Hypersonic vehicle thermal protection material and structure ultra-high temperature environment performance verification device

Abstract

The application discloses a hypersonic vehicle thermal protection material and structure superhigh-temperature environment performance verification device, which is used for hypersonic vehicle thermal protection material and structure superhigh-temperature environment performance verification test, and checks the reliability and integrity of materials and structures under thermal environment. The superhigh-temperature environment performance verification device comprises a modular quartz lamp array with a water-cooled baffle, a large-range heat flow meter with a water-cooled pipeline, a quickly movable heat insulation baffle, a test operation table, a modular infrared lamp array, a water-cooling system for heat flow meter cooling, and a temperature / heat flow measurement control system. A double-acting cylinder and a moving control system are arranged to drive the heat insulation baffle to move up and down quickly. By using the device, the heat exchange characteristics of the outer surface of the structure in the flight process of the hypersonic vehicle can be reproduced, the temperature field distribution and deformation response of the structure are researched, the reliability and integrity of the materials and structures under the superhigh-temperature thermal environment are checked, defects in the thermal protection design are found, and the thermal protection design is optimized.

Description

Technical Field

[0001] This invention belongs to the field of hypersonic vehicle performance verification testing, specifically relating to a device for verifying the performance of hypersonic vehicle thermal protection materials and structures in ultra-high temperature environments. Background Technology

[0002] With the increasing number of spacecraft missions in my country, the development of deep space exploration, hypersonic vehicles, and space shuttle vehicles presents significant challenges. During flight, hypersonic vehicles experience aerodynamic heating, causing their structural surfaces and components to encounter transient high-temperature thermal environments. The maximum heat flux density can reach 420 solar constants, with maximum temperatures reaching 1800℃, and the shortest thermal shock duration being 1 second, while the longest can last up to 1500 seconds. Ground-based simulations of high heat flux and high-temperature control are necessary to verify the thermal performance of relevant thermal protection materials and structures. Ground tests are crucial for assessing the adaptability of the spacecraft's thermal protection design to the thermal environment, identifying design flaws, optimizing the design, and evaluating the functional characteristics of the thermal protection system to ensure mission success. To accomplish these testing tasks, relevant technological research is essential.

[0003] High-temperature wind tunnels are expensive to build, limited by operating pressure and power, and their airflow can only be controlled in a stepped manner, failing to meet the needs of ground-based thermal simulation tests of hypersonic vehicle thermal protection structural components. Radiant heating primarily employs various heating methods such as quartz lamps, graphite heaters, and arc lamp heaters. It is the only testing method capable of multi-temperature zone, time-varying, full-scale / whole-machine thermal testing. The development and research of new radiant heating elements can gradually meet the testing capabilities required for high-temperature, high-heating-power hypersonic vehicles. Compared to airflow heating methods, radiant heating equipment is more economical to construct and operate, and it has unique advantages in addressing heat transfer, thermal deformation, thermal matching, and structural integrity under complex environments in aircraft structures.

[0004] Currently, in the field of radiant heating, the heat sources used in heaters mainly include quartz lamps, silicon carbide heaters, silicon molybdenum heaters, and graphite heaters. However, these types of heaters have relatively large thermal inertia and slow heating and cooling rates, making it impossible to simulate transient heat flow, let alone large heat flow abrupt changes. They also cannot meet the minimum thermal shock duration requirement of 1 second, which can easily lead to overtesting and product damage. Summary of the Invention

[0005] To address the aforementioned issues, this invention provides a high-temperature environment performance verification device for thermal protection materials and structures of hypersonic vehicles. This device simulates the high-temperature thermal environment of the outer surface of the thermal protection materials and structures of hypersonic vehicles during flight, reproduces the heat transfer characteristics of the outer surface of the structure during hypersonic vehicle flight, studies the temperature field distribution and deformation response of the structure, assesses the reliability and integrity of the materials and structures under high-temperature thermal conditions, identifies defects in thermal protection design, optimizes the thermal protection design, and provides technical support to ensure the success of flight missions.

[0006] The objective of this invention is achieved through the following technical solution:

[0007] This invention provides a device for verifying the ultra-high temperature environment performance of thermal protection materials and structures for hypersonic vehicles, comprising:

[0008] Test operation table;

[0009] A modular quartz lamp array with a water-cooled baffle is installed on the test operating table, including an infrared lamp array, the irradiation surface of which is perpendicular to the ground;

[0010] A large-range heat flow meter with water-cooled piping is installed on the modular quartz lamp array with water-cooled baffles. The sensitive surface of the heat flow meter faces the irradiation surface of the infrared lamp array. The output signal of the heat flow meter is connected to the temperature / heat flow measurement and control system.

[0011] A rapidly movable heat insulation baffle is installed on the experimental operating table. The plane of the heat insulation baffle is parallel to the irradiation surface of the infrared lamp array. The plane area of ​​the heat insulation baffle is larger than the irradiation surface of the infrared lamp array, which can completely block the infrared light emitted by the infrared lamp array. The infrared lamp array and the heat insulation baffle are enclosed in a sealed space by a high-temperature heat insulation component, so that the radiant heat of the infrared lamp array can only be radiated to the heat insulation baffle.

[0012] The test specimen is positioned on the side of the modular quartz lamp array with water-cooled baffle away from the rapidly movable heat insulation baffle. The irradiated surface of the test specimen faces the irradiated surface of the infrared lamp array and is parallel to the irradiated surface of the infrared lamp array. A temperature sensor is installed on the test specimen, and the output of the temperature sensor is connected to the temperature / heat flow measurement and control system.

[0013] The water cooling system is connected to the water cooling pipes installed on the infrared lamp array and the heat flow meter, respectively.

[0014] The output power of the infrared lamp array is controlled by the power regulator of the temperature / heat flux measurement and control system. The test heat flux value and the temperature value on the specimen are measured by the temperature / heat flux measurement and control system.

[0015] A double-acting cylinder and its movement control system are used to drive the heat insulation baffle to move up and down rapidly.

[0016] Furthermore, the test platform has a load-bearing area greater than 10m². 2 Large-scale precision testing platform, the flatness of the platform surface is no greater than 1mm / m. 2 The table surface has regularly arranged mounting holes, which makes it easy to install various test equipment.

[0017] Furthermore, in the modular quartz lamp array with water-cooled baffle, the infrared lamps are 500mm long U-shaped infrared lamps, powered by 380VAC, with a single lamp power of 7.5KW, and a total of 15 infrared lamps form the 300mm×500mm infrared lamp array; the maximum radiation power of the infrared lamp array irradiation surface reaches 600KW / m. 2 Bright reflective screens were designed on the back and around the light array. The reflective screens adopted an active cooling design to ensure the structural stability of the light array and provide a certain cooling effect for the infrared lamps. The reflective screens were cooled by water, which ensured the safety of the infrared lamps during the test and extended their service life.

[0018] Furthermore, the large-range heat flow meter with water-cooled piping is equipped with one water-cooled Gordon heat flow meter, with a measurement range of 0-1 MW / m. 2 The heat flow meter is designed with a separate water-cooled circuit. The water inlet of the cooling circuit is designed separately from the cooling circuit of the infrared lamp array. A flow meter is installed at the water outlet of the heat flow meter cooling circuit. The signal output lead of the heat flow meter is perpendicular to the layout direction of the infrared lamps and is led out of the infrared lamp array along the water-cooled pipeline. The water-cooled pipeline inside the infrared lamp array is covered with aluminum silicate refractory fiber felt.

[0019] Furthermore, the rapidly movable heat insulation baffle is made of 10mm carbon plate with dimensions of 600mm×400mm×10mm. The carbon plate is covered with aluminum silicate refractory fiber felt on both sides for heat insulation. The upper part of the carbon plate is connected to the piston rod of the double-acting cylinder, and the connection is made of 99 corundum ceramic tube for heat insulation.

[0020] Furthermore, the water cooling system includes a water tank, a water pump, a check valve, a filter screen, a rotor flow meter, a water distributor, a water collector, a water supply pipeline, and a water return pipeline.

[0021] Furthermore, the flow rate of the modular infrared lamp array cooling water supply pipeline is 5L / Min-10L / Min, and the pressure is 0.3MPa; the flow rate of the heat flow meter cooling water supply pipeline is 0.15L / Min-0.2L / Min, and the pressure is 0.3MPa.

[0022] Furthermore, in the temperature / heat flux measurement and control system, temperature is measured using platinum-rhodium 10-platinum thermocouples, nickel-chromium-nickel-silicon thermocouples, and copper-constantan thermocouples to measure the temperature values ​​on the surface, inside, and back of the test piece, respectively; the heat flux measurement and control system includes a heat flux meter, a heat flux signal isolation amplifier, a PID controller, a high-power regulator, etc., to achieve precise control of the heat flux value.

[0023] Furthermore, in the double-acting cylinder and its movement control system, the double-acting cylinder is vertically installed directly above the rapidly moving heat insulation baffle, the piston rod is connected to the rapidly moving heat insulation baffle, and the air inlet of the double-acting cylinder is connected to the air outlet of the automatic compressed air unit through a three-way directional control valve.

[0024] Furthermore, the double-acting cylinder has a stroke greater than 500mm and an operating speed greater than 500mm / s. The air inlet of the double-acting cylinder is connected to the air outlet of the automatic compressed air unit through a three-way directional control valve. By changing the air supply direction of the cylinder, the cylinder drives the heat insulation baffle to move rapidly between the infrared lamp array irradiation surface and the test piece, thereby simulating transient heat flow (thermal shock) with a test irradiation loading time of a minimum of 1s and a maximum of 1500s.

[0025] The beneficial effects of this invention are:

[0026] This invention solves the problem of transient simulation such as large thermal inertia of radiant heaters and difficulty in achieving thermal shock, and achieves a heat flux density exceeding 600 KW / m³. 2 The key technical indicator of minimum thermal shock time of 1 second can reproduce the heat transfer characteristics of the outer surface of the structure during the flight of hypersonic aircraft, study the temperature field distribution and deformation response of the structure, and assess the reliability and integrity of materials and structures under thermal environment. Attached Figure Description

[0027] Figure 1 A schematic diagram of a device for verifying the performance of thermal protection materials and structures in ultra-high temperature environments for hypersonic aircraft.

[0028] Figure 2 A schematic diagram of the installation of a heat flow meter for calibrating the heat flow position relationship coefficient.

[0029] In the figure, 1-a large-range heat flow meter with water-cooled piping; 2-a modular quartz lamp array with water-cooled baffle; 3-a rapidly movable heat insulation baffle; 4-a double-acting cylinder and its movement control system; 5-a thermal protection material assembly (test piece); 6-a test operating table; 7-a large-range heat flow meter with water-cooled piping calibrated at the test piece. Detailed Implementation

[0030] The following describes specific embodiments of the content described in this invention, further clarifying the content of this invention through these specific embodiments. Of course, the following specific embodiments are merely illustrative of different aspects of this invention and should not be construed as limiting the scope of this invention.

[0031] The specific embodiments of the present invention will be further described below:

[0032] To accurately simulate the time-heat flow curve of the thermal shock to the thermal protection system caused by aerodynamic heating during hypersonic vehicle flight, and to conduct ultra-high temperature environment performance tests on the components of the thermal protection system to evaluate the thermal insulation performance of the components, this invention provides an ultra-high temperature environment performance verification device for hypersonic vehicle thermal protection materials and structures, comprising:

[0033] The test platform includes a modular quartz lamp array with a water-cooled baffle, mounted on the platform. This array includes an infrared lamp array, the irradiation surface of which is perpendicular to the ground. A large-range heat flow meter with water-cooled piping is mounted on the modular quartz lamp array with the water-cooled baffle, its sensitive surface facing the irradiation surface of the infrared lamp array. The output signal of the heat flow meter is connected to a temperature / heat flow measurement and control system. A rapidly movable heat insulation baffle is mounted on the test platform. The plane of the heat insulation baffle is parallel to the irradiation surface of the infrared lamp array, and its area is larger than that of the irradiation surface, effectively blocking the infrared light emitted by the lamp array. A high-temperature heat insulation component encloses the infrared lamp array and the heat insulation baffle into a sealed space, limiting the radiated heat from the infrared lamp array to a smaller area. The test specimen is positioned on the side of the rapidly movable heat-insulating baffle away from the modular quartz lamp array with the water-cooled baffle. The irradiated surface of the test specimen faces the irradiated surface of the infrared lamp array and is parallel to it. A temperature sensor is installed on the test specimen, and the output of the temperature sensor is connected to the temperature / heat flow measurement and control system. A water-cooling system is connected to the water-cooling pipes installed on the infrared lamp array and the heat flow meter, respectively. The output power value of the infrared lamp array is controlled by the power regulator of the heat flow control system, and the test heat flow value and the temperature value on the test specimen are measured by the temperature / heat flow measurement and control system. A double-acting cylinder and its movement control system are used to drive the heat-insulating baffle to move up and down rapidly.

[0034] In some embodiments, the test platform has a load-bearing area greater than 10m². 2 Large-scale precision testing platform, the flatness of the platform surface is no greater than 1mm / m. 2The platform features regularly arranged mounting holes for easy installation of various testing equipment. The modular quartz lamp array with water-cooled baffle contains 500mm long U-shaped infrared lamps powered by 380VAC, with a single lamp power of 7.5KW. A total of 15 infrared lamps form a 300mm×500mm infrared lamp array; the maximum radiation power of the infrared lamp array's irradiation surface reaches 600KW / m². 2 Bright reflective screens are designed on the back and around the light array. These screens feature active cooling to ensure the stability of the light array structure and provide cooling for the infrared lamps. Water cooling of the reflective screens ensures the safety of the infrared lamps during testing and extends their lifespan. The large-range heat flow meter with water-cooled piping is equipped with one water-cooled Gordon heat flow meter, with a measurement range of 0-1 MW / m. 2 The heat flow meter has a separate water-cooled circuit, with the inlet water circuit separate from the infrared lamp array cooling circuit. A flow meter is installed at the outlet of the heat flow meter's cooling circuit. The signal output lead of the heat flow meter is perpendicular to the layout direction of the infrared lamps and leads out of the infrared lamp array along the water-cooled pipeline. The water-cooled pipeline inside the infrared lamp array is covered with aluminosilicate refractory fiber felt. The rapidly movable heat-insulating baffle is made of 10mm carbon plate, with dimensions of 600mm×400mm×10mm. The carbon plate is double-sided covered with aluminosilicate refractory fiber felt for heat insulation. The upper part of the carbon plate is connected to the piston rod of the double-acting cylinder, and the connection is insulated with 99% corundum ceramic tube. The water-cooling system includes a water tank, water pump, check valve, filter screen, rotor flow meter, water distributor, water collector, supply water pipeline, and return water pipeline. The modular infrared lamp array cooling water supply pipeline has a flow rate of 5L / min-10L / min and a pressure of 0.3MPa. The heat flow meter cooling water supply pipeline has a flow rate of 0.15L / min-0.2L / min and a pressure of 0.3MPa. In the temperature / heat flow measurement and control system, platinum-rhodium 10-platinum thermocouples, nickel-chromium-nickel-silicon thermocouples, and copper-constantan thermocouples are used to measure the temperature values ​​of the surface, interior, and back of the test piece, respectively. The heat flow measurement and control system includes a heat flow meter, a heat flow signal isolation amplifier, a PID controller, and a high-power regulator to achieve precise control of the heat flow value. In the double-acting cylinder and its movement control system, the double-acting cylinder is vertically installed directly above the rapidly moving heat insulation baffle. The piston rod is connected to the rapidly moving heat insulation baffle, and the air inlet of the double-acting cylinder is connected to the air outlet of the automatic compressed air unit through a three-way directional control valve. The double-acting cylinder has a stroke greater than 500mm and an operating speed greater than 500mm / s. The air inlet of the double-acting cylinder is connected to the air outlet of the automatic compressed air unit through a three-way directional control valve. By changing the air supply direction of the cylinder, the cylinder drives the heat insulation baffle to move rapidly between the infrared lamp array irradiation surface and the test piece, realizing transient heat flow simulation (thermal shock) with a test irradiation loading time of a minimum of 1s and a maximum of 1500s.

[0035] The present solution will now be described in conjunction with the accompanying drawings and a specific embodiment:

[0036] The ultra-high temperature environment performance verification device includes a large-range heat flow meter with water-cooled piping 1, a modular quartz lamp array with water-cooled baffles 2, a rapidly movable heat insulation baffle 3, a double-acting cylinder and its movement control system for rapidly moving the heat insulation baffle up and down 4, a thermal protection material assembly (test specimen) 5, and a test operating platform 6. Additionally, it includes a test temperature / heat flow measurement and control system and a water-cooling system to provide cooling water for the heat flow meter and infrared lamp array.

[0037] like Figure 1 As shown, the modular quartz lamp array 2 with water-cooled baffle is installed on the test platform 6. The irradiation surface of the infrared lamp array 2 is perpendicular to the ground. A coordinate system is established with the center of the irradiation surface of the infrared lamp array 2 as the origin, the horizontal direction as the X-axis, the vertical direction as the Y-axis, and the vertical direction in front of the irradiation surface of the infrared lamp array 2 as the Z-axis. The coordinate range of the irradiation surface of the infrared lamp array 2 is (-150, -250, 0 to 150, 250, 0). The heat flow meter 1 with water-cooled pipe is installed at (100, 200, 50). The sensitive surface of the heat flow meter 1 faces the irradiation surface of the infrared lamp array 2. The output signal of the heat flow meter 1 is connected to the temperature / heat flow measurement and control system. The center point of the rapidly moving heat insulation baffle 3 is installed at (0, 0, 70). The plane of the heat insulation baffle 3... Parallel to the irradiation surface of the infrared lamp array 2, the heat insulation baffle 3 has a larger planar area than the irradiation surface of the infrared lamp array 2, completely blocking the infrared light emitted by the infrared lamp array 2. The infrared lamp array 2 and the heat insulation baffle 3 are enclosed in a sealed space by a high-temperature heat insulation component, so that the radiant heat of the infrared lamp array 2 can only be radiated onto the heat insulation baffle 3. The center point of the irradiated surface of the thermal protection material component (test piece) 5 is installed at (0,0,90), and the irradiated surface of the test piece 5 is directly opposite to the irradiation surface of the infrared lamp array 2 and parallel to the irradiation surface of the infrared lamp array 2. A temperature sensor is installed on the test piece 5, and the output of the temperature sensor is connected to the temperature / heat flow measurement and control system. The water cooling system is connected to the water cooling pipelines of the infrared lamp array 2 and the heat flow meter 1 respectively. The double-acting cylinder 4 is vertically mounted directly above the rapidly moving heat insulation baffle 3. The piston rod of the double-acting cylinder 4 is connected to the rapidly moving heat insulation baffle 3. The air inlet of the double-acting cylinder 4 is connected to the air outlet of the automatic compressed air unit through a three-way directional control valve. The output power of the infrared lamp array 2 is controlled by the power regulator of the temperature / heat flow measurement and control system. The test heat flow value and the temperature value on the test piece 5 are measured by the temperature measurement / heat flow control system.

[0038] like Figure 1As shown, since the distance from the sensitive surface of the heat flux meter 1 installed in the device to the irradiation surface of the infrared lamp array 2 is not equal to the distance from the irradiated surface of the test piece 5 to the irradiation surface of the infrared lamp array 2, it is necessary to calibrate the correspondence between the heat flux density irradiated by the infrared lamp array 2 to the sensitive surface of the heat flux meter 1 and the heat flux density irradiated by the infrared lamp array 2 to the irradiated surface of the test piece 5, i.e., the heat flux density position coefficient, to achieve closed-loop control and accurate simulation of the heat flux value.

[0039] The method for calibrating the location coefficient of heat flux density is as follows:

[0040] Figure 2 A schematic diagram of the installation of a heat flow meter for calibrating the heat flow position relationship coefficient.

[0041] 1) Install the heat flow meter 7 with water-cooled piping at the installation position of the test piece 5. The sensitive surface of the heat flow meter 7 faces the irradiation surface of the infrared lamp array 2. The output signal of the heat flow meter 7 is connected to the temperature / heat flow control system. The water cooling system is connected to the water cooling piping of the heat flow meter 7.

[0042] 2) Activate the movement control system 4 of the fast-moving heat insulation baffle 3, change the air supply direction of the cylinder, and vertically lift the fast-moving heat insulation baffle 3 to the specified position, ensuring that the lower edge of the fast-moving heat insulation baffle 3 is higher than the upper edge of the infrared lamp array 2.

[0043] 3) Adjust the output power of the infrared lamp array 2, with an adjustment range of 0-100%, and record the measured values ​​of the heat flow meter 1 and the heat flow meter 7;

[0044] 4) The measured value at each power is x, based on the heat flow meter 7 installed at the test specimen location. i The measured value of heat flow meter 1 inside the device is y. i The least squares method is used for curve fitting, and the fitting formula is: y = a + bx + cx 2 +dx 3 The four coefficients a, b, c, and d are obtained. During the formal test, the heat flow value of the heat flow meter 1 in the device is calculated according to the heat flow value required by the test piece 5. The heat flow value is used as a feedback signal, and the heat flow control system adjusts the output power value of the infrared lamp array to control the heat flow meter 1 in the device at the required value.

[0045] The formal assessment and verification test methods are as follows:

[0046] 1) The center point of the irradiated surface of the test specimen 5 to be tested is installed at the test specimen mounting location (0,0,90), and the output of the temperature sensor installed on the test specimen is connected to the temperature / heat flow measurement and control system.

[0047] 2) The fast-moving heat insulation baffle 3 returns to its original position, separating the test piece 5 from the irradiation surface of the infrared lamp array 2, and the high-temperature heat insulation component forms a sealed space between the fast-moving heat insulation baffle 3 and the irradiation surface of the infrared lamp array 2.

[0048] 3) Calculate the heat flux value that the heat flux meter 1 in the device needs to achieve based on the heat flux density value required by the test piece 5;

[0049] 4) Turn on the water cooling system, cylinder movement control system, temperature / heat flow measurement and heat flow control system, and adjust the output power of the infrared lamp array so that the heat flow value of the heat flow meter 1 in the device reaches the required value.

[0050] 5) After the heat flow value stabilizes, change the air supply direction of the cylinder 4 to quickly move the middle fast-moving heat insulation baffle 3 away from the irradiation area of ​​the infrared lamp array 2, so that the radiant heat of the infrared lamp array 2 directly irradiates the irradiated surface of the test piece 5. After the specified irradiation time is completed, turn off the power supply of the infrared lamp array 2, and at the same time change the air supply direction of the cylinder 4 to move the fast-moving heat insulation baffle 3 between the irradiated surface of the infrared lamp array 2 and the test piece 5 to isolate the influence of the residual heat of the infrared lamp array 2 on the test piece 5.

[0051] 6) Analyze the temperature data of the measuring points on the test piece 5, perform appearance inspection and performance testing on the test piece 5, and evaluate the test results.

[0052] Although the specific embodiments of the present invention have been described and illustrated above, it should be noted that those skilled in the art can make various equivalent changes and modifications to the above embodiments in accordance with the spirit of the present invention, and the resulting functions and effects should be within the protection scope of the present invention as long as they do not exceed the spirit covered by the specification and drawings.

Claims

1. A device for verifying the performance of thermal protection materials and structures in ultra-high temperature environments for hypersonic aircraft, characterized in that, include: Test operation table; A modular quartz lamp array with a water-cooled baffle is installed on the test operating table, including an infrared lamp array, the irradiation surface of which is perpendicular to the ground; A large-range heat flow meter with water-cooled piping is installed on the modular quartz lamp array with water-cooled baffles. The sensitive surface of the heat flow meter faces the irradiation surface of the infrared lamp array. The output signal of the heat flow meter is connected to the temperature / heat flow measurement and control system. A rapidly movable heat insulation baffle is installed on the test operating table. The plane of the heat insulation baffle is parallel to the irradiation surface of the infrared lamp array. The plane area of ​​the heat insulation baffle is larger than the irradiation surface area of ​​the infrared lamp array, which can completely block the infrared light emitted by the infrared lamp array. The infrared lamp array and the heat insulation baffle are enclosed in a sealed space by a high-temperature heat insulation component, so that the radiant heat of the infrared lamp array can only be radiated to the heat insulation baffle. The test specimen is positioned on the side of the modular quartz lamp array with water-cooled baffle away from the rapidly movable heat insulation baffle. The irradiated surface of the test specimen faces the irradiated surface of the infrared lamp array and is parallel to the irradiated surface of the infrared lamp array. A temperature sensor is installed on the test specimen, and the output of the temperature sensor is connected to the temperature / heat flow measurement and control system. The water cooling system is connected to the water cooling pipes installed on the infrared lamp array and the heat flow meter, respectively. The output power of the infrared lamp array is controlled by the power regulator of the temperature / heat flux measurement and control system. The test heat flux value and the temperature value on the specimen are measured by the temperature / heat flux measurement and control system. A double-acting cylinder and its movement control system are used to drive the heat insulation baffle to move up and down rapidly.

2. The ultra-high temperature environment performance verification device for thermal protection materials and structures of hypersonic aircraft according to claim 1, characterized in that, The test platform has a load-bearing area greater than 10m². 2 Large-scale precision testing platform, the flatness of the platform surface is no greater than 1mm / m. 2 The mounting holes are arranged in a regular pattern on the tabletop.

3. The ultra-high temperature environment performance verification device for thermal protection materials and structures of hypersonic aircraft according to claim 1, characterized in that, In the modular quartz lamp array with water-cooled baffle, the infrared lamps are 500mm long U-shaped infrared lamps, powered by 380VAC, with a single lamp power of 7.5KW, and a total of 15 infrared lamps form an infrared lamp array of 300mm×500mm; the maximum radiation power of the infrared lamp array irradiation surface reaches 600KW / m. 2 A reflector is provided on the back and around the light array, and the reflector is a water-cooled structure.

4. The ultra-high temperature environment performance verification device for thermal protection materials and structures of hypersonic aircraft according to claim 1, characterized in that, The large-range heat flow meter with water-cooled piping is equipped with one water-cooled Gordon heat flow meter, with a measurement range of 0-1 MW / m. 2 The heat flow meter is designed with a separate water-cooled circuit. The water inlet of the cooling circuit is designed separately from the cooling circuit of the infrared lamp array. A flow meter is installed at the water outlet of the heat flow meter cooling circuit. The signal output lead of the heat flow meter is perpendicular to the layout direction of the infrared lamps and is led out of the infrared lamp array along the water-cooled pipeline. The water-cooled pipeline inside the infrared lamp array is covered with aluminum silicate refractory fiber felt.

5. The ultra-high temperature environment performance verification device for thermal protection materials and structures of hypersonic aircraft according to claim 1, characterized in that, The rapidly movable heat-insulating baffle is made of 10mm carbon plate with dimensions of 600mm×400mm×10mm. The carbon plate is covered with aluminum silicate refractory fiber felt on both sides for heat insulation. The upper part of the carbon plate is connected to the piston rod of the double-acting cylinder, and the connection is made of 99% corundum ceramic tube for heat insulation.

6. The ultra-high temperature environment performance verification device for thermal protection materials and structures of hypersonic aircraft according to claim 1, characterized in that, The water cooling system includes a water tank, a water pump, a check valve, a filter screen, a rotor flow meter, a water distributor, a water collector, a water supply pipeline, and a water return pipeline.

7. The ultra-high temperature environment performance verification device for thermal protection materials and structures of hypersonic aircraft according to claim 6, characterized in that, The modular infrared lamp array cooling water supply pipeline has a flow rate of 5L / min-10L / min and a pressure of 0.3MPa, while the heat flow meter cooling water supply pipeline has a flow rate of 0.15L / min-0.2L / min and a pressure of 0.3MPa.

8. The ultra-high temperature environment performance verification device for thermal protection materials and structures of hypersonic aircraft according to claim 1, characterized in that, In the temperature / heat flow measurement and control system, temperature is measured using platinum-rhodium 10-platinum thermocouples, nickel-chromium-nickel-silicon thermocouples, and copper-constantan thermocouples to measure the temperature values ​​of the test piece's surface, interior, and back side, respectively; the heat flow measurement and control system includes a heat flow meter, a heat flow signal isolation amplifier, a PID controller, and a high-power regulator.

9. The ultra-high temperature environment performance verification device for thermal protection materials and structures of hypersonic aircraft according to claim 1, characterized in that, In the double-acting cylinder and its movement control system, the double-acting cylinder is vertically installed directly above the fast-moving heat insulation baffle, the piston rod is connected to the fast-moving heat insulation baffle, and the air inlet of the double-acting cylinder is connected to the air outlet of the automatic compressed air unit through a three-way directional control valve.

10. The ultra-high temperature environment performance verification device for thermal protection materials and structures of hypersonic aircraft according to claim 9, characterized in that, The double-acting cylinder has a stroke greater than 500mm and an operating speed greater than 500mm / s. The air inlet of the double-acting cylinder is connected to the air outlet of the automatic compressed air unit through a three-way directional control valve. By changing the air supply direction of the cylinder, the cylinder drives the heat insulation baffle to move rapidly between the infrared lamp array irradiation surface and the test piece, realizing transient heat flow simulation with a test irradiation loading time of 1s to 1500s.

Images