CN102853918A - Pneumatic optical wavefront ultra-high frequency measurement system and method - Google Patents
Pneumatic optical wavefront ultra-high frequency measurement system and method Download PDFInfo
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Abstract
The invention provides a pneumatic optical wavefront ultra-high frequency measurement system. The pneumatic optical wavefront ultra-high frequency measurement system comprises a first dual-cavity laser device and a second dual-cavity laser device, a first semi-transparent mirror opposite to a light outlet of the first dual-cavity laser device, a first reflector opposite to the light outlet of the second dual-cavity laser device, a first CCD (charge coupled device) camera and a second CCD camera, a synchronous controller, a computer system, a second semi-transparent mirror, a second reflector, a background image, a convex lens and a pore, wherein the first CCD camera and the second CCD camera are arranged in parallel; the computer system is connected to the first CCD camera, the second CCD camera and the synchronous controller; the second semi-transparent mirror is opposite to the lens of the second CCD camera; the second reflector is opposite to the lens of the first CCD camera; the backlight image, the convex lens and the pore are respectively arranged at two opposite sides of a wind tunnel experiment module; the backlight image and the second dual-cavity laser device are arranged at the same side; and the first CCD camera, the second CCD camera, the first dual-cavity laser device and the second dual-cavity laser device are connected to the synchronous controller respectively. The invention also relates to a measurement method. According to the method, the shot background image is subjected to analysis calculation by the computer, so that ultra-high frequency measurement of whole-field pneumatic optical wavefront distortion is achieved.
Description
Technical field
The present invention relates to aerospace field, especially, relate to a kind of Pneumatic optical wavefront ultrahigh frequency measuring system for fields such as supersonic speed Imaging Guidance, airphoto and flying telescopes.In addition, the invention still further relates to a kind of method that comprises above-mentioned measuring system.
Background technology
Pneumatic optical wavefront measurement technology can be used for studying the aero-optical effect that the fields such as supersonic speed Imaging Guidance, airphoto and flying telescope run into.Existing measuring method has a variety of, such as: interferometry, small-bore Beam Technique and Malley probe measurement method etc.Malley probe measurement method commonly used can only be measured the single-point wavefront by the deviation of position transducer with very high frequency measurement light beam, can not carry out measurement of full field.Malley probe measurement method is to utilize frozen flow hypothesis, and the frozen flow hypothesis thinks, air-flow is through in the process of light beam, and the refractive index in flow field only has along the translation on the airflow direction, and does not have the variation of space distribution.Yet in the practical flow field, convection velocity is time-dependent, and flow field structure also is development and change, so the frozen flow hypothesis is not strict correct.Especially for the Pneumatic optical research of supersonic flows, be badly in need of the technology and equipment of a kind of high frequency, measurement of full field wavefront distortion.
Summary of the invention
The object of the invention is to provide a kind of system and method that can measuring intervals of TIME reaches the whole audience Pneumatic optical wavefront of microsecond magnitude, to obtain the data of supersonic turbulent Pneumatic optical wavefront variation time history, realizes that ultrahigh frequency measures.And the equipment of Pneumatic optical wavefront measurement system of the present invention is simple, easy operating.
For achieving the above object, according to an aspect of the present invention, a kind of Pneumatic optical wavefront ultrahigh frequency measuring system is provided, be used for the measurement of ultrahigh frequency is carried out in the Pneumatic optical wavefront distortion of the laser beam by the supersonic wind tunnel Laboratory Module, the supersonic wind tunnel Laboratory Module produces supersonic flow field, comprises the first dual-cavity laser and the second dual-cavity laser that are arranged side by side; The first semi-transparent semi-reflecting lens, the first semi-transparent semi-reflecting lens is over against the light-emitting window of the first dual-cavity laser; The first catoptron, the first catoptron is over against the light-emitting window of the second dual-cavity laser; A CCD camera that is arranged side by side and the 2nd CCD camera; Isochronous controller, first and second CCD camera and first and second dual-cavity laser all are connected in isochronous controller; Computer system, computer system are connected in first and second CCD camera and isochronous controller; The second semi-transparent semi-reflecting lens, the second semi-transparent semi-reflecting lens is over against the camera lens of the 2nd CCD camera; The second catoptron, the second catoptron is over against the camera lens of a CCD camera; Lay respectively at background image and the convex lens of the relative both sides in wind tunnel experiment cabin, background image and first and second dual-cavity laser are positioned at the same side, and contiguous the first semi-transparent semi-reflecting lens; And the aperture between convex lens and the second semi-transparent semi-reflecting lens.
Further, first and second CCD camera is frame straddling cameras.
Further, the first dual-cavity laser and a CCD camera use simultaneously; The second dual-cavity laser and the 2nd CCD camera use simultaneously.
Further, every a branch of laser beam of the first or second dual-cavity laser emission just in time is in respectively within the time shutter scope of the first or the 2nd corresponding CCD camera.
Further, the wind tunnel experiment cabin is provided with optical window, and background image and convex lens are all over against optical window.
According to a further aspect in the invention, a kind of method of Pneumatic optical wavefront ultrahigh frequency measuring system also is provided, it comprises above-mentioned Pneumatic optical wavefront measurement system, computer system is sent first instruction to isochronous controller, and isochronous controller receives that backward the first dual-cavity laser of first instruction and a CCD camera send first control signal; After receiving first control signal, the first predetermined pulse sequential that the first dual-cavity laser is reserved in advance according to computer system is launched the laser beam that illuminates wind tunnel experiment cabin flow field successively; The second predetermined pulse sequential that the one CCD camera is reserved in advance according to computer system is successively to being taken pictures by the background image of illuminated with laser light; Computer system stores the one CCD camera take each time by the background image of illuminated with laser light; Computer system is sent second instruction to isochronous controller, and isochronous controller receives that second backward the second dual-cavity laser of instruction and the 2nd CCD camera send second control signal; After receiving second control signal, the 3rd predetermined pulse sequential that the second dual-cavity laser is reserved in advance according to computer system is launched the laser beam that illuminates wind tunnel experiment cabin flow field successively; The 4th predetermined pulse sequential that the 2nd CCD camera is reserved in advance according to computer system is successively to being taken pictures by the background image of illuminated with laser light; Computer system stores the 2nd CCD camera take each time by the background image of illuminated with laser light; Computing machine carries out cross-correlation calculation to background image and the reference picture of its preservation, obtain the picture displacement of background image, calculate again the Pneumatic optical wavefront distortion in the different moment by picture displacement and the relation of Pneumatic optical wavefront, wherein, in the said process, the first predetermined pulse sequential, the second predetermined pulse sequential, the 3rd predetermined pulse sequential all are less than or equal to 0.2 microsecond ~ 10 microseconds according to the time interval between every adjacent two pulse sequences that reach the 4th predetermined pulse sequential.
Further, after the first dual-cavity laser is received first control signal, each laser cavity of the first laser instrument gives off laser beam according to the first predetermined pulse sequential, each laser beam is successively through the first semi-transparent semi-reflecting lens, background image, wind tunnel experiment cabin, convex lens, aperture, the second semi-transparent semi-reflecting lens and the second catoptron, a CCD camera according to the exposure of the second predetermined pulse sequential respectively to being taken by the background image after being illuminated by each laser beam after the second mirror reflects.
Further, when the first dual-cavity laser and CCD camera work, the second dual-cavity laser and the 2nd CCD camera are closed.
Further, after the second dual-cavity laser is received the second control signal, each laser cavity of the second dual-cavity laser gives off laser beam according to the 3rd predetermined pulse sequential, each laser beam is successively through the first catoptron, the first semi-transparent semi-reflecting lens, background image, wind tunnel experiment cabin, convex lens, aperture, the second semi-transparent semi-reflecting lens, the 2nd CCD camera according to the second predetermined pulse sequential exposure and respectively to seen through by the second semi-transparent semi-reflecting lens illuminated by each laser beam after background image take.
Further, when the second dual-cavity laser and the work of the 2nd CCD camera, the first dual-cavity laser and a CCD camera are closed.
The present invention has following beneficial effect: the present invention utilizes first and second laser instrument of two-chamber, reduced the interval time between every adjacent twice laser beam, thereby effectively reduced the time interval of taking between adjacent twice Pneumatic optical wavefront image, again by background image difference constantly displacement so that calculate different Pneumatic optical wavefront distortions constantly, measure with the ultrahigh frequency of realizing the wavefront distortion of whole audience Pneumatic optical.
Except purpose described above, feature and advantage, the present invention also has other purpose, feature and advantage.The below is with reference to figure, and the present invention is further detailed explanation.
Description of drawings
The accompanying drawing that consists of the application's a part is used to provide a further understanding of the present invention, and illustrative examples of the present invention and explanation thereof are used for explaining the present invention, do not consist of improper restriction of the present invention.In the accompanying drawings:
Fig. 1 is the schematic diagram of the Pneumatic optical wavefront ultrahigh frequency measuring system of the preferred embodiment of the present invention; And
Fig. 2 is the schematic diagram of method of the use Pneumatic optical wavefront ultrahigh frequency measuring system of the preferred embodiment of the present invention.
Embodiment
Below in conjunction with accompanying drawing embodiments of the invention are elaborated, but the multitude of different ways that the present invention can be defined by the claims and cover is implemented.
Referring to Fig. 1, the Pneumatic optical wavefront ultrahigh frequency measuring system of the preferred embodiment of the present invention is used for that ultrahigh frequency is carried out in the Pneumatic optical wavefront distortion of the laser beam by wind tunnel experiment cabin 10 and measures.Wind tunnel experiment cabin 10 comprises optical window 12, so that the background image light that is illuminated by laser beam sees through the optical window 12 in wind tunnel experiment cabin 10.When carrying out the test of Pneumatic optical wavefront, wind tunnel experiment cabin 10 interior generation supersonic flow fields.
The Pneumatic optical wavefront measurement system comprises the first dual-cavity laser 20 and the second dual-cavity laser 26, the first semi-transparent semi-reflecting lens 30, the first catoptron 36, background image 40, convex lens 50, aperture 55, the second semi-transparent semi-reflecting lens 60, the second catoptron 66, a CCD camera 70, the 2nd CCD camera 72, isochronous controller 80 and the computer system 90 that is arranged side by side.The one CCD camera 70 and the 2nd CCD camera 72 are frame straddling cameras.In other embodiments, also can use a plurality of dual-cavity lasers to use side by side.
Preferably, the width of first and second dual- cavity laser 20,26, emission single-pulse laser bundle is 6ns, and the energy of single-pulse laser bundle reaches as high as 500mJ, and wavelength X equals 532nm.The light-emitting window of the first dual-cavity laser 20 is over against the first semi-transparent semi-reflecting lens 30.The light-emitting window of the second dual-cavity laser 26 is over against the first catoptron 36.Apparently, in other embodiments, the first dual-cavity laser 20 and the second dual-cavity laser 26 also can be the multi-cavity laser instrument; Also can adopt a plurality of dual-cavity lasers to use side by side.
The opposite side relative with background image 40 that convex lens 50 are positioned at wind tunnel experiment cabin 10, and over against optical window 12, be used for being received from the laser beam that optical window 12 sees through.
The one CCD camera 70, the 2nd CCD camera 72 are arranged side by side.Wherein, the camera lens of a CCD camera is over against the second catoptron 66; The camera lens of the 2nd CCD camera 72 is over against the second semi-transparent semi-reflecting lens 60.The one CCD camera 70, the 2nd CCD camera 72 all adopt and the first dual-cavity laser 20 and the consistent double-exposure high resolution CCD camera of the second dual-cavity laser 26, and the shortest 200ns that reaches of the time interval of adjacent double exposure, and resolution is 2Kx2K.The one CCD camera 70, the 2nd CCD camera 72 also are connected in computer system 90, so that store the image of a CCD camera 70, the 2nd CCD camera 72 each background images 40 of taking by computer system 90.
Please in conjunction with reference Fig. 2, utilize the method for Pneumatic optical wavefront measurement system of the present invention to comprise the steps:
S1: computer system 90 is sent first instruction to isochronous controller 80.
After isochronous controller 80 is received first instruction, send first control signal to the first dual-cavity laser 20, a CCD camera 70, make the first dual-cavity laser 20 and a CCD camera 70 synchronous workings.At this moment, the second dual-cavity laser 26 and the 2nd CCD camera 72 are closed.
S2: after receiving first control signal of isochronous controller 80, each laser cavity of the first dual-cavity laser 20 is reserved in advance the first predetermined pulse sequential according to computer system 90 and is launched successively the laser beam that illuminates described background image 40; The one CCD camera 70 is reserved the second predetermined pulse sequential successively to being taken pictures by the background image 40 of illuminated with laser light in advance according to computer system 90.
Detailed process is as follows: send laser by one of them laser cavity after the laser delay of the first dual-cavity laser 20 through self, laser is realized swashing by the optical module of the first dual-cavity laser 20 and is shone the first semi-transparent semi-reflecting lens 30 after combiner becomes laser beam.The part light source of this laser beam illuminates background image 40 after seeing through the first semi-transparent semi-reflecting lens 30, and the light of background image sees through optical window 12 again.See through the light beam of optical window 12 through convex lens 50, again by aperture 55 imagings.But after reflecting by the second catoptron 66, the image of small holes 55 imagings falls into the coverage of a CCD camera 70.At this moment, a CCD camera 70 just in time is in the shooting exposure stage after delaying time through camera, with realization this moment is taken by the background image 40 of illuminated with laser light.The one CCD camera 70 is saved to the buffer memory of a CCD camera 70 at the background image 40 that the above-mentioned moment is taken of finishing exposure.
At this moment, the another one laser cavity of the first dual-cavity laser 20 sends laser, based on above-mentioned identical process, 70 pairs of these moment of the one CCD camera are taken by the background image 40 that the laser beam of this another one laser cavity generation illuminates, and will be saved at the background image 40 of taking the buffer memory of a CCD camera 70.Afterwards, the first dual-cavity laser 20 and a CCD camera 70 are closed.
In this step, the laser of launching every a branch of laser beam is generally determined by this first dual-cavity laser 20 time delay, so can by adjusting the camera delay time of a CCD camera 70, just in time be in the time range of a CCD camera 70 corresponding exposures to guarantee every a branch of laser beam that the first dual-cavity laser 20 sends.
S3: the photograph by the background image 40 of illuminated with laser light in these two moment in the buffer memory of a CCD camera 70 transfers to computer system 90, and by computer system 90 storages.
S4: computer system 90 is sent second instruction to isochronous controller 80.
After isochronous controller 80 is received second instruction, send second control signal to the second dual-cavity laser 26 and the 2nd CCD camera 72, make the second dual-cavity laser 26 and the 2nd CCD camera 72 synchronous workings.
S5: after receiving second control signal of isochronous controller 80, each laser cavity of the second dual-cavity laser 26 is reserved in advance the 3rd predetermined pulse sequential according to computer system 90 and is launched successively the laser beam that illuminates described background image 40; The 2nd CCD camera 72 is reserved the 4th predetermined pulse sequential successively to being taken pictures by the background image 40 of illuminated with laser light in advance according to computer system 90.
Detailed process is as follows: send laser by one of them laser cavity after the laser delay of the second dual-cavity laser 26 through self, laser shines the first catoptron 36 after realizing swashing combiner by the optical module of the second dual-cavity laser 26, through laser beam irradiation to the first semi-transparent semi-reflecting lens 30 after 36 reflections of the first catoptron.The part light source of this laser beam illuminates background image 40 after seeing through the first semi-transparent semi-reflecting lens 30, and the light of background image sees through optical window 12 again.See through the light of optical window 12 through convex lens 50, again by aperture 55 imagings.Image through small holes 55 imagings sees through the 60 part transmissions of the second semi-transparent semi-reflecting lens at the camera lens of the 2nd CCD camera 72.At this moment, the 2nd CCD camera 72 just in time is in the shooting exposure stage after delaying time through camera, with realization this moment is taken by the background image 40 of illuminated with laser light.The background image 40 that the 2nd CCD camera 72 is taken the above-mentioned moment after finishing exposure is saved to the buffer memory of the 2nd CCD camera 72.
At this moment, the another one laser cavity of the second dual-cavity laser 26 sends laser, based on above-mentioned identical process, 70 pairs of these moment of the 2nd CCD camera are taken by the background image 40 that the laser beam of this another one laser cavity generation illuminates, and will be saved at the background image 40 of taking the buffer memory of the 2nd CCD camera 70.
In this step, the laser of launching every a branch of laser beam is generally determined by this second dual-cavity laser 26 time delay, so can by adjusting the camera delay time of the 2nd CCD camera 72, just in time be in the time range of the 2nd CCD camera 72 corresponding exposures to guarantee every a branch of laser beam that the second dual-cavity laser 26 sends.
In above-mentioned steps S2 and S5, the first predetermined pulse sequential, the second predetermined pulse sequential, the 3rd predetermined pulse sequential all are less than or equal to 0.2 microsecond ~ 10 microseconds according to the time interval between every adjacent two pulse sequences that reach the 4th predetermined pulse sequential, namely the frequency between every adjacent two pulse sequences can up to 160MHz, be measured with the ultrahigh frequency of realizing the Pneumatic optical distortion.
S6: the background image in the buffer memory of the 2nd CCD camera 72 transfers to computer system 90, and by computer system 90 storages.
S7: computer system 90 is according to the schlieren principle, image and the reference picture of the background image of computer system 90 interior preservations are carried out cross-correlation calculation, can obtain background image 40 in difference displacement constantly, again by background image 40 difference constantly displacement so that calculate different Pneumatic optical wavefront distortions constantly, realize that the hyperfrequency waves front-distortion measures.
The present invention utilizes first and second laser instrument 20,26 of two-chamber, reduced the interval time between every adjacent twice laser beam, thereby effectively reduced the time interval of taking between adjacent twice Pneumatic optical wavefront image, guaranteed that time interval between adjacent twice Pneumatic optical wavefront image is to reaching the microsecond magnitude.
Apparently, in other embodiments, first and second laser instrument 20,26 in the said method also can adopt the multi-cavity laser instrument, with the photo of several very short background images 40 of shooting time interval.
The above is the preferred embodiments of the present invention only, is not limited to the present invention, and for a person skilled in the art, the present invention can have various modifications and variations.Within the spirit and principles in the present invention all, any modification of doing, be equal to replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (10)
1. Pneumatic optical wavefront ultrahigh frequency measuring system, being used for that ultrahigh frequency is carried out in the Pneumatic optical wavefront distortion of the laser beam by the supersonic wind tunnel Laboratory Module measures, described supersonic wind tunnel Laboratory Module produces supersonic flow field, it is characterized in that, described Pneumatic optical wavefront measurement system comprises:
At least one that is arranged side by side the first dual-cavity laser and at least one the second dual-cavity laser;
The first semi-transparent semi-reflecting lens, described the first semi-transparent semi-reflecting lens is over against the light-emitting window of described the first dual-cavity laser;
The first catoptron, described the first catoptron is over against the light-emitting window of described the second dual-cavity laser;
A CCD camera that is arranged side by side and the 2nd CCD camera;
Isochronous controller, described first and second CCD camera and described first and second dual-cavity laser all are connected in described
Isochronous controller;
Computer system, described computer system are connected in described first and second CCD camera and described isochronous controller;
The second semi-transparent semi-reflecting lens, described the second semi-transparent semi-reflecting lens is over against the camera lens of described the 2nd CCD camera;
The second catoptron, described the second catoptron is over against the camera lens of a described CCD camera;
Lay respectively at background image and the convex lens of the relative both sides in described wind tunnel experiment cabin, described background image and described first and second dual-cavity laser are positioned at the same side, and contiguous described the first semi-transparent semi-reflecting lens; And
Aperture between described convex lens and described the second semi-transparent semi-reflecting lens.
2. Pneumatic optical wavefront ultrahigh frequency measuring system according to claim 1 is characterized in that,
Described first and second CCD camera is frame straddling cameras.
3. Pneumatic optical wavefront ultrahigh frequency measuring system according to claim 2 is characterized in that,
Described the first dual-cavity laser and a described CCD camera use simultaneously;
Described the second dual-cavity laser and described the 2nd CCD camera use simultaneously.
4. Pneumatic optical wavefront ultrahigh frequency measuring system according to claim 3 is characterized in that,
Every a branch of laser beam of the described first or second dual-cavity laser emission just in time is in respectively within the time shutter scope of the first or the 2nd corresponding CCD camera.
5. Pneumatic optical wavefront ultrahigh frequency measuring system according to claim 4 is characterized in that,
Described wind tunnel experiment cabin is provided with optical window, and described background image and described convex lens are all over against described optical window.
6. a method of using the Pneumatic optical wavefront ultrahigh frequency measuring system of described claim 1 to 5 any one is characterized in that, comprises the steps:
Described computer system is sent first instruction to described isochronous controller, and described isochronous controller receives that backward described the first dual-cavity laser of described first instruction and a CCD camera send first control signal;
After receiving first control signal, the first predetermined pulse sequential that described the first dual-cavity laser is reserved in advance according to described computer system is launched the laser beam that illuminates described wind tunnel experiment cabin flow field successively; The second predetermined pulse sequential that a described CCD camera is reserved in advance according to described computer system is successively to being taken pictures by the described background image of illuminated with laser light;
The described CCD camera of described computer system stores take each time by the described background image of illuminated with laser light;
Described computer system is sent second instruction to described isochronous controller, and described isochronous controller receives that backward described the second dual-cavity laser of described second instruction and the 2nd CCD camera send second control signal;
After receiving second control signal, the 3rd predetermined pulse sequential that described the second dual-cavity laser (a plurality of dual-cavity lasers and so that every group of result's the time interval can be very little under sequential control) is reserved in advance according to described computer system is launched the laser beam that illuminates described wind tunnel experiment cabin flow field successively; The 4th predetermined pulse sequential that described the 2nd CCD camera is reserved in advance according to described computer system is successively to being taken pictures by the described background image of illuminated with laser light;
Described the 2nd CCD camera of described computer system stores take each time by the described background image of illuminated with laser light;
Described computing machine carries out cross-correlation calculation to described background image and the reference picture of its preservation, obtain the picture displacement of described background image, relation by described picture displacement and Pneumatic optical wavefront calculates Pneumatic optical wavefront distortion OPD again, wherein, in the said process, described the first predetermined pulse sequential, described the second predetermined pulse sequential, described the 3rd predetermined pulse sequential all are less than or equal to 0.2 microsecond ~ 10 microseconds according to the time interval between every adjacent two pulse sequences that reach described the 4th predetermined pulse sequential.
7. Pneumatic optical wavefront ultrahigh frequency measuring method according to claim 6 is characterized in that,
After described the first dual-cavity laser is received described first control signal, each laser cavity of described the first laser instrument gives off laser beam according to described the first predetermined pulse sequential, each laser beam is passed through described the first semi-transparent semi-reflecting lens, described background image, described wind tunnel experiment cabin, described convex lens, described aperture, described the second semi-transparent semi-reflecting lens and described the second catoptron successively, a described CCD camera according to the exposure of described the second predetermined pulse sequential respectively to being taken by the background image after being illuminated by each laser beam after described the second mirror reflects.
8. Pneumatic optical wavefront ultrahigh frequency measuring method according to claim 7 is characterized in that,
When described the first dual-cavity laser and the work of a described CCD camera, described the second dual-cavity laser and the 2nd CCD camera are closed.
9. Pneumatic optical wavefront ultrahigh frequency measuring method according to claim 6 is characterized in that,
After described the second dual-cavity laser is received described the second control signal, each laser cavity of described the second dual-cavity laser gives off laser beam according to described the 3rd predetermined pulse sequential, each laser beam is passed through described the first catoptron successively, described the first semi-transparent semi-reflecting lens, described background image, described wind tunnel experiment cabin, described convex lens, described aperture, described the second semi-transparent semi-reflecting lens, described the 2nd CCD camera according to the exposure of described the second predetermined pulse sequential respectively to seen through by described the second semi-transparent semi-reflecting lens illuminated by each laser beam after background image take.
10. Pneumatic optical wavefront ultrahigh frequency measuring method according to claim 9 is characterized in that,
When described the second dual-cavity laser and the work of described the 2nd CCD camera, described the first dual-cavity laser and a CCD camera are closed.
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5304809A (en) * | 1992-09-15 | 1994-04-19 | Luxtron Corporation | Luminescent decay time measurements by use of a CCD camera |
| CN102435411A (en) * | 2011-09-05 | 2012-05-02 | 中国人民解放军国防科学技术大学 | Full-field measurement system and method for reynolds stress of compressible turbulent flow |
| CN102435407A (en) * | 2011-09-05 | 2012-05-02 | 中国人民解放军国防科学技术大学 | Shooting system and method for shooting high-speed turbulence flowing image in wind tunnel test |
| CN102564731A (en) * | 2010-12-16 | 2012-07-11 | 中国科学院西安光学精密机械研究所 | Lens focal length and wavefront distortion measuring device |
-
2012
- 2012-08-24 CN CN201210305954.4A patent/CN102853918B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5304809A (en) * | 1992-09-15 | 1994-04-19 | Luxtron Corporation | Luminescent decay time measurements by use of a CCD camera |
| CN102564731A (en) * | 2010-12-16 | 2012-07-11 | 中国科学院西安光学精密机械研究所 | Lens focal length and wavefront distortion measuring device |
| CN102435411A (en) * | 2011-09-05 | 2012-05-02 | 中国人民解放军国防科学技术大学 | Full-field measurement system and method for reynolds stress of compressible turbulent flow |
| CN102435407A (en) * | 2011-09-05 | 2012-05-02 | 中国人民解放军国防科学技术大学 | Shooting system and method for shooting high-speed turbulence flowing image in wind tunnel test |
Non-Patent Citations (1)
| Title |
|---|
| 田立丰: "超声速光学头罩流场精细结构及其气动光学效应的机理研究", 《中国博士学位论文全文数据库》, 31 December 2011 (2011-12-31) * |
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