CN111458101A - Method for measuring surface pulsating pressure of wind tunnel fixed wing model - Google Patents
Method for measuring surface pulsating pressure of wind tunnel fixed wing model Download PDFInfo
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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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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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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
- G01M9/02—Wind tunnels
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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
- G01M9/08—Aerodynamic models
Abstract
The invention discloses a method for measuring the surface pulsating pressure of a wind tunnel fixed wing model, which comprises the following steps: step S1: shooting a dark background through a camera; erecting a camera and an exciting light source right above a pressure surface to be tested of the model, placing a test site in a darkroom environment, and shooting an environmental dark background picture through the camera; step S2: turning on the excitation light source; step S3: shooting a windless reference image through a camera; step S4: wind tunnel wind-up; starting a wind tunnel, and running to a test wind speed and a test state; in the flow field of the model, the pressure change of the surface of the model is sensed by using pressure-sensitive paint, and the excitation light source and the camera are out of the flow field; step S5: shooting an experimental image by a camera, and recording the pulsating pressure condition on the surface of the model; step S6: and (5) calculating and displaying an experimental result. The invention has the advantages of simple and convenient operation and use, high intelligent degree, high detection efficiency, good detection effect and the like.
Description
Technical Field
The invention mainly relates to the technical field of aircraft performance detection, in particular to a method for measuring surface pulsating pressure of a wind tunnel fixed wing model.
Background
With the continuous improvement of performance indexes of the aircraft, the aerodynamic appearance of the aircraft is more complex, the structural design margin is smaller, and the aerodynamic load distribution has great influence on the performance, the stability control characteristic and the structural strength of the aircraft. In the design, improvement and design development of various aircrafts, the data such as the surface pressure distribution of a model, the separation characteristic of airflow on the model, the lift force, the pressure difference resistance and the pressure center position acting on the model and the like can be obtained through the measurement of the surface pressure distribution of the model, and the data is a direct basis for optimizing the aerodynamic performance of the aircrafts, checking the structural strength and verifying the numerical calculation result.
The traditional wind tunnel pressure measuring test method is that holes are formed at positions measured on the surface of a model and are connected to a pressure sensor through a pipeline, and a pulsation pressure sensor is adopted to measure unsteady pressure distribution. The method for measuring in the mode of the discrete pressure hole array has the following defects in the practical application process:
1. need for the pressure measurement test special design processing model, arrange hundreds to thousands of pressure ports, experimental preparation degree of difficulty big cycle length.
2. The pressure hole can damage the surface of the measured model, and the surface pressure measurement precision is influenced.
3. A certain distance exists between the adjacent pressure holes, so that the spatial resolution of the pressure measurement test is limited.
4. The pressure hole has certain installation size, and holes are formed at the edges of thin wings, flaps, horizontal tails, vertical tails, the joints of wings and an engine nacelle and the like, so that the structural strength of a model is weakened, the spatial layout of a pressure transmission pipeline is difficult to install, and the holes are difficult to measure; model moving parts such as helicopter rotors cannot be provided with sensors for measurement because the sensors need pipeline connection.
In order to solve the problems faced by the conventional Pressure measuring method, a non-contact measuring method for acquiring Pressure distribution by using a Pressure Sensitive Paint (PSP) technology is developed internationally and generally adopted. The PSP technology utilizes the phenomenon that the fluorescence intensity of luminous coating molecules changes along with pressure under the irradiation of exciting light with specific wavelength, converts the pressure into light intensity information, then carries out image processing, calculates the pressure distribution on the surface of the model, and has the advantages of high spatial resolution, no limitation of the model structure, no damage to the flow field on the surface of the model, capability of realizing large-area pressure distribution measurement and the like. At present, the application of the PSP technology covers a plurality of fields such as aerospace craft surface pressure distribution measurement, helicopter rotor surface pressure distribution measurement, aero-engine fan/compressor blade component surface pressure distribution measurement, complex flow mechanism research and the like. In a series of tasks such as aerodynamic research and model development in the fields of foreign aviation and aerospace, the PSP technology plays an extremely important key technical support role. In particular, the united states, the constant PSP technology has been used as a routine configuration to perform model testing. In addition, the fast response PSP technology also plays an extremely important role in the measurement of unsteady pressure of a model with complex aerodynamic characteristics, such as the measurement of the surface pressure distribution of a helicopter rotor and the measurement of the surface pressure distribution of the model in unsteady complex flow such as turbulence.
However, currently, pressure sensitive coatings are only used for constant surface pressure non-contact measurement, complementary to scanning valves; there is no established protocol for testing pressure sensitive paints for pulsating pressure measurements.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: aiming at the technical problems in the prior art, the invention provides the method for measuring the surface pulsating pressure of the wind tunnel fixed wing model, which is simple and convenient to operate and use, high in intelligent degree, high in detection efficiency and good in detection effect.
In order to solve the technical problems, the invention adopts the following technical scheme:
a method for measuring the surface pulsating pressure of a wind tunnel fixed wing model comprises the following steps:
step S1: shooting a dark background through a camera; the method comprises the following steps that a camera and an exciting light source are erected right above a pressure surface to be tested of a model, a test site is in a darkroom environment, and a dark background picture of the environment is shot through the camera and is used for deducting background noise interference in a later stage;
step S2: turning on the excitation light source; firstly, turning on an excitation light source for preheating, and carrying out the next test after the light intensity is stable;
step S3: shooting a windless reference image through a camera; after the excitation light source is stable, the excitation light source uniformly irradiates the surface of the model;
step S4: wind tunnel wind-up; starting a wind tunnel, and running to a test wind speed and a test state; in the flow field of the model, the pressure change of the surface of the model is sensed by using pressure-sensitive paint, and the excitation light source and the camera are out of the flow field;
step S5: shooting an experimental image by a camera, and recording the pulsating pressure condition on the surface of the model;
step S6: calculating and displaying experimental results; and (3) calibrating the coating sprayed on the surface of the model in a calibration box to obtain a calibration curve, and then calculating and displaying the experimental result of the image shot by the experiment.
As a further improvement of the invention: in the step S3, before the air blowing, the model image under the light condition is photographed by the camera and used as a test reference for deducting the measurement error caused by the uneven light intensity distribution of the excitation light source during the later data processing.
As a further improvement of the invention: in step S5, the excitation light source continuously irradiates the model surface according to the test conditions, and the camera performs image capturing in a high frequency mode from the beginning of wind attack or after the wind speed stabilizes.
As a further improvement of the invention, the excitation light source is L ED or a high-power continuous laser, the wavelength is near 400nm, and the excitation light source is an ultraviolet band.
As a further improvement of the invention: the image acquisition frequency of the camera is more than 5K/fps.
As a further improvement of the invention: the pressure-sensitive paint is a single-component pressure-sensitive paint or a two-component pressure-sensitive paint.
As a further improvement of the invention: the response speed of the pressure-sensitive paint is less than 200 mus.
As a further improvement of the invention: the filter on the camera adopts a narrow-band-pass filter, and comprises a signal filter and a reference filter.
As a further improvement of the invention: the optical filter switching device is additionally arranged in front of the lens of the camera, and when the two-component pressure-sensitive paint is used, the optical filter switching device is used for obtaining light intensity images collected by different filters in the same state.
As a further improvement of the invention: the optical filter switching device comprises a digital steering engine and an optical filter clamping plate, and the upper computer controls the steering engine to rotate the optical filter clamping plate so as to realize the quick switching of the signal optical filter and the reference optical filter.
Compared with the prior art, the invention has the advantages that:
1. the method for measuring the surface pulsating pressure of the wind tunnel fixed wing model has the advantages of simple and convenient operation and use, high intelligent degree, high detection efficiency and good detection effect.
2. The method for measuring the surface pulsating pressure of the wind tunnel fixed wing model has strong robustness. Because the system has simple structure and few adjusting variables, the error probability is low when the system works for a long time.
3. The method for measuring the surface pulsating pressure of the wind tunnel fixed wing model is convenient to measure and high in resolution. Compared with the traditional pulse pressure sensor scheme, the scheme does not need to open holes on the surface of the model, saves cost and time, and can achieve the pixel level of measurement resolution.
Drawings
FIG. 1 is a schematic flow diagram of the process of the present invention.
FIG. 2 is a schematic diagram of a detection system constructed in an embodiment of the present invention.
FIG. 3 is a model diagram of the present invention in a specific application example.
Fig. 4 is a diagram illustrating a detection result by a conventional method in a specific application example.
FIG. 5 is a diagram showing the results of the detection using the method of the present invention in a specific application example.
Detailed Description
The invention will be described in further detail below with reference to the drawings and specific examples.
As shown in figure 1, the method for measuring the surface pulsating pressure of the wind tunnel fixed wing model is a method for measuring the surface pulsating pressure of the wind tunnel fixed wing model based on quick response pressure-sensitive paint, and comprises the following steps:
step S1: the dark background is photographed by a camera, such as a high speed camera CCD.
A high-speed camera (CCD) and an exciting light source are erected right above a pressure surface to be tested of the model, a test site is required to be in a darkroom environment as much as possible, and a dark background picture of the environment is shot by the high-speed camera (CCD) and is used for deducting background noise interference in the later stage.
Step S2, turn on the excitation light source (e.g., L ED or laser light source).
L ED or laser light source intensity stability can also introduce measurement errors, so the excitation light source needs to be turned on for preheating, usually about 30-60 seconds, and the next test is carried out after the intensity is stable.
Step S3: the windless reference image is taken by a high speed camera (CCD).
After the excitation light source is stable, the excitation light source uniformly irradiates the surface of the model.
Furthermore, before pneumatic blowing, a model image under the light condition can be shot through the CCD and used as a test reference for deducting measurement errors caused by uneven light distribution of the excitation light source during later data processing.
Step S4: the wind tunnel is windy.
And (5) starting the wind tunnel, and running to a test wind speed and a test state. At the moment, the model is in the flow field, the pressure sensitive paint senses the pressure change on the surface of the model, and the excitation light source and the high-speed camera are out of the flow field.
Step S5: the CCD shoots an experimental image.
According to the test condition, the excitation light source continuously irradiates the surface of the model, and the camera acquires images in a high-frequency mode from the beginning of wind attack or after the wind speed is stable and records the pulsating pressure condition of the surface of the model.
Step S6: and (5) calculating and displaying an experimental result.
And (3) calibrating the coating sprayed on the surface of the model in a calibration box to obtain a calibration curve, and then calculating and displaying the experimental result of the image shot by the experiment.
In a specific application example, the excitation light source of the invention is L ED or a high-power continuous laser, and the wavelength of the excitation light source is near 400nm and is an ultraviolet band.
In a specific application example, the picture acquisition frequency of the high-speed camera is more than 5K/fps.
In a specific application example, the single-component pressure-sensitive paint or the double-component pressure-sensitive paint can be selected according to actual needs, and the response speed is less than 200 mu s; the surface of the fixed wing model can be sprayed with single-component or double-component pressure-sensitive paint.
In a specific application example, the filter on the camera adopts a narrow-band-pass filter, comprises a signal filter and a reference filter, a filter switching device is additionally arranged in front of a lens of the camera, and when the two-component pressure-sensitive paint is used, the filter switching device is used for obtaining light intensity images acquired by different filters in the same state.
In a specific application example, the switching device comprises a digital steering engine and an optical filter clamping plate, and the upper computer controls the steering engine to rotate the optical filter clamping plate so as to realize the quick switching between the signal optical filter and the reference optical filter.
The method of the invention is adopted, compared with a steady PSP method, firstly, the light source stability is higher than that of the steady PSP, the measurement time is longer (about several minutes) due to the dynamic process of measuring the surface pulsating pressure of the model, and the L ED light source for the ordinary steady PSP test is short in use time, and the change of the measurement result caused by the power fluctuation of the light source can cover the real pressure change without considering the long-term stability problem, so that the method can not meet the requirement of the scheme.
In a specific application example, the single-component pressure-sensitive paint is adopted, and a dark background image is shot by a high-speed camera (CCD) and is used for deducting background noise interference at the later stage; then, the excitation light source is turned on, so that the light intensity is stable; after the light source is stable, a model image under the light condition is shot through the CCD and is used as an experimental reference; starting a wind tunnel, and running to an experimental wind speed and an experimental state; at the moment, the camera collects images in a high-frequency mode, the optical filter adopts a signal optical filter and is not switched, and the condition of the pulsating pressure on the surface of the model is recorded; and calculating the image shot by the experiment according to the pre-calibrated data, and displaying the experiment result.
In another specific application example, the two-component pressure-sensitive paint is adopted, and a dark background image is firstly shot by a high-speed camera (CCD) and is used for deducting background noise interference at the later stage; then, the excitation light source is turned on, so that the light intensity is stable; after the light source is stable, a model image under the light condition is shot through the CCD and is used as an experimental reference; starting a wind tunnel, and running to an experimental wind speed and an experimental state; at the moment, the camera acquires images in a high-frequency mode, and the pulsating pressure condition on the surface of the model is shot and recorded. The optical filter comprises a signal optical filter and a reference optical filter, and the optical filter switching device is switched by taking 6s as a period: the signal optical filter is switched once after shooting for 5 seconds, and a temperature reference image for 1s is recorded; and finally, calculating the image shot by the experiment and displaying the experiment result through the pre-calibrated data.
Compared with the traditional method, the method for measuring the surface pulsating pressure of the wind tunnel fixed wing model has the advantages as shown in the following table:
TABLE 1 comparison of the conventional pulse pressure measuring method with the advantages and disadvantages of the quick-response pressure-sensitive paint technology
The experimental model is shown in fig. 3, the original method needs to arrange pressure measuring holes on the surface of the model, the measuring result is discrete points, and the model design is complex. Referring to fig. 4 and 5, taking the test with an attack angle of 10 ° and a wind speed of 60m/s as an example, the test result of the original method is discrete points (shown in fig. 4), the pressure sensitive paint measurement result is shown in fig. 5, a continuous distribution of surface pressure can be obtained, the measurement is simple, the model does not need to be perforated, and the experimental process is simple.
The above is only a preferred embodiment of the present invention, and the protection scope of the present invention is not limited to the above-mentioned embodiments, and all technical solutions belonging to the idea of the present invention belong to the protection scope of the present invention. It should be noted that modifications and embellishments within the scope of the invention may be made by those skilled in the art without departing from the principle of the invention.
Claims (10)
1. A method for measuring surface pulsating pressure of a wind tunnel fixed wing model is characterized by comprising the following steps:
step S1: shooting a dark background through a camera; the method comprises the following steps that a camera and an exciting light source are erected right above a pressure surface to be tested of a model, a test site is in a darkroom environment, and a dark background picture of the environment is shot through the camera and is used for deducting background noise interference in a later stage;
step S2: turning on the excitation light source; firstly, turning on an excitation light source for preheating, and carrying out the next test after the light intensity is stable;
step S3: shooting a windless reference image through a camera; after the excitation light source is stable, the excitation light source uniformly irradiates the surface of the model;
step S4: wind tunnel wind-up; starting a wind tunnel, and running to a test wind speed and a test state; in the flow field of the model, the pressure change of the surface of the model is sensed by using pressure-sensitive paint, and the excitation light source and the camera are out of the flow field;
step S5: shooting an experimental image by a camera, and recording the pulsating pressure condition on the surface of the model;
step S6: calculating and displaying experimental results; and (3) calibrating the coating sprayed on the surface of the model in a calibration box to obtain a calibration curve, and then calculating and displaying the experimental result of the image shot by the experiment.
2. The method for measuring the surface pulsating pressure of the wind tunnel fixed wing model according to claim 1, wherein in the step S3, before wind blowing, a model image under the condition of light is shot by a camera and used as a test reference for deducting the measurement error caused by the uneven light distribution of the excitation light source during the later data processing.
3. The method for measuring the pulsating pressure on the surface of the wind tunnel fixed wing model according to claim 1, wherein in step S5, the excitation light source continuously irradiates the model surface according to the test condition, and the camera performs image acquisition in a high frequency mode from the beginning of the wind attack or after the wind speed is stabilized.
4. The method for measuring the pulsating pressure on the surface of the wind tunnel fixed wing model according to any one of claims 1 to 3, wherein the excitation light source is L ED or a high-power continuous laser, the wavelength is about 400nm, and the wavelength is an ultraviolet band.
5. The method for measuring the pulsating pressure on the surface of the wind tunnel fixed wing model according to any one of claims 1 to 3, wherein the image acquisition frequency of the camera is greater than 5K/fps.
6. The method for measuring the pulsating pressure on the surface of the wind tunnel fixed wing model according to any one of claims 1 to 3, wherein the pressure-sensitive paint is a single-component pressure-sensitive paint or a two-component pressure-sensitive paint.
7. The method for measuring the pulsating pressure on the surface of the wind tunnel fixed wing model according to claim 6, wherein the response speed of the pressure sensitive paint is less than 200 μ s.
8. The method for measuring the pulsating pressure on the surface of the wind tunnel fixed wing model according to any one of claims 1 to 3, wherein a narrow band pass filter is adopted as the filter on the camera, and the narrow band pass filter comprises a signal filter and a reference filter.
9. The method for measuring the surface pulsating pressure of the wind tunnel fixed wing model according to claim 8, wherein an optical filter switching device is additionally arranged in front of a lens of the camera, and when the two-component pressure-sensitive paint is used, the optical filter switching device is used for obtaining light intensity images acquired by using different filters in the same state.
10. The method for measuring the surface pulsating pressure of the wind tunnel fixed wing model according to claim 8, wherein the optical filter switching device comprises a digital steering engine and an optical filter clamping plate, and an upper computer controls the steering engine to rotate the optical filter clamping plate so as to realize the rapid switching between the signal optical filter and the reference optical filter.
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| CHRISTIAN KLEIN: "Application of pressure-sensitive paint for determination of the pressure field and calculation of the forces and moments of models in a wind tunnel", 《EXPERIMENTS IN FLUIDS》 * |
| 任一鹏: "基于快速响应 ＰＳＰ技术的跨声速脉动压力实验研究", 《宇航总体技术》 * |
| 刘祥: "双组份压敏漆试验技术测量不确定度研究", 《中国博士学位论文全文数据库工程科技II辑》 * |
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| CN114323543A (en) * | 2022-03-10 | 2022-04-12 | 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 pressure-sensitive paint test efficiency |
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