High-temporal-spatial-resolution optical test system and test method for measuring components and temperature of non-equilibrium flow field

Abstract

The invention discloses a high-temporal-spatial-resolution optical test system and test method for measuring components and temperature of an unbalanced flow field, and relates to the field of unbalanced flow field test and measurement, and the system comprises a test environment module which is used for generating and simulating a detached shock wave generated by the front edge of an aircraft in a flight state of the aircraft; the first absorption spectrum measurement module is used for measuring NO generation and eliminating signals in the detached shock wave layer; the second absorption spectrum measurement module is used for measuring generation and eliminating signals of O and N in the detached shock wave layer; the signal acquisition and data analysis module is used for recording O, N and NO generation and eliminating signals to obtain original signals, and inverting the flow field temperature of the measured position according to the original signals; according to the invention, multi-position and high-time-resolution non-contact test measurement of non-equilibrium characteristics in a front edge detached shock wave layer of a hypersonic aircraft can be realized in a ground wind tunnel test process.

Description

Technical Field

[0001] The present invention relates to the field of non-equilibrium flow field testing and measurement, and in particular to a high-time-space resolution optical test system and test method for measuring non-equilibrium flow field components and temperature. Background Art

[0002] The non-equilibrium flow state formed by the detached shock layer at the leading edge of the aircraft often occurs in the near-wall area of ​​the aircraft moving at hypersonic speed in the atmospheric environment such as the reentry capsule. The speed of the aircraft can reach 10,000 kilometers per hour. The high total temperature caused by the high-speed movement causes the oxygen and nitrogen to dissociate and ionize successively when the airflow is stagnant. At present, there is no optical measurement of the above-mentioned non-equilibrium flow field during flight tests. During ground tests, due to the difficulty in simulating the flight environment and the inability of measurement technology to effectively match the test environment, there are few reports on quantitative, synchronous, high-time-resolution, and non-contact test methods for the physical quantities of the non-equilibrium flow field in the detached shock layer. Summary of the invention

[0003] The purpose of the present invention is to realize the multi-position and high time resolution non-contact test measurement of the non-equilibrium characteristics in the detached shock layer at the leading edge of a hypersonic aircraft during the ground wind tunnel test.

[0004] To achieve the above-mentioned object of the invention, the present invention provides a high temporal and spatial resolution optical test system for measuring non-equilibrium flow field components and temperature, the system comprising:

[0005] The test environment module is used to generate the detached shock wave generated by the leading edge of the aircraft in the flight state;

[0006] The first absorption spectrum measurement module is used to measure the generation and elimination signals of NO in the exfoliated shock layer;

[0007] The second absorption spectrum measurement module is used to measure the generation and elimination signals of O and N in the exfoliated shock layer;

[0008] The signal acquisition and data analysis module is used to record the generation and elimination signals of O, N and NO to obtain the original signals, and invert the flow field temperature at the measured position based on the original signals.

[0009] Among them, the present invention simulates the flight environment based on arc heating, ultra-high pressure driving and vacuuming to reduce back pressure. The gas is heated by an electric arc to initially obtain a relatively high temperature; the upstream ultra-high pressure gas is used to drive the downstream test gas by extrusion, so that the test gas has a high total pressure; the test section is evacuated into a vacuum state with a vacuum pump downstream of the test section, so that a high pressure ratio is formed upstream and downstream. According to the three substances O, N, and NO that may exist in the non-equilibrium flow field and the characteristics of the high temperature, high pressure, small area, and confined space of the measured flow field, the lasers required for the absorption spectrum of each substance, the compact space layout design, and the sapphire wedge-shaped optical glass visualization window are preferably used to match the test environment to achieve high-quality and efficient test results.

[0010] Among them, the present invention is based on the absorption characteristics of different substances to lasers of specific wavelengths. According to the absorption characteristics of O, N and NO to lasers of different wavelengths, suitable absorption spectra are selected respectively, and the laser wavelength is selected according to the spectra. Then, through optical path design, environment construction, multi-system matching and single-line temperature measurement method and double-line temperature measurement method based on absorption spectrum (such as the literature Zhang Guangle. Research on one-dimensional temperature inhomogeneity measurement method based on multi-absorption line TDLAS [D]. Hefei: University of Chinese Academy of Sciences, 2016.), etc., the non-equilibrium characteristics in the detached shock layer at the leading edge of the hypersonic vehicle during the ground wind tunnel test are obtained by multi-position, high time resolution non-contact test measurement.

[0011] Among them, in some embodiments, the test environment module includes:

[0012] Model tester, used to simulate the actual aircraft;

[0013] A tester support frame is used to fix and support the model tester at a position corresponding to the central streamline of the incoming flow nozzle outlet in the wind tunnel measurement section;

[0014] The wind tunnel measurement section is used to provide test space for model testers and signal measurements;

[0015] Incoming flow nozzle, used to generate flow field conditions simulating the flight environment;

[0016] The first wedge-shaped sapphire window and the second wedge-shaped sapphire window are both used to support optical experiments and allow light to pass through a measurement area.

[0017] Wherein, in some embodiments, the first absorption spectrum measurement module includes:

[0018] The first 1900nm band semiconductor laser is used to generate laser light that scans at a fixed frequency within a certain range;

[0019] A first laser controller, used for controlling the output wavelength and frequency of the first 1900nm band semiconductor laser;

[0020] A 1900nm band photoelectric detector, used to receive a signal after the laser emitted by the first 1900nm band semiconductor laser passes through the flow field;

[0021] The first photoelectric signal acquisition line is used to transmit the signal collected by the 1900nm band photoelectric detector to the industrial computer;

[0022] The first signal synchronization line is used to transmit a synchronization trigger signal.

[0023] In some embodiments, the laser generated by the first 1900nm band semiconductor laser passes through the first wedge-shaped sapphire window into the test area and then passes through the second wedge-shaped sapphire window into the 1900nm band photoelectric detector. The 1900nm band photoelectric detector is connected to the industrial computer through the first photoelectric signal acquisition line, and the industrial computer is connected to the first laser controller through the first signal synchronization line.

[0024] Wherein, in some embodiments, the second absorption spectrum measurement module includes:

[0025] The first 777nm band semiconductor laser is used to generate laser light that scans at a fixed frequency within a certain range;

[0026] The first 824nm band semiconductor laser is used to generate laser light that scans at a fixed frequency within a certain range;

[0027] The first 926nm band semiconductor laser is used to generate laser light that scans at a fixed frequency within a certain range;

[0028] A second laser controller, used for controlling the output wavelength and frequency of the first 777nm band semiconductor laser, the first 824nm band semiconductor laser and the first 926nm band semiconductor laser;

[0029] A 777nm-926nm band photoelectric detector receives signals after the lasers emitted by the first 777nm band semiconductor laser, the first 824nm band semiconductor laser and the first 926nm band semiconductor laser pass through the flow field;

[0030] The second to fifth photoelectric signal acquisition lines are used to transmit the signals collected by the 777nm-926nm band photoelectric detector to the industrial computer;

[0031] A second signal synchronization line, used for transmitting a synchronization trigger signal;

[0032] A first wavelength division multiplexer is used to combine the laser beams generated by the first 777nm band semiconductor laser, the first 824nm band semiconductor laser and the first 926nm band semiconductor laser to obtain a combined laser beam;

[0033] A second wavelength division multiplexer is used to split the combined laser beam into four laser beams;

[0034] The first to fourth laser collimators are respectively used to collimate the four laser beams split by the second wavelength division multiplexer;

[0035] A reflecting prism mounting platform, used for fixing the first to third prisms;

[0036] The first to third prisms are used to change the transmission direction of the laser after being collimated by the first to fourth laser collimators.

[0037] In some embodiments, the second laser controller controls the first 777nm band semiconductor laser, the first 824nm band semiconductor laser and the first 926nm band semiconductor laser to generate lasers in the 777nm band, the 824nm band and the 926nm band respectively, the lasers in the 777nm band, the 824nm band and the 926nm band are combined into a combined laser by the first wavelength division multiplexer, the combined laser is divided into four laser beams by the second wavelength division multiplexer, the four laser beams are collimated by the first to fourth laser collimators respectively, the laser collimated by the first laser collimator is reflected by the first prism and then emitted into the test area, the laser collimated by the second and third laser collimators is reflected by the second prism and then emitted into the test area, and the laser collimated by the fourth laser collimator is reflected by the third prism and then emitted into the test area.

[0038] In some embodiments, the first wedge-shaped sapphire window and the second wedge-shaped sapphire window are symmetrically installed on both sides of the incoming flow nozzle with respect to the central streamline of the incoming flow nozzle.

[0039] In some embodiments, the signal acquisition and data analysis module includes an industrial computer and a signal monitor, the industrial computer is used to control the first and second laser controllers, and is used to collect and store information of the 1900nm band photodetector and the 777nm-926nm band photodetector, and is used to process test data; the signal monitor monitors and displays the control program.

[0040] In some embodiments, four photoelectric converters are integrated in the 777nm-926nm band photoelectric detector, and the detection windows of the four photoelectric converters are distributed in parallel with equal intervals.

[0041] The present invention also provides a test method of a high-time-space resolution optical test system based on the non-equilibrium flow field component and temperature measurement, the method comprising:

[0042] Step 1: Build the test system;

[0043] Step 2: Connect the components in the test system;

[0044] Step 3: Turn on the equipment in the test system;

[0045] Step 4: Adjust the first absorption spectrum measurement module to meet the signal detection requirements;

[0046] Step 5: Adjust the position of the laser spot on the model tester in the test environment module, and determine the distance between the laser spot and the model tester;

[0047] Step 6: Adjust the second absorption spectrum measurement module to meet the signal detection requirements;

[0048] Step 7: Return to step 5 until the optical path is adjusted;

[0049] Step 8: Close the test section door and start the test;

[0050] Step 9: Adjust each module in the system to standby mode;

[0051] Step 10: Turn on the test environment module and send a test start signal to the first absorption spectrum measurement module, the second absorption spectrum measurement module and the signal acquisition and data analysis module;

[0052] Step 11: The first absorption spectrum measurement module, the second absorption spectrum measurement module and the signal acquisition and data analysis module start emitting lasers and collecting photoelectric signals after receiving the test start signal;

[0053] Step 12: At the preset end time of the test, the test environment module stops working, and then the first absorption spectrum measurement module, the second absorption spectrum measurement module and the signal acquisition and data analysis module stop working;

[0054] Step 13: After the test, check the original signal;

[0055] Step 14: Result processing and analysis.

[0056] One or more technical solutions provided by the present invention have at least the following technical effects or advantages:

[0057] The present invention can realize the multi-position and high time resolution non-contact test measurement of the non-equilibrium characteristics in the detached shock layer at the leading edge of a hypersonic aircraft during the ground wind tunnel test. BRIEF DESCRIPTION OF THE DRAWINGS

[0058] The drawings described herein are used to provide a further understanding of the embodiments of the present invention, constitute a part of the present invention, and do not constitute a limitation on the embodiments of the present invention;

[0059] Figure 1 Schematic diagram of the composition of the optical experimental system with high temporal and spatial resolution for measuring non-equilibrium flow field components and temperature;

[0060] Figure 2 This is a schematic diagram of the test site measurement points;

[0061] Figure 3 This is a schematic diagram of the timing relationship between the appearance and disappearance of NO, O, and N signals;

[0062] Figure 4 A schematic diagram of the test results. DETAILED DESCRIPTION

[0063] In order to more clearly understand the above-mentioned purpose, features and advantages of the present invention, the present invention is further described in detail below in conjunction with the accompanying drawings and specific embodiments. It should be noted that the embodiments of the present invention and the features in the embodiments can be combined with each other without conflict.

[0064] In the following description, many specific details are set forth to facilitate a full understanding of the present invention. However, the present invention may also be implemented in other ways different from those within the scope of this description. Therefore, the protection scope of the present invention is not limited to the specific embodiments disclosed below.

[0065] Embodiment 1;

[0066] Please refer to Figure 1 , Figure 1 The figure is a schematic diagram of the composition of the optical test system with high spatiotemporal resolution for measuring non-equilibrium flow field components and temperature. The whole system includes multiple components and necessary accessories such as optical fiber connectors. The names and main functions of the components are as follows: model tester 1, used to simulate the aircraft entity; tester support frame 2, used to support the model tester at the central streamline position of the outlet of the incoming flow nozzle; wind tunnel measurement section 3, used to provide test space for the model and measurement technology; incoming flow nozzle 4, used to generate flow field conditions simulating the real flight environment; first wedge-shaped sapphire window 5, used to support optical experiments so that light can pass through the measurement area; second wedge-shaped sapphire window 6, with the same function as 5;

[0067] The first 1900nm band semiconductor laser 7 is used to generate laser light that can be scanned at a fixed frequency within a certain range. The range and frequency are controlled by the first laser controller 8 according to the specific test object. The laser light in this band can be absorbed by NO, thereby causing the signal collected by the 1900nm band photoelectric detector 9 to change. The flow field parameters can be inversely calculated through the specific change amount; the first laser controller 8 controls the output wavelength and frequency of the first 1900nm band semiconductor laser 7; the 1900nm band photoelectric detector 9 receives the signal of the laser light emitted by the first 1900nm band semiconductor laser 7 after passing through the flow field; the first photoelectric signal acquisition line 10 transmits the signal collected by the 1900nm band photoelectric detector to the industrial computer 31; the first signal synchronization line 11 is used to transmit the synchronization trigger signal;

[0068] The first 777nm band semiconductor laser 12 is used to generate a laser that can be scanned at a fixed frequency within a certain range. The range and frequency are controlled by the second laser controller 15 according to the specific test object. The laser in this band can be absorbed by O, thereby causing the signal collected by the 777nm-926nm band photoelectric detector 16 to change. The flow field parameters can be inversely calculated based on the specific change amount; the first 824nm band semiconductor laser 13 is used to generate a laser that can be scanned at a fixed frequency within a certain range. The range and frequency are controlled by the second laser controller 15 according to the specific test object. 5 is controlled, the laser in this band can be absorbed by N, thereby causing the signal collected by the photoelectric detector 16 in the 777nm-926nm band to change, and the flow field parameters can be inversely calculated through the specific change amount; the first 926nm band semiconductor laser 14 is used to generate a laser that can be scanned at a fixed frequency within a certain range, and the range and frequency are controlled by the second laser controller 15 according to the specific test object, and the laser in this band can be absorbed by O, thereby causing the signal collected by the photoelectric detector 16 in the 777nm-926nm band to change, and the flow field parameters can be inversely calculated through the specific change amount;

[0069] The second laser controller 15 is used to control the output wavelength and frequency of 12-14; the 777nm-926nm band photoelectric detector 16 is used to receive the signal after the laser emitted by 12-14 passes through the flow field; the second photoelectric signal acquisition line 17 is used to transmit the signal collected by the 777nm-926nm band photoelectric detector 16 to the industrial computer 31; the third photoelectric signal acquisition line 18 has the same function as 17; the fourth photoelectric signal acquisition line 19 has the same function as 17; the fifth photoelectric signal acquisition line 20 has the same function as 17; the second signal synchronization line 21 is used to transmit the synchronization trigger signal; the second wavelength division multiplexer 22 (1 in 4 out ), used to divide 1 laser beam into 4 beams; a first laser collimator 23, used to improve the collimation of the laser at the end of the second wavelength division multiplexer 22; a second laser collimator 24, with the same function as 23; a third laser collimator 25, with the same function as 23; a fourth laser collimator 26, with the same function as 23; a reflecting prism mounting table 27, used to fix the first to third prisms; a first prism 28, used to change the laser transmission direction; a second prism 29, with the same function as 28; a third prism 30, with the same function; an industrial computer 31, used to control 8, 15, collect and store the information of 9, 16, and process test data; a signal monitor 32, a control program visualization medium.

[0070] The spatial relationship of each component is as follows Figure 1 As shown, components 1-6 constitute a test environment module, which is used to generate a detached shock wave generated by the leading edge of a hypersonic aircraft in flight; components 7-11 constitute a NO absorption spectrum measurement module (i.e., a first absorption spectrum measurement module), which is used to measure the generation and elimination signals of NO in the shock layer; components 12-30 constitute a 4-way absorption spectrum measurement module of two components, O and N (i.e., a second absorption spectrum measurement module), which is used to measure the generation and elimination signals of O and N in the shock layer; components 31 and 32 constitute a signal acquisition and data analysis module, which is used to record the original signals of the three components, O, N, and NO, and invert the flow field temperature at the measured position according to the original signals.

[0071] Figure 1 The 777, 824, 926 and 1900 in the figure represent semiconductor lasers in the corresponding wavelength bands respectively.

[0072] The details that need to be explained in detail for each module are as follows:

[0073] Test environment module: Parts 5 and 6 are two symmetrically installed wedge-shaped sapphire glass windows. These two glasses are used to Figure 1The five-way detection light shown in the figure effectively passes through the flow field. The sapphire material supports the four wavelengths of 777nm, 824nm, 926nm and 1900nm required in this system to pass through the glass medium with high transmittance. The wedge shape is used to solve the interference clutter information formed by the laser at the detection end due to the plane reflection, making the detection signal cleaner, so that weak signals can be extracted efficiently.

[0074] NO measurement module: Component 7 can generate spatial light in the 1900nm band with high collimation, so no additional laser collimator is required.

[0075] O, N4-channel measurement module: The laser wavelengths of the three bands of 777nm, 824nm and 926nm are slightly different, which can achieve efficient transmission and splitting in the same medium. O absorbs in both the 777nm and 926nm bands, and N absorbs in 824nm. Therefore, the present invention designs the lasers of these three bands to be combined first and then split, wherein the first wavelength division multiplexer with 3 inputs and 1 output is used in the beam combining process, and the second wavelength division multiplexer with 1 input and 4 outputs is used in the beam splitting process. The beam combining is to achieve two purposes. The first purpose is to measure the signals of O and N at the same position at the same time, and the second purpose is to use a single wavelength to calculate the results of O and N and a dual wavelength to calculate the results of O when the components and temperature are inverted. Different calculation methods complement each other and finally output a result with higher credibility. The collimation of the 4-channel multi-wavelength laser output by the second wavelength division multiplexer is poor. It is connected to the collimator through a flexible optical fiber, and a laser with a higher collimation like component 7 is output from the output end of the collimator. The difference from component 7 is that components 23-26 output multi-wavelength lasers. The laser output by the collimator passes through three reflecting prisms fixed on component 27, and the four lasers are reflected into the measured flow field. By adjusting the adjustment frame on the collimator, the spacing and direction of the four lasers can be fine-tuned. Component 16 is a multi-wavelength photoelectric detector integrating four photoelectric converters, and the four detection windows are distributed in parallel with equal spacing.

[0076] Signal acquisition and data analysis module: This module realizes two functions. The first function is to synchronously collect 5-channel photoelectric signals, and the second function is to post-process the signals to obtain non-equilibrium flow field temperature information.

[0077] The two laser controllers, component 8 and component 15, can realize the scanning of the laser at a fixed frequency within their respective bands (for example, component 8 can control component 7 to scan at a frequency of 10kHz within the range of 1989nm-1901nm, thereby allowing multiple absorption peaks of NO within this band to be recorded at high frequency). The acquisition board in component 31 can realize data acquisition at MHz or even higher frequencies. During the test, the synchronous acquisition with the same frequency as component 8 and component 15 can be realized through the signal synchronization line and basic settings.

[0078] Embodiment 2:

[0079] Based on the first embodiment, the present invention provides a test method corresponding to the above test system, which specifically includes:

[0080] Step 1: Install the model tester in the wind tunnel measurement section and adjust its position so that it is near the central axis of the incoming flow nozzle and the leading edge of the model tester is in the area observable by the optical glass;

[0081] Step 2: Place an optical platform on each side of the wind tunnel measurement section for installing measurement and monitoring equipment;

[0082] Step 3: Figure 1 The components on both sides of the wind tunnel measurement section are fixed by means of screws, nuts, etc., so that the laser emission and receiving positions are at the same height;

[0083] Step 4: Arrange the components according to Figure 1 Connect the relationships shown;

[0084] Step 5: Turn on the laser, laser controller, photodetector, industrial computer and signal monitor;

[0085] Step 6: Adjust the relative positions of component 7 and component 9 so that component 9 can detect the signal of component 7;

[0086] Step 7: Use an infrared photosensitive plate to check the laser spot position near the model tester to ensure that the spot position is in the ideal test area, that is, close to the front edge of the model tester but not blocked by the model, and determine the distance between the spot and the model;

[0087] Step 8: Adjust the relative position between components 23-26 and component 16 so that component 16 can detect the signals of components 23-26;

[0088] Step9: Repeat step7;

[0089] Step 10: After the optical path is debugged, close the test section door and prepare to start the test;

[0090] Step 11: Each module is adjusted to standby state;

[0091] Step 12: The test environment module is turned on and sends a test start signal to the other three modules;

[0092] Step 13: After receiving the test start signal, the two measurement modules and the acquisition module start emitting lasers and collecting photoelectric signals;

[0093] Step 14: At the preset end time of the test, the test environment module stops working first, and the other three modules stop working at the same time;

[0094] Step 15: After the test, check the original signal;

[0095] Step 16: Result processing and analysis.

[0096] Please refer to Figure 2 , Figure 2 Schematic diagram of test site measurement points, the present invention Figure 2 The measurement points shown in the figure realize the acquisition of multi-wavelength absorption signals of O and N, and the distance between each measurement point is about 7mm; the measurement point of NO is located between measurement point ① and measurement point ④, realizing the acquisition of single-channel single-wavelength absorption signal of NO; ​​through the acquisition of multi-wavelength, multi-channel, multi-component, high-time-resolution absorption spectrum information, the leading edge detached body shock layer during the ground test of the hypersonic vehicle was obtained. Figure 3 The multi-component non-equilibrium characteristic relationship shown in the figure is shown in the figure. After data processing and analysis, the temperature change information at measuring points ①, ② and ③ is obtained, and the time resolution reaches 20μs. The following conclusions are obtained: 1) The temperature in the detached shock layer can be as high as 10000K; 2) The temperature at different positions along the flow direction in the detached shock layer is close but different. As time goes by, the relative high and low temperature relationship at each position has a certain change, but the law is not obvious; 3) After the flow field is established, O2 and N2 in the airflow will first dissociate into O and N. At this time, there is no NO in the flow field. After the high-temperature flow field passes, O and N will recombine to form NO and last for a long time; 4) There is no atomic signal outside the detached shock layer, indicating that the physical quantity gradient between the detached shock layer and the external flow field is very large, and the material composition achieves a higher-scale step in the scale of mm.

[0097] Please refer to Figure 3 , Figure 3 for Figure 3 Test results - Schematic diagram of the timing relationship between the appearance and disappearance of NO, O, and N signals. Figure 3 It can be seen that the time period when the wind tunnel is open is from t0 to t4, the time period when the NO signal is generated is from t3 to t4, and the time period when the O and N signals are generated is from t1 to t2. Figure 3 The timing relationship between the wind tunnel on / off signal and the detected NO signal, O, and N signal is given. It can be found that after a period of time after the wind tunnel is turned on, the O and N signals are detected first, and after a short time, the O and N signals disappear, and then the NO signal is detected. This shows that after the wind tunnel is turned on, a stable flow field will be established on the surface of the model after a period of time, thereby forming a detached shock layer. The non-equilibrium process in the detached shock layer is that oxygen and nitrogen molecules directly dissociate into atomic states at high temperatures, and then recombine into NO, and atomic and molecular NO cannot coexist.

[0098] Figure 4 The schematic diagram of the test results is shown in Figure 2. Figure 4 The three lines in Figure 2 The temperatures of the first three measurement locations are shown.

[0099] Although the preferred embodiments of the present invention have been described, those skilled in the art may make other changes and modifications to these embodiments once they have learned the basic creative concept. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments and all changes and modifications that fall within the scope of the present invention.

[0100] Obviously, those skilled in the art can make various changes and modifications to the present invention without departing from the spirit and scope of the present invention. Thus, if these modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to include these modifications and variations.

Claims

1. A high-temporal-spatial resolution optical test system for non-equilibrium flow field component and temperature measurement, characterized by: The system comprises: The test environment module is used to generate the detached shock wave generated by the leading edge of the aircraft in the flight state; The first absorption spectrum measurement module is used to measure the generation and elimination signals of NO in the exfoliated shock layer; The second absorption spectrum measurement module is used to measure the generation and elimination signals of O and N in the exfoliated shock layer; The signal acquisition and data analysis module is used to record the generation and elimination signals of O, N and NO to obtain the original signals, and invert the flow field temperature at the measured position based on the original signals.

2. The optical test system with high temporal and spatial resolution for measuring non-equilibrium flow field components and temperature according to claim 1, characterized in that: The test environment modules include: Model tester, used to simulate the actual aircraft; A tester support frame is used to fix and support the model tester at a position corresponding to the central streamline of the incoming flow nozzle outlet in the wind tunnel measurement section; The wind tunnel measurement section is used to provide test space for model testers and signal measurements; Incoming flow nozzle, used to generate flow field conditions simulating the flight environment; The first wedge-shaped sapphire window and the second wedge-shaped sapphire window are both used to support optical experiments and allow light to pass through a measurement area.

3. The optical test system with high temporal and spatial resolution for measuring non-equilibrium flow field components and temperature according to claim 1, characterized in that: The first absorption spectrum measurement module includes: The first 1900nm band semiconductor laser is used to generate laser light that scans at a fixed frequency within a certain range; A first laser controller, used for controlling the output wavelength and frequency of the first 1900nm band semiconductor laser; A 1900nm band photoelectric detector, used to receive a signal after the laser emitted by the first 1900nm band semiconductor laser passes through the flow field; The first photoelectric signal acquisition line is used to transmit the signal collected by the 1900nm band photoelectric detector to the industrial computer; The first signal synchronization line is used to transmit a synchronization trigger signal.

4. The optical test system with high temporal and spatial resolution for measuring non-equilibrium flow field components and temperature according to claim 3, characterized in that: The laser generated by the first 1900nm band semiconductor laser passes through the first wedge-shaped sapphire window into the test area and then passes through the second wedge-shaped sapphire window into the 1900nm band photoelectric detector. The 1900nm band photoelectric detector is connected to the industrial computer through the first photoelectric signal acquisition line, and the industrial computer is connected to the first laser controller through the first signal synchronization line.

5. The optical test system with high temporal and spatial resolution for measuring non-equilibrium flow field components and temperature according to claim 1, characterized in that: The second absorption spectrum measurement module includes: The first 777nm band semiconductor laser is used to generate laser light that scans at a fixed frequency within a certain range; The first 824nm band semiconductor laser is used to generate laser light that scans at a fixed frequency within a certain range; The first 926nm band semiconductor laser is used to generate laser light that scans at a fixed frequency within a certain range; A second laser controller, used for controlling the output wavelength and frequency of the first 777nm band semiconductor laser, the first 824nm band semiconductor laser and the first 926nm band semiconductor laser; A 777nm-926nm band photoelectric detector receives signals after the lasers emitted by the first 777nm band semiconductor laser, the first 824nm band semiconductor laser and the first 926nm band semiconductor laser pass through the flow field; The second to fifth photoelectric signal acquisition lines are used to transmit the signals collected by the 777nm-926nm band photoelectric detector to the industrial computer; A second signal synchronization line, used for transmitting a synchronization trigger signal; A first wavelength division multiplexer is used to combine the laser beams generated by the first 777nm band semiconductor laser, the first 824nm band semiconductor laser and the first 926nm band semiconductor laser to obtain a combined laser beam; A second wavelength division multiplexer is used to split the combined laser beam into four laser beams; The first to fourth laser collimators are respectively used to collimate the four laser beams split by the second wavelength division multiplexer; A reflecting prism mounting platform, used for fixing the first to third prisms; The first to third prisms are used to change the transmission direction of the laser after being collimated by the first to fourth laser collimators.

6. The optical test system with high temporal and spatial resolution for measuring non-equilibrium flow field components and temperature according to claim 5, characterized in that: The second laser controller controls the first 777nm band semiconductor laser, the first 824nm band semiconductor laser and the first 926nm band semiconductor laser to generate lasers of the 777nm band, the 824nm band and the 926nm band respectively. The lasers of the 777nm band, the 824nm band and the 926nm band are combined into a combined laser beam by the first wavelength division multiplexer. The combined laser beam is divided into four laser beams by the second wavelength division multiplexer. The four laser beams are collimated by the first to fourth laser collimators respectively. The laser collimated by the first laser collimator is reflected by the first prism and then emitted into the test area. The laser collimated by the second and third laser collimators is reflected by the second prism and then emitted into the test area. The laser collimated by the fourth laser collimator is reflected by the third prism and then emitted into the test area.

7. The optical test system with high temporal and spatial resolution for measuring non-equilibrium flow field components and temperature according to claim 1, characterized in that: The first wedge-shaped sapphire window and the second wedge-shaped sapphire window are symmetrically mounted on both sides of the incoming flow nozzle with respect to the central streamline of the incoming flow nozzle.

8. The optical test system with high temporal and spatial resolution for measuring non-equilibrium flow field components and temperature according to claim 1, characterized in that: The signal acquisition and data analysis module includes an industrial computer and a signal monitor. The industrial computer is used to control the first and second laser controllers, and is used to collect and store information of the 1900nm band photoelectric detector and the 777nm-926nm band photoelectric detector, and is used to process test data; the signal monitor monitors and displays the control program.

9. The optical test system with high temporal and spatial resolution for measuring non-equilibrium flow field components and temperature according to claim 6, characterized in that: The 777nm-926nm band photoelectric detector integrates four photoelectric converters, and the detection windows of the four photoelectric converters are distributed in parallel with equal intervals.

10. An experimental method based on a high temporal and spatial resolution optical experimental system for measuring non-equilibrium flow field components and temperature according to any one of claims 1 to 9, characterized in that: The method comprises: Step 1: Build the test system; Step 2: Connect the components in the test system; Step 3: Turn on the equipment in the test system; Step 4: Adjust the first absorption spectrum measurement module to meet the signal detection requirements; Step 5: Adjust the position of the laser spot on the model tester in the test environment module, and determine the distance between the laser spot and the model tester; Step 6: Adjust the second absorption spectrum measurement module to meet the signal detection requirements; Step 7: Return to step 5 until the optical path is adjusted; Step 8: Close the test section door and start the test; Step 9: Adjust each module in the system to standby mode; Step 10: Turn on the test environment module and send a test start signal to the first absorption spectrum measurement module, the second absorption spectrum measurement module and the signal acquisition and data analysis module; Step 11: The first absorption spectrum measurement module, the second absorption spectrum measurement module and the signal acquisition and data analysis module start emitting lasers and collecting photoelectric signals after receiving the test start signal; Step 12: At the preset end time of the test, the test environment module stops working, and then the first absorption spectrum measurement module, the second absorption spectrum measurement module and the signal acquisition and data analysis module stop working; Step 13: After the test, check the original signal; Step 14: Result processing and analysis.

Images