A test system and method for simulating long-term flight response of a high-speed air intake.

Abstract

A test system and method for simulating the long-term flight response of a high-speed air intake, belonging to the field of wind tunnel air intake thermo-aggregate testing technology. It includes a preheater and an air intake model housed within a wind tunnel chamber. The preheater preheats the air intake model to simulate temperature accumulation during long-term flight. An active cooler is installed within the air intake model. The air intake model is mounted on a lifting mechanism via a support structure. Temperature sensors acquire the temperature of the air intake model, and the temperature is fed back to temperature control software, which adjusts the heating power of the preheater and the cooling power of the active cooler to ensure that the elastic panels of the air intake model exhibit the temperature response characteristics after long-term flight. This method addresses the challenges of obtaining the structural response and flow field changes under the combined stress and heat loads of a high-speed air intake during long-term flight through wind tunnel testing, controlling the model temperature, and obtaining multi-physics coupled test data. Multiple measurement methods are used simultaneously to acquire multi-physics data of the air intake.

Description

Technical Field

[0001] This invention relates to a test system and method for simulating the long-term flight response of a high-speed air intake, belonging to the technical field of wind tunnel air intake thermo-gastrobomb test. Background Technology

[0002] As flight speeds increase, higher demands are placed on the aircraft's propulsion system. Scramjet engine inlets face extreme heating environments due to gas compression and friction. Increased temperatures on the inlet's inner walls cause softening of structural materials, and the coupled force and heat intensify deformation of the inlet's inner walls. Changes to the inlet's profile may disrupt the original aerodynamic design, making shock wave and boundary layer interference more complex, affecting flow stability and shock wave system matching. In severe cases, this can lead to inlet failure, negatively impacting engine thrust generation and flight safety.

[0003] Therefore, scramjet engine inlets are usually designed with active cooling walls to keep the inlet temperature below the design limit. In order to simulate the deformation and flow field changes of the inlet under the combined stress and heat load during long-term flight, a two-way coupling method is required for simulation. However, this simulation method is computationally complex and time-consuming, and its application in engineering problems is too costly. Currently, a one-way coupling method is often used for calculation, but it lacks accuracy compared with the real situation and lacks effective prediction and verification methods.

[0004] Therefore, there is an urgent need to propose a test system and method for simulating the long-term flight response of a high-speed air intake, which can effectively reproduce the initial thermal state of the air intake after long-term flight in ground wind tunnel tests, and on this basis, apply high-speed aerodynamic loads instantaneously, thereby realizing a test method for simulating a strong coupling environment of force-heat-air multi-physics fields, so as to solve the above-mentioned technical problems. Summary of the Invention

[0005] The purpose of this invention is to address the current limitations of wind tunnel testing in capturing the structural response and flow field changes of high-speed air intakes under combined stress and heat loading during long-duration flight. Specifically, it addresses the challenge of using preheaters and active coolers for model temperature control and obtaining multiphysics coupling test data. By using preheaters and active coolers, a temperature difference is generated on the air intake model before the wind tunnel test. A temperature controller ensures the main structure and elastic panels of the air intake are at a specified temperature before the wind tunnel test. This simulates the structural response and flow field changes of a high-speed air intake under combined stress and heat loading during long-duration flight, solving the problem that existing wind tunnel tests cannot simulate the force-thermal-air multiphysics coupling response of high-speed air intakes during long-duration flight. A brief overview of the invention is provided below to offer a basic understanding of certain aspects of the invention. It should be understood that this overview is not an exhaustive summary of the invention. It is not intended to identify key or essential parts of the invention, nor is it intended to limit the scope of the invention.

[0006] The technical solution of this invention:

[0007] Option 1: A test system for simulating the long-term flight response of a high-speed air intake, comprising a preheater, an air intake model, an active cooler, a temperature sensor, a temperature controller, a support mechanism, a wind tunnel chamber, and a lifting mechanism. The wind tunnel chamber houses the preheater and the air intake model. The preheater preheats the air intake model to simulate the temperature accumulation during long-term flight. The active cooler is installed inside the air intake model. The air intake model is mounted on the lifting mechanism via the support mechanism. A temperature sensor is installed on the air intake model. The temperature controller is connected to the preheater, the temperature sensor, and the active cooler.

[0008] Preferably, the bottom of the wind tunnel chamber is covered with a wind tunnel floor, the lifting mechanism passes through the wind tunnel floor, and a movement gap is reserved between the two. A preheater is installed on the wind tunnel floor.

[0009] Preferably, the air intake model has a model optical window on its side and the wind tunnel chamber has a wind tunnel optical window on its side, through which the wave system structure of the air intake model under the action of the elastic wall plate can be observed.

[0010] Preferably, a flow field control unit for controlling the intake pressure ratio is arranged at the rear end of the intake duct model.

[0011] Preferably, a dynamic pressure sensor is arranged on the surface of the elastic wall panel, and a vibration sensor 11 is embedded in the surface of the elastic wall panel.

[0012] Option 2, a test method for simulating the long-term flight response of a high-speed air intake, is based on the test system for simulating the long-term flight response of a high-speed air intake described in Option 1, and includes the following steps:

[0013] Step 1, Experimental preparation and model pre-heating:

[0014] Close the wind tunnel chamber door and equalize the pressure in the wind tunnel chamber until the specified simulated flight altitude pressure conditions are reached;

[0015] During or after the pressure equalization process, the preheater and active cooler are activated; the lifting mechanism sends the intake manifold model into the preheater.

[0016] Step 2, Wind Tunnel Flow Field Establishment and Model Placement:

[0017] Once the pressure and temperature conditions are met, the wind tunnel is started up, and a stable high-speed flow field is established in the wind tunnel chamber.

[0018] The lifting mechanism quickly raises the inlet model, which has reached the target thermal state, from the preheater and cuts into the mainstream of the wind tunnel; at the same time, the power supply to the preheater is turned off and its outer casing is opened to avoid disturbing the flow field.

[0019] Step 3: Coupled experiment and synchronous data acquisition:

[0020] After the air intake model was raised into place, the formal test began;

[0021] The measurement and control system connected to the temperature controller activates the central synchronization trigger unit to synchronously collect the following data:

[0022] 1. Temperature transients on the surface of the elastic wall panel are collected using a temperature sensor;

[0023] 2. Dynamic pressure on the wall surface is collected using a dynamic pressure sensor;

[0024] 3. The vibration acceleration / strain of the elastic wall panel is collected using vibration sensors;

[0025] 4. Record the changes in the wave system structure inside the air intake using a schlieren system or high-speed photography through the wind tunnel optical window and the model optical window;

[0026] Step 4: End of Experiment and Data Saving

[0027] After the preset test time is reached, the lifting mechanism first lowers the air intake model and removes it from the main flow of the wind tunnel to avoid the impact load when the wind tunnel stops; the wind tunnel stops blowing and data acquisition stops.

[0028] The present invention has the following beneficial effects:

[0029] 1. The present invention combines a preheater and an active cooler, and through closed-loop temperature control, enables the inlet model to accurately reach the target temperature distribution after long-term flight before wind tunnel testing, laying a key foundation for subsequent coupled tests.

[0030] 2. Based on the precise pre-set thermal state, this invention rapidly sends the model into a high-speed airflow, simultaneously applying high aerodynamic loads and continuous aerodynamic heating, which can effectively simulate the force-thermal coupling environment of a high-speed air intake during long-term flight. Compared with existing unidirectional coupling simulations, it improves the accuracy of experimental data.

[0031] 3. In the experiment, this invention simultaneously collects multi-physics field data such as temperature, dynamic pressure, and vibration of the elastic wall panel, and combines it with an optical observation window to visualize the flow field structure, directly obtaining key response information on the interaction between thermal deformation and the flow field, resulting in high data value;

[0032] 4. This invention provides a relatively efficient and controllable ground test method, overcoming the shortcomings of high cost of long-term two-way simulation and insufficient accuracy of one-way simulation. It provides important experimental basis for evaluating the thermo-aeroelastic performance of the air intake, verifying the effectiveness of the cooling system, and optimizing the design. It successfully simulates the key thermal state of the high-speed air intake after long-term flight and its coupled response under real aerodynamic forces in the wind tunnel, and can efficiently acquire multi-field synchronous data, significantly improving the experimental research capability and engineering design verification level of thermo-aeroelastic problems. Attached Figure Description

[0033] Figure 1 This is a schematic diagram of a test system for simulating the long-term flight response of a high-speed air intake according to the present invention.

[0034] Figure 2 This is a diagram showing the assembly of the air intake model and the lifting mechanism of the present invention.

[0035] Figure 3 This is a schematic diagram of the intake duct model of the present invention.

[0036] Figure 4 This is a schematic diagram showing the arrangement of the active cooler and the elastic wall panel of the present invention.

[0037] Figure 5 This is a schematic diagram of the intake duct model and the arrangement of the active cooler of the present invention.

[0038] Figure 6 This is a schematic diagram of the air intake model and the arrangement of the temperature sensor according to the present invention.

[0039] Figure 7 This is a flowchart of an experimental method for simulating the long-term flight response of a high-speed air intake according to the present invention.

[0040] In the diagram: 1-Preheater, 2-Inlet model, 2-1-Elastic wall panel, 2-2-Inlet main structure, 3-Active cooler, 4-Temperature sensor, 5-Temperature controller, 6-Support mechanism, 7-Wind tunnel chamber, 8-Lifting mechanism, 9-Floor, 10-Dynamic pressure sensor, 11-Vibration sensor, 12-1-Model optical window, 12-2-Wind tunnel optical window. Detailed Implementation

[0041] To make the objectives, technical solutions, and advantages of this invention clearer, the invention is described below with reference to specific embodiments shown in the accompanying drawings. However, it should be understood that these descriptions are merely exemplary and not intended to limit the scope of the invention. Furthermore, descriptions of well-known structures and technologies are omitted in the following description to avoid unnecessarily obscuring the concept of the invention.

[0042] The connections mentioned in this invention are divided into fixed connections and detachable connections. Fixed connections, also known as non-detachable connections, include but are not limited to conventional fixed connection methods such as folded connections, riveted connections, adhesive connections, and welded connections. Detachable connections include but are not limited to conventional disassembly methods such as threaded connections, snap-fit ​​connections, pin connections, and hinged connections. When a specific connection method is not explicitly defined, it is assumed that at least one existing connection method can always be found to achieve the function, and those skilled in the art can choose according to their needs. For example, a welded connection can be chosen for fixed connections, and a hinged connection can be chosen for detachable connections.

[0043] Specific implementation method one: Combining Figures 1-6 This embodiment describes a test system for simulating the long-term flight response of a high-speed air intake. It includes a preheater 1, an air intake model 2, an active cooler 3, a temperature sensor 4, a temperature controller 5, a support mechanism 6, a wind tunnel chamber 7, and a lifting mechanism 8. The wind tunnel chamber 7 houses the preheater 1 and the air intake model 2. The preheater 1 preheats the air intake model 2 to simulate the temperature accumulation during long-term flight. The active cooler 3 is installed inside the air intake model 2. The air intake model 2 is mounted on the lifting mechanism 8 via the support mechanism 6. The temperature of the air intake model 2 is obtained by the temperature sensor 4 and fed back to the temperature controller 5. The controller then adjusts the heating power of the preheater 1 and the cooling power of the active cooler 3 to ensure that the elastic wall panel 2-1 of the air intake model 2 exhibits the temperature response characteristics after long-term flight.

[0044] Before the formal test begins, the intake duct model 2 is encased in the preheater 1 and rises to the uniform flow field zone of the wind tunnel after the wind tunnel starts blowing. The temperature controller 5 is placed outside the wind tunnel chamber 7. The temperature controller 5 uses the temperature sensor 4 arranged on the intake duct model 2 as a feedback source, compares the temperature feedback from the temperature sensor 4 with the set temperature, and adjusts the power of the preheater 1 and the active cooler 3 to make the intake duct model 2 reach the final set temperature.

[0045] The aforementioned air intake model 2 includes an air intake main structure 2-2 and an elastic wall panel 2-1, which can be made of stainless steel plate, titanium alloy plate, aluminum alloy plate, etc., with a thickness designed to be in the sub-millimeter range.

[0046] The bottom of the wind tunnel chamber 7 is covered with a wind tunnel floor 9. The lifting mechanism 8 passes through the wind tunnel floor 9, and a movement gap is reserved between the two. The lifting mechanism 8 is connected to the air intake model 2 through the support mechanism 6 to control the lifting and lowering of the air intake model 2. A preheater 1 is installed on the wind tunnel floor 9. Before the test starts, the lifting mechanism 8 drives the air intake model 2 into the preheater 1 for preheating. After the test starts, the lifting mechanism 8 drives the air intake model 2 to leave the preheater 1 and enter the wind tunnel mainstream of the wind tunnel chamber 7. Before the wind tunnel stops, the lifting mechanism 8 drives the air intake model 2 out of the wind tunnel mainstream to avoid the influence of impact load.

[0047] A hot air bombardment wind tunnel test was conducted on the intake duct model 2 to obtain the surface temperature, surface pressure, and vibration characteristics of the elastic wall plate 2-1. When calculating the vibration characteristics of the elastic wall plate 2-1, the weight of the sensors installed on the elastic wall plate 2-1 was taken into account. The designed structural modes were tested on the ground, and the simulation and experimental errors of the main vibration modal frequencies were generally no more than 10%.

[0048] The surface temperature, surface pressure, and vibration characteristics of the elastic wall panel 2-1 are obtained by contact measurement. Specifically, the surface temperature is measured by a temperature sensor 4 embedded in the surface, the surface pressure is obtained by a dynamic pressure sensor 10 arranged on the surface of the elastic wall panel 2-1, and the vibration characteristics are measured by a vibration sensor 11 embedded in the surface of the elastic wall panel 2-1, thereby obtaining the real-time response of the elastic wall panel 2-1. The sensor wiring is led out of the wind tunnel chamber 7 through the internal cavity of the support mechanism 6.

[0049] The air intake model 2 has a model optical window 12-1 on its side, and the wind tunnel chamber 7 has a wind tunnel optical window 12-2 on its side. The wave system structure of the air intake model 2 under the action of the elastic wall plate 2-1 can be observed through the wind tunnel optical window 12-2 and the model optical window 12-1.

[0050] The rear end of the intake duct model 2 is equipped with a flow field control unit for controlling the intake duct pressure ratio.

[0051] The preheater 1 is heated by quartz lamps arranged inside the outer casing of the preheater 1. The structural design of the outer casing of the preheater 1 and the selection of lamp power must be appropriate. The power system of the preheater 1 can supply power to the heating system through a high-voltage power supply, a low-voltage distribution cabinet, and a power control cabinet.

[0052] The active cooler 3 can use a thermoelectric cooling chip, which needs to be connected to a power source. Thermoelectric cooling technology utilizes the galvanic effect of p-type and n-type semiconductor materials to efficiently transfer heat between the cold and hot ends by finely controlling the current, thereby achieving precise local temperature regulation.

[0053] A schlieren system frame is installed outside the wind tunnel chamber 7. The flow field near the elastic wall plate 2-1 of the air inlet is observed through optical windows 12-1 and 12-2 via the designed optical path.

[0054] In order to control the intake duct model 2 within a certain temperature range, it is necessary to analyze it using the law of conservation of energy:

[0055]

[0056] In the formula, C is the heat capacity of the intake duct model; T is the instantaneous temperature of the model; and t is time. The energy obtained by the model from the heater; The energy transferred from the model to the cooler; The energy dissipated by the model to its surrounding environment;

[0057] in,

[0058]

[0059]

[0060] A PID controller is used to dynamically adjust the power of the heater and cooler based on the temperature error. The specific parameters are determined through experiments.

[0061] Based on the above equation, the temperature T of the intake manifold model 2 is monitored, and the power of the heater and cooler is dynamically adjusted. The temperature controller 5 uses PID control to maintain the intake manifold model 2 at a certain temperature. If multiple temperature zones are required for the intake manifold model 2, multiple temperature monitoring points should be provided.

[0062] Specifically, the temperature controller 5 incorporates a PID control algorithm, and its control logic is as follows:

[0063] The input is the real-time measurement value of multiple temperature sensors 4 arranged on the main structure 2-2 of the air intake and the elastic wall plate 2-1;

[0064] The set value is the target temperature distribution curve of different regions of the air intake model, which is calculated based on long-duration flight thermal simulation.

[0065] The output is the heating power of the quartz lamp tubes in the corresponding zones of the preheater 1, and the driving current of the thermoelectric cooling elements of each active cooler 3.

[0066] The specific control process includes:

[0067] 1. Initialization phase: The lifting mechanism 8 sends the intake manifold model 2 into the preheater 1, and the system heats up rapidly with high power.

[0068] 2. Temperature Precision Control Stage: When the model temperature approaches the target value, the system switches to PID precision control mode. The controller calculates and outputs control signals in real time based on the error between the instantaneous temperature and the target temperature, the integral of the error, and the derivative of the error.

[0069] 3. Feedforward compensation: In order to cope with the severe cooling effect brought about by the airflow after the wind tunnel starts blowing, before the wind tunnel starts blowing, a feedforward control signal can be applied to the active cooler 3 according to historical test data or simulation results to adjust its cooling power in advance, so as to reduce temperature overshoot.

[0070] Specific Implementation Method Two: Combining Figures 1-7 This embodiment describes a test method for simulating the long-term flight response of a high-speed air intake, which is based on the test system for simulating the long-term flight response of a high-speed air intake described in Specific Embodiment 1, and includes the following steps:

[0071] Step 1, Experimental preparation and model pre-heating:

[0072] Close the door of wind tunnel chamber 7 and equalize the pressure in wind tunnel chamber 7 until the specified simulated flight altitude pressure conditions are reached.

[0073] During or after the pressure equalization process, the preheater 1 and active cooler 3 are activated. The lifting mechanism 8 sends the intake manifold model 2 into the preheater 1.

[0074] Temperature closed-loop control: Temperature controller 5 monitors the model temperature in real time through temperature sensor 4, and dynamically adjusts the partition heating power of preheater 1 and the cooling power of active cooler 3 through PID algorithm, so that the elastic wall panel 2-1 of intake model 2 and intake main structure 2-2 present a non-uniform temperature distribution consistent with long-term flight, and maintains this thermal state until step S3.

[0075] Step 2, Wind Tunnel Flow Field Establishment and Model Placement:

[0076] Once the pressure and temperature conditions are met, the wind tunnel is started up, and a stable high-speed flow field is established in wind tunnel chamber 7.

[0077] The lifting mechanism 8 quickly raises the inlet model 2, which has reached the target thermal state, from the preheater 1 and cuts it into the mainstream of the wind tunnel. This process needs to be completed in a very short time, for example, less than 2 seconds, to minimize the heat loss of the model before the airflow impact.

[0078] Simultaneously, the power supply to preheater 1 is turned off and its outer casing is opened to avoid interfering with the flow field. Whether the active cooler 3 is turned off depends on the test design: if simulating an adiabatic wall, it is turned off; if simulating an actively cooled wall, it continues to operate during the wind tunnel test.

[0079] Step 3: Coupled experiment and synchronous data acquisition:

[0080] After the intake manifold model 2 was raised into position, the formal test began.

[0081] The measurement and control system connected to temperature controller 5 activates the central synchronization trigger unit to synchronously collect the following data:

[0082] 1. The temperature transients on the surface of the elastic wall panel 2-1 are collected by temperature sensor 4.

[0083] 2. Dynamic pressure on the wall surface is collected by dynamic pressure sensor 10.

[0084] 3. The vibration acceleration / strain of the elastic wall panel 2-1 is collected by the vibration sensor 11.

[0085] 4. Through the wind tunnel optical window 12-2 and the model optical window 12-1, record the changes in the wave system structure inside the air intake using a schlieren system or high-speed photography.

[0086] Step 4: End of Experiment and Data Saving

[0087] After the preset test time is reached, the lifting mechanism 8 first lowers the air intake model 2 and removes it from the main flow of the wind tunnel to avoid the impact load when the wind tunnel stops.

[0088] The wind tunnel was shut down, and data acquisition was stopped.

[0089] Save all synchronously acquired multiphysics data for subsequent analysis.

[0090] The surface temperature, surface pressure, and vibration characteristics of the elastic wall panel 2-1 are obtained by contact measurement. Specifically, the surface temperature is measured by the temperature sensor 4 embedded in the surface, the surface pressure is obtained by the dynamic pressure sensor 10 arranged on the surface of the elastic wall panel 2-1, and the vibration characteristics are measured by the vibration sensor 11 embedded in the surface of the elastic wall panel 2-1. The temperature sensor 4, the dynamic pressure sensor 10, and the vibration sensor 11 simultaneously collect and record data.

[0091] It should be noted that in the above embodiments, as long as the technical solutions are not contradictory, they can be permuted and combined. Those skilled in the art can exhaust all possibilities based on the mathematical knowledge of permutation and combination. Therefore, the present invention will not describe the technical solutions after permutation and combination one by one, but it should be understood that the technical solutions after permutation and combination have been disclosed by the present invention.

[0092] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A test system for simulating long-term flight response of a high-speed air intake, characterized in that: It includes a preheater (1), an air intake model (2), an active cooler (3), a temperature sensor (4), a temperature controller (5), a support mechanism (6), a wind tunnel chamber (7), and a lifting mechanism (8). The wind tunnel chamber (7) is equipped with a preheater (1) and an air intake model (2). The preheater (1) preheats the air intake model (2). The air intake model (2) is equipped with an active cooler (3). The air intake model (2) is mounted on the lifting mechanism (8) through the support mechanism (6). The air intake model (2) is equipped with a temperature sensor (4). The temperature controller (5) is connected to the preheater (1), the temperature sensor (4), and the active cooler (3). The air intake model (2) has a model optical window (12-1) on its side and a wind tunnel optical window (12-2) on its side. The wave system structure of the air intake model (2) under the action of the elastic wall plate (2-1) can be observed through the wind tunnel optical window (12-2) and the model optical window (12-1). In order to control the intake model (2) within a certain temperature range, it is necessary to analyze it using the law of conservation of energy: ； In the formula, C is the heat capacity of the intake duct model; T is the instantaneous temperature of the model; and t is time. The energy obtained by the model from the heater; The energy transferred from the model to the cooler; The energy dissipated by the model to its surrounding environment; in, ； ； A PID controller is used to dynamically adjust the power of the preheater (1) and the active cooler (3) according to the temperature error; according to the above equation, the temperature T of the intake duct model (2) is monitored, and the power of the heater and cooler is dynamically adjusted. The bottom of the wind tunnel chamber (7) is covered with a wind tunnel floor (9), the lifting mechanism (8) passes through the wind tunnel floor (9), and a movement gap is reserved between the two. A preheater (1) is installed on the wind tunnel floor (9). The temperature controller (5) has a built-in PID control algorithm, and its control logic is as follows: The input quantity is the real-time measurement value of multiple temperature sensors (4) arranged on the main structure (2-2) and elastic wall plate (2-1) of the air intake duct; The set value is the target temperature distribution curve of different regions of the air intake model, which is obtained from long-term flight thermal simulation calculations. The output is the heating power of the quartz lamp tubes in the corresponding partition of the preheater (1) and the driving current of the thermoelectric cooling element of each active cooler (3); The specific control process includes:

1. Initialization stage: The lifting mechanism (8) sends the intake manifold model (2) into the preheater (1), and the system heats up rapidly with a large power; 2. Temperature Precision Control Stage: When the model temperature approaches the target value, switch to PID precision control mode. The controller calculates and outputs control signals in real time based on the error between the instantaneous temperature and the target temperature, the integral of the error, and the derivative of the error.

3. Feedforward compensation: In order to cope with the severe cooling effect brought about by the airflow after the wind tunnel starts to blow, before the wind tunnel starts to blow, a feedforward control signal can be applied to the active cooler (3) according to historical test data or simulation results to adjust its cooling power in advance in order to reduce temperature overshoot.

2. The test system for simulating long-term flight response of a high-speed air intake according to claim 1, characterized in that: The rear end of the intake model (2) is equipped with a flow field control unit for controlling the intake pressure ratio.

3. The test system for simulating long-term flight response of a high-speed air intake according to claim 2, characterized in that: A dynamic pressure sensor (10) is arranged on the surface of the elastic wall panel (2-1), and a vibration sensor (11) is embedded in the surface of the elastic wall panel (2-1).

4. A test method for simulating the long-term flight response of a high-speed air intake, implemented using the test system for simulating the long-term flight response of a high-speed air intake as described in claim 3, characterized by comprising the following steps: Step 1, Experimental preparation and model pre-heating: Close the door of the wind tunnel chamber (7) and equalize the pressure in the wind tunnel chamber (7) until the specified simulated flight altitude pressure conditions are reached; During or after the equalization process, the preheater (1) and active cooler (3) are started; the lifting mechanism (8) sends the intake manifold model (2) into the preheater (1); Step 2, Wind Tunnel Flow Field Establishment and Model Placement: Once the pressure and temperature conditions are met, the wind tunnel is started up, and a stable high-speed flow field is established in the wind tunnel chamber (7); The lifting mechanism (8) quickly lifts the inlet model (2) that has reached the target thermal state from the preheater (1) and cuts into the mainstream of the wind tunnel; at the same time, it turns off the power of the preheater (1) and opens its outer cover to avoid disturbing the flow field. Step 3: Coupled experiment and synchronous data acquisition: After the intake manifold model (2) is raised into place, the formal test begins; The temperature controller (5) connected to the measurement and control system starts the central synchronization trigger unit to synchronously collect the following data:

1. The transient temperature change of the surface of the elastic wall panel (2-1) is collected by temperature sensor (4); 2. Dynamic pressure on the wall surface is collected by a dynamic pressure sensor (10); 3. The vibration acceleration / strain of the elastic wall panel (2-1) is collected by the vibration sensor (11); 4. Through the wind tunnel optical window (12-2) and the model optical window (12-1), record the changes in the wave system structure inside the air intake using a schlieren system or high-speed photography; Step 4: End of Experiment and Data Saving After the preset test time is reached, the lifting mechanism (8) first lowers the air intake model (2) and exits the wind tunnel mainstream to avoid the impact load when the wind tunnel stops; the wind tunnel stops blowing and data acquisition stops.

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