CN106017858B - System is tested in a kind of air duct for ice-removing and ice-preventing liquid air aerodynamic properties - Google Patents
System is tested in a kind of air duct for ice-removing and ice-preventing liquid air aerodynamic properties Download PDFInfo
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- CN106017858B CN106017858B CN201610533974.5A CN201610533974A CN106017858B CN 106017858 B CN106017858 B CN 106017858B CN 201610533974 A CN201610533974 A CN 201610533974A CN 106017858 B CN106017858 B CN 106017858B
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- air duct
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- air channel
- section air
- pressure sensor
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- 239000007788 liquid Substances 0.000 title claims abstract description 26
- 238000012360 testing method Methods 0.000 claims abstract description 61
- 230000008602 contraction Effects 0.000 claims abstract description 23
- 238000002474 experimental method Methods 0.000 claims description 12
- 238000009792 diffusion process Methods 0.000 claims description 6
- 230000000087 stabilizing effect Effects 0.000 claims description 5
- 238000013016 damping Methods 0.000 claims description 4
- 238000006073 displacement reaction Methods 0.000 claims description 3
- 238000012423 maintenance Methods 0.000 claims description 2
- 238000000034 method Methods 0.000 description 4
- 241000264877 Hippospongia communis Species 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 239000012530 fluid Substances 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
- 238000013142 basic testing Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000011056 performance test Methods 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 230000003746 surface roughness Effects 0.000 description 1
Classifications
-
- 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
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
-
- 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
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
- G01M9/065—Measuring arrangements specially adapted for aerodynamic testing dealing with flow
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- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The present invention relates to dynamic performance testing fields, disclose a kind of air duct test system for ice-removing and ice-preventing liquid air aerodynamic properties.Including support unit, test air duct, wind turbine, motor, control unit, the support unit is located at the lower section in test air duct, the test air duct includes sequentially connected air inlet stable section air duct, contraction section air duct, experimental section air duct and diffuser air duct, the diffuser air duct is sequentially connected wind turbine and motor, described control unit includes the pressure sensor I positioned at air inlet stable section air duct, positioned at the pressure sensor II of experimental section tunnel inlet, positioned at the pressure sensor III of experimental section ducting outlet, temperature sensor positioned at experimental section air duct and external computer terminal, the air duct test system is placed on low temperature control room, the computer terminal is used to acquire the data of pressure sensor and temperature sensor, room temperature is controlled for controlling rotation speed of fan and low temperature.Realize the test of ice-removing and ice-preventing liquid air aerodynamic properties.
Description
Technical Field
The invention relates to the technical field of aerodynamic performance testing, in particular to an air channel testing system for aerodynamic performance of deicing and anti-icing fluid.
Background
The deicing and anti-icing liquid is an important aviation chemical product for guaranteeing the aviation operation safety in winter, and the use of the deicing and anti-icing liquid can directly influence the shape and the surface roughness of the outer surface of the airplane, further influence the flight performance of the airplane, and particularly influence the flight performance of the airplane in a takeoff stage. Therefore, it is necessary to study and evaluate whether the deicing and anti-icing liquid sprayed on the outer surface of the airplane can be blown off during the takeoff of the airplane.
The testing device mentioned in the basic testing method about the aerodynamic performance of the deicing and anti-icing liquid at present is a large-scale backflow type air channel, the accuracy and stability of pipeline wind speed control are not high, and the volume of the testing device is large.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: aiming at the problems, the air channel testing system for the aerodynamic performance of the deicing and anti-icing liquid is provided.
The technical scheme adopted by the invention is as follows: an air duct testing system for aerodynamic performance of deicing and anti-icing liquid comprises a supporting unit, a testing air duct, a fan, a motor and a control unit, wherein the supporting unit is positioned below the testing air duct, the testing air duct comprises an air inlet stable section air duct, a contraction section air duct, an experiment section air duct and a diffusion section air duct which are sequentially connected, the diffusion section air duct is connected with the fan, the fan is connected with the motor, the control unit comprises a pressure sensor I positioned in the air inlet stable section air duct, a pressure sensor II positioned at an inlet of the experiment section air duct, a pressure sensor III positioned at an outlet of the experiment section air duct, a temperature sensor positioned in the experiment section air duct and an external computer terminal, the air duct testing system is placed in a low-temperature control room, and the computer terminal is used for collecting data of the pressure sensor I, the pressure sensor II, the pressure sensor III and the temperature sensor, the temperature control device is used for controlling the rotating speed of the fan and the temperature of the low-temperature control chamber.
Further, the supporting unit comprises a base and 4 supports for supporting the test air duct.
Further, the air inlet stabilizing section air duct is sequentially provided with the honeycombs and the 4 damping nets at equal intervals.
Further, the contraction section air duct contracts along the pipe diameter in the wind speed direction, and the contraction ratio of the contraction section air duct is 9: 1.
further, the pipe diameter shrinkage rate of the shrinkage section air duct is increased and then reduced along the wind speed direction.
Furthermore, the top of the experimental section air duct inlet and the bottom of the experimental section air duct outlet are respectively provided with a temperature sensor.
Furthermore, the experimental section air duct is formed by hermetically connecting an upper half pipe wall and a lower half pipe wall, and a handle is arranged on the upper half pipe wall.
In summary, due to the adoption of the technical scheme, the invention has the beneficial effects that: divide into the air duct system multistage, guarantee the stability of wind speed, test the air duct and set up the sensor in many places and effectively improve from the test accuracy, whole test system is small moreover.
Drawings
FIG. 1 is a schematic structural diagram of an air duct testing system according to the present invention.
Fig. 2 is a schematic diagram of the internal structure of the air duct of the intake stabilizing section in fig. 1.
FIG. 3 is a schematic view of the structure of the convergent section duct of FIG. 1.
FIG. 4 is a schematic structural diagram of the experimental segment air duct in FIG. 1.
Detailed Description
The invention is further described below with reference to the accompanying drawings.
As shown in fig. 1-4, an air duct testing system for aerodynamic performance of deicing and anti-icing fluid specifically comprises a supporting unit, a testing air duct, a fan 5, a motor 6 and a control unit, wherein the supporting unit is located below the testing air duct, and the testing air duct comprises an air inlet stabilizing section air duct 1, a contraction section air duct 2, an experiment section air duct 3 and a diffusion section air duct 4 which are sequentially connected; the diffusion section air duct 4 is connected with a fan 5, the fan 5 is connected with a motor 6, the motor 6 drives the fan to rotate, and different air speeds are provided for the test air duct when the fan rotating speeds are different; the control unit (not shown in the drawing) comprises a pressure sensor I positioned in an air inlet stable section air channel, a pressure sensor II positioned at an experimental section air channel inlet 13, a pressure sensor III positioned at an experimental section air channel outlet 14, a temperature sensor positioned in an experimental section air channel 3 and an external computer terminal, wherein the computer terminal is used for collecting data of the pressure sensor I, the pressure sensor II, the pressure sensor III and the temperature sensor, the air channel testing system is placed in a low-temperature control room, the air channel testing system can be used for testing the pressure difference between the air inlet stable section air channel 1 and the experimental section air channel inlet 13 according to the pressure sensor I and the pressure sensor II, testing the pressure difference between the experimental section air channel inlet 13 and the experimental section air channel outlet 14 according to the pressure sensor II and the pressure sensor III, the air speed of the experimental section air channel can be tested according to the two pressure differences, the wind speed is set up from constant acceleration to 30s or more, and the wind speed is controlled by a computer terminal program to control the rotating speed of the motor. And the computer terminal controls the rotating speed of the fan 5 and the temperature of the low-temperature control chamber. The method comprises the steps of uniformly spreading deicing anti-icing liquid at the bottom of an experimental section air channel before testing, leveling to 2mm in thickness by using a scraper tool, placing for a period of time, then collecting the pressure and temperature of a tested air channel by using a starting system under the control of a computer terminal, realizing that an air channel testing system runs under a testing environment with certain low temperature and certain air speed, and testing the boundary layer displacement thickness of the deicing anti-icing liquid in an experimental end to judge the maintenance condition of the deicing anti-icing liquid under the testing environment.
The supporting unit comprises a base 7 and 4 supports 8 and is used for supporting the test air channel, keeping the stability of the test air channel and being beneficial to ensuring the accuracy and stability of controlling the air speed of the test air channel.
The air inlet stabilizing section air duct 1 is sequentially provided with the honeycombs 9 and the 4 damping nets 10 at equal intervals, and air enters from the outside and then is distributed stably and uniformly through the honeycombs 9 and the damping nets 10.
The contraction section air duct 2 contracts along the pipe diameter in the wind speed direction, and the contraction ratio of the contraction section air duct 2 is 6: 1-10: 1, the contraction ratio of the contraction section air duct 2 is preferably 9: 1. The contraction section air duct 2 contracts along the pipe diameter in the air speed direction, the pipe diameter contraction rate is increased firstly and then reduced along the air speed direction, the contraction ratio of the front end 11 of the contraction section air duct is small, the contraction is slow, the contraction ratio is increased, and the contraction ratio of the rear end 12 of the contraction section air duct is small.
The top of the experimental section air duct inlet 13 and the bottom of the experimental section air duct outlet 14 are respectively provided with a temperature sensor for measuring the temperature of air flow and the temperature of liquid in the experimental section air duct 3, so that the measurement of the air duct temperature is more accurate.
Experiment section wind channel 3 forms through first pipe wall and second pipe wall sealing connection, be provided with handle 15 on the first pipe wall, when experiment section wind channel 3 placed deicing anti-icing liquid, open first pipe wall, can be more convenient evenly spread deicing anti-icing liquid in experiment section wind channel 3 bottom.
Through the test of the air channel test system, the test result obtained by the computer terminal is the boundary displacement thickness of the deicing and anti-icing liquid, and the aerodynamic performance test of the deicing and anti-icing liquid is realized by combining the air speed corresponding to the pressure value acquired by the system and the temperature value acquired by the system.
The invention is not limited to the foregoing embodiments. The invention extends to any novel feature or any novel combination of features disclosed in this specification and any novel method or process steps or any novel combination of features disclosed. Those skilled in the art to which the invention pertains will appreciate that insubstantial changes or modifications can be made without departing from the spirit of the invention as defined by the appended claims.
Claims (6)
1. The utility model provides an air duct test system for deicing anti-icing liquid aerodynamic performance which characterized in that: the device comprises a supporting unit, a testing air channel, a fan, a motor and a control unit, wherein the supporting unit is located below the testing air channel, the testing air channel comprises an air inlet stable section air channel, a contraction section air channel, an experiment section air channel and a diffusion section air channel which are sequentially connected, the diffusion section air channel is connected with the fan, the fan is connected with the motor, the control unit comprises a pressure sensor I located in the air inlet stable section air channel, a pressure sensor II located at an inlet of the experiment section air channel, a pressure sensor III located at an outlet of the experiment section air channel, a temperature sensor located in the experiment section air channel and an external computer terminal, the air channel testing system is placed in a low-temperature control room, the computer terminal is used for collecting data of the pressure sensor I, the pressure sensor II, the pressure sensor III and the temperature sensor and is used for controlling the rotating speed of the fan and the temperature of the low-temperature control room, and the air channel ) And the pressure difference before the inlet (13) of the experimental section air duct, the pressure difference between the inlet (13) of the experimental section air duct and the outlet (14) of the experimental section air duct is measured according to the pressure sensor II and the pressure sensor III, the wind speed of the experimental section air duct can be measured according to the two pressure differences; before testing, the deicing and anti-icing liquid is uniformly spread at the bottom of an air duct of an experimental section, is strickled off to 2mm in thickness by a scraper tool and is placed for a period of time T, then starting an air channel testing system, collecting the pressure and temperature of a testing air channel under the control of a computer terminal, realizing that the air channel testing system runs under a testing environment with set temperature and set air speed, and testing the boundary layer displacement thickness of the deicing and anti-icing liquid in an experimental end to judge the maintenance condition of the deicing and anti-icing liquid under the testing environment; wherein, the air inlet stabilizing section air duct is sequentially provided with a honeycomb device and 4 damping nets at equal intervals.
2. The system for testing the aerodynamic properties of ice and liquid according to claim 1, wherein: the supporting unit comprises a base and 4 supports and is used for supporting the test air channel.
3. The system for testing the aerodynamic properties of ice and liquid according to claim 2, wherein: the contraction section air duct contracts along the pipe diameter of the wind speed direction, and the contraction ratio of the contraction section air duct is 9: 1.
4. the system for testing the aerodynamic properties of ice and liquid according to claim 3, wherein: the pipe diameter shrinkage rate of the shrinkage section air duct is increased and then reduced along the wind speed direction.
5. The system for testing the aerodynamic performance of ice and liquid according to claim 4, wherein: and the top of the experimental section air duct inlet and the bottom of the experimental section air duct outlet are respectively provided with a temperature sensor.
6. The system for testing the aerodynamic performance of ice and liquid according to claim 5, wherein: the experimental section air duct is formed by hermetically connecting an upper half duct wall and a lower half duct wall, and a handle is arranged on the upper half duct wall.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610533974.5A CN106017858B (en) | 2016-07-08 | 2016-07-08 | System is tested in a kind of air duct for ice-removing and ice-preventing liquid air aerodynamic properties |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610533974.5A CN106017858B (en) | 2016-07-08 | 2016-07-08 | System is tested in a kind of air duct for ice-removing and ice-preventing liquid air aerodynamic properties |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106017858A CN106017858A (en) | 2016-10-12 |
| CN106017858B true CN106017858B (en) | 2018-08-14 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201610533974.5A Active CN106017858B (en) | 2016-07-08 | 2016-07-08 | System is tested in a kind of air duct for ice-removing and ice-preventing liquid air aerodynamic properties |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107436219B (en) * | 2017-08-02 | 2023-05-26 | 中国航空工业集团公司哈尔滨空气动力研究所 | Inlet and exhaust pipeline device in unconventional layout form |
| CN108593244B (en) * | 2018-04-24 | 2020-01-07 | 厦门大学 | Pressure difference adjustable binary channels device |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5389276A (en) * | 1993-11-15 | 1995-02-14 | Texaco Inc. | Aircraft deicing fluid with thermal and pH-stable wetting agent |
| CN202453205U (en) * | 2011-11-28 | 2012-09-26 | 成都民航六维航化有限责任公司 | Low temperature anti-icing test box |
| CN105466713A (en) * | 2015-12-11 | 2016-04-06 | 中国航空工业集团公司西安飞机设计研究所 | Testing device for simulating plane anti-icing and de-icing system |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP4028981B2 (en) * | 2001-12-25 | 2008-01-09 | 株式会社前川製作所 | Aircraft ice / snow removal processing method and processing apparatus therefor |
-
2016
- 2016-07-08 CN CN201610533974.5A patent/CN106017858B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5389276A (en) * | 1993-11-15 | 1995-02-14 | Texaco Inc. | Aircraft deicing fluid with thermal and pH-stable wetting agent |
| CN202453205U (en) * | 2011-11-28 | 2012-09-26 | 成都民航六维航化有限责任公司 | Low temperature anti-icing test box |
| CN105466713A (en) * | 2015-12-11 | 2016-04-06 | 中国航空工业集团公司西安飞机设计研究所 | Testing device for simulating plane anti-icing and de-icing system |
Non-Patent Citations (2)
| Title |
|---|
| 机除冰液空气动力学性能研究;彭华乔 等;《应用化工》;20151031;第44卷(第10期);第1934-1937页 * |
| 飞机除冰/防冰液的流变特性研究;张亚博 等;《应用化工》;20150331;第44卷(第3期);第419-422页 * |
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| CN106017858A (en) | 2016-10-12 |
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