CN210426948U - Hypersonic wind tunnel model bottom pressure measuring device - Google Patents
Hypersonic wind tunnel model bottom pressure measuring device Download PDFInfo
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- CN210426948U CN210426948U CN201921604992.3U CN201921604992U CN210426948U CN 210426948 U CN210426948 U CN 210426948U CN 201921604992 U CN201921604992 U CN 201921604992U CN 210426948 U CN210426948 U CN 210426948U
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Abstract
The utility model discloses a hypersonic wind tunnel model bottom pressure measuring device, which comprises a box body, a water cooling pipeline and a heat preservation cotton layer, wherein the box body is composed of a stainless steel shell, a water cooling pipeline and a heat preservation cotton layer; the water cooling pipelines are arranged at the top and the side wall of the box body; the heat insulation cotton layer is positioned between the gap of the water cooling pipeline and the double-layer stainless steel shell interlayer; the overpressure protection device consists of a micro vacuum pump, a three-way electromagnetic valve and a protection gas circuit; the three-way electromagnetic valve is respectively connected with an absolute pressure sensor, a micro vacuum pump and a measuring gas circuit; the three-way electromagnetic valve is communicated with the micro vacuum pump through the protection gas circuit; the absolute pressure sensor is arranged at the bottom of the box body; a thermal resistor for monitoring the temperature of the inner cavity of the box body is arranged near the absolute pressure sensor; the electric control system consists of an electric interface, a power supply cable and a signal cable; the aviation plug leads the power cable and the signal cable out of the box body; the device has the advantages of high bottom pressure measurement precision, short pressure stabilization time, low failure rate, low test cost and high test efficiency.
Description
Technical Field
The utility model belongs to the technical field of aerospace aerodynamic wind tunnel test, more specifically says, the utility model relates to a hypersonic wind tunnel model bottom pressure measuring device.
Background
The measurement of the pressure at the bottom of the model is used as an important component in a dynamic test of the wind tunnel, and the measurement of the aerodynamic characteristics of the model, particularly the measurement of the axial force, is directly influenced by the accuracy of the measurement. According to the different shapes of the test models, the model bottom resistance generally accounts for about 5% -20% of the total resistance of the model, so if the bottom pressure cannot be accurately measured, great uncertain factors can be brought to the prediction of the aircraft range and the flight control performance, and the high-precision requirement of the wind tunnel test cannot be met. Particularly under the condition of a hypersonic flow field, the pressure value at the bottom of the model is very low and is close to vacuum, and a small-range high-precision absolute pressure sensor is selected for improving the pressure measurement precision. However, in an atmospheric environment, the small-range high-precision absolute pressure sensor has serious overpressure after being electrified, and meanwhile, in order to guarantee the measurement precision of the sensor, the sensor needs to be electrified and preheated in advance, so that the small-range high-precision absolute pressure sensor needs to be subjected to overvoltage protection design. And moreover, the air flow is generally heated when the hypersonic wind tunnel runs, the temperature of the test section is higher, the model bottom pressure measurement system is generally arranged outside the wind tunnel test section, and a differential pressure sensor is adopted for pressure measurement, so that the defects of long air path distance, more switching, low pressure measurement precision, complex operation and the like exist.
In order to solve the problems existing in the measurement of the bottom pressure of the hypersonic wind tunnel model, a hypersonic wind tunnel model bottom pressure measuring device with thermal protection, sensor overvoltage protection, remote automatic control, stability and high pressure measurement accuracy needs to be developed. The overvoltage protection device comprises an absolute pressure sensor, an overvoltage protection device, a box body and an electrical control system.
SUMMERY OF THE UTILITY MODEL
An object of the present invention is to solve at least the above problems and/or disadvantages and to provide at least the advantages which will be described later.
In order to achieve these objects and other advantages in accordance with the purpose of the invention, there is provided a hypersonic wind tunnel model bottom pressure measuring device, comprising:
a box body which is a stainless steel shell;
the bottom of the stainless steel shell adopts a single-layer structure, the side wall and the top of the stainless steel shell adopt a double-layer structure, and the top of the stainless steel shell is provided with an opening door through a hinge;
the water cooling pipelines are arranged at the top and the side wall of the box body and are tightly attached to the outer wall of the stainless steel shell; the heat insulation cotton layer is positioned between the gap of the water cooling pipeline and the double-layer stainless steel shell interlayer;
the water cooling pipeline is provided with a water cooling pipeline interface used for connecting a cooling hose, and the leeward side of the box body is provided with a breathing hole;
three ports of the three-way electromagnetic valve are respectively connected with an absolute pressure sensor, a micro vacuum pump and a measuring gas circuit; the protection gas circuit is used for communicating the three-way electromagnetic valve with the micro vacuum pump; the micro vacuum pump, the three-way electromagnetic valve and the protective gas circuit jointly form an overvoltage protection device;
the absolute pressure sensor is arranged at the bottom of the box body, is respectively connected with the micro vacuum pump and the measuring gas circuit through a three-way electromagnetic valve, and is connected with the red copper pipe outside the box body through a measuring gas circuit switching port; the copper pipe is of a flexible structure and extends into and is fixed at the bottom of the model; a thermal resistor for monitoring the temperature of the inner cavity of the box body is arranged near the absolute pressure sensor;
an electrical interface disposed outside the case; the power supply cable comprises an absolute pressure sensor power supply cable, a micro vacuum pump power supply cable and a three-way electromagnetic valve power supply cable; a signal cable including an absolute pressure sensor signal cable and a micro vacuum pump signal cable; the electric interface, the power cable and the signal cable jointly form an electric control system; and the aviation plug is used for leading the power cable and the signal cable out of the box body.
Preferably, the absolute pressure sensor is a small-range absolute pressure sensor with high reading precision, and the reading precision is better than 0.5%.
Preferably, the micro vacuum pump can be operated continuously for a long time, and has a high odor speed and a low leakage rate.
Preferably, the sealing mode of the measuring air passage adapter and the copper tube is hard sealing.
Preferably, a cooling sleeve is arranged outside the measurement gas path and perpendicular to the measurement gas path.
Preferably, the measurement gas circuit, the protection gas circuit and the water cooling circuit are preferably stainless steel pipes, and the measurement gas circuit, the protection gas circuit and the three-way electromagnetic valve are connected by welding; the connector of the three-way electromagnetic valve and the water cooling pipeline are changed into a double-clamping sleeve joint through a welding mode.
Preferably, the incoming flow side of the upper surface of the box body is provided with a slope for reducing the influence on the incoming flow.
Preferably, the power cable and the signal cable are separately arranged and are led out of the box body by different aviation plugs.
Preferably, the measurement air passage adapter and the water cooling pipeline adapter are located outside the box body.
The utility model discloses at least, include following beneficial effect:
(1) by using the hypersonic wind tunnel model bottom pressure measuring device of the utility model, the overvoltage protection of an absolute pressure sensor and the heat insulation protection of electrical equipment can be effectively realized; the device is suitable for high-temperature environment, the safety of internal electronic components is protected in the high-temperature environment, and the service life of the device is prolonged;
(2) use the utility model discloses a hypersonic wind tunnel model bottom pressure measuring device is applicable to the experiment of mach number between 5 ~ 9, especially the accurate measurement of mach number model bottom pressure between 8 ~ 9 to voltage stabilization time is short in the measurement process, and the device is small, and the mountable is staying indoor portion, be close to model afterbody position at the test section, and has reduced pipeline length in a large number, practices thrift test cost, test efficiency height.
Additional advantages, objects, and features of the invention will be set forth in part in the description which follows and in part will become apparent to those having ordinary skill in the art upon examination of the following or may be learned from practice of the invention.
Description of the drawings:
fig. 1 is a schematic structural diagram of a hypersonic wind tunnel model bottom pressure measuring device provided by the utility model;
FIG. 2 is a rear view of the hypersonic wind tunnel model bottom pressure measuring device provided by the present invention;
FIG. 3 is a top view of the hypersonic wind tunnel model bottom pressure measuring device provided by the present invention;
fig. 4 is the utility model provides a hypersonic wind tunnel model bottom pressure measuring device measures bottom pressure test flow chart.
The specific implementation mode is as follows:
the present invention is further described in detail below with reference to the drawings so that those skilled in the art can implement the invention with reference to the description.
It will be understood that terms such as "having," "including," and "comprising," as used herein, do not preclude the presence or addition of one or more other elements or groups thereof.
As shown in fig. 1-3: the utility model discloses a hypersonic wind tunnel model bottom pressure measuring device, include:
a box body which is a stainless steel shell 9;
the bottom of the stainless steel shell 9 adopts a single-layer structure, the side wall and the top of the stainless steel shell 9 adopt a double-layer structure, and an opening door (not shown) is arranged at the top of the stainless steel shell 9 through a hinge;
the water cooling pipelines 10 are arranged at the top and the side wall of the box body and are tightly attached to the outer wall of the stainless steel shell 9; the heat insulation cotton layer 11 is positioned between the gap of the water cooling pipeline 10 and the inner and outer stainless steel shells 9; the heat insulation cotton layer 11 and the stainless steel shell 9 can insulate and protect various devices in the box body, and the bottom of the box body is fixed in the wind tunnel, so that the influence of external airflow on the bottom of the box body is small, and the bottom of the stainless steel shell 9 is of a single-layer structure; the water cooling pipeline 10 is provided with a water cooling pipeline interface 7 for connecting a cooling hose, and the leeward side of the box body is provided with a breathing hole which can enable the internal pressure of the box body to be rapidly balanced with the environment;
three ports of the three-way electromagnetic valve 3 are respectively connected with an absolute pressure sensor 1, a micro vacuum pump 2 and a measuring gas circuit 4; the specific gas circuit connection mode is as follows: when the three-way electromagnetic valve 3 is not electrified, the absolute pressure sensor 1 is communicated with the micro vacuum pump 2; the absolute pressure sensor 1 is communicated with the measuring gas circuit 4 after the three-way electromagnetic valve 3 is electrified; the protective gas circuit 5 is used for communicating the three-way electromagnetic valve 3 with the micro vacuum pump 2, and the pumping action of the micro vacuum pump 2 enables the absolute pressure sensor 1 to work in an acceptable negative pressure environment, so that the absolute pressure sensor 1 has an overvoltage protection function; the micro vacuum pump 2, the three-way electromagnetic valve 3 and the protective gas circuit 5 jointly form an overvoltage protection device;
the absolute pressure sensor 1 is used for measuring the bottom pressure of the model and is arranged at the bottom of the box body, the absolute pressure sensor 1 is respectively connected with the micro vacuum pump 2 and the measuring gas circuit 4 through the three-way electromagnetic valve 3, and the absolute pressure sensor 1 is connected with the red copper pipe outside the box body through the measuring gas circuit adapter 6; the red copper pipe is of a flexible structure and extends into and is fixed at the bottom of the model; a thermal resistor (not shown) for monitoring the temperature of the inner cavity of the box body is arranged near the absolute pressure sensor 1, so that the situation that the maximum working temperature allowed by components is exceeded is avoided;
an electrical interface disposed outside the case; the power supply cable comprises an absolute pressure sensor power supply cable, a micro vacuum pump power supply cable and a three-way electromagnetic valve power supply cable; a signal cable including an absolute pressure sensor signal cable and a micro vacuum pump signal cable; the electric interface, the power supply cable and the signal cable form an electric control system; and the aviation plug 8 is used for leading the power cable and the signal cable out of the box body.
The working principle is as follows: the experimental control flow is shown in fig. 4: the model bottom pressure measuring device is fixedly arranged in the wind tunnel through a bolt and is close to the tail part of the model, before the test is started, the three-way electromagnetic valve 3 is powered off, the power supply of the micro vacuum pump 2 is switched on, and when the pressure is reduced to the range of the absolute pressure sensor 1, the power supply of the absolute pressure sensor 1 is switched on; in the test process, after the flow field is established and the model is put in, the three-way electromagnetic valve 3 is electrified, the gas path is switched, the absolute pressure sensor 1 is communicated with the measurement gas path 4, gas enters the box body through the measurement gas path 4, the absolute pressure sensor 1 obtains the bottom pressure of the model through measuring the pressure of the gas, and data acquisition is carried out after the pressure stabilization time delay to be measured; after data acquisition of all working conditions is completed, the three-way electromagnetic valve 3 is powered off, the gas circuit is switched, and the absolute pressure sensor 1 is communicated with the micro vacuum pump 2; after the test is finished, the power supply of the absolute pressure sensor is disconnected, and the power supply of the micro vacuum pump is disconnected; compared with the existing wind tunnel model bottom pressure measuring device, the box body of the device is completely arranged in the wind tunnel, the device is small in size and can be arranged in a wind tunnel test section chamber and close to the tail part of the model, so that the air path distance is short, the pipeline switching is less, the pressure measuring precision is high, the operation is simple, and the overpressure protection of the absolute pressure sensor 1 can be effectively realized; the arrangement of the water cooling pipeline 10 and the heat preservation cotton layer 11 protects the safety of electronic components inside the device, prevents the temperature of the electronic components inside from being too high, and effectively prolongs the service life of the device.
In the technical scheme, the absolute pressure sensor 1 is a small-range absolute pressure sensor with high reading precision, the reading precision of the absolute pressure sensor is better than 0.5%, and the precision of the measurement of the bottom pressure of the model is improved.
In the above technical scheme, the micro vacuum pump 2 is a micro vacuum pump which can continuously run for a long time, has a high air exhaust speed and a low leakage rate.
In the above technical scheme, the sealing manner of the measurement gas path adapter 6 and the copper tube is hard sealing.
In the above technical scheme, the outside of the measurement gas circuit 4 is perpendicular to the measurement gas circuit 4 and is provided with the cooling sleeve 12, and after the outside gas enters the box body through the measurement gas circuit 4, the outside gas is cooled by the cooling sleeve 12, so that the measurement precision is prevented from being influenced by the overhigh temperature of the gas in the measurement gas circuit 4.
In the above technical scheme, the measurement gas circuit 4, the protection gas circuit 5 and the water cooling pipeline are preferably stainless steel pipelines, and the connection mode of the measurement gas circuit, the protection gas circuit 5 and the three-way electromagnetic valve 3 is welding; the connector of the three-way electromagnetic valve 3 and the water cooling pipeline 10 are changed into a double-clamping sleeve joint by a welding method, and the arrangement can effectively ensure that the condition of gas and water leakage does not occur in the system.
In the technical scheme, a certain gradient is arranged on the incoming flow side of the upper surface of the box body, so that the influence on the incoming flow in the wind tunnel can be reduced.
In the technical scheme, the power cable and the signal cable are separately arranged and are led out of the box body by different aviation plugs 8.
In the above technical scheme, the measurement gas path adapter port 6 and the water cooling pipeline adapter port 7 are arranged outside the box body.
The number of apparatuses and the scale of the process described here are intended to simplify the description of the present invention. Applications, modifications and variations of the present invention will be apparent to those skilled in the art.
While the embodiments of the invention have been described above, it is not intended to be limited to the details shown, or described, but rather to cover all modifications, which would come within the scope of the appended claims, and all changes which come within the meaning and range of equivalency of the art are therefore intended to be embraced therein.
Claims (9)
1. The utility model provides a hypersonic wind tunnel model bottom pressure measuring device which characterized in that includes:
a box body which is a stainless steel shell;
the bottom of the stainless steel shell adopts a single-layer structure, the side wall and the top of the stainless steel shell adopt a double-layer structure, and the top of the stainless steel shell is provided with an opening door through a hinge;
the water cooling pipelines are arranged at the top and the side wall of the box body and are tightly attached to the outer wall of the stainless steel shell; the heat insulation cotton layer is positioned between the gap of the water cooling pipeline and the double-layer stainless steel shell interlayer;
the water cooling pipeline is provided with a water cooling pipeline interface used for connecting a cooling hose, and the leeward side of the box body is provided with a breathing hole;
three ports of the three-way electromagnetic valve are respectively connected with an absolute pressure sensor, a micro vacuum pump and a measuring gas circuit; the protection gas circuit is used for communicating the three-way electromagnetic valve with the micro vacuum pump; the micro vacuum pump, the three-way electromagnetic valve and the protective gas circuit jointly form an overvoltage protection device;
the absolute pressure sensor is arranged at the bottom of the box body, is respectively connected with the micro vacuum pump and the measuring gas circuit through a three-way electromagnetic valve, and is connected with the red copper pipe outside the box body through a measuring gas circuit switching port; the copper pipe is of a flexible structure and extends into and is fixed at the bottom of the model; a thermal resistor for monitoring the temperature of the inner cavity of the box body is arranged near the absolute pressure sensor;
an electrical interface disposed outside the case; the power supply cable comprises an absolute pressure sensor power supply cable, a micro vacuum pump power supply cable and a three-way electromagnetic valve power supply cable; a signal cable including an absolute pressure sensor signal cable and a micro vacuum pump signal cable; the electric interface, the power cable and the signal cable jointly form an electric control system; and the aviation plug is used for leading the power cable and the signal cable out of the box body.
2. The hypersonic wind tunnel model bottom pressure measuring device of claim 1, characterized in that said absolute pressure sensor is a small-range high-reading precision absolute pressure sensor, and the reading precision is better than 0.5%.
3. The hypersonic wind tunnel model bottom pressure measuring device of claim 1, wherein said micro vacuum pump is a micro vacuum pump capable of continuous long-time operation, fast odor speed and low leakage rate.
4. The hypersonic wind tunnel model bottom pressure measuring device of claim 1, characterized in that the sealing mode of the measuring air passage adapter and the copper tube is hard sealing.
5. The hypersonic wind tunnel model bottom pressure measuring device of claim 1, wherein a cooling sleeve is arranged outside the measuring air passage and perpendicular to the measuring air passage.
6. The hypersonic wind tunnel model bottom pressure measuring device of claim 1, characterized in that the measuring gas path, the protection gas path and the water cooling pipeline are stainless steel pipelines and the connecting mode of the measuring gas path, the protection gas path and the three-way solenoid valve is welding; the connector of the three-way electromagnetic valve and the water cooling pipeline are changed into a double-clamping sleeve joint through a welding mode.
7. The hypersonic wind tunnel model bottom pressure measuring device of claim 1, characterized in that a slope for reducing influence on the incoming flow is arranged on the incoming flow side of the upper surface of the box body.
8. The hypersonic wind tunnel model bottom pressure measuring device of claim 1, wherein the power cable and the signal cable are separately arranged and are led out of the box body by different aviation plugs.
9. The hypersonic wind tunnel model bottom pressure measuring device of claim 1, wherein the measuring air passage adapter and the water cooling pipeline adapter are located outside the box body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921604992.3U CN210426948U (en) | 2019-09-25 | 2019-09-25 | Hypersonic wind tunnel model bottom pressure measuring device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921604992.3U CN210426948U (en) | 2019-09-25 | 2019-09-25 | Hypersonic wind tunnel model bottom pressure measuring device |
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| CN210426948U true CN210426948U (en) | 2020-04-28 |
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| CN201921604992.3U Active CN210426948U (en) | 2019-09-25 | 2019-09-25 | Hypersonic wind tunnel model bottom pressure measuring device |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112556917A (en) * | 2021-02-22 | 2021-03-26 | 中国空气动力研究与发展中心低速空气动力研究所 | Method for measuring pressure by using pressure measuring device |
| CN113029508A (en) * | 2021-03-24 | 2021-06-25 | 中国空气动力研究与发展中心高速空气动力研究所 | Miniature combined pressure sensor for measuring bottom pressure of wind tunnel model |
| CN116358823A (en) * | 2023-05-26 | 2023-06-30 | 中国空气动力研究与发展中心高速空气动力研究所 | High-speed wind tunnel free incoming flow mass flow and total temperature pulsation uncertainty evaluation method |
-
2019
- 2019-09-25 CN CN201921604992.3U patent/CN210426948U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112556917A (en) * | 2021-02-22 | 2021-03-26 | 中国空气动力研究与发展中心低速空气动力研究所 | Method for measuring pressure by using pressure measuring device |
| CN113029508A (en) * | 2021-03-24 | 2021-06-25 | 中国空气动力研究与发展中心高速空气动力研究所 | Miniature combined pressure sensor for measuring bottom pressure of wind tunnel model |
| CN113029508B (en) * | 2021-03-24 | 2023-06-02 | 中国空气动力研究与发展中心高速空气动力研究所 | Miniature combined pressure sensor for measuring pressure at bottom of wind tunnel model |
| CN116358823A (en) * | 2023-05-26 | 2023-06-30 | 中国空气动力研究与发展中心高速空气动力研究所 | High-speed wind tunnel free incoming flow mass flow and total temperature pulsation uncertainty evaluation method |
| CN116358823B (en) * | 2023-05-26 | 2023-08-18 | 中国空气动力研究与发展中心高速空气动力研究所 | High-speed wind tunnel free incoming flow mass flow and total temperature pulsation uncertainty evaluation method |
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