CN209166785U - Pilot system is continuously measured based on pressure scanning valve model surface pressure - Google Patents
Pilot system is continuously measured based on pressure scanning valve model surface pressure Download PDFInfo
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- CN209166785U CN209166785U CN201821835209.XU CN201821835209U CN209166785U CN 209166785 U CN209166785 U CN 209166785U CN 201821835209 U CN201821835209 U CN 201821835209U CN 209166785 U CN209166785 U CN 209166785U
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Abstract
The utility model provides one kind and continuously measures pilot system based on pressure scanning valve model surface pressure, including main controller, multiple pressure scanning valves, system processor, optical fiber interface unit, scanning valve digital interface unit, scanning valve interface unit and more set pressure calibration units, system processor is connect with optical fiber interface unit, more set pressure calibration unit electric signals respectively, optical fiber interface unit and scanning valve digital interface unit optical-fibre communications, scanning valve digital interface unit are connect by scanning valve interface unit with multiple pressure scanning valves.The utility model can be realized the continuous acquisition that model sport process completes pressure data, so that primary experiment can obtain a series of pressure data under mechanism angle changes；During model attitude angle at the uniform velocity changes, aerodynamic characteristic data intensive enough can be collected, wind tunnel pressure measuring test efficiency is greatly improved, provided more complete aerodynamic data abundant, improve test efficiency, and reduce experimentation cost.
Description
Technical field
The utility model belongs to aviation aerodynamic force wind-tunnel technique field, and in particular to one kind is based on pressure scanning valve mould
Type surface pressing continuously measures pilot system.
Background technique
With development in science and technology, the method that wind tunnel technique is widely used as aerodynamic studies is Aeronautics and Astronautics
The development in equal fields provides necessary guarantee.Wind-tunnel routine manometric test is to propose the test angle of demand in advance by client unit
Sequence is measured according to these angles one by one in test.In test each angle will Holding Model in place, stablize after, then adopt
Collect the test data of this position, each demand angle will carry out the step until train number terminates.This method is adopted in data
Collect very good in stability, the state of current angular drag can be truly reflected.But this method is lacked there is also certain
It falls into, such as test data amount is less, the aerodynamic characteristic information of aircraft is not congruent.
Utility model content
Based on the above shortcomings, the utility model is provided one kind and is continuously measured based on pressure scanning valve model surface pressure
Pilot system overcomes the conventional stepping attitude angle static test low efficiency carried out in low-speed wind tunnel in the past, test result information
Measure few disadvantage.
The technical scheme adopted by the utility model is a kind of continuously measure examination based on pressure scanning valve model surface pressure
Check system, including main controller, and further include system processor, optical fiber interface unit, scanning valve digital interface unit, scanning
Valve interface unit, more set pressure calibration units and multiple pressure scanning valves, main controller and system processor pass through ethernet communication,
System processor is connect with optical fiber interface unit, more set pressure calibration unit electric signals respectively, optical fiber interface unit and scanning valve
Digital interface unit optical-fibre communications, scanning valve digital interface unit pass through scanning valve interface unit and multiple pressure scanning valves
Connection.
The advantages of the utility model and the utility model has the advantages that can be realized model sport process complete pressure data continuously adopting
Collection, so that primary experiment can obtain a series of pressure data under mechanism angle changes；At the uniform velocity change in model attitude angle
In the process, aerodynamic characteristic data intensive enough can be collected, wind tunnel pressure measuring test efficiency is greatly improved, provides and more add
Whole aerodynamic data abundant reduces blow-time, improves test efficiency, and reduce experimentation cost, is more advantageous to completely, accurately
Grasp the aerodynamic characteristic of aircraft.
Detailed description of the invention
Fig. 1 is the structure principle chart of the utility model.
Fig. 2 is the flow chart of data processing figure of the utility model.
Specific embodiment
The utility model is described further below in conjunction with attached drawing citing.
Embodiment 1
As shown in Figure 1, a kind of continuously measure pilot system, including main controller based on pressure scanning valve model surface pressure
1, two sets of pressure scanning valves 6, system processor 2, optical fiber interface unit 3, scanning valve digital interface unit 4, scanning valve interface
Unit 5 and three sets of pressure calibration units 7, main controller 1 and system processor 2 by ethernet communication, system processor 2 respectively with
3, three sets of 7 electric signal of the pressure calibration unit connections of optical fiber interface unit, optical fiber interface unit 3 and scanning valve digital interface unit
4 optical-fibre communications, scanning valve digital interface unit 4 are connect by scanning valve interface unit 5 with two sets of pressure scanning valves 6.
Embodiment 2
For testing 0 ° -20 ° of angle, after the test wind is stablized, angle changing mechanism is traveled at the uniform speed since 0 ° to 20 °,
The measuring point frequency of pressure scanning valve is 20Hz, when the value of angular channel signal enters test angle respective value, records corresponding angles
The time that this moment distance starts sampling instant is spent, system acquisition test angle corresponds to the pressure measuring value at moment and analyzes aobvious
Show, store, recycles the data acquisition until completing all test angles, that is, complete train number test.This system can be primary
From start angle continuous acquisition to angle at the end in test, a large amount of test data is measured.
Claims (1)
1. one kind continuously measures pilot system, including main controller based on pressure scanning valve model surface pressure, it is characterised in that: also
Including system processor, optical fiber interface unit, scanning valve digital interface unit, scanning valve interface unit, cover pressure calibration more
Unit and multiple pressure scanning valves, main controller and system processor are connect with optical fiber respectively by ethernet communication, system processor
Mouthful unit, more set pressure calibration unit electric signal connections, optical fiber interface unit and scanning valve digital interface unit optical-fibre communications,
Scanning valve digital interface unit is connect by scanning valve interface unit with multiple pressure scanning valves.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821835209.XU CN209166785U (en) | 2018-11-08 | 2018-11-08 | Pilot system is continuously measured based on pressure scanning valve model surface pressure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821835209.XU CN209166785U (en) | 2018-11-08 | 2018-11-08 | Pilot system is continuously measured based on pressure scanning valve model surface pressure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209166785U true CN209166785U (en) | 2019-07-26 |
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| CN201821835209.XU Active CN209166785U (en) | 2018-11-08 | 2018-11-08 | Pilot system is continuously measured based on pressure scanning valve model surface pressure |
Country Status (1)
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109297674A (en) * | 2018-11-08 | 2019-02-01 | 中国航空工业集团公司哈尔滨空气动力研究所 | Pilot system is continuously measured based on pressure scanning valve model surface pressure |
| 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 |
| CN112113740A (en) * | 2020-11-18 | 2020-12-22 | 中国空气动力研究与发展中心低速空气动力研究所 | Pressure measuring device, pressure measuring method and wind tunnel local airflow deflection angle measuring method |
-
2018
- 2018-11-08 CN CN201821835209.XU patent/CN209166785U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109297674A (en) * | 2018-11-08 | 2019-02-01 | 中国航空工业集团公司哈尔滨空气动力研究所 | Pilot system is continuously measured based on pressure scanning valve model surface pressure |
| 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 |
| CN111238759B (en) * | 2020-03-31 | 2021-07-13 | 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 |
| CN112113740A (en) * | 2020-11-18 | 2020-12-22 | 中国空气动力研究与发展中心低速空气动力研究所 | Pressure measuring device, pressure measuring method and wind tunnel local airflow deflection angle measuring method |
| CN112113740B (en) * | 2020-11-18 | 2021-02-09 | 中国空气动力研究与发展中心低速空气动力研究所 | Pressure measuring device, pressure measuring method and wind tunnel local airflow deflection angle measuring method |
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