CN107091725A - A kind of measuring method for improving wind tunnel pressure measuring test pressure scan data precision - Google Patents
A kind of measuring method for improving wind tunnel pressure measuring test pressure scan data precision Download PDFInfo
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- CN107091725A CN107091725A CN201611218272.4A CN201611218272A CN107091725A CN 107091725 A CN107091725 A CN 107091725A CN 201611218272 A CN201611218272 A CN 201611218272A CN 107091725 A CN107091725 A CN 107091725A
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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
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Abstract
The invention discloses a kind of measuring method for improving wind tunnel pressure measuring test pressure scan data precision, by the scanning valve measurement pipeline for increasing wind-tunnel stagnation pressure, static pressure signal, and Mach number judgement is carried out according to scanning valve pressure measuring system, the quality of data of wind tunnel pressure measuring experiment greatly improved, solves and the problem of model surface pressure is difficult to high-acruracy survey in larger wind-tunnel is fluctuated in flow field.
Description
Technical field
The present invention relates to wind tunnel test e measurement technology, a kind of raising wind tunnel pressure measuring test pressure scan data is specifically related to
The measuring method of precision.
Background technology
Wind-tunnel is a kind of tubulose experimental rig for producing controllable uniform air flow.The measurement experiment of wind tunnel model surface pressure distribution
(hereinafter referred to as manometric test), is that, in order to measure the pressure distribution on dummy vehicle surface, understanding is around the flow behavior of model
Vehicle Structure Strength calculates a kind of wind tunnel test for providing load data.Conventional pressure distribution test method is in model table
The pressure at many pressure taps, pressure tap is opened on face and is connected to pressure scanning valve through connected pipeline, by data acquisition and modulus
Conversion obtains the pressure data of model surface.
Domestic and international tunnel pressure distribution measuring experiment is most of all to become angle of attack test method using ladder, i.e.,：Process of the test
In, wind tunnel control system regulation flow field reaches preset state, and the Controlling model angle of attack moves to a series of predeterminated positions successively,
Each predetermined position is static to wait for a period of time (hereinafter referred to as the time is wait delay wt), makes pressure measurement overpressure and mould
The pressure of type surface measuring point reaches balance, and control system judges that now flow field meets the requirements and is informed about pressure measuring system and starts collection
Pressure data, otherwise continues to adjust flow field until meeting the requirements and notifying pressure measuring system to gather pressure data；Pressure measuring system is connected to
Gathered after notice, preserve pressure data and feed back to control system；Control system is connected to the control angle of attack after feedback and continues to move to
Next predeterminated position and gathered data, until the data under all default angle of attack position all gather complete, this experiment knot
Beam.
When control system adjusts flow field state, the signal of the stagnation pressure being installed in wind-tunnel and static pressure transducer is based on,
The signal real-time is strong, and the fluctuating change in flow field can be reflected rapidly.And model surface pressure is by elongated pressure measurement pipeline
It is connected to pressure scanning valve to measure, because pipeline has transmission delay, (Δ t), its pressure change is relative to stagnation pressure and static pressure
There is necessarily delayed in sensor signal.Control system t judge flow field stablize and notify scanning valve collection pressure when, sweep
Retouch valve collection by be t- Δ ts model surface pressure.
When Flow Field in Wind Tunnel is more stable (Mach number fuctuation within a narrow range in setting range), as long as the wait delay wt of setting
Long enough (wt>Δ t), what scanning valve was collected is still the satisfactory pressure data in flow field, and pipeline delay will not be to measurement essence
Degree causes big influence.But, in Flow Field in Wind Tunnel less stable (Mach number fluctuation exceeds setting range), although control system
Judge that t flow field is met to require, but it cannot be guaranteed that t- Δ ts are also to meet what is required, therefore, what scanning valve was collected can
It can be the undesirable pressure data in flow field.Further, since the randomness of Flow Field in Wind Tunnel fluctuation, is caused in same experimental condition
The manometric test data redundancy precision of lower multi collect is poor, it is difficult to meet the demand of model experiment.This problem is at home
Temporarily rush in formula transonic wind tunnel than more prominent.
The content of the invention
It is an object of the invention to provide a kind of measuring method for improving wind tunnel pressure measuring test pressure scan data precision, it is used to
Wind tunnel pressure measuring experiment is solved the problem of model surface pressure measurement accuracy is poor in the case that flow field fluctuation is larger.
To achieve these goals, the present invention is adopted the following technical scheme that：
A kind of measuring method for improving wind tunnel pressure measuring test pressure scan data precision, comprises the following steps：
Step one：A vent line is drawn respectively from wind-tunnel stagnation pressure and static pressure transducer, and accesses scanning valve pressure measurement system
System, tubing internal diameter and length are consistent with model pressure measurement pipeline, make it have the delay of identical pressure transmission；
Step 2：Stagnation pressure P0 and static pressure Pct that wind tunnel control system collection pressure sensor is measured, it is real according to Mach number Ma
When regulation flow field until meet the requirements, while the Controlling model angle of attack reaches predeterminated position；
Step 3：Wind tunnel control system persistently controls flow field and keeps the static wt that waits for a period of time of model；
Step 4：Wind tunnel control system calculates Mach number Ma now, continues regulation flow field if undesirable straight
To meeting the requirements；
Step 5：Control system sends acquisition instructions to scanning valve pressure measuring system；
Step 6：Scan stagnation pressure P0s, the static pressure Pcts and all model measuring point pressure Psi of valve pressure measuring system collection access
(i=1~n, n count for model surface pressure measurement), calculates Mach number Mas, and this group of data are saved in into buffering area；
Step 7：Scanning valve pressure measuring system judges that Mach number Mas meets the requirements, then goes to step 8；
If scanning valve pressure measuring system judges that Mach number Mas is undesirable, scanning valve pressure measuring system is judged in present bit
Put repeated acquisition and whether the number of times judged exceeds threshold value T；
If beyond threshold value T, scanning valve pressure measuring system selects one group of optimal work of Mach number Mas from the data of buffering area
It is pressure measuring model in the final data of current location, the pressure measurements Mas for recording "current" model preset position is below standard
Information, then perform step 9.
If without departing from threshold value T, system returns to step 6 and continued executing with.
Step 8：Scan valve pressure measuring system using this group of data of collection as pressure measuring model current location final number
According to, and preserve；
Step 9：Scan valve pressure measuring system emptying buffer and send collection and finish information to control system；
Step 10：Control system is received after feedback information, this off-test.
In the above-mentioned technical solutions, in step 6, the buffer area is a memory space, the memory space it is big
The small memory space being multiplied by equal to the threshold value T needed for every group of scan data, for temporarily storing in current location repeated acquisition
All data groups.
In the above-mentioned technical solutions, acquisition instructions described in the step 5, can be the character strings that content is fixed, also may be used
To be to include current test status information, and the character string of dynamic generation, scanning valve pressure measuring system can be by parsing the character string
Obtain corresponding information.
In the above-mentioned technical solutions, feedback information described in the step 9, can be the character string that content is fixed, also may be used
To be to include collection result information, and the character string of dynamic generation, control system can be corresponding by parsing character string acquisition
Information.
In summary, by adopting the above-described technical solution, the beneficial effects of the invention are as follows：It is disclosed in this invention to improve
The measuring method of wind tunnel pressure measuring test pressure scan data precision, by the scanning valve measurement for increasing wind-tunnel stagnation pressure, static pressure signal
Pipeline, and Mach number judgement is carried out according to scanning valve system, the quality of data of wind tunnel pressure measuring experiment greatly improved, solves
Fluctuate the problem of model surface pressure is difficult to high-acruracy survey in larger wind-tunnel in flow field.
Brief description of the drawings
Examples of the present invention will be described by way of reference to the accompanying drawings, wherein：
Fig. 1 is that wind tunnel pressure measuring pilot system connects sketch；
Fig. 2 is the method flow diagram of embodiment.
Embodiment
All features disclosed in this specification, or disclosed all methods or during the step of, except mutually exclusive
Feature and/or step beyond, can combine in any way.
According to the specific embodiment of the invention, a kind of measurement for improving wind tunnel pressure measuring test pressure scan data precision is disclosed
Method, the pilot system that this method is used connects sketch as shown in figure 1, the step of measuring method is included is as shown in Figure 2.
S201. the total-pressure probe and static pressure transducer of wind-tunnel are generally respectively arranged in the cup of wind tunnel body and in room,
Same position is not in test model.In wind tunnel test, in order to realize by scanning valve while measuring total static pressure data,
Need to separate all the way and be connected to pressure scanning valve pressure measuring system from the pressure piping of sensor using three-way connection.
Pressure measurement pipeline described in the present embodiment, the general plastic flexible pipe using internal diameter 0.8mm~1.0mm, due to pipeline
Relatively thin, the pressure tap that the pressure change of model surface is transferred to pressure scanning valve has certain transmission delay (Δ t), in order to protect
The synchronism of the signals such as total static pressure signal, Flow Field in Wind Tunnel fluctuation, the model surface pressure of scanning valve measurement is held, identical length can be used
Degree and the flexible pipe of internal diameter specification connection scanning valve model pressure tap and total static pressure transducer.If pipeline specification used is different,
Need to choose suitable length or internal diameter by way of experiment test or theoretical analysis and calculation.
S202. wind tunnel control system gathers the measured value P0 and Pct of total static pressure transducer according to controlling cycle in real time, and calculates
Mach number Ma, according to test requirements document constantly regulate flow field, makes Ma stable within the specific limits, while the Controlling model angle of attack reaches pre-
If position.
The angle of attack predeterminated position, such as sequence of typically one angle of attack angle, " -2,0,2,4,6 ", wind-tunnel control
System first spends model sport to -2, then gathered data, then move to 0 degree, then gathered data, the like, wait model
Data acquisition at 6 degree is finished, and experiment just finishes.
S203. after angle of attack reaches predeterminated position, wind tunnel control system persistently controls flow field and keeps model static
Wait for a period of time wt.
The stand-by period wt is a fixed value of setting before experiment, transmission delay Δ t of its value more than pressure measurement pipeline.
S204. after delay is waited, in order to ensure flow field still conforms to require, wind tunnel control system needs to calculate this again
When Mach number Ma, continue to adjust flow field if undesirable until meet the requirements.
S205. control system sends acquisition instructions to scanning valve pressure measuring system.Instruction can be the character string that content is fixed,
Can also include current test status information, and the character string of dynamic generation, scanning valve pressure measuring system can be somebody's turn to do by parsing
Character string obtains corresponding information.
S206. scanning valve pressure measuring system is received after acquisition instructions, gathers stagnation pressure P0s, the static pressure Pcts of access and owns
Model measuring point pressure Psi (i=1~n, n count for model surface pressure measurement), calculates Mach number Mas, and this group of data are saved in
Buffering area.
The buffer area, refers to a memory space, and its size is equal to threshold value T described in S209 and is multiplied by every group of scan data
Required memory space, for temporarily storing in all data groups of current location repeated acquisition.
S207. scanning valve pressure measuring system judges whether Mach number Mas meets the requirements.Meet the requirements, illustrate to have got
Satisfactory pressure data, goes to step S208；It is undesirable, go to step S209 and further judge.
S208. scanning valve pressure measuring system using this group of data of collection as pressure measuring model current location final data simultaneously
Preserve, then go to step S211.
S209. whether scanning valve pressure measuring system judges the number of times in "current" model preset position repeated acquisition beyond threshold
Value T, if going to step S210 if, continues to gather and judgement if going to step S206 without departing from if.
The threshold value T, is to scan a preset integer value of valve pressure measuring system, the numerical value is limited meets in each model
Under Angle Position, repeated attempt gathers the maximum times of pressure data.When flow field is highly unstable, it is possible to scan valve pressure measurement system
The Mas that statistics is calculated does not reach requirement always, causes the feedback of the wind tunnel control system valve pressure measuring system to be scanned such as a long time, makes
Into energy waste, such case can be avoided by threshold value T.
S210. this step represent model had attempted at current preset position collection number of times beyond threshold value T not yet
The satisfactory data of Mas are got, in order to save the energy, it is optimal that scanning valve pressure measuring system now selects Mas from buffering area
Pressure measurements and preservation of one group of data as "current" model preset position, then turn S211.
Pressure measurements Mas it is possible to further the record "current" model preset position in experiment daily record is below standard
Warning message, be easy to investigation problem.
S211. the feedback information for scanning valve pressure measuring system emptying buffer and finishing collection is sent to control system.
The feedback information can be the character string that content is fixed or raw comprising collection result information, and dynamically
Into character string, control system can obtain corresponding information by parsing the character string.
Further, the data of buffering area can also be saved in file by scanning valve pressure measuring system before emptying buffer,
For analyzing process of the test.
S212. control system is received after feedback information, if there is other model predeterminated positions, goes to S202 weights
Multiple processing, otherwise, this off-test.
Mach number Ma and Mas described in the step S202 and step S206 are by total static pressure data and formula (1) calculating
Obtain.
It should be noted that " sensor ", " pressure tap " in description and claims of this specification and accompanying drawing,
" pressure measurement pipeline " or " pressure scanning valve ", its quantity can be single or multiple.Control system is sent to scanning valve pressure measuring system
The complete instruction of collection of acquisition instructions and scanning valve pressure measuring system feedback, can be fixed character string or comprising ought
Preceding trystate information, the character string of dynamic generation, recipient can obtain corresponding information by parsing the character string.This
Outside, term " comprising " and " having " and its any deformation, it is intended that covering is non-exclusive to be included, for example, containing one and being
The process of row step, it is not necessary to be confined to those steps clearly listed, but can include not listing clearly for
These steps other intrinsic steps, the preservation step of such as data no doubt includes the opening and closing step of file.
The measuring method for the raising wind tunnel pressure measuring test pressure scan data precision that the specific embodiment of the invention is provided, leads to
The scanning valve measurement pipeline of increase wind-tunnel stagnation pressure, static pressure signal is crossed, and Mach number judgement is carried out according to scanning valve system, is significantly carried
The high quality of data of wind tunnel pressure measuring experiment, solves and model surface pressure in larger wind-tunnel is fluctuated in flow field is difficult to height
The problem of precision measure.
The invention is not limited in foregoing embodiment.The present invention, which is expanded to, any in this manual to be disclosed
New feature or any new combination, and disclose any new method or process the step of or any new combination.
Claims (4)
1. a kind of measuring method for improving wind tunnel pressure measuring test pressure scan data precision, it is characterised in that comprise the following steps：
Step one：A vent line is drawn respectively from wind-tunnel stagnation pressure and static pressure transducer, and accesses scanning valve pressure measuring system, pipe
Road internal diameter and length are consistent with model pressure measurement pipeline, make it have the delay of identical pressure transmission；
Step 2：Stagnation pressure P0 and static pressure Pct that wind tunnel control system collection pressure sensor is measured, are adjusted in real time according to Mach number Ma
Throttling field is until meet the requirements, while the Controlling model angle of attack reaches predeterminated position；
Step 3：Wind tunnel control system persistently controls flow field and keeps the static wt that waits for a period of time of model；
Step 4：Wind tunnel control system calculates Mach number Ma now, continues to adjust flow field if undesirable until symbol
Close and require；
Step 5：Control system sends acquisition instructions to scanning valve pressure measuring system；
Step 6：Stagnation pressure P0s, the static pressure Pcts and all model measuring point pressure Psi of valve pressure measuring system collection access are scanned, its
In：I=1~n, n counts for model surface pressure measurement, calculates Mach number Mas, and this group of data are saved in into buffering area；
Step 7：Scanning valve pressure measuring system judges that Mach number Mas meets the requirements, then goes to step 8；
If scanning valve pressure measuring system judges that Mach number Mas is undesirable, scanning valve pressure measuring system is judged in current location weight
Whether second mining collection and the number of times judged exceed threshold value T；
If beyond threshold value T, scanning valve pressure measuring system select Mach number Mas optimal from the data of buffering area one group is used as survey
Pressing mold type records the below standard letters of the pressure measurements Mas of "current" model preset position in the final data of current location
Breath；Then step 9 is performed；
If without departing from threshold value T, system returns to step 6 and continued executing with；
Step 8：Scan valve pressure measuring system using this group of data of collection as pressure measuring model current location final data, and
Preserve；
Step 9：Scan valve pressure measuring system emptying buffer and send collection and finish information to control system；
Step 10：Control system is received after feedback information, this off-test.
2. a kind of measuring method for improving wind tunnel pressure measuring test pressure scan data precision according to claim 1, it is special
Levy and be in step 6, the buffer area is a memory space, the size of the memory space is multiplied by equal to the threshold value T
Memory space needed for every group of scan data, for temporarily storing in all data groups of "current" model position repeated acquisition.
3. a kind of measuring method for improving wind tunnel pressure measuring test pressure scan data precision according to claim 1, it is special
Levy and be acquisition instructions described in the step 5, can be content fix character string or comprising current test shape
State information, and the character string of dynamic generation, scanning valve pressure measuring system can obtain corresponding information by parsing the character string.
4. a kind of measuring method for improving wind tunnel pressure measuring test pressure scan data precision according to claim 1, it is special
Levy and be feedback information described in the step 9, can be character string or believe comprising collection result that content is fixed
Breath, and the character string of dynamic generation, control system can obtain corresponding information by parsing the character string.
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| CN109540454A (en) * | 2018-12-14 | 2019-03-29 | 华南理工大学 | A kind of experimental rig and its method for simulating skyscraper stack effect |
| CN110044570A (en) * | 2019-04-16 | 2019-07-23 | 沈阳航空航天大学 | A kind of body of revolution fuselage surveys compacting and tests the error correcting method that pneumatically trembles |
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| CN111238759A (en) * | 2020-03-31 | 2020-06-05 | 中国空气动力研究与发展中心低速空气动力研究所 | Icing wind tunnel pressure measurement test method |
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| CN112461489A (en) * | 2020-11-25 | 2021-03-09 | 中国空气动力研究与发展中心高速空气动力研究所 | Electronic scanning valve reference pressure control system for low-pressure measurement and application method |
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| CN108020396A (en) * | 2017-12-29 | 2018-05-11 | 北京航天测控技术有限公司 | A kind of intelligent monitoring device and system suitable for wind-tunnel measurements system |
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| CN116007890A (en) * | 2023-03-23 | 2023-04-25 | 中国空气动力研究与发展中心超高速空气动力研究所 | Device for measuring micro pressure on surface of inner model of wind tunnel height Wen Liuchang |
| CN116213364A (en) * | 2023-05-11 | 2023-06-06 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Automatic wet gas cleaning method and system for large low-temperature wind tunnel |
| CN116213364B (en) * | 2023-05-11 | 2023-07-21 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Automatic wet gas cleaning method and system for large low-temperature wind tunnel |
| CN116380396A (en) * | 2023-05-30 | 2023-07-04 | 中国航空工业集团公司沈阳空气动力研究所 | Continuous wind tunnel aircraft atmospheric data system identification test system and method |
| CN116380396B (en) * | 2023-05-30 | 2023-08-15 | 中国航空工业集团公司沈阳空气动力研究所 | Continuous wind tunnel aircraft atmospheric data system identification test system and method |
| 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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