A hypersonic inlet / isolator forced oscillation generation device and a design method thereof

Abstract

The present application belongs to the field of direct connection hypersonic inlet / isolator ground wind tunnel experiment, and particularly relates to a forced oscillation generating device for hypersonic inlet / isolator and a design method thereof. Step 1: determining the static pressure and Mach number of the incoming flow gas; Step 2: based on the static pressure and Mach number of the incoming flow gas in step 1, determining the material adopted by the shell of the oscillation generating device and the oscillation back pressure generating mechanism; Step 3: based on the material selected in step 2, determining the type of the driving device in the oscillation back pressure generating mechanism; Step 4: based on the type of the driving device in step 3, determining the transmission ratio of the gear and the throttling ratio range of the rotating blade in the oscillation back pressure generating mechanism; Step 5: based on the transmission ratio and the throttling ratio in step 4, processing the forced oscillation device experimental piece and installing it on the ground wind tunnel experiment table, selecting the throttling ratio and the oscillation frequency and conducting the experiment, and the forced oscillation device will generate the expected oscillation back pressure at the outlet of the isolator. To solve the problem of flow separation in the inlet in the prior art, and further affect the power and control performance of the aircraft.

Description

Technical Field

[0001] This invention belongs to the field of ground wind tunnel experimental technology for direct-connection hypersonic inlet / isolation section, specifically relating to a forced oscillation generator for a hypersonic inlet / isolation section and its design method. Background Technology

[0002] In the field of hypersonic flight, the study of forced oscillations downstream of the inlet / isolation section is of great significance, especially when facing changes in back pressure. The oscillation characteristics of the shock train inside the inlet / isolation section directly affect the inlet's start-up and performance stability. This forced oscillation phenomenon is usually related to the dynamic pressure changes caused by organized combustion in the combustion chamber, which may lead to flow separation within the inlet, thereby affecting the vehicle's power and handling performance. Therefore, in-depth research on the forced oscillation characteristics of hypersonic inlets / isolation sections under different back pressure conditions is crucial for designing more efficient and stable inlet systems and improving the overall performance and reliability of hypersonic vehicles. Summary of the Invention

[0003] This invention provides a forced oscillation generator for hypersonic inlet / isolation section and its design method, which solves the problem of flow separation inside the inlet in the prior art, which affects the power and handling performance of the aircraft.

[0004] This invention is achieved through the following technical solution:

[0005] A design method for a forced oscillation generator for a hypersonic inlet / isolation section, the method comprising the following steps:

[0006] Step 1: Determine the static pressure and Mach number of the incoming gas;

[0007] Step 2: Based on the static pressure and Mach number of the incoming gas in Step 1, determine the materials to be used for the housing of the oscillation generator and the oscillation back pressure generating mechanism;

[0008] Step 3: Based on the material selected in Step 2, determine the model of the drive device in the oscillation back pressure generating mechanism;

[0009] Step 4: Based on the model of the drive device in Step 3, determine the transmission ratio of the gears and the throttling ratio range of the rotating blades in the oscillation back pressure generating mechanism;

[0010] Step 5: Based on the transmission ratio and throttling ratio in Step 4, process the forced oscillation device test piece and install it on the ground wind tunnel test bench. Select the throttling ratio and oscillation frequency and conduct the experiment. The forced oscillation device will generate the expected oscillation back pressure at the outlet of the isolation section.

[0011] Furthermore, step 1 specifically involves setting the incoming Mach number according to the specific experimental conditions, and given the total outflow pressure, the static pressure is:

[0012]

[0013] Where p0 is the static pressure of the incoming gas, p * Let Ma be the total pressure of the incoming gas, Ma be the Mach number of the incoming gas, and k be the gas constant.

[0014] Furthermore, step 2 specifically involves the oscillation generating device comprising a housing and an oscillation back pressure generating mechanism. The housing is used for load bearing and sealing, while the oscillation back pressure generating mechanism is used for generating oscillation back pressure.

[0015] Furthermore, step 3 specifically involves ensuring that the rated torque of the drive device is at least 10 N·m and the power is above 1 kW.

[0016] Furthermore, step 4 specifically involves setting the gear transmission ratio to 1 by default unless otherwise specified; the throttling ratio is determined based on the specific experimental conditions, and its definition is as follows:

[0017]

[0018] Where t is the throttling ratio, s1 is the area of ​​the throttling rotating blade extending into the flow channel, and s2 is the spanwise cross-sectional area of ​​the flow channel.

[0019] Furthermore, step 5 specifically involves ensuring that during the processing of the experimental piece, the surface roughness of all parts is 0.63 on the outer surface and 0.32 on the internal flow channels and sealing contact surfaces.

[0020] Furthermore, the throttling ratio is changed by moving the throttling vane up and down in the flow channel and observing the scale to determine whether the changed throttling ratio meets expectations.

[0021] Furthermore, the oscillation frequency is changed by programming and controlling the drive device in the drive mechanism, setting pulse signals of different frequencies to be fed back to the drive device, the drive device drives the gear set keyed to its shaft, and finally drives the throttling vane to generate oscillating back pressure of different frequencies.

[0022] A hypersonic inlet / isolation section forced oscillation generator, designed according to the above-mentioned design method for a hypersonic inlet / isolation section forced oscillation generator, the device includes an experimental platform 1, an oscillation generator 2, and a wind tunnel experimental platform flow channel 3.

[0023] The oscillation generating device includes a housing 21 and an oscillation back pressure generating mechanism 22. The housing 21 includes a gear sealing box 211, a rear cover 212, a front cover 213, a rear cover flow channel inlet 214, and a front cover flow channel inlet 215. The gear sealing box 211 is disposed between the rear cover 212 and the front cover 213. The rear cover flow channel inlet 214 and the front cover flow channel inlet 215 are connected to the downstream section of the wind tunnel test bench flow channel 3.

[0024] The rear cover 212 has a rear cover slide rail 2121;

[0025] The front cover 213 has a front cover slide rail 2131;

[0026] The oscillation back pressure generating mechanism 22 includes a bearing 221, gear I 222, gear II 224 and throttling rotating blade 223. The center of the throttling rotating blade 223 passes through the throttling rotating shaft 2231. One side of the throttling rotating shaft 2231 passes through the front cover slide rail 2131, and the other side of the throttling rotating shaft 2231 passes through the shaft core of gear II 224 and is fixed on the rear cover 212.

[0027] The gear II 224 meshes with the gear I 222. The center of the gear I 222 passes through the output shaft of the motor 225, and the output shaft of the motor 225 also passes through the rear cover slide rail 2121.

[0028] The bearing 221, gear I 222, gear II 224 and throttling rotating blade 223 are all installed in the gear sealing box 211.

[0029] Furthermore, the experimental platform 1 includes a gas storage tank 11, a pressure reducing valve 12, a static pressure sensor 13, a total pressure sensor 14, a servo electric cylinder 15, an optical window 16, a hypersonic air intake 17, and an isolation section 18 for the hypersonic air intake.

[0030] The gas storage tank 11 is connected to the hypersonic inlet duct 17 via an inlet pipe. A pressure reducing valve 12 is installed on the inlet pipe. A total pressure sensor 14, a servo electric cylinder 15, and a static pressure sensor 13 are sequentially installed on the hypersonic inlet duct 17. An optical window 16 is installed on the isolation section 18 of the hypersonic inlet duct 17. One end of the isolation section 18 of the hypersonic inlet duct is connected to the hypersonic inlet duct 17, and the other end of the isolation section 18 of the hypersonic inlet duct is connected to the oscillation generator. The isolation section 18 of the hypersonic inlet duct is connected to the wind tunnel test bench via the wind tunnel test bench flow channel 3.

[0031] The beneficial effects of this invention are:

[0032] This invention enables high-precision real-time online adjustment of the oscillation back pressure frequency over an extremely wide range (0-250Hz) through programming;

[0033] This invention enables adjustment of the throttling ratio over an extremely wide range (0-85%);

[0034] This invention can adapt to a wide range of incoming gas static pressures (0-10 MPa) and Mach numbers (0-3). Attached Figure Description

[0035] Figure 1 This is a schematic diagram illustrating the throttling ratio definition of the oscillation back pressure generating device of the present invention.

[0036] Figure 2 This is the housing part of the present invention.

[0037] Figure 3 This is the driving mechanism part of the present invention.

[0038] Figure 4 This is the overall installation effect of the oscillation back pressure generating device (within the red box) and the experimental platform of the present invention.

[0039] Figure 5 This invention presents partial experimental data and fast Fourier transform analysis results of a pressure measuring point TC2 downstream of the intake / isolation section when the drive device frequency is set to 100Hz.

[0040] Figure 6 This is a flowchart of the method of the present invention. Detailed Implementation

[0041] In the following description, specific details such as particular system architectures and techniques are set forth for illustrative purposes and not for limitation, in order to provide a thorough understanding of the embodiments of this application. However, those skilled in the art will understand that this application may also be implemented in other embodiments without these specific details. In other instances, detailed descriptions of well-known systems, apparatuses, circuits, and methods are omitted so as not to obscure the description of this application with unnecessary detail.

[0042] It should be understood that, when used in this specification and the appended claims, the term "comprising" indicates the presence of the described features, integrals, steps, operations, elements and / or components, but does not exclude the presence or addition of one or more other features, integrals, steps, operations, elements, components and / or collections thereof.

[0043] It should also be understood that the terminology used in this application specification is for the purpose of describing particular embodiments only and is not intended to limit the application. As used in this application specification and the appended claims, the singular forms “a,” “an,” and “the” are intended to include the plural forms unless the context clearly indicates otherwise.

[0044] The following is in conjunction with the appendix to this application specification. Figure 1-6 The technical solutions in the embodiments of this application are clearly and completely described. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of the embodiments. Based on the embodiments in this application, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of this application.

[0045] Many specific details are set forth in the following description in order to provide a full understanding of this application. However, this application may also be implemented in other ways different from those described herein. Those skilled in the art can make similar extensions without departing from the spirit of this application. Therefore, this application is not limited to the specific embodiments disclosed below.

[0046] Implementation Method 1

[0047] This embodiment provides a design method for a hypersonic inlet / isolation section forced oscillation generator, the method comprising the following steps:

[0048] Step 1: Determine the static pressure and Mach number of the incoming gas;

[0049] Step 2: Based on the static pressure and Mach number of the incoming gas in Step 1, determine the materials to be used for the housing of the oscillation generator and the oscillation back pressure generating mechanism;

[0050] Step 3: Based on the material selected in Step 2, determine the model of the drive device in the oscillation back pressure generating mechanism;

[0051] Step 4: Based on the model of the drive device in Step 3, determine the transmission ratio of the gears and the throttling ratio range of the rotating blades in the oscillation back pressure generating mechanism;

[0052] Step 5: Based on the transmission ratio and throttling ratio in Step 4, process the forced oscillation device test piece and install it on the ground wind tunnel test bench. Select the throttling ratio and oscillation frequency and conduct the experiment. The forced oscillation device will generate the expected oscillation back pressure at the outlet of the isolation section.

[0053] Furthermore, step 1 specifically involves setting the incoming Mach number according to the specific experimental conditions, and given the total outflow pressure, the static pressure is:

[0054]

[0055] Where p0 is the static pressure of the incoming gas, p * Let Ma be the total pressure of the incoming gas, Ma be the Mach number of the incoming gas, and k be the gas constant.

[0056] Furthermore, step 2 specifically involves the oscillation generating device comprising a housing and an oscillation back pressure generating mechanism. The housing is used for load-bearing and sealing, and requires high strength, typically alloy steel. The oscillation back pressure generating mechanism is used to generate oscillation back pressure, and requires high strength and good wear resistance, typically titanium alloy.

[0057] Furthermore, step 3 specifically involves ensuring that the experiment can proceed smoothly. The rated torque of the drive device must be at least 10 N·m, the power must be above 1 kW, and the rated speed can be selected according to actual needs. Other parameters of the drive device are not required if the above conditions are met.

[0058] Furthermore, step 4 specifically involves setting the gear transmission ratio to 1 by default unless otherwise specified; the throttling ratio is determined based on the specific experimental conditions, and its definition is as follows:

[0059]

[0060] Where t is the throttling ratio, s1 is the area of ​​the throttling rotating blade extending into the flow channel, and s2 is the spanwise cross-sectional area of ​​the flow channel; in order to ensure the safety of ground wind tunnel experiments, the throttling ratio is generally lower than 85% to avoid excessive blockage of the flow channel and flow congestion.

[0061] Furthermore, step 5 specifically involves ensuring that during the processing of the experimental piece, the surface roughness of all parts is 0.63 on the outer surface and 0.32 on the internal flow channels and sealing contact surfaces.

[0062] Furthermore, the throttling ratio is changed by moving the throttling vane up and down in the flow channel and observing the scale to determine whether the changed throttling ratio meets expectations.

[0063] Furthermore, the oscillation frequency is changed by programming and controlling the drive device in the drive mechanism, setting pulse signals of different frequencies to be fed back to the drive device, the drive device drives the gear set keyed to its shaft, and finally drives the throttling vane to generate oscillating back pressure of different frequencies.

[0064] The oscillation back pressure generating mechanism (including the throttling vane) moves up and down as a whole to adjust the oscillation amplitude. However, the inside of the flow channel is completely enclosed. During the movement, it is necessary to know the distance moved to determine the throttling ratio. Therefore, a scale is installed on the housing next to the oscillation back pressure generating mechanism to determine the moving distance.

[0065] The drive device uses an electric motor as its power source.

[0066] In this embodiment, step 1 specifically involves the incoming gas being air, and the total pressure being p. *=2.2Mpa, the incoming Mach number is 2.70, the incoming total temperature is 287.15K, k is 1.4, and according to formula (1), the static pressure p0 = 0.094Mpa can be obtained.

[0067] Step 2 of this embodiment specifically involves the following: the incoming gas exerts a strong impact on the rotating blades, placing certain requirements on the blade material. In this example, titanium alloy is selected as the blade material. Each blade has a semi-circular top and a rectangular bottom, with a total of 6 sets of blades. The centers of the semi-circular tops of each blade are connected sequentially to form a regular hexagon. This is to ensure that the throttling time accounts for 1 / 3 to 2 / 3 of the entire time cycle as much as possible. The blade thickness is 5mm. The total pressure and Mach number of the incoming gas are relatively high. To ensure the safety and accuracy of the experiment, the strength and sealing requirements of the oscillation back pressure generating device are high. In this example, the materials used for the device housing and drive mechanism, except for the servo motor, are all Q460 steel.

[0068] Step 3 of this embodiment specifically involves selecting a WEIDE-130ST-M15025 drive device in the drive mechanism. This device has a rated power of 3.8kW, a rated speed of 2500rpm, a rated torque of 15N·m, and a 2500-line magnetic encoder. A corresponding driver is used, which utilizes high-precision feedback control combined with a high-speed digital signal processor (DSP) to control the IGBT to generate precise current output, achieving accurate positioning and excellent servo performance. The PLC uses an EX16X16Y-MT controller to output pulse signals. Its drive device control interface supports a frequency range of 100Hz-50000Hz, and the control method is position control. A 3P data cable is used to connect to the PC port via an RS485-to-USB converter. Commands are sent to the PLC controller on the PC to control the movement of the drive device.

[0069] Step 4 of this embodiment specifically involves selecting a gear ratio of 1:1 because the rated power and rated torque of the servo motor already meet the experimental requirements. To ensure experimental safety and cover as many experimental conditions as possible, the throttling ratio in this example ranges from a minimum of 0% to a maximum of 81.19%, meaning the blade tip is exactly aligned with the bottom of the device's flow channel. Figure 1 Tangent to the blue outline.

[0070] Step 5 of this embodiment specifically involves setting the surface roughness of all parts to 0.63 on the outer surface and 0.32 on the internal flow channels and sealing contact surfaces. For example... Figure 4As shown, the throttling ratio changes by moving the throttling vane up and down within the flow channel, generating oscillating back pressures of different amplitudes. A scale is located on the front cover of the device housing, allowing observation of the distance the vane moves during this process. The oscillation frequency changes by programming and controlling the drive mechanism, setting pulse signals of different frequencies to be fed back to the drive device. The drive device drives a gear set keyed to its shaft, ultimately driving the rotating throttling vane to generate oscillating back pressures of different frequencies. Figure 5 Experimental data and Fast Fourier Transform (FFT) analysis results for a pressure measuring point TC2 downstream of the intake / isolation section are presented when the frequency of the drive device is adjusted to 100Hz. The results show that when the drive device frequency is 100Hz, periodically oscillating pressure is generated within the isolation section. After performing a FFT on the pressure, the dominant frequency of the pressure oscillation is 100Hz, exactly the same as the drive device frequency, indicating that the device of this invention can generate high-precision frequency oscillating back pressure.

[0071] Implementation Method 2

[0072] This embodiment provides a hypersonic inlet / isolation section forced oscillation generator, which is designed according to the design method of a hypersonic inlet / isolation section forced oscillation generator described in Embodiment 1. The device includes an experimental platform 1, an oscillation generator 2, and a wind tunnel experimental platform flow channel 3.

[0073] The oscillation generating device includes a housing 21 and an oscillation back pressure generating mechanism 22. The housing 21 includes a gear sealing box 211, a rear cover 212, a front cover 213, a rear cover flow channel inlet 214, and a front cover flow channel inlet 215. The gear sealing box 211 is disposed between the rear cover 212 and the front cover 213. The rear cover flow channel inlet 214 and the front cover flow channel inlet 215 are connected to the downstream section of the wind tunnel test bench flow channel 3.

[0074] The rear cover 212 has a rear cover slide rail 2121;

[0075] The front cover 213 has a front cover slide rail 2131;

[0076] The oscillation back pressure generating mechanism 22 includes a bearing 221, gear I 222, gear II 224 and throttling rotating blade 223. The center of the throttling rotating blade 223 passes through the throttling rotating shaft 2231. One side of the throttling rotating shaft 2231 passes through the front cover slide rail 2131, and the other side of the throttling rotating shaft 2231 passes through the shaft core of gear II 224 and is fixed on the rear cover 212.

[0077] The gear II 224 meshes with the gear I 222. The center of the gear I 222 passes through the output shaft of the motor 225, and the output shaft of the motor 225 also passes through the rear cover slide rail 2121.

[0078] The bearing 221, gear I 222, gear II 224 and throttling rotating blade 223 are all installed in the gear sealing box 211.

[0079] Implementation Method 3

[0080] This embodiment incorporates the forced oscillation generator from Embodiment 2 into an existing experimental setup to create a new, highly precise, real-time online adjustment of the oscillation back pressure frequency over an extremely wide range (0-250Hz) through programming; an extremely wide range (0-85%) of throttling ratio adjustment; and a novel hypersonic inlet / isolation section experimental setup capable of adapting to a wide range of incoming gas static pressure (0-10MPa) and Mach number (0-3).

[0081] The experimental platform 1 includes a gas storage tank 11, a pressure reducing valve 12, a static pressure sensor 13, a total pressure sensor 14, a servo electric cylinder 15, an optical window 16, a hypersonic air intake 17, and an isolation section 18 for the hypersonic air intake.

[0082] The gas storage tank 11 is connected to the hypersonic inlet duct 17 via an inlet pipe. A pressure reducing valve 12 is installed on the inlet pipe. A total pressure sensor 14, a servo electric cylinder 15, and a static pressure sensor 13 are sequentially installed on the hypersonic inlet duct 17. An optical window 16 is installed on the isolation section 18 of the hypersonic inlet duct 17. One end of the isolation section 18 of the hypersonic inlet duct is connected to the hypersonic inlet duct 17, and the other end of the isolation section 18 of the hypersonic inlet duct is connected to the oscillation generator. The isolation section 18 of the hypersonic inlet duct is connected to the wind tunnel test bench via the wind tunnel test bench flow channel 3.

[0083] like Figure 4 As shown, the throttling ratio changes by moving the throttling vane up and down within the flow channel, generating oscillating back pressures of different amplitudes. A scale is located on the front cover of the device housing, allowing observation of the distance the vane moves during this process. The oscillation frequency changes by programming and controlling the drive mechanism, setting pulse signals of different frequencies to be fed back to the drive device. The drive device drives a gear set keyed to its shaft, ultimately driving the rotating throttling vane to generate oscillating back pressures of different frequencies. Figure 5Experimental data and Fast Fourier Transform (FFT) analysis results for a pressure measuring point TC2 downstream of the intake / isolation section are presented when the frequency of the drive device is adjusted to 100Hz. The results show that when the drive device frequency is 100Hz, periodically oscillating pressure is generated within the isolation section. After performing a FFT on the pressure, the dominant frequency of the pressure oscillation is 100Hz, exactly the same as the drive device frequency, indicating that the device of this invention can generate high-precision frequency oscillating back pressure.

Claims

1. A design method for a forced oscillation generator for a hypersonic inlet / isolation section, characterized in that, The method includes the following steps: Step 1: Determine the static pressure and Mach number of the incoming gas; Step 2: Based on the static pressure and Mach number of the incoming gas in Step 1, determine the materials to be used for the housing of the oscillation generator and the oscillation back pressure generating mechanism; Step 3: Based on the material selected in Step 2, determine the model of the drive device in the oscillation back pressure generating mechanism; Step 4: Based on the model of the drive device in Step 3, determine the transmission ratio of the gears and the throttling ratio range of the rotating blades in the oscillation back pressure generating mechanism; Step 5: Based on the transmission ratio and throttling ratio in Step 4, process the forced oscillation device test piece and install it on the ground wind tunnel test bench. Select the throttling ratio and oscillation frequency and conduct the experiment. The forced oscillation device will generate the expected oscillation back pressure at the outlet of the isolation section.

2. The design method of a forced oscillation generator for a hypersonic inlet / isolation section according to claim 1, characterized in that, Step 1 specifically involves setting the incoming Mach number based on the specific experimental conditions, and given the total outflow pressure, the static pressure is: Where p0 is the static pressure of the incoming gas, p * Let Ma be the total pressure of the incoming gas, Ma be the Mach number of the incoming gas, and k be the gas constant.

3. The design method of a forced oscillation generator for a hypersonic inlet / isolation section according to claim 1, characterized in that, Step 2 specifically involves the oscillation generating device comprising a housing and an oscillation back pressure generating mechanism. The housing is used for load bearing and sealing, while the oscillation back pressure generating mechanism is used for generating oscillation back pressure.

4. The design method of a forced oscillation generator for a hypersonic inlet / isolation section according to claim 1, characterized in that, Specifically, step 3 involves ensuring that the rated torque of the drive device is at least 10 N·m and the power is above 1 kW.

5. The design method of a forced oscillation generator for a hypersonic inlet / isolation section according to claim 1, characterized in that, Step 4 specifically involves selecting a gear transmission ratio of 1 by default unless otherwise specified; the throttling ratio is determined based on the specific experimental conditions and is defined as follows: Where t is the throttling ratio, s1 is the area of ​​the throttling rotating blade extending into the flow channel, and s2 is the spanwise cross-sectional area of ​​the flow channel.

6. The design method of a forced oscillation generator for a hypersonic inlet / isolation section according to claim 5, characterized in that, Specifically, step 5 involves ensuring that the surface roughness of all parts is 0.63 during the processing of the experimental piece, and that the surface roughness of the internal flow channels and sealing contact surfaces is 0.

32.

7. The design method of a forced oscillation generator for a hypersonic inlet / isolation section according to claim 6, characterized in that, The throttling ratio is changed by moving the throttling vane up and down in the flow channel and observing the scale to determine whether the changed throttling ratio meets expectations.

8. The design method of a forced oscillation generator for a hypersonic inlet / isolation section according to claim 7, characterized in that, The oscillation frequency is changed by programming and controlling the drive device in the drive mechanism, setting pulse signals of different frequencies to be fed back to the drive device, the drive device drives the gear set keyed to its shaft, and finally drives the throttling vane to generate oscillation back pressure of different frequencies.

9. A forced oscillation generator for a hypersonic inlet / isolation section, characterized in that, The hypersonic inlet / isolation section forced oscillation generator designed according to any one of claims 1-8 includes an experimental platform (1), an oscillation generator (2), and a wind tunnel experimental platform flow channel (3). The oscillation generating device includes a housing (21) and an oscillation back pressure generating mechanism (22). The housing (21) includes a gear sealing box (211), a rear cover (212), a front cover (213), a rear cover flow channel inlet (214), and a front cover flow channel inlet (215). The gear sealing box (211) is provided between the rear cover (212) and the front cover (213). The rear cover flow channel inlet (214) and the front cover flow channel inlet (215) are connected to the downstream section of the wind tunnel test bench flow channel (3). The rear cover (212) is provided with a rear cover slide rail (2121); The front cover (213) has a front cover slide rail (2131); The oscillation back pressure generating mechanism (22) includes a bearing (221), gear I (222), gear II (224) and a throttling rotating blade (223). The center of the throttling rotating blade (223) passes through the throttling rotating shaft (2231). One side of the throttling rotating shaft (2231) passes through the front cover slide rail (2131), and the other side of the throttling rotating shaft (2231) passes through the shaft core of gear II (224) and is fixed on the rear cover (212). The gear II (224) meshes with the gear I (222), the center of which passes through the output shaft of the motor (225), and the output shaft of the motor (225) also passes through the rear cover slide rail (2121). The bearing (221), gear I (222), gear II (224) and throttling rotating blade (223) are all installed in the gear sealing box (211).

10. The hypersonic inlet / isolation section forced oscillation generator according to claim 9, characterized in that, The experimental platform (1) includes a gas storage tank (11), a pressure reducing valve (12), a static pressure sensor (13), a total pressure sensor (14), a servo electric cylinder (15), an optical window (16), a hypersonic air intake (17), and an isolation section (18) for the hypersonic air intake. The gas storage tank (11) is connected to the hypersonic intake duct (17) through the intake pipe. A pressure reducing valve (12) is installed on the intake pipe. A total pressure sensor (14), a servo electric cylinder (15) and a static pressure sensor (13) are installed sequentially on the hypersonic intake duct (17). An optical window (16) is installed on the isolation section (18) of the hypersonic intake duct (17). One end of the isolation section (18) of the hypersonic intake duct is connected to the hypersonic intake duct (17), and the other end of the isolation section (18) of the hypersonic intake duct is connected to the oscillation generator. The isolation section (18) of the hypersonic intake duct is connected to the wind tunnel test bench through the wind tunnel test bench flow channel (3).

Images