CN110702366B - Embedded optical pressure measurement method for shielding position of hypersonic wind tunnel model - Google Patents
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- 230000003287 optical effect Effects 0.000 title claims abstract description 38
- 238000000034 method Methods 0.000 title claims abstract description 25
- 238000009530 blood pressure measurement Methods 0.000 title claims abstract description 19
- 238000012360 testing method Methods 0.000 claims abstract description 32
- 238000012545 processing Methods 0.000 claims abstract description 31
- 239000005304 optical glass Substances 0.000 claims abstract description 21
- 239000000523 sample Substances 0.000 claims abstract description 20
- 239000003973 paint Substances 0.000 claims abstract description 10
- 239000011248 coating agent Substances 0.000 claims abstract description 7
- 238000000576 coating method Methods 0.000 claims abstract description 7
- 238000011088 calibration curve Methods 0.000 claims abstract description 4
- 238000005259 measurement Methods 0.000 claims description 13
- 239000013307 optical fiber Substances 0.000 claims description 10
- 238000012935 Averaging Methods 0.000 claims description 6
- 230000003068 static effect Effects 0.000 claims description 3
- 238000010586 diagram Methods 0.000 description 2
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 230000005284 excitation Effects 0.000 description 1
- 239000011521 glass Substances 0.000 description 1
- 238000000691 measurement method Methods 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
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- 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
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Abstract
The invention discloses an embedded optical pressure measurement method for a shielding position of a hypersonic wind tunnel model. Firstly, processing a set of parallel two-stage wind tunnel test model, installing an embedded LED array light source and an embedded optical probe in a groove on the lower surface of the second-stage model in parallel, covering an optical glass window on the surface of the groove, and connecting the embedded optical probe with an external scientific-grade CCD camera and an image storage processing system; and coating pressure-sensitive paint on the upper surface of the primary model at a measuring position corresponding to the optical glass window, and processing a pressure measuring hole, wherein the pressure measuring hole is connected with a wind tunnel pressure measuring system. Secondly, acquiring a wind-on image, a wind-off image and a wind-dark image at a measuring position in a wind tunnel test, and then processing the images to obtain a gray scale ratio image; and finally, drawing a calibration curve through the gray scale ratio image and the pressure value of the pressure measuring hole, and fitting a calibration formula to obtain a pressure distribution map. The measuring method is simple and efficient, and solves the problem of large-area pressure measurement of models under the shielding condition.
Description
Technical Field
The invention belongs to the technical field of hypersonic wind tunnel tests, and particularly relates to an embedded optical pressure measurement method for a shielding position of a hypersonic wind tunnel model.
Background
In the high-speed separation process of the parallel two-stage aircraft, a very complex flow field structure exists between the first stage and the second stage, the flow field structure is a main measurement area of a hypersonic wind tunnel test, and a parallel two-stage aircraft model is a test model with a model shielding position. Although the conventional pressure-sensitive paint can obtain large-area pressure continuous measurement data, for a test model with a model shielding position, a light source or a camera cannot reach the surface of the measurement position due to mutual shielding among primary models, secondary models or inside models. The conventional method is to simplify the first-order model into a glass plate so that light can directly pass through, and the method is only suitable for models with a plane surface. However, for the model with larger surface curvature, the model appearance is changed in the simplified mode, and the difference between the measurement result and the real result is larger. Similarly, similar to a parallel two-stage aircraft, the independent aircraft with the air inlet channel cannot directly reach the inside of the air inlet channel due to the shielding of the aircraft main body, and the measurement of the internal pressure of the air inlet channel cannot be implemented from the outside of the independent aircraft model with the air inlet channel.
Currently, there is a need to develop an embedded optical pressure measurement method for the shielding position of a hypersonic wind tunnel model.
Disclosure of Invention
The invention aims to provide an embedded optical pressure measurement method for a shielding position of a hypersonic wind tunnel model.
The invention discloses an embedded optical pressure measurement method for a shielding position of a hypersonic wind tunnel model, which is characterized by comprising the following steps of: the device used by the measuring method comprises an embedded LED array light source, an embedded optical probe, a scientific grade CCD camera, a filter, an optical fiber and an image storage and processing system, wherein the image storage and processing system comprises a VCR, an image processor and a computer, and the measuring method comprises the following steps:
a. processing a set of parallel two-stage wind tunnel test model, wherein the first-stage model is an aircraft main body, and the second-stage model is an aircraft sub-stage which is fixedly arranged above the aircraft main body and has a gap with the aircraft main body;
b. processing a groove on the lower surface of the secondary model, installing the embedded LED array light source and the embedded optical probe in the groove in parallel, covering an optical glass window on the surface of the groove, and enabling the optical glass window to be flush with the lower surface of the secondary model; coating pressure-sensitive paint on the upper surface of the primary model at a measuring position corresponding to the optical glass window and processing a pressure measuring hole, wherein the pressure measuring hole is connected with a wind tunnel pressure measuring system;
c. the embedded optical probe is connected with an external filter through an optical fiber, the filter is connected with a scientific grade CCD camera, and the scientific grade CCD camera is connected with an image storage processing system;
d. before the wind tunnel test, an embedded LED array light source and an embedded optical probe are turned on; during wind tunnel test, after the airflow of the test section is stable, opening a scientific-grade CCD camera and shooting a wind-on image at a measurement position by using the scientific-grade CCD camera; after the wind tunnel test, after the airflow of the test section is static, a scientific-grade CCD camera is used for shooting a wind-off image of a measuring position; turning off the embedded LED array light source, and shooting a wind-dark image at the measurement position by using a scientific grade CCD camera; inputting the wind-on image, the wind-off image and the wind-dark image into an image storage and processing system;
e. carrying out image averaging on the wind-dark image to obtain a wind-dark-av image, and carrying out image averaging and image registration on the wind-on image and the wind-off image to obtain a wind-on-av image and a wind-off-av image;
f. respectively subtracting the wind-dark-av image from the wind-on-av image and the wind-off-av image to obtain a wind-on-dif image and a wind-off-dif image;
g. dividing the wind-off-dif image by the corresponding wind-on-dif image to obtain a gray scale ratio image;
h. and drawing a calibration curve according to the gray scale ratio at the pressure measuring hole position in the gray scale ratio image and the pressure value of the pressure measuring hole, fitting to obtain a calibration formula, and calculating the pressure distribution map of the surface of the measuring position through the calibration formula.
The optical fiber is replaced by a light guide arm.
The step b can be replaced by the following step b 1:
b1. processing a groove on the upper surface of the primary model, installing the embedded LED array light source and the embedded optical probe in the groove in parallel, covering an optical glass window on the surface of the groove, and enabling the optical glass window to be flush with the upper surface of the primary model; and coating pressure-sensitive paint on the lower surface of the secondary model at a measuring position corresponding to the optical glass window, and processing a pressure measuring hole, wherein the pressure measuring hole is connected with a wind tunnel pressure measuring system.
The parallel two-stage wind tunnel test model in the step a can be replaced by an independent aircraft model with an air inlet channel, the first-stage model of the independent aircraft model with the air inlet channel is an aircraft main body, and the second-stage model is an air inlet channel.
According to the embedded optical pressure measurement method for the shielding position of the hypersonic wind tunnel model, pressure-sensitive paint is adopted according to a light intensity method, and luminous molecules which can be excited by ultraviolet light or visible light and are contained in the pressure-sensitive paint can emit radiation light with the intensity highly related to the oxygen concentration under the excitation of an embedded LED array light source.
According to the embedded optical pressure measurement method for the shielding position of the hypersonic wind tunnel model, the embedded LED array light source and the embedded optical probe are embedded in the secondary model in a groove mode, the internal space of the secondary model is fully utilized, the power supply leading-out wire of the embedded LED array light source and the optical fiber of the embedded optical probe are LED out from the bottom of the test model, excessive interference on the flow field around the model is avoided, the distance from the embedded LED array light source to the surface of the measurement position of the test model is shortened, only one layer of optical glass is arranged between the embedded LED array light source, the embedded optical probe and the surface of the measurement position of the model, the energy loss of exciting light is reduced, and the definition of collected images is improved.
The embedded optical pressure measuring method for the shielding position of the hypersonic wind tunnel model adopts a scientific-grade CCD camera, a power line and a control line of an embedded LED array light source penetrate out of the test model through a bottom opening of the test model and are fixed on the supporting frame and then are externally connected to the scientific-grade CCD camera, the scientific-grade CCD camera still can adopt an originally external high dynamic range, the characteristics of high stability, high reliability, light intensity uniformity, low noise and the like of the scientific-grade CCD camera are completely reserved, and the technical parameters of the scientific-grade CCD camera are kept unchanged.
The embedded optical pressure measurement method for the shielding position of the hypersonic wind tunnel model is simple and efficient, and solves the problem of large-area pressure measurement of the model under the shielding condition.
Drawings
FIG. 1 is a schematic diagram of an embedded optical pressure measurement method for a shielding position of a hypersonic wind tunnel model applied to a parallel two-stage wind tunnel test model;
FIG. 2 is a schematic diagram of an embedded optical pressure measurement method for a shielding position of a hypersonic wind tunnel model applied to an independent aircraft model with an air inlet channel.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings and examples.
Example 1
As shown in FIG. 1, the device used in the embedded optical pressure measurement method for the shielding position of the hypersonic wind tunnel model comprises an embedded LED array light source, an embedded optical probe, a scientific CCD camera, a filter, an optical fiber and an image storage and processing system, wherein the image storage and processing system comprises a VCR, an image processor and a computer, and the measurement method comprises the following steps:
a. processing a set of parallel two-stage wind tunnel test model, wherein the first-stage model is an aircraft main body, and the second-stage model is an aircraft sub-stage which is fixedly arranged above the aircraft main body and has a gap with the aircraft main body;
b. processing a groove on the lower surface of the secondary model, installing the embedded LED array light source and the embedded optical probe in the groove in parallel, covering an optical glass window on the surface of the groove, and enabling the optical glass window to be flush with the lower surface of the secondary model; coating pressure-sensitive paint on the upper surface of the primary model at a measuring position corresponding to the optical glass window and processing a pressure measuring hole, wherein the pressure measuring hole is connected with a wind tunnel pressure measuring system;
c. the embedded optical probe is connected with an external filter through an optical fiber, the filter is connected with a scientific grade CCD camera, and the scientific grade CCD camera is connected with an image storage processing system;
d. before the wind tunnel test, an embedded LED array light source and an embedded optical probe are turned on; during wind tunnel test, after the airflow of the test section is stable, opening a scientific-grade CCD camera and shooting a wind-on image at a measurement position by using the scientific-grade CCD camera; after the wind tunnel test, after the airflow of the test section is static, a scientific-grade CCD camera is used for shooting a wind-off image of a measuring position; turning off the embedded LED array light source, and shooting a wind-dark image at the measurement position by using a scientific grade CCD camera; inputting the wind-on image, the wind-off image and the wind-dark image into an image storage and processing system;
e. carrying out image averaging on the wind-dark image to obtain a wind-dark-av image, and carrying out image averaging and image registration on the wind-on image and the wind-off image to obtain a wind-on-av image and a wind-off-av image;
f. respectively subtracting the wind-dark-av image from the wind-on-av image and the wind-off-av image to obtain a wind-on-dif image and a wind-off-dif image;
g. dividing the wind-off-dif image by the corresponding wind-on-dif image to obtain a gray scale ratio image;
h. and drawing a calibration curve according to the gray scale ratio at the pressure measuring hole position in the gray scale ratio image and the pressure value of the pressure measuring hole, fitting to obtain a calibration formula, and calculating the pressure distribution map of the surface of the measuring position through the calibration formula.
Step b in this embodiment may be replaced by step b1 as follows:
b1. processing a groove on the upper surface of the primary model, installing the embedded LED array light source and the embedded optical probe in the groove in parallel, covering an optical glass window on the surface of the groove, and enabling the optical glass window to be flush with the upper surface of the primary model; and coating pressure-sensitive paint on the lower surface of the secondary model at a measuring position corresponding to the optical glass window, and processing a pressure measuring hole, wherein the pressure measuring hole is connected with a wind tunnel pressure measuring system.
Example 2
As shown in fig. 2, this embodiment is substantially the same as the embodiment of embodiment 1, and the main difference is that the parallel two-stage wind tunnel test model in step a is replaced by an independent aircraft model with an air intake duct, the primary model of the independent aircraft model with the air intake duct is an aircraft body, and the secondary model is an air intake duct.
The optical fibers of embodiments 1 and 2 may be replaced with light guiding arms.
Claims (4)
1. The embedded optical pressure measurement method for the shielding position of the hypersonic wind tunnel model is characterized by comprising the following steps of: the device used by the measuring method comprises an embedded LED array light source, an embedded optical probe, a scientific grade CCD camera, a filter, an optical fiber and an image storage and processing system, wherein the image storage and processing system comprises a VCR, an image processor and a computer, and the measuring method comprises the following steps:
a. processing a set of parallel two-stage wind tunnel test model, wherein the first-stage model is an aircraft main body, and the second-stage model is an aircraft sub-stage which is fixedly arranged above the aircraft main body and has a gap with the aircraft main body;
b. processing a groove on the lower surface of the secondary model, installing the embedded LED array light source and the embedded optical probe in the groove in parallel, covering an optical glass window on the surface of the groove, and enabling the optical glass window to be flush with the lower surface of the secondary model; coating pressure-sensitive paint on the upper surface of the primary model at a measuring position corresponding to the optical glass window and processing a pressure measuring hole, wherein the pressure measuring hole is connected with a wind tunnel pressure measuring system;
c. the embedded optical probe is connected with an external filter through an optical fiber, the filter is connected with a scientific grade CCD camera, and the scientific grade CCD camera is connected with an image storage processing system;
d. before the wind tunnel test, an embedded LED array light source and an embedded optical probe are turned on; during wind tunnel test, after the airflow of the test section is stable, opening a scientific-grade CCD camera and shooting a wind-on image at a measurement position by using the scientific-grade CCD camera; after the wind tunnel test, after the airflow of the test section is static, a scientific-grade CCD camera is used for shooting a wind-off image of a measuring position; turning off the embedded LED array light source, and shooting a wind-dark image at the measurement position by using a scientific grade CCD camera; inputting the wind-on image, the wind-off image and the wind-dark image into an image storage and processing system;
e. carrying out image averaging on the wind-dark image to obtain a wind-dark-av image, and carrying out image averaging and image registration on the wind-on image and the wind-off image to obtain a wind-on-av image and a wind-off-av image;
f. respectively subtracting the wind-dark-av image from the wind-on-av image and the wind-off-av image to obtain a wind-on-dif image and a wind-off-dif image;
g. dividing the wind-off-dif image by the corresponding wind-on-dif image to obtain a gray scale ratio image;
h. and drawing a calibration curve according to the gray scale ratio at the pressure measuring hole position in the gray scale ratio image and the pressure value of the pressure measuring hole, fitting to obtain a calibration formula, and calculating the pressure distribution map of the surface of the measuring position through the calibration formula.
2. The embedded optical pressure measurement method for the shielding position of the hypersonic wind tunnel model according to claim 1, characterized in that: the optical fiber is replaced by a light guide arm.
3. The embedded optical pressure measurement method for the shielding position of the hypersonic wind tunnel model according to claim 1, characterized in that: the step b is replaced by the following step b 1:
b1. processing a groove on the upper surface of the primary model, installing the embedded LED array light source and the embedded optical probe in the groove in parallel, covering an optical glass window on the surface of the groove, and enabling the optical glass window to be flush with the upper surface of the primary model; and coating pressure-sensitive paint on the lower surface of the secondary model at a measuring position corresponding to the optical glass window, and processing a pressure measuring hole, wherein the pressure measuring hole is connected with a wind tunnel pressure measuring system.
4. The embedded optical pressure measurement method for the shielding position of the hypersonic wind tunnel model according to claim 1, characterized in that: and a parallel two-stage wind tunnel test model in the step a is replaced by an independent aircraft model with an air inlet passage, a primary model of the independent aircraft model with the air inlet passage is an aircraft main body, and a secondary model of the independent aircraft model with the air inlet passage is an air inlet passage.
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| 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 |
| CN112067193B (en) * | 2020-09-14 | 2022-03-25 | 中国空气动力研究与发展中心超高速空气动力研究所 | Aircraft surface pressure sensor testing device and testing method |
| CN112816174A (en) * | 2020-12-30 | 2021-05-18 | 中国航空工业集团公司沈阳空气动力研究所 | Embedded pressure-sensitive paint measurement test system and test method |
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| CN114323543B (en) * | 2022-03-10 | 2022-05-17 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for improving test efficiency of pressure-sensitive paint |
| CN118533420B (en) * | 2024-07-26 | 2024-09-20 | 中国空气动力研究与发展中心超高速空气动力研究所 | Optical fiber-based embedded model detouring optical radiation measuring device and measuring method |
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