Synchronous measurement system and method for pneumatic pressure, temperature and shape on surface of static model

Abstract

The invention relates to the technical field of optical flow testing, in particular to a static model surface pneumatic pressure, temperature and shape synchronous measuring system and method.The method comprises the steps that a two-component coating is sprayed on the surface of a model to be measured, and mark points are arranged; respectively acquiring a first light-emitting image and a second light-emitting image corresponding to temperature-sensitive molecules and pressure-sensitive molecules in the double-component coating, and acquiring reference pressure and reference temperature; acquiring corresponding shapes and deformation information of the to-be-tested model during blowing and non-blowing; acquiring a first light intensity ratio containing temperature information and a second light intensity ratio containing pressure information; obtaining corresponding relative light intensity distribution diagrams of bimolecules in the two-component coating at different temperatures and pressures; and acquiring the pressure and temperature of the surface of the to-be-measured model. According to the invention, the global pneumatic pressure and temperature of the surface of the model and the shape under the pneumatic working condition can be synchronously measured, and the pressure of the surface of the model is accurately measured on the basis of considering the temperature.

Description

Technical Field

[0001] The present invention relates to the technical field of optical flow measurement, and particularly relates to a system and method for synchronously measuring aerodynamic pressure, temperature, and shape on the surface of a stationary model. Background Art

[0002] In the field of aerodynamic experiments, parameters such as pressure, temperature, and velocity are basic thermodynamic parameters, and the acquisition of their experimental data is of great significance for the aerodynamic performance evaluation and design of the model.

[0003] The experimental testing technologies corresponding to temperature measurement and pressure measurement can be divided into two categories: contact type and non-contact type. Among them, contact type technologies such as pressure sensors, pressure measurement holes, thermocouples, and thermal resistors can only measure a single parameter. However, temperature and pressure usually change synchronously with the flow field at the local area of the model. Therefore, contact type measurement technologies cannot provide multi-source data that are synchronous in the time domain, which is not conducive to the performance evaluation of the model in the unsteady aerodynamic flow field. Non-contact testing technologies mainly rely on optical flow display and testing technologies. Among them, pressure sensitive paint (PSP) pressure measurement technology, temperature sensitive paint (TSP) temperature measurement technology, infrared temperature measurement technology, etc. are several typical non-contact optical testing technologies. They all have the advantages of global measurement, high spatial resolution, and non-invasive measurement, and can obtain wall temperature and pressure without modifying the model, greatly breaking through the limitations of traditional contact type technologies.

[0004] However, the above non-contact technologies are difficult to perform synchronous testing on the same model and cannot obtain multi-source parameters simultaneously. In addition, under some typical aerodynamic conditions, due to the loading of aerodynamic loads, the shape of the hot model will change, making it difficult to map the measurement results to the surface of the cold model. At the same time, the PSP technology itself has a temperature effect, resulting in its measurement accuracy being severely interfered by the local temperature of the model. Related research on using the PSP technology for wing surface pressure measurement has been disclosed in the prior art. A large number of marker points were arranged on the model surface for data mapping in this experiment, and the non-local temperature on the model surface was used to eliminate the temperature effect in the main measurement area. This method cannot obtain model deformation data, and on the other hand, it cannot directly obtain the temperature data at the pressure measurement location, so the temperature effect correction range is small. There is also a system and method for synchronously measuring model surface pressure and deformation proposed in the prior art. By combining the PSP technology and binocular stereo vision technology, the measurement of the model surface pressure under deformation is realized. However, the prior art still does not consider the influence of temperature on the accuracy of local PSP measurement results, resulting in low accuracy of the measured pressure parameters.

[0005] Current research has combined the PSP technology with the binocular stereo vision technology, but it cannot measure temperature synchronously, so it cannot completely solve the interference problem of local temperature on the pressure measurement result. For aerodynamic experiments, obtaining synchronous pressure, temperature, and shape test data on the surface of the aerodynamic model can not only provide data feedback for the aerodynamic performance evaluation and styling design of various research objects such as aircraft and automobiles, but also provide multi-source synchronous test verification data for CFD. Therefore, developing technologies for synchronous measurement of temperature, pressure, and shape has important value. Therefore, it is necessary to provide a system and method for synchronous measurement of aerodynamic pressure, temperature, and shape on the surface of a stationary model to solve the above problems. Summary of the Invention

[0006] The present invention provides a system and method for synchronous measurement of aerodynamic pressure, temperature, and shape on the surface of a stationary model to solve the existing problems.

[0007] The system for synchronous measurement of aerodynamic pressure, temperature, and shape on the surface of a stationary model according to the present invention adopts the following technical solutions, including: A two-component coating, which includes temperature-sensitive molecules and pressure-sensitive molecules, and a plurality of marking points are arranged on both of them. It is arranged on the surface of the model to be measured and is used to respond to temperature and pressure respectively through the change of the luminescence intensity of the two luminescent molecules in different luminescence bands under a stable excitation state; A light source for outputting a beam to excite the temperature-sensitive molecules and pressure-sensitive molecules in the two-component coating; A binocular camera for collecting the luminescence images corresponding to the temperature-sensitive molecules and pressure-sensitive molecules in the two-component coating on the surface of the model to be measured in their respective luminescence bands; And a processing module for obtaining the pressure, temperature, and shape of the model surface according to the luminescence images collected by the binocular camera.

[0008] Preferably, the binocular camera includes: A first camera, on which a first filter is arranged, wherein the light transmission band of the first filter is adapted to the luminescence band of the temperature-sensitive molecules; And a second camera, on which a second filter is arranged, wherein the light transmission band of the second filter is adapted to the luminescence band of the pressure-sensitive molecules; Among them, the first camera is used to collect the luminescence image of the temperature-sensitive molecules in the two-component coating on the surface of the model to be measured; the second camera is used to collect the luminescence image of the pressure-sensitive molecules in the two-component coating on the surface of the model to be measured.

[0009] Preferably, both the first filter and the second filter adopt band-pass filters.

[0010] A method for synchronously measuring the aerodynamic pressure, temperature, and shape of a static model surface according to the present invention adopts the following technical solution. The measurement is carried out based on the device for synchronously measuring the aerodynamic pressure, temperature, and shape of the static model surface according to the present invention. The measurement steps include: Spray a two-component coating on the surface of the model to be measured, and evenly distribute a plurality of marking points on the two-component coating. Among them, the two-component coating contains temperature-sensitive molecules and pressure-sensitive molecules; Under the blowing condition, use a binocular camera to synchronously collect the first luminescence images corresponding to the temperature-sensitive molecules and pressure-sensitive molecules in the two-component coating; After exiting the blowing condition, use a binocular camera to synchronously collect the second luminescence images corresponding to the temperature-sensitive molecules and pressure-sensitive molecules in the two-component coating, and use the atmospheric pressure and atmospheric temperature at this time as the reference pressure and reference temperature; Perform stereo matching on the marking points of the two first luminescence images respectively, and perform stereo matching on the marking points of the two second luminescence images. According to the matching results and the internal and external parameters of the binocular camera, obtain the shape and deformation information of the model to be measured when blowing and not blowing; Register the first luminescence image to the second luminescence image according to the deformation information. Compare the first luminescence image corresponding to the temperature-sensitive molecules with the registered second luminescence image to obtain the first light intensity ratio containing temperature information; compare the first luminescence image corresponding to the pressure-sensitive molecules with the registered second luminescence image to obtain the second light intensity ratio containing pressure information; Calibrate the two-component coating. Based on the reference pressure and reference temperature, draw the first relative light intensity distribution map of the temperature-sensitive molecules in the calibrated two-component coating at different temperatures and pressures, and draw the second relative light intensity distribution map of the pressure-sensitive molecules in the calibrated two-component coating at different temperatures and pressures; Obtain the temperature on the surface of the model to be measured according to the first light intensity ratio and the first relative light intensity distribution map. According to the temperature on the surface of the model to be measured, the second light intensity ratio, and the second relative light intensity distribution map, obtain the pressure on the surface of the model to be measured.

[0011] Preferably, under typical aerodynamic conditions, the step of using a binocular camera to synchronously collect the first luminescence images corresponding to the temperature-sensitive molecules and pressure-sensitive molecules in the two-component coating is as follows: Turn on the light source, and adjust the exposure times of the two cameras of the binocular camera so that the luminescence intensity of the two-component coating on the collected luminescence image of the binocular camera is not lower than 80% of the full-well gray value of the two cameras; Turn on the wind tunnel to typical aerodynamic conditions, and use a binocular camera to synchronously collect the first luminescence images corresponding to the temperature-sensitive molecules and pressure-sensitive molecules in the two-component coating at the corresponding exposure time.

[0012] Preferably, the exposure times of the binocular camera when collecting the first luminescence image and the second luminescence image are the same.

[0013] Preferably, the steps of obtaining the shape of the model to be measured and the deformation information of the model to be measured when blowing and not blowing are as follows: Perform stereo matching on the marked points on the first luminescence image corresponding to the temperature-sensitive molecules and the first luminescence image corresponding to the pressure-sensitive molecules to obtain the first matching marked points; Perform stereo matching on the marked points on the second luminescence image corresponding to the temperature-sensitive molecules and the second luminescence image corresponding to the pressure-sensitive molecules to obtain the second matching marked points; Based on the internal and external parameters of the binocular camera, convert the first matching marked points from the image coordinate system to the world coordinate system to obtain the three-dimensional blowing point cloud in the world coordinate system, and convert the second matching marked points from the image coordinate system to the world coordinate system to obtain the three-dimensional reference point cloud in the world coordinate system; Fit the surface shape of the model to be measured according to the two three-dimensional point clouds respectively to obtain the reference shape and the blowing shape corresponding to the model to be measured; Obtain the deformation information of the model to be measured according to the position coordinates of the marked points on the surfaces corresponding to the blowing shape and the reference shape.

[0014] Preferably, put the first light intensity ratio into the first relative light intensity distribution map for retrieval, and solve to obtain the temperature of the model to be measured.

[0015] Preferably, put the second light intensity ratio and the temperature of the model to be measured into the second relative light intensity distribution map for retrieval, and solve to obtain the pressure of the model to be measured.

[0016] Preferably, calibrate the binocular camera to obtain the internal and external parameters of the binocular camera.

[0017] The beneficial effects of the present invention are as follows: 1. For the largest error source faced by the existing PSP pressure measurement technology - the temperature effect, the dual-component coating technology adopted by the present invention contains both temperature-sensitive luminescent molecules and pressure-sensitive luminescent molecules in the coating, and the pressure sensitivity of the temperature-sensitive luminescent molecules is almost negligible. Therefore, it can achieve pixel-level synchronous correction of the temperature effect of the pressure-sensitive luminescent molecules. Compared with the asynchronous correction method in the prior art, based on considering the temperature, the present invention accurately measures the pressure on the surface of the model, and the measurement accuracy of the pressure is higher. 2. In the model surface aerodynamic pressure, temperature, and shape synchronous measurement system proposed by the present invention, the pressure-sensitive component and the temperature-sensitive component in the dual-component coating integrate the characteristics of the PSP pressure measurement technology and the TSP temperature measurement technology. The luminescence of the two components in different bands is captured by a binocular camera respectively, which is perfectly adapted to the binocular vision principle in the DIC three-dimensional topography measurement method. Therefore, the present invention combines the advantages of non-invasive measurement and global measurement of the above three independent technologies.

[0018] 3. Based on the luminous intensity of the model surface coating and the characteristics of the marked points in a set of binocular images, the present invention can directly analyze and obtain the shape, temperature, and aerodynamic pressure of the model surface. Compared with the prior art where at most two of these parameters can be obtained simultaneously, it fills the gap in the synchronous measurement of the model surface shape, temperature, and aerodynamic pressure. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for the description of the embodiments or the prior art. Obviously, the drawings in the following description are only some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can be obtained based on these drawings.

[0020] Figure 1 It is a schematic structural diagram of a synchronous measurement system for aerodynamic pressure, temperature, and shape of a static model surface according to the present invention; Figure 2 It is a schematic diagram of a model to be measured with a two-component coating with marked points in an embodiment of the present invention; Figure 3 It is a flowchart of a method for synchronous measurement of aerodynamic pressure, temperature, and shape of a static model surface according to the present invention; Figure 4 It is a response curve graph of the luminous intensity of temperature-sensitive molecules in a two-component coating to pressure and temperature in an embodiment of the present invention; Figure 5 It is a response curve graph of the luminous intensity of pressure-sensitive molecules in a two-component coating to pressure and temperature in an embodiment of the present invention.

[0021] In the figure: 1. Two-component coating; 2. First camera; 3. Second camera; 4. First filter; 5. Second filter; 6. Light source; 7. Computer; 8. Model to be measured. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0022] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the drawings in the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, not all of them. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts belong to the scope of protection of the present invention.

[0023] In an embodiment of a synchronous measurement system for aerodynamic pressure, temperature, and shape of a static model surface according to the present invention, in this embodiment, the model to be measured 8 is the suction surface of the compressor cascade blade, and the aerodynamic conditions are selected as an angle of attack of 0° and an incoming flow Mach number of 0.6, as Figure 1As shown in the figure, it includes: a two-component coating 1, a light source 6, a binocular camera, and a processing module. The two-component coating 1 includes thermosensitive molecules and piezoresistive molecules. Multiple marking points are arranged on the two-component coating 1. The two-component coating 1 is disposed on the surface of the model to be measured, and is used to respond to temperature and pressure respectively through the change of the luminescence intensity at two different luminescence bands under a stable excitation state; the light source 6 is used to output a light beam for exciting the thermosensitive molecules and piezoresistive molecules in the two-component coating 1; the binocular camera is used to collect the luminescence images of the thermosensitive molecules and piezoresistive molecules in the two-component coating 1 on the surface of the model to be measured at their respective luminescence bands; the processing module is a computer 7, and the computer 7 is electrically connected to the binocular camera as the upper computer of the binocular camera, and the computer 7 is used to obtain the pressure, temperature and shape of the model surface according to the luminescence images collected by the binocular camera.

[0024] Among them, the binocular camera includes: a first camera 2 and a second camera 3. A first filter 4 is disposed on the first camera 2. Among them, the light transmission band of the first filter 4 is adapted to the luminescence band of the thermosensitive molecules; a second filter 5 is disposed on the second camera 3, that is, the first camera 2 and the first filter 4 are integrally connected by a thread on the lens; the second camera 3 and the second filter 5 are integrally connected by a thread on the lens. Among them, the light transmission band of the second filter 5 is adapted to the luminescence band of the piezoresistive molecules; among them, the first camera 2 is used to collect the luminescence image of the thermosensitive molecules in the two-component coating 1 on the surface of the model to be measured; the second camera 3 is used to collect the luminescence image of the piezoresistive molecules in the two-component coating 1 on the surface of the model to be measured. Both the first filter 4 and the second filter 5 adopt band-pass filters. Among them, the first camera 2 and the second camera 3 are respectively aligned with the model to be measured, and the first camera 2 and the second camera 3 are respectively connected to the computer 7 through control communication lines.

[0025] Exemplarily, in a specific embodiment, the absorption spectra of the thermosensitive molecules and piezoresistive molecules of the two-component coating both include the luminescence wavelength 395nm of the light source. The peak of the luminescence band of the thermosensitive molecules is 550nm, and the peak of the luminescence band of the piezoresistive molecules is 650nm; among them, the binocular camera is equipped with band-pass filters adapted to the peak of the luminescence band of the thermosensitive molecules and the peak of the luminescence band of the piezoresistive molecules. Among them, the peak of the luminescence band of the thermosensitive molecules 550nm is adapted to a band-pass filter of 550±20nm, and the peak of the luminescence band of the piezoresistive molecules is 650nm and is adapted to a band-pass filter of 650±20nm.

[0026] An embodiment of the method for synchronously measuring the aerodynamic pressure, temperature and shape of the surface of a stationary model of the present invention is as Figure 3 shown, including: S1. Spray a two-component coating on the surface of the model to be measured and arrange marking points; Specifically, a two-component coating is sprayed on the surface of the model to be measured, and the two-component coating includes both temperature-sensitive molecules and pressure-sensitive molecules at the same time. And a plurality of marking points are evenly arranged on the two-component coating. Exemplarily, in a specific embodiment, the two-component coating is sprayed on the surface of the model to be measured by air spraying, and then black marking points are evenly arranged on the surface of the two-component coating by using a marker pen. The marking points can be evenly distributed over the entire surface of the model to be measured, and the number of pixels occupied by a single marking point is not less than 5×5 pixels. After arranging the marking points, as Figure 2 shown.

[0027] S2. Respectively obtain the first luminescence image and the second luminescence image corresponding to the temperature-sensitive molecules and the pressure-sensitive molecules in the two-component coating, and obtain the reference pressure and the reference temperature. Specifically, under the blowing condition, the computer 7 is used to control the binocular cameras to synchronously collect the first luminescence image corresponding to the temperature-sensitive molecules and the pressure-sensitive molecules in the two-component coating; after exiting the blowing condition, the computer 7 is used to control the binocular cameras to synchronously collect the second luminescence image corresponding to the temperature-sensitive molecules and the pressure-sensitive molecules in the two-component coating, and the atmospheric pressure and the atmospheric temperature at this time are used as the reference pressure P ref and the reference temperature T ref .

[0028] Exemplarily, in a specific embodiment, the step of synchronously collecting the first luminescence image corresponding to the temperature-sensitive molecules and the pressure-sensitive molecules in the two-component coating by using the binocular cameras under the blowing condition is as follows: turn on the light source, and debug the exposure time t of the first camera 2 and the second camera 3 of the binocular cameras so that the luminescence intensity of the two-component coating on the collected luminescence image is not less than 80% of the full-well gray value of the first camera 2 and the second camera 3. After turning on the wind tunnel to the predetermined blowing working condition, control the first camera 2 and the second camera 3 to respectively collect the first luminescence image at the same set of exposure time t. Exemplarily, in a specific embodiment, the step of synchronously collecting the second luminescence image corresponding to the temperature-sensitive molecules and the pressure-sensitive molecules in the two-component coating by using the binocular cameras after exiting the blowing condition is as follows: turn off the wind tunnel, and control the first camera 2 and the second camera 3 to respectively collect the second luminescence image at the same set of exposure time t.

[0029] S3. Obtain the shape and deformation information of the model to be measured when blowing and not blowing. Specifically, perform stereo matching on the marking points of the two first luminescence images respectively, and perform stereo matching on the marking points on the two second luminescence images. According to the matching results and the internal and external parameters of the binocular cameras, obtain the shape of the model to be measured when blowing and not blowing and the deformation information of the model to be measured.

[0030] Exemplarily, in a specific embodiment, the steps for obtaining the internal and external parameters of the binocular camera are as follows: Keeping the relative position of the measurement system unchanged, use a checkerboard calibration board to perform binocular calibration on the first camera 2 and the second camera 3 of the binocular camera to obtain the internal and external parameters of the binocular camera. Among them, binocular calibration can be conveniently implemented using various open-source algorithms. In this embodiment, the Stereo Calibration algorithm in OpenCV is used for binocular calibration.

[0031] Exemplarily, in a specific embodiment, the steps for obtaining the shape of the model under test and the deformation information of the model under test when blowing air and not blowing air are as follows: Perform stereo matching on the marked points on the first luminescence image corresponding to the thermosensitive molecule and the first luminescence image corresponding to the pressure-sensitive molecule to obtain the first matching marked points; perform stereo matching on the marked points on the second luminescence image corresponding to the thermosensitive molecule and the second luminescence image corresponding to the pressure-sensitive molecule to obtain the second matching marked points; among them, stereo matching is implemented using the cross-correlation algorithm in OpenCV; based on the internal and external parameters of the binocular camera, convert the first matching marked points from the image coordinate system to the world coordinate system to obtain the three-dimensional blowing point cloud in the world coordinate system, and convert the second matching marked points from the image coordinate system to the world coordinate system to obtain the three-dimensional reference point cloud in the world coordinate system; use the open-source software Cloudcompare and fit the surface shape of the model under test according to the three-dimensional blowing point cloud to obtain the blowing shape corresponding to the model under test; use an algorithm and fit the surface shape of the model under test according to the three-dimensional reference point cloud to obtain the reference shape corresponding to the model under test; take the difference between the position coordinates of the marked points on the surfaces corresponding to the blowing shape and the reference shape to obtain the deformation information of the model under test.

[0032] Thus, the blowing shape corresponding to the model under test when blowing air, the reference shape corresponding to the model under test when not blowing air, and the deformation information of the model under test when blowing air and not blowing air can be obtained.

[0033] S4. Obtain the first light intensity ratio containing temperature information and the second light intensity ratio containing pressure information; Specifically, register the first luminescence image to the second luminescence image according to the deformation information, and compare the first luminescence image corresponding to the thermosensitive molecule with the registered second luminescence image to obtain the first light intensity ratio containing temperature information; compare the first luminescence image corresponding to the pressure-sensitive molecule with the registered second luminescence image to obtain the second light intensity ratio containing pressure information.

[0034] S5. Obtain the relative light intensity distribution maps of the bimolecules in the two-component coating at different temperatures and pressures; Specifically, calibrate the two-component coating, and based on the reference pressure and reference temperature, plot the first relative light intensity distribution map of the temperature-sensitive molecules in the calibrated two-component coating at different temperatures and pressures, and plot the second relative light intensity distribution map of the pressure-sensitive molecules in the calibrated two-component coating at different temperatures and pressures.

[0035] Exemplarily, in a specific embodiment, calibrate the two-component coating with an optical pressure-sensitive coating pressure calibration device based on a CCD camera with the patent number CN112378576B; based on the reference pressure and reference temperature, plot the first relative light intensity distribution map of the temperature-sensitive molecules in the calibrated two-component coating at different temperatures and pressures. The first relative light intensity distribution map is as Figure 4 shown. Plot the second relative light intensity distribution map of the pressure-sensitive molecules in the calibrated two-component coating at different temperatures and pressures. The second relative light intensity distribution map is as Figure 5 shown.

[0036] The calibration result of the temperature-sensitive component is expressed as: I 550 / I ref,550 = f(T); The calibration result of the pressure-sensitive component is expressed as: I ref,650 / I 650 = f(T, P); wherein, I ref,550 represents the luminous intensity in the 550 nm band under the reference working condition ref; I ref,650 represents the luminous intensity in the 650 nm band under the reference working condition ref; I 550 represents the luminous intensity in the 550 nm band; I 650 represents the luminous intensity in the 650 nm band; T is the temperature; P represents the pneumatic pressure; and f represents a function.

[0037] S6. Obtain the pressure and temperature on the surface of the model to be measured; Specifically, obtain the temperature on the surface of the model to be measured according to the first light intensity ratio and the first relative light intensity distribution map, and obtain the pressure on the surface of the model to be measured according to the temperature on the surface of the model to be measured, the second light intensity ratio, and the second relative light intensity distribution map.

[0038] Exemplarily, in a specific embodiment, put the first light intensity ratio into the first relative light intensity distribution map for retrieval, and solve to obtain the temperature of the model to be measured; put the second light intensity ratio and the temperature of the model to be measured into the second relative light intensity distribution map for retrieval, and solve to obtain the pressure of the model to be measured. Among them, as Figure 4 shown, the relative light intensity of the temperature-sensitive molecules is almost a single-valued function of the temperature. In the pressure change range of 30 kPa, its relative light intensity fluctuates slightly, but there is no overall change trend. Therefore, after obtaining the first light intensity ratio of the temperature-sensitive molecules in the 550 nm band under the blowing condition, the temperature can be obtained. AsFigure 5 As shown, the relative light intensity of the pressure-sensitive molecule in the 650 nm band is a two-valued function of temperature and pressure. However, since the temperature at the same spatial position has been obtained through Figure 4 retrieval, therefore, under the blowing condition, by combining the obtained temperature and the second light intensity ratio in the 650 nm band, the pressure can be obtained.

[0039] The mathematical process for retrieving temperature is T = f(I 550 / I ref,550 ) The mathematical process for retrieving pressure is P = f(I 650 / I ref,650 , T) Thus, the measurement of the pressure, temperature, and shape of the model to be measured is completed.

[0040] The above are only the preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention shall be included within the protection scope of the present invention.

Claims

1. A synchronous measurement system for pneumatic pressure, temperature, and shape on the surface of a stationary model, characterized in that, Comprising: A two-component coating, which includes temperature-sensitive molecules and pressure-sensitive molecules, on which a plurality of marking points are uniformly arranged, and which is disposed on the surface of the model to be measured, for responding to temperature and pressure respectively through the luminous intensity changes of the two luminous molecules in different luminous bands under a stable excitation state; A light source for outputting a light beam to excite the temperature-sensitive molecules and pressure-sensitive molecules in the two-component coating; A binocular camera for collecting the luminous images corresponding to the temperature-sensitive molecules and pressure-sensitive molecules in the two-component coating on the surface of the model to be measured in their respective luminous bands; And a processing module for obtaining the pressure, temperature and shape of the model surface according to the luminous images collected by the binocular camera.

2. The synchronous measurement system for pneumatic pressure, temperature, and shape of a static model surface according to claim 1, wherein The binocular camera includes: A first camera, on which a first filter is arranged, wherein the light transmission band of the first filter is adapted to the luminous band of the temperature-sensitive molecules; And a second camera, on which a second filter is arranged, wherein the light transmission band of the second filter is adapted to the luminous band of the pressure-sensitive molecules; Wherein, the first camera is used to collect the luminous image of the temperature-sensitive molecules in the two-component coating on the surface of the model to be measured; the second camera is used to collect the luminous image of the pressure-sensitive molecules in the two-component coating on the surface of the model to be measured.

3. The synchronous measurement system for aerodynamic pressure, temperature and shape on the surface of a stationary model according to claim 2, characterized in that, Both the first filter and the second filter adopt band-pass filters.

4. A method for synchronously measuring the aerodynamic pressure, temperature, and shape of a static model surface, characterized in that, When measuring based on the measuring device according to any one of claims 1-3, the measuring steps include: Spraying a two-component coating on the surface of the model to be measured, and arranging a plurality of marking points on the two-component coating, wherein the two-component coating contains temperature-sensitive molecules and pressure-sensitive molecules; Under the blowing condition, synchronously collecting the first luminous images corresponding to the temperature-sensitive molecules and pressure-sensitive molecules in the two-component coating by using the binocular camera; After exiting the blowing condition, synchronously collecting the second luminous images corresponding to the temperature-sensitive molecules and pressure-sensitive molecules in the two-component coating by using the binocular camera, and taking the atmospheric pressure and atmospheric temperature at this time as the reference pressure and reference temperature; Performing stereo matching on the marking points of the two first luminous images respectively, and performing stereo matching on the marking points of the two second luminous images, and obtaining the shape and deformation information of the model to be measured when blowing and not blowing according to the matching results and the internal and external parameters of the binocular camera; Registering the first luminous image corresponding to the temperature-sensitive molecules to the second luminous image according to the deformation information, comparing the first luminous image corresponding to the temperature-sensitive molecules with the registered second luminous image to obtain a first light intensity ratio containing temperature information; comparing the first luminous image corresponding to the pressure-sensitive molecules with the registered second luminous image to obtain a second light intensity ratio containing pressure information; Calibrating the two-component coating, and based on the reference pressure and reference temperature, drawing a first relative light intensity distribution map of the temperature-sensitive molecules in the calibrated two-component coating at different temperatures and pressures, and drawing a second relative light intensity distribution map of the pressure-sensitive molecules in the calibrated two-component coating at different temperatures and pressures; Obtaining the temperature of the surface of the model to be measured according to the first light intensity ratio and the first relative light intensity distribution map, and obtaining the pressure of the surface of the model to be measured according to the temperature of the surface of the model to be measured, the second light intensity ratio and the second relative light intensity distribution map.

5. A method for synchronously measuring the aerodynamic pressure, temperature, and shape of a static model surface according to claim 4, characterized in that Under typical pneumatic conditions, the step of synchronously collecting the first luminous images corresponding to the temperature-sensitive molecules and pressure-sensitive molecules in the two-component coating by using the binocular camera is: Turn on the light source and adjust the exposure times of the two cameras of the binocular camera so that the luminous intensity of the two-component coating on the luminous image collected by the binocular camera is not lower than 80% of the full-well gray value of the two cameras; Turn on the wind tunnel to typical aerodynamic conditions, and use the binocular camera to synchronously collect the first luminous images corresponding to the temperature-sensitive molecules and pressure-sensitive molecules in the two-component coating at the corresponding exposure times.

6. A method for synchronously measuring the aerodynamic pressure, temperature, and shape of a static model surface according to claim 4, characterized in that, The exposure times of the binocular camera when collecting the first luminous image and the second luminous image are the same.

7. A method for synchronously measuring the aerodynamic pressure, temperature, and shape of a static model surface according to claim 4, characterized in that The steps for obtaining the shape of the model under test and the deformation information of the model under test when blowing and not blowing are as follows: Perform stereo matching on the marked points on the first luminous image corresponding to the temperature-sensitive molecules and the first luminous image corresponding to the pressure-sensitive molecules to obtain the first matching marked points; Perform stereo matching on the marked points on the second luminous image corresponding to the temperature-sensitive molecules and the second luminous image corresponding to the pressure-sensitive molecules to obtain the second matching marked points; Based on the internal and external parameters of the binocular camera, convert the first matching marked points from the image coordinate system to the world coordinate system to obtain the three-dimensional blowing point cloud in the world coordinate system, and convert the second matching marked points from the image coordinate system to the world coordinate system to obtain the three-dimensional reference point cloud in the world coordinate system; Fit the surface shape of the model under test according to the two three-dimensional point clouds respectively to obtain the reference shape and the blowing shape corresponding to the model under test; Obtain the deformation information of the model under test according to the position coordinates of the marked points on the surfaces corresponding to the blowing shape and the reference shape.

8. A method for synchronously measuring the aerodynamic pressure, temperature, and shape of a static model surface according to claim 4, characterized in that, Put the first light intensity ratio into the first relative light intensity distribution map for retrieval, and solve to obtain the temperature of the model under test.

9. A method for synchronously measuring the aerodynamic pressure, temperature, and shape of a static model surface according to claim 4, characterized in that, Put the second light intensity ratio and the temperature of the model under test into the second relative light intensity distribution map for retrieval, and solve to obtain the pressure of the model under test.

10. A method for synchronously measuring the aerodynamic pressure, temperature, and shape of a static model surface according to claim 4, characterized in that, Calibrate the binocular camera to obtain the internal and external parameters of the binocular camera.

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