A hypersonic dynamic flow test simulation device

Abstract

This invention provides a hypersonic dynamic incoming flow test simulation device, comprising a flat plate, a jet cavity located on one side of the plate, a throttling cavity connected at one end to the inlet of the jet cavity, a rectifying section connected to the other end of the throttling cavity, and a gas delivery pipe connected to the other end of the rectifying section; the flat plate has several jet holes, and the jet cavity is connected to the jet holes; a throttling block is provided in the throttling cavity, and the throttling block is connected to a driver, which can drive the throttling block to rotate. The rotating throttling block in the simulation device of this invention provides continuously varying jet intensity, thereby affecting the intensity of the separated shock wave and the reattached shock wave, thus obtaining a hypersonic incoming flow with dynamically changing parameters after the test device. This provides a practical and feasible test scheme for conducting hypersonic dynamic incoming flow wind tunnel tests and for in-depth research into the influence mechanism of dynamic changes in incoming flow parameters on hypersonic inlets.

Description

Technical Field

[0001] This invention relates to the field of hypersonic wind tunnel testing, and more specifically to a hypersonic dynamic incoming flow test simulation device. Background Technology

[0002] Hypersonic inlets are a crucial component of scramjet engines, playing a vital role in the safe and stable operation of aircraft. During flight, due to complex wind environments, aircraft frequently encounter various atmospheric disturbances, such as gusts, wind shear, and eddies. When hypersonic vehicles fly at altitudes exceeding 20 kilometers, the primary atmospheric disturbance is wind shear, i.e., changes in wind direction and speed in the horizontal or vertical directions. This causes temporary changes in the aircraft's flight attitude, thereby altering the internal flow characteristics of the hypersonic inlet.

[0003] To address the dynamic incoming flow conditions encountered by aircraft during high-altitude flight, several simulation methods exist in wind tunnel testing. For example, Chinese invention patent CN 116337396 A discloses "An Active Simulation Wind Tunnel Test Method for High-Altitude Atmospheric Turbulence," which generates turbulent flow by adding a turbulence device in front of the test section. The turbulence device in this method is a swinging plate located in the mainstream area, which is only suitable for simulating dynamic incoming flow in low-speed wind tunnels. Its use in hypersonic wind tunnels would have a significant impact on the downstream test section and is not suitable for simulating dynamic incoming flow in hypersonic wind tunnels.

[0004] Therefore, it is necessary to design a dynamic incoming flow simulation device specifically for hypersonic wind tunnel testing, so as to explore in depth the influence mechanism of dynamic changes in incoming flow parameters on hypersonic air intakes and provide important experimental conditions for the development of hypersonic vehicles. Summary of the Invention

[0005] Purpose of the invention: The purpose of this invention is to provide a hypersonic dynamic incoming flow test simulation device with controllable change of jet parameters.

[0006] Technical solution: A hypersonic dynamic inflow test simulation device includes a flat plate, a jet cavity located on one side of the flat plate, a throttling cavity connected to the end of the jet cavity away from the flat plate, a rectifier section connected to the other end of the throttling cavity, and a gas delivery pipe connected to the other end of the rectifier section; the flat plate has a plurality of jet holes, and the jet cavity is connected to the jet holes; a throttling block is provided in the throttling cavity, and the throttling block is connected to a driver. When the driver drives the throttling block to rotate, the flow area of ​​the throttling cavity changes.

[0007] Specifically, the plate is equipped with a static pressure probe and a total pressure probe.

[0008] Specifically, the rectifier section is connected to the gas transmission pipe via a flange.

[0009] Specifically, the gas supply pipe is connected to the atmosphere and is equipped with a ball valve and a quick valve in sequence along the gas intake direction.

[0010] Preferably, the driver is a speed reducer motor.

[0011] Preferably, the jet hole is a circular hole, and the axis of the jet hole is perpendicular to the plane of the plate.

[0012] Preferably, the throttling block is an elliptical cylinder, and the major axis of the ellipse in the cross-section of the throttling block is the same as the width of the cross-section of the throttling cavity.

[0013] Preferably, the total flow area of ​​the jet orifice is between the minimum and maximum flow area of ​​the throttling cavity.

[0014] Specifically, the total pressure probe is connected to a drive motor, and when the drive motor is started, it causes the total pressure probe to move up and down relative to the flat plate surface.

[0015] Beneficial effects: Compared with the prior art, the significant effect of this invention is that, based on the existing wind tunnel test equipment, by adding a jet device in front of the test section, a hypersonic dynamic incoming flow that meets the test requirements can be effectively simulated in the test section. Under this premise, no additional flow interference will be generated downstream of the wind tunnel, and the test data fits the simulation data well. At the same time, the rotating throttling block provides a continuously changing jet intensity, which in turn affects the intensity of the separated shock wave and the reattached shock wave. Thus, a hypersonic incoming flow with dynamically changing parameters is obtained after the test equipment. This provides a practical and feasible test scheme for carrying out wind tunnel tests of hypersonic dynamic incoming flow and for in-depth research on the influence mechanism of dynamic changes in incoming flow parameters on hypersonic inlets. Attached Figure Description

[0016] Figure 1 This is a cross-sectional view of the hypersonic dynamic incoming flow test simulation device of Embodiment 1 of the present invention.

[0017] Figure 2 This is a three-dimensional sectional view of the hypersonic dynamic incoming flow test simulation device of Embodiment 1 of the present invention.

[0018] Figure 3 This is a schematic diagram showing the changes of motor synchronization signal, jet cavity pressure and boundary layer Mach number over time during the test of the hypersonic dynamic incoming flow simulation device in Embodiment 1 of the present invention. Detailed Implementation

[0019] The present invention will be further explained below with reference to the accompanying drawings and specific embodiments.

[0020] Example 1

[0021] Please see Figure 1 and Figure 2As shown, this embodiment provides a hypersonic dynamic incoming flow test simulation device, including a plate 1, a jet cavity 2 located on the lower side of the plate 1, a throttling cavity 3 connected to the inlet of the jet cavity 2 at one end, a rectifier section 4 connected to the throttling cavity 3 and the other end of the throttling cavity 3, a gas supply pipe 5 connected to the other end of the rectifier section 4 through a flange 9, and a throttling block 6 disposed in the throttling cavity 3; a row of circular jet holes 11 are opened on the plate 1, and the jet holes 11 connect the upper side of the plate 1 and the jet cavity 2; the throttling block 6 is connected to a reducer motor 61; a static pressure probe 7 and a total pressure probe 8 are also provided on one side of the plate 1, and the lower end of the total pressure probe 8 is connected to a drive motor 81; a ball valve 51 and a quick valve 52 are sequentially provided along the gas supply direction of the gas supply pipe 5.

[0022] In this embodiment, the throttling block 6 is an elliptical cylinder, and the throttling cavity 3 is a cuboid. The major axis of the ellipse of the cross-section of the throttling block 6 is equal to the width of the cross-section of the throttling cavity 3, and the height of the cylinder of the throttling block 6 is equal to the length of the cross-section of the throttling cavity 3. When the throttling block 6 is in a horizontal position, that is, when the major axis of the cross-section of the throttling block 6 is horizontal, the throttling cavity 3 is completely blocked, and the flow area of ​​the throttling cavity 3 is the smallest, which is 0. When the throttling block 6 is in a vertical position, that is, when the minor axis of the cross-section of the throttling block 6 is horizontal, the flow area of ​​the throttling cavity 3 is the largest. Different flow areas of the throttling cavity 3 bring different flow losses, thereby dynamically and continuously changing the airflow pressure in the jet cavity 2.

[0023] In this embodiment, the axis of the jet orifice 11 is perpendicular to the plane of the plate 1 to enhance the jet disturbance intensity; the distance between the jet orifice 11 and the front end of the plate 1 is greater than or equal to 70mm to avoid the jet separating at the front end of the plate 1 and affecting the main flow area; the total flow area of ​​the jet orifice 11 is less than or equal to the maximum flow area of ​​the throttling cavity 3 and greater than the minimum flow area of ​​the throttling cavity 3, so that the jet volume is equivalent to the intake volume, and the jet cavity 2 will not be filled or de-filled too quickly. In this embodiment, the total flow area of ​​the jet orifice 11 is equal to the maximum flow area of ​​the throttling cavity 3.

[0024] In this embodiment, the gas supply pipe 5 is connected to the atmosphere to provide airflow for the hypersonic dynamic incoming flow test simulation device, the ball valve 51 is used to adjust the total pressure of the input airflow, and the quick valve 52 is used to connect / cut off the gas source.

[0025] In this embodiment, after the drive motor 81 starts, it drives the total pressure probe 8 to move up or down.

[0026] In this embodiment, an elliptical cylindrical throttling block 6 is set in the throttling cavity 3, and the throttling block 6 is driven to rotate by the reducer motor 61, thereby controlling the flow area of ​​the throttling cavity 3 and indirectly controlling the jet intensity of the jet orifice 11, so as to realize the generation of a continuously changing jet perpendicular to the dynamic incoming flow above the plate 1, thereby simulating a hypersonic dynamic incoming flow with controllable parameters that conforms to the actual situation.

[0027] Example 2

[0028] This embodiment utilizes the hypersonic dynamic incoming flow simulation device described in Embodiment 1 to conduct a hypersonic dynamic incoming flow simulation experiment. The simulation device is set in the uniform dynamic incoming flow zone of the hypersonic wind tunnel, which is located behind the reattached shock wave. The position of the reattached shock wave is determined by the schlieren method. At this time, the plate 1 is parallel to the dynamic incoming flow, and the outlet direction of the jet orifice 11 is perpendicular to the direction of the dynamic incoming flow. When the hypersonic wind tunnel is started, the pressure in the jet cavity 2 is greater than the pressure above the plate 1. The high-pressure jet is ejected through the jet orifice 11, which has a separation effect on the mainstream above the plate 1, thereby generating a separation shock wave and a reattached shock wave. The rotation of the throttling block 6 changes the intensity of the high-pressure jet, thereby changing the intensity of the separation shock wave and the reattached shock wave. The total pressure probe 8 moves up and down to measure the total pressure in the boundary layer of the wind tunnel. Then, based on the local static pressure measured by the static pressure probe 7, the change in Mach number in the boundary layer is obtained, thereby determining the characteristics of the disturbance generation.

[0029] Please see Figure 3 As shown, tests were conducted on the aforementioned simulation device to obtain the time-varying relationships of the synchronization signal of the reducer motor 61, the pressure value of the jet cavity 2, and the boundary layer Mach number over multiple cycles. Further analysis of the test data yielded Table 1 below.

[0030] Table 1

[0031] 0 2000 5.638 0.597 45 2000 5.638 0.597 67.5 2000 5.634 0.644 90 2000 5.632 0.683

[0032] In this embodiment, the initial state of the throttling block 6 is set to a horizontal position, that is, the throttling cavity 3 is completely blocked. As can be seen from the data in Table 1, when the total input pressure set by the ball valve 51 is constant, as the deflection angle of the throttling block 6 increases, the mainstream Mach number at the outlet of the jet orifice 11 decreases and the mainstream deflection angle increases. (The mainstream Mach number when the block deflects at 45° and the mainstream deflection angle relative to the block deflection at 0° are only four decimal places apart, the change is extremely small, and three decimal places are retained in Table 1 for explanation.) This is because the pressure inside the jet cavity 2 increases, the jet becomes stronger, and the shock wave angle generated at the jet becomes larger, causing the mainstream velocity to decrease and the direction to deflect when passing through the shock wave. This embodiment uses the simulation device described in Embodiment 1 to obtain a hypersonic airflow with incoming flow parameter changes that are consistent with the design concept, effectively simulating the dynamic incoming flow under hypersonic flight conditions in the wind tunnel.

Claims

1. A hypersonic dynamic incoming flow test simulation device, characterized in that, It includes a flat plate (1), a jet cavity (2) located on one side of the flat plate (1), a throttling cavity (3) connected to the end of the jet cavity (2) away from the flat plate (1), a rectifier section (4) connected to the other end of the throttling cavity (3), and a gas delivery pipe (5) connected to the other end of the rectifier section (4); the flat plate (1) is provided with a plurality of jet holes (11), and the jet cavity (2) is connected to the jet holes (11); the throttling cavity (3) is provided with a throttling block (6), the throttling block (6) is connected to a driver, and when the driver drives the throttling block (6) to rotate, the flow area of ​​the throttling cavity (3) changes.

2. The hypersonic dynamic incoming flow test simulation device according to claim 1, characterized in that: The plate (1) is provided with a static pressure probe (7) and a total pressure probe (8).

3. The hypersonic dynamic incoming flow test simulation device according to claim 1, characterized in that: The rectifier section (4) is connected to the gas pipeline (5) via a flange (9).

4. The hypersonic dynamic incoming flow test simulation device according to claim 1, characterized in that: The gas pipeline (5) is connected to the atmosphere, and a ball valve (51) and a quick valve (52) are arranged in sequence along the gas inlet direction of the gas pipeline (5).

5. The hypersonic dynamic incoming flow test simulation device according to claim 1, characterized in that: The driver is a reducer motor (61).

6. The hypersonic dynamic incoming flow test simulation device according to claim 1, characterized in that: The jet hole (11) is a circular hole.

7. The hypersonic dynamic incoming flow test simulation device according to claim 1, characterized in that: The axis of the jet hole (11) is perpendicular to the plane of the plate (1).

8. The hypersonic dynamic incoming flow test simulation device according to claim 1, characterized in that: The throttling block (6) is an elliptical cylinder, and the major axis of the ellipse of the cross-section of the throttling block (6) is the same as the width of the cross-section of the throttling cavity (3).

9. The hypersonic dynamic incoming flow test simulation device according to claim 1, characterized in that: The total flow area of ​​the jet orifice (11) is between the minimum and maximum values ​​of the flow area of ​​the throttling cavity (3).

10. The hypersonic dynamic incoming flow test simulation device according to claim 2, characterized in that: The total pressure probe (8) is connected to the drive motor (81). When the drive motor (81) is started, it causes the total pressure probe (8) to move up and down relative to the surface of the plate (1).

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