CN114754967A - Supersonic flow field pneumatic optical effect wind tunnel comprehensive test platform - Google Patents
Supersonic flow field pneumatic optical effect wind tunnel comprehensive test platform Download PDFInfo
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Abstract
The invention discloses a supersonic flow field aerodynamic optical effect wind tunnel comprehensive test platform, which can simultaneously perform wave advance test, MP test, NPLS test and PIV test under the same wind tunnel operation train number, has large information amount obtained by single measurement, effectively saves the wind tunnel operation train number, reduces the experiment cost, can synchronously obtain flow field parameter information and relevant parameters of aerodynamic optical effect, and is beneficial to analyzing the internal flow mechanism of the aerodynamic optical effect. And moreover, different types of pneumatic optical effect information in the same region can be acquired by using the semi-transparent semi-reflecting mirror, so that the accuracy and the reliability of the pneumatic optical effect test are improved. In addition, through arranging the separation cavity structures which are hermetically arranged above and below the test area, the turbulent boundary layers on the upper wall surface and the lower wall surface of the wind tunnel can not interfere with light transmission, and the accuracy of the pneumatic optical effect test is greatly improved.
Description
Technical Field
The invention relates to the technical field of supersonic flow field experimental devices, in particular to a supersonic flow field aerodynamic optical effect wind tunnel comprehensive test platform.
Background
The existing supersonic flow field aerodynamic optical effect wind tunnel testing device mainly uses a wavefront sensor to record distorted wavefront information of a light beam after passing through a flow field, wherein the wavefront sensor can be a Hartmann wavefront sensor or a shearing interferometer wavefront sensor, and then researchers can evaluate the strength and distribution characteristics of the flow field aerodynamic optical effect based on the distorted wavefront information, so as to provide a basis for aerodynamic optical effect research and correction.
However, since the wavefront sensor is limited by the performance of its own sensor, the frame rate of general test is relatively low, and it is not possible to obtain the beam jitter information of high frequency frames (Malley Probe, MP technique). I.e. MP testing cannot be performed. In addition, corresponding flow field parameter information is not synchronously acquired, and the physical connotation of the related law of the pneumatic optical effect cannot be researched from the flow mechanism. Therefore, the conventional wind tunnel testing device for the aerodynamic optical effect of the supersonic flow field can only perform a single testing means of forward wave testing, cannot acquire flow field parameter information and information required by MP testing, and cannot deeply analyze the internal flow mechanism of the aerodynamic optical effect.
Disclosure of Invention
The invention provides a supersonic flow field aerodynamic optical effect wind tunnel comprehensive test platform, which solves the technical problems that the conventional supersonic flow field aerodynamic optical effect wind tunnel test device can only carry out a single test means of forward test, cannot acquire flow field parameter information and information required by MP test, and cannot deeply analyze the flow mechanism in the aerodynamic optical effect.
According to one aspect of the invention, a wind tunnel comprehensive test platform for aerodynamic optical effects of an ultrasonic flow field is provided, which comprises a first separation chamber, a second separation chamber, a laser light source, a laser, a semi-transparent and semi-reflective mirror, a wavefront detection device, a first position detector, a diaphragm and a CCD camera, wherein the first separation chamber is hermetically installed on an upper side plate of an experimental section of wind tunnel equipment, the second separation chamber is hermetically installed on a lower side plate of the experimental section of the wind tunnel equipment, the first separation chamber and the second separation chamber are arranged oppositely, the laser light source is positioned on the outer side of the second separation chamber and used for emitting continuous laser, the diaphragm is arranged in the second separation chamber and positioned on a transmission path of the continuous laser and used for adjusting the size of an optical aperture, the semi-transparent and semi-reflective mirror is positioned on the outer side of the first separation chamber and used for dividing the continuous laser which passes through the second separation chamber and the first separation chamber into two transmission light paths, the first position detector and the wavefront detection device are respectively located on two light paths, the first position detector is used for obtaining information required by MP test, the wavefront detection device is used for obtaining information required by the wavefront test, the laser is located on the outer side of the first separation cavity and used for emitting laser pulse, and the CCD camera is located on the outer side of the second separation cavity and used for shooting particle images of tracer particles in supersonic airflow and obtaining information required by NPLS test and PIV test.
The multi-channel high-precision synchronous controller is respectively connected with the CCD camera, the wavefront detection device, the first position detector and the pressure sensor of the wind tunnel, and when testing is carried out, the multi-channel high-precision synchronous controller detects a pressure jump signal when the wind tunnel starts to operate by using the pressure sensor of the wind tunnel as a synchronous control trigger signal, and controls the CCD camera, the wavefront detection device and the first position detector to carry out synchronous acquisition after the preset time is prolonged.
Furthermore, the laser pulse wavelength that the laser instrument sent is 532nm, the continuous laser wavelength that laser light source sent is 632.8nm, install the notch filter who contains 632.8nm wave band in front of the camera lens of CCD camera for eliminate the interference of continuous laser to NPLS test and PIV test.
Furthermore, a spatial filter for beam shrinking and filtering is arranged between the laser light source and the diaphragm.
Furthermore, the device also comprises a second position detector for recording environment and noise of the test system, and provides basis for data noise filtering of the recorded data of the first position detector in the later period.
Furthermore, the first separation cavity comprises an experiment model, a vertical knife, an optical separation cavity and optical glass, the top of the optical separation cavity is hermetically installed on an upper side plate of the wind tunnel experiment section, the vertical knife is installed on the upper side plate of the wind tunnel experiment section and located in front of the optical separation cavity, the experiment model is hermetically installed at the bottoms of the vertical knife and the optical separation cavity, a glass installation hole is formed in the experiment model, and the optical glass is hermetically installed in the glass installation hole.
Further, the included angle of the front edge of the vertical knife ranges from 15 degrees to 30 degrees.
Furthermore, the optical glass is provided with a step, the glass mounting hole on the experimental model is a step hole, a first sealing ring is arranged between the step surface of the optical glass and the step surface of the glass mounting hole, and a second sealing ring is arranged between the top surface of the optical glass and the bottom surface of the optical separation cavity.
Furthermore, a third sealing ring is arranged between the top surface of the optical separation cavity and the upper side plate of the wind tunnel experiment section, and a fourth sealing ring is arranged between the bottom surface of the optical separation cavity and the experiment model.
Further, the experiment model is supersonic speed air film experiment board, supersonic speed air film experiment board forms spray tube and supersonic speed air film air supply line including experiment board, the supersonic speed air film of taking the back step, take the experiment board seal installation of back step optics separate the chamber and found the sword on, supersonic speed air film forms spray tube detachably seal installation on take the experiment board of back step, supersonic speed air film air supply line installs take on the experiment board of back step, supersonic speed air film air supply line respectively with outside air supply supersonic speed air film forms the spray tube intercommunication for supersonic speed air film forms the spray tube and provides cooling gas.
The invention has the following effects:
the supersonic flow field aerodynamic optical effect wind tunnel comprehensive test platform can simultaneously perform wave front test, MP test, NPLS test and PIV test under the same wind tunnel operation train number, the amount of information obtained by single measurement is large, the wind tunnel operation train number is effectively saved, the experiment cost is reduced, flow field parameter information and aerodynamic optical effect related parameters can be synchronously obtained, and the analysis of the internal flow mechanism of the aerodynamic optical effect is facilitated. And moreover, different types of pneumatic optical effect information in the same region can be acquired by using the semi-transparent semi-reflecting mirror, so that the accuracy and the reliability of the pneumatic optical effect test are improved. In addition, the influence of an upper wall turbulence boundary layer of the wind tunnel can be eliminated by arranging the first separation cavity in a sealing manner above the test area, and the influence of a lower wall turbulence boundary layer of the wind tunnel can be eliminated by arranging the second separation cavity in a sealing manner below the test area, so that the upper wall turbulence boundary layer and the lower wall turbulence boundary layer of the wind tunnel cannot interfere with light transmission, and the accuracy of the aerodynamic optical effect test is greatly improved.
In addition to the objects, features and advantages described above, other objects, features and advantages of the present invention are also provided. The present invention will be described in further detail below with reference to the drawings.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, are included to provide a further understanding of the invention, and are incorporated in and constitute a part of this specification. In the drawings:
fig. 1 is a schematic structural arrangement diagram of a supersonic flow field aero-optical effect wind tunnel comprehensive test platform according to a preferred embodiment of the present invention.
Fig. 2 is a schematic timing control diagram of a supersonic flow field aerodynamic optical effect wind tunnel comprehensive test platform according to a preferred embodiment of the present invention.
Fig. 3 is a recording data timing of the NPLS/PIV test determined using the photodetector in the preferred embodiment of the present invention.
Fig. 4 is a schematic view of the structure of the first compartment of the preferred embodiment of the present invention mounted on the upper side plate of the experimental section.
Fig. 5 is a schematic view of the optical compartment and optical glass mounting structure of the first compartment according to the preferred embodiment of the invention.
Fig. 6 is a schematic diagram of an exploded configuration of the optical compartment and optical glass of the first compartment of the preferred embodiment of the present invention.
FIG. 7 is a schematic structural view of a laboratory plate with a back step according to a preferred embodiment of the present invention.
Fig. 8 is a schematic structural view of a supersonic gas film forming nozzle according to a preferred embodiment of the present invention.
Description of the reference numerals
1. A first compartment; 2. a second compartment; 3. a laser light source; 4. a laser; 5. a semi-transparent semi-reflective mirror; 6. a wavefront sensing device; 7. a first position detector; 8. a diaphragm; 9. a spatial filter; 10. a second position detector; 11. an experimental model; 12. erecting a cutter; 13. an optical compartment; 14. an optical glass; 141. a first seal ring; 142. a second seal ring; 131. a third seal ring; 132. a fourth seal ring; 111. an experimental plate with a rear step; 112. forming a spray pipe by using a supersonic air film; 113. supersonic air film air supply pipeline; 1121. a sealing strip; 1111. a front plate body; 1112. a rear plate body; 1113. a groove; 1114. an air inlet; 100. a gas supply adapter.
Detailed Description
The embodiments of the invention will be described in detail below with reference to the accompanying drawings, but the invention can be embodied in many different forms, which are defined and covered by the following description.
As shown in fig. 1 to 6, a preferred embodiment of the present invention provides an ultrasonic flow field aerodynamic optical effect wind tunnel comprehensive test platform, which is used for performing an aerodynamic optical effect test in an experimental section of a wind tunnel, and includes a first separation chamber 1, a second separation chamber 2, a laser light source 3, a laser 4, a half-mirror 5, a wavefront detection device 6, a first position detector 7, a diaphragm 8, and a CCD camera (not shown in the drawings), where the first separation chamber 1 is hermetically installed on an upper side plate of the experimental section of wind tunnel equipment, the second separation chamber 2 is hermetically installed on a lower side plate of the experimental section of wind tunnel equipment, the first separation chamber 1 and the second separation chamber 2 are oppositely disposed, and a flow field between the first separation chamber 1 and the second separation chamber 2 is a test region. The laser light source 3 is located outside the second separation cavity 2 and is used for emitting continuous laser light, and the diaphragm 8 is arranged in the second separation cavity 2 and located on a transmission path of the continuous laser light and is used for adjusting the size of an optical aperture. The half-transmitting and half-reflecting mirror 5 is located outside the first separation chamber 1 and is configured to divide continuous laser light that has passed through the second separation chamber 2 and the first separation chamber 1 into two transmission light paths, the first position detector 7 and the wavefront detection device 6 are respectively located on the two light paths, the first position detector 7 is configured to acquire information required by an MP test, and the wavefront detection device 6 is configured to acquire information required by a wavefront test. The Laser 4 is located outside the first separation chamber 1 and used for emitting Laser pulses, and the CCD camera is located outside the second separation chamber 2 and used for capturing particle images of tracer particles in supersonic airflow and acquiring information required for NPLS (Nano-concentrator-based Planar Laser Scattering) testing and PIV testing.
The laser source 3 is a continuous laser source, a continuous laser sequentially passes through the second separation chamber 2, the flow field of a test area and the first separation chamber 1 and then is divided into two transmission light paths by the semi-transparent and semi-reflective mirror 5, the wavefront detection device 6 is arranged on one light path and is used for collecting distorted wavefront information required by the wavefront test so as to carry out the wavefront test, the first position detector 7 is arranged on the other light path and is used for collecting light deviation information caused by the flow field in an optical aperture so as to carry out an MP test, different types of pneumatic optical effect information in the same area can be obtained by using the semi-transparent and semi-reflective mirror 5, and the accuracy and the reliability of the pneumatic optical effect test are improved. The laser 4 is a dual-cavity Nd: the YAG laser can emit laser pulses, the laser pulses are captured by the CCD camera after sequentially passing through the first separation chamber 1, the test area flow field and the second separation chamber 2, a trace amount of nanometer tracer particles are deployed in supersonic airflow of the wind tunnel, and the CCD camera can shoot particle images of the nanometer tracer particles, so that plane laser scattering information required by NPLS test and particle image speed field information required by PIV test are obtained, and the NPLS test and the PIV test are facilitated. The plane laser scattering information and the particle image velocity field information are flow field parameter information, and the distorted wavefront information and the light deviation information are pneumatic optical effect parameter information.
In addition, considering that the aerodynamic optical effect test is influenced by the light path integral effect, the invention designs a specific structure to eliminate the influence of a wind tunnel wall surface boundary layer on a test result so as to ensure the accuracy of the test result, particularly, the influence of a wind tunnel upper wall surface turbulent flow boundary layer can be eliminated by arranging the first separation chamber 1 which is hermetically installed above the test area, and the influence of the wind tunnel lower wall surface turbulent flow boundary layer can be eliminated by arranging the second separation chamber 2 which is hermetically installed below the test area, so that the wind tunnel upper and lower wall surface turbulent flow boundary layers can not generate interference on light transmission, and the accuracy of the aerodynamic optical effect test is greatly improved.
It can be understood that the supersonic flow field aerodynamic optical effect wind tunnel comprehensive test platform of the embodiment can simultaneously perform wave advance test, MP test, NPLS test and PIV test under the same wind tunnel operation train number, the amount of information obtained by a single measurement is large, the wind tunnel operation train number is effectively saved, the experiment cost is reduced, flow field parameter information and relevant parameters of the aerodynamic optical effect can be synchronously obtained, and the analysis of the internal flow mechanism of the aerodynamic optical effect is facilitated. Moreover, different types of pneumatic optical effect information in the same area can be obtained by using the semi-transparent semi-reflecting mirror 5, and the accuracy and the reliability of the pneumatic optical effect test are improved. In addition, the influence of a turbulent boundary layer on the upper wall surface of the wind tunnel can be eliminated by arranging the first separation cavity 1 in a sealing manner above the test area, and the influence of the turbulent boundary layer on the lower wall surface of the wind tunnel can be eliminated by arranging the second separation cavity 2 in a sealing manner below the test area, so that the turbulent boundary layers on the upper wall surface and the lower wall surface of the wind tunnel cannot interfere with light transmission, and the accuracy of the pneumatic optical effect test is greatly improved.
It can be understood that the supersonic flow field aerodynamic optical effect wind tunnel comprehensive test platform further comprises a multi-channel high-precision synchronous controller (not shown), and the multi-channel high-precision synchronous controller is respectively connected with the CCD camera, the wavefront detection device 6, the first position detector 7 and the pressure sensor of the wind tunnel. As shown in fig. 2, during testing, the multi-channel high-precision synchronous controller uses a pressure jump signal detected by a pressure sensor of the wind tunnel when the wind tunnel starts to operate as a synchronous control trigger signal, and controls the CCD camera, the wavefront detection device 6, and the first position detector 7 to perform synchronous acquisition after a preset time is prolonged. Wherein, when data acquisition is carried out, the wind tunnel is in a stable operation stage. In addition, as shown in fig. 3, a photodetector can also be used to record the double cavity Nd: and the light-emitting time of the YAG laser, namely the time of positioning NPLS/PIV technology test data.
The wavelength of laser pulse emitted by the laser 4 is 532nm, the wavelength of continuous laser emitted by the laser light source 3 is 632.8nm, and in order to avoid interference of continuous laser adopted by wavefront test and MP test on NPLS/PIV test, a notch filter containing 632.8nm waveband is installed in front of the lens of the CCD camera, so that interference of the continuous laser on the NPLS test and the PIV test can be eliminated, and the accuracy of the NPLS/PIV test is ensured.
Optionally, a spatial filter 9 for beam shrinking and filtering is further arranged between the laser light source 3 and the diaphragm 8, so that on one hand, the size of the light beam can be changed conveniently according to experimental requirements, on the other hand, high-frequency cost in the laser can be filtered, and the quality of the light spot is ensured. In addition, the diaphragm 8 is a circular diaphragm which can be continuously adjusted, the optical aperture of the wavefront test can be adjusted, and the test optical aperture can be changed within the range of 0.1 mm-20 mm.
Optionally, the wind tunnel comprehensive test platform for the aerodynamic optical effect of the supersonic flow field further comprises a second position detector 10 for recording environment and noise of the test system, so as to provide a basis for data noise filtering of the recorded data of the first position detector 7 in a later stage. When the data collected by the first position detector 7 is processed, the data collected by the second position detector 10 is required to be used as data noise, and the data collected by the first position detector 7 is subjected to data noise removal, so that the interference of the noise of the environment and the test system on the MP test is eliminated, and the accuracy of the MP test is ensured.
It is understood that the first compartment 1 and the second compartment 2 have the same structure, and the structures of the two are mirror images, so the structure of the first compartment 1 is used for illustration, and the structure of the second compartment 2 is not described herein again. As shown in fig. 4 to 8, the first separation chamber 1 includes an experiment model 11, a vertical knife 12, an optical separation chamber 13, and optical glass 14, where the optical separation chamber 13 is a cavity structure with two open ends, a top of the optical separation chamber 13 is hermetically mounted on an upper side plate of a wind tunnel experiment section, the vertical knife 12 is mounted on the upper side plate of the wind tunnel experiment section and located in front of the optical separation chamber 13, the experiment model 11 is hermetically mounted at bottoms of the vertical knife 12 and the optical separation chamber 13, a glass mounting hole is formed in the experiment model 11, the optical glass 14 is hermetically mounted in the glass mounting hole, and laser passes through the optical glass 14 and enters a flow field of a test area. The vertical knife 12 and the optical separating cavity 13 may be of an integrated structure or a split structure, and the split structure is preferably adopted in the invention, so that the processing cost can be significantly reduced compared with the overall processing. It can be understood that the first compartment 1 transmits laser light by arranging the sealed optical compartment 13, and the transmission of the laser light is not influenced by a turbulent boundary layer on the upper wall surface of the wind tunnel, so that the accuracy of the pneumatic optical effect test is ensured.
In addition, the front edge of the vertical knife 12 needs to be sharpened, and the included angle of the front edge is made as small as possible, so that the strength of the oblique fundamental wave generated in the supersonic airflow flow field of the wind tunnel is reduced, the direct-connection type wind tunnel overflow blockage caused by overhigh flow pressure at the lower part of the experimental model 11 is avoided, preferably, the included angle of the front edge of the vertical knife 12 is 15-30 degrees, on one hand, the design and processing of the vertical knife 12 are facilitated, and on the other hand, the strength of the oblique fundamental wave is also effectively reduced.
It can be understood that the optical glass 14 is provided with a step, the glass mounting hole on the experimental model 11 is a step hole, a first sealing ring 141 is arranged between the step surface of the optical glass 14 and the step surface of the glass mounting hole, and a second sealing ring 142 is arranged between the top surface of the optical glass 14 and the bottom surface of the optical separation chamber 13. The first sealing ring 141 ensures the sealing requirement between the optical glass 14 and the experimental model 11, and the second sealing ring 142 can enable the optical glass 14 to be tightly pressed against the optical compartment 13, thereby ensuring the sealing performance between the two.
In addition, a third sealing ring 131 is arranged between the top surface of the optical separation cavity 13 and the upper side plate of the wind tunnel experiment section, and a fourth sealing ring 132 is arranged between the bottom surface of the optical separation cavity 13 and the experiment model 11. The third sealing ring 131 is used for sealing between the optical separation cavity 13 and the upper side plate of the wind tunnel experiment section, the fourth sealing ring 132 is used for sealing between the optical separation cavity 13 and the experiment model 11, and the fact that the interior of the optical separation cavity 13 cannot be communicated with a flow field is guaranteed.
It can be understood that the aerodynamic optical effect test mainly studies the influence of a flow field structure generated after supersonic air flow in the wind tunnel passes through the experimental model 11 on light transmission, wherein the structural design of the experimental model 11 is different, and the influence on the light transmission is also different. The experimental model 11 may be a laminar flow flat plate, a supersonic air film experimental plate, or an experimental plate with other structure. In the present invention, the experimental model 11 of the first compartment 1 is a laminar flow flat plate, and the experimental model 11 of the second compartment 2 is an ultrasonic air film experimental plate for illustration. Of course, in other embodiments of the present invention, the experiment models 11 of the two compartments may both adopt laminar flow flat plates, and at this time, the influence of the flat plate boundary layer on the light transmission is mainly studied, or the first compartment 1 adopts an ultrasonic air film experiment plate, and the second compartment 2 adopts a laminar flow flat plate. In addition, the structure of the supersonic air film experimental plate is innovatively designed, specifically, the supersonic air film experimental plate comprises an experimental plate 111 with a back step, a supersonic air film forming nozzle 112 and a supersonic air film air supply pipeline 113, the experimental plate 111 with the back step is hermetically installed at the tops of the optical separation chamber 13 and the vertical knife 12, a glass installation hole with a step is formed in the position, corresponding to the top opening of the optical separation chamber 13, of the experimental plate 111 with the back step, and the optical glass 14 is installed in the glass installation hole. Supersonic speed air film forms spray tube 112 detachably seal installation on taking the experiment board 111 of back step, supersonic speed air film air supply line 113 is installed take on the experiment board 111 of back step, supersonic speed air film air supply line 113 respectively with outside air supply supersonic speed air film forms spray tube 112 intercommunication for it provides cooling gas to form spray tube 112 for supersonic speed air film, and wherein, outside air supply can select an air supply with the wind-tunnel sharing. When the aerodynamic optical effect test is performed, the supersonic air film forming nozzle 112 can form a supersonic cooling air film flow field in a test area, when laser passes through the supersonic cooling air film flow field, the laser is affected by the flow field to generate deviation, and then the wave front test, the MP test, the NPLS test and the PIV test are performed synchronously by collecting information through related sensors. Specifically, supersonic speed air film forms spray tube 112 and has seted up a plurality of installation screw on circumference, supersonic speed air film forms spray tube 112 with take the experiment board 111 of backstage to pass through screwed connection, it is very convenient to install and remove. The spray pipe profile of the supersonic air film forming spray pipe 112 is usually designed by adopting a B-spline curve spray pipe design method, different spray pipe profiles can be designed according to different Mach numbers, and when the supersonic air film forming spray pipe 112 needs to be replaced independently when different Mach numbers are needed, the whole experiment model 11 does not need to be replaced. In addition, the sealing strips 1121 are circumferentially arranged on the bottom surface of the supersonic air film forming nozzle 112, so that the supersonic air film forming nozzle 112 is effectively sealed, only the supersonic cooling air film is allowed to be sprayed out from an outlet, and meanwhile, the installation accuracy of the molded surface of the nozzle is also ensured.
Optionally, take preceding plate body 1111 and the back plate body 1112 of back step of experiment board 111 including integral type structure, the design has the step transition between preceding plate body 1111 and the back plate body 1112, the glass mounting hole is opened promptly and is established on the back plate body 1112, supersonic speed air film forms spray tube 112 and installs on the preceding plate body 1111, preceding plate body 1111 is in supersonic speed air film forms spray tube 112's mounted position department is provided with recess 1113 for form the flat spray tube of big volume and reside in the room, the structural design that the flat spray tube of big volume resided in the room can satisfy the inside cooling demand of last step portion subregion, thereby guarantees that the supersonic speed cooling air film flow field of formation distributes more evenly. Be provided with inlet port 1114 in the recess 1113, inlet port 1114 with supersonic speed air film air supply line 113 sealing connection, cooling gas enters into recess 1113 through supersonic speed air film air supply line 113, inlet port 1114 in, then forms spray tube 112 blowout formation supersonic speed cooling air film through supersonic speed air film.
Optionally, a gas supply adapter joint 100 is further disposed on the upper side plate and/or the lower side plate of the wind tunnel experiment section, and the gas supply adapter joint 100 is connected to the supersonic air film gas supply pipeline 113 and the gas source respectively. Because whole test platform places in the experiment section of wind-tunnel equipment, for the convenience of the arrangement of air supply line, set up gas supply adapter joint 100 on the upper plate and/or the lower plate of wind-tunnel experiment section and realize the intercommunication between air supply and supersonic speed air film air supply line 113.
In addition, still be provided with the threading board on the curb plate and/or the lower plate of wind-tunnel experiment section for supply the sensor circuit to pass, satisfied diversified test demand on the one hand, on the other hand has also guaranteed the leakproofness.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A wind tunnel comprehensive test platform for the aerodynamic optical effect of an ultrasonic flow field is characterized by comprising a first separation chamber (1), a second separation chamber (2), a laser light source (3), a laser (4), a semi-transparent semi-reflective mirror (5), a wavefront detection device (6), a first position detector (7), a diaphragm (8) and a CCD camera, wherein the first separation chamber (1) is hermetically mounted on an upper side plate of an experimental section of wind tunnel equipment, the second separation chamber (2) is hermetically mounted on a lower side plate of the experimental section of the wind tunnel equipment, the first separation chamber (1) and the second separation chamber (2) are oppositely arranged, the laser light source (3) is located on the outer side of the second separation chamber (2) and used for emitting continuous laser, the diaphragm (8) is arranged in the second separation chamber (2) and located on a transmission path of the continuous laser and used for adjusting the size of an optical aperture, the semi-transparent semi-reflecting mirror (5) is located on the outer side of the first separation cavity (1) and used for dividing continuous laser passing through the second separation cavity (2) and the first separation cavity (1) into two transmission light paths, the first position detector (7) and the wavefront detection device (6) are located on the two light paths respectively, the first position detector (7) is used for obtaining information required by MP testing, the wavefront detection device (6) is used for obtaining information required by wavefront testing, the laser (4) is located on the outer side of the first separation cavity (1) and used for emitting laser pulses, and the CCD camera is located on the outer side of the second separation cavity (2) and used for shooting particle images of tracer particles in supersonic velocity airflow and obtaining information required by NPLS testing and PIV testing.
2. The supersonic flow field aerodynamic optical effect wind tunnel comprehensive test platform according to claim 1, further comprising a multi-channel high-precision synchronous controller, wherein the multi-channel high-precision synchronous controller is respectively connected with the CCD camera, the wavefront detection device (6), the first position detector (7) and a pressure sensor of the wind tunnel, and when testing is performed, the multi-channel high-precision synchronous controller detects a pressure jump signal when the wind tunnel starts to operate as a synchronous control trigger signal by using the pressure sensor of the wind tunnel, and controls the CCD camera, the wavefront detection device (6) and the first position detector (7) to perform synchronous acquisition after a preset time is prolonged.
3. The aerodynamic optical effect wind tunnel comprehensive test platform for the supersonic flow field according to claim 1, wherein a laser pulse wavelength emitted by the laser (4) is 532nm, a continuous laser wavelength emitted by the laser light source (3) is 632.8nm, and a notch filter having a band of 632.8nm is installed in front of a lens of the CCD camera to eliminate interference of continuous laser on NPLS test and PIV test.
4. The wind tunnel comprehensive test platform for the aerodynamic optical effect of the supersonic flow field according to claim 1, wherein a spatial filter (9) for beam shrinking and filtering is further arranged between the laser light source (3) and the diaphragm (8).
5. The wind tunnel comprehensive test platform for the aerodynamic optical effect of the supersonic flow field according to claim 1, further comprising a second position detector (10) for recording environmental and test system noise, and providing a basis for data noise filtering of the recorded data of the first position detector (7) at a later stage.
6. The wind tunnel comprehensive test platform for the aerodynamic optical effect in the supersonic flow field according to claim 1, wherein the first separation chamber (1) comprises an experimental model (11), a vertical knife (12), an optical separation chamber (13) and optical glass (14), the top of the optical separation chamber (13) is hermetically installed on an upper side plate of a wind tunnel experimental section, the vertical knife (12) is installed on the upper side plate of the wind tunnel experimental section and located in front of the optical separation chamber (13), the experimental model (11) is hermetically installed at the bottoms of the vertical knife (12) and the optical separation chamber (13), a glass installation hole is formed in the experimental model (11), and the optical glass (14) is hermetically installed in the glass installation hole.
7. The supersonic flow field aerodynamic optical effect wind tunnel comprehensive test platform according to claim 6, wherein the included angle of the front edge of the vertical knife (12) is 15-30 °.
8. The wind tunnel comprehensive test platform for the aerodynamic optical effect of the supersonic flow field according to claim 6, wherein the optical glass (14) has a step, the glass mounting hole on the experimental model (11) is a step hole, a first sealing ring (141) is arranged between a step surface of the optical glass (14) and the step surface of the glass mounting hole, and a second sealing ring (142) is arranged between a top surface of the optical glass (14) and a bottom surface of the optical separation chamber (13).
9. The wind tunnel comprehensive test platform for the aerodynamic optical effect of supersonic flow field according to claim 8, wherein a third seal ring (131) is disposed between the top surface of the optical separation chamber (13) and the upper side plate of the wind tunnel experiment section, and a fourth seal ring (132) is disposed between the bottom surface of the optical separation chamber (13) and the experiment model (11).
10. The wind tunnel comprehensive test platform for supersonic flow field aerodynamic optical effect according to claim 6, it is characterized in that the experimental model (11) is an ultrasonic air film experimental plate, the ultrasonic air film experimental plate comprises an experimental plate (111) with a back step, an ultrasonic air film forming spray pipe (112) and an ultrasonic air film air supply pipeline (113), the experimental plate (111) with the back step is hermetically arranged on the optical separation cavity (13) and the vertical knife (12), the supersonic air film forming spray pipe (112) is detachably and hermetically arranged on the experimental plate (111) with the back step, the supersonic air film air supply pipeline (113) is arranged on the experimental plate (111) with the back step, the supersonic air film air supply pipeline (113) is communicated with an external air source and the supersonic air film forming spray pipe (112) respectively and used for providing cooling air for the supersonic air film forming spray pipe (112).
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN117969012A (en) * | 2024-03-28 | 2024-05-03 | 中国空气动力研究与发展中心高速空气动力研究所 | Multi-period phase shifting synchronous measurement method for flow display of wind tunnel dynamic test |
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