CN112268684B - Variable azimuth angle surface pressure measuring system and method for low-speed wind tunnel rotor model - Google Patents
Variable azimuth angle surface pressure measuring system and method for low-speed wind tunnel rotor model Download PDFInfo
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- CN112268684B CN112268684B CN202011461313.9A CN202011461313A CN112268684B CN 112268684 B CN112268684 B CN 112268684B CN 202011461313 A CN202011461313 A CN 202011461313A CN 112268684 B CN112268684 B CN 112268684B
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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
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L11/00—Measuring steady or quasi-steady pressure of a fluid or a fluent solid material by means not provided for in group G01L7/00 or G01L9/00
- G01L11/02—Measuring steady or quasi-steady pressure of a fluid or a fluent solid material by means not provided for in group G01L7/00 or G01L9/00 by optical means
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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
- G01M9/04—Details
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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 a system and a method for measuring surface pressure of a rotor model with a variable azimuth angle in a low-speed wind tunnel, wherein the system comprises an excitation light source and a measuring device, and the measuring device comprises a beam expanding unit, a camera and a reflector; the beam expanding unit comprises a concave lens, a first cylindrical lens and a second cylindrical lens which are sequentially arranged, a point light source output by the excitation light source expands beams through the concave lens, then expands beams in two orthogonal dimensions through the first cylindrical lens and the second cylindrical lens, and the size of a light spot after beam expansion is determined according to the size of a component to be measured; after the light source is expanded by the beam expanding unit, the light is reflected to the part to be measured through a reflector, and then image acquisition is carried out through the camera. The method is implemented based on the system. The invention has the advantages of realizing variable azimuth angle of the rotor wing, real-time measurement of the upper surface and the lower surface, improvement of the measurement efficiency and the like.
Description
Technical Field
The invention mainly relates to the technical field of wind tunnel tests, in particular to a system and a method for measuring surface pressure of a low-speed wind tunnel rotor model with a variable azimuth angle.
Background
The helicopter has the capability of vertical take-off and landing, flying and hovering, and has irreplaceable status in the fields of military war, disaster rescue, aerial surveillance and the like. From theoretical analysis, measurement of rotor blade surface pressure distribution is a fundamental means for obtaining rotor blade aerodynamic load distribution and time variation history thereof, and is also the most important method adopted by researchers at home and abroad.
The pressure distribution measuring result on the blade can provide local flow structure information at each position of the blade, and is a direct basis for analyzing noise sources; sufficient pressure measurement is carried out along the chord direction, and better local lift force and pitching moment load history can be obtained, so that the method is a direct basis for analyzing the vibration problem. However, because the helicopter rotor rotates at a high speed, even in a relatively stable hovering state, the pressure distribution on the surface of the rotor blade is in an unsteady state, and in addition, the thin and thin appearance of the rotor blade has higher technological requirements for arranging the pressure sensor, and the influence of the displacement and deformation of the blade caused by the flexible structure on test data and other factors cause great difficulty in measuring the pulsating pressure on the surface of the blade, and special technical means are required.
The main means for measuring the pulsating pressure on the surface of the rotor blade are as follows: wind tunnel and flight test. The wind tunnel test is mainly carried out in a low-speed wind tunnel, and the feasible technical methods comprise two methods: conventional blade surface placement dynamic pressure sensors, and fast response Pressure Sensitive Paint (PSP) methods. The traditional pressure sensor method needs to embed an expensive dynamic pressure sensor on the premise of keeping the appearance of the paddle, the test points are limited, the paddle needs to be specially made, the period is long, the process is complex, and the manufacturing cost is high. Compared with the prior art, the fast-response PSP can be directly sprayed on the conventional rotor wing for use, a blade model with an embedded pressure sensor does not need to be additionally manufactured, the test area is large, the result acquisition is fast, the cost is low, and the fast-response PSP is a main measurement means at present.
The existing fast response PSP rotor wing surface pressure measuring system generally adopts a fixed structure, uses a pulse laser of 200mJ-500mJ, expands a point light source into a circular light spot through a concave lens or ground glass, and irradiates the circular light spot on an azimuth angle to be measured of a rotor wing for measurement. The existing method has low measurement efficiency, the laser needs to be moved when measuring different azimuth angles, the adjustment time is usually several hours, and the real-time measurement of different azimuth angles cannot be realized. When the upper surface and the lower surface are measured, a laser needs to be moved up and down in the wind tunnel or a large portal frame needs to be installed, so that the test efficiency is low. The 500mJ laser of current scheme can only just barely satisfy the independent surface measurement of 3 meters diameter rotor, if carry out bigger size rotor test (like 4 meters diameter rotor models), then can't realize, need purchase more powerful pulse laser, and the input cost is huge. The main reason is that the existing test scheme has defects, the beam expanding system has the problem of serious power waste, and the optimization and the space improvement are large.
Examples of two conventional solutions, such as those shown in fig. 1 and 2, include an excitation light source 1, a rotor 2, a concave lens 3, a camera 4, a first mirror 7, a synchronization controller 11, and a computer 12. Light output by a 532nm laser irradiates an azimuth angle to be measured of a rotor wing after passing through a reflector and a beam expanding lens (the reflector and the beam expanding lens are fixed on an optical bread board), when different azimuth angles are measured, the laser and the optical bread board need to be readjusted, time consumption is long, multi-azimuth angle real-time measurement cannot be achieved, and simultaneous measurement of the upper surface and the lower surface cannot be achieved.
As shown in fig. 3, 8 azimuth angles a, b, c, d, e, f, g and h (if the measurement is convenient, more azimuth angles can be measured) which are often required to be measured in a wind tunnel test of a rotor wing are given, when the pressure of one surface of the rotor wing is measured by using the conventional method, all optical path hardware equipment needs to be moved for 8 times, if the upper surface and the lower surface need to be measured, the movement needs to be performed for 16 times, the process takes several days to tens of days, the time consumption is long, and the simultaneous measurement cannot be performed.
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 system and the method for measuring the surface pressure of the variable azimuth angle of the rotor wing model of the low-speed wind tunnel, which can realize the real-time measurement of the variable azimuth angle and the upper and lower surfaces of the rotor wing and improve the measurement efficiency.
In order to solve the technical problems, the invention adopts the following technical scheme:
a variable azimuth angle surface pressure measuring system of a low-speed wind tunnel rotor model comprises an excitation light source and a measuring device, wherein the measuring device comprises a beam expanding unit, a camera and a reflector; the beam expanding unit comprises a concave lens, a first cylindrical lens and a second cylindrical lens which are sequentially arranged, a point light source output by the excitation light source expands beams through the concave lens, then expands beams in two orthogonal dimensions through the first cylindrical lens and the second cylindrical lens, and the size of a light spot after beam expansion is determined according to the size of a component to be measured; after the light source is expanded by the beam expanding unit, the light is reflected to the part to be measured through a reflector, and then image acquisition is carried out through the camera.
As a further improvement of the system of the invention: the camera is mounted on the camera angle adjusting frame.
As a further improvement of the system of the invention: the camera angle adjusting frame is an electric angle adjusting frame.
As a further improvement of the system of the invention: the camera angle adjusting frame is a two-dimensional electric angle adjusting frame.
As a further improvement of the system of the invention: the reflector is arranged on the reflector angle adjusting frame.
As a further improvement of the system of the invention: the reflector angle adjusting frame is an electric angle adjusting frame.
As a further improvement of the system of the invention: the reflector angle adjusting frame is a three-dimensional electric angle adjusting frame.
As a further improvement of the system of the invention: the excitation light source, the concave lens, the first cylindrical lens, the second cylindrical lens, the camera and the reflector are all fixed on one optical bread board.
As a further improvement of the system of the invention: the measuring devices are divided into two groups, one group of measuring devices is positioned above the component to be measured, the other group of measuring devices is positioned below the component to be measured, and light output by the excitation light source is equally divided into an upper path and a lower path through a light splitting unit and a second reflector, and the upper path and the lower path are respectively used for the beam expanding units on the upper surface and the lower surface.
The invention further provides a method for measuring the surface pressure of the rotor wing model of the low-speed wind tunnel with the variable azimuth angle, which comprises the following steps:
step S1: shooting a dark background by a camera;
step S2: raising to a test rotating speed, and after the rotating speed is stable, blowing wind in the wind tunnel;
step S3: synchronously triggering a camera and an excitation light source to shoot a PSP image; after the rotating speed and the wind speed are stable, synchronously triggering signals for an excitation light source and a camera through a photoelectric encoder of the test bed, and collecting a pressure-sensitive paint image;
step S4: synchronously triggering a camera and an excitation light source to shoot a TSP image; after the pressure-sensitive paint image is shot, changing a trigger signal to the temperature-sensitive paint, and collecting a TSP image;
step S5: judging whether the acquisition of all azimuth angles to be detected is finished; if not, controlling the angle adjusting frames of the camera and the excitation light source to the azimuth angle area to be measured, changing the synchronous trigger signal, and repeating the steps S3 and S4 until all azimuth angles are measured;
step S6: stopping the wind tunnel and the test stand, and finishing the test;
step S7: and (5) calculating and displaying an experimental result.
Compared with the prior art, the invention has the advantages that:
the system and the method for measuring the surface pressure of the rotor wing model of the low-speed wind tunnel have the advantages of simple structure and low cost, and the system for splitting and expanding beams is designed and the three-dimensional angle adjusting mechanism is added by optimizing the shape and the size of light spots, so that the real-time measurement of the variable azimuth angle and the upper and lower surfaces of the rotor wing is realized, and the measurement efficiency is greatly improved.
Drawings
Fig. 1 is a schematic diagram of an experimental apparatus for measuring the upper surface of a blade in the prior art.
Fig. 2 is a schematic diagram of an experimental device for measuring the lower surface of a blade in the prior art.
Fig. 3 is a schematic diagram of experimental measurements at different azimuth angles.
Fig. 4 is a schematic structural diagram of a measuring system of the present invention in embodiment 1.
Fig. 5 is a schematic structural diagram of a measuring system of the present invention in embodiment 2.
Fig. 6 is a schematic flow chart of a measurement method of the present invention in an embodiment.
Illustration of the drawings:
1. an excitation light source; 2. a rotor; 3. a concave lens; 4. a camera; 5. a first cylindrical lens; 6. a second cylindrical lens; 7. a first reflective mirror; 8. a reflector angle adjusting bracket; 9. a camera angle adjustment bracket; 10. a beam splitter prism; 11. a synchronization controller; 12. a computer; 13. a second reflective mirror.
Detailed Description
The invention will be described in further detail below with reference to the drawings and specific examples.
Example 1: taking a component to be measured as a rotor 2 as an example, as shown in fig. 4, the system for measuring the surface pressure of the variable azimuth angle of the rotor model of the low-speed wind tunnel according to the present invention includes: the device comprises an excitation light source 1 and a measuring device, wherein the measuring device comprises a beam expanding unit, a camera 4 and a first reflector 7; wherein, the excitation light source 1 is a high-power pulse laser (usually a pulse laser with an output power of 500mJ and an output wavelength of 532 nm); the solution of figure 4 is used when the test only requires the measurement of one of the upper and lower surfaces of the rotor 2. The point light source output by the excitation light source 1 firstly expands the beam through a circular concave lens 3, then expands the beam through a first cylindrical lens 5 and a second cylindrical lens 6 in two orthogonal dimensions, and the size of a light spot after expanding the beam is determined according to the size of the rotor 2. For example, in a 2-meter diameter rotor wing test, the area of a rectangular light spot after beam expansion is-1200 mm multiplied by 200 mm; for example, in a rotor wing test with the diameter of 3 meters, the area of the expanded rectangular light is-1800 mm multiplied by 300mm, and the area of the expanded rectangular smooth surface is slightly larger than that of the rotor wing 2; in specific application, the lens focal lengths of the first cylindrical lens 5 and the second cylindrical lens 6 are selected according to the specific opening size of the wind tunnel and the distance between the excitation light source 1 and the test smooth surface, and the common focal lengths are selectedfThe range is-20 mm-400 mm.
The light source expands the back through three lens plastic, passes through a first reflector 7 with light reflection to rotor oar plane again, and camera 4 installs on camera angle alignment jig 9, and first reflector 7 installs on reflector angle alignment jig 8, and camera angle alignment jig 9 and reflector angle alignment jig 8 all can adopt automatically controlled angle alignment jig to realize in the experiment that the rotor does not stop rotating, the wind-tunnel does not stop wind the real-time change and the measurement of rotor measurement azimuth under the state.
In a specific application example, the camera angle adjusting bracket 9 may be a two-dimensional electric angle adjusting bracket, and the reflector angle adjusting bracket 8 may be a three-dimensional electric angle adjusting bracket.
In a specific application example, the camera 4 should select a suitable lens, so that the field of view of the camera 4 covers the entire rotor 2 and is slightly larger than the size of the rotor 2 (the focal length of the lens of the camera 4 is typically 30mm-160 mm).
In a specific application example, the excitation light source 1, the concave lens 3, the first cylindrical lens 5, the second cylindrical lens 6, the camera 4, the first reflector 7 and the angle adjusting frames are all fixed on an optical bread board, so that the whole debugging, installation and movement are convenient.
Example 2: this example is mainly applicable to when the experiment needs to measure the upper and lower surface pressure of rotor simultaneously, as shown in fig. 5, the structure excitation light source 1, two sets of measuring device, second reflector 13 and beam splitter prism 10 of this embodiment, measuring device's structure is the same basically with embodiment 1, a set of measuring device is located the top of rotor 2, another set of measuring device is located the below of rotor 2, divide the light that excitation light source 1 output equally into two upper and lower ways through beam splitting unit and second reflector 13, be used for the beam expanding unit of upper and lower surface respectively. At the moment, the pressure measurement of the upper surface and the lower surface can adjust the beam expanding smooth surface and the camera view field to the same azimuth angle of the rotor wing 2 according to the test requirement to carry out synchronous measurement of the upper surface and the lower surface; or adjusted to different azimuths for independent measurements.
As shown in fig. 6, the present invention further provides a method for measuring surface pressure of a rotor model of a low-speed wind tunnel with variable azimuth angle, which comprises the following steps:
step S1: the CCD shoots a dark background.
The camera 4 and the excitation light source 1 are erected right above a pressure surface (rotor wing 2) to be tested of the model, a test site is required to be in a darkroom environment as much as possible, and firstly, a dark background image of the environment is shot through the camera 4 (CCD) and is used for deducting background noise interference in a later period.
Step S2: the rotor 2 rises to the test rotating speed, and the wind tunnel blows after the rotating speed is stable.
The test usually simulates the tip mach number of a real helicopter, rotating at about 2100rpm for a 2 meter diameter rotor 2; a 3 meter diameter rotor 2, rotating at approximately 1400 rpm. The diameter of the rotor 2 increases and the speed decreases, gradually approaching the real helicopter speed.
Step S3: the camera 4 and the excitation light source 1 are triggered synchronously to take PSP images. After the rotating speed and the wind speed are stable, a photoelectric encoder of the rotor wing test bed synchronously triggers signals for the excitation light source 1 and the camera 4, and Pressure Sensitive Paint (PSP) rotor wing images are collected.
Step S4: the synchronous trigger camera 4 and the excitation light source 1 capture a TSP image.
After the pressure-sensitive paint image is shot, a trigger signal is changed to the temperature-sensitive paint (TSP) rotor wing 2, and a TSP rotor wing image is collected. In which temperature-sensitive lacquer rotors are used for temperature compensation, usually sprayed onto the blades of two adjacent or symmetrical rotors 2 together with pressure-sensitive lacquer rotors.
Step S5: and judging whether the acquisition of all azimuth angles to be detected is finished.
If not, controlling the camera 4 and the electric control angle adjusting frame of the excitation light source 1 to the azimuth angle area to be measured (the adjusting time is less than 5 seconds), and repeating the steps S3 and S4 after changing the synchronous trigger signal until all azimuth angles are measured.
Step S6: the wind tunnel and rotor 2 are stopped and the test is finished.
The wind tunnel wind speed gradually decreases to zero and then the rotor 2 stops rotating.
Step S7: 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.
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 (8)
1. A variable azimuth angle surface pressure measuring system of a low-speed wind tunnel rotor model is characterized by comprising an excitation light source and a measuring device, wherein the measuring device comprises a beam expanding unit, a camera and a reflector; the beam expanding unit comprises a concave lens, a first cylindrical lens and a second cylindrical lens which are sequentially arranged, a point light source output by the excitation light source expands beams through the concave lens, then expands beams in two orthogonal dimensions through the first cylindrical lens and the second cylindrical lens, and the size of a light spot after beam expansion is determined according to the size of a component to be measured; after the light source is expanded by the beam expanding unit, the light is reflected to a component to be measured through a reflector, and then image acquisition is carried out through a camera; the camera is arranged on the camera angle adjusting frame; the reflector is arranged on the reflector angle adjusting frame.
2. The variable azimuth surface pressure measurement system of a low-speed wind tunnel rotor model according to claim 1, wherein the camera angle adjustment mount is an electric angle adjustment mount.
3. The variable azimuth surface pressure measurement system of a low-speed wind tunnel rotor model according to claim 1, wherein the camera angle adjustment mount is a two-dimensional motorized angle adjustment mount.
4. The system according to claim 1, wherein said mirror angle adjustment mount is an electric angle adjustment mount.
5. The variable azimuth surface pressure measurement system of a low-speed wind tunnel rotor model according to claim 1, wherein the mirror angle adjustment mount is a three-dimensional motorized angle adjustment mount.
6. The system according to any one of claims 1-5, wherein the excitation light source, the concave lens, the first cylindrical lens, the second cylindrical lens, the camera, and the reflector are all fixed to an optical bread board.
7. The system for measuring the surface pressure of the low-speed wind tunnel rotor model with the variable azimuth angle according to any one of claims 1 to 5, wherein the measuring devices are divided into two groups, one group of measuring devices is positioned above the component to be measured, the other group of measuring devices is positioned below the component to be measured, and light output by the excitation light source is divided into an upper path and a lower path through a light splitting unit and a second reflector, and the upper path and the lower path are respectively used for the beam expanding units on the upper surface and the lower surface.
8. A method for measuring variable azimuth surface pressure of a low-speed wind tunnel rotor model based on the measuring system of any one of the claims 1-7, characterized by comprising the following steps:
step S1: shooting a dark background by a camera;
step S2: raising to a test rotating speed, and after the rotating speed is stable, blowing wind in the wind tunnel;
step S3: synchronously triggering a camera and an excitation light source to shoot a PSP image; after the rotating speed and the wind speed are stable, synchronously triggering signals for an excitation light source and a camera through a photoelectric encoder of the test bed, and collecting a pressure-sensitive paint image;
step S4: synchronously triggering a camera and an excitation light source to shoot a TSP image; after the pressure-sensitive paint image is shot, changing a trigger signal to the temperature-sensitive paint, and collecting a TSP image;
step S5: judging whether the acquisition of all azimuth angles to be detected is finished; if not, controlling the angle adjusting frames of the camera and the excitation light source to the azimuth angle area to be measured, changing the synchronous trigger signal, and repeating the steps S3 and S4 until all azimuth angles are measured;
step S6: stopping the wind tunnel and the test stand, and finishing the test;
step S7: and (5) calculating and displaying an experimental result.
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| CN114061894B (en) * | 2021-11-12 | 2023-12-19 | 中国空气动力研究与发展中心高速空气动力研究所 | Cavity model pulsating pressure and noise measurement system |
| CN114061895B (en) * | 2021-11-12 | 2023-12-19 | 中国空气动力研究与发展中心高速空气动力研究所 | Image acquisition method for measuring pulsating pressure and noise of cavity model |
| CN114166487B (en) * | 2021-11-23 | 2023-06-06 | 中国直升机设计研究所 | Rotor azimuth triggering system and method for rotor model test |
| CN114459728B (en) * | 2022-04-13 | 2022-06-24 | 中国空气动力研究与发展中心高速空气动力研究所 | Low-temperature-sensitive paint transition measurement test method |
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| 快响应压敏漆的性能优化及其在大型旋翼风洞试验中的应用;焦灵睿、彭迪、刘应征等;《第十届全国流体力学学术会议论文摘要集》;20181025;第242页第2段，图1-2 * |
| 焦灵睿、彭迪、刘应征等.快响应压敏漆的性能优化及其在大型旋翼风洞试验中的应用.《第十届全国流体力学学术会议论文摘要集》.2018,第242页. * |
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