CN110595727A - Continuous pressure distribution measuring device in air inlet channel for hypersonic wind tunnel - Google Patents
Continuous pressure distribution measuring device in air inlet channel for hypersonic wind tunnel Download PDFInfo
- Publication number
- CN110595727A CN110595727A CN201911061514.7A CN201911061514A CN110595727A CN 110595727 A CN110595727 A CN 110595727A CN 201911061514 A CN201911061514 A CN 201911061514A CN 110595727 A CN110595727 A CN 110595727A
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- air inlet
- inlet channel
- optical glass
- measuring
- glass window
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- 239000005304 optical glass Substances 0.000 claims abstract description 45
- 238000012360 testing method Methods 0.000 claims abstract description 39
- 230000003287 optical effect Effects 0.000 claims abstract description 20
- 239000000523 sample Substances 0.000 claims abstract description 19
- 239000003973 paint Substances 0.000 claims abstract description 10
- 239000002184 metal Substances 0.000 claims description 7
- 239000010453 quartz Substances 0.000 claims description 6
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N silicon dioxide Inorganic materials O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 6
- 239000011521 glass Substances 0.000 claims description 3
- 239000013307 optical fiber Substances 0.000 claims description 3
- 238000012545 processing Methods 0.000 claims description 3
- 238000002834 transmittance Methods 0.000 claims description 3
- 238000009530 blood pressure measurement Methods 0.000 abstract description 3
- 238000009413 insulation Methods 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- 230000035939 shock Effects 0.000 description 2
- 210000001015 abdomen Anatomy 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000007664 blowing Methods 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000005286 illumination Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/08—Aerodynamic models
Landscapes
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention discloses a continuous pressure distribution measuring device in an air inlet passage for a hypersonic wind tunnel. The device comprises a test model main body arranged on a hypersonic wind tunnel supporting device and an air inlet channel test model positioned below the test model main body; the lower surface of the test model main body is provided with a groove, an optical glass window I covers the groove, and an LED light source array and an optical probe array are arranged in the groove; an air inlet channel is formed in the air inlet channel test model, a hole communicated with the air inlet channel is formed in the upper surface of the air inlet channel test model, and an optical glass window II corresponding to the optical glass window I is covered on the hole; the lower surface of the inner surface of the air inlet channel is a measuring surface, and pressure-sensitive paint is coated on the measuring surface; the optical probe array is connected with the light guide arm, the light guide arm is connected with an external scientific grade CCD camera, and the scientific grade CCD camera is connected with a computer. The device simple structure, simple to operate has effectively solved the inside large tracts of land pressure measurement problem of stand alone type intake duct model under the part shelters from the condition.
Description
Technical Field
The invention belongs to the technical field of hypersonic wind tunnel tests, and particularly relates to a continuous pressure distribution measuring device in an air inlet passage for a hypersonic wind tunnel.
Background
The pressure sensitive paint technology is a new non-contact large-area continuous pressure measurement method developed in the 80 international years. The geometric scaling of the model can cause the wall thickness of the air inlet channel to be thin, measuring points cannot be arranged on a local complex key structure, and therefore enough pressure information cannot be obtained. The pressure sensitive paint measuring device comprises a main model, a pressure sensitive paint measuring device and a pressure sensitive paint measuring device, wherein the main model is used for measuring the pressure of the inner surface of the air inlet channel model. If the model is made to be completely transparent, the light transmission of the model is poor due to large curvature change of the surface of the model main body. This overall transparency or complete opacity does not effectively address the measurement of pressure sensitive paint pressure on the interior surface of the air scoop.
Disclosure of Invention
The invention aims to solve the technical problem of providing a continuous pressure distribution measuring device in an air inlet passage of a hypersonic wind tunnel.
The invention relates to a continuous pressure distribution measuring device in an air inlet passage of a hypersonic wind tunnel, which is characterized in that: the measuring device comprises a test model main body arranged on the hypersonic wind tunnel supporting device and an air inlet channel test model positioned below the test model main body; the lower surface of the test model main body is provided with a groove, an optical glass window I covers the groove, and an LED light source array and an optical probe array are arranged in the groove; the air inlet channel test model is internally provided with an air inlet channel, the upper surface of the air inlet channel test model is provided with a hole communicated with the air inlet channel, and the hole is covered with an optical glass window II corresponding to the optical glass window I; the lower surface of the inner surface of the air inlet channel is a measuring surface, and pressure-sensitive paint is coated on the measuring surface; the optical probe array is connected with the light guide arm, the light guide arm is connected with the external scientific grade CCD camera, and data signals collected by the scientific grade CCD camera are transmitted to the computer for processing.
If the LED light sources in the LED light source array emit ultraviolet light, the optical glass window I and the optical glass window II are quartz optical glass windows, and the ultraviolet light transmittance of the quartz optical glass windows is more than or equal to 70%.
And if the LED light sources in the LED light source array emit visible light, the optical glass window I and the optical glass window II are organic glass windows.
The optical glass window I and the optical glass window II are fixed in a mode of combining bonding and metal edge strip screw pressing.
The LED light source array and the optical probe array are arranged in a crossed mode.
Pressure measuring holes are distributed on the measuring surface.
The light guide arm is replaced by an optical fiber.
The optical glass window I and the optical glass window II in the continuous pressure distribution measuring device for the hypersonic wind tunnel in the invention have uniform thickness, and the collected image has no distortion basically.
The pressure measuring hole in the continuous pressure distribution measuring device used in the air inlet channel of the hypersonic wind tunnel is used as a detection point or a calibration point, and the pressure is measured by adopting a conventional method and is used for calibrating pressure-sensitive paint data.
The scientific grade CCD camera used in the device for measuring the continuous pressure distribution in the air inlet channel of the hypersonic wind tunnel can also adopt a common miniature camera to be directly embedded in the model under the condition that the measurement precision is satisfied.
The scientific grade CCD camera in the device for measuring the continuous pressure distribution in the air inlet channel of the hypersonic wind tunnel is arranged above the test section of the hypersonic wind tunnel, and is not in contact with the main body of the test section in order to avoid the influence caused by vibration of the test section.
The continuous pressure distribution measuring device in the air inlet channel for the hypersonic wind tunnel adopts the embedded LED light source array to realize the illumination of the measuring surface which partially shields the inner surface of the model air inlet channel, adopts the embedded optical probe array and the light guide arm to guide out the optical image, still can adopt the external scientific-grade CCD camera to pick up the image, and keeps the technical parameters of the scientific-grade CCD camera.
The device for measuring the continuous pressure distribution in the air inlet channel of the hypersonic wind tunnel adopts the mode of slotting the test model main body to install the LED light source array and the optical probe array, fully utilizes the internal space of the test model main body, leads the power supply leading-out wire and the light guide arm leading-out wire of the LED light source array and the optical probe array out of the bottom of the test model main body, does not generate excessive interference on the flow around the test model main body, shortens the distance from the LED light source array to the measuring surface, only has optical glass between the LED light source array and the measuring surface and between the LED light source array and the optical probe array and the measuring surface, reduces the energy loss of exciting light, and improves the definition of collected images.
The continuous pressure distribution measuring device in the air inlet channel for the hypersonic wind tunnel has the advantages of simple structure and convenience in installation, and effectively solves the problem of large-area pressure measurement in an independent air inlet channel model under the condition of part shielding.
Drawings
FIG. 1 is a schematic diagram of a device for measuring the continuous pressure distribution in an air inlet of a hypersonic wind tunnel according to the present invention.
In the figure, 1 is a test model main body 2, an air inlet channel test model 3, an optical glass window I4, an LED light source array 5, an optical probe array 6, an optical glass window II 7 and a measuring surface.
Detailed Description
The invention is described in further detail below with reference to the figures and the embodiments.
As shown in fig. 1, the device for measuring the continuous pressure distribution in the air inlet duct of the hypersonic wind tunnel according to the present invention includes a test model main body 1 mounted on a hypersonic wind tunnel supporting device, and an air inlet duct test model 2 located below the test model main body 1; the lower surface of the test model main body 1 is provided with a groove, an optical glass window I3 covers the groove, and an LED light source array 4 and an optical probe array 5 are arranged in the groove; an air inlet channel is formed in the air inlet channel test model 2, a hole communicated with the air inlet channel is formed in the upper surface of the air inlet channel test model 2, and an optical glass window II 6 corresponding to the optical glass window I3 is covered on the hole; the lower surface of the inner surface of the air inlet channel is a measuring surface 7, and pressure-sensitive paint is coated on the measuring surface 7; the optical probe array 5 is connected with a light guide arm, the light guide arm is connected with an external scientific grade CCD camera, and data signals collected by the scientific grade CCD camera are transmitted to a computer for processing.
If the LED light sources in the LED light source array 4 emit ultraviolet light, the optical glass window I3 and the optical glass window II 6 are quartz optical glass windows, and the ultraviolet light transmittance of the quartz optical glass windows is more than or equal to 70%.
And if the LED light sources in the LED light source array 4 emit visible light, the optical glass window I3 and the optical glass window II 6 are organic glass windows.
The optical glass window I3 and the optical glass window II 6 are fixed in a mode of combining bonding and metal edge strip screw pressing.
The LED light source array 4 and the optical probe array 5 are arranged in a crossed manner.
Pressure measuring holes are distributed on the measuring surface 7.
The light guide arm is replaced by an optical fiber.
Example 1
The specific implementation of this example is as follows:
1. a model supporting device is installed in a hypersonic wind tunnel, an LED light source array 4 and an optical probe array 5 which are arranged in a cross mode are installed in a test model main body 1, then an optical glass window I3 is fixed in a mode of combining bonding and metal edge strip screw pressing, and meanwhile a rubber gasket is added between a metal edge strip and the optical glass window I3 for shock insulation.
2. The power supply outgoing lines and the light guide arm outgoing lines of the LED light source array 4 and the optical probe array 5 are LED out from the bottom of the test model main body 1 and fixed on a model tail support rod or an abdomen support plate through a binding belt, the impact of windward airflow is avoided, then the optical probe array 5 is connected to a scientific grade CCD camera, and the scientific grade CCD camera is connected with a computer.
3. Fixing an optical glass window II 6 on the air inlet channel test model 2 in a mode of combining bonding and metal edge strip screw pressing, and simultaneously adding a soft rubber gasket between the metal edge strip and the optical glass window II 6 for shock insulation; the air inlet test model 2 is installed below the test model main body 1.
4. The pressure measuring holes on the measuring surface 7 are calibrated.
5. Hypersonic wind tunnel blowing is carried out, and a scientific grade CCD camera collects a background image and a reference image of the measuring surface 7.
6. And acquiring a continuous pressure distribution image in the air inlet channel by using an image acquired by a computer science-level CCD camera.
Claims (7)
1. A continuous pressure distribution measuring device in intake duct for hypersonic wind tunnel, its characterized in that: the measuring device comprises a test model main body (1) arranged on the hypersonic wind tunnel supporting device and an air inlet channel test model (2) positioned below the test model main body (1); the lower surface of the test model main body (1) is provided with a groove, an optical glass window I (3) covers the groove, and an LED light source array (4) and an optical probe array (5) are arranged in the groove; an air inlet channel is formed in the air inlet channel test model (2), a hole communicated with the air inlet channel is formed in the upper surface of the air inlet channel test model (2), and an optical glass window II (6) corresponding to the optical glass window I (3) is covered on the hole; the lower surface of the inner surface of the air inlet channel is a measuring surface (7), and pressure-sensitive paint is coated on the measuring surface (7); the optical probe array (5) is connected with a light guide arm, the light guide arm is connected with an external scientific grade CCD camera, and data signals collected by the scientific grade CCD camera are transmitted to a computer for processing.
2. The device for measuring the continuous pressure distribution in the air intake duct of the hypersonic wind tunnel according to claim 1, characterized in that: the LED light sources in the LED light source array (4) emit ultraviolet light, the optical glass window I (3) and the optical glass window II (6) are quartz optical glass windows, and the ultraviolet light transmittance of the quartz optical glass windows is more than or equal to 70%.
3. The device for measuring the continuous pressure distribution in the air intake duct of the hypersonic wind tunnel according to claim 1, characterized in that: the LED light sources in the LED light source array (4) emit visible light, and the optical glass window I (3) and the optical glass window II (6) are organic glass windows.
4. The device for measuring the continuous pressure distribution in the air intake duct of the hypersonic wind tunnel according to claim 1, characterized in that: the optical glass window I (3) and the optical glass window II (6) are fixed in a mode of combining bonding and metal edge strip screw pressing.
5. The device for measuring the continuous pressure distribution in the air intake duct of the hypersonic wind tunnel according to claim 1, characterized in that: the LED light source array (4) and the optical probe array (5) are arranged in a crossed mode.
6. The device for measuring the continuous pressure distribution in the air intake duct of the hypersonic wind tunnel according to claim 1, characterized in that: pressure measuring holes are distributed on the measuring surface (7).
7. The device for measuring the continuous pressure distribution in the air intake duct of the hypersonic wind tunnel according to claim 1, characterized in that: the light guide arm is replaced by an optical fiber.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911061514.7A CN110595727A (en) | 2019-11-01 | 2019-11-01 | Continuous pressure distribution measuring device in air inlet channel for hypersonic wind tunnel |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911061514.7A CN110595727A (en) | 2019-11-01 | 2019-11-01 | Continuous pressure distribution measuring device in air inlet channel for hypersonic wind tunnel |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110595727A true CN110595727A (en) | 2019-12-20 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911061514.7A Pending CN110595727A (en) | 2019-11-01 | 2019-11-01 | Continuous pressure distribution measuring device in air inlet channel for hypersonic wind tunnel |
Country Status (1)
| Country | Link |
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| CN (1) | CN110595727A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110702367A (en) * | 2019-11-01 | 2020-01-17 | 中国空气动力研究与发展中心超高速空气动力研究所 | Continuous pressure measuring device for shielding position of parallel model of hypersonic wind tunnel |
| CN111751076A (en) * | 2020-06-09 | 2020-10-09 | 西安交通大学 | Device and method for measuring flow coefficient of pressurizing cabin runner based on pressure sensitive paint |
| CN113252282A (en) * | 2021-06-23 | 2021-08-13 | 中国空气动力研究与发展中心超高速空气动力研究所 | Wind tunnel closed experiment section window observation device and application thereof |
| CN114486152A (en) * | 2021-12-29 | 2022-05-13 | 中国航空工业集团公司西安飞机设计研究所 | Pressure-sensitive paint pressure measurement data correction method |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2006010517A (en) * | 2004-06-25 | 2006-01-12 | Japan Aerospace Exploration Agency | Insitu measuring technique of pressure-sensitive coating to which correction of temperature dependence is added and apparatus therefor |
| CN106989891A (en) * | 2017-03-30 | 2017-07-28 | 南京航空航天大学 | Hypersonic inlet accelerates self-starting experimental method |
| CN210603820U (en) * | 2019-11-01 | 2020-05-22 | 中国空气动力研究与发展中心超高速空气动力研究所 | Continuous pressure distribution measuring device in air inlet channel for hypersonic wind tunnel |
-
2019
- 2019-11-01 CN CN201911061514.7A patent/CN110595727A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2006010517A (en) * | 2004-06-25 | 2006-01-12 | Japan Aerospace Exploration Agency | Insitu measuring technique of pressure-sensitive coating to which correction of temperature dependence is added and apparatus therefor |
| CN106989891A (en) * | 2017-03-30 | 2017-07-28 | 南京航空航天大学 | Hypersonic inlet accelerates self-starting experimental method |
| CN210603820U (en) * | 2019-11-01 | 2020-05-22 | 中国空气动力研究与发展中心超高速空气动力研究所 | Continuous pressure distribution measuring device in air inlet channel for hypersonic wind tunnel |
Non-Patent Citations (1)
| Title |
|---|
| 向星居 等: "压敏漆测量三角翼模型气动载荷的超声速风洞实验", 《实验流体力学》, vol. 24, no. 3, pages 81 - 86 * |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110702367A (en) * | 2019-11-01 | 2020-01-17 | 中国空气动力研究与发展中心超高速空气动力研究所 | Continuous pressure measuring device for shielding position of parallel model of hypersonic wind tunnel |
| CN110702367B (en) * | 2019-11-01 | 2024-03-19 | 中国空气动力研究与发展中心超高速空气动力研究所 | Continuous pressure measuring device for shielding position of parallel model of hypersonic wind tunnel |
| CN111751076A (en) * | 2020-06-09 | 2020-10-09 | 西安交通大学 | Device and method for measuring flow coefficient of pressurizing cabin runner based on pressure sensitive paint |
| CN113252282A (en) * | 2021-06-23 | 2021-08-13 | 中国空气动力研究与发展中心超高速空气动力研究所 | Wind tunnel closed experiment section window observation device and application thereof |
| CN114486152A (en) * | 2021-12-29 | 2022-05-13 | 中国航空工业集团公司西安飞机设计研究所 | Pressure-sensitive paint pressure measurement data correction method |
| CN114486152B (en) * | 2021-12-29 | 2024-04-12 | 中国航空工业集团公司西安飞机设计研究所 | Pressure-sensitive paint pressure measurement data correction method |
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