CN112881004A - Airspeed tube wind tunnel check test device and check test method - Google Patents
Airspeed tube wind tunnel check test device and check test method Download PDFInfo
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Abstract
The invention relates to the technical field of airspeed head, in particular to an airspeed head wind tunnel check test device and a check test method, wherein the device comprises a pressure sensor and a pressure scanning valve; the pressure sensor is arranged on a wind tunnel front chamber, the pressure scanning valve is respectively connected with a total pressure measuring point and a static pressure measuring point of the airspeed tube, and one output of the pressure sensor is connected to the pressure scanning valve; the airspeed head is arranged at the wind tunnel test section; the pressure sensor is used for measuring the total pressure of the incoming flow of the wind tunnel and adjusting a flow field of the wind tunnel according to the total pressure of the incoming flow; the pressure scanning valve is used for synchronously measuring the total pressure of the incoming flow of the wind tunnel, the total pressure of the local incoming flow of the airspeed head and the static pressure of the local incoming flow of the airspeed head. The device provided by the invention improves the validity of the measured data and reduces the cost of the wind tunnel nuclear test; the method provided by the invention can calibrate and evaluate the pneumatic performance of the airspeed head more accurately, objectively and truly, and provides reliable ground model data for practical installation application.
Description
Technical Field
The invention relates to the technical field of airspeed tubes, in particular to an airspeed tube wind tunnel check test device and a check test method.
Background
The airspeed head is an indispensable measuring device for sensing and measuring the flying speed, flying attitude and flying height (static pressure height) of an aircraft (particularly a civil aircraft and a fighter) in real time in flight; the method has important significance for guaranteeing the flight safety of the aircraft and improving the flight quality, and is indispensable.
In most cases, the airspeed head is installed in the head area of the aircraft (right in front of the aircraft head or on the left and right sides of the aircraft head), so that the aerodynamic interference of the aircraft body on the airspeed head is reduced as much as possible, and the accuracy of the airspeed head in measuring the inflow parameters is improved.
The operating principle of a pitot tube, in short, is based on the bernoulli equation: p0＝P∞+1/2ρV2. Wherein, P0Is total pressure, P∞Is static pressure. In actual flight, the total pressure P of local incoming flow is measured by a measuring airspeed head0And the local incoming flow static pressure P of the airspeed head∞Thereby calculating the flying speed V and other atmospheric numbersAccording to the parameters. If the total pressure P is0Static pressure P∞If the pressure value has measurement deviation, the calculated atmospheric data parameter will be obviously distorted.
The finished airspeed head produced and processed is subjected to necessary wind tunnel tests before being mounted on an airplane. Through an actual blowing test, whether the produced product is qualified or not and whether the product meets the design requirements or not is checked; on the basis, a pneumatic data curve of each qualified airspeed head is obtained, and basic input data are provided for the final installation.
At present, the size of the finished pitot tube is developed towards miniaturization, the diameter of the pitot tube body is generally about 20.0mm, the height H is about 100.0mm, and the whole structure is in an L-shaped form. Based on the basic configuration, the test purpose and the actual size, when airspeed tube check tests are carried out at home at present, a wind tunnel with the caliber of 0.6m multiplied by 0.6m is generally selected to carry out the tests. The wind tunnel with the caliber meets the test requirement and reduces the test cost to the maximum extent. The '0.6 m multiplied by 0.6m aperture' wind tunnel is a wind tunnel with a test section of a rectangular cross section and 0.6m long and wide.
When the wind tunnel test is carried out, the airspeed head is fixed on the side wall of the wind tunnel through the special supporting device, and the arbitrary change of the attitude angle of the airspeed head in the blowing process is realized through the special attack angle driving mechanism outside the side wall so as to meet the test requirement.
The pitot tube generally comprises a total pressure Pm0Measuring point (located at the top of the head of the pipe body) and static pressure PiAnd a measuring point (positioned in the middle of the equal straight section of the pipe body) is led out through a piezometer pipe and is connected into the electronic pressure scanning valve, so that the total pressure and the static pressure of the air flow flowing through the pipe body of the airspeed pipe are measured. Fig. 1 shows a schematic diagram of a prior art measurement method.
Theoretically, when the verification test is carried out in a speed range of subsonic speed, the total pressure P of local incoming flow of the airspeed headm0Should be in total pressure P with wind tunnel incoming flow0The difference should not be so great that even considering the losses in flow viscosity, energy, etc., the difference is generally 200Pa and P0＞Pm0The test result is more reasonable; and is a judgment standard for judging whether the test data of the airspeed tube is reasonable or not.
However, in recent test work, it is found that the two total pressure values in the prior art, namely the total pressure of the wind tunnel incoming flow and the local total pressure of the airspeed head, have a larger difference from a theoretical analysis result, and even have a test phenomenon obviously contrary to the conventional principle, which always troubles the improvement of the quality of test data.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provides a wind tunnel check test device and a check test method for an airspeed tube.
In order to achieve the aim, the invention provides a wind tunnel check test device for an airspeed head, which comprises a pressure sensor and a pressure scanning valve; the pressure sensor is arranged at a wind tunnel front chamber, the pressure scanning valve is respectively connected with a total pressure measuring point and a static pressure measuring point of the airspeed tube, and one output of the pressure sensor is connected with the pressure scanning valve; the air speed pipe is arranged in the wind tunnel test section; wherein the content of the first and second substances,
the pressure sensor is used for measuring the total pressure of the incoming flow of the wind tunnel and adjusting the flow field of the wind tunnel according to the total pressure of the incoming flow;
the pressure scanning valve is used for synchronously measuring the total pressure of the incoming flow of the wind tunnel, the total pressure of the local incoming flow of the airspeed head and the static pressure of the local incoming flow of the airspeed head.
As an improvement of the device, the pressure sensor leads out a path to be connected with the input end of the pressure scanning valve through a three-way joint.
A airspeed tube wind tunnel check test method is realized based on the airspeed tube wind tunnel check test device, and the method comprises the following steps:
setting different attack angles of the airspeed head, and synchronously measuring the total pressure of the incoming flow of the wind tunnel, the total pressure of the local incoming flow of the airspeed head and the static pressure of the local incoming flow of the airspeed head by a pressure scanning valve;
judging whether the difference value between the total pressure of the wind tunnel incoming flow and the total pressure of the local incoming flow of the airspeed head is within a set threshold range, if so, obtaining the flight speed according to a Bernoulli equation by measuring the obtained total pressure of the local incoming flow of the airspeed head and the local incoming flow static pressure of the airspeed head; otherwise, the measurement data is invalid and the measurement is carried out again;
and obtaining a pneumatic data curve of the airspeed head according to the attack angle of the airspeed head, the corresponding local inflow total pressure of the airspeed head, the local inflow static pressure of the airspeed head and the flying speed.
As an improvement of the method, the method also comprises the steps of installing a airspeed head at the test section of the wind tunnel; the method specifically comprises the following steps:
the airspeed head to be tested is fixed on the side wall of the wind tunnel through a special supporting device, and the incidence angle of the airspeed head is adjusted in the blowing process through a special incidence angle driving mechanism outside the side wall.
As an improvement of the above method, the method further comprises: and according to the total pressure of the wind tunnel incoming flow measured by the pressure sensor of the airspeed tube wind tunnel check test device, the mach number of the wind tunnel incoming flow can meet the parameter requirement by adjusting the wind tunnel test parameters.
As an improvement of the method, the total local inflow pressure of the pitot tube and the static local inflow pressure of the pitot tube obtained by measurement are used for obtaining the flight speed according to the Bernoulli equation; the method specifically comprises the following steps:
wherein V is the flight speed, PS1Is the total pressure of local incoming flow of the airspeed head, P∞The local incoming flow static pressure of the airspeed head, and rho is the incoming flow density of the wind tunnel.
Compared with the prior art, the invention has the advantages that:
1. the device provided by the invention overcomes the defects that in the device in the prior art, the effectiveness of measured data is improved due to asynchronous measurement of the sensor, and the cost of a wind tunnel nuclear test is reduced;
2. the method provided by the invention can calibrate and evaluate the pneumatic performance of the airspeed tube/the batch of airspeeds more accurately, objectively and truly, and provides reliable ground model data for practical installation application.
Drawings
FIG. 1 is a schematic illustration of a prior art airspeed tube wind tunnel check test apparatus;
FIG. 2 is a schematic view of a wind tunnel check test device of an airspeed tube in accordance with embodiment 1 of the present invention;
FIG. 3 is a flow chart of a airspeed tube wind tunnel verification test method according to embodiment 2 of the present invention;
fig. 4 is test data for a wind tunnel verification test method using an airspeed head in accordance with the present invention.
Detailed Description
After technical factors such as air leakage of a pressure measuring pipeline, abnormal working of a sensor and the like are eliminated, reasons and technical solutions for data abnormity caused by measurement in the prior art are found after repeated exploration.
The reasons for the occurrence of data anomalies are: out of sync of sensor measurements; the solution measures are as follows: and connecting the two paths of pressure signals to the same sensor.
When a conventional wind tunnel test is carried out, the total pressure probe positioned in the wind tunnel front chamber is used for measuring the total pressure P of incoming flow in the wind tunnel operation process0And driving a wind tunnel pressure regulating valve to regulate the total pressure in a closed-loop PID regulation mode, and finally regulating the Mach number Ma of the test section to a target value. The wind tunnel operation mode is feasible for conventional force and pressure measuring tests, and the technology is mature, reliable and stable. As shown in fig. 1.
The requirement on refinement is higher, the requirement on test data accuracy is higher, and the requirement and wind tunnel operation parameters (such as total pressure P of wind tunnel incoming flow)0) For airspeed tube check tests of detailed comparison and inverse judgment verification, certain technical defects exist. Total pressure Ps1 measured by airspeed head and total pressure P of wind tunnel incoming flow0The comparison is a key standard for judging/verifying the validity and the rationality of data in the airspeed tube calibration test; it is through this comparison that the technical defects in the prior art are discovered. Two typical abnormal and unreasonable data for this type of test are given in the following two tables. In the table, Ps1 is a measurement value of the total pressure of the airspeed tube, P0 is the total pressure of the incoming flow of the wind tunnel, and the difference between Ps1 and P0 is too large to exceed the normal threshold range.
TABLE 1 one of the unreasonable data phenomena-two total pressure data volumes differ greatly
| Total pressure probe | |||||||||||||
| First-time vehicle | 0003 times of the car | ||||||||||||
| STEP | M | αM | βM | γM | Pa | P0 | Pct | p | q | Ps1 | Cpt | Ps1-P0 (total pressure-wind of pitot tube) Hole coming current total pressure) | |
| 1 | 0.782 | -20 | 0 | 0 | 94914.5 | 105864.073 | 71294.026 | 70690.44 | 30260.238 | 105341.13 | -0.01728 | -522.943 | |
| 2 | 0.7843 | -18 | 0 | 0 | 94914.5 | 106015.767 | 71238.953 | 70633.245 | 30413.485 | 105386.89 | -0.02068 | -628.877 | |
| 3 | 0.78243 | -16 | 0 | 0 | 94914.5 | 105891.653 | 71283.011 | 70679.03 | 30288.823 | 105442.85 | -0.01482 | -448.803 | |
| 4 | 0.78477 | -14 | 0 | 0 | 94914.5 | 105933.025 | 71150.838 | 70545.343 | 30412.436 | 105445.86 | -0.01602 | -487.165 | |
| 5 | 0.78369 | -12 | 0 | 0 | 94914.5 | 105905.444 | 71205.91 | 70601.159 | 30353.147 | 105490.75 | -0.01366 | -414.694 | |
| 6 | 0.78192 | -8 | 0 | 0 | 94914.5 | 105864.073 | 71299.533 | 70695.991 | 30256.384 | 105448.71 | -0.01373 | -415.363 | |
| 7 | 0.7837 | -4 | 0 | 0 | 94914.5 | 105946.815 | 71233.446 | 70628.457 | 30365.199 | 105423.38 | -0.01724 | -523.435 | |
| 8 | 0.78485 | 0 | 0 | 0 | 94914.5 | 105891.653 | 71117.794 | 70512.494 | 30404.225 | 105480.3 | -0.01353 | -411.353 | |
| 9 | 0.78568 | 2 | 0 | 0 | 94914.5 | 105960.605 | 71106.78 | 70500.63 | 30463.988 | 105485.68 | -0.01559 | -474.925 | |
| 10 | 0.78246 | 4 | 0 | 0 | 94914.5 | 105877.863 | 71271.997 | 70668.081 | 30286.09 | 105468.89 | -0.0135 | -408.973 | |
| 11 | 0.78461 | 6 | 0 | 0 | 94914.5 | 105933.025 | 71161.852 | 70556.445 | 30404.752 | 105509.9 | -0.01392 | -423.125 | |
| 12 | 0.78391 | 8 | 0 | 0 | 94914.5 | 105960.605 | 71227.939 | 70622.753 | 30379.473 | 105494.23 | -0.01535 | -466.375 | |
| 13 | 0.78224 | 10 | 0 | 0 | 94914.5 | 105864.073 | 71277.504 | 70673.785 | 30271.799 | 105470.72 | -0.01299 | -393.353 | |
| 14 | 0.78617 | 12 | 0 | 0 | 94914.5 | 106043.348 | 71128.809 | 70521.92 | 30511.111 | 105507.85 | -0.01755 | -535.498 | |
| 15 | 0.78405 | 14 | 0 | 0 | 94914.5 | 105933.025 | 71200.403 | 70595.303 | 30377.847 | 105516.24 | -0.01372 | -416.785 | |
| 16 | 0.78306 | 16 | 0 | 0 | 94914.5 | 105946.815 | 71277.504 | 70672.867 | 30334.416 | 105502.31 | -0.01465 | -444.505 | |
| 17 | 0.7852 | 18 | 0 | 0 | 94914.5 | 106001.977 | 71167.359 | 70561.234 | 30453.008 | 105441.59 | -0.0184 | -560.387 | |
| 18 | 0.78421 | 20 | 0 | 0 | 94914.5 | 106015.767 | 71244.461 | 70638.796 | 30409.641 | 105401.37 | -0.0202 | -614.397 | |
TABLE 2 second phenomenon of unreasonable data, the total pressure of airspeed head is higher than the total pressure of wind tunnel incoming flow
| Repetitive vehicle number | 0004 times of vehicle | |||||||||||
| STEP | M | αM | βM | γM | Pa | P0 | Pct | p | q | Ps1 | Cpt | Ps1-P0 (total pressure-wind of pitot tube) Hole coming current total pressure) |
| 1 | 0.78297 | -20 | 0 | 0 | 95145.5 | 105708.942 | 71122.998 | 70519.763 | 30262.445 | 105610.64 | -0.00325 | -98.302 |
| 2 | 0.78461 | -18 | 0 | 0 | 95145.5 | 105695.151 | 71001.84 | 70397.79 | 30336.63 | 105655.25 | -0.00132 | -39.901 |
| 3 | 0.7824 | -16 | 0 | 0 | 95145.5 | 105626.199 | 71106.477 | 70504.027 | 30211.382 | 105632.39 | 0.0002 | 6.191 |
| 4 | 078284 | -14 | 0 | 0 | 95145.5 | 105695.151 | 71122.998 | 70519.916 | 30252.011 | 105789.88 | 0.00313 | 94.729 |
| 5 | 0.78248 | -12 | 0 | 0 | 95145.5 | 105626.199 | 71100.97 | 70498.476 | 30215.234 | 105848.41 | 0.00735 | 222.211 |
| 6 | 0.78469 | -8 | 0 | 0 | 95145.5 | 105695.151 | 70996.332 | 70392.239 | 30340.473 | 105728.02 | 0.00108 | 32.869 |
| 7 | 0.78285 | -4 | 0 | 0 | 95145.5 | 105515.876 | 71001.84 | 70399.776 | 30201.065 | 105751.91 | 0.00782 | 236.034 |
| 8 | 0.78407 | 0 | 0 | 0 | 95145.5 | 105639.99 | 71001.84 | 70398.401 | 30294.936 | 105801.9 | 0.00534 | 161.91 |
| 9 | 0.7824 | 2 | 0 | 0 | 95145.5 | 105626.199 | 71106.477 | 70504.027 | 30211.382 | 105742.5 | 0.00385 | 116.301 |
| 10 | 0.7832 | 4 | 0 | 0 | 95145.5 | 105584.828 | 71023.868 | 70421.217 | 30237.834 | 105779.43 | 0.00644 | 194.602 |
| 11 | 0.78348 | 6 | 0 | 0 | 95145.5 | 105612.409 | 71023.868 | 70420.911 | 30258.696 | 105797.39 | 0.00611 | 184.981 |
| 12 | 0.78359 | 8 | 0 | 0 | 95145.5 | 105639.99 | 71034.883 | 70431.708 | 30271.861 | 105803.25 | 0.00539 | 163.26 |
| 13 | 0.58377 | 10 | 0 | 0 | 95145.5 | 105584.828 | 70985.318 | 70382.358 | 30264.766 | 105871.19 | 0.00946 | 286.362 |
| 14 | 0.78566 | 12 | 0 | 0 | 95145.5 | 105695.151 | 70930.246 | 70325.627 | 30386.551 | 105854.82 | 0.00525 | 159.669 |
| 15 | 0.78232 | 14 | 0 | 0 | 95145.5 | 105626.199 | 71111.984 | 70509.579 | 30207.53 | 105789.88 | 0.00542 | 163.681 |
| 16 | 0.78446 | 16 | 0 | 0 | 95145.5 | 105777.894 | 71067.926 | 70463.487 | 30353.05 | 105906.63 | 0.00424 | 128.736 |
| 17 | 0.78435 | 18 | 0 | 0 | 95145.5 | 105791.684 | 71084.448 | 70479.988 | 30351.943 | 105843.27 | 0.0017 | 51.586 |
| 18 | 0.78311 | 20 | 0 | 0 | 95145.5 | 105722.732 | 71122.998 | 70519.61 | 30272.878 | 105718.69 | -0.00013 | -4.042 |
As can be seen from the last column of Table 2, the measurement P of the total pressure of the pitot tube in this set of tests S1 ratio wind tunnel incoming flow total pressure P0Large, unreasonable data.
In a wind tunnel test, a wind tunnel total pressure sensor adopts a PPT pressure sensor, the measuring range is 100psig, the precision is 0.05 percent FS, and the sampling frequency is 5 Hz. The total pressure data is obtained by low-pass filtering the voltage output signal of a PPT total pressure sensor through a front-end signal conditioner 1Hz hardware, then entering a 16-bit A/D acquisition card, converting the voltage output signal into a digital signal, and calculating a pressure value according to a sensor calibration curve formula, thereby obtaining the total pressure P of the incoming flow of the wind tunnel0。
And the total pressure P of the pitot tube S1 is acquired by pressure scanning valve acquisition. The pressure scanning valve adopts a DTC initial system, the pressure acquisition module adopts a DTC 64HDC type scanner which supports high-speed sampling and low-speed sampling, the high-speed sampling rate is 330Hz, the low-speed sampling rate is 165Hz, and the sampling rate is far higher than that of a wind tunnel total pressure sensor by 5Hz regardless of low speed or high speed. In the test, for the collection of airspeed tube pressure data, the pressure in a step state is generally obtained by adopting a software averaging methodAnd (4) data.
The technical performance introduction of the two aspects shows that the total pressure sensor and the pressure scanning valve have obvious differences in pressure acquisition time sequence, acquisition mode and sampling rate; for the same pressure signal, the pressure values measured by the total pressure sensor and the pressure scanning valve are necessarily out of synchronization, and the data difference is inevitable.
Example 1
As shown in fig. 1, embodiment 1 of the present invention provides an airspeed head wind tunnel check test device, which includes a pressure sensor and a pressure scanning valve; the pressure sensor is arranged in a wind tunnel front chamber, the pressure scanning valve is respectively connected with a total pressure measuring point and a static pressure measuring point of the airspeed tube, and one output of the pressure sensor is connected with the pressure scanning valve; the air speed pipe is arranged in the wind tunnel test section; wherein the content of the first and second substances,
the pressure sensor is used for measuring the total pressure of the incoming flow of the wind tunnel and adjusting the flow field of the wind tunnel according to the total pressure of the incoming flow;
the pressure scanning valve is used for synchronously measuring the total pressure of the incoming flow of the wind tunnel, the total pressure of the local incoming flow of the airspeed head and the static pressure of the local incoming flow of the airspeed head.
A path of total pressure signal of the front chamber is led out through a three-way joint and is connected into a pressure scanning valve for measuring a pressure signal of an airspeed tube, and the technical idea of measuring the pressure signal by using the same hardware equipment is realized. An original path of pressure signal is still connected to the wind tunnel total pressure sensor, and the pressure signal is used for adjusting a wind tunnel flow field and always exists and normally works.
Example 2
As shown in fig. 3, an embodiment 2 of the present invention provides a method for performing a verification wind tunnel test by using the apparatus of embodiment 1, and the specific steps are as follows:
the airspeed head to be tested is fixed on the side wall of the wind tunnel through a special supporting device, and the incidence angle of the airspeed head is adjusted in the blowing process through a special incidence angle driving mechanism outside the side wall;
according to the total pressure of incoming flow measured by a pressure sensor of the airspeed tube wind tunnel check test device, the mach number of the incoming flow of the wind tunnel reaches the parameter requirement by adjusting the test parameters of the wind tunnel;
setting different attack angles of the airspeed head, and synchronously measuring the total pressure of the incoming flow of the wind tunnel, the total pressure of the local incoming flow of the airspeed head and the local incoming flow static pressure of the airspeed head by a pressure scanning valve of a wind tunnel check test device of the airspeed head;
judging whether the difference value between the total pressure of the wind tunnel incoming flow and the total pressure of the airspeed head gas is within a set threshold range, if so, obtaining the flight speed according to a Bernoulli equation by measuring the measured total pressure of the airspeed head local incoming flow and the airspeed head local incoming flow static pressure; otherwise, the measurement data is invalid and the measurement is carried out again;
and obtaining a pneumatic data curve of the airspeed head according to the attack angle of the airspeed head, the corresponding local inflow total pressure of the airspeed head, the local inflow static pressure of the airspeed head and the flying speed.
The test data obtained by the method of the invention is shown in figure 4, and compared with the common wind tunnel total pressure P0 (still measured by a total pressure sensor), the difference between the data measured by the P0-scan and the data measured by the P0m in a reasonable interval and the size relationship between the data measured by the P0-scan and the data measured by the P0m also accord with theoretical expectation, and simultaneously accord with the simulation result of the CFD technology before the test. In the table, P0-scan and P0m are total pressure of the wind tunnel incoming flow and total pressure of the air ground incoming flow measured by the scanning valve.
The invention achieves the following technical effects:
1. the aerodynamic performance of the airspeed tube/the batch of airspeeds can be calibrated and evaluated more accurately, objectively and truly, and reliable ground model data are provided for actual installed application;
2. the purpose of measuring total pressure based on the bernoulli equation pitot tube has been to solve for airspeed V, previously described. From this perspective, if the data P0-scan in FIG. 4 is taken as "true value" and P0 is taken as "false true value" (or referred to as error value), then | P0 m-P0-scan | ≈ 250Pa and | P0 m-P0 | ≈ 400 Pa. The difference between the two is very different. In the airspeed head after the wind tunnel test, the measured total pressure P0m of the airspeed head is corrected and optimized based on the wind tunnel total pressure, the correction based on P0-scan is reasonable, and the correction based on P0 has obvious errors/deviations. On one hand, the deviation of the total pressure introduces obvious deviation to the calculation of the airspeed V, so that the calculation result is distorted; on the other hand, optimization of the geometric configuration of the blank pipe is misled, and a wrong optimization direction is indicated.
Through the work and the technical improvement and the verification of the test result, the invention achieves the following purposes:
1. the problem that the total pressure measurement is asynchronous in the airspeed tube calibration test in the prior art is solved;
2. the question that the two total pressure values are different and even unreasonable all the time in airspeed head check tests for many years is answered;
3. a reliable, feasible and convenient technical approach and solution idea are explored for developing airspeed head check tests (or tests needing data cross validation) in the future.
Finally, it should be noted that the above embodiments are only used for illustrating the technical solutions of the present invention and are not limited. Although the present invention has been described in detail with reference to the embodiments, it will be understood by those skilled in the art that various changes may be made and equivalents may be substituted without departing from the spirit and scope of the invention as defined in the appended claims.
Claims (6)
1. A wind tunnel check test device for an airspeed head is characterized by comprising a pressure sensor and a pressure scanning valve; the pressure sensor is arranged on a wind tunnel front chamber, the pressure scanning valve is respectively connected with a total pressure measuring point and a static pressure measuring point of the airspeed tube, and one output of the pressure sensor is connected to the pressure scanning valve; the airspeed head is arranged at the wind tunnel test section; wherein the content of the first and second substances,
the pressure sensor is used for measuring the total pressure of the incoming flow of the wind tunnel and adjusting the flow field of the wind tunnel according to the total pressure of the incoming flow;
the pressure scanning valve is used for synchronously measuring the total pressure of the incoming flow of the wind tunnel, the total pressure of the local incoming flow of the airspeed head and the static pressure of the local incoming flow of the airspeed head.
2. The airspeed tube wind tunnel check test device of claim 1, wherein the pressure sensor is connected to the input end of the pressure scanning valve through a tee joint leading out one path.
3. A airspeed tube wind tunnel check test method realized based on the airspeed tube wind tunnel check test device of one of claims 1-2, the method comprising:
setting different attack angles of the airspeed head, and synchronously measuring the total pressure of the incoming flow of the wind tunnel, the total pressure of the local incoming flow of the airspeed head and the static pressure of the local incoming flow of the airspeed head by a pressure scanning valve;
judging whether the difference value between the total pressure of the wind tunnel incoming flow and the total pressure of the local incoming flow of the airspeed head is within a set threshold range, if so, obtaining the flight speed according to a Bernoulli equation by measuring the obtained total pressure of the local incoming flow of the airspeed head and the local incoming flow static pressure of the airspeed head; otherwise, the measurement data is invalid and the measurement is carried out again;
and obtaining a pneumatic data curve of the airspeed head according to the attack angle of the airspeed head, the corresponding local inflow total pressure of the airspeed head, the local inflow static pressure of the airspeed head and the flying speed.
4. The airspeed tube wind tunnel check test method according to claim 3, characterized in that the method further comprises installing an airspeed tube at the wind tunnel test section; the method specifically comprises the following steps:
the airspeed head to be tested is fixed on the side wall of the wind tunnel through a special supporting device, and the incidence angle of the airspeed head is adjusted in the blowing process through a special incidence angle driving mechanism outside the side wall.
5. The airspeed tube wind tunnel check test method of claim 4, wherein the method further comprises: and according to the total pressure of the wind tunnel incoming flow measured by the pressure sensor of the airspeed tube wind tunnel check test device, the mach number of the wind tunnel incoming flow can meet the parameter requirement by adjusting the wind tunnel test parameters.
6. The airspeed tube wind tunnel check test method according to claim 3, wherein the flying speed is obtained according to Bernoulli's equation by measuring the local incoming flow total pressure and the local incoming flow static pressure of the airspeed tube; the method specifically comprises the following steps:
wherein V is the flight speed, PS1Is the total pressure of local incoming flow of the airspeed head, P∞The local incoming flow static pressure of the airspeed head, and rho is the incoming flow density of the wind tunnel.
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| CN117147093A (en) * | 2023-10-30 | 2023-12-01 | 中国航空工业集团公司沈阳空气动力研究所 | Wind tunnel test measuring device for acoustic explosion characteristics of low acoustic explosion supersonic civil aircraft |
| CN117147093B (en) * | 2023-10-30 | 2024-01-23 | 中国航空工业集团公司沈阳空气动力研究所 | Wind tunnel test measuring device for acoustic explosion characteristics of low acoustic explosion supersonic civil aircraft |
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