CN207964241U - Device for measuring hypersonic wind tunnel experiment dynamic pressure and space flow field - Google Patents
Device for measuring hypersonic wind tunnel experiment dynamic pressure and space flow field Download PDFInfo
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- CN207964241U CN207964241U CN201820095262.4U CN201820095262U CN207964241U CN 207964241 U CN207964241 U CN 207964241U CN 201820095262 U CN201820095262 U CN 201820095262U CN 207964241 U CN207964241 U CN 207964241U
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- 238000002474 experimental method Methods 0.000 title claims abstract description 31
- 238000012545 processing Methods 0.000 claims abstract description 7
- 230000001360 synchronised effect Effects 0.000 claims abstract description 6
- 238000012360 testing method Methods 0.000 claims description 24
- 239000011248 coating agent Substances 0.000 claims description 12
- 238000000576 coating method Methods 0.000 claims description 12
- 230000003287 optical effect Effects 0.000 claims description 9
- 230000005284 excitation Effects 0.000 claims description 8
- 239000002245 particle Substances 0.000 claims description 8
- 230000009977 dual effect Effects 0.000 claims description 4
- 238000003466 welding Methods 0.000 claims description 4
- 230000011514 reflex Effects 0.000 claims description 3
- 230000001960 triggered effect Effects 0.000 claims description 3
- 230000006835 compression Effects 0.000 abstract description 5
- 238000007906 compression Methods 0.000 abstract description 5
- 238000005259 measurement Methods 0.000 abstract description 5
- 238000000917 particle-image velocimetry Methods 0.000 description 26
- 239000000463 material Substances 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 239000003973 paint Substances 0.000 description 2
- 238000003825 pressing Methods 0.000 description 2
- 210000001367 artery Anatomy 0.000 description 1
- 230000000052 comparative effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000004080 punching Methods 0.000 description 1
- 230000011664 signaling Effects 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- 238000002604 ultrasonography Methods 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
- 210000003462 vein Anatomy 0.000 description 1
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- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The utility model discloses a kind of for measuring hypersonic wind tunnel experiment dynamic pressure and the device of space flow field, including synchronizer, PIV systems, PSP systems, dynamic collect system, dynamic pressure transducer.An initial signal is sent out to BNC synchronizers by trigger switch, and synchronizer inspires two signals simultaneously and triggers measurement and PSP cameras record model surface Pressure behaviour situation of change of the PIV systems to model space flow field respectively；Meanwhile dynamic collect system synchronous acquisition the two signals, and the dynamic pressure transducer by being embedded in inside model, the pressure data on record cast surface are used as the compression force reference value of PSP systems.The utility model has been connected a variety of measuring systems using synchronizer, is realized the synchro measure of multiple physical descriptors, is efficiently solved the sequential correspondence problem of multiple physical descriptors in hypersonic wind tunnel experiment, be effectively improved the efficiency of experiment and data processing.
Description
Technical field
The utility model belongs to hypersonic wind tunnel model test equipment technical field, specifically a kind of to be used for synchro measure
The device of hypersonic wind tunnel model test dynamic pressure and space flow field.
Background technology
For hypersonic wind tunnel, generally by upstream high gas blow punching effect and downstream vacuum container swabbing action come
Generate hypersonic air-flow (Ma >=5).Due to many technical aspects, test required stabilization Hypersonic Flow Field without
Method maintains for a long time, therefore, when Hypersonic Flow Field is established, synchronously completes the measurement of multiple physical descriptors, can effectively contract
The short test period, test efficiency is improved, saves a large amount of human and material resources, financial resources.Also, the same pacing of multiple physical descriptors
Amount, can efficiently solve the sequential correspondence problem of multiple physical descriptors in hypersonic wind tunnel experiment, data processing is greatly improved
Efficiency.
Utility model content
The technical problem to be solved by the present invention is to provide one kind for measuring hypersonic wind tunnel experiment dynamic pressure
With the device of space flow field, which can measure hypersonic wind tunnel experiment dynamic pressure and space flow field simultaneously, promote examination
It tests and data-handling efficiency, solves the sequential correspondence problem of multiple physical descriptors.
For achieving the above object, the utility model uses following technical scheme：
It is a kind of to be used to measure hypersonic wind tunnel experiment dynamic pressure and the device of space flow field, including PIV（Particle
Image velocimetry, Particle Image Velocity）System, PSP（Pressure Sensitive Paint, presser sensor apply
Material）System, dynamic pressure transducer, synchronizer, dynamic collect system；The PIV systems include PIV laser light sources, CCD phases
Machine, particle generator, PIV piece light optical modules and data processing stations；The PSP systems include PSP excitation light sources,
PSP acquires camera, pressure sensitive coating；The pressure sensitive coating is sprayed on test model surface, the dynamic pressure sensing
Device is mounted on inside test model；The CCD camera, PSP acquisition cameras and dynamic collect system are connect with synchronizer.
Further, the PSP excitation light sources, PSP acquisition cameras are directed to high-speed wind tunnel and stay indoor test model.
Further, the light of the PIV laser light sources transmitting reflexes to PIV piece light optical modules by optical mirror；
High-speed wind tunnel side wall in room offers the window of schlieren in room, and the CCD camera passes through the window of schlieren in room and shoots test model.
Further, the PIV laser light sources are dual pulse welding.
Further, the PSP excitation light sources are continuous LED self-luminous ultraviolet light.
Further, the PSP acquisitions camera is high speed camera.
Further, the synchronizer is BNC（Bayonet Nut Connector, bayonet nut connector）Synchronizer.
Further, the PIV systems are triggered with the PSP systems by the way that the synchronizer is synchronous, and by described dynamic
State acquisition system trigger collection signal.
The utility model is used to measure hypersonic wind tunnel experiment dynamic pressure and the device of space flow field, operation principle
It is as follows：
After setting up stable flow fields environment after hypersonic wind tunnel, artificially sent out to BNC synchronizers by trigger switch
An initial trigger signal is sent, after BNC synchronizers receive signal, while two signals is inspired and triggering PIV systems respectively
The situation of change of the acquisition cameras record model surface pressure sensitive coating of measurement and PSP systems to model space flow field；
Meanwhile dynamic collect system synchronous acquisition the two signals, and the dynamic pressure transducer by being embedded in inside model, record
The dynamic pressure data of model surface are used as the compression force reference value of PSP systems.After PIV systems receive trigger signal, pass through arteries and veins
The trace particle in illuminated with laser light region to be measured is rushed, and CCD camera is coordinated to record image, then the operation for passing through data processing stations
Processing obtains the relevant information of space flow field.After PSP systems receive trigger signal, model is coated in by high-speed camera record in advance
The state of the pressure sensitive coating on surface, is transmitted to collecting computer.Dynamic collect system receives PIV systems and PSP systems
Trigger signal is used as initial sequential and corresponds to, meanwhile, it is embedded in mould in multiple dynamic pressure transducers record experiment of model surface
The situation of change of type surface pressing, and gathered data is transmitted to dynamic collect system, it is used as the compression force reference value of PSP systems.
The utility model is used to measure hypersonic wind tunnel experiment dynamic pressure and the device of space flow field, in high ultrasound
Dynamic pressure and the synchro measure of space flow field are realized in fast wind tunnel model test, are effectively increased test efficiency, are shortened
Test period solves the sequential correspondence problem of multiple physical descriptors in experiment, saves experimentation cost and people, material resources consumption,
Application prospect is extensive.And the light path of PIV systems, which is set up, to be used and habitually in the past different methods：With optical mirror and magnetic force mirror
Seat cooperation wind-tunnel schlieren window and laser light sheet make light path can easily be accommodated by laser projection to wind tunnel reservoir structure room, while saving sky
Between.
Description of the drawings
Fig. 1 is the utility model for measuring the one of hypersonic wind tunnel experiment dynamic pressure and the device of space flow field
The structural schematic diagram of a embodiment；
Fig. 2 is the functional block diagram of the measuring device of Fig. 1；
Fig. 3 is that the device for measuring hypersonic wind tunnel experiment dynamic pressure and space flow field of the utility model is practical
Using the Comparative result of measured pressure result and moral aerospace research center；
Fig. 4 is that the device for measuring hypersonic wind tunnel experiment dynamic pressure and space flow field of the utility model is practical
It is distributed using measured model surface pressure；
Fig. 5 is that the device for measuring hypersonic wind tunnel experiment dynamic pressure and space flow field of the utility model is practical
Using measured space flow field result.
Specific implementation mode
Below in conjunction with the accompanying drawings, to the utility model proposes one kind for measure hypersonic wind tunnel experiment dynamic pressure and
The device of space flow field is described in detail.In the description of the present invention, it should be understood that term " left side ", " right side
The orientation or positional relationship of the instructions such as side ", " top ", " lower part ", " bottom " is to be based on the orientation or positional relationship shown in the drawings,
It is merely for convenience of describing the present invention and simplifying the description, not indicating or implying the indicated device or element must have
Specific orientation, with specific azimuth configuration and operation, " first ", " second " etc. are not offered as the significance level of parts, because
This should not be understood as limiting the present invention.The specific size used in the present embodiment technical side solely for the purpose of illustration
Case is not intended to limit the scope of protection of the utility model.
As shown in Fig. 1, the utility model is used to measure hypersonic wind tunnel experiment dynamic pressure and the dress of space flow field
It sets, including PIV（Particle Image Velocity）System, PSP（Pressure Sensitive Paint, pressure sensitive coating）System,
Dynamic pressure transducer 9, synchronizer 12, dynamic collect system 13.PIV systems include PIV laser light sources 5, CCD camera 11, grain
Electronic generator, PIV piece light optical module 7 and data processing stations.PSP systems include PSP excitation light sources 2, PSP acquisition phases
Machine 3, pressure sensitive coating.Pressure sensitive coating is sprayed on 8 surface of test model, and dynamic pressure transducer 9 is mounted on experiment mould
Inside type 8.CCD camera 11, PSP acquisition cameras 3 and dynamic collect system 13 are connect with synchronizer.PIV systems and PSP systems
It is synchronized and is triggered by synchronizer, and pass through dynamic collect system trigger collection signal.
The observation window 4 that PSP excitation light sources 2, PSP acquisitions camera 3 stay 1 top of room by high-speed wind tunnel is directed toward high-speed wind tunnel
Test model 8 in room 1.
The light that PIV laser light sources 5 emit reflexes to PIV piece light light by the optical mirror 6 on magnetic force microscope base
Learn component 7.High-speed wind tunnel offers the window of schlieren in room 10 in 1 side wall of room, and CCD camera 11 is shot by the window of schlieren in room 10 and tested
Model 8.
In the present embodiment, PIV laser light sources 5 select dual pulse welding.PSP excitation light sources select continuous LED self-luminous
Ultraviolet light.PSP acquires camera and selects high speed camera.Synchronizer selects BNC synchronizers.
As shown in Fig. 2, the measuring device work step of the utility model is as follows：
1. preceding completion model 8 installation of experiment and dynamic pressure transducer 9 are embedded, equipment connection is debugged, model surface pressure
The work such as sensitive coating spraying.When Hypersonic Flow Field is begun setting up, the particle generator in PIV systems is controlled, superb
There is dispensing trace particle on velocity of sound wind-tunnel；
2. after setting up stable flow fields environment after hypersonic wind tunnel, by trigger switch artificially to BNC synchronizers
13 send an initial trigger signal, after BNC synchronizers receive signal, while inspiring two signals and triggering PIV respectively
System records the measurement in model space flow field and PSP system acquisitions camera 3 change of test model surface pressing sensitive coating
Change situation；Meanwhile 13 synchronous acquisition of dynamic collect system the two signals, and passed by being embedded in the dynamic pressure inside model
Sensor 9, the dynamic pressure data on record test model surface, is used as the compression force reference value of PSP systems.PIV systems receive tactile
After signalling, the trace particle in region to be measured is illuminated by dual pulse welding 5, and CCD camera 11 is coordinated to record image.PSP
After system receives trigger signal, it is coated in the state of the pressure sensitive coating on test model surface in advance by high-speed camera record,
It is transmitted to collecting computer.Dynamic collect system receives the trigger signal of PIV systems and PSP systems, is used as initial sequential and corresponds to,
Meanwhile being embedded in the variation that model surface pressure is tested in the record experiment of multiple dynamic pressure transducers 9 on test model surface
Situation, and gathered data is transmitted to dynamic collect system 13, it is used as the compression force reference value of PSP systems.
3. PIV systems, the collected related data of PSP systems and dynamic pressure transducer institute are carried out calculation process, obtain
To the dynamic pressure situation of change and space fluency information on test model surface.
From Fig. 3 to 5 as can be seen that the device of the utility model can measure hypersonic wind tunnel experiment dynamic pressure simultaneously
Power, space flow field, and measurement result is accurate and reliable.
Based on the description to the preferred embodiments of the present invention, it should be apparent that be defined by the appended claims
The utility model be not limited only to the specific detail illustrated in specification above, without departing from the utility model aims or
Many obviously change to the utility model of range equally possible reaches the purpose of this utility model.
Claims (8)
1. a kind of for measuring hypersonic wind tunnel experiment dynamic pressure and the device of space flow field, which is characterized in that including PIV
System, PSP systems, dynamic pressure transducer, synchronizer, dynamic collect system；The PIV systems include PIV laser light sources,
CCD camera, particle generator, PIV piece light optical modules and data processing stations；The PSP systems include PSP exciting lights
Source, PSP acquisitions camera, pressure sensitive coating；The pressure sensitive coating is sprayed on test model surface, and the dynamic pressure passes
Sensor is mounted on inside test model；The CCD camera, PSP acquisition cameras and dynamic collect system are connect with synchronizer.
2. it is according to claim 1 for measuring hypersonic wind tunnel experiment dynamic pressure and the device of space flow field,
It is characterized in that, the PSP excitation light sources, PSP acquisition cameras are directed to high-speed wind tunnel and stay indoor test model.
3. it is according to claim 1 for measuring hypersonic wind tunnel experiment dynamic pressure and the device of space flow field,
It is characterized in that, the light of the PIV laser light sources transmitting reflexes to PIV piece light optical modules by optical mirror；High-speed wind tunnel
Side wall in room offers the window of schlieren in room, and the CCD camera passes through the window of schlieren in room and shoots test model.
4. it is according to claim 1 for measuring hypersonic wind tunnel experiment dynamic pressure and the device of space flow field,
It is characterized in that, the PIV laser light sources are dual pulse welding.
5. it is according to claim 1 for measuring hypersonic wind tunnel experiment dynamic pressure and the device of space flow field,
It is characterized in that, the PSP excitation light sources are continuous LED self-luminous ultraviolet light.
6. it is according to claim 1 for measuring hypersonic wind tunnel experiment dynamic pressure and the device of space flow field,
It is characterized in that, the PSP acquisitions camera is high speed camera.
7. it is according to claim 1 for measuring hypersonic wind tunnel experiment dynamic pressure and the device of space flow field,
It is characterized in that, the synchronizer is BNC synchronizers.
8. it is according to claim 1 for measuring hypersonic wind tunnel experiment dynamic pressure and the device of space flow field,
It is characterized in that, the PIV systems are triggered with the PSP systems by the way that the synchronizer is synchronous, and pass through the dynamic acquisition system
System trigger collection signal.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820095262.4U CN207964241U (en) | 2018-01-20 | 2018-01-20 | Device for measuring hypersonic wind tunnel experiment dynamic pressure and space flow field |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820095262.4U CN207964241U (en) | 2018-01-20 | 2018-01-20 | Device for measuring hypersonic wind tunnel experiment dynamic pressure and space flow field |
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| Publication Number | Publication Date |
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| CN207964241U true CN207964241U (en) | 2018-10-12 |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108120583A (en) * | 2018-01-20 | 2018-06-05 | 南京航空航天大学 | For measuring the device of hypersonic wind tunnel experiment dynamic pressure and space flow field |
| CN109520699A (en) * | 2018-12-20 | 2019-03-26 | 中国航天空气动力技术研究院 | A kind of shock tunnel jet flow response speed and stagnation pressure test macro and test method |
| CN110186639A (en) * | 2019-05-17 | 2019-08-30 | 广东工业大学 | A kind of PIV-PTR-TOF-MS wind tunnel test methods and its application |
| CN110823500A (en) * | 2019-11-15 | 2020-02-21 | 中国空气动力研究与发展中心超高速空气动力研究所 | Hypersonic-velocity low-density wind tunnel flow field display method based on electron beam fluorescence |
| CN111174958A (en) * | 2020-01-03 | 2020-05-19 | 西北工业大学 | Rotor blade surface universe dynamic pressure measuring device and method based on phase locking method |
| CN111637591A (en) * | 2020-05-15 | 2020-09-08 | 宁波奥克斯电气股份有限公司 | Filter screen dust removal reminding control method and dust removal reminding device |
| CN112268684A (en) * | 2020-12-14 | 2021-01-26 | 中国空气动力研究与发展中心低速空气动力研究所 | Variable azimuth angle surface pressure measuring system and method for low-speed wind tunnel rotor model |
| CN113092051A (en) * | 2021-06-07 | 2021-07-09 | 中国空气动力研究与发展中心低速空气动力研究所 | Measuring system and measuring method for dynamic pressure and flow field distribution of wind tunnel test |
| CN117969006A (en) * | 2024-03-28 | 2024-05-03 | 中国航空工业集团公司沈阳空气动力研究所 | High-speed wind tunnel high Wen Moxing static aeroelastic test system and method |
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- 2018-01-20 CN CN201820095262.4U patent/CN207964241U/en active Active
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108120583A (en) * | 2018-01-20 | 2018-06-05 | 南京航空航天大学 | For measuring the device of hypersonic wind tunnel experiment dynamic pressure and space flow field |
| CN109520699A (en) * | 2018-12-20 | 2019-03-26 | 中国航天空气动力技术研究院 | A kind of shock tunnel jet flow response speed and stagnation pressure test macro and test method |
| CN109520699B (en) * | 2018-12-20 | 2024-05-03 | 中国航天空气动力技术研究院 | Shock tunnel jet response speed and total pressure testing system and testing method |
| CN110186639B (en) * | 2019-05-17 | 2020-12-08 | 广东工业大学 | PIV-PTR-TOF-MS wind tunnel test method and application thereof |
| CN110186639A (en) * | 2019-05-17 | 2019-08-30 | 广东工业大学 | A kind of PIV-PTR-TOF-MS wind tunnel test methods and its application |
| CN110823500A (en) * | 2019-11-15 | 2020-02-21 | 中国空气动力研究与发展中心超高速空气动力研究所 | Hypersonic-velocity low-density wind tunnel flow field display method based on electron beam fluorescence |
| CN110823500B (en) * | 2019-11-15 | 2021-02-09 | 中国空气动力研究与发展中心超高速空气动力研究所 | Hypersonic-velocity low-density wind tunnel flow field display method based on electron beam fluorescence |
| CN111174958B (en) * | 2020-01-03 | 2021-09-07 | 西北工业大学 | Rotor blade surface universe dynamic pressure measuring device and method based on phase locking method |
| CN111174958A (en) * | 2020-01-03 | 2020-05-19 | 西北工业大学 | Rotor blade surface universe dynamic pressure measuring device and method based on phase locking method |
| CN111637591A (en) * | 2020-05-15 | 2020-09-08 | 宁波奥克斯电气股份有限公司 | Filter screen dust removal reminding control method and dust removal reminding device |
| CN111637591B (en) * | 2020-05-15 | 2021-12-31 | 宁波奥克斯电气股份有限公司 | Filter screen dust removal reminding control method and dust removal reminding device |
| CN112268684A (en) * | 2020-12-14 | 2021-01-26 | 中国空气动力研究与发展中心低速空气动力研究所 | Variable azimuth angle surface pressure measuring system and method for low-speed wind tunnel rotor model |
| CN112268684B (en) * | 2020-12-14 | 2021-03-19 | 中国空气动力研究与发展中心低速空气动力研究所 | Variable azimuth angle surface pressure measuring system and method for low-speed wind tunnel rotor model |
| CN113092051A (en) * | 2021-06-07 | 2021-07-09 | 中国空气动力研究与发展中心低速空气动力研究所 | Measuring system and measuring method for dynamic pressure and flow field distribution of wind tunnel test |
| CN117969006A (en) * | 2024-03-28 | 2024-05-03 | 中国航空工业集团公司沈阳空气动力研究所 | High-speed wind tunnel high Wen Moxing static aeroelastic test system and method |
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