corner, forming a corner vortex. This will consume a large amount of energy, increase pressure loss, and may also entrain low-speed airflow, disrupting the velocity uniformity of the sub-wind tunnel 2 outlet. Increase the turbulence at the air outlet; in this embodiment, the contraction section 24 adopts a three-dimensional contraction structure. The four Vickers curved walls within the contraction section 24 contract synchronously and uniformly toward the center. The pressure gradient distribution at any position is three-dimensionally symmetrical. Under normal circumstances, no lateral pressure difference will be generated, preventing the generation of angular vortices and ensuring the uniformity of airflow velocity at the outlet of the sub-wind tunnel 2. For each sub-wind tunnel 2, this is equivalent to outputting a rectangular flow field with basically uniformity. When the airflow of multiple sub-wind tunnels 2 converges, it is not easy to generate shear, ensuring that the airflow quality of each sub-wind tunnel 2 is better, and the overall airflow quality can be guaranteed.

[0065] In some alternative embodiments, the diffuser section 22 is configured as a square-to-round diameter reducer.

[0066] In this embodiment, when the diffuser section 22 is configured as a square-to-round diameter reducer, it can form a precise geometric match with the outlet of the fan section 21, ensuring that energy is completely captured and avoiding energy loss caused by sudden diameter change. The inside of the square-to-round diameter reducer can provide a smooth and continuously expanding flow channel for the airflow, and can guide the airflow to decelerate in an orderly manner to convert dynamic pressure into static pressure, providing a high-pressure and stable airflow input for the stabilization section 23.

[0067] In some optional embodiments, the complex wind environment simulation test device further includes a damping section 6, and the air outlets of all the sub-wind tunnels 2 are connected to the damping section 6.

[0068] In this embodiment of the application, by setting the damping section 6, the instantaneous pressure fluctuations of the air outlet of the sub-wind tunnel 2 can be absorbed, so that the airflow from all the sub-wind tunnels 2 is in a dynamic equilibrium state, ensuring the pressure stability after the airflow of the sub-wind tunnels 2 merges.

[0069] In some alternative embodiments, a counterweight plate 3 is mounted on the bracket 1.

[0070] In this embodiment, the counterweight plate 3 can increase the overall stability of the device and reduce the shaking generated during the operation of the device.

[0071] In some optional embodiments, casters 5 may also be configured on the bracket 1 to facilitate the overall transportation of the device. An adjustable support 4 is also connected to the bracket 1. The adjustable support 4 may be connected to the bracket 1 by means of, for example, a threaded connection. By rotating the adjustable support 4, the adjustable support 4 can be made to serve as a load-bearing component of the device. At this time, the casters 5 leave the support platform, and the device as a whole will have better stability.

[0072] To verify the effectiveness of the above embodiments, the inventors conducted the following experiments:

[0073] I. Verification of Flow Field Characteristics in Sub-Wind Tunnel

[0074] The sub-wind tunnels are constructed of thin plates and are independent of each other. The roughness of the inner wall of each sub-wind tunnel does not exceed Ra3.2. Axial flow fan mounting brackets are installed at the front of each independent sub-wind tunnel. The fans are independent structures for easy maintenance or replacement in case of failure. To reduce the impact of installation gaps on the wind field, steel plates are used to fill the gaps between the fans and the contraction section. The rectification effect of the fan area in a single sub-wind tunnel is simulated, and the simplified model is shown below. Figure 7 As shown. The static pressure at both the inlet and outlet of the sub-wind tunnel was set to 0 Pa, and the wind speed contour map at the z=0 section was obtained. Here, z is the directional coordinate in three-dimensional space. In actual experiments, z is interpreted as the height relative to the origin of the working coordinate system, such as... Figure 8 As shown, the results indicate that the fan in a single sub-wind tunnel can effectively accelerate the airflow to 13.0 m / s.

[0075] To verify the degree of mutual influence between the fans of the 48 sub-wind tunnels when they are running simultaneously, a system was established as follows: Figure 9 The multi-fan interference model shown has an inlet and outlet region of 1000 mm and a fan width of 76 mm. To monitor the actual flow rate during simultaneous fan operation, fan performance curves were input into the calculations for each fan. According to the simulation results, the average mass flow rate of the 48 fans is 0.16918 kg / s, the maximum mass flow rate is 0.17089 kg / s, the minimum mass flow rate is 0.16671 kg / s, and the range is 0.004185 kg / s, indicating minimal mutual interference between fan performance. Based on this model, outlet streamline simulation yields uniformly distributed fan outlet streamlines without significant mutual interference.

[0076] II. Verification of Flow Field Characteristics in the Contraction Section

[0077] The computational domain was set as follows: the inlet of the contraction section was used as the flow field inlet, with a given inlet velocity of 6 m / s. The outlet of the test section was set as a pressure outlet. The two sides and the upper and lower surfaces of the computational domain were the four walls of the sub-wind tunnel, using no-slip walls. A cross-section at 0.5 m from the outlet of the contraction section, i.e., the center of the test section, was selected to analyze the influence of three different contraction curves (Vidosinski curve, bicubic curve, and quintic curve) on the wind speed distribution of this cross-section. The wind speed contour maps of the three curves are shown below. Figure 10 , Figure 11 and Figure 12 As shown in Table 1, the wind speed distribution parameters of the test section cross-section are as follows. As can be seen from Table 1, when using the three curves, the average wind speed on the test section cross-section has an error of less than 0.0378 m / s compared with the theoretical value. However, the wind speed non-uniformity under the Vidosinski curve is smaller, reaching 0.0144, which indicates that the wind speed distribution on the test section cross-section is more uniform when the Vidosinski curve is used in the contraction section.

[0078] Table 1. Airflow velocity distribution parameters of the test section cross section

[0079]

[0080] To analyze the development characteristics of the entire sub-wind tunnel flow channel, a longitudinal section of the sub-wind tunnel was selected for comparison. The change in the flow field from the inlet of the contraction section to the outlet of the test section can be observed on the longitudinal section of the sub-wind tunnel. For example... Figure 13 , Figure 14 and Figure 15 As shown in the streamline diagrams of the longitudinal section of the wind tunnel under the three contraction curves, the streamline distribution is relatively uniform under all three contraction curves. The wind speed increases uniformly as the contraction section contracts, and the velocity along the flow direction does not change much in the test section.

[0081] like Figure 16 , Figure 17 and Figure 18 As shown in the static pressure cloud diagrams of the sub-wind tunnel longitudinal section under the three contraction curves, when all three contraction curves are used in the contraction section, the static pressure decreases uniformly as the contraction section contracts, with little change along the flow direction in the test section. When using the Vidosinski curve, although uneven static pressure distribution occurs at the inlet of the contraction section, it has a smaller impact on the overall flow field of the sub-wind tunnel. The static pressure decreases more sharply near the inlet of the contraction section and decreases more gently near the outlet. Compared with the other two contraction curves, the Vidosinski curve can achieve better airflow uniformity.

[0082] III. Verification of Overall Flow Field Characteristics

[0083] The flow field stability test focused on the technical specifications of the test apparatus, including rotational speed-wind speed calibration, dynamic pressure stability measurement, and velocity uniformity measurement, to verify the steady-state characteristics of the wind field generated by the test apparatus and the accuracy of wind speed generation. During the test, a five-hole probe was mounted on a two-degree-of-freedom side-shifting frame, with the measuring end positioned at the center of the test section. Measurements were taken starting at the maximum rotational speed of 2800 r / min, decreasing in increments of 50 r / min to 600 r / min, with each rotational speed point measured for 3 minutes. A pressure measuring tube was led out of the test section and connected to a miniature digital anemometer. The miniature digital anemometer, with a sampling frequency of 30 Hz, simultaneously collected wind speed and dynamic pressure data at the center of the test section.

[0084] like Figure 19 The rotational speed-wind speed fitting curves shown indicate that the wind speed coverage range is 3 m / s to 15 m / s, and the control system can achieve accurate wind speed prediction and adjustment. The relationship between rotational speed and wind speed is as follows:

[0085]

[0086] In the formula: y Wind speed is expressed in m / s. x This indicates the motor speed, expressed in r / min.

[0087] The dynamic pressure at the center of the test section was collected, and the dynamic pressure stability coefficient η was derived using the formula:

[0088]

[0089] In the formula: q max This indicates the maximum dynamic pressure within one minute, expressed in Pa. q min This indicates the minimum dynamic pressure within one minute, expressed in Pa.

[0090] Dynamic pressure data and stability coefficients at different wind speeds are as follows: Figure 20 As shown in Table 2, the aerodynamic load fluctuates significantly at low wind speeds due to the low fan speed; however, the dynamic pressure fluctuation is smaller at high wind speeds. This indicates that the dynamic pressure stability in the central region of the test section is good within the wind speed range of 3 m / s to 13 m / s.

[0091] Table 2. Test data on dynamic pressure stability at different wind speeds

[0092]

[0093] The velocity uniformity measurement aimed to verify whether the experimental setup met the initial technical specifications for the size of the uniform zone and the quality of the flow field. Measurements were conducted within a 0.9m × 0.7m area centered on the axis of the test section's central cross-section. An 8×6 array of 48 measurement points (129mm laterally and 140mm longitudinally) was arranged within this area. Measurements were taken point-by-point at wind speeds of 7m / s and 12m / s. During the experiment, the five-hole probe's spatial positioning within the axial normal plane was achieved through automated movement of a two-degree-of-freedom measuring frame along the Y and Z axes. The experimental results are as follows: Figure 21 , Figure 22 As shown, experimental data indicate that when the wind speed is 7 m / s, the uniform region fluctuates between 6.96 m / s and 7.67 m / s, with a fluctuation range of ±0.35 m / s; when the wind speed is 12 m / s, the uniform region fluctuates between 11.77 m / s and 12.59 m / s, with a fluctuation range of ±0.4 m / s. The wind speed cloud map shows that the wind speed distribution in the measured area is relatively uniform, with wind speed deviation within ±0.5 m / s. This result indicates that the measured uniform region size and flow field stability both meet and exceed the design expectations.

[0094] The specific embodiments described above illustrate the implementation of this application. Those skilled in the art can easily understand other advantages and effects of this application from the content disclosed in this specification. Although the description of this application is presented in conjunction with some embodiments, this does not mean that the features of this application are limited to this embodiment. On the contrary, the purpose of describing the application in conjunction with embodiments is to cover other options or modifications that may be derived based on the claims of this application. To provide a thorough understanding of this application, many specific details are included in the above description. This application may also be implemented without using these details. Furthermore, to avoid confusion or obscuring the focus of this application, some specific details will be omitted in the description. It should be noted that, unless otherwise specified, the embodiments and features in the embodiments of this application can be combined with each other.

[0095] It should be noted that in this specification, similar reference numerals and letters in the above figures indicate similar items. Therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures. In the description of this application, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the figures, and are only for the convenience of describing this application 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 on this application. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance. In the description of this application, it should be noted that unless otherwise expressly specified and limited, the terms "installed," "connected," and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal communication between two elements. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.

[0096] Obviously, those skilled in the art can make various modifications and variations to this application without departing from the spirit and scope of this application. Therefore, if such modifications and variations fall within the scope of the claims of this application and their equivalents, this application also intends to include such modifications and variations.

Claims

1. A complex wind environment simulation test device, characterized in that, Includes a support frame (1) and a wind tunnel assembly connected to the support frame (1); The wind tunnel assembly includes multiple sub-wind tunnels (2), each sub-wind tunnel (2) having an air inlet and an air outlet. All the air inlets are arranged in a spherical array, and all the air outlets are arranged in a rectangular array. The air inlets are arc-shaped flared structures, and the air outlets of all the sub-wind tunnels (2) are arranged adjacent to each other so that the structure of all the sub-wind tunnels (2) as a whole forms a contracted shape. The sub-wind tunnel (2) includes a fan section (21), a diffuser section (22), a stabilizing section (23), a contraction section (24), and a buffer section (25) connected in sequence. The buffer section (25) extends in a broken line direction and the bending angle of the buffer section (25) is 132°~176°. The inlet and outlet of the contraction section (24) are both rectangular. The profile of the contraction section (24) is defined by the Vickers curve and its four outer walls are generated by the profile.

2. The complex wind environment simulation test device according to claim 1, characterized in that, In the first array direction, adjacent air inlets have a gap of 2±0.25mm; in the second array direction, adjacent air inlets have a gap of 40±1.5mm.

3. The complex wind environment simulation test device according to claim 2, characterized in that, In the second array direction, the number of sub-wind tunnels (2) is not less than 6, and the included angle between the centers of the first and last sub-wind tunnels (2) is not less than 36°.

4. The complex wind environment simulation test device according to claim 2, characterized in that, In the first array direction, the number of sub-wind tunnels (2) is not less than 8.

5. The complex wind environment simulation test device according to claim 1, characterized in that, The diffuser section (22) is configured as a square-to-circular reducing pipe.

6. The complex wind environment simulation test device according to claim 1, characterized in that, It also includes a damping section (6), and the air outlets of all the sub-wind tunnels (2) are connected to the damping section (6).

7. The complex wind environment simulation test device according to claim 1, characterized in that, A counterweight plate (3) is installed on the bracket (1).

Images