Optical test system and test method for synchronously acquiring total temperature and Mach number line distribution of combustion flow field

Abstract

The invention discloses an optical test system and test method for synchronously obtaining the total temperature and Mach number line distribution of a combustion flow field, and relates to the field of combustion flow field measurement. The two-dimensional static temperature measurement module is used for generating and controlling laser which can be absorbed by the measured object, receiving laser spectrum information after the laser is absorbed by the measured object, and obtaining a static temperature measurement result of a plane area of the measured object based on the laser spectrum information; the linear velocity measurement module is used for generating pulse laser, marking the spatial position of water molecules after focusing the pulse laser, and obtaining a marking line; the laser excitation module is used for obtaining slice laser and exciting the marked water molecule decomposer by utilizing the slice laser; the recording module is used for recording the excitation process of the marked water molecule decomposition product to obtain image data and time data; calculating speed information of the mark line based on the image data and the time data; and the control module is used for performing time sequence control on the two-dimensional static temperature measurement module and the linear speed measurement module, and calculating and obtaining a total temperature and Mach number measurement result in the two-dimensional plane of the supersonic combustion flow field based on the static temperature measurement result of the plane area and the speed information of the marking line. The system can measure the Mach number and the total temperature in the two-dimensional plane of the supersonic combustion flow field at the same time.

Description

Technical Field

[0001] The invention relates to the field of combustion flow field measurement, and in particular to an optical test system and a test method for synchronously acquiring the total temperature and Mach number line distribution of the combustion flow field. Background Art

[0002] In the field of supersonic combustion, total temperature is an important parameter that reflects combustion efficiency and flow state. Capturing the Mach number distribution, especially the speed of sound line, is a necessary condition for accurately obtaining the position of the thermal throat of an air-breathing engine. Synchronously obtaining the total temperature and total pressure at multiple points can effectively evaluate the overall performance of the engine. Today, the test method for measuring total temperature is mainly based on a contact-type total temperature probe. This method has two characteristics. One is single-point measurement, which cannot obtain the total temperature in the plane. The other is that it invades the flow field and destroys the supersonic flow structure. The contact method of the moving probe has a very obvious impact on the supersonic flow field structure, causing unnecessary oblique shock waves, which in turn affects the flow and combustion state at the probe location and downstream, resulting in inaccurate measurement results. The prior art lacks an optical test system that can simultaneously measure the Mach number and total temperature in a two-dimensional plane of a supersonic combustion flow field. Summary of the invention

[0003] The object of the present invention is to provide an optical test method for simultaneously measuring the Mach number and the total temperature in a two-dimensional plane of a supersonic combustion flow field.

[0004] To achieve the above-mentioned object of the invention, the present invention provides an optical test system for synchronously acquiring the total temperature and Mach number line distribution of the combustion flow field, the system comprising:

[0005] Measurement object: the measurement object is the supersonic gas flow field;

[0006] A two-dimensional static temperature measurement module, used to generate and control laser light that can be absorbed by the object being measured, receive spectrum information of the laser light after being absorbed by the object being measured, and obtain a static temperature measurement result of a planar area of ​​the object being measured based on the spectrum information of the laser light;

[0007] A linear velocity measurement module is used to generate a pulsed laser, focus the pulsed laser and mark the spatial position of the water molecules to obtain a marked line; and to obtain a thin sheet laser, and use the thin sheet laser to excite the marked water molecule decomposition products; and to record the excitation process of the marked water molecule decomposition products to obtain image data and time data; and calculate the speed information of the marked line based on the image data and time data;

[0008] The control module is used to perform timing control on the two-dimensional static temperature measurement module and the linear velocity measurement module, and to calculate the total temperature and Mach number measurement results in the two-dimensional plane of the supersonic combustion flow field based on the static temperature measurement results of the plane area and the velocity information of the marking line.

[0009] The present invention obtains the static temperature distribution in the two-dimensional parallelogram network area by means of multi-optical network emission-detection. In the area where the static temperature distribution is obtained, another spatial laser marks the combustion intermediate products in the flow field to record the flow field velocity on the marked line segment. On the basis of simultaneously obtaining the static temperature and velocity of the flow field, according to the relationship between the static temperature, velocity, sound velocity, total temperature and Mach number of the gas, an optical test system for synchronously obtaining the line distribution of the total temperature and Mach number in the two-dimensional plane of the supersonic combustion flow field is provided for a supersonic air-breathing engine.

[0010] Preferably, the two-dimensional static temperature measurement module comprises: a first laser group, a second laser group, a first detector group, a second detector group, a laser controller, an industrial computer and a monitor;

[0011] The laser controller is used to control the first laser group and the second laser group. The first laser group is used to emit a number of parallel lasers of a fixed band that can be absorbed by the measured object, and the first detector group is used to receive laser spectrum information after the laser emitted by the first laser group is absorbed by the measured object; the second laser group is used to emit a number of parallel lasers of a fixed band that can be absorbed by the measured object, and the second detector group is used to receive laser spectrum information after the laser emitted by the second laser group is absorbed by the measured object; the industrial computer is used to record and process the collected laser spectrum information, and calculate the static temperature measurement result of the plane area of ​​the measured object; the monitor is used to monitor the laser spectrum information and data post-processing in real time.

[0012] Preferably, the first laser group and the second laser group each include N lasers arranged in parallel, and the first detector group and the second detector group each include N detectors arranged in parallel; the first laser group and the second laser group each emit N parallel laser beams, wherein any laser beam emitted by the first laser group intersects with the N laser beams emitted by the second laser group, and all intersection points of the lasers emitted by the first laser group and the lasers emitted by the second laser group are located in the same plane, and N is an integer greater than 1.

[0013] Preferably, the linear velocity measurement module comprises: a 193nm excimer laser, a YAG laser, a Dye laser, a first focusing lens group, a sheet light lens group, an oscilloscope, an ICCD and a computer;

[0014] The 193nm excimer laser is used to generate a pulse laser with a central wavelength of 193nm, and the pulse laser is used to mark the spatial position of the water molecule; the YAG laser is used to generate a pulse laser with a central wavelength of 532nm; the Dye laser is used to process the pulse laser in the 532nm band and output a pulse laser with a central wavelength of 282nm, and the pulse laser is used to excite the decomposition products of the marked water molecules; the first focusing lens group focuses the 193nm band pulse laser, and the focused 193nm band pulse laser is emitted to the center of the plane area corresponding to the measurement object; the sheet light lens group is used to process the 282nm band pulse laser to form a thin sheet laser in the area where the measurement object is located; the ICCD is used for imaging, and the material marked by the 193nm band pulse laser is excited by the 282nm band pulse laser and recorded at a known time point; the oscilloscope is used to visualize the timing relationship between the 193nm band pulse laser, the 282nm band pulse laser and the ICCD; the computer is used to calculate the speed information of the marking line based on the data recorded by the ICCD and the time data.

[0015] Preferably, the linear velocity measurement module also includes: a first total reflection mirror, a second total reflection mirror and a second focusing mirror group; the pulse laser with a central wavelength of 193nm generated by the 193nm excimer laser is reflected by the first total reflection mirror and then emitted into the first focusing mirror group; the pulse laser with a central wavelength of 282nm output by the Dye laser is reflected by the second total reflection mirror and then emitted into the second focusing mirror group, and the 282nm band pulse laser is focused by the second focusing mirror group and then emitted into the sheet light mirror group.

[0016] Preferably, the control module includes: a timing controller and a processor; the timing controller is used to perform timing control on the two-dimensional static temperature measurement module and the linear velocity measurement module, and the processor is used to calculate and obtain the total temperature and Mach number measurement results in the two-dimensional plane of the supersonic combustion flow field.

[0017] Preferably, according to the relationship between the static temperature, velocity, sonic velocity, total temperature and Mach number of the gas, the following calculation formula is used to calculate the total temperature and Mach number in the two-dimensional plane of the supersonic combustion flow field:

[0018]

[0019] T * =T·(1+0.165·Ma 2 );

[0020] Where c is the speed of sound, T is the static temperature, Ma is the Mach number, V is the speed, T * is the total temperature.

[0021] One or more technical solutions provided by the present invention have at least the following technical effects or advantages:

[0022] The present invention provides an optical test system for synchronously acquiring the dual-parameter line distribution of the total temperature and Mach number of the combustion flow field. The most significant features are: it realizes non-contact measurement, has no interference with the flow field itself, can acquire flow field information without disturbing the flow field, and has accurate measurement results; it realizes line measurement, effectively expands the traditional point measurement, makes it possible to identify the position of the thermal throat of the engine which cannot be achieved by point measurement, and can simultaneously measure the Mach number and total temperature in the two-dimensional plane of the supersonic combustion flow field.

[0023] The present invention also provides a test method for an optical test system for synchronously acquiring the total temperature and Mach number line distribution of a combustion flow field, the method comprising:

[0024] Step 1: Build the test system;

[0025] Step 2: Connect the components in the test system;

[0026] Step 3: Turn on the equipment in the test system;

[0027] Step 4: Adjust the relative position between the first laser group and the first detector group so that the four laser signals can be detected by the corresponding detectors;

[0028] Step 5: Adjust the relative position between the second laser group and the second detector group so that the four laser signals can be detected by the corresponding detectors and are coplanar with the first laser group and the first detector group;

[0029] Step 6: Turn on the 193nm excimer laser, adjust the first total reflection mirror and the first focusing lens group, focus the laser at the measured position of the flow field, and make the 193 laser coplanar with the network laser of step 4 and step 5 when passing through the flow field;

[0030] Step 7: Turn on the Nd:YAG laser and the Dye laser to make them emit light normally. Adjust the second total reflection mirror, the second focusing lens group and the light sheet lens to focus the light sheet at the measured position of the flow field, and make the light sheet and the 193nm laser coplanar at the measured position of the flow field;

[0031] Step 8: Use an oscilloscope and computer to check the timing relationship between 193nm laser emission and ICCD acquisition, 282nm laser, and near-infrared laser, and adjust them to meet Figure 2 The temporal relationship of

[0032] Step 9: After debugging, start the test;

[0033] Step 10: Adjust each module in the system to standby mode;

[0034] Step 11: Turn on the test environment module and send a test start signal to the timing controller;

[0035] Step 12: Each component is triggered and signals are collected according to the preset timing;

[0036] Step 13: After the test, check the original signal;

[0037] Step 14: Result processing and analysis.

[0038] One or more technical solutions provided by the present invention have at least the following technical effects or advantages:

[0039] The present invention provides an optical test system and test method for synchronously obtaining the dual-parameter line distribution of the total temperature and Mach number of the combustion flow field. The most significant features are: non-contact measurement is realized, and there is no interference with the flow field itself. The flow field information can be obtained without disturbing the flow field, and the measurement results are accurate; line measurement is realized, and traditional point measurement is effectively expanded, making it possible to identify the position of the engine thermal throat that cannot be achieved by point measurement, and the Mach number and total temperature in the two-dimensional plane of the supersonic combustion flow field can be measured simultaneously.

[0040] The invention can realize the measurement of Mach number and total temperature on a space line in supersonic combustion flow. BRIEF DESCRIPTION OF THE DRAWINGS

[0041] 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;

[0042] Figure 1 Schematic diagram of the optical test system for synchronously acquiring the total temperature and Mach number line distribution of the combustion flow field;

[0043] Figure 2 It is a schematic diagram of the timing relationship of each component within a pulse time;

[0044] Figure 3 This is a schematic diagram of the measurement location of the test site;

[0045] Figure 4 for Figure 2 Schematic diagram of test results of measuring position velocity;

[0046] Figure 5 for Figure 2 Schematic diagram of test results of static temperature distribution at the measurement position shown;

[0047] Figure 6 for Figure 2 Schematic diagram of test results of Mach number distribution at the measurement position shown;

[0048] Figure 7 for Figure 2 Schematic diagram of the test results of the total temperature distribution at the measurement position shown;

[0049] Among them, 1-YAG laser, 2-Dye laser, 3-second total reflection mirror, 4-second detector group, 5-second focusing lens, 6-light mirror group, 7-supersonic combustion gas flow, 8-timing controller, 9-oscilloscope, 10-computer, 11-ICCD, 12-193nm excimer laser, 13-first laser group, 14-first total reflection mirror, 15 first focusing lens, 16-first detector group, 17-monitor, 18-industrial computer, 19-second laser group, 20-laser controller. DETAILED DESCRIPTION

[0050] 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.

[0051] 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.

[0052] Embodiment 1;

[0053] Embodiment 1 of the present invention provides an optical test system for synchronously acquiring the total temperature and Mach number line distribution of a combustion flow field, the system comprising:

[0054] The measurement object is a supersonic gas flow field, which is generated by a supersonic gas flow 7;

[0055] A two-dimensional static temperature measurement module, used to generate and control laser light that can be absorbed by the object being measured, receive spectrum information of the laser light after being absorbed by the object being measured, and obtain a static temperature measurement result of a planar area of ​​the object being measured based on the spectrum information of the laser light;

[0056] A linear velocity measurement module is used to generate a pulsed laser, focus the pulsed laser and mark the spatial position of the water molecules to obtain a marked line; and to obtain a thin sheet laser, and use the thin sheet laser to excite the marked water molecule decomposition products; and to record the excitation process of the marked water molecule decomposition products to obtain image data and time data; and calculate the speed information of the marked line based on the image data and time data;

[0057] The control module is used to perform timing control on the two-dimensional static temperature measurement module and the linear velocity measurement module, and to calculate the total temperature and Mach number measurement results in the two-dimensional plane of the supersonic combustion flow field based on the static temperature measurement results of the plane area and the velocity information of the marking line.

[0058] The principle of the system mentioned in the present invention is as follows Figure 1 As shown, it includes: a measurement object, a two-dimensional static temperature measurement module, a linear velocity measurement module and a control module. The specific composition is as follows: the measurement object is a supersonic gas flow field. If the flow field is a confined space, it is necessary to design a window for the area where the laser is to pass through, and use quartz glass to replace the original opaque structure so that the laser can effectively pass through the measured flow field area; if the measured flow field is an open space, no window is required.

[0059] The two-dimensional static temperature measurement module includes a first laser group 13, a second laser group 19, a first detector group 16, a second detector group 4, a laser controller 20, an industrial computer 18 and a monitor 17. The two laser groups are used to generate lasers of a fixed wavelength band that can be absorbed by specific components of the measured flow field; the two detector groups are used to receive the laser spectrum information after being absorbed by specific components of the flow field; the laser controller is used to control the laser to output lasers within a certain wavelength range, at a certain frequency, range and intensity; the industrial computer is used to record and process the collected signals; and the monitor is used to monitor the signal characteristics and data post-processing in real time.

[0060] Wherein, in actual application, the laser group includes 4 parallel lasers, the detector group includes 4 parallel detectors, the number of lasers and detectors can be designed according to actual needs, the first laser group and the second laser group each include 4 parallel lasers, the first detector group and the second detector group each include 4 parallel detectors; the first laser group and the second laser group each emit 4 parallel laser beams, wherein any laser beam emitted by the first laser group intersects with the 4 laser beams emitted by the second laser group, and all intersection points of the laser beam emitted by the first laser group and the laser beam emitted by the second laser group are located in the same plane, such as Figure 1 The plane area composed of the 16 intersection points shown in the figure, the static temperature of the flow field in this area can be obtained by Figure 1 The absorption signals of the laser by the combustion flow field components on 8 optical paths are calculated and inverted. The specific calculation method can adopt the existing flow field static temperature calculation method in the art, and the embodiment of the present invention does not specifically limit it. During the test, the laser controller is used to control the time and frequency of the laser light emission, and to exchange signals with the industrial computer, so that the industrial computer can synchronize the photoelectric signal collection at the end of the detector with the laser.

[0061] The 4*4-path design is to form a spatial network. In the same measured area, the denser the optical paths are, the more accurate the temperature measurement results are. The spatial network is formed by the first laser group, the second laser group, the first detector group 16, and the second detector group 4; the first laser group, the second laser group, the first detector group, and the second detector group do not interfere with or block each other in structure.

[0062] The linear velocity measurement module includes: a 193nm excimer laser 12, a YAG laser 1, a Dye laser 2, a first focusing lens group, a sheet light lens group 6, a computer 10ICCD 11 and an oscilloscope 9.

[0063] The 193nm excimer laser is used to generate a pulsed laser with a central wavelength of 193nm, which is used to mark the spatial position of water molecules; the YAG laser is used to generate a pulsed laser with a central wavelength of 532nm; the Dye laser converts the laser in the 532nm band, that is, converts the wavelength to obtain a 282nm laser, which can excite the decomposition products of water, and outputs a pulsed laser with a central wavelength of 282nm, which excites the decomposition products (OH) of the marked water molecules; the first focusing lens group focuses the 193nm band laser to increase the laser intensity in the unit space, so that the marking efficiency is improved. High; the sheet light mirror group focuses the 282nm band laser in one direction and stretches it in another perpendicular direction, such as focusing in a preset direction, which is toward the center of the measured area, and stretching it perpendicular to the preset direction, so that the 282nm laser forms a thin sheet of laser in the measured area of ​​the flow field; ICCD is used for imaging, and the material marked with 193nm laser is excited by 282nm laser and recorded at a known time point; the oscilloscope is used to visualize the timing relationship between the 193nm laser, the 282nm laser and the ICCD, and the computer is used to calculate the speed information of the marked line based on the data recorded by the ICCD and the time data.

[0064] During the test, the 193nm excimer laser generates a narrow linewidth high-energy laser with a central wavelength of 193nm. After passing through the first total reflection mirror 14 and the first focusing lens 15, a high-energy-density laser thread is formed in the plane of the parallelogram area of ​​the static temperature measurement. According to the focusing lens principle, the thread is a waist-type structure. The laser space energy density is the highest at the midpoint of the waist and decreases toward both ends. In a certain area, the water molecules in the flow field can be decomposed into OH groups and H ions by the high-energy-density 193nm laser. At this time, the water molecules at this position in the flow field are marked by the 193nm laser. The YAG laser generates a 532nm laser. After passing through the Dye fuel laser, the 532nm laser is converted into a 282nm laser. After passing through the second total reflection mirror 3 and the second focusing lens 5, the laser is stretched in one direction by the sheet light mirror group, thereby forming a thin sheet laser entering the flow field. By adjusting the mirror frames and installation positions of each lens and reflector, the sheet light passes through the plane where the 193nm laser and the 4×4 network area are located. After the 193nm laser marks the water molecules for a period of time (about 100 microseconds), the 282nm laser passes through the flow field, and the OH groups in the flow field are excited by the 282nm laser, and their energy state jumps to the excited state. The excited OH emits a fixed wavelength spectrum in the process of returning to the ground state and is recorded by the ICCD. The speed is calculated by the movement displacement of the marked substance and the specific time. The control module includes a timing controller 8 and a processor. During the test, the timing controller controls the working time of the devices connected to it. The timing controller sends electrical signals to each component to achieve the purpose of controlling the actuation of each component. The control timing is as follows Figure 2 As shown, an oscilloscope is used to check the timing of the operation of each component, the processor records and presents the image information of the OH spatial distribution of the calculation speed, and records and processes the data of the temperature measurement module.

[0065] The present invention is Figure 3 The supersonic jet flame shown in the figure was measured from left to right. Figure 3 (a) shows the original image of the measured object and the 0 point position, x direction, and y direction. Figure 3 (b) shows the optical path diagram of the absorption spectrum network temperature measurement and velocity measurement. From the brightness distribution of the gas, it can be found that a series of Mach disks distributed along the flow direction can be used to determine that the jet flame is in a supersonic flow state. Due to the combustion chemical reaction, Figure 3 (b) There is H2O in the middle position. Figure 3 The 193 nm laser from bottom to top dissociates H2O into OH and H( Figure 2 At t0 as shown in the figure, the 282nm light from the lower left to the upper right excites OH to a state that can be recorded by ICCD ( Figure 2 At the moment t1 shown); when the 193nm laser is triggered, Figure 3(b) The signal of H2O is absorbed by the networked mid-infrared laser and recorded by the photodetector ( Figure 2 time t0 as shown).

[0066] Figure 4 The velocity of the measured flow field recorded by 193nm laser and 282nm laser in the time t1-t0 is given. At t0, 193nm laser acts on H2O to produce OH, and at t1, 282nm laser records the position of OH. The velocity can be calculated by the time difference and the displacement at the two moments. Figure 3 The velocity distribution in the vertical direction from 12.9 mm to 23.6 mm is as follows: Figure 4 As shown, the average flow velocity is 671.7 m / s.

[0067] Figure 5 The temperature distribution on the diamond network plane obtained by networking the mid-infrared laser absorption spectrum of H2O is given, and the temperature on the 193nm laser optical path is extracted. Its distribution is shown in the figure. The average temperature on this optical path is 918K.

[0068] According to the calculation formula of the sonic velocity of the gas, the calculation formula of the Mach number, and the relationship between the total temperature and the static temperature, the total temperature calculation process of the measured area is as follows:

[0069]

[0070] T * =T·(1+0.165·Ma 2 )(3)

[0071] In formula (1), c is the speed of sound, T is the static temperature, in formula (2), Ma is the Mach number, V is the speed, and in formula (3), T * is the total temperature. Through calculation, the Mach number and total temperature distribution of the measured area are obtained as follows: Figure 6 and Figure 7 shown.

[0072] Embodiment 2:

[0073] On the basis of the first embodiment, the present invention also provides a second embodiment of a test method for an optical test system for synchronously acquiring the total temperature and Mach number line distribution of a combustion flow field, the method comprising:

[0074] Step 1: Build the test system;

[0075] Step 2: Connect the components in the test system;

[0076] Step 3: Turn on the equipment in the test system;

[0077] Step 4: Adjust the relative position between the first laser group and the first detector group so that the four laser signals can be detected by the corresponding detectors;

[0078] Step 5: Adjust the relative position between the second laser group and the second detector group so that the four laser signals can be detected by the corresponding detectors and are coplanar with the first laser group and the first detector group;

[0079] Step 6: Turn on the 193nm excimer laser, adjust the first total reflection mirror and the first focusing lens group, focus the laser at the measured position of the flow field, and make the 193 laser coplanar with the network laser of step 4 and step 5 when passing through the flow field;

[0080] Step 7: Turn on the Nd:YAG laser and the Dye laser to make them emit light normally. Adjust the second total reflection mirror, the second focusing lens group and the light sheet lens group to focus the light sheet at the measured position of the flow field, and make the light sheet and the 193nm laser coplanar at the measured position of the flow field;

[0081] Step 8: Use an oscilloscope and computer to check the timing relationship between 193nm laser emission and ICCD acquisition, 282nm laser, and near-infrared laser, and adjust them to meet Figure 2 The temporal relationship of

[0082] Step 9: After debugging, start the test;

[0083] Step 10: Adjust each module in the system to standby mode;

[0084] Step 11: Turn on the test environment module and send a test start signal to the timing controller;

[0085] Step 12: Each component is triggered and signals are collected according to the preset timing;

[0086] Step 13: After the test, check the original signal;

[0087] Step 14: Result processing and analysis.

[0088] 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.

[0089] 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. An optical test system for synchronously acquiring the total temperature and Mach number line distribution of the combustion flow field, characterized in that: The system comprises: Measurement object: the measurement object is the supersonic gas flow field; A two-dimensional static temperature measurement module, used to generate and control laser light that can be absorbed by the object being measured, receive spectrum information of the laser light after being absorbed by the object being measured, and obtain a static temperature measurement result of a planar area of ​​the object being measured based on the spectrum information of the laser light; A linear velocity measurement module is used to generate a pulsed laser, focus the pulsed laser and mark the spatial position of the water molecules to obtain a marked line; and to obtain a thin sheet laser, and use the thin sheet laser to excite the marked water molecule decomposition products; and to record the excitation process of the marked water molecule decomposition products to obtain image data and time data; and calculate the speed information of the marked line based on the image data and time data; The control module is used to perform timing control on the two-dimensional static temperature measurement module and the linear velocity measurement module, and to calculate the total temperature and Mach number measurement results in the two-dimensional plane of the supersonic combustion flow field based on the static temperature measurement results of the plane area and the velocity information of the marking line.

2. The optical test system for synchronously acquiring the total temperature and Mach number line distribution of the combustion flow field according to claim 1 is characterized in that: The two-dimensional static temperature measurement module includes: a first laser group, a second laser group, a first detector group, a second detector group, a laser controller, an industrial computer and a monitor; The laser controller is used to control the first laser group and the second laser group. The first laser group is used to emit a number of parallel lasers of a fixed band that can be absorbed by the measured object, and the first detector group is used to receive laser spectrum information after the laser emitted by the first laser group is absorbed by the measured object; the second laser group is used to emit a number of parallel lasers of a fixed band that can be absorbed by the measured object, and the second detector group is used to receive laser spectrum information after the laser emitted by the second laser group is absorbed by the measured object; the industrial computer is used to record and process the collected laser spectrum information, and calculate the static temperature measurement result of the plane area of ​​the measured object; the monitor is used to monitor the laser spectrum information and data post-processing in real time.

3. The optical test system for synchronously acquiring the total temperature and Mach number line distribution of the combustion flow field according to claim 2 is characterized in that: The first laser group and the second laser group each include N lasers arranged in parallel, and the first detector group and the second detector group each include N detectors arranged in parallel; the first laser group and the second laser group each emit N parallel laser beams, wherein any laser beam emitted by the first laser group intersects with the N laser beams emitted by the second laser group, and all intersection points of the laser beams emitted by the first laser group and the laser beams emitted by the second laser group are located in the same plane, and N is an integer greater than 1.

4. The optical test system for synchronously acquiring the total temperature and Mach number line distribution of the combustion flow field according to claim 1 is characterized in that: The linear velocity measurement module includes: 193nm excimer laser, YAG laser, Dye laser, first focusing lens group, sheet light lens group, oscilloscope, ICCD and computer; The 193nm excimer laser is used to generate a pulse laser with a central wavelength of 193nm, and the pulse laser is used to mark the spatial position of the water molecule; the YAG laser is used to generate a pulse laser with a central wavelength of 532nm; the Dye laser is used to process the pulse laser in the 532nm band and output a pulse laser with a central wavelength of 282nm, and the pulse laser is used to excite the decomposition products of the marked water molecules; the first focusing lens group focuses the 193nm band pulse laser, and the focused 193nm band pulse laser is emitted to the center of the plane area corresponding to the measurement object; the sheet light lens group is used to process the 282nm band pulse laser to form a thin sheet laser in the area where the measurement object is located; the ICCD is used for imaging, and the material marked by the 193nm band pulse laser is excited by the 282nm band pulse laser and recorded at a known time point; the oscilloscope is used to visualize the timing relationship between the 193nm band pulse laser, the 282nm band pulse laser and the ICCD; the computer is used to calculate the speed information of the marking line based on the data recorded by the ICCD and the time data.

5. The optical test system for synchronously acquiring the total temperature and Mach number line distribution of the combustion flow field according to claim 4 is characterized in that: The linear velocity measurement module also includes: a first total reflection mirror, a second total reflection mirror and a second focusing mirror group; the pulse laser with a central wavelength of 193nm generated by the 193nm excimer laser is reflected by the first total reflection mirror and then emitted into the first focusing mirror group; the pulse laser with a central wavelength of 282nm output by the Dye laser is reflected by the second total reflection mirror and then emitted into the second focusing mirror group, and the 282nm band pulse laser is focused by the second focusing mirror group and then emitted into the sheet light mirror group.

6. The optical test system for synchronously acquiring the total temperature and Mach number line distribution of the combustion flow field according to claim 1 is characterized in that: The control module includes: a timing controller and a processor; the timing controller is used to perform timing control on the two-dimensional static temperature measurement module and the linear velocity measurement module, and the processor is used to calculate and obtain the total temperature and Mach number measurement results in the two-dimensional plane of the supersonic combustion flow field.

7. The optical test system for synchronously acquiring the total temperature and Mach number line distribution of the combustion flow field according to claim 1 is characterized in that: The total temperature and Mach number in the two-dimensional plane of the supersonic combustion flow field are calculated as follows: T * =T·(1+0.165·Ma 2 ); Where c is the speed of sound, T is the static temperature, Ma is the Mach number, V is the speed, T * is the total temperature.

8. An optical test method for synchronously obtaining the total temperature and Mach number line distribution of the combustion flow field, characterized in that: The method comprises: Step 1: construct a test system as claimed in any one of claims 1 to 7; Step 2: Connect the components in the test system; Step 3: Turn on the equipment in the test system; Step 4: Adjust the relative position between the first laser group and the first detector group so that the laser signals can be detected by the corresponding detectors; Step 5: Adjust the relative position between the second laser group and the second detector group so that the laser signals can be detected by the corresponding detectors and are coplanar with the first laser group and the first detector group; Step 6: Turn on the 193nm excimer laser, adjust the first total reflection mirror and the first focusing lens group, focus the laser at the measured position of the flow field, and make the 193nm band pulse laser coplanar with the network laser of step 4 and step 5 when passing through the flow field; Step 7: Turn on the YAG laser and the Dye laser, adjust the second total reflection mirror, the second focusing lens group and the light sheet mirror group, focus the light sheet at the measured position of the flow field, and make the light sheet and the 193nm band pulse laser coplanar at the measured position of the flow field; Step 8: Use an oscilloscope and a computer to check the timing relationship between the 193nm pulse laser emission and ICCD acquisition, the 282nm pulse laser and the near-infrared laser, and adjust them to meet the corresponding timing relationship; Step 9: After debugging, start the test; Step 10: Adjust each module in the system to standby mode; Step 11: Turn on the test environment module and send a test start signal to the timing controller; Step 12: Each component is triggered and signals are collected according to the preset timing; Step 13: After the test, check the original signal; Step 14: Result processing and analysis.

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