Scramjet engine experiment table component-pressure field depth coupling monitoring method

Abstract

The invention belongs to the technical field of scramjet engine ground test optical diagnosis, and discloses a scramjet engine experiment table component-pressure field depth coupling monitoring method, which comprises the following steps: when an experiment table is adjusted to a test working condition, constructing a single-wavelength laser-component response matrix; when the experiment table is adjusted from a test working condition to an experiment working condition, exciting a flow field and a wall surface pressure sensitive coating by using a single-wavelength excitation light source, and collecting component fluorescence intensity signals of different wavebands to form a fluorescence intensity observation vector and a coating light-emitting signal; according to the response matrix, performing inversion calculation on the fluorescence intensity observation vector to obtain content information of each target component including oxygen; calculating pressure information of the monitoring position by using the oxygen component content information, and outputting the component content information and pressure distribution of the monitoring position. And the accuracy and the reliability of component and pressure measurement of the experiment table are improved.

Description

Technical Field

[0001] This application relates to the field of optical diagnostic technology for ground testing of scramjet engines, and in particular to a method for deep coupling monitoring of component-pressure field on a scramjet engine test bench. Background Technology

[0002] Scramjet engines hold significant promise for applications in hypersonic vehicles, and their internal flow fields typically exhibit high Mach numbers, strong shock wave structures, and complex chemical reactions. To accurately assess the engine's combustion characteristics, thrust performance, and structural safety during ground testing, it is essential to precisely measure the composition distribution and wall pressure characteristics of the internal flow field. The flow field composition distribution reflects fuel mixing efficiency, combustion reaction intensity, and oxygen consumption processes, while the wall pressure distribution directly relates to the engine's internal shock wave structure, load distribution, and overall aerodynamic performance. Therefore, simultaneously acquiring compositional and wall pressure information under ground testing conditions is crucial for revealing the physical mechanisms of the scramjet engine's internal flow field.

[0003] Currently, flow field component monitoring typically employs optical diagnostic methods based on laser-induced fluorescence. Since different target components often correspond to different excitation wavelengths, existing technologies usually require multiple laser sources with different wavelengths and multiple optical systems to achieve simultaneous measurement of multiple components. Furthermore, when measuring wall pressure, commonly used pressure-sensitive coatings are susceptible to changes in local oxygen content under combustion conditions, leading to measurement deviations.

[0004] In the process of realizing this invention, the inventors discovered at least the following problems in the prior art: 1. The experimental system is complex and costly. Traditional multi-wavelength monitoring schemes significantly increase the complexity and cost of the system structure, and have extremely high requirements for optical path stability and time synchronization, making them unsuitable for the space-constrained and complex working conditions of scramjet engine test benches. 2. The accuracy of pressure measurement is limited. Since it is impossible to obtain the local oxygen content changes during combustion in real time and accurately, the wall pressure measurement based on the pressure-sensitive coating has obvious systematic errors and cannot truly reflect the wall pressure distribution under complex combustion conditions. Summary of the Invention

[0005] The purpose of this application is to provide a method for deep coupling monitoring of components and pressure fields on a scramjet engine test rig, in order to solve the technical problems in related technologies where component monitoring on a scramjet engine test rig usually requires a multi-wavelength laser system and the measurement results of pressure-sensitive coatings are easily affected by changes in local oxygen content.

[0006] According to a first aspect of the embodiments of this application, a method for deep coupling monitoring of component-pressure fields on a scramjet engine test rig is provided, comprising: When the experimental platform is adjusted to the test condition, the laser energy and detection efficiency are normalized, and the fluorescence intensity information of various flow field target components in multiple detection bands is collected. The response coefficients of multiple target components under the test single-wavelength laser in different detection bands are obtained, and then the single-wavelength laser-component response matrix is ​​constructed. When the experimental platform is adjusted from the test condition to the experimental condition, a single-wavelength excitation light source is used to excite the flow field and the pressure-sensitive coating on the wall. The fluorescence intensity signals of the components in different detection bands are collected simultaneously to form the fluorescence intensity observation vector and the coating emission signal. Based on the single-wavelength laser-component response matrix, the fluorescence intensity observation vector is inverted to obtain the content information of each target component, including oxygen. The pressure information at the monitoring location is calculated using the oxygen component content information, and the component content information and pressure distribution at the monitoring location are output.

[0007] Optionally, the construction of the single-wavelength laser-component response matrix includes: A single-wavelength pulsed laser with spectral frequency selection is used as the excitation source. After the optical path angle is adjusted by a reflector, the original three-dimensional laser is shaped into a sheet laser by a beam-shaping cylindrical lens. While maintaining the same excitation source and optical detection conditions, a single target component is introduced into a controllable calibration environment to excite the flow field within a predetermined two-dimensional cross-section. The excited flow field component generates a fluorescence intensity signal, which enters the imaging system through the engine optical window and is collected by the imaging lens. The signal is then separated into different bands by the spectral separation component and projected onto different areas or different imaging units of the imaging sensor to achieve the acquisition of fluorescence intensity signals of different components. By normalizing the fluorescence intensity signals of the different components based on laser energy and detection efficiency, the response coefficients of each target component in different detection channels are obtained, thereby constructing a single-wavelength laser-component response matrix.

[0008] Optionally, it also includes the initialization of the experimental platform, the initialization including: (1) Initialize the experimental platform spatially, including determining the spatial position of the excitation laser relative to the engine flow channel and the focal length of the imaging system so that the imaging range covers the cross section of the flow field to be measured and the pressure-sensitive coating area. (2) Keep the experimental laser wavelength and the spectral separation components of the camera consistent with those used when constructing the single-wavelength laser-component response matrix; (3) Adjust the operating parameters of the engine test bench to make the flow field reach the predetermined experimental conditions.

[0009] Optionally, component fluorescence intensity signals from different detection bands are collected to form a fluorescence intensity observation vector and a coating luminescence signal, including: After the experimental equipment was initialized, the aforementioned single-wavelength pulsed laser was used as the excitation source to simultaneously excite the target components in the flow field and the pressure-sensitive coating on the wall. The fluorescence signal of the flow field components generated after excitation and the luminescence signal of the pressure-sensitive coating on the wall enter the imaging system through the optical window of the scramjet engine test bench. They are separated by the spectrophotometer according to the preset wavelength and projected onto the sensors of multiple detection channels. At each sampling time, the fluorescence intensity signal is normalized and corrected for laser energy fluctuations and spatial distribution non-uniformity. Simultaneously acquire component fluorescence intensity signals in different bands, combine fluorescence intensity signals from multiple detection channels at the same spatial location to form a fluorescence intensity observation vector, and simultaneously record the luminescence signal of the pressure-sensitive coating.

[0010] Optionally, based on the single-wavelength laser-component response matrix, the fluorescence intensity observation vector is inverted to obtain the content information of each target component, including oxygen, including: Based on the pre-constructed spectral response matrix, the observation vector is inverted to obtain the content information of each target component at the corresponding location; Physical constraints are imposed on the inversion results to eliminate non-physical results and improve the stability and reliability of component inversion.

[0011] Optionally, the original pressure distribution data is corrected in real time using oxygen component content information, and the component content information and pressure distribution at the monitoring location are output, including: Extract the oxygen composition content of the region adjacent to the target wall from the database; The oxygen component content is introduced as a dynamic parameter into the pressure calculation model of the pressure-sensitive coating. The oxygen partial pressure term in the model is updated to obtain the true wall pressure distribution after component correction.

[0012] According to a second aspect of the embodiments of this application, a component-pressure field deep coupling monitoring device for a scramjet engine test rig is provided, comprising: The response matrix construction module is used to normalize the laser energy and detection efficiency when the experimental platform is adjusted to the test condition, collect fluorescence intensity information of multiple flow field target components in multiple detection bands, obtain the response coefficients of multiple target components under the test single-wavelength laser in different detection bands, and then construct the single-wavelength laser-component response matrix. The experimental module is used to excite the flow field and wall pressure-sensitive coating with a single wavelength excitation light source when the experimental platform is adjusted from the test condition to the experimental condition, and simultaneously collect component fluorescence intensity signals of different detection bands to form a fluorescence intensity observation vector and coating luminescence signal. The component inversion calculation module is used to perform inversion calculation on the fluorescence intensity observation vector based on the single-wavelength laser-component response matrix to obtain the content information of each target component, including oxygen. The pressure calculation module is used to calculate the pressure information at the monitoring location using the oxygen component content information, and outputs the component content information and pressure distribution at the monitoring location.

[0013] According to a third aspect of the embodiments of this application, an electronic device is provided, comprising: One or more processors; Memory, used to store one or more programs; When the one or more programs are executed by the one or more processors, the one or more processors perform the method as described in the first aspect.

[0014] According to a fourth aspect of the embodiments of this application, a computer-readable storage medium is provided that stores computer instructions thereon, which, when executed by a processor, implement the steps of the method as described in the first aspect.

[0015] The technical solutions provided by the embodiments of this application may include the following beneficial effects: As can be seen from the above embodiments, this application overcomes the technical problems of complex optical paths and high costs of multi-component monitoring systems in traditional scramjet engine experiments, as well as the measurement deviation of pressure-sensitive coatings caused by local oxygen changes in the combustion environment, by constructing a single-wavelength laser-component spectral response matrix and dynamically correcting the wall pressure using real-time inverted oxygen content. This simplifies the experimental setup and significantly improves the reliability of flow field component and wall pressure measurements.

[0016] It should be understood that the above general description and the following detailed description are exemplary and explanatory only, and do not limit this application. Attached Figure Description

[0017] The accompanying drawings, which are incorporated in and form part of this specification, illustrate embodiments consistent with this application and, together with the description, serve to explain the principles of this application.

[0018] Figure 1 This is a schematic diagram of a supersonic ramjet engine test bench according to an exemplary embodiment.

[0019] Figure 2This is a flowchart illustrating a method for deep coupling monitoring of component-pressure fields on a scramjet engine test bench, according to an exemplary embodiment.

[0020] Figure 3 This is a schematic diagram of the structure of a component-pressure field deep coupling monitoring device for a scramjet engine test bench, according to an exemplary embodiment. Detailed Implementation

[0021] Exemplary embodiments will now be described in detail, examples of which are illustrated in the accompanying drawings. When the following description relates to the drawings, unless otherwise indicated, the same numbers in different drawings denote the same or similar elements. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with this application. Rather, they are merely examples of apparatuses and methods consistent with some aspects of this application.

[0022] The terminology used in this application is for the purpose of describing particular embodiments only and is not intended to be limiting of the application. The singular forms “a,” “the,” and “the” used herein are also intended to include the plural forms unless the context clearly indicates otherwise. It should also be understood that the term “and / or” as used herein refers to and includes any and all possible combinations of one or more of the associated listed items.

[0023] Figure 1 This is a schematic diagram of a scramjet engine test bench according to an exemplary embodiment. The scramjet engine test bench includes a gas storage tank 1, a drying device 2, an air compressor 3, a laser emission source 4, a reflector 5, a beam shaping device 6, a pressure regulating valve 7, a silencer 8, a scramjet engine model 9, an experimental chamber 10, a thermometer 11, a pressure gauge 12, a pressure stabilizing chamber 13, a flow meter 14, an electric control valve 15, a computer 16, and a high-speed camera 17. Before the experiment begins, the air compressor 3 compresses the outside air and dries it through the drying device 2. The high-pressure dried gas is stored in the gas storage tank 1. At the start of the experiment, the opening of the electric control valve 15 is adjusted, and the airflow flows from the gas storage tank 1 to the pressure stabilizing chamber 13. In the pressure stabilizing chamber 13, the pressure pulsation of the gas is largely eliminated, and a stable airflow under experimental conditions moves from the pressure stabilizing chamber 13 to the scramjet engine model 9. The back pressure under experimental conditions is controlled by the pressure regulating valve 7, and the experimental chamber 10 isolates the external environment from the experimental environment. The exhaust gas generated in the experiment is discharged into the atmosphere after noise is eliminated by silencer 8. The single-wavelength laser emitted by laser source 4 is oriented by mirror 5 and shaped into a thin sheet laser by beam shaper 6. The laser then excites the components to be monitored and the pressure-sensitive coating in the flow field. The fluorescence generated after excitation is reflected by mirror 5 and captured by high-speed camera 17. All captured information is digitally processed in computer 16.

[0024] Figure 2This is a flowchart illustrating a method for deep coupling monitoring of component-pressure fields on a scramjet engine test rig, according to an exemplary embodiment. Figure 2 As shown, the method may include the following steps: S1: When the experimental platform is adjusted to the test condition, the laser energy and detection efficiency are normalized, and the fluorescence intensity information of various flow field target components in multiple detection bands is collected to obtain the response coefficients of multiple target components under the test single-wavelength laser in different detection bands, and then the single-wavelength laser-component response matrix is ​​constructed. S2: When the test bench is adjusted from the test condition to the experimental condition, a single-wavelength excitation light source is used to excite the flow field and the pressure-sensitive coating on the wall. The fluorescence intensity signals of the components in different detection bands are collected simultaneously to form the fluorescence intensity observation vector and the coating emission signal. S3: Based on the single-wavelength laser-component response matrix, the fluorescence intensity observation vector is inverted to obtain the content information of each target component, including oxygen. S4: Using the oxygen component content information, calculate the pressure information at the monitoring location, and output the component content information and pressure distribution at the monitoring location.

[0025] As can be seen from the above embodiments, this application effectively solves the technical problems of complex structure of multi-component monitoring system in ground experiment of scramjet engine and systematic deviation of wall pressure measurement caused by local oxygen content change under combustion conditions by constructing single-wavelength laser-component spectral response matrix and using real-time inverted oxygen component information to dynamically correct wall pressure data; it achieves high-precision non-contact monitoring of flow field components and wall pressure field under the premise of significantly simplifying experimental equipment configuration.

[0026] In the specific implementation of S1: when the experimental platform is adjusted to the test condition, the laser energy and detection efficiency are normalized, the fluorescence intensity information of multiple flow field target components in multiple detection bands is collected, the response coefficients of multiple target components under the test single-wavelength laser in different detection bands are obtained, and then the single-wavelength laser-component response matrix is ​​constructed. Specifically, based on the flow field characteristics of the scramjet engine to be monitored, the types of target components to be monitored during the experiment are determined, and a single-wavelength pulsed laser capable of simultaneously generating fluorescence excitation of the target components is selected as the excitation source. The excitation source is positioned away from the engine experimental area, the optical path angle is adjusted by a reflector, and the original three-dimensional laser is shaped into a thin sheet laser with a thickness much smaller than the size of the experimental platform using a beam-shaping cylindrical lens, so that it uniformly passes through the monitoring area within a predetermined two-dimensional cross-section.

[0027] Under laser irradiation, the target component located within the monitoring plane generates a fluorescence intensity signal, which enters the imaging detection system through the engine's optical window. The imaging detection system is equipped with a spectral separation component to separate the fluorescence signal according to preset wavelengths. The separated fluorescence intensity signals of different wavelengths are then projected onto different photosensitive areas or imaging units of the imaging sensor, achieving synchronous acquisition of multi-channel signals. After the optical path and detection system are constructed, a single target component of known concentration is sequentially introduced into the scramjet engine flow channel or calibration equipment. While maintaining consistent excitation source parameters, optical path structure, and imaging detection conditions, the fluorescence intensity information of the target component in multiple detection channels is acquired.

[0028] Laser energy and detection efficiency were introduced to normalize the fluorescence intensity signals of the different components. Laser pulse energy was monitored synchronously in real time using an energy meter, and energy fluctuation correction was applied to the acquired fluorescence intensity images. The response coefficients of each target component in different detection channels were obtained by extracting the average fluorescence intensity of the specific component across all detection channels. A single-wavelength laser-component spectral response matrix was constructed by summarizing the response coefficients of each target component. This matrix establishes the mapping relationship between the observed signals of each detection channel and the concentration of each component under single-wavelength excitation conditions, and is used for the inversion calculation of the component content in the flow field under subsequent experimental conditions.

[0029] Specifically, the response coefficient of the i-th component in the j-th detection channel The calculation method is as follows: Here, 'i' represents a component, determined by the actual number of monitored components. For example, if 5 components are actually monitored, then 'i' can be 1, 2, 3, 4, or 5; if 3 components are actually monitored, then 'i' can only be 1, 2, or 3. 'j' represents a detection channel. To ensure that the number of detection channels is always greater than or equal to the number of monitored components, there is no upper limit to the number of monitoring channels. Increasing the number of monitoring channels will increase costs. If there are 5 monitored components, then the number of detection channels must be greater than or equal to 5. To obtain the fluorescence intensity of component i in detector channel j, the number of detector channels needs to be determined based on the actual number of components to be monitored, and it is necessary to ensure that the number of detector channels is always no less than the number of monitored components. E For laser energy, Let i be the efficiency of component i being detected by probe channel j. Let i be the concentration of component i.

[0030] The response coefficients of all target components in each channel are summarized. If there are m target components and n detection channels, an m×n order single-wavelength laser-component response matrix M is constructed. This matrix establishes the mapping relationship between the observed signal and the component concentration, which is used for component inversion calculations under subsequent experimental conditions.

[0031] The response matrix of a single component i across n channels is as follows: The response matrix of m target components in n channels is as follows: In the specific implementation of S2: when the experimental platform is adjusted from the test condition to the experimental condition, a single-wavelength excitation light source is used to excite the flow field and the pressure-sensitive coating on the wall surface, and the component fluorescence intensity signals of different detection bands are collected simultaneously to form a fluorescence intensity observation vector and the coating emission signal; this step includes the following sub-steps: S21: The experimental system performs spatial initialization; Specifically, this includes determining the spatial position of the excitation laser relative to the engine flow channel and the focal length of the imaging system. Adjustments are made to ensure that the field of view of the imaging detection system completely covers the cross-section of the flow field under test and the wall area with the pressure-sensitive coating. The excitation laser wavelength, beam shaping method, and spectral separation component parameters used in the experiment are kept completely consistent with those used when constructing the single-wavelength laser-component response matrix to ensure that the physical correspondence between the experimentally acquired signals and the response matrix does not shift during subsequent processing.

[0032] S22: Acquisition of raw experimental data; Specifically, after initialization, the operating parameters of the scramjet engine test bench are adjusted to achieve the predetermined experimental conditions by controlling parameters such as gas supply pressure and fuel flow rate. During engine experiments after the flow field reaches a stable state, the aforementioned single-wavelength pulsed laser is used as the excitation source to simultaneously excite the target components and the pressure-sensitive coating on the wall within the flow field. The fluorescence signals of the flow field components and the luminescence signals of the pressure-sensitive coating on the wall generated after excitation enter the imaging system through the optical window of the scramjet engine test bench, are separated by a spectrophotometer according to a preset wavelength, and projected onto the sensor.

[0033] S23: Normalize and correct the fluorescence intensity signal for laser energy fluctuations and spatial distribution non-uniformity; Specifically, an energy monitoring device synchronized with laser emission is used to record the energy value of each laser pulse in real time. and compared it with the reference laser energy used when constructing the response matrix. E Compare the results and record the energy correction coefficient. Meanwhile, under calibrated conditions with no flow field or filled with uniform components, the spatial energy distribution image of the sheet laser, i.e., the flat-field compensation image, is pre-captured and stored to characterize the relative intensity difference of the laser at each pixel position within the two-dimensional cross-section.

[0034] When processing the raw fluorescence images acquired under experimental conditions, the original grayscale value of each pixel in the image is divided by the corresponding energy correction coefficient, and spatial intensity compensation is performed in conjunction with the flat-field compensation image. This correction process effectively eliminates intensity deviations caused by laser fluctuations and uneven energy spatial distribution during optical path transmission. This ensures that the corrected fluorescence intensity signal accurately reflects the contribution of the component molecule concentration at the corresponding spatial location, providing a standardized data foundation for subsequently constructing accurate fluorescence intensity observation vectors and achieving high-precision inversion.

[0035] S24: Combine the fluorescence intensity signals of multiple detection channels at the same spatial location to form an observation vector, and simultaneously record the luminescence signal of the pressure-sensitive coating; Specifically, the multi-channel images acquired synchronously in phase S22 and corrected in phase S23 are first spatially registered to establish pixel-level coordinate mapping relationships between the images of each detection channel, ensuring that for any physical point in the flow field, the corresponding pixel coordinates in different detection band channels are completely consistent. The pressure-sensitive coating fluorescence signal intensity field after spatial registration is directly stored in the device.

[0036] Based on spatial registration, extract the coordinates of the same pixel. The corrected component fluorescence intensities are obtained from all detection channels (assuming there are n detection channels). These intensity values ​​are arranged according to the preset band order of the spectral separation component and combined into an n-dimensional column vector, defined as the fluorescence intensity observation vector at that spatial location. , where I n Represents the coordinates of a pixel The component fluorescence intensity in the nth detection channel. The above combined operation is performed on each pixel within the monitoring area to obtain the fluorescence intensity observation vector at the corresponding location.

[0037] Each observation vector contains the aliased spectral features contributed by multiple target components at that point, thus transforming the complex image recognition problem into a computable linear algebraic solution problem, laying a standardized input format for the next step of calling the single-wavelength laser-component response matrix for accurate inversion.

[0038] In the specific implementation of S3: based on the single-wavelength laser-component response matrix, the fluorescence intensity observation vector is inverted to obtain the content information of each target component, including oxygen; this step includes the following sub-steps: S31: Based on the pre-constructed spectral response matrix, the observation vector is inverted to obtain the content information of each target component at the corresponding position; Specifically, the fluorescence intensity observation vector at each pixel location A system of linear algebraic equations is established between the laser-component response matrix M and the concentration vector C of the component to be determined. Based on the single-wavelength laser-component response matrix M obtained in step S1, the system of equations is expressed as follows: ,in ,in This represents the concentration value of the m-th target component at that spatial location. By inverting or decomposing the equations, numerical solutions for the concentrations of each component at that pixel are calculated. By traversing all pixel coordinates within the monitoring section, the component content information for each pixel is finally output. The obtained oxygen concentration distribution field will be used as reference data for subsequent non-uniform concentration correction of the pressure-sensitive coating measurement results.

[0039] S32: Apply physical constraints to the inversion results to eliminate non-physical results and improve the stability and reliability of component inversion; Specifically, a non-negativity constraint is first implemented. During matrix inversion, background noise or detector reading fluctuations may cause slight negative values ​​in the concentration calculations of some components. To address this, all concentration values ​​less than zero are forcibly corrected to zero to conform to the physical fact that substance concentration must be greater than or equal to zero.

[0040] Secondly, a constraint on the total amount of components is implemented. Based on the compositional characteristics of the mixed gas, the proportion of each component at each pixel location is verified. If the sum of the concentrations of all known target components obtained from the inversion exceeds the total mass threshold under this condition, a proportional reduction correction is performed based on the residual contribution rate of each component, thereby ensuring that the inversion result satisfies the law of mass conservation.

[0041] Furthermore, spatial consistency constraints are used to eliminate anomalous jump points. By implementing spatial median filtering or neighborhood grayscale consistency checks, isolated noise points with excessively large concentration differences from surrounding pixels in the component distribution cloud map are smoothed. Applying these physical constraints significantly improves the robustness of the component inversion algorithm under extreme combustion environments such as strong vibrations and strong background radiation. The final output component content data exhibits higher stability and reliability, providing high-quality input field data for the subsequent S4 step of accurate pressure field correction.

[0042] In the specific implementation of S4: using the oxygen component content information, the pressure information at the monitoring location is calculated, and the component content information and pressure distribution at the monitoring location are output; Specifically, the two-dimensional oxygen concentration field obtained in step S3 is... and the real-time pressure-sensitive coating fluorescence signal intensity field acquired by the sensor. As input variables, the pixel points are obtained according to the following formula. Pressure at the location ; Quenching coefficient With constant A The values ​​are entirely determined by the chemical properties of the pressure-sensitive coating, and all are known quantities.

[0043] The pressure level of each pixel is calculated using the same algorithm.

[0044] Finally, a two-dimensional component content distribution map of the monitoring location and a high-precision wall pressure distribution cloud map after component correction are output simultaneously. This output enables the coordinated monitoring of the component and pressure distribution inside the scramjet engine.

[0045] Corresponding to the aforementioned embodiments of the deep coupling monitoring method for the component-pressure field of a scramjet engine test rig, this application also provides embodiments of a deep coupling monitoring device for the component-pressure field of a scramjet engine test rig.

[0046] Figure 3 This is a block diagram of a component-pressure field deep coupling monitoring device for a scramjet engine test rig, according to an exemplary embodiment. (Refer to...) Figure 3 The device includes: The response matrix construction module 1 is used to normalize the laser energy and detection efficiency when the experimental platform is adjusted to the test condition, collect the fluorescence intensity information of multiple flow field target components in multiple detection bands, obtain the response coefficients of multiple target components under the test single-wavelength laser in different detection bands, and then construct the single-wavelength laser-component response matrix. Experimental module 2 is used to excite the flow field and wall pressure sensitive coating with a single wavelength excitation light source when the experimental platform is adjusted from the test condition to the experimental condition, and simultaneously collect component fluorescence intensity signals of different detection bands to form a fluorescence intensity observation vector and coating luminescence signal. The component inversion calculation module 3 is used to perform inversion calculation on the fluorescence intensity observation vector based on the single-wavelength laser-component response matrix to obtain the content information of each target component, including oxygen. Pressure calculation module 4 is used to calculate the pressure information at the monitoring location using the oxygen component content information, and output the component content information and pressure distribution at the monitoring location.

[0047] Regarding the apparatus in the above embodiments, the specific manner in which each module performs its operation has been described in detail in the embodiments related to the method, and will not be elaborated upon here.

[0048] For the device embodiments, since they basically correspond to the method embodiments, the relevant parts can be referred to in the description of the method embodiments. The device embodiments described above are merely illustrative. The units described as separate components may or may not be physically separate, and the components shown as units may or may not be physical units, that is, they may be located in one place or distributed across multiple network units. Some or all of the modules can be selected to achieve the purpose of this application according to actual needs. Those skilled in the art can understand and implement this without creative effort.

[0049] Accordingly, this application also provides an electronic device, comprising: one or more processors; a memory for storing one or more programs; and when the one or more programs are executed by the one or more processors, causing the one or more processors to implement the above-described method for deep coupling monitoring of the component-pressure field of a scramjet engine test bench.

[0050] Accordingly, this application also provides a computer-readable storage medium storing computer instructions that, when executed by a processor, implement the aforementioned method for deep coupling monitoring of the component-pressure field of a scramjet engine test bench.

[0051] Other embodiments of this application will readily occur to those skilled in the art upon consideration of the specification and practice of the disclosure herein. This application is intended to cover any variations, uses, or adaptations of this application that follow the general principles of this application and include common knowledge or customary techniques in the art not disclosed herein. The specification and embodiments are to be considered exemplary only.

[0052] It should be understood that this application is not limited to the precise structure described above and shown in the accompanying drawings, and various modifications and changes can be made without departing from its scope.

Claims

1. A method for deep coupling monitoring of component-pressure field on a scramjet engine test rig, characterized in that, include: When the experimental platform is adjusted to the test condition, the laser energy and detection efficiency are normalized, and the fluorescence intensity information of various flow field target components in multiple detection bands is collected. The response coefficients of multiple target components under the test single-wavelength laser in different detection bands are obtained, and then the single-wavelength laser-component response matrix is ​​constructed. When the experimental platform is adjusted from the test condition to the experimental condition, a single-wavelength excitation light source is used to excite the flow field and the pressure-sensitive coating on the wall. The fluorescence intensity signals of the components in different detection bands are collected simultaneously to form the fluorescence intensity observation vector and the coating emission signal. Based on the single-wavelength laser-component response matrix, the fluorescence intensity observation vector is inverted to obtain the content information of each target component, including oxygen. The pressure information at the monitoring location is calculated using the oxygen component content information, and the component content information and pressure distribution at the monitoring location are output.

2. The method according to claim 1, characterized in that, The construction of the single-wavelength laser-component response matrix includes: A single-wavelength pulsed laser with spectral frequency selection is used as the excitation source. After the optical path angle is adjusted by a reflector, the original three-dimensional laser is shaped into a sheet laser by a beam-shaping cylindrical lens. While maintaining consistency in the excitation source and optical detection conditions, a single target component is introduced into a controllable calibration environment according to experimental needs, and then the flow field in a predetermined two-dimensional section is excited. The excited flow field component generates a fluorescence intensity signal, which enters the imaging system through the optical window of the scramjet engine test bench. After being collected by the imaging lens, the signal is separated into bands by the spectral separation component and projected into different imaging units of the imaging sensor to realize the acquisition of fluorescence intensity signals of different components. By normalizing the fluorescence intensity signals of the different components based on laser energy and detection efficiency, the response coefficients of each target component in different detection channels are obtained, thereby constructing a single-wavelength laser-component response matrix.

3. The method according to claim 1, characterized in that, It also includes the initialization of the experimental platform, which includes: (1) Initialize the experimental platform spatially, including determining the spatial position of the excitation laser relative to the engine flow channel and the focal length of the imaging system so that the imaging range covers the cross section of the flow field to be measured and the pressure-sensitive coating area. (2) Keep the experimental laser wavelength and the spectral separation components of the camera consistent with those used when constructing the single-wavelength laser-component response matrix; (3) Adjust the operating parameters of the engine test bench to make the flow field reach the predetermined experimental conditions.

4. The method according to claim 1, characterized in that, The fluorescence intensity signals of components collected at different detection bands are used to construct the fluorescence intensity observation vector and the coating luminescence signal, including: After the experimental equipment was initialized, the aforementioned single-wavelength pulsed laser was used as the excitation source to simultaneously excite the target components in the flow field and the pressure-sensitive coating on the wall. The fluorescence signal of the flow field components generated after excitation and the luminescence signal of the pressure-sensitive coating on the wall enter the imaging system through the optical window of the scramjet engine test bench. They are separated by the spectrophotometer according to the preset wavelength and projected onto the sensors of multiple detection channels. At each sampling time, the fluorescence intensity signal is normalized and corrected for laser energy fluctuations and spatial distribution non-uniformity. Simultaneously acquire component fluorescence intensity signals in different bands, combine fluorescence intensity signals from multiple detection channels at the same spatial location to form a fluorescence intensity observation vector, and simultaneously record the luminescence signal of the pressure-sensitive coating.

5. The method according to claim 1, characterized in that, Based on the single-wavelength laser-component response matrix, the fluorescence intensity observation vector is inverted to obtain the content information of each target component, including oxygen, including: Based on the pre-constructed single-wavelength laser-component response matrix, the fluorescence intensity observation vector is inverted to obtain the content information of each target component at the corresponding location; Physical constraints are imposed on the inversion results to eliminate non-physical results and improve the stability and reliability of component inversion.

6. The method according to claim 1, characterized in that, Using the oxygen component content information, the pressure information at the monitoring location is calculated, and the component content information and pressure distribution at the monitoring location are output, including: Using the two-dimensional oxygen concentration field from the content information of each target component and the real-time fluorescence intensity field acquired by the sensor as input variables, the pressure information at the monitoring location is calculated, thereby outputting the component content information and pressure distribution at the monitoring location.

7. A component-pressure field deep coupling monitoring device for a scramjet engine test rig, characterized in that, include: The response matrix construction module is used to normalize the laser energy and detection efficiency when the experimental platform is adjusted to the test condition, collect fluorescence intensity information of multiple flow field target components in multiple detection bands, obtain the response coefficients of multiple target components under the test single-wavelength laser in different detection bands, and then construct the single-wavelength laser-component response matrix. The experimental module is used to excite the flow field and wall pressure-sensitive coating with a single wavelength excitation light source when the experimental platform is adjusted from the test condition to the experimental condition, and simultaneously collect component fluorescence intensity signals of different detection bands to form a fluorescence intensity observation vector and coating luminescence signal. The component inversion calculation module is used to perform inversion calculation on the fluorescence intensity observation vector based on the single-wavelength laser-component response matrix to obtain the content information of each target component, including oxygen. The pressure calculation module is used to calculate the pressure information at the monitoring location using the oxygen component content information, and outputs the component content information and pressure distribution at the monitoring location.

8. An electronic device, characterized in that, include: One or more processors; Memory, used to store one or more programs; When the one or more programs are executed by the one or more processors, the one or more processors implement the method as described in any one of claims 1-6.

9. A computer-readable storage medium storing computer instructions thereon, characterized in that, When executed by the processor, this instruction implements the steps of the method as described in any one of claims 1-6.

Images