Aerodynamic pressure and aerodynamic heating simulation test device and test method thereof

Abstract

The application discloses a kind of pneumatic pressure and pneumatic hot environment simulation test device and test method thereof, high-temperature high-pressure gas is generated by fuel and air premixed combustion, after gas compression nozzle, release into test chamber, the test projectile of the position posture of test chamber center is pre-adjusted, erosion is carried out, and the environment of aerodynamic pressure field and aerodynamic heat temperature field is formed on the surface of test projectile, while heating coil is arranged around test projectile, and local heating is carried out to realize the temperature gradient distribution around projectile, test chamber is provided with observation window, and the temperature field distribution of projectile is obtained by infrared camera, and multiple columns of patch type pressure sensors are distributed on the surface of test projectile along axial direction, and the aerodynamic pressure suffered by each part of test projectile is collected.The application can simultaneously load the aerodynamic pressure and pneumatic hot environment of test projectile in laboratory environment, and the dynamic test range of aerodynamic pressure and pneumatic hot environment is wide, and the controllability of test process is strong.

Description

Technical Field

[0001] This invention belongs to the field of aerodynamic environment simulation test technology for projectiles, specifically relating to an aerodynamic pressure and aerodynamic heat simulation test device and its test method. Background Technology

[0002] High-speed projectiles flying in dense atmospheres are subjected to aerodynamic pressure and heating effects from shock waves. These harsh flight conditions pose significant challenges to the projectile's surface materials and internal components. During actual flight, the projectile surface experiences complex thermal and mechanical coupling due to the harsh aerodynamic environment, potentially leading to material peeling and internal component failure. Therefore, research on projectile performance under aerodynamic conditions is crucial. Currently, conventional testing methods include wind tunnel testing, such as shock tunnels and arc tunnels. However, these wind tunnel tests are expensive and primarily used for large-scale aircraft model testing, limiting their application to small components. A low-cost testing system is needed to replace wind tunnel testing, thereby enabling performance testing of the projectile's surface and internal components under aerodynamic conditions.

[0003] Chinese patent CN113640164B discloses an "Ultra-High Temperature Wind Tunnel Erosion Testing System," comprising a fuel system, an erosion system, an erosion spray gun, a specimen fixture, and a testing device. The erosion spray gun is connected to both the fuel system and the erosion system, and is mounted on a lifting and rotating mechanism. The specimen fixture is located on one side of the lifting and rotating mechanism and is positioned opposite the nozzle of the erosion spray gun. This system provides a lifting and rotating mechanism that arranges multiple sets of specimens in a ring around it. The lifting and rotating mechanism drives the high-speed erosion spray gun to be lifted or rotated, allowing adjustment of the spray gun's angle and relative position to different specimens, while simultaneously testing the erosion performance of multiple sets of specimens. However, this testing device can only test a localized area of ​​the test object, generating localized thermal loading within a limited range. Its environmental simulation capabilities are limited, and it cannot simulate the temperature and pressure fields experienced by the test object in real-world conditions. Summary of the Invention

[0004] This invention proposes an aerodynamic pressure and aerothermal simulation test device and its test method to replace traditional wind tunnel tests. It can reproduce the aerodynamic pressure and aerothermal environment experienced by the projectile during actual flight in a laboratory environment, thereby reducing test costs, shortening the test cycle, and improving research efficiency.

[0005] The technical solution for achieving this invention is as follows: a pneumatic pressure and aerothermal simulation test device, comprising two high-pressure air tanks, a fuel tank, a nitrogen control tank, a tank monitoring instrument, a high-pressure air pipeline, a fuel pipeline, a nitrogen control pipeline, a gas premixing chamber, a combustion chamber, a gas compression nozzle, monitoring instruments, a test chamber, a test projectile, an infrared imaging camera, a thermocouple sensor, a heat dissipation chamber, a pressure sensor, and a gas mass fraction sensor. The high-pressure air tanks are connected to the gas premixing chamber via high-pressure air pipelines, the fuel tank is connected to the gas premixing chamber via a fuel pipeline, and the nitrogen control tank is connected to both the high-pressure air pipeline and the fuel pipeline via a nitrogen control pipeline. Each tank is equipped with a tank monitoring instrument. The gas premixing chamber is equipped with a pressure sensor and a gas mass fraction sensor. The gas premixing chamber is connected to the combustion chamber via a pipeline. The gas after combustion in the combustion chamber enters the test chamber through the gas compression nozzle. The test projectile is located in the test chamber. The rear end of the test chamber is connected to the heat dissipation chamber. An observation window is opened on the test chamber. An infrared imaging camera takes pictures of the test projectile through the observation window. Thermocouple sensors and monitoring instruments are fixed in the test chamber. The monitoring instruments monitor the state of the gas entering the test chamber. The thermocouple sensors and infrared imaging camera monitor the test process and the state of the test projectile. The exhaust gas during the experiment is discharged after entering the heat dissipation chamber.

[0006] A test method for an aerodynamic pressure and aerodynamic heat simulation test device, comprising the following steps:

[0007] Step 1: Build an aerodynamic pressure and aerodynamic heat simulation test device, adjust the position and attitude of the test projectile in the test chamber through the feed device, and install the gas compression nozzle required for the test.

[0008] Step 2: Open the switch valve of the high-pressure air tank to purge the gas inside the test pipeline. Adjust the values ​​of the pressure regulating valves on each pipeline and check the working status of each instrument. After the purge is completed, close the switch valve of the high-pressure air tank.

[0009] Step 3: Connect the water inlet pipe inside the heat dissipation chamber, check the working status of the water outlet pipe and heat dissipation fins, and the device enters the test-ready state.

[0010] Step 4: After the test begins, open the valves of the high-pressure air tank, fuel tank, and nitrogen control tank to release high-pressure air and fuel gas into the gas premixing chamber. Nitrogen, as the control gas, regulates the air and fuel entering the gas premixing chamber via a pneumatic pressure regulating valve. The state inside the gas premixing chamber is monitored by pressure sensors and gas mass fraction sensors located above the chamber.

[0011] Step 5: Release the premixed gas in the premixed gas chamber into the combustion chamber, ignite the premixed gas through an electric pulse igniter, and the gas generated by combustion is further pressurized and accelerated through the gas compression nozzle before entering the test chamber and acting on the test projectile.

[0012] Step 6: Turn on and adjust the heating coil to rapidly heat the test projectile, so that the surface temperature of the test projectile is distributed in a gradient.

[0013] Step 7: Record the test process data of each sensor: The infrared imaging camera records the temperature distribution data of the test projectile through the observation window, the patch pressure sensor collects the pressure distribution data on the surface of the test projectile, the inlet flow detector set above the test chamber records the gas state data at the inlet of the test chamber, and the thermocouple sensor records the internal temperature data of the test chamber.

[0014] Step 7: After data recording and backup are completed, close the fuel tank valve and keep the high-pressure air tank continuously supplying air for cooling and cleaning of the test device.

[0015] Step 8: After the temperature inside the test chamber returns to room temperature using thermocouple sensors, close the valves of the high-pressure air tank and nitrogen control tank, disconnect the water inlet pipe, and shut down all testing equipment. Remove the test projectile, record the data from the monitoring tables of each gas tank, and replenish the gas in each tank.

[0016] Compared with the prior art, the significant advantages of this invention are:

[0017] (1) Nitrogen, a non-flammable gas, was used as the control gas for the pneumatic pressure regulating valve in the air and fuel pipeline, which increased the safety of gas regulation during the test.

[0018] (2) The gas premixing chamber design is adopted. By distributing the air and fuel intake pipes at different positions in the gas premixing chamber, the fuel and air can be self-mixed in the gas premixing chamber, resulting in higher combustion efficiency.

[0019] (3) By utilizing the combined action of gas and heating coil, the surface temperature of the test projectile can be locally controlled to form a gradient distribution while the test projectile is in a high temperature and high pressure flow field, thus accurately simulating the temperature and pressure field distribution on the surface of the projectile during actual flight.

[0020] (4) This test device and its test method can test projectiles of various sizes, and can test the high dynamic range aerodynamic pressure and temperature environmental parameters of the test projectile by adjusting the fuel-air mixing ratio, premixing pressure, changing the size of the gas compression nozzle, adjusting the heating coil frequency, and adjusting the position of the test projectile in the test chamber. Attached Figure Description

[0021] Figure 1 This is an overall perspective view of a pneumatic pressure and pneumatic heat environment simulation device according to the present invention.

[0022] Figure 2 This is a front view of a pneumatic pressure and pneumatic heat environment simulation device according to the present invention.

[0023] Figure 3 This is a cross-sectional view of the test chamber of a pneumatic pressure and pneumatic heat environment simulation device according to the present invention.

[0024] Figure 4 This is a perspective view of the test chamber of a pneumatic pressure and pneumatic heat environment simulation device according to the present invention.

[0025] Figure 5 This is a perspective view of the premixing chamber of a pneumatic pressure and pneumatic heat environment simulation device according to the present invention.

[0026] Figure 6 This is a cross-sectional view of the heat dissipation chamber of a pneumatic pressure and pneumatic heat environment simulation device according to the present invention.

[0027] Figure 7 This is a perspective view of the heat dissipation chamber of a pneumatic pressure and pneumatic heat environment simulation device according to the present invention.

[0028] In the diagram: 1-High-pressure air tank, 2-Nitrogen control tank, 3-Fuel tank, 4-Switch valve, 5-Pressure regulating valve, 6-Fuel line, 7-Nitrogen control line, 8-Pneumatic pressure regulating valve, 9-High-pressure air line, 10-One-way pressure regulating valve, 11-Gas premixing chamber, 12-Mass flow monitor, 13-Combustion chamber, 14-Electric pulse igniter, 15-Gas compression nozzle, 16-Inlet flow meter, 17-Test chamber, 18- Heat dissipation chamber, 19-Thermocouple sensor, 20-Infrared imaging camera, 21-Gas tank monitoring gauge, 22-Heating coil, 23-Test projectile body, 24-Water inlet pipe, 25-Water outlet pipe, 26-Heat dissipation fins, 27-Pressure sensor, 28-Gas mass fraction sensor, 29-Main air intake pipe, 30-Three-part fuel intake pipe, 31-Feeding device, 32-Three-part air intake pipe, 33-Surface mount pressure sensor. Detailed Implementation

[0029] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of them. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0030] It should be noted that all directional indications (such as up, down, left, right, front, back, etc.) in the embodiments of the present invention are only used to explain the relative positional relationship and movement of each component in a certain specific posture (as shown in the figure). If the specific posture changes, the directional indication will also change accordingly.

[0031] In this invention, unless otherwise explicitly specified and limited, the terms "connection," "fixing," etc., should be interpreted broadly. For example, "fixing" can mean a fixed connection, a detachable connection, or an integral part; "connection" can mean a mechanical connection or an electrical connection. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0032] Furthermore, the technical solutions of the various embodiments of the present invention can be combined with each other, but only if they are feasible to those skilled in the art. If the combination of technical solutions is contradictory or cannot be implemented, it should be considered that such combination of technical solutions does not exist and is not within the scope of protection claimed by the present invention.

[0033] The following section will further introduce the specific implementation method, as well as the technical difficulties and inventive points of this invention, using this design example as an example.

[0034] Combination Figures 1-7 The present invention discloses a pneumatic pressure and pneumatic thermal environment simulation device, comprising two high-pressure air tanks 1, a fuel tank 3, a nitrogen control tank 2, a gas tank monitoring instrument 21, a high-pressure air pipeline 9, a fuel pipeline 6, a nitrogen control pipeline 7, a gas premixing chamber 11, a combustion chamber 13, a gas compression nozzle 15, a monitoring instrument 16, a test chamber 17, a test projectile 23, an infrared imaging camera 20, a thermocouple sensor 19, a heat dissipation chamber 18, a pressure sensor 27, and a gas mass fraction sensor 28. High-pressure air tank 1 is connected to gas premixing chamber 11 via high-pressure air pipeline 9, fuel tank 3 is connected to gas premixing chamber 11 via fuel pipeline 6, and nitrogen control tank 2 is connected to high-pressure air pipeline 9 and fuel pipeline 6 via nitrogen control pipeline 7. Each tank is equipped with a tank monitoring gauge 21. Gas premixing chamber 11 is equipped with pressure sensor 27 and gas mass fraction sensor 28. Gas premixing chamber 11 is connected to combustion chamber 13 via pipeline, and the gas after combustion in combustion chamber 13 enters test chamber 17 through gas compression nozzle 15. The test chamber 17 contains the test projectile 23. The rear end of the test chamber 17 is connected to the heat dissipation chamber 18. The test chamber 17 has an observation window. The infrared imaging camera 20 takes pictures of the test projectile 23 through the observation window. Thermocouple sensor 19 and monitoring instrument 16 are fixed inside the test chamber 17. The monitoring instrument 16 monitors the state of the gas entering the test chamber 17. The thermocouple sensor 19 and infrared imaging camera 20 monitor the test process and the state of the test projectile 23. The exhaust gas during the experiment is discharged after entering the heat dissipation chamber 18.

[0035] Combination Figure 1The aerodynamic pressure and aerodynamic thermal environment simulation device uses a high-pressure air tank 1 and a fuel tank 3 to provide air and fuel, which are mixed in the gas premixing chamber 11 and then introduced into the combustion chamber 13. The high-temperature and high-pressure gas generated by combustion is released into the test chamber 17 after passing through the gas compression nozzle 15. This gas erodes the test projectile 23, which has been pre-adjusted in position and attitude at the center of the test chamber 17, forming an aerodynamic pressure field and aerodynamic thermal temperature field environment on the surface of the test projectile. At the same time, multiple sets of heating coils 22 are provided around the test projectile 23 to locally heat the test projectile 23 and achieve a temperature gradient distribution around the projectile. An observation window is provided on the side of the test chamber 17, and the temperature field distribution of the test projectile 23 is obtained through an infrared imaging camera 20. Multiple rows of patch pressure sensors 33 are distributed along the axial direction on the surface of the test projectile 23 to collect the aerodynamic pressure on various parts of the test projectile 23. This invention can replace some traditional wind tunnel tests. It simultaneously loads the test projectile 23 with aerodynamic temperature field and aerodynamic pressure field in a laboratory environment, thus restoring the aerodynamic pressure and aerodynamic thermal environment experienced by the projectile during actual flight. The dynamic testing range of aerodynamic pressure and aerodynamic thermal environment generated during the test is wide and the test process is highly controllable.

[0036] The test requires a large amount of high-pressure air, so the high-pressure air tank 1 is a dual tank and is equipped with an independent compressor. The fuel tank 3 and the nitrogen control tank 2 are single tanks. All tanks are equipped with a switch valve 4 and a pressure regulating valve 5 for pressure regulation at the tank outlet. The tank monitoring table 21 is used to monitor the status of each tank.

[0037] The nitrogen control tank 2 provides control gas, and through the nitrogen control pipeline 7, it controls the pneumatic pressure regulating valves 8 connected to the high-pressure air pipeline 9 and the fuel pipeline 6 respectively, so as to independently regulate the air and methane pressure entering the gas premixing chamber 11.

[0038] Combination Figure 1 and Figure 5The gas premixing chamber 11 has a main air intake pipe 29 at its head, connecting the high-pressure air pipe 9 and the main air intake pipe 29. Two parallel and symmetrically distributed three-way air intake pipes 32 branch off from the main air intake pipe 29 and connect to the tail of the gas premixing chamber 11. The top of the gas premixing chamber 11 has a three-way fuel intake pipe 30, connecting the fuel pipe 6 and the gas premixing chamber 11. Each of these pipes is equipped with a one-way pressure regulating valve 10. The main gas in the gas premixing chamber 11 is supplied by the main air intake pipe 29 and the three-way fuel intake pipes 30. Air injected from the tail-end three-way air intake pipes 32 accelerates its flow within the gas premixing chamber 11, promoting air-fuel mixing. In ordinary pipelines, uneven mixing of gas components can easily occur, leading to uneven pressure and temperature fields generated by the gases released after combustion. This special pipeline design ensures more uniform air-fuel mixing and a more uniform pressure and temperature field generated by the gases released after combustion, meeting the experimental requirements.

[0039] A pressure sensor 27 and a gas mass fraction sensor 28 are installed above the gas premixing chamber 11. A pneumatic pressure regulating valve 8 and a mass flow monitor 12 are installed on the pipeline connecting the gas premixing chamber 11 and the combustion chamber 13. When the pressure sensor 27 and the gas mass fraction sensor 28 reach the preset value, the pneumatic pressure regulating valve 8 is controlled to release the mixed gas into the combustion chamber 13, and the gas is ignited by the electric pulse igniter 14 in the combustion chamber 13.

[0040] Combustion chamber 13 is connected to gas compression nozzle 15. The high-temperature gas ignited in combustion chamber 13 is injected into test chamber 17 after passing through gas compression nozzle 15. Gas compression nozzle 15 has a Laval nozzle structure, which is a replaceable part and can be replaced with various sizes according to test needs.

[0041] Combination Figures 1-4 The test chamber 17 has a circular opening at the front end connected to the gas compression nozzle 15. The test chamber 17 is equipped with a feeding device 31, which can install test projectiles 23 of different sizes and can adjust their position and attitude to meet different test requirements. The test chamber 17 is equipped with a monitoring instrument 16 above it to measure and record state parameters such as gas inlet pressure and gas flow rate at the inlet. Thermocouple sensors 19 are provided on the side to record the circumferential temperature data of the test chamber 17. The test chamber 17 has a rectangular observation window on the side, and an infrared imaging camera 20 is arranged outside the window to record the temperature field cloud map around the projectile through the window.

[0042] The test missile body 23 is equipped with multiple sets of heating coils 22 around its circumference. By controlling different coils, the surface temperature gradient distribution of the test missile body 23 can be achieved, simulating the aerodynamic thermal temperature field during actual flight. Multiple rows of patch-type pressure sensors 33 are provided on the surface of the test missile body 23 along the generatrix direction, which can collect surface pressure parameters at different positions of the test missile body 23, thereby obtaining the surface pressure field distribution of the test missile body 23.

[0043] Combination Figure 1 and Figure 5 The heat dissipation chamber 18 is connected to the test chamber 17. Three rows of heat dissipation fins 26 are distributed in parallel at the connection. The heat dissipation fins 26 are staggered between adjacent rows. The heat dissipation fins 26 are connected to the water inlet pipe 24 and the water outlet pipe 25 on the same side wall of the heat dissipation chamber 18. The staggered distribution of the heat dissipation fins 26 can reduce the flow rate of the test airflow into the test chamber 17 and perform water cooling.

[0044] The test method of the aerodynamic pressure and aerodynamic heat simulation test device of the present invention comprises the following steps:

[0045] Step 1: Build an aerodynamic pressure and aerodynamic heat simulation test device, adjust the position and attitude of the test projectile 23 in the test chamber 17 through the feed device 31, and install the gas compression nozzle 15 required for the test.

[0046] Step 2: Open the switch valve 4 of the high-pressure air tank 1 to purge the gas inside the test pipeline, adjust the values ​​of the pressure regulating valves 5 on each pipeline, and check the working status of each instrument. After the gas purging is completed, close the switch valve 4 of the high-pressure air tank 1.

[0047] Step 3: Connect the water inlet pipe 24 inside the heat dissipation chamber 18, check the working status of the water outlet pipe 25 and the heat dissipation fins 26, and the device enters the test state.

[0048] Step 4: After the test begins, open the switch valves 4 of the high-pressure air tank 1, fuel tank 3 and nitrogen control tank 2 to release high-pressure air and fuel gas into the gas premixing chamber 11. Nitrogen is used as the control gas to regulate the air and fuel entering the gas premixing chamber 11 through the pneumatic pressure regulating valve 8. The state inside the gas premixing chamber 11 is monitored by the pressure sensor 27 and the gas mass fraction sensor 28 installed above the gas premixing chamber 11.

[0049] Step 5: Release the premixed gas in the premixed gas chamber 11 into the combustion chamber, ignite the premixed gas through the electric pulse igniter 14, and the gas generated by combustion is further pressurized and accelerated through the gas compression nozzle 15 before entering the test chamber 17 and acting on the test projectile 23.

[0050] Step 6: Turn on and adjust the heating coil 22 to rapidly heat the test projectile 23, so that the surface temperature of the test projectile 23 is distributed in a gradient.

[0051] Step 7: Record the test process data of each sensor: The infrared imaging camera 20 records the temperature distribution data of the test projectile 23 through the observation window, the patch pressure sensor 33 collects the surface pressure distribution data of the test projectile 23, the inlet flow detector 16 set above the test chamber 17 records the gas state data at the inlet of the test chamber 17, and the thermocouple sensor 19 records the internal temperature data of the test chamber 17.

[0052] Step 7: After data recording and backup are completed, close valve 4 of fuel tank 3 and keep air flowing into high-pressure air tank 1 to cool and clean the test device.

[0053] Step 8: After the temperature inside the test chamber 17 is restored to room temperature by detecting the temperature through thermocouple sensor 19, close the switch valve 4 of high-pressure air tank 1 and nitrogen control tank 2, disconnect the water inlet pipe 24, and shut down all testing equipment; take out the test projectile 23, record the data of each gas tank monitoring table 21, and replenish the gas in each gas tank.

Claims

1. A pneumatic pressure and aerothermal simulation test apparatus, characterized in that: It includes two high-pressure air tanks (1), a fuel tank (3), a nitrogen control tank (2), a gas tank monitoring instrument (21), a high-pressure air pipeline (9), a fuel pipeline (6), a nitrogen control pipeline (7), a gas premixing chamber (11), a combustion chamber (13), a gas compression nozzle (15), monitoring instruments (16), a test chamber (17), a test projectile (23), an infrared imaging camera (20), a thermocouple sensor (19), a heat dissipation chamber (18), a pressure sensor (27), and a gas mass fraction sensor (28). The high-pressure air tank (1) is connected to the gas premixing chamber (11) via a high-pressure air pipeline (9), the fuel tank (3) is connected to the gas premixing chamber (11) via a fuel pipeline (6), and the nitrogen control tank (2) is connected to the high-pressure air pipeline (9) and the fuel pipeline (6) via a nitrogen control pipeline (7). Each tank is equipped with a tank monitoring gauge (21). The gas premixing chamber (11) is equipped with a pressure sensor (27) and a gas mass fraction sensor (28). The gas premixing chamber (11) is connected to the combustion chamber (13) via a pipeline. The gas produced after combustion in the combustion chamber (13) enters the test chamber (17) through the gas compression nozzle (15). The test projectile (23) is located inside the test chamber (17). The rear end of the test chamber (17) is connected to the heat dissipation chamber (18). An observation window is opened on the test chamber (17). An infrared imaging camera (20) takes pictures of the test projectile (23) through the observation window. Thermocouple sensors (19) and monitoring instruments (16) are fixed inside the test chamber (17). The monitoring instruments (16) monitor the gas entering the test chamber (17). The state of the gas is monitored by thermocouple sensor (19) and infrared imaging camera (20) during the test process and the state of the test projectile (23). The exhaust gas during the test process is discharged after entering the heat dissipation chamber (18). The position and attitude of the test projectile in the test chamber are adjusted by the feeding device. Multiple sets of heating coils (22) are provided around the test projectile (23) to locally heat the test projectile (23) and realize the temperature gradient distribution around the projectile. Multiple rows of patch pressure sensors (33) are provided along the generatrix direction of the test projectile (23).

2. The aerodynamic pressure and aerodynamic heat simulation test apparatus according to claim 1, characterized in that: The high-pressure air tank (1) is a dual-tank unit with an independent compressor. The fuel tank (3) and the nitrogen control tank (2) are single-tank units. Each tank is equipped with a switch valve (4) and a pressure regulating valve (5). The nitrogen control pipeline (7) is connected to the high-pressure air pipeline (9) and the fuel pipeline (6) through a pneumatic pressure regulating valve (8).

3. The aerodynamic pressure and aerodynamic heat simulation test apparatus according to claim 1, characterized in that: A pneumatic pressure regulating valve (8) and a mass flow monitor (12) are provided on the pipeline connecting the gas premixing chamber (11) and the combustion chamber (13). An electric pulse igniter (14) is provided on the combustion chamber (13).

4. The aerodynamic pressure and aerodynamic heat simulation test apparatus according to claim 1, characterized in that: The head of the gas premixing chamber (11) is provided with a main air intake pipe (29) that connects the high-pressure air pipe (9) and the gas premixing chamber (11). The main air intake pipe (29) is connected to the tail of the gas premixing chamber (11) through two parallel and symmetrically distributed three-part air intake pipes (32) on both sides of the gas premixing chamber (11). The top is provided with a three-part fuel intake pipe (30) that connects the fuel pipe (6) and the gas premixing chamber (11). Each of the above pipes is provided with a one-way pressure regulating valve (10).

5. The aerodynamic pressure and aerodynamic heat simulation test apparatus according to claim 1, characterized in that: The gas compression nozzle (15) has a Laval nozzle structure. The high-temperature gas ignited in the combustion chamber (13) is injected into the test chamber (17) after passing through the gas compression nozzle (15). The gas compression nozzle (15) is a replaceable part and can be replaced in various sizes according to the test requirements.

6. The aerodynamic pressure and aerodynamic heat simulation test device according to claim 1, the front end of the test chamber (17) is connected to the gas compression nozzle (15), and the rear end is connected to the heat dissipation chamber (18). The test chamber (17) is equipped with a monitoring instrument (16) above and a thermocouple sensor (19) on the side. The test chamber (17) is equipped with a feeding device (31) that can adjust the position and attitude of the test projectile (23). The test chamber (17) is equipped with a rectangular observation window on the side.

7. The aerodynamic pressure and aerodynamic heat simulation test apparatus according to claim 1, characterized in that: An infrared imaging camera (20) is arranged on the side of the test chamber (17) to monitor the test projectile (23) through a rectangular observation window.

8. The aerodynamic pressure and aerodynamic heat simulation test apparatus according to claim 1, characterized in that: Three rows of heat dissipation fins (26) are distributed in parallel at the connection between the heat dissipation chamber (18) and the test chamber (17). The heat dissipation fins (26) are arranged alternately between adjacent rows. The heat dissipation fins (26) exchange water cooling heat through the water inlet pipe (24) and the water outlet pipe (25) on the same side wall of the heat dissipation chamber (18).

9. A test method for a pneumatic pressure and aerothermal simulation test apparatus, characterized in that, The steps are as follows: Step 1: Build a pneumatic pressure and aerothermal simulation test device. Adjust the position and attitude of the test projectile (23) in the test chamber (17) through the feed device (31), and install the gas compression nozzle (15) required for the test. Adjust the position and attitude of the test projectile in the test chamber through the feed device. Multiple sets of heating coils (22) are provided around the test projectile (23) to locally heat the test projectile (23) and realize the temperature gradient distribution around the projectile. Multiple rows of patch pressure sensors (33) are provided along the generatrix direction of the test projectile (23). Step 2: Open the switch valve (4) of the high-pressure air tank (1) to purge the gas inside the test pipeline, adjust the value of the pressure regulating valve (5) on each pipeline and check the working status of each instrument. After the gas purging is completed, close the switch valve (4) of the high-pressure air tank (1). Step 3: Connect the water inlet pipe (24) inside the heat dissipation chamber (18), check the working status of the water outlet pipe (25) and heat dissipation fins (26), and the device enters the test state; Step 4: After the test begins, open the switch valves (4) of the high-pressure air tank (1), fuel tank (3) and nitrogen control tank (2) to release high-pressure air and fuel gas into the gas premixing chamber (11). Nitrogen is used as the control gas to regulate the air and fuel entering the gas premixing chamber (11) through the pneumatic pressure regulating valve (8). The pressure sensor (27) and gas mass fraction sensor (28) installed above the gas premixing chamber (11) monitor the state inside the gas premixing chamber (11). Step 5: Release the premixed gas in the premixed gas chamber (11) into the combustion chamber, ignite the premixed gas through the electric pulse igniter (14), and the gas generated by combustion is further pressurized and accelerated through the gas compression nozzle (15) before entering the test chamber (17) and acting on the test projectile (23); Step 6: Turn on and adjust the heating coil (22) to rapidly heat the test projectile (23) so that the surface temperature of the test projectile (23) is distributed in a gradient. Step 7: Record the test process data of each sensor: The infrared imaging camera (20) records the temperature distribution data of the test projectile (23) through the observation window; the patch pressure sensor (33) collects the surface pressure distribution data of the test projectile (23); the inlet flow detector (16) set above the test chamber (17) records the gas state data at the inlet of the test chamber (17); and the thermocouple sensor (19) records the internal temperature data of the test chamber (17). Step 7: After data recording is completed and backed up, close the switch valve (4) of the fuel tank (3) and keep the high-pressure air tank (1) continuously supplying air to cool and clean the test device; Step 8: After the temperature inside the test chamber (17) is restored to room temperature by detecting the thermocouple sensor (19), close the switch valve (4) of the high-pressure air tank (1) and the nitrogen control tank (2), disconnect the water inlet pipe (24), and shut down each detection device; take out the test projectile (23), record the data of each gas tank monitoring table (21), and replenish the gas in each gas tank.

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