CN113390603B - Wind speed measuring device for low-pressure high-speed Mars wind tunnel and precision improving method thereof - Google Patents
Wind speed measuring device for low-pressure high-speed Mars wind tunnel and precision improving method thereof Download PDFInfo
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- CN113390603B CN113390603B CN202110672529.8A CN202110672529A CN113390603B CN 113390603 B CN113390603 B CN 113390603B CN 202110672529 A CN202110672529 A CN 202110672529A CN 113390603 B CN113390603 B CN 113390603B
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- G—PHYSICS
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- 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
Abstract
The invention discloses a wind speed measuring device for a low-pressure high-speed Mars wind tunnel and a precision improving method thereof. The device includes laser instrument (1), L type pitot tube (2), CCD camera (3), sand and dust (4), mars wind-tunnel (5) and lens (6), evenly spread sand and dust (4) in mars wind-tunnel (5), the fixed laser instrument (1) that sets up in top of mars wind-tunnel (5), fixed lens (6) that set up in below of laser instrument (1), L type pitot tube (2) are inserted to the top slant of mars wind-tunnel (5), the full pressure pore alignment incoming flow direction of L type pitot tube (2), install in the planar vertical direction of piece light in CCD camera (3), it is regional the place ahead of L type pitot tube (2) to shoot the back CCD camera (3). The invention is used for solving the problem that the wind speed measurement requirement of the low-pressure high-speed Mars wind tunnel test cannot be met in the prior art.
Description
Technical Field
The invention relates to the field of wind tunnel experiment measurement, in particular to a wind speed measuring device for a low-pressure high-speed Mars wind tunnel and a precision improving method thereof.
Background
Wind tunnel tests are the main means of research on aerodynamic properties of aircraft. In the field of Mars detection, it is used for reliability of detectors before test flightAnd (5) sex verification. Two common methods of wind tunnel wind speed measurement are: (1) measuring the difference between the total pressure and the static pressure at a certain point in the wind tunnel by using a pitot tube, and calculating the wind speed at the certain point based on a Bernoulli equation; (2) the method is characterized in that a Particle Image Velocimetry (PIV) technology is utilized, the PIV technology is a non-contact instantaneous full-flow-field velocimetry technology, in the measurement process, tracer particles are distributed in a flow field to be measured, a laser light source illuminates the area of the flow field to be measured, an image acquisition system is used for carrying out image acquisition on the area of the flow field to be measured, and the obtained particle images are processed to obtain the velocity distribution of the flow field. The low-pressure high-speed is characterized in that the internal environment of the wind tunnel is low in air pressure and high in wind speed and is used for simulating the wind of the fire stars. The tracer particles required in the PIV method are sand and dust in a wind tunnel, and the concentration is 0.1-1 g/m 3 。
In the prior art, the wind speed range which can be accurately measured by a pitot tube is limited, the measurement range is generally about 2-70 m/s, the wind speed measurement range of a Mars wind tunnel is required to reach 180m/s according to the quality of a specific instrument; the particle image velocimetry has a limited measurement accuracy on wind speed. Therefore, the prior art can not meet the requirement of wind speed measurement in low-pressure high-speed spark wind tunnel tests.
Disclosure of Invention
The invention provides a wind speed measuring device for a low-pressure high-speed spark wind tunnel and a precision improving method thereof, which are used for solving the problem that the wind speed measuring requirement of a low-pressure high-speed spark wind tunnel test cannot be met in the prior art.
The invention is realized by the following technical scheme:
the utility model provides a be used for high-speed mars wind-tunnel wind speed measuring device of low pressure, the device includes laser instrument 1, L type pitot tube 2, CCD camera 3, sand dust 4, mars wind-tunnel 5 and lens 6, evenly spread sand dust 4 in the mars wind-tunnel 5, the fixed laser instrument 1 that sets up in top of mars wind-tunnel 5, the fixed lens 6 that sets up in below of laser instrument 1, L type pitot tube 2 is inserted to the top slant of mars wind-tunnel 5, L type pitot tube 2's full pressure hole aligns the incoming flow direction, CCD camera 3 is installed in the planar vertical direction of piece of light, the regional place ahead that is L type pitot tube 2 of shooting behind CCD camera 3 installation.
Further, it is characterized byThe concentration of the sand dust 4 in the wind tunnel 5 is 0.1-1 g/m 3 。
A precision improving method for a wind speed measuring device of a low-pressure high-speed Mars wind tunnel comprises the following steps:
step 1: powering on a laser 1, a CCD camera 3, an L-shaped pitot tube 2 and a Mars wind tunnel 5;
step 2: calibrating a particle image speed measurement method by using an L-shaped pitot tube 2;
and step 3: and (3) measuring the wind speed of the low-pressure spark wind tunnel by utilizing the calibration in the step (2).
Further, the step 2 specifically includes the following steps:
step 2.1: when the wind speed measured by the L-shaped pitot tube 2 is less than 70m/s, recording that the wind speed in the low-pressure Mars wind tunnel is measured to be u by utilizing particle image velocimetry 1 Recording that the wind speed u in the low-pressure Mars wind tunnel is measured by using an L-shaped pitot tube 2 2 ；
Step 2.2: measuring the wind speed u in the low-pressure Mars wind tunnel by using the particle image velocimetry technology of the step 2.1 1 And measuring the wind speed u in the low-pressure Mars wind tunnel by using the L-shaped pitot tube 2 2 Calculating the error delta u ═ u of the wind speed measured by the particle image velocimetry 1 -u 2 ；
Step 2.3: gradually increasing the wind speed in the low-pressure Mars wind tunnel, and repeating the steps 2.1 and 2.2 according to the wind speed value based on the Pitot tube measurement result;
step 2.4: obtaining the error delta u of the wind speed measured by the particle image velocimetry technology under different wind speeds according to the obtained step 2.1-2.3, and obtaining the function f (u) of the wind speed error measured by the particle image velocimetry technology relative to the wind speed measured by the L-shaped pitot tube 2 through interpolation or fitting 2 )。
Further, in the step 3, specifically,
when L-shaped pitot tube 2 measures Mars wind tunnel wind speed result u 2 When the wind speed is less than 70m/s, the final result u-u of the wind speed measurement of the starry wind tunnel is taken 2 ；
When L-shaped pitot tube 2 measures the Mars wind speed result u 2 When the wind speed is more than 70m/s, the final result of the wind speed measurement of the starry wind tunnel is taken as the particle image technology velocity measurementSum of the result and the estimated error at that wind speed, i.e. u-u 1 +f(u 1 )。
The invention has the beneficial effects that:
the invention improves the measurement precision.
The invention greatly widens the range of measuring the wind speed of the Mars wind tunnel.
The invention improves the method based on the prior art, and is easy for technical personnel to master the technology and adjust the equipment structure.
The experimental equipment is simple and convenient to operate, and can meet the wind speed measurement requirements of various wind tunnels.
Drawings
FIG. 1 is a front view of the test apparatus of the present invention.
FIG. 2 is a top view of the testing device of the present invention.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be obtained by a person skilled in the art without making any creative effort based on the embodiments in the present invention, belong to the protection scope of the present invention.
Example 1
With reference to the attached drawing figure 1, the device for measuring the wind speed of the low-pressure high-speed Mars wind tunnel comprises a laser 1, an L-shaped pitot tube 2, a CCD (charge coupled device) camera 3, sand dust 4, a Mars wind tunnel 5 and a lens 6, wherein the sand dust 4 is uniformly distributed in the Mars wind tunnel 5, the laser 1 is fixedly arranged at the top end of the Mars wind tunnel 5, the lens 6 is fixedly arranged below the laser 1, sheet light obtained by the laser 1 and the lens 6 irradiates the area near the front of the L-shaped pitot tube 2, the L-shaped pitot tube 2 is obliquely inserted into the upper part of the Mars wind tunnel 5, a full pressure hole of the L-shaped pitot tube 2 is aligned with the incoming flow direction, the CCD camera 3 is arranged in the vertical direction of the sheet light plane, and the shooting area of the CCD camera 3 after being arranged is the area in front of the L-shaped pitot tube 2.
Further, the wind tunnel5 the concentration of the sand 4 in the dust collector is 0.1-1 g/m 3 。
With reference to fig. 1 and fig. 2 of the accompanying drawings, a precision improving method for a low-pressure high-speed mars wind tunnel wind speed measuring device includes the following steps:
step 1: powering on a laser 1, a CCD camera 3, an L-shaped pitot tube 2 and a Mars wind tunnel 5;
step 2: calibrating a particle image speed measurement method by using an L-shaped pitot tube 2;
and step 3: and (3) measuring the wind speed of the low-pressure spark wind tunnel by utilizing the calibration in the step (2).
Further, the step 2 specifically includes the following steps:
step 2.1: when the wind speed measured by the L-shaped pitot tube 2 is less than 70m/s, recording that the low pressure is measured by using particle image velocimetry, namely less than 10kPa, and the wind speed in the Mars wind tunnel is u 1 Recording the wind speed u in the low-pressure Mars wind tunnel measured by using the L-shaped pitot tube 2 2 ；
Step 2.2: measuring the wind speed u in the low-pressure Mars wind tunnel by using the particle image velocimetry technology of the step 2.1 1 And measuring the wind speed u in the low-pressure Mars wind tunnel by using the L-shaped pitot tube 2 2 Calculating the error delta u ═ u of the wind speed measured by the particle image velocimetry 1 -u 2 ；
Step 2.3: gradually increasing the wind speed in the low-pressure Mars wind tunnel, and repeating the steps 2.1 and 2.2 based on the Pitot tube measurement result at the moment;
step 2.4: according to the obtained wind speeds in different wind speeds (namely the error delta u of the wind speed measured by the particle image velocimetry technology of less than 70 m/s) obtained in the steps 2.1-2.3, a function f (u) of the wind speed error measured by the particle image velocimetry technology and the wind speed measured by the L-shaped pitot tube 2 is obtained through interpolation or fitting 2 )。
Further, the step 3 is specifically that,
when L-shaped pitot tube 2 measures Mars wind tunnel wind speed result u 2 When the wind speed is less than 70m/s, the final result u-u of the wind speed measurement of the starry wind tunnel is taken 2 ；
When L-shaped pitot tube 2 measures Mars wind tunnel wind speed result u 2 When the air pressure is more than 70m/s, the starry wind is takenThe final result of the measurement of the wind speed of the tunnel is the sum of the speed measurement result of the particle image technology and the estimation error under the wind speed, namely u is equal to u 1 +f(u 1 )。
Example 2
The following will explain the test of the pressure in the Mars tunnel of 1.0kPa as an example.
The test Mars wind tunnel vessel size phi 812 x 2000, the test section cross-sectional size 63mm x 63mm, and the volume 1.03m 3 . The PIV system adopts a frame-spanning digital CCD (1024x1024 pixel resolution, 256 gray levels, 16-level image gain and minimum frame-spanning time of 1 mu s); the maximum energy of the laser is 200mJ, the frequency is 10Hz, and the thickness of the sheet light source is less than or equal to 2 mm.
The test comprises the following specific steps:
step 1: powering on a laser 1, a CCD camera 3, an L-shaped pitot tube 2 and a Mars wind tunnel 5;
step 2: calibrating a particle image speed measurement method by using an L-shaped pitot tube 2;
and 3, step 3: and (3) measuring the wind speed of the low-pressure spark wind tunnel by utilizing the calibration in the step (2).
Further, the step 2 specifically includes the following steps:
step 2.1: when the wind speed measured by the L-shaped pitot tube 2 is less than 70m/s, recording that the wind speed in the low-pressure Mars wind tunnel is measured to be u by utilizing particle image velocimetry 1 Recording the differential pressure measured by the L-shaped pitot tube 2 as delta p; using formulas
Calculating to obtain the wind speed u in the low-pressure spark wind tunnel 2 ；
Step 2.2: measuring the wind speed u in the low-pressure Mars wind tunnel by using the particle image velocimetry technology of the step 2.1 1 And measuring the wind speed u in the low-pressure Mars wind tunnel by using the L-shaped pitot tube 2 2 Calculating the error delta u of the wind speed measured by particle image velocimetry (Uu) 1 -u 2 ；
Step 2.3: starting from 0m/s, increasing the wind speed in the low-pressure spark wind tunnel every 5m/s to 70m/s, and repeating the steps 2.1 and 2.2 according to the measurement result of a pitot tube at the moment; the test result shows that the maximum wind speed measured by a pitot tube under the cabin pressure of 1.0kPa is 98.05m/s, which is consistent with the result of 97m/s of the air speed of an MWT wind tunnel of TohokuUniversal;
step 2.4: obtaining a function f (u) of the wind speed error measured by the particle image velocimetry technology relative to the wind speed measured by the L-shaped pitot tube 2 by interpolation or fitting according to the error delta u of the wind speed measured by the particle image velocimetry technology under different wind speeds obtained in the steps 2.1-2.3 2 )。
Further, the step 3 is specifically that,
when L-shaped pitot tube 2 measures the Mars wind speed result u 2 When the wind speed is less than 70m/s, the final result u-u of the wind speed measurement of the starry wind tunnel is taken 2 ；
When L-shaped pitot tube 2 measures Mars wind tunnel wind speed result u 2 When the wind speed is more than 70m/s, the final result of the wind speed measurement of the starry wind tunnel is the sum of the speed measurement result of the particle image technology and the estimation error under the wind speed, namely u is u 1 +f(u 1 )。
Claims (3)
1. The utility model provides a be used for high-speed mars wind-tunnel wind speed measuring device of low pressure, its characterized in that, the device includes laser instrument (1), L type pitot tube (2), CCD camera (3), sand dust (4), mars wind-tunnel (5) and lens (6), evenly distribute in mars wind-tunnel (5) and spill sand dust (4), the fixed laser instrument (1) that sets up in top of mars wind-tunnel (5), fixed lens (6) that set up in below of laser instrument (1), L type pitot tube (2) are inserted to the top slope of mars wind-tunnel (5), the full pressure port of L type pitot tube (2) aims at the incoming flow direction, CCD camera (3) are installed in the planar vertical direction of piece of light, CCD camera (3) are installed the back and are shot the place ahead region of L type pitot tube (2).
2. The low-pressure high-speed Mars wind tunnel wind speed measuring device according to claim 1, characterized in that the concentration of the sand and dust (4) in the Mars wind tunnel (5) is 0.1-1 g/m 3 。
3. The accuracy improving method for the low-pressure high-speed Mars wind tunnel wind speed measuring device according to claim 1, characterized by comprising the following steps of:
step 1: the system comprises a power-on starting laser (1), a CCD camera (3), an L-shaped pitot tube (2) and a Mars wind tunnel (5);
step 2: calibrating a particle image speed measurement method by using an L-shaped pitot tube (2);
and 3, step 3: measuring the wind speed of the low-pressure spark wind tunnel by utilizing the calibration of the step 2;
the step 2 specifically comprises the following steps:
step 2.1: when the wind speed measured by the L-shaped pitot tube (2) is less than 70m/s, recording that the wind speed in the low-pressure Mars wind tunnel is u by measuring the speed by using the particle image 1 Recording that the wind speed u in the low-pressure Mars wind tunnel is measured by using the L-shaped pitot tube (2) 2 ；
Step 2.2: measuring the wind speed u in the low-pressure Mars wind tunnel by using the particle image velocimetry technology of the step 2.1 1 And measuring the wind speed u in the low-pressure Mars wind tunnel by using the L-shaped pitot tube (2) 2 Calculating the error delta u ═ u of the wind speed measured by the particle image velocimetry 1 -u 2 ；
Step 2.3: gradually increasing the wind speed in the low-pressure Mars wind tunnel, and repeating the steps 2.1 and 2.2 based on the Pitot tube measurement result at the moment;
step 2.4: obtaining a function f (u) of the error of the wind speed measured by the particle image velocimetry technology relative to the wind speed measured by the L-shaped pitot tube (2) by interpolation or fitting according to the error delta u of the wind speed measured by the particle image velocimetry technology under different wind speeds obtained in the steps 2.1-2.3 2 )；
The step 3 is specifically that the step of the method is that,
when the L-shaped pitot tube (2) measures the Mars wind tunnel wind speed result u 2 When the wind speed is less than 70m/s, the final result u-u of the wind speed measurement of the starry wind tunnel is taken 2 ；
When the L-shaped pitot tube (2) measures the Mars wind tunnel wind speed result u 2 When the wind speed is more than 70m/s, the final result of the wind speed measurement of the starry wind tunnel is the sum of the speed measurement result of the particle image technology and the estimation error under the wind speed, namely u is u 1 +f(u 1 )。
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