CN114184348B - High-enthalpy flow field photoelectric characteristic identification device and method - Google Patents
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Abstract
The invention provides a device and a method for identifying high-enthalpy flow field photoelectric characteristics, wherein the device comprises a model, a high-enthalpy shock tunnel, a test light path system and a data processing system; the high enthalpy shock tunnel is used for generating high enthalpy airflow; a plurality of photoelectric probes are arranged at different positions in the model and used for acquiring spectral information of the surface of the model; the test light path system is arranged outside the test section and comprises a photoelectric probe II, a grating and a spectrometer, the photoelectric probe II collects the spectral information of the surface of the model through an optical window of the test section, and the collection light path of the photoelectric probe II is intersected with the collection light path of the photoelectric probe I on the surface of the model; the spectral information acquired by the photoelectric probe II is transmitted to the spectrometer after being processed by the grating, the photoelectric probe I transmits the acquired spectral information to the spectrometer, then the spectrometer transmits the spectral information to the data processing system, the spectral information is extracted according to a spectral analysis method and principle, and the photoelectric characteristics of the high-enthalpy flow field on the surface of the model are obtained by combining the non-equilibrium numerical simulation technology of the multi-component multi-temperature model.
Description
Technical Field
The invention belongs to the technical field of high-enthalpy shock wave wind tunnel engineering, and particularly relates to a high-enthalpy flow field photoelectric characteristic identification device and method.
Background
When the aircraft enters planet atmosphere such as the earth, mars and the like, ambient gas can generate high temperature of thousands of degrees or even tens of thousands of degrees through shock wave heating or viscosity retardation, so that gas molecule vibration energy is excited, dissociated, compounded and ionized, the ambient gas of the aircraft presents high-temperature gas properties, and the physical properties and flow field properties of the gas molecules are obviously changed. The high temperature effect is mainly expressed in the following three aspects: 1) the molecular and atomic energy excitation and chemical reaction of the gas absorb a large amount of energy, the temperature of a flow field can be reduced, and the pressure gradient can be changed, so that the stress and heating environment of the aircraft can be changed; 2) the plasma sheath formed by ions and electrons generated by thermochemical reaction at high temperature has a shielding effect on the wireless communication of the aircraft, so that the black account phenomenon is caused; 3) photon radiation is generated by energy level transition of gas atoms and molecules at high temperature, the optical characteristics of the aircraft are changed due to the optical radiation phenomenon, and the thermal environment of the aircraft can be changed due to serious optical radiation. The photoelectric properties of the aircraft and its wake also have an impact on the identification, surveillance, tracking and interception of targets. The non-equilibrium effect is dominant in high temperature due to low density and fast flying speed. The photoelectric characteristics of the aircraft are always the leading topic of aerodynamic research due to the importance and complexity of the photoelectric characteristics, so that the identification research on the photoelectric characteristics of a high-enthalpy flow field needs to be continuously and deeply carried out, and a feasible idea verified by a ground test is provided for the identification, monitoring, tracking and interception of an aircraft target.
Disclosure of Invention
In order to overcome the defects in the prior art, the inventor of the invention carries out intensive research and provides a device and a method for identifying the photoelectric characteristics of a high-enthalpy flow field, and the device and the method can obtain continuous spectrum information of components of the flow field around a model through a single test, further obtain the ultraviolet, visible light and infrared light radiation intensity of the flow field around the model, and also can obtain the vibration temperature of the flow field and the component information of each molecule, thereby completing the invention.
The technical scheme provided by the invention is as follows:
in a first aspect, a high enthalpy flow field photoelectric characteristic identification device comprises a model 1, a high enthalpy shock tunnel, a test light path system and a data processing system; the high-enthalpy shock tunnel comprises a spray pipe, a test section and a shock tube, wherein the shock tube is sequentially communicated with the downstream spray pipe and the downstream test section, test gas subjected to temperature and pressure increase in the shock tube flows through the spray pipe to form high-enthalpy gas, and the high-enthalpy gas flows through a model after entering the test section; a plurality of optical windows are arranged on the test section and are sealed by optical glass II;
the model is of a large blunt head or flat head structure, and a plurality of photoelectric probes (shown in figure 2) are arranged at different positions in the model and are used for acquiring spectral information of the surface of the model;
the test light path system is arranged outside the test section and is built based on a spectrograph, and comprises a photoelectric probe II, a grating and a spectrograph, wherein the photoelectric probe II acquires spectral information of the surface of the model through an optical window of the test section, the number of the photoelectric probes II is the same as that of the photoelectric probes I, and an acquisition light path of the photoelectric probes II is intersected with that of an acquisition light path of the photoelectric probes I on the surface of the model; the spectrum information collected by the photoelectric probe II is processed by the grating and then is sent to the spectrometer, the photoelectric probe I sends the collected spectrum information to the spectrometer, the spectrometer is used for recording the spectrum information emitted by flowing gas along a certain direction, the two paths of spectrum information are sent to the data processing system for comparison and fusion, and then the nonequilibrium numerical simulation technology of the multi-component multi-temperature model is combined to obtain the photoelectric characteristics of the high enthalpy flow field on the surface of the model.
In a second aspect, a method for identifying photoelectric characteristics of a high enthalpy flow field includes the following steps:
triggering the pressure sensor after the incident shock wave reaches the tail end of the shock tube, and starting the spectrometer to work by a triggering signal generated by the shock tube tail end sensor;
the number of the photoelectric probes II is the same as that of the photoelectric probes I, the acquisition light paths of the photoelectric probes II and the photoelectric probes I are intersected on the surface of the model, and the spectral information of the surface of the model is respectively acquired;
the spectrum information collected by the photoelectric probe II is processed by a grating and then is sent to the spectrometer, the photoelectric probe I sends the collected spectrum information to the spectrometer, the spectrometer is used for recording the spectrum information emitted by flowing gas along a certain direction, the two paths of spectrum information are sent to the data processing system through optical fibers for comparison and fusion, and then the nonequilibrium numerical simulation technology of the multi-component multi-temperature model is combined to obtain the photoelectric characteristics of the high enthalpy flow field on the surface of the model.
The device and the method for identifying the photoelectric characteristics of the high-enthalpy flow field have the following beneficial effects:
the device and the method for identifying the photoelectric characteristics of the high-enthalpy flow field provide a feasible idea verified by a ground test for identification, monitoring, tracking and interception of an aircraft target, and not only can continuous spectrum information of components of the flow field at multiple positions around the model be obtained through one test, further ultraviolet, visible light and infrared light radiation intensity of the flow field around the model be obtained, but also vibration temperature of the flow field and component information of each molecule can be obtained.
Drawings
FIG. 1 is a schematic diagram of a high enthalpy flow field photoelectric characteristic identification device;
FIG. 2 is a schematic structural diagram of a model for mounting an optoelectronic probe;
FIG. 3 is the spectrum information measured by the photoelectric probe II;
fig. 4 is the spectrum information measured by the photoelectric probe I.
Description of the reference numerals
1-model; 2-photoelectric probe I; 3-optical glass I; 4-spraying a pipe; 5-test section; 6-photoelectric probe II; 7-grating; 8-optical glass II; 9-a spectrometer; 10-a data processing system; 11-shock tube.
Detailed Description
The features and advantages of the present invention will become more apparent and appreciated from the following detailed description of the invention.
The word "exemplary" is used exclusively herein to mean "serving as an example, embodiment, or illustration. Any embodiment described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other embodiments. While the various aspects of the embodiments are presented in drawings, the drawings are not necessarily drawn to scale unless specifically indicated.
According to a first aspect of the present invention, a high enthalpy flow field photoelectric characteristic identification apparatus is provided, as shown in fig. 1, including a model 1, a high enthalpy shock tunnel, a test light path system and a data processing system; wherein,
the high-enthalpy shock tunnel comprises a spray pipe 4, a test section 5 and a shock tube 11, wherein the shock tube 11 is sequentially communicated with the downstream spray pipe 4 and the downstream test section 5, the test gas subjected to temperature and pressure increase in the shock tube 11 flows through the spray pipe 4 to form high-enthalpy gas, and the high-enthalpy gas flows through a model 1 after entering the test section 5; a plurality of optical windows are arranged on the test section 5 and are sealed by optical glass II 8;
the model 1 is of a large blunt head or flat head structure, and a plurality of photoelectric probes 2 (shown in figure 2) are arranged at different positions in the model and used for collecting spectral information of the surface of the model;
the test light path system is arranged outside the test section 5 and is built based on a spectrometer 9, and comprises a photoelectric probe II 6, a grating 7 and the spectrometer 9, wherein the photoelectric probe II 6 collects spectrum information of the surface of the model through an optical window of the test section 5, the number of the photoelectric probes II 6 is the same as that of the photoelectric probes I2, and the collection light paths of the photoelectric probes II 6 and the photoelectric probes I2 are intersected on the surface of the model (namely, the collection light paths outside the test section and the collection light paths in the model 1 are intersected on the surface of the model); the spectrum information collected by the photoelectric probe II 6 is processed by the grating 7 and then is sent to the spectrometer 9, the photoelectric probe I2 sends the collected spectrum information to the spectrometer 9, the spectrometer 9 is used for recording the spectrum information emitted by flowing gas along a certain direction, the two paths of spectrum information are sent to the data processing system 10 for comparison and fusion, and then the non-equilibrium numerical simulation technology of the multi-component multi-temperature model is combined to obtain the photoelectric characteristics of the high enthalpy flow field on the surface of the model.
In a preferred embodiment, an optical glass I3 is mounted on the model 1 corresponding to the mounting position of the photoelectric probe I2, the optical glass I3 does not absorb and reflect the flow field spectrum, the surface is polished, the optical glass I3 is matched with the model for processing, and the surface of the joint is in smooth transition.
In a preferred embodiment, a grating may be installed between the photoelectric probe I2 and the spectrometer 9, and the collected spectral information is processed by the grating and then sent to the spectrometer 9. Spectral information I recorded by the spectrometer (9)VIs the integral effect of a certain path through the flow area. Because the model 1 is positioned on the axis of the spray pipe (4), the flow of the flow field on the surface of the model is axisymmetric, and for the axisymmetric flow, the following flows are provided:
wherein, R is the radius of the flow section, namely the distance reached by the spectrum emitted by the photoelectric probe; r is the radial coordinate, i.e. the path from the starting point to R, and x is the starting point coordinate, i.e. the position of the photoelectric probe. For axisymmetric flows or complex three-dimensional flows, integral equations similar to those described above can be established, and solutions to the spectral emittance ε have been developedvThe numerical method of (1).
Spectral emissivity epsilonvIs a convolution of the spectral line profile and the instrument function, i.e.
Wherein A, B-intercept and slope of the continuum;
ν0-measuring the centre frequency of a selected reference line within the spectrum;
εlk-the total emissivity of the kth spectral line in the spectral band;
Pk(k) -a profile function of the kth spectral line within the spectral segment;
s (v) -Meter function;
v-spectral line frequency;
v "-high vibrational state frequency;
v-Low vibrational state frequency.
In a preferred embodiment, the high enthalpy flow field is generated by a high enthalpy shock tunnel, the high enthalpy shock tunnel can reproduce a high-temperature and high-pressure flight environment, the outlet of the high enthalpy spray pipe 4 provides pure test gas, the test gas can be air, carbon dioxide, pure nitrogen and the like, and the total temperature of the test gas exceeds 3000K.
In a preferred embodiment, a pressure sensor is mounted at the end of the shock tube 11, the pressure sensor is triggered when the test gas reaches the end of the shock tube 11, and the spectrometer 9 is started to operate by a trigger signal generated by the pressure sensor.
In the invention, the spectrometer 9 can not only measure the flowing ultraviolet spectrum, visible light spectrum and infrared spectrum, but also obtain the vibration temperature and component information of the flow field. Specifically, the vibration temperature T is measured by a bilinear methodVCalculating T by using the emission intensity of two spectral lines of a certain elementV:
In the formula, E1And E2Respectively excitation potential, cm, of two spectral lines-1；λ1、λ2Two lines of wavelength, nm; I.C. A1And I2Is its relative strength; a. the1And A2Two lines of self-luminous transition probabilities are respectively; the coefficient 0.6247 is related to the unit used for the excitation potential, e.g., in electron volts (eV), the coefficient would be 5040.
Quantitative measurement of different component components can be obtained by matching the obtained spectral information (formula 1) with a Lomakin formula and an internal standard method, and a Boltzmann distribution map is obtained according to the Boltzmann distribution law.
In the invention, a spectrometer acquires two paths of flow field information, and the molecular spectrum detection and data processing system 10 is combined with the unbalanced numerical simulation technology of a multi-component multi-temperature model to obtain the photoelectric characteristics of the high-enthalpy flow field. Specifically, the invention adopts two measurement angles to acquire the photoelectric characteristics of the flow field: one is to collect the light path focusing from the outside of the surrounding flow field; one method is to install a small quartz glass observation window on the surface of the model to realize measurement from the surface of the model, avoid flow field interference and focus the light path on the surface of the front section of the model.
In a preferred embodiment, the data processing system (10) determines physical quantities such as continuous spectral brightness, total spectral line emissivity, Doppler width, half-width of dispersion and the like by using a least square method to obtain molecular spectral data with different energy levels.
In a preferred embodiment, the control equation of the non-equilibrium numerical simulation technique of the multi-component multi-temperature model is a three-dimensional non-equilibrium Navier-Stokes equation:
in the formula, U is a constant vector, F, G, E is a convection flux vector in each direction of a rectangular coordinate system, Fv、Gv、EvIs viscous flux term in each direction, W is chemical reaction and vibration energy source term vector, QRThe divergence term of the radiation flux, x, y, z are the coordinate axes, and t is time.
According to a second aspect of the present invention, there is provided a method for identifying an optoelectronic characteristic of a high enthalpy flow field, the specific process is as shown in fig. 1, and the method includes the following steps:
when the incident shock wave reaches the end of the shock tube 11, the spectrometer 9 works by a trigger signal generated by a sensor at the end of the shock tube 11;
the number of the photoelectric probes II 6 is the same as that of the photoelectric probes I2, and the acquisition light paths of the photoelectric probes II and the photoelectric probes I are intersected on the surface of the model to respectively acquire spectral information of the surface of the model;
the spectrum information collected by the photoelectric probe II 6 is processed by the grating 7 and then is sent to the spectrometer 9, the photoelectric probe I2 sends the collected spectrum information to the spectrometer 9, the spectrometer 9 is used for recording the spectrum information emitted by flowing gas along a certain direction, the two paths of spectrum information are sent to the data processing system 10 through optical fibers for comparison and fusion, the spectrum information of a flow field is obtained after processing, and the graph in FIGS. 3 and 4 is the measurement result of the total temperature 4050K and the total pressure 20.3MPa on the surface of the model, so that the spectrum can be clearly seen to have a peak value in the graph from 500 nm to 600 nm. And comparing and verifying by combining a non-equilibrium numerical simulation technology of the multi-component multi-temperature model to obtain the photoelectric characteristics of the high-enthalpy flow field on the surface of the model.
The invention has been described in detail with reference to specific embodiments and illustrative examples, but the description is not intended to be construed in a limiting sense. Those skilled in the art will appreciate that various equivalent substitutions, modifications or improvements may be made to the technical solution of the present invention and its embodiments without departing from the spirit and scope of the present invention, which fall within the scope of the present invention. The scope of the invention is defined by the appended claims.
Those skilled in the art will appreciate that those matters not described in detail in the present specification are well known in the art.
Claims (10)
1. A high enthalpy flow field photoelectric characteristic identification device is characterized by comprising a model (1), a high enthalpy shock wave wind tunnel, a test light path system and a data processing system; the high-enthalpy shock tunnel comprises a spray pipe (4), a test section (5) and a shock tube (11), wherein the shock tube (11) is sequentially communicated with the downstream spray pipe (4) and the test section (5), test gas subjected to temperature and pressure increase in the shock tube (11) flows through the spray pipe (4) to form high-enthalpy gas, and the high-enthalpy gas flows through a model (1) after entering the test section (5); a plurality of optical windows are arranged on the test section (5), and the optical windows are sealed by optical glass II (8);
the model (1) is of a large blunt head or flat head structure, and a plurality of photoelectric probes (2) are arranged at different positions in the model and used for collecting spectral information of the surface of the model;
the test light path system is arranged outside the test section (5) and comprises a photoelectric probe II (6), a grating (7) and a spectrometer (9), the photoelectric probe II (6) collects the spectral information of the surface of the model through an optical window of the test section (5), the number of the photoelectric probes II (6) is the same as that of the photoelectric probes I (2), and the collection light paths of the photoelectric probes II (6) and the collection light paths of the photoelectric probes I (2) are intersected on the surface of the model; the spectrum information collected by the photoelectric probe II (6) is processed by the grating (7) and then is sent to the spectrometer (9), the collected spectrum information is sent to the spectrometer (9) by the photoelectric probe I (2), the spectrometer (9) is used for recording the spectrum information emitted by flowing gas along a certain direction, the two paths of spectrum information are sent to the data processing system (10) for comparison and fusion, and then the photoelectric characteristics of the high enthalpy flow field on the surface of the model are obtained by combining the unbalanced numerical simulation technology of the multi-component multi-temperature model.
2. The device for identifying the photoelectric characteristics of the high enthalpy flow field according to claim 1, characterized in that an optical glass I (3) is mounted on the model (1) at a position corresponding to the mounting position of the photoelectric probe I (2), the optical glass I (3) does not absorb and reflect the flow field spectrum, the surface is polished, the optical glass I (3) is matched with the model for processing, and the surface of the joint is in smooth transition.
3. The device for identifying the photoelectric characteristics of the high enthalpy flow field according to claim 1, wherein a grating is installed between the photoelectric probe I (2) and the spectrometer (9), and the collected spectral information IVThe grating is processed and then sent to a spectrometer (9).
4. Device for identifying the photoelectric characteristics of a high enthalpy flow field according to claim 1, characterized in that the spectrometer (9) records spectral information IVIs the integral effect of a certain path through the flow region; because the model (1) is positioned on the axis of the spray pipe (4), the flow of the flow field on the surface of the model is axisymmetric, and for the axisymmetric flow, the flow comprises the following components:
wherein, R is the radius of the flow section, namely the distance reached by the spectrum emitted by the photoelectric probe; r is a radial coordinate, namely a path from a starting point to R, and x is a coordinate of the starting point, namely the position of the photoelectric probe;
spectral emissivity epsilonvIs a convolution of the spectral line profile and the instrument function, i.e.
Wherein A, B-intercept and slope of the continuum;
ν0-measuring the centre frequency of a selected reference line within the spectrum;
εlk-the total emissivity of the kth spectral line in the spectral band;
Pk(k) -a profile function of the kth spectral line within the spectral segment;
s (v) -Meter function;
v-spectral line frequency;
v "-high vibrational state frequency;
v-low vibrational state frequency.
5. The identification device for the photoelectric characteristics of the high enthalpy flow field according to claim 4, wherein the spectrometer (9) is further configured to obtain a vibration temperature of the flow field:
measuring vibration temperature T using a bilinear methodVCalculating T by using the emission intensity of two spectral lines of a certain elementV:
In the formula, E1And E2Respectively excitation potential, cm, of two spectral lines-1；λ1、λ2Two lines of wavelength, nm; I.C. A1And I2Is its relative strength; a. the1And A2Two lines of self-luminous transition probabilities are respectively; the coefficient 0.6247 relates to the unit used for the excitation potential, and if electron volts is used, the coefficient should be 5040.
6. The device for identifying the photoelectric characteristics of the high enthalpy flow field according to claim 4, wherein the spectrometer (9) is further configured to obtain component information of the flow field:
the obtained spectral information is matched with an internal standard method by utilizing a Lomakin formula, so that the quantitative measurement of different component compositions can be obtained.
7. The device for identifying the photoelectric characteristic of the high enthalpy flow field according to claim 1, wherein the total temperature of the test gas provided by the outlet of the nozzle (4) exceeds 3000K, and the nozzle (4) is a high enthalpy nozzle.
8. The device for identifying the photoelectric characteristics of the high enthalpy flow field according to claim 1, wherein a pressure sensor is installed at the end of the shock tube (11), the pressure sensor is triggered when the test gas reaches the end of the shock tube (11), and a trigger signal generated by the pressure sensor starts the spectrometer (9) to work.
9. The identification device for the photoelectric characteristics of the high enthalpy flow field according to claim 1, characterized in that the data processing system (10) determines continuous spectral brightness, total spectral line emissivity, doppler width, and half-width of dispersion by using a least square method to obtain molecular spectral data of different energy levels.
10. A high enthalpy flow field photoelectric characteristic identification method is characterized by comprising the following steps:
the pressure sensor is triggered after the incident shock wave reaches the tail end of the shock tube (11), and a trigger signal generated by the sensor at the tail end of the shock tube (11) starts the spectrometer (9) to work;
the number of the photoelectric probes II (6) is the same as that of the photoelectric probes I (2), and the acquisition light paths of the photoelectric probes II (6) and the photoelectric probes I (2) are intersected on the surface of the model to respectively acquire spectral information of the surface of the model;
the spectrum information collected by the photoelectric probe II (6) is processed by the grating (7) and then is sent to the spectrometer (9), the collected spectrum information is sent to the spectrometer (9) by the photoelectric probe I (2), the spectrometer (9) is used for recording the spectrum information emitted by flowing gas along a certain direction, the two paths of spectrum information are sent to the data processing system (10) through optical fibers for comparison and fusion, and then the photoelectric characteristics of the high-enthalpy flow field on the surface of the model are obtained by combining the unbalanced numerical simulation technology of the multi-component multi-temperature model.
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112067241A (en) * | 2020-08-19 | 2020-12-11 | 中国航天空气动力技术研究院 | High-enthalpy shock tunnel total temperature measurement method |
| CN112067243A (en) * | 2020-08-25 | 2020-12-11 | 中国航天空气动力技术研究院 | Flow field temperature measuring method for high-enthalpy shock tunnel |
| CN112378616A (en) * | 2020-11-16 | 2021-02-19 | 中国科学技术大学 | High-speed flow field multi-parameter measurement system and method based on wavelength modulation absorption spectrum |
| CN112747891A (en) * | 2020-12-23 | 2021-05-04 | 中国航天空气动力技术研究院 | High-enthalpy airflow space resolution measuring device and method based on mid-infrared laser absorption spectrum |
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Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112067241A (en) * | 2020-08-19 | 2020-12-11 | 中国航天空气动力技术研究院 | High-enthalpy shock tunnel total temperature measurement method |
| CN112067243A (en) * | 2020-08-25 | 2020-12-11 | 中国航天空气动力技术研究院 | Flow field temperature measuring method for high-enthalpy shock tunnel |
| CN112378616A (en) * | 2020-11-16 | 2021-02-19 | 中国科学技术大学 | High-speed flow field multi-parameter measurement system and method based on wavelength modulation absorption spectrum |
| CN112747891A (en) * | 2020-12-23 | 2021-05-04 | 中国航天空气动力技术研究院 | High-enthalpy airflow space resolution measuring device and method based on mid-infrared laser absorption spectrum |
Non-Patent Citations (2)
| Title |
|---|
| 高焓激波风洞试验技术综述;谌君谋等;《空气动力学学报》;20180815(第04期);4 * |
| 高超声速再入试验的辐射光谱定量测量;余晓娅等;《中国光学》;20200215(第01期);92-99 * |
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