CN111380665B - Method for reducing scouring damage of hypersonic wind tunnel tail gas to test model sensor - Google Patents
Method for reducing scouring damage of hypersonic wind tunnel tail gas to test model sensor Download PDFInfo
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- CN111380665B CN111380665B CN202010370809.9A CN202010370809A CN111380665B CN 111380665 B CN111380665 B CN 111380665B CN 202010370809 A CN202010370809 A CN 202010370809A CN 111380665 B CN111380665 B CN 111380665B
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- 238000000034 method Methods 0.000 title claims abstract description 25
- 238000009991 scouring Methods 0.000 title claims abstract description 21
- 239000007921 spray Substances 0.000 claims abstract description 17
- 230000035939 shock Effects 0.000 claims abstract description 8
- 239000012535 impurity Substances 0.000 claims description 10
- 230000000694 effects Effects 0.000 abstract description 2
- 230000003628 erosive effect Effects 0.000 description 2
- 239000005304 optical glass Substances 0.000 description 2
- 230000002035 prolonged effect Effects 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
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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
- G01M9/02—Wind tunnels
- G01M9/04—Details
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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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- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention discloses a method for reducing the scouring damage of hypersonic wind tunnel tail gas to a test model sensor. The device used by the method comprises a rapid feeding mechanism arranged between a spray pipe of the hypersonic wind tunnel and a test model and positioned below an outlet of the spray pipe, and a wedge-shaped stop block positioned at the top end of the rapid feeding mechanism. The method comprises the following steps: a. filling required driving gas and test gas into the shock tube according to the requirement of a hypersonic wind tunnel test; b. starting a hypersonic wind tunnel test, after the test effective time passes, quickly feeding a wedge-shaped stop block into a working position from a hidden position by a quick feeding mechanism, and preventing tail gas of the hypersonic wind tunnel from scouring a sensor arranged on a test model by the wedge-shaped stop block; c. after the hypersonic wind tunnel test is finished, the wedge-shaped stop block is retracted to the hidden position by the rapid feeding mechanism to prepare for the next test. The device used by the method has simple structure, can be repeatedly used and has low use cost; the method is convenient to operate and good in protection effect.
Description
Technical Field
The invention belongs to the technical field of wind tunnel tests, and particularly relates to a method for reducing scouring damage of hypersonic wind tunnel tail gas to a test model sensor.
Background
In the hypersonic wind tunnel test, the hypersonic wind tunnel tail gas after the test effective time is high-pressure tail gas, the high-pressure tail gas can scour a sensor on a model, the hypersonic wind tunnel test effective time is millisecond magnitude, the scouring time of the high-pressure tail gas to the sensor is hundreds of milliseconds to several seconds, namely the sensor is exposed in the high-pressure tail gas most of the time, most of damage is caused by the high-pressure tail gas, and the high-pressure tail gas can greatly accelerate the damage of the sensor. Meanwhile, as the sensor used in the hypersonic wind tunnel is expensive, the installation space of the key sensor of the test model is mostly narrow and difficult to operate, and the high-pressure tail gas is very necessary to be prevented from scouring the sensor.
At present, a few foreign wind tunnels adopt a central body technology to block high-pressure driving gas impurities, but the central body technology is complex, a certain interference is caused to a flow field, and test tail gas needs to be discharged from a shock tube through a vent valve, so that the overall test time is prolonged.
At present, a method for reducing the scouring damage of the tail gas of the hypersonic wind tunnel to the test model sensor needs to be developed urgently.
Disclosure of Invention
The invention aims to solve the technical problem of providing a method for reducing the scouring damage of the tail gas of a hypersonic wind tunnel to a test model sensor.
The invention discloses a method for reducing the scouring damage of tail gas of a hypersonic wind tunnel to a test model sensor, which is characterized in that a device used in the method comprises a rapid feeding mechanism arranged between a spray pipe of the hypersonic wind tunnel and a test model, positioned below the outlet of the spray pipe and a wedge-shaped stop block positioned at the top end of the rapid feeding mechanism;
the quick feeding mechanism is driven by hydraulic pressure to push the wedge-shaped stop block from a hidden position below the outlet of the spray pipe to a working position on the central axis of the spray pipe and in front of the test model;
the wedge-shaped baffle block comprises 2 wedge-shaped reflecting baffle plates which are symmetrical up and down and face the hypersonic wind tunnel airflow, and a baffle mounting seat which is positioned behind the wedge-shaped reflecting baffle plates and is used for fixedly mounting the wedge-shaped reflecting baffle plates; the included angle between the wedge-shaped reflecting baffle and the hypersonic wind tunnel airflow ranges from 120 degrees to 150 degrees, the reflecting surface of the wedge-shaped reflecting baffle is a plane, and impurities in the hypersonic wind tunnel tail gas are ejected onto the upper wall plate and the lower wall plate of the test section by the reflecting surface;
the method comprises the following steps:
a. filling required driving gas and test gas into the shock tube according to the requirement of a hypersonic wind tunnel test;
b. starting a hypersonic wind tunnel test, after the test effective time passes, quickly feeding a wedge-shaped stop block into a working position from a hidden position by a quick feeding mechanism, and preventing tail gas of the hypersonic wind tunnel from scouring a sensor arranged on a test model by the wedge-shaped stop block;
c. after the hypersonic wind tunnel test is finished, the wedge-shaped stop block is retracted to the hidden position by the rapid feeding mechanism to prepare for the next test.
The hydraulic drive of the rapid feeding mechanism can be replaced by gas drive or electromagnetic drive.
The 2 wedge-shaped reflecting baffles which are symmetrical up and down can be replaced by reflecting baffles with a plurality of reflecting planes, and each reflecting plane can eject impurities in the tail gas of the hypersonic wind tunnel to the corresponding position of the preset inner wall of the test section.
The wedge-shaped stop block in the method for reducing the erosion damage of the hypersonic wind tunnel tail gas to the test model sensor can eject impurities in the high-pressure tail gas to the upper wall plate and the lower wall plate of the test section, so that the impurities in the high-pressure tail gas are prevented from hitting optical glass observation windows on two sides of the test section, the impurities in the high-pressure tail gas can also be prevented from hitting other important parts of the test section through further design, and the ejection damage of the optical glass observation windows and the important parts of the test section is reduced.
The method for reducing the scouring damage of the tail gas of the hypersonic wind tunnel to the test model sensor has the following advantages:
1. the scouring of the sensor is reduced, and the service life of the sensor is prolonged;
2. the replacement times of the sensors are reduced, the test cost is saved, and the test efficiency is improved;
3. can be repeatedly used, and has low use cost.
In conclusion, the device used in the method for reducing the scouring damage of the hypersonic wind tunnel tail gas to the test model sensor has the advantages of simple structure, repeated use and low use cost; the method is convenient to operate and good in protection effect.
Drawings
FIG. 1 is a working schematic diagram of the method for reducing the erosion damage of the hypersonic wind tunnel tail gas to the test model sensor according to the invention.
In the figure, 1, a shock tube 2, a spray tube 3, a test model 4, an attack angle mechanism 5, a test section 6, a rapid feeding mechanism 7 and a wedge-shaped stop block are arranged.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings and examples.
The following examples are intended to illustrate the invention but are not intended to limit the scope of the invention.
Example 1
As shown in fig. 1, the hypersonic wind tunnel sequentially comprises a shock tube 1, a spray pipe 2 and a test section 5 from front to back along the airflow direction of the hypersonic wind tunnel, a test model 3 is installed on an attack angle mechanism 4 in the test section 5, and a sensor is installed on the test model 3. The device used in the method for reducing the scouring damage of the tail gas of the hypersonic wind tunnel to the test model sensor comprises a rapid feeding mechanism 6 arranged between a spray pipe 2 and a test model 3 of the hypersonic wind tunnel and positioned below an outlet of the spray pipe 2 and a wedge-shaped stop block 7 positioned at the top end of the rapid feeding mechanism 6;
the rapid feeding mechanism 6 is driven by hydraulic pressure to push the wedge-shaped stop block 7 from a hidden position below the outlet of the spray pipe 2 to a working position on the central axis of the spray pipe 2 and in front of the test model 3;
the wedge-shaped baffle 7 comprises 2 wedge-shaped reflecting baffles which are symmetrical up and down and face the hypersonic wind tunnel airflow, and a baffle mounting seat which is positioned behind the wedge-shaped reflecting baffles and is used for fixedly mounting the wedge-shaped reflecting baffles; the included angle between the wedge-shaped reflecting baffle and the hypersonic wind tunnel airflow ranges from 120 degrees to 150 degrees, the reflecting surface of the wedge-shaped reflecting baffle is a plane, and impurities in the hypersonic wind tunnel tail gas are ejected onto the upper wall plate and the lower wall plate of the test section 5 by the reflecting surface;
the method for reducing the scouring damage of the tail gas of the hypersonic wind tunnel to the test model sensor comprises the following steps:
a. filling required driving gas and test gas into the shock tube 1 according to the requirement of a hypersonic wind tunnel test;
b. starting a hypersonic wind tunnel test, after the test effective time passes, quickly feeding the wedge-shaped stop block 7 into a working position from a hidden position by the quick feeding mechanism 6, and preventing tail gas of the hypersonic wind tunnel from scouring a sensor arranged on the test model 3 by the wedge-shaped stop block 7;
c. after the hypersonic wind tunnel test is finished, the rapid feeding mechanism 6 retracts the wedge-shaped stop block 7 to a hidden position to prepare for the next test.
The hydraulic drive of the rapid-feed mechanism 6 in this embodiment is replaced with a gas drive or an electromagnetic drive.
In the embodiment, the 2 wedge-shaped reflecting baffles which are symmetrical up and down are replaced by the reflecting baffles with a plurality of reflecting planes, and each reflecting plane ejects impurities in the tail gas of the hypersonic wind tunnel to a corresponding position of the inner wall of the preset test section 5.
The above is only a preferred embodiment of the present invention, and it should be noted that: it will be apparent to those skilled in the art that various modifications and adaptations can be made without departing from the principles of the invention and these are intended to be within the scope of the invention.
Claims (3)
1. The method for reducing the scouring damage of the tail gas of the hypersonic wind tunnel to the test model sensor is characterized in that the hypersonic wind tunnel sequentially comprises a shock tube (1), a spray tube (2) and a test section (5) from front to back along the airflow direction of the hypersonic wind tunnel, a test model (3) is installed on an attack angle mechanism (4) in the test section (5), and the test model (3) is provided with the sensor; the device used by the method comprises a rapid feeding mechanism (6) arranged between a spray pipe (2) and a test model (3) of the hypersonic wind tunnel and positioned below an outlet of the spray pipe (2), and a wedge-shaped stop block (7) positioned at the top end of the rapid feeding mechanism (6);
the rapid feeding mechanism (6) is driven by hydraulic pressure to push the wedge-shaped stop block (7) to a working position on the central axis of the spray pipe (2) and in front of the test model (3) from a hidden position below the outlet of the spray pipe (2);
the wedge-shaped stop block (7) comprises 2 wedge-shaped reflecting baffle plates which are symmetrical up and down and face the hypersonic wind tunnel airflow, and a baffle plate mounting seat which is positioned behind the wedge-shaped reflecting baffle plates and is used for fixedly mounting the wedge-shaped reflecting baffle plates; the included angle between the wedge-shaped reflecting baffle and the hypersonic wind tunnel airflow ranges from 120 degrees to 150 degrees, the reflecting surface of the wedge-shaped reflecting baffle is a plane, and impurities in the hypersonic wind tunnel tail gas are ejected onto the upper wall plate and the lower wall plate of the test section (5) by the reflecting surface;
the method comprises the following steps:
a. filling required driving gas and test gas into the shock tube (1) according to the test requirement of the hypersonic wind tunnel;
b. starting a hypersonic wind tunnel test, after the test effective time passes, quickly feeding a wedge-shaped stop block (7) into a working position from a hidden position by a quick feeding mechanism (6), and preventing tail gas of the hypersonic wind tunnel from scouring a sensor arranged on a test model (3) by the wedge-shaped stop block (7);
c. after the hypersonic wind tunnel test is finished, the wedge-shaped stop block (7) is retracted to a hidden position by the rapid feeding mechanism (6) to prepare for the next test.
2. The method for reducing the scouring damage of the hypersonic wind tunnel tail gas to the test model sensor according to claim 1, characterized in that the hydraulic drive of the rapid feeding mechanism (6) is replaced by a gas drive or an electromagnetic drive.
3. The method for reducing the scouring damage of the hypersonic wind tunnel tail gas to the test model sensor according to claim 1, wherein the 2 wedge-shaped reflecting baffles which are symmetrical up and down are replaced by reflecting baffles with a plurality of reflecting planes, and each reflecting plane ejects impurities in the hypersonic wind tunnel tail gas to a corresponding position of the inner wall of a preset test section (5).
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010370809.9A CN111380665B (en) | 2020-05-06 | 2020-05-06 | Method for reducing scouring damage of hypersonic wind tunnel tail gas to test model sensor |
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| CN202010370809.9A CN111380665B (en) | 2020-05-06 | 2020-05-06 | Method for reducing scouring damage of hypersonic wind tunnel tail gas to test model sensor |
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| Publication Number | Publication Date |
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| CN111380665A CN111380665A (en) | 2020-07-07 |
| CN111380665B true CN111380665B (en) | 2021-09-03 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112629806B (en) * | 2021-01-11 | 2022-05-13 | 中国空气动力研究与发展中心超高速空气动力研究所 | Device and method for stopping shock tunnel non-effective test airflow |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103091066A (en) * | 2013-01-17 | 2013-05-08 | 中国科学院力学研究所 | Protection device of hypersonic flowing pitot pressure sensor |
| CN205228773U (en) * | 2015-12-09 | 2016-05-11 | 中国航天空气动力技术研究院 | Device for balance impact load is experimental with wind -tunnel tail gas |
| CN106768805A (en) * | 2016-12-23 | 2017-05-31 | 中国航天空气动力技术研究院 | A kind of impulse wind tunnel flat plate model sliding support |
| CN207095818U (en) * | 2017-08-25 | 2018-03-13 | 同度能源科技（江苏）股份有限公司 | A kind of conventional hypersonic wind tunnel device |
| CN108362468A (en) * | 2018-05-25 | 2018-08-03 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of model vibration-repressing device that wind-tunnel supersonic speed starts and cut-offs |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2012078260A (en) * | 2010-10-04 | 2012-04-19 | Mitsubishi Heavy Ind Ltd | Wind tunnel test model and method for wind tunnel test |
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- 2020-05-06 CN CN202010370809.9A patent/CN111380665B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103091066A (en) * | 2013-01-17 | 2013-05-08 | 中国科学院力学研究所 | Protection device of hypersonic flowing pitot pressure sensor |
| CN205228773U (en) * | 2015-12-09 | 2016-05-11 | 中国航天空气动力技术研究院 | Device for balance impact load is experimental with wind -tunnel tail gas |
| CN106768805A (en) * | 2016-12-23 | 2017-05-31 | 中国航天空气动力技术研究院 | A kind of impulse wind tunnel flat plate model sliding support |
| CN207095818U (en) * | 2017-08-25 | 2018-03-13 | 同度能源科技（江苏）股份有限公司 | A kind of conventional hypersonic wind tunnel device |
| CN108362468A (en) * | 2018-05-25 | 2018-08-03 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of model vibration-repressing device that wind-tunnel supersonic speed starts and cut-offs |
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