Optical Test System and Test Method for Synchronously Obtaining Line Distributions of Total Temperature and Mach Number in Combustion Flow Field

Abstract

The present invention discloses an optical test system and a test method for synchronously obtaining the line distributions of total temperature and Mach number in a combustion flow field, which relates to the field of combustion flow field measurement and includes: a measurement object, which is a supersonic gas flow field; a two-dimensional static temperature measurement module, which is used to generate and control the laser that can be absorbed by the measurement object, receive the laser spectral information after being absorbed by the measurement object, and obtain the static temperature measurement result of the planar region of the measurement object based on the laser spectral information; a linear velocity measurement module, which is used to generate pulsed laser, focus the pulsed laser to mark the spatial position of water molecules to obtain a marked line; and is used to obtain a thin-sheet laser, and use the thin-sheet laser to excite the decomposition products of the marked water molecules; and is used to record the excitation process of the decomposition products of the marked water molecules to obtain image data and time data; calculate the velocity information of the marked line based on the image data and time data; a control module, which is used to perform timing control on the two-dimensional static temperature measurement module and the linear velocity measurement module, and is used to calculate the measurement results of total temperature and Mach number in the two-dimensional plane of the supersonic combustion flow field based on the static temperature measurement result of the planar region and the velocity information of the marked line. This system can simultaneously measure the Mach number and total temperature in the two-dimensional plane of the supersonic combustion flow field.

Description

Technical Field

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

[0002] In the field of supersonic combustion, the total temperature is an important parameter reflecting combustion efficiency and flow state. The capture of the Mach number distribution, especially the capture of the sonic line, is a necessary condition for accurately obtaining the position of the thermal throat of a scramjet engine. Synchronously obtaining the total temperature and total pressure at multiple points can effectively evaluate the overall performance of the engine. Currently, the test method for measuring the total temperature mainly uses a contact total temperature probe. This method has two characteristics. One is single-point measurement, and it is impossible to obtain the total temperature in a plane. The other is that it invades the flow field and destroys the supersonic flow structure. The moving probe, this contact method, has a very obvious impact on the supersonic flow field structure, which will cause unnecessary oblique shock waves, and then affect the flow and combustion states in the local area and downstream where the probe is located, resulting in inaccurate measurement results. There is a lack of an optical test system in the prior art that can simultaneously measure the Mach number and total temperature in the 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 total temperature in the two-dimensional plane of a supersonic combustion flow field.

[0004] To achieve the above object of the invention, the present invention provides an optical test system for synchronously obtaining the line distributions of total temperature and Mach number in a combustion flow field. The system includes:

[0005] A measurement object, which is a supersonic gas flow field;

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

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

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

[0009] Among them, the present invention obtains the static temperature distribution in a two-dimensional planar parallelogram networking area through a multi-optical-path networking emission-detection method. In the area where the static temperature distribution is obtained, the flow field velocity on the marked line segment is recorded by marking the combustion intermediate products in the flow field through another spatial laser. On the basis of simultaneously obtaining the static temperature and velocity of the flow field, according to the relationships among the static temperature, velocity, sound speed, total temperature and Mach number of the gas, an optical test system for synchronously obtaining the line distributions 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 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;

[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 plurality of parallel lasers with a fixed wavelength band that can be absorbed by the measurement object. The first detector group is used to receive the laser spectrum information after the laser emitted by the first laser group is absorbed by the measurement object. The second laser group is used to emit a plurality of parallel lasers with a fixed wavelength band that can be absorbed by the measurement object. The second detector group is used to receive the laser spectrum information after the laser emitted by the second laser group is absorbed by the measurement object. The industrial computer is used to record and process the collected laser spectrum information and calculate the static temperature measurement result of the planar area of the measurement object. The monitor is used to monitor the laser spectrum information and data post-processing in real time.

[0012] Preferably, both the first laser group and the second laser group include N lasers arranged in parallel. Both the first detector group and the second detector group include N detectors arranged in parallel. Both the first laser group and the second laser group emit N parallel lasers. Among them, any one laser emitted by the first laser group intersects with all N lasers emitted by the second laser group. All the 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 includes: a 193nm excimer laser, a YAG laser, a Dye laser, a first focusing lens group, a sheet light mirror group, an oscilloscope, an ICCD and a computer;

[0014] The 193nm excimer laser is used to generate pulsed laser with a central wavelength of 193nm, and this pulsed laser is used to mark the spatial position of water molecules; the YAG laser is used to generate pulsed laser with a central wavelength of 532nm; the Dye laser is used to process the pulsed laser in the 532nm band and output pulsed laser with a central wavelength of 282nm, and this pulsed laser is used to excite the decomposed products of the marked water molecules; the first focusing lens group focuses the pulsed laser in the 193nm band, and the focused pulsed laser in the 193nm band shoots towards the center of the corresponding planar area of the measurement object; the sheet light lens group is used to process the pulsed laser in the 282nm band to form a sheet laser in the area where the measurement object is located; the ICCD is used for imaging, and records the substances marked by the pulsed laser in the 193nm band after being excited by the pulsed laser in the 282nm band at known time points; the oscilloscope is used to visualize the timing relationship between the pulsed laser in the 193nm band, the pulsed laser in the 282nm band and the ICCD; the computer is used to calculate the velocity information of the marked line based on the data recorded by the ICCD and the time data.

[0015] Preferably, the linear velocity measurement module further includes: a first total reflection mirror, a second total reflection mirror and a second focusing lens group; the pulsed laser with a central wavelength of 193nm generated by the 193nm excimer laser is reflected by the first total reflection mirror and then enters the first focusing lens group; the pulsed laser with a central wavelength of 282nm output by the Dye laser is reflected by the second total reflection mirror and then enters the second focusing lens group, and the pulsed laser in the 282nm band enters the sheet light lens group after being focused by the second focusing lens 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 the measurement results of the total temperature and Mach number in the two-dimensional plane of the supersonic combustion flow field.

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

[0018]

[0019] T * = T · (1 + 0.165 · Ma 2 );

[0020] where c is the sound speed, T is the static temperature, Ma is the Mach number, V is the velocity, and 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 obtaining the line distributions of the total temperature and Mach number of a combustion flow field. Its greatest feature is that it realizes non-contact measurement, has no interference on the flow field itself, can obtain flow field information without disturbing the flow field, and the measurement results are accurate; it realizes line measurement, effectively expands the traditional point measurement, makes it possible to identify the position of the engine thermal throat that cannot be reached by point measurement, and can measure the Mach number and total temperature in the two-dimensional plane of the supersonic combustion flow field simultaneously.

[0023] The present invention also provides a test method for the optical test system for synchronously obtaining the line distributions of the total temperature and Mach number of a combustion flow field. The method includes:

[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 positions between the first laser group and the first detector group so that all four laser signals can be detected by the corresponding detectors;

[0028] Step 5: Adjust the relative positions between the second laser group and the second detector group so that all four laser signals can be detected by the corresponding detectors and make it 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 so that the laser is focused at the measured position in the flow field and make the 193 laser coplanar with the networked lasers in 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 sheet light lens so that the sheet light is focused at the measured position in the flow field and make the sheet light coplanar with the 193nm laser at the measured position in the flow field;

[0031] Step 8: Use an oscilloscope and a computer to view the timing relationship between the 193nm laser emission, ICCD acquisition, 282nm laser, and near-infrared laser, and adjust and make it meet Figure 2 the timing relationship;

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

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

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

[0035] Step 12: Each component triggers and acquires signals according to the preset timing;

[0036] Step 13: When the test ends, check the original signals;

[0037] Step 14: Process and analyze the results.

[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 a test method for synchronously obtaining the line distributions of the total temperature and Mach number of a combustion flow field. The most prominent feature is: realizing non-contact measurement, without interference to the flow field itself, being able to obtain flow field information without disturbing the flow field, and the measurement results are accurate; realizing line measurement, effectively expanding the traditional point measurement, making it possible to identify the position of the engine thermal throat that cannot be reached by point measurement, and being able to measure the Mach number and total temperature in the two-dimensional plane of the supersonic combustion flow field simultaneously.

[0040] The present invention can realize the measurement of the Mach number and total temperature on a spatial 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, form a part of the present invention, and do not limit the embodiments of the present invention;

[0042] Figure 1 It is a schematic diagram of the principle of an optical test system for synchronously obtaining the line distributions of the total temperature and Mach number of a 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 It is a schematic diagram of the measurement positions at the test site;

[0045] Figure 4 For Figure 2 It is a schematic diagram of the test results of the velocity at the indicated measurement position;

[0046] Figure 5 For Figure 2 It is a schematic diagram of the test results of the static temperature distribution at the indicated measurement position;

[0047] Figure 6 For Figure 2 It is a schematic diagram of the test results of the Mach number distribution at the indicated measurement position;

[0048] Figure 7 ForFigure 2 Schematic diagram of the test results of the total temperature distribution at the measured positions 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 sheet mirror group, 7 - supersonic gas incoming 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 control computer, 19 - second laser group, 20 - laser controller. Specific implementation manners

[0050] In order to more clearly understand the above objects, features and advantages of the present invention, the present invention will be further described in detail below in conjunction with the drawings and specific implementation manners. It should be noted that, without conflict, the embodiments of the present invention and the features in the embodiments can be combined with each other.

[0051] In the following description, many specific details are set forth in order to fully understand the present invention. However, the present invention can also be implemented in other ways different from those described herein. Therefore, the protection scope of the present invention is not limited by the specific embodiments disclosed below.

[0052] Embodiment 1

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

[0054] A measurement object, which is a supersonic gas flow field generated by a supersonic gas incoming flow 7.

[0055] A two - dimensional static temperature measurement module, which is used to generate and control the laser that can be absorbed by the measurement object, receive the laser spectrum information after being absorbed by the measurement object, and obtain the static temperature measurement result of the plane area of the measurement object based on the laser spectrum information.

[0056] A linear velocity measurement module, which is used to generate pulsed laser, focus the pulsed laser to mark the spatial position of water molecules to obtain a marked line; and is used to obtain a thin - sheet laser, and use the thin - sheet laser to excite the decomposition products of the marked water molecules; and is used to record the excitation process of the decomposition products of the marked water molecules to obtain image data and time data; and calculate the velocity 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-way * 4-way design is for forming a spatial network. In the same area under test, the denser the optical paths, the more accurate the temperature measurement results. A 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 structurally.

[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 mirror group 6, a computer 10, an ICCD 11, and an oscilloscope 9.

[0063] The 193nm excimer laser is used to generate pulsed laser with a central wavelength of 193nm, and this laser is used to mark the spatial position of water molecules; the YAG laser is used to generate 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 282nm laser. The laser of this wavelength can excite the decomposition products of water, and outputs pulsed laser with a central wavelength of 282nm, and this laser excites the decomposed products (OH) of the marked water molecules; the first focusing lens group focuses the laser in the 193nm band to increase the laser intensity per unit space and improve the marking efficiency; the sheet light mirror group focuses the 282nm band laser in a single direction and stretches it in another perpendicular direction, such as focusing towards a preset direction, the preset direction is towards the center direction of the area under test, and stretches perpendicular to the preset direction, so that the 282nm laser forms a thin sheet laser in the flow field area under test; the ICCD is used for imaging, and records the substances marked by the 193nm laser after being excited by the 282nm laser at known time points; 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 velocity information of the marked line based on the data recorded by the ICCD and the time data.

[0064] During the experiment, a 193 nm excimer laser generates high-energy laser with a narrow linewidth and a central wavelength of 193 nm. After passing through the first total reflection mirror 14 and the first focusing lens 15, a high-energy density laser filament is formed in the plane of the parallelogram region for static temperature measurement. According to the focusing lens principle, this filament has a waist-type structure, and the spatial energy density of the laser is the highest at the midpoint of the waist and decreases towards both ends. In a certain region, water molecules in the flow field can be decomposed into OH radicals and H ions by the 193 nm laser with a high energy density. At this time, the water molecules at this position in the flow field are marked at the initial position by the 193 nm laser. The YAG laser generates a laser of 532 nm. After passing through the Dye laser, the 532 nm laser is converted into a 282 nm laser. This laser passes through the second total reflection mirror 3 and the second focusing lens 5 and then is unidirectionally stretched by the light sheet mirror group, and then a thin sheet of laser enters the flow field. By adjusting the mirror frames of each lens and mirror and their installation positions, the light sheet passes through the plane where the 193 nm laser and the 4×4 networking region are located. After the 193 nm laser marks the water molecules for a period of time (about a hundred microseconds), the 282 nm laser passes through the flow field. The OH radicals in the flow field are excited by the 282 nm laser, and their energy states jump to the excited state. The excited OH emits a spectrum with a fixed wavelength during the process of returning to the ground state and is recorded by the ICCD. The velocity is calculated based on the movement displacement and specific time of the marked substance. The control module includes a timing controller 8 and a processor. During the experiment, 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 Figure 2 shown. The oscilloscope is used to check the timing of each component's operation. The processor records and presents the image information of the OH spatial distribution for calculating the velocity and records and processes the data of the temperature measurement module.

[0065] The present invention has carried out measurement experiments on the Figure 3 supersonic jet flame flowing from left to right as shown, Figure 3 in which (a) shows the original image of the measurement object, the 0 point position, the x direction, and the y direction. Figure 3 In (b), the optical path schematic for temperature measurement by absorption spectrum networking and the optical path schematic for velocity measurement are given. From the brightness distribution of the fuel gas, a series of Mach disks distributed along the flow direction can be found, indicating that the jet flame is in a supersonic flow state. Due to the combustion chemical reaction, Figure 3 H2O exists at the middle measured position shown in (b), Figure 3 and the 193 nm laser from bottom to top in it dissociates H2O into OH and H ( Figure 2 at the t0 moment shown), and the 282 nm light sheet from bottom left to top right in the figure excites OH to a state that can be recorded by the ICCD ( Figure 2 at the t1 moment shown); at the same time when the 193 nm laser is triggered, Figure 3(b) The signal of the mid-infrared band laser absorbing H2O formed by networking in the figure is recorded by a photodetector ( Figure 2 at the moment t0 shown in the figure).

[0066] Figure 4 The velocity of the measured flow field within the time period from t1 to t0 recorded by the 193nm laser and the 282nm laser is given. At the moment t0, the 193nm laser acts on H2O to generate OH. At the moment t1, the 282nm laser records the position of OH. The velocity can be calculated through the time difference and the displacements at the two moments. During the experiment, the Figure 3 velocity within the vertical region from 12.9mm to 23.6mm is recorded. The velocity distribution is as Figure 4 shown in the figure, and the average velocity of the flow field is 671.7m / s.

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

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

[0069]

[0070] T * = T·(1 + 0.165·Ma 2 )(3)

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

[0072] Example 2;

[0073] Based on Example 1, the present invention also provides, in Example 2, an experimental method for an optical experimental system that synchronously obtains the line distributions of the total temperature and Mach number of a combustion flow field. The method includes:

[0074] Step 1: Set up the experimental system;

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

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

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

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

[0079] Step 6: Turn on the 193 nm excimer laser, adjust the first total reflection mirror and the first focusing lens group so that the laser is focused at the measured position of the flow field and make the 193 laser coplanar with the network lasers in Steps 4 and 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 sheet light mirror group so that the sheet light is focused at the measured position of the flow field and make the sheet light coplanar with the 193 nm laser at the measured position of the flow field;

[0081] Step 8: Use an oscilloscope and a computer to view the timing relationship between the emission of the 193 nm laser, the ICCD acquisition, the 282 nm laser, and the near-infrared laser, and adjust and make it meet Figure 2 the timing relationship;

[0082] Step 9: End the debugging and start the experiment;

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

[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: End the experiment and check the original signals;

[0087] Step 14: Result processing and analysis.

[0088] Although the preferred embodiments of the present invention have been described, those skilled in the art can make additional changes and modifications once they learn the basic creative concepts. Therefore, the appended claims are intended to be construed to include the preferred embodiments as well as all changes and modifications falling 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 equivalent technologies, the present invention is also intended to include these modifications and variations.

Claims

1. An optical test system for synchronously acquiring the line distributions of total temperature and Mach number of a combustion flow field, characterized in that, The system includes: A measurement object, which is a supersonic gas flow field; A two-dimensional static temperature measurement module, which is used to generate and control the laser that can be absorbed by the measurement object, receive the laser spectral information after being absorbed by the measurement object, and obtain the static temperature measurement result of the planar region of the measurement object based on the laser spectral information; A linear velocity measurement module, which is used to generate pulsed laser, focus the pulsed laser to mark the spatial position of water molecules to obtain a marked line; and is used to obtain a thin-sheet laser, and use the thin-sheet laser to excite the decomposition products of the marked water molecules; and is used to record the excitation process of the decomposition products of the marked water molecules to obtain image data and time data; calculate and obtain the velocity information of the marked line based on the image data and time data; A control module, which is used to perform timing control on the two-dimensional static temperature measurement module and the linear velocity measurement module, and 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 based on the static temperature measurement result of the planar region and the velocity information of the marked line.

2. The optical test system for synchronously obtaining the line distributions of total temperature and Mach number of a combustion flow field according to claim 1, wherein 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 control 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 several parallel lasers of a fixed wavelength band that can be absorbed by the measurement object. The first detector group is used to receive the laser spectral information after the laser emitted by the first laser group is absorbed by the measurement object. The second laser group is used to emit several parallel lasers of a fixed wavelength band that can be absorbed by the measurement object. The second detector group is used to receive the laser spectral information after the laser emitted by the second laser group is absorbed by the measurement object. The industrial control computer is used to record and process the collected laser spectral information, and calculate and obtain the static temperature measurement result of the planar region of the measurement object. The monitor is used to monitor the laser spectral information and data post-processing in real time.

3. The optical test system for synchronously obtaining the line distribution of total temperature and Mach number of a combustion flow field according to claim 2, characterized in that, Both the first laser group and the second laser group include N lasers arranged in parallel. Both the first detector group and the second detector group include N detectors arranged in parallel. Both the first laser group and the second laser group emit N parallel lasers. Among them, any one laser emitted by the first laser group intersects with all N lasers emitted by the second laser group. All the 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.

4. The optical test system for synchronously obtaining the line distributions of total temperature and Mach number of a combustion flow field according to claim 1, wherein The linear velocity measurement module includes: a 193nm excimer laser, a YAG laser, a Dye laser, a first focusing lens group, a sheet light mirror group, an oscilloscope, an ICCD, and a computer; The 193nm excimer laser is used to generate pulsed laser with a central wavelength of 193nm, and this pulsed laser is used to mark the spatial position of water molecules; the YAG laser is used to generate pulsed laser with a central wavelength of 532nm; the Dye laser is used to process the pulsed laser in the 532nm band and output pulsed laser with a central wavelength of 282nm, and this pulsed laser is used to excite the decomposed products of the marked water molecules; the first focusing lens group focuses the pulsed laser in the 193nm band, and the focused pulsed laser in the 193nm band shoots towards the center of the corresponding planar area of the measurement object; the sheet light mirror group is used to process the pulsed laser in the 282nm band to form a sheet laser in the area where the measurement object is located; the ICCD is used for imaging, and records the substances marked by the pulsed laser in the 193nm band after being excited by the pulsed laser in the 282nm band at known time points; the oscilloscope is used to visualize the timing relationship between the pulsed laser in the 193nm band, the pulsed laser in the 282nm band and the ICCD; the computer is used to calculate and obtain the velocity information of the marked line based on the data recorded by the ICCD and the time data.

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

6. The optical test system for synchronously obtaining the line distributions of total temperature and Mach number of a combustion flow field according to claim 1, 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 line velocity measurement module, and the processor is used to calculate and obtain the measurement results of the total temperature and Mach number in the two-dimensional plane of the supersonic combustion flow field.

7. The optical test system for synchronously obtaining the line distribution of total temperature and Mach number of a combustion flow field according to claim 1, characterized in that, The calculation methods of the total temperature and Mach number in the two-dimensional plane of the supersonic combustion flow field are 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 velocity, and T * is the total temperature.

8. An optical test method for synchronously obtaining the line distributions of total temperature and Mach number in a combustion flow field, characterized in that, The method includes: Step 1: Build the test system described in any one of claims 1-7. Step 2: Connect the components in the test system. Step 3: Turn on the equipment in the test system. Step 4: Adjust the relative positions between the first laser group and the first detector group so that the laser signals can all be detected by the corresponding detectors. Step 5: Adjust the relative positions between the second laser group and the second detector group so that the laser signals can all be detected by the corresponding detectors, and make it 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 so that the laser is focused at the measured position in the flow field, and make the pulsed laser in the 193nm band coplanar with the networked laser in steps 4 and 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 sheet light mirror group so that the sheet light is focused at the measured position in the flow field, and make this sheet light coplanar with the pulsed laser in the 193nm band at the measured position in the flow field. Step 8: Use an oscilloscope and a computer to view the timing relationship between the output of the 193 nm pulsed laser, ICCD acquisition, the 282 nm pulsed laser, and the near-infrared laser, and adjust it to meet the corresponding timing relationship; Step 9: After the debugging is completed, start the experiment; Step 10: Adjust each module in the system to the standby state; Step 11: Turn on the experimental environment module and send a test start signal to the timing controller; Step 12: Each component triggers and acquires signals according to the preset timing; Step 13: After the experiment is completed, check the original signals; Step 14: Result processing and analysis.

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