Aerodynamic thermal environment simulation test device

Abstract

The application provides a kind of pneumatic thermal environment simulation test device, comprising: test platform, which is provided with the load table that can vibrate;Mounting seat, which is arranged on the load table, is used to fix the test piece, and the heat insulation protective piece that covers the test piece is arranged on the mounting seat, the end of the heat insulation protective piece close to the mounting seat is circumferentially provided with a plurality of air outlets, and the other end is provided with a heat input port with an opening upward;Heat input piece, for inputting high-temperature heat into the inside of the heat insulation protective piece through the heat input port, and the high-temperature heat flows out of the heat insulation protective piece through the air outlet, wherein the test piece in the heat insulation protective piece is arranged opposite to the input direction of high-temperature heat.The pneumatic thermal environment simulation test device provided by the application can directly heat the test piece with high-temperature heat, and the heat insulation protective piece can make the high-temperature heat more concentrated, and the temperature and heating speed adjustment more stable and accurate.

Description

Technical Field

[0001] This application relates to the technical field of aircraft material testing equipment, and in particular to an aerodynamic thermal environment simulation test device. Background Technology

[0002] High-speed aircraft are in extremely harsh aerodynamic heating and vibration coupling environments. The combined effects of prolonged high temperatures and vibration loads can cause cracks, misalignments, peeling, or detachment of the aircraft's thermal insulation materials, and may even lead to fatal safety accidents. Therefore, ground thermal / vibration combined testing of thermal insulation materials under extreme high-temperature environments is extremely important for the safety and reliability design of aircraft.

[0003] Current thermal and vibration tests of insulation materials generally use quartz lamps to provide the thermal environment. However, quartz lamps can only simulate high-temperature environments and cannot simulate the strong shearing effect of high-speed airflow on the surface of an aircraft during flight, thus weakening the reference value and persuasiveness of the test data for insulation materials. Summary of the Invention

[0004] In view of this, the purpose of this application is to provide an aerodynamic thermal environment simulation test device to solve the problems mentioned in the prior art.

[0005] To achieve the above objectives, this application provides an aerodynamic thermal environment simulation test apparatus, comprising:

[0006] The test platform is equipped with a vibrating material loading platform;

[0007] A mounting base is provided on the loading platform. The mounting base is used to fix the loaded test specimen. The mounting base is provided with a heat insulation protective component covering the test specimen. The heat insulation protective component has multiple air outlets circumferentially opened at one end near the mounting base, and a heat input port with an upward opening at the other end.

[0008] A heat input component is used to input high-temperature heat into the interior of the heat insulation component through the heat input port, and the high-temperature heat flows out of the heat insulation component through the air outlet. The test piece inside the heat insulation component is positioned facing the direction of the high-temperature heat input.

[0009] Furthermore, the mounting base includes a first base connected to the material platform and a second base disposed on the first base, wherein the first base and the second base are respectively constructed with liquid cooling channels for unidirectional flow of external coolant.

[0010] The first base has a first inlet and a first outlet at its bottom ends, and a second inlet and a second outlet at its top ends. The second base has a liquid guiding channel inside, which is connected to the second inlet and the second outlet.

[0011] A connecting channel is constructed between the first inlet and the second outlet of the first base, and between the first outlet and the second inlet. External coolant enters the liquid guiding channel through the connecting channel between the first inlet and the second outlet, and flows out of the first outlet through the connecting channel between the first outlet and the second inlet.

[0012] Furthermore, the first base is provided with a liquid storage chamber at its top and bottom, the liquid storage chamber at the bottom communicating with the first inlet and connected to the liquid storage chamber at the top via multiple connecting channels, the liquid storage chamber at the top communicating with the second outlet; and / or,

[0013] The first base has a liquid storage chamber at the top and a liquid storage chamber at the bottom. The liquid storage chamber at the top is connected to the second inlet and is connected to the liquid storage chamber at the bottom through multiple connecting channels. The liquid storage chamber at the bottom is connected to the first outlet.

[0014] Furthermore, the liquid guiding channel is arranged circumferentially around the second base and close to its edge.

[0015] Furthermore, the test piece is clamped between the first base and the second base. The second base has a limiting part that extends through it along its axial direction. The limiting part is used to limit and constrain the test piece from the second base. At least a portion of the test piece extends out of the limiting part and is positioned facing the direction of high-temperature heat input.

[0016] Furthermore, the limiting part is gradually extended toward the first base along its axial direction, and a heat insulation layer is provided between the limiting part and the test piece.

[0017] Furthermore, it also includes a vibrator and a vibration controller connected to the vibrator. The vibrator is rigidly connected to the material platform, and the vibration controller controls the vibrator to drive the material platform to vibrate.

[0018] Furthermore, the heat input component is an acetylene flame heating torch.

[0019] Furthermore, it also includes a temperature measuring element disposed on the test piece for detecting the real-time temperature of the test piece.

[0020] As can be seen from the above, the aerodynamic thermal environment simulation test device provided in this application has a material platform that can simulate the high-altitude vibration environment of the test piece. The heat input component inputs high-temperature heat into the thermal insulation protection component. Since the test piece inside the thermal insulation protection component is set to face the direction of the high-temperature heat input, by adjusting the heating temperature, speed and other related conditions of the high-temperature heat on the test piece, the impact high-temperature heat is sprayed onto the surface of the test piece, simulating the strong shearing effect of high-speed airflow on the test piece during flight, making the test environment closer to the real service environment, and effectively improving the reliability and accuracy of the thermal vibration test data of the thermal insulation material. Attached Figure Description

[0021] To more clearly illustrate the technical solutions in this application or related technologies, the drawings used in the description of the embodiments or related technologies will be briefly introduced below. Obviously, the drawings described below are only embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0022] Figure 1 This is a schematic diagram of the structure of the aerodynamic thermal environment simulation test device according to an embodiment of this application;

[0023] Figure 2 This is a schematic diagram of the structure of the heat insulation protection component according to an embodiment of this application;

[0024] Figure 3 This is a schematic diagram of the mounting base according to an embodiment of this application;

[0025] Figure 4 This is a cross-sectional view of the second base according to an embodiment of this application;

[0026] Figure 5 This is a side sectional view of the second base according to an embodiment of this application;

[0027] Figure 6 This is an assembly cross-sectional view of the first base and the second base in an embodiment of this application;

[0028] Figure 7 This is a perspective view of the first base in an embodiment of this application.

[0029] Explanation of reference numerals in the attached figures

[0030] 1. Test platform; 11. Material loading platform; 12. Heat-insulating platform pad; 13. Vibrator;

[0031] 2. Thermal insulation components; 21. Air outlet; 22. Mounting assembly;

[0032] 3. Mounting bracket;

[0033] 31. First base; 311. Heat insulation pad; 312. First inlet; 313. First outlet; 314. Second inlet; 315. Second outlet; 316. Connecting channel; 317. Liquid storage chamber; 318. Liquid storage chamber;

[0034] 32. Second base; 321. Limiting part; 322. Liquid guiding channel; 323. Mounting hole; 324. Heat insulation layer;

[0035] 33. U-shaped connecting pipe;

[0036] 4. Test specimen; 5. Heat input component; 6. Infusion pipeline. Detailed Implementation

[0037] To make the objectives, technical solutions, and advantages of this application clearer, the following detailed description is provided in conjunction with specific embodiments and the accompanying drawings.

[0038] It should be noted that, unless otherwise defined, the technical or scientific terms used in the embodiments of this application should have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The terms "first," "second," and similar terms used in the embodiments of this application do not indicate any order, quantity, or importance, but are merely used to distinguish different components. Terms such as "comprising" or "including" mean that the element or object preceding the word encompasses the elements or objects listed after the word and their equivalents, without excluding other elements or objects. Terms such as "connected" or "linked" are not limited to physical or mechanical connections, but can include electrical connections, whether direct or indirect. Terms such as "upper," "lower," "left," and "right" are only used to indicate relative positional relationships; when the absolute position of the described object changes, the relative positional relationship may also change accordingly.

[0039] When an aircraft travels at high speeds at high altitudes, it generates enormous amounts of heat through friction with the airflow, causing a rapid rise in the temperature of its fuselage materials—a process known as aerodynamic heating. When the operating speed is approximately 20 times the speed of sound at its local location, the temperature at the leading edge of the aircraft can reach as high as 10,000 K. It is conceivable that such high temperatures would jeopardize the normal operation of the aircraft, threaten the structural safety of the fuselage, and adversely affect the reliability and stability of the aircraft's internal electronic equipment.

[0040] Furthermore, during long-term flight, the natural frequencies and mode shapes of structures such as the nose cone, wings, and rudders of an aircraft change, significantly affecting its flutter and control characteristics. To ensure the smooth progress of aircraft design, an aerodynamic heating simulation test system is typically used to simulate the heating and vibration conditions of the aircraft during friction with the air. This allows for a relatively accurate assessment of the temperature distribution and structural stress and strain during high-speed flight. Finally, based on the test results, appropriate adjustments are made to the aircraft's materials and structure to ensure its safe operation.

[0041] When using quartz lamp radiation heating to simulate aerodynamic heating environments, the upper limit of the quartz lamp heating temperature is 1200℃, while the actual aerodynamic heating environment faced by high-speed aircraft is often around 600℃ to 2000℃. To address the different high-temperature thermal environments faced by different parts of the aircraft, different thermal insulation materials are required to provide thermal protection for the aircraft structure. In particular, the thermal insulation material at the nose cone end of the aircraft often exceeds 1500℃ during high-speed operation, resulting in a significant temperature difference between the simulated heating test environment and the actual aerodynamic thermal environment in service. Furthermore, the thermal radiation heating method of quartz lamps can only simulate high-temperature environments and cannot simulate the strong shearing effect of high-speed airflow on the aircraft surface during flight, weakening the reference value and persuasiveness of the test data of thermal insulation materials.

[0042] Based on the aforementioned technologies, this application provides an aerodynamic thermal environment simulation test device to make the test environment closer to the actual aerodynamic thermal environment in service.

[0043] The embodiments of this application will be described in detail below with reference to the accompanying drawings.

[0044] like Figure 1 As shown, the aerodynamic thermal environment simulation test apparatus provided in this application includes:

[0045] Test platform 1, which is equipped with a vibrating material loading platform 11;

[0046] Mounting base 3 is provided on the loading platform 11. Mounting base 3 is used to fix the loading test piece. Mounting base 3 is provided with a heat insulation protection component 2 covering the test piece 4. The heat insulation protection component 2 has multiple air outlets 21 circumferentially opened at one end near the mounting base 3, and a heat input port with an upward opening at the other end.

[0047] The heat input component 5 is used to input high-temperature heat into the interior of the heat insulation component 2 through the heat input port. The high-temperature heat flows out of the heat insulation component 2 through the air outlet 21. The test piece 4 inside the heat insulation component 2 is positioned facing the direction of input of high-temperature heat.

[0048] As can be seen from the above description, the aerodynamic thermal environment simulation test device provided in this application has a material platform 11 that can simulate the high-altitude vibration environment of the test piece 4. The heat input device 5 inputs high-temperature heat into the thermal insulation protection device 2. Since the test piece 4 inside the thermal insulation protection device 2 is set to face the direction of the high-temperature heat input, by adjusting the heating temperature, speed and other related conditions of the high-temperature heat on the test piece 4, the impact high-temperature heat is sprayed onto the surface of the test piece 4, simulating the strong shearing effect of the high-speed airflow on the test piece 4 during flight, making the test environment closer to the real service environment, providing a theoretical reference for the thermal field distribution change of the thermal insulation material in the aerodynamic thermal environment, and improving the authenticity and accuracy of the thermal vibration test data.

[0049] It should be noted that the heat input device 5 described in this application can be an oxy-acetylene heating spray gun, an oxy-methane heating spray gun, or other combustible gas heating devices. Using combustible gas heating allows for higher temperature heat input. Simultaneously, during combustible gas heating, the heating flame impacts the surface of the test specimen 4. By adjusting the opening of the flow control valve on the spray gun, the temperature and velocity of the high-temperature flame can be controlled. The controlled heating flame can simulate the strong shearing effect of high-speed airflow on the surface of an aircraft during flight, thus making the aerodynamic heating environment closer to real-world service scenarios. Hereinafter, this application will describe the heat input device 5 as an oxy-acetylene heating spray gun.

[0050] In some embodiments, such as Figure 1 As shown, the loading platform 11 on the test platform 1 is slidably connected to the test platform 1. A vibrator 13 and a vibration controller connected to the vibrator 13 are arranged on the side of the test platform 1. The vibrator 13 is rigidly connected to the loading platform 11, and the vibration controller controls the vibrator 13 to drive the loading platform 11 to vibrate. Here, the vibrator 13 can be a mature device from related technologies. For example, the frequency range of the vibrator 13 is 5Hz to 2500Hz, the rated thrust is 200kN, and the maximum acceleration is 85g. The output control mode of the vibration controller for the vibrator 13 can be random vibration, sinusoidal vibration, typical impact, or mixed vibration, etc., to more realistically simulate the actual vibration environment.

[0051] In the above embodiment, a heat-insulating pad 12 is also provided on the material carrier 11. The mounting base 3 passes through the heat-insulating pad 12 and is fixedly connected to the material carrier 11. Here, the heat-insulating pad 12 can be made of mica heat-insulating material in related technologies. Setting the heat-insulating pad 12 can prevent high-temperature heat from flowing out of the air outlet 21 and scorching the material carrier 11, effectively ensuring the normal operation of the test platform 1.

[0052] like Figure 2As shown, in some embodiments, the heat insulation component 2 is a cylindrical shape with openings at the top and bottom. The lower end of the heat insulation component 2 is fixedly connected to the mounting base 3, and the heat input port at the upper end of the heat insulation component 2 is used for the heat input component 5 to input heat. Here, the upward-facing heat input port allows the heat from the heat input component 5 to directly impact the test piece 4 without causing any bending or loss in the direction of the flame, thereby allowing the test piece 4 to counteract the heating flame and simulate the strong shear effect in actual flight scenarios. Here, the air outlet 21 of the heat insulation component 2 is a plurality of strip-shaped openings along its circumference. The air outlet 21 allows the high-temperature heat to flow out of the heat insulation component 2 smoothly, avoiding the accumulation of high-temperature heat inside the heat insulation component 2.

[0053] Furthermore, the lower opening section of the heat insulation component 2 is smaller than its upper opening section, and the lower end of the heat insulation component 2 forms a mounting portion 22 that seals the opening. The mounting portion 22 and the mounting base 3 are fixedly connected by fasteners that pass through both. The mounting portion 22 can prevent the heating flame from directly impacting and heating the mounting base 3, thereby effectively reducing the heat conduction of high-temperature heat to the mounting base 3.

[0054] like Figure 3 As shown, in some embodiments, the mounting base 3 includes a first base 31 connected to the loading platform 11, and a second base 32 disposed on the first base 31.

[0055] Specifically, the test piece 4 is clamped between the first base 31 and the second base 32. The second base 32 is provided with a limiting part 321 that extends through it along its axial direction. The limiting part 321 is used to limit and constrain the test piece 4 from the second base 32. At least a portion of the test piece 4 extends out of the limiting part 321 and is positioned facing the direction of high temperature heat input.

[0056] In the above embodiment, the first base 31 has multiple through holes along its outer peripheral edge. The first base 31 is fixed to the material carrier 11 by fasteners that pass through the through holes and the heat insulation pad 12. In order to further improve the heat insulation capacity, a heat insulation pad 311 is also sandwiched between the first base 31 and the heat insulation pad 12 on the material carrier 11. The heat insulation pad 311 can be made of bakelite board or other materials with low thermal conductivity.

[0057] like Figure 3 and Figure 4As shown, the distance between the second base 32 and the first base 31 is adjustable. For example, the second base 32 has a plurality of through mounting holes 323 spaced along its circumference. The first base 31 has mounting holes coaxial with the mounting holes 323. After the fastener passes through the mounting holes 323, it engages with the corresponding mounting holes on the first base 31 to achieve the connection between the first base 31 and the second base 32. Here, the distance between the first base 31 and the second base 32 is adjusted by changing the thread length of the fastener on the first base 31. When the test piece 4 is clamped between the first base 31 and the second base 32, the fastener is rotated until the second base 32 completely presses the test piece 4.

[0058] like Figure 5 As shown, in the above embodiment, the limiting part 321 is gradually extended towards the first base 31 along its axial direction. The side cross-sectional view of the limiting part 321 is approximately conical. The pointed conical part of the test piece 4 passes through the limiting part 321 to be heated in contact with high-temperature heat. In order to avoid the contact surface of the limiting part 321 being heated and affecting the overall heat distribution of the test piece 4, a heat insulation layer 324 is also sandwiched between the limiting part 321 and the test piece 4. The heat insulation layer 324 can be made of heat insulation materials in related technologies, such as quartz fiber materials.

[0059] The aerodynamic thermal environment simulation test device described in this application also includes a temperature measuring element. For example, the temperature measuring element can be a type B thermocouple or a type K thermocouple in related technologies. The temperature measuring element can be bonded to the surface of the test piece 4 with high-temperature resistant adhesive or fixed to the test piece 4 in other ways to detect the temperature of the test piece 4.

[0060] It should be noted that the aforementioned test piece 4 is cone-shaped. This cone-shaped test piece 4 can simulate the shape of the nose area of ​​the aircraft, which is the part of the aircraft that is first impacted by the high-temperature airflow. The cone-shaped test piece 4 is only used as an example. When the test piece 4 is of other shapes, the limiting part 321 can be changed accordingly, as long as the test piece 4 can be fastened between the first base 31 and the second base 32.

[0061] During the aerodynamic thermal environment test simulation, if the surface temperature of the test piece 4 is too high, continuous high-temperature baking will cause excessive thermal stress on the mounting base 3, leading to deformation and cracking, and causing the entire test device to malfunction. In addition, the excessively hot mounting base 3 will transfer heat to the loading platform 11, and the material of the loading platform 11 itself will be deformed by heat, which will easily affect the vibration control accuracy, thus affecting the overall test data. In the thermal test, since this application uses an oxyacetylene heating flame to heat the test piece 4, the heating flame itself has a high impact on the mounting base 3 and a high heating heat flux density, generally around 500KW / m. 2In summary, simple ventilation and cooling are insufficient to meet the heat dissipation requirements, and additional cooling treatment is needed for mounting base 3.

[0062] like Figure 6 and Figure 7 As shown, based on the above description, in some embodiments, the bottom ends of the first base 31 are respectively provided with a first inlet 312 and a first outlet 313, the top ends of the first base 31 are respectively provided with a second inlet 314 and a second outlet 315, and the second base 32 is provided with a liquid guiding channel 322, which is connected to the second inlet 314 and the second outlet 315 respectively.

[0063] A connecting channel 316 is constructed between the first inlet 312 and the second outlet 315, and between the first outlet 313 and the second inlet 314 of the first base 31. External coolant enters the liquid guiding channel 322 through the connecting channel 316 between the first inlet 312 and the second outlet 315, and flows out of the first outlet 313 through the connecting channel 316 between the first outlet 313 and the second inlet 314.

[0064] Here, the external coolant supply line 6 is connected to the first inlet 312 through a ferrule straight pipe connector on the first base 31, and is also connected to the first outlet 313 through the ferrule straight pipe connector on the first base 31. After the external coolant enters the first base 31 through the first inlet 312, it flows from the second outlet 315 into the liquid guiding channel 322 of the second base 32 along the connecting channel 316 of the first base 31. The coolant in the liquid guiding channel 322 flows into the first base 31 through the second inlet 314 of the first base 31, and flows out from the first outlet 313 along the connecting channel 316 of the first base 31.

[0065] Furthermore, such as Figure 7 As shown, the first base 31 has a liquid storage chamber 317 at its top and bottom. The liquid storage chamber 317 at the bottom is connected to the first inlet 312 and is also connected to the liquid storage chamber 317 at the top through multiple connecting channels 316. The liquid storage chamber 317 at the top is connected to the second outlet 315; and / or,

[0066] The first base 31 has a liquid storage cavity 318 at the top and bottom respectively. The liquid storage cavity 318 at the top is connected to the second inlet 314 and is connected to the liquid storage cavity 318 at the bottom through multiple connecting channels 316. The liquid storage cavity 317 at the bottom is connected to the first outlet 313.

[0067] In the above embodiment, the liquid storage chamber 317 and the liquid storage chamber 318 at the bottom of the first base 31 are arranged opposite to each other. The liquid storage chambers 317 and 318 are connected by multiple connecting channels 316. When the external coolant enters the liquid storage chamber 317 at the bottom through the first inlet 312, a portion of the coolant will be stored in the liquid storage chamber 317. Then, with hydraulic pressure, it will enter the liquid storage chamber 317 at the top through the multiple connecting channels 316. The liquid storage chambers 317 and 318 are arranged to form multiple connecting channels 316 in the first base 31. The external coolant is diverted into each connecting channel 316, thereby maximizing the heat exchange area and effectively enhancing the liquid cooling effect.

[0068] In some embodiments, to simplify the manufacturing process, the connecting channel 316 is a channel parallel to the axis of the first base 31, that is, a channel extending along the height direction. Of course, the connecting channel 316 can also be constructed as an oblique shape, a curved shape, or other shapes to further increase the heat exchange contact area and improve the liquid cooling effect.

[0069] It should be noted that, in order to simplify the manufacturing process, for example, the liquid guiding channel 322 can be directly cut into an annular groove on the second base 32 during the setting process, and after the groove is cut, a cover plate is placed on the top of the groove to form the liquid guiding channel 322; the liquid storage chamber 317 and the liquid storage chamber 318 can also be set in the same way as above, that is, the groove cutting process is carried out first, and then the cover plate is used to cover the groove to seal and form the liquid storage chamber 317 and the liquid storage chamber 318.

[0070] In the above embodiment, the second inlet 314 of the first base 31 and the liquid cooling channel of the second base 32, and the second outlet 315 of the first base 31 and the liquid cooling channel of the second base 32 are connected by a deformable U-shaped connecting pipe 33. The U-shaped connecting pipe 33 can be a metal braided flexible hose. The use of a deformable U-shaped connecting pipe 33 can ensure a sealed connection effect when the distance between the first base 31 and the second base 32 changes.

[0071] like Figure 4 As shown, in some embodiments, the liquid guiding channel 322 on the second base 32 is arranged circumferentially around the second base 32 and close to the edge. The liquid guiding channel 322 is generally annular, the second outlet 315 and the second inlet 314 at the top of the first base 31 are arranged opposite to each other, and the first inlet 312 and the first outlet 313 at the bottom of the first base 31 are arranged opposite to each other, so that the external coolant can stay in the first base 31 and the second base 32 as much as possible for heat absorption and exchange.

[0072] In some embodiments, the aerodynamic thermal environment simulation test device described in this application further includes a temperature acquisition instrument for receiving temperature data from the temperature measurement room. Both the temperature acquisition instrument and the vibration controller are connected to an external electronic control device. The operator receives and views the temperature data from the temperature measurement room through the external electronic control device and controls the vibration frequency, amplitude, and other parameters of the vibration controller through the external electronic control device.

[0073] The fasteners described in the embodiments of this application can be bolts, studs, or pins, etc.

[0074] It should be noted that the method in this embodiment can be executed by a single device, such as a computer or server. The method can also be applied in a distributed scenario, where multiple devices cooperate to complete the task. In such a distributed scenario, one of these devices may execute only one or more steps of the method in this embodiment, and the multiple devices will interact with each other to complete the method described.

[0075] It should be noted that the above description describes some embodiments of this application. Other embodiments are within the scope of the appended claims. In some cases, the actions or steps recorded in the claims can be performed in a different order than that shown in the above embodiments and still achieve the desired result. Furthermore, the processes depicted in the drawings do not necessarily require a specific or sequential order to achieve the desired result. In some embodiments, multitasking and parallel processing are also possible or may be advantageous.

[0076] Those skilled in the art should understand that the discussion of any of the above embodiments is merely exemplary and is not intended to imply that the scope of this application (including the claims) is limited to these examples; within the framework of this application, the technical features of the above embodiments or different embodiments can also be combined, the steps can be implemented in any order, and there are many other variations of different aspects of the embodiments of this application as described above, which are not provided in the details for the sake of brevity.

[0077] The embodiments of this application are intended to cover all such substitutions, modifications, and variations that fall within the broad scope of the appended claims. Therefore, any omissions, modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the embodiments of this application should be included within the protection scope of this application.

Claims

1. A device for simulating a gas dynamic thermal environment, characterized in that include: The test platform is equipped with a vibrating material loading platform; A mounting base is provided on the loading platform. The mounting base is used to fix the loaded test specimen. The mounting base is provided with a heat insulation protective component covering the test specimen. The heat insulation protective component has multiple air outlets circumferentially opened at one end near the mounting base, and a heat input port with an upward opening at the other end. A heat input component is used to input high-temperature heat into the interior of the heat insulation component through the heat input port, and the high-temperature heat flows out of the heat insulation component through the air outlet. The test piece inside the heat insulation component is positioned facing the direction of the high-temperature heat input.

2. The aeroheating environment simulation test device according to claim 1, characterized in that, The mounting base includes a first base connected to the material platform and a second base disposed on the first base. The first base and the second base are respectively constructed with liquid cooling channels for unidirectional flow of external coolant.

3. The aerothermoenvironmental simulation test apparatus according to claim 2, characterized in that The first base has a first inlet and a first outlet at its bottom ends, and a second inlet and a second outlet at its top ends. The second base has a liquid guiding channel inside, which is connected to the second inlet and the second outlet. A connecting channel is constructed between the first inlet and the second outlet of the first base, and between the first outlet and the second inlet. External coolant enters the liquid guiding channel through the connecting channel between the first inlet and the second outlet, and flows out of the first outlet through the connecting channel between the first outlet and the second inlet.

4. The aerothermoenvironmental simulation test apparatus according to claim 3, characterized in that The first base has a liquid storage chamber at its top and bottom. The liquid storage chamber at the bottom is connected to the first inlet and is also connected to the liquid storage chamber at the top via multiple connecting channels. The liquid storage chamber at the top is connected to the second outlet; and / or, The first base has a liquid storage chamber at the top and a liquid storage chamber at the bottom. The liquid storage chamber at the top is connected to the second inlet and is connected to the liquid storage chamber at the bottom through multiple connecting channels. The liquid storage chamber at the bottom is connected to the first outlet.

5. The aerothermoenvironmental simulation test apparatus according to claim 3, characterized in that The liquid guiding channel is arranged around the circumference of the second base and near its edge.

6. The aerothermoenvironmental simulation test apparatus according to claim 2, characterized in that The test piece is clamped between the first base and the second base. The second base has a limiting part that extends through it along its axial direction. The limiting part is used to limit and constrain the test piece from the second base. At least a portion of the test piece extends out of the limiting part and is positioned facing the direction of high-temperature heat input.

7. The aerothermoenvironmental simulation test apparatus according to claim 6, characterized in that The limiting part is gradually extended toward the first base along its axial direction, and a heat insulation layer is provided between the limiting part and the test piece.

8. The aerothermal environment simulation test apparatus according to claim 1, wherein It also includes a vibrator and a vibration controller connected to the vibrator. The vibrator is rigidly connected to the material platform, and the vibration controller controls the vibrator to drive the material platform to vibrate.

9. The aerothermal environment simulation test apparatus according to claim 1, wherein The heat input component is an acetylene flame heating torch.

10. The aerothermal environment simulation test apparatus according to claim 1, characterized in that, It also includes a temperature measuring element, which is disposed on the test piece and used to detect the real-time temperature of the test piece.

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