CN104296995A - Engine jet flame characteristic test device and method in atmospheric absorption wave band - Google Patents
Engine jet flame characteristic test device and method in atmospheric absorption wave band Download PDFInfo
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- CN104296995A CN104296995A CN201410528328.0A CN201410528328A CN104296995A CN 104296995 A CN104296995 A CN 104296995A CN 201410528328 A CN201410528328 A CN 201410528328A CN 104296995 A CN104296995 A CN 104296995A
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- infrared imager
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Abstract
The invention discloses an engine jet flame characteristic test device and method in the atmospheric absorption wave band. The device comprises a Fourier spectrometer, a high-temperature calibration black body and a thermal infrared imager, wherein the Fourier spectrometer, the thermal infrared imager and an engine to be tested are all located in the plane of an engine test bed, the Fourier spectrometer and the body of the engine to be tested are located on the same side of a nozzle of the engine to be tested, and the thermal infrared imager is located on the other side of the nozzle of the engine to be tested. The test method comprises the steps that first, the atmospheric transmissivity of a tested environment is calculated, and a lens of the Fourier spectrometer is selected, and the position of the thermal infrared imager is chosen; second, the high-temperature calibration black body is used for carrying out multi-point radiometric calibration; third, the test device is started, the Fourier spectrometer carries out data acquisition, and the thermal infrared imager acquires infrared image data; finally, atmospheric correction processing is carried out on the acquired data. According to the engine jet flame characteristic test device and method in the atmospheric absorption wave band, the path length of radiation transfer is fully reduced, absorption of atmosphere to jet flame radiation is reduced, high-precision atmospheric correction is achieved through dynamic data, and the precision of test data is improved.
Description
Technical field
The present invention relates to a kind of engine bright eruption characteristic test apparatus and test method, particularly a kind of Atmospheric Absorption wave band intrinsic motivation bright eruption characteristic test apparatus and test method, infrared spectrometer is adopted to be combined the method measuring engine plume ir radiation data with thermal imaging system, be applicable to the test of gas absorption bands intrinsic motivation bright eruption characteristic, belong to engine characteristics test field.
Background technology
The infrared signature of engine bright eruption is the key foundation data of the application such as early warning, supervision.Compared with target surface radiation, there is stronger singularity in the radiation of engine bright eruption, Research Challenges is mainly reflected in: one is that the flow field that the burning of engine non-fully is formed has stronger uncertainty, airsetting two-way coupling body also exists the energy level transition mechanism such as transmitting, scattering, absorption simultaneously, and flow field is formed and radiation transporting mechanism complex; Two be the radiation of engine bright eruption concentrate on 2.7 μm with 4.3 μm, belong to strong Atmospheric Absorption wave band, affect by steam in air and carbon dioxide absorption, actinometry test cannot be carried out on ground at a distance, space-based measurement means does not still possess, and relevant rudimentary data accumulation is in blank substantially.
Mainly both at home and abroad to carry and airborne measurement mode based on spaceborne, ball, but experimentation cost and complicacy larger.Journal of writings " Comparison of calculated and measured radiation from a rocket motor plume " (AIAA, calendar year 2001) attempt the liquid engine Radiation biodosimetry carried out in 4-5 μm of atmospheric window broadband, but the data of 4.3 μm of absorption bands cannot be obtained;
Journal of writings " experiment of solid propellant rocket jet flow infrared radiation and calculating research " (Acta Astronautica, 01 phase in 2008) describe bright eruption measurement scheme under vacuum environment, under about 90kPa and 5kPa two environmental pressures, the infrared intensity of Scaled rocket motor chamber pressure and jet flow is measured, because vacuum environment cannot be measured 1:1 high thrust motor, therefore the method has limitation, cannot be applied to the feature measurement of rocket sustainer.
Summary of the invention
Technology of the present invention is dealt with problems and is: overcome the deficiencies in the prior art, a kind of Atmospheric Absorption wave band intrinsic motivation bright eruption characteristic test apparatus and test method are proposed, the engine bright eruption multi-dimensional feature data acquisition methods adopting near field light spectrometer to combine with far field thermal imaging system and data processing method, the method fully have compressed the path of radiation transmission, thus reduce the absorption of air to bright eruption radiation, improve valid signal strengths, and realize high precision atmospheric correction by dynamic data, improve the precision of test figure.
Technical solution of the present invention is: a kind of Atmospheric Absorption wave band intrinsic motivation bright eruption characteristic test apparatus, comprising: Fourier spectrometer, high temperature calibration blackbody and thermal infrared imager;
Before test, high temperature calibration blackbody is connected with Fourier spectrometer and thermal infrared imager optics respectively, completes the radiation calibration to Fourier spectrometer and thermal infrared imager;
Tested engine is fixedly mounted on engine testsand, and Fourier spectrometer, thermal infrared imager and tested engine are all positioned at engine testsand plane;
The fuselage of Fourier spectrometer and tested engine is positioned at the homonymy of tested engine nozzle, thermal infrared imager is positioned at opposite side, distance wherein between Fourier spectrometer and tested engine nozzle is 4 ~ 6m, and the distance between thermal infrared imager and tested engine nozzle is greater than 40m;
The optical axis of Fourier spectrometer and the optical axis of thermal infrared imager intersect, and intersection point is positioned on the extended line of tested engine nozzle axis.
The intersection point of the optical axis of described Fourier spectrometer and the optical axis of thermal infrared imager and the distance of spout end are 0.5 ~ 1m.
Based on a test method for test unit in claim 1, step is as follows:
(1) utilize propagation in atmosphere software, calculate test environment atmospheric transmittance;
(2) according to the distance of Fourier spectrometer and tested engine, select the camera lens of Fourier spectrometer, and determine the angle between line between Fourier spectrometer and tested engine nozzle and tested engine fuselage axis;
(3) according to field range and the test site size of thermal infrared imager, the position of thermal infrared imager is determined;
(4) according to the temperature range of tested engine given in advance, high temperature calibration blackbody is utilized to carry out multiple spot radiation calibration to Fourier spectrometer in temperature range given in advance; The temperature range of described tested engine varies in size given in advance according to the thrust of tested engine;
(5) respectively Fourier spectrometer and thermal infrared imager are aimed at, make preset points on the spout axis extended line of tested engine in field of view center position;
(6) time standard of Fourier spectrometer and thermal infrared imager is unified, start proving installation, tested engine ignition starts to carry out Atmospheric Absorption wave band intrinsic motivation bright eruption attribute testing, the emittance data of Fourier spectrometer to tested engine gather, and the infrared picture data of thermal infrared imager to tested engine gathers;
(7) data acquisition in step (6) is completed, the atmospheric transmittance of the infrared picture data that the emittance data utilizing Fourier spectrometer to gather, thermal infrared imager gather and step (1) carries out atmospheric correction process, is specially:
Period of the tested engine radiation energy stabilization of emittance extracting data collected from Fourier spectrometer is as the analystal section of absorption bands, the integral energy that selective radiation secondary peak is 4.145 ~ 4.176 μm is as basis for estimation, analyze and show that radiation variation is less than the period of predetermined threshold value, emittance mean value is asked in this analystal section, after atmospheric correction, obtain bright eruption radiance size, extract wake flame area according to the infrared picture data that thermal infrared imager gathers, radiance is multiplied by wake flame area and can obtains bright eruption radiation intensity mean size.
The present invention's beneficial effect is compared with prior art:
(1) Fourier spectrometer is placed in and carries out approaching measurement under the minimum safe distance of bright eruption by the present invention, and the transmission path of bright eruption radiation is at utmost compressed, particularly evident to strong absorption bands (4.3 μm) effect especially;
(2) traditional measurement is placed in front, bright eruption side, and the spectral radiance recorded is vulnerable to the white cigarette interference produced in commissioning process; Fourier spectrometer of the present invention is placed in bright eruption proceeds posterolateral to carry out approaching measurement, and on direction of visual lines, medium interference is few, greatly reduces the uncertainty that optical thickness calculates, and improves the precision of atmospheric correction process;
(3) dynamic rule that the present invention is based on measurement data carries out atmospheric correction process, reduces air and absorbs by force the impact with noise of equipment, improve the precision of data processing.
Accompanying drawing explanation
Fig. 1 is testing equipment schematic layout pattern of the present invention;
Fig. 2 is method of testing process flow diagram of the present invention;
Fig. 3 is traditional measurement mode and the measure spectrum Data Comparison example approaching metering system, and the curve of spectrum wherein a) for utilizing traditional measurement mode to draw, b) for utilizing the curve of spectrum approaching metering system and draw of the present invention;
Fig. 4 is the atmospheric transmittance curve under different transmission range.
Embodiment
Be illustrated in figure 1 experimental layout of the present invention schematic diagram, as shown in Figure 1, a kind of Atmospheric Absorption wave band intrinsic motivation bright eruption characteristic test apparatus that the present invention proposes, a kind of Atmospheric Absorption wave band intrinsic motivation bright eruption characteristic test apparatus, is characterized in that comprising: Fourier spectrometer 1, high temperature calibration blackbody 2 and thermal infrared imager 4;
Before test, high temperature calibration blackbody 2 is connected with Fourier spectrometer 1 and thermal infrared imager 4 optics respectively, completes the radiation calibration to Fourier spectrometer 1 and thermal infrared imager 4;
Tested engine 3 is fixedly mounted on engine testsand, and Fourier spectrometer 1, thermal infrared imager 4 and tested engine 3 are all positioned at engine testsand plane;
The fuselage of Fourier spectrometer 1 and tested engine 3 is positioned at the homonymy of tested engine 3 spout, thermal infrared imager 4 is positioned at opposite side, distance wherein between Fourier spectrometer 1 and tested engine 3 spout is 4 ~ 6m, and the distance between thermal infrared imager 4 and tested engine 3 spout is greater than 40m;
The optical axis of Fourier spectrometer 1 and the optical axis of thermal infrared imager 4 intersect, and intersection point is positioned on the extended line of tested engine 3 spout axis, and the intersection point of the optical axis of described Fourier spectrometer 1 and the optical axis of thermal infrared imager 4 and the distance of spout end are 0.5 ~ 1m.
Based on a test method for test unit in claim 1, as shown in Figure 2, as shown in Figure 2, the method step in the present invention is as follows for process flow diagram:
(1) utilize propagation in atmosphere software, calculate test environment atmospheric transmittance;
(2) according to the distance of Fourier spectrometer and tested engine, select the camera lens of Fourier spectrometer, and determine the angle between line between Fourier spectrometer and tested engine nozzle and tested engine fuselage axis; According to the distance of Fourier spectrometer 1 with tested engine 3, select the camera lens of Fourier spectrometer 1, the camera lens selection principle of Fourier spectrometer is as follows:
I the visual field fabric width of () spectrometer 1 can not exceed bright eruption diameter, namely can not comprise the component of non-bright eruption in visual field;
(ii) visual field of spectrometer 1 can not be too small, should be easy to aim at location.
Angle determination principle is as follows:
Under guaranteeing that spectrometer visual field does not cover the prerequisite of tested engine 3 spout, select less security standpoint according to test site actual conditions;
(3) according to field range and the test site size of thermal infrared imager, the position of thermal infrared imager is determined; In Fig. 1, B is thermal infrared imager 4 position, and A is that thermal infrared imager 4 hangs down a little with tested engine 3 spout extended line, and O is for aiming at scaling point, and C is spectrometer 1 position, and D is that spectrometer 1 hangs down a little with tested engine 3 fuselage extended line.The instrument explosive area corresponding according to tested engine 3 thrust, thermal infrared imager 4 is placed in outside explosive area; Distance between Fourier spectrometer 1 and tested engine 3 spout is 4 ~ 6m, and during calibration, high temperature calibration blackbody 2 is placed in Fourier spectrometer 1 dead ahead;
(4) according to the temperature range of tested engine given in advance, high temperature calibration blackbody is utilized to carry out multiple spot radiation calibration to Fourier spectrometer in temperature range given in advance; The temperature range of described tested engine varies in size given in advance according to the thrust of tested engine;
(5) respectively Fourier spectrometer and thermal infrared imager are aimed at, make preset points on the spout axis extended line of tested engine 3 in field of view center position;
(6) time standard of Fourier spectrometer and thermal infrared imager is unified, start proving installation, tested engine ignition starts to carry out Atmospheric Absorption wave band intrinsic motivation bright eruption attribute testing, the emittance data of Fourier spectrometer to tested engine gather, and the infrared picture data of thermal infrared imager to tested engine gathers;
(7) data acquisition in step (6) is completed, the atmospheric transmittance of the infrared picture data that the emittance data utilizing Fourier spectrometer to gather, thermal infrared imager gather and step (1) carries out atmospheric correction process, is specially: be specially:
I
t＝(L
w-L
n)·A/τ
Wherein L
wfor containing the spectrometer measurement value (radiance) during target, L
nfor the spectrometer measurement value (measured value before engine ignition) not containing target, τ is atmospheric transmittance, and A is wake flame area, I
tfor target radiant intensity;
Period of the tested engine radiation energy stabilization of emittance extracting data collected from Fourier spectrometer is as the analystal section of absorption bands, the integral energy that selective radiation secondary peak is 4.145 ~ 4.176 μm is as basis for estimation, analysis draws the radiation metastable period, emittance mean value is asked in this analystal section, after atmospheric correction, obtain bright eruption radiance size, extract wake flame area according to the infrared picture data that thermal infrared imager gathers, radiance is multiplied by wake flame area and can obtains bright eruption radiation intensity mean size.
Embodiment 1
(1) according to test environment condition, the rule of atmospheric transmittance and transmission range is calculated.Be 16.5 DEG C in medial temperature, air medial humidity is 65%, and Fourier spectrometer 1 is placed in the proceeds posterolateral at distance engine nozzle 5m place, 4.21 ~ 4.32 μm of mean transmissivities can reach 0.2, nearly 20 times of the signal increase that instrument receives.
(2) according to the distance of Fourier spectrometer 1 with tested engine 3, determine to select suitable camera lens, visual field is 28mrad.According to the profile of field angle and engine, guaranteeing in the unscreened situation in visual field, selecting ∠ COD=30 °.
(3) according to the visual field 5mrad of thermal infrared imager 4, and test site size, determine the position of thermal infrared imager 4, OB=42m, AB=14m.
(4) according to the roughly temperature range of tested engine 3, utilize high temperature calibration blackbody 2 to carry out multiple spot radiation calibration at similar temperature place to Fourier spectrometer 1, calibration temperature gets 500 DEG C, 800 DEG C.
(5) Fourier spectrometer 1, thermal infrared imager 4 are manually aimed at, guarantee that the spout of tested engine 3 is in field of view center position.
(6) starting outfit, personnel withdraw scene, wait for that tested engine 3 is lighted a fire.
(7) Fig. 3 provides the measurement data curve that test gathers, a) curve of spectrum for utilizing traditional measurement mode (spectrometer is placed in front, bright eruption side) to draw, b) for utilizing the curve of spectrum approaching metering system and draw of the present invention, can find out, near 4.3 μm, original signal is flooded by noise substantially, approaches measurement and is significantly improved.
(8) Dynamic radiation data are utilized to carry out atmospheric correction process.Adopt based on the method for Dynamic radiation data, from spectrometer collection to dynamic data spectral space extract period of stable radiation, and as the analystal section of absorption bands.
(9) Fig. 4 gives the atmospheric transmittance curve under 4.15 ~ 4.4 μm of different transmission ranges.In figure, three curves are by the transmitance representing 5m, 15m, 30m under upper respectively.Calculate through atmospheric correction, Fourier spectrometer measuring equipment is placed in the proceeds posterolateral at distance engine nozzle 5m place by the present invention, 4.21 ~ 4.32 μm of mean transmissivities can reach 0.2, the signal that instrument receives increases nearly 20 times than traditional measurement method, significantly improves the contrast of useful signal and system noise.
The present invention proposes engine bright eruption characteristic test method, and the infrared flame plume radiation feature measurement that can be in absorption bands provides resolving ideas, for the detecting band optimization, detectivity assessment etc. of high temperature military target provide test method to support.
Claims (3)
1. an Atmospheric Absorption wave band intrinsic motivation bright eruption characteristic test apparatus, is characterized in that comprising: Fourier spectrometer (1), high temperature calibration blackbody (2) and thermal infrared imager (4);
Before test, high temperature calibration blackbody (2) is connected with Fourier spectrometer (1) and thermal infrared imager (4) optics respectively, completes the radiation calibration to Fourier spectrometer (1) and thermal infrared imager (4);
Tested engine (3) is fixedly mounted on engine testsand, and Fourier spectrometer (1), thermal infrared imager (4) and tested engine (3) are all positioned at engine testsand plane;
The fuselage of Fourier spectrometer (1) and tested engine (3) is positioned at the homonymy of tested engine (3) spout, thermal infrared imager (4) is positioned at opposite side, distance wherein between Fourier spectrometer (1) and tested engine (3) spout is 4 ~ 6m, and the distance between thermal infrared imager (4) and tested engine (3) spout is greater than 40m;
The optical axis of Fourier spectrometer (1) and the optical axis of thermal infrared imager (4) intersect, and intersection point is positioned on the extended line of tested engine (3) spout axis.
2. a kind of Atmospheric Absorption wave band intrinsic motivation bright eruption characteristic test apparatus according to claim 1.It is characterized in that: the optical axis of described Fourier spectrometer (1) and the intersection point of optical axis of thermal infrared imager (4) and the distance of spout end are 0.5 ~ 1m.
3., based on a test method for test unit in claim 1, it is characterized in that step is as follows:
(1) utilize propagation in atmosphere software, calculate test environment atmospheric transmittance;
(2) according to the distance of Fourier spectrometer (1) with tested engine (3), select the camera lens of Fourier spectrometer (1), and determine the angle between line between Fourier spectrometer (1) and tested engine (3) spout and tested engine (3) fuselage axis;
(3) according to field range and the test site size of thermal infrared imager (4), the position of thermal infrared imager (4) is determined;
(4) according to the temperature range of tested engine (3) given in advance, high temperature calibration blackbody (2) is utilized to carry out multiple spot radiation calibration to Fourier spectrometer (1) in temperature range given in advance; The temperature range of described tested engine (3) varies in size given in advance according to the thrust of tested engine (3);
(5) respectively Fourier spectrometer (1) and thermal infrared imager (4) are aimed at, make preset points on the spout axis extended line of tested engine (3) in field of view center position;
(6) time standard of Fourier spectrometer (1) and thermal infrared imager (4) is unified, start proving installation, tested engine (3) igniting starts to carry out Atmospheric Absorption wave band intrinsic motivation bright eruption attribute testing, the emittance data of Fourier spectrometer (1) to tested engine (3) gather, and the infrared picture data of thermal infrared imager (4) to tested engine (3) gathers;
(7) data acquisition in step (6) is completed, the atmospheric transmittance of the infrared picture data that the emittance data utilizing Fourier spectrometer (1) to gather, thermal infrared imager (4) gather and step (1) carries out atmospheric correction process, is specially:
The tested engine of emittance extracting data (3) emittance collected from Fourier spectrometer (1) stable period is as the analystal section of absorption bands, the integral energy that selective radiation secondary peak is 4.145 ~ 4.176 μm is as basis for estimation, analyze and show that radiation variation is less than the period of predetermined threshold value, emittance mean value is asked in this analystal section, after atmospheric correction, obtain bright eruption radiance size, wake flame area is extracted according to the infrared picture data that thermal infrared imager (4) gathers, radiance is multiplied by wake flame area and can obtains bright eruption radiation intensity mean size.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201410528328.0A CN104296995B (en) | 2014-10-09 | Engine flame characteristic test device and test method in atmospheric absorption waveband |
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| CN201410528328.0A CN104296995B (en) | 2014-10-09 | Engine flame characteristic test device and test method in atmospheric absorption waveband |
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| CN104296995A true CN104296995A (en) | 2015-01-21 |
| CN104296995B CN104296995B (en) | 2017-01-04 |
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| CN106382992A (en) * | 2016-09-23 | 2017-02-08 | 西安近代化学研究所 | Rocket engine plume infrared radiation temperature dynamic measurement method |
| CN113281051A (en) * | 2021-06-20 | 2021-08-20 | 昆明理工大学 | Engine infrared heat flow three-dimensional visual air passage flow stabilization experiment table and test method |
| CN115308167A (en) * | 2022-10-11 | 2022-11-08 | 中国航发四川燃气涡轮研究院 | Real-time atmospheric transmittance testing and calculating method for infrared spectrum radiometer of aircraft engine |
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| CN115308167A (en) * | 2022-10-11 | 2022-11-08 | 中国航发四川燃气涡轮研究院 | Real-time atmospheric transmittance testing and calculating method for infrared spectrum radiometer of aircraft engine |
| CN115308167B (en) * | 2022-10-11 | 2023-02-21 | 中国航发四川燃气涡轮研究院 | Real-time atmospheric transmittance testing and calculating method for infrared spectrum radiometer of aircraft engine |
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